Sample records for cost engineering

  1. Cost and price estimate of Brayton and Stirling engines in selected production volumes

    NASA Technical Reports Server (NTRS)

    Fortgang, H. R.; Mayers, H. F.

    1980-01-01

    The methods used to determine the production costs and required selling price of Brayton and Stirling engines modified for use in solar power conversion units are presented. Each engine part, component and assembly was examined and evaluated to determine the costs of its material and the method of manufacture based on specific annual production volumes. Cost estimates are presented for both the Stirling and Brayton engines in annual production volumes of 1,000, 25,000, 100,000 and 400,000. At annual production volumes above 50,000 units, the costs of both engines are similar, although the Stirling engine costs are somewhat lower. It is concluded that modifications to both the Brayton and Stirling engine designs could reduce the estimated costs.

  2. 48 CFR 31.205-25 - Manufacturing and production engineering costs.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... production engineering costs. 31.205-25 Section 31.205-25 Federal Acquisition Regulations System FEDERAL... Commercial Organizations 31.205-25 Manufacturing and production engineering costs. (a) The costs of manufacturing and production engineering effort as described in (1) through (4) below are all allowable: (1...

  3. 48 CFR 31.205-25 - Manufacturing and production engineering costs.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... production engineering costs. 31.205-25 Section 31.205-25 Federal Acquisition Regulations System FEDERAL... Commercial Organizations 31.205-25 Manufacturing and production engineering costs. (a) The costs of manufacturing and production engineering effort as described in (1) through (4) below are all allowable: (1...

  4. 48 CFR 31.205-25 - Manufacturing and production engineering costs.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... production engineering costs. 31.205-25 Section 31.205-25 Federal Acquisition Regulations System FEDERAL... Commercial Organizations 31.205-25 Manufacturing and production engineering costs. (a) The costs of manufacturing and production engineering effort as described in (1) through (4) below are all allowable: (1...

  5. 48 CFR 31.205-25 - Manufacturing and production engineering costs.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... production engineering costs. 31.205-25 Section 31.205-25 Federal Acquisition Regulations System FEDERAL... Commercial Organizations 31.205-25 Manufacturing and production engineering costs. (a) The costs of manufacturing and production engineering effort as described in (1) through (4) below are all allowable: (1...

  6. 48 CFR 31.205-25 - Manufacturing and production engineering costs.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... production engineering costs. 31.205-25 Section 31.205-25 Federal Acquisition Regulations System FEDERAL... Commercial Organizations 31.205-25 Manufacturing and production engineering costs. (a) The costs of manufacturing and production engineering effort as described in (1) through (4) below are all allowable: (1...

  7. Cost estimating Brayton and Stirling engines

    NASA Technical Reports Server (NTRS)

    Fortgang, H. R.

    1980-01-01

    Brayton and Stirling engines were analyzed for cost and selling price for production quantities ranging from 1000 to 400,000 units per year. Parts and components were subjected to indepth scrutiny to determine optimum manufacturing processes coupled with make or buy decisions on materials and small parts. Tooling and capital equipment costs were estimated for each detail and/or assembly. For low annual production volumes, the Brayton engine appears to have a lower cost and selling price than the Stirling Engine. As annual production quantities increase, the Stirling becomes a lower cost engine than the Brayton. Both engines could benefit cost wise if changes were made in materials, design and manufacturing process as annual production quantities increase.

  8. The cost of performance - A comparison of the space transportation main engine and the Space Shuttle main engine

    NASA Technical Reports Server (NTRS)

    Barisa, B. B.; Flinchbaugh, G. D.; Zachary, A. T.

    1989-01-01

    This paper compares the cost of the Space Shuttle Main Engine (SSME) and the Space Transportation Main Engine (STME) proposed by the Advanced Launch System Program. A brief description of the SSME and STME engines is presented, followed by a comparison of these engines that illustrates the impact of focusing on acceptable performance at minimum cost (as for the STME) or on maximum performance (as for the SSME). Several examples of cost reduction methods are presented.

  9. 26 CFR 1.263A-1 - Uniform capitalization of costs.

    Code of Federal Regulations, 2014 CFR

    2014-04-01

    ... or facilities. (P) Engineering and design costs. Engineering and design costs include pre-production costs, such as costs attributable to research, experimental, engineering, and design activities (to the... customer demand. (9) Research and experimental expenditures. See section 263A(c)(2) for an exception for...

  10. The common engine concept for ALS application - A cost reduction approach

    NASA Technical Reports Server (NTRS)

    Bair, E. K.; Schindler, C. M.

    1989-01-01

    Future launch systems require the application of propulsion systems which have been designed and developed to meet mission model needs while providing high degrees of reliability and cost effectiveness. Vehicle configurations which utilize different propellant combinations for booster and core stages can benefit from a common engine approach where a single engine design can be configured to operate on either set of propellants and thus serve as either a booster or core engine. Engine design concepts and mission application for a vehicle employing a common engine are discussed. Engine program cost estimates were made and cost savings, over the design and development of two unique engines, estimated.

  11. Advanced General Aviation Turbine Engine (GATE) concepts

    NASA Technical Reports Server (NTRS)

    Lays, E. J.; Murray, G. L.

    1979-01-01

    Concepts are discussed that project turbine engine cost savings through use of geometrically constrained components designed for low rotational speeds and low stress to permit manufacturing economies. Aerodynamic development of geometrically constrained components is recommended to maximize component efficiency. Conceptual engines, airplane applications, airplane performance, engine cost, and engine-related life cycle costs are presented. The powerplants proposed offer encouragement with respect to fuel efficiency and life cycle costs, and make possible remarkable airplane performance gains.

  12. Preliminary study of advanced turboprop and turboshaft engines for light aircraft. [cost effectiveness

    NASA Technical Reports Server (NTRS)

    Knip, G.; Plencner, R. M.; Eisenberg, J. D.

    1980-01-01

    The effects of engine configuration, advanced component technology, compressor pressure ratio and turbine rotor-inlet temperature on such figures of merit as vehicle gross weight, mission fuel, aircraft acquisition cost, operating, cost and life cycle cost are determined for three fixed- and two rotary-wing aircraft. Compared with a current production turboprop, an advanced technology (1988) engine results in a 23 percent decrease in specific fuel consumption. Depending on the figure of merit and the mission, turbine engine cost reductions required to achieve aircraft cost parity with a current spark ignition reciprocating (SIR) engine vary from 0 to 60 percent and from 6 to 74 percent with a hypothetical advanced SIR engine. Compared with a hypothetical turboshaft using currently available technology (1978), an advanced technology (1988) engine installed in a light twin-engine helicopter results in a 16 percent reduction in mission fuel and about 11 percent in most of the other figures of merit.

  13. A white paper: Operational efficiency. New approaches to future propulsion systems

    NASA Technical Reports Server (NTRS)

    Rhodes, Russel; Wong, George

    1991-01-01

    Advanced launch systems for the next generation of space transportation systems (1995 to 2010) must deliver large payloads (125,000 to 500,000 lbs) to low earth orbit (LEO) at one tenth of today's cost, or 300 to 400 $/lb of payload. This cost represents an order of magnitude reduction from the Titan unmanned vehicle cost of delivering payload to orbit. To achieve this sizable reduction, the operations cost as well as the engine cost must both be lower than current engine system. The Advanced Launch System (ALS) is studying advanced engine designs, such as the Space Transportation Main Engine (STME), which has achieved notable reduction in cost. The results are presented of a current study wherein another level of cost reduction can be achieved by designing the propulsion module utilizing these advanced engines for enhanced operations efficiency and reduced operations cost.

  14. The JPL Cost Risk Analysis Approach that Incorporates Engineering Realism

    NASA Technical Reports Server (NTRS)

    Harmon, Corey C.; Warfield, Keith R.; Rosenberg, Leigh S.

    2006-01-01

    This paper discusses the JPL Cost Engineering Group (CEG) cost risk analysis approach that accounts for all three types of cost risk. It will also describe the evaluation of historical cost data upon which this method is based. This investigation is essential in developing a method that is rooted in engineering realism and produces credible, dependable results to aid decision makers.

  15. A Framework for Automating Cost Estimates in Assembly Processes

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    Calton, T.L.; Peters, R.R.

    1998-12-09

    When a product concept emerges, the manufacturing engineer is asked to sketch out a production strategy and estimate its cost. The engineer is given an initial product design, along with a schedule of expected production volumes. The engineer then determines the best approach to manufacturing the product, comparing a variey of alternative production strategies. The engineer must consider capital cost, operating cost, lead-time, and other issues in an attempt to maximize pro$ts. After making these basic choices and sketching the design of overall production, the engineer produces estimates of the required capital, operating costs, and production capacity. 177is process maymore » iterate as the product design is refined in order to improve its pe~ormance or manufacturability. The focus of this paper is on the development of computer tools to aid manufacturing engineers in their decision-making processes. This computer sof~are tool provides aj?amework in which accurate cost estimates can be seamlessly derivedfiom design requirements at the start of any engineering project. Z+e result is faster cycle times through first-pass success; lower ll~e cycie cost due to requirements-driven design and accurate cost estimates derived early in the process.« less

  16. 7 CFR 1710.253 - Engineering and cost studies-addition of generation capacity.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 7 Agriculture 11 2014-01-01 2014-01-01 false Engineering and cost studies-addition of generation... TO ELECTRIC LOANS AND GUARANTEES Construction Work Plans and Related Studies § 1710.253 Engineering... engineering and cost studies as specified by RUS. The studies shall cover a period from the beginning of the...

  17. 7 CFR 1710.253 - Engineering and cost studies-addition of generation capacity.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 7 Agriculture 11 2012-01-01 2012-01-01 false Engineering and cost studies-addition of generation... TO ELECTRIC LOANS AND GUARANTEES Construction Work Plans and Related Studies § 1710.253 Engineering... engineering and cost studies as specified by RUS. The studies shall cover a period from the beginning of the...

  18. 7 CFR 1710.253 - Engineering and cost studies-addition of generation capacity.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 7 Agriculture 11 2010-01-01 2010-01-01 false Engineering and cost studies-addition of generation... TO ELECTRIC LOANS AND GUARANTEES Construction Work Plans and Related Studies § 1710.253 Engineering... engineering and cost studies as specified by RUS. The studies shall cover a period from the beginning of the...

  19. 7 CFR 1710.253 - Engineering and cost studies-addition of generation capacity.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 7 Agriculture 11 2013-01-01 2013-01-01 false Engineering and cost studies-addition of generation... TO ELECTRIC LOANS AND GUARANTEES Construction Work Plans and Related Studies § 1710.253 Engineering... engineering and cost studies as specified by RUS. The studies shall cover a period from the beginning of the...

  20. 7 CFR 1710.253 - Engineering and cost studies-addition of generation capacity.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 7 Agriculture 11 2011-01-01 2011-01-01 false Engineering and cost studies-addition of generation... TO ELECTRIC LOANS AND GUARANTEES Construction Work Plans and Related Studies § 1710.253 Engineering... engineering and cost studies as specified by RUS. The studies shall cover a period from the beginning of the...

  1. A Holistic Approach to Systems Development

    NASA Technical Reports Server (NTRS)

    Wong, Douglas T.

    2008-01-01

    Introduces a Holistic and Iterative Design Process. Continuous process but can be loosely divided into four stages. More effort spent early on in the design. Human-centered and Multidisciplinary. Emphasis on Life-Cycle Cost. Extensive use of modeling, simulation, mockups, human subjects, and proven technologies. Human-centered design doesn t mean the human factors discipline is the most important Disciplines should be involved in the design: Subsystem vendors, configuration management, operations research, manufacturing engineering, simulation/modeling, cost engineering, hardware engineering, software engineering, test and evaluation, human factors, electromagnetic compatibility, integrated logistics support, reliability/maintainability/availability, safety engineering, test equipment, training systems, design-to-cost, life cycle cost, application engineering etc. 9

  2. Determination and Applications of Environmental Costs at Different Sized Airports: Aircraft Noise and Engine Emissions

    NASA Technical Reports Server (NTRS)

    Lu, Cherie; Lierens, Abigail

    2003-01-01

    With the increasing trend of charging for externalities and the aim of encouraging the sustainable development of the air transport industry, there is a need to evaluate the social costs of these undesirable side effects, mainly aircraft noise and engine emissions, for different airports. The aircraft noise and engine emissions social costs are calculated in monetary terms for five different airports, ranging from hub airports to small regional airports. The number of residences within different levels of airport noise contours and the aircraft noise classifications are the main determinants for accessing aircraft noise social costs. Whist, based on the damages of different engine pollutants on the human health, vegetation, materials, aquatic ecosystem and climate, the aircraft engine emissions social costs vary from engine types to aircraft categories. The results indicate that the relationship appears to be curvilinear between environmental costs and the traffic volume of an airport. The results and methodology of environmental cost calculation could input for to the proposed European wide harmonized noise charges as well as the social cost benefit analysis of airports.

  3. Cost Effective Repair Techniques for Turbine Airfoils. Volume 2

    DTIC Science & Technology

    1979-04-01

    BLADES , *GUIDE VANES , *REPAIR, TURBOFAN ENGINES , DIFFUSION BONDING, COST EFFECTIVENESS Identifiers: (U) * Turbine vanes , TF-39 engines , Activated...REPAIR TECHNIQUES FOR TURBINE AIRFOILS J. A. WEIN W. R. YOUNG GENERAL ELECTRIC COMPANY AIRCRAFT ENGINE GROUP CINCINNATI, OHIO 45215 APRIL 1979...Author: GENERAL ELECTRIC CO CINCINNATI OH AIRCRAFT ENGINE BUSINESS GROUP Unclassified Title: (U) Cost Effective Repair Techniques for

  4. 14 CFR 151.55 - Accounting and audit.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ...) Costs of force account construction. (5) Engineering costs of plans and designs. (6) Engineering costs... allowability of all incurred costs of the project. The sponsor shall segregate and group project costs so that it can furnish, on due notice, cost information in the following cost classifications: (1) Purchase...

  5. 14 CFR 151.55 - Accounting and audit.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ...) Costs of force account construction. (5) Engineering costs of plans and designs. (6) Engineering costs... allowability of all incurred costs of the project. The sponsor shall segregate and group project costs so that it can furnish, on due notice, cost information in the following cost classifications: (1) Purchase...

  6. 14 CFR 151.55 - Accounting and audit.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ...) Costs of force account construction. (5) Engineering costs of plans and designs. (6) Engineering costs... allowability of all incurred costs of the project. The sponsor shall segregate and group project costs so that it can furnish, on due notice, cost information in the following cost classifications: (1) Purchase...

  7. 14 CFR 151.55 - Accounting and audit.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ...) Costs of force account construction. (5) Engineering costs of plans and designs. (6) Engineering costs... allowability of all incurred costs of the project. The sponsor shall segregate and group project costs so that it can furnish, on due notice, cost information in the following cost classifications: (1) Purchase...

  8. Parametric Cost Analysis: A Design Function

    NASA Technical Reports Server (NTRS)

    Dean, Edwin B.

    1989-01-01

    Parametric cost analysis uses equations to map measurable system attributes into cost. The measures of the system attributes are called metrics. The equations are called cost estimating relationships (CER's), and are obtained by the analysis of cost and technical metric data of products analogous to those to be estimated. Examples of system metrics include mass, power, failure_rate, mean_time_to_repair, energy _consumed, payload_to_orbit, pointing_accuracy, manufacturing_complexity, number_of_fasteners, and percent_of_electronics_weight. The basic assumption is that a measurable relationship exists between system attributes and the cost of the system. If a function exists, the attributes are cost drivers. Candidates for metrics include system requirement metrics and engineering process metrics. Requirements are constraints on the engineering process. From optimization theory we know that any active constraint generates cost by not permitting full optimization of the objective. Thus, requirements are cost drivers. Engineering processes reflect a projection of the requirements onto the corporate culture, engineering technology, and system technology. Engineering processes are an indirect measure of the requirements and, hence, are cost drivers.

  9. A Cost-Minimization Analysis of Tissue-Engineered Constructs for Corneal Endothelial Transplantation

    PubMed Central

    Tan, Tien-En; Peh, Gary S. L.; George, Benjamin L.; Cajucom-Uy, Howard Y.; Dong, Di; Finkelstein, Eric A.; Mehta, Jodhbir S.

    2014-01-01

    Corneal endothelial transplantation or endothelial keratoplasty has become the preferred choice of transplantation for patients with corneal blindness due to endothelial dysfunction. Currently, there is a worldwide shortage of transplantable tissue, and demand is expected to increase further with aging populations. Tissue-engineered alternatives are being developed, and are likely to be available soon. However, the cost of these constructs may impair their widespread use. A cost-minimization analysis comparing tissue-engineered constructs to donor tissue procured from eye banks for endothelial keratoplasty was performed. Both initial investment costs and recurring costs were considered in the analysis to arrive at a final tissue cost per transplant. The clinical outcomes of endothelial keratoplasty with tissue-engineered constructs and with donor tissue procured from eye banks were assumed to be equivalent. One-way and probabilistic sensitivity analyses were performed to simulate various possible scenarios, and to determine the robustness of the results. A tissue engineering strategy was cheaper in both investment cost and recurring cost. Tissue-engineered constructs for endothelial keratoplasty could be produced at a cost of US$880 per transplant. In contrast, utilizing donor tissue procured from eye banks for endothelial keratoplasty required US$3,710 per transplant. Sensitivity analyses performed further support the results of this cost-minimization analysis across a wide range of possible scenarios. The use of tissue-engineered constructs for endothelial keratoplasty could potentially increase the supply of transplantable tissue and bring the costs of corneal endothelial transplantation down, making this intervention accessible to a larger group of patients. Tissue-engineering strategies for corneal epithelial constructs or other tissue types, such as pancreatic islet cells, should also be subject to similar pharmacoeconomic analyses. PMID:24949869

  10. A cost-minimization analysis of tissue-engineered constructs for corneal endothelial transplantation.

    PubMed

    Tan, Tien-En; Peh, Gary S L; George, Benjamin L; Cajucom-Uy, Howard Y; Dong, Di; Finkelstein, Eric A; Mehta, Jodhbir S

    2014-01-01

    Corneal endothelial transplantation or endothelial keratoplasty has become the preferred choice of transplantation for patients with corneal blindness due to endothelial dysfunction. Currently, there is a worldwide shortage of transplantable tissue, and demand is expected to increase further with aging populations. Tissue-engineered alternatives are being developed, and are likely to be available soon. However, the cost of these constructs may impair their widespread use. A cost-minimization analysis comparing tissue-engineered constructs to donor tissue procured from eye banks for endothelial keratoplasty was performed. Both initial investment costs and recurring costs were considered in the analysis to arrive at a final tissue cost per transplant. The clinical outcomes of endothelial keratoplasty with tissue-engineered constructs and with donor tissue procured from eye banks were assumed to be equivalent. One-way and probabilistic sensitivity analyses were performed to simulate various possible scenarios, and to determine the robustness of the results. A tissue engineering strategy was cheaper in both investment cost and recurring cost. Tissue-engineered constructs for endothelial keratoplasty could be produced at a cost of US$880 per transplant. In contrast, utilizing donor tissue procured from eye banks for endothelial keratoplasty required US$3,710 per transplant. Sensitivity analyses performed further support the results of this cost-minimization analysis across a wide range of possible scenarios. The use of tissue-engineered constructs for endothelial keratoplasty could potentially increase the supply of transplantable tissue and bring the costs of corneal endothelial transplantation down, making this intervention accessible to a larger group of patients. Tissue-engineering strategies for corneal epithelial constructs or other tissue types, such as pancreatic islet cells, should also be subject to similar pharmacoeconomic analyses.

  11. Researchers View the Small Low Cost Engine and the Large Quiet Engine

    NASA Image and Video Library

    1972-02-21

    Researchers Robert Cummings, left, and Harold Gold with the small Low Cost Engine in the shadow of the much larger Quiet Engine at the National Aeronautics and Space Administration (NASA) Lewis Research Center. The two engines were being studied in different test cells at the Propulsion Systems Laboratory. Jet engines had proven themselves on military and large transport aircraft, but their use on small general aviation aircraft was precluded by cost. Lewis undertook a multiyear effort to develop a less expensive engine to fill this niche using existing technologies. Lewis researchers designed a four-stage, axial-flow engine constructed from sheet metal. It was only 11.5 inches in diameter and weighed 100 pounds. The final design specifications were turned over to a manufacturer in 1972. Four engines were created, and, as expected, the fabrication and assembly of the engine were comparatively inexpensive. In 1973 the Low Cost Engine had its first realistic analysis in the Propulsion Systems Laboratory altitude tank. The engine successfully operated at speeds up to Mach 1.24 and simulated altitudes of 30,000 feet. NASA released the engine to private industry in the hope that design elements would be incorporated into future projects and reduce the overall cost of small jet aircraft. Small jet and turboprop engines became relatively common in general aviation aircraft by the late 1970s.

  12. 48 CFR 436.605 - Government cost estimate for architect-engineer work.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... for architect-engineer work. 436.605 Section 436.605 Federal Acquisition Regulations System DEPARTMENT OF AGRICULTURE SPECIAL CATEGORIES OF CONTRACTING CONSTRUCTION AND ARCHITECT-ENGINEER CONTRACTS Architect-Engineer Service 436.605 Government cost estimate for architect-engineer work. The contracting...

  13. 48 CFR 436.605 - Government cost estimate for architect-engineer work.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... for architect-engineer work. 436.605 Section 436.605 Federal Acquisition Regulations System DEPARTMENT OF AGRICULTURE SPECIAL CATEGORIES OF CONTRACTING CONSTRUCTION AND ARCHITECT-ENGINEER CONTRACTS Architect-Engineer Service 436.605 Government cost estimate for architect-engineer work. The contracting...

  14. 48 CFR 36.605 - Government cost estimate for architect-engineer work.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... for architect-engineer work. 36.605 Section 36.605 Federal Acquisition Regulations System FEDERAL ACQUISITION REGULATION SPECIAL CATEGORIES OF CONTRACTING CONSTRUCTION AND ARCHITECT-ENGINEER CONTRACTS Architect-Engineer Services 36.605 Government cost estimate for architect-engineer work. (a) An independent...

  15. 48 CFR 1336.605 - Government cost estimate for architect-engineer work.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... for architect-engineer work. 1336.605 Section 1336.605 Federal Acquisition Regulations System DEPARTMENT OF COMMERCE SPECIAL CATEGORIES OF CONTRACTING CONSTRUCTION AND ARCHITECT-ENGINEER CONTRACTS Architect-Engineer Services 1336.605 Government cost estimate for architect-engineer work. After award, the...

  16. 48 CFR 1336.605 - Government cost estimate for architect-engineer work.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... for architect-engineer work. 1336.605 Section 1336.605 Federal Acquisition Regulations System DEPARTMENT OF COMMERCE SPECIAL CATEGORIES OF CONTRACTING CONSTRUCTION AND ARCHITECT-ENGINEER CONTRACTS Architect-Engineer Services 1336.605 Government cost estimate for architect-engineer work. After award, the...

  17. 48 CFR 1336.605 - Government cost estimate for architect-engineer work.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... for architect-engineer work. 1336.605 Section 1336.605 Federal Acquisition Regulations System DEPARTMENT OF COMMERCE SPECIAL CATEGORIES OF CONTRACTING CONSTRUCTION AND ARCHITECT-ENGINEER CONTRACTS Architect-Engineer Services 1336.605 Government cost estimate for architect-engineer work. After award, the...

  18. 48 CFR 36.605 - Government cost estimate for architect-engineer work.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... for architect-engineer work. 36.605 Section 36.605 Federal Acquisition Regulations System FEDERAL ACQUISITION REGULATION SPECIAL CATEGORIES OF CONTRACTING CONSTRUCTION AND ARCHITECT-ENGINEER CONTRACTS Architect-Engineer Services 36.605 Government cost estimate for architect-engineer work. (a) An independent...

  19. 48 CFR 36.605 - Government cost estimate for architect-engineer work.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... for architect-engineer work. 36.605 Section 36.605 Federal Acquisition Regulations System FEDERAL ACQUISITION REGULATION SPECIAL CATEGORIES OF CONTRACTING CONSTRUCTION AND ARCHITECT-ENGINEER CONTRACTS Architect-Engineer Services 36.605 Government cost estimate for architect-engineer work. (a) An independent...

  20. 48 CFR 436.605 - Government cost estimate for architect-engineer work.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... for architect-engineer work. 436.605 Section 436.605 Federal Acquisition Regulations System DEPARTMENT OF AGRICULTURE SPECIAL CATEGORIES OF CONTRACTING CONSTRUCTION AND ARCHITECT-ENGINEER CONTRACTS Architect-Engineer Service 436.605 Government cost estimate for architect-engineer work. The contracting...

  1. 48 CFR 436.605 - Government cost estimate for architect-engineer work.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... for architect-engineer work. 436.605 Section 436.605 Federal Acquisition Regulations System DEPARTMENT OF AGRICULTURE SPECIAL CATEGORIES OF CONTRACTING CONSTRUCTION AND ARCHITECT-ENGINEER CONTRACTS Architect-Engineer Service 436.605 Government cost estimate for architect-engineer work. The contracting...

  2. 48 CFR 1336.605 - Government cost estimate for architect-engineer work.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... for architect-engineer work. 1336.605 Section 1336.605 Federal Acquisition Regulations System DEPARTMENT OF COMMERCE SPECIAL CATEGORIES OF CONTRACTING CONSTRUCTION AND ARCHITECT-ENGINEER CONTRACTS Architect-Engineer Services 1336.605 Government cost estimate for architect-engineer work. After award, the...

  3. 48 CFR 36.605 - Government cost estimate for architect-engineer work.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... for architect-engineer work. 36.605 Section 36.605 Federal Acquisition Regulations System FEDERAL ACQUISITION REGULATION SPECIAL CATEGORIES OF CONTRACTING CONSTRUCTION AND ARCHITECT-ENGINEER CONTRACTS Architect-Engineer Services 36.605 Government cost estimate for architect-engineer work. (a) An independent...

  4. 48 CFR 436.605 - Government cost estimate for architect-engineer work.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... for architect-engineer work. 436.605 Section 436.605 Federal Acquisition Regulations System DEPARTMENT OF AGRICULTURE SPECIAL CATEGORIES OF CONTRACTING CONSTRUCTION AND ARCHITECT-ENGINEER CONTRACTS Architect-Engineer Service 436.605 Government cost estimate for architect-engineer work. The contracting...

  5. 48 CFR 36.605 - Government cost estimate for architect-engineer work.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... for architect-engineer work. 36.605 Section 36.605 Federal Acquisition Regulations System FEDERAL ACQUISITION REGULATION SPECIAL CATEGORIES OF CONTRACTING CONSTRUCTION AND ARCHITECT-ENGINEER CONTRACTS Architect-Engineer Services 36.605 Government cost estimate for architect-engineer work. (a) An independent...

  6. 48 CFR 1336.605 - Government cost estimate for architect-engineer work.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... for architect-engineer work. 1336.605 Section 1336.605 Federal Acquisition Regulations System DEPARTMENT OF COMMERCE SPECIAL CATEGORIES OF CONTRACTING CONSTRUCTION AND ARCHITECT-ENGINEER CONTRACTS Architect-Engineer Services 1336.605 Government cost estimate for architect-engineer work. After award, the...

  7. 40 CFR 35.936-20 - Allowable costs.

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... costs. (b) Appropriate cost principles which apply to subagreements under EPA grants are identified in... engineering services are allowable, even when conducted before award of the grant. Legal and engineering costs...

  8. 40 CFR 35.936-20 - Allowable costs.

    Code of Federal Regulations, 2014 CFR

    2014-07-01

    ... costs. (b) Appropriate cost principles which apply to subagreements under EPA grants are identified in... engineering services are allowable, even when conducted before award of the grant. Legal and engineering costs...

  9. 40 CFR 35.936-20 - Allowable costs.

    Code of Federal Regulations, 2013 CFR

    2013-07-01

    ... costs. (b) Appropriate cost principles which apply to subagreements under EPA grants are identified in... engineering services are allowable, even when conducted before award of the grant. Legal and engineering costs...

  10. 40 CFR 35.936-20 - Allowable costs.

    Code of Federal Regulations, 2011 CFR

    2011-07-01

    ... costs. (b) Appropriate cost principles which apply to subagreements under EPA grants are identified in... engineering services are allowable, even when conducted before award of the grant. Legal and engineering costs...

  11. Research requirements for development of regenerative engines for helicopters

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    Semple, R.D.

    1976-12-01

    The improved specific fuel consumption of the regenerative engine was compared to a simple-cycle turboshaft engine. The performance improvement and fuel saving are obtained at the expense of increased engine weight, development and production costs, and maintenance costs. Costs and schedules are estimated for the elements of the research and development program. Interaction of the regenerative engine with other technology goals for an advanced civil helicopter is examined, including its impact on engine noise, hover and cruise performance, helicopter empty weight, drive-system efficiency and weight, one-engine-inoperative hover capability, and maintenance and reliability.

  12. Research requirements for development of regenerative engines for helicopters

    NASA Technical Reports Server (NTRS)

    Semple, R. D.

    1976-01-01

    The improved specific fuel consumption of the regenerative engine was compared to a simple-cycle turboshaft engine. The performance improvement and fuel saving are obtained at the expense of increased engine weight, development and production costs, and maintenance costs. Costs and schedules are estimated for the elements of the research and development program. Interaction of the regenerative engine with other technology goals for an advanced civil helicopter is examined, including its impact on engine noise, hover and cruise performance, helicopter empty weight, drive-system efficiency and weight, one-engine-inoperative hover capability, and maintenance and reliability.

  13. 33 CFR 242.3 - References.

    Code of Federal Regulations, 2014 CFR

    2014-07-01

    ... MANAGEMENT SERVICES PROGRAM ESTABLISHMENT OF FEES FOR COST RECOVERY § 242.3 References. The references in... Engineers Engineering Regulation 1105-2-100, Planning Guidance Notebook. (c) Corps of Engineers Engineering Pamphlet 37-1-4, Cost of Doing Business. ...

  14. 33 CFR 242.3 - References.

    Code of Federal Regulations, 2013 CFR

    2013-07-01

    ... MANAGEMENT SERVICES PROGRAM ESTABLISHMENT OF FEES FOR COST RECOVERY § 242.3 References. The references in... Engineers Engineering Regulation 1105-2-100, Planning Guidance Notebook. (c) Corps of Engineers Engineering Pamphlet 37-1-4, Cost of Doing Business. ...

  15. 33 CFR 242.3 - References.

    Code of Federal Regulations, 2012 CFR

    2012-07-01

    ... MANAGEMENT SERVICES PROGRAM ESTABLISHMENT OF FEES FOR COST RECOVERY § 242.3 References. The references in... Engineers Engineering Regulation 1105-2-100, Planning Guidance Notebook. (c) Corps of Engineers Engineering Pamphlet 37-1-4, Cost of Doing Business. ...

  16. 33 CFR 242.3 - References.

    Code of Federal Regulations, 2011 CFR

    2011-07-01

    ... MANAGEMENT SERVICES PROGRAM ESTABLISHMENT OF FEES FOR COST RECOVERY § 242.3 References. The references in... Engineers Engineering Regulation 1105-2-100, Planning Guidance Notebook. (c) Corps of Engineers Engineering Pamphlet 37-1-4, Cost of Doing Business. ...

  17. Improving Space Project Cost Estimating with Engineering Management Variables

    NASA Technical Reports Server (NTRS)

    Hamaker, Joseph W.; Roth, Axel (Technical Monitor)

    2001-01-01

    Current space project cost models attempt to predict space flight project cost via regression equations, which relate the cost of projects to technical performance metrics (e.g. weight, thrust, power, pointing accuracy, etc.). This paper examines the introduction of engineering management parameters to the set of explanatory variables. A number of specific engineering management variables are considered and exploratory regression analysis is performed to determine if there is statistical evidence for cost effects apart from technical aspects of the projects. It is concluded that there are other non-technical effects at work and that further research is warranted to determine if it can be shown that these cost effects are definitely related to engineering management.

  18. Space Transportation Booster Engine Configuration Study. Volume 3: Program Cost estimates and work breakdown structure and WBS dictionary

    NASA Technical Reports Server (NTRS)

    1989-01-01

    The objective of the Space Transportation Booster Engine Configuration Study is to contribute to the ALS development effort by providing highly reliable, low cost booster engine concepts for both expendable and reusable rocket engines. The objectives of the Space Transportation Booster Engine (STBE) Configuration Study were: (1) to identify engine development configurations which enhance vehicle performance and provide operational flexibility at low cost; and (2) to explore innovative approaches to the follow-on Full-Scale Development (FSD) phase for the STBE.

  19. Economic analysis of transmission line engineering based on industrial engineering

    NASA Astrophysics Data System (ADS)

    Li, Yixuan

    2017-05-01

    The modern industrial engineering is applied to the technical analysis and cost analysis of power transmission and transformation engineering. It can effectively reduce the cost of investment. First, the power transmission project is economically analyzed. Based on the feasibility study of power transmission and transformation project investment, the proposal on the company system cost management is put forward through the economic analysis of the effect of the system. The cost management system is optimized. Then, through the cost analysis of power transmission and transformation project, the new situation caused by the cost of construction is found. It is of guiding significance to further improve the cost management of power transmission and transformation project. Finally, according to the present situation of current power transmission project cost management, concrete measures to reduce the cost of power transmission project are given from the two aspects of system optimization and technology optimization.

  20. 48 CFR 9904.403-60 - Illustrations.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... personnel, labor hours, payroll, number of hires. 2. Manufacturing policies, (quality control, industrial engineering, production, scheduling, tooling, inspection and testing, etc 2. Manufacturing cost input, manufacturing direct labor. 3. Engineering policies 3. Total engineering costs, engineering direct labor, number...

  1. 48 CFR 9904.403-60 - Illustrations.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... personnel, labor hours, payroll, number of hires. 2. Manufacturing policies, (quality control, industrial engineering, production, scheduling, tooling, inspection and testing, etc 2. Manufacturing cost input, manufacturing direct labor. 3. Engineering policies 3. Total engineering costs, engineering direct labor, number...

  2. 48 CFR 9904.403-60 - Illustrations.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... personnel, labor hours, payroll, number of hires. 2. Manufacturing policies, (quality control, industrial engineering, production, scheduling, tooling, inspection and testing, etc 2. Manufacturing cost input, manufacturing direct labor. 3. Engineering policies 3. Total engineering costs, engineering direct labor, number...

  3. 48 CFR 736.605 - Government cost estimate for architect-engineer work.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... for architect-engineer work. 736.605 Section 736.605 Federal Acquisition Regulations System AGENCY FOR INTERNATIONAL DEVELOPMENT SPECIAL CATEGORIES OF CONTRACTING CONSTRUCTION AND ARCHITECT-ENGINEER CONTRACTS Architect-Engineer Services 736.605 Government cost estimate for architect-engineer work. See 736.602-3(c)(5). ...

  4. 48 CFR 736.605 - Government cost estimate for architect-engineer work.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... for architect-engineer work. 736.605 Section 736.605 Federal Acquisition Regulations System AGENCY FOR INTERNATIONAL DEVELOPMENT SPECIAL CATEGORIES OF CONTRACTING CONSTRUCTION AND ARCHITECT-ENGINEER CONTRACTS Architect-Engineer Services 736.605 Government cost estimate for architect-engineer work. See 736.602-3(c)(5). ...

  5. 48 CFR 736.605 - Government cost estimate for architect-engineer work.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... for architect-engineer work. 736.605 Section 736.605 Federal Acquisition Regulations System AGENCY FOR INTERNATIONAL DEVELOPMENT SPECIAL CATEGORIES OF CONTRACTING CONSTRUCTION AND ARCHITECT-ENGINEER CONTRACTS Architect-Engineer Services 736.605 Government cost estimate for architect-engineer work. See 736.602-3(c)(5). ...

  6. 48 CFR 736.605 - Government cost estimate for architect-engineer work.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... for architect-engineer work. 736.605 Section 736.605 Federal Acquisition Regulations System AGENCY FOR INTERNATIONAL DEVELOPMENT SPECIAL CATEGORIES OF CONTRACTING CONSTRUCTION AND ARCHITECT-ENGINEER CONTRACTS Architect-Engineer Services 736.605 Government cost estimate for architect-engineer work. See 736.602-3(c)(5). ...

  7. 48 CFR 736.605 - Government cost estimate for architect-engineer work.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... for architect-engineer work. 736.605 Section 736.605 Federal Acquisition Regulations System AGENCY FOR INTERNATIONAL DEVELOPMENT SPECIAL CATEGORIES OF CONTRACTING CONSTRUCTION AND ARCHITECT-ENGINEER CONTRACTS Architect-Engineer Services 736.605 Government cost estimate for architect-engineer work. See 736.602-3(c)(5). ...

  8. Design concepts for low-cost composite engine frames

    NASA Technical Reports Server (NTRS)

    Chamis, C. C.

    1983-01-01

    Design concepts for low-cost, lightweight composite engine frames were applied to the design requirements for the frame of commercial, high-bypass turbine engines. The concepts consist of generic-type components and subcomponents that could be adapted for use in different locations in the engine and to different engine sizes. A variety of materials and manufacturing methods were assessed with a goal of having the lowest number of parts possible at the lowest possible cost. The evaluation of the design concepts resulted in the identification of a hybrid composite frame which would weigh about 70 percent of the state-of-the-art metal frame and cost would be about 60 percent.

  9. 26 CFR 1.263A-0 - Outline of regulations under section 263A.

    Code of Federal Regulations, 2014 CFR

    2014-04-01

    ...) In general. (ii) Pre-production costs. (iii) Post-production costs. (4) Practical capacity concept...) Taxes. (M) Insurance. (N) Utilities. (O) Repairs and maintenance. (P) Engineering and design costs. (Q... processing services. (E) Engineering and design services. (F) Safety engineering services. (v) Accounting...

  10. Systems Engineering | Wind | NREL

    Science.gov Websites

    platform to leverage its research capabilities toward integrating wind energy engineering and cost models achieve a better understanding of how to improve system-level performance and achieve system-level cost research capabilities to: Integrate wind plant engineering performance and cost software modeling to enable

  11. Engineering and Design: Civil Works Cost Engineering

    DTIC Science & Technology

    1994-03-31

    labor cost requirements are broken into tasks of work. Each task is usually performd by a labor crew. Crews may vary in size and mix of skills. The...requested in advance of the expected purchase date. Suppliers are reluctant to guarantee future pricw and ofien will only quote current prices. It may be...unit cost is the overhead cost for the item. g. Sources for Pricing. The Cost Engineer must rely on judgement, historical data, and current labor market

  12. Analysis of the JSF Engine Competition

    DTIC Science & Technology

    2012-09-01

    even 25 Competition for Support Services  Support costs are typically more than half of life-cycle costs and normally incurred in a sole-source...Strike Fighter), Aircraft Engines, Competition, Military Procurement, Defense Industry, Cost Analysis Analysis of the JSF Engine Competition James...different designs to meet the same functional requirements. Such a case was examined by the Institute for Defense Analyses in a forward-looking cost and

  13. Elements of Designing for Cost

    NASA Technical Reports Server (NTRS)

    Dean, Edwin B.; Unal, Resit

    1992-01-01

    During recent history in the United States, government systems development has been performance driven. As a result, systems within a class have experienced exponentially increasing cost over time in fixed year dollars. Moreover, little emphasis has been placed on reducing cost. This paper defines designing for cost and presents several tools which, if used in the engineering process, offer the promise of reducing cost. Although other potential tools exist for designing for cost, this paper focuses on rules of thumb, quality function deployment, Taguchi methods, concurrent engineering, and activity based costing. Each of these tools has been demonstrated to reduce cost if used within the engineering process.

  14. Elements of designing for cost

    NASA Technical Reports Server (NTRS)

    Dean, Edwin B.; Unal, Resit

    1992-01-01

    During recent history in the United States, government systems development has been performance driven. As a result, systems within a class have experienced exponentially increasing cost over time in fixed year dollars. Moreover, little emphasis has been placed on reducing cost. This paper defines designing for cost and presents several tools which, if used in the engineering process, offer the promise of reducing cost. Although other potential tools exist for designing for cost, this paper focuses on rules of thumb, quality function deployment, Taguchi methods, concurrent engineering, and activity-based costing. Each of these tools has been demonstrated to reduce cost if used within the engineering process.

  15. 26 CFR 1.263A-0 - Outline of regulations under section 263A.

    Code of Federal Regulations, 2010 CFR

    2010-04-01

    ...) Utilities. (O) Repairs and maintenance. (P) Engineering and design costs. (Q) Spoilage. (R) Tools and...) Engineering and design services. (F) Safety engineering services. (v) Accounting method change. (h) Simplified... mixed service costs. (7) Costs allocable to more than one business. (8) De minimis rule. (9) Separate...

  16. 26 CFR 1.263A-0 - Outline of regulations under section 263A.

    Code of Federal Regulations, 2012 CFR

    2012-04-01

    ...) Utilities. (O) Repairs and maintenance. (P) Engineering and design costs. (Q) Spoilage. (R) Tools and...) Engineering and design services. (F) Safety engineering services. (v) Accounting method change. (h) Simplified... mixed service costs. (7) Costs allocable to more than one business. (8) De minimis rule. (9) Separate...

  17. 26 CFR 1.263A-0 - Outline of regulations under section 263A.

    Code of Federal Regulations, 2011 CFR

    2011-04-01

    ...) Utilities. (O) Repairs and maintenance. (P) Engineering and design costs. (Q) Spoilage. (R) Tools and...) Engineering and design services. (F) Safety engineering services. (v) Accounting method change. (h) Simplified... mixed service costs. (7) Costs allocable to more than one business. (8) De minimis rule. (9) Separate...

  18. 26 CFR 1.263A-0 - Outline of regulations under section 263A.

    Code of Federal Regulations, 2013 CFR

    2013-04-01

    ...) Utilities. (O) Repairs and maintenance. (P) Engineering and design costs. (Q) Spoilage. (R) Tools and...) Engineering and design services. (F) Safety engineering services. (v) Accounting method change. (h) Simplified... mixed service costs. (7) Costs allocable to more than one business. (8) De minimis rule. (9) Separate...

  19. Ceramic automotive Stirling engine study

    NASA Technical Reports Server (NTRS)

    Musikant, S.; Chiu, W.; Darooka, D.; Mullings, D. M.; Johnson, C. A.

    1985-01-01

    A conceptual design study for a Ceramic Automotive Stirling Engine (CASE) is performed. Year 1990 structural ceramic technology is assumed. Structural and performance analyses of the conceptual design are performed as well as a manufacturing and cost analysis. The general conclusions from this study are that such an engine would be 10-26% more efficient over its performance map than the current metal Automotive Stirling Reference Engine (ASRE). Cost of such a ceramic engine is likely to be somewhat higher than that of the ASRE but engine cost is very sensitive to the ultimate cost of the high purity, ceramic powder raw materials required to fabricate high performance parts. When the design study is projected to the year 2000 technology, substantinal net efficiency improvements, on the order of 25 to 46% over the ASRE, are computed.

  20. Monitoring and Controlling Engineering and Construction Management Cost Performance Within the Corps of Engineers

    DTIC Science & Technology

    1988-12-01

    COST MANAGEMENT The CMIF approach addresses total costs but does not permit the analysis of indirect costs. We found that indirect costs vary...responsibility USACE/divisions Increasing CMIF Districts/divisions level of by fund type detail G&A, technical indirect, burden Districts by fund type

  1. 32 CFR 165.3 - Definitions.

    Code of Federal Regulations, 2012 CFR

    2012-07-01

    .... That includes costs of any engineering change proposals initiated before the date of calculations of...-house DoD effort. This includes costs of any engineering change proposal started before the date of... NONRECURRING COSTS ON SALES OF U.S. ITEMS § 165.3 Definitions. (a) Cost pool. Represents the total cost to be...

  2. 40 CFR 35.936-20 - Allowable costs.

    Code of Federal Regulations, 2012 CFR

    2012-07-01

    ... engineering services are allowable, even when conducted before award of the grant. Legal and engineering costs... 40 Protection of Environment 1 2012-07-01 2012-07-01 false Allowable costs. 35.936-20 Section 35... Allowable costs. (a) Incurring costs under subagreements which are not awarded or administered in compliance...

  3. 26 CFR 1.263A-1 - Uniform capitalization of costs.

    Code of Federal Regulations, 2013 CFR

    2013-04-01

    ... costs. Engineering and design costs include pre-production costs, such as costs attributable to research, experimental, engineering, and design activities (to the extent that such amounts are not research and... customer demand. (9) Research and experimental expenditures. See section 263A(c)(2) for an exception for...

  4. 26 CFR 1.263A-1 - Uniform capitalization of costs.

    Code of Federal Regulations, 2011 CFR

    2011-04-01

    ... costs. Engineering and design costs include pre-production costs, such as costs attributable to research, experimental, engineering, and design activities (to the extent that such amounts are not research and... customer demand. (9) Research and experimental expenditures. See section 263A(c)(2) for an exception for...

  5. 26 CFR 1.263A-1 - Uniform capitalization of costs.

    Code of Federal Regulations, 2012 CFR

    2012-04-01

    ... costs. Engineering and design costs include pre-production costs, such as costs attributable to research, experimental, engineering, and design activities (to the extent that such amounts are not research and... customer demand. (9) Research and experimental expenditures. See section 263A(c)(2) for an exception for...

  6. Cost estimation and analysis using the Sherpa Automated Mine Cost Engineering System

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    Stebbins, P.E.

    1993-09-01

    The Sherpa Automated Mine Cost Engineering System is a menu-driven software package designed to estimate capital and operating costs for proposed surface mining operations. The program is engineering (as opposed to statistically) based, meaning that all equipment, manpower, and supply requirements are determined from deposit geology, project design and mine production information using standard engineering techniques. These requirements are used in conjunction with equipment, supply, and labor cost databases internal to the program to estimate all associated costs. Because virtually all on-site cost parameters are interrelated within the program, Sherpa provides an efficient means of examining the impact of changesmore » in the equipment mix on total capital and operating costs. If any aspect of the operation is changed, Sherpa immediately adjusts all related aspects as necessary. For instance, if the user wishes to examine the cost ramifications of selecting larger trucks, the program not only considers truck purchase and operation costs, it also automatically and immediately adjusts excavator requirements, operator and mechanic needs, repair facility size, haul road construction and maintenance costs, and ancillary equipment specifications.« less

  7. Cost Analysis of Maintenance Programs for Pre-Positioned War Reserve Material Stock (PWRMS)

    DTIC Science & Technology

    2002-06-01

    perform electronic engine diagnosis and repair, complete engine and transmission rebuilding, powertrain and suspension work, bodywork , painting, and...cost is reimbursed by N44 • Any cost of breakdown maintenance such as transmission or engine failure. • Any cost of accident repair such as bodywork ...equipment in other TOA designators (TA10, P35, etc.) or any other maintenance such as corrective, breakdown, bodywork , or SLEP. Further studies need

  8. Ceramic automotive Stirling engine program

    NASA Technical Reports Server (NTRS)

    1986-01-01

    The Ceramic Automotive Stirling Engine Program evaluated the application of advanced ceramic materials to an automotive Stirling engine. The objective of the program was to evaluate the technical feasibility of utilizing advanced ceramics to increase peak engine operating temperature, and to evaluate the performance benefits of such an increase. Manufacturing cost estimates were also developed for various ceramic engine components and compared with conventional metallic engine component costs.

  9. Study of an advanced General Aviation Turbine Engine (GATE)

    NASA Technical Reports Server (NTRS)

    Gill, J. C.; Short, F. R.; Staton, D. V.; Zolezzi, B. A.; Curry, C. E.; Orelup, M. J.; Vaught, J. M.; Humphrey, J. M.

    1979-01-01

    The best technology program for a small, economically viable gas turbine engine applicable to the general aviation helicopter and aircraft market for 1985-1990 was studied. Turboshaft and turboprop engines in the 112 to 746 kW (150 to 1000 hp) range and turbofan engines up to 6672 N (1500 lbf) thrust were considered. A good market for new turbine engines was predicted for 1988 providing aircraft are designed to capitalize on the advantages of the turbine engine. Parametric engine families were defined in terms of design and off-design performance, mass, and cost. These were evaluated in aircraft design missions selected to represent important market segments for fixed and rotary-wing applications. Payoff parameters influenced by engine cycle and configuration changes were aircraft gross mass, acquisition cost, total cost of ownership, and cash flow. Significant advantage over a current technology, small gas turbine engines was found especially in cost of ownership and fuel economy for airframes incorporating an air-cooled high-pressure ratio engine. A power class of 373 kW (500 hp) was recommended as the next frontier for technology advance where large improvements in fuel economy and engine mass appear possible through component research and development.

  10. 47 CFR 27.1164 - The cost-sharing formula.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... control equipment; engineering costs (design/path survey); installation; systems testing; FCC filing costs; site acquisition and civil works; zoning costs; training; disposal of old equipment; test equipment... a replacement system, such as equipment and engineering expenses. C may not exceed $250,000 per...

  11. Application of composite materials to turbofan engine fan exit guide vanes

    NASA Technical Reports Server (NTRS)

    Smith, G. T.

    1980-01-01

    A program was conducted by NASA with the JT9D engine manufacturer to develop a lightweight, cost effective, composite material fan exit guide vane design having satisfactory structural durability for commerical engine use. Based on the results of a previous company supported program, eight graphite/epoxy and graphite-glass/epoxy guide vane designs were evaluated and four were selected for fabrication and testing. Two commercial fabricators each fabricated 13 vanes. Fatigue tests were used to qualify the selected design configurations under nominally dry, 38 C (100 F) and fully wet and 60 C (140 F) environmental conditions. Cost estimates for a production rate of 1000 vanes per month ranged from 1.7 to 2.6 times the cost of an all aluminum vane. This cost is 50 to 80 percent less than the initial program target cost ratio which was 3 times the cost of an aluminum vane. Application to the JT9D commercial engine is projected to provide a weight savings of 236 N (53 lb) per engine.

  12. A simplified life-cycle cost comparison of various engines for small helicopter use

    NASA Technical Reports Server (NTRS)

    Civinskas, K. C.; Fishbach, L. M.

    1974-01-01

    A ten-year, life-cycle cost comparison is made of the following engines for small helicopter use: (1) simple turboshaft; (2) regenerative turboshaft; (3) compression-ignition reciprocator; (4) spark-ignited rotary; and (5) spark-ignited reciprocator. Based on a simplified analysis and somewhat approximate data, the simple turboshaft engine apparently has the lowest costs for mission times up to just under 2 hours. At 2 hours and above, the regenerative turboshaft appears promising. The reciprocating and rotary engines are less attractive, requiring from 10 percent to 80 percent more aircraft to have the same total payload capability as a given number of turbine powered craft. A nomogram was developed for estimating total costs of engines not covered in this study.

  13. Cost/Effort Drivers and Decision Analysis

    NASA Technical Reports Server (NTRS)

    Seidel, Jonathan

    2010-01-01

    Engineering trade study analyses demand consideration of performance, cost and schedule impacts across the spectrum of alternative concepts and in direct reference to product requirements. Prior to detailed design, requirements are too often ill-defined (only goals ) and prone to creep, extending well beyond the Systems Requirements Review. Though lack of engineering design and definitive requirements inhibit the ability to perform detailed cost analyses, affordability trades still comprise the foundation of these future product decisions and must evolve in concert. This presentation excerpts results of the recent NASA subsonic Engine Concept Study for an Advanced Single Aisle Transport to demonstrate an affordability evaluation of performance characteristics and the subsequent impacts on engine architecture decisions. Applying the Process Based Economic Analysis Tool (PBEAT), development cost, production cost, as well as operation and support costs were considered in a traditional weighted ranking of the following system-level figures of merit: mission fuel burn, take-off noise, NOx emissions, and cruise speed. Weighting factors were varied to ascertain the architecture ranking sensitivities to these performance figures of merit with companion cost considerations. A more detailed examination of supersonic variable cycle engine cost is also briefly presented, with observations and recommendations for further refinements.

  14. Engine dynamic analysis with general nonlinear finite element codes

    NASA Technical Reports Server (NTRS)

    Adams, M. L.; Padovan, J.; Fertis, D. G.

    1991-01-01

    A general engine dynamic analysis as a standard design study computational tool is described for the prediction and understanding of complex engine dynamic behavior. Improved definition of engine dynamic response provides valuable information and insights leading to reduced maintenance and overhaul costs on existing engine configurations. Application of advanced engine dynamic simulation methods provides a considerable cost reduction in the development of new engine designs by eliminating some of the trial and error process done with engine hardware development.

  15. Design concepts for low-cost composite turbofan engine frame

    NASA Technical Reports Server (NTRS)

    Mitchell, S. C.; Stoffer, L. J.

    1980-01-01

    Design concepts for low cost, lightweight composite engine frames were applied to the design requirements for the frame of a commercial, high bypass engine. Four alternative composite frame design concepts identified which consisted of generic type components and subcomponents that could be adapted to use in different locations in the engine and the different engine sizes. A variety of materials and manufacturing methods were projected with a goal for the lowest number of parts at the lowest possible cost. After a preliminary evaluation of all four frame concepts, two designs were selected for an extended design and evaluation which narrowed the final selection down to one frame that was significantly lower in cost and slighty lighter than the other frame. An implementation plan for this lowest cost frame is projected for future development and includes prospects for reducing its weight with proposed unproven, innovative fabrication techniques.

  16. 45 CFR 13.7 - Studies, exhibits, analyses, engineering reports, tests and projects.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... 45 Public Welfare 1 2011-10-01 2011-10-01 false Studies, exhibits, analyses, engineering reports... Studies, exhibits, analyses, engineering reports, tests and projects. The reasonable cost (or the reasonable portion of the cost) for any study, exhibit, analysis, engineering report, test, project or...

  17. 45 CFR 13.7 - Studies, exhibits, analyses, engineering reports, tests and projects.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... 45 Public Welfare 1 2013-10-01 2013-10-01 false Studies, exhibits, analyses, engineering reports... Studies, exhibits, analyses, engineering reports, tests and projects. The reasonable cost (or the reasonable portion of the cost) for any study, exhibit, analysis, engineering report, test, project or...

  18. 45 CFR 13.7 - Studies, exhibits, analyses, engineering reports, tests and projects.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... 45 Public Welfare 1 2014-10-01 2014-10-01 false Studies, exhibits, analyses, engineering reports... Studies, exhibits, analyses, engineering reports, tests and projects. The reasonable cost (or the reasonable portion of the cost) for any study, exhibit, analysis, engineering report, test, project or...

  19. 45 CFR 13.7 - Studies, exhibits, analyses, engineering reports, tests and projects.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... 45 Public Welfare 1 2010-10-01 2010-10-01 false Studies, exhibits, analyses, engineering reports... Studies, exhibits, analyses, engineering reports, tests and projects. The reasonable cost (or the reasonable portion of the cost) for any study, exhibit, analysis, engineering report, test, project or...

  20. 45 CFR 13.7 - Studies, exhibits, analyses, engineering reports, tests and projects.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... 45 Public Welfare 1 2012-10-01 2012-10-01 false Studies, exhibits, analyses, engineering reports... Studies, exhibits, analyses, engineering reports, tests and projects. The reasonable cost (or the reasonable portion of the cost) for any study, exhibit, analysis, engineering report, test, project or...

  1. The Stirling engine as a low cost tool to educate mechanical engineers

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    Gros, J.; Munoz, M.; Moreno, F.

    1995-12-31

    The University of Zaragoza through CIRCE, the New Enterprise foundation, an Opel foundation and the local Government of Aragon have been developed a program to introduce the Stirling Engine as a low cost tool to educate students in mechanical engineering. The promotion of a prize like GNAT Power organized by the magazine Model Engineer in London, has improved the practical education of students in the field of mechanical devices and thermal engines. Two editions of the contest, 1993 and 1994, awarded the greatest power Stirling engine made by only using a little candle of paraffin as a heat source. Fourmore » engines were presented in the first edition, with an average power of about 100 mW, and seven engines in the second one, achieving a power of about 230 mW. Presentations in Technical Schools and the University have been carried out. Also low cost tools have been made for measuring an electronic device to draw the real internal pressure volume diagram using a PC. A very didactic software to design classic kinematic alpha, beta and gamma engines plus Ringbom beta and gamma engines has been created. A book is going to be published (in Spanish) explaining the design of small Stirling engines as a way to start with low cost research in thermal engines, a very difficult target with IC engines.« less

  2. 47 CFR 27.1180 - The cost-sharing formula.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ...); towers and/or modifications; back-up power equipment; monitoring or control equipment; engineering costs (design/path survey); installation; systems testing; FCC filing costs; site acquisition and civil works... as equipment and engineering expenses. There is no cap on the actual costs of relocation. (c) An AWS...

  3. 19 CFR 10.197 - Direct costs of processing operations performed in a beneficiary country or countries.

    Code of Federal Regulations, 2013 CFR

    2013-04-01

    ... specific merchandise, including fringe benefits, on-the-job training, and the cost of engineering..., engineering, and blueprint costs insofar as they are allocable to the specific merchandise and; (4) Costs of... 19 Customs Duties 1 2013-04-01 2013-04-01 false Direct costs of processing operations performed in...

  4. 19 CFR 10.197 - Direct costs of processing operations performed in a beneficiary country or countries.

    Code of Federal Regulations, 2014 CFR

    2014-04-01

    ... specific merchandise, including fringe benefits, on-the-job training, and the cost of engineering..., engineering, and blueprint costs insofar as they are allocable to the specific merchandise and; (4) Costs of... 19 Customs Duties 1 2014-04-01 2014-04-01 false Direct costs of processing operations performed in...

  5. Engine Seal Technology Requirements to Meet NASA's Advanced Subsonic Technology Program Goals

    NASA Technical Reports Server (NTRS)

    Steinetz, Bruce M.; Hendricks, Robert C.

    1994-01-01

    Cycle studies have shown the benefits of increasing engine pressure ratios and cycle temperatures to decrease engine weight and improve performance of commercial turbine engines. NASA is working with industry to define technology requirements of advanced engines and engine technology to meet the goals of NASA's Advanced Subsonic Technology Initiative. As engine operating conditions become more severe and customers demand lower operating costs, NASA and engine manufacturers are investigating methods of improving engine efficiency and reducing operating costs. A number of new technologies are being examined that will allow next generation engines to operate at higher pressures and temperatures. Improving seal performance - reducing leakage and increasing service life while operating under more demanding conditions - will play an important role in meeting overall program goals of reducing specific fuel consumption and ultimately reducing direct operating costs. This paper provides an overview of the Advanced Subsonic Technology program goals, discusses the motivation for advanced seal development, and highlights seal technology requirements to meet future engine performance goals.

  6. An Exploratory Study of Cost Engineering in Axiomatic Design: Creation of the Cost Model Based on an FR-DP Map

    NASA Technical Reports Server (NTRS)

    Lee, Taesik; Jeziorek, Peter

    2004-01-01

    Large complex projects cost large sums of money throughout their life cycle for a variety of reasons and causes. For such large programs, the credible estimation of the project cost, a quick assessment of the cost of making changes, and the management of the project budget with effective cost reduction determine the viability of the project. Cost engineering that deals with these issues requires a rigorous method and systematic processes. This paper introduces a logical framework to a&e effective cost engineering. The framework is built upon Axiomatic Design process. The structure in the Axiomatic Design process provides a good foundation to closely tie engineering design and cost information together. The cost framework presented in this paper is a systematic link between the functional domain (FRs), physical domain (DPs), cost domain (CUs), and a task/process-based model. The FR-DP map relates a system s functional requirements to design solutions across all levels and branches of the decomposition hierarchy. DPs are mapped into CUs, which provides a means to estimate the cost of design solutions - DPs - from the cost of the physical entities in the system - CUs. The task/process model describes the iterative process ot-developing each of the CUs, and is used to estimate the cost of CUs. By linking the four domains, this framework provides a superior traceability from requirements to cost information.

  7. Cost Benefit Analysis: Cost Benefit Analysis for Human Effectiveness Research: Bioacoustic Protection

    DTIC Science & Technology

    2001-07-21

    APPENDIX A. ACRONYMS ACCES Attenuating Custom Communication Earpiece System ACEIT Automated Cost estimating Integrated Tools AFSC Air Force...documented in the ACEIT cost estimating tool developed by Tecolote, Inc. The factor used was 14 percent of PMP. 1.3 System Engineering/ Program...The data source is the ASC Aeronautical Engineering Products Cost Factor Handbook which is documented in the ACEIT cost estimating tool developed

  8. 48 CFR 48.102 - Policies.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... cost-effective value engineering procedures and processes. Agencies shall provide contractors a... services must require a mandatory value engineering program to reduce total ownership cost in accordance... VALUE ENGINEERING Policies and Procedures 48.102 Policies. (a) As required by Section 36 of the Office...

  9. 48 CFR 48.102 - Policies.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... cost-effective value engineering procedures and processes. Agencies shall provide contractors a... services must require a mandatory value engineering program to reduce total ownership cost in accordance... VALUE ENGINEERING Policies and Procedures 48.102 Policies. (a) As required by Section 36 of the Office...

  10. 33 CFR 385.26 - Project Implementation Reports.

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... Implementation Report is a document that provides information on plan formulation and evaluation, engineering and..., environmental and/or economic benefits, engineering and design, costs, environmental impacts, real estate..., optimization and justification, cost-effectiveness, and engineering feasibility of the project; (xiii) Include...

  11. Free-Piston Stirling Engines

    NASA Technical Reports Server (NTRS)

    Shaltens, Richard K.

    1989-01-01

    Engines promise cost-effective solar-power generation. Report describes two concepts for Stirling-engine systems for conversion of solar heat to electrical energy. Recognized most promising technologies for meeting U.S. Department of Energy goals for performance and cost for terrestrial electrical-energy sources.

  12. Low-cost commercial transport

    NASA Technical Reports Server (NTRS)

    Mcpherson, J.

    1991-01-01

    The topics presented are covered in viewgraph form. The objectives are to develop and validate technology, design tools and methodologies to enable the low cost commercial development and operational uses of hydrogen and hydrocarbon fueled liquid engines, low pressure booster engines and hybrid engines.

  13. Examining engineering costs for development of highway projects.

    DOT National Transportation Integrated Search

    2012-12-01

    The Texas Department of Transportation (TxDOT) commissioned a research team at Texas State University-San Marcos Department of Accounting to analyze the cost of projects by determining the cost of a preliminary engineering hour necessary to develop h...

  14. Orbit transfer vehicle engine study. Volume 2: Technical report

    NASA Technical Reports Server (NTRS)

    1980-01-01

    The orbit transfer vehicle (OTV) engine study provided parametric performance, engine programmatic, and cost data on the complete propulsive spectrum that is available for a variety of high energy, space maneuvering missions. Candidate OTV engines from the near term RL 10 (and its derivatives) to advanced high performance expander and staged combustion cycle engines were examined. The RL 10/RL 10 derivative performance, cost and schedule data were updated and provisions defined which would be necessary to accommodate extended low thrust operation. Parametric performance, weight, envelope, and cost data were generated for advanced expander and staged combustion OTV engine concepts. A prepoint design study was conducted to optimize thrust chamber geometry and cooling, engine cycle variations, and controls for an advanced expander engine. Operation at low thrust was defined for the advanced expander engine and the feasibility and design impact of kitting was investigated. An analysis of crew safety and mission reliability was conducted for both the staged combustion and advanced expander OTV engine candidates.

  15. 19 CFR 10.814 - Direct costs of processing operations.

    Code of Federal Regulations, 2014 CFR

    2014-04-01

    ... manufacture of the specific good, including fringe benefits, on-the-job training, and the costs of engineering..., design, engineering, and blueprint costs, to the extent that they are allocable to the specific good; (4... 19 Customs Duties 1 2014-04-01 2014-04-01 false Direct costs of processing operations. 10.814...

  16. 19 CFR 10.774 - Direct costs of processing operations.

    Code of Federal Regulations, 2014 CFR

    2014-04-01

    ... manufacture of the specific good, including fringe benefits, on-the-job training, and the costs of engineering..., design, engineering, and blueprint costs, to the extent that they are allocable to the specific good; (4... 19 Customs Duties 1 2014-04-01 2014-04-01 false Direct costs of processing operations. 10.774...

  17. Conceptual design study of improved automotives gas turbine powertrain

    NASA Technical Reports Server (NTRS)

    1979-01-01

    Twenty-two candidate engine concepts and nineteen transmission concepts. Screening of these concepts, predominantly for fuel economy, cost and technical risk, resulted in a recommended powertrain consisting of a single-shaft engine, with a ceramic radial turbine rotor, connected through a differential split-power transmission utilizing a variable stator torque converter and a four speed automatic gearbox. Vehicle fuel economy and performance projections, preliminary design analyses and installation studies in a were completed. A cost comparison with the conventional spark ignited gasoline engine showed that the turbine engine would be more expensive initially, however, lifetime cost of ownership is in favor of the gas turbine. A powertrain research and development plan was constructed to gain information on timing and costs to achieve the required level of technology and demonstrate the engine in a vehicle by the year 1983.

  18. Advanced Transportation System Studies. Technical Area 3: Alternate Propulsion Subsystem Concepts. Volume 1; Executive Summary

    NASA Technical Reports Server (NTRS)

    Levack, Daniel J. H.

    2000-01-01

    The Alternate Propulsion Subsystem Concepts contract had seven tasks defined that are reported under this contract deliverable. The tasks were: FAA Restart Study, J-2S Restart Study, Propulsion Database Development. SSME Upper Stage Use. CERs for Liquid Propellant Rocket Engines. Advanced Low Cost Engines, and Tripropellant Comparison Study. The two restart studies, F-1A and J-2S, generated program plans for restarting production of each engine. Special emphasis was placed on determining changes to individual parts due to obsolete materials, changes in OSHA and environmental concerns, new processes available, and any configuration changes to the engines. The Propulsion Database Development task developed a database structure and format which is easy to use and modify while also being comprehensive in the level of detail available. The database structure included extensive engine information and allows for parametric data generation for conceptual engine concepts. The SSME Upper Stage Use task examined the changes needed or desirable to use the SSME as an upper stage engine both in a second stage and in a translunar injection stage. The CERs for Liquid Engines task developed qualitative parametric cost estimating relationships at the engine and major subassembly level for estimating development and production costs of chemical propulsion liquid rocket engines. The Advanced Low Cost Engines task examined propulsion systems for SSTO applications including engine concept definition, mission analysis. trade studies. operating point selection, turbomachinery alternatives, life cycle cost, weight definition. and point design conceptual drawings and component design. The task concentrated on bipropellant engines, but also examined tripropellant engines. The Tripropellant Comparison Study task provided an unambiguous comparison among various tripropellant implementation approaches and cycle choices, and then compared them to similarly designed bipropellant engines in the SSTO mission This volume overviews each of the tasks giving its objectives, main results. and conclusions. More detailed Final Task Reports are available on each individual task.

  19. Low-Cost Virtual Laboratory Workbench for Electronic Engineering

    ERIC Educational Resources Information Center

    Achumba, Ifeyinwa E.; Azzi, Djamel; Stocker, James

    2010-01-01

    The laboratory component of undergraduate engineering education poses challenges in resource constrained engineering faculties. The cost, time, space and physical presence requirements of the traditional (real) laboratory approach are the contributory factors. These resource constraints may mitigate the acquisition of meaningful laboratory…

  20. 48 CFR 9904.420-60 - Illustrations.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... STANDARDS COST ACCOUNTING STANDARDS 9904.420-60 Illustrations. (a) Business Unit A's engineering department... typing its overhead cost pool. In submitting a proposal, the engineering department assigns several... Section 9904.420-60 Federal Acquisition Regulations System COST ACCOUNTING STANDARDS BOARD, OFFICE OF...

  1. Cost/benefit analysis of advanced materials technologies for future aircraft turbine engines

    NASA Technical Reports Server (NTRS)

    Stephens, G. E.

    1980-01-01

    The materials technologies studied included thermal barrier coatings for turbine airfoils, turbine disks, cases, turbine vanes and engine and nacelle composite materials. The cost/benefit of each technology was determined in terms of Relative Value defined as change in return on investment times probability of success divided by development cost. A recommended final ranking of technologies was based primarily on consideration of Relative Values with secondary consideration given to changes in other economic parameters. Technologies showing the most promising cost/benefits were thermal barrier coated temperature nacelle/engine system composites.

  2. Space transportation booster engine configuration study. Volume 1: Executive Summary

    NASA Technical Reports Server (NTRS)

    1989-01-01

    The objective of the Space Transportation Booster Engine (STBE) Configuration Study is to contribute to the Advanced Launch System (ALS) development effort by providing highly reliable, low cost booster engine concepts for both expendable and reusable rocket engines. The objectives of the Space Transportation Booster Engine (STBE) Configuration Study were to identify engine configurations which enhance vehicle performance and provide operational flexibility at low cost, and to explore innovative approaches to the follow-on full-scale development (FSD) phase for the STBE.

  3. Local Government Planning Tool to Calculate Institutional and Engineering Control Costs for Brownfield Properties

    EPA Pesticide Factsheets

    This cost calculator is designed as a guide for municipal or local governments to assist in calculating their expected costs of implementing and conducting long-term stewardship of institutional controls and engineering controls at brownfield properties.

  4. 48 CFR 17.106-1 - General.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ..., preproduction engineering, initial rework, initial spoilage, pilot runs, allocable portions of the costs of... should obtain in-house engineering cost estimates identifying the detailed recurring and nonrecurring... cancellation. For example, consider that the total nonrecurring costs (see 15.408, Table 15-2, Formats for...

  5. 48 CFR 17.106-1 - General.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ..., preproduction engineering, initial rework, initial spoilage, pilot runs, allocable portions of the costs of... should obtain in-house engineering cost estimates identifying the detailed recurring and nonrecurring... cancellation. For example, consider that the total nonrecurring costs (see 15.408, Table 15-2, Formats for...

  6. 48 CFR 17.106-1 - General.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ..., preproduction engineering, initial rework, initial spoilage, pilot runs, allocable portions of the costs of... should obtain in-house engineering cost estimates identifying the detailed recurring and nonrecurring... cancellation. For example, consider that the total nonrecurring costs (see 15.408, Table 15-2, Formats for...

  7. An Introduction to the Cost of Engineering and Institutional Controls at Brownfield Properties

    EPA Pesticide Factsheets

    This fact sheet introduces and explores the costs of site cleanup and, where cleanup leaves site contamination that restricts reuse, outlines the engineering and institutional controls and their monitoring and maintenance costs over a longer time frame.

  8. Repurposing Mass-produced Internal Combustion Engines Quantifying the Value and Use of Low-cost Internal Combustion Piston Engines for Modular Applications in Energy and Chemical Engineering Industries

    NASA Astrophysics Data System (ADS)

    L'Heureux, Zara E.

    This thesis proposes that internal combustion piston engines can help clear the way for a transformation in the energy, chemical, and refining industries that is akin to the transition computer technology experienced with the shift from large mainframes to small personal computers and large farms of individually small, modular processing units. This thesis provides a mathematical foundation, multi-dimensional optimizations, experimental results, an engine model, and a techno-economic assessment, all working towards quantifying the value of repurposing internal combustion piston engines for new applications in modular, small-scale technologies, particularly for energy and chemical engineering systems. Many chemical engineering and power generation industries have focused on increasing individual unit sizes and centralizing production. This "bigger is better" concept makes it difficult to evolve and incorporate change. Large systems are often designed with long lifetimes, incorporate innovation slowly, and necessitate high upfront investment costs. Breaking away from this cycle is essential for promoting change, especially change happening quickly in the energy and chemical engineering industries. The ability to evolve during a system's lifetime provides a competitive advantage in a field dominated by large and often very old equipment that cannot respond to technology change. This thesis specifically highlights the value of small, mass-manufactured internal combustion piston engines retrofitted to participate in non-automotive system designs. The applications are unconventional and stem first from the observation that, when normalized by power output, internal combustion engines are one hundred times less expensive than conventional, large power plants. This cost disparity motivated a look at scaling laws to determine if scaling across both individual unit size and number of units produced would predict the two order of magnitude difference seen here. For the first time, this thesis provides a mathematical analysis of scaling with a combination of both changing individual unit size and varying the total number of units produced. Different paths to meet a particular cumulative capacity are analyzed and show that total costs are path dependent and vary as a function of the unit size and number of units produced. The path dependence identified is fairly weak, however, and for all practical applications, the underlying scaling laws seem unaffected. This analysis continues to support the interest in pursuing designs built around small, modular infrastructure. Building on the observation that internal combustion engines are an inexpensive power-producing unit, the first optimization in this thesis focuses on quantifying the value of engine capacity committing to deliver power in the day-ahead electricity and reserve markets, specifically based on pricing from the New York Independent System Operator (NYISO). An optimization was written in Python to determine, based on engine cost, fuel cost, engine wear, engine lifetime, and electricity prices, when and how much of an engine's power should be committed to a particular energy market. The optimization aimed to maximize profit for the engine and generator (engine genset) system acting as a price-taker. The result is an annual profit on the order of \\$30 per kilowatt. The most value in the engine genset is in its commitments to the spinning reserve market, where power is often committed but not always called on to deliver. This analysis highlights the benefits of modularity in energy generation and provides one example where the system is so inexpensive and short-lived, that the optimization views the engine replacement cost as a consumable operating expense rather than a capital cost. Having the opportunity to incorporate incremental technological improvements in a system's infrastructure throughout its lifetime allows introduction of new technology with higher efficiencies and better designs. An alternative to traditionally large infrastructure that locks in a design and today's state-of-the-art technology for the next 50 - 70 years, is a system designed to incorporate new technology in a modular fashion. The modular engine genset system used for power generation is one example of how this works in practice. The largest single component of this thesis is modeling, designing, retrofitting, and testing a reciprocating piston engine used as a compressor. Motivated again by the low cost of an internal combustion engine, this work looks at how an engine (which is, in its conventional form, essentially a reciprocating compressor) can be cost-effectively retrofitted to perform as a small-scale gas compressor. In the laboratory, an engine compressor was built by retrofitting a one-cylinder, 79 cc engine. Various retrofitting techniques were incorporated into the system design, and the engine compressor performance was quantified in each iteration. Because the retrofitted engine is now a power consumer rather than a power-producing unit, the engine compressor is driven in the laboratory with an electric motor. Experimentally, compressed air engine exhaust (starting at elevated inlet pressures) surpassed 650 psia (about 45 bar), which makes this system very attractive for many applications in chemical engineering and refining industries. A model of the engine compressor system was written in Python and incorporates experimentally-derived parameters to quantify gas leakage, engine friction, and flow (including backflow) through valves. The model as a whole was calibrated and verified with experimental data and is used to explore engine retrofits beyond what was tested in the laboratory. Along with the experimental and modeling work, a techno-economic assessment is included to compare the engine compressor system with state-of-the-art, commercially-available compressors. Included in the financial analysis is a case study where an engine compressor system is modeled to achieve specific compression needs. The result of the assessment is that, indeed, the low engine cost, even with the necessary retrofits, provides a cost advantage over incumbent compression technologies. Lastly, this thesis provides an algorithm and case study for another application of small-scale units in energy infrastructure, specifically in energy storage. This study focuses on quantifying the value of small-scale, onsite energy storage in shaving peak power demands. This case study focuses on university-level power demands. The analysis finds that, because peak power is so costly, even small amounts of energy storage, when dispatched optimally, can provide significant cost reductions. This provides another example of the value of small-scale implementations, particularly in energy infrastructure. While the study focuses on flywheels and batteries as the energy storage medium, engine gensets could also be used to deliver power and shave peak power demands. The overarching goal of this thesis is to introduce small-scale, modular infrastructure, with a particular focus on the opportunity to retrofit and repurpose inexpensive, mass-manufactured internal combustion engines in new and unconventional applications. The modeling and experimental work presented in this dissertation show very compelling results for engines incorporated into both energy generation infrastructure and chemical engineering industries via compression technologies. The low engine cost provides an opportunity to add retrofits whilst remaining cost competitive with the incumbent technology. This work supports the claim that modular infrastructure, built on the indivisible unit of an internal combustion engine, can revolutionize many industries by providing a low-cost mechanism for rapid change and promoting small-scale designs.

  9. What kind of students should be developed through aeronautical engineering education?

    NASA Technical Reports Server (NTRS)

    Holloway, R. B.

    1975-01-01

    The educational requirements for future aeronautical engineering students are postulated. The change in aeronautical engineering from increasing aircraft performance without regard to cost is compared with the cost effective aspects of future research. The capabilities of future engineers are discussed with respect to the following areas: (1) problem solving, (2) planning and organizing, (3) communication, and (4) professionalism.

  10. New opportunities for future small civil turbine engines: Overviewing the GATE studies

    NASA Technical Reports Server (NTRS)

    Strack, W. C.

    1979-01-01

    An overview of four independent studies forecasts the potential impact of advanced technology turbine engines in the post 1988 market, identifies important aircraft and missions, desirable engine sizes, engine performance, and cost goals. Parametric evaluations of various engine cycles, configurations, design features, and advanced technology elements defined baseline conceptual engines for each of the important missions identified by the market analysis. Both fixed-wing and helicopter aircraft, and turboshaft, turboprop, and turbofan engines were considered. Sizable performance gains (e.g., 20% SFC decrease), and large engine cost reductions of sufficient magnitude are predicted to challenge the reciprocating engine in the 300-500 SHP class.

  11. Design the Cost Approach in Trade-Off's for Structural Components, Illustrated on the Baseline Selection of the Engine Thrust Frame of Ariane 5 ESC-B

    NASA Astrophysics Data System (ADS)

    Appolloni, L.; Juhls, A.; Rieck, U.

    2002-01-01

    Designing for value is one of the very actual upcoming methods for design optimization, which broke into the domain of aerospace engineering in the late 90's. In the frame of designing for value two main design philosophies exist: Design For Cost and Design To Cost. Design To Cost is the iterative redesign of a project until the content of the project meets a given budget. Designing For Cost is the conscious use of engineering process technology to reduce life cycle cost while satisfying, and hopefully exceeding, customer demands. The key to understanding cost, and hence to reducing cost, is the ability to measure cost accurately and to allocate it appropriately to products. Only then can intelligent decisions be made. Therefore the necessity of new methods as "Design For Value" or "Design For Competitiveness", set up with a generally multidisciplinary approach to find an optimized technical solution driven by many parameters, depending on the mission scenario and the customer/market needs. Very often three, but not more than five parametric drivers are sufficient. The more variable exist, the higher is in fact the risk to find just a sub-optimized local and not the global optimum, and the less robust is the found solution against change of input parameters. When the main parameters for optimization have been identified, the system engineer has to communicate them to all design engineers, who shall take care of these assessment variables during the entire design and decision process. The design process which has taken to the definition of the feasible structural concepts for the Engine Thrust Frame of the Ariane 5 Upper Cryogenic Stage ESC-B follows these most actual design philosophy methodologies, and combines a design for cost approach, to a design to cost optimization loop. Ariane 5 is the first member of a family of heavy-lift launchers. It aims to evolve into a family of launchers that responds to the space transportation challenges of the 21st century. New upper stages, along with modifications to the main cryogenic stage and solid boosters, will increase performance and meet demands of a changing market. A two-steps approach was decided for future developments of the launcher upper stage, in order to increase the payload lift capability of Ariane 5. The first step ESC-A is scheduled for first launch in 2002. As later step ESC-B shall grow up to 12 tons in GTO orbit, with multiple restart capability, i.e. re-ignitable engine. Ariane 5 ESC-B first flight is targeted for 2006. It will be loaded with 28 metric tons of liquid oxygen and liquid hydrogen and powered by a new expander cycle engine "Vinci". The Vinci engine will be connected to the tanks of the ESC-B stage via the structure named from the designers ETF, or Engine Thrust Frame. In order to develop a design concept for the ETF component a trade off was performed, based on the most modern system engineering methodologies. This paper will describe the basis of the system engineering approach in the design to cost process, and illustrate such approach as it has been applied during the trade off for the baseline selection of the Engine Thrust Frame of Ariane 5 ESC-B.

  12. A review of findings of a study of rocket based combined cycle engines applied to extensively axisymmetric single stage to orbit vehicles

    NASA Technical Reports Server (NTRS)

    Foster, Richard W.

    1992-01-01

    Extensively axisymmetric and non-axisymmetric Single Stage To Orbit (SSTO) vehicles are considered. The information is presented in viewgraph form and the following topics are presented: payload comparisons; payload as a percent of dry weight - a system hardware cost indicator; life cycle cost estimations; operations and support costs estimation; selected engine type; and rocket engine specific impulse calculation.

  13. 48 CFR 48.102 - Policies.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... VALUE ENGINEERING Policies and Procedures 48.102 Policies. (a) As required by 41 U.S.C. 1711, agencies shall establish and maintain cost-effective value engineering procedures and processes. Agencies shall... cost in accordance with 48.101(b)(2). However, there must be no sharing of value engineering savings in...

  14. 737/CFM56-7 Aircraft Engine Systems

    NASA Technical Reports Server (NTRS)

    Wright, Steve; Shiosaki, Justin

    2006-01-01

    The configuration of the propulsion system engine externals must meet many airplane requirements such as cost, thrust, weight, range and systems power extraction. On the 737-700 several program requirements also played a major role in the development of the engine externals. These program goals were increased range, same cost as a 1994 737-300, 15% reduction in maintenance costs from the 737-300, and a propulsion package that appeared as if it was designed by one company. This presentation will show how these requirements shaped the design of the engine externals for the 737-700/CFM56-7B.

  15. Exergo-Economic Analysis of an Experimental Aircraft Turboprop Engine Under Low Torque Condition

    NASA Astrophysics Data System (ADS)

    Atilgan, Ramazan; Turan, Onder; Aydin, Hakan

    Exergo-economic analysis is an unique combination of exergy analysis and cost analysis conducted at the component level. In exergo-economic analysis, cost of each exergy stream is determined. Inlet and outlet exergy streams of the each component are associated to a monetary cost. This is essential to detect cost-ineffective processes and identify technical options which could improve the cost effectiveness of the overall energy system. In this study, exergo-economic analysis is applied to an aircraft turboprop engine. Analysis is based on experimental values at low torque condition (240 N m). Main components of investigated turboprop engine are the compressor, the combustor, the gas generator turbine, the free power turbine and the exhaust. Cost balance equations have been formed for all components individually and exergo-economic parameters including cost rates and unit exergy costs have been calculated for each component.

  16. Cost/benefit analysis of advanced materials technology candidates for the 1980's, part 2

    NASA Technical Reports Server (NTRS)

    Dennis, R. E.; Maertins, H. F.

    1980-01-01

    Cost/benefit analyses to evaluate advanced material technologies projects considered for general aviation and turboprop commuter aircraft through estimated life-cycle costs, direct operating costs, and development costs are discussed. Specifically addressed is the selection of technologies to be evaluated; development of property goals; assessment of candidate technologies on typical engines and aircraft; sensitivity analysis of the changes in property goals on performance and economics, cost, and risk analysis for each technology; and ranking of each technology by relative value. The cost/benefit analysis was applied to a domestic, nonrevenue producing, business-type jet aircraft configured with two TFE731-3 turbofan engines, and to a domestic, nonrevenue producing, business type turboprop aircraft configured with two TPE331-10 turboprop engines. In addition, a cost/benefit analysis was applied to a commercial turboprop aircraft configured with a growth version of the TPE331-10.

  17. Development of advanced high temperature in-cylinder components and tribological systems for low heat rejection diesel engines, phase 1

    NASA Astrophysics Data System (ADS)

    Kroeger, C. A.; Larson, H. J.

    1992-03-01

    Analysis and concept design work completed in Phase 1 have identified a low heat rejection engine configuration with the potential to meet the Heavy Duty Transport Technology program specific fuel consumption goal of 152 g/kW-hr. The proposed engine configuration incorporates low heat rejection, in-cylinder components designed for operation at 24 MPa peak cylinder pressure. Water cooling is eliminated by selective oil cooling of the components. A high temperature lubricant will be required due to increased in-cylinder operating temperatures. A two-stage turbocharger air system with intercooling and aftercooling was selected to meet engine boost and BMEP requirements. A turbocompound turbine stage is incorporated for exhaust energy recovery. The concept engine cost was estimated to be 43 percent higher compared to a Caterpillar 3176 engine. The higher initial engine cost is predicted to be offset by reduced operating costs due the lower fuel consumption.

  18. Development of advanced high temperature in-cylinder components and tribological systems for low heat rejection diesel engines, phase 1

    NASA Technical Reports Server (NTRS)

    Kroeger, C. A.; Larson, H. J.

    1992-01-01

    Analysis and concept design work completed in Phase 1 have identified a low heat rejection engine configuration with the potential to meet the Heavy Duty Transport Technology program specific fuel consumption goal of 152 g/kW-hr. The proposed engine configuration incorporates low heat rejection, in-cylinder components designed for operation at 24 MPa peak cylinder pressure. Water cooling is eliminated by selective oil cooling of the components. A high temperature lubricant will be required due to increased in-cylinder operating temperatures. A two-stage turbocharger air system with intercooling and aftercooling was selected to meet engine boost and BMEP requirements. A turbocompound turbine stage is incorporated for exhaust energy recovery. The concept engine cost was estimated to be 43 percent higher compared to a Caterpillar 3176 engine. The higher initial engine cost is predicted to be offset by reduced operating costs due the lower fuel consumption.

  19. First-Grade Engineers

    ERIC Educational Resources Information Center

    Bautista, Nazan Uludag; Peters, Kari Nichole

    2010-01-01

    Can students build a house that is cost effective and strong enough to survive strong winds, heavy rains, and earthquakes? First graders in Ms. Peter's classroom worked like engineers to answer this question. They participated in a design challenge that required them to plan like engineers and build strong and cost-effective houses that would fit…

  20. On the Cost of Engineering Education.

    ERIC Educational Resources Information Center

    Black, Guy

    This study examines how the cost of engineering education changes with the size and characteristics of programs, and tries to establish whether there is some minimum scale at which point engineering education becomes financially viable, and considers the manner in which financial viability is affected by program characteristics. Chapter I presents…

  1. Engineering and Fabrication Considerations for Cost-Effective Space Reactor Shield Development

    NASA Astrophysics Data System (ADS)

    Berg, Thomas A.; Disney, Richard K.

    2004-02-01

    Investment in developing nuclear power for space missions cannot be made on the basis of a single mission. Current efforts in the design and fabrication of the reactor module, including the reactor shield, must be cost-effective and take into account scalability and fabricability for planned and future missions. Engineering considerations for the shield need to accommodate passive thermal management, varying radiation levels and effects, and structural/mechanical issues. Considering these challenges, design principles and cost drivers specific to the engineering and fabrication of the reactor shield are presented that contribute to lower recurring mission costs.

  2. Engineering and Fabrication Considerations for Cost-Effective Space Reactor Shield Development

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    Berg, Thomas A.; Disney, Richard K.

    Investment in developing nuclear power for space missions cannot be made on the basis of a single mission. Current efforts in the design and fabrication of the reactor module, including the reactor shield, must be cost-effective and take into account scalability and fabricability for planned and future missions. Engineering considerations for the shield need to accommodate passive thermal management, varying radiation levels and effects, and structural/mechanical issues. Considering these challenges, design principles and cost drivers specific to the engineering and fabrication of the reactor shield are presented that contribute to lower recurring mission costs.

  3. Low-Cost Resin Transfer Molding Process Developed for High-Temperature Polyimide Matrix Composites

    NASA Technical Reports Server (NTRS)

    1996-01-01

    The use of high-temperature polymer matrix composites (PMC's) in aircraft engine applications can significantly reduce engine weight and improve performance and fuel efficiency. High-temperature PMC's, such as those based on the PMR-15 polyimide matrix resin developed by the NASA Lewis Research Center, have been used extensively in military applications where performance improvements have justified their use regardless of the cost involved in producing the component. However, in commercial engines cost is a primary driver, and PMC components must be produced at costs comparable to those of the metal components that they will replace.

  4. Study of small turbofan engines applicable to single-engine light airplanes

    NASA Technical Reports Server (NTRS)

    Merrill, G. L.

    1976-01-01

    The design, efficiency and cost factors are investigated for application of turbofan propulsion engines to single engine, general aviation light airplanes. A companion study of a hypothetical engine family of a thrust range suitable to such aircraft and having a high degree of commonality of design features and parts is presented. Future turbofan powered light airplanes can have a lower fuel consumption, lower weight, reduced airframe maintenance requirements and improved engine overhaul periods as compared to current piston engined powered airplanes. Achievement of compliance with noise and chemical emission regulations is expected without impairing performance, operating cost or safety.

  5. 32 CFR 165.3 - Definitions.

    Code of Federal Regulations, 2013 CFR

    2013-07-01

    ... evaluation. That includes costs of any engineering change proposals initiated before the date of calculations... includes costs of any engineering change proposal started before the date of calculation of the NC... NONRECURRING COSTS (NCs) ON SALES OF U.S. ITEMS § 165.3 Definitions. The following definitions apply to this...

  6. 32 CFR 165.3 - Definitions.

    Code of Federal Regulations, 2014 CFR

    2014-07-01

    ... evaluation. That includes costs of any engineering change proposals initiated before the date of calculations... includes costs of any engineering change proposal started before the date of calculation of the NC... NONRECURRING COSTS (NCs) ON SALES OF U.S. ITEMS § 165.3 Definitions. The following definitions apply to this...

  7. Space transportation booster engine configuration study. Volume 2: Design definition document and environmental analysis

    NASA Technical Reports Server (NTRS)

    1989-01-01

    The objective of the Space Transportation Booster Engine (STBE) Configuration Study is to contribute to the Advanced Launch System (ALS) development effort by providing highly reliable, low cost booster engine concepts for both expendable and reusable rocket engines. The objectives of the space Transportation Booster Engine (STBE) Configuration Study were: (1) to identify engine configurations which enhance vehicle performance and provide operational flexibility at low cost, and (2) to explore innovative approaches to the follow-on Full-Scale Development (FSD) phase for the STBE.

  8. Reducing the Time and Cost of Testing Engines

    NASA Technical Reports Server (NTRS)

    2004-01-01

    Producing a new aircraft engine currently costs approximately $1 billion, with 3 years of development time for a commercial engine and 10 years for a military engine. The high development time and cost make it extremely difficult to transition advanced technologies for cleaner, quieter, and more efficient new engines. To reduce this time and cost, NASA created a vision for the future where designers would use high-fidelity computer simulations early in the design process in order to resolve critical design issues before building the expensive engine hardware. To accomplish this vision, NASA's Glenn Research Center initiated a collaborative effort with the aerospace industry and academia to develop its Numerical Propulsion System Simulation (NPSS), an advanced engineering environment for the analysis and design of aerospace propulsion systems and components. Partners estimate that using NPSS has the potential to dramatically reduce the time, effort, and expense necessary to design and test jet engines by generating sophisticated computer simulations of an aerospace object or system. These simulations will permit an engineer to test various design options without having to conduct costly and time-consuming real-life tests. By accelerating and streamlining the engine system design analysis and test phases, NPSS facilitates bringing the final product to market faster. NASA's NPSS Version (V)1.X effort was a task within the Agency s Computational Aerospace Sciences project of the High Performance Computing and Communication program, which had a mission to accelerate the availability of high-performance computing hardware and software to the U.S. aerospace community for its use in design processes. The technology brings value back to NASA by improving methods of analyzing and testing space transportation components.

  9. Research requirements to reduce civil helicopter life cycle cost

    NASA Technical Reports Server (NTRS)

    Blewitt, S. J.

    1978-01-01

    The problem of the high cost of helicopter development, production, operation, and maintenance is defined and the cost drivers are identified. Helicopter life cycle costs would decrease by about 17 percent if currently available technology were applied. With advanced technology, a reduction of about 30 percent in helicopter life cycle costs is projected. Technological and managerial deficiencies which contribute to high costs are examined, basic research and development projects which can reduce costs include methods for reduced fuel consumption; improved turbine engines; airframe and engine production methods; safety; rotor systems; and advanced transmission systems.

  10. 24 CFR 905.314 - Cost and other limitations.

    Code of Federal Regulations, 2014 CFR

    2014-04-01

    ... excluding any costs related to lead-based paint or asbestos testing, in-house architectural and engineering... lead-based paint or asbestos testing, in-house Architectural and Engineering work, or other special... completion of the project, the actual project cost is determined based upon the amount of public housing...

  11. A probabilistic maintenance model for diesel engines

    NASA Astrophysics Data System (ADS)

    Pathirana, Shan; Abeygunawardane, Saranga Kumudu

    2018-02-01

    In this paper, a probabilistic maintenance model is developed for inspection based preventive maintenance of diesel engines based on the practical model concepts discussed in the literature. Developed model is solved using real data obtained from inspection and maintenance histories of diesel engines and experts' views. Reliability indices and costs were calculated for the present maintenance policy of diesel engines. A sensitivity analysis is conducted to observe the effect of inspection based preventive maintenance on the life cycle cost of diesel engines.

  12. A 150 and 300 kW lightweight diesel aircraft engine design study

    NASA Technical Reports Server (NTRS)

    Brouwers, A. P.

    1980-01-01

    The diesel engine was reinvestigated as an aircraft powerplant through design study conducted to arrive at engine configurations and applicable advanced technologies. Two engines are discussed, a 300 kW six-cylinder engine for twin engine general aviation aircraft and a 150 kW four-cylinder engine for single engine aircraft. Descriptions of each engine include concept drawings, a performance analysis, stress and weight data, and a cost study. This information was used to develop two airplane concepts, a six-place twin and a four-place single engine aircraft. The aircraft study consists of installation drawings, computer generated performance data, aircraft operating costs, and drawings of the resulting airplanes. The performance data show a vast improvement over current gasoline-powered aircraft.

  13. The gate studies: Assessing the potential of future small general aviation turbine engines

    NASA Technical Reports Server (NTRS)

    Strack, W. C.

    1979-01-01

    Four studies were completed that explore the opportunities for future General Aviation turbine engines (GATE) in the 150-1000 SHP class. These studies forecasted the potential impact of advanced technology turbine engines in the post-1988 market, identified important aircraft and missions, desirable engine sizes, engine performance, and cost goals. Parametric evaluations of various engine cycles, configurations, design features, and advanced technology elements defined baseline conceptual engines for each of the important missions identified by the market analysis. Both fixed-wing and helicopter aircraft, and turboshaft, turboprop, and turbofan engines were considered. Sizable performance gains (e.g., 20% SFC decrease), and large engine cost reductions of sufficient magnitude to challenge the reciprocating engine in the 300-500 SHP class were predicted.

  14. Software reengineering

    NASA Technical Reports Server (NTRS)

    Fridge, Ernest M., III

    1991-01-01

    Today's software systems generally use obsolete technology, are not integrated properly with other software systems, and are difficult and costly to maintain. The discipline of reverse engineering is becoming prominent as organizations try to move their systems up to more modern and maintainable technology in a cost effective manner. JSC created a significant set of tools to develop and maintain FORTRAN and C code during development of the Space Shuttle. This tool set forms the basis for an integrated environment to re-engineer existing code into modern software engineering structures which are then easier and less costly to maintain and which allow a fairly straightforward translation into other target languages. The environment will support these structures and practices even in areas where the language definition and compilers do not enforce good software engineering. The knowledge and data captured using the reverse engineering tools is passed to standard forward engineering tools to redesign or perform major upgrades to software systems in a much more cost effective manner than using older technologies. A beta vision of the environment was released in Mar. 1991. The commercial potential for such re-engineering tools is very great. CASE TRENDS magazine reported it to be the primary concern of over four hundred of the top MIS executives.

  15. Teaching Risk Analysis in an Aircraft Gas Turbine Engine Design Capstone Course

    DTIC Science & Technology

    2016-01-01

    American Institute of Aeronautics and Astronautics 1 Teaching Risk Analysis in an Aircraft Gas Turbine Engine Design Capstone Course...development costs, engine production costs, and scheduling (Byerley A. R., 2013) as well as the linkage between turbine inlet temperature, blade cooling...analysis SE majors have studied and how this is linked to the specific issues they must face in aircraft gas turbine engine design. Aeronautical and

  16. Review of Air Force Compressor Blade and Vane Rework and It’s Impact on Performance and Costs

    DTIC Science & Technology

    1990-05-01

    rework effort for reasons other than FOD. The actuarial data for March 1988, indicate that there are 977 J-79-17 engines and 2413 J-79-15 engines...maintenance shops about once every seven years (Engine Depot actuarial data). Consequently, the increased fuel cost to be used for rework cost comparisons...actual count made by personnel at Oklahoma City was only for the month of August. Additional information was based on actuarial data, assuming the data

  17. Methanator Fueled Engines for Pollution Control

    NASA Technical Reports Server (NTRS)

    Cagliostro, D. E.; Winkler, E. L.

    1973-01-01

    A methanator fueled Otto-cycle engine is compared with other methods proposed to control pollution due to automobile exhaust emissions. The comparison is made with respect to state of development, emission factors, capital cost, operational and maintenance costs, performance, operational limitations, and impact on the automotive industries. The methanator fueled Otto-cycle engine is projected to meet 1975 emission standards and operate at a lower relative total cost compared to the catalytic muffler system and to have low impact. Additional study is required for system development.

  18. Orbit Transfer Vehicle (OTV) engine phase A study, extension 1. Volume 3: Study cost estimates

    NASA Technical Reports Server (NTRS)

    Christensen, K. L.

    1980-01-01

    Program cost and planning data based on 1980 technology and shown in 1979 dollars for a 20K lb Thrust Staged Combustion Cycle Engine are presented. These data were compared with those for the Advanced Expander Cycle Engine at 10K lb and 20K lb thrust levels.

  19. Software engineering

    NASA Technical Reports Server (NTRS)

    Fridge, Ernest M., III; Hiott, Jim; Golej, Jim; Plumb, Allan

    1993-01-01

    Today's software systems generally use obsolete technology, are not integrated properly with other software systems, and are difficult and costly to maintain. The discipline of reverse engineering is becoming prominent as organizations try to move their systems up to more modern and maintainable technology in a cost effective manner. The Johnson Space Center (JSC) created a significant set of tools to develop and maintain FORTRAN and C code during development of the space shuttle. This tool set forms the basis for an integrated environment to reengineer existing code into modern software engineering structures which are then easier and less costly to maintain and which allow a fairly straightforward translation into other target languages. The environment will support these structures and practices even in areas where the language definition and compilers do not enforce good software engineering. The knowledge and data captured using the reverse engineering tools is passed to standard forward engineering tools to redesign or perform major upgrades to software systems in a much more cost effective manner than using older technologies. The latest release of the environment was in Feb. 1992.

  20. Cost/benefit analysis of advanced material technologies for small aircraft turbine engines

    NASA Technical Reports Server (NTRS)

    Comey, D. H.

    1977-01-01

    Cost/benefit studies were conducted on ten advanced material technologies applicable to small aircraft gas turbine engines to be produced in the 1985 time frame. The cost/benefit studies were applied to a two engine, business-type jet aircraft in the 6800- to 9100-Kg (15,000- to 20,000-lb) gross weight class. The new material technologies are intended to provide improvements in the areas of high-pressure turbine rotor components, high-pressure turbine rotor components, high-pressure turbine stator airfoils, and static structural components. The cost/benefit of each technology is presented in terms of relative value, which is defined as a change in life cycle cost times probability of success divided by development cost. Technologies showing the most promising cost/benefits based on relative value are uncooled single crystal MAR-M 247 turbine blades, cooled DS MAR-M 247 turbine blades, and cooled ODS 'M'CrAl laminate turbine stator vanes.

  1. Knowledge-based assistance in costing the space station DMS

    NASA Technical Reports Server (NTRS)

    Henson, Troy; Rone, Kyle

    1988-01-01

    The Software Cost Engineering (SCE) methodology developed over the last two decades at IBM Systems Integration Division (SID) in Houston is utilized to cost the NASA Space Station Data Management System (DMS). An ongoing project to capture this methodology, which is built on a foundation of experiences and lessons learned, has resulted in the development of an internal-use-only, PC-based prototype that integrates algorithmic tools with knowledge-based decision support assistants. This prototype Software Cost Engineering Automation Tool (SCEAT) is being employed to assist in the DMS costing exercises. At the same time, DMS costing serves as a forcing function and provides a platform for the continuing, iterative development, calibration, and validation and verification of SCEAT. The data that forms the cost engineering database is derived from more than 15 years of development of NASA Space Shuttle software, ranging from low criticality, low complexity support tools to highly complex and highly critical onboard software.

  2. 12 CFR 1071.202 - Documentation of fees and expenses.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... initiation of the adversary adjudication, including the cost of any study, engineering report, test, or... incurred after initiation of the adversary adjudication, including the cost of any study, engineering...

  3. Cost-engineering modeling to support rapid concept development of an advanced infrared satellite system

    NASA Astrophysics Data System (ADS)

    Bell, Kevin D.; Dafesh, Philip A.; Hsu, L. A.; Tsuda, A. S.

    1995-12-01

    Current architectural and design trade techniques often carry unaffordable alternatives late into the decision process. Early decisions made during the concept exploration and development (CE&D) phase will drive the cost of a program more than any other phase of development; thus, designers must be able to assess both the performance and cost impacts of their early choices. The Space Based Infrared System (SBIRS) cost engineering model (CEM) described in this paper is an end-to-end process integrating engineering and cost expertise through commonly available spreadsheet software, allowing for concurrent design engineering and cost estimation to identify and balance system drives to reduce acquisition costs. The automated interconnectivity between subsystem models using spreadsheet software allows for the quick and consistent assessment of the system design impacts and relative cost impacts due to requirement changes. It is different from most CEM efforts attempted in the past as it incorporates more detailed spacecraft and sensor payload models, and has been applied to determine the cost drivers for an advanced infrared satellite system acquisition. The CEM is comprised of integrated detailed engineering and cost estimating relationships describing performance, design, and cost parameters. Detailed models have been developed to evaluate design parameters for the spacecraft bus and sensor; both step-starer and scanner sensor types incorporate models of focal plane array, optics, processing, thermal, communications, and mission performance. The current CEM effort has provided visibility to requirements, design, and cost drivers for system architects and decision makers to determine the configuration of an infrared satellite architecture that meets essential requirements cost effectively. In general, the methodology described in this paper consists of process building blocks that can be tailored to the needs of many applications. Descriptions of the spacecraft and payload subsystem models provide insight into The Aerospace Corporation expertise and scope of the SBIRS concept development effort.

  4. Study of small turbofan engines applicable to single-engine light airplanes. Final report

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    Merrill, G.L.

    1976-09-01

    The design, efficiency and cost factors are investigated for application of turbofan propulsion engines to single engine, general aviation light airplanes. A companion study of a hypothetical engine family of a thrust range suitable to such aircraft and having a high degree of commonality of design features and parts is presented. Future turbofan powered light airplanes can have a lower fuel consumption, lower weight, reduced airframe maintenance requirements and improved engine overhaul periods as compared to current piston engined powered airplanes. Achievement of compliance with noise and chemical emission regulations is expected without impairing performance, operating cost or safety.

  5. Automotive Stirling reference engine design report

    NASA Technical Reports Server (NTRS)

    1981-01-01

    The reference Stirling engine system is described which provides the best possible fuel economy while meeting or exceeding all other program objectives. The system was designed to meet the requirements of a 1984 Pontiac Phoenix (X-body). This design utilizes all new technology that can reasonably be expected to be developed by 1984 and that is judged to provide significant improvement, relative to development risk and cost. Topics covered include: (1) external heat system; (2) hot engine system; (3) cold engine system; (4) engine drive system; (5) power control system and auxiliaries; (6) engine instalation; (7) optimization and vehicle simulation; (8) engine materials; and (9) production cost analysis.

  6. Cost and fuel consumption per nautical mile for two engine jet transports using OPTIM and TRAGEN

    NASA Technical Reports Server (NTRS)

    Wiggs, J. F.

    1982-01-01

    The cost and fuel consumption per nautical mile for two engine jet transports are computed using OPTIM and TRAGEN. The savings in fuel and direct operating costs per nautical mile for each of the different types of optimal trajectories over a standard profile are shown.

  7. Parametric sensitivity study for solar-assisted heat-pump systems

    NASA Astrophysics Data System (ADS)

    White, N. M.; Morehouse, J. H.

    1981-07-01

    The engineering and economic parameters affecting life-cycle costs for solar-assisted heat pump systems are investigted. The change in energy usage resulting from each engineering parameter varied was developed from computer simulations, and is compared with results from a stand-alone heat pump system. Three geographical locations are considered: Washington, DC, Fort Worth, TX, and Madison, WI. Results indicate that most engineering changes to the systems studied do not provide significant energy savings. The most promising parameters to ary are the solar collector parameters tau (-) and U/sub L/ the heat pump capacity at design point, and the minimum utilizable evaporator temperature. Costs associated with each change are estimated, and life-cycle costs computed for both engineering parameters and economic variations in interest rate, discount rate, tax credits, fuel unit costs and fuel inflation rates. Results indicate that none of the feasibile engineering changes for the system configuration studied will make these systems economically competitive with the stand-alone heat pump without a considerable tax credit.

  8. Introducing WISDEM:An Integrated System Modeling for Wind Turbines and Plant (Presentation)

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    Dykes, K.; Graf, P.; Scott, G.

    2015-01-01

    The National Wind Technology Center wind energy systems engineering initiative has developed an analysis platform to leverage its research capabilities toward integrating wind energy engineering and cost models across wind plants. This Wind-Plant Integrated System Design & Engineering Model (WISDEM) platform captures the important interactions between various subsystems to achieve a better National Wind Technology Center wind energy systems engineering initiative has developed an analysis platform to leverage its research capabilities toward integrating wind energy engineering and cost models across wind plants. This Wind-Plant Integrated System Design & Engineering Model (WISDEM) platform captures the important interactions between various subsystems tomore » achieve a better understanding of how to improve system-level performance and achieve system-level cost reductions. This work illustrates a few case studies with WISDEM that focus on the design and analysis of wind turbines and plants at different system levels.« less

  9. Weapon System Requirements: Detailed Systems Engineering Prior to Product Development Positions Programs for Success

    DTIC Science & Technology

    2016-11-01

    systems engineering had better outcomes. For example, the Small Diameter Bomb Increment I program, which delivered within cost and schedule estimates ...its current portfolio. This portfolio has experienced cost growth of 48 percent since first full estimates and average delays in delivering initial...stable design, building and testing of prototypes, and demonstration of mature production processes. • Realistic cost estimate : Sound cost estimates

  10. Engineering Change Management Method Framework in Mechanical Engineering

    NASA Astrophysics Data System (ADS)

    Stekolschik, Alexander

    2016-11-01

    Engineering changes make an impact on different process chains in and outside the company, and lead to most error costs and time shifts. In fact, 30 to 50 per cent of development costs result from technical changes. Controlling engineering change processes can help us to avoid errors and risks, and contribute to cost optimization and a shorter time to market. This paper presents a method framework for controlling engineering changes at mechanical engineering companies. The developed classification of engineering changes and accordingly process requirements build the basis for the method framework. The developed method framework comprises two main areas: special data objects managed in different engineering IT tools and process framework. Objects from both areas are building blocks that can be selected to the overall business process based on the engineering process type and change classification. The process framework contains steps for the creation of change objects (both for overall change and for parts), change implementation, and release. Companies can select singleprocess building blocks from the framework, depending on the product development process and change impact. The developed change framework has been implemented at a division (10,000 employees) of a big German mechanical engineering company.

  11. Selecting and Ranking Cost Research Projects

    DTIC Science & Technology

    1993-09-01

    Model (STACM) Enhancements Automated Cost Estimating Integrated Tools ( ACEIT ) Libraries BM/C 3 GEP Engineering and Cost BM/C 3 EP Engineering and Cost...50K NOM VHI 0.02635481 STACM ENHANCEMENTS NOM អK NOM VHI 0.02468682 ACEIT LIBRARIES VHI 50-IOOK HI VHI 0.06357704 GEP ENGRG. & COST VHI 100-150K VHl...0.02505922 SCATS LOW អK NOM VIII 0.02468682 PICES SUPPORT NOM 50-100K NOM VlIl 0.02455186 ACEIT SUPPORT VIII 50-100K VHI VHI 0.08208244 GUARDIAN

  12. Energy efficient engine component development and integration program

    NASA Technical Reports Server (NTRS)

    1982-01-01

    The objective of the Energy Efficient Engine Component Development and Integration program is to develop, evaluate, and demonstrate the technology for achieving lower installed fuel consumption and lower operating costs in future commercial turbofan engines. Minimum goals have been set for a 12 percent reduction in thrust specific fuel consumption (TSFC), 5 percent reduction in direct operating cost (DOC), and 50 percent reduction in performance degradation for the Energy Efficient Engine (flight propulsion system) relative to the JT9D-7A reference engine. The Energy Efficienct Engine features a twin spool, direct drive, mixed flow exhaust configuration, utilizing an integrated engine nacelle structure. A short, stiff, high rotor and a single stage high pressure turbine are among the major enhancements in providing for both performance retention and major reductions in maintenance and direct operating costs. Improved clearance control in the high pressure compressor and turbines, and advanced single crystal materials in turbine blades and vanes are among the major features providing performance improvement. Highlights of work accomplished and programs modifications and deletions are presented.

  13. Contingency power concepts for helicopter turboshaft engine

    NASA Technical Reports Server (NTRS)

    Hirschkron, R.; Davis, R. H.; Goldstein, D. N.; Haynes, J. F.; Gauntner, J. W.

    1984-01-01

    Twin helicopter engines are often sized by power requirement of safe mission completion after the failure of one of the two engines. This study was undertaken for NASA Lewis by General Electric Co. to evaluate the merits of special design features to provide a 2-1/2 minute Contingency Power rating, permitting an engine size reduction. The merits of water injection, cooling flow modulation, throttle push and an auxiliary power plant were evaluated using military life cycle cost (LCC) and commercial helicopter direct operating cost (DOC) merit factors in a rubber engine/rubber aircraft scenario.

  14. Engine for the next-generation launcher

    NASA Astrophysics Data System (ADS)

    Beichel, Rudi; Grey, Jerry

    1995-05-01

    The proposed dual-fuel/dual-expansion engine for the Reusable Launch Vehicle (RLV) could solve the vehicle's need for a high-performance, lightweight, low-cost, maintainable engine. The features that make dual-fuel/dual-expansion engine a prime candidate for RLV include oxygen-rich combustion, high-pressure staged-combustion cycle and dual-fuel operation. Cost-reducing, reliability-enhancing innovations such as the elimination of regenerative cooling, elimination of gimbaling and replacement of kerosene-based hydrocarbon fuel by subcooled propane have also made the this type of engine an attractive option.

  15. Construction engineering inspection direct cost survey.

    DOT National Transportation Integrated Search

    2014-07-01

    The objective of the study was to provide a rationale to Georgia Department of Transportation : (GDOT) for Direct Costs in terms of salary and wages charged by qualified independent : contractors performing Construction Engineering Inspection (CEI) s...

  16. Measurement Uncertainty Within the Uniform Engine Test Programme

    DTIC Science & Technology

    1989-05-01

    Design to Cost and l.ifc (.cle Cost to Aircraft Engines AGARD LS 107 (May 1980) Microcomputer Applications in Power and Propulsion Systems AGARD LS...Flows in Propulsion Systems AGARD LS 140 (June 1985) Engine Airframe Integration for Rotorcraft AGARD LS 148 (June 1986) Design Methods Used in Solid...modest nero-thermodynamic design was of no consequence. Two engines were loaned to the proeram by the U.S. Air Force. Due to higher priority test workload

  17. Proceedings of OSD Aircraft Engine Design & Life Cycle Cost Seminar Held at Naval Air Development Center, Warminster, Pennsylvania, May 17, 18 & 19, 1978,

    DTIC Science & Technology

    1978-01-01

    AD-A092 043 NAVAL AIR DEVELOPMENT CENTER WARMINSTER PA F/6 2/ I PROCEEDINGS OF 050 AIRCRAFT ENGINE DESIGN & LIFE CYCLE COST SEN--ETC (U NSI FE 1978 R...4 STANDAHAR, R R SHOREY. A PRESSMAN N PROCEEDINGS OFOSD AIRCRAFT ENGINE DESIGN & LIFE CYCLE COST SEMINAR HELD AT ,NAVAL AIR DEVELOPMENT CENTER f...RELIABILITY CAN BE MET. THIS INFORMATION WILL BE USED BY THE ACQUISITION ACTIVITY TO ESTABLISH THE PROPER DESIGN AND TEST REQUIREMENTS TO INSURE THAT THE

  18. Decision Making Methods in Space Economics and Systems Engineering

    NASA Technical Reports Server (NTRS)

    Shishko, Robert

    2006-01-01

    This viewgraph presentation reviews various methods of decision making and the impact that they have on space economics and systems engineering. Some of the methods discussed are: Present Value and Internal Rate of Return (IRR); Cost-Benefit Analysis; Real Options; Cost-Effectiveness Analysis; Cost-Utility Analysis; Multi-Attribute Utility Theory (MAUT); and Analytic Hierarchy Process (AHP).

  19. Study of the costs and benefits of composite materials in advanced turbofan engines

    NASA Technical Reports Server (NTRS)

    Steinhagen, C. A.; Stotler, C. L.; Neitzel, R. E.

    1974-01-01

    Composite component designs were developed for a number of applicable engine parts and functions. The cost and weight of each detail component was determined and its effect on the total engine cost to the aircraft manufacturer was ascertained. The economic benefits of engine or nacelle composite or eutectic turbine alloy substitutions was then calculated. Two time periods of engine certification were considered for this investigation, namely 1979 and 1985. Two methods of applying composites to these engines were employed. The first method just considered replacing an existing metal part with a composite part with no other change to the engine. The other method involved major engine redesign so that more efficient composite designs could be employed. Utilization of polymeric composites wherever payoffs were available indicated that a total improvement in Direct Operating Cost (DOC) of 2.82 to 4.64 percent, depending on the engine considered, could be attained. In addition, the percent fuel saving ranged from 1.91 to 3.53 percent. The advantages of using advanced materials in the turbine are more difficult to quantify but could go as high as an improvement in DOC of 2.33 percent and a fuel savings of 2.62 percent. Typically, based on a fleet of one hundred aircraft, a percent savings in DOC represents a savings of four million dollars per year and a percent of fuel savings equals 23,000 cu m (7,000,000 gallons) per year.

  20. Determination of the flight equipment maintenance costs of commuter airlines

    NASA Technical Reports Server (NTRS)

    1977-01-01

    Labor and materials costs associated with maintaining and operating 12 commuter airlines carrying an average of from 42 to 1,100 passengers daily in a variety of aircraft types were studied to determine the total direct maintenance cost per flight hour for the airframe, engine, and avionics and other instruments. The distribution of maintenance costs are analyzed for two carriers, one using turboprop aircraft and the other using piston engine aircraft.

  1. A Work-Based Research Assessment of the Impact of "Lean Manufacturing" on Health and Safety Education within an SME

    ERIC Educational Resources Information Center

    Nikolou-Walker, Elda; Lavery, Kathy

    2009-01-01

    Globalisation has had a major impact on the engineering industry as Pacific Rim countries undercut manufacturing costs and provide a more cost-effective location for many businesses. Engineering in Northern Ireland has mostly declined owing to increased competition from these countries. Engineering companies are now forced to streamline their…

  2. Structures, performance, benefit, cost study. [gas turbine engines

    NASA Technical Reports Server (NTRS)

    Feder, E.

    1981-01-01

    Aircraft engine structures were studied to identify the advanced structural technologies that would provide the most benefits to future aircraft operations. A series of studies identified engine systems with the greatest potential for improvements. Based on these studies, six advanced generic structural concepts were selected and conceptually designed. The benefits of each concept were quantitatively assessed in terms of thrust specific fuel consumption, weight, cost, maintenance cost, fuel burned and direct operating cost plus interest. The probability of success of each concept was also determined. The concepts were ranked and the three most promising were selected for further study which consisted of identifying and comprehensively outlining the advanced technologies required to develop these concepts for aircraft engine application. Analytic, fabrication, and test technology developments are required. The technology programs outlined emphasize the need to provide basic, fundamental understanding of technology to obtain the benefit goals.

  3. Engine-Out Capabilities Assessment of Heavy Lift Launch Vehicles

    NASA Technical Reports Server (NTRS)

    Holladay, Jon; Baggett, Keithe; Thrasher, Chad; Bellamy, K. Scott; Feldman, Stuart

    2012-01-01

    Engine-out (EO) is a condition that might occur during flight due to the failure of one or more engines. Protection against this occurrence can be called engine-out capability (EOC) whereupon significantly improved loss of mission may occur, in addition to reduction in performance and increased cost. A standardized engine-out capability has not been studied exhaustively as it pertains to space launch systems. This work presents results for a specific vehicle design with specific engines, but also uniquely provides an approach to realizing the necessity of EOC for any launch vehicle system design. A derived top-level approach to engine-out philosophy for a heavy lift launch vehicle is given herein, based on an historical assessment of launch vehicle capabilities. The methodology itself is not intended to present a best path forward, but instead provides three parameters for assessment of a particular vehicle. Of the several parameters affected by this EOC, the three parameters of interest in this research are reliability (Loss of Mission (LOM) and Loss of Crew (LOC)), vehicle performance, and cost. The intent of this effort is to provide insight into the impacts of EO capability on these parameters. The effects of EOC on reliability, performance and cost are detailed, including how these important launch vehicle metrics can be combined to assess what could be considered overall launch vehicle affordability. In support of achieving the first critical milestone (Mission Concept Review) in the development of the Space Launch System (SLS), a team assessed two-stage, large-diameter vehicles that utilized liquid oxygen (LOX)-RP propellants in the First Stage and LOX/LH2 propellant in the Upper Stage. With multiple large thrust-class engines employed on the stages, engine-out capability could be a significant driver to mission success. It was determined that LOM results improve by a factor of five when assuming EOC for both Core Stage (CS) (first stage) and Upper Stage (US) EO, assuming a reference launch vehicle with 5 RP engines on the CS and 3 LOX/LH2 engines on the US. The benefit of adding both CS and US engine-out capability is significant. When adding EOC for either first or second stages, there is less than a 20% benefit. Performance analysis has shown that if the vehicle is not protected for EO during the first part of the flight and only protected in the later part of the flight, there is a diminishing performance penalty, as indicated by failures occurring in the first stage at different times. This work did not consider any options to abort. While adding an engine for EOC drives cost upward, the impact depends on the number of needed engines manufactured per year and the launch manifest. There is a significant cost savings if multiple flights occur within one year. Flying two flights per year would cost approximately $4,000 per pound less than the same configuration with one flight per year, assuming both CS and US EOC. The cost is within 15% of the cost of one flight per year with no engine-out capability for the same vehicle. This study can be extended to other launch vehicles. While the numbers given in this paper are specific to a certain vehicle configuration, the process requires only a high level of data to allow an analyst to draw conclusions. The weighting of each of the identified parameters will determine the optimization of each launch vehicle. The results of this engine-out assessment provide a means to understand this optimization while maintaining an unbiased perspective.

  4. Life cycle cost assessment of future low heat rejection engines

    NASA Technical Reports Server (NTRS)

    Petersen, D. R.

    1986-01-01

    The Adiabatic Diesel Engine Component Development (ADECD) represents a project which has the objective to accelerate the development of highway truck engines with advanced technology aimed at reduced fuel consumption. The project comprises three steps, including the synthesis of a number of engine candidate designs, the coupling of each with a number of systems for utilizing exhaust gas energy, and the evaluation of each combination in terms of desirability. Particular attention is given to the employed evaluation method and the development of this method. The objective of Life Cycle Cost (LCC) evaluation in the ADECD program was to select the best from among 42 different low heat rejection engine (LHRE)/exhaust energy recovery system configurations. The LCC model is discussed along with a maintenance cost model, the evaluation strategy, the selection of parameter ranges, and a full factorial analysis.

  5. Design and optimization of smart grid system based on renewable energy in Nyamuk Island, Karimunjawa district, Central Java

    NASA Astrophysics Data System (ADS)

    Novitasari, D.; Indartono, Y. S.; Rachmidha, T. D.; Reksowardojo, I. K.; Irsyad, M.

    2017-03-01

    Nyamuk Island in Karimunjawa District is one of the regions in Java that has no access to electricity grid. The electricity in Nyamuk Island relies on diesel engine which is managed by local government and only operated for 6 hours per day. It occurs as a consequence of high fuel cost. A study on smart micro grid system based on renewable energy was conducted in Combustion Engine and Propulsion System Laboratory of Institut Teknologi Bandung by using 1 kWp solar panels and a 3 kW bio based diesel engine. The fuels used to run the bio based diesel engine were diesel, virgin coconut oil and pure palm oil. The results show that the smart grid system run well at varying load and also with different fuel. Based on the experiments, average inverter efficiency was about 87%. This experiments proved that the use of biofuels had no effects to the overall system performance. Based on the results of prototype experiments, this paper will focus on design and optimization of smart micro grid system using HOMER software for Nyamuk Island. The design consists of (1) a diesel engine existing in Nyamuk Island whose fuel was diesel, (2) a lister engine whose fuel was from vegetable oil from Callophyllum inophyllum, (3) solar panels, (4) batteries and (5) converter. In this simulation, the existing diesel engine was set to operate 2 hours per day, while operating time of the lister engine has been varied with several scenarios. In scenario I, the lister engine was operated 5 hours per day, in scenario II the lister engine was operated 24 hours per day and in scenario III the lister engine was operated 8 hours per week in the weekend. In addition, a design using a modified diesel engine was conducted as well with an assumption that the modified cost was about 10% of new diesel engine cost. By modifying the diesel engine, the system will not need a lister engine. Assessments has been done to evaluate the designs, and the result shows that the optimal value obtains by the lister engine being operated for 24 hours a day in which the capacity of each component was 27 kWp PV, 7 kW lister engine, 26 kVA existing diesel engine, 40 kW converter and 128 batteries. The result is based on the lowest value of Net Present Cost (NPC) of 542.682 and Cost Of Electricity (COE) of 0.49.

  6. Magnetohydrodynamics MHD Engineering Test Facility ETF 200 MWe power plant. Conceptual Design Engineering Report CDER. Volume 3: Costs and schedules

    NASA Astrophysics Data System (ADS)

    1981-09-01

    The estimated plant capital cost for a coal fired 200 MWE electric generating plant with open cycle magnetohydrodynamics is divided into principal accounts based on Federal Energy Regulatory Commision account structure. Each principal account is defined and its estimated cost subdivided into identifiable and major equipment systems. The cost data sources for compiling the estimates, cost parameters, allotments, assumptions, and contingencies, are discussed. Uncertainties associated with developing the costs are quantified to show the confidence level acquired. Guidelines established in preparing the estimated costs are included. Based on an overall milestone schedule related to conventional power plant scheduling experience and starting procurement of MHD components during the preliminary design phase there is a 6 1/2-year construction period. The duration of the project from start to commercial operation is 79 months. The engineering phase of the project is 4 1/2 years; the construction duration following the start of the man power block is 37 months.

  7. Magnetohydrodynamics MHD Engineering Test Facility ETF 200 MWe power plant. Conceptual Design Engineering Report CDER. Volume 3: Costs and schedules

    NASA Technical Reports Server (NTRS)

    1981-01-01

    The estimated plant capital cost for a coal fired 200 MWE electric generating plant with open cycle magnetohydrodynamics is divided into principal accounts based on Federal Energy Regulatory Commision account structure. Each principal account is defined and its estimated cost subdivided into identifiable and major equipment systems. The cost data sources for compiling the estimates, cost parameters, allotments, assumptions, and contingencies, are discussed. Uncertainties associated with developing the costs are quantified to show the confidence level acquired. Guidelines established in preparing the estimated costs are included. Based on an overall milestone schedule related to conventional power plant scheduling experience and starting procurement of MHD components during the preliminary design phase there is a 6 1/2-year construction period. The duration of the project from start to commercial operation is 79 months. The engineering phase of the project is 4 1/2 years; the construction duration following the start of the man power block is 37 months.

  8. Developing Information Storage and Retrieval Systems on the Internet: A Knowledge Management Approach

    DTIC Science & Technology

    2011-09-01

    search engines to find information. Most commercial search engines (Google, Yahoo, Bing, etc.) provide their indexing and search services...at no cost. The DoD can achieve large gains at a small cost by making public documents available to search engines . This can be achieved through the...were organized on the website dodreports.com. The results of this research revealed improvement gains of 8-20% for finding reports through commercial search engines during the first six months of

  9. 10 CFR 609.12 - Project Costs.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... incurred in the design, engineering, financing, construction, startup, commissioning and shakedown of the... rental of real property, including engineering fees, surveys, title insurance, recording fees, and legal... transportation for facility design, construction, startup, commissioning and shakedown; (3) Costs of equipment...

  10. 10 CFR 609.12 - Project Costs.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... incurred in the design, engineering, financing, construction, startup, commissioning and shakedown of the... rental of real property, including engineering fees, surveys, title insurance, recording fees, and legal... transportation for facility design, construction, startup, commissioning and shakedown; (3) Costs of equipment...

  11. 10 CFR 609.12 - Project Costs.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... incurred in the design, engineering, financing, construction, startup, commissioning and shakedown of the... rental of real property, including engineering fees, surveys, title insurance, recording fees, and legal... transportation for facility design, construction, startup, commissioning and shakedown; (3) Costs of equipment...

  12. 10 CFR 609.12 - Project Costs.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... incurred in the design, engineering, financing, construction, startup, commissioning and shakedown of the... rental of real property, including engineering fees, surveys, title insurance, recording fees, and legal... transportation for facility design, construction, startup, commissioning and shakedown; (3) Costs of equipment...

  13. 10 CFR 609.12 - Project Costs.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... incurred in the design, engineering, financing, construction, startup, commissioning and shakedown of the... rental of real property, including engineering fees, surveys, title insurance, recording fees, and legal... transportation for facility design, construction, startup, commissioning and shakedown; (3) Costs of equipment...

  14. Preliminary engineering analysis for clothes washers

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    Biermayer, Peter J.

    1996-10-01

    The Engineering Analysis provides information on efficiencies, manufacturer costs, and other characteristics of the appliance class being analyzed. For clothes washers, there are two classes: standard and compact. Since data were not available to analyze the compact class, only clothes washers were analyzed in this report. For this analysis, individual design options were combined and ordered in a manner that resulted in the lowest cumulative cost/savings ratio. The cost/savings ratio is the increase in manufacturer cost for a design option divided by the reduction in operating costs due to fuel and water savings.

  15. Lower operational costs in heat treatment and process engineering through improved temperature measurement

    NASA Astrophysics Data System (ADS)

    Furniss, C. P.

    New metal-sheathed thermocouple systems are described which have lowered operational heat treatment costs and process engineering. The improvements which these thermocouples represent over conventional ones with regard to chemical composition, thermomechanical properties, oxidation resistance, weldability, and coefficient of linear expansion are pointed out. Experimentally determined cost savings for a variety of applications are reported.

  16. Value Engineering. "A Working Tool for Cost Control in the Design of Educational Facilities."

    ERIC Educational Resources Information Center

    Lawrence, Jerry

    Value Engineering (VE) is a cost optimizing technique used to analyze design quality and cost-effectiveness. The application of VE procedures to the design and construction of school facilities has been adopted by the state of Washington. By using VE, the optimum value for every life cycle dollar spent on a facility is obtained by identifying not…

  17. Fuzzy/Neural Software Estimates Costs of Rocket-Engine Tests

    NASA Technical Reports Server (NTRS)

    Douglas, Freddie; Bourgeois, Edit Kaminsky

    2005-01-01

    The Highly Accurate Cost Estimating Model (HACEM) is a software system for estimating the costs of testing rocket engines and components at Stennis Space Center. HACEM is built on a foundation of adaptive-network-based fuzzy inference systems (ANFIS) a hybrid software concept that combines the adaptive capabilities of neural networks with the ease of development and additional benefits of fuzzy-logic-based systems. In ANFIS, fuzzy inference systems are trained by use of neural networks. HACEM includes selectable subsystems that utilize various numbers and types of inputs, various numbers of fuzzy membership functions, and various input-preprocessing techniques. The inputs to HACEM are parameters of specific tests or series of tests. These parameters include test type (component or engine test), number and duration of tests, and thrust level(s) (in the case of engine tests). The ANFIS in HACEM are trained by use of sets of these parameters, along with costs of past tests. Thereafter, the user feeds HACEM a simple input text file that contains the parameters of a planned test or series of tests, the user selects the desired HACEM subsystem, and the subsystem processes the parameters into an estimate of cost(s).

  18. Space shuttle main engine definition (phase B). Volume 2: Avionics. [for space shuttle

    NASA Technical Reports Server (NTRS)

    1971-01-01

    The advent of the space shuttle engine with its requirements for high specific impulse, long life, and low cost have dictated a combustion cycle and a closed loop control system to allow the engine components to run close to operating limits. These performance requirements, combined with the necessity for low operational costs, have placed new demands on rocket engine control, system checkout, and diagnosis technology. Based on considerations of precision environment, and compatibility with vehicle interface commands, an electronic control, makes available many functions that logically provide the information required for engine system checkout and diagnosis.

  19. Injector element characterization methodology

    NASA Technical Reports Server (NTRS)

    Cox, George B., Jr.

    1988-01-01

    Characterization of liquid rocket engine injector elements is an important part of the development process for rocket engine combustion devices. Modern nonintrusive instrumentation for flow velocity and spray droplet size measurement, and automated, computer-controlled test facilities allow rapid, low-cost evaluation of injector element performance and behavior. Application of these methods in rocket engine development, paralleling their use in gas turbine engine development, will reduce rocket engine development cost and risk. The Alternate Turbopump (ATP) Hot Gas Systems (HGS) preburner injector elements were characterized using such methods, and the methodology and some of the results obtained will be shown.

  20. Small, low-cost, expendable turbojet engine. 1: Design, fabrication, and preliminary testing

    NASA Technical Reports Server (NTRS)

    Dengler, R. P.; Macioce, L. E.

    1976-01-01

    A small experimental axial-flow turbojet engine in the 2,669-Newton (600-lbf) thrust class was designed, fabricated, and tested to demonstrate the feasibility of several low-cost concepts. Design simplicity was stressed in order to reduce the number of components and machining operations. Four engines were built and tested for a total of 157 hours. Engine testing was conducted at both sea-level static and simulated flight conditions for engine speeds as high as 38,000 rpm and turbine-inlet temperatures as high as 1,255 K (1,800 F).

  1. The Strutjet Rocket Based Combined Cycle Engine

    NASA Technical Reports Server (NTRS)

    Siebenhaar, A.; Bulman, M. J.; Bonnar, D. K.

    1998-01-01

    The multi stage chemical rocket has been established over many years as the propulsion System for space transportation vehicles, while, at the same time, there is increasing concern about its continued affordability and rather involved reusability. Two broad approaches to addressing this overall launch cost problem consist in one, the further development of the rocket motor, and two, the use of airbreathing propulsion to the maximum extent possible as a complement to the limited use of a conventional rocket. In both cases, a single-stage-to-orbit (SSTO) vehicle is considered a desirable goal. However, neither the "all-rocket" nor the "all-airbreathing" approach seems realizable and workable in practice without appreciable advances in materials and manufacturing. An affordable system must be reusable with minimal refurbishing on-ground, and large mean time between overhauls, and thus with high margins in design. It has been suggested that one may use different engine cycles, some rocket and others airbreathing, in a combination over a flight trajectory, but this approach does not lead to a converged solution with thrust-to-mass, specific impulse, and other performance and operational characteristics that can be obtained in the different engines. The reason is this type of engine is simply a combination of different engines with no commonality of gas flowpath or components, and therefore tends to have the deficiencies of each of the combined engines. A further development in this approach is a truly combined cycle that incorporates a series of cycles for different modes of propulsion along a flight path with multiple use of a set of components and an essentially single gas flowpath through the engine. This integrated approach is based on realizing the benefits of both a rocket engine and airbreathing engine in various combinations by a systematic functional integration of components in an engine class usually referred to as a rocket-based combined cycle (RBCC) engine. RBCC engines exhibit a high potential for lowering the operating cost of launching payloads into orbit. Two sources of cost reductions can be identified. First, RBCC powered vehicles require only 20% takeoff thrust compared to conventional rockets, thereby lowering the thrust requirements and the replacement cost of the engines. Second, due to the higher structural and thermal margins achievable with RBCC engines coupled with a higher degree of subsystem redundance lower maintenance and operating cost are obtainable.

  2. Defense Acquisitions: Addressing Incentives is Key to Further Reform Efforts

    DTIC Science & Technology

    2014-04-30

    championed sound management practices, such as realistic cost estimating, prototyping, and systems engineering . While some progress has been made...other reforms have championed sound management practices, such as realistic cost estimating, prototyping, and systems engineering . DOD’s declining...principles from disciplines such as systems engineering , as well as lessons learned and past reforms. The body of work we have done on benchmarking

  3. Affordability Engineering: Bridging the Gap Between Design and Cost

    NASA Technical Reports Server (NTRS)

    Reeves, J. D.; DePasquale, Dominic; Lim, Evan

    2010-01-01

    Affordability is a commonly used term that takes on numerous meanings depending on the context used. Within conceptual design of complex systems, the term generally implies comparisons between expected costs and expected resources. This characterization is largely correct, but does not convey the many nuances and considerations that are frequently misunderstood and underappreciated. In the most fundamental sense, affordability and cost directly relate to engineering and programmatic decisions made throughout development programs. Systems engineering texts point out that there is a temporal aspect to this relationship, for decisions made earlier in a program dictate design implications much more so than those made during latter phases. This paper explores affordability engineering and its many sub-disciplines by discussing how it can be considered an additional engineering discipline to be balanced throughout the systems engineering and systems analysis processes. Example methods of multidisciplinary design analysis with affordability as a key driver will be discussed, as will example methods of data visualization, probabilistic analysis, and other ways of relating design decisions to affordability results.

  4. Advanced Propulsion System Studies for General Aviation Aircraft

    NASA Technical Reports Server (NTRS)

    Eisenberg, Joseph D. (Technical Monitor); German, Jon

    2003-01-01

    This final report addresses the following topics: Market Impact Analysis (1) assessment of general aviation, including commuter/regional, aircraft market impact due to incorporation of advanced technology propulsion system on acquisition and operating costs, job creation and/or manpower demand, and future fleet size; (2) selecting an aircraft and engine for the study by focusing on the next generation 19-passenger commuter and the Williams International FJ44 turbofan engine growth. Propulsion System Analysis Conducted mission analysis studies and engine cycle analysis to define a new commuter mission and required engine performance, define acquisition and operating costs and, select engine configuration and initiated preliminary design for hardware modifications required. Propulsion System Benefits (1) assessed and defined engine emissions improvements, (2) assessed and defined noise reduction potential and, (3) conducted a cost analysis impact study. Review of Relevant NASA Programs Conducted literature searches using NERAC and NASA RECON services for related technology in the emissions and acoustics area. Preliminary Technology Development Plans Defined plan to incorporate technology improvements for an FJ44-2 growth engine in performance, emissions, and noise suppression.

  5. The Science of and Advanced Technology for Cost-Effective Manufacture of High Precision Engineering Products. Volume 5. Automatic Generation of Process Outlines of Forming and Machining Processes.

    DTIC Science & Technology

    1986-08-01

    THE SCIENCE OF AND ADVANCED TECHNOLOGY FOR COST-EFFECTIVE MANUFACTURE Lfl OF HIGH PRECISION ENGINEERING PRODUCTS N iA6/*N ONR Contract No. 83K0385...ADVANCED TECHNOLOGY FOR1 COST-EFFECTIVE MANUFACTURE OF1’ HIGH PRECISION ENGINEERING PRODUCTS ONR Contract No. 83K0385 Final Report Vol. 5 AUTOMATIC...Ck 53N Drawing #: 03116-6233 Raw Material: Iiz’ 500mm diameter and 3000mm length Ma, rial Alloy steel. high carbon content, quenched to Min 45Rc

  6. STOL propulsion systems

    NASA Technical Reports Server (NTRS)

    Denington, R. J.; Koenig, R. W.; Vanco, M. R.; Sagerser, D. A.

    1972-01-01

    The selection and the characteristics of quiet, clean propulsion systems for STOL aircraft are discussed. Engines are evaluated for augmentor wing and externally blown flap STOL aircraft with the engines located both under and over the wings. Some supporting test data are presented. Optimum engines are selected based on achieving the performance, economic, acoustic, and pollution goals presently being considered for future STOL aircraft. The data and results presented were obtained from a number of contracted studies and some supporting NASA inhouse programs, most of which began in early 1972. The contracts include: (1) two aircraft and mission studies, (2) two propulsion system studies, (3) the experimental and analytic work on the augmentor wing, and (4) the experimental programs on Q-Fan. Engines are selected and discussed based on aircraft economics using the direct operating cost as the primary criterion. This cost includes the cost of the crew, fuel, aircraft, and engine maintenance and depreciation.

  7. Numerical Propulsion System Simulation (NPSS): An Award Winning Propulsion System Simulation Tool

    NASA Technical Reports Server (NTRS)

    Stauber, Laurel J.; Naiman, Cynthia G.

    2002-01-01

    The Numerical Propulsion System Simulation (NPSS) is a full propulsion system simulation tool used by aerospace engineers to predict and analyze the aerothermodynamic behavior of commercial jet aircraft, military applications, and space transportation. The NPSS framework was developed to support aerospace, but other applications are already leveraging the initial capabilities, such as aviation safety, ground-based power, and alternative energy conversion devices such as fuel cells. By using the framework and developing the necessary components, future applications that NPSS could support include nuclear power, water treatment, biomedicine, chemical processing, and marine propulsion. NPSS will dramatically reduce the time, effort, and expense necessary to design and test jet engines. It accomplishes that by generating sophisticated computer simulations of an aerospace object or system, thus enabling engineers to "test" various design options without having to conduct costly, time-consuming real-life tests. The ultimate goal of NPSS is to create a numerical "test cell" that enables engineers to create complete engine simulations overnight on cost-effective computing platforms. Using NPSS, engine designers will be able to analyze different parts of the engine simultaneously, perform different types of analysis simultaneously (e.g., aerodynamic and structural), and perform analysis in a more efficient and less costly manner. NPSS will cut the development time of a new engine in half, from 10 years to 5 years. And NPSS will have a similar effect on the cost of development: new jet engines will cost about a billion dollars to develop rather than two billion. NPSS is also being applied to the development of space transportation technologies, and it is expected that similar efficiencies and cost savings will result. Advancements of NPSS in fiscal year 2001 included enhancing the NPSS Developer's Kit to easily integrate external components of varying fidelities, providing the initial Visual-Based Syntax (VBS) capability, and developing additional capabilities to support space transportation. NPSS was supported under NASA's High Performance Computing and Communications Program. Through the NASA/Industry Cooperative Effort agreement, NASA Glenn and its industry and Government partners are developing NPSS. The NPSS team consists of propulsion experts and software engineers from GE Aircraft Engines, Pratt & Whitney, The Boeing Company, Honeywell, Rolls-Royce Corporation, Williams International, Teledyne Continental Motors, Arnold Engineering Development Center, Wright Patterson Air Force Base, and the NASA Glenn Research Center. Glenn is leading the way in developing NPSS--a method for solving complex design problems that's faster, better, and cheaper.

  8. Additive Manufacturing for Affordable Rocket Engines

    NASA Technical Reports Server (NTRS)

    West, Brian; Robertson, Elizabeth; Osborne, Robin; Calvert, Marty

    2016-01-01

    Additive manufacturing (also known as 3D printing) technology has the potential to drastically reduce costs and lead times associated with the development of complex liquid rocket engine systems. NASA is using 3D printing to manufacture rocket engine components including augmented spark igniters, injectors, turbopumps, and valves. NASA is advancing the process to certify these components for flight. Success Story: MSFC has been developing rocket 3D-printing technology using the Selective Laser Melting (SLM) process. Over the last several years, NASA has built and tested several injectors and combustion chambers. Recently, MSFC has 3D printed an augmented spark igniter for potential use the RS-25 engines that will be used on the Space Launch System. The new design is expected to reduce the cost of the igniter by a factor of four. MSFC has also 3D printed and tested a liquid hydrogen turbopump for potential use on an Upper Stage Engine. Additive manufacturing of the turbopump resulted in a 45% part count reduction. To understanding how the 3D printed parts perform and to certify them for flight, MSFC built a breadboard liquid rocket engine using additive manufactured components including injectors, turbomachinery, and valves. The liquid rocket engine was tested seven times in 2016 using liquid oxygen and liquid hydrogen. In addition to exposing the hardware to harsh environments, engineers learned to design for the new manufacturing technique, taking advantage of its capabilities and gaining awareness of its limitations. Benefit: The 3D-printing technology promises reduced cost and schedule for rocket engines. Cost is a function of complexity, and the most complicated features provide the largest opportunities for cost reductions. This is especially true where brazes or welds can be eliminated. The drastic reduction in part count achievable with 3D printing creates a waterfall effect that reduces the number of processes and drawings, decreases the amount of touch labor required, and increases reliability. When certification is achieved, NASA missions will be able to realize these benefits.

  9. Army Corps of Engineers: Water Resource Authorizations, Appropriations, and Activities

    DTIC Science & Technology

    2016-02-09

    favorable benefit -cost ratio. 31 Local sponsors assume any rehabilitation cost for damage to an active project attributable to deficient maintenance...infrastructure activities are not traditional Corps water resources projects, they are not subject to the Corps planning process (e.g., a benefit -cost...Army Corps of Engineers: Water Resource Authorizations, Appropriations, and Activities Nicole T. Carter Specialist in Natural Resources Policy

  10. Implementation of activity-based costing (ABC) to drive cost reduction efforts in a semiconductor manufacturing operation

    NASA Astrophysics Data System (ADS)

    Naguib, Hussein; Bol, Igor I.; Lora, J.; Chowdhry, R.

    1994-09-01

    This paper presents a case study on the implementation of ABC to calculate the cost per wafer and to drive cost reduction efforts for a new IC product line. The cost reduction activities were conducted through the efforts of 11 cross-functional teams which included members of the finance, purchasing, technology development, process engineering, equipment engineering, production control, and facility groups. The activities of these cross functional teams were coordinated by a cost council. It will be shown that these activities have resulted in a 57% reduction in the wafer manufacturing cost of the new product line. Factors contributed to successful implementation of an ABC management system are discussed.

  11. Value engineering and cost effectiveness of various fiber reinforced polymer (FRP) repair systems.

    DOT National Transportation Integrated Search

    2006-06-01

    Seventeen 40 year old C-Channel type prestressed concrete bridge girders and one impact damaged AASHTO : Type II prestressed concrete girder were tested under static and fatigue loading to determine the cost-effectiveness : and value engineering aspe...

  12. Space Nuclear Reactor Engineering

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    Poston, David Irvin

    We needed to find a space reactor concept that could be attractive to NASA for flight and proven with a rapid turnaround, low-cost nuclear test. Heat-pipe-cooled reactors coupled to Stirling engines long identified as the easiest path to near-term, low-cost concept.

  13. Defense Acquisitions: Where Should Reform Aim Next?

    DTIC Science & Technology

    2013-10-29

    realistic cost estimating, prototyping, and systems engineering . Too often, GAO reports on the same kinds of problems today that it did over 20... engineering . DOD’s declining budgets and the impact of sequestration have lent additional impetus to reduce the costs of weapons. While some progress has been...3 The sequence of events that comprise the process defined in policy reflects principles from disciplines such as systems engineering , as well as

  14. Low-Cost, Net-Shape Ceramic Radial Turbine Program

    DTIC Science & Technology

    1985-05-01

    PROGRAM ELEMENT. PROJECT. TASK Garrett Turbine Engine Company AE OKUI UBR 111 South 34th Street, P.O. Box 2517 Phoenix, Arizona 85010 %I. CONTROLLING...processing iterations. Program management and materials characterization were conducted at Garrett Turbine Engine Company (GTEC), test bar and rotor...automotive gas turbine engine rotor development efforts at ACC. xvii PREFACE This is the final technical report of the Low-Cost, Net- Shape Ceramic

  15. Software for Estimating Costs of Testing Rocket Engines

    NASA Technical Reports Server (NTRS)

    Hines, Merlon M.

    2004-01-01

    A high-level parametric mathematical model for estimating the costs of testing rocket engines and components at Stennis Space Center has been implemented as a Microsoft Excel program that generates multiple spreadsheets. The model and the program are both denoted, simply, the Cost Estimating Model (CEM). The inputs to the CEM are the parameters that describe particular tests, including test types (component or engine test), numbers and duration of tests, thrust levels, and other parameters. The CEM estimates anticipated total project costs for a specific test. Estimates are broken down into testing categories based on a work-breakdown structure and a cost-element structure. A notable historical assumption incorporated into the CEM is that total labor times depend mainly on thrust levels. As a result of a recent modification of the CEM to increase the accuracy of predicted labor times, the dependence of labor time on thrust level is now embodied in third- and fourth-order polynomials.

  16. Software for Estimating Costs of Testing Rocket Engines

    NASA Technical Reports Server (NTRS)

    Hines, Merion M.

    2002-01-01

    A high-level parametric mathematical model for estimating the costs of testing rocket engines and components at Stennis Space Center has been implemented as a Microsoft Excel program that generates multiple spreadsheets. The model and the program are both denoted, simply, the Cost Estimating Model (CEM). The inputs to the CEM are the parameters that describe particular tests, including test types (component or engine test), numbers and duration of tests, thrust levels, and other parameters. The CEM estimates anticipated total project costs for a specific test. Estimates are broken down into testing categories based on a work-breakdown structure and a cost-element structure. A notable historical assumption incorporated into the CEM is that total labor times depend mainly on thrust levels. As a result of a recent modification of the CEM to increase the accuracy of predicted labor times, the dependence of labor time on thrust level is now embodied in third- and fourth-order polynomials.

  17. Software for Estimating Costs of Testing Rocket Engines

    NASA Technical Reports Server (NTRS)

    Hines, Merlon M.

    2003-01-01

    A high-level parametric mathematical model for estimating the costs of testing rocket engines and components at Stennis Space Center has been implemented as a Microsoft Excel program that generates multiple spreadsheets. The model and the program are both denoted, simply, the Cost Estimating Model (CEM). The inputs to the CEM are the parameters that describe particular tests, including test types (component or engine test), numbers and duration of tests, thrust levels, and other parameters. The CEM estimates anticipated total project costs for a specific test. Estimates are broken down into testing categories based on a work-breakdown structure and a cost-element structure. A notable historical assumption incorporated into the CEM is that total labor times depend mainly on thrust levels. As a result of a recent modification of the CEM to increase the accuracy of predicted labor times, the dependence of labor time on thrust level is now embodied in third- and fourth-order polynomials.

  18. An Industrial Engineering Approach to Cost Containment of Pharmacy Education.

    PubMed

    Duncan, Wendy; Bottenberg, Michelle; Chase, Marilea; Chesnut, Renae; Clarke, Cheryl; Schott, Kathryn; Torry, Ronald; Welty, Tim

    2015-11-25

    A 2-semester project explored employing teams of fourth-year industrial engineering students to optimize some of our academic management processes. Results included significant cost savings and increases in efficiency, effectiveness, and student and faculty satisfaction. While we did not adopt all of the students' recommendations, we did learn some important lessons. For example, an initial investment of time in developing a mutually clear understanding of the problems, constraints, and goals maximizes the value of industrial engineering analysis and recommendations. Overall, industrial engineering was a valuable tool for optimizing certain academic management processes.

  19. Inspection planning development: An evolutionary approach using reliability engineering as a tool

    NASA Technical Reports Server (NTRS)

    Graf, David A.; Huang, Zhaofeng

    1994-01-01

    This paper proposes an evolutionary approach for inspection planning which introduces various reliability engineering tools into the process and assess system trade-offs among reliability, engineering requirement, manufacturing capability and inspection cost to establish an optimal inspection plan. The examples presented in the paper illustrate some advantages and benefits of the new approach. Through the analysis, reliability and engineering impacts due to manufacturing process capability and inspection uncertainty are clearly understood; the most cost effective and efficient inspection plan can be established and associated risks are well controlled; some inspection reductions and relaxations are well justified; and design feedbacks and changes may be initiated from the analysis conclusion to further enhance reliability and reduce cost. The approach is particularly promising as global competitions and customer quality improvement expectations are rapidly increasing.

  20. Lightweight diesel aircraft engines for general aviation

    NASA Technical Reports Server (NTRS)

    Berenyi, S. G.; Brouwers, A. P.

    1980-01-01

    A methodical design study was conducted to arrive at new diesel engine configurations and applicable advanced technologies. Two engines are discussed and the description of each engine includes concept drawings. A performance analysis, stress and weight prediction, and a cost study were also conducted. This information was then applied to two airplane concepts, a six-place twin and a four-place single engine aircraft. The aircraft study consisted of installation drawings, computer generated performance data, aircraft operating costs and drawings of the resulting airplanes. The performance data shows a vast improvement over current gasoline-powered aircraft. At the completion of this basic study, the program was expanded to evaluate a third engine configuration. This third engine incorporates the best features of the original two, and its design is currently in progress. Preliminary information on this engine is presented.

  1. Study of solid rocket motors for a space shuttle booster. Volume 2, book 3, addendum 1: Cost estimating data

    NASA Technical Reports Server (NTRS)

    Vonderesch, A. H.

    1972-01-01

    A second iteration of the program baseline configuration and cost for the solid propellant rocket engines used with the space shuttle booster system is presented. The purpose of the study was to ensure that total program costs were complete and to review areas where costs might be overly conservative and could be reduced. Labor and material were analyzed in more depth, more definition was prepared to separate recurring from nonrecurring costs, and the operations portions of the engine and stage were separated into more identifiable activities.

  2. Extracting Work from Quantum Measurement in Maxwell's Demon Engines

    NASA Astrophysics Data System (ADS)

    Elouard, Cyril; Herrera-Martí, David; Huard, Benjamin; Auffèves, Alexia

    2017-06-01

    The essence of both classical and quantum engines is to extract useful energy (work) from stochastic energy sources, e.g., thermal baths. In Maxwell's demon engines, work extraction is assisted by a feedback control based on measurements performed by a demon, whose memory is erased at some nonzero energy cost. Here we propose a new type of quantum Maxwell's demon engine where work is directly extracted from the measurement channel, such that no heat bath is required. We show that in the Zeno regime of frequent measurements, memory erasure costs eventually vanish. Our findings provide a new paradigm to analyze quantum heat engines and work extraction in the quantum world.

  3. The influence of engine technology advancements on aircraft economics

    NASA Technical Reports Server (NTRS)

    Witherspoon, J. W.; Gaffin, W. O.

    1973-01-01

    A technology advancement in a new powerplant has both favorable and unfavorable effects. Increased bypass ratio and compression ratio, coupled with high turbine temperatures, improve performance but also increase engine price and maintenance cost. The factors that should be evaluated in choosing an engine for airline use are discussed. These factors are compared for two engines that might be considered for future 150 to 200 passenger airplanes: an all-new turbofan and a quiet derivative of an existing first generation turbofan. The results of the performance and cost evaluations of the example engines are reduced to common units so they can be combined.

  4. Contingency Power Study for Short Haul Civil Tiltrotor

    NASA Technical Reports Server (NTRS)

    Eisenberg, Joseph D. (Technical Monitor); Wait, John

    2003-01-01

    AlliedSignal Engines (AE) defined a number of concepts that significantly increased the horsepower of a turboshaft engine to accommodate the loss of an engine and enable the safe landing of a twin-engined, 40-passenger, short haul civil tiltrotor. From these concepts, "Water/Methanol Injection," a "Better Power Turbine Than Required," and a "Secondary Combustor For Interturbine Reheat" were chosen, based on system safety and economics, for more detailed examination. Engine performance, mission, and cost analysis of these systems indicated contingency power levels of 26 to 70 percent greater than normal rated takeoff could be attained for short durations, thus enabling direct operating cost savings between 2 and 6 percent.

  5. High Level Rule Modeling Language for Airline Crew Pairing

    NASA Astrophysics Data System (ADS)

    Mutlu, Erdal; Birbil, Ş. Ilker; Bülbül, Kerem; Yenigün, Hüsnü

    2011-09-01

    The crew pairing problem is an airline optimization problem where a set of least costly pairings (consecutive flights to be flown by a single crew) that covers every flight in a given flight network is sought. A pairing is defined by using a very complex set of feasibility rules imposed by international and national regulatory agencies, and also by the airline itself. The cost of a pairing is also defined by using complicated rules. When an optimization engine generates a sequence of flights from a given flight network, it has to check all these feasibility rules to ensure whether the sequence forms a valid pairing. Likewise, the engine needs to calculate the cost of the pairing by using certain rules. However, the rules used for checking the feasibility and calculating the costs are usually not static. Furthermore, the airline companies carry out what-if-type analyses through testing several alternate scenarios in each planning period. Therefore, embedding the implementation of feasibility checking and cost calculation rules into the source code of the optimization engine is not a practical approach. In this work, a high level language called ARUS is introduced for describing the feasibility and cost calculation rules. A compiler for ARUS is also implemented in this work to generate a dynamic link library to be used by crew pairing optimization engines.

  6. Can IR scene projectors reduce total system cost?

    NASA Astrophysics Data System (ADS)

    Ginn, Robert; Solomon, Steven

    2006-05-01

    There is an incredible amount of system engineering involved in turning the typical infrared system needs of probability of detection, probability of identification, and probability of false alarm into focal plane array (FPA) requirements of noise equivalent irradiance (NEI), modulation transfer function (MTF), fixed pattern noise (FPN), and defective pixels. Unfortunately, there are no analytic solutions to this problem so many approximations and plenty of "seat of the pants" engineering is employed. This leads to conservative specifications, which needlessly drive up system costs by increasing system engineering costs, reducing FPA yields, increasing test costs, increasing rework and the never ending renegotiation of requirements in an effort to rein in costs. These issues do not include the added complexity to the FPA factory manager of trying to meet varied, and changing, requirements for similar products because different customers have made different approximations and flown down different specifications. Scene generation technology may well be mature and cost effective enough to generate considerable overall savings for FPA based systems. We will compare the costs and capabilities of various existing scene generation systems and estimate the potential savings if implemented at several locations in the IR system fabrication cycle. The costs of implementing this new testing methodology will be compared to the probable savings in systems engineering, test, rework, yield improvement and others. The diverse requirements and techniques required for testing missile warning systems, missile seekers, and FLIRs will be defined. Last, we will discuss both the hardware and software requirements necessary to meet the new test paradigm and discuss additional cost improvements related to the incorporation of these technologies.

  7. Computerized systems analysis and optimization of aircraft engine performance, weight, and life cycle costs

    NASA Technical Reports Server (NTRS)

    Fishbach, L. H.

    1980-01-01

    The computational techniques are described which are utilized at Lewis Research Center to determine the optimum propulsion systems for future aircraft applications and to identify system tradeoffs and technology requirements. Cycle performance, and engine weight can be calculated along with costs and installation effects as opposed to fuel consumption alone. Almost any conceivable turbine engine cycle can be studied. These computer codes are: NNEP, WATE, LIFCYC, INSTAL, and POD DRG. Examples are given to illustrate how these computer techniques can be applied to analyze and optimize propulsion system fuel consumption, weight and cost for representative types of aircraft and missions.

  8. Cost effective launch operations of the SSME

    NASA Technical Reports Server (NTRS)

    Klatt, F. P.

    1985-01-01

    The Space Shuttle Main Engine (SSME) represents the beginning of reusable rocket engine operations in the space transportation system (STS). Steps taken to reduce the overall cost of flight operations of the SSME by improving turnaround operations, extending the life of the engine, and improving the cost effectiveness of overhaul operations at the Canoga Park home plant are described. Ground certification testing to ensure safe launch operations is described, as well as certification extension testing that leads to a service life equivalent to 40 flights. The proven flight record of the SSME, which has demonstrated the utility of the SSME as a key component of America's space transportation system, is discussed.

  9. Lean Stability augmentation study

    NASA Technical Reports Server (NTRS)

    Mcvey, J. B.; Kennedy, J. B.

    1979-01-01

    An analytical and experimental program was conducted to investigate techniques and develop technology for improving the lean combustion limits of premixing, prevaporizing combustors applicable to gas turbine engine main burners. Three concepts for improving lean stability limits were selected for experimental evaluation among twelve approaches considered. Concepts were selected on the basis of the potential for improving stability limits and achieving emission goals, the technological risks associated with development of practical burners employing the concepts, and the penalties to airline direct operating costs resulting from decreased combustor performance, increased engine cost, increased maintenance cost and increased engine weight associated with implementation of the concepts. Tests of flameholders embodying the selected concepts were conducted.

  10. Study of small turbofan engines applicable to general-aviation aircraft

    NASA Technical Reports Server (NTRS)

    Merrill, G. L.; Burnett, G. A.; Alsworth, C. C.

    1973-01-01

    The applicability of small turbofan engines to general aviation aircraft is discussed. The engine and engine/airplane performance, weight, size, and cost interrelationships are examined. The effects of specific engine noise constraints are evaluated. The factors inhibiting the use of turbofan engines in general aviation aircraft are identified.

  11. A Case Study of a College-Wide First-Year Undergraduate Engineering Course

    ERIC Educational Resources Information Center

    Aloul, Fadi; Zualkernan, Imran; Husseini, Ghaleb; El-Hag, Ayman; Al-Assaf, Yousef

    2015-01-01

    Introductory engineering courses are either programme specific or expose students to engineering as a broad discipline by including materials from various engineering programmes. A common introductory engineering course that spans different engineering programmes raises challenges, including the high cost of resources as well as the lack of…

  12. 23 CFR 1.11 - Engineering services.

    Code of Federal Regulations, 2013 CFR

    2013-04-01

    ... 23 Highways 1 2013-04-01 2013-04-01 false Engineering services. 1.11 Section 1.11 Highways FEDERAL... Engineering services. (a) Federal participation. Costs of engineering services performed by the State highway... to specific projects. (b) Governmental engineering organizations. The State highway department may...

  13. 23 CFR 1.11 - Engineering services.

    Code of Federal Regulations, 2011 CFR

    2011-04-01

    ... 23 Highways 1 2011-04-01 2011-04-01 false Engineering services. 1.11 Section 1.11 Highways FEDERAL... Engineering services. (a) Federal participation. Costs of engineering services performed by the State highway... to specific projects. (b) Governmental engineering organizations. The State highway department may...

  14. 23 CFR 1.11 - Engineering services.

    Code of Federal Regulations, 2014 CFR

    2014-04-01

    ... 23 Highways 1 2014-04-01 2014-04-01 false Engineering services. 1.11 Section 1.11 Highways FEDERAL... Engineering services. (a) Federal participation. Costs of engineering services performed by the State highway... to specific projects. (b) Governmental engineering organizations. The State highway department may...

  15. 23 CFR 1.11 - Engineering services.

    Code of Federal Regulations, 2010 CFR

    2010-04-01

    ... 23 Highways 1 2010-04-01 2010-04-01 false Engineering services. 1.11 Section 1.11 Highways FEDERAL... Engineering services. (a) Federal participation. Costs of engineering services performed by the State highway... to specific projects. (b) Governmental engineering organizations. The State highway department may...

  16. 23 CFR 1.11 - Engineering services.

    Code of Federal Regulations, 2012 CFR

    2012-04-01

    ... 23 Highways 1 2012-04-01 2012-04-01 false Engineering services. 1.11 Section 1.11 Highways FEDERAL... Engineering services. (a) Federal participation. Costs of engineering services performed by the State highway... to specific projects. (b) Governmental engineering organizations. The State highway department may...

  17. 23 CFR 646.218 - Simplified procedure for accelerating grade crossing improvements.

    Code of Federal Regulations, 2014 CFR

    2014-04-01

    ... preliminary engineering costs may include those incurred in selecting crossings to be improved, determining the type of improvement for each crossing, estimating the cost and preparing the required agreement... ENGINEERING AND TRAFFIC OPERATIONS RAILROADS Railroad-Highway Projects § 646.218 Simplified procedure for...

  18. 23 CFR 646.218 - Simplified procedure for accelerating grade crossing improvements.

    Code of Federal Regulations, 2013 CFR

    2013-04-01

    ... preliminary engineering costs may include those incurred in selecting crossings to be improved, determining the type of improvement for each crossing, estimating the cost and preparing the required agreement... ENGINEERING AND TRAFFIC OPERATIONS RAILROADS Railroad-Highway Projects § 646.218 Simplified procedure for...

  19. 23 CFR 646.218 - Simplified procedure for accelerating grade crossing improvements.

    Code of Federal Regulations, 2011 CFR

    2011-04-01

    ... preliminary engineering costs may include those incurred in selecting crossings to be improved, determining the type of improvement for each crossing, estimating the cost and preparing the required agreement... ENGINEERING AND TRAFFIC OPERATIONS RAILROADS Railroad-Highway Projects § 646.218 Simplified procedure for...

  20. 23 CFR 646.218 - Simplified procedure for accelerating grade crossing improvements.

    Code of Federal Regulations, 2010 CFR

    2010-04-01

    ... preliminary engineering costs may include those incurred in selecting crossings to be improved, determining the type of improvement for each crossing, estimating the cost and preparing the required agreement... ENGINEERING AND TRAFFIC OPERATIONS RAILROADS Railroad-Highway Projects § 646.218 Simplified procedure for...

  1. 33 CFR 276.6 - General policy.

    Code of Federal Regulations, 2011 CFR

    2011-07-01

    ... specifications for the work they propose to undertake. However, those non-Federal engineering costs and overhead... commenced after certification shall be eligible for certification except for local engineering work noted...; certification of the proposal will be in the general public interest. (d) Costs assigned to that part of the...

  2. 23 CFR 646.218 - Simplified procedure for accelerating grade crossing improvements.

    Code of Federal Regulations, 2012 CFR

    2012-04-01

    ... preliminary engineering costs may include those incurred in selecting crossings to be improved, determining the type of improvement for each crossing, estimating the cost and preparing the required agreement... ENGINEERING AND TRAFFIC OPERATIONS RAILROADS Railroad-Highway Projects § 646.218 Simplified procedure for...

  3. The cost of biomedical equipment repair and maintenance: results of a survey.

    PubMed

    Cohen, T

    1982-01-01

    The survey presented in this paper shows that for 19 large hospitals the average ratio of equipment repair costs to acquisition cost was 7.4%. In addition, this survey shows that costs such as rent for building space, utilities, and test equipment are not included in many clinical engineering department budgets. This is one reason for the divergent cost data reported by the various hospitals. These costs should be considered particularly for comparisons between in-house service costs and other sources of service. It seems that, of the indicators observed in this survey, equipment acquisition cost provides the best indicator for equipment maintenance costs. All hospital finance officers should have acquisition value information, because this information is used in calculating capital equipment depreciation. This information should also be available to clinical engineers. In addition, procedures need to be set up so that the total annual repair and maintenance costs can be easily obtained from hospital finance departments. Providing the clinical engineer with this type of data will allow further analysis of repair cost and will aid in long-term planning for the hospital. The ratio of equipment repair cost to acquisition value may be useful as a tool to predict future costs of a given hospital's medical equipment maintenance. This tool may also be useful as a measurement of the effectiveness of a change in a hospital's approach to biomedical equipment maintenance. Further work must be done to standardize equipment maintenance cost reporting so that more detailed comparisons can be made.

  4. 47 CFR 24.243 - The cost-sharing formula.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ...; monitoring or control equipment; engineering costs (design/path survey); installation; systems testing; FCC filing costs; site acquisition and civil works; zoning costs; training; disposal of old equipment; test...

  5. The Faster, Better, Cheaper Approach to Space Missions: An Engineering Management Assessment

    NASA Technical Reports Server (NTRS)

    Hamaker, Joe

    2000-01-01

    This paper describes, in viewgraph form, the faster, better, cheaper approach to space missions. The topics include: 1) What drives "Faster, Better, Cheaper"? 2) Why Space Programs are Costly; 3) Background; 4) Aerospace Project Management (Old Culture); 5) Aerospace Project Management (New Culture); 6) Scope of Analysis Limited to Engineering Management Culture; 7) Qualitative Analysis; 8) Some Basic Principles of the New Culture; 9) Cause and Effect; 10) "New Ways of Doing Business" Survey Results; 11) Quantitative Analysis; 12) Recent Space System Cost Trends; 13) Spacecraft Dry Weight Trend; 14) Complexity Factor Trends; 15) Cost Normalization; 16) Cost Normalization Algorithm; 17) Unnormalized Cost vs. Normalized Cost; and 18) Concluding Observations.

  6. [Hospital clinical engineer orientation and function in the maintenance system of hospital medical equipment].

    PubMed

    Li, Bin; Zheng, Yunxin; He, Dehua; Jiang, Ruiyao; Chen, Ying; Jing, Wei

    2012-03-01

    The quantity of medical equipment in hospital rise quickly recent year. It provides the comprehensive support to the clinical service. The maintenance of medical equipment becomes more important than before. It is necessary to study on the orientation and function of clinical engineer in medical equipment maintenance system. Refer to three grade health care system, the community doctors which is called General practitioner, play an important role as the gatekeeper of health care system to triage and cost control. The paper suggests that hospital clinical engineer should play similar role as the gatekeeper of medical equipment maintenance system which composed by hospital clinical engineer, manufacture engineer and third party engineer. The hospital clinical engineer should be responsible of guard a pass of medical equipment maintenance quality and cost control. As the gatekeeper, hospital clinical engineer should take the responsibility of "General engineer" and pay more attention to safety and health of medical equipment. The responsibility description and future transition? development of clinical engineer as "General Engineer" is discussed. More attention should be recommended to the team building of hospital clinical engineer as "General Engineer".

  7. Fastrac Nozzle Design, Performance and Development

    NASA Technical Reports Server (NTRS)

    Peters, Warren; Rogers, Pat; Lawrence, Tim; Davis, Darrell; DAgostino, Mark; Brown, Andy

    2000-01-01

    With the goal of lowering the cost of payload to orbit, NASA/MSFC (Marshall Space Flight Center) researched ways to decrease the complexity and cost of an engine system and its components for a small two-stage booster vehicle. The composite nozzle for this Fastrac Engine was designed, built and tested by MSFC with fabrication support and engineering from Thiokol-SEHO (Science and Engineering Huntsville Operation). The Fastrac nozzle uses materials, fabrication processes and design features that are inexpensive, simple and easily manufactured. As the low cost nozzle (and injector) design matured through the subscale tests and into full scale hot fire testing, X-34 chose the Fastrac engine for the propulsion plant for the X-34. Modifications were made to nozzle design in order to meet the new flight requirements. The nozzle design has evolved through subscale testing and manufacturing demonstrations to full CFD (Computational Fluid Dynamics), thermal, thermomechanical and dynamic analysis and the required component and engine system tests to validate the design. The Fastrac nozzle is now in final development hot fire testing and has successfully accumulated 66 hot fire tests and 1804 seconds on 18 different nozzles.

  8. Definition, technology readiness, and development cost of the orbit transfer vehicle engine integrated control and health monitoring system elements

    NASA Technical Reports Server (NTRS)

    Cannon, I.; Balcer, S.; Cochran, M.; Klop, J.; Peterson, S.

    1991-01-01

    An Integrated Control and Health Monitoring (ICHM) system was conceived for use on a 20 Klb thrust baseline Orbit Transfer Vehicle (OTV) engine. Considered for space used, the ICHM was defined for reusability requirements for an OTV engine service free life of 20 missions, with 100 starts and a total engine operational time of 4 hours. Functions were derived by flowing down requirements from NASA guidelines, previous OTV engine or ICHM documents, and related contracts. The elements of an ICHM were identified and listed, and these elements were described in sufficient detail to allow estimation of their technology readiness levels. These elements were assessed in terms of technology readiness level, and supporting rationale for these assessments presented. The remaining cost for development of a minimal ICHM system to technology readiness level 6 was estimated. The estimates are within an accuracy range of minus/plus 20 percent. The cost estimates cover what is needed to prepare an ICHM system for use on a focussed testbed for an expander cycle engine, excluding support to the actual test firings.

  9. Evolving technologies drive the new roles of Biomedical Engineering.

    PubMed

    Frisch, P H; St Germain, J; Lui, W

    2008-01-01

    Rapidly changing technology coupled with the financial impact of organized health care, has required hospital Biomedical Engineering organizations to augment their traditional operational and business models to increase their role in developing enhanced clinical applications utilizing new and evolving technologies. The deployment of these technology based applications has required Biomedical Engineering organizations to re-organize to optimize the manner in which they provide and manage services. Memorial Sloan-Kettering Cancer Center has implemented a strategy to explore evolving technologies integrating them into enhanced clinical applications while optimally utilizing the expertise of the traditional Biomedical Engineering component (Clinical Engineering) to provide expanded support in technology / equipment management, device repair, preventive maintenance and integration with legacy clinical systems. Specifically, Biomedical Engineering is an integral component of the Medical Physics Department which provides comprehensive and integrated support to the Center in advanced physical, technical and engineering technology. This organizational structure emphasizes the integration and collaboration between a spectrum of technical expertise for clinical support and equipment management roles. The high cost of clinical equipment purchases coupled with the increasing cost of service has driven equipment management responsibilities to include significant business and financial aspects to provide a cost effective service model. This case study details the dynamics of these expanded roles, future initiatives and benefits for Biomedical Engineering and Memorial Sloan Kettering Cancer Center.

  10. Energy efficient engine: Flight propulsion system preliminary analysis and design

    NASA Technical Reports Server (NTRS)

    Johnston, R. P.; Beitler, R. S.; Bobinger, R. O.; Broman, C. L.; Gravitt, R. D.; Heineke, H.; Holloway, P. R.; Klem, J. S.; Nash, D. O.; Ortiz, P.

    1980-01-01

    The characteristics of an advanced flight propulsion system (FPS), suitable for introduction in the late 1980's to early 1990's, was more fully defined. It was determined that all goals for efficiency, environmental considerations, and economics could be met or exceeded with the possible exception of NOx emission. In evaluating the FPS, all aspects were considered including component design, performance, weight, initial cost, maintenance cost, engine system integration (including nacelle), and aircraft integration considerations. The current FPS installed specific fuel consumption was reduced 14.2% from that of the CF6-50C reference engine. When integrated into an advanced, subsonic, study transport, the FPS produced a fuel burn savings of 15 to 23% and a direct operating cost reduction of 5 to 12% depending on the mission and study aircraft characteristics relative to the reference engine.

  11. Value engineering and cost effectiveness of various fiber reinforced polymer (FRP) repair systems : final report, June 2007.

    DOT National Transportation Integrated Search

    2007-06-01

    This report is an extension to the final report for NCDOT project 2004-15 Value Engineering and Cost-Effectiveness of : Various Fiber Reinforced Polymers (FRP) Repair Systems, submitted in June 2005. In that report, seventeen 30-ft long : prest...

  12. 7 CFR 1753.81 - Inspection and certification.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... using RUS Form 245, Engineering Service Contract—Special Services. Costs for these services may be... and certified to be in compliance with RUS construction standards, to be reasonable in cost, and to... the requirements of the “employee in charge” of force account engineering as described in subpart B of...

  13. 48 CFR 48.105 - Relationship to other incentives.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... should not be rewarded both as value engineering shares and under performance, design-to-cost, or similar incentives of the contract. To that end, when performance, design-to-cost, or similar targets are set and... CONTRACT MANAGEMENT VALUE ENGINEERING Policies and Procedures 48.105 Relationship to other incentives...

  14. 48 CFR 48.105 - Relationship to other incentives.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... should not be rewarded both as value engineering shares and under performance, design-to-cost, or similar incentives of the contract. To that end, when performance, design-to-cost, or similar targets are set and... CONTRACT MANAGEMENT VALUE ENGINEERING Policies and Procedures 48.105 Relationship to other incentives...

  15. 7 CFR 1753.81 - Inspection and certification.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... using RUS Form 245, Engineering Service Contract—Special Services. Costs for these services may be... and certified to be in compliance with RUS construction standards, to be reasonable in cost, and to... the requirements of the “employee in charge” of force account engineering as described in subpart B of...

  16. 48 CFR 48.105 - Relationship to other incentives.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... should not be rewarded both as value engineering shares and under performance, design-to-cost, or similar incentives of the contract. To that end, when performance, design-to-cost, or similar targets are set and... CONTRACT MANAGEMENT VALUE ENGINEERING Policies and Procedures 48.105 Relationship to other incentives...

  17. Which Refrigeration System is Best for Your School?

    ERIC Educational Resources Information Center

    Little, Philip F.

    1963-01-01

    Several types of refrigeration systems available to the consulting engineer are discussed. The engineer should analyze all energy sources and base his recommendations on comparative costs and availability of sources, keeping in mind that operating costs are of primary importance to schools. The analysis begins with a careful appraisal of the…

  18. National Research Council Dialogue to Assess Progress on NASA's Systems Engineering Cost/Risk Analysis Capability Roadmap Development: General Background and Introduction

    NASA Technical Reports Server (NTRS)

    Regenie, Victoria

    2005-01-01

    Contents include the following: General Background and Introduction of Capability. Roadmaps for Systems Engineering Cost/Risk Analysis. Agency Objectives. Strategic Planning Transformation. Review Capability Roadmaps and Schedule. Review Purpose of NRC Review. Capability Roadmap Development (Progress to Date).

  19. 30 CFR 1220.011 - Schedule of allowable direct and allocable joint costs and credits.

    Code of Federal Regulations, 2014 CFR

    2014-07-01

    ... engineering design problems related to equipment or facilities required for NPSL operations. (4) The cost of any contract service related to research and development is specifically excluded, as are contract services calling for feasibility studies not directly related to specific engineering design problems or...

  20. Reservoir management cost-cutting

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    Gulati, M.S.

    This article by Mohinder S. Gulati, Chief Engineer, Unocal Geothermal Operations, discusses cost cutting in geothermal reservoir management. The reservoir engineer or geoscientist can make a big difference in the economical outcome of a project by improving well performance and thus making geothermal energy more competitive in the energy marketplace. Bringing plants online in less time and proving resources to reduce the cycle time are some of the ways to reduce reservoir management costs discussed in this article.

  1. Electric Power Engineering Cost Predicting Model Based on the PCA-GA-BP

    NASA Astrophysics Data System (ADS)

    Wen, Lei; Yu, Jiake; Zhao, Xin

    2017-10-01

    In this paper a hybrid prediction algorithm: PCA-GA-BP model is proposed. PCA algorithm is established to reduce the correlation between indicators of original data and decrease difficulty of BP neural network in complex dimensional calculation. The BP neural network is established to estimate the cost of power transmission project. The results show that PCA-GA-BP algorithm can improve result of prediction of electric power engineering cost.

  2. Total cost of ownership: the role of clinical engineering.

    PubMed

    Hockel, Dale; Kintner, Michael

    2014-06-01

    Hospitals often incur substantial hidden costs associated with service agreements that they enter into with original equipment manufacturers at the time of equipment purchase. Hospitals should perform an analysis of the total cost of ownership (TCO) of their organizations' medical equipment to identify opportunities for performance improvement and savings. The findings of the TCO analysis can point to areas where clinical engineering service management can be improved through investments in technology, training, and teamwork.

  3. Microeconomic analysis of military aircraft bearing restoration

    NASA Technical Reports Server (NTRS)

    Hein, G. F.

    1976-01-01

    The risk and cost of a bearing restoration by grinding program was analyzed. A microeconomic impact analysis was performed. The annual cost savings to U.S. Army aviation is approximately $950,000.00 for three engines and three transmissions. The capital value over an indefinite life is approximately ten million dollars. The annual cost savings for U.S. Air Force engines are approximately $313,000.00 with a capital value of approximately 3.1 million dollars.

  4. The 25 kWe solar thermal Stirling hydraulic engine system: Conceptual design

    NASA Technical Reports Server (NTRS)

    White, Maurice; Emigh, Grant; Noble, Jack; Riggle, Peter; Sorenson, Torvald

    1988-01-01

    The conceptual design and analysis of a solar thermal free-piston Stirling hydraulic engine system designed to deliver 25 kWe when coupled to a 11 meter test bed concentrator is documented. A manufacturing cost assessment for 10,000 units per year was made. The design meets all program objectives including a 60,000 hr design life, dynamic balancing, fully automated control, more than 33.3 percent overall system efficiency, properly conditioned power, maximum utilization of annualized insolation, and projected production costs. The system incorporates a simple, rugged, reliable pool boiler reflux heat pipe to transfer heat from the solar receiver to the Stirling engine. The free-piston engine produces high pressure hydraulic flow which powers a commercial hydraulic motor that, in turn, drives a commercial rotary induction generator. The Stirling hydraulic engine uses hermetic bellows seals to separate helium working gas from hydraulic fluid which provides hydrodynamic lubrication to all moving parts. Maximum utilization of highly refined, field proven commercial components for electric power generation minimizes development cost and risk.

  5. Advanced Engineering Environments: Implications for Aerospace Manufacturing

    NASA Technical Reports Server (NTRS)

    Thomas, D.

    2001-01-01

    There are significant challenges facing today's aerospace industry. Global competition, more complex products, geographically-distributed design teams, demands for lower cost, higher reliability and safer vehicles, and the need to incorporate the latest technologies quicker all face the developer of aerospace systems. New information technologies offer promising opportunities to develop advanced engineering environments (AEEs) to meet these challenges. Significant advances in the state-of-the-art of aerospace engineering practice are envisioned in the areas of engineering design and analytical tools, cost and risk tools, collaborative engineering, and high-fidelity simulations early in the development cycle. These advances will enable modeling and simulation of manufacturing methods, which will in turn allow manufacturing considerations to be included much earlier in the system development cycle. Significant cost savings, increased quality, and decreased manufacturing cycle time are expected to result. This paper will give an overview of the NASA's Intelligent Synthesis Environment, the agency initiative to develop an AEE, with a focus on the anticipated benefits in aerospace manufacturing.

  6. Integrated analysis of engine structures

    NASA Technical Reports Server (NTRS)

    Chamis, C. C.

    1981-01-01

    The need for light, durable, fuel efficient, cost effective aircraft requires the development of engine structures which are flexible, made from advaced materials (including composites), resist higher temperatures, maintain tighter clearances and have lower maintenance costs. The formal quantification of any or several of these requires integrated computer programs (multilevel and/or interdisciplinary analysis programs interconnected) for engine structural analysis/design. Several integrated analysis computer prorams are under development at Lewis Reseach Center. These programs include: (1) COBSTRAN-Composite Blade Structural Analysis, (2) CODSTRAN-Composite Durability Structural Analysis, (3) CISTRAN-Composite Impact Structural Analysis, (4) STAEBL-StruTailoring of Engine Blades, and (5) ESMOSS-Engine Structures Modeling Software System. Three other related programs, developed under Lewis sponsorship, are described.

  7. A segmented ion engine design for solar electric propulsion systems

    NASA Technical Reports Server (NTRS)

    Brophy, John R.

    1992-01-01

    A new ion engine design, called a segmented ion engine, is described which is capable of reducing the required ion source life time for small body rendezvous missions from 18,000 h to about 8,000 h. The use of SAND ion optics for the engine accelerator system makes it possible to substantially reduce the cost of demonstrating the required engine endurance. It is concluded that a flight test of a 5-kW xenon ion propulsion system on the ELITE spacecraft would enormously reduce the cost and risk of using ion propulsion on a planetary vehicle by addressing systems level issues associated with flying a spacecraft radically different from conventional planetary vehicles.

  8. Microeconomic analysis of military aircraft bearing restoration

    NASA Technical Reports Server (NTRS)

    Hein, G. F.

    1976-01-01

    The risk and cost of a bearing restoration by grinding program was analyzed. A microeconomic impact analysis was performed. The annual cost savings to U.S. Army aviation is approximately $950,000.00 for three engines and three transmissions. The capital value over an indefinite life is approximately ten million dollars. The annual cost savings for U.S. Air Force engines is approximately $313,000.00 with a capital value of approximately 3.1 million dollars. The program will result in the government obtaining bearings at lower costs at equivalent reliability. The bearing industry can recover lost profits during a period of reduced demand and higher costs.

  9. Cost Risk Analysis Based on Perception of the Engineering Process

    NASA Technical Reports Server (NTRS)

    Dean, Edwin B.; Wood, Darrell A.; Moore, Arlene A.; Bogart, Edward H.

    1986-01-01

    In most cost estimating applications at the NASA Langley Research Center (LaRC), it is desirable to present predicted cost as a range of possible costs rather than a single predicted cost. A cost risk analysis generates a range of cost for a project and assigns a probability level to each cost value in the range. Constructing a cost risk curve requires a good estimate of the expected cost of a project. It must also include a good estimate of expected variance of the cost. Many cost risk analyses are based upon an expert's knowledge of the cost of similar projects in the past. In a common scenario, a manager or engineer, asked to estimate the cost of a project in his area of expertise, will gather historical cost data from a similar completed project. The cost of the completed project is adjusted using the perceived technical and economic differences between the two projects. This allows errors from at least three sources. The historical cost data may be in error by some unknown amount. The managers' evaluation of the new project and its similarity to the old project may be in error. The factors used to adjust the cost of the old project may not correctly reflect the differences. Some risk analyses are based on untested hypotheses about the form of the statistical distribution that underlies the distribution of possible cost. The usual problem is not just to come up with an estimate of the cost of a project, but to predict the range of values into which the cost may fall and with what level of confidence the prediction is made. Risk analysis techniques that assume the shape of the underlying cost distribution and derive the risk curve from a single estimate plus and minus some amount usually fail to take into account the actual magnitude of the uncertainty in cost due to technical factors in the project itself. This paper addresses a cost risk method that is based on parametric estimates of the technical factors involved in the project being costed. The engineering process parameters are elicited from the engineer/expert on the project and are based on that expert's technical knowledge. These are converted by a parametric cost model into a cost estimate. The method discussed makes no assumptions about the distribution underlying the distribution of possible costs, and is not tied to the analysis of previous projects, except through the expert calibrations performed by the parametric cost analyst.

  10. Rotorcraft contingency power study

    NASA Technical Reports Server (NTRS)

    Hirschkron, R.; Haynes, J. F.; Goldstein, D. N.; Davis, R. H.

    1984-01-01

    Twin helicopter engines are often sized by the power requirement of a safe mission completion after the failure of one of the two engines. This study was undertaken for NASA Lewis by General Electric Co. to evaluate the merits of special design features to provide a 2-1/2 Contingency Power rating, permitting an engine size reduction. The merits of water injection, turbine cooling airflow modulation, throttle push, and a propellant auxiliary power plant were evaluated using military Life Cycle Cost (LCC) and commercial helicopter Direct Operating Cost (DOC) merit factors in a rubber engine and a rubber aircraft scenario.

  11. Engineering support for magnetohydrodynamic power plant analysis and design studies

    NASA Technical Reports Server (NTRS)

    Carlson, A. W.; Chait, I. L.; Marchmont, G.; Rogali, R.; Shikar, D.

    1980-01-01

    The major factors which influence the economic engineering selection of stack inlet temperatures in combined cycle MHD powerplants are identified and the range of suitable stack inlet temperatures under typical operating conditions is indicated. Engineering data and cost estimates are provided for four separately fired high temperature air heater (HTAH) system designs for HTAH system thermal capacity levels of 100, 250, 500 and 1000 MWt. An engineering survey of coal drying and pulverizing equipment for MHD powerplant application is presented as well as capital and operating cost estimates for varying degrees of coal pulverization.

  12. Calibration and Forward Uncertainty Propagation for Large-eddy Simulations of Engineering Flows

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    Templeton, Jeremy Alan; Blaylock, Myra L.; Domino, Stefan P.

    2015-09-01

    The objective of this work is to investigate the efficacy of using calibration strategies from Uncertainty Quantification (UQ) to determine model coefficients for LES. As the target methods are for engineering LES, uncertainty from numerical aspects of the model must also be quantified. 15 The ultimate goal of this research thread is to generate a cost versus accuracy curve for LES such that the cost could be minimized given an accuracy prescribed by an engineering need. Realization of this goal would enable LES to serve as a predictive simulation tool within the engineering design process.

  13. An Industrial Engineering Approach to Cost Containment of Pharmacy Education

    PubMed Central

    Bottenberg, Michelle; Chase, Marilea; Chesnut, Renae; Clarke, Cheryl; Schott, Kathryn; Torry, Ronald; Welty, Tim

    2015-01-01

    A 2-semester project explored employing teams of fourth-year industrial engineering students to optimize some of our academic management processes. Results included significant cost savings and increases in efficiency, effectiveness, and student and faculty satisfaction. While we did not adopt all of the students’ recommendations, we did learn some important lessons. For example, an initial investment of time in developing a mutually clear understanding of the problems, constraints, and goals maximizes the value of industrial engineering analysis and recommendations. Overall, industrial engineering was a valuable tool for optimizing certain academic management processes. PMID:26839421

  14. Ti/Al Design/Cost Trade-Off Analysis

    DTIC Science & Technology

    1978-10-01

    evaluate the applV!ati’an of selected titanium aluuinide alloys to both dynamic and static components of aircraft gas turbine engines . Mr. D. 0. Nash...the development of advanced aircraft gas turbine engines , a continuing objective has been to develop lightweight, high-performance designs. A parallel... engines for the design/cost trade-off study are as follows: Dynamic Components "* F1O1 Fourth-Stage Compressor Blade "* JlO1 Low Pressure Turbine Blade

  15. CrossTalk: The Journal of Defense Software Engineering. Volume 20, Number 6, June 2007

    DTIC Science & Technology

    2007-06-01

    California. He has co-authored the book Software Cost Estimation With COCOMO II with Barry Boehm and others. Clark helped define the COCOMO II model...Software Engineering at the University of Southern California. She worked with Barry Boehm and Chris Abts to develop and calibrate a cost-estimation...2003/02/ schorsch.html>. 2. See “Software Engineering, A Practitioners Approach” by Roger Pressman for a good description of coupling, cohesion

  16. Secondary electric power generation with minimum engine bleed

    NASA Technical Reports Server (NTRS)

    Tagge, G. E.

    1983-01-01

    Secondary electric power generation with minimum engine bleed is discussed. Present and future jet engine systems are compared. The role of auxiliary power units is evaluated. Details of secondary electric power generation systems with and without auxiliary power units are given. Advanced bleed systems are compared with minimum bleed systems. A cost model of ownership is given. The difference in the cost of ownership between a minimum bleed system and an advanced bleed system is given.

  17. Additive Manufacture of Plasma Diagnostic Components Final Report Phase II

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    Woodruff, Simon; Romero-Talamas, Carlos; You, Setthivoine

    There is now a well-established set of plasma diagnostics (see e.g. [3]), but these remain some of the mostexpensive assemblies in fusion systems since for every system they have to be custom built, and time fordiagnostic development can pace the project. Additive manufacturing (AM) has the potential to decreaseproduction cost and significantly lower design time of fusion diagnostic subsystems, which would realizesignificant cost reduction for standard diagnostics. In some cases, these basic components can be additivelymanufactured for less than 1/100th costs of conventional manufacturing.In our DOE Phase II SBIR, we examined the impact that AM can have on plasma diagnosticmore » cost bytaking 15 separate diagnostics through an engineering design using Conventional Manufacturing (CM) tech-niques, then optimizing the design to exploit the benefits of AM. The impact of AM techniques on cost isfound to be in several areas. First, the cost of materials falls because AM parts can be manufactured withlittle to no waste, and engineered to use less material than CM. Next, the cost of fabrication falls for AMparts relative to CM since the fabrication time can be computed exactly, and often no post-processing isrequired for the part to be functional. We find that AM techniques are well suited for plasma diagnosticssince typical diagnostic complexity comes at no additional cost. Cooling channels, for example, can be builtin to plasma-facing components at no extra cost. Fabrication costs associated with assembly are lower forAM parts because many components can be combined and printed as monoliths, thereby mitigating the needfor alignment or calibration. Finally, the cost of engineering is impacted by exploiting AM design tools thatallow standard components to be customized through web-interfaces. Furthermore, we find that conceptdesign costs can be impacted by scripting interfaces for online engineering design tools.« less

  18. Impacts of a Flat World on Engineering Education

    ERIC Educational Resources Information Center

    Chatziioanou, Alypios

    2006-01-01

    This paper discusses the changes to engineering education introduced through the accelerated engineering-related industrial growth in Asian and other developing countries. While the demand for engineering services is increasing, these nations educate a large number of engineers themselves and many are providing lower-cost alternatives for…

  19. 48 CFR 48.102 - Policies.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... VALUE ENGINEERING Policies and Procedures 48.102 Policies. (a) As required by Section 36 of the Office... cost-effective value engineering procedures and processes. Agencies shall provide contractors a... engineering provisions in appropriate supply, service, architect-engineer and construction contracts as...

  20. COST Action TU1208 "Civil Engineering Applications of Ground Penetrating Radar": ongoing research activities and third-year results

    NASA Astrophysics Data System (ADS)

    Pajewski, Lara; Benedetto, Andrea; Loizos, Andreas; Tosti, Fabio

    2016-04-01

    This work aims at disseminating the ongoing research activities and third-year results of the COST (European COoperation in Science and Technology) Action TU1208 "Civil Engineering Applications of Ground Penetrating Radar." About 350 experts are participating to the Action, from 28 COST Countries (Austria, Belgium, Croatia, Czech Republic, Denmark, Estonia, Finland, France, Germany, Greece, Ireland, Italy, Latvia, Malta, Macedonia, The Netherlands, Norway, Poland, Portugal, Romania, Serbia, Slovakia, Slovenia, Spain, Sweden, Switzerland, Turkey, United Kingdom), and from Albania, Armenia, Australia, Colombia, Egypt, Hong Kong, Jordan, Israel, Philippines, Russia, Rwanda, Ukraine, and United States of America. In September 2014, TU1208 has been recognised among the running Actions as "COST Success Story" ("The Cities of Tomorrow: The Challenges of Horizon 2020," September 17-19, 2014, Torino, IT - A COST strategic workshop on the development and needs of the European cities). The principal goal of the COST Action TU1208 is to exchange and increase scientific-technical knowledge and experience of GPR techniques in civil engineering, whilst simultaneously promoting throughout Europe the effective use of this safe and non-destructive technique in the monitoring of infrastructures and structures. Moreover, the Action is oriented to the following specific objectives and expected deliverables: (i) coordinating European scientists to highlight problems, merits and limits of current GPR systems; (ii) developing innovative protocols and guidelines, which will be published in a handbook and constitute a basis for European standards, for an effective GPR application in civil- engineering tasks; safety, economic and financial criteria will be integrated within the protocols; (iii) integrating competences for the improvement and merging of electromagnetic scattering techniques and of data- processing techniques; this will lead to a novel freeware tool for the localization of buried objects, shape-reconstruction and estimation of geophysical parameters useful for civil engineering needs; (iv) networking for the design, realization and optimization of innovative GPR equipment; (v) comparing GPR with different NDT techniques, such as ultrasonic, radiographic, liquid-penetrant, magnetic-particle, acoustic-emission and eddy-current testing; (vi) comparing GPR technology and methodology used in civil engineering with those used in other fields; (vii) promotion of a more widespread, advanced and efficient use of GPR in civil engineering; and (viii) organization of a high-level modular training program for GPR European users. Four Working Groups (WGs) carry out the research activities. WG 1 focuses on the design of innovative GPR equipment, on the building of prototypes and on the testing and optimisation of new systems. WG 2 focuses on the GPR surveying of pavement, bridges, tunnels and buildings, as well as on the sensing of underground utilities and voids. WG 3 deals with the development of electromagnetic forward and inverse scattering methods, for the characterization of GPR scenarios, as well as with data-processing algorithms for the elaboration of the data collected during GPR surveys. WG 4 works on the use of GPR in fields different from the civil engineering, as well as on the integration of GPR with other non-destructive testing techniques. Each WG includes several Projects. COST Action TU1208 is active through a range of networking tools: meetings, workshops, conferences, training schools, short-term scientific missions, dissemination activities. For more information on COST Action TU1208, please visit www.GPRadar.eu and www.cost.eu. Acknowledgement The Authors wish to thank COST, for funding the COST Action TU1208 "Civil engineering applications of Ground Penetrating Radar."

  1. Comparison of low-cost and engineered materials for phosphorus removal from organic-rich surface water.

    PubMed

    Boyer, Treavor H; Persaud, Amar; Banerjee, Poulomi; Palomino, Pedro

    2011-10-15

    Excess phosphorus (P) in lakes and rivers remains a major water quality problem on a global scale. As a result, new materials and innovative approaches to P remediation are required. Natural materials and waste byproduct materials from industrial processes have the potential to be effective materials for P removal from surface water. Advantages of natural and waste byproduct materials include their low-cost, abundant supply, and minimal preparation, especially compared with engineered materials, such as ion exchange resins and polymeric adsorbents. As a result, natural and waste byproduct materials are commonly referred to as low-cost materials. Despite the potential advantages of low-cost materials, there are critical gaps in knowledge that are preventing their effective use. In particular, there are limited data on the performance of low-cost materials in surface waters that have high concentrations of natural organic matter (NOM), and there are no systematic studies that track the changes in water chemistry following treatment with low-cost materials or compare their performance with engineered materials. Accordingly, the goal of this work was to evaluate and compare the effectiveness of low-cost and engineered materials for P removal from NOM-rich surface water. Seven low-cost materials and three engineered materials were evaluated using jar tests and mini-column experiments. The test water was a surface water that had a total P concentration of 132-250 μg P/L and a total organic carbon concentration of 15-32 mg C/L. Alum sludge, a byproduct of drinking water treatment, and a hybrid anion exchange resin loaded with nanosize iron oxide were the best performing materials in terms of selective P removal in the presence of NOM and minimum undesirable secondary changes to the water chemistry. Copyright © 2011 Elsevier Ltd. All rights reserved.

  2. Computerized systems analysis and optimization of aircraft engine performance, weight, and life cycle costs

    NASA Technical Reports Server (NTRS)

    Fishbach, L. H.

    1979-01-01

    The paper describes the computational techniques employed in determining the optimal propulsion systems for future aircraft applications and to identify system tradeoffs and technology requirements. The computer programs used to perform calculations for all the factors that enter into the selection process of determining the optimum combinations of airplanes and engines are examined. Attention is given to the description of the computer codes including NNEP, WATE, LIFCYC, INSTAL, and POD DRG. A process is illustrated by which turbine engines can be evaluated as to fuel consumption, engine weight, cost and installation effects. Examples are shown as to the benefits of variable geometry and of the tradeoff between fuel burned and engine weights. Future plans for further improvements in the analytical modeling of engine systems are also described.

  3. The Base Engine for Solar Stirling Power

    NASA Technical Reports Server (NTRS)

    Meijer, R. J.; Godett, T. M.

    1984-01-01

    A new concept in Stirling engine technology is embodied in the base engine now being developed at Stirling Thermal Motors, Inc. This is a versatile energy conversion unit suitable for many different applications and heat sources. The base engine, rated 40 kW at 2800 RPM, is a four-cylinder, double-acting variable displacement Stirling engine with pressurized crankcase and rotating shaft seal. Remote-heating technology is incorporated with a stacked-heat-exchanger configuration and a liquid metal heat pipe connected to a distinctly separate combustor or other heat source. High efficiency over a wide range of operating conditions, long life, low manufacturing cost and low material cost are specifically emphasized. The base engine, its design philosophy and approach, its projected performance, and some of its more attractive applications are described.

  4. 49 CFR 262.3 - Definitions.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ..., including architectural and engineering costs, and costs associated with compliance with the National.... Allowable costs means those project costs for which Federal funding may be expended under this part. Only construction and construction-related costs will be allowable. Construction means supervising, inspecting...

  5. 49 CFR 262.3 - Definitions.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ..., including architectural and engineering costs, and costs associated with compliance with the National.... Allowable costs means those project costs for which Federal funding may be expended under this part. Only construction and construction-related costs will be allowable. Construction means supervising, inspecting...

  6. 49 CFR 262.3 - Definitions.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ..., including architectural and engineering costs, and costs associated with compliance with the National.... Allowable costs means those project costs for which Federal funding may be expended under this part. Only construction and construction-related costs will be allowable. Construction means supervising, inspecting...

  7. Design of preventive maintenance system using the reliability engineering and maintenance value stream mapping methods in PT. XYZ

    NASA Astrophysics Data System (ADS)

    Sembiring, N.; Panjaitan, N.; Angelita, S.

    2018-02-01

    PT. XYZ is a company owned by non-governmental organizations engaged in the field of production of rubber processing becoming crumb rubber. Part of the production is supported by some of machines and interacting equipment to achieve optimal productivity. Types of the machine that are used in the production process are Conveyor Breaker, Breaker, Rolling Pin, Hammer Mill, Mill Roll, Conveyor, Shredder Crumb, and Dryer. Maintenance system in PT. XYZ is corrective maintenance i.e. repairing or replacing the engine components after the crash on the machine. Replacement of engine components on corrective maintenance causes the machine to stop operating during the production process is in progress. The result is in the loss of production time due to the operator must replace the damaged engine components. The loss of production time can impact on the production targets which were not reached and lead to high loss costs. The cost for all components is Rp. 4.088.514.505. This cost is really high just for maintaining a Mill Roll Machine. Therefore PT. XYZ is needed to do preventive maintenance i.e. scheduling engine components and improving maintenance efficiency. The used methods are Reliability Engineering and Maintenance Value Stream Mapping (MVSM). The needed data in this research are the interval of time damage to engine components, opportunity cost, labor cost, component cost, corrective repair time, preventive repair time, Mean Time To Opportunity (MTTO), Mean Time To Repair (MTTR), and Mean Time To Yield (MTTY). In this research, the critical components of Mill Roll machine are Spier, Bushing, Bearing, Coupling and Roll. Determination of damage distribution, reliability, MTTF, cost of failure, cost of preventive, current state map, and future state map are done so that the replacement time for each critical component with the lowest maintenance cost and preparation of Standard Operation Procedure (SOP) are developed. For the critical component that has been determined, the Spier component replacement time interval is 228 days with a reliability value of 0,503171, Bushing component is 240 days with reliability value of 0.36861, Bearing component is 202 days with reliability value of 0,503058, Coupling component is 247 days with reliability value of 0,50108 and Roll component is 301 days with reliability value of 0,373525. The results show that the cost decreases from Rp 300,688,114 to Rp 244,384,371 obtained from corrective maintenance to preventive maintenance. While maintenance efficiency increases with the application of preventive maintenance i.e. for Spier component from 54,0540541% to 74,07407%, Bushing component from 52,3809524% to 68,75%, Bearing component from 40% to 52,63158%, Coupling component from 60.9756098% to 71.42857%, and Roll components from 64.516129% to 74.7663551%.

  8. The importance of cost considerations in the systems engineering process

    NASA Technical Reports Server (NTRS)

    Hodge, John D.

    1993-01-01

    This paper examines the question of cost, from the birth of a program to its conclusion, particularly from the point of view of large multi-center programs, and suggests how to avoid some of the traps and pitfalls. Emphasis is given to cost in the systems engineering process, but there is an inevitable overlap with program management. (These terms, systems engineering and program management, have never been clearly defined.) In these days of vast Federal budget deficits and increasing overseas competition, it is imperative that we get more for each research and development dollar. This is the only way we will retain our leadership in high technology and, in the long run, our way of life.

  9. Intelligent Life-Extending Controls for Aircraft Engines

    NASA Technical Reports Server (NTRS)

    Guo, Ten-Huei; Chen, Philip; Jaw, Link

    2005-01-01

    Aircraft engine controllers are designed and operated to provide desired performance and stability margins. The purpose of life-extending-control (LEC) is to study the relationship between control action and engine component life usage, and to design an intelligent control algorithm to provide proper trade-offs between performance and engine life usage. The benefit of this approach is that it is expected to maintain safety while minimizing the overall operating costs. With the advances of computer technology, engine operation models, and damage physics, it is necessary to reevaluate the control strategy fro overall operating cost consideration. This paper uses the thermo-mechanical fatigue (TMF) of a critical component to demonstrate how an intelligent engine control algorithm can drastically reduce the engine life usage with minimum sacrifice in performance. A Monte Carlo simulation is also performed to evaluate the likely engine damage accumulation under various operating conditions. The simulation results show that an optimized acceleration schedule can provide a significant life saving in selected engine components.

  10. Application of advanced technologies to small, short-haul transport aircraft

    NASA Technical Reports Server (NTRS)

    Coussens, T. G.; Tullis, R. H.

    1980-01-01

    The performance and economic benefits available by incorporation of advanced technologies into the small, short haul air transport were assessed. Low cost structure and advanced composite material, advanced turboprop engines and new propellers, advanced high lift systems and active controls; and alternate aircraft configurations with aft mounted engines were investigated. Improvements in fuel consumed and aircraft economics (acquisition cost and direct operating cost) are available by incorporating selected advanced technologies into the small, short haul aircraft.

  11. Cost of Stem Cell-Based Tissue-Engineered Airway Transplants in the United Kingdom: Case Series

    PubMed Central

    Culme-Seymour, Emily J.; Mason, Katrina; Vallejo-Torres, Laura; Carvalho, Carla; Partington, Leanne; Crowley, Claire; Hamilton, Nick J.; Toll, Ed C.; Butler, Colin R.; Elliott, Martin J.; Birchall, Martin A.; Lowdell, Mark W.

    2016-01-01

    Stem cell-based tissue-engineered tracheas are at an early stage in their product development cycle. Tens of patients have been treated worldwide in predominantly compassionate use settings, demonstrating significant promise. This potentially life-saving treatment is complex, and the cost and its implications for such treatments are yet to be fully understood. The costs are compounded by varying strategies for graft preparation and transplant, resulting in differing clinical and laboratory costs from different research groups. In this study, we present a detailed breakdown of the clinical and manufacturing costs for three of the United Kingdom (UK) patients treated with such transplants. All three patients were treated under Compassionate Use legislation, within the UK National Health Service (NHS) hospital setting. The total costs for the three UK patients treated ranged from $174,420 to $740,500. All three patients were in a state of poor health at time of treatment and had a number of complexities in addition to the restricted airway. This is the first time a cost analysis has been made for a tissue-engineered organ and provides a benchmark for future studies, as well as comparative data for use in reimbursement considerations. PMID:26559535

  12. Software Estimates Costs of Testing Rocket Engines

    NASA Technical Reports Server (NTRS)

    Smith, C. L.

    2003-01-01

    Simulation-Based Cost Model (SiCM), a discrete event simulation developed in Extend , simulates pertinent aspects of the testing of rocket propulsion test articles for the purpose of estimating the costs of such testing during time intervals specified by its users. A user enters input data for control of simulations; information on the nature of, and activity in, a given testing project; and information on resources. Simulation objects are created on the basis of this input. Costs of the engineering-design, construction, and testing phases of a given project are estimated from numbers and labor rates of engineers and technicians employed in each phase, the duration of each phase; costs of materials used in each phase; and, for the testing phase, the rate of maintenance of the testing facility. The three main outputs of SiCM are (1) a curve, updated at each iteration of the simulation, that shows overall expenditures vs. time during the interval specified by the user; (2) a histogram of the total costs from all iterations of the simulation; and (3) table displaying means and variances of cumulative costs for each phase from all iterations. Other outputs include spending curves for each phase.

  13. Cost of Stem Cell-Based Tissue-Engineered Airway Transplants in the United Kingdom: Case Series.

    PubMed

    Culme-Seymour, Emily J; Mason, Katrina; Vallejo-Torres, Laura; Carvalho, Carla; Partington, Leanne; Crowley, Claire; Hamilton, Nick J; Toll, Ed C; Butler, Colin R; Elliott, Martin J; Birchall, Martin A; Lowdell, Mark W; Mason, Chris

    2016-02-01

    Stem cell-based tissue-engineered tracheas are at an early stage in their product development cycle. Tens of patients have been treated worldwide in predominantly compassionate use settings, demonstrating significant promise. This potentially life-saving treatment is complex, and the cost and its implications for such treatments are yet to be fully understood. The costs are compounded by varying strategies for graft preparation and transplant, resulting in differing clinical and laboratory costs from different research groups. In this study, we present a detailed breakdown of the clinical and manufacturing costs for three of the United Kingdom (UK) patients treated with such transplants. All three patients were treated under Compassionate Use legislation, within the UK National Health Service (NHS) hospital setting. The total costs for the three UK patients treated ranged from $174,420 to $740,500. All three patients were in a state of poor health at time of treatment and had a number of complexities in addition to the restricted airway. This is the first time a cost analysis has been made for a tissue-engineered organ and provides a benchmark for future studies, as well as comparative data for use in reimbursement considerations.

  14. Affordable Rankine Cycle Waste Heat Recovery for Heavy Duty Trucks

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    Subramanian, Swami Nathan

    Nearly 30% of fuel energy is not utilized and wasted in the engine exhaust. Organic Rankine Cycle (ORC) based waste heat recovery (WHR) systems offer a promising approach on waste energy recovery and improving the efficiency of Heavy-Duty diesel engines. Major barriers in the ORC WHR system are the system cost and controversial waste heat recovery working fluids. More than 40% of the system cost is from the additional heat exchangers (recuperator, condenser and tail pipe boiler). The secondary working fluid loop designed in ORC system is either flammable or environmentally sensitive. The Eaton team investigated a novel approach tomore » reduce the cost of implementing ORC based WHR systems to Heavy-Duty (HD) Diesel engines while utilizing safest working fluids. Affordable Rankine Cycle (ARC) concept aimed to define the next generation of waste energy recuperation with a cost optimized WHR system. ARC project used engine coolant as the working fluid. This approach reduced the need for a secondary working fluid circuit and subsequent complexity. A portion of the liquid phase engine coolant has been pressurized through a set of working fluid pumps and used to recover waste heat from the exhaust gas recirculation (EGR) and exhaust tail pipe exhaust energy. While absorbing heat, the mixture is partially vaporized but remains a wet binary mixture. The pressurized mixed-phase engine coolant mixture is then expanded through a fixed-volume ratio expander that is compatible with two-phase conditions. Heat rejection is accomplished through the engine radiator, avoiding the need for a separate condenser. The ARC system has been investigated for PACCAR’s MX-13 HD diesel engine.« less

  15. Sensitivities of projected 1980 photovoltaic system costs to major system cost drivers

    NASA Technical Reports Server (NTRS)

    Zimmerman, L. W.; Smith, J. L.

    1984-01-01

    The sensitivity of projected 1990 photovoltaic (PV) system costs to major system cost drivers was examined. It includes: (1) module costs and module efficiencies; (2) area related balance of system (BOS) costs; (3) inverter costs and efficiencies; and (4) module marketing and distribution markups and system integration fees. Recent PV system cost experiences and the high costs of electricity from the systems are reviewed. The 1990 system costs are projected for five classes of PV systems, including four ground mounted 5-MWp systems and one residential 5-kWp system. System cost projections are derived by first projecting costs and efficiencies for all subsystems and components. Sensitivity analyses reveal that reductions in module cost and engineering and system integration fees seem to have the greatest potential for contributing to system cost reduction. Although module cost is clearly the prime candidate for fruitful PV research and development activities, engineering and system integration fees seem to be more amenable to reduction through appropriate choice of system size and market strategy. Increases in inverter and module efficiency yield significant benefits, especially for systems with high area related costs.

  16. Management Science/Industrial Engineering Techniques to Reduce Food Costs.

    ERIC Educational Resources Information Center

    Greenberg, Murray

    This paper examines the contributions of Industrial Engineering and Management Science toward reduction in the cost of production and distribution of food. Food processing firms were requested to respond to a questionnaire which asked for examples of their use of various operations research tools and information on the number of operations…

  17. Software Process Improvement through the Removal of Project-Level Knowledge Flow Obstacles: The Perceptions of Software Engineers

    ERIC Educational Resources Information Center

    Mitchell, Susan Marie

    2012-01-01

    Uncontrollable costs, schedule overruns, and poor end product quality continue to plague the software engineering field. Innovations formulated with the expectation to minimize or eliminate cost, schedule, and quality problems have generally fallen into one of three categories: programming paradigms, software tools, and software process…

  18. 48 CFR 36.608 - Liability for Government costs resulting from design errors or deficiencies.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... 48 Federal Acquisition Regulations System 1 2013-10-01 2013-10-01 false Liability for Government costs resulting from design errors or deficiencies. 36.608 Section 36.608 Federal Acquisition Regulations System FEDERAL ACQUISITION REGULATION SPECIAL CATEGORIES OF CONTRACTING CONSTRUCTION AND ARCHITECT-ENGINEER CONTRACTS Architect-Engineer Service...

  19. Value Engineering. Technical Manual. School Facilities Development Procedures Manual.

    ERIC Educational Resources Information Center

    Washington Office of the State Superintendent of Public Instruction, Olympia.

    Value Engineering (VE) is a cost-optimizing technique used to analyze design quality and cost-effectiveness. The application of VE procedures to the design and construction of school facilities has been adopted by the state of Washington. This technical manual provides guidance in developing the scope and applicability of VE to school projects; in…

  20. Relative Economy of Different Methods of Airplane Construction

    NASA Technical Reports Server (NTRS)

    Herrmann, H

    1931-01-01

    A comparison of the relative economy of airplane construction shows that monoplanes are cheaper than biplanes; that all-metal construction is much more expensive than mixed construction; that multi-engine airplanes are more expensive than single-engine types of the same carrying capacity and speed;that the cost of airplanes is materially reduced by increasing their size without increasing the number of engines. The greatest economy usually coincides with the best aerodynamic and static conditions and the cost is always increased by safety requirements.

  1. Value Engineering Should Be Improved as Part of the Defense Department’s Approach to Reducing Acquisition Cost.

    DTIC Science & Technology

    1983-09-27

    monitoring subcontractor activity, DOD officials must take into account practical and cost considerations 20 * *, l o *° as well as legal constraints...AD-A134 967 VALUE ENGINEERING SHOULD BE IMPROYED AS PART OF THE i/i DEFENSE DEPARTMENT’S~ (U) GENERAL ACCOUNTING OFFICE WASHINGTON DC ACCOUNTING AND...RESOLUTION TEST CHART NATIONAL BUREAU OF STANDAR DS -I96 3 -A 7.... REPORT BY THE U.S. & General Accounting Office ,:: Value Engineering Should Be Improved

  2. United States Air Force 611th Civil Engineer Squadron, Elmendorf AFB, Alaska. Final engineering evaluation/cost analysis potential tce impact to the drinking water supply, Galena Airport, Alaska

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    NONE

    1996-02-05

    This decision document presents the selected removal action to address potential trichloroethene (TCE) impact to drinking water supply wells, located in the Installation Restoration Program (IRP) site ST009, otherwise known as the West Unit, at Galena Airport, Alaska. The information fron the RI Report is summarized, along with an analysis of potential removal action alternatives, in the Engineering Evaluation/Cost Analysis (EE/CA).

  3. United States Air Force 611th Civil Engineer Squadron, Elmendorf, AFB, Alaska. Final engineering evaluation/cost analysis, million gallon hill source area of the West Unit, Galena Airport, Alaska

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    NONE

    1996-02-05

    This decision document presents the selected removal action for the Million Gallon Hill source area of the Installation Restoration Program (IRP) site ST009, otherwise known as the West Unit at Galena Airport, Alaska. The information from the RI Report is summarized, along with an analysis of potential removal action alternatives in the Engineering Evaluation/Cost Analysis (EE/CA).

  4. The Application of Design to Cost and Life Cycle to Aircraft Engines.

    DTIC Science & Technology

    1980-05-01

    appearing in both columns include AGE (common and peculiar), transportation, management, and training. These cost elements are not usually large in...Proc. of install engine X CIP x Spare engine X Spare parts (base/depot) X Depot labor X Base labor X ECPs-mod/retro X X AGE (peculiar/common) X X...introduits de maniere aleatoire dans le cadre j’hypotheses. En outre les moteurs ou les sous-ensembles, compte tenu du suivi de leur age et de leur

  5. Ablative material testing for low-pressure, low-cost rocket engines

    NASA Technical Reports Server (NTRS)

    Richter, G. Paul; Smith, Timothy D.

    1995-01-01

    The results of an experimental evaluation of ablative materials suitable for the production of light weight, low cost rocket engine combustion chambers and nozzles are presented. Ten individual specimens of four different compositions of silica cloth-reinforced phenolic resin materials were evaluated for comparative erosion in a subscale rocket engine combustion chamber. Gaseous hydrogen and gaseous oxygen were used as propellants, operating at a nominal chamber pressure of 1138 kPa (165 psi) and a nominal mixture ratio (O/F) of 3.3. These conditions were used to thermally simulate operation with RP-1 and liquid oxygen, and achieved a specimen throat gas temperature of approximately 2456 K (4420 R). Two high-density composition materials exhibited high erosion resistance, while two low-density compositions exhibited approximately 6-75 times lower average erosion resistance. The results compare favorably with previous testing by NASA and provide adequate data for selection of ablatives for low pressure, low cost rocket engines.

  6. Genetically Engineered Materials for Biofuels Production

    NASA Astrophysics Data System (ADS)

    Raab, Michael

    2012-02-01

    Agrivida, Inc., is an agricultural biotechnology company developing industrial crop feedstocks for the fuel and chemical industries. Agrivida's crops have improved processing traits that enable efficient, low cost conversion of the crops' cellulosic components into fermentable sugars. Currently, pretreatment and enzymatic conversion of the major cell wall components, cellulose and hemicellulose, into fermentable sugars is the most expensive processing step that prevents widespread adoption of biomass in biofuels processes. To lower production costs we are consolidating pretreatment and enzyme production within the crop. In this strategy, transgenic plants express engineered cell wall degrading enzymes in an inactive form, which can be reactivated after harvest. We have engineered protein elements that disrupt enzyme activity during normal plant growth. Upon exposure to specific processing conditions, the engineered enzymes are converted into their active forms. This mechanism significantly lowers pretreatment costs and enzyme loadings (>75% reduction) below those currently available to the industry.

  7. Advanced rocket propulsion

    NASA Technical Reports Server (NTRS)

    Obrien, Charles J.

    1993-01-01

    Existing NASA research contracts are supporting development of advanced reinforced polymer and metal matrix composites for use in liquid rocket engines of the future. Advanced rocket propulsion concepts, such as modular platelet engines, dual-fuel dual-expander engines, and variable mixture ratio engines, require advanced materials and structures to reduce overall vehicle weight as well as address specific propulsion system problems related to elevated operating temperatures, new engine components, and unique operating processes. High performance propulsion systems with improved manufacturability and maintainability are needed for single stage to orbit vehicles and other high performance mission applications. One way to satisfy these needs is to develop a small engine which can be clustered in modules to provide required levels of total thrust. This approach should reduce development schedule and cost requirements by lowering hardware lead times and permitting the use of existing test facilities. Modular engines should also reduce operational costs associated with maintenance and parts inventories.

  8. An experimental investigation of performance of diesel to CNG engine

    NASA Astrophysics Data System (ADS)

    Misra, Sheelam; Gupta, Ayush; Garg, Ashutosh

    2018-05-01

    Over the past few decades, diesel engines are widely used in automobiles which is responsible for hazardous increase in pollution. Around the world, many countries are trying to reduce it by replacing diesel with CNG as a fuel which is more economical and leads to pollution free environment. Engineers came up with an idea to convert diesel engine to CNG engine. This conversion is possible by doing some alteration of engine components and it also include adding some extra components to the system which includes spark plug, valves etc. and by decreasing the compression ratio of the engine. It is used worldwide today and many countries have many programs to convert older, polluting diesel vehicles to CNG enable vehicles so that they can run on clean, economical natural gas. This is, an excellent way to reduce fuel cost, reduce pollution, reduce noise with minimum possible capital costs.first, second, and third level headings.

  9. Main propulsion system design recommendations for an advanced Orbit Transfer Vehicle

    NASA Technical Reports Server (NTRS)

    Redd, L.

    1985-01-01

    Various main propulsion system configurations of an advanced OTV are evaluated with respect to the probability of nonindependent failures, i.e., engine failures that disable the entire main propulsion system. Analysis of the life-cycle cost (LCC) indicates that LCC is sensitive to the main propulsion system reliability, vehicle dry weight, and propellant cost; it is relatively insensitive to the number of missions/overhaul, failures per mission, and EVA and IVA cost. In conclusion, two or three engines are recommended in view of their highest reliability, minimum life-cycle cost, and fail operational/fail safe capability.

  10. Electricity from fossil fuels without CO2 emissions: assessing the costs of carbon dioxide capture and sequestration in U.S. electricity markets.

    PubMed

    Johnson, T L; Keith, D W

    2001-10-01

    The decoupling of fossil-fueled electricity production from atmospheric CO2 emissions via CO2 capture and sequestration (CCS) is increasingly regarded as an important means of mitigating climate change at a reasonable cost. Engineering analyses of CO2 mitigation typically compare the cost of electricity for a base generation technology to that for a similar plant with CO2 capture and then compute the carbon emissions mitigated per unit of cost. It can be hard to interpret mitigation cost estimates from this plant-level approach when a consistent base technology cannot be identified. In addition, neither engineering analyses nor general equilibrium models can capture the economics of plant dispatch. A realistic assessment of the costs of carbon sequestration as an emissions abatement strategy in the electric sector therefore requires a systems-level analysis. We discuss various frameworks for computing mitigation costs and introduce a simplified model of electric sector planning. Results from a "bottom-up" engineering-economic analysis for a representative U.S. North American Electric Reliability Council (NERC) region illustrate how the penetration of CCS technologies and the dispatch of generating units vary with the price of carbon emissions and thereby determine the relationship between mitigation cost and emissions reduction.

  11. Electricity from Fossil Fuels without CO2 Emissions: Assessing the Costs of Carbon Dioxide Capture and Sequestration in U.S. Electricity Markets.

    PubMed

    Johnson, Timothy L; Keith, David W

    2001-10-01

    The decoupling of fossil-fueled electricity production from atmospheric CO 2 emissions via CO 2 capture and sequestration (CCS) is increasingly regarded as an important means of mitigating climate change at a reasonable cost. Engineering analyses of CO 2 mitigation typically compare the cost of electricity for a base generation technology to that for a similar plant with CO 2 capture and then compute the carbon emissions mitigated per unit of cost. It can be hard to interpret mitigation cost estimates from this plant-level approach when a consistent base technology cannot be identified. In addition, neither engineering analyses nor general equilibrium models can capture the economics of plant dispatch. A realistic assessment of the costs of carbon sequestration as an emissions abatement strategy in the electric sector therefore requires a systems-level analysis. We discuss various frameworks for computing mitigation costs and introduce a simplified model of electric sector planning. Results from a "bottom-up" engineering-economic analysis for a representative U.S. North American Electric Reliability Council (NERC) region illustrate how the penetration of CCS technologies and the dispatch of generating units vary with the price of carbon emissions and thereby determine the relationship between mitigation cost and emissions reduction.

  12. 47 CFR 32.6535 - Engineering expense.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... 47 Telecommunication 2 2014-10-01 2014-10-01 false Engineering expense. 32.6535 Section 32.6535... FOR TELECOMMUNICATIONS COMPANIES Instructions for Expense Accounts § 32.6535 Engineering expense. (a) This account shall include costs incurred in the general engineering of the telecommunications plant...

  13. 47 CFR 32.6535 - Engineering expense.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... 47 Telecommunication 2 2011-10-01 2011-10-01 false Engineering expense. 32.6535 Section 32.6535... FOR TELECOMMUNICATIONS COMPANIES Instructions for Expense Accounts § 32.6535 Engineering expense. (a) This account shall include costs incurred in the general engineering of the telecommunications plant...

  14. 47 CFR 32.6535 - Engineering expense.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... 47 Telecommunication 2 2012-10-01 2012-10-01 false Engineering expense. 32.6535 Section 32.6535... FOR TELECOMMUNICATIONS COMPANIES Instructions for Expense Accounts § 32.6535 Engineering expense. (a) This account shall include costs incurred in the general engineering of the telecommunications plant...

  15. 47 CFR 32.6535 - Engineering expense.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... 47 Telecommunication 2 2013-10-01 2013-10-01 false Engineering expense. 32.6535 Section 32.6535... FOR TELECOMMUNICATIONS COMPANIES Instructions for Expense Accounts § 32.6535 Engineering expense. (a) This account shall include costs incurred in the general engineering of the telecommunications plant...

  16. 47 CFR 32.6535 - Engineering expense.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... 47 Telecommunication 2 2010-10-01 2010-10-01 false Engineering expense. 32.6535 Section 32.6535... FOR TELECOMMUNICATIONS COMPANIES Instructions for Expense Accounts § 32.6535 Engineering expense. (a) This account shall include costs incurred in the general engineering of the telecommunications plant...

  17. Automotive Stirling Engine Development Program. RESD summary report

    NASA Technical Reports Server (NTRS)

    1984-01-01

    The design of reference Stirling engine system as well as the engine auxiliaries and controls is described. Manufacturing costs in production quantity are also presented. Engine system performance predictions are discussed and vehicle integration is developed, along with projected fuel economy levels.

  18. Radiological controls integrated into design

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    Kindred, G.W.

    1995-03-01

    Radiological controls are required by law in the design of commercial nuclear power reactor facilities. These controls can be relatively minor or significant, relative to cost. To ensure that radiological controls are designed into a project, the health physicist (radiological engineer) must be involved from the beginning. This is especially true regarding keeping costs down. For every radiological engineer at a nuclear power plant there must be fifty engineers of other disciplines. The radiological engineer cannot be an expert on every discipline of engineering. However, he must be knowledgeable to the degree of how a design will impact the facilitymore » from a radiological perspective. This paper will address how to effectively perform radiological analyses with the goal of radiological controls integrated into the design package.« less

  19. Damage-Tolerant Fan Casings for Jet Engines

    NASA Technical Reports Server (NTRS)

    2006-01-01

    All turbofan engines work on the same principle. A large fan at the front of the engine draws air in. A portion of the air enters the compressor, but a greater portion passes on the outside of the engine this is called bypass air. The air that enters the compressor then passes through several stages of rotating fan blades that compress the air more, and then it passes into the combustor. In the combustor, fuel is injected into the airstream, and the fuel-air mixture is ignited. The hot gasses produced expand rapidly to the rear, and the engine reacts by moving forward. If there is a flaw in the system, such as an unexpected obstruction, the fan blade can break, spin off, and harm other engine components. Fan casings, therefore, need to be strong enough to contain errant blades and damage-tolerant to withstand the punishment of a loose blade-turned-projectile. NASA has spearheaded research into improving jet engine fan casings, ultimately discovering a cost-effective approach to manufacturing damage-tolerant fan cases that also boast significant weight reduction. In an aircraft, weight reduction translates directly into fuel burn savings, increased payload, and greater aircraft range. This technology increases safety and structural integrity; is an attractive, viable option for engine manufacturers, because of the low-cost manufacturing; and it is a practical alternative for customers, as it has the added cost saving benefits of the weight reduction.

  20. 50 CFR 85.41 - Allowable costs.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    .... Preliminary costs may include such items as feasibility surveys, engineering design, biological reconnaissance... symbols designating pumpout and dump stations, are allowable costs. (b) Grants or facilities designed to...

  1. 50 CFR 85.41 - Allowable costs.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    .... Preliminary costs may include such items as feasibility surveys, engineering design, biological reconnaissance... symbols designating pumpout and dump stations, are allowable costs. (b) Grants or facilities designed to...

  2. 50 CFR 85.41 - Allowable costs.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    .... Preliminary costs may include such items as feasibility surveys, engineering design, biological reconnaissance... symbols designating pumpout and dump stations, are allowable costs. (b) Grants or facilities designed to...

  3. 50 CFR 85.41 - Allowable costs.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    .... Preliminary costs may include such items as feasibility surveys, engineering design, biological reconnaissance... symbols designating pumpout and dump stations, are allowable costs. (b) Grants or facilities designed to...

  4. 50 CFR 85.41 - Allowable costs.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    .... Preliminary costs may include such items as feasibility surveys, engineering design, biological reconnaissance... symbols designating pumpout and dump stations, are allowable costs. (b) Grants or facilities designed to...

  5. An air-liquid contactor for large-scale capture of CO2 from air.

    PubMed

    Holmes, Geoffrey; Keith, David W

    2012-09-13

    We present a conceptually simple method for optimizing the design of a gas-liquid contactor for capture of carbon dioxide from ambient air, or 'air capture'. We apply the method to a slab geometry contactor that uses components, design and fabrication methods derived from cooling towers. We use mass transfer data appropriate for capture using a strong NaOH solution, combined with engineering and cost data derived from engineering studies performed by Carbon Engineering Ltd, and find that the total costs for air contacting alone-no regeneration-can be of the order of $60 per tonne CO(2). We analyse the reasons why our cost estimate diverges from that of other recent reports and conclude that the divergence arises from fundamental design choices rather than from differences in costing methodology. Finally, we review the technology risks and conclude that they can be readily addressed by prototype testing.

  6. Forecasting Construction Cost Index based on visibility graph: A network approach

    NASA Astrophysics Data System (ADS)

    Zhang, Rong; Ashuri, Baabak; Shyr, Yu; Deng, Yong

    2018-03-01

    Engineering News-Record (ENR), a professional magazine in the field of global construction engineering, publishes Construction Cost Index (CCI) every month. Cost estimators and contractors assess projects, arrange budgets and prepare bids by forecasting CCI. However, fluctuations and uncertainties of CCI cause irrational estimations now and then. This paper aims at achieving more accurate predictions of CCI based on a network approach in which time series is firstly converted into a visibility graph and future values are forecasted relied on link prediction. According to the experimental results, the proposed method shows satisfactory performance since the error measures are acceptable. Compared with other methods, the proposed method is easier to implement and is able to forecast CCI with less errors. It is convinced that the proposed method is efficient to provide considerably accurate CCI predictions, which will make contributions to the construction engineering by assisting individuals and organizations in reducing costs and making project schedules.

  7. BMP COST ANALYSIS FOR SOURCE WATER PROTECTION

    EPA Science Inventory

    Cost equations are developed to estimate capital, and operations and maintenance (O&M) costs for commonly used best management practices (BMPs). Total BMP volume and/or surface area is used to predict these costs. Engineering News Record (ENR) construction cost index was used t...

  8. Integration of safety engineering into a cost optimized development program.

    NASA Technical Reports Server (NTRS)

    Ball, L. W.

    1972-01-01

    A six-segment management model is presented, each segment of which represents a major area in a new product development program. The first segment of the model covers integration of specialist engineers into 'systems requirement definition' or the system engineering documentation process. The second covers preparation of five basic types of 'development program plans.' The third segment covers integration of system requirements, scheduling, and funding of specialist engineering activities into 'work breakdown structures,' 'cost accounts,' and 'work packages.' The fourth covers 'requirement communication' by line organizations. The fifth covers 'performance measurement' based on work package data. The sixth covers 'baseline requirements achievement tracking.'

  9. A Programmatic and Engineering Approach to the Development of a Nuclear Thermal Rocket for Space Exploration

    NASA Technical Reports Server (NTRS)

    Bordelon, Wayne J., Jr.; Ballard, Rick O.; Gerrish, Harold P., Jr.

    2006-01-01

    With the announcement of the Vision for Space Exploration on January 14, 2004, there has been a renewed interest in nuclear thermal propulsion. Nuclear thermal propulsion is a leading candidate for in-space propulsion for human Mars missions; however, the cost to develop a nuclear thermal rocket engine system is uncertain. Key to determining the engine development cost will be the engine requirements, the technology used in the development and the development approach. The engine requirements and technology selection have not been defined and are awaiting definition of the Mars architecture and vehicle definitions. The paper discusses an engine development approach in light of top-level strategic questions and considerations for nuclear thermal propulsion and provides a suggested approach based on work conducted at the NASA Marshall Space Flight Center to support planning and requirements for the Prometheus Power and Propulsion Office. This work is intended to help support the development of a comprehensive strategy for nuclear thermal propulsion, to help reduce the uncertainty in the development cost estimate, and to help assess the potential value of and need for nuclear thermal propulsion for a human Mars mission.

  10. Study of Advanced Propulsion Systems for Small Transport Aircraft Technology (STAT) Program

    NASA Technical Reports Server (NTRS)

    Baerst, C. F.; Heldenbrand, R. W.; Rowse, J. H.

    1981-01-01

    Definitions of takeoff gross weight, performance, and direct operating cost for both a 30 and 50 passenger airplane were established. The results indicate that a potential direct operating cost benefit, resulting from advanced technologies, of approximately 20 percent would be achieved for the 1990 engines. Of the numerous design features that were evaluated, only maintenance-related items contributed to a significant decrease in direct operating cost. Recommendations are made to continue research and technology programs for advanced component and engine development.

  11. U.S. Army Corps of Engineers: Building Overhead Costs into Projects and Customers’ Views on Information Provided

    DTIC Science & Technology

    2013-06-01

    U.S. ARMY CORPS OF ENGINEERS Building Overhead Costs into Projects and Customers ’ Views on Information Provided...Overhead Costs into Projects and Customers ’ Views on Information Provided 5a. CONTRACT NUMBER 5b. GRANT NUMBER 5c. PROGRAM ELEMENT NUMBER 6. AUTHOR(S...and Customers ’ Views on Information Provided Why GAO Did This Study The Corps spends billions of dollars annually on projects in its Civil Works

  12. The National Shipbuilding Research Program. Application of Industrial Engineering Techniques to Reduce Workers’ Compensation and Environmental Costs - Deliverable G

    DTIC Science & Technology

    1999-10-01

    to prove that we can operate as efficiently as other nations where worker safety and health are emphasized as highly. With the support of government...N8-96-3 Application of Industrial Engineering Techniques to Reduce Workers ’ Compensation and Environmental Costs - Deliverable G U.S. DEPARTMENT OF THE...Techniques to Reduce Workers ’ Compensation and Environmental Costs - Deliverable G 5a. CONTRACT NUMBER 5b. GRANT NUMBER 5c. PROGRAM ELEMENT NUMBER 6

  13. U.S. Army Corps of Engineers Manpower Information System: An Integrated Approach to Manpower Management

    DTIC Science & Technology

    1994-04-01

    engineering and con- struction management services for both military and civil works programs. In FY93, the cost of those programs exceeded $10 billion and...A related issue was to explore the USACE costs , benefits, and barriers to implementing a single Class VI system software package for both the military...provide information in useful ways, track utilization information, I A Class HI system is defined in AR 25-3. It is a system whose total program costs are

  14. Component Cost Reduction by Value Engineering: A Case Study

    NASA Astrophysics Data System (ADS)

    Kalluri, Vinayak; Kodali, Rambabu

    2017-04-01

    The concept value engineering (VE) acts to increase the value of a product through the improvement in existent functions without increasing their costs. In other words, VE is a function oriented, systematic team approach study to provide value in a product, system or service. The authors systematically explore VE through the six step framework proposed by SAVE and a case study is presented to address the concern of reduction in cost without compromising the function of a hydraulic steering cylinder through the aforementioned VE framework.

  15. Advanced Reciprocating Engine Systems (ARES): Raising the Bar on Engine Technology with Increased Efficiency and Reduced Emissions, at Attractive Costs

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    None

    This is a fact sheet on the U.S. Department of Energy's (DOE) Advanced Reciprocating Engine Systems program (ARES), which is designed to promote separate, but parallel engine development between the major stationary, gaseous fueled engine manufacturers in the United States.

  16. Atlas Centaur Rocket With Reusable Booster Engines

    NASA Technical Reports Server (NTRS)

    Martin, James A.

    1993-01-01

    Proposed modification of Atlas Centaur enables reuse of booster engines. Includes replacement of current booster engines with engine of new design in which hydrogen used for both cooling and generation of power. Use of hydrogen in new engine eliminates coking and clogging and improves performance significantly. Primary advantages: reduction of cost; increased reliability; and increased payload.

  17. Automotive Stirling Engine Development Program

    NASA Technical Reports Server (NTRS)

    Nightingale, N.; Ernst, W.; Richey, A.; Simetkosky, M.; Antonelli, M. (Editor)

    1982-01-01

    Activities performed on Mod I engine testing and test results; the manufacture, assembly, and test of a Mod I engine in the United States; design initiation of the Mod I-A engine system; transient performance testing; Stirling reference engine manufacturing and reduced size studies; components and subsystems; and the study and test of low cost alloys are summarized.

  18. 18 CFR 4.3 - Report on project cost.

    Code of Federal Regulations, 2012 CFR

    2012-04-01

    ... 18 Conservation of Power and Water Resources 1 2012-04-01 2012-04-01 false Report on project cost... OF PROJECT COSTS Determination of Cost of Projects Constructed Under License § 4.3 Report on project..., cost records, engineering reports, and other records supporting the project's original cost. The audit...

  19. 18 CFR 4.3 - Report on project cost.

    Code of Federal Regulations, 2013 CFR

    2013-04-01

    ... 18 Conservation of Power and Water Resources 1 2013-04-01 2013-04-01 false Report on project cost... OF PROJECT COSTS Determination of Cost of Projects Constructed Under License § 4.3 Report on project..., cost records, engineering reports, and other records supporting the project's original cost. The audit...

  20. 18 CFR 4.3 - Report on project cost.

    Code of Federal Regulations, 2014 CFR

    2014-04-01

    ... 18 Conservation of Power and Water Resources 1 2014-04-01 2014-04-01 false Report on project cost... OF PROJECT COSTS Determination of Cost of Projects Constructed Under License § 4.3 Report on project..., cost records, engineering reports, and other records supporting the project's original cost. The audit...

  1. 18 CFR 4.3 - Report on project cost.

    Code of Federal Regulations, 2011 CFR

    2011-04-01

    ... 18 Conservation of Power and Water Resources 1 2011-04-01 2011-04-01 false Report on project cost... OF PROJECT COSTS Determination of Cost of Projects Constructed Under License § 4.3 Report on project..., cost records, engineering reports, and other records supporting the project's original cost. The audit...

  2. Proposed Reliability/Cost Model

    NASA Technical Reports Server (NTRS)

    Delionback, L. M.

    1982-01-01

    New technique estimates cost of improvement in reliability for complex system. Model format/approach is dependent upon use of subsystem cost-estimating relationships (CER's) in devising cost-effective policy. Proposed methodology should have application in broad range of engineering management decisions.

  3. 47 CFR 27.1164 - The cost-sharing formula.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... control equipment; engineering costs (design/path survey); installation; systems testing; FCC filing costs... plant upgrade (if required); electrical grounding systems; Heating Ventilation and Air Conditioning (HVAC) (if required); alternate transport equipment; and leased facilities. Increased recurring costs...

  4. 47 CFR 27.1164 - The cost-sharing formula.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... control equipment; engineering costs (design/path survey); installation; systems testing; FCC filing costs... plant upgrade (if required); electrical grounding systems; Heating Ventilation and Air Conditioning (HVAC) (if required); alternate transport equipment; and leased facilities. Increased recurring costs...

  5. 48 CFR 52.248-1 - Value Engineering.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... contract requirement and the proposed requirement, the comparative advantages and disadvantages of each, a... not rewardable under performance, design-to-cost (production unit cost, operating and support costs...

  6. 48 CFR 52.248-1 - Value Engineering.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... contract requirement and the proposed requirement, the comparative advantages and disadvantages of each, a... not rewardable under performance, design-to-cost (production unit cost, operating and support costs...

  7. 48 CFR 52.248-1 - Value Engineering.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... contract requirement and the proposed requirement, the comparative advantages and disadvantages of each, a... not rewardable under performance, design-to-cost (production unit cost, operating and support costs...

  8. 48 CFR 52.248-1 - Value Engineering.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... contract requirement and the proposed requirement, the comparative advantages and disadvantages of each, a... not rewardable under performance, design-to-cost (production unit cost, operating and support costs...

  9. 48 CFR 52.248-1 - Value Engineering.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... contract requirement and the proposed requirement, the comparative advantages and disadvantages of each, a... not rewardable under performance, design-to-cost (production unit cost, operating and support costs...

  10. Repository Planning, Design, and Engineering: Part II-Equipment and Costing.

    PubMed

    Baird, Phillip M; Gunter, Elaine W

    2016-08-01

    Part II of this article discusses and provides guidance on the equipment and systems necessary to operate a repository. The various types of storage equipment and monitoring and support systems are presented in detail. While the material focuses on the large repository, the requirements for a small-scale startup are also presented. Cost estimates and a cost model for establishing a repository are presented. The cost model presents an expected range of acquisition costs for the large capital items in developing a repository. A range of 5,000-7,000 ft(2) constructed has been assumed, with 50 frozen storage units, to reflect a successful operation with growth potential. No design or engineering costs, permit or regulatory costs, or smaller items such as the computers, software, furniture, phones, and barcode readers required for operations have been included.

  11. Construction Performance Optimization toward Green Building Premium Cost Based on Greenship Rating Tools Assessment with Value Engineering Method

    NASA Astrophysics Data System (ADS)

    Latief, Yusuf; Berawi, Mohammed Ali; Basten, Van; Riswanto; Budiman, Rachmat

    2017-07-01

    Green building concept becomes important in current building life cycle to mitigate environment issues. The purpose of this paper is to optimize building construction performance towards green building premium cost, achieving green building rating tools with optimizing life cycle cost. Therefore, this study helps building stakeholder determining building fixture to achieve green building certification target. Empirically the paper collects data of green building in the Indonesian construction industry such as green building fixture, initial cost, operational and maintenance cost, and certification score achievement. After that, using value engineering method optimized green building fixture based on building function and cost aspects. Findings indicate that construction performance optimization affected green building achievement with increasing energy and water efficiency factors and life cycle cost effectively especially chosen green building fixture.

  12. Advanced Earth-to-orbit propulsion technology program overview: Impact of civil space technology initiative

    NASA Technical Reports Server (NTRS)

    Stephenson, Frank W., Jr.

    1988-01-01

    The NASA Earth-to-Orbit (ETO) Propulsion Technology Program is dedicated to advancing rocket engine technologies for the development of fully reusable engine systems that will enable space transportation systems to achieve low cost, routine access to space. The program addresses technology advancements in the areas of engine life extension/prediction, performance enhancements, reduced ground operations costs, and in-flight fault tolerant engine operations. The primary objective is to acquire increased knowledge and understanding of rocket engine chemical and physical processes in order to evolve more realistic analytical simulations of engine internal environments, to derive more accurate predictions of steady and unsteady loads, and using improved structural analyses, to more accurately predict component life and performance, and finally to identify and verify more durable advanced design concepts. In addition, efforts were focused on engine diagnostic needs and advances that would allow integrated health monitoring systems to be developed for enhanced maintainability, automated servicing, inspection, and checkout, and ultimately, in-flight fault tolerant engine operations.

  13. A simplified fuel control approach for low cost aircraft gas turbines

    NASA Technical Reports Server (NTRS)

    Gold, H.

    1973-01-01

    Reduction in the complexity of gas turbine fuel controls without loss of control accuracy, reliability, or effectiveness as a method for reducing engine costs is discussed. A description and analysis of hydromechanical approach are presented. A computer simulation of the control mechanism is given and performance of a physical model in engine test is reported.

  14. Emulation-Based Virtual Laboratories: A Low-Cost Alternative to Physical Experiments in Control Engineering Education

    ERIC Educational Resources Information Center

    Goodwin, G. C.; Medioli, A. M.; Sher, W.; Vlacic, L. B.; Welsh, J. S.

    2011-01-01

    This paper argues the case for emulation-based virtual laboratories in control engineering education. It demonstrates that such emulation experiments can give students an industrially relevant educational experience at relatively low cost. The paper also describes a particular emulation-based system that has been developed with the aim of giving…

  15. A Cost Benefit Analysis of Professional Accreditation by ABET for Baccalaureate Engineering Degree Programs

    ERIC Educational Resources Information Center

    Yuen, Faye Sui Yee

    2012-01-01

    Tightening fiscal budgets and the growing emphasis on accountability has created a need to assess the value that programmatic accreditation provides. For degrees in engineering, ABET is the only organization recognized in the U.S. responsible for the programmatic accreditation. This research examines the costs and benefits of ABET accreditation to…

  16. Cost Effective Repair Techniques for Turbine Airfoils. Volume I

    DTIC Science & Technology

    1978-11-01

    Turbine blades and vanes in current engines are subjected to the most hostile environment...payoff potential in turbine vanes / blades . The criteria used included: • Incidence of damage - Scrapped or damaged turbine airfoils at the ALC centers...Corporate Author: GENERAL ELECTRIC CO CINCINNATI OHIO AIRCRAFT ENGINE GROUP Unclassified Title: (U) Cost Effective Repair Techniques for Turbine

  17. Comparison of Design-Build to Design-Bid Build as a Project Delivery Method

    DTIC Science & Technology

    2001-12-01

    Time growth is generally coupled with cost growth, and this rule holds true when looking at the cost growth on the DB and DBB projects and similarly...to Remember,” The Military Engineer, No. 609, pp. 25-26, January-February 2001. 4. Crammer , Mark, “Design-Build in the Corps of Engineers, A work

  18. Building Models to Better Understand the Importance of Cost versus Safety in Engineering

    ERIC Educational Resources Information Center

    Sumrall, William; Mott, Michael

    2010-01-01

    While some disasters involving engineered structures are due to events in nature (e.g., tornadoes, hurricanes, earthquakes), others may be caused by inadequate materials, design flaws, and poor maintenance. These catastrophes result in the loss of human lives and cost billions of dollars. In the set of lessons described here, students design a…

  19. Investigation into the cost-effectiveness of using consultants versus in-house staff in providing professional engineering services for Louisiana's Department of Transportation and Development : technical assistance report.

    DOT National Transportation Integrated Search

    1995-06-01

    The objective of the work reported in this document is to: (i) review past studies of the cost-effectiveness of using consultants versus in-house staff in conducting professional engineering services for state Departments of Transportation, (ii) repo...

  20. Integrated thermal and energy management of plug-in hybrid electric vehicles

    NASA Astrophysics Data System (ADS)

    Shams-Zahraei, Mojtaba; Kouzani, Abbas Z.; Kutter, Steffen; Bäker, Bernard

    2012-10-01

    In plug-in hybrid electric vehicles (PHEVs), the engine temperature declines due to reduced engine load and extended engine off period. It is proven that the engine efficiency and emissions depend on the engine temperature. Also, temperature influences the vehicle air-conditioner and the cabin heater loads. Particularly, while the engine is cold, the power demand of the cabin heater needs to be provided by the batteries instead of the waste heat of engine coolant. The existing energy management strategies (EMS) of PHEVs focus on the improvement of fuel efficiency based on hot engine characteristics neglecting the effect of temperature on the engine performance and the vehicle power demand. This paper presents a new EMS incorporating an engine thermal management method which derives the global optimal battery charge depletion trajectories. A dynamic programming-based algorithm is developed to enforce the charge depletion boundaries, while optimizing a fuel consumption cost function by controlling the engine power. The optimal control problem formulates the cost function based on two state variables: battery charge and engine internal temperature. Simulation results demonstrate that temperature and the cabin heater/air-conditioner power demand can significantly influence the optimal solution for the EMS, and accordingly fuel efficiency and emissions of PHEVs.

  1. 48 CFR 9904.420-60 - Illustrations.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... typing its overhead cost pool. In submitting a proposal, the engineering department assigns several... established accounting practice does not charge the cost of typing directly to final cost objectives, the...

  2. Comparing NASA and ESA Cost Estimating Methods for Human Missions to Mars

    NASA Technical Reports Server (NTRS)

    Hunt, Charles D.; vanPelt, Michel O.

    2004-01-01

    To compare working methodologies between the cost engineering functions in NASA Marshall Space Flight Center (MSFC) and ESA European Space Research and Technology Centre (ESTEC), as well as to set-up cost engineering capabilities for future manned Mars projects and other studies which involve similar subsystem technologies in MSFC and ESTEC, a demonstration cost estimate exercise was organized. This exercise was a direct way of enhancing not only cooperation between agencies but also both agencies commitment to credible cost analyses. Cost engineers in MSFC and ESTEC independently prepared life-cycle cost estimates for a reference human Mars project and subsequently compared the results and estimate methods in detail. As a non-sensitive, public domain reference case for human Mars projects, the Mars Direct concept was chosen. In this paper the results of the exercise are shown; the differences and similarities in estimate methodologies, philosophies, and databases between MSFC and ESTEC, as well as the estimate results for the Mars Direct concept. The most significant differences are explained and possible estimate improvements identified. In addition, the Mars Direct plan and the extensive cost breakdown structure jointly set-up by MSFC and ESTEC for this concept are presented. It was found that NASA applied estimate models mainly based on historic Apollo and Space Shuttle cost data, taking into account the changes in technology since then. ESA used models mostly based on European satellite and launcher cost data, taking into account the higher equipment and testing standards for human space flight. Most of NASA's and ESA s estimates for the Mars Direct case are comparable, but there are some important, consistent differences in the estimates for: 1) Large Structures and Thermal Control subsystems; 2) System Level Management, Engineering, Product Assurance and Assembly, Integration and Test/Verification activities; 3) Mission Control; 4) Space Agency Program Level activities.

  3. Preliminary engineering cost trends for highway projects.

    DOT National Transportation Integrated Search

    2011-10-21

    Preliminary engineering (PE) for a highway project encompasses two efforts: planning to minimize the physical, social, and human environmental impacts of projects and engineering design to deliver the best alternative. PE efforts begin years in advan...

  4. Engine Development Design Margins Briefing Charts

    NASA Technical Reports Server (NTRS)

    Bentz, Chuck

    2006-01-01

    New engines experience durability problems after entering service. The most prevalent and costly is the hot section, particularly the high-pressure turbine. The origin of durability problems can be traced back to: 1) the basic aero-mechanical design systems, assumptions, and design margins used by the engine designers, 2) the available materials systems, and 3) to a large extent, aggressive marketing in a highly competitive environment that pushes engine components beyond the demonstrated capability of the basic technology available for the hardware designs. Unfortunately the user must operate the engine in the service environment in order to learn the actual thrust loading and the time at max effort take-off conditions used in service are needed to determine the hot section life. Several hundred thousand hours of operational service will be required before the demonstrated reliability of a fleet of engines or the design deficiencies of the engine hot section parts can be determined. Also, it may take three to four engine shop visits for heavy maintenance on the gas path hardware to establish cost effective build standards. Spare parts drive the oerator's engine maintenance costs but spare parts also makes lots of money for the engine manufacturer during the service life of an engine. Unless competition prevails for follow-on engine buys, there is really no motivation for an OEM to spend internal money to improve parts durability and reduce earnings derived from a lucrative spare parts business. If the hot section life is below design goals or promised values, the OEM migh argue that the engine is being operated beyond its basic design intent. On the other hand, the airframer and the operator will continue to remind the OEM that his engine was selected based on a lot of promises to deliver spec thrust with little impact on engine service life if higher thrust is used intermittently. In the end, a standoff prevails and nothing gets fixed. This briefing will propose ways to hold competing engine manufacturers more accountable for engine hot section design margins during the entire Engine Development process as well as provide tools to assess the design temperature margins in the hot section parts of Service Engines.

  5. Integration of Mahalanobis-Taguchi system and traditional cost accounting for remanufacturing crankshaft

    NASA Astrophysics Data System (ADS)

    Abu, M. Y.; Norizan, N. S.; Rahman, M. S. Abd

    2018-04-01

    Remanufacturing is a sustainability strategic planning which transforming the end of life product to as new performance with their warranty is same or better than the original product. In order to quantify the advantages of this strategy, all the processes must implement the optimization to reach the ultimate goal and reduce the waste generated. The aim of this work is to evaluate the criticality of parameters on the end of life crankshaft based on Taguchi’s orthogonal array. Then, estimate the cost using traditional cost accounting by considering the critical parameters. By implementing the optimization, the remanufacturer obviously produced lower cost and waste during production with higher potential to gain the profit. Mahalanobis-Taguchi System was proven as a powerful method of optimization that revealed the criticality of parameters. When subjected the method to the MAN engine model, there was 5 out of 6 crankpins were critical which need for grinding process while no changes happened to the Caterpillar engine model. Meanwhile, the cost per unit for MAN engine model was changed from MYR1401.29 to RM1251.29 while for Caterpillar engine model have no changes due to the no changes on criticality of parameters consideration. Therefore, by integrating the optimization and costing through remanufacturing process, a better decision can be achieved after observing the potential profit will be gained. The significant of output demonstrated through promoting sustainability by reducing re-melting process of damaged parts to ensure consistent benefit of return cores.

  6. Energy efficient engine component development and integration program

    NASA Technical Reports Server (NTRS)

    1980-01-01

    The design of an energy efficient commercial turbofan engine is examined with emphasis on lower fuel consumption and operating costs. Propulsion system performance, emission standards, and noise reduction are also investigated. A detailed design analysis of the engine/aircraft configuration, engine components, and core engine is presented along with an evaluation of the technology and testing involved.

  7. Gas-Centered Swirl Coaxial Liquid Injector Evaluations

    NASA Technical Reports Server (NTRS)

    Cohn, A. K.; Strakey, P. A.; Talley, D. G.

    2005-01-01

    Development of Liquid Rocket Engines is expensive. Extensive testing at large scales usually required. In order to verify engine lifetime, large number of tests required. Limited Resources available for development. Sub-scale cold-flow and hot-fire testing is extremely cost effective. Could be a necessary (but not sufficient) condition for long engine lifetime. Reduces overall costs and risk of large scale testing. Goal: Determine knowledge that can be gained from sub-scale cold-flow and hot-fire evaluations of LRE injectors. Determine relationships between cold-flow and hot-fire data.

  8. Fabrication of Composite Combustion Chamber/Nozzle for Fastrac Engine

    NASA Technical Reports Server (NTRS)

    Lawerence, T.; Beshears, R.; Burlingame, S.; Peters, W.; Prince, M.; Suits, M.; Tillery, S.; Burns, L.; Kovach, M.; Roberts, K.; hide

    2000-01-01

    The Fastrac Engine developed by the Marshall Space Flight Center for the X-34 vehicle began as a low cost engine development program for a small booster system. One of the key components to reducing the engine cost was the development of an inexpensive combustion chamber/nozzle. Fabrication of a regeneratively cooled thrust chamber and nozzle was considered too expensive and time consuming. In looking for an alternate design concept, the Space Shuttle's Reusable Solid Rocket Motor Project provided an extensive background with ablative composite materials in a combustion environment. An integral combustion chamber/nozzle was designed and fabricated with a silica/phenolic ablative liner and a carbon/epoxy structural overwrap. This paper describes the fabrication process and developmental hurdles overcome for the Fastrac engine one-piece composite combustion chamber/nozzle.

  9. Fabrication of Composite Combustion Chamber/Nozzle for Fastrac Engine

    NASA Technical Reports Server (NTRS)

    Lawrence, T.; Beshears, R.; Burlingame, S.; Peters, W.; Prince, M.; Suits, M.; Tillery, S.; Burns, L.; Kovach, M.; Roberts, K.

    2001-01-01

    The Fastrac Engine developed by the Marshall Space Flight Center for the X-34 vehicle began as a low cost engine development program for a small booster system. One of the key components to reducing the engine cost was the development of an inexpensive combustion chamber/nozzle. Fabrication of a regeneratively cooled thrust chamber and nozzle was considered too expensive and time consuming. In looking for an alternate design concept, the Space Shuttle's Reusable Solid Rocket Motor Project provided an extensive background with ablative composite materials in a combustion environment. An integral combustion chamber/nozzle was designed and fabricated with a silica/phenolic ablative liner and a carbon/epoxy structural overwrap. This paper describes the fabrication process and developmental hurdles overcome for the Fastrac engine one-piece composite combustion chamber/nozzle.

  10. 40 CFR 610.14 - Payment of program costs.

    Code of Federal Regulations, 2012 CFR

    2012-07-01

    ... from the costs of testing a device, EPA shall be responsible for costs of formulating its engineering... 40 Protection of Environment 31 2012-07-01 2012-07-01 false Payment of program costs. 610.14... program costs. (a) All costs incurred in an evaluation program initiated at the request of the FTC or at...

  11. 40 CFR 610.14 - Payment of program costs.

    Code of Federal Regulations, 2011 CFR

    2011-07-01

    ... from the costs of testing a device, EPA shall be responsible for costs of formulating its engineering... 40 Protection of Environment 30 2011-07-01 2011-07-01 false Payment of program costs. 610.14... program costs. (a) All costs incurred in an evaluation program initiated at the request of the FTC or at...

  12. 40 CFR 610.14 - Payment of program costs.

    Code of Federal Regulations, 2013 CFR

    2013-07-01

    ... from the costs of testing a device, EPA shall be responsible for costs of formulating its engineering... 40 Protection of Environment 31 2013-07-01 2013-07-01 false Payment of program costs. 610.14... program costs. (a) All costs incurred in an evaluation program initiated at the request of the FTC or at...

  13. 40 CFR 610.14 - Payment of program costs.

    Code of Federal Regulations, 2014 CFR

    2014-07-01

    ... from the costs of testing a device, EPA shall be responsible for costs of formulating its engineering... 40 Protection of Environment 30 2014-07-01 2014-07-01 false Payment of program costs. 610.14... program costs. (a) All costs incurred in an evaluation program initiated at the request of the FTC or at...

  14. KSC Construction Cost Index

    NASA Technical Reports Server (NTRS)

    Brown, J. A.

    1983-01-01

    Kennedy Space Center cost Index aids in conceptual design cost estimates. Report discusses development of KSC Cost Index since January 1974. Index since January 1974. Index provides management, design engineers, and estimators an up-to-data reference for local labor and material process. Also provides mount and rate of change in these costs used to predict future construction costs.

  15. Orbit Transfer Vehicle (OTV) engine, phase A study. Volume 2: Study

    NASA Technical Reports Server (NTRS)

    Mellish, J. A.

    1979-01-01

    The hydrogen oxygen engine used in the orbiter transfer vehicle is described. The engine design is analyzed and minimum engine performance and man rating requirements are discussed. Reliability and safety analysis test results are presented and payload, risk and cost, and engine installation parameters are defined. Engine tests were performed including performance analysis, structural analysis, thermal analysis, turbomachinery analysis, controls analysis, and cycle analysis.

  16. The performance of solar thermal electric power systems employing small heat engines

    NASA Technical Reports Server (NTRS)

    Pons, R. L.

    1980-01-01

    The paper presents a comparative analysis of small (10 to 100 KWe) heat engines for use with a solar thermal electric system employing the point-focusing, distributed receiver (PF-DR) concept. Stirling, Brayton, and Rankine cycle engines are evaluated for a nominal overall system power level of 1 MWe, although the concept is applicable to power levels up to at least 10 MWe. Multiple concentrators are electrically connected to achieve the desired plant output. Best performance is achieved with the Stirling engine, resulting in a system Levelized Busbar Energy Cost of just under 50 mills/kWH and a Capital Cost of $900/kW, based on the use of mass-produced components. Brayton and Rankine engines show somewhat less performance but are viable alternatives with particular benefits for special applications. All three engines show excellent performance for the small community application.

  17. 33 CFR 263.15 - Program policies.

    Code of Federal Regulations, 2013 CFR

    2013-07-01

    ... undertaken, without regard to time. (b) Applicability of costs to Federal and non-Federal shares. Unless... Corps of Engineers costs for investigations, design, and construction (including costs of supervision... costs of investigations, planning, design and construction, to include those incurred prior to...

  18. 33 CFR 263.15 - Program policies.

    Code of Federal Regulations, 2012 CFR

    2012-07-01

    ... undertaken, without regard to time. (b) Applicability of costs to Federal and non-Federal shares. Unless... Corps of Engineers costs for investigations, design, and construction (including costs of supervision... costs of investigations, planning, design and construction, to include those incurred prior to...

  19. 48 CFR 31.105 - Construction and architect-engineer contracts.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ..., include unallowable interest costs, or use improper cost of money rates or computations. Contracting... contracts, including cost-reimbursement subcontracts thereunder; (2) Negotiating indirect cost rates; (3... appropriate they serve to express the parties' understanding and avoid possible subsequent disputes or...

  20. 18 CFR 367.52 - Overhead construction costs.

    Code of Federal Regulations, 2010 CFR

    2010-04-01

    ... ACT Service Company Property Instructions § 367.52 Overhead construction costs. (a) All overhead construction costs, such as engineering, supervision, general office salaries and expenses, construction... costs. 367.52 Section 367.52 Conservation of Power and Water Resources FEDERAL ENERGY REGULATORY...

  1. 18 CFR 367.52 - Overhead construction costs.

    Code of Federal Regulations, 2012 CFR

    2012-04-01

    ... ACT Service Company Property Instructions § 367.52 Overhead construction costs. (a) All overhead construction costs, such as engineering, supervision, general office salaries and expenses, construction... costs. 367.52 Section 367.52 Conservation of Power and Water Resources FEDERAL ENERGY REGULATORY...

  2. Reducing Operating Costs by Optimizing Space in Facilities

    DTIC Science & Technology

    2012-03-01

    Base level 5 engineering units will provide facility floor plans, furniture layouts, and staffing documentation as necessary. One obstacle...due to the quantity and diverse locations. Base level engineering units provided facility floor plans, furniture layouts, and staffing documentation... furniture purchases and placement 5. Follow a quality systematic process in all decisions The per person costs can be better understood with a real

  3. Using Multi-Robot Systems for Engineering Education: Teaching and Outreach with Large Numbers of an Advanced, Low-Cost Robot

    ERIC Educational Resources Information Center

    McLurkin, J.; Rykowski, J.; John, M.; Kaseman, Q.; Lynch, A. J.

    2013-01-01

    This paper describes the experiences of using an advanced, low-cost robot in science, technology, engineering, and mathematics (STEM) education. It presents three innovations: It is a powerful, cheap, robust, and small advanced personal robot; it forms the foundation of a problem-based learning curriculum; and it enables a novel multi-robot…

  4. Low-Cost Approach to the Design and Fabrication of a LOX/RP-1 Injector

    NASA Technical Reports Server (NTRS)

    Shadoan, Michael D.; Sparks, Dave L.; Turner, James E. (Technical Monitor)

    2000-01-01

    NASA Marshall Space Flight Center (MSFC) has designed, built, and is currently testing Fastrac, a liquid oxygen (LOX)/RP-1 fueled 60K-lb thrust class rocket engine. One facet of Fastrac, which makes it unique is that it is the first large-scale engine designed and developed in accordance with the Agency's mandated "faster, better, cheaper" (FBC) program policy. The engine was developed under the auspices of MSFC's Low Cost Boost Technology office. Development work for the main injector actually began in 1993 in subscale form. In 1996, work began on the full-scale unit approximately 1 year prior to initiation of the engine development program. In order to achieve the value goals established by the FBC policy, a review of traditional design practices was necessary. This internal reevaluation would ultimately challenge more conventional methods of material selection. design process, and fabrication techniques. The effort was highly successful. This "new way" of thinking has resulted in an innovative injector design, one with reduced complexity and significantly lower cost. Application of lessons learned during this effort to new or existing designs can have a similar effect on costs and future program successes.

  5. 7 CFR 1709.110 - Use of grant funds.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... help establish the financial and technical sustainability of the project, provided that such costs do not exceed more than 10 percent of total project costs; (2) Design and engineering costs, including...

  6. 33 CFR 214.11 - Costs.

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... 33 Navigation and Navigable Waters 3 2010-07-01 2010-07-01 false Costs. 214.11 Section 214.11... SUPPLIES OF DRINKING WATER § 214.11 Costs. Costs incurred by the Corps of Engineers in furnishing emergency... by the community generally will not be required. Costs of necessary measures for the decontamination...

  7. 48 CFR 43.203 - Change order accounting procedures.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ...., engineering costs and costs of obsolete or reperformed work). (2) Costs of added distinct work caused by the...) Contractors' accounting systems are seldom designed to segregate the costs of performing changed work... possible need to revise their accounting procedures to comply with the cost segregation requirements of the...

  8. 48 CFR 43.203 - Change order accounting procedures.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ...., engineering costs and costs of obsolete or reperformed work). (2) Costs of added distinct work caused by the...) Contractors' accounting systems are seldom designed to segregate the costs of performing changed work... possible need to revise their accounting procedures to comply with the cost segregation requirements of the...

  9. 48 CFR 43.203 - Change order accounting procedures.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ...., engineering costs and costs of obsolete or reperformed work). (2) Costs of added distinct work caused by the...) Contractors' accounting systems are seldom designed to segregate the costs of performing changed work... possible need to revise their accounting procedures to comply with the cost segregation requirements of the...

  10. 48 CFR 43.203 - Change order accounting procedures.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ...., engineering costs and costs of obsolete or reperformed work). (2) Costs of added distinct work caused by the...) Contractors' accounting systems are seldom designed to segregate the costs of performing changed work... possible need to revise their accounting procedures to comply with the cost segregation requirements of the...

  11. 47 CFR 27.1180 - The cost-sharing formula.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... § 27.1180 The cost-sharing formula. (a) An AWS licensee that relocates a BRS system with which it... forth in paragraph (b) of this section. (b) C is the actual cost of relocating the system, and includes... equipment; engineering costs (design/path survey); installation; systems testing; FCC filing costs; site...

  12. Engine Company Evaluation of Feasibility of Aircraft Retrofit Water-Injected Turbomachines

    NASA Technical Reports Server (NTRS)

    Becker, Arthur

    2006-01-01

    This study supports the NASA Glenn Research Center and the U.S. Air Force Research Laboratory in their efforts to evaluate the effect of water injection on aircraft engine performance and emissions. In this study, water is only injected during the takeoff and initial climb phase of a flight. There is no water injection during engine start or ground operations, nor during climb, cruise, descent, or landing. This study determined the maintenance benefit of water injection during takeoff and initial climb and evaluated the feasibility of retrofitting a current production engine, the PW4062 (Pratt & Whitney, East Hartford, CT), with a water injection system. Predicted NO(x) emissions based on a 1:1 water-tofuel ratio are likely to be reduced between 30 to 60 percent in Environmental Protection Agency parameter (EPAP). The maintenance cost benefit for an idealized combustor water injection system installed on a PW4062 engine in a Boeing 747-400ER aircraft (The Boeing Company, Chicago, IL) is computed to be $22 per engine flight hour (EFH). Adding water injection as a retrofit kit would cost up to $375,000 per engine because of the required modifications to the fuel system and addition of the water supply system. There would also be significant nonrecurring costs associated with the development and certification of the system that may drive the system price beyond affordability.

  13. Expanded study of feasibility of measuring in-flight 747/JT9D loads, performance, clearance, and thermal data

    NASA Technical Reports Server (NTRS)

    Sallee, G. P.; Martin, R. L.

    1980-01-01

    The JT9D jet engine exhibits a TSFC loss of about 1 percent in the initial 50 flight cycles of a new engine. These early losses are caused by seal-wear induced opening of running clearances in the engine gas path. The causes of this seal wear have been identified as flight induced loads which deflect the engine cases and rotors, causing the rotating blades to rub against the seal surfaces, producing permanent clearance changes. The real level of flight loads encountered during airplane acceptance testing and revenue service and the engine's response in the dynamic flight environment were investigated. The feasibility of direct measurement of these flight loads and their effects by concurrent measurement of 747/JT9D propulsion system aerodynamic and inertia loads and the critical engine clearance and performance changes during 747 flight and ground operations was evaluated. A number of technical options were examined in relation to the total estimated program cost to facilitate selection of the most cost effective option. It is concluded that a flight test program meeting the overall objective of determining the levels of aerodynamic and inertia load levels to which the engine is exposed during the initial flight acceptance test and normal flight maneuvers is feasible and desirable. A specific recommended flight test program, based on the evaluation of cost effectiveness, is defined.

  14. Automotive Stirling Engine Development Program

    NASA Technical Reports Server (NTRS)

    Nightingale, N.; Ernst, W.; Richey, A.; Simetkosky, M.; Smith, G.; Antonelli, M. (Editor)

    1983-01-01

    Mod I engine testing and test results, the test of a Mod I engine in the United States, Mod I engine characterization and analysis, Mod I Transient Test Bed fuel economy, Mod I-A engine performance are discussed. Stirling engine reference engine manufacturing and reduced size studies, components and subsystems, and the study and test of low-cost casting alloys are also covered. The overall program philosophy is outlined, and data and results are presented.

  15. Advanced space engine preliminary design

    NASA Technical Reports Server (NTRS)

    Cuffe, J. P. B.; Bradie, R. E.

    1973-01-01

    A preliminary design was completed for an O2/H2, 89 kN (20,000 lb) thrust staged combustion rocket engine that has a single-bell nozzle with an overall expansion ratio of 400:1. The engine has a best estimate vacuum specific impulse of 4623.8 N-s/kg (471.5 sec) at full thrust and mixture ratio = 6.0. The engine employs gear-driven, low pressure pumps to provide low NPSH capability while individual turbine-driven, high-speed main pumps provide the system pressures required for high-chamber pressure operation. The engine design dry weight for the fixed-nozzle configuration is 206.9 kg (456.3 lb). Engine overall length is 234 cm (92.1 in.). The extendible nozzle version has a stowed length of 141.5 cm (55.7 in.). Critical technology items in the development of the engine were defined. Development program plans and their costs for development, production, operation, and flight support of the ASE were established for minimum cost and minimum time programs.

  16. Analysis of environmental factors impacting the life cycle cost analysis of conventional and fuel cell/battery-powered passenger vehicles. Final report

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    NONE

    This report presents the results of the further developments and testing of the Life Cycle Cost (LCC) Model previously developed by Engineering Systems Management, Inc. (ESM) on behalf of the U.S. Department of Energy (DOE) under contract No. DE-AC02-91CH10491. The Model incorporates specific analytical relationships and cost/performance data relevant to internal combustion engine (ICE) powered vehicles, battery powered electric vehicles (BPEVs), and fuel cell/battery-powered electric vehicles (FCEVs).

  17. Electric and hybrid vehicle environmental control subsystem study

    NASA Technical Reports Server (NTRS)

    Heitner, K. L.

    1980-01-01

    An environmental control subsystem (ECS) in electric and hybrid vehicles is studied. A combination of a combustion heater and gasoline engine (Otto cycle) driven vapor compression air conditioner is selected. The combustion heater, the small gasoline engine, and the vapor compression air conditioner are commercially available. These technologies have good cost and performance characteristics. The cost for this ECS is relatively close to the cost of current ECS's. Its effect on the vehicle's propulsion battery is minimal and the ECS size and weight do not have significant impact on the vehicle's range.

  18. Conceptual Cost Estimating

    NASA Technical Reports Server (NTRS)

    Brown, J. A.

    1983-01-01

    Kennedy Space Center data aid in efficient construction-cost managment. Report discusses development and use of NASA TR-1508, Kennedy Space Center Aerospace Construction price book for preparing conceptual budget, funding cost estimating, and preliminary cost engineering reports. Report based on actual bid prices and Government estimates.

  19. 7 CFR 1753.15 - General.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... funds, postloan architectural or engineering services shall be obtained if (1) the construction cost... TELECOMMUNICATIONS SYSTEM CONSTRUCTION POLICIES AND PROCEDURES Engineering Services § 1753.15 General. (a)(1) The standard RUS loan documents contain provisions regarding engineering and architectural services performed...

  20. 7 CFR 1753.15 - General.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... funds, postloan architectural or engineering services shall be obtained if (1) the construction cost... TELECOMMUNICATIONS SYSTEM CONSTRUCTION POLICIES AND PROCEDURES Engineering Services § 1753.15 General. (a)(1) The standard RUS loan documents contain provisions regarding engineering and architectural services performed...

  1. 7 CFR 1753.15 - General.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... funds, postloan architectural or engineering services shall be obtained if (1) the construction cost... TELECOMMUNICATIONS SYSTEM CONSTRUCTION POLICIES AND PROCEDURES Engineering Services § 1753.15 General. (a)(1) The standard RUS loan documents contain provisions regarding engineering and architectural services performed...

  2. 7 CFR 1753.15 - General.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... funds, postloan architectural or engineering services shall be obtained if (1) the construction cost... TELECOMMUNICATIONS SYSTEM CONSTRUCTION POLICIES AND PROCEDURES Engineering Services § 1753.15 General. (a)(1) The standard RUS loan documents contain provisions regarding engineering and architectural services performed...

  3. 7 CFR 1753.15 - General.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... funds, postloan architectural or engineering services shall be obtained if (1) the construction cost... TELECOMMUNICATIONS SYSTEM CONSTRUCTION POLICIES AND PROCEDURES Engineering Services § 1753.15 General. (a)(1) The standard RUS loan documents contain provisions regarding engineering and architectural services performed...

  4. Computerized systems analysis and optimization of aircraft engine performance, weight, and life cycle costs

    NASA Technical Reports Server (NTRS)

    Fishbach, L. H.

    1979-01-01

    The computational techniques utilized to determine the optimum propulsion systems for future aircraft applications and to identify system tradeoffs and technology requirements are described. The characteristics and use of the following computer codes are discussed: (1) NNEP - a very general cycle analysis code that can assemble an arbitrary matrix fans, turbines, ducts, shafts, etc., into a complete gas turbine engine and compute on- and off-design thermodynamic performance; (2) WATE - a preliminary design procedure for calculating engine weight using the component characteristics determined by NNEP; (3) POD DRG - a table look-up program to calculate wave and friction drag of nacelles; (4) LIFCYC - a computer code developed to calculate life cycle costs of engines based on the output from WATE; and (5) INSTAL - a computer code developed to calculate installation effects, inlet performance and inlet weight. Examples are given to illustrate how these computer techniques can be applied to analyze and optimize propulsion system fuel consumption, weight, and cost for representative types of aircraft and missions.

  5. Energy Efficient Engine program advanced turbofan nacelle definition study

    NASA Technical Reports Server (NTRS)

    Howe, David C.; Wynosky, T. A.

    1985-01-01

    Advanced, low drag, nacelle configurations were defined for some of the more promising propulsion systems identified in the earlier Benefit/Cost Study, to assess the benefits associated with these advanced technology nacelles and formulate programs for developing these nacelles and low volume thrust reversers/spoilers to a state of technology readiness in the early 1990's. The study results established the design feasibility of advanced technology, slim line nacelles applicable to advanced technology, high bypass ratio turbofan engines. Design feasibility was also established for two low volume thrust reverse/spoiler concepts that meet or exceed the required effectiveness for these engines. These nacelle and thrust reverse/spoiler designs were shown to be applicable in engines with takeoff thrust sizes ranging from 24,000 to 60,000 pounds. The reduced weight, drag, and cost of the advanced technology nacelle installations relative to current technology nacelles offer a mission fuel burn savings ranging from 3.0 to 4.5 percent and direct operating cost plus interest improvements from 1.6 to 2.2 percent.

  6. Open access to biomedical engineering publications.

    PubMed

    Flexman, Jennifer A

    2008-01-01

    Scientific research is disseminated within the community and to the public in part through journals. Most scientific journals, in turn, protect the manuscript through copyright and recover their costs by charging subscription fees to individuals and institutions. This revenue stream is used to support the management of the journal and, in some cases, professional activities of the sponsoring society such as the Institute of Electrical and Electronics Engineers (IEEE). For example, the IEEE Engineering in Medicine and Biology Society (EMBS) manages seven academic publications representing the various areas of biomedical engineering. New business models have been proposed to distribute journal articles free of charge, either immediately or after a delay, to enable a greater dissemination of knowledge to both the public and the scientific community. However, publication costs must be recovered and likely at a higher cost to the manuscript authors. While there is little doubt that the foundations of scientific publication will change, the specifics and implications of an open source framework must be discussed.

  7. Energetic Combustion Devices for Aerospace Propulsion and Power

    NASA Technical Reports Server (NTRS)

    Litchford, Ron J.

    2000-01-01

    Chemical reactions have long been the mainstay thermal energy source for aerospace propulsion and power. Although it is widely recognized that the intrinsic energy density limitations of chemical bonds place severe constraints on maximum realizable performance, it will likely be several years before systems based on high energy density nuclear fuels can be placed into routine service. In the mean time, efforts to develop high energy density chemicals and advanced combustion devices which can utilize such energetic fuels may yield worthwhile returns in overall system performance and cost. Current efforts in this vein are being carried out at NASA MSFC under the direction of the author in the areas of pulse detonation engine technology development and light metals combustion devices. Pulse detonation engines are touted as a low cost alternative to gas turbine engines and to conventional rocket engines, but actual performance and cost benefits have yet to be convincingly demonstrated. Light metal fueled engines also offer potential benefits in certain niche applications such as aluminum/CO2 fueled engines for endo-atmospheric Martian propulsion. Light metal fueled MHD generators also present promising opportunities with respect to electric power generation for electromagnetic launch assist. This presentation will discuss the applications potential of these concepts with respect to aero ace propulsion and power and will review the current status of the development efforts.

  8. Investigation of NO(x) Removal from Small Engine Exhaust

    NASA Technical Reports Server (NTRS)

    Akyurtlu, Ates; Akyurtlu, Jale F.

    1999-01-01

    Contribution of emissions from small engines to the air pollution is significant. Due to differences in operating conditions and economics, the pollution control systems designed for automobiles will be neither suitable nor economically feasible for use on small engines. The objective of this project was to find a catalyst for the removal of NOx from the exhaust of small engines which use a rich air to fuel ratio. The desired catalyst should be inexpensive so that the cost of the pollution control unit will be only a small fraction of the total equipment cost. The high cost of noble metals makes them too expensive for use as NOx catalyst for small engines. Catalytic reduction of NO can also be accomplished by base-metal oxide catalysts. The main disadvantage of base-metal catalysts is their deactivation by poisons and high temperatures. Requirements for the length of the life of the small engine exhaust catalysts are much less than those for automobile exhaust catalysts. Since there is no oxygen in the exhaust gases, reduction selectivity is not a problem. Also, the reducing exhaust gases might help prevent the harmful interactions of the catalyst with the support. For these reasons only the supported metal oxide catalysts were investigated in this project.

  9. Investigation of NOx Removal from Small Engine Exhaust

    NASA Technical Reports Server (NTRS)

    Akyurtlu, Ates; Akyurtlu, Jale F.

    1999-01-01

    Contribution of emissions from small engines to the air pollution is significant. Due to differences in operating conditions and economics, the pollution control systems designed for automobiles will be neither suitable nor economically feasible for use on small engines. The objective of this project was to find a catalyst for the removal of NOx from the exhaust of small engines which use a rich air to fuel ratio. The desired catalyst should be inexpensive so that the cost of the pollution control unit will be only a small fraction of the total equipment cost. The high cost of noble metals makes them too expensive for use as NOx catalyst for small engines. Catalytic reduction of Nitrogen Oxide (NO) can also be accomplished by base-metal oxide catalysts. The main disadvantage of base-metal catalysts is their deactivation by poisons and high temperatures. Requirements for the length of the life of the small engine exhaust catalysts are much less than those for automobile exhaust catalysts. Since there is no oxygen in the exhaust gases, reduction selectivity is not a problem. Also, the reducing exhaust gases might help prevent the harmful interactions of the catalyst with the support. For these reasons only the supported metal oxide catalysts were investigated in this project.

  10. A Sensitivity Study of Commercial Aircraft Engine Response for Emergency Situations

    NASA Technical Reports Server (NTRS)

    Csank, Jeffrey T.; May, Ryan D.; Litt, Jonathan S.; Guo, Ten-Huei

    2011-01-01

    This paper contains the details of a sensitivity study in which the variation in a commercial aircraft engine's outputs is observed for perturbations in its operating condition inputs or control parameters. This study seeks to determine the extent to which various controller limits can be modified to improve engine performance, while capturing the increased risk that results from the changes. In an emergency, the engine may be required to produce additional thrust, respond faster, or both, to improve the survivability of the aircraft. The objective of this paper is to propose changes to the engine controller and determine the costs and benefits of the additional capabilities produced by the engine. This study indicates that the aircraft engine is capable of producing additional thrust, but at the cost of an increased risk of an engine failure due to higher turbine temperatures and rotor speeds. The engine can also respond more quickly to transient commands, but this action reduces the remaining stall margin to possibly dangerous levels. To improve transient response in landing scenarios, a control mode known as High Speed Idle is proposed that increases the responsiveness of the engine and conserves stall margin

  11. Space Transportation Main Engine

    NASA Technical Reports Server (NTRS)

    Monk, Jan C.

    1992-01-01

    The topics are presented in viewgraph form and include the following: Space Transportation Main Engine (STME) definition, design philosophy, robust design, maximum design condition, casting vs. machined and welded forgings, operability considerations, high reliability design philosophy, engine reliability enhancement, low cost design philosophy, engine systems requirements, STME schematic, fuel turbopump, liquid oxygen turbopump, main injector, and gas generator. The major engine components of the STME and the Space Shuttle Main Engine are compared.

  12. Building Safer Systems With SpecTRM

    NASA Technical Reports Server (NTRS)

    2003-01-01

    System safety, an integral component in software development, often poses a challenge to engineers designing computer-based systems. While the relaxed constraints on software design allow for increased power and flexibility, this flexibility introduces more possibilities for error. As a result, system engineers must identify the design constraints necessary to maintain safety and ensure that the system and software design enforces them. Safeware Engineering Corporation, of Seattle, Washington, provides the information, tools, and techniques to accomplish this task with its Specification Tools and Requirements Methodology (SpecTRM). NASA assisted in developing this engineering toolset by awarding the company several Small Business Innovation Research (SBIR) contracts with Ames Research Center and Langley Research Center. The technology benefits NASA through its applications for Space Station rendezvous and docking. SpecTRM aids system and software engineers in developing specifications for large, complex safety critical systems. The product enables engineers to find errors early in development so that they can be fixed with the lowest cost and impact on the system design. SpecTRM traces both the requirements and design rationale (including safety constraints) throughout the system design and documentation, allowing engineers to build required system properties into the design from the beginning, rather than emphasizing assessment at the end of the development process when changes are limited and costly.System safety, an integral component in software development, often poses a challenge to engineers designing computer-based systems. While the relaxed constraints on software design allow for increased power and flexibility, this flexibility introduces more possibilities for error. As a result, system engineers must identify the design constraints necessary to maintain safety and ensure that the system and software design enforces them. Safeware Engineering Corporation, of Seattle, Washington, provides the information, tools, and techniques to accomplish this task with its Specification Tools and Requirements Methodology (SpecTRM). NASA assisted in developing this engineering toolset by awarding the company several Small Business Innovation Research (SBIR) contracts with Ames Research Center and Langley Research Center. The technology benefits NASA through its applications for Space Station rendezvous and docking. SpecTRM aids system and software engineers in developing specifications for large, complex safety critical systems. The product enables engineers to find errors early in development so that they can be fixed with the lowest cost and impact on the system design. SpecTRM traces both the requirements and design rationale (including safety constraints) throughout the system design and documentation, allowing engineers to build required system properties into the design from the beginning, rather than emphasizing assessment at the end of the development process when changes are limited and costly.

  13. Update on Risk Reduction Activities for a Liquid Advanced Booster for NASA's Space Launch System

    NASA Technical Reports Server (NTRS)

    Crocker, Andrew M.; Greene, William D.

    2017-01-01

    The stated goals of NASA's Research Announcement for the Space Launch System (SLS) Advanced Booster Engineering Demonstration and/or Risk Reduction (ABEDRR) are to reduce risks leading to an affordable Advanced Booster that meets the evolved capabilities of SLS and enable competition by mitigating targeted Advanced Booster risks to enhance SLS affordability. Dynetics, Inc. and Aerojet Rocketdyne (AR) formed a team to offer a wide-ranging set of risk reduction activities and full-scale, system-level demonstrations that support NASA's ABEDRR goals. During the ABEDRR effort, the Dynetics Team has modified flight-proven Apollo-Saturn F-1 engine components and subsystems to improve affordability and reliability (e.g., reduce parts counts, touch labor, or use lower cost manufacturing processes and materials). The team has built hardware to validate production costs and completed tests to demonstrate it can meet performance requirements. State-of-the-art manufacturing and processing techniques have been applied to the heritage F-1, resulting in a low recurring cost engine while retaining the benefits of Apollo-era experience. NASA test facilities have been used to perform low-cost risk-reduction engine testing. In early 2014, NASA and the Dynetics Team agreed to move additional large liquid oxygen/kerosene engine work under Dynetics' ABEDRR contract. Also led by AR, the objectives of this work are to demonstrate combustion stability and measure performance of a 500,000 lbf class Oxidizer-Rich Staged Combustion (ORSC) cycle main injector. A trade study was completed to investigate the feasibility, cost effectiveness, and technical maturity of a domestically-produced engine that could potentially both replace the RD-180 on Atlas V and satisfy NASA SLS payload-to-orbit requirements via an advanced booster application. Engine physical dimensions and performance parameters resulting from this study provide the system level requirements for the ORSC risk reduction test article. The test article is scheduled to complete fabrication and assembly soon and continue testing through late 2019. Dynetics has also designed, developed, and built innovative tank and structure assemblies using friction stir welding to leverage recent NASA investments in manufacturing tools, facilities, and processes, significantly reducing development and recurring costs. The full-scale cryotank assembly was used to verify the structural design and prove affordable processes. Dynetics performed hydrostatic and cryothermal proof tests on the assembly to verify the assembly meets performance requirements..

  14. The effectiveness of insurer-supported safety and health engineering controls in reducing workers' compensation claims and costs.

    PubMed

    Wurzelbacher, Steven J; Bertke, Stephen J; Lampl, Michael P; Bushnell, P Timothy; Meyers, Alysha R; Robins, David C; Al-Tarawneh, Ibraheem S

    2014-12-01

    This study evaluated the effectiveness of a program in which a workers' compensation (WC) insurer provided matching funds to insured employers to implement safety/health engineering controls. Pre- and post-intervention WC metrics were compiled for the employees designated as affected by the interventions within 468 employers for interventions occurring from 2003 to 2009. Poisson, two-part, and linear regression models with repeated measures were used to evaluate differences in pre- and post-data, controlling for time trends independent of the interventions. For affected employees, total WC claim frequency rates (both medical-only and lost-time claims) decreased 66%, lost-time WC claim frequency rates decreased 78%, WC paid cost per employee decreased 81%, and WC geometric mean paid claim cost decreased 30% post-intervention. Reductions varied by employer size, specific industry, and intervention type. The insurer-supported safety/health engineering control program was effective in reducing WC claims and costs for affected employees. © 2014 Wiley Periodicals, Inc.

  15. Solar photochemical process engineering for production of fuels and chemicals

    NASA Technical Reports Server (NTRS)

    Biddle, J. R.; Peterson, D. B.; Fujita, T.

    1984-01-01

    The engineering costs and performance of a nominal 25,000 scmd (883,000 scfd) photochemical plant to produce dihydrogen from water were studied. Two systems were considered, one based on flat-plate collector/reactors and the other on linear parabolic troughs. Engineering subsystems were specified including the collector/reactor, support hardware, field transport piping, gas compression equipment, and balance-of-plant (BOP) items. Overall plant efficiencies of 10.3 and 11.6% are estimated for the flat-plate and trough systems, respectively, based on assumed solar photochemical efficiencies of 12.9 and 14.6%. Because of the opposing effects of concentration ratio and operating temperature on efficiency, it was concluded that reactor cooling would be necessary with the trough system. Both active and passive cooling methods were considered. Capital costs and energy costs, for both concentrating and non-concentrating systems, were determined and their sensitivity to efficiency and economic parameters were analyzed. The overall plant efficiency is the single most important factor in determining the cost of the fuel.

  16. Solar photochemical process engineering for production of fuels and chemicals

    NASA Technical Reports Server (NTRS)

    Biddle, J. R.; Peterson, D. B.; Fujita, T.

    1985-01-01

    The engineering costs and performance of a nominal 25,000 scmd (883,000 scfd) photochemical plant to produce dihydrogen from water were studied. Two systems were considered, one based on flat-plate collector/reactors and the other on linear parabolic troughs. Engineering subsystems were specified including the collector/reactor, support hardware, field transport piping, gas compression equipment, and balance-of-plant (BOP) items. Overall plant efficiencies of 10.3 and 11.6 percent are estimated for the flat-plate and trough systems, respectively, based on assumed solar photochemical efficiencies of 12.9 and 14.6 percent. Because of the opposing effects of concentration ratio and operating temperature on efficiency, it was concluded that reactor cooling would be necessary with the trough system. Both active and passive cooling methods were considered. Capital costs and energy costs, for both concentrating and non-concentrating systems, were determined and their sensitivity to efficiency and economic parameters were analyzed. The overall plant efficiency is the single most important factor in determining the cost of the fuel.

  17. The Effectiveness of Insurer-Supported Safety and Health Engineering Controls in Reducing Workers’ Compensation Claims and Costs

    PubMed Central

    Wurzelbacher, Steven J.; Bertke, Stephen J.; Lampl, Michael P.; Bushnell, P. Timothy; Meyers, Alysha R.; Robins, David C.; Al-Tarawneh, Ibraheem S.

    2015-01-01

    Background This study evaluated the effectiveness of a program in which a workers’ compensation (WC) insurer provided matching funds to insured employers to implement safety/health engineering controls. Methods Pre- and post-intervention WC metrics were compiled for the employees designated as affected by the interventions within 468 employers for interventions occurring from 2003 to 2009. Poisson, two-part, and linear regression models with repeated measures were used to evaluate differences in pre- and post-data, controlling for time trends independent of the interventions. Results For affected employees, total WC claim frequency rates (both medical-only and lost-time claims) decreased 66%, lost-time WC claim frequency rates decreased 78%, WC paid cost per employee decreased 81%, and WC geometric mean paid claim cost decreased 30% post-intervention. Reductions varied by employer size, specific industry, and intervention type. Conclusions The insurer-supported safety/health engineering control program was effective in reducing WC claims and costs for affected employees. PMID:25223846

  18. Energy efficient engine component development and integration program

    NASA Technical Reports Server (NTRS)

    1982-01-01

    The development of the technology to improve energy efficiency of propulsion systems for subsonic commercial aircrafts was examined. Goals established include: (1) fuel consumption, reduction in flight propulsion system; (2) direct operation cost; (3) noise, with provision for engine growth corresponding to future engine application; and (4) emissions, EPA new engine standards.

  19. Liquid Rocket Booster Study. Volume 2, Book 1

    NASA Technical Reports Server (NTRS)

    1989-01-01

    The recommended Liquid Rocket Booster (LRB) concept is shown which uses a common main engine with the Advanced Launch System (ALS) which burns LO2 and LH2. The central rationale is based on the belief that the U.S. can only afford one big new rocket engine development in the 1990's. A LO2/LH2 engine in the half million pound thrust class could satisfy STS LRB, ALS, and Shuttle C (instead of SSMEs). Development costs and higher production rates can be shared by NASA and USAF. If the ALS program does not occur, the LO2/RP-1 propellants would produce slight lower costs for and STS LRB. When the planned Booster Engine portion of the Civil Space Transportation Initiatives has provided data on large pressure fed LO2/RP-1 engines, then the choice should be reevaluated.

  20. Single-Lever Power Control for General Aviation Aircraft Promises Improved Efficiency and Simplified Pilot Controls

    NASA Technical Reports Server (NTRS)

    Musgrave, Jeffrey L.

    1997-01-01

    General aviation research is leading to major advances in internal combustion engine control systems for single-engine, single-pilot aircraft. These advances promise to increase engine performance and fuel efficiency while substantially reducing pilot workload and increasing flight safety. One such advance is a single-lever power control (SLPC) system, a welcome departure from older, less user-friendly, multilever engine control systems. The benefits of using single-lever power controls for general aviation aircraft are improved flight safety through advanced engine diagnostics, simplified powerplant operations, increased time between overhauls, and cost-effective technology (extends fuel burn and reduces overhaul costs). The single-lever concept has proven to be so effective in preliminary studies that general aviation manufacturers are making plans to retrofit current aircraft with the technology and are incorporating it in designs for future aircraft.

  1. Metabolic engineering of microbial competitive advantage for industrial fermentation processes.

    PubMed

    Shaw, A Joe; Lam, Felix H; Hamilton, Maureen; Consiglio, Andrew; MacEwen, Kyle; Brevnova, Elena E; Greenhagen, Emily; LaTouf, W Greg; South, Colin R; van Dijken, Hans; Stephanopoulos, Gregory

    2016-08-05

    Microbial contamination is an obstacle to widespread production of advanced biofuels and chemicals. Current practices such as process sterilization or antibiotic dosage carry excess costs or encourage the development of antibiotic resistance. We engineered Escherichia coli to assimilate melamine, a xenobiotic compound containing nitrogen. After adaptive laboratory evolution to improve pathway efficiency, the engineered strain rapidly outcompeted a control strain when melamine was supplied as the nitrogen source. We additionally engineered the yeasts Saccharomyces cerevisiae and Yarrowia lipolytica to assimilate nitrogen from cyanamide and phosphorus from potassium phosphite, and they outcompeted contaminating strains in several low-cost feedstocks. Supplying essential growth nutrients through xenobiotic or ecologically rare chemicals provides microbial competitive advantage with minimal external risks, given that engineered biocatalysts only have improved fitness within the customized fermentation environment. Copyright © 2016, American Association for the Advancement of Science.

  2. Calculation of the Actual Cost of Engine Maintenance

    DTIC Science & Technology

    2003-03-01

    Cost Estimating Integrated Tools ( ACEIT ) helps analysts store, retrieve, and analyze data; build cost models; analyze risk; time phase budgets; and...Tools ( ACEIT ).” n. pag. http://www.aceit.com/ 21 February 2003. • USAMC Logistics Support Activity (LOGSA). “Cost Analysis Strategy Assessment

  3. Estimating Environmental Compliance Costs for Industry (1981)

    EPA Pesticide Factsheets

    The paper discusses the pros and cons of existing approaches to compliance cost estimation such as ex post survey estimation and ex ante estimation techniques (input cost accounting methods, engineering process models and, econometric models).

  4. An Improved Effective Cost Review Process for Value Engineering

    PubMed Central

    Joo, D. S.; Park, J. I.

    2014-01-01

    Second-look value engineering (VE) is an approach that aims to lower the costs of products for which target costs are not being met during the production stage. Participants in second-look VE typically come up with a variety of ideas for cost cutting, but the outcomes often depend on their levels of experience, and not many good alternatives are available during the production stage. Nonetheless, good ideas have been consistently generated by VE experts. This paper investigates past second-look VE cases and the thinking processes of VE experts and proposes a cost review process as a systematic means of investigating cost-cutting ideas. This cost review process includes the use of an idea checklist and a specification review process. In addition to presenting the process, this paper reports on its feasibility, based on its introduction into a VE training course as part of a pilot study. The results indicate that the cost review process is effective in generating ideas for later analysis. PMID:25580459

  5. An improved effective cost review process for value engineering.

    PubMed

    Joo, D S; Park, J I

    2014-01-01

    Second-look value engineering (VE) is an approach that aims to lower the costs of products for which target costs are not being met during the production stage. Participants in second-look VE typically come up with a variety of ideas for cost cutting, but the outcomes often depend on their levels of experience, and not many good alternatives are available during the production stage. Nonetheless, good ideas have been consistently generated by VE experts. This paper investigates past second-look VE cases and the thinking processes of VE experts and proposes a cost review process as a systematic means of investigating cost-cutting ideas. This cost review process includes the use of an idea checklist and a specification review process. In addition to presenting the process, this paper reports on its feasibility, based on its introduction into a VE training course as part of a pilot study. The results indicate that the cost review process is effective in generating ideas for later analysis.

  6. Life-Cycle Analysis of Aircraft Turbine Engines

    DTIC Science & Technology

    1977-11-01

    actual experience. Mixed but promisng results were obtained in modeling ownership costs for military engines. Depot maintenance costs were more...Acquisition Experience, The Rand Corporation, RM-6072-PR, November 1969. System Acquisition Stategies , The Rand Corporation, R-733-PR/ARPA, June 1971. 98...Paris, 1971I. Phillips. Almarin, Technology and Market Structure, IA•xington Books, D.C. Heath and Company, Lexington, Mass.. 1971. A Position Paper on

  7. 7 CFR 1710.250 - General.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    .... (i) A borrower's CWP or special engineering studies must be supported by a Borrower's Environmental..., and retirements. The primary components of the system consist of long-range engineering plans, construction work plans (CWPs), CWP amendments, and special engineering and cost studies. Long range...

  8. 77 FR 40026 - 36(b)(1) Arms Sales Notification

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-07-06

    ... and contractor logistics, Quality Assurance Team support services, engineering and technical support..., engineering and technical support, and other related elements of program support. The estimated cost is $49..., maintenance, or training is Confidential. Reverse engineering could reveal Confidential information...

  9. Costing improvement of remanufacturing crankshaft by integrating Mahalanobis-Taguchi System and Activity based Costing

    NASA Astrophysics Data System (ADS)

    Abu, M. Y.; Nor, E. E. Mohd; Rahman, M. S. Abd

    2018-04-01

    Integration between quality and costing system is very crucial in order to achieve an accurate product cost and profit. Current practice by most of remanufacturers, there are still lacking on optimization during the remanufacturing process which contributed to incorrect variables consideration to the costing system. Meanwhile, traditional costing accounting being practice has distortion in the cost unit which lead to inaccurate cost of product. The aim of this work is to identify the critical and non-critical variables during remanufacturing process using Mahalanobis-Taguchi System and simultaneously estimate the cost using Activity Based Costing method. The orthogonal array was applied to indicate the contribution of variables in the factorial effect graph and the critical variables were considered with overhead costs that are actually demanding the activities. This work improved the quality inspection together with costing system to produce an accurate profitability information. As a result, the cost per unit of remanufactured crankshaft of MAN engine model with 5 critical crankpins is MYR609.50 while Detroit engine model with 4 critical crankpins is MYR1254.80. The significant of output demonstrated through promoting green by reducing re-melting process of damaged parts to ensure consistent benefit of return cores.

  10. 23 CFR 505.13 - Federal Government's share of project cost.

    Code of Federal Regulations, 2012 CFR

    2012-04-01

    ... 23 Highways 1 2012-04-01 2012-04-01 false Federal Government's share of project cost. 505.13... Government's share of project cost. (a) Based on engineering studies, studies of economic feasibility, and... eligible costs. (b) A FFGA for the project shall not exceed 80 percent of the eligible project cost. A...

  11. 23 CFR 505.13 - Federal Government's share of project cost.

    Code of Federal Regulations, 2014 CFR

    2014-04-01

    ... 23 Highways 1 2014-04-01 2014-04-01 false Federal Government's share of project cost. 505.13... Government's share of project cost. (a) Based on engineering studies, studies of economic feasibility, and... eligible costs. (b) A FFGA for the project shall not exceed 80 percent of the eligible project cost. A...

  12. 23 CFR 505.13 - Federal Government's share of project cost.

    Code of Federal Regulations, 2013 CFR

    2013-04-01

    ... 23 Highways 1 2013-04-01 2013-04-01 false Federal Government's share of project cost. 505.13... Government's share of project cost. (a) Based on engineering studies, studies of economic feasibility, and... eligible costs. (b) A FFGA for the project shall not exceed 80 percent of the eligible project cost. A...

  13. 23 CFR 505.13 - Federal Government's share of project cost.

    Code of Federal Regulations, 2011 CFR

    2011-04-01

    ... 23 Highways 1 2011-04-01 2011-04-01 false Federal Government's share of project cost. 505.13... Government's share of project cost. (a) Based on engineering studies, studies of economic feasibility, and... eligible costs. (b) A FFGA for the project shall not exceed 80 percent of the eligible project cost. A...

  14. Optimizing conceptual aircraft designs for minimum life cycle cost

    NASA Technical Reports Server (NTRS)

    Johnson, Vicki S.

    1989-01-01

    A life cycle cost (LCC) module has been added to the FLight Optimization System (FLOPS), allowing the additional optimization variables of life cycle cost, direct operating cost, and acquisition cost. Extensive use of the methodology on short-, medium-, and medium-to-long range aircraft has demonstrated that the system works well. Results from the study show that optimization parameter has a definite effect on the aircraft, and that optimizing an aircraft for minimum LCC results in a different airplane than when optimizing for minimum take-off gross weight (TOGW), fuel burned, direct operation cost (DOC), or acquisition cost. Additionally, the economic assumptions can have a strong impact on the configurations optimized for minimum LCC or DOC. Also, results show that advanced technology can be worthwhile, even if it results in higher manufacturing and operating costs. Examining the number of engines a configuration should have demonstrated a real payoff of including life cycle cost in the conceptual design process: the minimum TOGW of fuel aircraft did not always have the lowest life cycle cost when considering the number of engines.

  15. Weight and cost estimating relationships for heavy lift airships

    NASA Technical Reports Server (NTRS)

    Gray, D. W.

    1979-01-01

    Weight and cost estimating relationships, including additional parameters that influence the cost and performance of heavy-lift airships (HLA), are discussed. Inputs to a closed loop computer program, consisting of useful load, forward speed, lift module positive or negative thrust, and rotors and propellers, are examined. Detail is given to the HLA cost and weight program (HLACW), which computes component weights, vehicle size, buoyancy lift, rotor and propellar thrust, and engine horse power. This program solves the problem of interrelating the different aerostat, rotors, engines and propeller sizes. Six sets of 'default parameters' are left for the operator to change during each computer run enabling slight data manipulation without altering the program.

  16. An economic analysis of adherence engineering to improve use of best practices during central line maintenance procedures.

    PubMed

    Nelson, Richard E; Angelovic, Aaron W; Nelson, Scott D; Gleed, Jeremy R; Drews, Frank A

    2015-05-01

    Adherence engineering applies human factors principles to examine non-adherence within a specific task and to guide the development of materials or equipment to increase protocol adherence and reduce human error. Central line maintenance (CLM) for intensive care unit (ICU) patients is a task through which error or non-adherence to protocols can cause central line-associated bloodstream infections (CLABSIs). We conducted an economic analysis of an adherence engineering CLM kit designed to improve the CLM task and reduce the risk of CLABSI. We constructed a Markov model to compare the cost-effectiveness of the CLM kit, which contains each of the 27 items necessary for performing the CLM procedure, compared with the standard care procedure for CLM, in which each item for dressing maintenance is gathered separately. We estimated the model using the cost of CLABSI overall ($45,685) as well as the excess LOS (6.9 excess ICU days, 3.5 excess general ward days). Assuming the CLM kit reduces the risk of CLABSI by 100% and 50%, this strategy was less costly (cost savings between $306 and $860) and more effective (between 0.05 and 0.13 more quality-adjusted life-years) compared with not using the pre-packaged kit. We identified threshold values for the effectiveness of the kit in reducing CLABSI for which the kit strategy was no longer less costly. An adherence engineering-based intervention to streamline the CLM process can improve patient outcomes and lower costs. Patient safety can be improved by adopting new approaches that are based on human factors principles.

  17. Hubble Space Telescope: cost reduction by re-engineering telemetry processing and archiving

    NASA Astrophysics Data System (ADS)

    Miebach, Manfred P.

    1998-05-01

    The Hubble Space Telescope (HST), the first of NASA's Great Observatories, was launched on April 24, 1990. The HST was designed for a minimum fifteen-year mission with on-orbit servicing by the Space Shuttle System planned at approximately three-year intervals. Major changes to the HST ground system are planned to be in place for the third servicing mission in December 1999. The primary objectives of the ground system reengineering effort, a project called 'vision December 1999. The primary objectives of the ground system re-engineering effort, a project called 'vision 2000 control center systems (CCS)', are to reduce both development and operating costs significantly for the remaining years of HST's lifetime. Development costs will be reduced by providing a modern hardware and software architecture and utilizing commercial of f the shelf (COTS) products wherever possible. Operating costs will be reduced by eliminating redundant legacy systems and processes and by providing an integrated ground system geared toward autonomous operation. Part of CCS is a Space Telescope Engineering Data Store, the design of which is based on current Data Warehouse technology. The purpose of this data store is to provide a common data source of telemetry data for all HST subsystems. This data store will become the engineering data archive and will include a queryable database for the user to analyze HST telemetry. The access to the engineering data in the Data Warehouse is platform- independent from an office environment using commercial standards. Latest internet technology is used to reach the HST engineering community. A WEB-based user interface allows easy access to the data archives. This paper will provide a high level overview of the CCS system and will illustrate some of the CCS telemetry capabilities. Samples of CCS user interface pages will be given. Vision 2000 is an ambitious project, but one that is well under way. It will allow the HST program to realize reduced operations costs for the Third Servicing Mission and beyond.

  18. Mental Models of Software Forecasting

    NASA Technical Reports Server (NTRS)

    Hihn, J.; Griesel, A.; Bruno, K.; Fouser, T.; Tausworthe, R.

    1993-01-01

    The majority of software engineers resist the use of the currently available cost models. One problem is that the mathematical and statistical models that are currently available do not correspond with the mental models of the software engineers. In an earlier JPL funded study (Hihn and Habib-agahi, 1991) it was found that software engineers prefer to use analogical or analogy-like techniques to derive size and cost estimates, whereas curren CER's hide any analogy in the regression equations. In addition, the currently available models depend upon information which is not available during early planning when the most important forecasts must be made.

  19. United States Air Force 611th Civil Engineer Squadron, Elmendorf AFB, Alaska. Final engineering evaluation/cost analysis: Petroleum, oil, and lubricants area, Galena Airport, Alaska

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    NONE

    1996-02-05

    This decision document presents the selected removal action for the Installation Restoration Program (IRP) site ST005, otherwise known as the POL Tank Farm, at Galena Airport, Alaska. This decision is based on the administrative record for this site, specifically the draft Remedial Investigation Report (March 1995) and the Treatability Study Report (January 1995) (PB95-225314). The information from these documents is summarized, along with an analysis of potential removal action alternatives in the Engineering Evaluation/Cost Analysis (EE/CA).

  20. Embedded image processing engine using ARM cortex-M4 based STM32F407 microcontroller

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    Samaiya, Devesh, E-mail: samaiya.devesh@gmail.com

    2014-10-06

    Due to advancement in low cost, easily available, yet powerful hardware and revolution in open source software, urge to make newer, more interactive machines and electronic systems have increased manifold among engineers. To make system more interactive, designers need easy to use sensor systems. Giving the boon of vision to machines was never easy, though it is not impossible these days; it is still not easy and expensive. This work presents a low cost, moderate performance and programmable Image processing engine. This Image processing engine is able to capture real time images, can store the images in the permanent storagemore » and can perform preprogrammed image processing operations on the captured images.« less

  1. Implications of multiplane-multispeed balancing for future turbine engine design and cost

    NASA Technical Reports Server (NTRS)

    Badgley, R. H.

    1974-01-01

    This paper describes several alternative approaches, provided by multiplane-multispeed balancing, to traditional gas turbine engine manufacture and assembly procedures. These alternatives, which range from addition of trim-balancing at the end of the traditional assembly process to modular design of the rotating system for assembly and balancing external to the engine, require attention by the engine designer as an integral part of the design process. Since multiplane-multispeed balancing may be incorporated at one or more of several points during manufacture-assembly, its deliberate use is expected to provide significant cost and performance (reduced vibration) benefits. Moreover, its availability provides the designer with a firm base from which he may advance, with reasonable assurance of success, into the flexible rotor dynamic regime.

  2. 48 CFR 970.5215-4 - Cost reduction.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... 48 Federal Acquisition Regulations System 5 2010-10-01 2010-10-01 false Cost reduction. 970.5215-4 Section 970.5215-4 Federal Acquisition Regulations System DEPARTMENT OF ENERGY AGENCY SUPPLEMENTARY.... Development cost is the Contractor cost of up-front planning, engineering, prototyping, and testing of a...

  3. Automotive Stirling engine development program

    NASA Technical Reports Server (NTRS)

    Nightingale, N.; Ernst, W.; Richey, A.; Simetkosky, M.; Smith, G.; Rohdenburg, C.; Vatsky, A.; Antonelli, M. (Editor)

    1983-01-01

    Activities performed on Mod I engine testing and test results, testing of the Mod I engine in the United States, Mod I engine characterization and analyses, Mod I Transient Test Bed fuel economy, upgraded Mod I performance and testing, Stirling engine reference engine manufacturing and reduced size studied, components and subsystems, and the study and test of low cost casting alloys are summarized. The overall program philosophy is outlined, and data and results are presented.

  4. 7 CFR 1710.250 - General.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ..., and retirements. The primary components of the system consist of long-range engineering plans, construction work plans (CWPs), CWP amendments, and special engineering and cost studies. Long range engineering plans identify plant investments required over a period of 10 years or more. CWPs specify and...

  5. 7 CFR 1710.250 - General.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ..., and retirements. The primary components of the system consist of long-range engineering plans, construction work plans (CWPs), CWP amendments, and special engineering and cost studies. Long range engineering plans identify plant investments required over a period of 10 years or more. CWPs specify and...

  6. 7 CFR 1710.250 - General.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ..., and retirements. The primary components of the system consist of long-range engineering plans, construction work plans (CWPs), CWP amendments, and special engineering and cost studies. Long range engineering plans identify plant investments required over a period of 10 years or more. CWPs specify and...

  7. 7 CFR 1710.250 - General.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ..., and retirements. The primary components of the system consist of long-range engineering plans, construction work plans (CWPs), CWP amendments, and special engineering and cost studies. Long range engineering plans identify plant investments required over a period of 10 years or more. CWPs specify and...

  8. Improving building performance using smart building concept: Benefit cost ratio comparison

    NASA Astrophysics Data System (ADS)

    Berawi, Mohammed Ali; Miraj, Perdana; Sayuti, Mustika Sari; Berawi, Abdur Rohim Boy

    2017-11-01

    Smart building concept is an implementation of technology developed in the construction industry throughout the world. However, the implementation of this concept is still below expectations due to various obstacles such as higher initial cost than a conventional concept and existing regulation siding with the lowest cost in the tender process. This research aims to develop intelligent building concept using value engineering approach to obtain added value regarding quality, efficiency, and innovation. The research combined quantitative and qualitative approach using questionnaire survey and value engineering method to achieve the research objectives. The research output will show additional functions regarding technology innovation that may increase the value of a building. This study shows that smart building concept requires higher initial cost, but produces lower operational and maintenance costs. Furthermore, it also confirms that benefit-cost ratio on the smart building was much higher than a conventional building, that is 1.99 to 0.88.

  9. Contingency Power Study for Short Haul Civil Tiltrotor

    NASA Technical Reports Server (NTRS)

    D'Angelo, Marin M.

    2004-01-01

    NASA has concluded from previous studies that the twin engine tiltrotor is the most economical and technologically viable rotorcraft for near-term civil applications. Twin engine civil rotorcraft must be able to hover safely on one engine in an emergency. This emergency power requirement generally results in engines 20 to 50 percent larger than needed for normal engine operation, negatively impacting aircraft economics. This study identifies several contingency power enhancement concepts, and quantifies their potential to reduce aircraft operating costs. Many unique concepts were examined, and the selected concepts are simple, reliable, and have a high potential for near term realization. These engine concepts allow extremely high turbine temperatures during emergency operation by providing cooling to the power turbine and augmenting cooling of both turbines and structural hardware. Direct operating cost are reduced 3 to percent, which could yield a 30 to 80 percent increase in operating profits. The study consists of the definition of an aircraft economics model and a baseline engine, and an engine concept screening study, and a preliminary definition of the selected concepts. The selected concepts are evaluated against the baseline engine, and the critical technologies and development needs are identified, along with applications for this technology.

  10. Cost/benefit studies of advanced materials technologies for future aircraft turbine engines: Materials for advanced turbine engines

    NASA Technical Reports Server (NTRS)

    Stearns, M.; Wilbers, L.

    1982-01-01

    Cost benefit studies were conducted on six advanced materials and processes technologies applicable to commercial engines planned for production in the 1985 to 1990 time frame. These technologies consisted of thermal barrier coatings for combustor and high pressure turbine airfoils, directionally solidified eutectic high pressure turbine blades, (both cast and fabricated), and mixers, tail cones, and piping made of titanium-aluminum alloys. A fabricated titanium fan blisk, an advanced turbine disk alloy with improved low cycle fatigue life, and a long-life high pressure turbine blade abrasive tip and ceramic shroud system were also analyzed. Technologies showing considerable promise as to benefits, low development costs, and high probability of success were thermal barrier coating, directionally solidified eutectic turbine blades, and abrasive-tip blades/ceramic-shroud turbine systems.

  11. Low Cost Manufacturing Approach of High Temperature PMC Components

    NASA Technical Reports Server (NTRS)

    Kannmacher, Kevin

    1997-01-01

    The overall objective is to develop a satisfactory sheet molding compound (SMC) of a high temperature polyimide, such as PMR-11-50, VCAP-75, or NB2-76, and to develop compression molding processing parameters for a random, chopped fiber, high temperature, sheet molding compound that will be more affordable than the traditional hand lay-up fabrication methods. Compression molding will reduce manufacturing costs of composites by: (1) minimizing the conventional machining required after fabrication due to the use of full 360 deg matched tooling, (2) reducing fabrication time by minimizing the intensive hand lay-up operations associated with individual ply fabrication techniques, such as ply orientation and ply count and (3) possibly reducing component mold time by advanced B-staging prior to molding. This program is an integral part of Allison's T406/AE engine family's growth plan, which will utilize technologies developed under NASA's Sub-sonic Transport (AST) programs, UHPTET initiatives, and internally through Allison's IR&D projects. Allison is aggressively pursuing this next generation of engines, with both commercial and military applications, by reducing the overall weight of the engine through the incorporation of advanced, lightweight, high temperature materials, such as polymer matrix composites. This infusion of new materials into the engine is also a major factor in reducing engine cost because it permits the use of physically smaller structural components to achieve the same thrust levels as the generation that it replaced. A lighter, more efficient propulsion system translates to a substantial cost and weight savings to an airframe's structure.

  12. Demonstration of Remotely Operated Vehicles to Aid Underwater Inspection of Corps of Engineers Navigation Structures. Winfield Locks and Dam 13-17 August 2007

    DTIC Science & Technology

    2008-09-01

    2 Deep Ocean Engineering Triggerfish ...Figures Figure 1. Deep Ocean Engineering Triggerfish ROV carried by two divers (top)................................... 4 Figure 2. SeaBotix...the physical parameters and approximate costs of the systems as tested. Deep Ocean Engineering Triggerfish Figure 1 shows the Deep Ocean

  13. Integrating Cost Engineering and Project Management in a Junior Engineering Economics Course and a Senior Capstone Project Design Course

    ERIC Educational Resources Information Center

    Tickles, Virginia C.; Li, Yadong; Walters, Wilbur L.

    2013-01-01

    Much criticism exists concerning a lack of focus on real-world problem-solving in the science, technology, engineering and mathematics (STEM) infrastructures. Many of these critics say that current educational infrastructures are incapable in preparing future scientists and engineers to solve the complex and multidisciplinary problems this society…

  14. An Analysis of Cost Premiums and Losses Associated with USAF Military Construction (MILCON)

    DTIC Science & Technology

    2013-03-01

    Corps of Engineers (USACE) or the Naval Facilities Engineering Command (NAVFAC) for design and construction of the annual military construction...AFCEC in lieu of AFCEE or AFCESA. The selection, and policies, of design and construction agents may cause cost premiums for Air Force MILCON...private industry best practices such as relational contracting, schedule performance, and design -build procurement methods. All of these research

  15. An Analysis of the Cost Estimating Process in Air Force Research and Development Laboratories.

    DTIC Science & Technology

    1981-09-01

    inexperienced military or civilian engineer/scientist new to the laboratory environ - ment the cost eatimating dilemma may be especially acute. Problem...several components are subjected to repeated environmental testing. Thus, the data from Question 6 was used to address the first two research questions: 1...Research Scientific study and experimentation directed toward increasing knowledge and understanding in the physical, engineering, environmental , and

  16. DOE/NASA Automotive Stirling Engine Project overview '83

    NASA Technical Reports Server (NTRS)

    Beremand, D. G.

    1982-01-01

    An overview of the DOE/NASA Automotive Stirling Engine Project is presented. The background and objectives of the project are reviewed. Project activities are described and technical progress and status are presented and assessed. Prospects for achieving the objective 30% fuel economy improvement are considered good. The key remaining technology issues are primarily related to life, reliability and cost, such as piston rod seals, and low cost heat exchanges.

  17. The automotive application of discontinuously reinforced TiB-Ti composites

    NASA Astrophysics Data System (ADS)

    Saito, Takashi

    2004-05-01

    In 1998, Toyota Motor Corporation adopted intake valves and exhaust valves made of titanium-based alloys for the engine of its Altezza. Both valves were manufactured via a newly developed cost-effective powder metallurgy process. The exhaust valve is made of a newly developed titanium metal-matrix composite (MMC). The valve has achieved sufficient durability and reliability with a manufacturing cost acceptable for the mass-produced automobile engine components.

  18. Engineering innovation to reduce wind power COE

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    Ammerman, Curtt Nelson

    There are enough wind resources in the US to provide 10 times the electric power we currently use, however wind power only accounts for 2% of our total electricity production. One of the main limitations to wind use is cost. Wind power currently costs 5-to-8 cents per kilowatt-hour, which is more than twice the cost of electricity generated by burning coal. Our Intelligent Wind Turbine LDRD Project is applying LANL's leading-edge engineering expertise in modeling and simulation, experimental validation, and advanced sensing technologies to challenges faced in the design and operation of modern wind turbines.

  19. 78 FR 7718 - Review of the General Purpose Costing System

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-02-04

    ... for switching cars, regardless of car ownership. These costs are referred to as ``switch engine minute... provide the railroad industry and shippers with a standardized costing model; to cost the Board's Car Load... movement. Next, URCS applies ``efficiency adjustments'' to higher-volume movements (multi-car and trainload...

  20. As Easy as ABC: Re-engineering the Cost Accounting System.

    ERIC Educational Resources Information Center

    Trussel, John M.; Bitner, Larry N.

    1996-01-01

    To be useful for management decision making, the college or university's cost accounting system must capture and measure improvements. Activity-based costing (ABC), which determines more accurately the full costs of services and products, tracks improvements and should proceed alongside reengineering of institutional accounting. Guidelines are…

  1. Space Station engineering and technology development

    NASA Technical Reports Server (NTRS)

    1985-01-01

    Historical background, costs, organizational assignments, technology development, user requirements, mission evolution, systems analyses and design, systems engineering and integration, contracting, and policies of the space station are discussed.

  2. Advanced General Aviation Turbine Engine (GATE) study

    NASA Technical Reports Server (NTRS)

    Smith, R.; Benstein, E. H.

    1979-01-01

    The small engine technology requirements suitable for general aviation service in the 1987 to 1988 time frame were defined. The market analysis showed potential United States engines sales of 31,500 per year providing that the turbine engine sales price approaches current reciprocating engine prices. An optimum engine design was prepared for four categories of fixed wing aircraft and for rotary wing applications. A common core approach was derived from the optimum engines that maximizes engine commonality over the power spectrum with a projected price competitive with reciprocating piston engines. The advanced technology features reduced engine cost, approximately 50 percent compared with current technology.

  3. CHARACTERIZATION OF EMISSIONS FROM HAND-HELD TWO-STROKE ENGINES

    EPA Science Inventory

    Despite their extremely high organic and particulate matter emission rates, two-stroke engines remain among the least studied of engine types. Such studies are rare because they are costly to perform. Results reported in this paper were obtained using a facility that shares e...

  4. 48 CFR 48.104-2 - Sharing acquisition savings.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... CONTRACT MANAGEMENT VALUE ENGINEERING Policies and Procedures 48.104-2 Sharing acquisition savings. (a... value engineering clause or alternate used, and the type of savings, as follows: Government/Contractor... percent for fixed-price contracts; or (2) 75 percent for cost-reimbursement contracts. Value engineering...

  5. Virtual aluminum castings: An industrial application of ICME

    NASA Astrophysics Data System (ADS)

    Allison, John; Li, Mei; Wolverton, C.; Su, Xuming

    2006-11-01

    The automotive product design and manufacturing community is continually besieged by Hercule an engineering, timing, and cost challenges. Nowhere is this more evident than in the development of designs and manufacturing processes for cast aluminum engine blocks and cylinder heads. Increasing engine performance requirements coupled with stringent weight and packaging constraints are pushing aluminum alloys to the limits of their capabilities. To provide high-quality blocks and heads at the lowest possible cost, manufacturing process engineers are required to find increasingly innovative ways to cast and heat treat components. Additionally, to remain competitive, products and manufacturing methods must be developed and implemented in record time. To bridge the gaps between program needs and engineering reality, the use of robust computational models in up-front analysis will take on an increasingly important role. This article describes just such a computational approach, the Virtual Aluminum Castings methodology, which was developed and implemented at Ford Motor Company and demonstrates the feasibility and benefits of integrated computational materials engineering.

  6. Quantum heat engine operating between thermal and spin reservoirs

    NASA Astrophysics Data System (ADS)

    Wright, Jackson S. S. T.; Gould, Tim; Carvalho, André R. R.; Bedkihal, Salil; Vaccaro, Joan A.

    2018-05-01

    Landauer's erasure principle is a cornerstone of thermodynamics and information theory [R. Landauer, IBM J. Res. Dev. 5, 183 (1961), 10.1147/rd.53.0183]. According to this principle, erasing information incurs a minimum energy cost. Recently, Vaccaro and Barnett [J. A. Vaccaro and S. M. Barnett, Proc. R. Soc. A 467, 1770 (2011), 10.1098/rspa.2010.0577] explored information erasure in the context of multiple conserved quantities and showed that the erasure cost can be solely in terms of spin angular momentum. As Landauer's erasure principle plays a fundamental role in heat engines, their result considerably widens the possible configurations that heat engines can have. Motivated by this, we propose here an optical heat engine that operates under a single thermal reservoir and a spin angular momentum reservoir coupled to a three-level system with two energy degenerate ground states. The proposed heat engine operates without producing waste heat and goes beyond the traditional Carnot engine where the working fluid is subjected to two thermal baths at different temperatures.

  7. Maintenance and operations cost model for DSN subsystems

    NASA Technical Reports Server (NTRS)

    Burt, R. W.; Lesh, J. R.

    1977-01-01

    A procedure is described which partitions the recurring costs of the Deep Space Network (DSN) over the individual DSN subsystems. The procedure results in a table showing the maintenance, operations, sustaining engineering and supportive costs for each subsystems.

  8. Conceptual design and cost analysis of hydraulic output unit for 15 kW free-piston Stirling engine

    NASA Technical Reports Server (NTRS)

    White, M. A.

    1982-01-01

    A long-life hydraulic converter with unique features was conceptually designed to interface with a specified 15 kW(e) free-piston Stirling engine in a solar thermal dish application. Hydraulic fluid at 34.5 MPa (5000 psi) is produced to drive a conventional hydraulic motor and rotary alternator. Efficiency of the low-maintenance converter design was calculated at 93.5% for a counterbalanced version and 97.0% without the counterbalance feature. If the converter were coupled to a Stirling engine with design parameters more typcial of high-technology Stirling engines, counterbalanced converter efficiency could be increased to 99.6%. Dynamic computer simulation studies were conducted to evaluate performance and system sensitivities. Production costs of the complete Stirling hydraulic/electric power system were evaluated at $6506 which compared with $8746 for an alternative Stirling engine/linear alternator system.

  9. Evaluation of undeveloped rocket engine cycle applications to advanced transportation

    NASA Technical Reports Server (NTRS)

    1990-01-01

    Undeveloped pump-fed, liquid propellant rocket engine cycles were assessed and evaluated for application to Next Manned Transportation System (NMTS) vehicles, which would include the evolving Space Transportation System (STS Evolution), the Personnel Launch System (PLS), and the Advanced Manned Launch System (AMLS). Undeveloped engine cycles selected for further analysis had potential for increased reliability, more maintainability, reduced cost, and improved (or possibly level) performance when compared to the existing SSME and proposed STME engines. The split expander (SX) cycle, the full flow staged combustion (FFSC) cycle, and a hybrid version of the FFSC, which has a LOX expander drive for the LOX pump, were selected for definition and analysis. Technology requirements and issues were identified and analyses of vehicle systems weight deltas using the SX and FFSC cycles in AMLS vehicles were performed. A strawman schedule and cost estimate for FFSC subsystem technology developments and integrated engine system demonstration was also provided.

  10. Prospects for energy efficiency improvement and reduction of emissions and life cycle costs for natural gas vehicles

    NASA Astrophysics Data System (ADS)

    Kozlov, A. V.; Terenchenko, A. S.; Luksho, V. A.; Karpukhin, K. E.

    2017-01-01

    This work is devoted to the experimental investigation of the possibilities to reduce greenhouse gas emissions and to increase energy efficiency of engines that use natural gas as the main fuel and the analysis of economic efficiency of use of dual fuel engines in vehicles compared to conventional diesel. The results of experimental investigation of a 190 kW dual-fuel engine are presented; it is shown that quantitative and qualitative working process control may ensure thermal efficiency at the same level as that of the diesel engine and in certain conditions 5...8% higher. The prospects for reduction of greenhouse gas emissions have been assessed. The technical and economic evaluation of use of dual fuel engines in heavy-duty vehicles has been performed, taking into account the total life cycle. It is shown that it is possible to reduce life cycle costs by two times.

  11. A minimum cost tolerance allocation method for rocket engines and robust rocket engine design

    NASA Technical Reports Server (NTRS)

    Gerth, Richard J.

    1993-01-01

    Rocket engine design follows three phases: systems design, parameter design, and tolerance design. Systems design and parameter design are most effectively conducted in a concurrent engineering (CE) environment that utilize methods such as Quality Function Deployment and Taguchi methods. However, tolerance allocation remains an art driven by experience, handbooks, and rules of thumb. It was desirable to develop and optimization approach to tolerancing. The case study engine was the STME gas generator cycle. The design of the major components had been completed and the functional relationship between the component tolerances and system performance had been computed using the Generic Power Balance model. The system performance nominals (thrust, MR, and Isp) and tolerances were already specified, as were an initial set of component tolerances. However, the question was whether there existed an optimal combination of tolerances that would result in the minimum cost without any degradation in system performance.

  12. Engineering and fabrication cost considerations for cryogenic wind tunnel models

    NASA Technical Reports Server (NTRS)

    Boykin, R. M., Jr.; Davenport, J. B., Jr.

    1983-01-01

    Design and fabrication cost drivers for cryogenic transonic wind tunnel models are defined. The major cost factors for wind tunnel models are model complexity, tolerances, surface finishes, materials, material validation, and model inspection. The cryogenic temperatures require the use of materials with relatively high fracture toughness but at the same time high strength. Some of these materials are very difficult to machine, requiring extensive machine hours which can add significantly to the manufacturing costs. Some additional engineering costs are incurred to certify the materials through mechanical tests and nondestructive evaluation techniques, which are not normally required with conventional models. When instrumentation such as accelerometers and electronically scanned pressure modules is required, temperature control of these devices needs to be incorporated into the design, which requires added effort. Additional thermal analyses and subsystem tests may be necessary, which also adds to the design costs. The largest driver to the design costs is potentially the additional static and dynamic analyses required to insure structural integrity of the model and support system.

  13. Innovative Airbreathing Propulsion Concepts for Access to Space

    NASA Technical Reports Server (NTRS)

    Whitlow, Jr., Woodrow; Blech, Richard A.; Blankson, Isaiah M.

    2001-01-01

    This paper will present technologies and concepts for novel aeropropulsion systems. These technologies will enhance the safety of operations, reduce life cycle costs, and contribute to reduced costs of air travel and access to space. One of the goals of the NASA program is to reduce the carbon-dioxide emissions of aircraft engines. Engine concepts that use highly efficient fuel cell/electric drive technologies in hydrogen-fueled engines will be presented in the proposed paper. Carbon-dioxide emissions will be eliminated by replacing hydrocarbon fuel with hydrogen, and reduce NOx emissions through better combustion process control. A revolutionary exoskeletal engine concept, in which the engine drum is rotated, will be shown. This concept has the potential to allow a propulsion system that can be used for subsonic through hypersonic flight. Dual fan concepts that have ultra-high bypass ratios, low noise, and low drag will be presented. Flow-controlled turbofans and control-configured turbofans also will be discussed. To increase efficiency, a system of microengines distributed along lifting surfaces and on the fuselage is being investigated. This concept will be presented in the paper. Small propulsion systems for affordable, safe personal transportation vehicles will be discussed. These low-oil/oilless systems use technologies that enable significant cost and weight reductions. Pulse detonation engine-based hybrid-cycle and combined-cycle propulsion systems for aviation and space access will be presented.

  14. High-Speed, High-Temperature Finger Seal Test Evaluated

    NASA Technical Reports Server (NTRS)

    Proctor, Margaret P.

    2003-01-01

    A finger seal, designed and fabricated by Honeywell Engines, Systems and Services, was tested at the NASA Glenn Research Center at surface speeds up to 1200 ft/s, air temperatures up to 1200 F, and pressures across the seal of 75 psid. These are the first test results obtained with NASA s new High-Temperature, High-Speed Turbine Seal Test Rig (see the photograph). The finger seal is an innovative design recently patented by AlliedSignal Engines, which has demonstrated considerably lower leakage than commonly used labyrinth seals and is considerably cheaper than brush seals. The cost to produce finger seals is estimated to be about half of the cost to produce brush seals. Replacing labyrinth seals with fingers seals at locations that have high-pressure drops in gas turbine engines, typically main engine and thrust seals, can reduce air leakage at each location by 50 percent or more. This directly results in a 0.7- to 1.4-percent reduction in specific fuel consumption and a 0.35- to 0.7-percent reduction in direct operating costs . Because the finger seal is a contacting seal, this testing was conducted to address concerns about its heat generation and life capability at the higher speeds and temperatures required for advanced engines. The test results showed that the seal leakage and wear performance are acceptable for advanced engines.

  15. Ultra Clean 1.1MW High Efficiency Natural Gas Engine Powered System

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    Zurlo, James; Lueck, Steve

    Dresser, Inc. (GE Energy, Waukesha gas engines) will develop, test, demonstrate, and commercialize a 1.1 Megawatt (MW) natural gas fueled combined heat and power reciprocating engine powered package. This package will feature a total efficiency > 75% and ultra low CARB permitting emissions. Our modular design will cover the 1 – 6 MW size range, and this scalable technology can be used in both smaller and larger engine powered CHP packages. To further advance one of the key advantages of reciprocating engines, the engine, generator and CHP package will be optimized for low initial and operating costs. Dresser, Inc. willmore » leverage the knowledge gained in the DOE - ARES program. Dresser, Inc. will work with commercial, regulatory, and government entities to help break down barriers to wider deployment of CHP. The outcome of this project will be a commercially successful 1.1 MW CHP package with high electrical and total efficiency that will significantly reduce emissions compared to the current central power plant paradigm. Principal objectives by phases for Budget Period 1 include: • Phase 1 – market study to determine optimum system performance, target first cost, lifecycle cost, and creation of a detailed product specification. • Phase 2 – Refinement of the Waukesha CHP system design concepts, identification of critical characteristics, initial evaluation of technical solutions, and risk mitigation plans. Background« less

  16. Reaction Control Engine for Space Launch Initiative

    NASA Technical Reports Server (NTRS)

    2002-01-01

    Engineers at the Marshall Space Flight Center (MSFC) have begun a series of engine tests on a new breed of space propulsion: a Reaction Control Engine developed for the Space Launch Initiative (SLI). The engine, developed by TRW Space and Electronics of Redondo Beach, California, is an auxiliary propulsion engine designed to maneuver vehicles in orbit. It is used for docking, reentry, attitude control, and fine-pointing while the vehicle is in orbit. The engine uses nontoxic chemicals as propellants, a feature that creates a safer environment for ground operators, lowers cost, and increases efficiency with less maintenance and quicker turnaround time between missions. Testing includes 30 hot-firings. This photograph shows the first engine test performed at MSFC that includes SLI technology. Another unique feature of the Reaction Control Engine is that it operates at dual thrust modes, combining two engine functions into one engine. The engine operates at both 25 and 1,000 pounds of force, reducing overall propulsion weight and allowing vehicles to easily maneuver in space. The low-level thrust of 25 pounds of force allows the vehicle to fine-point maneuver and dock while the high-level thrust of 1,000 pounds of force is used for reentry, orbit transfer, and coarse positioning. SLI is a NASA-wide research and development program, managed by the MSFC, designed to improve safety, reliability, and cost effectiveness of space travel for second generation reusable launch vehicles.

  17. Military Jet Engine Acquisition: Technology Basics and Cost-Estimating Methodology

    DTIC Science & Technology

    2002-01-01

    aircraft , rather than by these forms of jet engines . Like the turbofan or turbojet , these engines have a nozzle down- stream of the low-pressure...2.5 illustrates the process of turbine blade cooling. Figure 2.6 illustrates the steady and rapid increase in RIT for turbo - jets , turbofans , and...87 B. AN OVERVIEW OF MILITARY JET ENGINE HISTORY ... 97 C. AIRCRAFT TURBINE ENGINE DEVELOPMENT ...... 121 D.

  18. Experimental Evaluation of a Method for Turbocharging Four-Stroke, Single Cylinder, Internal Combustion Engines

    NASA Astrophysics Data System (ADS)

    Buchman, Michael; Winter, Amos

    2015-11-01

    Turbocharging an engine increases specific power, improves fuel economy, reduces emissions, and lowers cost compared to a naturally aspirated engine of the same power output. These advantages make turbocharging commonplace for multi-cylinder engines. Single cylinder engineers are not commonly turbocharged due to the phase lag between the exhaust stroke, which powers the turbocharger, and the intake stroke, when air is pumped into the engine. Our proposed method of turbocharging single cylinder engines is to add an ``air capacitor'' to the intake manifold, an additional volume that acts as a buffer to store compressed air between the exhaust and intake strokes, and smooth out the pressure pulses from the turbocharger. This talk presents experimental results from a single cylinder, turbocharged diesel engine fit with various sized air capacitors. Power output from the engine was measured using a dynamometer made from a generator, with the electrical power dissipated with resistive heating elements. We found that intake air density increases with capacitor size as theoretically predicted, ranging from 40 to 60 percent depending on heat transfer. Our experiment was able to produce 29 percent more power compared to using natural aspiration. These results validated that an air capacitor and turbocharger may be a simple, cost effective means of increasing the power density of single cylinder engines.

  19. Small gas turbine engine technology

    NASA Technical Reports Server (NTRS)

    Niedzwiecki, Richard W.; Meitner, Peter L.

    1988-01-01

    Performance of small gas turbine engines in the 250 to 1,000 horsepower size range is significantly lower than that of large engines. Engines of this size are typically used in rotorcraft, commutercraft, general aviation, and cruise missile applications. Principal reasons for the lower efficiencies of a smaller engine are well known: component efficients are lower by as much as 8 to 10 percentage points because of size effects. Small engines are designed for lower cycle pressures and temperatures because of smaller blading and cooling limitations. The highly developed analytical and manufacturing techniques evolved for large engines are not directly transferrable to small engines. Thus, it was recognized that a focused effort addressing technologies for small engies was needed and could significantly impact their performance. Recently, in-house and contract studies were undertaken at the NASA Lewis Research Center to identify advanced engine cycle and component requirements for substantial performance improvement of small gas turbines for projected year 2000 applications. The results of both in-house research and contract studies are presented. In summary, projected fuel savings of 22 to 42 percent could be obtained. Accompanying direct operating cost reductions of 11 to 17 percent, depending on fuel cost, were also estimated. High payoff technologies are identified for all engine applications, and recent results of experimental research to evolve the high payoff technologies are described.

  20. The next generation rocket engines

    NASA Astrophysics Data System (ADS)

    Beichel, Rudi; O'Brien, Charles J.; Taylor, James P.

    This paper examines propulsion system technologies for earth-to-orbit vehicles, and describes several propulsion system concepts which could support the recommendations of the Commission for Space Development for the year 2000. The hallmark of that system must and will be reliability. Reliability will be obtained through a very structured design approach, coupled with a rational, cost effective, development and qualification program. To improve the next generation space transportation propulsion systems we need to select the very best of alternative power and performance cycles and engine physical concepts with a rigid requirement to achieve a robust, dependable, affordable propulsion system. For example, engine concepts using either propellants or non-propellant fluids for cooling and/or power drive offer the potential to provide smooth, controlled engine starts, low turbine temperatures, etc. as required for long life turbomachinery. Concepts examined are LOX/LH 2, |LOX/LH 2 + hydrocarbon, and LOX/LH 2 + hydrocarbon + Al dual expander engines, separate LOX/LH 2 and LOX/hydrocarbon engines, and variable mixture ratio engines. A fully reusable propulsion system that is perceived to be very low risk and low in operation cost is described.

  1. Incremental Scheduling Engines: Cost Savings through Automation

    NASA Technical Reports Server (NTRS)

    Jaap, John; Phillips, Shaun

    2005-01-01

    As humankind embarks on longer space missions farther from home, the requirements and environments for scheduling the activities performed on these missions are changing. As we begin to prepare for these missions it is appropriate to evaluate the merits and applicability of the different types of scheduling engines. Scheduling engines temporally arrange tasks onto a timeline so that all constraints and ob.jectives are met and resources are not over-booked. Scheduling engines used to schedule space missions fall into three general categories: batch, mixed-initiative, and incremental. This paper, presents an assessment of the engine types, a discussion of the impact of human exploration of the moon and Mars on planning and scheduling, and the applicability of the different types of scheduling engines. This paper will pursue the hypothesis that incremental scheduling engines may have a place in the new environment; they have the potential to reduce cost, to improve the satisfaction of those who execute or benefit from a particular timeline (the customers), and to allow astronauts to plan their own tasks and those of their companion robots.

  2. Systems analysis of solid fuel nuclear engines in cislunar space

    NASA Astrophysics Data System (ADS)

    Thomas, U.; Koelle, H. H.; Balzer-Sieb, R.; Bernau, D.; Czarnitzki, J.; Floete, A.; Goericke, D.; Lindenthal, A.; Protsch, R.; Teschner, O.

    1984-12-01

    The use of nuclear engines in cislunar space was studied and the restrictions imposed on nuclear ferries by the chemical Earth to lower Earth orbit (LEO) transportation system were analyzed. The operating conditions are best met by tungsten-water-moderated reactors due to a high specific impulse and long durability. Specific transportation cost for LEO to geostationary orbit (GEO) and LEO to lunar orbit flights were calculated for a transportation system life of 50 yr. Average transportation costs are estimated to be 141 $/kg. No difference is made for both routes. An additional analysis of smaller and larger flight units shows only small cost reductions by employing larger ferries but a significant cost increase in case smaller flight units are used.

  3. Industrial ecology: Quantitative methods for exploring a lower carbon future

    NASA Astrophysics Data System (ADS)

    Thomas, Valerie M.

    2015-03-01

    Quantitative methods for environmental and cost analyses of energy, industrial, and infrastructure systems are briefly introduced and surveyed, with the aim of encouraging broader utilization and development of quantitative methods in sustainable energy research. Material and energy flow analyses can provide an overall system overview. The methods of engineering economics and cost benefit analysis, such as net present values, are the most straightforward approach for evaluating investment options, with the levelized cost of energy being a widely used metric in electricity analyses. Environmental lifecycle assessment has been extensively developed, with both detailed process-based and comprehensive input-output approaches available. Optimization methods provide an opportunity to go beyond engineering economics to develop detailed least-cost or least-impact combinations of many different choices.

  4. COST Action TU1208 - Working Group 4 - Combined use of GPR and other NDT methods & GPR applications in geosciences

    NASA Astrophysics Data System (ADS)

    Pajewski, Lara; Solla, Mercedes; Fontul, Simona

    2017-04-01

    This work aims at presenting the main results achieved by Working Group (WG) 4 "Different applications of GPR and other NDT technologies in civil engineering" of the COST (European COoperation in Science and Technology) Action TU1208 "Civil Engineering Applications of Ground Penetrating Radar" (www.GPRadar.eu, www.cost.eu). The main objective of the Action TU1208, started in April 2013 and ending in October 2017, is to exchange and increase scientific-technical knowledge and experience of Ground Penetrating Radar (GPR) techniques in civil engineering, whilst promoting in Europe the effective use of this safe non-destructive technique. The Action involves more than 150 Institutions from 28 COST Countries, a Cooperating State, 6 Near Neighbour Countries and 6 International Partner Countries. WG4 deals with the use of GPR outside from the civil engineering area, namely in archaeological prospecting and cultural heritage diagnostics, agriculture and management of water resources, investigation of polluted industrial sites, non-destructive testing of living tree trunks, planetary exploration, demining, localization of people buried under avalanches and debris, and more. Furthermore, this WG studies the integration of GPR with other Non-Destructive Testing (NDT) methods. The most relevant achievements stemming from WG4 will be presented during the 2017 EGU GA. These are: (i) The collection of thorough information on the state-of-the-art, ongoing studies, problems and future research needs on the topics of interest for this WG; (ii) The performance of a plethora of interesting case studies in important sites all over Europe, including well-known historical places such as Stonehenge (United Kingdom), Carnuntum (Austria), the Wawel Cathedral (Cracow, Poland), the Tholos Tomb of Acharnon (Athens, Greece), the Łazienki Royal Palace (Warsaw, Poland), and more; (iii) WG4 contributed to the TU1208 Education Pack, an open educational package conceived to teach GPR in University courses. Additionally, WG4 was very active in offering training activities. In cooperation with the other WGs, the following courses were successfully organised: Training School (TS) "Civil engineering applications of Ground Penetrating Radar" (Pisa, Italy, September 2014), TS "Applications of Ground Penetrating Radar in urban areas: the sensitive case of historical cities" (Cracow, Poland, May 2015), TS "Applications of GPR to civil engineering and archaeology" (Valletta, Malta, January 2016), and TS "Non-destructive testing techniques for civil engineering" (Barcelona, Spain, March 2016). Finally, WG4 contributed to the organization of a series of national events devoted to fostering the interaction of Action Members with stakeholders, new potential GPR end-users, and interested citizens. During such events, participants could discover what is Ground Penetrating Radar (GPR) and how this technique can be effectively used in civil engineering works as well as in different fields ("TU1208 GPR Road Show"). Acknowledgement: The Authors are deeply grateful to COST (European Cooperation in Science and Technology, www.cost.eu), for funding and supporting the COST Action TU1208 "Civil engineering applications of Ground Penetrating Radar" (www.GPRadar.eu).

  5. Engineering Education's Contribution to the Space Program.

    ERIC Educational Resources Information Center

    Stever, H. Guyford

    1988-01-01

    States that an expanding future in space requires new technology. Stresses that from engineering education, space requires people with a fundamental knowledge of modern science instruments, all engineering sciences, an appreciation and capability for detail and systems design, and an understanding of costs and competitiveness, machines, materials,…

  6. RADON REMOVAL BY POINT-OF-ENTRY GRANULAR ACTIVATED CARBON SYSTEMS: DESIGN PERFORMANCE AND COST

    EPA Science Inventory

    The report summarizes previous research conducted by Lowry Engineering, Inc. (LEI), the Maine Department of Human Services, Division of Health Engineering, and the University of Maine, Department of Civil Engineering, on the removal of Rn from drinking water supplies using granul...

  7. How to renovate a 50-year-old wastewater treating plant: Part 1

    DOE Office of Scientific and Technical Information (OSTI.GOV)

    Hunter, M.L.

    1996-01-01

    How does an existing refinery cost-effectively renovate wastewater/stormwater treating systems to meet today`s environmental regulations and standards? Faced with solving this problem, Amoco`s Whiting Refinery developed a project team consisting of plant and operations engineers, corporate project and design engineers, contractors and vendors to map out a strategy to re-engineer the existing wastewater treating plant (WWTP) and auxiliary functions. This case history shows how an old refinery limited by existing equipment, building space, operation`s availability requirements and costs divided the project into several design phases. The design team used a proactive approach with empowerment responsibilities to solve construction, equipment usagemore » and regulatory problems throughout the project`s lifetime. Focusing on front-end planning and customer service (the refinery), team members applied value-based engineering designs to keep costs down, implemented safe work practices during construction, used HAZOP reviews to scrutinize proposed designs for operating and maintenance procedures, etc. The result has been the renovation of a 50-year-old WWTP completed under budget, ontime and in compliance with federal mandates.« less

  8. A Regeneratively Cooled Thrust Chamber For The Fastrac Engine

    NASA Technical Reports Server (NTRS)

    Brown, Kendall K.; Sparks, Dave; Woodcock, Gordon

    2000-01-01

    Abstract This paper presents the development of a low-cost, regeneratively-cooled thrust chamber for the Fastrac engine. The chamber was fabricated using hydraformed copper tubing to form the coolant jacket and wrapped with a fiber reinforced polymer composite Material to form a structural jacket. The thrust chamber design and fabrication approach was based upon Space America. Inc.'s 12,000 lb regeneratively-cooled LOX/kerosene rocket engine. Fabrication of regeneratively cooled thrust chambers by tubewall construction dates back to the early US ballistic missile programs. The most significant innovations in this design was the development of a low-cost process for fabrication from copper tubing (nickel alloy was the usual practice) and use of graphite composite overwrap as the pressure containment, which yields an easily fabricated, lightweight pressure jacket around the copper tubes A regeneratively-cooled reusable thrust chamber can benefit the Fastrac engine program by allowing more efficient (cost and scheduler testing). A proof-of-concept test article has been fabricated and will he tested at Marshall Space Flight Center in the late Summer or Fall of 2000.

  9. Safety effects of low-cost engineering measures. An observational study in a Portuguese multilane road.

    PubMed

    Vieira Gomes, Sandra; Cardoso, João Lourenço

    2012-09-01

    Single carriageway multilane roads are not, in general, a very safe type of road, mainly because of the high number of seriously injured victims in head-on collisions, when compared with dual carriageway multilane roads, with a median barrier. In this paper the results of a study on the effect of the application of several low cost engineering measures, aimed at road infrastructure correction and road safety improvement on a multilane road (EN6), are presented. The study was developed by the National Laboratory of Civil Engineering (LNEC) for the Portuguese Road Administration and involved a comparison of selected aspects of motorized traffic behaviour (traffic volumes and speeds) measured in several sections of EN6, as well as monitoring of road safety developments in the same road. The applied low cost engineering measures allowed a reduction of 10% in the expected annual number of personal injury accidents and a 70% decrease in the expected annual number of head-on collisions; the expected annual frequency of accidents involving killed and seriously injured persons was reduced by 26%. Copyright © 2012 Elsevier Ltd. All rights reserved.

  10. Analyzing system safety in lithium-ion grid energy storage

    NASA Astrophysics Data System (ADS)

    Rosewater, David; Williams, Adam

    2015-12-01

    As grid energy storage systems become more complex, it grows more difficult to design them for safe operation. This paper first reviews the properties of lithium-ion batteries that can produce hazards in grid scale systems. Then the conventional safety engineering technique Probabilistic Risk Assessment (PRA) is reviewed to identify its limitations in complex systems. To address this gap, new research is presented on the application of Systems-Theoretic Process Analysis (STPA) to a lithium-ion battery based grid energy storage system. STPA is anticipated to fill the gaps recognized in PRA for designing complex systems and hence be more effective or less costly to use during safety engineering. It was observed that STPA is able to capture causal scenarios for accidents not identified using PRA. Additionally, STPA enabled a more rational assessment of uncertainty (all that is not known) thereby promoting a healthy skepticism of design assumptions. We conclude that STPA may indeed be more cost effective than PRA for safety engineering in lithium-ion battery systems. However, further research is needed to determine if this approach actually reduces safety engineering costs in development, or improves industry safety standards.

  11. Energy Efficient Engine Program: Technology Benefit/Cost Study, Volume II

    NASA Technical Reports Server (NTRS)

    Gray, D. E.; Gardner, W. B.

    1983-01-01

    The Benefit/Cost Study portion of the NASA-sponsored Energy Efficient Engine Component Development and Integration program was successful in achieving its objectives: identification of air transport propulsion system technology requirements for the years 2000 and 2010, and formulation of programs for developing these technologies. It is projected that the advanced technologies identified, when developed to a state of readiness, will provide future commercial and military turbofan engines with significant savings in fuel consumption and related operating costs. These benefits are significant and far from exhausted. The potential savings translate into billions of dollars in annual savings for the airlines. Analyses indicate that a significant portion of the overall savings is attributed to aerodynamic and structure advancements. Another important consideration in acquiring these benefits is developing a viable reference technology base that will permit engines to operate at substantially higher overall pressure ratios and bypass ratios. Results have pointed the direction for future research and a comprehensive program plan for achieving this was formulated. The next major step is initiating the program effort that will convert the advanced technologies into the expected benefits.

  12. 23 CFR 661.21 - When is a bridge eligible for rehabilitation?

    Code of Federal Regulations, 2014 CFR

    2014-04-01

    ... Section 661.21 Highways FEDERAL HIGHWAY ADMINISTRATION, DEPARTMENT OF TRANSPORTATION ENGINEERING AND... eligible for rehabilitation may be replaced if the life cycle cost analysis is conducted which shows the cost for bridge rehabilitation exceeds the replacement cost. ...

  13. 23 CFR 661.21 - When is a bridge eligible for rehabilitation?

    Code of Federal Regulations, 2013 CFR

    2013-04-01

    ... Section 661.21 Highways FEDERAL HIGHWAY ADMINISTRATION, DEPARTMENT OF TRANSPORTATION ENGINEERING AND... eligible for rehabilitation may be replaced if the life cycle cost analysis is conducted which shows the cost for bridge rehabilitation exceeds the replacement cost. ...

  14. 23 CFR 661.21 - When is a bridge eligible for rehabilitation?

    Code of Federal Regulations, 2012 CFR

    2012-04-01

    ... Section 661.21 Highways FEDERAL HIGHWAY ADMINISTRATION, DEPARTMENT OF TRANSPORTATION ENGINEERING AND... eligible for rehabilitation may be replaced if the life cycle cost analysis is conducted which shows the cost for bridge rehabilitation exceeds the replacement cost. ...

  15. Concepts for Distributed Engine Control

    NASA Technical Reports Server (NTRS)

    Culley, Dennis E.; Thomas, Randy; Saus, Joseph

    2007-01-01

    Gas turbine engines for aero-propulsion systems are found to be highly optimized machines after over 70 years of development. Still, additional performance improvements are sought while reduction in the overall cost is increasingly a driving factor. Control systems play a vitally important part in these metrics but are severely constrained by the operating environment and the consequences of system failure. The considerable challenges facing future engine control system design have been investigated. A preliminary analysis has been conducted of the potential benefits of distributed control architecture when applied to aero-engines. In particular, reductions in size, weight, and cost of the control system are possible. NASA is conducting research to further explore these benefits, with emphasis on the particular benefits enabled by high temperature electronics and an open-systems approach to standardized communications interfaces.

  16. Pros, Cons, and Alternatives to Weight Based Cost Estimating

    NASA Technical Reports Server (NTRS)

    Joyner, Claude R.; Lauriem, Jonathan R.; Levack, Daniel H.; Zapata, Edgar

    2011-01-01

    Many cost estimating tools use weight as a major parameter in projecting the cost. This is often combined with modifying factors such as complexity, technical maturity of design, environment of operation, etc. to increase the fidelity of the estimate. For a set of conceptual designs, all meeting the same requirements, increased weight can be a major driver in increased cost. However, once a design is fixed, increased weight generally decreases cost, while decreased weight generally increases cost - and the relationship is not linear. Alternative approaches to estimating cost without using weight (except perhaps for materials costs) have been attempted to try to produce a tool usable throughout the design process - from concept studies through development. This paper will address the pros and cons of using weight based models for cost estimating, using liquid rocket engines as the example. It will then examine approaches that minimize the impct of weight based cost estimating. The Rocket Engine- Cost Model (RECM) is an attribute based model developed internally by Pratt & Whitney Rocketdyne for NASA. RECM will be presented primarily to show a successful method to use design and programmatic parameters instead of weight to estimate both design and development costs and production costs. An operations model developed by KSC, the Launch and Landing Effects Ground Operations model (LLEGO), will also be discussed.

  17. Small Engine Component Technology (SECT)

    NASA Technical Reports Server (NTRS)

    Early, M.; Dawson, R.; Zeiner, P.; Turk, M.; Benn, K.

    1986-01-01

    A study of small gas turbine engines was conducted to identify high payoff technologies for year-2000 engines and to define companion technology plans. The study addressed engines in the 186 to 746 KW (250 to 1000 shp) or equivalent thrust range for rotorcraft, commuter (turboprop), cruise missile (turbojet), and APU applications. The results show that aggressive advancement of high payoff technologies can produce significant benefits, including reduced SFC, weight, and cost for year-2000 engines. Mission studies for these engines show potential fuel burn reductions of 22 to 71 percent. These engine benefits translate into reductions in rotorcraft and commuter aircraft direct operating costs (DOC) of 7 to 11 percent, and in APU-related DOCs of 37 to 47 percent. The study further shows that cruise missile range can be increased by as much as 200 percent (320 percent with slurry fuels) for a year-2000 missile-turbojet system compared to a current rocket-powered system. The high payoff technologies were identified and the benefits quantified. Based on this, technology plans were defined for each of the four engine applications as recommended guidelines for further NASA research and technology efforts to establish technological readiness for the year 2000.

  18. An Application of Cost-Effectiveness Analysis in a Major Defense Acquisition Program: the Decision by the U.S. Department of Defense to Retain the C-17 Transport Aircraft

    DTIC Science & Technology

    2010-12-01

    adding hush kits to dampen the sound of the engines and adding extra material to the fuselage. The cost to restart the C-5 line was estimated at $750...include adding hush kits to dampen the sound of the engines and extra material to the fuselage. A recently completed SAB had recommended that the weep

  19. A Cost Estimation Analysis of U.S. Navy Ship Fuel-Savings Techniques and Technologies

    DTIC Science & Technology

    2009-09-01

    readings to the boiler operator. The PLC will provide constant automatic trimming of the excess oxygen based upon real time SGA readings. An SCD...the author): The Aegis Combat System is controlled by an advanced, automatic detect-and-track, multi-function three-dimensional passive...subsequently offloaded. An Online Wash System would reduce these maintenance costs and improve fuel efficiency of these engines by keeping the engines

  20. Military Free Fall Scheduling And Manifest Optimization Model

    DTIC Science & Technology

    2016-12-01

    engines running waiting for the next student load. The annual blade hour cost, which consists of fuel, maintenance, and personnel, is $5.6M for FY-16...tarmac with engines running waiting for the next student load (J. Enke, personal communication, 2016). The annual blade hour cost, which consists of...33 Scenario 2 Nonstandard Run #1 C-27 Two Passes per Lift .......................34 Table 9. xii THIS PAGE INTENTIONALLY LEFT BLANK xiii

Some links on this page may take you to non-federal websites. Their policies may differ from this site.
Top