550 research outputs found

    Aeronautical engineering: A special bibliography with indexes, supplement 80

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    This bibliography lists 277 reports, articles, and other documents introduced into the NASA scientific and technical information system in January 1977

    Bibliography of Lewis Research Center technical publications announced in 1980

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    This compilation of abstracts describes and indexes over 780 research reports, journal articles, conference presentations, patents and patent applications, and theses resulting from the scientific and engineering work performed and managed by the Lewis Research Center in 1980. All the publications were announced in Scientific and Technical Aerospace Reports and/or International Aerospace Abstracts

    Aeronautical Engineering: A special bibliography with indexes, supplement 64, December 1975

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    This bibliography lists 288 reports, articles, and other documents introduced into the NASA scientific and technical information system in November 1975

    Aeronautical Engineering: A continuing bibliography with indexes, supplement 99

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    This bibliography lists 292 reports, articles, and other documents introduced into the NASA scientific and technical information system in July 1978

    The advanced low-emissions catalytic-combuster program. Phase 1: Description and status

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    An overview of the ongoing program is presented. Objectives, plan, schedule, pollution and performance goals, catalyst advantages, present problems, and the present status of identified combustor concepts are discussed. The possible increase in upper atmosphere oxides of nitrogen (NOx) levels due to aircraft number density increases was predicted to adversely decrease ozone concentration levels. A technique for achieving low NOx emission levels was experimentally demonstrated with a lean, premixing prevaporizing flame-tube combustor

    Effects of turbine cooling assumptions on performance and sizing of high-speed civil transport

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    The analytical study presented examines the effects of varying turbine cooling assumptions on the performance of a high speed civil transport propulsion system as well as the sizing sensitivity of this aircraft to these performance variations. The propulsion concept employed in this study was a two spool, variable cycle engine with a sea level thrust of 55,000 lbf. The aircraft used for this study was a 250 passenger vehicle with a cruise Mach number of 2.4 and 5000 nautical mile range. The differences in turbine cooling assumptions were represented by varying the amount of high pressure compressor bleed air used to cool the turbines. It was found that as this cooling amount increased, engine size and weight increased, but specific fuel consumption (SFC) decreased at takeoff and climb only. Because most time is spent at cruise, the SFC advantage of the higher bleed engines seen during subsonic flight was minimized and the lower bleed, lighter engines led to the lowest takeoff gross weight vehicles. Finally, the change in aircraft takeoff gross weight versus turbine cooling level is presented

    Aeronautical engineering. A continuing bibliography with indexes, supplement 121, April 1980

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    This bibliography lists 411 reports, articles, and other documents introduced into the NASA Scientific and Technical Information system in March 1980

    The impact of emissions standards on the design of aircraft gas turbine engine combustors

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    Effective emission control techniques have been identified and a wide spectrum of potential applications for these techniques to existing and advanced engines are being considered. Results from advanced combustor concept evaluations and from fundamental experiments are presented and discussed and comparisons are made with existing EPA emission standards and recommended levels for high altitude cruise. The impact that the advanced low emission concepts may impose on future aircraft engine combustor designs and related engine components is discussed

    NASA broad-specification fuels combustion technology program: Status and description

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    The program presented is a contracted effort to evolve and demonstrate the technology required to utilize broad-specification fuels in current and next generation commercial Conventional Takeoff and Landing aircraft engines, and to verify this technology in full-scale engine tests in 1983. The program consists of three phases: Combustor Concept Screening, Combustor Optimization Testing, and Engine Verification Testing. The development and screening of the combustion system designs for the CF6-80 engine and the JT9D-7 engine, respectively, in high-pressure sector test rigs are reported

    State of technology on hydrogen fueled gas turbine engines

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    A series of investigations was conducted episodically from the 1950's to the early 1970's to investigate the feasibility and potential problem areas in the use of hydrogen fuel for gas turbine engines. A brief summary and bibliography are presented of the research that has been conducted by NASA, its predecessor NACA, and by industry under U. S. Air Force sponsorship. Although development efforts would be required to provide hydrogen fueled gas turbine engines for aircraft, past research has shown that hydrogen fueled engines are feasible, and except for flight weight liquid hydrogen pumps, there are no problem areas relating to engines requiring significant research
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