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  • AIRCRAFT PROPULSION AND POWER  (43)
  • 1995-1999
  • 1990-1994
  • 1980-1984  (43)
  • 1975-1979
  • 1945-1949
  • 1980  (43)
Collection
Keywords
Years
  • 1995-1999
  • 1990-1994
  • 1980-1984  (43)
  • 1975-1979
  • 1945-1949
Year
  • 1
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    Preparing aircraft propulsion for a new era in energy and the environment (1980)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: Improving fuel efficiency, new sources of jet fuel, and noise and emission control are subjects of NASA's aeronautics program. Projects aimed at attaining a 5% fuel savings for existing engines and a 13-22% savings for the next generation of turbofan engines using advanced components, and establishing a basis for turboprop-powered commercial air transports with 30-40% savings over conventional turbofan aircraft at comparable speeds and altitudes, are discussed. Fuel sources are considered in terms of reduced hydrogen and higher aromatic contents and resultant higher liner temperatures, and attention is given to lean burning, improved fuel atomization, higher freezing-point fuel, and deriving jet fuel from shale oil or coal. Noise sources including the fan, turbine, combustion process, and flow over internal struts, and attenuation using acoustic treatment, are discussed, while near-term reduction of polluting gaseous emissions at both low and high power, and far-term defining of the minimum gaseous-pollutant levels possible from turbine engines are also under study.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Astronautics and Aeronautics; 18; Jan. 198
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Propulsion Study for Small Transport Aircraft Technology (STAT) (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Propulsion requirements were determined for 0.5 and 0.7 Mach aircraft. Sensitivity studies were conducted on both these aircraft to determine parametrically the influence of propulsion characteristics on aircraft size and direct operating cost (DOC). Candidate technology elements and design features were identified and parametric studies conducted to select the STAT advanced engine cycle. Trade off studies were conducted to determine those advanced technologies and design features that would offer a reduction in DOC for operation of the STAT engines. These features were incorporated in the two STAT engines. A benefit assessment was conducted comparing the STAT engines to current technology engines of the same power and to 1985 derivatives of the current technology engines. Research and development programs were recommended as part of an overall technology development plan to ensure that full commercial development of the STAT engines could be initiated in 1988.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165499 , DDA-EDR-10470
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Energy efficient engine (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The feasibility of meeting or closely approaching the emissions goals established for the Energy Efficient Engine (E3) Project with an advanced design, single annular combustor was determined. A total of nine sector combustor configurations and one full-annular-combustor configuration were evaluated. Acceptable levels of carbon monoxide and hydrocarbon emissions were obtained with several of the sector combustor configurations tested, and several of the configurations tested demonstrated reduced levels of nitrogen oxides compared to conventional, single annular designs. None of the configurations tested demonstrated nitrogen oxide emission levels that meet the goal of the E3 Project.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-159685 , R79AEG562
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    A theoretical and experimental investigation of propeller performance methodologies (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper briefly covers aspects related to propeller performance by means of a review of propeller methodologies; presentation of wind tunnel propeller performance data taken in the NASA Lewis Research Center 10 x 10 wind tunnel; discussion of the predominent limitations of existing propeller performance methodologies; and a brief review of airfoil developments appropriate for propeller applications.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 80-1240 , Joint Propulsion Conference; Jun 30, 1980 - Jul 02, 1980; Hartford, CT
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Energy efficient engine: Flight propulsion system preliminary analysis and design (1980)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: 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.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-159583 , R79AEG623
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Results from tests on a high work transonic turbine for an energy efficient engine (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The experimental results of the evaluation of two high work, transonic, single-stage turbines investigated under the Energy Efficient Engine (E3) Program are presented. The objective of the E3 program is to provide an advanced technology base for a new generation of fuel-conservative turbofan engines. A single-stage turbine required fewer cooled airfoils, a reduced number of leakage paths and no interstage seals. These advanced energy efficient engines require high engine pressure ratios resulting in high expansion ratio, transonic, turbine designs which must have high aerodynamic efficiency. The goal of the turbine program is to develop a high pressure turbine that is compatible with the overall engine design and has an uncooled efficiency of 90.8 percent.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: ASME PAPER 80-GT-146 , Gas Turbine Conference and Products Show; Mar 10, 1980 - Mar 13, 1980; New Orleans, LA
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Propulsion controls (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Increased system requirements and functional integration with the aircraft have placed an increased demand on control system capability and reliability. To provide these at an affordable cost and weight and because of the rapid advances in electronic technology, hydromechanical systems are being phased out in favor of digital electronic systems. The transition is expected to be orderly from electronic trimming of hydromechanical controls to full authority digital electronic control. Future propulsion system controls will be highly reliable full authority digital electronic with selected component and circuit redundancy to provide the required safety and reliability. Redundancy may include a complete backup control of a different technology for single engine applications. The propulsion control will be required to communicate rapidly with the various flight and fire control avionics as part of an integrated control concept.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Propulsion Controls, 1979; p 49-59
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Low speed propellers: Impact of advanced technologies (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Sensitivity studies performed to evaluate the potential of several advanced technological elements on propeller performance, noise, weight, and cost for general aviation aircraft are discussed. Studies indicate that the application of advanced technologies to general aviation propellers can reduce fuel consumption in future aircraft an average of ten percent, meeting current regulatory noise limits. Through the use of composite blade construction, up to 25 percent propeller weight reduction can be achieved. This weight reduction in addition to seven percent propeller efficiency improvements through application of advanced technologies result in four percent reduction in direct operating costs, ten percent reduction in aircraft acquisition cost, and seven percent lower gross weight for general aviation aircraft.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Gen. Aviation Propulsion; p 327-343
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    NASA propeller technology program (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A program on propeller technology applicable to both low and high speed general aviation aircraft is summarized, and the overall program objectives and approach are outlined.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Gen. Aviation Propulsion; p 315-325
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Effect of fuel molecular structure on soot formation in gas turbine combustion (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The effect of fuel variations at the same hydrogen content on the formation of soot in a gas turbine combustor was studied. Six fuels were burned to a combustor over a matrix of about 50 test conditions with test conditions ranging over 500-1800 kPa (5-18 atm) pressure and 500-1000 K burner inlet temperature; fuel-air ratios were varied from 0.008-0.024. Flame radiation measurements were made through a sapphire window toward the end of the primary zone. The hydrogen content of the six test fuels ranged from 12.80 to 12.88%. Five fuels emphasized hydrocarbon types: (mono, di, and tricyclic), naphthenes (decalin) and partially hydrogenated aromatics (tetralin); the sixth fuel emphasized final boiling point.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 147-152
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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