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  • 1
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    Advanced Propfan Engine Technology (APET) definition study, single and counter-rotation gearbox/pitch change mechanism design (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Single-rotation propfan-powered regional transport aircraft were studied to identify key technology development issues and programs. The need for improved thrust specific fuel consumption to reduce fuel burned and aircraft direct operating cost is the dominant factor. Typical cycle trends for minimizing fuel consumption are reviewed, and two 10,000 shp class engine configurations for propfan propulsion systems for the 1990's are presented. Recommended engine configurations are both three-spool design with dual spool compressors and free power turbines. The benefits of these new propulsion system concepts were evaluated using an advanced airframe, and results are compared for single-rotation propfan and turbofan advanced technology propulsion systems. The single-rotation gearbox is compared to a similar design with current technology to establish the benefits of the advanced gearbox technology. The conceptual design of the advanced pitch change mechanism identified a high pressure hydraulic system that is superior to the other contenders and completely external to the gearboxes.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-168115 , NAS 1.26:168115 , EDR-11283
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Advanced propfan engine characteristics and technology needs (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A comparative study is presented for two of the advanced gas turbine engine designs developed in the course of a proprietary research effort for the NASA Advanced Propfan Engine Technology research program. In these engines, a cycle pressure ratio of 32.5:1 and a 2500 F maximum turbine temperature provide fuel efficient operation in the 32,000-ft altitude, Mach 0.72 cruise speed regime stipulated. Both of the engine configurations incorporate three spools, of which the compressors are dual-spool and the power turbines are free. A major design challenge for axial compressors in the 10,000-shp class was the maintenance of adequate blade heights in the later stages.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 83-1155
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Advanced propfan drive system characteristics and technology needs (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Characteristics of a single-rotation drive system for an advanced turboprop engine are described. The gearbox is designed for a 10,000 shp three-spool, free-turbine engine and is installed in a wing-mounted nacelle. An offset gearbox from an earlier APET study provided the background for the preliminary design and benefit analysis for a 1990s advanced technology versus 1980s state-of-the-art gearbox. High efficiencies were achieved for both designs with inherently high life goals. Increases in design allowables for gears, bearings, and lubricants resulted in improvements for the 1990s design.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 84-1194
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Pollution Reduction Technology Program, Turboprop Engines, Phase 1 (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Exhaust pollutant emissions were measured from a 501-D22A turboprop engine combustor and three low emission combustor types -- reverse flow, prechamber, and staged fuel, operating over a fuel-air ratio range of .0096 to .020. The EPAP LTO cycle data were obtained for a total of nineteen configurations. Hydrocarbon emissions were reduced from 15.0 to .3 lb/1000 Hp-Hr/cycle, CO from 31.5 to 4.6 lb/1000 Hp-Hr/cycle with an increase in NOx of 17 percent, which is still 25% below the program goal. The smoke number was reduced from 59 to 17. Emissions given here are for the reverse flow Mod. IV combustor which is the best candidate for further development into eventual use with the 501-D22A turboprop engine. Even lower emissions were obtained with the advanced technology combustors.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135040 , EDR-8708
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Two-Dimensional Imaging of OH in a Lean Burning High Pressure Combustor (1995)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Planar laser-induced fluorescence (PLIF) images of OH have been obtained from an optically accessible, lean burning high pressure combustor burning Jet-A fuel. These images were obtained using various laser excitation lines of the OH A (reverse arrow) X (1,0) band for several fuel injector configurations with pressures ranging from 1013 kPa (10 atm) to 1419 kPa (14 atm). Non-uniformities in the combusting flow, attributed to differences in fuel injector configuration, are revealed by these images. Contributions attributable to fluorescent aromatic hydrocarbons and complex fuel chemistries are also not evident.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-106854 , E-9444 , NAS 1.15:106854 , AIAA PAPER 95-0173 , Aerospace Sciences Meeting and Exhibit; Jan 09, 1995 - Jan 12, 1995; Reno, NV; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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