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  • AIRCRAFT PROPULSION AND POWER  (65)
  • 1980-1984
  • 1975-1979  (65)
  • 1935-1939
  • 1975  (65)
  • 1
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    A study of casing treatment stall margin improvement phenomena (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The results of a program of experimental and analytical research in casing treatments over axial compressor rotor blade tips are presented. Circumferential groove, axial-skewed slot and blade angle slot treatments were tested at low speeds. With the circumferential groove treatment the stalling flow was reduced 5.8% at negligible efficiency sacrifice. The axial-skewed slot treatment improved the stalling flow by 15.3%; 1.8 points in peak efficiency were sacrificed. The blade angle slot treatment improved the stalling flow by 15.0%; 1.4 points in peak efficiency were sacrificed. The favorable stalling flow situations correlated well with observations of higher-than-normal surface pressures on the rotor blade pressure surfaces in the tip region, and with increased maximum diffusions on the suction surfaces. Annulus wall pressure gradients, especially in the 50 to 75% chord region, are also increased and blade surface pressure loadings are shifted toward the trailing edge for treated configurations.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: ASME PAPER 75-GT-60 , American Society of Mechanical Engineers, Gas Turbine Conference and Products Show; Mar 02, 1975 - Mar 06, 1975; Houston, TX
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Further studies of methods for reducing community noise around airports (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A simplified method of analysis was used in which all flights at a 'simulated' airport were assumed to operate from one runway in a single direction. For this simulated airport, contours of noise exposure forecast were obtained and evaluated. A flight schedule of the simulated airport which is representative of the 23 major U. S. airports was used. The effect of banning night-time operations by four-engine, narrow-body aircraft in combination with other noise reduction options was studied. The reductions in noise which would occur of two- and three-engine, narrow-body aircraft equipped with a refanned engine was examined. A detailed comparison of the effects of engine cutback on takeoff versus the effects of retrofitting quiet nacelles for narrow-body aircraft was also examined. A method of presenting the effects of various noise reduction options was treated.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-137739 , NEAR-TR-86
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Propulsion system noise reduction (1975)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: The progress in propulsion system noise reduction is reviewed. The noise technology areas discussed include: fan noise; advances in suppression including conventional acoustic treatment, high Mach number inlets, and wing shielding; engine core noise; flap noise from both under-the-wing and over-the-wing powered-lift systems; supersonic jet noise suppression; and the NASA program in noise prediction.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeron. Propulsion; p 1-63
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Upper atmosphere pollution measurements (GASP) (1975)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The environmental effects are discussed of engine effluents of future large fleets of aircraft operating in the stratosphere. Topics discussed include: atmospheric properties, aircraft engine effluents, upper atmospheric measurements, global air sampling, and data reduction and analysis
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeron. Propulsion; p 139-156
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Combustion and emissions technology (1975)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: Combustor development is discussed as it relates to emissions reduction. The nature of the aircraft pollution problem is examined along with the aircraft pollution standards that have been established by the Environmental Protection Agency. The effect of engine operating conditions on pollutant formation levels is shown, as well as how close present-day engines are to meeting the established standards. The magnitude of the emissions reductions required to meet these standards is indicated. The progress that has been made in evolving the needed emissions reduction technology is the main topic.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeron. Propulsion; p 99-137
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Demonstration of short-haul aircraft aft noise reduction techniques on a twenty inch (50.8) diameter fan, volume 2 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Aft fan noise reduction techniques were investigated. The 1/3 octave band sound data were plotted with the following plots included: perceived noise level vs acoustic angle at 2 fan speeds; PWL vs frequency at 2 fan speeds; and sound pressure level vs frequency at 2 aft angles and 2 fan speeds. The source noise plots included: band pass filter sound pressure level vs acoustic angle at 2 fan speeds; and 2nd harmonic SPL acoustic angle at 2 fan speeds.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-134850 , R75AEG252-VOL-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Demonstration of short haul aircraft aft noise reduction techniques on a twenty inch (50.8 cm) diameter fan, volume 3 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Tests of a twenty inch diameter, low tip speed, low pressure ratio fan which investigated aft fan noise reduction techniques are reported. The 1/3 octave band sound data are presented for all the configurations tested. The model data are presented on 17 foot arc and extrapolated to 200 foot sideline.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-134851 , R75AEG252-VOL-3
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Demonstration of short-haul aircraft aft noise reduction techniques on a twenty inch (50.8 cm) diameter fan, volume 1 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Tests of a 20 inch diameter, low tip speed, low pressure ratio fan which investigated aft fan noise reduction techniques are reported. These techniques included source noise reduction features of selection of vane-blade ratio to reduce second harmonic noise, spacing effects, and lowering the Mach number through a vane row. Aft suppression features investigated included porosity effects, variable depth treatment, and treatment regenerated flow noise. Initial results and selected comparisons are presented.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-134849 , R75AEG252-VOL-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Effect of a 180 deg-extent inlet pressure distortion on the internal flow conditions of a TF30-P-3 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The measured effects of inlet pressure distortion on the internal flow temperatures and pressures of a TF30-P-3 afterburning turbofan engine are reported. Extensive inner-stage instrumentation combined with stepwise rotation of pressure distortion provided a high degree of circumferential resolution in the data. The steady-state spatial variation in pressures, temperature, and calculated flow velocity and the amplitude and extent of the distorted sectors are given. Data are presented for runs of 77 and 90 percent of low-speed-rotor design speed at pressure distortion levels two-thirds of that required to stall the engine. These data are compared with data taken at clean-inlet conditions. Results indicate that the inlet pressure distortion was quickly attenuated within the compressor, except at the hub of the low-pressure compressor. The distorted sectors also swirled and varied in extent as they passed through the engine. Average velocities within the compressor were about equal to the clean-inlet values.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-3267 , E-8206
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Analysis of turbofan engine performance deterioration and proposed follow-on tests (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Data and engine parts on in-service JT3D and JT8D engines were analyzed and documented relative to engine deterioration. It is concluded that the fan-compressor system of these engines contributes to the long term engine deterioration. An engine test and instrumentation plan was formulated for a proposed follow-on program. The goal of this program is to verify the above conclusion and to attempt to identify more precisely which components of the fan-compressor system are at fault.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-134769
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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