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  • Other Sources  (218)
  • AIRCRAFT PROPULSION AND POWER  (207)
  • Aircraft Stability and Control
  • Chemical Engineering
  • GENERAL
  • 1980-1984  (218)
  • 1
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    Aerodynamic and acoustic behavior of a YF-12 inlet at static conditions (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An aeroacoustic test program to determine the cause of YF-12 inlet noise suppression was performed with a YF-12 aircraft at ground static conditions. Data obtained over a wide range of engine speeds and inlet configurations are reported. Acoustic measurements were made in the far field and aerodynamic and acoustic measurements were made inside the inlet. The J-58 test engine was removed from the aircraft and tested separately with a bellmouth inlet. The far field noise level was significantly lower for the YF-12 inlet than for the bellmouth inlet at engine speeds above 5500 rpm. There was no evidence that noise suppression was caused by flow choking. Multiple pure tones were reduced and the spectral peak near the blade passing frequency disappeared in the region of the spike support struts at engine speeds between 6000 and 6600 rpm.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-163106 , LR-29623
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Recent propulsion system flight tests at the NASA Dryden Flight Research Center (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The article presents a summary of the propulsion system tests conducted on a number of aircraft at the NASA Dryden Flight Research Center. The tests included digital engine control systems, engine-inlet compatibility, inlet-airframe interactions, nozzle-boattail drag and advanced turboprop acoustics. Among the aircraft evaluated were the F-15, HiMAT, F-14, and the JetStar.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 81-2438 , Flight Testing Conference; Nov 11, 1981 - Nov 13, 1981; Las Vegas, NV
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Comparison of several inflow control devices for flight simulation of fan tone noise using a JT15D-1 engine (1980)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: To enable accurate simulation of in-flight fan tone noise during ground static tests, four devices intended to reduce inflow disturbances and turbulence were tested with a JT15D-1 turbofan engine. These inflow control devices (ICD's) consisted of honeycomb/screen structures mounted over the engine inlet. The ICD's ranged from 1.6 to 4 fan diameters in size, and differed in shape and fabrication method. All the ICD's significantly reduced the BPF tone in the far-field directivity patterns, but the smallest ICD's apparently introduced propagating modes which could be recognized by additional lobes in the speeds; at supersonic fan tip speed the smallest ICD's had some measurable loss, but the largest had no loss. Data from a typical transducer show that the unsteady inflow distortion modes (turbulence) were eliminated or significantly reduced when either of the ICD's was installed. However, some steady inflow distortion modes remained.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-81505 , E-443 , Aeroacoustics Conf.; Jun 04, 1980 - Jun 06, 1980; Hartford
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Aerodynamic and acoustic behavior of a YF-12 inlet at static conditions (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An aeroacoustic test program was performed with a YF-12 aircraft at ground static conditions. The objective was to collect acoustic and aerodynamic data that could determine the cause of YF-12 inlet noise suppression observed earlier. The results showed that the far-field noise level was lower with the YF-12 inlet than with a bellmouth inlet at engine speeds above 5500 rpm. The differences were about 5 PNdB to 11 PNdB, depending on YF-12 inlet configuration and on engine speed. Measurements showed that YF-12 inlet noise suppression was not caused by flow choking. The spike support struts were probably responsible, as in that region the spectral peak near the blade passing frequency disappeared between 6000 and 6600 rpm, and multiple pure tones were greatly reduced.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 81-1597 , Joint Propulsion Conference; Jul 27, 1981 - Jul 29, 1981; Colorado Springs, CO; US
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Comparison of several inflow control devices for flight simulation of fan tone noise using a JT15D-1 engine (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The paper describes the tests of four devices intended to reduce inflow disturbances and turbulences using a JT15D-1 turbofan engine. The tests were made to simulate the in-flight fan tone noise; the inflow control devices (ICD's) consisted of honeycomb/screen structures mounted over the engine inlet. The ICD's ranged from 1.6 to 4 fan diameters in size, and were made with several fabrication methods. All the ICD's significantly reduced the BPF tone in the far-field directivity patterns, but the smallest ICD's introduced propagating modes which could be recognized by additional lobes in the patterns. The JT15D-1 engine had a tone source which generated a strong propagating mode at fan speeds corresponding to 'approach' power and higher. Data from a typical transducer showed that the unsteady inflow distortion modes were eliminated or reduced when either of the ICD's was installed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 80-1025 , Aeroacoustics Conference; Jun 04, 1980 - Jun 06, 1980; Hartford, CT
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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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
  • 7
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    End-wall boundary layer measurements in a two-stage fan (1983)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: Detailed flow measurements made in the casing boundary layer of a two-stage transonic fan are summarized. These measurements were taken at stations upstream of the fan, between all blade rows, and downstream of the last blade row. At the design tip speed of 429 m/sec the fan achieved a peak efficiency of 0.846 at a pressure ratio of 2.471. The boundary layer data were obtained at three weight flows at the design speed: one near choke flow, one near peak efficiency, and one near stall. Conventional boundary layer parameters were calculated from the data measured at each measuring station for each of the three flows. A classical two dimensional casing boundary layer was measured at the fan inlet and extended inward to approximately 15 percent of span. A highly three dimensional boundary layer was measured at the exit of each blade row and extended inward to approximately 10 percent of span. The steep radial gradient of axial velocity noted at the exit of the rotors was reduced substantially as the flow passed through the stators. This reduced gradient is attributed to flow mixing. The amount of flow mixing was reflected in the radial redistribution of total temperature as the flow passed through the stators. The data also show overturning of the tip flow at the stator exits that is consistent with the expected effect of the secondary flow field. The blockage factors calculated from the measured data show an increase in blockage across the rotors and a decrease across the stators.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AGARD Viscous Effects in Turbomachines; 23 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Energy Efficient Engine (E3) combustion system component technology performance report (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The Energy Efficient Engine (E3) combustor effort was conducted as part of the overall NASA/GE E3 Program. This effort included the selection of an advanced double-annular combustion system design. The primary intent of this effort was to evolve a design that meets the stringent emissions and life goals of the E3, as well as all of the usual performance requirements of combustion systems for modern turbofan engines. Numerous detailed design studies were conducted to define the features of the combustion system design. Development test hardware was fabricated, and an extensive testing effort was undertaken to evaluate the combustion system subcomponents in order to verify and refine the design. Technology derived from this effort was incorporated into the engine combustion hardware design. The advanced engine combustion system was then evaluated in component testing to verify the design intent. What evolved from this effort was an advanced combustion system capable of satisfying all of the combustion system design objectives and requirements of the E3.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-168274 , NAS 1.26:168274 , R82AEB401
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Energy Efficient Engine combustor test hardware detailed design report (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The Energy Efficient Engine (E3) Combustor Development effort was conducted as part of the overall NASA/GE E3 Program. This effort included the selection of an advanced double-annular combustion system design. The primary intent was to evolve a design which meets the stringent emissions and life goals of the E3 as well as all of the usual performance requirements of combustion systems for modern turbofan engines. Numerous detailed design studies were conducted to define the features of the combustion system design. Development test hardware was fabricated, and an extensive testing effort was undertaken to evaluate the combustion system subcomponents in order to verify and refine the design. Technology derived from this development effort will be incorporated into the engine combustion system hardware design. This advanced engine combustion system will then be evaluated in component testing to verify the design intent. What is evolving from this development effort is an advanced combustion system capable of satisfying all of the combustion system design objectives and requirements of the E3. Fuel nozzle, diffuser, starting, and emissions design studies are discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-168301 , NAS 1.26:168301 , R82AEB472
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Energy efficient engine. High pressure compressor detail design report (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A compressor optimization study defined a 10-stage configuration with a 22.6:1 pressure ratio, and adiabatic efficiency goal of 86.1%, and a polytropic efficiency of 90.6%; the corrected airflow is 53.5 kg/sec. Subsequent component testing included three full-scale tests: a six-stage rig test, and another 10-stage rig test completed in the second quarter of 1982. Information from these tests is being used to select the configuration for a core engine test scheduled for July 1982 and an integrated core/low spool test slated for early 1983. The test results will also provide data base for the flight propulsion system.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165558 , NAS 1.26:165558 , R81AEG710
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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