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  • 1
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    Experimental study of ceramic-coated tip seals for turbojet engines (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Ceramic gas-path seals were fabricated and successfully operated over 1000 cycles from flight idle to maximum power in a small turboshaft engine. The seals were fabricated by plasma spraying zirconia over a NiCoCrAlX bond coat on the Haynes 25 substrate. Coolant-side substrate temperatures and related engine parameters were recorded. Post-test inspection revealed mudflat surface cracking with penetration to the ceramic bond-coat interface.
    Keywords: MECHANICAL ENGINEERING
    Type: Ceramic Engineering and Science Proceedings (ISSN 0196-6219); 6; 880-895
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Uniform engine testing program phase 7: NASA Lewis Research Center second entry (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The propulsion and Energetics Panel, Working Group 15, of the Advisory Group for Aerospace Research and Development (AGARD) is sponsoring a Uniform Engine Testing Program (UETP). In this program, two jet engines were tested under identical conditions in certain NATO altitude and ground-level facilities as a means of correlating these facilities. With this second entry, NASA documented engine deterioration that may have occurred since inception of the UETP. Additionally, NASA investigated anomalies discovered during review of data from the five facilities which had participated in the program between the two NASA entries.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-87272 , E-2971 , NAS 1.15:87272
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Response of a small-turboshaft-engine compression system to inlet temperature distortion (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An experimental investigation was conducted into the response of a small-turboshaft-engine compression system to steady-state and transient inlet temperature distortions. Transient temperature ramps range from less than 100 K/sec to above 610 K/sec and generated instantaneous temperatures to 420 K above ambient. Steady-state temperature distortion levels were limited by the engine hardware temperature list. Simple analysis of the steady-state distortion data indicated that a particle separator at the engine inlet permitted higher levels of temperature distortion before onset of compressor surge than would be expected without the separator.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-83765 , E-2198 , NAS 1.26:83765 , USAAVSCOM-TR-84-C-13
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Nuclear rocket simulator tests, flow initiation with no turbine gas tank pressure, 35 PSIA Run 1 (1964)
    In:  CASI
    Details
    Publication Date: 2019-05-29
    Description: Nuclear reactor simulator test - liquid hydrogen run, instrumentation and data acquisition system operational procedure checkout
    Keywords: NUCLEAR ENGINEERING
    Type: NASA-TM-X-52044
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Experimental investigation of baffle effectiveness in a confined fluid subjected to wall and nonuniform source heating (1966)
    In:  CASI
    Details
    Publication Date: 2019-05-30
    Description: Baffle effectiveness in heating liquid hydrogen in propellant tank
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-52236
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Airflow and thrust calibration of an F100 engine, S/N P680059, at selected flight conditions (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An airflow and thrust calibration of an F100 engine, S/N P680059, was conducted to study airframe propulsion system integration losses in turbofan-powered high-performance aircraft. The tests were conducted with and without thrust augmentation for a variety of simulated flight conditions with emphasis on the transonic regime. The resulting corrected airflow data generalized into one curve with corrected fan speed while corrected gross thrust increased as simulated flight conditions increased. Overall agreement between measured data and computed results was 1 percent for corrected airflow and -1 1/2 percent for gross thrust. The results of an uncertainty analysis are presented for both parameters at each simulated flight condition.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1069 , E-9257
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Altitude performance of a low-noise-technology fan in a turbofan engine with and without a sound suppressing nacelle (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Test variables were inlet Reynolds number index (0.2 to 0.5), flight Mach number (0.2 to 0.8), and flow distortion (tip radial and combined circumferential - tip radial patterns). Results are limited to fan bypass and overall engine performance. There were no discernible effects of Reynolds number on fan performance. Increasing flight Mach number shifted the fan operating line such that pressure ratio decreased and airflow increased. Inlet flow distortion lowered stall margin. For a Reynolds number index of 0.2 and flight Mach number of 0.54, the sound suppressing nacelle lowered fan efficiency three points and increased specific fuel consumption about 10 percent.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-3385 , E-8592
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Altitude calibration of an F100, S/N P680063, turbofan engine (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An airflow and thrust calibration of an F100 engine was conducted in coordination with a flight test program to study airframe-propulsion system integration characteristics of turbofan-powered high-performance aircraft. The tests were conducted with and without augmentation for a variety of simulated flight conditions with emphasis on the transonic regime. Test results for all conditions are presented in terms of corrected airflow and corrected gross thrust as functions of corrected fan speed for nonaugmented power and an augmented thrust ratio as a function of fuel-air ratio for augmented power. Comparisons of measured and predicted data are presented along with the results of an uncertainty analysis for both corrected airflow and gross thrust.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1228 , E-9355
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Experimental and analytical study of ceramic-coated turbine-tip shroud seals for small turbine engines (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The results of an experimental and analytical evaluation of ceramic turbine tip shrouds within a small turbine engine operating environment are presented. The ceramic shrouds were subjected to 1001 cycles between idle and high power and steady-state conditions for a total of 57.8 engine hr. Posttest engine inspection revealed mud-flat surface cracking, which was attributed to microcracking under tension with crack penetration to the ceramic and bond coat interface. Sections and micrographs tend to corroborate the thesis. The engine test data provided input to a thermomechanical analysis to predict temperature and stress profiles throughout the ceramic gas-path seal. The analysis predicts cyclic thermal stresses large enough to cause the seal to fail. These stresses are, however, mitigated by inelastic behavior of the shroud materials and by the microfracturing that tensile stresses produce. Microfracturing enhances shroud longevity during early life but provides the failure mechanism during life but provides the failure mechanism during extended life when coupled with the time dependent inelastic materials effects.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-86881 , E-2343 , NAS 1.15:86881 , USAAVSCOM-TR-84-C-19
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Test techniques for obtaining off-nominal compressor data during engine tests (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Several unique techniques and related devices are in use at the Lewis Research Center for off-design testing of fan and compressor sections in full-scale jet engines. The devices presented not only permit a wide range of experimental conditions but also minimize downtime for hardware changes. The techniques involve use of such devices as inlet pressure distortion jets, a hydrogen burner for inlet temperature distortions, fan back pressure jets to simulate a variable area nozzle, and either an inflow-outflow bleed system or a fuel spurt system to alter compressor discharge pressure.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: SAE PAPER 740822 , Society of Automotive Engineers, National Aerospace Engineering and Manufacturing Meeting; Oct 01, 1974 - Oct 03, 1974; San Diego, CA
    Format: text
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    NASA TECHNICAL REPORTS
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