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  • Other Sources  (4)
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  • 1
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    Unknown
    Low-cost directionally-solidified turbine blades, volume 2 (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An endothermically heated technology was used to manufacture low cost, directionally solidified, uncooled nickel-alloy blades for the TFE731-3 turbofan engine. The MAR-M 247 and MER-M 100+Hf blades were finish processed through heat treatment, machining, and coating operations prior to 150 hour engine tests consisting of the following sequences: (1) 50 hours of simulated cruise cycling (high fatigue evaluation); (2) 50 hours at the maximum continuous power rating (stress rupture endurance (low cycle fatigue). None of the blades visually showed any detrimental effects from the test. This was verified by post test metallurgical evaluation. The specific fuel consumption was reduced by 2.4% with the uncooled blades.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-159562 , AIRESEARCH-21-2953-2-VOL-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Abradable compressor and turbine seals, volume 1 (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The application and advantages of abradable coatings as gas-path seals in a general aviation turbine engine were evaluated for use on the high-pressure compressor, the high-pressure turbine, and the low-pressure turbine shrouds. Topics covered include: (1) the initial selection of candidate materials for interim full-scale engine testing; (2) interim engine testing of the initially selected materials and additional candidate materials; (3) the design of the component required to adapt the hardware to permit full-scale engine testing of the most promising materials; (4) finalization of the fabrication methods used in the manufacture of engine test hardware; and (5) the manufacture of the hardware necessary to support the final full-scale engine tests.
    Keywords: METALLIC MATERIALS
    Type: NASA-CR-159600 , AIRESEARCH-21-3213-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Unknown
    Abradable compressor and turbine seals, volume 2 (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The applications and advantages of abradable coatings as gas path seals in a general aviation turbofan engine were investigated. Abradable materials were evaluated for the high pressure radial compressor and the axial high and low pressure turbine shrouds.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-159662 , AIRESEARCH-21-3213-2 , PCRP-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    An analytical and experimental study of sound propagation and attenuation in variable-area ducts (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The performance of sound suppression techniques in ducts that produce refraction effects due to axial velocity gradients was evaluated. A computer code based on the method of multiple scales was used to calculate the influence of axial variations due to slow changes in the cross-sectional area as well as transverse gradients due to the wall boundary layers. An attempt was made to verify the analytical model through direct comparison of experimental and computational results and the analytical determination of the influence of axial gradients on optimum liner properties. However, the analytical studies were unable to examine the influence of non-parallel ducts on the optimum linear conditions. For liner properties not close to optimum, the analytical predictions and the experimental measurements were compared. The circumferential variations of pressure amplitudes and phases at several axial positions were examined in straight and variable-area ducts, hard-wall and lined sections with and without a mean flow. Reasonable agreement between the theoretical and experimental results was obtained.
    Keywords: ACOUSTICS
    Type: NASA-CR-135392
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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