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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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    Low-cost directionally-solidified turbine blades, volume 1 (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A low cost process of manufacturing high stress rupture strength directionally-solidified high pressure turbine blades was successfully developed for the TFE731-3 Turbofan Engine. The basic processing parameters were established using MAR-M 247 and employing the exothermic directional-solidification process in trial castings of turbine blades. Nickel-based alloys were evaluated as directionally-solidified cast blades. A new turbine blade, disk, and associated components were then designed using previously determined material properties. Engine tests were run and the results were analyzed and compared to the originally established goals. The results showed that the stress rupture strength of exothermically heated, directionally-solidified MAR-M 247 turbine blades exceeded program objectives and that the performance and cost reduction goals were achieved.
    Keywords: METALLIC MATERIALS
    Type: NASA-CR-159464 , AIRESEARCH-21-2953-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Development of exothermically cast single-crystal Mar-M 247 and derivative alloys (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: A low-cost, exothermic directional-solidification (DS) process was developed to produce single-crystal (SC) Mar-M 247 high-pressure turbine blades. Stress-rupture data indicated that SC Mar-M 247 provides only marginal improvements in longitudinal strength relative to the columnar grained DS material. Removal of grain boundary strengthening elements (B, C, Zr, Hf) from the Mar-M 247 composition (which are also melting point depressants) permitted the alloy to be solutioned at significantly higher temperatures. An order of magnitude improvement in rupture life relative to SC Mar-M 247 was observed for several derivative alloys at 103.5 MPa (15 KSI) and 1093 C. Rupture lives of the modified SC alloys were significantly affected by both alloy purity and heat treatment. Critical aspects of vacuum induction refining, exothermic casting technology, alloy development and heat treatment, which contributed to this new class of turbine blades, are reviewed
    Keywords: METALLIC MATERIALS
    Type: AIRESEARCH-21-3469 , International Symposium on Superalloys; Sept. 21-25, 1980; Champion, PA
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Development of low-cost directionally-solidified turbine blades (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: A low-cost directionally solidified (DS) casting of turbine blades of high stress rupture is discussed. The process uses an exothermically heated mold; a newly designed solid blade was cast for the high-pressure turbine of the TFE731-3 turbofan engine. Ni-based alloys Mar-M 247 and Mar-M 200 + Hf were used. The solid DS blade replaced a conventionally cast IN100 component; a 40% cost saving is expected, with a 2.4% reduction in the takeoff specific fuel consumption. The DS Mar-M 247 blade has been selected for production in the TFE731-3B-100, and advanced version of the TFE731-3.
    Keywords: MECHANICAL ENGINEERING
    Type: International Symposium on Superalloys; Sept. 21-25, 1980; Champion, PA
    Format: text
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  • 5
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    Fusion welding of age-hardenable superalloys. (1969)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Wrought superalloys fusion welding behavior, discussing hot cracking, hot microfissuring and strain age cracking
    Keywords: MACHINE ELEMENTS AND PROCESSES
    Type: SAE PAPER 690102 , SOCIETY OF AUTOMOTIVE ENGINEERS, INTERNATIONAL AUTOMOTIVE ENGINEERING CONGRESS; Jan 13, 1969 - Jan 17, 1969; DETROIT, MICH.
    Format: text
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    NASA TECHNICAL REPORTS
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