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  • 1975-1979  (6)
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  • 1
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    Tungsten fiber reinforced FeCralY: A first generation composite turbine blade material (1979)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Tungsten-fiber/FeCrAlY (W/FeCrAlY) was identified as a promising aircraft engine, first generation, turbine blade composite material. Based on available data, W/FeCrAlY should have the stress-rupture, creep, tensile, fatigue, and impact strengths required for turbine blades operating from 1250 to 1370 K. It should also have adequate oxidation, hot corrosion, and thermal cycling damage resistance as well as high thermal conductivity. Concepts for potentially low cost blade fabrication were developed. These concepts were used to design a first stage JT9D convection cooled turbine blade having a calculated 50 K use-temperature advantage over the directionally solidified superalloy blade.
    Keywords: COMPOSITE MATERIALS
    Type: NASA-TM-79094 , E-9918 , Ann. meeting of the Am. Inst. of Mining, Met. and Petroleum Engr.; Feb 18, 1979 - Feb 22, 1979; New Orleans, LA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Predicted inlet gas temperatures for tungsten fiber reinforced superalloy turbine blades (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Tungsten fiber-reinforced superalloy composite (TFRS) impingement-cooled turbine blade inlet gas temperatures were calculated taking into account material spanwise strength, thermal conductivity, material oxidation resistance, fiber-matrix interaction, and coolant flow. Measured values of TFRS thermal conductivities are presented. Calculations indicate that blades made of 30 volume percent fiber content TFRS having a 12,000 N-m/kg stress-to-density ratio while operating at 40 atm and a 0.06 coolant flow ratio could permit a turbine blade inlet gas temperature of over 1900 K. This is more than 150 K greater than similar superalloy blades.
    Keywords: COMPOSITE MATERIALS
    Type: International Conference on Composite Materials; Apr 16, 1978 - Apr 20, 1978; Toronto; Canada
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Unknown
    Predicted inlet gas temperatures for tungsten fiber reinforced superalloy turbine blades (1978)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Tungsten fiber reinforced superalloy composite (TFRS) impingement cooled turbine blade inlet gas temperatures were calculated taking into account material spanwise strength, thermal conductivity, material oxidation resistance, fiber-matrix interaction, and coolant flow. Measured values of TFRS thermal conductivities are presented. Calculations indicate that blades made of 30 volume percent fiber content TFRS having a 12,000 N-m/kg stress-to-density ratio while operating at 40 atmospheres and a 0.06 coolant flow ratio could permit a turbine blade inlet gas temperature of over 1900K. This is more than 150K greater than similar superalloy blades.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-73842 , Intern. Conf. on Composite Materials; Apr 16, 1978 - Apr 20, 1978; Toronto; Canada
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Unknown
    Predicted inlet gas temperatures for tungsten fiber reinforced superalloy turbine blades (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A procedure is presented for predicting the magnitude of the turbine inlet gas temperatures potentially achievable using first generation tungsten fiber reinforced superalloys (TFRS) turbine blades. Both uncoated blades and blades with thermal barrier coatings are considered. The thermal conductivities of two representative TFRS were measured over a range of temperatures. The results show that cooled TFRS blades may allow significantly higher gas temperatures than are possible with superalloy blades. For one design, the difference is about 150-200 K.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: ICCM/2; Second International Conference on Composite Materials; Apr 16, 1978 - Apr 20, 1978; Toronto; Canada
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Thermal-conductivity measurements of tungsten-fiber-reinforced superalloy composites using a thermal-conductivity comparator (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The thermal conductivity (TC) of tungsten-fiber-reinforced superalloys was determined for two composite systems by using a thermal conductivity standard from the National Bureau of Standards and a comparator and technique developed for that purpose. The results were compared with TC data for the nickel-base alloy MAR-M200. The technique lends itself to applications involving thin specimens, such as thin-walled turbine blades. The TC's of the composite systems were considerably higher in both the longitudinal and transverse directions than that of the monolithic superalloys used as the matrices.
    Keywords: COMPOSITE MATERIALS
    Type: NASA-TP-1445 , E-9910
    Format: application/pdf
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  • 6
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    Tungsten fiber reinforced FeCrAlY - A first generation composite turbine blade material (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: General and composite turbine blade material requirements are examined to identify a specific tungsten fiber reinforced superalloy (TFRS) having, in addition to strength, the desired combination of other material properties needed in turbine blades. Experimental data indicated that a thoriated tungsten fiber reinforced FeCrAlY matrix composite should have the stress-rupture, creep, tensile, fatigue, and impact strengths required for turbine blades operating from 1250 to 1370 K. Fabrication and design concepts are developed to demonstrate the feasibility of fabricating a hollow TFRS turbine blade at reasonable cost.
    Keywords: COMPOSITE MATERIALS
    Type: American Institute of Mining, Metallurgical and Petroleum Engineers, Annual Meeting; Feb 18, 1979 - Feb 22, 1979; New Orleans, LA
    Format: text
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    NASA TECHNICAL REPORTS
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