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  • 1
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    Dendritic Growth Velocities in Microgravity (1994)
    American Physical Society
    Details
    Publication Date: 1994-07-25
    Print ISSN: 0031-9007
    Electronic ISSN: 1079-7114
    Topics: Physics
    Published by American Physical Society
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    PAPER CURRENT
  • 2
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    Dendritic Growth tip velocities and radii of curvature in microgravity (1999)
    Springer
    Details
    Publication Date: 1999-12-01
    Print ISSN: 1073-5623
    Electronic ISSN: 1543-1940
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Published by Springer
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    PAPER CURRENT
  • 3
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    Tungsten-fiber-reinforced superalloy composite, high-temperature component design considerations (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Tungsten fiber reinforced superalloy composites (TFRS) are intended for use in high temperature turbine components. Current turbine component design methodology is based on applying the experience, sometimes semiempirical, gained from over 30 years of superalloy component design. Current composite component design capability is generally limited to the methodology for low temperature resin matrix composites. Often the tendency is to treat TFRS as just another superalloy or low temperature composite. However, TFRS behavior is significantly different than that of superalloys, and the high environment adds consideration not common in low temperature composite component design. The methodology used for preliminary design of TFRS components are described. Considerations unique to TFRS are emphasized. Previously announced in STAR as N82-21259
    Keywords: COMPOSITE MATERIALS
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Gravitational macrosegregation in binary Pb-Sn alloy ingots (1987)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: A space shuttle experiment employing the General Purpose (Rocket) Furnace (GPF) in its isothermal mode of operation is manifested on MSL-3, circa 1989. The central aim of this experiment is to investigate the effect of reduced gravity levels on the segregation behavior in a slowly, and isothermally, cooled sample of a binary Pb-15 wt pct Sn alloy. This experiment should be able to simulate, in a small laboratory sample, some aspects of the segregation phenomena occurring in large industrial ingots. Ground-based experiments conducted in the single-cavity simulator of the GPF, in support of the microgravity experiment are described in detail. The results of the MSFC experiments are compared with other related experiments conducted at Case Western Reserve University (CWRS), wherein the isothermal constraints were relaxed. The isothermally processed samples indicate a small and gradual increase in fraction eutectic, and a corresponding increase in tin content, from the bottom to the top of the ingot. The radial variations are minimal near the ingot bottom, but there are large radial variations in the top half. In the CWRU experiments, more severe segregations, including segregation defects known as freckles. Follow up experiments employing the GPF without the isothermal constraints, or other suitably modified space shuttle hardware are suggested.
    Keywords: MATERIALS PROCESSING
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    NASA TECHNICAL REPORTS
  • 5
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    Gravitational macrosegregation in binary Pb-Sn alloy ingots (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A space shuttle experiment employing the General Purpose (Rocket) Furnace (GPF) in its isothermal mode of operation is manifested on MSL-3, circa 1989. The central aim of this experiment is to investigate the effect of reduced gravity levels on the segregation behavior in a slowly, and isothermally, cooled sample of a binary Pb-15 wt% Sn alloy. This experiment should be able to simulate, in a small laboratory sample, some aspects of the segragation phenomena occurring in large industrial ingots. Ground-based experiments conducted in the single-cavity simulator of the GPF, in support of the microgravity experiment are described in detail. The results of the MSFC experiments are compared with other related experiments conducted at Case Western Reserve University (CWRS), wherein the isothermal constraints were relaxed. The isothermally processed samples indicate a small and gradual increase in fraction eutectic, and a corresponding increase in tin content, from the bottom to the top of the ingot. The radial variations are minimal near the ingot bottom, but there are large radial variations in the top half. In the CWRU experiments, more severe segregations, including segregation defects known as freckles. Follow up experiments employing the GPF without the isothermal constraints, or other suitably modified space shuttle hardware are suggested.
    Keywords: MATERIALS PROCESSING
    Type: NASA-TM-89885 , E-3570 , NAS 1.15:89885
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Space flight data from the isothermal dendritic growth experiment (1995)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The Isothermal Dendritic Growth Experiment (IDGE) is a NASA space flight experiment which flew as part of the United States Microgravity Payload (USMP-2), in early 1994. The IDGE measured dendritic growth rates, tip radii, and crystal morphologies of ultra-pure succinonitrile (CN-(CH2)2-CN) at supercoolings in the range from 0.05 - 2.0 K. Data taken in the form of slow-scan binary digitized images telemetered to the ground from orbit in near-real time, combined with the IDGE terrestrial data set, provide the first quantitative assessment of various theories on dendritic solidification and the effects of convection on dendritic growth.
    Keywords: MATERIALS PROCESSING
    Type: Advances in Space Research (ISSN 0273-1177); 16; 7; p. (7)181-(7)184
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Tungsten fiber reinforced superalloy composite high temperature component design considerations (1982)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Tungsten fiber reinforced superalloy composites (TFRS) are intended for use in high temperature turbine components. Current turbine component design methodology is based on applying the experience, sometimes semiempirical, gained from over 30 years of superalloy component design. Current composite component design capability is generally limited to the methodology for low temperature resin matrix composites. Often the tendency is to treat TFRS as just another superalloy or low temperature composite. However, TFRS behavior is significantly different than that of superalloys, and the high environment adds consideration not common in low temperature composite component design. The methodology used for preliminary design of TFRS components are described. Considerations unique to TFRS are emphasized.
    Keywords: COMPOSITE MATERIALS
    Type: NASA-TM-82811 , E-1152 , NAS 1.15:82811 , Ann. Meeting of the Am. Inst. of Mining, Met. and Petrol. Engr.,; Feb 14, 1982 - Feb 18, 1982; Dallas, TX; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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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
  • 9
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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
  • 10
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    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
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