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  • 1
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    Unknown
    Fatigue failure of hydrogen embrittled high strength steels (1975)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Results of an experimental investigation are presented concerning the fracture behavior of cathodically charged, quenched and tempered martensitic steels under cyclic load conditions. Introduction of H2 by cathodic charging reduced fatigue life by as much as 60%. It is proposed that subsurface transverse fatigue cracks nucleate simultaneously at multiple sites, such as at microcracks, voids, or inclusions. Fatigue crack growth then occurs on planes perpendicular to the major applied stress axis in the presence of the critical combination of applied external stress and hydrogen.
    Keywords: METALLIC MATERIALS
    Type: Metallurgical Transactions A - Physical Metallurgy and Materials Science; 6A; July 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Characterization of an oxide dispersion strengthened superalloy, MA-6000E, for turbine blade applications (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Alloy MA 6000E was developed by the mechanical alloying process for turbine blade applications. The nominal composition of the experimental alloy is Ni-15CR-2Mo-4W-4.5Al- 2.5Ti-2Ta- .15Zr-.05C-.01B-1.1Y2O3. The 1000 hour rupture strength in the longitudinal direction is about 145 MPa at 1093 C and about 483 MPa at 760 C. The alloy displays normal three-stage creep behavior. Typically the creep elongation is 3.5% at 760 C and 2% at 1093 C. The alloy is notch ductile (K sub 1 = 3.5). The rupture properties of the alloy are not significantly degraded by thermal cycling or prior stress isothermal exposure. The alloy also has excellent longitudinal high and low cycle fatigue resistance. Limited testing indicates that MA 6000E posesses good off-axis mechanical properties. The transverse tensile elongation at 760 C is about 3%. The 100 hour transverse rupture strength is 331 MPa at 760 C and about 55 MPa at 1093 C.
    Keywords: METALLIC MATERIALS
    Type: NASA-CR-159493
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Directionally solidified pseudo-binary eutectics of Ni-Cr-(Hf, Zr) (1975)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A pseudo-binary eutectic, in which the intermetallic Ni7Hf2 reinforces the Ni-Cr solid solution phase, was previously predicted in the Ni-Cr-Hf system by a computer analysis. The experimental determination of pseudo binary eutectic compositions and the directional solidification of the Ni-Cr-Hf, Zr, and Ni-Cr-Zr eutectic alloys are discussed. To determine unknown eutectics, chemical analyses were made of material bled from near eutectic ingots during incipient melting. Nominal compositions in weight percent of Ni-18.6Cr-24.0HF, Ni19.6Cr-12.8Zr-2.8Hf, and Ni-19.2Cr-14.8Zr formed aligned pseudo-binary eutectic structures. The melting points were about 1270 C. The reinforcing intermetallic phases were identified as noncubic (Ni,Cr)7Hf2 and (Ni,Cr)7(Hf,Zr)2, and face centered cubic (Ni,Cr)5Zr. The volume fraction of the reinforcing phases were about 0.5.
    Keywords: METALLIC MATERIALS
    Type: NASA-TM-X-71765 , E-8417 , Conf. on In-Situ Composites; Sep 02, 1975 - Sep 05, 1975; Lake George, N. Y.; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Structure and thermal cycling stability of a hafnium monocarbide reinforced directionally solidified cobalt-base eutectic alloy (1975)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A nominal composition of Co-15Cr-2ONi-10.5 Hf-0.7 C (NASA-HAFCO-11) was directionally solidified at 0.8 cm/hr growth rate to produce aligned HfC in a cobalt matrix alloy. The aligned HfC fibers were present as rod and plate types. The diameter of the aligned fibers was about 1 micron, with volume fraction in the range of 11 to 15 percent. The growth direction of the fibers was parallel to the 100. The NASA-HAFCO-11 alloy was subjected to thermal cycling between 425 deg and 1100 C, using a 2.5 minute cycle. No microstructural degradation of the HfC fibers in the alloy was observed after 2500 cycles.
    Keywords: METALLIC MATERIALS
    Type: NASA-TM-X-71751 , E-8391 , Conf. on In-Situ Composites; Sep 02, 1975 - Sep 05, 1975; Lake George, N. Y.; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Unknown
    Development of oxide dispersion strengthened turbine blade alloy by mechanical alloying (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: There were three nickel-base alloys containing up to 18 wt. % of refractory metal examined initially for oxide dispersion strengthening. To provide greater processing freedom, however, a leaner alloy was finally selected. This base alloy, alloy D, contained 0.05C/15Cr / 2Mo/4W/2Ta/4.5Al/2.Ti/015Zr/0.01-B/Bal. Ni. Following alloy selection, the effect of extrusion, heat treatment, and oxide volume fraction and size on microstructure and properties were examined. The optimum structure was achieved in zone annealed alloy D which contained 2.5 vol. % of 35 mm Y2O3 and which was extruded 16:1 at 1038 C.
    Keywords: METALLIC MATERIALS
    Type: NASA-CR-135150
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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