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  • 1
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    Defects in Nickel-Base Superalloys (1987)
    Springer
    Details
    Publication Date: 1987-07-01
    Print ISSN: 1047-4838
    Electronic ISSN: 1543-1851
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Published by Springer
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    PAPER CURRENT
  • 2
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    High-Performance dispersion-strengthened Cu-8 Cr-4 Nb alloy (1995)
    Springer
    Details
    Publication Date: 1995-09-01
    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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    Understanding single-crystal superalloys (1986)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The unique properties of single crystals are considered. The anisotropic properties of single crystals, and the relation between crystal orientation and the fatigue life and slip systems of the crystals are examined. The effect of raft formation on the creep-rupture life of the crystals is studied. Proposed research on the properties of and new applications for single crystals is discussed.
    Keywords: METALLIC MATERIALS
    Type: Metal Progress (ISSN 0026-0665)
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Defects in nickel-base superalloys (1987)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The presence of substantial amounts of the sigma phase in Ni-base superalloys can drastically reduce the alloy's stress rupture life. No predictive system exists which is entirely successful in anticipating the formation of sigma, mu, and similar phases in new and substantially different alloys. Freckles are defects due to the segregation of elements in quantities that can lead to phase precipitation, and are caused by gravity-driven fluid motion that yields microsegregation in the ingots typically used in the fabrication of structures based on these alloys. Also noted are the effects of porosity and grain boundaries on superalloy mechanical properties.
    Keywords: METALLIC MATERIALS
    Type: Journal of Metals (ISSN 0148-6608); 39; 16-21
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    The effect of porosity and gamma-gamma' eutectic content on the low cycle fatigue behavior of hydrogen-charged PWA-1480 (1991)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Single crystal superalloys such as PWA 1480 are considered for turbopump blades in the main engines of the space shuttle. As fatigue resistance in a hydrogen environment is a key issue in this application, a study of the effect of porosity and gamma-gamma' eutectic content on the fatigue life of a hydrogen-charged PWA 1480 was performed. Porosity and eutectic were linked to fatigue initiation, and therefore reduction of either of both may be one means to improve fatigue life of PWA 1480 when hydrogen is present.
    Keywords: METALLIC MATERIALS
    Type: Structural Integrity and Durability of Reusable Space Propulsion Systems; p 179-185
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Propulsion Systems Panel (1993)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Topics addressed are: (1) cryogenic tankage; (2) launch vehicle TPS/insulation; (3) durable passive thermal control devices and/or coatings; (4) development and characterization of processing methods to reduce anisotropy of material properties in Al-Li; (5) durable thermal protection system (TPS); (6) unpressurized Al-Li structures (interstages, thrust structures); (7) near net shape sections; (8) pressurized structures; (9) welding and joining; (10) micrometeoroid and debris hypervelocity shields; (11) state-of-the-art shell buckling structure optimizer program to serve as a rapid design tool; (12) test philosophy; (13) reduced load cycle time; (14) structural analysis methods; (15) optimization of structural criteria; and (16) develop an engineering approach to properly trade material and structural concepts selection, fabrication, facilities, and cost.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center, Space Transportation Materials and Structures Technology Workshop. Volume 2: Proceedings; p 210-256
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Propulsion Systems Panel deliberations (1993)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The Propulsion Systems Panel was established because of the specialized nature of many of the materials and structures technology issues related to propulsion systems. This panel was co-chaired by Carmelo Bianca, MSFC, and Bob Miner, LeRC. Because of the diverse range of missions anticipated for the Space Transportation program, three distinct propulsion system types were identified in the workshop planning process: liquid propulsion systems, solid propulsion systems and nuclear electric/nuclear thermal propulsion systems.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center, Space Transportation Materials and Structures Technology Workshop. Volume 2: Proceedings; p 295-300
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Post-test examination of a pool boiler receiver (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A subscale pool boiler test apparatus to evaluate boiling stability developed a leak after being operated with boiling NaK for 791.4 hr at temperatures from 700 to 750 C. The boiler was constructed using Inconel 625 with a type 304L stainless steel wick for the boiler and type 316 stainless steel for the condenser. The boiler assembly was metallurgically evaluated to determine the cause of the leak and to assess the effects of the NaK on the materials. It was found that the leak was caused by insufficient (about 30 pct.) joint penetration in a butt joint. There was no general corrosion of the construction materials, but the room temperature ductility of the Inconel 625 was only about 6.5 pct. A crack in the heat affected zone of the Inconel 625 near the Inconel 625 to type 316 stainless steel butt joint was probably caused by excessive heat input. The crack was observed to have a zone depleted of iron at the crack surface and porosity below that zone. The mechanism of the iron depletion was not conclusively determined.
    Keywords: METALLIC MATERIALS
    Type: NASA-TM-105635 , E-6978 , DOE/NASA/33408-6 , NAS 1.15:105635
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Observations of directional gamma prime coarsening during engine operation (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Two alloys with negative mismatch parameters, NASAIR 100 and a modified NASAIR 100 called Alloy 3 were run as turbine blades in an experimental ground based Garret TFE731 engine for up to 200 hr. The directional coarsening of gamma prime (rafting) that developed during engine testing was analyzed and compared to previous research from laboratory tests. The blades were found to be rafted normal to the centrifugal stress axis over much of the span, but near the surfaces, the blades were found to be rafted parallel to the centrifugal stress axis for certain cycles. Representative photomicrographs of the blades and the effects of stress and temperature on raft formation are shown.
    Keywords: METALLIC MATERIALS
    Type: NASA-TM-100105 , E-3642 , NAS 1.15:100105
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Effect of hydrogen exposure on a Cu-8 Cr-4 Nb alloy (1993)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The advanced regeneratively cooled rocket thrust chamber may require new materials to achieve long life and improved performance. Current materials such as NARloy-Z (Cu-3 wt. percent Ag-0.5 wt. percent Zr), while highly conductive, do not have sufficient high temperature strength and creep resistance to meet the projected needs of advanced rocket motors. A Cu-8 at. percent Cr-4 at. percent Nb (Cu-8 Cr-4 Nb) alloy has been identified as a promising material for this application. However, hydrogen embrittlement is a concern given the presence of high pressure, high temperature hydrogen in regeneratively cooled rocket motors. Thermodynamic analysis of the reaction between Cr-rich Cr2Nb and H2 showed that there is a possibility of reaction at temperatures up to 323 K in a 35 MPa H2 environment. Above 323 K the pressure necessary to achieve reaction rapidly increased beyond the range experienced in rocket motors. Tensile specimens exposed in 34.5 MPa H2 at room temperatures and during cycling to 705 C did not show any degradation of properties. No evidence of reaction was observed for Cr2Nb precipitate observed on the fracture surfaces. Based on these results the Cu-8 Cr-4 Nb alloy was judged to be sufficiently stable for use in rocket motors.
    Keywords: METALLIC MATERIALS
    Type: NASA-TM-106429 , E-8271 , NAS 1.15:106429
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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