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  • 1
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    Comparative thermal fatigue resistance of several oxide dispersion strengthened alloys (1981)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The thermal fatigue resistance of several oxide dispersion strengthened (ODS) alloys has been evaluated through cyclic exposure in fluidized beds. The ODS nickel-base alloy MA 754 and ODS iron-base alloy MA 956 as well as four experimental ODS Ni-16Cr-4.5Al base alloys with and without Ta additions were examined. Both bare and coated alloys were subjected to up to 6000 cycles where each cycle consisted of a 3 minute immersion in a fluidized bed at 1130 C followed by a 3 minute immersion in a bed at 357 C. Testing revealed that the thermal fatigue resistance of the ODS nickel-base alloys was excellent and about equal to that of directionally solidified superalloys. However, the thermal fatigue resistance of MA 956 was found to be poor. Metallographic examination of tested specimens revealed that, in general, the post-test microstructures can be rationalized on the basis of previous diffusion, mechanical property, and oxidation studies.
    Keywords: METALLIC MATERIALS
    Type: International Journal of Fatigue; 3; Oct. 198
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Interaction of High-cycle and Low-cycle Fatigue of Haynes 188 Alloy at 1400 F Deg (1985)
    In:  CASI
    Details
    Publication Date: 2014-09-04
    Description: The interaction of low-cycle fatigue (LCF) and high-cycle fatigue (HCF) was evaluated at the NASA Lewis Research Center on Haynes 188 alloy at 1400 F. Completely reversed, axial-load, strain-controlled fatigue tests were performed to determine the baseline data for this study. Additional specimens for interaction tests were cycled first at a high strain range for various small portions of expected LCF life followed by a step change to a low strain range to failure in HCF. Failure was defined as complete specimen separation. The resultant lives varied between 10 and 5000 cycles for the low-cycle fatigue tests and between 4500 and 3 million for the high-cycle fatigue tests. For the interaction tests the low-cycle-life portion ranged from 30 and 1000 applied cycles while the high-frequency life ranged from 300 and 300,000 cycles to failure. The step change results showed a significant nonlinear interaction in expected life. Application of a small part of the LCF life drastically decreased the available HCF life as compared with what would have been expected by the classical linear damage rule (LDR).
    Keywords: STRUCTURAL MECHANICS
    Type: Struct. Integrity and Durability of Reusable Space Propulsion Systems; p 129-138
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Elastic stresses at a mismatched circumferential joint in a pressurized cylinder including thickness changes and meredional load coupling (1966)
    In:  CASI
    Details
    Publication Date: 2019-05-30
    Description: Elastic stresses at mismatched circumferential joint in pressurized cylinder
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TN-D-3609
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Comparison of experimental and theoretical stresses at a mismatch in a circumferential joint in a cylindrical pressure vessel (1966)
    In:  CASI
    Details
    Publication Date: 2019-05-30
    Description: Comparison of experimental and theoretical stresses at mismatch in circumferential joint in cylindrical pressure vessel
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TN-D-3608
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Thermal-fatigue and oxidation resistance of cobalt-modified Udimet 700 alloy (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Comparative thermal-fatigue and oxidation resistances of cobalt-modified wrought Udimet 700 alloy (obtained by reducing the cobalt level by direct substitution of nickel) were determined from fluidized-bed tests. Bed temperatures were 1010 and 288 C (1850 and 550 C) for the first 5500 symmetrical 6-min cycles. From cycle 5501 to the 14000-cycle limit of testing, the heating bed temperature was increased to 1050 C (1922 F). Cobalt levels between 0 and 17 wt% were studied in both the bare and NiCrAlY overlay coated conditions. A cobalt level of about 8 wt% gave the best thermal-fatigue life. The conventional alloy specification is for 18.5% cobalt, and hence, a factor of 2 in savings of cobalt could be achieved by using the modified alloy. After 13500 cycles, all bare cobalt-modified alloys lost 10 to 13 percent of their initial weight. Application of the NiCrAlY overlay coating resulted in weight losses of 1/20 to 1/100 of that of the corresponding bare alloy.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TP-2591 , E-2704 , NAS 1.60:2591
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Thermal fatigue resistance of cobalt-modified UDIMET 700 (1982)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: The determination of comparative thermal fatigue resistances of five cobalt composition modifications of UDIMET 700 from fluidized bed tests is described. Cobalt compositional levels of 0.1, 4.3, 8.6, 12.8, 17.0 percent were being investigated in both the bare and coated (NiCrAlY overlay) conditions. Triplicate tests of each variation including duplicate tests of three control alloys are under investigation. Fluidized beds were maintained at 550 and 1850 F for the first 5500 cycles at which time the hot bed was increased to 1922 F. Immersion time in each bed is always 3 minutes. Upon the completion of 10,000 cycles, it appears that the 8.6 percent cobalt level gives the best thermal fatigue life. Considerable deformation of the test bars was observed.
    Keywords: METALLIC MATERIALS
    Type: COSAM (Conserv. Of Strategic Aerospace Mater.) Program Overview; p 77-81
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    EXPERIMENTAL EVALUATION OF THEORETICAL ELASTIC STRESS DISTRIBUTIONS FOR CYLINDER-TO-HEMISPHERE AND CONE-TO-SPHERE JUNCTIONS IN PRESSURIZED SHELL STRUCTURES (1963)
    In:  CASI
    Details
    Publication Date: 2019-05-11
    Description: Stress state in toriconical structure of constant wall thickness
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TN-D-1565
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Comparative thermal fatigue resistance (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Nineteen cast nickel-base alloys, five cast cobalt-base alloys, and two wrought nickel-base alloys are included in study. Five nickel-base alloys have directionally-solidified polycrystalline grain structure. Three diffusion coatings and vapor-deposited overlay coating are also included in investigation.
    Keywords: MATERIALS
    Type: LEW-12563 , NASA Tech Briefs (ISSN 0145-319X); 1; 1; P. 71
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Thermal fatigue-and-oxidation-resistant alloy (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Cast nickel-base alloy designated as NASA TAZ-8A has been developed for use in high temperature aircraft engine components. TAZ-8A composition is 8Ta, 6Cr, 6A1, 4Mo, 4W, 2Cb, 0.5Zr, 0.125C, 0.004B, and balance Ni (weight percent). Its specific gravity at room temperature is 8.65.
    Keywords: MATERIALS
    Type: LEW-12564 , NASA Tech Briefs (ISSN 0145-319X); 1; 1; P. 70
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Experimental determination of transient strain in a thermally-cycled simulated turbine blade utilizing a non-contact technique (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A type of noncontacting electro-optical extensometer was used to measure the displacement between parallel targets mounted on the leading edge of a simulated turbine blade throughout a complete heating and cooling cycle. The blade was cyclically heated and cooled by moving it into and out of a Mach 1 hot gas stream. The principle of operation and measurement procedure of the electro-optics extensometer are described.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-73886 , E-9500
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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