Fatigue Behavior of Aluminum and Titanium Sheet Materials Down to -423°F

Schwartzberg, F. R.; Kiefer, T. F.; Keys, R. D.

doi:10.1007/978-1-4684-3108-7_1

Cited by 3 publications

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“…Figure 2 shows S–N diagrams at 4 K, 77 K and 293 K for the present material and those for the Ti–5% Al–2.5% Sn ELI alloys examined by Nagai et al (at 4 K and 77 K) 5 and Schwartzberg et al (at 20 K, 77 K and 294 K) 22 . The fatigue strength of each material tends to increase with decreasing temperature.…”

Section: Resultsmentioning

confidence: 62%

“…The fatigue properties in this alloy are discussed in terms of how they correlate with the fatigue crack initiation sites. The results obtained are as follows: This study Schwartzberg et al 22 Nagai et al 5 Fatigue strength at 10 There is no facet which is clearly identified as internal fatigue crack initiation site. * 2 These values were measured and calculated by the authors of this paper.…”

Section: O N C L U S I O N Smentioning

confidence: 75%

“…The 0.2% proof stress and the ultimate tensile strength of the present material increased with decreasing temperature and both properties at 4 K and 77 K are 1.8 times and 1.6 times higher than those at 293 K, respectively. In Table 2, data from Nagai et al 5 and Schwartzberg et al 22 are also listed as references. Compared with the present material, the 0.2% proof stress and the ultimate tensile strength of their materials are somewhat higher and show similar temperature dependence.…”

Section: Resultsmentioning

confidence: 99%

“…Compared with the present material, the 0.2% proof stress and the ultimate tensile strength of their materials are somewhat higher and show similar temperature dependence. 22 -1614 1283 800 * * Fatigue tests were performed at 294 K. Figure 2 shows S-N diagrams at 4 K, 77 K and 293 K for the present material and those for the Ti-5% Al-2.5% Sn ELI alloys examined by Nagai et al (at 4 K and 77 K) 5 and Schwartzberg et al (at 20 K, 77 K and 294 K). 22 The fatigue strength of each material tends to increase with decreasing temperature.…”

Section: E X P E R I M E N Ta L P R O C E D U R Ementioning

confidence: 86%

“…22 -1614 1283 800 * * Fatigue tests were performed at 294 K. Figure 2 shows S-N diagrams at 4 K, 77 K and 293 K for the present material and those for the Ti-5% Al-2.5% Sn ELI alloys examined by Nagai et al (at 4 K and 77 K) 5 and Schwartzberg et al (at 20 K, 77 K and 294 K). 22 The fatigue strength of each material tends to increase with decreasing temperature. However, the low-temperature fatigue strength of the present material is lower than those of the reference materials.…”

Section: E X P E R I M E N Ta L P R O C E D U R Ementioning

confidence: 86%

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High‐cycle fatigue properties in Ti–5% Al–2.5% Sn ELI alloy with large grain size at cryogenic temperatures

Ono¹,

Yuri²,

Sumiyoshi³

et al. 2004

Fatigue Fract Eng Mat Struct

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A B S T R A C T High-cycle fatigue properties were investigated for Ti-5% Al-2.5% Sn ELI alloy with a mean α grain size of 80 µm, which had been used for liquid hydrogen turbo-pumps of Japanese-built launch vehicles. At cryogenic temperatures, the fatigue strength in highcycle region did not increase in proportion to increments of the ultimate tensile strength and the fatigue strengths at around 10 6 cycles were about 300 MPa independent of test temperatures. Fatigue cracks initiated in the specimen interior independent of the test temperatures of 4 K, 77 K and 293 K. At 4 K and 77 K, several crystallographic facet-like structures were formed at crack initiation sites. On the other hand, there were no facetlike structures that could be clearly identified at the crack initiation sites at 293 K. Low fatigue strengths in longer-life region at cryogenic temperatures could be attributable to the formation of large sub-surface crack initiation sites, where large facet-like structure are formed.

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Section: Resultsmentioning

confidence: 62%

Section: O N C L U S I O N Smentioning

confidence: 75%

Section: Resultsmentioning

confidence: 99%

Section: E X P E R I M E N Ta L P R O C E D U R Ementioning

confidence: 86%

Section: E X P E R I M E N Ta L P R O C E D U R Ementioning

confidence: 86%

See 3 more Smart Citations

High‐cycle fatigue properties in Ti–5% Al–2.5% Sn ELI alloy with large grain size at cryogenic temperatures

Ono¹,

Yuri²,

Sumiyoshi³

et al. 2004

Fatigue Fract Eng Mat Struct

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Mechanical Properties of Metals and Alloys at Cryogenic Temperatures

Fukushima

1975

Tetsu-to-Hagane

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Mechanical Properties

Read¹

1983

Materials at Low Temperatures

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The mechanical properties of a material describe the relations between the stresses acting on the material and its resulting deformations. Stresses capable of producing permanent deformations, which remain after the stresses are removed, are considered in this chapter. The effects of cryogenic temperatures on the mechanical properties of metals and alloys are reviewed in this chapter; the effects on polymers and glasses are discussed briefly. The fundamental mechanisms controlling temperature-dependent mechanical behavior, phenomena encountered in low-temperature testing, and the mechanical properties of some representative engineering metals and alloys are described. Modifications of test procedures for low temperatures and sources of data are also included.

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Fatigue Behavior of Aluminum and Titanium Sheet Materials Down to -423°F

Cited by 3 publications

References 0 publications

High‐cycle fatigue properties in Ti–5% Al–2.5% Sn ELI alloy with large grain size at cryogenic temperatures

High‐cycle fatigue properties in Ti–5% Al–2.5% Sn ELI alloy with large grain size at cryogenic temperatures

Mechanical Properties of Metals and Alloys at Cryogenic Temperatures

Mechanical Properties

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