Effects of Laser Peening on the Fatigue Performance of 7050-T7451 Aluminum and Carburized 9310 Steel PDF Download
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Author: Marc Edward Hopkins
Publisher:
ISBN:
Category :
Languages : en
Pages : 244
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Author: Marc Edward Hopkins
Publisher:
ISBN:
Category :
Languages : en
Pages : 244
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Author: Chanh Hung Truong
Publisher:
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Category :
Languages : en
Pages : 164
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Author: Harold Luong
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Category :
Languages : en
Pages : 196
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Author: Theresa Elizabeth Pistochini
Publisher:
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Category :
Languages : en
Pages : 222
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Author: Jasleen Bhoon
Publisher:
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Category :
Languages : en
Pages : 178
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Author:
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Category :
Languages : en
Pages : 26
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Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781726673556
Category : Science
Languages : en
Pages : 38
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Fatigue and crack growth tests have been conducted on 4340 steel and 2024-T3 aluminum alloy, respectively, to assess the effects of shot peening on fatigue life and the effects of shot and laser peening on crack growth. Two current programs involving fixed and rotary-wing aircraft will not be using shot peened structures. Since the shot peening compressive residual stress depth is usually less than the 0.05-inch initial damage tolerance crack size, it is believed by some that shot peening should have no beneficial effects toward retarding crack growth. In this study cracks were initiated from an electronic-discharged machining flaw which was cycled to produce a fatigue crack of approximately 0.05-inches in length and then the specimens were peened. Test results showed that after peening the crack growth rates were noticeably slower when the cracks were fairly short for both the shot and laser peened specimens resulting in a crack growth life that was a factor of 2 to 4 times greater than the results of the average unpeened test. Once the cracks reached a length of approximately 0.1-inches the growth rates were about the same for the peened and unpeened specimens. Fatigue tests on 4340 steel showed that the endurance limit of a test specimen with a 0.002-inch-deep machining-like scratch was reduced by approximately 40 percent. However, if the "scratched" specimen was shot peened after inserting the scratch, the fatigue life returned to almost 100 percent of the unflawed specimens original fatigue life. Everett, R. A., Jr. and Matthews, W. T. and Prabhakaran, R. and Newman, J. C., Jr. and Dubberly, M. J. Langley Research Center NASA/TM-2001-210843, NAS 1.15:210843, ARL-TR-2363, L-18065
Author:
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Category : Aluminum alloys
Languages : en
Pages : 18
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Author: Niall Smyth
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Category :
Languages : en
Pages :
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Author: George S. Owens
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Category :
Languages : en
Pages :
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