Fatigue Life Extension and the Effects of Laser Peening on 7050-T7451 Aluminum, 7085-T7651 Aluminum, and Ti-6Al-4V Titanium Alloys PDF Download
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Author: Harold Luong
Publisher:
ISBN:
Category :
Languages : en
Pages : 196
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Author: Harold Luong
Publisher:
ISBN:
Category :
Languages : en
Pages : 196
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Author: Marc Edward Hopkins
Publisher:
ISBN:
Category :
Languages : en
Pages : 244
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Author: Chanh Hung Truong
Publisher:
ISBN:
Category :
Languages : en
Pages : 164
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Author: Jasleen Bhoon
Publisher:
ISBN:
Category :
Languages : en
Pages : 178
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Author: Theresa Elizabeth Pistochini
Publisher:
ISBN:
Category :
Languages : en
Pages : 222
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Author: James Campbell
Publisher:
ISBN:
Category :
Languages : en
Pages : 7
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The fatigue strength of three shot-peened aluminum alloys (Al 7075-T651, Al 2024-T351 and Al 2014-T6) and a titanium alloy (Ti-6Al-4V) was measured to determine the differences in shot peening quality from three vendors that were given the same shot peening parameters. Shot peening produces surface roughness, a cold-worked layer and, most importantly, a residual stress layer that resists the propagation of fatigue cracks. Significant vendor-to-vendor differences in fatigue properties were found, with Vendor 1 giving the greatest fatigue lifetimes.
Author:
Publisher:
ISBN:
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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ISBN:
Category : Airframes
Languages : en
Pages :
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This report summarises the state-of-the-art, benefits, limitations and risks of laser shock peening (LSP). The experimental results showed that LSP technology can effectively extend fatigue life for AA7075 Al alloy. However, the fatigue lives in LSP treated AA7050 specimens are reduced when the laser power density exceeds 3 GW/cm2. The cause for the reduction of the fatigue life was determined to be internal cracking, surface "burnt" defects, or "over-peening" due to inappropriate LSP processing. Numerical analysis has been carried out to investigate the effect of laser power density on both dynamic and residual stresses. The optimum process conditions for LSP were established, and the cost-effectiveness of the technique has been analysed. The DSTO investigation showed that LSP is an effective fatigue life extension technology, although it has a high capital investment and running costs.
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ISBN:
Category : Aluminum alloys
Languages : en
Pages : 18
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