The Effects of Laser Peening on Fatigue Performance of Overloaded 7050-T7451 Aluminum and In-service T-38 MLG Trunnion Component PDF Download
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Author: Chanh Hung Truong
Publisher:
ISBN:
Category :
Languages : en
Pages : 164
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Book Description
Author: Chanh Hung Truong
Publisher:
ISBN:
Category :
Languages : en
Pages : 164
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Book Description
Author: Jasleen Bhoon
Publisher:
ISBN:
Category :
Languages : en
Pages : 178
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Book Description
Author: Marc Edward Hopkins
Publisher:
ISBN:
Category :
Languages : en
Pages : 244
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Author: Harold Luong
Publisher:
ISBN:
Category :
Languages : en
Pages : 196
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Book Description
Author: Theresa Elizabeth Pistochini
Publisher:
ISBN:
Category :
Languages : en
Pages : 222
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721288151
Category :
Languages : en
Pages : 38
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Book Description
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: Liucheng Zhou
Publisher: Springer Nature
ISBN: 9811617473
Category : Technology & Engineering
Languages : en
Pages : 241
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Book Description
This book introduces the fundamentals and principles of laser shock peening (LSP) for aeronautical materials. It focuses on the innovation in both theory and method related to LSP-induced gradient structures in titanium alloys and Ni-based alloys which have been commonly used in aircraft industries. The main contents of the book include: the characteristics of laser shock wave, the formation mechanism of gradient structures and the strengthening-toughing mechanism by gradient structures. The research has accumulated a large amount of experimental data, which has proven the significant effectiveness of LSP on the improvement of the fatigue performance of metal parts, and related findings have been successfully applied in aerospace field. This book could be used by the researchers who work in the field of LSP, mechanical strength, machine manufacturing and surface engineering, as well as who major in laser shock wave and materials science.
