Mechanism of Fatigue Life Improvement due to Fine Particle Shot Peening in High Strength Aluminum Alloy

被引：13

作者：

Inoue, Akiko ^{[1
,2
]}

Sekigawa, Takahiro ^{[2
]}

Oguri, Kazuyuki ^{[2
]}

Tagawa, Tetsuya ^{[3
]}

Ishikawa, Takashi ^{[1
]}

机构：

[1] Nagoya Univ, Grad Sch Engn, Dept Mat Sci & Engn, Nagoya, Aichi 4648603, Japan

[2] Mitsubishi Heavy Ind Co Ltd, Nagoya Aerosp Syst Works, Nagoya, Aichi 4558515, Japan

[3] Osaka Univ, Grad Sch Engn, Dept Mat & Mfg Sci, Suita, Osaka 5650871, Japan

来源：

JOURNAL OF THE JAPAN INSTITUTE OF METALS | 2010年 / 74卷 / 06期

关键词：

shot peening; fatigue life; aluminum alloy; fine particles; crack initiation; linear fracture mechanic; INITIAL FLAW SIZES; GROWTH;

D O I：

10.2320/jinstmet.74.370

中图分类号：

TF [冶金工业];

学科分类号：

0806 ;

摘要：

Shot peening is widely used in the aerospace industry in order to improve fatigue property of structural high strength aluminum alloy. However, the optimum shot peening condition has not been revealed, considering the effect of the shot peened surface roughness and the residual stress profile on fatigue life. In this study, fatigue life improvement of 7050-T7451 due to the shot peening with the fine particles whose diameter was less than 0.1 mm was studied and compared with the fatigue life of the shot peened material with the conventional steel shot of 0.6 mm in diameter. The fine particle shot peened (FPSP) specimens endured about ten times longer fatigue life than the virgin specimens and several times longer than the conventional shot peened specimens. The fatigue crack in FPSP specimens initiated at the subsurface layer or the inside of the specimen, while the fatigue crack initiation site in the conventional shot peened specimen or the virgin specimen located on the specimen surface. It was revealed that the fatigue improvement effect of FPSP mainly resulted from the transition of the crack initiation site due to the shallow compressive residual stress layer near the specimen surface, considering the arrested small cracks detected on the fractured specimen side surface K analysis based on the compressive residual stress profiles.

引用

页码：370 / 377

页数：8

共 15 条

[1] Initiation and early growth of fatigue cracks in an aerospace aluminium alloy
Barter, SA
Sharp, PK
Holden, G
Clark, G
[J]. FATIGUE & FRACTURE OF ENGINEERING MATERIALS & STRUCTURES, 2002, 25 (02) : 111 - 125
[2] Bueckner H. F., 1973, Mechanics of fracture. Vol.1: Methods of analysis and solutions of crack problems, P239
[3] The surface treatment influence on the fatigue crack propagation of Al 7050-T7451 alloy
Carvalho, A. L. M.
Voorwald, H. J. C.
[J]. MATERIALS SCIENCE AND ENGINEERING A-STRUCTURAL MATERIALS PROPERTIES MICROSTRUCTURE AND PROCESSING, 2009, 505 (1-2): : 31 - 40
[4] DeBartolo EA, 2001, INT J FATIGUE, V23, pS79, DOI 10.1016/S0142-1123(01)00122-0
[5] Effects of constituent particle clusters on fatigue behavior of 2024-T3 aluminum alloy
DeBartolo, EA
Hillberry, BM
[J]. INTERNATIONAL JOURNAL OF FATIGUE, 1998, 20 (10) : 727 - 735
[6] Egami N., 2000, Trans. Jpn. Soc. Mech. Eng. A, V66, P1936, DOI [10.1299/kikaia.66.1936, DOI 10.1299/KIKAIA.66.1936]
[7] The effect of constituent particles in aluminum alloys on fatigue damage evolution: Statistical observations
Harlow, D. G.
Nardiello, J.
Payne, J.
[J]. INTERNATIONAL JOURNAL OF FATIGUE, 2010, 32 (03) : 505 - 511
[8] Residual stress effects on near-threshold fatigue crack growth in friction stir welds in aerospace alloys
John, R
Jata, KV
Sadananda, K
[J]. INTERNATIONAL JOURNAL OF FATIGUE, 2003, 25 (9-11) : 939 - 948
[9] Characterisation of equivalent initial flaw sizes in 7050 aluminium alloy
Molent, L.
Sun, Q.
Green, A. J.
[J]. FATIGUE & FRACTURE OF ENGINEERING MATERIALS & STRUCTURES, 2006, 29 (11) : 916 - 937
[10] Kmax effects on the near-threshold fatigue crack growth of powder-metallurgy aluminum alloys
Newman, John A.
Smith, Stephen W.
Piascik, Robert S.
[J]. INTERNATIONAL JOURNAL OF FATIGUE, 2009, 31 (8-9) : 1237 - 1245

← 1 2 →