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HomeMaterials Science ForumMaterials Science Forum Vols. 524-525Influence of Residual Stress Redistribution on...

Influence of Residual Stress Redistribution on Fatigue Crack Growth and Damage Tolerant Design

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Abstract:

The safe operation of many structures and components is ensured through the operation of damage tolerant design and evaluation. Substantial residual stresses can exist in many systems and it is important that these are incorporated in damage tolerance calculations of fatigue crack growth. Recent improvements in non-destructive measurement techniques and in the application of weight or Green’s functions methods of including residual stress fields into stress intensity factor (SIF) calculations have enabled predictions of the effects of residual stresses on fatigue crack propagation to be made more readily. Two examples from the aerospace industry, structures containing (i) cold expanded holes and (ii) fusion welds are used to show that presently, although final crack growth lives can be accurately predicted, the details of crack growth are not well represented with initial growth typically being underestimated and later growth being over estimated. It is shown that this is most likely to be due to residual stress redistribution. and that this must be built into fatigue life prediction models if accurate damage tolerance based procedures are to be developed for components and systems containing substantial residual stresses.

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Periodical:

Materials Science Forum (Volumes 524-525)

Pages:

363-372

DOI:

https://doi.org/10.4028/www.scientific.net/MSF.524-525.363

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Online since:

September 2006

Authors:

Lyndon Edwards

Keywords:

Damage Tolerant Design, Fatigue Crack Growth (FCG), Residual Stress, Structural Integrity

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© 2006 Trans Tech Publications Ltd. All Rights Reserved

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[1] D.V. Nelson, in: Residual Stress Effects in Fatigue, ASTM STP 776 (1982) 172-187.

[2] V.M. Leitao, M.H. Aliabadi, D.P. Rooke and R. Cook, J Mat. Eng. & Perf., Vol. 7 (1998) 352360.

[3] H. F Bueckner, Zeit. für Angewandte Math. und Mech., Vol 50, (1970)529-546.

[4] J.R. Rice, Int. J. Solids Struct., Vol. 8 (1972) 751-758.

[5] A.P. Parker, in: Residual Stress Effects in Fatigue, ASTM STP 776 (1982) 13-31.

[6] G. Glinka in: Fracture Mechanics ASTM STP 677 (1979) 198-214.

[7] K. Masubuchi and D.C. Martin, Weld. J. Vol. 40 (1961) 553-563.

[8] J. M-L. Tan, M. E Fitzpatrick and L. Edwards, submitted to Eng Fract Mech.

[9] J. M-L. Tan, M. E Fitzpatrick and L. Edwards, in: Proc. ICAF 2005 EMAS, Cradley Heath, UK.

[10] M. E. Fitzpatrick and L. Edwards, J. Mat. Eng. & Perf., Vol. 9 (1978) 190-198.

[11] A.T. Ozdemir, R. Cook, R., and L. Edwards, in Durability and Structural Integrity of Airframes, Proc. ICAF 1993, EMAS, UK, Vol. 1, (1993) 207-237.

[12] D. Stefanescu, A. Steuwer, R. A. Owen, B., Nadri, L, Edwards, M.E., Fitzpatrick and P J Withers, J. Strain Anal. Eng. Des., Vol 39, (2004) 459-469.

DOI: 10.1243/0309324041896470

[13] D. Stefanescu, L. Edwards, and M.E. Fitzpatrick, Int. J. Fatigue, Vol. 25 (2003) 569-576.

[14] E.T. Eastbrook, B.D. Flinn, C. Meyer, and N. Juhlin, N. The StressWave Fatigue life Enhancement Process. in Proc. 2001 Aerospace Congress, SAE 2001-01-2578. (2001).

DOI: 10.4271/2001-01-2578

[15] A.F. Liu, AIAA J., Vol. 22 (1984) 1784-1785.

[16] A.F.J. Grandt, Int. J. Fracture, Vol. 11 (1975) 283-294.

[17] J.A. Harter, AFGROW Users Guide and Technical Manual. (2004)AFRL-VA-WP-TR-(2004).

[18] R.G. Forman, V. Shivakumar, S. Mettu, and J.C. Newman, (2000)NASGRO Version 3. 00 Reference Manual : Fatigue crack growth computer program, NASA Document JSC-22267B.

[19] Z. Wang and X. Zhang, Int. J. Fatigue, Vol. 25 (2003) 1285-1291.

[20] A. T Ozdemir and L. Edwards Fat & Fract Eng Mar Str, Vol. 3 (1998) 12-15.

[21] D. Stephanescu, Ph. D Thesis (2001) Dept of Materials Engineering, Open University, UK.

[22] B. Nadri, Ph. D Thesis (2004) Dept of Materials Engineering, Open University, UK.

[23] J. M-L. Tan, S. Pratihar, M. E Fitzpatrick and L. Edwards, Residual Stress Redistribution in Fatigue-aged StressWave Cold-Worked holes, in: Proc. MECA-SENS (2005).

[24] L. Edwards, M.E. Fitzpatrick, P.E. Irving, I. Sinclair, X. Zhang, and D. Yapp. D. (2006) J ASTM Int Vol. 3, (2006) paper JAI12547, doi: 10. 1520/JAI12547.

[25] X. Zhang and Y. Li, AIAA J., Vol. 43 (2005) 1613-1623.

[26] X. Zhang, P.E. Irving, L. Edwards, M.E. Fitzpatrick, I. Sinclair, J. Lin and D. Yapp. D. (2006) in Proc ICAF 2005 EMAS, Cradley Heath, UK.

[27] S. Pratihar, S. Ganguly, J.A. James, M.E. Fitzpatrick and L. Edwards, in: Proc MECA-SENS (2005).

[28] J. M-L. Tan Ph. D Thesis (2006) Dept of Materials Engineering, Open University UK.