For transport aircraft with long lifetimes, crack growth data to implement the durability life requirements in the low AK range are needed. This is the region comprising most of the lifetime for the cracks of interest, and it is also the region where there is little data available. Crack growth data
An evaluation of ΔKeff estimation procedures on 6061-T6 and 2024-T3 aluminum alloys
✍ Scribed by Keith Donald; Paul C. Paris
- Book ID
- 104288838
- Publisher
- Elsevier Science
- Year
- 1999
- Tongue
- English
- Weight
- 578 KB
- Volume
- 21
- Category
- Article
- ISSN
- 0142-1123
No coin nor oath required. For personal study only.
✦ Synopsis
Experimental and analytical evidence indicates that 'closure' or interference of crack faces does not entirely isolate the crack tip from damaging strains due to cyclic loading. Therefore, an estimation of the effective stress intensity range at the crack tip, ⌬K eff , should take into account the additional cyclic crack tip strain below the opening load. In this investigation, the estimation of ⌬K eff is based on the traditional opening load method and also on numerous new methods that show improved correlation of fatigue crack growth rate stress ratio effects in general but mostly at near-threshold growth rates. The experimental results of this study also indicate that the fatigue crack growth rate is not determined solely by ⌬K eff but also depends on K max . A procedure for determining an intrinsic crack growth rate curve is described.
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