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
The effect of sheet thickness on fatigue crack retardation in 2024-T3 aluminum alloy
โ Scribed by W.J. Mills; R.W. Hertzberg
- Publisher
- Elsevier Science
- Year
- 1975
- Tongue
- English
- Weight
- 794 KB
- Volume
- 7
- Category
- Article
- ISSN
- 0013-7944
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โฆ Synopsis
Variable-amplitude fat@ue studies of 2024-13 ab&num alloy were performed to examine the effect of sheet thickness on fatigue crack growth rate retardation. Results indicated tbat the amouot of retardation increased with decreasing specimen thickness. This phenomenon was attrii to enhanced plastic strains under plane stress conditions (i.e. in a tbin sheet) which formed abead of the advanchy crack tip as a result of a hi,@ load excursioo. These strains are believed to produce both crack closure and a favorable compressive residual stress field around the crack tip. Evidence of increased crack surface interference under plane stress situations was vcri&d with electron fractograpbic observations.
๐ SIMILAR VOLUMES
Experiments have been made to investigate the effect of mean stress on fatigue crack propagation in +in. (12.7mm) thick specimens of six aluminium alloys of high and low fracture toughness. The resuits are presented in terms of the stress intensity factor range, AK and the R value where R is the rat