Abstract
Al-Li alloy 2198-T8 was chosen to be used. The friction stir welded integral panel for fuselage application was designed and simplified into two typical testing samples. Residual stress profiles in single weld sample and double weld sample were respectively measured by neutron diffraction method. The distribution of residual stress was analyzed. Fatigue tests of two samples and parent material were performed and crack growth rates were measured and compared. In order to study the effect of residual stress, the finite element model was built and Kresidual of each type was calculated. Kresidualeffects on fatigue parameters were analyzed, and Newman closure model was used to calculate fatigue lives, which were compared with the experimental lives. It was shown that: the fatigue life of double weld sample is four times than that of single weld sample; residual stresses changed the distributions of fatigue property parameters with crack growing.
| Original language | English |
|---|---|
| Pages (from-to) | 98-102 |
| Number of pages | 5 |
| Journal | Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University |
| Volume | 31 |
| Issue number | 1 |
| State | Published - Feb 2013 |
Keywords
- Aluminium alloys
- Fatigue crack propagation
- Friction stir welding
- Fuselages
- Residual stresses
- Stress concentration