A study of the residual stresses and distortion processes in aircraft aluminium forgings was performed by finite element modeling. Results showed that the use of 7050-T7451 thick plate in place of the 7050-T7452 compression stress-relieved forgings improved the machining issues and distortion in parts. The reduction of residual stresses also enabled improvement in fatigue life, corrosion resistance, mechanical properties and performance of the parts.
Residual stress analysis of aircraft aluminum forgings
Advanced Materials & Processes ; 160 , 6 ; 57-60
2002
4 Seiten
Article (Journal)
English
Fatigue Life Variability in Large Aluminum Forgings with Residual Stress
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