Author(s)

S.R Claridge & B.E. Powell

Abstract

Fatigue crack growth lives at room temperature have been measured for a forged titanium aeroengine alloy. The experimental loadings used simulate two features of the engine flight pattern: the major stress cycles representing the start-stop operation, and the minor stress cycles representing the in-flight vibrations. The fatigue crack growth lives for the same conditions have also been predicted using the nCode software package "Kraken" in conjunction with materials data established by the experimental programme. The comparison of experimental and predicted lives shows good correlation, with the majority of predictions being within ±50% of the actual observed life. It is concluded tha

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