Fatigue specimen with central hole was designed based on the bolthole of a high pressure compressor disk. Of the asreceived (AR) specimens and after holeexpansion (HE)

the surface profile and fatigue property in multiple alternating loads were characterized; moreover

failure analysis and the evolution of HE residual stress profile during fatigue cycle were investigated. Results showed that

after HE

the roughness of hole wall decreased

besides

the high temperature fatigue performances improved 1-3 times under multiple large load condition with the slight rise of fatigue data dispersion. The HE residual stress released to 60% during 20000 cycles at the maximum tensile stress of 663MPa

temperature of 600℃ and stress ratio of 01. Compared with the untreated specimens nucleating at machining marks

the HE crack initiated at metal accumulation by HE in the chamfer

presenting single source crack initiations.