The low cycle fatigue life test of high pressure turbine disk of an engine was studied by using safe life procedure based on Britain military standard Defence Standard 00971 safety requirements for disks. The finite element method was used for analyzing the stress field of high pressure turbine disk of engine under working conditions

and the effect of temperature field on stress distribution was considered. The critical position and reference cycle of high pressure turbine disk were determined according to Defence Standard 00971; then the test plan of low cycle fatigue life of high pressure turbine disk was formed

and the safe life assessment method of high pressure turbine disk based on test results was determined finally. The analysis shows that the stress factors of hub and bolt-hole are 1.0 and 1.017 respectively

which are within a reasonable scale; the test method of increasing rotation speed and cutting turbine blade simultaneously can simulate the effect of thermal stress on life effectively

giving important guidelines for low cycle fatigue life test of high pressure turbine disk.