Fatigue tests were conducted on DD6［001］ single crystal alloy specimens with the same service state as aeroengine gas turbine blades，and sufficient fatigue test data were acquired.Based on data transformation，four subsamples for fatigue life testing and one subsample for fatigue strength testing under 10⁷ cycles were designed.The safety screening subsample method was adopted to optimize all subsamples.Fatigue P-S-N curves corresponding to survival probabilities of 0.13%，50% and 99.87% were fitted with fatigue stress-life data via Origin software.According to the random fatigue limit model，the relational equations between fatigue strength （stress） and fatigue life of DD6［001］ alloy under the three survival probabilities were established，and the reliability evaluation system for aeroengines was constructed.The research conclusions can provide basic fatigue reliability data for the modeling，testing and probabilistic design of endurance tolerance of DD6［001］ alloy structural components in aeroengines.They can also be applied to predict the service life and fatigue strength of DD6［001］ alloy parts，and serve as quantitative indexes for the acceptance and performance evaluation of fatigue properties of aeroengine components made of DD6［001］ alloy.