The high temperature low cycle fatigue life of the 2nd stage turbine blade in an aircraft engine in service has been evaluated by use of the experimental method

in which the effect of creep has been considered.In order to shorten the test period

according to the principle of damage-equivalence

the equivalent accelerated test loading-spectrum has been determined.The test has been implemented on a test-bed in which eddy current inducted heating and hydraulic pressure driven force are applied.The test results have been analyzed statistically by use of logarithmic normal distribution and Weibull distribution

and the safe in-service life of the blade with the confidence level of 95% and the reliability of 99.87% has been determined.