In this paper

a typical condition method is proposed for compressing the creep/ duration load spectrum of aeroengine. Using this method a lot of load conditions of a model of tur-boshaft aeroengine are compressed to four typical load conditions. The approach provides the technical basis for formulating the Simulation Mission Equivalent Test spectrum

and the Accelerated Mission Test spectrum

and assessing the strength and life of the turboshaft aeroengine components. The result of research shows that

in the existing conditions

the creep/duration load spectrum for the turbine blades

compressed by the typical condition method

can satisfy the application of engineering

and this method is reasonable and feasible.