The application belongs to the field of aero-engine design, and is a service damage evaluation method for
single crystal high-pressure
turbine working blades. The method comprises the following steps: firstly, determining the stress and temperature range of each working condition of the actual service
single crystal high-pressure
turbine working blades; secondly, designing and manufacturing a plurality of blade
simulation pieces corresponding to the stress and temperature range of the different working conditions of the actual service
single crystal high-pressure
turbine working blades to perform a
creep interruption test, so as to obtain the corresponding relationship between different temperature-stress and
coating,
coating-substrate interface
microstructure damage; thirdly, comparing the interface
microstructure damage atlas and the main phase content with the standard atlas of the blade
simulation pieces under different temperatures and stress degrees, and selecting the temperature and stress of the blade
simulation piece closest to the actual service single
crystal high-pressure turbine working blades as the temperature and stress of the sampling position of the actual service single
crystal high-pressure turbine working blades; and finally, evaluating the
coating microstructure damage and performance degradation degree, so that the
coating microstructure damage degree of the service single
crystal high-pressure turbine working blades can be comprehensively and truly evaluated.