Reliability analysis method for high-pressure turbine blade of aero-engine

The invention provides a reliability analysis method for a high-pressure turbine blade of an aero-engine, which comprises the following steps of: S1, extracting a first group of calculation parameters from a parameter matrix, and carrying out finite element analysis on an overall model of the high-pressure turbine blade by adopting a rough mesh; s2, for a plurality of regions of interest, sub-models for establishing fine grids are segmented, and boundary conditions of the sub-models are extracted; s3, carrying out grid independence verification on the sub-model of each region, adjusting the boundary of the sub-model, repeating the step S2, and checking a sub-model result; s4, circularly calculating other groups of parameters until all sampling points are calculated; and S5, according to a calculation result, establishing a multi-region agent model for each sub-model region. The method provides important reference for blade reliability design and optimization. Compared with a traditional method, the method is