Aero-engine turbine disc stress prediction method

The invention relates to the technical field of aero-engine turbine disc stress prediction, and discloses an aero-engine turbine disc stress prediction method, which comprises the following steps of: performing dimension reduction processing on data in an overall parameter set on the basis of turbine disc stress distribution under a corresponding steady-state working condition to obtain a characteristic monitoring parameter set with relatively high correlation with turbine disc stress; and by taking the characteristic parameter set subjected to dimensionality reduction preprocessing under each steady-state working condition as input and the turbine disc stress corresponding to the steady-state working condition as output, establishing an aero-engine turbine disc stress random forest prediction model, and predicting the turbine disc stress of the aero-engine under the to-be-measured working condition. Main control factors highly associated with the turbine disk stress are found out through dimensionality reduc