Aero-engine Gas Path Analysis Method during Transient Process

At present, most of the research on aero-engine gas path analysis is based on the steady-state process of the engine, but the steady-state data is usually difficult to obtain, and some fault features can only be displayed in the transient working state, so the transition state data which is relatively easy to obtain can be used to evaluate the health state of the engine more comprehensively. In the case of a small number of gas path sensors, a large number of health parameters are analyzed by using the sequential operating points method, which can increase the available information and reduce the systematic error of parameter estimation introduced by the average effect of the multiple working points method. An indirect recursive Newton Raphson method is proposed to enhance the non-dominated sorting differential evolution algorithm to solve the problem of computational convergence in the estimation of large deviation performance degradation health parameters of engines. The results show that this method can effectively and accurately estimate a large number of health parameters in a large deviation range by using engine transition state data under the condition of limited number of gas path sensors.