Correction Methods for Aeroengine Performance Parameters under Broad Flight Envelopes and Extensive Operating States

Abstract

To ensure the accuracy of parameter correction under broad flight envelopes and extensive operating states, a parameter correction method based on modified exponents is proposed for common parameters, along with a correction method based on the contour lines of total inlet pressure for the surge margin. First, using the engine component-level model (CLM), the steady-state operational data of the engine under broad flight envelopes and extensive operating states are collected. Second, the control settings under different flight conditions are mapped to equivalent corrected control variables. For common parameters, the correction exponents are modified by incorporating control variables and nonlinear functions. For the surge margin, the deviations are corrected along the contour lines of total inlet pressure, thereby establishing a correction model suitable for broad flight envelopes and extensive operating states. Finally, the simulation results demonstrate that, compared with the traditional correction method, the improved correction methods enhance the correction accuracy of the rotor speed, the turbine inlet temperature, and the compressor inlet pressure by approximately 4 times; the correction accuracy of specific fuel consumption and thrust by approximately 40 times; and reduce the average error of the corrected fan and compressor surge margin to less than 1%, thus verifying the effectiveness of the improved correction methods.