压力-温度组合畸变下航空发动机失速/ 喘振适航审定

Due to its complex nonlinear mechanism， the combined distortion of pressure and temperature poses great challenges to the stability evaluation. Through numerical simulation of a single stage axial compressor，the influence of the combined pressure-temperature distortion on the stability of the compressor under different combined distortion intensities and combined phase angles was investigated. The results show that the smaller the phase angle is，the greater the loss of stability margin is，and the maximum loss of surge margin is at 0° phase angle. Changing the total pressure distortion intensity affects the relative Mach number distribution of the aerodynamic measurement section and the inlet angle of attack. The increase of the total pressure distortion intensity leads to the delay of the leading edge overflow，so the flow difference at the instability point is small under different total pressure distortion intensities. Finally， according to the requirements of relevant clauses， the verification process of aeroengine stall/surge compliance under the combined distortion of pressure and temperature is established.