湍流型动态畸变下涡喷发动机稳定性分析

ANALYSIS AND PREDICTION OF AERODYNAMIC STABILITY OF AEROENGINE WITH TURBULENCE-TYPE DYNAMIC INLET DISTORTION

对湍流型动态畸变进气流场进行了分析和描述，给出了随机涡在压气机进口所产生的总压脉动的通用分布曲线，并统计地分析和预测了该总压脉动引起的最可能最大失速裕度损失。数值分析表明在考虑压气机对非定常流响应方面，最为关心的压气机最大失速裕度损失值是脉动压力的均方根值、功率谱密度、压气机进口转子弦长和转速的函数。

Inlet destortion is analyzed and described by combining aerodynamics with statistical mathematics according to randomness of its instantaneous distorted field.The normalized curve of total pressure fluctuation produced by random vortex at compressor inlet is given.The most probable maximum loss in stall margin resulted from the total pressure fluctuation is statistically analyzed and predicted.Numerical analysis shows that the most probable maximum loss in stall margin,which is of significance in the compressor reaction to unsteady inlet flow,is the function of the Root Mean Square (RMS) level,Power Spectral Density (PSD),compressor rotor chord and RPM.