真实进气条件下发动机气动稳定性计算方法

基于平行压气机理论，采用非定常、二维、无黏的积分型欧拉方程，以蒸汽吸入试验中产生的温度和压力组合畸变为边界条件，开展真实进气条件下温度和压力组合畸变对发动机影响的计算方法研究。在保证畸变强度、高温区范围、低压区范围等特征不变的前提下，对畸变图谱进行规则化等效转换，同时协调温度和压力畸变图谱，使两者可以进行相互叠加计算。结果表明:当周向子发动机数量大于2时，子发动机数量对计算结果影响不大；组合畸变对风扇、压气机压比影响规律与单独的压力畸变相同；与试验的推力损失对比显示，对畸变图谱进行等效规则化转换，可以用于真实组合畸变的计算。 

Aerodynamic calculation method of engine stabilityunder actual inlet condition

Based on the theory of parallel compressor, the calculation method of the influence of actual combined distortion on the engine was studied with the temperature and pressure distortion generated by the steam suction as boundary conditions. The unsteady two-dimensional inviscid integral Euler’s equations were used. While the distortion intensity, the high temperature range, and the low pressure range were kept the same, the regularized equivalent conversion of the distortion contour maps was performed. And the temperature and pressure distortion contour maps were coordinated, so that these two could be superimposed on each other. Results showed that when the number of circumferential sub-engines was greater than 2, the number of sub-engines had little effect on the calculation results. The influence of combined distortion on the fan and compressor pressure ratio was the same as the single pressure distortion. Compared with the experimental thrust loss, the equivalent regularization transformation of the distortion map can be used for the calculation of the actual combined distortion.