S弯进气道出口旋流对轴流压气机性能的影响

为探究S弯进气道出口旋流对轴流压气机性能的影响，优化设计了旋流畸变网以模拟旋流，利用数值模拟的方法探究了单级轴流压气机在S弯进气道出口旋流作用下的气动响应，获得均匀进气条件和旋流进气条件下的压气机特性线和流场分布。结果表明:优化后的旋流畸变网总体旋流角误差降低了。S弯进气道出口旋流对增压能力影响不大，但会导致压气机效率下降，稳定工作范围减小。在100%和80%换算转速，压气机的压比最大降幅分别为0.12%和0.28%，在峰值效率点附近的效率最大降幅为3.2%和14.4%。S弯进气道出口旋流中的反向旋流区增大了转子叶片进气攻角，导致气流叶背分离、叶片通道堵塞，最终导致压气机失稳。 

Effects of swirl at outlet of S-shaped inlet on axial flow compressor perfor mance

In order to estimate the effects of swirl at outlet of S-shaped inlet on the performance of axial flow compressor, a swirl distortion network was optimized and designed to simulate the swirl flow field. The aerodynamic response of the single-stage axial flow compressor under the effect of the swirl at the outlet of the S-shaped inlet was investigated by numerical simulation. The characteristic map and flow field distributions of the compressor under the condition of uniform intake and swirling intake were obtained. The results show that the overall swirl angle error of the optimized swirl distortion network is reduced. The swirl flow at the outlet of S-shaped inlet has little influence on the pressurization ability, but it will lead to the decrease of compressor efficiency and decrease of stability. At the corrected speed of 100% and 80%, the maximum reduction of pressure ratio is 0.12% and 0.28% respectively, and the maximum reduction of efficiency near the peak efficiency point is 3.2% and 14.4% respectively. The reverse swirl zone in the swirl at the outlet of the S-shaped inlet increases the inlet attack angle of the rotor blade, resulting in the separation of airflow at the suction side and the blockage of the blade passage, which eventually leads to the instability of the compressor.