叶顶间隙和减振阻尼台对多级轴流压气机性能影响的数值模拟

A multi-stage axial flow compressor was studied by numerical simulation to determine the effect of tip clearance and damper table on its aerodynamic performance. The influence principle of tip clearance change on tip leakage flow was revealed，and the relative magnitude of the influence of rotor tip clearance change on the performance of multi-stage axial compressor was analyzed. It was found that for the studied multi-stage axial flow compressors，the change of the tip clearance of the fifth stage rotor had the largest impact on the compressor performance. Stage efficiency decreased by 1.72% when the tip clearance increased from 0.390 mm to 1.007 mm. There was a maximum reduction of 0.6% in other stages. Furthermore，the first-stage and fifth-stage rotor blade damper tables were investigated for their effects on compressor performance. The influence of the damper table on the flow field structure and flow capacity was analyzed，and the mechanism of the damper table affecting the performance was revealed. The results showed that when there was the damping table，the peak efficiency，peak pressure ratio and choke flow rate of multi-stage axial flow compressor decreased; as the peak efficiency decreased by 1.6%，the peak pressure ratio decreased by 1.2%，and the choke flow decreased by 1.2%. Especially，the efficiency of the first and fifth staged decreased obviously，the efficiency of the first stage decreased by about 5.2%，and that of the fifth stage decreased by about 1.6%. As a result of the damping table，the pressure loss was caused，the density flow and flow capacity decreased.