整体涡旋流对跨声速压气机Stage 67影响的定常数值仿真研究

Steady Numerical Simulation of Transonic Compressor Stage 67 with Bulk Swirl Distortion

关键词:  旋流  畸变  整体涡  压气机  数值仿真

Key words:  Swirl  Distortion  Bulk swirl  Compressor  Numerical simulation

摘要:

为研究不同旋流强度的整体涡旋流畸变对跨声速压气机的影响，采用定常数值仿真的方法，基于一种整体涡旋流畸变发生器与Stage 67跨声速压气机展开联合仿真研究。通过改变旋流畸变发生器叶片角度，可以模拟不同强度的整体涡旋流畸变流场，在不同旋流进气工况下得到了压气机的压比、效率特性曲线，并针对流场细节进行分析，研究其失速机理。结果表明：同向整体涡有效降低近失速点叶顶通道堵塞程度，使叶片流动损失减小，压气机稳定裕度扩大；反向整体涡加剧叶背气流流动分离程度，引起吸力面尾部低速区面积扩大，导致叶顶堵塞程度的显著加剧，通道流动损失增加明显，造成压气机稳定裕度下降。

Abstract:

In order to study the effects of the bulk swirl distortion with different intensity on transonic compressor， a steady numerical simulation study was carried out based on a bulk swirl distortion generator and Stage 67 transonic compressor. By changing the swirl distortion generator blade angle， the bulk swirl flow field with different intensity can be simulated. The pressure ratio and efficiency characteristic curves of the compressor are obtained under different swirl inlet conditions. The flow field details are analyzed to study the stall mechanism. The results show that the positive swirl in the same direction effectively reduces the choke of the tip passage near the stall point， reduces the blade flow loss and enlarges the stability margin of the compressor. The negative swirl intensifies the flow separation at the back of the blade， which causes the expansion of the low-speed area at the tail of the suction surface and then significantly aggravates the choke of blade tip. The negative swirl significantly increases the flow loss of the passage， and causes the decrease of the stability margin of the compressor.