槽深对跨音速压气机稳定性影响的数值仿真

Numerical Simulation of Influence of Groove's Depth on Stability of Transonic Compressor

为了研究不同槽深下的周向槽对压气机稳定性的影响,由于带槽结构下的转子37失速类型仍是叶尖失速,但是带周向槽结构的主要失速因素是叶尖间隙的泄漏涡,且不同轴向位置的周向槽所造成的损失也是不同的。为解决上述问题,利用NUMECA软件和系统的数值模型对某跨音速压气机进行了数值仿真,对三类带周向槽结构的计算结果进行了分析,结果表明,设计中讨论最佳槽深应先给定效率损失要求,并且应以研究最佳槽位置的选择为主。对压气机周向槽处理机匣的设计,不一定要设计涉及整个叶片的处理机匣。对于跨音速压气机在叶尖泄漏涡严重的位置优化设计,可提高压气机稳定性能。

With the aid of CFD software NUMECA and a dependable numerical model, computational simulating was performed on an transonic compressor, hoping to discover the effects of different depth grooves on the compressor stability. And it was found that the stall of Rotor 37 with casing treatment is still on the blade tip, but the main effect of the stall is the tip clearance leakage vortex（ TLV）, besides, the grooves of the different axial position have differ- ent effects on the efficiency loss. We should set the efficiency loss limit when talking about the best circumferential groove depth, and it is more useful to discuss the most effective position where the groove should be given than loo- king for the best depth. And we do not have to design the casing treatment that covers the whole blade. It is better to put them on where the TLV happens seriously in the transonic compressor.