叶顶间隙对压气机非设计转速气动性能影响的试验研究

Experimental Study on the Influence of Tip Clearance on Aerodynamic Performance of Compressor at Off-design Rotational Speed

为研究叶尖间隙对压气机非设计转速性能特性与稳定边界的影响,以某大涵道比涡扇发动机的十级高压压气机为研究对象,在高转速压气机试验器上开展了试验研究。采用精细化的级间参数测量,以揭示叶尖间隙影响多级压气机级间匹配的机理。结果表明:叶尖间隙增大后,压气机非设计转速的流量减小、效率降低,且间隙对气动稳定性有显著影响,压气机的前面级未出现压比降低的情况,后面级做功能力明显降低,间隙影响主要集中在叶高80%截面以上,使得压气机更容易进入失速状态。

In order to investigate the effects of tip clearance on the off-design rotating speed performance and stable boundary of compressors,taking a ten stages highly loaded compressor of a high bypass ratio turbofan engine as the research object,the experimental study was carried out on a high speed compressor tester.Detailed measurement of inter stage parameters was adopted to reveal the mechanism of tip clearance effects on the inter stage matching of multistage compressors.The results show that increased tip clearance leads to a reduction of the mas flow and efficiency of the compressor at off-design rotating speed.In addition,the tip clearance has a significant impact on the aerodynamic stability.There is no pressure ratio reduction in the front stages of the compressor while the tip clearance increases,but the work capacity of the back stages decreases obviously.The influence of the tip clearance is mainly on the section above 80%of the blade height,which makes the compressor more likely to stall.