进气弯管几何参数对跨声速离心压气机性能的影响  

Effect of Geometric Parameters of Intake Bend Pipe on Performance of Transonic Centrifugal Compressor

作　　者：孔庆国[1] KONG Qingguo(Sino-European Institute of Aviation Engineering,Civil Aviation University of China,Tianjin 300300,China)

机构地区：[1]中国民航大学中欧航空工程师学院,天津300300

出　　处：《天津科技》2022年第8期26-30,共5页Tianjin Science & Technology

基　　金：中国民航大学实验技术创新基金项目“小型离心式压气机进气畸变特性实验台研究”(2020CXJJ83)。

摘　　要：对弯管进气的跨声速离心压气机进行数值模拟分析,研究不同弯管几何参数对压气机性能的影响规律并分析其影响机理,结果表明弯管进气下压气机性能均有所下降。叶轮与上游弯管的气流存在较强的相互作用,弯道出口与离心压气机叶轮前缘截面距离越小弯管角度越大,叶轮进口截面的周向畸变越严重;周向畸变程度与压气机性能下降程度之间无必然联系,畸变进口与叶轮端区的二次流相互作用能够改变叶轮进口激波形貌及端区的损失特性,进而影响离心压气机的工作性能。A transonic centrifugal compressor with intake bend pipe is numerically simulated to study the influence of different geometric parameters of the intake bend pipe on the performance of the compressor and analyze its influence mechanism. The results show that the compressor performance decreases under the effect of intake bend pipe. There is a strong interaction between the impeller and the upstream bend pipe. The smaller the distance between the bend outlet and the leading edge of the impeller and the larger the bend angle,the more serious the circumferential distortion of the impeller inlet section. There is no inevitable relationship between the degree of circumferential distortion and the degradation of compressor performance. The interaction between the distorted inlet and the secondary flow in the end wall region of the impeller can change the shape of the shock wave at the inlet of the impeller and the loss mechanisms therein,which affects the working performance of the centrifugal compressor.

关 键 词：跨声速离心压气机 进气弯管 数值模拟 畸变 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]