端壁自适应射流对跨声速压气机近失速工况性能影响的数值研究  

Numerical study on effects of endwall self-adaptive injection on performance of transonic compressor at near stall condition

作　　者：李晓东 梁作召 孙鹏 崔兴达 刘晗 LI Xiaodong;LIANG Zuozhao;SUN Peng;CUI Xingda;LIU Han(School of Safety Science and Engineering,Civil Aviation University of China,Tianjin 300300,China;No.703 Research Institute of China Shipbuilding Industry Corporation,Harbin 150078,China)

机构地区：[1]中国民航大学安全科学与工程学院,天津300300 [2]中国船舶重工集团公司第七〇三研究所,黑龙江哈尔滨150078

出　　处：《推进技术》2024年第8期56-65,共10页Journal of Propulsion Technology

基　　金：中央高校基本科研业务费专项资金(3122019172)。

摘　　要：为了提升压气机的稳定工作裕度和近失速工况性能,提出了一种在压气机静叶端壁施加端壁自适应射流的被动控制方法。利用数值模拟方法开展了不同出口轴向位置和出口偏航角的端壁自适应射流结构对跨声速压气机级性能影响的研究。研究结果表明:端壁自适应射流结构能够有效提升压气机的稳定工作裕度,并能提高近失速工况的总压比和等熵效率,在目前综合表现最佳的端壁自适应射流方案中,稳定工作裕度改进量为27.99%,近失速工况的总压比和等熵效率分别提升了0.61%和1.07%,峰值点效率略微下降0.55%。端壁自适应射流结构能够在一定程度上抑制低能流体回流,缓解流道堵塞,降低总压损失,提升叶片负荷,射流出口位于角区分离起始位置附近的作用效果较好。To improve the stable operating margin and the performance of the compressor at near stall condi⁃tion,a passive control method with endwall self-adaptive injection(ESAI)applied on the stator vane endwall was proposed.The effects of different outlet axial positions and yaw angles of the endwall self-adaptive injection structure on the performance of transonic compressor stage were studied by numerical simulation method.The re⁃sults showed that endwall self-adaptive injection structure can improve the stable operating margin of the com⁃pressor effectively and the total pressure ratio and isentropic efficiency at near stall condition.At the ESAI of the best overall performance,the improvement in stable operating margin is 27.99%,the total pressure ratio and is⁃entropic efficiency at near stall condition increase by 0.61%and 1.07%respectively,and the peak efficiency is re⁃duced by 0.55%slightly.The endwall self-adaptive injection structure can inhibit the low energy fluid backflow to a certain extent,alleviate the channel blockage,reduce the total pressure loss,and increase the blade load.The effect of the outlet injection positions near the initial position of the corner separation is better.

关 键 词：跨声速压气机 端壁自适应射流 稳定裕度 角区分离 流动控制 近失速工况 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]