跨声速轴流压气机转子Rotor37周向槽机匣处理的数值研究  

Numerical Investigation of the Transonic Compressor Rotor37 with Circumferential Casing Treatment

作　　者：何文博 史磊 HE Wen-bo;SHI Lei(Tianjin Key Laboratory of Civil Aircraft Airworthiness and Maintenance,Civil Aviation University of China,Tianjin 300300,China)

机构地区：[1]中国民航大学天津市民用航空器适航与维修重点实验室,天津300300

出　　处：《科学技术与工程》2018年第28期164-169,共6页Science Technology and Engineering

基　　金：中央高校基金(3122017088)资助

摘　　要：以跨声速压气机转子Rotor37为研究对象,采用商业软件NUMECA数值研究了单槽处理机匣的轴向位置对于压气机性能及内部流场的影响。周向槽处理机匣的宽度为3 mm,深度为10倍叶尖间隙,即3.56 mm,起始位置分别位于轮缘机匣尖部型面的10%、20%、30%、40%、50%相对弦长处。数值计算结果表明:原始光壁压气机转子的失速原因为叶尖泄漏流动引发的低速区对于尖部叶片通道的堵塞,其稳定工作裕度为14.74%。采取的周向槽机匣处理能够改变转子叶尖流动堵塞状况。当机匣处理起始位置位于30%相对弦长时,压气机转子稳定工作裕度的提升量最大,相比原始压气机转子的稳定裕度提高了1.86%。Based on the transonic compressor rotor,Rotor37,the effect of the axial position of single slot treated casing on the compressor s performance and internal flow-field are numerically investigated by commercial software NUMECA.The casing treatment is 3 mm in width and 10 times tip clearance in depth,which is 3.56 mm.The start of these casing treatments are respectively located at the 10%,20%,30%,40%and 50%relative chord length of the tip blade section.Numerical investigations reveal that the flow blockage caused by tip leakage vortex is the main cause of stall in original compressor rotor and the calculated stall margin is 14.74%.The circumferential groove casing treatment used can change the flow condition of tip region.The increasing of compressor rotor s stability margin is biggest when the start of casing treatment is located on 30%of relative chord length,which increases by 1.86%than original compressor rotor.

关 键 词：跨声速压气机 周向槽机匣处理 叶尖泄漏流动 稳定工作裕度 

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]