叶表和端壁抽吸对跨音速压气机稳定性影响对比分析  

Comparing Effects of Blade Surface with Those of End-Wall Boundary Layer Suction(BLS) on Stability of Transonic Compressor

作　　者：王掩刚[1] 牛楠[1,2] 任思源[1] 国睿[1] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072 [2]中国航天科技集团第四研究院41研究所,陕西西安710025

出　　处：《西北工业大学学报》2012年第2期251-255,共5页Journal of Northwestern Polytechnical University

基　　金：国家自然科学基金(50806061);西北工业大学翱翔之星计划资助

摘　　要：以NASA Rotor35为研究对象,应用数值模拟手段深入分析了叶表和端壁不同位置抽吸对该压气机稳定性的影响效应。研究结果表明:叶表抽吸虽然使得压气机压比和效率有所升高,但使叶顶前缘脱体激波和间隙泄漏流强度的增加,导致两者相互作用引起的低能堵塞团尺度过早增长,压气机提前进入失速;端壁抽吸改善了转子顶部前缘激波结构,削弱了叶顶低能阻塞团中的高熵流体,改善了叶顶区域的流动,实现了压气机的扩稳效果,但对压气机压比和效率性能改善不明显。Sections 1 and 2 of the full paper explain the comparison mentioned in the title.Their core consists of： with the numerical simulation method,we compare the effects of the blade surface suction with those of end-wall suction on the stability of the transonic compressor with NASA Rotor 35;Fig.1 in section 2 gives the schematic diagram of the BLS.Subsection 3.1 analyzes the effects of the blade surface suction on the stability of the compressor;subsection 3.2 analyzes the effects of the end-wall suction on the stability of the compressor;then they make comparison of the analysis results.The comparison results,given in Figs.2 through 7,and their analysis show preliminarily that：（1） the blade surface suction improves the pressure ratio and efficiency of the compressor but may strengthen the shock wave and tip clearance flow,causing the lower energy blockage flow to grow too early;the early growth of the lower energy blockage flow may lead to the instability of the compressor;（2） the end-wall suction changes the shock wave structure near the front edge of the rotor tip,reduces the lower energy blockage and improves the flow of the blade tip region,thus enhancing the stability of the compressor;however,the end-wall suction can not greatly improve the compressor＇s pressure ratio and efficiency.

关 键 词：跨音速压气机 附面层抽吸 抽吸位置 流动稳定性 

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]