Radial vortex phenomenon and instability mechanism of transonic axial-flow compressor
-
摘要: 对NASA Rotor 37进行数值模拟并与实验结果对比,计算了堵塞点到失稳点的全部工况,详细探究了跨声速轴流压气机附面层分离规律与失稳机理.研究发现:激波后的吸力面附面层中存在一条径向涡,它增强了附面层分离,使部分靠近吸力面的主流向叶尖堆积.随着工况向失稳点推进,压气机转子叶尖出现两块堵塞区,由叶尖泄漏涡与激波作用引起的堵塞区位于压力面前端,由叶尖泄漏涡与径向附面层分离涡耦合作用引起的堵塞区位于吸力面50%弦长后,两块堵塞区的叠加作用最终引起压气机失稳.Abstract: Numerical investigation was made on NASA Rotor 37 and the result was compared with an experiment. Working conditions from blocking point to stall point were calculated to study the rules of boundary layer separation and the instability mechanism of transonic axial-flow compressor. The research discovers a radial vortex behind passage shock wave in suction side boundary layer, which facilitates boundary layer separation and converges part of airflow near suction side to blade tip. With working conditions go to stall point, blade tip passage is jammed by two pieces of blocking zone; one located in the front of blade pressure side is caused by the interference of clearance leakage vortex and passage shock, while the other located on suction side after 50% chord is caused by the interference of radial vortex and leakage flow. The two blocking zones' expansion arouses instability of the compressor.
-
[1] Schlechtriem W E,Lotzerich M.Breakdown of tip leakage vortices in compressors at flow conditions close to stall[R].ASME Paper 97-GT-41,1997. [2] Hoffman W H,Ballman J.Some aspects of tip vortex behavior in a transonic turbo compressor[R].International Society for Air Breathing Engines,ISABE Paper 2003-1223,2003. [3] Hoffman W H,Ballman J.Flow mechanisms in a transonic turbo compressor at conditions near stall[R].International Society for Air Breathing Engines,ISABE Paper 2005-1139,2005. [4] Hah C,Rabe D C.Role of tip clearance flows on flow instability in axial flow compressors[R].International Society for Air Breathing Engines,ISABE Paper 2001-1223,2001. [5] 张燕峰,楚武利,卢新根.跨音速轴流压气机近失速状态的间隙泄漏流流动特性[J].航空动力学报,2008,23(7):1293-1298. ZHANG Yanfeng,CHU Wuli,LU Xingen.Numerical simulation of the flow characteristic of tip leakage flow in a transonic axial-flow compressor at a near stall condition[J].Journal of Aerospace Power,2008,23(7):1293-1298.(in Chinese) [6] 卢新根.轴流压气机内部流动失稳及其被动控制策略研究[D].西安:西北工业大学,2007. LU Xingen.Flow instability and its passive control strategies in axial-compressor[D].Xi'an:Northwestern Polytechnical University,2007.(in Chinese) [7] 周敏.低雷诺数下跨音速压气机流动失稳及附面层控制策略研究[D].西安:空军工程大学,2009. ZHOU Min.Flow instability mechanism of transonic compressor at low Reynolds number and boundary layer control strategies[D].Xi'an:Air Force Engineering University,2009.(in Chinese) [8] 王沛,朱俊强,黄伟光,等.间隙流触发压气机内部流动失稳机制及周向槽扩稳机理[J].航空动力学报,2008,23(6):1067-1071. WANG Pei,ZHU Junqiang,HUANG Weiguang,et al.Role of tip leakage flow on flow instability and its control with circumferential groove casing treatment[J].Journal of Aerospace Power,2008,23(6):1067-1071.(in Chinese) [9] Merchant A A.Design and analysis of axial aspirated compressor stage[D].Cambridge,US:Massachusetts Institute of Technology,1999. [10] 夏钦斌,王如根,周敏.低雷诺数下跨音速转子流动失稳及附面层抽吸扩稳研究[J].航空动力学报,2009,24(7):1610-1615. XIA Qinbin,WANG Rugen,ZHOU Min.Research on flow instability of transonic compressor rotor and boundary suction effect at low Reynolds number[J].Journal of Aerospace Power,2009,24(7):1610-1615.(in Chinese) [11] 王如根,周敏,赵英武,等.跨声速压气机低雷诺数下流动失稳机制研究[J].航空动力学报,2009,24(2):414-419. WANG Rugen,ZHOU Min,ZHAO Yingwu,et al.Research on flow instability mechanism of transonic compressor at low Reynolds number[J].Journal of Aerospace Power,2009,24(2):414-419.(in Chinese) [12] 周敏,王如根,白云,等.低雷诺数下跨声速压气机转子失速工况时流动失稳触发过程研究[J].航空动力学报,2009,24(6):1379-1384. ZHOU Min,WANG Rugen,BAI Yun,et al.Research on flow instability triggering process at stall condition of transonic compressor rotor at low Reynolds number[J].Journal of Aerospace Power,2009,24(6):1379-1384.(in Chinese) [13] Reid L,Moore R D.Design and overall performance of four highly-loaded,high-speed inlet stages for an advanced,high-pressure-ratio core compressor[R].NASA TP-1337,1978. [14] Boretti A.Experimental and computational analysis of a transonic compressor rotor[R].Auckland:17th Australasian Fluid Mechanics Conference,2010. [15] Dawes W N.A numerical analysis of the three-dimensional viscous flow in a transonic compressor rotor and comparison with experiment[J].Journal of Turbomachinery,1987,109(3):83-90. [16] 于宏军,刘宝杰,刘火星.设计状态下压气机转子叶尖泄漏涡流动研究[J].航空学报,2004,25(1):1-8. YU Hongjun,LIU Baojie,LIU Huoxing.Investigation of tip leakage vortex in compressor on design condition[J].Acta Aeronautica et Astronautica Sinica,2004,25(1):1-8.(in Chinese)
点击查看大图
计量
- 文章访问数: 1294
- HTML浏览量: 3
- PDF量: 848
- 被引次数: 0