转子叶顶间隙泄漏流轨迹前移的动力学机制

刘东健; 李军; 李建伟; 罗志煌; 李凡玉

doi:10.13224/j.cnki.jasp.2014.07.022

转子叶顶间隙泄漏流轨迹前移的动力学机制

doi: 10.13224/j.cnki.jasp.2014.07.022

1. 空军工程大学航空航天工程学院等离子体动力学重点实验室, 西安 710038;
2. 总参谋部陆航部驻景德镇地区军代表室, 江西景德镇 333000

基金项目:

国家自然科学基金（51276197）

详细信息

作者简介:
刘东健（1986-），男，湖南邵阳人，博士生，主要从事飞机推进系统气动热力理论与工程研究。

中图分类号: V231.3
计量
- 文章访问数: 1553
- HTML浏览量: 1
- PDF量: 840
- 被引次数: 0
出版历程
- 收稿日期: 2013-04-26
- 刊出日期: 2014-07-28

Dynamics mechanism of tip leakage flow trajectory movement in rotor

1. Science and Technology on Plasma Dynamics Laboratory, Aeronautics and Astronautics Engineering College, Air Force Engineering University, Xi'an 710038, China;
2. Military Representative Office in Jingdezhen Region, Army Aviation Department, General Staff Headquters, Jingdezhen Jiangxi 333000, China

摘要

摘要: 为了揭示压气机转子节流时其叶顶间隙流动的演变趋势及其形成机理，选取某亚声速轴流压气机转子为研究对象，采用多通道非定常数值计算方法对其内部流场进行了全三维数值模拟.结果表明：随着压气机转子流量减少，主流轴向动量减小，而在叶顶间隙两侧压力梯度和二次泄漏流的共同作用下，叶顶间隙泄漏流的轴向动量却不断增大，导致叶顶间隙区域内泄漏流与主流的轴向动量比不断增大，从而推动叶顶间隙泄漏流与主流的交界面不断向上游移动，这意味着叶顶间隙泄漏流在叶顶通道内造成的流动阻塞区不断扩大，正是叶顶间隙泄漏流相对于主流的增强造成的叶顶流动阻塞区不断扩大最终导致了该压气机转子进入失速状态.
- 压气机 /
- 叶顶间隙泄漏流 /
- 流场 /
- 失速 /
- 非定常数值计算
Abstract: In order to uncover the evolutionary tendency of the tip clearance flow in a subsonic axial-flow compressor rotor as well as its associated flow mechanism, the unsteady three-dimensional multi-passage numerical simulations were carried out to investigate the flow field of the compressor rotor. The computational results show that as the compressor rotor's mass flow decreases, the axial momentum of the incoming flow reduces, and that of the tip leakage flow increases under the impact of the pressure gradient between the pressure side and suction side of the tip clearance block combined with the secondary leakage flow, thus increasing the axial momentum ratio of the tip leakage flow to the approach flow in the clearance region. The consequence is a movement of the interface between the incoming flow and the tip leakage backflow toward the leading edge of the rotor. As the strength of the axial reversed flow is increased from design status to near stall, the flow blockage zone in the rotor tip region becomes more severe and moves further upstream, which plays a role in triggering the compressor stall.
- compressor /
- tip leakage flow /
- flow field /
- stall /
- unsteady numerical caculation

HTML

参考文献(18)

[1]	Day I J.Stall inception in axial flow compressors[J].Journal of Turbomachinery,1993,115(1):1-9.
[2]	McDougal N M,Cumpsty N A,Hynes T P.Stall inception in axial compressors[J].Journal of Turbomachinery,1990,112(1):116-125.
[3]	Camp T R,Day I J.A study of spike and modal stall phenomena in a low-speed axial compressor[J].Journal of Turbomachinery,1998,120(3):393-401.
[4]	Baghdadi S.Modeling tip clearance effects in multi-stage axial compressors[J].Journal of Turbomachinery,1996,118(4):613-643.
[5]	ZHANG Hongwu,DENG Xiangyang,LIN Feng,et al.A study on the mechanism of tip leakage flow unsteadiness in an isolated compressor rotor[R].ASME Paper 2006-GT-91123,2006.
[6]	邓向阳.压气机叶顶间隙流的数值模拟研究 .北京:中国科学院,2006. DENG Xiangyang.Numerical investigation on tip clearance flow in compressor[D].Beijing:Chinese Academy of Sciences,2006.(in Chinese)
[7]	童志庭.轴流压气机中叶尖泄漏涡、失速先兆、叶尖微喷气非定常关联性的实验研究[D].北京:中国科学院,2006. TONG Zhiting.The interactive unsteady mechanism between tip leakage vortex,stall inception and micro tip injection in low-speed axial compressor[D].Beijing:Chinese Academy of Sciences,2006.(in Chinese)
[8]	Hoying D A,Tan C S,Vo H D,et al.Role of blade passage flow structures in axial compressor rotating stall inception[J].Journal of Turbomachinery,1999,121(4):735-742.
[9]	蒋康涛.低速轴流压气机旋转失速的数值模拟研究[D].北京:中国科学院,2004. JIANG Kangtao.Numerical investigation on rotating stall in a low-speed axial compressor[D].Beijing:Chinese Academy of Sciences,2004.(in Chinese)
[10]	Vo H D,Tan C S,Greitzer E M.Criteria for spike initiated rotating stall[J].Journal of Turbomachinery,2008,130(1):1-9.
[11]	Hah C,Bergner J,Schiffer H.Short length-scale rotating stall inception in a transonic axial compressor criteria and mechanisms[R].ASME Paper 2006-GT-90045,2006.
[12]	Hah C,Rabe D C,Wadia A R.Role of tip-leakage vortices and passage shock in stall inception in a swept transonic compressor rotor[R].ASME Paper 2004-GT-53867,2004.
[13]	TONG Zhiting,LIN Feng,CHEN Jingyi,et al.The self-induced unsteadiness of tip leakage vortex and its effect on compressor stall inception[R].ASME Paper 2007-GT-27010,2007.
[14]	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-flow compressor[D].Xi'an:Northwestern Polytechnical University,2007.(in Chinese)
[15]	张皓光.轴流压气机机匣处理的试验与数值研究[D].西安:西北工业大学,2008. ZHANG Haoguang.Experimental and numerical investigation of casing treatment on an axial flow compressor[D].Xi'an:Northwestern Polytechnical University,2008.(in Chinese)
[16]	张燕峰.高载荷压气机端壁流动及其控制策略研究[D].西安:西北工业大学,2010. ZHANG Yanfeng.Investigation of endwall flow behaviour and its control strategies in highly loaded compressor[D].Xi'an:Northwestern Polytechnical University,2010.(in Chinese)
[17]	张燕峰,楚武利,卢新根.跨声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 near stall condition[J].Journal of Aerospace Power,2008,23(7):1293-1298.(in Chinese)
[18]	Tan C S,Day I,Morris S,et al.Spike-type compressor stall inception,detection and control[J].Annual Review of Fluid Mechanics,2010,42:275-300.