驻涡式处理机匣对跨声速压气机扩稳的数值模拟

王卓奇; 陆利蓬; 袁巍; 宋西镇

doi:10.13224/j.cnki.jasp.2014.12.023

驻涡式处理机匣对跨声速压气机扩稳的数值模拟

doi: 10.13224/j.cnki.jasp.2014.12.023

1. 北京航空航天大学无人驾驶飞行器设计研究所, 北京 100191;
2. 北京航空航天大学能源与动力工程学院航空发动机气动热力国家级重点实验室, 北京 100191

基金项目:

国家自然科学基金(50906001)

详细信息

作者简介:
王卓奇(1983-), 男, 黑龙江哈尔滨人, 工程师, 博士, 主要从事航空发动机气动热力学研究.

中图分类号: V231
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- 被引次数: 0
出版历程
- 收稿日期: 2013-07-26
- 刊出日期: 2014-12-28

Numerical simulation on stall margin improvement of transonic compressor by a trapped vortex casing treatment

1. Research Institute of Unmanned Aerial Vehicle, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;
2. National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 提出了一种驻涡式处理机匣结构,通过叶片通道前后以及叶片压力面和吸力面共同作用的压差,驱动流体产生回流.将通道后部的附面层流体吸除,然后在叶片前缘注入,增大叶尖泄漏流内的动量,从而达到扩稳的效果.该设计将抽气槽与喷气槽的方向和主流流动方向设计成一致方向,以减少掺混损失.此外,该处理机匣在轴向上完全在转子叶片内部,不需要前伸量,因而可以方便地应用于多级压气机中的任何一级,而不会和静子叶片发生干涉.通过数值模拟对这一设计进行了验证,结果表明该处理机匣可以扩大跨声速压气机转子裕度17.39%,而对效率不会产生明显的影响.
- 扩稳 /
- 压气机 /
- 跨声速 /
- 叶尖泄漏流 /
- 旋转失速 /
- 处理机匣
Abstract: A type of trapped vortex casing treatment (CT) was designed, using pressure difference between suction side at front and pressure side at rear of passage to drive fluid flowing back. Boundary flow was sucked into slot at rear of passage, then injected into main flow at front of passage. During this process, momentum of the fluid in the leakage was increased, and then the stall margin of the blade was enhanced. The loss of mixing is decreased by adjusting the direction of suction and injection to the direction of main flow. Also the size of CT in axial direction is inside the blade dimention, which means this CT could be used in each stage of multistage compressors, without overlapping with stators. Numerical simulation was used to evaluate the effectiveness of this CT. Result shows that this CT could increase the stall margin 17.39% of a transonic compressor rotor without compromise on efficiency.
- stall margin improvement /
- compressor /
- transonic /
- tip leakage flow /
- rotating stall /
- casing treatment

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参考文献(19)

[1]	Wilke I,Kau H P,Brignole G.Numerically aided design of a high-efficient casing treatment for a transonic compressor[R].ASME Paper GT2005-68993,2005.
[2]	Wilke I,Kau H P.A numerical investigation of the flow mechanisms in a HPC front stage with axial slots[R].ASME Paper GT2003-38481,2003.
[3]	Wilke I,Kau H P.A numerical investigation of the influence of casing treatments on the tip leakage flow in a HPC front stage[R].ASME Paper GT2002-30642,2002.
[4]	Hoffman W H,Ballman J.Some aspects of tip vortex behavior in a transonic turbocompressor[J].ISABE 2003-1223,2003.
[5]	Hofman W,Ballmann J.Tip clearance vortex development and shock-vortex-interaction in a transonic axial compressor rotor[R].AIAA-2002-0083,2002.
[6]	Schlechtriem S,Loetzerich M.Breakdown of tip leakage vortices in compressors at flow conditions close to stall[R].ASME Paper 97-GT-41,1997.
[7]	Furukawa M,Inoue M,Saiki K,et al.The role of tip leakage vortex breakdown in compressor rotor aerodynamics[J].Journal of Turbomachinery,1999,121(3):469-480.
[8]	Hoeger M,Fritsch G,Bauer D.Numerical simulation of the shock-tip leakage vortex interaction in a HPC front stage[J].Journal of Turbomachinery,1999,121(3):456-468.
[9]	Smith G D J,Cumpsty N A.Flow phenomena in compressor casing treatment[J].Journal of Engineering for Gas Turbines and Power,1984,106(3):532-541.
[10]	Johnson M C,Greitzer E M.Effects of slotted hub and casing treatments on compressor endwall flow fields[J].Journal of Turbomachinery,1987,109(3):380-387.
[11]	Lee N K W,Greitzer E M.Effects of endwall suction and blowing on compressor stability enhancement[J].Journal of Turbomachinery,1990,112(1):133-144.
[12]	Prince D C,Wisler D D,Hilvers D E.Study of casing treatment stall margin improvement phenomena[R].ASME Paper 75-GT-60,1975.
[13]	Wisler D C,Hilvers D E.Stator hub treatment study[R].NASA Report CT-134729,1974.
[14]	Takata H,Tsukuda Y.Stall margin improvement by casing treatment:its mechanism and effectiveness[J].Journal of Engineering for Power,1977,99(1):121-133.
[15]	张燕东,陆亚钧.圆弧斜槽处理机匣的实验研究[J].航空动力学报,1998,13(3):255-259,344. ZHANG Yandong,LU Yajun.An experimental investigation on arc skewed slot casing treatment[J].Journal of Aerospace Power,1998,13(3):255-259,344.(in Chinese)
[16]	李玲,于清,陆亚钧.处理机匣在单级跨声速风扇上的实验研究[J].推进技术,2000,21(3):49-52. LI Ling,YU Qing,LU Yajun.Experimental research of casing treatment on single stage transonic fan[J].Journal of Propulsion Technology,2000,21(3):49-52.(in Chinese)
[17]	钱煜平,刘建勇,李秋实,等.实壁/圆弧斜槽周向不对称组合式处理机匣实验[J].航空动力学报,2009,24(7):1633-1638. QIAN Yuping,LIU Jianyong,LI Qiushi,et al.Experimental investigation of a solid/arc slot asymmetrical combined casing treatment[J].Journal of Aerospace Power,2009,24(7):1633-1638.(in Chinese)
[18]	楚武利,朱俊强,刘志伟.折线斜缝式机匣处理的实验研究及机理分析[J].航空动力学报,1999,14(3):270-274. CHU Wuli,ZHU Junqiang,LIU Zhiwei.Experimental research and analysis of sloped slotted casing treatment[J].Journal of Aerospace Power,1999,14(3):270-274.(in Chinese)
[19]	王卓奇,袁巍,宋西镇,等.跨声速压气机转子失速过程的实验[J].航空动力学报,2012,27(7):1456-1463. WANG Zhuoqi,YUAN Wei,SONG Xizhen,et al.Experimental investigation on the stall process of a transonic compressor rotor[J].Journal of Aerospace Power,2012,27(7):1456-1463.(in Chinese)