轴流转子梯形周向槽处理机匣的扩稳分析

邓敬亮; 楚武利; 张皓光

doi:10.13224/j.cnki.jasp.2015.07.025

轴流转子梯形周向槽处理机匣的扩稳分析

doi: 10.13224/j.cnki.jasp.2015.07.025

1. 西北工业大学动力与能源学院, 西安 710072;
2. 先进航空发动机协同创新中心, 北京 100191

基金项目:

国家自然科学基金(51006084)

国家自然科学基金重点项目(51236006)

详细信息

作者简介:
邓敬亮(1988-),男,湖北黄冈人,硕士生,主要从事叶轮机械气动热力学研究.

中图分类号: V231.3
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- 被引次数: 0
出版历程
- 收稿日期: 2014-03-03
- 刊出日期: 2015-07-28

Stabilizing analysis of trapezoidal circumferential grooves on an axial rotor

1. School of Power and Energy, Northwestern Polytechnical University, Xi'an 710072;
2. Collaborative Innovation Center for Advanced Aero-Engine, Beijing 100191, China

摘要

摘要: 为研究不同子午截面形状周向槽的扩稳效果,针对跨声速转子Rotor 67设计了两种梯形周向槽和一种常规等宽周向槽.通过数值模拟,设计转速下带周向槽转子的综合稳定裕度从原始的5.895%均提高到20%以上,其中正梯形槽的扩稳效果最好.周向槽改善了叶片的载荷分布,总体提高了叶片的加功量.对比各种周向槽内部流动状态表明:上游3个槽的贡献率占主要地位,正梯形槽相对扩稳贡献最大.
- 扩稳 /
- 处理机匣 /
- 梯形周向槽 /
- 轴流转子 /
- 数值模拟
Abstract: In order to investigate the stabilizing effect of circumferential grooves in different meridional shapes, two trapezoidal grooves structures and an equal-width grooves structure were designed for the transonic rotor— Rotor 67.The numerical simulations showed that the composite stability margin of circumferential grooves in design speed was increased from 5.9% to more than 20%, and the normal trapezoidal grooves had best effect in the mall flow margin. The blade load distribution was improved, and the average work of the blade was increased too. Comparison of these various grooves shows that the upstream three grooves dominate the biggest contribution, and the normal trapezoidal one's relative contribution to stabilizing effect is the best.
- stabilizing /
- casing treatment /
- trapezoidal circumferential grooves /
- axial rotor /
- numerical simulation

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参考文献(19)

[1]	卢新根,楚武利,朱俊强,等.轴流压气机机匣处理研究进展及评述[J].力学进展,2006,36(2):222-232. LU Xingen,CHU Wuli,ZHU Junqiang,et al.A review of studies on casing treatment of axial-folw compressor[J].Advances in Mechanics,2006,36(2):222-232.(in Chinese)
[2]	YU Qing,LI Qiushi,LI Ling.The experimental researches on improving operating stability of a single-stage transonic fan[R].ASME GT-2002-30640,2002.
[3]	Brignole G A,Danner F C T,Kau H P.Time resolved simulation and experimental validation of the flow in axial slot casing treatments for transonic axial compressors[R].ASME Paper 2008-GT-50593,2008.
[4]	Hembera M,Danner F C T,Brignole G A.Numerical design and optimization of casing treatments for transonic axial compressors[R].AIAA,2008-5063,2008.
[5]	陈美宁,朴英,王大磊.处理机匣对跨声压气机进气畸变的响应[J].航空动力学报,2010,25(11):2578-2583. CHEN Meining,PIAO Ying,WANG Dalei.Effect of inlet distortion on the stability of a transonic compressor with casing treatment[J].Journal of Aerospace Power,2010,25(11):2578-2583.(in Chinese)
[6]	张皓光,楚武利,吴艳辉.缝式处理机匣轴向位置对压气机特性影响的机理[J].航空动力学报,2011,26(1):92-98. ZHANG Haoguang,CHU Wuli,WU Yanhui.Mechanism of influences of axial positions of axial skewed slot casing treatment on a compressor performance[J].Journal of Aerospace Power,2011,26(1):92-98.(in Chinese)
[7]	张皓光,楚武利,吴艳辉,等.自适应流通机匣改善压气机性能的机理[J].推进技术,2010,31(3):301-308. ZHANG Haoguang,CHU Wuli,WU Yanhui,et al.Flow mechanisms of improving compressor performance through self recirculation casing treatment[J].Journal of Propulsion Technology,2010,31(3):301-308.(in Chinese)
[8]	张皓光,吴俊,楚武利,等.带自适应流通处理机匣的轴流压气机全通道数值研究[J].推进技术,2013,34(7):918-924. ZHANG Haoguang,WU Jun,CHU Wuli,et al.Full-annulus numerical investigation of axial flow compressor with self recirculation casing treatment[J].Journal of Propulsion Technology,2013,34(7):918-924.(in Chinese)
[9]	Yang H,Nuernberger D,Nicke E,et al.Numerical investigation of casing treatment mechanisms with a conservative mixed-cell approach[R].ASME Paper GT2003-38483,2003.
[10]	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 GT-2002-30642,2002.
[11]	楚武利,张皓光,吴艳辉,等.槽式机匣槽宽变化对扩稳效果影响的试验与数值研究[J].航空学报,2008,29(4):866-872. CHU Wuli,ZHANG Haoguang,WU Yanhui,et al.Impact of grooved width of grooved casing on stall margin improvement[J].Acta Aeronautlca et Astronautica Sinica,2008,29(4):866-872.(in Chinese)
[12]	卢家玲,楚武利,张皓光.轴流压气机周向槽扩稳机理的有效利用[J].西北工业大学学报,2007,25(5):620-624. LU Jialing,CHU Wuli,ZHANG Haoguang.Making circumferential grooves in axial-flow compressor more effective[J].Journal of Northwestern Polytechnical University,2007,25(5):620-624.(in Chinese)
[13]	祝剑虹,朴英,周建兴,等.跨声压气机周向槽处理机匣非设计工况研究[J].航空动力学报,2008,23(4):687-692. ZHU Jianhong,PIAO Ying,ZHOU Jianxing,et al.Investigation of off design performance of a transonic compressor with circumferential grooves[J].Journal of Aerospace Power,2008,23(4):687-692.(in Chinese)
[14]	祝剑虹,朴英,岂兴明,等.压气机周向槽处理机匣的周向位置研究[J].哈尔滨工程大学学报,2008,29(4):342-347. ZHU Jianhong,PIAO Ying,QI Xingming,et al.Deal location of a compressor's circumferential casing treatment[J].Journal of Harbin Engineering University,2008,29(4):342-347.(in Chinese)
[15]	Shabbir A,Adamczyk J J.Flow mechanism for stall margin improvement due to circumferential casing grooves on axial compressors[R].ASME Paper GT-2004-53903,2004.
[16]	Rabe D C,Hah C.Application of casing circumferential grooves for improved stall margin in a transonic axial compressor[R].ASME Paper GT-2002-30641,2002.
[17]	Müller M W,Biela C,Schiffer H P.Effect of circumferential on the aerodynamic performance of an axial single-stage transonic compressor[R].ASME Paper GT2007-27365,2007.
[18]	李相君,楚武利,张皓光.高负荷跨声速轴流压气机周向浅槽处理机匣扩稳机理[J].推进技术,2013,34(5):629-637. LI Xiangjun,CHU Wuli,ZHANG Haoguang.Stabilizing mechanism of shallow circumferential grooves on a high loaded transonic axial-flow compressor[J].Journal of Propulsion Technology,2013,34(5):629-637.(in Chinese)
[19]	Choi K J,Kim J H,Kim K Y.Design optimization of circumferential casing grooves for a transonic axial compressor to enhance stall margin[R].ASME Paper GT-2010-22396,2010.