反叶片角向缝机匣处理影响轴流压气机性能的机理

张皓光; 谭锋; 楚武利; 吴艳辉; 旷海洋

doi:10.13224/j.cnki.jasp.2016.10.011

反叶片角向缝机匣处理影响轴流压气机性能的机理

doi: 10.13224/j.cnki.jasp.2016.10.011

1. 西北工业大学动力与能源学院, 西安 71007;
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）；航空科学基金（2014ZB53014）；中央高校基本科研业务专项资金（3102014JCY01004）；陕西省自然科学基金（2015JM5202）

详细信息

作者简介:
张皓光(1981-),男,广西宾阳人,副教授、硕士生导师,博士,研究领域为叶轮机械气动热力学.E-mail:zhg@nwpu.edu.cn

中图分类号: V231.3
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出版历程
- 收稿日期: 2015-01-15
- 刊出日期: 2016-10-28

Mechanisms of affecting the performance of axial-flow compressor with athwart blade-angle slots casing treatment

1. School of Power and Energy, Northwestern Polytechnical University, Xi'an 71007;
2. Collaborative Innovation Center for Advanced Aero-Engine, Beijing 100191, China

摘要

摘要: 采用试验和非定常数值模拟方法研究了反叶片角向缝机匣处理对亚声速轴流压气机性能的影响.试验与数值计算结果均指出反叶片角向缝机匣处理后，转子在降低12%左右最大等熵效率的基础上获得30.1%左右的失速裕度改进量.详细的转子叶顶流场分析表明反叶片角向缝机匣处理改善了叶顶间隙泄漏流动，消除了实体壁机匣时叶顶通道低速泄漏流形成的堵塞，因此转子稳定性得以提高.同时转子叶片与处理缝的相对位置变化会影响处理缝的扩稳能力.处理缝中回流、处理缝形成的喷射流与叶顶通道主流的相互作用都造成较大的流动损失，进而使转子等熵效率降低.反叶片角向缝机匣处理前移约55%叶顶轴向弦长的数值研究结果表明，与反叶片角向缝机匣处理比较，反叶片角向缝机匣处理前移获得的失速裕度改进量降低约10.4%，但等熵效率的恶化程度降低近64%.
- 轴流压气机 /
- 反叶片角向缝机匣处理 /
- 失速裕度 /
- 间隙泄漏流 /
- 堵塞
Abstract: Influences of athwart blade-angle slots casing treatment on the performance of subsonic axial-flow compressor were investigated with the experimental and unsteady numerical simulation methods. The experimental and unsteady numerical calculation results showed that the rotor gained about 30.1% stall margin improvement at the cost of decreasing about 12% peak isentropic efficiency of smooth wall casing with athwart blade-angle slots casing treatment. The detailed analysis of rotor blade tip flow-field indicated that the tip clearance leakage flow was improved with athwart blade-angle slots casing treatment and the blockage created by low energy clearance leakage flow in blade tip was removed in blade tip with smooth wall casing,so the stability of rotor was improved. It was found that the ability to improve rotor stability of slot was affected by the relative position of blade and slot, and moreover, back flow in slot and the interaction of injecting flow brought by slot and blade tip mainstream resulted in serious flow loss, leading to decline of the rotor isentropic efficiency. The numerical calculation results also showed that the stall margin improvement and the level of decreasing isentropic efficiency reduced about 10.4% and 64% respectively by making the athwart blade-angle slots casing treatment move forward about the 55% axial chord of blade tip.
- axial-flow compressor /
- athwart blade-angle slots casing treatment /
- stall margin /
- clearance leakage flow /
- blockage

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参考文献(18)

[1]	Nezym V Y.Development of new casing treatment configuration[J].Japan Society of Mechanical Engineers International Journal Series B:Fluids and Thermal Engineering,2004,47(4):804-812.
[2]	Müller M W,Schiffer H P,Hah C.Effect of circumferential grooves on the aerodynamic performance of an axial single-stage transonic compressor[R].ASME Paper 2007-GT-27365,2007.
[3]	Müller M W,Biela C,Schiffer H P.Interaction of rotor and casing treatment flow in an axial single-stage transonic compressor with circumferential groove[R].ASME Paper 2008-GT-50135,2008.
[4]	Mileshin V,Brailko I.Application of casing circumferential grooves to counteract the influence of tip clearance[R].ASME Paper 2008-GT-51147,2008.
[5]	Houghton T,Day I.Enhancing the stability of subsonic compressors using casing grooves[R].ASME Paper 2009-GT-59210,2009.
[6]	楚武利,张皓光,吴艳辉,等.槽式处理机匣开槽数目对扩稳效果影响的实验与数值研究[J].推进技术,2008,29(5):598-603. CHU Wuli,ZHANG Haoguang,WU Yanhui,et al.Effects of grooved number of grooved casing treatment on stall margin[J].Journal of Propulsion Technology,2008,29(5):598-603.(in Chinese)
[7]	Osborn W M,Lewis G W,Heidelberg L J.Effect of several porous casing treatments on stall limit and on overall performance of an axial flow compressor rotor[R].NASA TN D-6537,1971.
[8]	Moore R D.Effect of ceasing treatment on overall and blade element performance of a compressor rotor[R].NASA TN D-6538,1971.
[9]	Prince D C,Wisler D C,Hilvers D E.Study of casing treatment stall margin improvement phenomena[R].NASA CR-134552,1974.
[10]	Urasek D C,Lewis G W,Moore R D,Jr.Effect of casing treatment on performance of an inlet stage for a transonic multistage compressor[R].NASA TM X-3347,1976
[11]	刘志伟.缝式机匣处理的若干观察和机理探索[M].西安:西北工业大学出版社,1985.
[12]	Wilke I,Kau H P.A numerical investigation of the flow mechanisms in a HPC front stage with axial slots[R].ASME Paper 2003-GT-38481,2003.
[13]	Danner F C,Kau H P.Experimental and numerical analysis of axial skewed slot casing treatments for a transonic compressor stage[R].ASME Paper 2009-GT-59647,2009.
[14]	Emmrich R,Niehuis R.Time resolved investigations of an axial compressor with casing treatment:Part 1 experiment[R].ASME Paper 2007-GT-27581,2007.
[15]	Hembera M,Kau H,Johann E.Simulation of casing treatments of a transonic compressor stage[J].International Journal of Rotating Machinery,2008,44(47):8605-8607.
[16]	Engel K,Zscherp C,Wolfrum N.CFD simulations of the TP400 IPC with enhanced casing treatment in off-design operating conditions[R].ASME Paper 2009-GT-60324,2009.
[17]	Madden D S,West M A.Effects of inlet distortion on the stability of an advanced military swept fan stage with casing treatment[R].ASME Paper 2005-GT-68693,2005.
[18]	张皓光,楚武利,吴艳辉,等.轴向倾斜缝机匣处理影响压气机性能的机理[J].推进技术,2010,31(5):555-561. ZHANG Haoguang,CHU Wuli,WU Yanhui,et al.Investigation of the flow mechanism of affecting compressor performance with axial skewed slots casing treatment[J].Journal of Propulsion Technology,2010,31(5):555-561.(in Chinese)