旋转畸变条件下新型机匣处理扩稳效果试验

doi:10.7527/S1000-6893.2014.0036

流体力学与飞行力学

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旋转畸变条件下新型机匣处理扩稳效果试验

董旭¹, 刘小华², 孙大坤¹, 孙晓峰¹

1. 北京航空航天大学能源与动力工程学院, 北京 100191;
2. 中国民航科学技术研究院发动机适航审定中心筹建办公室, 北京 100028

收稿日期:2013-11-08 修回日期:2014-04-01 出版日期:2014-09-25 发布日期:2014-04-09
通讯作者: 孙大坤，Tel.：010-82338262 E-mail：sundk@buaa.edu.cn E-mail:sundk@buaa.edu.cn
作者简介:董旭男，硕士研究生。主要研究方向：风扇/压气机稳定性研究。E-mail：buaadongxu@qq.com；孙大坤男，博士，讲师。主要研究方向：压气机流动稳定性。Tel：010-82338262 E-mail：sundk@buaa.edu.cn；孙晓峰男，博士，教授，博士生导师。主要研究方向：气动声学，非定常流动。Tel：010-82317408 E-mail：sunxf@buaa.edu.cn
基金资助:
国家自然科学基金（51106154，51236001）；国家“973”计划（2012CB720201）；中央高校基本科研业务费专项资金

Experimental Investigation of Stall Margin Enhancement Using Novel Casing Treatment Under the Rotating Inlet Distortion

DONG Xu¹, LIU Xiaohua², SUN Dakun¹, SUN Xiaofeng¹

1. School of Energy and Power Engineering, Beihang University, Beijing 100191, China;
2. Aeroengine Airworthiness Certification Center Preparatory Office, China Academy of Civil Aviation Science and Technology, Beijing 100028, China

Received:2013-11-08 Revised:2014-04-01 Online:2014-09-25 Published:2014-04-09
Supported by:
National Natural Science Foundation of China (51106154,51236001); National Basic Research Program of China(2012CB720201); Fundamental Research Funds for the Central Universities

摘要/Abstract

摘要：

开展了一种新型机匣处理扩大轴流风扇/压气机稳定裕度的试验研究。在低速风扇试验台上模拟旋转进气畸变，分析此种畸变进气条件对压气机工作性能造成的影响，并且考察一种新型机匣处理的扩稳效果。旋转进气畸变下，压升-流量特性曲线失速边界向右下偏移，压气机失速裕度明显降低。新型机匣处理在旋转进气畸变条件下对风扇/压气机有显著的扩稳效果，较小畸变转速（200，500 r/min）情况下，新型机匣处理能提高压气机稳定裕度10%~20%，同时并没有带来明显的效率损失；畸变转速为800 r/min情况下，机匣处理的扩稳效果相比并不明显，但可以提高压气机工作效率1%~2%。较大畸变转速情况下，畸变方向不同，机匣处理扩稳效果有所差别：正向畸变时机匣处理提高压气机失速裕度3%~10%，提高效率1%左右；而反向畸变时，失速裕度均提高10%以上，甚至达到20%，但压气机效率损失在1%左右。

关键词: 风扇/压气机, 旋转失速, 旋转畸变, 机匣处理, 稳定裕度

Abstract:

This paper carries out an experimental investigation of a new type of casing treatment to improve axial flow fan/compressor stall margin. The main work is, simulating the rotating inlet distortion on a low-speed fan, describing the pressure rise curve and efficiency curve under different conditions with the experimental data so as to analyze the compressor's performance under distortion inlet conditions on the fan and study the novel casing treatment's ability of stability enhancement. The experimental results show that when the pressure rise curve moves to the lower-right direction under inlet distortion, the stall margin is significantly decreased under the condition of different distortion degrees; the new type casing treatment has a significant effect on expanding the stability of compressor under the rotating inlet distortion; when the distortion speed is low (200, 500 r/min), the expansion of stabilizing effect is obvious, the stall margin enhancement is about 10% to 20%, and the efficiency loss caused by the casing treatment is small; when the distortion speed is 800 r/min, the enhancement of stability is not obvious, but the efficiency can be increased by 1%-2%; under the higher distortion speed condition, the different rotating directions of the distortion plates result in different effects on stability enhancement; the co-rotation distortion can enhance the stall margin by about 3%-10% with a efficiency increase about 1%; the counter rotation distortion can enhance the stall margin by more than 10%, even to 20% with a efficiency loss about 1%.

Key words: fan/compressor, rotating stall, rotating distortion, casing treatment, stability margin

中图分类号:

V231.3

董旭, 刘小华, 孙大坤, 孙晓峰. 旋转畸变条件下新型机匣处理扩稳效果试验[J]. 航空学报, 2014, 35(9): 2411-2425.

DONG Xu, LIU Xiaohua, SUN Dakun, SUN Xiaofeng. Experimental Investigation of Stall Margin Enhancement Using Novel Casing Treatment Under the Rotating Inlet Distortion[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014, 35(9): 2411-2425.

参考文献

[1] Spakovszky Z S, van Schalkwyk C M, Suder K L, et al. Rotating stall control in a high-speed stage with inlet distortion: Part I—Radial distortion[J]. Journal of Turbomachinery, 1999, 121(3): 510-516.

[2] Schaeffler A, Miatt D C.Experimental evaluation of heavy fan-high-pressure compressor interaction in a three-shaft engine: Part I—Experimental setup and result[J]. Journal of Engineering for Gas Turbine and Power, 1985, 107(4): 828-832.

[3] Schaeffler A, Miatt D C. Experimental evaluation of heavy fan-high-pressure compressor interaction in a three-shaft engine: Part Ⅱ-Analysis of distortion and fan loading[J].Journal of Engineering for Gas Turbine and Power, 1986, 108(1): 171-174.

[4] Li C P, Hu J. Effects of rotating inlet distortion on a 5-stage HP-compressor stability[J]. Journal of Aerospace Power, 2004, 19(4): 433-437. (in Chinese) 李传鹏, 胡骏.旋转进气畸变对轴流压气机气动稳定性影响实验研究[J].航空动力学报, 2004, 19(4): 433-437.

[5] Hathaway M D. Self-recirculating casing treatment concept for enhanced compressor performance, NASA/TM-2002-211569[R]. Washington, D.C.: NASA, 2002.

[6] Madden D S, West M A. Effects of inlet distortion on the stability of an advanced military swept fan stage with casing treatment, ASME Paper, GT2005-68693[R]. New York: ASME, 2005.

[7] Yang H, Nuernberger D, Nicke E. Numerical investigation of casing treatment mechanisms with a conservative mixed-cell approach, ASME Paper, GT2003-38483. New York: ASME, 2005.

[8] Wu Y H, Zhang H G, Chu W L, et al. Mechanism of stall margin improvement of two stages transonic fan with two-portion axial slot casing treatment[J]. Journal of Propulsion Technology, 2010, 31(2): 181-186. (in Chinese) 吴艳辉, 张皓光, 楚武利, 等. 双级跨声风扇双段轴向缝式机匣扩稳机理分析[J]. 推进技术, 2010, 31(2): 181-186.

[9] Bailey E E. Effect of grooved casing treatment on the flow range capability of a single-state axial-flow compressor, NASA TM X-2459[R]. Washington, D.C.: NASA, 1972.

[10] Moore R D, Kovich G, Blade R J. Effect of casing treatment on overall and blade-element performance of a compressor rotor, NASA TN D-6538[R]. Washington, D.C.: NASA, 1971.

[11] Osborn W M. Effect of several porous casing treatment on stall limit and overall performance of an axial-flow compressor rotor, NASA TN D-6537[R]. Washington, D.C.: NASA, 1971.

[12] Sun D K, Liu X H, Sun X F. An experimental investigation of stall margin improvement with unsteady casing treatment[J]. Journal of Engineering Thermophyscis, 2008, 29(12): 2022-2026. (in Chinese) 孙大坤, 刘小华, 孙晓峰. 新型机匣处理扩稳实验研究[J]. 工程热物理学报, 2008, 29(12): 2022-2026.

[13] Sun X F. On the relation between the inception of rotating stall and casing treatment, AIAA-1996-2579[R]. Reston: AIAA, 1996.

[14] Yu W W, Sun X F. Rotating stall stability theory of the transonic axial compressors/fans[J]. Journal of Aerospace Power, 2005, 20(6): 1018-1027. (in Chinese) 于巍巍, 孙晓峰. 跨音压气机/风扇旋转失速稳定性模型[J]. 航空动力学报, 2005, 20(6): 1018-1027.

[15] Yu W W, Wang X Y, Sun X F. Investigation on the theoretical model combined with the novel casting treatment with rotating stall[J]. Journal of Aerospace Power, 2005, 20(5): 873-881. (in Chinese) 于巍巍, 王晓宇, 孙晓峰. 包含机匣处理影响的压气机旋转失速稳定性模型[J]. 航空动力学报, 2005, 20(5): 873-881.

[16] Sun X F, Sun D K, Yu W W. A model to predict stall inception of transonic axial flow fan/compressors[J]. Chinese Journal of Aeronautics, 2011, 24(6): 687-700.

[17] Sun X F, Sun D K, Liu X H, et al. A theory of compressor stability enhancement using novel casing treatment, Part I: Methodology[J]. Journal of Propulsion and Power, 2014, 30. (in press)

[18] Sun X F, Liu X H, Hou R W, et al. A general theory of flow instability inception in turbomachinery[J]. AIAA Journal, 2013, 51(7): 1675-1687.

[19] Liu X H, Sun D K, Sun X F, et al. Flow stability model for fan/compressors with annular duct and novel casing treatment[J]. Chinese Journal of Aeronautics, 2012, 25(2): 143-154.

[20] Sun D K, Liu X H, Jin D H, et al. A theory of compressor stability enhancement using novel casing treatment, Part Ⅱ: experiment[J]. Journal of Propulsion and Power, 2014, 30. (in press)

[21] Sun D K, Sun X F. An experimental study on inhibition of unsteady casing treatment on stall inception[J]. Journal of Aerospace Power, 2008, 23(4): 671-679. (in Chinese) 孙大坤, 孙晓峰. 新型机匣处理对失速先兆波的抑制作用实验研究[J]. 航空动力学报, 2008, 23(4): 671-679.

[22] Xiong S, Sun D K, Suo Q L, et al. Experimental investigation of novel casing treatment on stall margin enhancement under inlet distortion[J]. Acta Aeronautica et Astronautica Sinica, 2013, 34(12): 2692-2700. (in Chinese) 熊珊, 孙大坤, 所秋玲, 等. 进气畸变条件下新型机匣处理扩稳效果实验研究[J]. 航空学报, 2013, 34(12): 2692-2700.

[23] Kang C S, McKenzie A B, Elder R L.Recessed casing treatment effects on fan performance and flow field, ASME Paper, GT95-197[R]. New York: ASME, 1995.

E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

旋转畸变条件下新型机匣处理扩稳效果试验

Experimental Investigation of Stall Margin Enhancement Using Novel Casing Treatment Under the Rotating Inlet Distortion

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