缝式机匣处理及其轴向偏转角对跨声速轴流压气机稳定性的改善

doi:10.7527/S1000-6893.2018.22101

流体力学与飞行力学

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缝式机匣处理及其轴向偏转角对跨声速轴流压气机稳定性的改善

张皓光¹, 谭锋¹, 安康¹, 楚武利^1,2, 吴艳辉^1,2

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 100083

收稿日期:2018-02-28 修回日期:2018-05-22 出版日期:2018-08-15 发布日期:2018-05-21
通讯作者: 谭锋 E-mail:tanfeng930124@163.com
基金资助:
国家自然科学基金（51536006，51006084）；航空科学基金（2014ZB53014）

Effect of slot casing treatment and it's axial deflection angle on stability of transonic axial flow compressor

ZHANG Haoguang¹, TAN Feng¹, AN Kang¹, CHU Wuli^1,2, WU Yanhui^1,2

1. School of Power and Energy, Northwestern Polytechnical University, Xi'an 710072, China;
2. Collaborative Innovation Center for Advanced Aero-Engine, Beijing 100083, China

Received:2018-02-28 Revised:2018-05-22 Online:2018-08-15 Published:2018-05-21
Supported by:
National Natural Science Foundation of China (51536006, 51006084);Aeronautical Science Foundation of China (2014ZB53014)

摘要/Abstract

摘要： 以NASA Rotor 67为研究对象，采用非定常数值模拟方法，开展缝式机匣处理及其轴向偏转角对跨声速轴流压气机稳定性改善的研究，并且揭示缝轴向偏转角的变化对其扩稳能力和扩稳机理的影响。结果表明，不同轴向偏转角的缝均提高了压气机的稳定裕度，但是均降低了压气机的峰值效率。反叶片角向缝获得的稳定裕度改进量和峰值效率改进量分别约为24.22%和-1.19%。随着缝的轴向偏转角由负向正变化，缝的扩稳能力逐渐减弱，缝带来的峰值效率损失亦逐渐减少。流场分析表明，实壁机匣时，压气机的失速类型为叶顶堵塞形式的突尖型失速。通过感受叶片通道和叶顶吸/压力面的压差，反叶片角向缝对泄漏流进行抽吸和射流作用，一方面消除了泄漏流及其泄漏涡扩散带来的负面影响，另一方面激励了泄漏流，提高了泄漏流的速度，降低了泄漏流的总压损失，增强了叶片的做功能力。随着缝的轴向偏转角由负向正变化，由于缝能够利用的叶顶载荷从两个减成一个，缝的抽吸和射流作用均减弱，泄漏流的速度降低，泄漏流的总压损失提高，叶片的做功能力减弱，这就导致缝的扩稳能力减弱。

关键词: 缝式机匣处理, 轴向偏转角, 跨声速, 轴流压气机, 稳定性

Abstract: The unsteady numerical simulation method is utilized to carry out the investigation on slot casting treatment and the effect of its axial deflection angle on the stability of the transonic axial flow compressor-NASA Rotor 67. The effect of the variation of axial deflection angle on the ability and mechanism of expanding stability for slots is revealed. The results show that all the slots with different axial deflection angles can improve the compressor stability margin, but reduce the compressor peak efficiency. The improvements of stability margin and peak efficiency generated by the reversed blade angle slot are about 24.22% and -1.19%, respectively. As the axial deflection angle of the slot is changed from negative to positive, the ability of expanding stability of the slot is weakened gradually, and the loss of peak efficiency caused by the slot is reduced gradually. An analysis of the flow field shows that the stall of the compressor is spike stall in the form of the blade tip blockage when the casing is solid wall. By feeling the pressure difference between the upstream and downstream of the blade passage and the pressure difference between the suction and pressure surface of the blade tip, the slot with the reversed blade angle can suck and inject the leakage flow. Therefore, the negative effects of the leakage flow diffusing and the corresponding vortex are eliminated; the leakage flow is also excited, and it leads to the improvement of the leakage flow velocity, the decrease of the total pressure loss of the leakage flow and the enhancement of the work ability for the blade. When the axial deflection angle of the slot is changed from negative to positive, the blade tip load, which can be use by the slot, is reduced from two to one. So, the suction and injection ability of the slots are weakened, and the velocity of leakage flow is lowered. Consequently, the total pressure loss of leakage flow is improved, and the work ability of blade is weakened. As a result, the expanding stability of the slot is weakened.

Key words: slot casing treatment, axial deflection angle, transonic, axial flow compressor, stability

中图分类号:

V231.1

张皓光, 谭锋, 安康, 楚武利, 吴艳辉. 缝式机匣处理及其轴向偏转角对跨声速轴流压气机稳定性的改善[J]. 航空学报, 2018, 39(8): 122101-122101.

ZHANG Haoguang, TAN Feng, AN Kang, CHU Wuli, WU Yanhui. Effect of slot casing treatment and it's axial deflection angle on stability of transonic axial flow compressor[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2018, 39(8): 122101-122101.

参考文献

[1] KOCH C C, SMITH L H. Experimental evaluation of outer case blowing or bleeding of a single stage axial flow compressor, Part VI-Final report:CR-54592[R]. Washington, D. C.:NASA, 1970.
[2] BAILEY E E, VOIT C H. Some observations of effects of porous casings on operating range of a single axial-flow compressor rotor:TM X-2120[R]. Washington, D. C.:NASA, 1970.
[3] OSCARSON R P, WRIGHT D L. Experimental evaluation of a honeycomb rotor shroud configuration to improve the stall margin of a 0.5 hub-tip ratio single-stage compressor:Volume 1-Data and performance report:CR-72808[R]. Washington, D. C.:NASA, 1995.
[4] OSCARSON R P, WRIGHT D L. Experimental evaluation of a honeycomb rotor shroud configuration to improve the stall margin of a 0.5 hub-tip ratio single-stage compressor:Volume 2-Data supplement:CR-72809[R]. Washington, D. C.:NASA, 1995.
[5] OSBORN W M, LEWIS G L, HEIDELBERG L J. Effect of several porous casing treatments on stall limit and on overall performance of an axial-flow compressor rotor:TN D-6537[R]. Washington, D. C.:NASA, 1971.
[6] MOORE R D, KOVICB G, BLADE R J. Effect of casing treatment on overall and blade-element performance of a compressor rotor:TN D-6538[R]. Washington, D. C.:NASA, 1971.
[7] HATHAWAY M D. Self-recirculating casing treatment concept for enhanced compressor performance:GT-2002-30368[R]. New York:ASME, 2002.
[8] YANG H, NUERNBERGER D, NICKE E, et al. Numerical investigation of casing treatment mechanisms with a conservative mixed-cell approach:GT2003-38483[R]. New York:ASME, 2003.
[9] STRAZISAR A J, BRIGHT M M, THORP S, et al. Compressor stall control through endwall recirculation:GT2004-54295[R]. New York:ASME, 2004.
[10] IYENGAR V, SANKAR L, NIAZA S. Assessment of the self-recirculating casing treatment concept applied to axial compressors:AIAA-2005-0632[R]. Reston, VA:AIAA, 2005.
[11] TAKATA H, TSUKUDA Y. A study on configurations of casing treatment for axial-flow compressor[J]. Japan Society of Mechanical Engineers, 1984, 27(230):1675-1681.
[12] 刘志伟, 张长生, 时静珣, 等. 缝式机匣处理的若干观测和机理探讨:DZH8521[R]. 西安:西北工业大学, 1985. LIU Z W, ZHANG C S, SHI J X, et al. Several observations and mechanisms explored of slots casing treatments:DZH8521[R]. Xi'an:Northwestern Polytechnical University, 1985(in Chinese).
[13] 刘志伟, 张长生, 时静珣, 等. 倾斜缝机匣处理轴向位置对压气机性能影响的研究[J]. 工程热物理学报, 1987, 8(1):52-54. LIU Z W, ZHANG C S, SHI J X, et al. A study on effects of axial positions of skewed slots casing treatment on compressor performance[J]. Journal of Engineering Thermophysics, 1987, 8(1):52-54(in Chinese).
[14] WILKE I, KAU H P. A numerical investigation of the influence of casing treatments on the tip leakage flow in a HPC front stage:GT2002-30642[R]. New York:ASME, 2002.
[15] WILKE I, KAU H P. A numerical investigation of the flow mechanisms in a HPC front stage with axial slots[J]. Journal of Turbomachinery, 2004, 126(3):339-349.
[16] 周小勇. 跨音速压气机机匣处理扩稳机理和设计方法研究[D]. 北京:中国科学院工程热物理研究所, 2015:113-130. ZHOU X Y. Investigation of the mechanism for stall margin improvement and design methods of casing treatments in transonic compressors[D]. Beijing:Institute of Engineering Thermophysics, Chinese Academy of Sciences, 2015:113-130(in Chinese).
[17] 马宁. 高速压气机低速模化相似准则及轴向缝机匣处理流动机理研究[D]. 北京:中国科学院工程热物理研究所,2016:86-103. MA N. Research on the low-speed modeling similarity criteria for high-speed compressors and the flow mechanisms of axial-slot casing treatment[D]. Beijing:Institute of Engineering Thermophysics, Chinese Academy of Sciences, 2016:86-103(in Chinese).
[18] STRAZISAR A J, WOOD J R, HATHAWAY M D, et al. Laser anemometer measurements in a transonic axial-flow fan rotor:TP-2879[R]. Washington, D. C.:NASA, 1989.
[19] FIDALGO V J, HALL C A, COLIN Y. A study of fan-distortion interaction within the NASA Rotor67 transonic stage:GT2010-22914[R]. New York:ASME, 2010.
[20] 杜娟. 跨音压气机/风扇转子叶顶泄漏流动的非定常机制研究[D]. 北京:中国科学院工程热物理研究所, 2010:64-95. DU J. Investigation on the unsteady mechanism of tip leakage flow in transonic compressor/fan rotors[D]. Beijing:Institute of Engineering Thermophysics, Chinese Academy of Sciences, 2010:64-95(in Chinese).
[21] 南希. 动叶端区轴向动量控制体分析方法及其在周向槽机匣处理中的应用[D]. 北京:中国科学院工程热物理研究所, 2011:33-38. NAN X. The compressor rotor tip control volume method and it's application on circumferential groove casing treatment[D]. Beijing:Institute of Engineering Thermophysics, Chinese Academy of Sciences, 2011:33-38(in Chinese).
[22] 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 H G, CHU W L, WU Y H, et al. Investigation of the flow mechanisms of affecting compressor performance with axial skewed slots casing treatment[J]. Journal of Propulsion Technology, 2010, 31(5):555-561(in Chinese).
[23] 张皓光, 楚武利, 吴艳辉. 缝式机匣处理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 H G, CHU W L, WU Y H. 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).
[24] VO H D, TAN C S, GRETIZER E M. Criteria for spike initiated rotating stall[J]. Journal of Turbomachinery, 2008, 130(1):011023.
[25] WILKE I, KAU H P, BRIGNOLE G. Numerically aided design of a high-efficient casing treatments for a transonic compressor:GT2005-68993[R]. New York:ASME, 2005.
[26] 王维. 轴流压气机处理机匣背腔机理及叶尖处理研究[D]. 西安:西北工业大学, 2013:32-39. WANG W. Investigation on mechanism of plenum on casing treatment and tip treatment in axial compressor[D]. Xi'an:Northwestern Polytechnical University, 2013:32-39(in Chinese).

E-mail：hkxb@buaa.edu.cn

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缝式机匣处理及其轴向偏转角对跨声速轴流压气机稳定性的改善

Effect of slot casing treatment and it's axial deflection angle on stability of transonic axial flow compressor

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