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.
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
.
DOI: 10.7527/S1000-6893.2018.22101
[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).
CJA