| Citation: | Chen Yanlong, Zhang Chaowei, Li Guangyong. Numerical investigation of interaction between shock wave and tip leakage flow in transonic centrifugal compressors[J]. Journal of Aerospace Power, 2026, 41（X）：20240788 doi: 10.13224/j.cnki.jasp.20240788
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For transonic centrifugal compressors, the interaction between shock wave and leakage flow has an important effect on stall. In this paper, a Krain impeller with pressure ratio of 6.1 was taken as the research object. The interaction between shock wave and tip leakage flow under the different mass flow and tip clearance was numerically investigated, including the shock wave structure, tip leakage vortex trajectory and the interface between the tip leakage flow and main flow. The results shows that the shock wave interacted with the leakage vortex form a low speed region, and the shock wave is pushed upstream, showing a concave shape, and the concave amplitude increased with the decrease of the mass flow rate. The tip leakage vortex trajectory and the interface between the tip leakage flow and main flow(ITLMF) undergo deflection after passing through the shock wave. As the mass flow rate decreased, the tip leakage vortex trajectory is gradually close to the pressure surface, and the deflection amplitude under shock wave decreases. The ITLMF gradually moves upstream and reaches the leading edge of the adjacent blade at near-stall point. With the increase of tip clearance, the tip leakage vortex trajectory is close to the pressure surface of adjacent blades, and the deflection amplitude under shock wave decreases, and the ITLMF gradually moves upstream of adjacent blades. The ITLMF is deflected by shock wave, which causes the interface to overflow at the leading edge of adjacent blades in advance, which has an important effect on stall prediction. Based on original model, taking into account the effects of normalized meridian velocity and normalized tip clearance on inlet relative Mach number, an improved ITLMF deflection Angle prediction model under shock wave is established and verified numerically. After using the improved model, the average error decreases from 46.59% to 5.83% under different flow rates and from 27.21% to 4.69% under different tip clearance. The results show that the improved model has higher prediction accuracy.
| [1] |
Sundström E, Semlitsch B, Mihăescu M. Generation mechanisms of rotating stall and surge in centrifugal compressors[J]. Flow, Turbulence and Combustion, 2018, 100(3): 705-719. doi: 10.1007/s10494-017-9877-z
|
| [2] |
Guan Di, Sun Dakun, Xu Ruize, et al. Experimental investigation on axial compressor stall phenomena using aeroacoustics measurements via empirical mode and proper orthogonal decomposition methods[J]. Aerospace Science and Technology, 2021, 112: 106655. doi: 10.1016/j.ast.2021.106655
|
| [3] |
Tamaki Y, Fukushima Y, Kuya Y, et al. Physics and modeling of trailing-edge stall phenomena for wall-modeled large-eddy simulation[J]. Physical Review Fluids, 2020, 5(7): 074602. doi: 10.1103/PhysRevFluids.5.074602
|
| [4] |
Wang Xu, Kou Jiaqing, Zhang Weiwei. A new dynamic stall prediction framework based on symbiosis of experimental and simulation data[J]. Physics of Fluids, 2021, 33(12): 127119. doi: 10.1063/5.0075083
|
| [5] |
Cameron J D, Bennington M A, Ross M H, et al. The influence of tip clearance momentum flux on stall inception in a high-speed axial compressor[J]. Journal of Turbomachinery, 2013, 135(5): 051005. doi: 10.1115/1.4007800
|
| [6] |
张超炜. 离心压气机性能预测模型及气动设计方法研究[D]. 北京: 中国科学院大学(中国科学院工程热物理研究所), 2020. Zhang Chaowei. Research on the performance prediction model and aerodynamic design method of centrifugal compressors[D]. Beijing: Institute of Engineering Thermophysics, Chinese Academy of Sciences, 2020. (in Chinese
Zhang Chaowei. Research on the performance prediction model and aerodynamic design method of centrifugal compressors[D]. Beijing: Institute of Engineering Thermophysics, Chinese Academy of Sciences, 2020. (in Chinese)
|
| [7] |
张超炜, 董学智, 刘锡阳, 等. 离心压气机叶顶泄漏涡轨迹数值模拟及失速预测[J]. 航空动力学报, 2019, 34(7): 1586-1597. Zhang Chaowei, Dong Xuezhi, Liu Xiyang, et al. Numerical simulation of tip leakage vortex trajectory and stall prediction for centrifugal impeller[J]. Journal of Aerospace Power, 2019, 34(7): 1586-1597. (in Chinese
Zhang Chaowei, Dong Xuezhi, Liu Xiyang, et al. Numerical simulation of tip leakage vortex trajectory and stall prediction for centrifugal impeller[J]. Journal of Aerospace Power, 2019, 34(7): 1586-1597. (in Chinese)
|
| [8] |
Ye S B, Zhao Q J, Xiang X R, et al. Modeling for tip clearance effects on stall-onset condition in transonic axial compressors: ASME Paper GT2016-57081[R]. Seoul: ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition, 2016.
|
| [9] |
Kang S, Hirsch C. Numerical simulation of three-dimensional viscous flow in a linear compressor cascade with tip clearance[J]. Journal of Turbomachinery, 1996, 118(3): 492-502. doi: 10.1115/1.2836694
|
| [10] |
洪树立, 陆惟煜, 邱磊. 离心压气机旋涡结构及近失速工况特征[J]. 宁波工程学院学报, 2022, 34(4): 22-28. Hong Shuli, Lu Weiyu, Qiu Lei. Vortex structure and characteristics of near-stall conditions of centrifugal compressor[J]. Journal of Ningbo University of Technology, 2022, 34(4): 22-28. (in Chinese
Hong Shuli, Lu Weiyu, Qiu Lei. Vortex structure and characteristics of near-stall conditions of centrifugal compressor[J]. Journal of Ningbo University of Technology, 2022, 34(4): 22-28. (in Chinese)
|
| [11] |
Zhao Huijing, Wang Zhiheng, Xi Guang. Unsteady flow structures in the tip region for a centrifugal compressor impeller before rotating stall[J]. Science China Technological Sciences, 2017, 60(6): 924-934. doi: 10.1007/s11431-016-9005-3
|
| [12] |
谢林旋, 葛宁. 离心压气机流场的计算研究[J]. 机械制造与自动化, 2020, 49(2): 74-76, 100. Xie Linxuan, Ge Ning. Numerical study of flow field in a centrifugal compressor[J]. Machine Building & Automation, 2020, 49(2): 74-76, 100. (in Chinese
Xie Linxuan, Ge Ning. Numerical study of flow field in a centrifugal compressor[J]. Machine Building & Automation, 2020, 49(2): 74-76, 100. (in Chinese)
|
| [13] |
王如根, 胡加国, 余超, 等. 跨声速压气机转子的二次流旋涡结构[J]. 推进技术, 2015, 36(4): 504-512. Wang Rugen, Hu Jiaguo, Yu Chao, et al. Research on secondary flow vortex structure in transonic compressor rotor[J]. Journal of Propulsion Technology, 2015, 36(4): 504-512. (in Chinese
Wang Rugen, Hu Jiaguo, Yu Chao, et al. Research on secondary flow vortex structure in transonic compressor rotor[J]. Journal of Propulsion Technology, 2015, 36(4): 504-512. (in Chinese)
|
| [14] |
王爽, 刘永葆, 贺星, 等. 叶顶间隙对跨音速离心压气机气动性能影响分析[J]. 汽轮机技术, 2020, 62(1): 19-22. Wang Shuang, Liu Yongbao, He Xing, et al. Analysis of the influence of tip clearance on aerodynamic performance of transonic centrifugal compressor[J]. Turbine Technology, 2020, 62(1): 19-22. (in Chinese
Wang Shuang, Liu Yongbao, He Xing, et al. Analysis of the influence of tip clearance on aerodynamic performance of transonic centrifugal compressor[J]. Turbine Technology, 2020, 62(1): 19-22. (in Chinese)
|
| [15] |
Zhao Huijing, Wang Zhiheng, Ye Shubo, et al. Numerical investigations on tip leakage flow characteristics and vortex trajectory prediction model in centrifugal compressor[J]. Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy, 2016, 230(8): 757-772. doi: 10.1177/0957650916673230
|
| [16] |
殷明霞, 冀国锋, 桂幸民. 叶尖间隙流动对某微小型离心压气机性能的影响[J]. 航空动力学报, 2010, 25(3): 565-570. Yin Mingxia, Ji Guofeng, Gui Xingmin. Influence of tip clearance flow on performance of one micro centrifugal compressor[J]. Journal of Aerospace Power, 2010, 25(3): 565-570. (in Chinese
Yin Mingxia, Ji Guofeng, Gui Xingmin. Influence of tip clearance flow on performance of one micro centrifugal compressor[J]. Journal of Aerospace Power, 2010, 25(3): 565-570. (in Chinese)
|
| [17] |
Xue Yan, Ge Ning. Numerical simulation of shock wave/tip leakage vortex interaction for a transonic axial fan rotor[J]. International Journal of Turbo & Jet-Engines, 2023, 40(4): 437-447. doi: 10.1515/tjj-2021-0012
|
| [18] |
温华兵, 宋震, 洪良星, 等. 叶顶间隙对高压比离心压气机性能的影响机理[J]. 江苏科技大学学报(自然科学版), 2018, 32(6): 793-798. Wen Huabing, Song Zhen, Hong Liangxing, et al. Mechanism of the effect of tip clearance on the performance of centrifugal compressors with high pressure ratio[J]. Journal of Jiangsu University of Science and Technology (Natural Science Edition), 2018, 32(6): 793-798. (in Chinese
Wen Huabing, Song Zhen, Hong Liangxing, et al. Mechanism of the effect of tip clearance on the performance of centrifugal compressors with high pressure ratio[J]. Journal of Jiangsu University of Science and Technology (Natural Science Edition), 2018, 32(6): 793-798. (in Chinese)
|
| [19] |
孙运政, 刘艳明, 王建华, 等. 叶顶微射流对小型高负荷离心压气机性能及流场结构的影响[J]. 热能动力工程, 2022, 37(11): 61-69. Sun Yunzheng, Liu Yanming, Wang Jianhua, et al. Influence of tip micro jet on performance and flow field structure of compact high load centrifugal compressor[J]. Journal of Engineering for Thermal Energy and Power, 2022, 37(11): 61-69. (in Chinese
Sun Yunzheng, Liu Yanming, Wang Jianhua, et al. Influence of tip micro jet on performance and flow field structure of compact high load centrifugal compressor[J]. Journal of Engineering for Thermal Energy and Power, 2022, 37(11): 61-69. (in Chinese)
|
| [20] |
Ye Xinlong, Zhou Zhenggui. Effects of the shock wave structure on the tip clearance leakage flow in transonic compressor rotors[J]. International Journal of Aerospace Engineering, 2023, 2023: 1477251. doi: 10.1155/2023/1477251
|
| [21] |
He Xiao, Zheng Xinqian. Mechanisms of sweep on the performance of transonic centrifugal compressor impellers[J]. Applied Sciences, 2017, 7(10): 1081. doi: 10.3390/app7101081
|
| [22] |
Wei Zuojun, Ren Guangming, Gan Xiaohua, et al. Influence of shock wave on loss and breakdown of tip-leakage vortex in turbine rotor with varying backpressure[J]. Applied Sciences, 2021, 11(11): 4991. doi: 10.3390/app11114991
|
| [23] |
Marconcini M, Rubechini F, Arnone A, et al. Numerical investigation of a transonic centrifugal compressor: ASME Paper GT2006-90098 [R]. Barcelona: ASME Turbo Expo 2006: Power for Land, Sea, and Air, 2008.
|
| [24] |
Kaneko M, Tsujita H. Numerical investigation of influence of tip leakage flow on secondary flow in transonic centrifugal compressor at design condition[J]. Journal of Thermal Science, 2015, 24(2): 117-122. doi: 10.1007/s11630-015-0763-5
|
| [25] |
Eisenlohr G, Krain H, Richter F A, et al. Investigations of the flow through a high pressure ratio centrifugal impeller: ASME Paper GT-2002-30394 [R]. Amsterdam: ASME Turbo Expo 2002: Power for Land, Sea, and Air, 2009.
|
| [26] |
Krain H, Hoffmann B, Pak H. Aerodynamics of a centrifugal compressor impeller with transonic inlet conditions: ASME Paper 95-GT-079 [R]. Houston: ASME 1995 International Gas Turbine and Aeroengine Congress and Exposition, 2015
|
| [27] |
ZHANG Wen, LUO Kailin, WEN Quan, et al. Axial assemblage deviation on performance of one transonic centrifugal compressor[R]. Shanghai: Congress of the International Council of the Aeronautical Sciences, 2020.
|
| [28] |
Kumar H, Mistry C S. Understanding of tip clearance flow structure in high speed mixed flow compressor[J]. Propulsion and Power Research, 2023, 12(3): 356-379. doi: 10.1016/j.jppr.2023.08.004
|
| [29] |
Wang H L, Xi G, Li J Y, et al. Effect of the tip clearance variation on the performance of a centrifugal compressor with considering impeller deformation[J]. Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy, 2011, 225(8): 1143-1155. doi: 10.1177/0957650911416914
|
| [30] |
Van Eck H, Van der Spuy S J, Gannon A J. The effect of impeller tip clearance on the performance of a MGT mixed flow compressor stage fitted with a crossover diffuser[J]. Aerotecnica Missili & Spazio, 2023, 102(3): 219-231. doi: 10.1007/s42496-023-00160-x
|
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