对转压气机变转速比失速类型试验

doi:10.7527/S1000-6893.2021.25596

Abstract

Abstract: Contra-rotating compressors have a unique aerodynamic configuration with a more complex and changeable stall form than conventional compressors. Through static pressure holes on the inlet and outlet wall and the high frequency dynamic pressure sensor array on the blade tip, the characteristic curves and the stall initiation-development-recovery process at different speed ratios are successfully obtained. The results show that the characteristic curves at different speed ratios have a similar variation law, with obvious hysteresis loops in the process of stall initiation-development-recovery. When the speed ratio is smaller than or equal to 1, the stall disturbance first appears in the rear rotor, and then occupies a certain range in the circumferential direction of the front and rear rotors, meanwhile rotating in the same direction as that of the rear rotor in the initiation phase of the stall. At the exit of the stall, the disturbance rotation speed increases while the size rapidly decreases. When the speed ratio equals to 1.333, the stall disturbance is fixed at a certain position in the circumferential direction, occupying a circumferential range of about 225° and penetrating both the front and rear rotors almost simultaneously. When the stall recovers, the disturbance decays rapidly in 1 s till complete disappearance.

Key words: contra-rotating compressors, stall disturbance, speed ratio, stall hysteresis, unsteady pressure measurementhttp

CLC Number:

V231.3

WANG Hao, XUE Fei, YUE Shaoyuan, WANG Yangang. Test on stall types of contra-rotating compressor with variable speed ratios[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(7): 125596-125596.

References

[1] DAY I J. Stall, surge, and 75 years of research[J]. Journal of Turbomachinery, 2016, 138(1):011001.
[2] CHESHIRE L J. The design and development of centrifugal compressors for aircraft gas turbines[J]. Proceedings of the Institution of Mechanical Engineers, 1945, 153(1):426-440.
[3] EMMONS H W, PEARSON C E, GRANT H P. Compressor surge and stall propagation[J]. ASME Transactions, 1955, 127(2):455-469.
[4] GREITZER E M. Surge and rotating stall in axial flow compressors-Part I:Theoretical compression system model[J]. Journal of Engineering for Power, 1976, 98(2):190-198.
[5] GREITZER E M. Surge and rotating stall in axial flow compressors-Part II:Experimental results and comparison with theory[J]. Journal of Engineering for Power, 1976, 98(2):199-211.
[6] STENNING A H. Rotating stall and surge[J]. Journal of Fluids Engineering, 1980, 102(1):14-20.
[7] MOORE F K, GREITZER E M. A theory of post-stall transients in axial compression systems:Part I-Development of equations[J]. Journal of Engineering for Gas Turbines and Power, 1986, 108(1):68-76.
[8] EPSTEIN A H, WILLIAMS J E F, GREITZER E M. Active suppression of aerodynamic instabilities in turbomachines[J]. Journal of Propulsion and Power, 1989, 5(2):204-211.
[9] MCDOUGALL N M, CUMPSTY N A, HYNES T P. Stall inception in axial compressors[J]. Journal of Turbomachinery, 1990, 112(1):116-123.
[10] DAY I J. Stall inception in axial flow compressors[J]. Journal of Turbomachinery, 1993, 115(1):1-9.
[11] CAMP T, DAY I J. A study of spike and modal stall phenomena in a low-speed axial compressor[J]. Journal of Turbomachinery, 1998, 120(3):393-401.
[12] HOYING D A, TAN C S, VO H D, et al. Role of blade passage flow structures in axial compressor rotating stall inception[J]. Journal of Turbomachinery, 1999, 121(4):735-742.
[13] INOUE M, KUROUMARU M, TANINO T, et al. Propagation of multiple short-length-scale stall cells in an axial compressor rotor[J]. Journal of Turbomachinery, 2000, 122(1):45-54.
[14] VO H D. Role of tip clearance flow on axial compressor stability[D]. Cambridge:Massachusetts Institute of Technology, 2001.
[15] VO H D, TAN C S, GREITZER E M. Criteria for spike initiated rotating stall[J]. Journal of Turbomachinery, 2008, 130(1):155-165.
[16] WEICHERT S. Tip clearance flows in axial compressors:stall inception and stability enhancement[D]. Cambridge:University of Cambridge, 2011.
[17] PULLAN G, YOUNG A M, DAY I J, et al. Origins and structure of spike-type rotating stall[J]. Journal of Turbomachinery, 2015, 137(5):051007.
[18] 高丽敏,苗芳,李晓军,等.对转压气机转速比对最先失速级的影响[J].应用力学学报, 2013, 30(6):845-848, 951. GAO L M, MIAO F, LI X J, et al. Effect of rotating speed ratio on the first rotating stall stage in contra-rotating compressor[J]. Chinese Journal of Applied Mechanics, 2013, 30(6):845-848, 951(in Chinese).
[19] GAO L M, LI R Y, MIAO F, et al. Unsteady investigation on tip flow field and rotating stall in counter-rotating axial compressor[J]. Journal of Engineering for Gas Turbines and Power, 2015, 137(7):072603.
[20] MAO X C, LIU B, ZHAO H. Numerical investigation for the impact of single groove on the stall margin improvement and the unsteadiness of tip leakage flow in a counter-rotating axial flow compressor[J]. Energies, 2017, 10(8):1153.
[21] ZHANG H W, DENG X Y, CHEN J Y, et al. Unsteady tip clearance flow in an isolated axial compressor rotor[J]. Journal of Thermal Science, 2005, 14(3):211-219.
[22] TONG Z T, LIN F, CHEN J Y, et al. The self-induced unsteadiness of tip leakage vortex and its effect on compressor stall inception:GT2007-27010[R]. New York:ASME, 2007.
[23] DU J, LIN F, ZHANG H W, et al. Numerical investigation on the self-induced unsteadiness in tip leakage flow for a transonic fan rotor[J]. Journal of Turbomachinery, 2010, 132(2):021017.
[24] CHEN J X, LAI H X. Numerical investigation on the self-induced unsteadiness in tip leakage flow of a micro-axial fan rotor[J]. Journal of Thermal Science, 2015, 24(4):334-343.
[25] CHEN W X, WANG Y G, WANG H. Investigation of the unsteady disturbance in tip region of a contra-rotating compressor near stall[J]. Journal of Thermal Science, 2019, 28(5):962-974.
[26] YUE S Y, WANG Y G, WEI L G, et al. Experimental investigation of the unsteady tip clearance flow in a low-speed axial contra-rotating compressor:GT2018-76055[R]. New York:ASME, 2018.
[27] YUE S Y, WANG Y G, WEI L G, et al. Experimental investigation on the development process of large-scale low-speed stall disturbance in contra-rotating compressor[J]. Journal of Thermal Science, 2020, 29(5):1282-1291.
[28] DAY I J, BREUER T, ESCURET J, et al. Stall inception and the prospects for active control in four high-speed compressors[J]. Journal of Turbomachinery, 1999, 121(1):18-27.

Test on stall types of contra-rotating compressor with variable speed ratios

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