轴流压气机转子叶尖泄漏堵塞特性的试验研究

doi:10.7527/S1000-6893.2013.0181

Abstract

Abstract:

Rotor passage flow fields are measured by stereoscopic particle image velocimetry (SPIV) in a large-scale low speed axial compressor test facility. The measurements are conducted in conditions of stages with different aerodynamic loading levels, different rotor tip gap sizes and different operating conditions. The variations of blockage inside the rotor passage are analyzed by a quantitative method. The results show that: in the test conditions the distribution of blockage by the tip leakage vortex has the characteristics of non-linearity and non-monotonicity, which means the peak blockage occurs inside the rotor passage; the adverse pressure gradient is the most important physical mechanism for the growing of the blockage; in an environment of adverse pressure gradient the higher the initial mass flow rate in the blockage region,the faster is the growth of blockage, and the higher the initial total pressure deficit, the easier it is to cause stall; intensive turbulent mixing occurs between the tip leakage flow and the mainstream, and the transport of kinetic energy between the mainstream and tip leakage flow by the viscosity and turbulent fluctuation in the turbulent mixing is the main mechanism for blockage decay.

Key words: tip leakage vortex, endwall blockage, adverse pressure gradient, turbulent mixing, stereoscopic particle image velocimetry, compressor

CLC Number:

V231.3

LIU Baojie, ZHANG Zhibo, YU Xianjun. Experimental Investigation on Characteristics of Tip Leakage Blockage in an Axial Compressor[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2013, 34(12): 2682-2691.

References

[1] Koch C C. Stalling pressure rise capability of axial flow compressor stages. Journal of Engineering for Power, 1981, 103(4): 645-656.

[2] Smith L H, Jr. The effect of tip clearance on the peak pressure rise of axial-flow fans and compressors. ASME Symposium on Stall, 1958: 149-152.

[3] Wisler D C. Loss reduction in axial-flow compressors through low-speed modal testing. Journal of Enieering for Gas Turbines and Power, 1985, 107(2): 354-363.

[4] Baghdadi S. Modeling tip clearance effects in multistage axial compressors. Journal of Turbomachinery 1996, 118 (4): 613-843.

[5] Rains D A. Tip clearance flows in axial flow compressors and pumps. Pasadena: Hydrodynamics and Mechanical Engineering Laboratories, California Institute of Technology, 1954.

[6] Chen G T, Greitzer E M, Tan C S, et al. Similarity analysis of compressor tip clearance flow structure. Journal of Turbomachinery, 1991, 113(2): 260-271.

[7] Kang S, Hirsch C. Numerical simulation of three-dimensional viscous flow in a linear compressor cascade with tip clearance. Journal of Turbomachinery, 1996, 118(3): 492-502.

[8] Kang S, Hirsch C. Experimental study on the three-dimensional flow within a compressor cascade with tip clearance: Part I-velocity and pressure fields. Journal of Turbomachinery, 1993, 115(3): 434-443.

[9] Kang S, Hirsch C. Experimental study on the three-dimensional flow within a compressor cascade with tip clearance: Part Ⅱ-the tip leakage vortex. Journal of Turbomachinery, 1993, 115(3): 444-450.

[10] Kang S, Hirsch C. Tip leakage flow in linear compressor cascade. Journal of Turbomachinery, 1994, 116(4): 657-664.

[11] Koch C C, Smith L H, Jr. Loss sources and magnitudes in axial-flow compressors. Journal of Engineering for Power, 1976, 98(3): 411-424.

[12] Vo H D. Role of tip clearance flow on axial compressor stability. Massachusetts: Department of Aeronautics and Astronautics, Massachusetts Institute of Technology, 2001.

[13] Hah C, Rabe D C. Role of tip clearance flows on flow instability in axial flow compressors. 15th International Symposium on Air Breathing Engines(ISABE), 2001.

[14] Khalid S A. The effects of tip clearance on axial compressor pressure rise. Massachusetts: Department of Mechanical Engineering, Massachusetts Institute of Technology, 1995.

[15] Khalid S A, Khalsa A S. Endwall blockage in axial compressors. Journal of Turbomachinery, 1999, 121(3): 499-509.

[16] Hoeger M, Lahmer M, Dupslaff M, et al. A correlation for tip leakage blockage in compressor blade passages. Journal of Turbomachinery, 2000, 122(3): 426-432.

[17] Liu B J, Yu X J, Yuan H J, et al. Application of SPIV in turbomachinery. Experiments in Fluids, 2006, 40(4): 621-642.

[18] Yu X J, Liu B J, Yuan H J, et al. Characteristics of the tip leakage vortex in a low-speed axial compressor. AIAA Journal, 2007, 45(4): 870-878.

[19] Zhang Z B, Yu X J, Liu B J. Precision analysis of the flow field measured in compressor rotor by using stereoscopic particle image velocimetry. Journal of Aerospace Power, 2010, 25(4): 868-876. (in Chinese) 张志博, 于贤君, 刘宝杰.压气机转子内部流场SPIV测量的精度分析.航空动力学报, 2010, 25(4): 868-876.

[20] Yu X J, Liu B J. Stereoscopic PIV measurement of unsteady flows in an axial compressor stage. Experimental Thermal & Fluid Science, 2007, 31(8): 1049-1060.

[21] Jiang H K, Li Y C, Zhang H, et al. A large-scale axial flow compressor facility and dynamic measurement techniques for rotor flow study. Journal of Aerospace Power, 1992, 7(1): 1-8. (in Chinese) 蒋浩康, 李雨春, 张洪, 等.研究转子内流动的大尺寸轴流压气机实验装置和动态测量技术.航空动力学报, 1992, 7(1): 1-8.

[22] Suder K L. Blockage development in a transonic, axial compressor rotor. Journal of Turbomachinery, 1998, 120(3): 465-476.

[23] Liu B J. The flow mechanism of wake vortices and its application. Beijing: School of Energy and Power Engineering, Beihang University, 1998. (in Chinese) 刘宝杰. 尾流旋涡的流动机制及其应用. 北京: 北京航空航天大学能源与动力工程学院, 1998.

Experimental Investigation on Characteristics of Tip Leakage Blockage in an Axial Compressor

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

References

Related Articles 15

Recommended Articles

Metrics

Comments

[1]	Bo WANG, Yanhui WU, Lingju HUANG, Zixu WANG. Corner separation control in compressor cascade based on L-shaped endwall groove [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(10): 129206-129206.
[2]	Yanzhao DONG, Yan ZHOU, Jixian ZOU, Xin WANG, Xiaodong LI, Hongshuai CUI. Grid-connection control method for air supply compressor unit of altitude test facility [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(9): 327221-327221.
[3]	Delong LIU, Haining GUO, Haibao YIN, Dejun MENG. Aerodynamic moment analysis of first stage variable stator vanes of single⁃stage transonic compressor in surge exit process [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(24): 128550-128550.
[4]	Jian ZHANG, Min ZHANG, Juan DU, Weiliang HUANG, Chaoqun NIE. Experimental investigation into adaptive Coanda jet control in highly loaded compressor [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(22): 128883-128883.
[5]	Rubing LIU, Zefan CHEN, Ruixin LIN, Qi LIN. Active control of flow-induced vibration of blades in a plane cascade by a plasma synthetic jet [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(20): 128430-128430.
[6]	Jiezhong DONG, Wuli CHU, Haoguang ZHANG, Bo LUO, Song YAN. Flow control mechanism of diffuser cascade with wavy leading⁃edge based on causal network analysis [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(19): 128336-128336.
[7]	Songbai WANG, Yong CHEN, Yadong WU, Shaoping ZHANG, Zhipeng CAO. Research progress on non-synchronous vibration of axial compressor rotor blade [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(17): 28044-028044.
[8]	Tantao LIU, Ruiyu LI, Limin GAO, Lei ZHAO. Experimental data driven cascade flow field prediction based on data assimilation [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(14): 628201-628201.
[9]	Shenren XU, Chen HE, Dakun SUN, Caijia YUAN, Dongming CAO, Jiazi ZHAO, Dingxi WANG. Efficient eigenvalue analysis method for rotating stall inception [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(14): 628248-628248.
[10]	Zhiyuan XU, Mingsui YANG, Meng WANG. Theoretical prediction and experimental study on acoustic resonance characteristics of certain type of compressor [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(14): 628236-628236.
[11]	Ronghui CHENG, Huawei YU, Songbai WANG, Lin DU, Dakun SUN, Xiaofeng SUN. Effect of aerodynamic loading coefficient on occurrence of non-synchronous vibration in a multi-stage compressor [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(14): 628722-628722.
[12]	Hongliang ZHAO, Wenqiang ZHANG, Jiahui QIU, Min ZHANG, Juan DU, Chaoqun NIE. Unsteady simulation of stall process in transonic compressor with total temperature distortion [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(14): 628319-628319.
[13]	Chuanjun CAO, Tianyi LIU, Wei ZHU, Jinchun WANG. Technology development in high pressure compressor of civil high bypass-ratio turbofan engine [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(12): 27824-027824.
[14]	Yinxin ZHU, Wenqiang PENG, Zhenbing LUO, Ying KANG, Zhijie ZHAO, Pan CHENG, Jiefu LIU. Influence of full⁃span dual synthetic jets on high⁃turning compressor cascade [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(12): 127734-127734.
[15]	AN Liping, WANG Hao, WANG Yangang, ZHU Zihuan. Wet compression performance and flow characteristics of transonic compressor [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(9): 126024-126024.