ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Influence of clearance variation on aerodynamic performance of a compressor stator cascade
Received date: 2015-12-09
Revised date: 2016-03-07
Online published: 2016-03-14
Supported by
National Natural Science Foundation of China (50906080)
In this paper, a linear compressor cascade is used to experimentally investigate the influence of clearance variation on the flow structures and cascade aerodynamic performance at the highly negative angle of attack, design condition and corner stall condition. The association between the flow structure and cascade performance is also analyzed. The experimental results show that the influence of clearance variation on flow structures and cascade performance is different at different working conditions. At highly negative angle of attack, a pair of three-dimensional separation vortexes near the pressure-side leading edge is originated from the end wall in different clearance cascades. With the increase of clearance size, the cascade total pressure loss decreases, and the clearance side cascade turning ability is slightly increased. At design condition, a slight corner separation exists between blade suction surface and end wall. By bringing in a small clearance (0.2% span), corner separation is first aggravated. As the clearance size continues to increase, the corner separation can be eliminated, and leakage vortex is formed. With the increase of clearance size, the cascade total pressure loss first increases, then decreases and finally goes up again. The elimination of corner separation will improve clearance side cascade flow turning ability. At corner stall condition, the introduction and increase of clearance can impair and eliminate the corner stall structure, and thus the cascade loss decreases and reaches the minimum value with a 0.5% span clearance size. But the cascade loss almost remains the same as clearance continues to increase. Flow structures at both enwalls can influence each other as clearance varies, and the change trends of performance near two end walls are opposite. By comparing the overall cascade aerodynamic performance at all working conditions, the 0.5% span clearance cascade shows an optimal performance.
WANG Zinan , GENG Shaojuan , ZHANG Hongwu . Influence of clearance variation on aerodynamic performance of a compressor stator cascade[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016 , 37(11) : 3304 -3316 . DOI: 10.7527/S1000-6893.2016.0066
[1] 蒋洪德, 任静, 李雪英, 等. 重型燃气轮机现状与发展趋势[J]. 中国电机工程学报, 2014, 34(29):5096-5102. JIANG H D, REN J, LI X Y, et al. Status and development trend of the heavy duty gas turbine[J]. Proceedings of the CSEE, 2014, 34(29):5096-5102(in Chinese).
[2] 刘永泉, 刘太秋, 季路成. 航空发动机风扇/压气机技术发展的若干问题与思考[J]. 航空学报, 2015, 36(8):2563-2576. LIU Y Q, LIU T Q, JI L C. Some problem and thoughts in the development of aero-engine fan/compressor[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(8):2563-2576(in Chinese).
[3] FREEMAN C. Effect of tip clearance flow on compressor stability and engine performance:VKILS-1985-05[R]. Brussels:VKILS, 1985.
[4] SWOBODA M, IVEY P C, WENGER U, et al. An experimental examination of cantilevered and shrouded stators in a multistage axial compressor:ASME-98-GT-282[R]. New York:ASME, 1998.
[5] CAMPOBASSO M S, MATTHESIS A, WENGER U, et al. Complementary use of CFD and experimental measurements to assess the impact of shrouded and cantilevered stators in axial compressors:ASME-GT-208[R]. New York:ASME, 1999.
[6] 蔡睿贤, 王锡刚, 彭惠君, 等. 静叶内围带对轴流式压气机气动性能的影响及4500马力机车燃气轮机的热力性能[J]. 工程热物理学报, 1980, 1(1):3-9. CAI R X, WANG X G, PENG H J, et al. Influence of stator shroud on aerodynamic performance of axial-flow compressor and thermodynamic test results of a 4500 HP locomotive gas turbine[J]. Journal of Engineering Thermophysics, 1980, 1(1):3-9(in Chinese).
[7] LANGE M, MAILACH R, VOGELER K. An experimental investigation of shrouded and cantilevered stators at varying clearance sizes:ASME-GT2010-22106[R]. New York:ASME, 2010.
[8] DONG Y, GALLIMORE S J, HODSON H P. Three dimensional flows and loss reduction in axial compressors[J]. Journal of Turbomachinery, 1987, 109(3):354-361.
[9] YOON S, SELMEIER R, CARGILL P, et al. Effect of the stator hub configuration and stage design parameters on aerodynamic loss in axial compressors[J]. Journal of Turbomachinery, 2015, 137(9):091001-1-091001-10.
[10] KEY N. PIV Study of negative incidence stator unsteady aerodynamics:AIAA-2002-0014[R]. Reston:AIAA, 2002.
[11] HOWARD J. Sub-idle modelling of gas turbines:altitude relight and windmilling[D]. Bedfordshire:Cranfield University, 2007:23-30.
[12] ZACHOS P K, GRECH N, CHARNLEY B, et al. Experimental and numerical investigation of a compressor cascade at highly negative incidence[J]. Engineering Applications of Computational Fluid Mechanics, 2011, 5(1):26-36.
[13] HORLOCK J H, LOUIS J F, PERCIVAL P M E, et al. Wall stall in compressor cascades[J]. Journal of Basic Engineering, 1966, 88(3):637-648.
[14] LEI V M, SPAKOVSZKY Z S, GREITZER E M. A criterion for axial compressor hub-corner stall[J]. Journal of Turbomachinery, 2008, 130(3):031006-1-031006-10.
[15] MCDOUGAL N M. A comparison between the design point and near-stall performance of an axial compressor[J]. Journal of Turbomachinery, 1990, 112(1):109-115.
[16] 王子楠, 高磊, 耿少娟, 等. 不同端壁间隙下压气机平面叶栅角区流动的数值模拟和试验研究[J]. 工程热物理学报, 2015, 36(7):1428-1432. WANG Z N, GAO L, GENG S J, et al. Numerical and experimental investigation on corner flow structure in a planar compressor cascade with different clearances[J]. Journal of Engineering Thermophysics, 2015, 36(7):1428-1432(in Chinese).
/
| 〈 |
|
〉 |
CJA