Experiment of turbine cascade under high Mach number and low Reynolds number conditions
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摘要:
以高速低压涡轮叶型为研究对象,在高马赫数低雷诺数条件下,对叶栅损失进行了平面叶栅试验研究和数值模拟研究。试验研究了等熵出口马赫数范围0.66~1.23,雷诺数范围1.1×105~9.0×105条件下平面叶栅损失特性,并对典型工况下的流场进行了数值模拟。重点分析了高亚声速条件下雷诺数对叶栅性能的影响及跨声速条件下不同雷诺数条件下激波对边界层流动的影响。结果表明:在高亚声速条件下,随着雷诺数的降低,吸力面从无分离逐步发展为闭式分离泡,最终开式分离;层流分离的起始位置受等熵出口马赫数影响不大,出口马赫数影响分离边界层的转捩和再附。跨声速条件下叶片吸力面将会发生激波层流边界层干涉,干涉后的边界层流动取决于雷诺数大小和激波的强度。数值模拟的结果与试验结果一致性良好,但在极低雷诺数条件下对压力系数的预测存在数值上的差异。
Abstract:A high speed low pressure turbine cascade was experimentally and numerically studied under high Mach number and low Reynolds number conditions. The loss characteristics of cascade under isentropic outlet Mach number range of 0.66—1.23 and Reynolds number range of 1.1×105—9.0×105 were studied experimentally, and the flow field under typical conditions was simulated. The influence of Reynolds number on cascade performance under high subsonic speed conditions and the influence of shock wave on boundary layer flow under different Reynolds number conditions were mainly analyzed. The results showed that when the Reynolds number decreased under high subsonic speed conditions, the suction side boundary layer developed from no separation to a closed separation bubble, and finally to an open separation. In the absence of shock wave, the starting position of laminar separation was not greatly affected by isentropic outlet Mach number, which mainly affected the transition and reattachment position of the separation boundary layer. Shock laminar boundary layer interactions occurred on the suction surface of the blade under transonic conditions. The development of the boundary layer after interaction relied on the Reynold number and the strength of shock. The numerical results were in good agreement with the experimental results, but there were differences in the prediction of the pressure coefficient at very low Reynolds numbers.
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Key words:
- high Mach number /
- low Reynolds number /
- low pressure turbine /
- planar cascade experiment /
- boundary layer /
- shock
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表 1 叶栅主要设计参数
Table 1. Main design parameters of the cascade
参数 数值 弦长 C/mm 81.24 轴向弦长 Cx/mm 68.68 叶片展向高度/mm 190 栅距 t/mm 65.2 栅距弦长比 t/C 0.80 叶片数 8 进口几何气流角 β1/(°) 39.9 出口几何气流角β2/(°) 65.2 几何安装角βs/(°) 32.3 -
[1] HODSON H P,HOWELL R J. The role of transition in high-lift low-pressure turbines for aeroengines[J]. Progress in Aerospace Sciences,2005,41(6): 419-454. doi: 10.1016/j.paerosci.2005.08.001 [2] WISLER D. The technical and economic relevance of understanding blade row interaction effects in turbomachinery[R]. Von Karman Institute for Fluid Dynamics Lecture Series,1998. [3] MALZACHER F J,GIER J,LIPPL F. Aerodesign and testing of an aeromechanically highly loaded LP turbine[J]. Journal of Turbomachinery,2006,128(4): 643-649. doi: 10.1115/1.2172646 [4] HATMAN A,WANG Ting. Separated-flow transition: Part Ⅰ experimental methodology and mode classification[R]. ASME Paper 1998-GT-461,1998. [5] HATMAN A,WANG Ting. Separated-flow transition: Part Ⅱ experimental results[R]. ASME Paper 1998-GT-462,1998. [6] HATMAN A,WANG Ting. Separated-flow transition: Part Ⅲ primary modes and vortex dynamics[R]. ASME Paper 1998-GT-463,1998. [7] HATMAN A,WANG Ting. A prediction model for separated-flow transition[R]. ASME Paper 1998-GT-237,1998. [8] VOLINO R J. Effect of unsteady wakes on boundary layer separation on a very high lift low pressure turbine airfoil[R]. ASME Paper GT2010-23573,2010. [9] LIANG Yun,ZOU Zhengping,LIU Houxing,et al. Experimental investigation on the effects of wake passing frequency on boundary layer transition in high-lift low-pressure turbines[J]. Experiments in Fluids,2015,56(4): 1-13. [10] SINKWITZ M,WINHART B,ENGELMANN D,et al. On the periodically unsteady interaction of wakes,secondary flow development and boundary layer flow in an annular LPT cascade: Part 1 experimental investigation[J]. Journal of Turbomachinery,2019,141(9): 091001. doi: 10.1115/1.4043577 [11] BOLINCHES-GISBERT M,CADRECHA D,CORRAL R,et al. Numerical and experimental investigation of the Reynolds number and reduced frequency effects on low-pressure turbine airfoils[J]. Journal of Turbomachinery,2021,143(2): 1-33. [12] FUNAZAKI K I,YAMADA K,CHIBA Y,et al. Numerical and experimental studies on separated boundary layers over ultra-high lift low-pressure turbine cascade airfoils with variable solidity: effects of free-stream turbulence[R]. ASME Paper GT2008-50718,2008. [13] MICHALEK J,STRAKA P. A comparison of experimental and numerical studies performed on a low-pressure turbine blade cascade at high-speed conditions,low Reynolds numbers and various turbulence intensities[J]. Journal of Thermal Science,2013,22(5): 413-423. doi: 10.1007/s11630-013-0643-9 [14] VERDOYA J,DELLACASAGRANDE M,BARSI D,et al. Identification of free-stream and boundary layer correlating events in free-stream turbulence-induced transition[J]. Physics of Fluids,2022,34(1): 014109. doi: 10.1063/5.0079658 [15] IYER A S,ABE Y,VERMEIRE B C,et al. High-order accurate direct numerical simulation of flow over a MTU-T161 low pressure turbine blade[J]. Computers & Fluids,2021,226: 104989. [16] WANG X,XIAO Z. Transition-based constrained large-eddy simulation method with application to an ultrahigh-lift low-pressure turbine cascade flow[J]. Journal of Fluid Mechanics,2022(941): A22. [17] MÜLLER-SCHINDEWOLFFS C,BAIER R D,SEUME J R,et al. Direct numerical simulation based analysis of RANS predictions of a low-pressure turbine cascade[J]. Journal of Turbomachinery,2017,139(8): 081006. doi: 10.1115/1.4035834 [18] MARTY J. Numerical investigations of separation-induced transition on high-lift low-pressure turbine using RANS and LES methods[J]. Proceedings of the Institution of Mechanical Engineers,Part A: Journal of Power and Energy,2014,228(8): 924-952. [19] MENTER F R,LANGTRY R B,LIKKI S R,et al. A correlation-based transition model using local variables: Part Ⅰ model formulation[J]. Journal of Turbomachinery,2006,128(3): 413-422. [20] LANGTRY R B,MENTER F R,LIKKI S R,et al. A correlation-based transition model using local variables: Part Ⅱ test cases and industrial applications[J]. Journal of Turbomachinery,2006,128(3): 423-434. doi: 10.1115/1.2184353 [21] MEMORY C L,CHEN J P,BONS J P. Implicit large eddy simulation of a stalled low-pressure turbine airfoil[J]. Journal of Turbomachinery,2016,138(7): 071008. doi: 10.1115/1.4032365 [22] MICHELASSI V,WISSINK J,RODI W. Analysis of DNS and LES of flow in a low pressure turbine cascade with incoming wakes and comparison with experiments[J]. Flow,Turbulence and Combustion,2002,69(3/4): 295-329. doi: 10.1023/A:1027334303200 [23] ROBERTS S K,YARAS M I. Large-eddy simulation of transition in a separation bubble[J]. Journal of Fluids Engineering,2006,128(2): 232-238. doi: 10.1115/1.2170123 [24] TANI I. Low-speed flows involving bubble separations[J]. Progress in Aerospace Sciences,1964,5: 70-103. doi: 10.1016/0376-0421(64)90004-1 [25] ROBERTS W B. Calculation of laminar separation bubbles and their effect on airfoil performance[J]. AIAA Journal,1980,18(1): 25-31. doi: 10.2514/3.50726 [26] BOOKEY P,WYCKHAM C,SMITS A. Experimental investigations of Mach 3 shock-wave turbulent boundary layer interactions[R]. AIAA 2005-4899,2005.