Numerical simulation of secondary flow control on high-speed compressor cascade with synthetic jets
-
摘要: 数值研究了合成射流控制高速扩压叶栅角区分离,并揭示其推迟分离、降低损失的作用机理。研究发现:合成射流可以显著改善叶栅内流场的时空结构,叶栅出口时均总压损失系数最大降低19.8%,静压系数也提高了近8.8%。合成射流通过周期性地吹/吸气有效控制角区分离,吹气阶段的高动量射流流体增大了吸力面附面层及角区流体的能量,吸气阶段则借助于附面层抽吸作用有效减少了高熵、低能流体的堆积,从而增强了角区流体抵抗流向逆压力梯度的能力、并推迟流动分离,且吸气阶段的流动控制效果明显更好。射流角度和射流动量是影响合成射流作用效果的重要参数,近切向的合成射流有利于向附面层注入动量,增大射流动量也有助于增强流动控制效果。析因设计研究表明,射流角度的影响效应更为显著,但与射流动量之间并不存在交互作用。Abstract: A simulation study on the use of synthetic jets for the corner separation control on a high-speed compressor cascade was conducted. The mechanisms of the active flow control on delaying flow separation and reducing flow losses were analyzed in detail. Results showed that the space-time structure of the flow field in the blade passage was improved significantly with a maximum loss reduction of 19.8%, while the static pressure rise increment of 8.8% was gained. By periodically adding or removing fluid to or from the boundary layer, synthetic jets could effectively control the corner separation. In the blowing phase, synthetic jets remarkably increased the energy level of the blade suction surface boundary layer and the corner region, while the accumulation of high entropy and low energy fluid towards the corner region was effectively suppressed in the suction phase. The above two contributed to enhancing the resistance to streamwise adverse pressure gradient and thus reducing flow separation. It was worthy to mention that the flow control effect during the suction phase was much more pronounced. Both jet angle and jet momentum were important parameters for the flow control effect. When the jet convected tangentially downstream, the flow control was very efficient in injecting high momentum fluid into the boundary layer, accounting mainly for the resistance to streamwise adverse pressure gradient. In addition, increasing the jet momentum could further improve the cascade time-averaged aerodynamic performance. Factorial design studies indicated that the effect of jet angle was much more pronounced than that of jet momentum, while there was no evidence to support the interaction between jet angle and jet momentum.
-
Key words:
- synthetic jets /
- flow control /
- high-speed compressor cascade /
- secondary flow /
- factorial design
-
[1] 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. [2] 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. [3] GBADEBO S A,CUMPSTY N A,HYNES T P.Three-dimensional separations in axial compressors[J].Journal of Turbomachinery,2005,127(2):331-339. [4] ZHANG Y,MAHALLATI A,BENNER M.Experimental and numerical investigation of corner stall in a highly-loaded compressor cascade[R].ASME Paper GT2014-27204,2014. [5] 张海灯,吴云,李应红,等.高速压气机叶栅旋涡结构及其流动损失研究[J].航空学报,2014,35(9):2438-2450.ZHANG Haideng,WU Yun,LI Yinghong,et al.Investigation of vortex structure and flow loss in a high-speed compressor cascade[J].Acta Aeronautica et Astronautica Sinica,2014,35(9):2438-2450.(in Chinese) [6] ZHANG Panfeng,WANG Jinjun,FENG Lihao.Review of zero-net-mass-flux jet and its application in separation flow control[J].Science in China:Series E Technological Sciences,2008,51(9):1315-1344. [7] SMITH B L,GLEZER A.The formation and evolution of synthetic jets[J].Physics of Fluids,1998,10(9):2281-2297. [8] SCHAEFFLER N W.The interaction of a synthetic jet and a turbulent boundary layer[R].AIAA-2003-643,2003. [9] AMITAY M,KIBENS V,PAREKH D,et al.The dynamics of flow reattachment over a thick airfoil controlled by synthetic jet actuators[R].AIAA 99-1001,1999. [10] BRAUNSCHEIDEL E P,CULLEY D E,ZAMAN K B M Q.Application of synthetic jets to reduce stator flow separation in a low speed axial compressor[J].AIAA-2008-602,2008. [11] ZHENG Xinqian,ZHOU Sheng,LU Yajun,et al.Flow control of annular compressor cascade by synthetic jets[J].Journal of Turbomachinery,2008,130(2):021018.1-021018.7. [12] GMELIN C,STEGER M,THIELE F,et al.Unsteady RANS simulations of a highly loaded low aspect ratio compressor stator cascade with active flow control[R].ASME Paper GT2010-22516,2010. [13] GMELIN C,STEGER M,ZANDER V,et al.Numerical investigations of active flow control using synthetic jets on a highly loaded compressor stator cascade[R].ASME FEDSM-ICNMM Paper 2010-30725,2010. [14] TORRES R B,JACOBS G B,CAVE M J.Experimental study on the use of synthetic jet actuators for lift control[R].ASME Paper GT2016-56403,2016. [15] ZANDER V,NITSCHE W.Control of secondary flow structures on a highly loaded compressor cascade[J].Proceedings of the Institution of Mechanical Engineers:Part A Journal of Power and Energy,2013,227(6):674-682. [16] DE GIORGI M G,DE LUCA C G,FICARELLA A,et al.Comparison between synthetic jets and continuous jets for active flow control:application on a NACA 0015 and a compressor stator cascade[J].Aerospace Science and Technology,2015,43:256-280. [17] BENINI E,BIOLLO R,PONZA R.Efficiency enhancement in transonic compressor rotor blades using synthetic jets:a numerical investigation[J].Applied Energy,2011,88(3):953-962. [18] BIOLLO R,STAFFIERI E,BENINI E.On the use of synthetic jets in transonic compressors[R].ASME Paper GT2012-69476,2012. [19] HERGT A,MEYER R,LIESNER K,et al.A new approach for compressor endwall contouring[R].ASME Paper GT2011-45858,2011. [20] QIN Yong,WANG Ruoyu,SONG Yanping,et al.Active flow control on a highly loaded compressor stator cascade with synthetic jets[R].ASME Paper GT2016-56830,2016. [21] 蒙哥马利.实验设计与分析[M].傅珏生,张健,王振羽,等译.北京:人民邮电出版社,2009.
点击查看大图
计量
- 文章访问数: 909
- HTML浏览量: 2
- PDF量: 1047
- 被引次数: 0