叶片通道内涡流发生器变工况适应性
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摘要
横向二次流是制约叶轮机气动负荷进一步提升的主要因素。在叶片通道内施加涡流发生器有抑制通道横向二次流的潜力,但涡流发生器的最优施加方案很难确定。基于涡流发生器经验统计模型(BAYC模型)和响应面方法建立了一种端壁涡流发生器的高效设计方法。基于这一方法,实施于NACA 65直列叶栅,得到了三种涡流发生器优化方案,并在设计工况下和非设计工况下讨论了涡流发生器对端壁横向二次流的控制机理,发现具有更大的涡流发生器高度和更多的涡流发生器数量的方案在面对大攻角下的强横向二次流情况时能够有更强的余力对横向二次流加以控制,大大扩展了叶栅的攻角适用范围。
Secondary cross flow limits the aerodynamic loading level of turbomachinery.Vortex generators have the potential to attenuate secondary cross flow when they are implemented at the endwall of the blade passage.An efficient method for designing the optimal vortex generator layout was presented based on a mathematical model(BAYC model)and an optimization procedure with response surface methods.In order to illustrate the proposed method,three layouts of vortex generators were optimized in an NACA 65 straight cascades.The flow mechanism of the vortex generators to control the endwall secondary cross flow were analyzed under design and off-design conditions.The results demonstrate that a higher vortex generator and a larger number of vortex generators can be more efficient to weaken the secondary cross flow when the incidence angle of the cascade is large.The application of the vortex generators can improve the load adaptability of the compressor cascade.
Secondary cross flow limits the aerodynamic loading level of turbomachinery.Vortex generators have the potential to attenuate secondary cross flow when they are implemented at the endwall of the blade passage.An efficient method for designing the optimal vortex generator layout was presented based on a mathematical model(BAYC model)and an optimization procedure with response surface methods.In order to illustrate the proposed method,three layouts of vortex generators were optimized in an NACA 65 straight cascades.The flow mechanism of the vortex generators to control the endwall secondary cross flow were analyzed under design and off-design conditions.The results demonstrate that a higher vortex generator and a larger number of vortex generators can be more efficient to weaken the secondary cross flow when the incidence angle of the cascade is large.The application of the vortex generators can improve the load adaptability of the compressor cascade.
引文
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[19]STEPHENS J,CORKE T,MORRIS S.Control of a turbine tip leakage vortex using casing vortex generators[R].AIAA-2009-299,2009.
[20]CHEN X,HUANG G P.Experimental research of reducing turbine tip leakage flow using backward vortex generators[R].AIAA-2015-4127,2015.
[21]HERGT A,MEYER R,ENGEL K.Effects of vortex generator application on the performance of a compressor cascade[J].Journal of Turbomachinery,2013,135(2):021026.1-021026.10.
[22]袁忻,刘火星.压气机叶栅的涡发生器流动控制研究[J].航空科学技术,2010(4):30-32.YUAN Xi,LIU Huoxing.Flow control research in compressor cascade with vortex generator[J].Aeronautical Science and Technology,2010(4):30-32.(in Chinese)
[23]王鹏,邹正平,綦蕾.流向涡与涡轮叶栅二次流相互作用研究[J].实验流体力学,2010,24(3):42-49.WANG Peng,ZOU Zhengping,QI Lei.Study of interactions between streamwise vortex and secondary vortices in turbine cascade[J].Journal of Experiments in Fluid Mechanics,2010,24(3):42-49.(in Chinese)
[24]吴培根,王如根,郭飞飞,等.涡流发生器对高负荷扩压叶栅性能影响的机理分析[J].推进技术,2016,37(1):49-56.WU Peigen,WANG Rugen,GUO Feifei,et al.Mechanism analysis of effects of vortex generator on high-load compressor cascade[J].Journal of Propulsion Technology,2016,37(1):49-56.(in Chinese)
[2]BESELT C H,ECK M,PEITSCH D.Three-dimensional flow field in highly loaded compressor cascade[J].Journal of Turbomachinery,2014,136(10):101007.1-101007.10.
[3]STAATS M,NITSCHE W.Active control of the corner separation on a highly loaded compressor cascade with periodic nonsteady boundary conditions by means of fluidic actuators[J].Journal of Turbomachinery,2016,138(3):031004.1-031004.9.
[4]LEI V M,SPAKOVSZKY Z S.A criterion for axial compressor hub-corner stall[J].Journal of Turbomachinery,2008,130(3):031006.1-031006.10.
[5]伊卫林,唐方明,陈志民,等.改善压气机端区流动的新方法:前缘边条叶片技术[J].航空动力学报,2015,30(7):1691-1698.YI Weilin,TANG Fangming,CHEN Zhimin,et al.New approach to improve the endwall flow of compressor:leading edge strake blade technique[J].Journal of Aerospace Power,2015,30(7):1691-1698.(in Chinese)
[6]季路成,田勇,李伟伟,等.叶身/端壁融合技术研究[J].航空发动机,2012,38(6):5-10.JI Lucheng,TIAN Yong,LI Weiwei,et al.Investigation on blended blade and endwall technique[J].Aeroengine,2012,38(6):5-10.(in Chinese)
[7]LIN J C.Review of research on low-profile vortex generators to control boundary-layer separation[J].Progress in Aerospace Sciences,2002,38(4):389-420.
[8]SERAKAWI A R,AHMAD K A.Experimental study of half-delta wing vortex generator for flow separation control[J].Journal of Aircraft,2012,49(1):76-81.
[9]HIRT S M,ZAMAN K B,BENCIC T J.Experimental study of boundary layer flow control using an array of rampshaped vortex generators[R].AIAA-2012-0741,2012.
[10]周敏,李航航,唐侃平.叶型附面层分离流动控制技术研究进展[J].航空工程进展,2011,2(3):298-304.ZHOU Min,LI Hanghang,TANG Kaiping.Investigation on blended blade and endwall technique[J].Advances in Aeronautical Science and Engineering,2011,2(3):298-304.(in Chinese)
[11]BRAGG M B,GREGOREK G M.Experimental study of airfoil performance with vortex generators[J].Journal of Aircraft,1987,24(5):305-309.
[12]JOUBERT G,LE P A,HEINE B,et al.Vortical interactions behind deployable vortex generator for airfoil static stall control[J].AIAA Journal,2013,51(1):240-252.
[13]HYOUNG S,CHUNG C A,THOMAS E M,et al.Vortex flow control over a delta wing by co-rotating and counterrotating vortex generator[R].AIAA-2010-4952,2010.
[14]刘宝杰,杨晓宁,沈遐龄,等.几种前缘流动控制的实验研究[J].工程热物理学报,1998,19(4):444-448.LIU Baojie,YANG Xiaoning,SHEN Xialing,et al.Experimental investigation of separation flow control using vortex generating devices[J].Journal of Engineering Thermophysics,1998,19(4):444-448.(in Chinese)
[15]李新凯,康顺,戴丽萍,等.涡发生器结构对翼型绕流场的影响[J].工程热物理学报,2015,36(2):326-329.LI Xinkai,KANG Shun,DAI Liping,et al.Effects on airfoil flow field by structure of vortex generators[J].Journal of Engineering Thermophysics,2015,36(2):326-329.(in Chinese)
[16]张磊,杨科,黄哀武,等.基于数值模型的涡流发生器参数设计[J].工程热物理学报,2012,33(12):2084-2087.ZHANG Lei,YANG Ke,HUANG Aiwu,et al.Parameters design of vortex generators based on numerical models[J].Journal of Engineering Thermophysics,2012,33(12):2084-2087.(in Chinese)
[17]郝礼书,乔志德,宋文萍.涡流发生器布局方式对翼型失速流动控制效果影响的实验研究[J].西北工业大学学报,2011,29(4):524-528.HAO Lishu,QIAO Zhide,SONG Wenping.Experimentally studying effects of different layouts of vortex generator on controlling stall flow over airfoil[J].Journal of Northwestern Polytechnical University,2011,29(4):524-528.(in Chinese)
[18]ANDERSON B,TINAPPLE J,SURBER L.Optimal control of shock wave turbulent boundary layer interactions using micro-array actuation[R].AIAA-2006-3197,2006.
[19]STEPHENS J,CORKE T,MORRIS S.Control of a turbine tip leakage vortex using casing vortex generators[R].AIAA-2009-299,2009.
[20]CHEN X,HUANG G P.Experimental research of reducing turbine tip leakage flow using backward vortex generators[R].AIAA-2015-4127,2015.
[21]HERGT A,MEYER R,ENGEL K.Effects of vortex generator application on the performance of a compressor cascade[J].Journal of Turbomachinery,2013,135(2):021026.1-021026.10.
[22]袁忻,刘火星.压气机叶栅的涡发生器流动控制研究[J].航空科学技术,2010(4):30-32.YUAN Xi,LIU Huoxing.Flow control research in compressor cascade with vortex generator[J].Aeronautical Science and Technology,2010(4):30-32.(in Chinese)
[23]王鹏,邹正平,綦蕾.流向涡与涡轮叶栅二次流相互作用研究[J].实验流体力学,2010,24(3):42-49.WANG Peng,ZOU Zhengping,QI Lei.Study of interactions between streamwise vortex and secondary vortices in turbine cascade[J].Journal of Experiments in Fluid Mechanics,2010,24(3):42-49.(in Chinese)
[24]吴培根,王如根,郭飞飞,等.涡流发生器对高负荷扩压叶栅性能影响的机理分析[J].推进技术,2016,37(1):49-56.WU Peigen,WANG Rugen,GUO Feifei,et al.Mechanism analysis of effects of vortex generator on high-load compressor cascade[J].Journal of Propulsion Technology,2016,37(1):49-56.(in Chinese)
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