变攻角下被动射流旋涡对高速扩压叶栅性能的影响

王若玉; 宋彦萍; 陈浮; 秦勇

doi:10.13224/j.cnki.jasp.2018.03.027

变攻角下被动射流旋涡对高速扩压叶栅性能的影响

doi: 10.13224/j.cnki.jasp.2018.03.027

哈尔滨工业大学能源科学与工程学院,哈尔滨 150001

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出版历程
- 收稿日期: 2016-08-29
- 刊出日期: 2018-03-28

Effect of passive jet vortex on high-speed compressor cascade under different angles of attack

摘要

摘要: 对被动射流旋涡(PJV)控制高速扩压叶栅内的流动分离控制展开数值研究,并探究其在变工况条件下的适应特性。结果表明,PJV在设计攻角下可使叶栅总压损失系数降低5.2%,变攻角条件下的损失降低幅度最高可达7.8%,表明其具有较高的控制效率和良好的变工况适应特性。随着攻角的增大,吸力面分离位置提前,射流出口与分离区间的距离减小,PJV能够更为有效地促进附面层内低能流体与主流间的动量交换,使得壁面涡结构得到重新组织,并进一步影响通道涡、集中脱落涡等涡系结构的发展,从而推迟流动分离、减小损失。在综合考虑变攻角流场特性的前提下,应使PJV的作用位置位于分离区上游不远处,所研究的最佳射流位置位于叶片前缘上游40%轴向弦长处。
- 攻角 /
- 被动射流旋涡（PJV） /
- 高速扩压叶栅 /
- 气动性能 /
- 流动控制
Abstract: The application of passive jet vortex (PJV) on a high-speed compressor cascade for flow separation control was studied numerically. The effectiveness of the technique at off-design conditions was investigated. Results indicated that the PJV could reduce the total pressure loss coefficient by 5.2% at the designed angle of attack, and by 7.8% under different angles of attack, validating its high control efficiency and good adaptability. With the increase of the angle of attack, the flow separation on the blade suction surface would take place earlier and the distance between the jet exit and the separation region would decrease, which could strengthen the effect of PJV in enhancing momentum exchange and reorganizing the vortex structures like the passage vortex and the concentrated shed vortex within the passage, thus delaying the flow separation and reducing flow losses. Taking different angles of attack into consideration, it is suggested that the PJV be located near the upstream separation region. The optimum location of the jet is at 40% axial chord length from the blade leading edge.
- angle of attack /
- passive jet vortex (PJV) /
- high-speed compressor cascade /
- aerodynamic performance /
- flow control

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参考文献(19)

[1]	HOSNY W,TABAKOFF W.An analysis of losses and secondary flow in turbine cascades［R］.Cincinnati,US:University of Cincinnati,1971.
[2]	CULLEY D E,BRIGHT M M,PRAHST P S,et al.Active flow separation control of a stator vane using surface injection in a multistage compressor experiment［R］.ASME Paper GT2003-38863,2003.
[3]	WIEDERHOLD O,HECKLAU M,KING R,et al.Multivariable control in a critically loaded compressor cascade［J］.International Journal of Flow Control,2011,2(4):219-236.
[4]	HECKLAU M,SALAZAR D P,NITSCHE W.Influence of the actuator jet angle on the reattachment process with pulsed excitation［M］.Berlin,Germany:Springer Berlin Heidelberg,2013.
[5]	ZANDER V,NITSCHE W.Control of secondary flow struc-tures on a highly loaded compressor cascade［J］.Journal of Power and Energy,2013,227(6):674-682.
[6]	徐大懋.压气机弦向缝隙叶栅的研究［R］.哈尔滨:哈尔滨汽轮机厂研究所,1980.
[7]	SONG Yanping,CHEN Huanlong,CHEN Fu,et al.Effects of air injection on performance of highly-loaded compressor cascades［R］.ASME Paper GT2007-27062,2007.
[8]	陈浮,陈焕龙,冯冬民.高负荷缝隙弯曲扩压叶栅尾迹特性实验［J］.推进技术,2009,30(2):197-201.CHEN Fu,CHEN Huanlong,FENG Dongmin.Experimental on wake characteristics in compound lean compressor cascades with slots injection［J］.Journal of Propulsion Technology,2009,30(2):197-201.(in Chinese)
[9]	周敏,王如根,张相毅,等.改变开孔位置对风扇叶片气动特性的影响［J］.汽轮机技术,2007,49(5):359-361.ZHOU Min,WANG Rugen,ZHANG Xiangyi,et al.Effect of hole position on the pneumatic performance of fan blade［J］.Turbine Technology,2007,49(5):359-361.(in Chinese)
[10]	周敏,王如根,曾令君,等.槽道宽度对压气机叶栅气动性能的影响［J］.航空动力学报,2008,23(6):1077-1081.ZHOU Min,WANG Rugen,ZENG Lingjun,et al.Effect of slot width on the aerodynamic performance of compressor cascade［J］.Journal of Aerospace Power,2008,23(6):1077-1081.(in Chinese)
[11]	吴培根,王如根,罗凯,等.开槽叶片对大转角扩压叶栅性能的影响［J］.航空动力学报,2013,28(11):2503-2509.WU Peigen,WANG Rugen,LUO Kai,et al.Effect of slotted blade on performance of high-turning angle compressor cascade［J］.Journal of Aerospace Power,2013 28(11):2503-2509.(in Chinese)
[12]	吴培根,王如根,胡加国,等.槽道出口位置对高负荷扩压叶栅性能的影响［J］.热能动力工程,2014,29(2):121-126.WU Peigen,WANG Rugen,HU Jiaguo,et al.Influence of the location of the slot at the outlet on the performance of a highly-loaded diffusion cascade［J］.Journal of Engineering for Thermal Energy and Power,2014,29(2):121-126.(in Chinese)
[13]	胡加国,王如根,李坤,等.跨声速压气机叶尖开槽射流扩稳策略探究［J］.推进技术,2014,35(11):1475-1481.HU Jiaguo,WANG Rugen,LI Kun,et al.Investigation on slot jetting flow method and mechanism of transonic compressor［J］.Journal of Propulsion Technology,2014,35(11):1475-1481.(in Chinese)
[14]	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.
[15]	EVANS S,HODSON H,HYNES T,et al.Controlling separation on a simulated compressor blade using vortex-generator jets［J］.Journal of Propulsion and Power,2010,26(4):819-827.
[16]	EVANS S,COULL J,HANEEF I,et al.Minimizing the loss produced by a turbulent separation using vortex generator jets［J］.AIAA Journal,2012,50(4):778-787.
[17]	刘华坪,陈焕龙,李德雄,等.射流旋涡发生器控制大折转角扩压叶栅二次流［J］.航空动力学报,2015,30(4):838-845.LIU Huaping,CHEN Huanlong,LI Dexiong,et al.Secondary flow control in high-turning compressor cascade using vortex generator jet［J］.Journal of Aerospace Power,2015,30(4):838-845.(in Chinese)
[18]	冯岩岩,宋彦萍,刘华坪,等.不同攻角下端壁射流旋涡控制扩压叶栅分离流动研究［J］.推进技术,2015,36(1):54-60.FENG Yanyan,SONG Yanping,LIU Huaping,et al.Effects of end-wall vortex generator jet on flow sepa-ration control in compressor cascade under different angles of attack［J］.Journal of Propulsion Technology,2015,36(1):54-60.(in Chinese)
[19]	HERGT A,ROBERT M,KARSTEN L,et al.A new approach for compressor endwall contouring［R］.ASME Paper GT2011-45858,2011.