不同来流附面层特性下端壁射流对弯曲叶栅内流场的影响

推进技术 ›› 2017, Vol. 38 ›› Issue (6): 1278-1286.

不同来流附面层特性下端壁射流对弯曲叶栅内流场的影响

李龙婷,宋彦萍,陈浮,刘华坪

哈尔滨工业大学能源科学与工程学院，黑龙江哈尔滨 150001,哈尔滨工业大学能源科学与工程学院，黑龙江哈尔滨 150001,哈尔滨工业大学能源科学与工程学院，黑龙江哈尔滨 150001,哈尔滨工业大学能源科学与工程学院，黑龙江哈尔滨 150001

发布日期:2021-08-15
作者简介:李龙婷，女，博士生，研究领域为叶轮机械气动热力学。
基金资助:
国家自然科学基金(50976026)；国家自然科学基金委创新研究群体基金(51121004)。

Effects of Endwall Jet on Flow Fields in Bowed Compressor Cascades at Different Inlet Boundary Layers

School of Energy and Engineering，Harbin Institute of Technology，Harbin 150001，China,School of Energy and Engineering，Harbin Institute of Technology，Harbin 150001，China,School of Energy and Engineering，Harbin Institute of Technology，Harbin 150001，China and School of Energy and Engineering，Harbin Institute of Technology，Harbin 150001，China

Published:2021-08-15

摘要/Abstract

摘要： 给定不同型式的来流附面层，采用数值模拟方法，旨在讨论变来流附面层特性下端壁射流式旋涡发生器对于弯曲扩压叶栅内流场的影响。结果表明，对于正弯叶栅，射流可有效减弱其吸力面上的流动分离，随着来流附面层变厚或附面层内总压亏损的增加，原型叶栅角区内的分离范围逐渐增加，因此提供给射流改善流场的空间也相应增大，损失降低程度由2.3%提高到8%。在反弯叶栅当中，射流作用之后，在零附面层来流条件下，角区内的分离范围减小且损失降低了9.1%；随着来流附面层增厚，在分离范围降低的同时，吸力面上的集中脱落涡也相应消失，因而损失降低程度增加到了12.5%。此时，随着来流附面层条件进一步恶化，射流对于流场的作用效果基本保持不变，这说明针对本文给定的射流参数，端壁射流对于反弯叶栅内流场的改善程度已达到极限。

关键词: 弯曲扩压叶栅；来流附面层；射流式旋涡发生器；流动分离；损失降低

Abstract: A numerical calculation was carried out to study the effects of endwall jet on the flow fields in bowed compressor cascades at different inlet boundary layers. The results show that，for the positively bowed blade，the endwall VGJ can effectively suppress the flow separation on the suction side. With the increase of the inlet boundary layer thickness or the total pressure defect into the boundary layer，under the effects of VGJ，the region of separation in the baseline cascade increases accordingly，which applies the larger space to the flow field improvement caused by the VGJ，and hence the loss reduction increases from 2.3% to 9.8%. For the negatively bowed blade，with the VGJ，under the condition without inlet boundary layer，the separation is suppressed and a loss reduction of 9.1% is obtained. As the inlet boundary layer thickens，the concentrated shedding vortex disappears while the flow separation weakens. Therefore，the loss reduction increases to 12.5%. With the further aggravation of the inlet boundary layer，the loss reduction keeps unchanged，which means that the improvement to the flow filed in the cascade caused by the VGJ has reached its limit under the jet parameters shown in this paper.

Key words: Bowed compressor cascades；Inlet boundary layers；Vortex generator jet；Flow separation；Loss reduction

李龙婷,宋彦萍,陈浮,刘华坪. 不同来流附面层特性下端壁射流对弯曲叶栅内流场的影响[J]. 推进技术, 2017, 38(6): 1278-1286.

LI Long-ting,SONG Yan-ping,CHEN Fu,LIU Hua-ping. Effects of Endwall Jet on Flow Fields in Bowed Compressor Cascades at Different Inlet Boundary Layers[J]. Journal of Propulsion Technology, 2017, 38(6): 1278-1286.

参考文献

[1] Li L T, Song Y P, Chen F, et al. Effects of Vortex Generator Jet on Flow Separations in Bowed Compressor Cascades[R]. ASME 2015-42308.
[2] 张漫, 乔渭阳. 射流式旋涡发生器对涡轮流动分离控制[J]. 推进技术, 2008, 29(1): 67-74. (ZHANG Man, QIAO Wei-yang. Numerical Simulation of the Vortex Generator Jets for Low-Pressure Turbine Separation Control[J]. Journal of Propulsion Technology, 2008, 29(1): 67-74.)
[3] 张漫, 乔渭阳. 逆主流射流式旋涡发生器对涡轮流动分离控制数值模拟[J]. 推进技术, 2008, 29(2): 168-173. (ZHANG Man, QIAO Wei-yang. Numerical Simulation of the Reversed Injection VGJs for Low-Pressure Turbine Separation Control[J]. Journal of Propulsion Technology, 2008, 29(2): 168-173.)
[4] 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.
[5] Benton S I, Bons J P, Sondergaard R. Secondary Flow Loss Reduction Through Blowing for a High-Lift Front-Loaded Low Pressure Turbine Cascade[J]. Journal of Turbomachinery, 2013, 135(2).
[6] Benton S I, Bernardini C, Bons J P, et al. Parametric Optimization of Unsteady End Wall Blowing on a Highly Loaded Low-Pressure Turbine[J]. Journal of Turbo-machinery, 2014, 136(7).
[7] 韩万今, 吕红卫, 卢文才, 等. 进口附面层厚度对大转角弯叶片损失的影响[J]. 工程热物理学报, 1994, 15(4): 391-394.
[8] 钟兢军, 刘毓国, 苏杰先, 等. 进口附面层厚度对弯叶片扩压叶栅损失的影响[J]. 工程热物理学报, 1997, 18(5): 553-557.
[9] Wagner J H, Dring R P, Joslyn H D. Inlet Boundary Layer Effects in an Axial Compressor Rotor: Part I-Blade-to-Blade Effects[J]. Journal of Engineering for Gas Turbines and Power, 1984, 107(2): 374-380.
[10] Wagner J H, Dring R P, Joslyn H D. Inlet Boundary Layer Effects in an Axial Compressor Rotor: Part II-Through Flow Effects[J]. Journal of Engineering for Gas Turbines and Power, 1985, 107(2): 381-386.
[11] De La Rosa Blanco E, Hodson H P, Vazquez R, et al. Influence of the State of the Inlet Endwall Boundary Layer on the Interaction between Pressure Surface Separation and Endwall Flows[J]. Journal of Power and Energy, 2003, 217(4): 433-441.
[12] Choi M, Park J Y, Baek J H. Effects of the Inlet Boundary Layer Thickness on the Loss Characteristics in an Axial Compressor[J]. International Journal of Turbo and Jet Engines, 2006, 23(1): 51-72.
[13] 陈绍文, 陈浮, 王可立, 等. 采用弯叶片的不同折转角压气机叶栅流场气动性能[J]. 推进技术, 2007, 28(2): 170-175. (CHEN Shao-wen, CHEN Fu, WANG Ke-li, et al. Aerodynamic Performance Study of Curved Compressor Cascades with Different Camber Angles[J]. Journal of Propulsion Technology, 2007, 28(2): 170-175.)
[14] Zhang L X, Chen S W, Xu H, et al. Effect of Boundary Layer Suction on Aerodynamic Performance of High-Turning Compressor Cascade[R]. ASME 2013-94907.
[15] Ding J, Chen S, Xu H, et al. Control of Flow Separations in Compressor Cascade by Boundary Layer Suction Holes in Suction Surface[R]. ASME 2013-94723.
[16] 陈绍文. 不同折转角压气机叶栅中应用弯曲叶片的实验与数值研究[D]. 哈尔滨:哈尔滨工业大学, 2007.
[17] 张永军, 冯国泰, 陈浮. 进口边界层对采用弯叶片的平面扩压静叶栅流场性能的影响[J]. 航空动力学报, 2006, 21(2): 254-260.
[18] Wang K C. Separation Pattern of Boundary Layer over an Inclined Body of Revolution[J]. AIAA Journal, 1972, 10(8): 1044-1050.
[19] 张华良, 王松涛, 王仲奇. 叶片弯曲对大折转压气机叶栅内分离结构的影响[J]. 推进技术, 2007, 28(1): 36-39. (ZHANG Hua-liang, WANG Song-tao, WANG Zhong-qi. Effect of Bowed Blades on the Separation Structures in High-Turning Compressor Cascades[J]. Journal of Propulsion Technology, 2007, 28(1): 36-39.)
[20] 张华良, 谭春青, 张新敬, 等. 采用附面层抽吸 (BLS) 控制流动分离的数值模拟[J]. 推进技术, 2009, 30(2): 192-196. (ZHANG Hua-liang, TAN Chun-qing, ZHANG Xin-jing, et al. Numerical Investigation on Application of Boundary Layer Suction to Control the Flow Separations[J]. Journal of Propulsion Technology, 2009, 30(2): 192-196.)
[21] Gbadebo S A, Cumpsty N A, Hynes T P. Three-Dimensional Separations in Axial Compressors[J]. Journal of Turbomachinery, 2005, 127(2): 331-339.　　　　　　　　　　　*　收稿日期:2016-01-29；修订日期:2016-04-01。基金项目:国家自然科学基金(50976026)；国家自然科学基金委创新研究群体基金(51121004)。作者简介:李龙婷,女,博士生,研究领域为叶轮机械气动热力学。E-mail: lilongting_0708@126.com(编辑:张荣莉)