叶型对扩压叶栅角区分离的影响

推进技术 ›› 2014, Vol. 35 ›› Issue (9): 1216-1226.

叶型对扩压叶栅角区分离的影响

凌　敬,杜　鑫,王松涛,王仲奇

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:凌　敬(1986—)，男，博士生，研究领域为叶轮机械气动热力学。

Effects of Blade Profile on Corner Separation in

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

Published:2021-08-15

摘要/Abstract

摘要： 为了在叶型设计阶段尽可能减小角区分离的可能性，用数值模拟方法研究角区分离形式对扩压叶栅气动性能的影响，以及叶型参数对角区分离形式和分离范围的影响。角区分离改变了吸力面的静压分布，静压沿叶展方向呈现出“C”型压力分布，与开式分离相比闭式分离加剧了吸力面的“C”型压力分布，闭式分离造成下端壁吸力面最低压力点后的流向逆压力梯度增加。分离降低叶栅扩压能力，增大损失，与开式分离相比闭式分离的气动性能降低更显著。研究结果表明:角区分离受叶型参数的影响较大，随着叶型相对厚度的增加、中弧线挠度增大、最大厚度位置后移吸力面最大厚度位置之后的型线曲率的变化梯度增大，吸力面最低压力点之后的流向逆压力梯度和吸力面展向压力梯度增大，进而增大角区分离范围，改变分离形式，由开式分离向闭式分离转变。

关键词: 扩压叶栅；角区分离；分离形式；逆压梯度；型线曲率

Abstract: Effects of suction surface corner separation on the aerodynamic performance and effects of the blade parameters on suction surface corner separation in linear compressor cascade were researched to prevent corner separation when designing profile. Static pressure on suction surface was changed，and a C-Shape pressure distribution along span wise was built owing to corner separation. The C-Shape pressure distribution of closed separation is much more significant than that of open separation. Stream wise adverse pressure gradient after the lowest pressure point on suction surface of closed separation is larger than that of open separation. Diffusion capability decreases and loss increases because of the separation，aerodynamic performance degradation of closed separation is larger than that of open separation. Results show that corner separation is influenced by profile parameters significantly，with the increase of the blade thickness，the maximum thickness position moving afterwards and the deflection of mean camber line，the curvature gradient after the max blade thickness position of suction surface increases，the stream wise adverse pressure gradient on the suction surface after the lowest pressure point increases，the scale of separation zone increases，even the separation form could change from open separation to closed separation.

Key words: Compressor cascade; Corner separation; Separation form; Adverse pressure gradient; Curvature

凌　敬,杜　鑫,王松涛,王仲奇. 叶型对扩压叶栅角区分离的影响[J]. 推进技术, 2014, 35(9): 1216-1226.

LING Jing,DU Xin,WANG Song-tao,WANG Zhong-qi. Effects of Blade Profile on Corner Separation in[J]. Journal of Propulsion Technology, 2014, 35(9): 1216-1226.

参考文献

[1] Mertz C.A Study of the Effect of Boundary Layer Control on an Axial Flow Compressor Stage[D].USA: Aeronautical Engineer Thesis,California Institute of Technology,1954.
[2] Horlock J H,Percival P M E,Louis J F,et al.Wall Stall in Compressor Cascades[R].ASME 1964,64-WA/FE-29.
[3] Schulz H D,Gallus H E,Lakshminarayana B.Three-Dimensional Separated Flow Field in the Endwall Region of an Annular Compressor Cascade in the Presence of Rotor-Stator Interaction.Part I.Quasi-Steady Flow Field and Comparison with Steady-State Data[J].Journal of Turbomachinery,1990,112(4): 669-678.
[4] Joslyn D H,Dring R P.Axial Compressor Stator Aerodynamics[J].ASME Journal of Engineering for Gas Turbines and Power,1985,107(3): 485-493.
[5] Lei.A Simple Criterion for Three-Dimensional Flow Separation in Axial Compressors[D].USA: Department of Aeronautics and Astronautics,MIT,2006.
[6] Gbadebo S A,Cumpsty N A.Three-Dimensional Separations in Axial Compressors[J].Journal of Turbomachinery,2005,127(2): 331-339.
[7] McDougal N M.A Comparison between the Design Point and Near-Stall Performance of an Axial Compressor[J].Journal of Turbomachinery,1990,112(1): 109-115.
[8] Lei V M,Spakovszky Z S,Greitzer E.M.A Criterion for Axial Compressor Hub-Corner Stall[J].Journal of Turbomachinery,2008,130(3).
[9] Dong Y,Gallimore S J.Three-Dimensional Flows and Loss Reduction in Axial Compressors[J].ASME Journal of Turbomachinery,1987,109(2): 354-361.
[10] Gbadebo S A,Cumpsty N A.Interaction of Tip Clearance Flow and Three-Dimensional Separations in Axial Compressors[J].ASME Journal of Turbomachinery,2007,129(4):679-685.
[11] Wellborn S R,Okiishi T H.Effects of Shrouded Stator Cavity Flows on Multistage Axial Compressor Aerodynamic Performance[R].NASA-CR-198536,1996.
[12] Demargne A A J,Longley J P.The Aerodynamic Interaction of Stator Shroud Leakage and Mainstream Flows in Compressors[R].ASME 2000-GT-570.
[13] Domercq O.Hp Compressor 3d Design[R].VKI Lecture Series "Advances in Axial Compressor Aerodynamics",2006.
[14] Gümmer V,Wenger U,Kau H P.Using Sweep and Dihedral to Control Three-Dimensional Flow in Transonic Stators of Axial Compressors[R].ASME 2000-GT-0491.
[15] Friedriches J,Baumgarten S,Kosyna G,et al.Effect of Stator Design on Stator Boundary Layer Flow in a Highly Loaded Single-Stage Axial-Flow Low-Speed Compressor[J].ASME Journal of Turbomachinery,2001,123(3):483-489.
[16] Nerger D,Saathoff H,Radespiel R.Experimental Investigation of Endwall and Suction Side Blowing in a Highly Loaded Stator Cascade[R].ASME 2010 GT-22578.
[17] 张华良.采用附面层弯_掠及附面层抽吸控制扩压叶栅内涡结构的研究[D].哈尔滨: 哈尔滨工业大学,2005.
[18] Dallmann U.Topological Structures of 3-D Flow Separation[R].DFVLR,IB 221-82-A07,Gottingen,Germany,1983.
[19] 张涵信.分离流与旋涡运动的结构分析[R].北京:国防工业出版社,2002.
[20] Lighthill M J.Attachment and Separation in Three-Dimension Flow[D].UK: Oxford Uni.Press,1963.
[21] Maskell.Flow Separation in Three Dimensions[R].RAE Report.Aero 2565,1995.
[22] Wang K C.Separation Patterns of Boundary Layer over an Inclined Body of Revolution[J].AIAA Journal,1972,10(1):1044~1050.
[23] Peake D J,Tobak M.3-D Interactions and Vortical Flows with Emphsis on High Speeds[R].AGAR Dograph,No.252,1980.
[24] Spalart P R,Allmaras S R.A One-Equation Turbulence Model for Aerodynamic Flows[R].AIAA 92-0439.
[25] 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(3): 170~175.(CHEN Shao-wen,CHEN Fu,WANG Li-ke,et al.Aerodynamic Performance Study of Curved Compressor Cascades with Different Camber Angles[J].Journal of Propulsion Technology,2007,28(3): 170-175.)
[26] 张永军.扩压叶栅采用弯叶片控制流场结构与改善气动性能的研究[D].哈尔滨: 哈尔滨工业大学,2007.(编辑:梅瑛)收稿日期:2013-09-05；修订日期:2013-11-26。作者简介:凌敬(1986—),男,博士生,研究领域为叶轮机械气动热力学。E-mail:hitlingjing@163.com