鼓包前缘静叶在跨声速压气机中应用初探

推进技术 ›› 2016, Vol. 37 ›› Issue (7): 1256-1262.

鼓包前缘静叶在跨声速压气机中应用初探

屠宝锋^1,2,张凯¹

南京航空航天大学能源与动力学院，江苏省航空动力系统重点实验室，江苏南京 210016; 先进航空发动机协同创新中心，北京 100191,南京航空航天大学能源与动力学院，江苏省航空动力系统重点实验室，江苏南京 210016

发布日期:2021-08-15
作者简介:屠宝锋，男，博士，讲师，研究领域为风扇/压气机气动稳定性。
基金资助:
南京航空航天大学青年科技创新基金(NS2014021)。

Preliminary Investigation on Tubercle Leading Edge

Nanjing University of Aeronautics and Astronautics，Jiangsu Province Key Laboratory of Aerospace Power Systems，Nanjing 210016，China; Collaborative Innovation Center of Advanced Aero-Engine，Beijing 100191，China and Nanjing University of Aeronautics and Astronautics，Jiangsu Province Key Laboratory of Aerospace Power Systems，Nanjing 210016，China

Published:2021-08-15

摘要/Abstract

摘要： 为减小静叶吸力面表面的流动分离，提高压气机气动性能，对跨声速压气机的静子叶片进行鼓包前缘造型，研究鼓包前缘设计参数的影响。数值模拟结果表明:鼓包前缘使静叶表面静压重新分布，改善了流场结构；鼓包波峰产生的对涡结构能够抑制静叶吸力面附面层分离，减小分离区范围；50%叶高以下范围提高效率和总压比较为显著，50%叶高以上范围效率和总压比反而略有降低；在不降低压气机气动稳定性的前提下，效率和总压比分别提升约2%和0.5%，表明鼓包前缘静叶可提高压气机气动性能。

关键词: 静叶；鼓包前缘；附面层分离；性能；数值模拟

Abstract: In order to reduce flow separation region on suction surface of stator blades，and improve aerodynamic performance of the compressor，tubercle leading edge stator blades with different design variables were used in a transonic compressor. The numerical simulation results show that tubercle leading edge can redistribute the static pressure on blade surface and improve the structure of flow field. The crest of each tubercle will generate twin swirl which will suppress suction surface boundary layer separation and reduce separation region. The efficiency and total pressure ratio are significantly improved within the region below 50% span，and reduced slightly above 50% span. Efficiency and the total pressure ratio will increase 2% and 0.5%，respectively，without reducing aerodynamic stability of the compressor，which means that the tubercle leading edge stator blades can improve aerodynamic performance of compressor.

Key words: Stator blade；Tubercle leading edge；Boundary layer separation；Performance；Numerical simulation

屠宝锋,张凯. 鼓包前缘静叶在跨声速压气机中应用初探[J]. 推进技术, 2016, 37(7): 1256-1262.

TU Bao-feng^1,2,ZHANG Kai¹. Preliminary Investigation on Tubercle Leading Edge[J]. Journal of Propulsion Technology, 2016, 37(7): 1256-1262.

参考文献

[1] Fish F E. Influence of Hydrodynamic Design and Propulsive Mode on Mammalian Swimming Energetics[J].Australian Journal of Zoology, 1993, 42(1): 79-101.
[2] Fish F E. Performance Constraints on the Maneuverability of Flexible and Rigid Biological Systems[C]. Durham: Proceedings of the Eleventh International Symposium on Unmanned Untethered Submersible Technology (UUST), UUST99, 1999: 394-406.
[3] Fish F E, Howle L E, Murray M M. Hydrodynamic Flow Control in Marine Mammals[J]. Integrative and Comparative Biology, 2008, 48(6): 788-800.
[4] Watts P, Fish F E. The Influence of Passive, Leading Edge Tubercles on Wing Performance[C]. Durham: Proceedings of Unmanned Untethered Submersible Technology (UUST), UUST01, Autonomous Undersea Systems Institute, 2001.
[5] Miklosovic D S, Murray M M, Howle L E. Experimental Evaluation of Sinusoidal Leading Edges[J]. Journal of Aircraft; Engineering Notes, 2007, 44(2): 1404-1407.
[6] Miklosovic D S, Murray M M, Howle L E. et al. Leading-Edge Tubercles Delay Stall on Humpback Whale (Megapteranovaeangliae) Flippers[J]. Phys.Fluids, 2004 16(5):L39–L42.
[7] Corsini A, Delibra G, Sheard A G. The Application of Sinusoidal Blade-Leading Edges in a Fan-Design Methodology to Improve Stall Resistance[J]. Journal of Power and Energy, 2014, 228(3): 255-271.
[8] Gruber T, Murray M M, Fredriksson D W. Effect of Humpback Whale Inspired Tubercles on Marine Tidal Turbine Blade [C]. Denver: ASME 2011 International Mechanical Engineering Congress and Exposition, 2011: 851-857.
[9] Hansen K L, Kelso R M. Performance Variations of Leading-Edge Tubercles for Distinct Airfoil Pro?les [J].AIAA Journal, 2011, 49(1): 187-196.
[10] CHEN Huang, PAN Chong, WANG JinJun. Effects of Sinusoidal Leading Edge on Delt Wing Performance and Mechanism[J]. Sci.China Tech.Sci. , 2013, 56(3):772-779.
[11] Arai H, Doi Y, Nakashima T. A Study on Stall Delay by Various Wavy Leading Edges[J]. Journal of Aero Aqua Bio-mechanisms, 2010, 1(1): 18-23.
[12] Stein B, Murray M M. Stall Mechanism Analysis of Humpback Whale Flipper Models[C]. Durham: Proceedings of Unmanned Untethered Submersible Technology (UUST), UUST05, 2005.
[13] Fish F E, Battle J M. Hydrodynamic Design of the Humpback Whale Flipper[J]. Journal of Morphology, 1995, 225(1): 51-60.
[14] Custodio D. The Effect of Humpback Whale-Like Leading Edge Protuberances on Hydrofoil Performance [D]. Worcester: Worcester Polytechnic Institute, 2007.
[15] Hasheminejad S M, Mitsudharmadi H, Winoto S H. Effect of Flat Plate Leading Edge Pattern on Structure of Streamwise Vortices Generated in Its Boundary Layer [J]. Journal of Flow Control, Measurement & Visualization, 2014, 2(1): 18-23.
[16] Bearman P W, Owen J C. Reduction of Bluff-Body Drag and Suppression of Vortex Shedding by the Introduction of Wavy Separation Lines[J]. Journal of Fluids and Structures, 1998, 12(1): 123-130.
[17] Bearman P W, Tombazis N. The Effect of Three-Dimensional Imposed Disturbances on Bluff Body Near Wake Flows[J]. Journal of Wind Engineering and Industrial Aerodynamics, 1993, 49(1): 339-350.
[18] Naumann A, Morsbach M, Kramer C. The Conditions of Separation and Vortex Formation Past Cylinders[R]. AGARD Conference Proceedings No.4, Separated Flows, 1966: 539-574.
[19] 陆宏志, 徐力平. 压气机叶片的带平台圆弧形前缘 [J]. 推进技术, 2003, 24(6): 532-536. (LU Hong-zhi, XU Li-ping. Circular Leading Edge with a Flat for Compressor Blades[J]. Journal of Propulsion Technology, 2003, 24(6): 532-536.)
[20] 靳允立, 胡骏. 叶片弯掠对多级风扇气动性能的影响[J]. 推进技术, 2009, 30(1): 77-82. (JIN Yun-li, Hu Jun. Effects of Swept Curved Blade on the Performance of the Multistage Fan [J]. Journal of Propulsion Technology, 2009, 30(1): 77-82.)(编辑:梅瑛)　　　　　　　　　　　　　*　收稿日期:2015-02-13；修订日期:2015-04-27。基金项目:南京航空航天大学青年科技创新基金(NS2014021)。作者简介:屠宝锋,男,博士,讲师,研究领域为风扇/压气机气动稳定性。E-mail: tubaofeng@126.com