一种压气机叶型的可控环量尾缘造型方法

宁方飞; 李一鸣

doi:10.13224/j.cnki.jasp.2019.01.017

一种压气机叶型的可控环量尾缘造型方法

doi: 10.13224/j.cnki.jasp.2019.01.017

宁方飞¹,
李一鸣²

1.
北京航空航天大学能源与动力工程学院航空发动机气动热力国家级重点实验室，北京 100191
2.
中国航天科工集团有限公司飞航技术研究院北京海鹰科技情报研究所，北京 100074

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出版历程
- 收稿日期: 2018-01-18
- 刊出日期: 2019-01-28

A method for controlled circulation trailing edge design ofcompressor blade

摘要

摘要: 为了提高压气机叶型负荷，提出了一种可控环量尾缘造型方法，该方法对叶型尾缘处弦长2%的区域进行特殊造型，通过改变流动后驻点位置从而提高叶型环量，增加叶型气流转角。在不同马赫数及雷诺数下进行数值模拟得到了一致的结论。数值模拟结果显示：以设计进气角D因子为0.52的叶型为基准叶型，采用可控环量尾缘造型后叶型气流转角可提高21%，同时总压损失基本无变化，部分叶型甚至在气流转角提高的同时总压损失有所降低。而当气流折转角相同时，可控环量尾缘可以比传统尾缘的总压损失更小。
- 尾缘 /
- 压气机 /
- 二维叶型 /
- 环量控制 /
- 高负荷
Abstract: A controlled circulation trailing edge design method for compressor blade was proposed to increase the circulation and the turning angle of cascades through the specific geometrical modelling at the region of 2% chord length of trailing edge. The conclusion was verified under different Mach numbers and Reynolds numbers. The numerical results showed that, for the cascade with the diffusion factor up to 0.52 at design condition, the controlled circulation trailing edge can improve the flow turning angle by about 21% while the total pressure loss was nearly kept unchanged. Some controlled circulation trailing edge designs can even have positive effect on the decrease of loss. At the same flow turning angle, the cascade with the controlled circulation trailing edge can have lower total pressure loss than that with traditional rounded trailing edge.
- trailing edge /
- compressor /
- two-dimensional cascade /
- circulation control /
- high loading

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参考文献(24)

[1]	KARAMCHETI K.Principles of ideal-fluid aerodynamics［M］.New York:John Wiley and Sons,Inc.,1966:376-401.
[2]	WOOD N J,NIELSON J N.Circulation control airfoils past,present,and future［R］.Reno NV:23rd Aerospace Sciences Meeting,Aerospace Sciences Meetings,1985.
[3]	ENGLAR R J.Circulation control pneumatic aerodynamics:blown force and moment augmentation and modifications past,present,and future［R］.Denver CO:Fluids 2000 Conference and Exhibit,Fluid Dynamics and Co-located Conferences,2000.
[4]	LIU Y,SANKAR L N,ENGLAR R J,et al.Numerical simulations of the steady and unsteady aerodynamic characteristics of a circulation control wing airfoil［R］.Reno NV:39th Aerospace Sciences Meeting and Exhibit,Aerospace Sciences Meetings,2001.
[5]	SMITH A M O.Highlift aerodynamics/37th wright brothers lecture［R］.Los Angeles CA:6th Aircraft Design,Flight Test and Operations Meeting,Aircraft Design and Operations Meetings,1974.
[6]	ANDERSON W K,BONHAUS D L,MCGHEE R J,et al.Navier-Stokes computations and experimental comparisons for multi-element airfoil configurations［J］.Journal of Aircraft,1995,32(6):1246-1253.
[7]	ENGLAR R J,STONE M B,HALL M.Circulation control:a bibliography of DTNSRDC research and selected outside references:DTN84/052［R］.Bethesda,MD:David Taylor Naval Ship Research and Development Center (DTNSRDC),1984.
[8]	孙卫平,杨康智,秦何军.大型水陆两栖飞机吹气襟翼设计与分析验证［J］.航空动力学报,2016,31(4):903-909.SUN Weiping,YANG Kangzhi,QIN Hejun.Design and test of a jet flap for a large amphibian［J］.Journal of Aerospace Power,2016,31(4):903-909.(in Chinese)
[9]	LIEBECK R H.Design of subsonic airfoils for high lift［J］.Journal of Aircraft,1978,15(9):547-561.
[10]	DAN H N,ODIS C P.A water tunnel study of Gurney flaps［R］.Hampton Virginia:NASA Technical Memorandum,1988.
[11]	DAVID J,XIN Z.Aerodynamics of Gurney flaps on a single-element high-lift wing［J］.Journal of Aircraft,2000,37(2):295-301.
[12]	DAVID J,DAVID H.Aerodynamics of the Gurney flap［R］.New Orleans LA:14th Applied Aerodynamics,1996.
[13]	MANISH K S,DHANALAKSHMI K,CHAKRABARTTY S K.Navier-Stokes analysis of airfoils with Gurney flap［J］.Journal of Aircraft,2007,44(5):1487-1493.
[14]	BAE E S,FARHAN G.CFD analysis of high-lift devices on the SC-1094R8 airfoil［R］.Virginia Beach,VA:67th American Helicopter Society International Annual Forum,2011.
[15]	JON W,HEATHER H,DAN L,et al.Analysis of Gurney flap effects on a NACA0012 airfoil/wing section［R］.Anaheim CA:19th AIAA Applied Aerodynamics Conference,Fluid Dynamics and Co-located Conferences,2001.
[16]	MICHAEL A C,PAUL R,WILLIAM H M.Windtunnel test of Gurney flaps and T-strips on an NACA23012 wing［R］.Miami FL:25th AIAA Applied Aerodynamics Conference,Fluid Dynamics and Co-located Conferences,2007.
[17]	KWANJUNG Y,WANDON J,DONG H L.Aerodynamic performance analysis of a Gurney flap for rotorcraft application［J］.Journal of Aircraft,2007,44(3):1003-1014.
[18]	LI Yachen,WANG Jinjun,ZHANG Panfeng.Influences of mounting angles and locations on the effects of Gurney flaps［J］.Journal of Aircraft,2003,40(3):494-498.
[19]	WANG J J,LI Y C,CHOI K S.Gurney fap-lift enhancement,mechanisms and applications［J］.Progress in Aerospace Sciences,2008,44(1):22-47.
[20]	周瑞兴,惠增宏,金承信.Gurney襟翼对单段翼型动态气动特性的影响［J］.流体力学实验与测量,2002,16(2):30-35.ZHOU Ruixing,HUI Zenghong,JIN Chengxin.Effect ofGurney flaps on aerodynamical characters of single airfoil［J］.Experiments and Measurements in Fluid Mechanics,2002,16(2):30-35.(in Chinese)
[21]	沈遐龄,万周迎,高歌.锯齿形格尼襟翼气动性能的实验研究［J］.北京航空航天大学学报,2003,29(3):202-204.SHEN Xialing,WAN Zhouying,GAO Ge.Experimental investigation on aerodynamic performance of serrated Gurney flap［J］.Journal of Beijing University of Aeronautics and Astronautics,2003,29(3):202-204.(in Chinese)
[22]	夏商周,申振华.改型尾缘对翼型流场影响的数值模拟［J］.沈阳航空航天大学学报,2005,22(5):1-3.XIA Shangzhou,SHEN Zhenhua.Numerical simulation effect of modified trailing edge on airfoil flow field［J］.Journal of Shenyang Institute of Aeronautical Engineering,2005,22(5):1-3.(in Chinese)
[23]	崔钊,韩东,李建波.翼型加装格尼襟翼的高亚声速气动特性研究［J］.航空学报,2013,34(10):2277-2286.CUI Zhao,HAN Dong,LI Jianbo.Study on aerodynamic characteristics of airfoil with Gurney flaps under high subsonic flow［J］.Acta Aeronautica et Astronautica Sinica,2013,34(10):2277-2286.(in Chinese)
[24]	宁方飞.考虑真实几何复杂性的跨音压气机内部流动的数值模拟［D］.北京:北京航空航天大学,2002.NING Fangfei.Numerical simulation of internal flow in transonic compressor considering real geometric complexity［D］.Beijing:Beijing University of Aeronautics Astronautics,2002.(in Chinese)