基于多项式的曲率连续前缘造型方法及应用

施恒涛; 刘宝杰; 于贤君

doi:10.13224/j.cnki.jasp.2020.02.019

基于多项式的曲率连续前缘造型方法及应用

doi: 10.13224/j.cnki.jasp.2020.02.019

基金项目: 国家科技重大专项(2017-Ⅱ-0001-0013)

计量
- 文章访问数: 952
- HTML浏览量: 1
- PDF量: 553
- 被引次数: 0
出版历程
- 收稿日期: 2019-07-27
- 刊出日期: 2020-02-28

Polynomial-based continuous-curvature leading edge design method and its application

1.
School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics,Beijing 100191,China
2.
National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics,School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics,Beijing 100191,China

摘要

摘要: 为了优化前缘(LE)形状以提高叶型气动性能,提出了一种基于多项式的曲率连续前缘造型方法。通过给定前缘和叶身交点处中弧线和厚度分布的各阶导数,保证形线曲率连续。前缘部分的长度和厚度分布的饱满性可根据设计需求指定。利用该方法对两个来流马赫数分别为075和060的亚声叶型进行前缘优化,数值计算表明：前缘优化后叶型的前缘吸力峰强度大幅降低,削弱了流动扩散造成的逆压梯度,不仅抑制了前缘分离泡的发展,而且避免附面层发生提前转捩,这两个因素使得前缘优化叶型在非设计工况的损失水平大幅降低,可用迎角范围比圆弧前缘叶型扩大了31°和38°。对某跨声速级的前缘亦采用该方法进行改进,转子和整级在近失速点的绝热效率提高了07和11个百分点,并提高了失速裕度。
- 前缘形状 /
- 多项式造型方法 /
- 曲率连续 /
- 吸力峰 /
- 气动性能
Abstract: To optimize the leading edge (LE) shape for improving airfoil aerodynamic performance, a polynomial based continuous-curvature LE design method was proposed. By specifying derivatives of camber-line and thickness distribution at the junction point, the continuous surface curvature was guaranteed. The length and the fullness of the LE portion could be specified according to design need. The method was used to optimize the LE portion of two subsonic airfoils with inlet Mach number of 075 and 060, respectively. Simulations indicated that the LE optimized airfoils had much lower suction spike strength, which decreased the gradient of adverse pressure caused by flow diffusion. Therefore, the LE separation bubble was suppressed and the premature transition of boundary-layer was avoided. Due to these two factors, the LE optimized airfoils had much lower loss level at off-design conditions and the useful operation range were increased by 31°and 38° compared with circular LE airfoil, respectively. The leading edge of a transonic compressor stage was also modified by this method, the increase of adiabatic efficiency for rotor and stage were 07 percent and 11 percent at near stall condition, respectively, with stall margin also extended.
- leading edge shape /
- polynomial methodology /
- continuous-curvature /
- suction spike /
- aerodynamic performance

HTML

参考文献(27)

[1]	WADIA A R,WOLF D P,HAASER F G.Aerodynamic design and testing of an axial flow compressor with pressure ratio of 233:1 for the LM25001 gas turbine［J］.Journal of Turbomachinery,2002,124(4):331-340.
[2]	RECHTER H,STEINERT W,LEHMANN K.Comparison of controlled diffusion airfoils with conventional NACA 65 airfoils developed for stator blade application in a multistage axial compressor［J］.Journal of Engineering for Gas Turbines and Power,1985,107:494-498.
[3]	BIOLLO R,BENINI E.Recent advances in transonic axial compressor aerodynamics［J］.Progress in Aerospace Sciences,2013,56:1-18.
[4]	CARTER A D S.Blade profiles for axial-flow fans,pumps,compressors,etc.［J］.Proceedings of the Institution of Mechanical Engineers,1961,175(1):775-806.
[5]	GOODHAND M N.Compressor leading edge［D］.Cambridge,UK:Cambridge University,2010.
[6]	WALRAEVENS R E,CUMPSTY N A.Leading edge separation bubbles on turbomachinery blades［J］.Journal of Turbomachinery,1995,117(1):115-125.
[7]	陆宏志,吴洋洲,陆利蓬,等.压气机叶片前缘楔形角对前缘分离泡的影响［J］.工程热物理学报,2002,23(5):569-572. LU Hongzhi,WU Yangzhou,LU Lipeng,et al.The inf luence of the compressor blade leading edge wedge angle on the leading edge separation bubble［J］.Journal of Engineering Thermophysics,2002,23(5):569-572.(in Chinese)
[8]	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 Hongzhi,XU Liping.Circular leading edge with a flat for compressor blades［J］.Journalof Propulsion Technology,2003,24(6):532-536.(in Chinese)
[9]	WHEELER A P S,SOFIA A,MILLER R J.The effect of leading-edge geometry on wake interactions in compressors［J］.Journal of Turbomachinery,2009,131(4):041013.1-041013.8.
[10]	GOODHAND M N,MILLER R J.The impact of real geometries on three-dimensional separations in compressors［C］∥Proceedings of ASME Turbomachinery Technical Conference and Exposition:Power for Land,Sea,and Air.Glasgow,UK:ASME,2010:129-138.
[11]	ELMSTROM M E,MILLSAPS K T,Hobson GV,et al.Impact of nonuniform leading edge coatings on the aerodynamic performance of compressor airfoils［J］.Journal of Turbomachinery,2011,133(4):041004.1-041004.9.
[12]	GOODHAND M N,MILLER R J.Compressor leading edge spikes:a new performance criterion［J］.Journal of Turbomachinery,2011,133(2):021006.1-021006.8.
[13]	KULFAN B M.A universal geometry representation method:“CST”［C］∥Proceedings of the 45th AIAA Aerospace Sciences Meeting and Exhibit.Reno,US:AIAA,2007.
[14]	刘宝杰,袁春香,于贤君.前缘形状对可控扩散叶型性能影响［J］.推进技术,2013,34(7):890-897. LIU Baojie,YUAN Chunxiang,YU Xianjun.Effects of leading-edge geometry on aerodynamic performancein controlled diffusion airfoil［J］.Journalof PropulsionTechnology,2013,34(7):890-897.(in Chinese)
[15]	宋寅,顾春伟.叶片前缘形状对压气机气动性能的影响［J］.工程热物理学报,2013,34(6):1051-1054. SONG Yin,GU Chunwei.Effect of leading edge shape on the aerodynamic performance of compressor［J］.Journal of Engineering Thermophysics,2013,34(6):1051-1054.(in Chinese)
[16]	宋寅,顾春伟.曲率连续的压气机叶片前缘设计方法［J］.推进技术,2013,34(11):1474-1481. SONG Yin,GU Chunwei.Continuous curvature leading edge of compressor blading［J］.Journal of Propulsion Technology,2013,34(11):1474-1481.(in Chinese)
[17]	杨炯,宁涛,席平.前缘点曲率可控的曲率连续前缘几何设计［J］.计算机辅助设计与图形学学报,2016,28(7):1195-1200. YANG Jiong,NING Tao,XI Ping.Geometric design of leading edge with specified curvature at leading edge point［J］.Journal of Computer-Aided Design and Computer Graphics,2016,28(7):1195-1200.(in Chinese)
[18]	LANGTRY R B,MENTER F R.Transition modeling for general CFD applications in aeronautics［R］.AIAA 2005-522,2005.
[19]	MENTER F R.Two-equation eddy-viscosity turbulence models for engineering applications［J］.AIAA Journal,1994,32(8):1598-1605.
[20]	SPALART P R,RUMSEY C L.Effective inflow conditions for turbulence models in aerodynamic calculations［J］.AIAA Journal,2007,45(10):2544-2553.
[21]	DENER C,HIRSCH C.IGG-an interactive 3D surface modelling and grid generation system［R］.AIAA-92-0073,1992.
[22]	SHI Hengtao,LIU Baojie,YU Xianjun.Criteria for designing low-loss and wide operation range variable inlet guide vanes［J］.Aerospace Science and Technology,2018,80:177-191.
[23]	BARTHMES S,HANDEL D,NIEHUIS R.2D investigation of the flow through a symmetric variable inlet guide vane:Part 2 numerical analysis［R］.AIAA 2013-3683,2013.
[24]	STEINERT W,EISENBERG B,STARKEN H.Design and testing of a controlled diffusion airfoil cascade for industrial axial flow compressor application［J］.Journal of Turbomachinery,1991,113(4):583-590.
[25]	任平,朱芳,赵连会.跨音轴流压气机气动设计与数值优化［J］.动力工程学报,2015,35(5):373-379. RENG Ping,ZHU Fang,ZHAO Lianhui.Aerodynamic design and numerical optimization of a transonic axial flow compressor［J］.Journal of Chinese Society of Power Engineering,2015,35(5):373-379.(in Chinese)
[26]	金东海,桂幸民.某涡扇发动机多级高负荷风扇/压气机气动性能数值模拟［J］.航空动力学报,2011,26(5):1059-1065. JIN Donghai,GUI Xingmin.Numerical simulation of highly loaded multi-stagefan/compressor of a turbofan engine［J］.Journal of Aerospace Power,2011,26(5):1059-1065.(in Chinese)
[27]	HAN Le,YUAN Wei,WANG Yanrong.Influence of tip leakage flow and ejection on stall mechanism in a transonic tandem rotor［J］.Aerospace Science and Technology,2018,77:499-509.