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施恒涛,刘宝杰,于贤君.基于多项式的曲率连续前缘造型方法及应用[J].航空动力学报,2020,(2):397~409
基于多项式的曲率连续前缘造型方法及应用
Polynomial-based continuous-curvature leading edge design method and its application
投稿时间:2019-07-27  
DOI:10.13224/j.cnki.jasp.2020.02.019
中文关键词:  前缘形状  多项式造型方法  曲率连续  吸力峰  气动性能
英文关键词:leading edge shape  polynomial methodology  continuous-curvature  suction spike  aerodynamic performance
基金项目:国家科技重大专项(2017-Ⅱ-0001-0013)
作者单位
施恒涛 School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics,Beijing 100191,China
 
刘宝杰 School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics,Beijing 100191,China
,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 
于贤君 School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics,Beijing 100191,China
,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 
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中文摘要:
      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。
英文摘要:
      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.
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