| 亚声速进气道出口流场畸变控制研究 |
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| 引用本文： | 王健,李应红,张百灵.亚声速进气道出口流场畸变控制研究[J].推进技术,2010,31(2):143-146. |
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| 作者姓名： | 王健 李应红 张百灵 |
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| 作者单位： | 空军工程大学,工程学院,陕西,西安,710038 |
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| 基金项目： | 空军重点科研项目; 空军工程大学工程学院优秀博士学位论文创新基金项目(BC08001) |
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| 摘 要： | 一种亚声速进气道出口流场存在较严重的总压畸变,为改善其出口流场品质,抑制总压畸变,首先分析了引起总压畸变的原因,即进气道扩张段内边界层发生分离;其次提出了在进气道内安装叶片式涡流发生器的流动控制方法,并进行了仿真验证;最后进行了进气道缩比模型的风洞试验。试验结果表明,在进气道设计马赫数(0.65)和非设计马赫数(0.21)条件下,安装叶片式涡流发生器后,在流量系数0.4～0.85范围内,进气道出口流场的综合畸变指数分别平均降低14.7%和23.8%,因此验证了流动控制方法的有效性。
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| 关 键 词： | 涡轮喷气发动机 进气道 进气道畸变 边界层分离 风洞试验 |
Investigation on flow distortion control of a subsonic inlet |
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| WANG Jian,LI Ying-hong and ZHANG Bai-ling.Investigation on flow distortion control of a subsonic inlet[J].Journal of Propulsion Technology,2010,31(2):143-146. |
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| Authors: | WANG Jian LI Ying-hong and ZHANG Bai-ling |
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| Institution: | WANG Jian,LI Ying-hong,ZHANG Bai-ling(Engineering Inst.,Air Force Engineering Univ.,Xi\'an 710038,China) |
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| Abstract: | In order to suppress the total pressure distortion at the exit plane of a subsonic inlet,the cause was analyzed and it indicated that the boundary layer separated severely in the inlet diffuser section. Then the flow control method of vane-type vortex generators (VG) was proposed,and the simulation results showed that vane-type VG were effective to suppress flow separation. Finally,the wind tunnel experiment of inlet scale model with or without vane-type VG was developed. When operating at design Mach numbe... |
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| Keywords: | Turbojet engine Inlet Inlet distortion Boundary layer separation Wind tunnel test |
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