| 马赫数2.5超燃室中超/亚声流流向涡掺混冷态流场数值研究 |
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| 引用本文： | 赵吕顺,单鹏,介克,杨占宇,王洪铭.马赫数2.5超燃室中超/亚声流流向涡掺混冷态流场数值研究[J].空气动力学学报,2009,27(2). |
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| 作者姓名： | 赵吕顺 单鹏 介克 杨占宇 王洪铭 |
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| 作者单位： | 北京航空航天大学能源与动力工程学院,北京,100083 |
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| 基金项目： | 国家自然科学基金，国家自然科学基金重大研究计划子课题 |
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| 摘 要： | 结合实验,对一种带亚声速预燃室和流向涡掺混器的超声速燃烧模型燃烧室,在其进口马赫数为2.5的来流条件下,进行了冷态流场的数值研究.计算与实验得到的燃烧室沿程压力分布相当一致,计算与实验得到的激波结构也基本吻合.计算结果表明:首先,在马赫数2.5的来流条件下,亚燃预燃室易于达到启动状态;其次,流向涡掺混器增强超/亚声速流之间的掺混的效果明显,但其掺混深度尚有限;最后,流向涡掺混的超燃室掺混段有着复杂的激波膨胀波波系,波涡干涉和激波附面层干涉结构.
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| 关 键 词： | 超声速燃烧 预燃室 波瓣掺混器 流向涡掺混 数值模拟 |
Numerical study of the cold flowfield of Mach number 2.5 supersonic combustor with supersonic/subsonic streamwise vortices mixing |
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| ZHAO Lu-shun,SHAN Peng,JIE Ke,YANG Zhan-yu,WANG Hong-ming.Numerical study of the cold flowfield of Mach number 2.5 supersonic combustor with supersonic/subsonic streamwise vortices mixing[J].Acta Aerodynamica Sinica,2009,27(2). |
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| Authors: | ZHAO Lu-shun SHAN Peng JIE Ke YANG Zhan-yu WANG Hong-ming |
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| Institution: | Department of Jet Propulsion;Beijing University of Aeronautics & Astronautics;Beijing 100083;China |
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| Abstract: | With CFD code NUMECA,the 3-D cold flowfield of a supersonic combustor model working at an inlet Mach number 2.5 with a streamwise vortices mixer is studied numerically.The static pressure distribution along the combustor channel and the shock series structure in it are compared with the experiment results.A good agreement is achieved between the simulation and experiment.Three conclusions are summarized.First,the supersonic inlet of the pilot-subsonic combustor can be started at the inlet Mach number 2.5.Se... |
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| Keywords: | supersonic combustion pilot-combustor lobed mixer streamwise vortices mixing CFD simulation |
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