北京航空航天大学学报 ›› 2015, Vol. 41 ›› Issue (12): 2356-2362.doi: 10.13700/j.bh.1001-5965.2014.0792

• 论文 • 上一篇    下一篇

超声速气流中液体横向射流的破碎特性

李锋1, 吕付国1, 罗卫国1, 赵凯1,2, 王昌胜1, 熊溢威1   

  1. 1. 北京航空航天大学 能源与动力工程学院, 北京 100191;
    2. 空军航空大学, 长春 130022
  • 收稿日期:2014-12-16 修回日期:2015-03-20 出版日期:2015-12-20 发布日期:2016-01-04
  • 通讯作者: 李锋(1966-),男,教授,主要研究方向为计算燃烧学、燃气轮机单/双环腔燃烧室设计及低污染技术、亚燃及超燃冲压发动机燃烧技术导弹红外隐身技术研究、等离子流动控制及推力矢量技术研究和脉冲发动机设计技术研究. E-mail:lifeng1966@263.net

Breakup characteristics of liquid jet in supersonic cross flow

LI Feng1, LYU Fuguo1, LUO Weidong1, ZHAO Kai1,2, WANG Changsheng1, XIONG Yiwei1   

  1. 1. School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;
    2. Aviation University of Air Force, Changchun 130022, China
  • Received:2014-12-16 Revised:2015-03-20 Online:2015-12-20 Published:2016-01-04

摘要: 为了研究超燃冲压发动机燃烧室内液体燃料雾化掺混特性,确定影响雾化的关键因素以实现高效燃烧,在超燃冷态雾化实验平台,以纹影法为主,同时辅助以平面激光诱导荧光(PLIF)技术和基于向前散射原理的颗粒直径测量技术,分别对横向射流航空煤油RP-3和水在超声速气流中的流场波系结构、射流穿透深度和诱导弓形激波强度等进行了实验研究,并对射流雾化掺混特性进行了数理分析.结果表明:定义的无量纲参数能够定性分析两种液体横向射流在超音速流场中的变化规律,并得到与实验结果一致的结论;在动压比1.0~3.3范围内,射流穿透深度和诱导弓形激波强度随着动压比和射流速度的增加而增加;表面张力和黏度对超声速射流掺混有重要影响.

关键词: 超燃冲压发动机, 横向射流, 纹影法, 平面激光诱导荧光(PLIF), 雾化

Abstract: In order to study the atomization mixing characteristics of liquid fuel in scramjet combustor as well as determine the key factors influencing the atomization so as to realize efficient combustion, the flow field structure of the shock wave, jet penetration and induced bow shock strength of liquid jet aviation kerosene RP-3 and water in supersonic flow were experimentally studied respectively by mainly using the schlieren method,assisted with planar laser induced fluorescence (PLIF) technology and particle diameter measurement technology in supersonic combustion cold spray experiment platform. And jet atomization mixing characteristics were mathematically analyzed. It is demonstrated that defined dimensionless parameters could qualitative analyze variation trend associated with both two kinds of liquid jet in supersonic cross flow, and the conclusion is consistent with the experimental result. Within the scope of the dynamic pressure ratio of 1.0-3.3, the jet penetration and induced bow shock strength increases with the increase of dynamic pressure ratio and jet velocity. Surface tension and viscosity have important effects on the supersonic jet mixing.

Key words: scramjet, traverse jet, schlieren method, planar laser induced fluorescence (PLIF), atomization

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