北京航空航天大学学报 ›› 2018, Vol. 44 ›› Issue (11): 2267-2272.doi: 10.13700/j.bh.1001-5965.2018.0161

• 论文 • 上一篇    下一篇

激波诱导推力矢量喷管不同气体喷注时的性能分析

王晓明1, 刘辉2, 韩龙柱3,4, 袁修干1   

  1. 1. 北京航空航天大学 航空科学与工程学院, 北京 100083;
    2. 中国航发商用航空发动机有限责任公司, 上海 200241;
    3. 北京航空航天大学 生物与医学工程学院, 北京 100083;
    4. 北京航空航天大学 生物医学工程高精尖创新中心, 北京 100083
  • 收稿日期:2018-03-26 修回日期:2018-04-08 出版日期:2018-11-20 发布日期:2018-11-27
  • 通讯作者: 韩龙柱,E-mail:hlz@buaa.edu.cn E-mail:hlz@buaa.edu.cn
  • 作者简介:王晓明,男,博士研究生。主要研究方向:人机环境工程;韩龙柱,男,博士,讲师,硕士生导师。主要研究方向:人机环境工程。
  • 基金资助:
    国家自然科学基金(11772038)

Performance analysis of shock thrust vector nozzle under different gas injections

WANG Xiaoming1, LIU Hui2, HAN Longzhu3,4, YUAN Xiugan1   

  1. 1. School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;
    2. AECC Commercial Aircraft Engine Co., Ltd., Shanghai 200241, China;
    3. School of Biological Science and Medical Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;
    4. Beijing Advanced Innovation Center for Biomedical Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
  • Received:2018-03-26 Revised:2018-04-08 Online:2018-11-20 Published:2018-11-27
  • Supported by:
    National Natural Science Foundation of China (11772038)

摘要: 针对激波诱导推力矢量控制研究仅限于主流和次流气体为同种气体的研究现状,开展了不同次流气体分子质量对推力矢量性能的影响规律研究。首先采用二阶精度AUSM+格式和k-ω SST两方程湍流模型求解三维Favre平均Navier-Stokes方程,模拟了喷管复杂干扰内流场。然后计算了He、N2和CO2等次流气体在不同注气角度、注气压力和主流落压比下的矢量偏转角度和推力系数。计算结果表明:平均分子质量越小的次流气体矢量偏转角度越大,推力损失越小。因此可选用平均分子质量小的气体作为次流气源,或者将从燃烧室引出的高温燃气与分子质量小的气体混合。

关键词: 推力矢量喷管, 推力系数, 矢量偏转角, 多组分, 数值模拟

Abstract: Aimed at the research status of the shock thrust vector control, which is limited to the mainstream and secondary flow gas as the same gas, the influence of different secondary flow gas molecular mass on thrust vector performance is investigated. First, a turbulence model described by two equations (AUSM+ scheme and k-ω SST) at two-order accuracy was utilized to solve the Favre averaged three-dimensional Navier-Stokes equations, which simulated the complex interference inner flow field of the nozzle, and the vectorial deflection angles and thrust coefficients were calculated under different gas injection angles, injection pressures and nozzle pressure ratios when the secondary flow gas of He, N2 and CO2 were selected. The calculation results show that the smaller the mean molecular mass of the secondary flow gas is, the larger the vectorial deflection angle is, the less the thrust loss is. Therefore, the gas with smaller mean molecular mass could be used as the gas source of the secondary flow, or the high temperature gas derived from the combustion chamber could be mixed with the gas with a smaller mean molecular mass.

Key words: thrust vector nozzle, thrust coefficient, vectorial deflection angle, multicomponent, numerical simulation

中图分类号: 


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