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[1]李永洲,刘晓伟,张蒙正,等.马赫数2.5~7.0的二元变几何进气道设计[J].火箭推进,2015,41(05):17-22.
　LI Yongzhou,LIU Xiaowei,ZHANG Mengzheng,et al.Design of a two dimensional variable geometry inlet with Mach number 2.5~7.0[J].Journal of Rocket Propulsion,2015,41(05):17-22.
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马赫数2.5~7.0的二元变几何进气道设计

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 41 期数: 2015年05期 页码: 17-22 栏目: 研究与设计 出版日期: 2015-10-31
Title:
Design of a two dimensional variable geometry inlet with Mach number 2.5~7.0
作者:
李永洲;  刘晓伟; 张蒙正; 南向军
西安航天动力研究所，陕西 西安 710100
Author(s):
LI Yongzhou;  LIU Xiaowei;  ZHANG Mengzheng;  NAN Xiangjun
Xi’an Aerospace Propulsion Institute, Xi’an 710100, China
关键词:
RBCC; 高超声速进气道; 宽马赫数; 变几何; 数值仿真
Keywords:
RBCChypersonic inletwide mach number rangevariable geometrynumerical simulation
分类号:
V235.213-34
文献标志码:
A
摘要:
针对RBCC发动机Ma=2.5~7.0的宽范围工作要求，提出了一种部分顶板转动+唇口平移的二元进气道变几何方案，并通过数值仿真对其总体性能和调节方法进行了研究。结果表明：采用激波依次封口设计概念的变几何进气道在高低马赫数下的总体性能较优，尤其具有良好的流量捕获能力。转动部分顶板的变几何方案拓宽了进气道工作范围，向后平移唇口可以实现超额定工况的起动和Ma=2.3的自起动。变几何进气道的调节方法简单、工程应用可行。
Abstract:
A scheme of two-dimensional RBCC variable-geometry inlet with rotating partial top wall and translating cowl is proposed for the RBCC engine with a wide Mach number range from 2.5 to 7.0. The general performance and adjusting method are studied by the numerical simulation. The results show that the general performance of variable-geometry inlet is better in the entire operating range while shock waves seal the cowl in turn in this design concept. Especially, it has nice flow capture ability. In addition, the operating range is broaden by rotating partial top wall, and the inlet is able to start under the over rated condition and at Ma=2.3 by the backward translating cowl. The adjusting method is simple and feasible in engineering application.

参考文献/References:

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备注/Memo

收稿日期：2015-06-02；修回日期：2015-07-15 基金项目：国家863项目（2010AA702308） 作者简介：李永洲（1984—），男，博士，研究领域为高超声速推进技术

更新日期/Last Update: 1900-01-01