Steady numerical study of aerodynamic throat formed by round injectors

XIE Kan; LIU Yu; WANG Yi-bai

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Steady numerical study of aerodynamic throat formed by round injectors

更新时间：2026-07-07

- Steady numerical study of aerodynamic throat formed by round injectors
- Vol. 26, Issue 4, (2011)
- 作者机构：
  
  北京航空航天大学宇航学院,北京,100191
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2011
- 稿件说明：
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XIE Kan, LIU Yu, WANG Yi-bai. Steady numerical study of aerodynamic throat formed by round injectors[J]. 2011, 26(4).
DOI：

XIE Kan, LIU Yu, WANG Yi-bai. Steady numerical study of aerodynamic throat formed by round injectors[J]. 2011, 26(4). DOI：

摘要

对固体火箭发动机上由圆孔喷嘴喷入二次流所形成的气动喉部进行了三维数值模拟.考察了圆孔喷嘴形成气动喉部的典型三维流动特征和喷嘴流量特性.研究了不同喷嘴面积比、喷嘴个数、喷射角度、喷嘴构型及主要喷管参数对气动喉部调节喉部面积能力的影响.结果表明在相同的喷嘴面积比下

增加喷嘴个数、采用逆向喷射或选用收缩喷嘴构型都能显著提高气动喉部的扼流性能.

Abstract

A three-dimensional (3-D) numerical simulation of aerodynamic throat formed by secondary flow from round injectors

which was applied to solid propellant rocket motors

was performed in this paper.The typical 3-D flow structure and mass flow character of round injectors were reviewed.The influence of different injector area ratios

injector numbers

injection angles

injector types and major nozzle parameter were studied.The results show that the mass control performance of aerodynamic throat can be obviously improved by increasing injector numbers

applying reverse injection or convergence injector type at the same injector area ratio.

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Related Institution

National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics,School of Jet Propulsion, Beijing University of Aeronautics and Astronautics

School of Aerospace Engineering, Beijing Institute of Technology

Institute of Engineering Thermophysics, Chinese Academy of Sciences

Graduate University of Chinese Academy of Sciences

Institute of Turbomachinery.Xi'an Jiaotong University

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