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[1]王玉峰,郭斌,吴宝元.冲压发动机燃烧室压力脉动对进气道的影响分析[J].火箭推进,2010,36(03):28-32.
　Wang Yufeng,Guo Bin,Wu Baoyuan.Effect of ramjet engine chamber pressure oscillation on the inlet work performance[J].Journal of Rocket Propulsion,2010,36(03):28-32.
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冲压发动机燃烧室压力脉动对进气道的影响分析

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 36 期数: 2010年03期 页码: 28-32 栏目: 出版日期: 2010-06-15
Title:
Effect of ramjet engine chamber pressure oscillation on the inlet work performance
文章编号:
(2010)03-0028-0５
作者:
王玉峰; 郭斌; 吴宝元
西安航天动力研究所，陕西 西安 710100
Author(s):
Wang Yufeng;  Guo Bin;  Wu Baoyuan
Xi'an Aerospace Propulsion Institute, Xi'an 710100, China
关键词:
进气道; 燃烧室; 压力振荡
分类号:
V434
文献标志码:
A
摘要:
冲压发动机燃烧室燃烧时产生的振荡会以声波的形式对进气道结尾激波产生干扰。本研究采用数值方法模拟了不同燃烧室压力脉动频率和振幅对进气道工作状态的影响情况。计算模型为轴对称混压式进气道，控制方程采用雷诺平均N-S方程，湍流模型为标准k-ε模型。求解时时间推进采用二阶隐式格式，空间离散采用AUSM格式。计算结果表明，燃烧室压力振荡频率越大进气道结尾激波运动幅度越小，而振荡幅值越大进气道结尾激波的运动幅度越大。
Abstract:
Pressure oscillations induced in ramjet combustion chamber may influence the inlet terminal shockwave. This paper describes numerical simulations of interactions between shockwave and acoustic wave at different oscillation amplitudes and frequencies. The AUSM scheme is used in finite volume method to solve unsteady Navier-Stokes equations. The results show that the response of the terminal shockwave increases with amplitude increasing of the imposed disturbance, but decreases with the frequency increasing.

参考文献/References:

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备注/Memo

收稿日期：2010-０1-05；修回日期：2010-03-05。
作者简介： 王玉峰（1980—），男，硕士，研究领域为火箭发动机系统设计。

更新日期/Last Update: 1900-01-01