冲压发动机进气道压力振荡过程的数值研究

推进技术 ›› 2008, Vol. 29 ›› Issue (5): 562-565.

冲压发动机进气道压力振荡过程的数值研究

白晓征,刘君,郭正,王巍

国防科技大学航天与材料工程学院;国防科技大学航天与材料工程学院;国防科技大学航天与材料工程学院;国防科技大学航天与材料工程学院

发布日期:2021-08-15
基金资助:
国家自然科学基金(90505003;10602064)

Numerical simulation of pressure oscillation in ramjet inlet

Inst.of Aerospace and Material Engineering,National Univ.of Denfence Technology,Changsha 410073,China;Inst.of Aerospace and Material Engineering,National Univ.of Denfence Technology,Changsha 410073,China;Inst.of Aerospace and Material Engineering,National Univ.of Denfence Technology,Changsha 410073,China;Inst.of Aerospace and Material Engineering,National Univ.of Denfence Technology,Changsha 410073,China

Published:2021-08-15

摘要/Abstract

摘要： 针对来流马赫数3.5,0°迎角飞行条件下冲压发动机的简化模型,数值模拟了进气道整流罩开启过程的非定常流动。计算采用AUSMPW有限体积格式,基于结构与非结构的混合网格技术,求解了非定常N-S方程。计算结果表明,在进气道整流罩打开以后,超声速气流会在燃烧室通道内形成振幅衰减较慢的低频剧烈振荡。在同样计算条件下采用Euler方程进行对比性研究,数值实验发现对这类大雷诺数、强非定常性的问题,Euler方程和N-S方程得到的结果相差不大。

关键词: 超声速冲压喷气发动机;非定常流;进气道;数值仿真

Abstract: Unsteady flows in the opening of inlet cover are investigated numerically,based on a simplified ramjet model with a Mach number 3.5 and angle of attack 0.The AUSMPW scheme is used in finite volume method to solve unsteady Navier-Stokes equations on mixed structured-unstructured grids.The results demonstrated that supersonic airflows will form a low-frequency oscillation in the combustor after the inlet cover is open,and the attenuation of the oscillation is very slow.To be a contrast,Euler equations were solved in the same condition,and the numerical experiments demonstrated that for such strongly unsteady flows with a high Reynold number,the Euler solution is comparable to the N-S solution.

Key words: Supersonic combustion ramjet engine;Unsteady flow;Inlet;Numerical simulation

白晓征,刘君,郭正,王巍. 冲压发动机进气道压力振荡过程的数值研究[J]. 推进技术, 2008, 29(5): 562-565.