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。
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.
出处
《火箭推进》
CAS
2010年第3期28-32,共5页
Journal of Rocket Propulsion
关键词
进气道
燃烧室
压力振荡
inlet
combustion chamber
pressure oscillations
