摘要
燃烧室中压力振荡可能会造成发动机及飞行器的不稳定工作。喷管作为发动机主要部件之一,对压力振荡存在着重要影响。文中主要研究了潜入式喷管所引入的空腔体积及其入口形状对燃烧室中压力振荡的影响,发现空腔对压力振荡的振幅和频率均具有调节作用,也验证了潜入式喷管的空腔体积与压力振荡幅值之间的近似线性关系。与潜入式喷管空腔的入口形状相比,空腔体积对压力振幅的影响较大。结论可为大型固体火箭发动机潜入式喷管的设计提供参考。
Pressure oscillation in combustion chamber could induce the unstable operation of motors or missiles.Nozzle,as a main part of motor,possesses great influence on pressure oscillation.The linear relationship between the pressure oscillation amplitude and the volume of cavity induced by submerged nozzle is validated in this paper using large eddy simulations.The effect of cavity volume on pressure oscillation amplitude is found to be larger than that of the cavity inlet geometry.The vortex-acoustic interaction is examined.The impingement of vortex on submerged nozzle serves as one of most important parts in vortex-acoustic interaction.The conclusion can be used as a reference for design of submerged nozzle of large solid rocket motor.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2010年第3期252-255,269,共5页
Journal of Solid Rocket Technology
基金
国家自然科学基金资助项目(10602047)
关键词
火箭发动机
压力振荡
潜入式喷管
大涡模拟
rocket motor
pressure oscillation
submerged nozzle
large eddy simulation
