摘要
用FLUENT软件对安装开式壁龛(长深比L/D<10)的超燃冲压发动机燃烧室内的高速可压缩流动进行冷态数值模拟,以方便处理试验结果。控制方程为二维N S方程,湍流模型采用剪切修正的k ω模型。结果证明:在飞行马赫数Ma=4的情况,安装壁龛稳定器可以达到掺混和稳定的目的,而且不会引起很大的总压损失。
Numerical simulation of the inner supersonic compressible flow in a scramjet combustor with open cavities was carried out using FLUENT software to dispose the process of the experimental data. The mass-averaged Navier-Stokes equations were solved. A κ-ω turbulence model was used with shear correction. Stable flow and high-speed mixing with low total pressure loss were obtained in the condition of flight Mach number 4.0.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2003年第6期521-523,共3页
Journal of Propulsion Technology
关键词
冲压喷气发动机
燃烧室
超音速燃烧
可压缩流
剪切层
数值仿真
Combustion chambers
Combustors
Compressible flow
Computer simulation
Mathematical models
Navier Stokes equations
Supersonic flow
Turbulent flow
