壁龛稳焰超声速燃烧室流场的数值模拟

Numerical simulation for flow in a supersonic combustor with cavity flame holders

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

Key words:  Ramjet engine  Combustion chamber  Supersonic combustion  Compressible flow  Shear layer  Numerical simulation

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。

Abstract:

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 k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 fight Mach number 4.0.