壁龛稳焰超声速燃烧室流场的数值模拟

推进技术 ›› 2003, Vol. 24 ›› Issue (6): 521-523.

壁龛稳焰超声速燃烧室流场的数值模拟

李丽,叶中元,刘兴洲

航天科工集团公司31所北京100074;航天科工集团公司31所北京100074;航天科工集团公司31所北京100074

发布日期:2021-08-15

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

The 31st Research Inst., Beijing 100074, China;The 31st Research Inst., Beijing 100074, China;The 31st Research Inst., Beijing 100074, China

Published:2021-08-15

摘要/Abstract

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。

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

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.

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

李丽,叶中元,刘兴洲. 壁龛稳焰超声速燃烧室流场的数值模拟[J]. 推进技术, 2003, 24(6): 521-523.