超燃冲压发动机凹腔稳焰的数值模拟  

Numerical Simulation of the Flow Field in Scramjet

作　　者：杨事民[1] 唐豪[1] 黄玥[1] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《飞机设计》2007年第6期47-51,共5页Aircraft Design

基　　金：国家863基金资助项目(2004AA723020)

摘　　要：采用迎风格式数值模拟带凹腔(L/D=4)的超燃冲压发动机燃烧室内的高速可压缩流动,首先采用二阶NND格式对欧拉方程进行冷态数值模拟,以更清楚的捕捉、分析激波的特点;然后采用迎风三阶精度MUSCL格式求解二维N-S方程,湍流模型采用剪切修正的k-ω模型,对喷氢燃烧工况进行数值模拟。结果证明,凹腔可以达到掺混和稳定燃烧的目的,冷态时,总压损失较大,但喷氢燃烧降低了马赫数,减小了激波强度,实际工作状况凹腔不会引起很大的总压损失。Numerical simulation of the inner supersonic compressible flow in a scramjet combustor with two cavities was carried out using up-wind. The numerical simulation in cold state for Euler equations was carried out using the NND scheme to catch shocks and analyze shock characteristics clearly; Then, the numerical simulation in hydrogen spraying burning for Navier-Stokes equations was carried out using the third-order MUSCL scheme. A k-ω turbulence model was used with shear correction. It was concluded that stable flow and high speed mixing were obtained with two cavities, and the total pressure loss was higher for the cold state, but actual operation in the cavities resulted in lower total pressure loss, because roach numbers were decreased and shock intensities were reduced for the burning state.

关 键 词：燃烧室 激波系 剪切层 总压损失 数值模拟 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]