固体火箭冲压发动机二次燃烧室流场数值计算和试验研究

NUMERICAL SIMULATION AND EXPERIMENTAL INVESTIGATION ON THE AIRBREATHING COMBUSTOR OF A SOLID PROPELLANT RAMROCKET

关键词:  火箭冲压发动机  冲压进气燃烧室  流动分布  数值计算  发动机试验

Key words:  Rocket ramjet  Ram-air combustor  Flow distribution  Numerical computation  Engine test

摘要:

用二维ｋ－ε湍流模型及简单一步无限快速化学反应模型，对固体火箭冲压发动机二次燃烧室反应流场进行了数值计算，并针对硼推进剂燃烧特性，提出了二次进气的燃烧室设计方案，在此基础上做了试验研究。结果表明，经数值模拟设计的二次燃烧室构型比普通二次燃烧室构型燃烧效率明显提高。

Abstract:

he purpose of this paper is to solve the specific problem of the combustion of boron in solid propellant ramrocket combustor. In this study, the reactingflow field in the combustor is described with two-dimension partial differential equations, k-ε two-equation model.SIMPLE method is adopted in the calculation. Asketch of a combustor with secondary air inlets is gaven and some experimental investigations have been done.The results show that higher combustion efficiency isachieved in the combustor with secondary air inlets than in normal combustor without them.