基于正交试验设计的二次进气燃烧仿真

Numerical Investigation on Second Air Inlet Combustion Based on Orthogonal Test

通过正交试验设计与CFD仿真相结合的方法,采用PDF燃烧模型针对二次进气结构不同参数对补燃室燃烧效率的影响进行了仿真研究。结果表明:1)一次进气角对补燃室燃烧效率影响最大,其余3个因子的影响程度相当;2)在考查参数范围内,采用75°一次进气角、60°二次进气角、250mm一、二次进气间距和1∶1的一、二次进气面积比时补燃室综合性能最好;3)二次进气结构在增强补燃室掺混燃烧的同时会带来一定的总压损失。

By combination of the orthogonal experimental design with CFD simulation,the influences of different parameters such as the first inlet angle,second inlet angle,air inlets distance and inlet area ratio,on the combustion efficiency of solid rocket ramjet were studied using PDF model.It shows that the first inlet angle has a major impact on combustion efficiency;the rest three ones are similar.Among the studied parameters,the first inlet with 75°,second inlet angle with 60°,air inlet distance with 250mm and inlet area ratio with 1∶ 1 obtains the best performances.Total pressure loss when it is enhancing mixing and combustion in afterburning chamber using secondary air inlets.