多孔介质结构参数对表面火焰熄火特性的影响  

Effect of porous media structure parameters on surface flame blow-out performance

作　　者：张龙[1] 许全宏[1] 张弛[1] 林培华[1] 林宇震[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院航空发动机气动热力国家级重点实验室,北京100191

出　　处：《航空动力学报》2014年第7期1654-1659,共6页Journal of Aerospace Power

摘　　要：为优化基于多孔介质头部的微型燃烧室,以甲烷/空气预混气为燃料,针对多孔介质结构参数(当量孔径、孔隙率)在不同预混气初始温度下,对表面火焰熄火特性进行实验研究.研究表明:当量孔径为120μm的多孔介质表面火焰两侧同时发生脱火,当量孔径为80μm时先发生一侧脱火.随孔隙率或当量孔径的减小,熄火速度提升.当量孔径为80μm,孔隙率为0.55,0.50,0.45的多孔介质在当量比为1.0,预混气初始温度为300K时的熄火速度分别为1.11,1.22,1.31m/s.孔隙率为0.50,孔径为120,80μm的多孔介质在当量比为1.0,预混气温度为300K时的熄火速度分别为0.73,1.22m/s.预混气初始温度的升高对当量孔径为120μm或孔隙率为0.45的多孔介质影响更加明显,预混气初始温度从300K升至500K时,熄火速度分别增加了120%,76%.To optimize a micro combustor with dome made of porous media,the influences of porous media structure parameters（equivalent aperture,porosity）on the surface flame blow-out performance were investigated experimentally under different premixed gas initial temperatures.Methane and air premixed gas was used as fuel in this experiment.The results show that both two sides of the porous media surface flame go out at the same time when equivalent aperture equals 120μm.One side goes out firstly when equivalent aperture equals 80μm.With the decrease of equivalent aperture or porosity,equivalent ratio equals1.0,premixed gas initial temperature equals 300K,the blow-out velocity increases.When equivalent aperture equals 80μm,and porosities equal 0.55,0.50 and 0.45,the blow-out velocities of porous media surface flame turn out to be 1.11,1.22 and 1.31m/s,respectively.When porosity equals 0.50,and equivalent apertures equal 120,80μm,equivalent ratio equals 1.0,premixed gas initial temperature equals 300K,the blow-out velocities turn out to be 0.73m/s and 1.22m/s,respectively.The increase of premixed gas initial temperature has obvious influence on porous media with equivalent aperture of 120μm or porosity of 0.45.When thepremixed gas initial temperature increases from 300K to 500K,the blow-out velocities increase by 120% and 76%,respectively.

关 键 词：微型燃烧室 多孔介质 当量孔径 孔隙率 预混气初始温度 熄火特性 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程]