驻涡加力燃烧室贫油熄火性能的影响

为了研究驻涡加力燃烧室的贫油熄火性能，设计了三种不同方案的凹腔结构，进行了贫油熄火（LBO）性能试验。采用航空煤油作为燃料，试验中的主要研究参数如下:外内涵进气压比在0.97~1.07之间变化；主流马赫数在0.13~0.20之间变化。研究结果表明:驻涡加力燃烧室贫油熄火油气比随着外内涵进气压比的增加而增加，随着主流马赫数的增大而增加，并且在马赫数较大时，变化幅度增大；在驻涡区上部分区域，轴向平均绝对速度越小，以及主涡涡心位置在一定范围内更贴近凹腔后壁面，驻涡加力燃烧室的贫油熄火性能更优。 

Effect of lean blowout performance of trapped vortex combustor of the afterburner

Three different schemes of cavity structure were designed to study the lean blowout （LBO） performance by test research method.Aviation kerosene was employed as fuel.In all operating conditions，the inlet pressure ratio of out and inner bypass varied from 0.97-1.07 and the mainstream Mach number ranged from 0.13-0.20.It was revealed that the fuel air ratio of lean blowout increased with the increasing inlet pressure ratio of out and inner bypass.LBO also increased with the increasing mainstream Mach number，and when the mainstream Mach number was larger，the increase was larger.In upper region of the vortex，the axial average of absolute velocity decreased，and the positon of the main vortex center was closer to the after wall of the cavity within a certain range，and the lean blowout performance of trapped vortex combustor of the afterburner was excellent.