为了研究单凹腔驻涡燃烧室的点火和贫油熄火特性，设计了一个带扩压器和内外机匣的单凹腔驻涡燃烧室矩形试验件，采用试验研究和半经验分析相结合的方法对其点火和贫油熄火进行了研究。试验在常压状态下进行，采用 RP3航空煤油作为燃料，所用供油喷嘴为空心锥离心喷嘴，试验中的进口空气温度在 287～487K变化，进口空气流量在 0.2109～0.4219kg/s变化，对应进口马赫数从 0.15变化到 0.31。结果表明:单凹腔驻涡燃烧室的点火和贫油熄火油气比均随着燃烧室进口温度和进口流量的增加而减小，单凹腔驻涡燃烧室的点火油气比比贫油熄火油气比约大 50%。经过半经验分析，得到了影响单凹腔点火和熄火的综合参数A，该参数能够较好地解释和评价各种因素对贫油熄火的影响。

A rectangular single-cavity trapped vortex combustor(STVC)comprising casing and diffuser was designed，and ignition and lean blowout characteristic experiments were accomplished at atmospheric pressure， and semi-analytical results were obtained. Aviation kerosene RP3 was employed as fuel，and cone-shaped pres. sure swirl atomizer was used for fuel supply. In all the operating conditions，inlet temperature of the combustor varies from 287K up to 487K，and inlet air mass flow rate ranges from 0.2109kg/s up to 0.4219kg/s，the corre. sponding Mach number ranges from 0.15 to 0.31. It is revealed that the fuel air ratios of ignition and lean blowoutdecrease while inlet temperature and air mass flow rate increase，and the former is approximately 50% more than the latter. A synthesized parameter，that affects ignition and lean blowout characteristics of the single-cavity trapped vortex combustor，is derived in a semi-empirical method. This parameter can well interpret and estimatethe effects of various factors on lean blowout.

V231.3

江苏省普通高校研究生科研创新计划资助项目( CXLX12_0167)