进气温度对航空发动机燃烧室辐射换热的影响  

Influence of Inlet Air Temperature on Radiation Heat Transfer for Aeroengine Combustor

作　　者：王成军[1] 江平[1] 辛欣[1] 曾文[1] 

机构地区：[1]沈阳航空航天大学航空航天工程学部,沈阳110136

出　　处：《航空发动机》2013年第5期31-33,59,共4页Aeroengine

摘　　要：为了解燃烧室内火焰辐射换热特性,建立了某型航空发动机燃烧室计算模型,利用数值模拟方法,研究了不同进气温度下燃烧室内燃气温度、碳黑粒子生成及分布变化对燃烧室辐射热流量和火焰筒壁温的影响。研究结果表明:随着进气温度的升高,燃气温度升高,碳黑粒子质量分数增大,且高温区和碳黑粒子生成区均往前移;火焰筒壁温急剧升高,高温区集中在燃烧室中间段和掺混段,主燃区火焰筒壁温相对较低;辐射热流量不断增加,由3245 W增加到8674 W,辐射热流量主要受燃气辐射特性影响。In order to understand the the combustor flame radiation transfercharacteristics, the calculation model of an aeroengine combustor was buih using numerical simulation method. The influence of combustor gas temperature, soot generation and distribution change on combustor radiant heat flux and liner wall temperature were studied under the different inlet air temperature. The results show that gas temperature and soot concentration increases, while the high temperature and high soot generation area all move forward with the inlet air temperature rise. The liner wall temperature has increased dramatically, and the high temperature area is concentrated on the combustor intermediate section and mixing section, the wall temperature in main combustion zone is relatively low. Radiation transfer increased by 3245 W to 8674 W, and radiation heat transfer rate is mainly affected by gas radiation properties.

关 键 词：燃烧室 辐射换热 进气温度 数值模拟 航空发动机 火焰筒壁温 

分 类 号：TK421.5[动力工程及工程热物理—动力机械及工程]