涡轮燃烧技术在涡扇航空发动机上的应用分析  

Performance study of technology of combustion inside turbine using in fanjet

作　　者：李建锋[1] 吕俊复[2] 

机构地区：[1]中国电力企业联合会科技服务中心,北京100038 [2]清华大学热科学与动力工程教育部重点实验室,北京100084

出　　处：《空气动力学学报》2010年第3期358-363,共6页Acta Aerodynamica Sinica

基　　金：国家重点基础研究发展规划项目(200026309)

摘　　要：分析了采用涡轮燃烧技术后的涡扇航空发动机的性能。分析结果表明:采用了涡轮燃烧技术以后,航空发动机的效率、推重比都得到了较大的提高。同时分析了采用涡轮燃烧的两种技术方案:一种是在静叶片间安装喷嘴,属于多级燃烧技术;一种是将整个涡轮作为一个大燃烧室,类似于高温空气燃烧技术。Through analyzed performance of fanjet adopted technology of combustion inside turbine,the results showed that the thermal-efficiency and the thrust of the fanjet were both increased after technology of combustion inside turbine being used. Two technical schemes of combustion inside turbine were analyzed similarly,the fuel nozzles were installed in stationary blades was a sort of schemes and the turbine as a big combustion chamber was the other one, the former one belongs to the technology of multilevel combustion and the latter belongs to high temperatureair combustion technology.

关 键 词：涡扇航空发动机 涡轮燃烧 效率 推力 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]