航空发动机燃烧室的现状和发展  

Status and Development of Aeroengine Combustors

作　　者：张宝诚[1] 

机构地区：[1]沈阳航空航天大学航空航天学部,沈阳110136

出　　处：《航空发动机》2013年第6期67-73,共7页Aeroengine

摘　　要：论述了燃烧室设计中各项技术指标的相互制约,分析了第3、4代发动机燃烧室的技术特点和燃烧室设计及研究方法的新进展。较详细介绍了驻涡(TVC)、富燃-快掺混-贫燃(RQL)、双环腔预混旋流(TAPS)、多喷嘴单元体和陶瓷燃烧室,指出其适用性。主动燃烧控制中更为主要的是出口温度分布系数控制,长远研究应开发快速、灵敏、配置严格的油气管理系统。最后讨论了燃用液氢的可行性。建议应加快CCD与燃烧室目标设计相结合的研发过程。The interactions of various technical targets in combustor design were demonstrated. The technical characters of the 3th--4th generation engine combustors and new advances of the combustor designs and the development methods were analyzed. The trapped vortex combustor, the rich queanch lean combustor, the twin annular premixing swirler combustor, the multiple-injectors-units, and the ceramic combustors were introduced in more detail, denoting their suitabilities. The temperature distributive coefficient control at the combustor outlet are more importance in the active combustion control, and the long-term research shall develop a fast, sensitive and strict disposed system of the fuel-air management. The feasibility with the burning of liquid hydrogen was discussed. The development process of the interactive binding of CCD with the combustor target design should be promoted.

关 键 词：航空发动机 燃烧室 主动燃烧控制 氢燃烧 计算燃烧动力学 

分 类 号：U467.42[机械工程—车辆工程]