摘要
为了给出航空发动机折流燃烧室火焰筒的构型设计方法,按照总体尺寸设计和具体构型设计的步骤进行,对折流燃烧室进行初步设计,依次进行一维流量分配计算和三维流场计算,结果满足初步设计的流量分配预期结果和燃烧效率与总压恢复系数要求。
The configuration design method of the aeroengine slinger combustion flame tube is defined and arranged according to the steps of overall size design and specific configuration design. The preliminary design of the slinger combustion chamber is carried out, and one-dimensional flow distribution calculation and three-dimensional flow field calculation are carried out in sequence The results prove that the expected results of the preliminary design of flow distribution and the requirements of combustion efficiency and total pressure recovery coefficient are both met.
作者
孟繁睿
雷雨冰
MENG Fanrui;LEI Yubing(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)
出处
《机械制造与自动化》
2022年第5期44-47,共4页
Machine Building & Automation
关键词
航空发动机
折流燃烧室
设计
程序开发
aircraft engine
slinger combustion chamber
design
development of program
