Numerical Study on the Performance of a High Temperature Rise Combustor

摘要：

　　A new high temperature rise combustor is designed for the thermal performance requirement of high engine thrust-to-weight ratio aircraft engine,with staging,multi-point injection,effusion cooling technology and without primary holes.Numerical simulation was conducted to study the performance of the combustor.Results show the combustor could work well under high fuel-air ratio,with combustion efficiency of 99%,total pressure loss of 5%and liner wall temperature of 1150 K.The velocity field characteristics,exit temperature profiles and emissions also are good.

关键词： Combustor High temperature rise Effusion cooling Multipoint Injection Numerical simulation

作者: YANG Xiong SUO Jian-qin LI Ming LIANG Hong-xia

作者单位: School of Power and Energy,Northwestern Polytechnical University,Xian 710072,China School of Power and Energy,Northwestern Polytechnical University,Xian 710072,China;Collaborative In

会议类型: 国际会议

会议名称: The 5th International Symposium on Jet Propulsion and Power Engineering(第五届喷气推进与动力工程国际会议)

会议地点: 北京

会议语种:英文

页码: 1-7

在线出版日期: 2014-09-15（万方平台首次上网日期，不代表论文的发表时间）