高温升燃烧室贫油熄火稳定性研究  

Research on the lean blow-out stabilities of the high temperature rise combustor

作　　者：刘百麟[1] 林宇震[1] 袁怡祥[1] 刘高恩[1] 胡正义[2] 徐华胜[2] 

机构地区：[1]北京航空航天大学热动力工程研究所,北京100083 [2]中国燃气涡轮研究院,四川成都610500

出　　处：《推进技术》2003年第5期456-459,共4页Journal of Propulsion Technology

摘　　要：高温升(ΔT=1150K)燃烧室的头部采用三级涡流器与单油路预膜气动雾化喷嘴相互匹配。为了分析二者对改善贫油熄火稳定性的最佳匹配,对8组三级涡流器的流量分配和出口角旋向组合不同的匹配方案进行了试验研究。结果表明:三级涡流器的流量分配对贫油熄火有一定影响;而出口角旋向组合则对其影响显著,且最佳旋向组合为第一级右旋45°—第二级左旋40°—第三级左旋40°。此外,最佳匹配方案的贫油熄火稳定性优于基准方案。The dome of the High Temperature Rise (T=1150K.) Combustor (HTRC) was designed with the method of triple swirler coupled with the single prefilm airblast atomization fuel nozzle. To achieve the optimal lean blow-out performance, research was conducted in the investigation, according to air flux distribution and the vane angle. The results show that the air flux distribution has little influence on the lean blow-out of the HTRC, while the vane angle of different stage swirlers in the triple swirler has considerable influences. The most optimal triple swirler configuration are of vane angle 45° on the 1st stage (clockwise), -40° of the 2nd stage and -40° of the 3rd stage (counter-clockwise), respectively. The lean blowout of the most optimal combination of the HTRC in this research is better than that of the based scheme.

关 键 词：航空发动机 燃烧室 贫油 熄火 空气燃料比 

分 类 号：V235.1[航空宇航科学与技术—航空宇航推进理论与工程]