摘要
采用试验方法研究了一种适用于切向驻涡燃烧室的自稳火双旋流杯在非受限空间内的燃烧特性.自稳火双旋流杯的方案特点是采用两级径向旋流器,燃油从中心离心喷嘴喷出,根据旋流器旋流强度和气量分配形成不同布局形式.在常温常压条件下,以RP-3航空煤油为燃料,测量了三种结构的自稳火双旋流杯火焰特性以及贫油熄火油气比,结果表明:随着内旋流器气量减少和旋流数增加,火焰稳定性将有所增强,但火焰长度及总体形状没有变化.
The combustion characteristics of the self-stabilized dual-swirler cup in the unconfined case, which is suitable for the tangential trapped vortex combustor, were investigated experimentally. The self-stabilized dual-swirler cup is characterized in that, the dual- swirler with radial holes is employed, and the fuel sprays from a pressure nozzle in the cen- ter. According to the different swirl numbers and air flux distributions of the swirler, different layouts are developed. In the experiment under normal temperature and pressure, RP-3, for example, was used as the fuel. Results show that, the flame stability increases and the length and shape of the flame remain unchanged with the decrease of the air flux distribution of the internal swirl and increase of its swirl number.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2008年第10期1778-1782,共5页
Journal of Aerospace Power
关键词
燃烧特性
航空发动机
切向驻涡燃烧室
双旋流杯
离心喷嘴
贫油熄火
combustion characteristics
aircraft engine
tangential trapped vortex combustor
dual swirler cup
pressure nozzle
lean blowout
