摘要
贫油熄火极限是衡量航空发动机燃烧室性能的重要参数之一。针对多级旋流燃烧室,对经典的Lefebrve熄火模型进行了验证,加入旋流雾化对熄火的影响,结合旋流雾化的燃油平均滴径公式使得计算熄火极限更简便。设计了一套三级旋流燃烧室单头部实验件,搭建实验台并进行常压熄火实验,结合实验结果对改进的熄火模型进行了验证。同时对临近熄火过程中燃烧室流场进行了数值模拟,重点对熄火过程中回流区核心内关键特征参数进行了研究,总结了这些特征参数的变化规律,辅助分析燃烧室的贫油熄火极限。
Lean blowout is one of the most important parameter to evaluate the performance of the gas turbine combustor. This paper fo- cusing on a multi-swirled gas turbine combustor, verify and improve the classical lean blowout model advanced by A. H. Lefebrve. The influence of swirled atomization on the lean blowout is taken into account to make the improved model more exact and pertinent. A tri- ple-swirled single-sector test eombustor is designed for the lean blowout test at atmospheric pressure. The test verifies the improved lean blowout model. Then the character of near lean blowout in the reeirculation zone is studied numerically. The study sums up the variety of the character to assist analysis of the lean blowout.
出处
《燃气轮机技术》
2015年第4期35-41,61,共8页
Gas Turbine Technology
关键词
燃烧室
贫油熄火
旋流雾化
数值分析
combustor
lean blowout
swirled atomization
numerical analysis
