驻涡加力燃烧室凹腔稳定器冷却特性实验研究

Experimental research of cooling characteristics of cavity flameholder on trapped vortex afterburner

关键词:  驻涡加力燃烧室  凹腔稳定器  气膜冷却  冷却性能  当量比  实验研究

Key words:  Trapped vortex afterburner  Cavity flameholder  Film-cooling  Cooling characteristics  Equivalence ratio  Experimental research

摘要:

为了研究驻涡加力燃烧室凹腔稳定器的冷却特性，设计了三种不同冷却结构的凹腔稳定器。采用实验研究的方法，对不同冷却结构的凹腔稳定器冷却特性进行研究，同时改变试验中凹腔油气当量比、次流与主流流量比（0.25~0.37）和主流马赫数（0.17~0.26），分析不同结构和气流参数下了凹腔冷却特性。结果表明：驻涡加力燃烧室的凹腔稳定器壁面最高温度出现在前壁面，前壁面温度较上壁和后壁偏高300 K左右；凹腔稳定器壁温受冷却孔开孔率、凹腔油气比、次流与主流流量比影响较大，受马赫数影响较小。综合考虑各个方案试验结果，在凹腔稳定器冷却孔开孔率较低时，凹腔内部油气当量比建议取1.2~1.5。

Abstract:

Three different kinds of cavity flameholer cooling structures were designed to study the cooling characteristics of cavity flameholder on the trapped vortex afterburner. The cooling characteristics of different cooling structures were studied using experiment method. Meanwhile， cavity flameholder cooling characteristics with different structures and flow parameters were analyzed by changing cavity fuel air equivalence ratio， mass flow ratio （0.25~0.37）of secondary flow to mainstream flow and mainstream Mach number（0.17~0.26）. The results showed that the highest temperature appeared in the front wall of the cavity flameholder wall，with 300 K higher than that of the upper wall and the back wall. The cooling hole opening rate， cavity fuel air ratio and ratio of secondary flow to mainstream flow had large impact on cavity flameholder wall temperature， while Mach number had little influence on cavity flameholder wall temperature. Considering testing results of various concepts， cavity fuel air equivalence ratio was suggested 1.2~1.5 when cavity flameholder cooling hole opening rate was low.