某回流燃烧室火焰筒冷却性能分析

Cooling performance analysis of combustion liner in reverse-flow combustor

为了研究回流燃烧室内部火焰筒的燃烧和冷却性能,建立了回流燃烧室模型,通过热流固耦合仿真分析其失效原因。通过引入不同孔型和不同孔倾角的气膜孔,与初始结构故障件的冷却效果进行对比分析。结果表明:原结构件最高温度和最高温度梯度的位置与实际故障件的失效位置相同,可认为失效原因是高温和高温度梯度共同导致的;改变孔结构后回流燃烧室壁面最高温度相对于原结构均下降,最多下降了281.34 K,最少下降了60.15 K;当采用同一种孔型时,孔倾角为30°的冷却效果最好,孔倾角为60°的冷却效果最差;当孔倾角相同时,收敛孔的冷却效果最好,因为在孔出口附近的截面上产生了一个与原旋涡对反向的旋涡对,从而改善冷却效果,柱形孔的冷却效果最差。

To study the combustion and cooling performance of the combustion liner in the reverse-flow combustor,a combustor model was built,and failure reasons were analyzed through heat fluid-structure coupling simulation.By introducing film cooling holes with different hole types and dip angles,the cooling effect of the original defective component part was compared.The results show that the location of the maximum temperature and maximum temperature gradient of the original structural part is the same as the failure location of the actual fault part,so that it can be considered that the failure is caused by high temperature and high temperature gradient;compared with initial cooling structure,the maximum temperature of the inner wall of the reverse combustor all decreased after the hole structure change,281.34 K at most and 60.15 K at least;with the same hole type,the cooling effectiveness is the best at a hole inclination angle of 30°,and the cooling effectiveness is the worst at the hole inclination angle of 60°.With the same hole inclination angle,the cooling effectiveness of the convergent hole is the best,because of a vortex pair opposite to the original structure generated on the section near the outlet end,therefore improving the cooling effect,while the cooling effectiveness of cylindrical holes is the worst.