Cooling performance analysis of combustion liner in reverse-flow combustor

被引：0
|
作者：
Li W. [1 ]
Yang L. [1 ]
机构：
[1] College of Mechanical and Vehicle Engineering, Hunan University, Changsha
来源：
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2023年 / 44卷 / 09期
关键词：
combustion; cooling hole; cooling performance; failure; reverse-flow combustor; vortex pair;
D O I：
10.7527/S1000-6893.2022.27326
中图分类号：
学科分类号：
摘要：
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 compo⁃ nent 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 consid⁃ ered that the failure is caused by high temperature and high temperature gradient；compared with initial cooling struc⁃ ture，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 op⁃ posite 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. © 2023 AAAS Press of Chinese Society of Aeronautics and Astronautics. All rights reserved.
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