摘要
为了研究一种小型发动机回流燃烧室弯曲段外壁的冷却方式特性以及不同冷却方式对燃烧室出口温度分布的影响,通过在模拟设计点工况下的温度分布试验对比分析大弯管壁气膜冷却及冲击/发散冷却对出口温度场的影响趋势。试验结果表明:采用气膜冷却和冲击/发散冷却方式大弯管壁的燃烧室出口温度场均呈现出三个明显的展向偏移热区,符合燃烧室出口温度的一般规律。采用冲击/发散冷却的方案具有较低的热点,其温度热区沿径向和展向更加均匀,温度梯度小,贴近壁面的温度与热区中心之间过渡平缓,热区中心温度比气膜冷却低,出口气流在径向和展向均有更加优异的扩散性。
In order to study the cooling characteristics of reverse flow combustor curved section of outer wall and different cooling effect on the combustion chamber outlet temperature distribution in a small engine, several temperature distribution tests at simulation design point were designed to comparatively analyze the influence of temperature distribution of the film cooling and impingement effusion cooling in curved section. The research results from experimental study show that the film cooling and impingement effusion cooling take on thine hot spots along the span direction at the exit of the combustion chamber, in line with the general law of the combustion chamber outlet temperature. The impingement effusion cooling scheme has low temperature hot pot, and the hot spots along the radial and span direction are more uniform with small temperature gradient near the wall. The temperature transits smoothly with lower heat center temperature than film cooling scheme between the wall and heat center. The impingement effusion cooling has more excellent diffusion than film cooling along the radial and span direction.
作者
代威
夏东坤
张雯
蔡昱
张弛
DAI Wei;XIA Dongkun;ZHANG Wen;CAI Yu;ZHANG Chi(China Academy of Launch Vehicle Technology- Research and Development Center,Beijing 100076,Ch;National Key Laboratory- of Science and Technology on Aero-Engine Aero-Thermodynamics,School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics,Beijing 100191,China)
出处
《兵器装备工程学报》
CAS
北大核心
2018年第5期21-25,共5页
Journal of Ordnance Equipment Engineering
关键词
回流燃烧室
气膜冷却
冲击发散冷却
出口温度分布
reverse-flow combustor
film cooling
impingement effusion cooling
exit temperature distribution
