摘要
对微通道传热应用于航空发动机火焰筒冷却进行了探索。构造了简单微通道模型,其上下平面分别代表火焰筒内外壁面;用工程方法计算火焰筒壁面的热环境作为计算模型的边界条件,以Fluent为工具模拟微通道换热结构的冷却性能;涉及两种长径比(20,40)和三种火焰筒压降(2.0%,2.5%,3.0%)。结果表明,含有微通道换热结构的火焰筒,能以较少的冷却气量维持较低的壁面温度;冷却气流吸热后升温明显,冷量利用率可达40%;冷却气量受长径比影响显著,受火焰筒压降影响不大;火焰筒壁面沿流向的温度梯度非常大。
Numerical investigation was made on the cooling characteristics of micro-and mini-channel heat transfer used in liner wall of an aero-engine comhustor. A one-dimensional heat-transfer model was employed to define the boundary condition of mini-channel walls. FLUENT was used to simulate the cool-ing performance, involving two aspect ratio of mini-channel （20, 40） at three liner pressure loss （2.0%, 2.5%, and 3.0%）. Results show a powerful cooling capacity of mini-channel with small cooling air, which show a significant increase of temperature and a high utilization of potential heat sink （40%）. Furthermore, the flux of cooling air is strongly affected by the aspect ratio of mini-channel, and is slightly affected by pressure loss of liner. Finally, the temperature gradients of liner are remarkable.
出处
《燃气涡轮试验与研究》
北大核心
2013年第4期18-21,43,共5页
Gas Turbine Experiment and Research
作者简介
苗辉（1984-），男，河南滑县人，工程师，博士，主要从事航空发动机传热与燃烧研究。
