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 combustor. 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.
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