轴向通流多级旋转盘腔内的稳态换热特性

Heat transfer in rotating cavity with axial throughflow of cooling air

针对航空发动机多级压气机盘腔的冷却问题 ,对具有轴向通流的三腔模型进行了系统的研究 ,通过对局部换热特性与平均换热特性的分析 ,可以表征旋转盘的热应力水平和相对冷却效果 ,结果表明表征旋转盘热应力水平的局部换热特性在旋转盘的半径上呈多峰分布 ,表征相对冷却效果的平均换热特性与旋转雷诺数Rew、进气雷诺数Re以及格拉晓夫数Gr有关 ,当Re及Gr增加时 ,平均努塞尔数 Nu随之增加 ,而Rew

A test model of four co-rotating disks was developed as the simplified version of a typical internal cooling system of a gas turbine compressor. The investigation was on the distribution of local heat transfer coefficient and the averaged Nusselt number of the downstream main disk. Experimental analysis may lead to following conclusions: the distribution is not of monotony and multi-peaks were found along the disk surface, N¯u increases with the decrease of the rotational Reynold number (Rew), N¯u increases with the axial Reynold number (Re) and the Grasholf number (Gr).