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为了获得一种具有直通式冷气预旋进气系统的小型燃气轮机涡轮叶片的流动与换热特性,采用气热耦合计算方法进行数值研究,分析了总压损失、冷却效果和涡轮效率随预旋角、冷气雷诺数和无量纲质量流量的变化规律。结果表明,涡轮叶片预旋进气冷却的总压损失随冷气雷诺数和无量纲质量流量的增大而增大,但基本不受预旋角大小的影响;涡轮叶片的冷却效果随预旋角的减小、冷气雷诺数或无量纲质量流量的增大而增强,但不会改变其表面的温度分布特征;预旋进气冷却时的涡轮效率随冷气雷诺数的增大、预旋角或无量纲质量流量的减小而提高。
In order to obtain the flow and heat transfer characteristics of turbine blades of a small gas turbine with a straight-through cold air pre-priming air intake system, a numerical study was conducted using the calculation method of air-heat coupling. The analysis of the total pressure loss, cooling effect and turbine efficiency with pre-rotation angle , Reynolds number of air conditioners and the variation of non-dimensional mass flow rate. The results show that the total pressure loss of the precooled turbine blades increases with Reynolds number and the non-dimensional mass flow, but it is not affected by the size of the pre-rotation angle. The cooling effect of the turbine blades varies with the pre-rotation angle , The Reynolds number of air-condition or the dimensionless mass flow increase, but it does not change the temperature distribution of its surface. The efficiency of the turbine when the pre-precession is cooled increases with the increase of Reynolds number of air-condition, The reduction of dimensionless mass flow increases.