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为了研究在旋转状态下射流冲击冷却在楔形通道径向末端的冷却效果,在主流通道进口雷诺数为15000、旋转数为0或0.1的工况下,实验研究了不同射流孔位置、射流流量条件下的楔形通道沿程壁面换热规律。研究结果表明:射流孔附近的通道壁面换热系数被极大地增强,但冷却效果被限制在一定范围内;射流对通道内侧的影响范围要大于中部和外侧,但增大射流流量并不会增加内侧的换热系数;旋转工况下,射流影响区的换热对比静止基本上没有变化;在本实验工况下,射流不能强化沿通道径向射流孔后侧位置的换热;不同工况下的通道整体平均换热在10%以内,末端射流冲击对通道整体换热影响有限。
In order to study the cooling effect of jet impingement cooling on the radial end of the wedge-shaped channel under the condition of rotating, under the conditions of inlet Reynolds number of 15000 and number of revolutions of 0 or 0.1, experiments were conducted to study the influence of different jet orifice locations, jet flow conditions Under the wedge-shaped channel along the wall surface heat transfer law. The results show that the wall heat transfer coefficient near the jet hole is greatly enhanced, but the cooling effect is limited within a certain range. The influence of jet on the inner side of the channel is greater than that on the middle and outer sides, but the increase of jet flow does not increase In the experimental conditions, the jet can not enhance the heat transfer along the rear side of the radial jet orifice along the channel. In different operating conditions, Under the channel the average heat transfer within the overall less than 10%, the impact of the end of the jet impact on the overall channel heat exchange has a limited impact.