This paper details and develops novel wing shape hydrocarbon fuel cooling channel for enhancing the heat transfer capability of hypersonic vehicle electricity supply blades under rotating conditions. The effect of parameters such as wing base position and height on the thermal performance in the rotating situation is studied. The calculation results show that the wing base height H = 0.6D-0.8D wing shape channels have generally higher thermal performance and generally lower friction coefficient. Thermal performance of the channel with wing base parameters L = 10 D, H = 0.6 D is maximally increased by 350.2 % and friction coefficient is maximally reduced by 98.5 % compared with the straight channel at inlet temperature of 590 K and rotational speed of 35,000 rpm. As the wing base position L increases, both the thermal performance and the friction coefficient increase and then decrease under the influence of the pressure difference. Under the condition of high rotational speed, the wing base height H = 0.8 D and H = 0.6 D wing shape channels will obtain the maximum value of thermal performance in the range of L = 2 D-4 D and L = 6 D-10 D of the wing base position, respectively.

中文翻译：

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不同机翼结构参数的旋翼形通道超临界压力碳氢燃料传热性能研究


本文详细介绍并开发了新型机翼形状碳氢燃料冷却通道，以增强高超声速飞行器供电叶片在旋转条件下的传热能力。研究了旋转工况下机翼基部位置、高度等参数对热性能的影响。计算结果表明，翼底高度H=0.6D-0.8D的翼型通道普遍具有​​较高的热性能和较低的摩擦系数。翼基参数L=10D、H=0.6D的流道在入口温度590K、转速35,000rpm下与直流道相比热性能最大提高了350.2%，摩擦系数最大降低了98.5% 。随着机翼基部位置L的增大，在压差的影响下，热性能和摩擦系数均先增大后减小。在高转速条件下，翼基高度H=0.8D和H=0.6D翼型通道将在L=2D-4D和L=6D-10范围内获得热性能最大值D 分别为机翼底座位置。