飞行器主动冷却热防护通道设计与分析

Design and Analysis of Active Cooling Thermal Protection Channel for Hypersonic Aircraft

飞行器以高超音速巡航时,表面会产生巨大的气动加热。本文通过对比不同截面形状的热防护通道流动与传热性能,设计了一种新型的飞行器主动冷却热防护通道,并对其进行了分析。取飞行器前缘单个流道作为分析对象,结构由外壁面、内壁面、多孔支撑结构和流体管道区域组成。在迎风面、背风面、前缘面分别施加150 kW,25 kW和750 kW的热流密度,固体材料与多孔材料均为耐高温镍基合金。结果显示矩形流道对飞行器防热结构外壁面的冷却效果最佳,三角形流道对飞行器防热结构内壁面冷却效果最好。而本文设计的新型通流结构可以有效结合两者内外壁面的冷却优势。同时,航空煤油代替液态水作为冷却剂时,飞行器主动热防护结构具有较好的热工水力性能。

When the hypersonic aircraft cruises at hypersonic speeds,its surface produces huge aerodynamic heating.In this paper,a new type of active cooling thermal protection channel is designed and analyzed by comparing the flow and heat transfer performance of thermal protection channels with different cross-section shapes.A single channel at the leading edge is taken as the analysis object.Heat of 660 kW,110 kW和1375 kW are applied to the windward,leeward and leading edge,respectively.Moreover,Solid material and bottom porous material are both nickel base alloy Inconel-625.The results show that rectangular and triangular have the best cooling effect on outer and inner walls,separately.The new channel designed in this paper can effectively combine the cooling advantages of both.Meanwhile,when aviation kerosene replaces liquid water as coolant,the active cooling thermal protection channel has better thermal-hydraulic performance.