The invention provides a heat dissipation system based on auxiliary aviation flight power, the heat dissipation system comprises a driving assembly, an injection assembly and a heat dissipation piece, the driving assembly is provided with a ventilation cavity, the injection assembly comprises a fixing unit and an injection unit, the ventilation cavity is communicated with the injection unit, the fixing unit sleeves the outer wall of the injection unit and forms a fixing space, and the heat dissipation piece is arranged in the fixing space. And injection holes are formed in the circumferential direction of the outer wall of the injection unit so that cold air can be evenly spread on the outer wall of the driving assembly through the injection holes, and the heat dissipation piece is arranged in the fixed space, located above the injection holes and arranged in the circumferential direction of the upper portion of the injection unit so as to dissipate heat of the lubricating oil. And through the unique design of the injection unit, cold air can be uniformly distributed on the outer wall of the driving assembly under the injection of the injection hole in all directions. And the heat dissipation piece is arranged in the circumferential direction above the injection unit, so that the heat dissipation area is enlarged, and the lubricating oil heat dissipation effect is improved. And the fixing unit is arranged in the injection unit, so that the heat dissipation piece is subjected to fireproof protection, and the ignition risk of the heat dissipation piece is reduced.
本发明提出一种基于辅助航空飞行动力的散热系统,包括:驱动组件、引射组件和散热件,驱动组件具有通气腔体,引射组件包括固定单元和引射单元,通气腔体和引射单元连通,固定单元套设于引射单元的外壁上并形成一固定空间,沿引射单元的外壁周向设有引射孔,以使冷气通过引射孔将冷气均匀遍布驱动组件的外壁上,散热件设置于固定空间内并位于引射孔的上方,且沿引射单元上方周向设置,以对滑油进行散热。通过引射单元的独特设计,能够使冷气全方位能够在引射孔的引射下均匀遍布驱动组件的外壁上。而散热件沿引射单元上方周向设置,扩大了散热面积,提升滑油散热效果。而固定单元设于引射单元内,使其对散热件的防火保护,降低散热件的着火风险。
Heat dissipation system based on auxiliary aviation flight power
一种基于辅助航空飞行动力的散热系统
27.09.2024
Patent
Elektronische Ressource
Chinesisch
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