The invention belongs to the field of aero-engines, and particularly relates to a heat dissipation structure and a heat dissipation method of an aviation hybrid electric propulsion system. According to the heat dissipation structure of the aviation hybrid electric pushing system, a lubricating oil tank is connected with an electric oil supply pump, the electric oil supply pump is connected with a lubricating oil temperature control valve, the lubricating oil temperature control valve is connected with an air lubricating oil radiator and a lubricating oil filter, the air lubricating oil radiator is connected with the lubricating oil filter and an air driver, and the air driver is connected with the lubricating oil filter. The lubricating oil filter is respectively connected with the battery, the motor, the gas turbine engine and the generator, the hybrid electric propulsion system is connected with the oil scavenger pump, and the electric oil scavenger pump is connected with the lubricating oil tank. According to the integrated heat dissipation layout, the use of heat dissipation equipment can be reduced, the integration level is higher, the weight of the aviation aircraft is reduced, and the heat dissipation structure can also play a role in heating the battery.
本发明属于航空发动机领域,具体涉及一种航空混合电推系统的散热结构及散热方法。其中一种航空混合电推系统的散热结构,所述滑油箱连接所述电动供油泵,所述电动供油泵连接所述滑油温控活门,所述滑油温控活门分别连接所述空气滑油散热器和所述滑油滤,所述空气滑油散热器分别连接所述滑油滤和空气驱动器,所述滑油滤分别与所述电池、电动机、燃气涡轮发动机和发电机连接,所述混合电推系统连接所述回油泵,所述电动回油泵连接所述滑油箱。本发明一体化散热布局不仅能够减少散热设备的使用,集成度更高,降低了航空飞行器的重量,而且本散热结构还能起到加热电池的作用。
Heat dissipation structure and heat dissipation method of aviation hybrid electric propulsion system
一种航空混合电推系统的散热结构及散热方法
28.05.2024
Patent
Elektronische Ressource
Chinesisch
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