The invention belongs to the technical field of aircraft hybrid power system design, and particularly relates to an aircraft hybrid power system hydrogen energy acceleration ducted fan which comprises an outer casing, a spray pipe, an air inlet cone, an inner casing, a tail cone, an electric fan, a motor, a rectification supporting plate, a hydrogen injection rod and an ignition electric nozzle. The spray pipe is connected to the rear end of the outer casing, and the air inlet cone, the inner casing and the tail cone are sequentially arranged in the outer casing. An annular gap exists between the rear end of the air inlet cone and the front end of the inner casing. The electric fan is arranged in the outer casing and located at the annular gap. The motor is arranged in the inner casing, and a rotor is connected with the electric fan; the rectifying support plates are supported between the outer casing and the inner casing in the circumferential direction; the hydrogen injection rods penetrate through the outer casing and extend into the rectification support plates, and nozzles on the hydrogen injection rods are aligned with the hydrogen injection holes in the side walls of the two sides of the rectification support plates; and the ignition electric nozzle penetrates through the outer casing and extends between the rear edges of the two adjacent rectification support plates.
本申请属于飞机混合动力系统设计技术领域,具体涉及一种飞机混合动力系统氢能加速涵道风扇,包括外机匣、喷管、进气锥、内机匣、尾锥、电动风扇、电动机、整流支板、氢气喷射杆、点火电嘴;喷管连接在外机匣后端,进气锥、内机匣、尾锥依次在外机匣内设置;进气锥后端与内机匣前端存在环形缝隙;电动风扇在外机匣内设置,处在环形缝隙位置处;电动机在内机匣内设置,其转子连接电动风扇;整流支板有多个,沿周向支撑在外机匣、内机匣之间;氢气喷射杆有多个,贯穿外机匣设置,伸入到各个整流支板内,其上各个喷嘴对准整流支板两侧侧壁上的各个氢气喷射孔;点火电嘴贯穿外机匣设置,伸入到两相邻整流支板后缘之间。
Hydrogen energy acceleration ducted fan of aircraft hybrid power system
一种飞机混合动力系统氢能加速涵道风扇
2025-03-04
Patent
Electronic Resource
Chinese
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