A propulsion system (2) for a helicopter (1) is disclosed, comprising a main engine (9), a main rotor (3), a main gearbox (4) comprising an output mechanically connected to the main rotor (3), a reduction gearbox (13) mechanically coupled between the main engine (9) and a first input of the main gearbox (4), and an auxiliary device (10). The auxiliary device (10) comprises a first electric machine mechanically coupled to the reduction gearbox (13) and configured to act as a generator to take away energy generated by the main engine (9) and a second electric machine mechanically coupled to a second input of the main gearbox (4), the second electric machine is powered by the first electric machine and is configured to act as an electric motor to deliver additional mechanical power to the main gearbox (4).
公开了一种用于直升机(1)的推进系统(2),包括:主发动机(9)、主旋翼(3)、包括机械地连接到主旋翼(3)的输出的主齿轮箱(4)、机械地耦接在主发动机(9)和主齿轮箱(4)的第一输入之间的减速齿轮箱(13)以及辅助设备(10)。辅助设备(10)包括第一电机和第二电机,第一电机机械地耦接到减速齿轮箱(13)并被配置为充当发电机以取走由主发动机(9)产生的能量,第二电机机械地耦接到主齿轮箱(4)的第二输入,第二电机由第一电机供应电力并被配置为充当电动马达以向主齿轮箱(4)递送附加机械功率。
Hybrid propulsion system for helicopters
用于直升机的混合推进系统
08.08.2023
Patent
Elektronische Ressource
Chinesisch
IPC: | B64C AEROPLANES , Flugzeuge |
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