An aircraft hybrid propulsion system (5) comprises an internal combustion engine (10) comprising a main drive shaft (24); an electric machine (28) comprising an electric machine rotor (78); a propulsor (12) mounted to a propulsor shaft (62); and a clutch arrangement configured to selectively couple each of the gas turbine engine main drive shaft (24) and the electric machine rotor (78) to a propulsor drive shaft (62). The electric machine rotor (78) is mounted coaxially with the main drive shaft (24) and the clutch arrangement comprises a first overrunning clutch (52) configured to couple the main drive shaft (24) to the propulsor drive shaft (62), and a second overrunning clutch (54) configured to couple the electric machine rotor (78) to the propulsor drive shaft (62).
飞机混合式推进系统(5)包括:内燃发动机(10),其包括主驱动轴(24);电机(28),其包括电机转子(78);推进器(12),其安装到推进器轴(62);和离合器装置,其配置成将燃气涡轮发动机主驱动轴(24)和电机转子(78)中的每一个选择性地联接到推进器驱动轴(62)。电机转子(78)与主驱动轴(24)同轴地安装,以及离合器装置包括配置成将主驱动轴(24)联接到推进器驱动轴(62)的第一过速离合器(52),以及配置成将电机转子(78)联接到推进器驱动轴(62)的第二过速离合器(54)。
Aircraft hybrid propulsion system
飞机混合式推进系统
18.06.2021
Patent
Elektronische Ressource
Chinesisch
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |