A fuselage (36, 74, 144) mounted gas turbine engine installation (30, 70, 110), the installation (30, 70, 110) comprising at least one propeller stage (46, 82, 122) and a gas turbine core (50, 92, 132) arranged in use to drive the propeller stage (46, 82, 122). The core (50, 92, 132) is external to the fuselage (36, 74, 144) and the rotational axes of the core (50, 92, 132) and propeller stage (46, 82, 122) are offset with respect to each other.
Gas turbine engine installation
Triebwerkseinbau
Installation d'une turbine à gaz
2019-04-10
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
European Patent Office | 2016
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