A gas turbine engine (300) comprises a pylon attachment (312), a shaft (308) defining an engine centreline (310) which lies in an engine central plane (320) intersecting the pylon attachment, a fan defining a fan plane (340) normal to the engine centreline and an intake (304) upstream of the fan plane. The geometric centreline (350) of the intake coincides with the engine centreline at an axial position (306) corresponding to the downstream end of the intake and curves away from the engine centreline upstream of said axial position. The engine may be mounted on one side of an aircraft such that the orientation of the highlight plane of the intake is aligned to the air flow field of the aircraft on that side during flight.
GAS TURBINE ENGINE
GASTURBINENMOTOR
TURBINE À GAZ
2022-01-19
Patent
Elektronische Ressource
Englisch