A gas turbine engine comprises a housing having an inlet leading to a fan rotor. A bypass door is mounted upstream of the inlet to the fan rotor, and is moveable away from a non-bypass position to a bypass position to selectively bypass boundary layer air vertically beneath the engine. An aircraft is also disclosed.
VARIABLE-GEOMETRY BOUNDARY LAYER DIVERTER
2018-10-18
Patent
Elektronische Ressource
Englisch