A gas turbine engine (24) comprises a housing having an inlet leading to a fan rotor (42). A bypass door (28) is mounted upstream of the inlet to the fan rotor (42), and is moveable away from a non-bypass position to a bypass position to selectively bypass boundary layer air vertically beneath (38) the engine (24). An aircraft (20) is also disclosed.
VARIABLE-GEOMETRY BOUNDARY LAYER DIVERTER
GRENZSCHICHTUMLENKER MIT VARIABLER GEOMETRIE
DÉVIATEUR DE COUCHE LIMITE À GÉOMÉTRIE VARIABLE
2022-08-24
Patent
Electronic Resource
English