A gas turbine engine (20,100,109) comprises a nacelle (94,110) that encloses a fan rotor (103) carrying a plurality of fan blades (98). The nacelle (94,110) is formed such that one portion (96) extends axially further from the fan blades (98) than does another portion (97). The nacelle (94,110) is rotatable such that a circumferential location of the one portion (96) and the other portion (97) may be varied dependent on flight conditions.
GAS TURBINE ENGINE WITH ROTATING INLET
GASTURBINENMOTOR MIT ROTIERENDEM EINLASS
TURBINE À GAZ AYANT UNE ADMISSION ROTATIVE
2020-04-22
Patent
Elektronische Ressource
Englisch