A gas turbine engine comprises a nacelle that encloses a fan rotor carrying a plurality of fan blades. The nacelle is formed with droop such that one portion extends axially further from the fan blades than does another portion. The nacelle is rotatable such that a circumferential location of the one portion and the other portion may be varied dependent on flight conditions. A method of operating a gas turbine engine is also disclosed.
GAS TURBINE ENGINE WITH ROTATING INLET
2017-06-22
Patent
Elektronische Ressource
Englisch