A nacelle for a gas turbine engine having a longitudinal centre line. The nacelle includes an air intake disposed at an upstream end of the nacelle. The air intake includes, in flow series, an intake lip, a throat and a diffuser. The nacelle further includes a protrusion extending radially inward from the air intake downstream of the intake lip. The protrusion extends circumferentially by a protrusion angle (θp) with respect to the longitudinal centre line of the gas turbine engine.
NACELLE FOR GAS TURBINE ENGINE
2021-11-18
Patent
Electronic Resource
English