Rolls-royce Corporation

John Richard Wells

Angus Roy Smith

Christopher Thomas John Sheaf

Christopher Alan Mosley

A fan nacelle for an aircraft gas turbine engine. The nacelle includes an aft nacelle portion including a radially outer surface and a radially inner surface, the radially outer and inner surfaces defining an internal cavity therebetween. The nacelle further includes an aft nacelle segment translatable along a translation vector having an axial component, wherein the aft nacelle segment is configured to translate between a forward deployed position in which the nacelle defines a first primary fan nozzle exit area (A) and a clean position in which the nacelle defines a second primary fan nozzle exit area (A) less than the first primary fan nozzle exit area A, wherein in the forward deployed position, the aft nacelle segment is at least partly located within the internal cavity.

Aircraft gas turbine engine nacelle

A nacelle for a turbofan gas turbine engine is provided. An inner wall of the nacelle defines an air intake which directs air into the fan section of the engine. The intake has, in flow series, an intake lip, a throat and a diffuser. The diffuser has, in flow series, first and second flow conditioning sections over both of which the flow cross-sectional area of the diffuser increases with increasing downstream distance from the throat. In addition, over the second section the nacelle inner wall lies substantially on a surface of an oblique circular cone having an apex which is offset from the centerline of the engine.

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Derby, United Kingdom

John Richard Wells