Patent ID: 9243647
Filing Date: 2016-01-26
CPC Classification: B64D,F02C,F04D,F05D,Y02T

Claim Text:
1. An aircraft propulsion system nacelle comprising: a) an engine assembly; and b) a fan assembly operatively connected to the engine assembly, and comprising a plurality of fan blades arranged circumferentially around an axis of rotation; and c) a monolithic nacelle structure which circumferentially encloses the fan assembly, and comprises a first, radially proximal, surface locatable radially outward of the plurality of fan blades, and an opposite, second, radially distal, surface which forms a radially outermost surface of the aircraft propulsion system nacelle, and wherein a radial thickness of the nacelle structure is greater at a first, inlet portion than at a plane of the fan assembly normal to the axis of rotation.