Patent ID: 8876042
Filing Date: 2014-11-04
Classification: A61P,B64D

Abstract:
1. An assembly comprising: a unitary nacelle structure including an inlet region and a fan cowl region, wherein the unitary nacelle structure is configured to circumscribe at least a portion of an associated core engine module and to direct an airstream to a fan assembly driven by the core engine module; an integrated fan housing in supported connection with the unitary nacelle structure and at least partly disposed within the unitary nacelle structure, wherein the integrated fan housing comprises an integral composite structure and transmits static and dynamic loads directly to a support member adapted for mounting in supported connection with an aircraft to relieve backbone bending of the core engine module, the integral composite structure being integrally formed to include a fan case adapted to encircle the fan assembly of the core engine module and surrounded by the fan cowl region of the unitary nacelle structure, a fan hub that is surrounded by the fan case and is adapted to be located upstream of a core cowl of the core engine module and to receive and support the fan assembly of the core engine module, and a plurality of fan outlet guide vanes extending between and being formed with and directly connected to the fan case and the fan hub to form the integral composite structure; and mounts for fixedly securing the integrated fan housing to the support member.