| 摘要 |
An assembly includes a unitary nacelle structure (11) and an integrated fan housing (30) for a gas turbine engine assembly. The unitary nacelle structure includes an inlet region and a fan cowl (50) region, and is configured to at least partially circumscribe the integrated fan housing (30). The integrated fan housing (30) comprises an integral composite structure and includes a fan case (32) sized and configured for encircling a fan blade assembly of an associated gas turbine engine, a fan hub, and a plurality of fan outlet guide vanes (38). The unitary nacelle structure (11) cooperates with the integrated fan housing (30) to transfer static and dynamic loads directly to a support structure (22), rather than through the engine core, to minimize backbone bending. |
