Intermediate structure for independently de-mountable propulsion components
View Patent ↗An intermediate structure of an aircraft configured to mechanically attach an engine core and an engine fan module to each other and to the aircraft. The intermediate structure may have a ring-shaped portion and/or an elongated mount beam extending substantially perpendicularly from the ring-shaped portion. The ring-shaped portion may have a forward edge and an aft edge opposite of the forward edge, and may include a first attachment portion for attaching to a flange of the engine core, a second attachment portion for attaching to a flange of the engine fan module, and a mounting portion configured for mounting directly to a pylon or airframe of an aircraft. The engine core and/or the engine fan module may independently mechanically attach to and detach from the intermediate structure. The intermediate structure may have a gearbox mounted thereto for interfacing with rotary components of the engine core and the engine fan module.
1. An intermediate structure of an aircraft mechanically attaching an engine core, having a core mounting flange, and an engine fan module, having a fan mounting flange, to each other and the aircraft, the intermediate structure comprising:
a ring portion having a circular shape, made of a rigid material and having a forward edge and an aft edge;
a first flange extending from the aft edge of the ring portion and attached to the fan mounting flange of the engine fan module;
a second flange extending from the forward edge of the ring portion and attached to the core mounting flange of the engine core; and
an elongated mount beam having a first end integrally formed with and extending substantially perpendicular from the forward or aft edge of the ring portion and a second end opposite of the first end, wherein the elongated mount beam is mounted directly to a pylon or airframe of the aircraft wherein the intermediate structure is independently mechanically detachable from one of the engine core and the engine fan module while another one of the engine core and the engine fan module remains mechanically attached to and supported on the aircraft by the intermediate structure.
2. The intermediate structure of claim 1 , wherein the elongated mount beam comprises one or more support links extending from the second end attached to and structurally supporting the engine core.
3. The intermediate structure of claim 1 , wherein the elongated mount beam further comprises a substantially tapering section extending from the ring portion to a point between the first and second ends of the elongated mount beam, wherein the substantially tapering section tapers in a direction away from the first end of the elongated mount beam.
4. The intermediate structure of claim 1 , further comprising a fan speed reduction gearbox mounted to the ring portion interfaced with the engine core and the fan module, and configured to compensate for a difference in rotary speed between the engine core and the fan module.
5. The intermediate structure of claim 1 , further comprising an accessory gearbox mounted to the ring portion and attached to the engine core or the fan module in a configuration to provide rotary power from the engine core or the fan module to other accessories of the aircraft.