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. A method of coupling and decoupling an engine core with an engine fan module via an intermediate structure of an aircraft, the method comprising:
mechanically attaching the engine core to the intermediate structure at a first edge of the intermediate structure, wherein the intermediate structure has a ring-shaped portion that is rigid and is mounted directly to a pylon or airframe of the aircraft;
mechanically attaching the engine fan module to the intermediate structure at a second edge of the intermediate structure, wherein the second edge of the intermediate structure is opposite of the first edge; and
mechanically disconnecting and removing one of the engine core and the engine fan module from the intermediate structure 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 method of claim 1 , wherein the step of mechanically disconnecting and removing comprises disconnecting and removing the engine core from the intermediate structure while the engine fan module remains mechanically attached to and supported on the aircraft by the intermediate structure.
3. The method of claim 1 , wherein the step of mechanically disconnecting and removing comprises disconnecting and removing the engine fan module from the intermediate structure while the engine core remains mechanically attached to and supported on the aircraft by the intermediate structure.
4. The method of claim 1 , wherein a fan speed reduction gearbox is mounted to the intermediate structure, wherein the steps of mechanically attaching the engine core and the fan module to the intermediate structure further comprise attaching rotary components of the engine core and the engine fan module with rotary components of the fan speed reduction gearbox mounted to the intermediate structure, wherein the fan speed reduction gearbox is configured for compensating for a difference in rotary speed between the engine core and the fan module.
5. The method of claim 1 , wherein the intermediate structure further comprises an elongated mount beam having a first end integrally formed with the ring-shaped portion at the first edge or the second edge and a second end opposite of the first end.
6. The method of claim 5 , further comprising attaching the engine core to the second end of the elongated mount beam to structurally support the engine core.
7. The method of claim 1 , wherein an accessory gearbox is mounted to the intermediate structure, wherein the steps of mechanically attaching the engine core and the fan module to the intermediate structure further comprising attaching rotary components of the engine core and the engine fan module with rotary components of the accessory gearbox, wherein the accessory gearbox is configured to provide rotary power from the engine core or the fan module to other accessories of the aircraft.
8. A method of coupling and decoupling an engine core with an engine fan module via an intermediate structure of an aircraft, the method comprising:
mechanically attaching the engine core to a ring-shaped portion of the intermediate structure at a first edge of the ring-shaped portion, wherein the ring-shaped portion is rigid, wherein the intermediate structure further includes an elongated mount beam having a first end integrally formed with the ring-shaped portion and a second end opposite of the first end, wherein the intermediate structure is mounted directly to a pylon or airframe of the aircraft;
mechanically attaching the engine fan module to the ring-shaped portion at a second edge of the ring-shaped portion, wherein the second edge is opposite of the first edge; and
mechanically disconnecting and removing the engine core from the intermediate structure while the engine fan module remains mechanically attached to and supported on the aircraft by the intermediate structure; or
mechanically disconnecting and removing the engine fan module from the intermediate structure while the engine core remains mechanically attached to and supported on the aircraft by the intermediate structure.
9. The method of claim 8 , wherein a fan speed reduction gearbox is mounted to the intermediate structure, wherein the steps of mechanically attaching the engine core and the fan module to the intermediate structure further comprise attaching rotary components of the engine core and the engine fan module with rotary components of the fan speed reduction gearbox mounted to the intermediate structure, wherein the fan speed reduction gearbox is configured for compensating for a difference in rotary speed between the engine core and the fan module.
10. The method of claim 8 , further comprising attaching the engine core to the second end of the elongated mount beam to structurally support the engine core.
11. The method of claim 8 , wherein an accessory gearbox is mounted to the intermediate structure, wherein the steps of mechanically attaching the engine core and the fan module to the intermediate structure further comprising attaching rotary components of the engine core and the engine fan module with rotary components of the accessory gearbox, wherein the accessory gearbox is configured to provide rotary power from the engine core or the fan module to other accessories of the aircraft.
12. The method of claim 8 , wherein the intermediate structure further comprises a first attachment flange extending from the ring-shaped portion at the first edge and a second attachment flange extending from the ring-shaped portion at the second edge, wherein the step of mechanically attaching the engine core to the ring-shaped portion comprises mechanically attaching the engine core to the first attachment flange, wherein the step of mechanically attaching the engine fan module to the ring-shaped portion comprises mechanically attaching the engine fan module to the second attachment flange.
13. The method of claim 12 , wherein mechanically attaching includes bolting portions of the engine core and the engine fan module to the first and second attachment flanges, respectively.
14. The method of claim 8 , further comprising attaching one or more support links extending from the second end of the mount beam to the engine core.
15. The method of claim 8 , wherein the mount beam further comprises a substantially tapering section extending from the first edge of the ring-shaped 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 mount beam.
16. The method of claim 8 , further comprising attaching at least one support link from the mount beam to the ring portion and at least one support link from the second end of the mount beam to the engine core.
17. A method of coupling and decoupling an engine core with an engine fan module via an intermediate structure of an aircraft, the method comprising:
mechanically attaching the engine core to a ring-shaped portion of the intermediate structure at a first edge of the ring-shaped portion, wherein the ring-shaped portion is rigid;
mechanically attaching the engine fan module to the ring-shaped portion at a second edge of the ring-shaped portion, wherein the second edge is opposite of the first edge;
attaching the engine core to a second end of an elongated mount beam of the intermediate structure to structurally support the engine core, wherein the elongated mount beam has a first end integrally formed with the ring-shaped portion and the second end opposite of the first end, wherein the intermediate structure is mounted directly to a pylon or airframe of the aircraft; and
mechanically disconnecting and removing the engine core from the ring-shaped portion and the elongated mount beam while the engine fan module remains mechanically attached to the ring-shaped portion and thus supported on the aircraft by the intermediate structure; or
mechanically disconnecting and removing the engine fan module from the ring-shaped portion while the engine core remains mechanically attached to the ring-shaped portion and the elongated mount beam and thus supported on the aircraft by the intermediate structure.
18. The method of claim 17 , wherein a fan speed reduction gearbox is mounted to the intermediate structure, wherein the steps of mechanically attaching the engine core and the fan module to the intermediate structure further comprise attaching rotary components of the engine core and the engine fan module with rotary components of the fan speed reduction gearbox mounted to the intermediate structure, wherein the fan speed reduction gearbox is configured for compensating for a difference in rotary speed between the engine core and the fan module.
19. The method of claim 17 , wherein an accessory gearbox is mounted to the intermediate structure, wherein the steps of mechanically attaching the engine core and the fan module to the intermediate structure further comprising attaching rotary components of the engine core and the engine fan module with rotary components of the accessory gearbox, wherein the accessory gearbox is configured to provide rotary power from the engine core or the fan module to other accessories of the aircraft.
20. The method of claim 17 , wherein the intermediate structure further comprises a first attachment flange extending from the ring-shaped portion at the first edge and a second attachment flange extending from the ring-shaped portion at the second edge, wherein the step of mechanically attaching the engine core to the ring-shaped portion comprises bolting portions of the engine core to the first attachment flange, wherein the step of mechanically attaching the engine fan module to the ring-shaped portion comprises bolting portions of the engine fan module to the second attachment flange.