Tiltrotor aircraft having journal bearing mounted pylon assemblies

Patent metadata

Field	Value
Publication number	US-9868541-B2
Application number	US-201715407449-A
Country	US
Kind code	B2
Filing date	Jan 17, 2017
Priority date	Aug 14, 2013
Publication date	Jan 16, 2018
Grant date	Jan 16, 2018

Abstract

A propulsion system for a tiltrotor aircraft includes an engine supported by the airframe and a fixed gearbox operably coupled to the engine. Inboard and outboard pedestals are supported by the airframe and positioned above the wing. A pylon assembly is rotatably coupled between the inboard and outboard pedestals. The pylon assembly includes a spindle gearbox having an input gear, a mast operably coupled to the input gear and a proprotor assembly operable to rotate with the mast. The spindle gearbox is rotatable about a conversion axis to selectively operate the tiltrotor aircraft between helicopter and airplane modes. A common shaft, rotatable about the conversion axis, is configured to transfer torque from an output gear of the fixed gearbox to the input gear of the spindle gearbox. Each of the inboard and outboard pedestals includes a journal bearing that provides a stiff coupling with the pylon assembly.

First claim

What is claimed is:

1. A propulsion system for a tiltrotor aircraft having a helicopter mode and an airplane mode, the tiltrotor aircraft having an airframe including a fuselage and a wing, the propulsion system comprising:
an engine supported by the airframe proximate an outboard end of the wing;
a fixed gearbox operably coupled to the engine and having an output gear;
inboard and outboard pedestals supported by the airframe and positioned above the wing;
a pylon assembly rotatably coupled between the inboard and outboard pedestals, the pylon assembly including a spindle gearbox having an input gear, a mast operably coupled to the input gear and a proprotor assembly operable to rotate with the mast, the spindle gearbox rotatable about a conversion axis to selectively operate the tiltrotor aircraft between the helicopter mode and the airplane mode; and
a common shaft configured to transfer torque from the output gear of the fixed gearbox to the input gear of the spindle gearbox, the common shaft rotatable about the conversion axis;
wherein, each of the inboard and outboard pedestals further comprises a journal bearing providing a stiff coupling between the pylon assembly and the inboard and outboard pedestals, thereby controlling dynamic modes between the pylon assembly and the airframe.

2. The propulsion system as recited in claim 1 wherein the coupling between the pylon assembly and the outboard pedestal further comprises a fixed bearing coupling to substantially prevent lateral movement of the pylon assembly relative to the outboard pedestal.

3. The propulsion system as recited in claim 2 wherein the fixed bearing coupling further comprises a lock washer and spanner nut coupling the pylon assembly to an inboard side of the outboard pedestal and a washer and clamp ring coupling the pylon assembly to an outboard side of the outboard pedestal.

4. The propulsion system as recited in claim 1 wherein the coupling between the pylon assembly and the inboard pedestal further comprises a floating bearing coupling to allow lateral movement of the pylon assembly relative to the inboard pedestal.

5. The propulsion system as recited in claim 1 wherein the pylon assembly further comprises an inboard sleeve positioned within the journal bearing of the inboard pedestal and an outboard sleeve positioned within the journal bearing of the outboard pedestal.

6. The propulsion system as recited in claim 1 wherein each of the inboard and outboard pedestals further comprises a full pillow block housing.

7. The propulsion system as recited in claim 1 wherein each of the inboard and outboard pedestals further comprises a split pillow block housing.

8. The propulsion system as recited in claim 1 wherein the inboard pedestal further comprises a full pillow block housing and wherein the outboard pedestal further comprises a split pillow block housing.

9. The propulsion system as recited in claim 1 wherein each of the inboard and outboard pedestals further comprises a tip rib extending above the wing and defining a slot and a bearing cartridge including a bearing assembly received within the slot.

10. The propulsion system as recited in claim 1 wherein the inboard and outboard pedestals support fore/aft loads generated by the proprotor assembly when the tiltrotor aircraft is in the airplane mode.

11. The propulsion system as recited in claim 1 wherein the inboard and outboard pedestals support vertical loads generated by the proprotor assembly when the tiltrotor aircraft is in the helicopter mode.

12. The propulsion system as recited in claim 1 wherein the stiff couplings between the pylon assembly and the inboard and outboard pedestals are operable to maintain the output gear of the fixed gearbox in substantial collinear alignment with the input gear of the spindle gearbox.

13. The propulsion system as recited in claim 1 wherein the fixed gearbox extends generally normal to the conversion axis and wherein the fixed gearbox is coupled to the outboard pedestal to maintain the output gear of the fixed gearbox in substantial collinear alignment with the input gear of the spindle gearbox.

14. A tiltrotor aircraft having a helicopter mode and an airplane mode, the tiltrotor aircraft comprising:
an airframe including a fuselage and a wing;
an engine supported by the airframe proximate an outboard end of the wing;
a fixed gearbox operably coupled to the engine and having an output gear;
inboard and outboard pedestals supported by the airframe and positioned above the wing;
a pylon assembly rotatably coupled between the inboard and outboard pedestals, the pylon assembly including a spindle gearbox having an input gear, a mast operably coupled to the input gear and a proprotor assembly operable to rotate with the mast, the spindle gearbox rotatable about a conversion axis to selectively operate the tiltrotor aircraft between the helicopter mode and the airplane mode; and
a common shaft configured to transfer torque from the output gear of the fixed gearbox to the input gear of the spindle gearbox, the common shaft rotatable about the conversion axis;
wherein, each of the inboard and outboard pedestals further comprises a journal bearing providing a stiff coupling between the pylon assembly and the inboard and outboard pedestals, thereby controlling dynamic modes between the pylon assembly and the airframe.

15. The tiltrotor aircraft as recited in claim 14 wherein the coupling between the pylon assembly and the outboard pedestal further comprises a fixed bearing coupling to substantially prevent lateral movement of the pylon assembly relative to the outboard pedestal and wherein the coupling between the pylon assembly and the inboard pedestal further comprises a floating bearing coupling to allow lateral movement of the pylon assembly relative to the inboard pedestal.

16. The tiltrotor aircraft as recited in claim 14 wherein each of the inboard and outboard pedestals further comprises a full pillow block housing.

17. The tiltrotor aircraft as recited in claim 14 wherein each of the inboard and outboard pedestals further comprises a split pillow block housing.

18. The tiltrotor aircraft as recited in claim 14 wherein the inboard pedestal further comprises a full pillow block housing and wherein the outboard pedestal further comprise a split pillow block housing.

19. The tiltrotor aircraft as recited in claim 14 wherein each of the inboard and outboard pedestals further comprises a tip rib extending above the wing and defining a slot and a bearing cartridge including a bearing assembly received within the slot.

20. The tiltrotor aircraft as recited in claim 14 wherein the stiff couplings between the pylon assembly and the inboard and outboard pedestals are operable to maintain the output gear of the fixed gearbox in substantial collinear alignment with the input gear of the spindle gearbox.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Kooiman James Everett
• Decker George Ryan
• Vanbuskirk Matthew Carl
• Baines Andrew G
• Stanney Keith Alan

Classifications

• B64C29/0033 Primary

  the propellers being tiltable relative to the fuselage · CPC title

• B64C27/26

  characterised by provision of fixed wings · CPC title

• B64D2027/266

  Operations & Transport · mapped topic

• B64D27/26 Primary

  Operations & Transport · mapped topic

• B64C3/32

  specially adapted for mounting power plant · CPC title