Lubrication management systems for tiltrotor aircraft

Patent metadata

Field	Value
Publication number	US-11280398-B2
Application number	US-201816025147-A
Country	US
Kind code	B2
Filing date	Jul 2, 2018
Priority date	Jul 2, 2018
Publication date	Mar 22, 2022
Grant date	Mar 22, 2022

Abstract

A drive system for a tiltrotor aircraft operable to transition between rotary and non rotary flight modes. The drive system includes an engine to provide rotational energy and a proprotor assembly to receive rotational energy from the engine when the tiltrotor aircraft is in the rotary flight mode. The proprotor assembly is disengaged from the engine in the non rotary flight mode. The drive system includes a proprotor gearbox including one or more gears mechanically interposed between the engine and the proprotor assembly. The proprotor gearbox transfers rotational energy from the engine to the proprotor assembly when the tiltrotor aircraft is in the rotary flight mode. The drive system includes a lubricant operable to reduce friction between the gears and a lubrication management system to affect a temperature of the lubricant to enhance lubrication between the gears in the proprotor gearbox in the rotary flight mode.

First claim

What is claimed is:

1. A drive system for a tiltrotor aircraft operable to transition between rotary and non rotary flight modes, the drive system comprising:
an engine to provide rotational energy;
a proprotor assembly to receive rotational energy from the engine when the tiltrotor aircraft is in the rotary flight mode, the proprotor assembly disengaged from the engine in the non rotary flight mode;
a proprotor gearbox including one or more gears mechanically interposed between the engine and the proprotor assembly, the proprotor gearbox transferring rotational energy from the engine to the proprotor assembly when the tiltrotor aircraft is in the rotary flight mode;
a lubricant operable to reduce friction between the gears in the proprotor gearbox; and
a lubrication management system to affect a temperature of the lubricant while the tiltrotor aircraft is in the non rotary flight mode to enhance lubrication between the gears in the proprotor gearbox in the rotary flight mode.

2. The drive system as recited in claim 1 wherein the gears in the proprotor gearbox rotate in the rotary flight mode and are substantially nonrotating in the non rotary flight mode.

3. The drive system as recited in claim 1 wherein the lubricant further comprises shared lubricant and the lubrication management system further comprises a shared lubricant reservoir to at least partially contain the shared lubricant, the shared lubricant operable to lubricate the engine and the gears in the proprotor gearbox.

4. The drive system as recited in claim 3 wherein the lubrication management system further comprises a lubricant circulation subsystem including lubrication conduits to circulate the shared lubricant between the engine and the proprotor gearbox.

5. The drive system as recited in claim 4 wherein the lubricant circulation subsystem includes a lubrication pump to pump the shared lubricant to the proprotor gearbox.

6. The drive system as recited in claim 5 wherein the lubrication pump pumps the shared lubricant to the proprotor gearbox prior to a transition from the non rotary flight mode to the rotary flight mode.

7. The drive system as recited in claim 1 further comprising an engine lubricant to lubricate the engine, the lubrication management system further comprising:
an engine lubricant reservoir to at least partially contain the engine lubricant; and
an engine lubricant circulation subsystem including an engine lubricant pump to circulate the engine lubricant toward the proprotor gearbox, proximate to the proprotor gearbox and back toward the engine, thereby heating the proprotor gearbox.

8. The drive system as recited in claim 7 wherein the lubrication management system further comprises a proprotor gearbox lubricant reservoir proximate to the proprotor gearbox to at least partially contain a proprotor gearbox lubricant, the engine lubricant circulation subsystem further circulating the engine lubricant proximate to the proprotor gearbox lubricant reservoir to heat the proprotor gearbox lubricant therein.

9. The drive system as recited in claim 1 wherein the lubrication management system further comprises an electrothermal heater proximate to the proprotor gearbox, the electrothermal heater operable to heat the proprotor gearbox.

10. The drive system as recited in claim 9 wherein the electrothermal heater further comprises a plurality of electrically heated resistive elements.

11. The drive system as recited in claim 9 wherein the lubrication management system further comprises a proprotor gearbox lubricant reservoir proximate to the proprotor gearbox to at least partially contain a proprotor gearbox lubricant; and
wherein the electrothermal heater is proximate to the proprotor gearbox lubricant reservoir and is operable to heat the proprotor gearbox lubricant therein.

12. The drive system as recited in claim 11 wherein the proprotor gearbox lubricant reservoir has an outer surface and the electrothermal heater at least partially covers the outer surface of the proprotor gearbox lubricant reservoir.

13. The drive system as recited in claim 1 wherein the engine outputs heated air, the lubrication management system further comprising an air distribution subsystem to transport the heated air from the engine to the proprotor gearbox to heat the gears therein.

14. The drive system as recited in claim 13 wherein the heated air further comprises compressed air and the engine further comprises a compressor to output the compressed air.

15. The drive system as recited in claim 13 wherein the lubrication management system further comprises a proprotor gearbox lubricant reservoir proximate to the proprotor gearbox to at least partially contain a proprotor gearbox lubricant, the air distribution subsystem further operable to transport the heated air to the proprotor gearbox lubricant reservoir to heat the proprotor gearbox lubricant therein.

16. The drive system as recited in claim 1 wherein the lubrication management system further comprises a portion of an environmental control system outputting heated air and an air distribution subsystem to transport the heated air from the environment control system to the proprotor gearbox to heat the gears therein.

17. The drive system as recited in claim 16 wherein the lubrication management system further comprises a proprotor gearbox lubricant reservoir proximate to the proprotor gearbox to at least partially contain a proprotor gearbox lubricant, the air distribution subsystem further operable to transport the heated air from the environmental control system to the proprotor gearbox lubricant reservoir to heat the proprotor gearbox lubricant therein.

18. A tiltrotor aircraft operable to transition between rotary and non rotary flight modes, the tiltrotor aircraft comprising:
a fuselage;
a wing coupled to the fuselage;
an engine disposed in the fuselage, the engine to provide rotational energy;
a pylon assembly rotatably coupled to the wing;
a proprotor assembly rotatably coupled to the pylon assembly, the proprotor assembly to receive rotational energy from the engine when the tiltrotor aircraft is in the rotary flight mode, the proprotor assembly disengaged from the engine in the non rotary flight mode;
a proprotor gearbox disposed in the pylon assembly, the proprotor gearbox including one or more gears mechanically interposed between the engine and the proprotor assembly, the proprotor gearbox transferring rotational energy from the engine to the proprotor assembly when the tiltrotor aircraft is in the rotary flight mode;
a lubricant operable to reduce friction between the gears in the proprotor gearbox; and
a lubrication management system to affect a temperature of the lubricant while the tiltrotor aircraft is in the non rotary flight mode to enhance lubrication between the gears in the proprotor gearbox in the rotary flight mode.

19. The tiltrotor aircraft as recited in claim 18 wherein the lubrication management system is further operable to selectively heat the lubricant.

20. The tiltrotor aircraft as recited in claim 18 wherein the lubrication management system heats the lubricant prior to a transition from the non rotary flight mode to the rotary flight mode.

Assignees

• Textron Innovations Inc

Inventors

• Parsons Thomas Dewey
• Schank Troy Cyril

Classifications

• F16H57/045 Primary

  Lubricant storage reservoirs, e.g. reservoirs in addition to a gear sump for collecting lubricant in the upper part of a gear case · CPC title

• F16H57/0441

  Arrangements of pumps · CPC title

• F16H57/0445 Primary

  for supply of different gearbox casings or sections · CPC title

• F16H57/0413

  Controlled cooling or heating of lubricant; Temperature control therefor · CPC title

• F16H57/0423

  Lubricant guiding means mounted or supported on the casing, e.g. shields or baffles for collecting lubricant, tubes or pipes · CPC title