Reconfigurable lubrication system for multiple powertrain orientations

• US 10,619,567 B2
• Filed: 04/06/2017
• Issued: 04/14/2020
• Est. Priority Date: 04/29/2016
• Status: Active Grant

• Current Assignee: Rolls-Royce Corporation (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce Corporation (Rolls-Royce Holdings Plc)
• Inventors: Roever, Douglas M.
• Primary Examiner(s): Walthour, Scott J
• Application Number:
  US15/481,006
• Publication Number:
  US 20170314469A1
• Time in Patent Office: 1,104 Days
• CPC Class Codes: B64D 27/20 within, or attached to, fuselages
• CPC Class Codes: B64D 33/00 Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
• CPC Class Codes: F01D 25/18 Lubricating arrangements of machines or engines in general F01M
• CPC Class Codes: F01D 25/20 using lubrication pumps
• CPC Class Codes: F02C 6/206 the vehicles being airscrew driven
• CPC Class Codes: F02C 7/06 Arrangements of bearings bearings F16C; Lubricating of turbo machines F01D25/18; of machines or engines in general F01M
• CPC Class Codes: F02C 7/20 Mounting or supporting of plant; Accommodating heat expansion or creep
• CPC Class Codes: F02C 7/32 Arrangement, mounting, or driving, of auxiliaries
• CPC Class Codes: F02C 7/36 Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user F02C3/107 - F02C3/13 and F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H
• CPC Class Codes: F05D 2260/4031 as in toothed gearing
• CPC Class Codes: F05D 2260/98 Lubrication

Abstract

A gas turbine engine assembly and a method for assembling a gas turbine engine assembly are disclosed herein. The gas turbine engine assembly includes an engine core and a gearbox. The gearbox includes a lubrication system having a first sump and a second sump. The lubrication system is configurable to provide oil from either of the first and second sumps in various configurations of the gas turbine engine assembly.

Claims

1. A method of assembling a gas turbine engine assembly comprising an engine core extending around a central axis, the method comprising:

coupling a gearbox to the engine core and arranging the engine core aft of the gearbox along the central axis, the gearbox including a lubrication system having a pump adapted to pressurize oil, a first sump located within a housing and configured to collect oil moved into the first sump by way of gravitational force when the housing is arranged in a first orientation, a second sump located within the housing and configured to collect oil moved into the second sump by way of gravitational force when the housing is arranged in a second orientation, and a manifold fluidly having a plenum;

coupling the pump to a plenum of the manifold by a pump line;

coupling the first sump to the plenum by a first-sump line;

coupling the second sump to the plenum by a second-sump line; and

blocking fluid communication into the plenum from one of the first sump or the second sump by coupling a configuration plate to the plenum.

2. The method of claim 1, wherein coupling the configuration plate to the plenum includes coupling the configuration plate to the plenum such that a plug of the configuration plate extends into one of the first-sump line or the second-sump line to block fluid communication into the plenum from the one of the first sump or the second sump.

3. A gas turbine engine assembly comprising:

an engine core extending around a central axis; and

a gearbox coupled to the engine core, the gearbox including a lubrication system having

a pump adapted to pressurize oil,

a first sump located within a housing and configured to collect oil moved into the first sump by way of gravitational force when the housing is arranged in a first orientation,

a second sump located within the housing and configured to collect oil moved into the second sump by way of gravitational force when the housing is arranged in a second orientation, and

a manifold fluidly coupled to the pump by a pump line, to the first sump by a first-sump line, and to the second sump by a second-sump line, the manifold including a configuration plate configured to fluidly couple the pump line to one of the first-sump line or the second-sump line;

wherein the engine core is configured to discharge pressurized gasses aftward along the central axis when the housing is arranged in each of the first and second orientations.

4. The gas turbine engine assembly of claim 3, wherein the configuration plate is further configured to block fluid communication between the pump line and one of the first-sump line or the second-sump line.

5. The gas turbine engine assembly of claim 4, wherein at least a portion of each of the first-sump line and the second-sump line are integrally formed in the housing.

6. The gas turbine engine assembly of claim 4, wherein the manifold includes a plenum formed to include a pump aperture opening into the pump line, a first-sump aperture opening into the first-sump line, and a second-sump aperture opening into the second-sump line.

7. The gas turbine engine assembly of claim 6, wherein the plenum is integrally formed in the housing.

8. The gas turbine engine assembly of claim 6, wherein the configuration plate includes a cap configured to cover the plenum and a plug extending from the cap into the plenum to block fluid communication into the plenum from one of the first-sump aperture and the second-sump aperture.

9. The gas turbine engine assembly of claim 8, wherein the configuration plate further includes a prevention tab coupled to the cap to prevent inadvertent mis-assembly of the plenum and the configuration plate.

10. The gas turbine engine assembly of claim 3, wherein the first orientation differs from the second orientation by 180 degrees measured about the central axis.

11. The gas turbine engine assembly of claim 3, wherein the gearbox is arranged about a centerline that is offset and parallel to the central axis.

12. An aircraft comprising:

a fuselage;

a first gas turbine engine assembly coupled to a first side of the fuselage; and

a second gas turbine engine assembly coupled to a second side of the fuselage opposite the first side,

wherein the first and second gas turbine engine assemblies each include a gearbox having a lubrication system, the lubrication system includes a pump, a first sump arranged within a housing and configured to collect oil moved by way of gravitational force when the housing is in a first orientation, a second sump arranged within the housing and configured to collect oil moved by way of gravitational force when the housing is in a second orientation, and a manifold fluidly coupled to the pump by a pump line, the manifold being coupled to the first sump by a first-sump line, and the manifold further being coupled to the second sump by a second-sump line, and the manifold includes a configuration plate configured to fluidly couple the pump line with one of the first-sump line or the second-sump line.

13. The aircraft of claim 12, wherein the gearbox includes a gear set supported by the housing and in fluid communication with the lubrication system.

14. The aircraft of claim 12, wherein the configuration plate is configured to block fluid communication between the pump line and the other of the first-sump line or the second-sump line.

15. The aircraft of claim 12, wherein at least a portion of each of the first-sump line and the second-sump line are integrally formed in the housing.

16. The aircraft of claim 12, wherein the manifold includes a plenum formed to include a pump aperture opening into the pump line, a first-sump aperture opening into the first-sump line, and a second-sump aperture opening into the second-sump line.

17. The aircraft of claim 16, wherein the plenum is integrally formed in the housing.

18. The aircraft of claim 16, wherein the configuration plate includes a cap configured to cover the plenum and a plug extending from the cap into the plenum to block fluid communication into the plenum from one of the first-sump aperture and the second-sump aperture.

19. The aircraft of claim 12, wherein each of the first and second gas turbine engine assemblies include an engine core extending around a central axis that is coupled to the gearbox, the gearbox is arranged about a centerline, and the central axis is located radially outward of the centerline.

20. The aircraft of claim 12, wherein each of the first and second gas turbine engine assemblies include an accessory gearbox, the accessory gearbox of the first gas turbine engine assembly has a first orientation relative to the fuselage, and the accessory gearbox of the second gas turbine engine assembly has a second orientation relative to the fuselage different from the first orientation.