INTEGRAL OFFSET OIL TANK FOR INLINE ACCESSORY GEARBOX

• US 20170314474A1
• Filed: 04/28/2016
• Published: 11/02/2017
• Est. Priority Date: 04/28/2016
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Wotzak, Mark Gregory
• Granted Patent: US 10,072,582 B2
• Time in Patent Office: Days
• CPC Class Codes: B64D 2027/005 Aircraft with an unducted turbofan comprising contra-rotating rotors, e.g. contra-rotating open rotors [CROR]
• CPC Class Codes: B64D 27/10 of gas-turbine type jet aircraft B64D27/16
• CPC Class Codes: F01D 25/18 Lubricating arrangements of machines or engines in general F01M
• 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 7/32 Arrangement, mounting, or driving, of auxiliaries
• CPC Class Codes: F02K 3/06 with front fan
• CPC Class Codes: F05D 2260/4031 as in toothed gearing
• CPC Class Codes: F05D 2260/98 Lubrication
• CPC Class Codes: F16H 57/04 Features relating to lubrication or cooling or heatingin hydrokinetic gearing F16H41/30; control of lubrication or cooling in hydrostatic gearing F16H61/4165
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An in-line propeller gearbox of a turboprop gas turbine engine includes a lubricant reservoir disposed spaced radially offset from the engine'"'"'s central axis of rotation and asymmetrically with respect to the central axis of rotation such that the central axis of rotation does not extend through the lubricant reservoir.

Claims

1. A lubrication assembly for auxiliary accessories disposed at the aft end of an in-line turboprop engine having a central axis of rotation defining an axial direction and including a compressor coupled to a compressor shaft that is rotatable about the central axis of rotation, a lubricant supply, an exhaust manifold and an air intake manifold disposed axially aft of the exhaust manifold, the lubrication assembly comprising:

an accessory gearbox including a forward wall extending transversely with respect to the axial direction, an aft wall spaced apart from the forward wall in the axial direction and disposed aft of the forward wall, and at least a first sidewall extending in the axial direction and connecting the forward wall to the aft wall, the forward wall of the accessory gearbox at least partially defining the air intake manifold of the engine;

a plurality of rotatable shafts that are extending along the axial direction through the aft wall of the accessory gearbox, each respective rotatable shaft being disposed to be connected to drive a respective one of the auxiliary accessories of the engine;

gearing disposed within the accessory gearbox and connected to the shafts; and

a lubricant reservoir for containing lubricant for the accessory gearbox, the lubricant reservoir being configured to be connected to be supplied with lubricant from the lubricant supply of the engine, the lubricant reservoir being defined in part by the first sidewall of the accessory gearbox, the first sidewall being disposed to separate the lubricant reservoir from the accessory gearbox, and

wherein the lubricant reservoir defines an aft chamber projecting axially aft beyond the aft wall of the accessory gearbox.

2. The lubrication assembly of claim 1, wherein the lubricant reservoir is disposed spaced radially offset from the central axis of rotation and asymmetrically with respect to the central axis of rotation such that the central axis of rotation does not extend through the lubricant reservoir.

3. The lubrication assembly of claim 1, wherein the lubricant reservoir includes a forward wall that forms part of the air intake manifold and renders the lubricant reservoir and the air intake manifold a unitary structure.

4. The lubrication assembly of claim 1, wherein the lubricant reservoir being of a shape that encloses less internal volume at the aft end than the internal volume enclosed at the forward end that is disposed opposite to the aft end of the lubricant reservoir.

5. The lubrication assembly of claim 1, wherein the lubricant reservoir defines an upper portion and a lower portion disposed spaced apart from the upper portion, wherein the lubricant reservoir defines an intermediate portion disposed intermediate the upper portion and the lower portion and wherein the volume of the interior of the intermediate portion of the lubricant reservoir is greater than the volume of the interior of the lower portion of the lubricant reservoir.

6. The lubrication assembly of claim 5, wherein the intermediate portion of the lubricant reservoir includes the aft chamber of the lubricant reservoir.

7. The lubrication assembly of claim 1, wherein the forward wall of the accessory gearbox defines an opening configured for receiving the compressor shaft therethrough and disposing an aft end of the compressor shaft within the accessory gearbox.

8. The lubrication assembly of claim 7, further comprising:

a journal having a first end configured for being non-rotatably coupled to the aft end of the compressor shaft and having a second end disposed axially spaced apart from the first end, and

a pinion non-rotatably coupled to the second end of the journal.

9. The lubrication assembly of claim 8, further comprising:

a take-off gear rotatably supported within the accessory gearbox and drivingly engaged by the pinion for transmitting driving torque from the compressor shaft to the take-off gear for powering the auxiliary accessories.

10. The lubrication assembly of claim 8, further comprising a bearing disposed within the accessory gearbox and having an outer race non-rotatably coupled to the accessory gearbox and an inner race rotatable with respect to the outer race and non-rotatably coupled to the journal.

11. The lubrication assembly of claim 7, further comprising a lubricant seal disposed within the opening defined through forward wall of the accessory gearbox.

12. An in-line turboprop engine comprising:

a propeller disposed at the forward end of the engine and including a plurality of blades extending radially from a hub and rotatable about a first axis of rotation defined centrally through the hub;

a plurality of auxiliary accessories disposed at the aft end of the engine, each of the auxiliary accessories being coupled to a respective accessory driveshaft that is rotatable for providing power to operate the respective auxiliary accessory;

an engine exhaust manifold disposed aft of the propeller;

a power turbine disposed aft of the engine exhaust manifold and coupled to drive rotation of the propeller;

a high pressure turbine disposed aft of the power turbine;

a combustor disposed aft of the high pressure turbine;

a compressor disposed aft of the combustor;

an air intake manifold disposed aft of the compressor and defining a front wall and a rear wall disposed aft of the front wall, the air intake manifold further defining a plurality of guide vanes, each guide vane extending between the front wall and the rear wall, each guide vane being spaced circumferentially apart from each adjacent guide vane;

a lubricant supply carried by the engine;

a lubrication assembly for connection to the auxiliary accessories, the lubrication assembly including;

an accessory gearbox including a forward wall extending transversely with respect to the axial direction, an aft wall spaced apart from the forward wall in the axial direction and disposed aft of the forward wall, and at least a first sidewall extending in the axial direction and connecting the forward wall to the aft wall, the forward wall of the accessory gearbox at least partially defining the rear wall of the air intake manifold of the engine, and

a plurality of rotatable shafts that are extending along the axial direction through the aft wall of the accessory gearbox, each respective rotatable shaft being disposed to be connected to drive a respective one of the auxiliary accessories of the engine,

gearing disposed within the accessory gearbox and connected to the shafts,

a lubricant reservoir for containing lubricant for the accessory gearbox, the lubricant reservoir being configured to be connected to be supplied with lubricant from the lubricant supply of the engine, the lubricant reservoir being defined in part by the first sidewall of the accessory gearbox, the first sidewall being disposed to separate the lubricant reservoir from the accessory gearbox, and

wherein the lubricant reservoir defines an aft chamber projecting axially aft beyond the aft wall of the accessory gearbox.

13. The turboprop engine of claim 12, wherein the lubricant reservoir is disposed spaced radially offset from the central axis of rotation and asymmetrically with respect to the central axis of rotation such that the central axis of rotation does not extend through the lubricant reservoir.

14. The turboprop engine of claim 12, wherein the lubricant reservoir defines an upper portion and a lower portion disposed spaced apart from the upper portion, wherein the lubricant reservoir defines an intermediate portion disposed intermediate the upper portion and the lower portion and wherein the volume of the interior of the intermediate portion of the lubricant reservoir is greater than the volume of the interior of the lower portion of the lubricant reservoir.

15. The turboprop engine of claim 14, wherein the intermediate portion of the lubricant reservoir includes the aft chamber of the lubricant reservoir.

16. The turboprop engine of claim 12, wherein the lubricant reservoir being of a shape that encloses less internal volume at the aft end than the internal volume enclosed at the forward end that is disposed opposite to the first end.

17. The turboprop engine of claim 12, wherein the lubricant reservoir includes a forward wall that forms part of the air intake manifold and renders the lubricant reservoir and the air intake manifold a unitary structure.

18. The turboprop engine of claim 12, wherein the forward wall of the accessory gearbox defines an opening configured for receiving the compressor shaft therethrough and disposing an aft end of the compressor shaft within the accessory gearbox.

19. The turboprop engine of claim 18, further comprising:

a journal having a first end configured for being non-rotatably coupled to the aft end of the compressor shaft and having a second end disposed axially spaced apart from the first end,

a bearing disposed within the accessory gearbox and having an outer race non-rotatably coupled to the accessory gearbox and an inner race rotatable with respect to the outer race and non-rotatably coupled to the journal, and

a pinion non-rotatably coupled to the second end of the journal.

20. The turboprop engine of claim 18 further comprising:

a lubricant seal disposed within the opening defined through forward wall of the accessory gearbox.