TRANSVERSE MOUNTED ACCESSORY GEARBOX

• US 20160040601A1
• Filed: 08/26/2015
• Published: 02/11/2016
• Est. Priority Date: 06/14/2011
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Frost, Cristopher, Crestin, Michael Stephen, Laffan, James, Hwang, Mingfong, Hollingshead, Doug, Schmittenberg, Marc, Hayden, Mariee
• Granted Patent: US 9,926,849 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• 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 2250/313 the axes being perpendicular to each other
• CPC Class Codes: F05D 2260/53 using gears
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An accessory gear box for a gas turbine engine having a drive shaft with a rotational axis and a tower shaft coupled to the drive shaft is provided. The accessory gear box includes a first plurality of gears arranged, which extend along a first axis substantially parallel to the rotational axis of the drive shaft. The accessory gear box includes a second plurality of gears, which extend along a second axis. The accessory gear box includes a first shaft, with one of the first plurality of gears coupled to the first shaft, and one of the second plurality of gears coupled to a second shaft. The one of the second plurality of gears coupled to the first shaft includes a first engagement surface and a second engagement surface, and the second engagement surface is coupled to another one of the second plurality of gears to drive the second shaft.

Claims

1. An accessory gear box for a gas turbine engine having a drive shaft with a rotational axis and a tower shaft coupled to the drive shaft, the accessory gear box comprising:

a first plurality of gears arranged within the accessory gear box, the first plurality of gears extending along a first axis substantially parallel to the rotational axis of the drive shaft;

a second plurality of gears arranged within the accessory gear box, the second plurality of gears extending along a second axis, the second axis offset from and substantially parallel to the first axis; and

a first shaft, with one of the first plurality of gears coupled to the first shaft, and one of the second plurality of gears coupled to a second shaft,

wherein the one of the second plurality of gears coupled to the first shaft includes a first engagement surface and a second engagement surface, the first engagement surface to engage the tower shaft and the second engagement surface is coupled to another one of the second plurality of gears to drive the second shaft.

2. The accessory gear box of claim 1, wherein the one of the first plurality of gears coupled to the first shaft is coupled to another one of the first plurality of gears to drive a third shaft.

3. The accessory gear box of claim 1, wherein each of the first plurality of gears include a rotational axis, and the rotational axis of each of the first plurality of gears is transverse to a longitudinal axis of the tower shaft.

4. The accessory gear box of claim 1, further comprising a housing that extends along a longitudinal axis, and the longitudinal axis of the housing is substantially parallel to the rotational axis of the drive shaft.

5. The accessory gear box of claim 1, wherein the first engagement surface is defined along a surface of the one of the second plurality of gears near a periphery of the one of the second plurality of gears.

6. The accessory gear box of claim 5, wherein the second engagement surface is defined at the periphery of the one of the second plurality of gears.

7. The accessory gear box of claim 1, wherein the first plurality of gears are arranged in a first row, and the second plurality of gears are arranged in a second row, the first row and the second row comprising the only gears arranged within the accessory gear box.

8. A gas turbine engine, comprising:

a drive shaft having a rotational axis;

a tower shaft having a first end coupled to the drive shaft, and a second end including a bevel gear, the tower shaft having a longitudinal axis transverse to the rotational axis of the drive shaft;

an accessory gear box comprising;

a first plurality of gears arranged within the accessory gear box, the first plurality of gears extending along a first axis substantially parallel to the rotational axis of the drive shaft and transverse to the longitudinal axis of the tower shaft;

a second plurality of gears arranged within the accessory gear box, the second plurality of gears extending along a second axis, the second axis offset from and substantially parallel to the first axis and the rotational axis of the drive shaft; and

a first shaft, with one of the first plurality of gears coupled to the first shaft, and one of the second plurality of gears coupled to a second shaft,

wherein the one of the second plurality of gears coupled to the first shaft includes a first engagement surface and a second engagement surface, and the first engagement surface is coupled to the bevel gear of the tower shaft.

9. The gas turbine engine of claim 8, wherein the second engagement surface is coupled to a third engagement surface of another of the second plurality of gears to drive the second shaft.

10. The gas turbine engine of claim 8, wherein the one of the first plurality of gears includes a fourth engagement surface, which is coupled to a fifth engagement surface of another one of the first plurality of gears to drive a third shaft.

11. The gas turbine engine of claim 8, wherein the first plurality of gears are arranged in a first row, and the second plurality of gears are arranged in a second row, the first row and the second row comprising the only gears arranged within the accessory gear box.

12. The gas turbine engine of claim 8, wherein the first engagement surface is defined along a surface of the one of the second plurality of gears near a periphery of the one of the second plurality of gears and the second engagement surface is defined at the periphery to extend about a perimeter of the one of the second plurality of gears.

13. The gas turbine engine of claim 9, wherein the second shaft drives an inlet particle accelerator fan, a permanent magnet alternator and an air turbine starter.

14. The gas turbine engine of claim 8, wherein the first shaft drives an air oil separator.

15. The gas turbine engine of claim 10, wherein the third shaft drives an oil pump and a fuel metering unit.

16. A gas turbine engine, comprising:

a drive shaft having a rotational axis;

a tower shaft having a first end coupled to the drive shaft, and a second end including a bevel gear, the tower shaft having a longitudinal axis transverse to the rotational axis of the drive shaft;

an accessory gear box comprising;

a first plurality of gears arranged within the accessory gear box, the first plurality of gears each having a rotational axis, the rotational axis of each of the first plurality of gears substantially perpendicular to the rotational axis of the drive shaft and the longitudinal axis of the tower shaft;

a second plurality of gears arranged within the accessory gear box, the second plurality of gears each having a rotational axis, the rotational axis of each of the second plurality of gears substantially perpendicular to the rotational axis of the drive shaft and the longitudinal axis of the tower shaft, and the rotational axis of each of the second plurality of gears substantially parallel to the rotational axis of each of the first plurality of gears; and

a first shaft, with one of the first plurality of gears coupled to the first shaft, and one of the second plurality of gears coupled to a second shaft,

wherein the one of the second plurality of gears coupled to the first shaft includes a first engagement surface and a second engagement surface, the first engagement surface is coupled to the bevel gear of the tower shaft and the second engagement surface is coupled to another one of the second plurality of gears to drive the second shaft.

17. The gas turbine engine of claim 16, wherein the one of the first plurality of gears includes a fourth engagement surface, which is coupled to a fifth engagement surface of another one of the first plurality of gears to drive a third shaft.

18. The gas turbine engine of claim 16, wherein the first plurality of gears are arranged in a first row, and the second plurality of gears are arranged in a second row, the first row and the second row comprising the only gears arranged within the accessory gear box.

19. The gas turbine engine of claim 16, wherein the second shaft drives an inlet particle accelerator fan, a permanent magnet alternator and an air turbine starter, and the first shaft drives an air oil separator.

20. The gas turbine engine of claim 17, wherein the third shaft drives an oil pump and a fuel metering unit.