Transverse mounted accessory gearbox

• US 9,145,834 B2
• Filed: 06/14/2011
• Issued: 09/29/2015
• Est. Priority Date: 06/14/2011
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Frost, Cristopher, Richardson, Mary Eileen, Crestin, Michael Stephen, Laffan, James, Hwang, Mingfong, Hollingshead, Doug, Schmittenberg, Marc
• Primary Examiner(s): White, Dwayne J
• Assistant Examiner(s): Brown, Adam W
• Application Number:
  US13/160,380
• Publication Number:
  US 20120317991A1
• Time in Patent Office: 1,568 Days
• Field of Search: 415/122.1, 415/124.1, 415/121.3, 416/170.R, 416/171, 608/02, 60/391.63
• 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 2250/312 the axes being parallel to each other
• 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

A gas turbine engine and an accessory gear box (AGB) are provided for. The gas turbine engine comprises a drive shaft, a compressor, a combustor and an exhaust turbine, where the exhaust turbine and the compressor are coaxially connected by the drive shaft. The gas turbine engine further comprises an engine casing of varying diameters circumferentially enveloping the compressor, the combustor and the exhaust turbine with a waist located between the compressor and the combustor. The gas turbine engine also includes an accessory gear box (AGB) attached to the engine casing at the waist, the AGB comprising a gear rotating on an axis extending in a transverse direction relative to that of the drive shaft.

Claims

1. A gas turbine engine, comprising:

a compressor, a combustor and an exhaust turbine each coaxially and serially coupled by a drive shaft having a rotational axis;

an engine casing of varying diameters circumferentially enveloping the compressor, the combustor and the exhaust turbine and having a waist located between the compressor and the combustor;

an accessory gear box (AGB) attached to the engine casing near the waist, the AGB comprising a plurality of gears rotating about a plurality of parallel axes, each of the parallel axes extending in a direction that is substantially perpendicular relative to the rotational axis of the drive shaft, each of the gears arranged in the AGB to form a single row within the AGB, the single row extending along an axis substantially parallel to the rotational axis of the drive shaft; and

a tower shaft that couples one of the plurality of gears to the drive shaft, the tower shaft having a longitudinal axis that is transverse to the rotational axis of the drive shaft and the plurality of axes of the plurality of gears.

2. The gas turbine engine of claim 1, wherein the AGB is connected to and is driven by the drive shaft via the tower shaft through a tower shaft opening between the AGB and the engine casing.

3. The gas turbine engine of claim 2, wherein the AGB is lubricated by oil.

4. The gas turbine engine of claim 3, wherein all of the oil drains into the engine casing via the tower shaft opening.

5. The gas turbine engine of claim 4, wherein the AGB comprises at least one oil scavenging port permitting scavenging oil during operation at non-level attitudes.

6. The gas turbine engine of claim 2, wherein the tower shaft engages the drive shaft downstream of a low pressure stage of the compressor.

7. A gas turbine engine comprising an accessory gear box (AGB) configured to drive one or more accessories of a gas turbine engine having a drive shaft, the drive shaft having a rotational axis, the drive shaft coaxially and serially coupling at least a compressor and a combustor of the gas turbine engine, the AGB comprising:

a housing having an opening;

two or more gears mounted within the housing, each of the two or more gears rotating about its own axis, each axis being parallel to the other axis and both axes being substantially perpendicular to the rotational axis of the drive shaft of the gas turbine engine, each of the gears arranged in the AGB to form a single row within the AGB, the single row extending along an axis substantially parallel to the rotational axis of the drive shaft; and

a tower shaft that couples one of the two or more gears to the drive shaft, the tower shaft having a longitudinal axis that is transverse to the rotational axis of the drive shaft and the axes of the two or more gears.

8. The AGB of claim 7, further comprising:

a translational gear,

wherein the tower shaft has a first end and a second end, the first end connected to one of the two or more gears via the translational gear and the second end connected to the drive shaft via the opening in the housing.

9. The AGB of claim 8, wherein lubricating oil is permitted to drain into the engine casing via the opening.

10. The AGB of claim 9, wherein the AGB comprises at least one oil scavenging port other than the opening permitting oil scavenging at non-level attitudes.

11. A gas turbine engine, comprising:

a compressor, a combustor and an exhaust turbine are each coaxially and serially coupled by a drive shaft having a rotational axis; and

an accessory gear box (AGB), the AGB further comprising;

a housing having an opening;

two or more gears mounted within the housing, each of the two or more gears rotating about its own axis, each axis being parallel to the other axis and both axes being substantially perpendicular to the rotational axis of the drive shaft of the gas turbine engine, each of the gears arranged in the AGB to form a single row within the AGB, the single row extending along an axis substantially parallel to the rotational axis of the drive shaft;

a translational gear; and

a tower shaft with a first end and a second end, the first end connected to one of the two or more gears via the translational gear and the second end connected to the drive shaft via the opening in the housing, the tower shaft having a longitudinal axis that is transverse to the rotational axis of the drive shaft and the axes of the two or more gears.

12. The gas turbine engine of claim 11, wherein lubricating oil is permitted to drain into an engine casing via the opening.

13. The gas turbine engine of claim 12, wherein the AGB comprises at least one oil scavenging port other than the opening permitting oil scavenging at non-level positional attitudes.