GAS TURBINE ENGINE ACCESSORIES ARRANGEMENT

• US 20180135522A1
• Filed: 11/15/2016
• Published: 05/17/2018
• Est. Priority Date: 11/15/2016
• Status: Active Grant

• Current Assignee: Pratt & Whitney Canada Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Pratt & Whitney Canada Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: MITROVIC, Lazar, DUBREUIL, Jean, DUROCHER, Eric, MORGAN, Keith, DESJARDINS, Michel
• Granted Patent: US 10,815,899 B2
• Time in Patent Office: Days
• CPC Class Codes: F02C 3/04 having a turbine driving a compressor power transmission arrangements F02C7/36; control of working fluid flow F02C9/16
• CPC Class Codes: F02C 3/145 the combustion chamber being in the reverse flow-type
• CPC Class Codes: F02C 7/04 Air intakes for gas-turbine plants or jet-propulsion plants
• 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: F05B 2220/302 in gas turbines
• CPC Class Codes: F05B 2260/40311 of the epicyclic, planetary or differential type
• CPC Class Codes: F05D 2250/311 the axes being in line
• CPC Class Codes: F05D 2250/313 the axes being perpendicular to each other
• CPC Class Codes: F05D 2250/314 the axes being inclined in relation to each other
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A gas turbine engine has an in-line mounted accessory gear box (AGB) and an accessory drivingly connected to the AGB, the accessory being oriented transversally to the engine centerline.

Claims

1. A gas turbine engine comprising:

an air inlet case for receiving air, a compressor, a combustor, a turbine having a shaft rotatable about a turbine shaft centerline, an accessory gear box (AGB) positioned adjacent an axial end of the air inlet case and driven by the turbine, and at least one engine accessory drivingly connected to the AGB and having an input shaft having an input axis which is disposed transverse to the turbine shaft.

2. The gas turbine engine defined in claim 1, wherein the input axis of the at least one engine accessory is perpendicular to the engine centerline.

3. The gas turbine engine defined in claim 1, wherein the AGB is centered relative to turbine shaft centerline.

4. The gas turbine engine defined in claim 1, wherein the AGB has an input axis parallel to the turbine shaft centerline.

5. The gas turbine engine defined in claim 4, wherein the input axis of the AGB is coaxial to the turbine shaft centerline.

6. The gas turbine engine defined in claim 1, wherein the at least one engine accessory extends laterally from the AGB.

7. The gas turbine engine defined in claim 5, wherein the AGB has a drive input shaft extending centrally through the air inlet case.

8. The gas turbine engine defined in claim 7, wherein the drive input shaft of the AGB is drivingly connected to a high pressure spool.

9. The gas turbine engine defined in claim 1, wherein the gas turbine engine has a low pressure (LP) spool and a high pressure (HP) spool, and wherein LP and the HP spools are both drivingly connected to the AGB.

10. The gas turbine engine defined in claim 9, wherein the AGB comprises first and second gear trains, the first gear train being drivingly connected to the HP spool, the second gear train being drivingly connected to the LP spool, and wherein the at least one accessory comprises a first group of accessories and a second group of accessories, the first and second groups of accessories being respectively drivingly connected to the first and second gear trains of the AGB.

11. The gas turbine engine defined in claim 10, wherein the first gear train has a first input shaft, the second gear train has a second input shaft, the first and second input shafts being parallel to the engine centerline and extending internally through a central bore of the air inlet case.

12. The gas turbine engine defined in claim 10, wherein the first gear train has a first input shaft, the second gear train has a second input shaft, the first input shaft being drivingly connected to the HP spool via a tower shaft, the second input shaft being connected to the LP spool centrally through the air inlet case.

13. The gas turbine engine defined in claim 10, wherein the first group of accessories comprises at least one of:

a starter, a fuel control unit and an oil pump; and

wherein the second group of accessories comprises at least one of;

an air vacuum pump and an electric generator.

14. A gas turbine engine comprising:

an air inlet case for receiving air, a compressor rotatable about an engine centerline for pressurizing the air from the air inlet case, a combustor in which the air compressed by the compressor is mixed with fuel and ignited for generating a stream of combustion gases, a turbine rotatable about the engine centerline for extracting energy from the combustion gases, an accessory gear box (AGB) centered relative to the engine centerline upstream of the air inlet case, and accessories drivingly connected to the AGB, the accessories being oriented transversally to the engine centerline.

15. The gas turbine engine defined in claim 14, wherein the accessories have respective input axes perpendicular to the engine centerline.

16. The gas turbine engine defined in claim 14, wherein the AGB is mounted to an axially facing surface of the air inlet case.

17. The gas turbine engine defined in claim 14, wherein the accessories comprise oil/fuel accessories and electrical accessories, the oil/fuel accessories being grouped together on a first side of a central plane of the engine, the electrical accessories being grouped together one a second side of the central plane of the engine.

18. A gas turbine engine comprising an air inlet case for receiving air, a compressor rotatable about an engine centerline for pressurizing the air from the air inlet case, a combustor in which the air compressed by the compressor is mixed with fuel and ignited for generating a stream of combustion gases, a turbine rotatable about the engine centerline for extracting energy from the combustion gases, an accessory gear box (AGB) mounted in-line with the engine centerline, and at least one accessory drivingly connected to the AGB, the at least one accessory being oriented transversally to the engine centerline.

19. The gas turbine engine defined in claim 18, wherein the AGB has an input axis coaxial to the engine centerline.

20. The gas turbine engine defined in claim 18, wherein the at least one accessory has an input axis perpendicular to an associated output axis of the AGB.