Gas turbine engine accessories arrangement

Patent metadata

Field	Value
Publication number	US-10815899-B2
Application number	US-201615351803-A
Country	US
Kind code	B2
Filing date	Nov 15, 2016
Priority date	Nov 15, 2016
Publication date	Oct 27, 2020
Grant date	Oct 27, 2020

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.

First claim

The invention claimed is:

1. An aircraft engine comprising: an air inlet case for receiving air, a compressor, a combustor, a turbine and an accessory gear box (AGB) axially stacked along an engine centerline, the AGB positioned adjacent an axial end of the air inlet case and driven by the turbine, the aircraft engine further comprising a first engine accessory and a second engine accessory drivingly connected to the AGB and having respective input shafts disposed transverse to the engine centerline, wherein the AGB has a front face normal to the engine centerline and a top side, a bottom side, a left side and a right side extending axially from the front face, wherein the first engine accessory and the second engine accessory extend laterally from the left side or the right side of the AGB in a direction away from the left side or the right side, and wherein the first engine accessory and the second engine accessory are vertically offset relative to one another.

2. The engine defined in claim 1 , wherein the input shafts of the first engine accessory and the second engine accessory are perpendicular to the engine centerline and vertically spaced-apart.

3. The engine defined in claim 1 , wherein the AGB has an input axis parallel to the engine centerline.

4. The engine defined in claim 3 , wherein the input axis of the AGB is coaxial to the engine centerline.

5. The engine defined in claim 4 , wherein the AGB has a drive input shaft extending centrally through the air inlet case.

6. The engine defined in claim 5 , wherein the drive input shaft of the AGB is drivingly connected to a high pressure spool.

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

8. The engine defined in claim 7 , wherein the AGB comprises a first gear train and a second gear train, 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 first engine accessory forms part of a first group of accessories and the second engine accessory forms part of a second group of accessories, the first group of accessories and the second group of accessories being respectively drivingly connected to the first and second gear trains of the AGB.

9. The engine defined in claim 8 , 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 turbine shaft centerline and extending internally through a central bore of the air inlet case.

10. The engine defined in claim 8 , 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.

11. The engine defined in claim 8 , 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.

12. An aircraft 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) axially stacked along the engine centerline upstream of the air inlet case relative to a flow of air through the air inlet case, and accessories drivingly connected to the AGB, the accessories being oriented transversally to the engine centerline, the AGB having a front face normal to the engine centerline and a top side, a bottom side, a left side and a right side extending axially from the front face, the accessories extending laterally outwardly relative to the left side and the right side of the AGB, wherein the accessories include at least two vertically spaced-apart accessories.

13. The aircraft engine defined in claim 12 , wherein the accessories have respective input axes perpendicular to the engine centerline.

14. The aircraft engine defined in claim 12 , wherein the AGB is mounted to an axially facing surface of the air inlet case.

15. The aircraft engine defined in claim 12 , 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.

16. 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, the AGB having a front face normal to the engine centerline and a top side, a bottom side, a left side and a right side extending axially from the front face, and a first accessory and a second accessory drivingly connected to the AGB, the first accessory and the second accessory being oriented transversally to the engine centerline and mounted on the left side or the right side of the AGB, the first accessory and the second accessory being vertically offset from one another.

17. The gas turbine engine defined in claim 16 , wherein the AGB has an input axis coaxial to the engine centerline.

18. The gas turbine engine defined in claim 16 , wherein the first accessory and the second accessory have respective input axes perpendicular to an associated output axis of the AGB.

Assignees

• Pratt & Whitney Canada

Inventors

• Mitrovic Lazar
• Dubreuil Jean
• Durocher Eric
• Morgan Keith
• Desjardins Michel

Classifications

• F02C3/145 Primary

  the combustion chamber being in the reverse flow-type · CPC title

• F05B2220/302

  in gas turbines · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F05B2260/40311

  of the epicyclic, planetary or differential type · CPC title

• F02C7/32

  Arrangement, mounting, or driving, of auxiliaries · CPC title