Multi-spool gas turbine engine architecture

Patent metadata

Field	Value
Publication number	US-11041443-B2
Application number	US-201916583896-A
Country	US
Kind code	B2
Filing date	Sep 26, 2019
Priority date	Sep 15, 2016
Publication date	Jun 22, 2021
Grant date	Jun 22, 2021

Abstract

A multi-spool gas turbine engine comprises a low pressure (LP) spool and a high pressure (HP) spool independently rotatable about a central axis extending through an accessory gear box (AGB). The LP spool has an LP compressor, which is axially positioned between the HP compressor of the HP spool and the AGB. A tower shaft drivingly connects the HP spool to the AGB.

First claim

The invention claimed is:

1. A turboprop or turboshaft engine comprising: an output drive shaft having a front end configurable to drivingly engage a rotatable load; a low pressure (LP) spool and a high pressure (HP) spool rotatable independently of one another about a central axis, the LP spool having an LP compressor and an LP turbine, the LP turbine drivingly engaged to the output drive shaft via a reduction gear box (RGB), the HP spool having an HP turbine and an HP compressor; the turboprop or turboshaft engine further comprising an accessory gear box (AGB) and a tower shaft drivingly connecting the AGB to the HP spool, the AGB is disposed on the turboprop or turboshaft engine so that the central axis extends through the AGB, wherein the LP compressor is axially positioned between the HP compressor and the AGB.

2. The turboprop or turboshaft engine defined in claim 1 , wherein the LP compressor is disposed forward of an air inlet along a direction of travel of the turboprop or turboshaft engine and in fluid communication with the air inlet, the AGB being disposed aft of the air inlet.

3. The turboprop or turboshaft engine defined in claim 2 , wherein the LP turbine is disposed forward of the LP compressor, the HP compressor is disposed forward of the LP compressor and in fluid communication therewith to receive pressurized air therefrom, the HP turbine is disposed forward of the HP compressor, the HP turbine is disposed aft of the LP turbine and in fluid communication therewith; and wherein the output drive shaft extends forwardly therefrom the LP turbine, the output drive shaft configurable to drivingly engage the rotatable load disposed forward of the LP turbine.

4. The turboprop or turboshaft engine as defined in claim 1 , wherein the AGB has a drive shaft having a first end mechanically coupled to the tower shaft and a second end mechanically coupled to the AGB.

5. The turboprop or turboshaft engine defined in claim 1 , wherein the AGB is mounted in-line to an axially facing surface of a casing of the turboprop or turboshaft engine.

6. The turboprop or turboshaft engine defined in claim 5 , wherein the AGB is centered relative to the central axis of the turboprop or turboshaft engine.

7. The turboprop or turboshaft engine defined in claim 1 , further comprising at least one accessory side-mounted to the AGB, the at least one accessory having an input axis which is non-parallel to the central axis.

8. The turboprop or turboshaft engine defined in claim 7 , wherein the input axis of the at least one accessory is transversal to the central axis.

9. The turboprop or turboshaft engine defined in claim 1 , wherein the LP and the HP spools are both drivingly connected to the AGB.

10. The turboprop or turboshaft engine defined in claim 1 , wherein the AGB comprises first and second gear trains, the first gear train having a first drive input, the second gear train having a second drive input, the first drive input being drivingly connected to the tower shaft, the second drive input being drivingly connected to the LP spool.

11. The turboprop or turboshaft engine defined in claim 10 , further comprising first and second groups of accessories, the first and second gear trains being respectively drivingly connected to the first and second groups of accessories.

12. The turboprop or turboshaft engine defined in claim 11 , 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.

13. A reverse flow gas turbine engine comprising:
an output drive shaft having a front end configurable to drivingly engage a rotatable load;
a low pressure (LP) spool rotatable about an engine axis and including an LP turbine drivingly engaged to the output drive shaft, and an LP compressor drivingly connected to the LP turbine, the LP turbine disposed forward of the LP compressor relative to a front end of the output drive shaft; and
a high pressure (HP) spool rotatable about the engine axis independently of the LP spool, the HP spool including an HP turbine and an HP compressor drivingly engaged to an HP shaft, the HP compressor disposed forward of the LP compressor and in fluid communication therewith, and the HP turbine disposed aft of the LP turbine and in fluid communication therewith;
a tower shaft mechanically coupled to the HP spool;
an accessory gearbox (AGB) disposed aft of the LP compressor, the engine axis extending through the AGB; and
an AGB drive shaft having a first end mechanically coupled to the tower shaft and a second end mechanically coupled to the AGB;
wherein the LP spool has an LP compressor shaft extending along the engine axis aft of the LP compressor, the LP compressor shaft in driving engagement with the AGB.

14. The reverse flow gas turbine engine defined in claim 13 , wherein the AGB is centered relative to the engine axis.

15. The reverse flow gas turbine engine defined in claim 13 , further comprising at least one accessory side-mounted to the AGB.

16. The reverse flow gas turbine engine defined in claim 15 , wherein the at least one accessory has an input axis oriented transversally to the engine axis.

17. The reverse flow gas turbine engine defined in claim 13 , wherein the AGB comprises first and second gear trains, the first gear train having a first drive input, the second gear train having a second drive input, the first drive input being drivingly connected to the tower shaft, the second drive input being drivingly connected to the LP compressor shaft.

18. The reverse flow gas turbine engine defined in claim 17 , further comprising first and second groups of accessories, the first and second gear trains being respectively drivingly connected to the first and second groups of accessories.

19. A multi-spool gas turbine engine comprising: a low pressure (LP) spool;
a high pressure (HP) spool, the LP spool and the HP spool being independently rotatable about a central axis, the LP pressure spool comprising an LP compressor and an LP turbine, the HP spool comprising an HP turbine and an HP compressor; and an accessory gear box (AGB), the central axis extending through the AGB and the LP compressor being axially positioned between the HP compressor and the AGB, the AGB comprising first and second gear trains, the first gear train having a first drive input, the second gear train having a second drive input, the first and second drive inputs being respectively drivingly connected to the HP and LP spools, wherein the LP spool has an LP compressor shaft extending along the central axis aft of the LP compressor, the LP compressor shaft in driving engagement with the second drive input of the AGB.

20. The multi spool gas turbine engine defined in claim 19 , wherein a tower shaft drivingly connects the HP spool to the first drive input of the first gear train, the tower shaft extending from the HP spool in a direction away from the central axis.

21. The multi spool gas turbine engine defined in claim 20 , wherein the tower shaft is drivingly connected to an AGB drive shaft, the AGB drive shaft having an axial component parallel to the central axis.

22. The multi spool gas turbine engine defined in claim 21 , wherein the second drive input is coaxial to the central axis.

23. The multi-spool gas turbine engine defined in claim 19 , further comprising first and second groups of accessories, the firs

Assignees

• Pratt & Whitney Canada

Inventors

• Durocher Eric
• Morgan Keith
• Mitrovic Lazar
• Dubreuil Jean
• Poulin Martin

Classifications

• F02C3/145

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

• Y02T50/60

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

• F02C7/32 Primary

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

• F02C6/206

  the vehicles being airscrew driven · CPC title

• F02C3/10

  with another turbine driving an output shaft but not driving the compressor · CPC title