Reverse-flow gas turbine engine

Patent metadata

Field	Value
Publication number	US-11773785-B2
Application number	US-202318096071-A
Country	US
Kind code	B2
Filing date	Jan 12, 2023
Priority date	Sep 15, 2016
Publication date	Oct 3, 2023
Grant date	Oct 3, 2023

Abstract

A gas turbine engine has a first spool having a low pressure compressor section disposed forward of an air inlet along a direction of travel of the engine, and a low pressure turbine section disposed forward of the low pressure compressor section and drivingly engaged thereto. A second spool has a high pressure compressor section disposed forward of the low pressure compressor section, and a high pressure turbine section disposed forward of the high pressure compressor section and drivingly engaged thereto. The high pressure turbine section is disposed aft of the low pressure turbine section. An output drive shaft drivingly engages the low pressure turbine section and extends forwardly therefrom to drive a rotatable load. A method of operating a gas turbine engine is also discussed.

First claim

The invention claimed is:

1. A gas turbine engine, comprising:
a gas path extending along an axis between an air inlet and an exhaust outlet, wherein the air inlet is disposed aft of the exhaust outlet such that fluid flows within the gas path away from an aft end of the gas turbine engine and towards a front end of the gas turbine engine;
a low pressure compressor section, a high pressure compressor section, a high pressure turbine section and a low pressure turbine section arranged sequentially along the gas path between the air inlet and the exhaust outlet;
a first rotating assembly including the low pressure compressor section, the low pressure turbine section, and a first shaft that connects the low pressure compressor section to the low pressure turbine section;
a second rotating assembly including the high pressure compressor section and the high pressure turbine section;
a rotatable load, wherein the exhaust outlet is arranged axially between the rotatable load and the low pressure turbine section along the axis; and
an output drive shaft axially between and rotatably coupling the rotatable load to the first rotating assembly.

2. The gas turbine engine of claim 1 , wherein an inlet portion of the gas path turns radially inward toward the axis as the gas path extends from the air inlet.

3. The gas turbine engine of claim 1 , wherein an exhaust portion of the gas path turns radially outward away from the axis as the gas path extends to the exhaust outlet.

4. The gas turbine engine of claim 1 , wherein a connection between the output drive shaft and the first rotating assembly is axially between the low pressure turbine section and the exhaust outlet.

5. The gas turbine engine of claim 1 , wherein the rotatable load comprises a propeller, and the gas turbine engine is configured as a turboprop gas turbine engine.

6. The gas turbine engine of claim 1 , wherein the air inlet is disposed at the aft end of the gas turbine engine.

7. The gas turbine engine of claim 1 , wherein the exhaust outlet is disposed at the front end of the gas turbine engine.

8. The gas turbine engine of claim 1 , wherein the output drive shaft mechanically connects to the rotatable load and the first shaft.

9. The gas turbine engine of claim 1 , wherein the low pressure turbine section is connected to the first shaft through the output drive shaft.

10. The gas turbine engine of claim 1 , wherein a mechanical connection between the output drive shaft and the first shaft is axially between the low pressure turbine section and the exhaust outlet.

11. The gas turbine engine of claim 1 , wherein the first shaft and the output drive shaft are co-axial.

12. The gas turbine engine of claim 1 , wherein the second rotating assembly further includes a second shaft that connects the high pressure compressor section to the high pressure turbine section.

13. The gas turbine engine of claim 1 , wherein the high pressure turbine section is arranged axially between the output drive shaft and the high pressure compressor section along the axis.

14. The gas turbine engine of claim 1 , further comprising:
an accessory gearbox, the air inlet arranged axially between the accessory gearbox and the low pressure compressor section along the axis;
a tower shaft mechanically coupled to the second rotating assembly; and
an accessory gearbox drive shaft including
a first end mechanically coupled to the tower shaft; and
a second end mechanically coupled to the accessory gearbox.

15. The gas turbine engine of claim 14 , wherein the accessory gearbox drive shaft extends across the air inlet.

16. The gas turbine engine of claim 1 , further comprising an inter-stage bleed arranged axially between the high pressure compressor section and the low pressure compressor section along the axis.

Assignees

• Pratt & Whitney Canada

Inventors

• Morgan Keith
• PELUSO Robert
• Plante Ghislain
• Gekht Eugene
• Durocher Eric
• Dubreuil Jean

Classifications

• F02C7/32 Primary

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

• F01D1/26

  traversed by the working-fluid substantially axially · CPC title

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• F02C3/067

  having counter-rotating rotors (F02C3/073 takes precedence) · CPC title

• F02C3/113

  with variable power transmission between rotors · CPC title