Reverse-flow gas turbine engine

• US 11,415,063 B2
• Filed: 09/15/2016
• Issued: 08/16/2022
• Est. Priority Date: 09/15/2016
• 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: Morgan, Keith, Peluso, Robert, Plante, Ghislain, Gekht, Eugene, Durocher, Eric, Dubreuil, Jean
• Primary Examiner(s): Gartenberg, Ehud
• Assistant Examiner(s): Ng, Henry
• Application Number:
  US15/266,321
• Publication Number:
  US 20180073428A1
• Time in Patent Office: 2,161 Days
• CPC Class Codes: F01D 1/26 traversed by the working-fluid substantially axially
• 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 3/067 having counter-rotating rotors F02C3/073 takes precedence
• CPC Class Codes: F02C 3/113 with variable power transmission between rotors
• CPC Class Codes: F02C 3/145 the combustion chamber being in the reverse flow-type
• CPC Class Codes: F02C 6/206 the vehicles being airscrew driven
• 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: F04D 25/024 the driving means being assisted by a power recovery turbine
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2250/38 angled, e.g. sweep angle
• CPC Class Codes: F05D 2260/40 Transmission of power
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

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.

Claims

1. A reverse-flow gas turbine engine, comprising:

an aft end and a front end, an air inlet disposed at the aft end of the reverse-flow gas turbine engine and an exhaust outlet disposed at the front end of the reverse-flow gas turbine engine, gases configured to flow through the reverse-flow gas turbine engine during operation thereof along a flow direction from the air inlet at the aft end of the reverse-flow gas turbine engine to the exhaust outlet at the front end of the reverse-flow gas turbine engine;

a first spool having a low pressure compressor section disposed forward of the air inlet along the flow direction and in fluid communication with the air inlet, and a low pressure turbine section disposed forward of the low pressure compressor section along the flow direction and at the front end of the reverse-flow gas turbine engine aft of the exhaust outlet, a power shaft extending between the low pressure compressor section and the low pressure turbine section;

a second spool having a high pressure compressor section disposed forward of the low pressure compressor section along the flow direction and in fluid communication therewith to receive pressurized air therefrom, and a high pressure turbine section disposed forward of the high pressure compressor section along the flow direction and drivingly engaged thereto, the high pressure turbine section disposed aft of the low pressure turbine section along the flow direction and in fluid communication therewith; and

an output drive shaft mechanically connected to the power shaft and extending forwardly from the low pressure turbine section, the output drive shaft drivingly engaging a rotatable load forward of the low pressure turbine section.

2. The reverse-flow gas turbine engine as defined in claim 1, wherein the power shaft and the output drive shaft are co-axial.

3. The reverse-flow gas turbine engine as defined in claim 1, further comprising an accessory gearbox disposed aft of the air inlet along the flow direction, a tower shaft mechanically coupled to a high pressure shaft extending between the high pressure compressor section and the high pressure turbine section, and an accessory gear box drive shaft having a first end mechanically coupled to the tower shaft and a second end mechanically coupled to the accessory gearbox.

4. The reverse-flow gas turbine engine as defined in claim 3, wherein the accessory gear box drive shaft extends across the air inlet.

5. The reverse-flow gas turbine engine as defined in claim 1, further comprising an inter-stage bleed disposed aft of the high pressure compressor section and forward of the low pressure compressor section along the flow direction.

6. The reverse-flow gas turbine engine as defined in claim 1, wherein the output drive shaft has a first segment extending between the low pressure compressor section and the low pressure turbine section, and a second segment extending forwardly from the low pressure turbine section along the flow direction to drivingly engage the rotatable load.

7. The reverse-flow gas turbine engine as defined in claim 1, wherein the rotatable load includes a propeller, and the reverse-flow gas turbine engine is a turboprop.

8. A method of operating a turboprop engine, comprising:

drawing air into a core of the turboprop engine through a low pressure compressor section and then through a high pressure compressor section along a forward direction with respect to a direction of travel of the turboprop engine to provide pressurized air;

igniting a mixture of the pressurized air and fuel to generate combustion gases;

circulating the combustion gases along the forward direction through a high pressure turbine section and then through a low pressure turbine section to drive the high pressure turbine section and the low pressure turbine section with the combustion gases;

driving the high pressure compressor section with the high pressure turbine section; and

driving the low pressure compressor section with the low pressure turbine section, and driving a propeller with the low pressure turbine section, a low-pressure-compressor-section shaft and a propeller shaft connected to a same low pressure turbine rotor of the low pressure turbine section, the low pressure turbine section and the high pressure turbine section rotating independently from one another.

9. The method as defined in claim 8, wherein driving the low pressure compressor section and the propeller includes rotating the propeller shaft driving the propeller, the propeller shaft and the low pressure compressor section rotating at a same rotational speed.

10. The method as defined in claim 8, wherein driving the high pressure compressor section includes rotating the high pressure compressor section at a first rotational speed, and driving the low pressure compressor section includes rotating the low pressure compressor section at a second rotational speed less than the first rotational speed.

11. The method as defined in claim 8, further comprising driving an accessory gearbox with the high pressure turbine section, the accessory gearbox disposed aft of an air inlet in fluid communication with the low pressure compressor section.

12. The method as defined in claim 11, wherein driving the accessory gearbox includes driving an accessory gear box drive shaft extending across the air inlet.

13. The method as defined in claim 8, further comprising bleeding pressurized air from the core of the turboprop engine at a location disposed aft of the high pressure compressor section and forward of the low pressure compressor section.

14. The method as defined in claim 8, wherein driving the propeller includes driving the propeller through a reduction gear box.

15. A reverse-flow gas turbine engine, comprising:

an output drive shaft having a front end drivingly engaged to a rotatable load disposed at a front end of the reverse-flow gas turbine engine;

a power shaft extending between a low pressure turbine section and a low pressure compressor section, the power shaft drivingly engaged to the output drive shaft, the low pressure turbine section disposed forward of the low pressure compressor section along a direction toward the front end of the reverse-flow gas turbine engine;

a high pressure shaft rotatable independently of the output drive shaft;

a high pressure turbine section and a high pressure compressor section drivingly engaged to the high pressure shaft, the high pressure compressor section disposed forward of the low pressure compressor section along a direction toward the front end of the reverse-flow gas turbine engine and in fluid communication therewith, and the high pressure turbine section disposed aft of the low pressure turbine section and in fluid communication therewith;

wherein during operation of the reverse-flow gas turbine engine, air flows toward the front end of the reverse-flow gas turbine engine through the low pressure compressor section and the high pressure compressor section, and combustion gases flow toward the front end of the reverse-flow gas turbine engine through the high pressure turbine section and the low pressure turbine section.

16. The reverse-flow gas turbine engine as defined in claim 15, further comprising a power shaft mechanically coupled to the output drive shaft, the power shaft extending between the low pressure turbine section and the low pressure compressor section.

17. The reverse-flow gas turbine engine as defined in claim 15, further comprising an accessory gearbox disposed aft of the low pressure compressor section, a tower shaft mechanically coupled to the high pressure shaft, and an accessory gear box drive shaft having a first end mechanically coupled to the tower shaft and a second end mechanically coupled to the accessory gearbox.

18. The reverse-flow gas turbine engine as defined in claim 17, wherein the accessory gear box drive shaft extends across an air inlet communicating with the low pressure compressor section.

19. The reverse-flow gas turbine engine as defined in claim 15, further comprising an inter-stage bleed disposed aft of the high pressure compressor section and forward of the low pressure compressor section.

20. The reverse-flow gas turbine engine as defined in claim 15, wherein the output drive shaft is configurable to drivingly engage the rotatable load including a propeller, and the reverse-flow gas turbine engine is a turboprop.