Turbofan engine assembly with gearbox

• US 10,450,952 B2
• Filed: 01/16/2017
• Issued: 10/22/2019
• Est. Priority Date: 01/16/2017
• 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: Julien, Andre, Thomassin, Jean, Dussault, Serge
• Primary Examiner(s): Sutherland, Steven M
• Assistant Examiner(s): Ford, Rene D
• Application Number:
  US15/406,989
• Publication Number:
  US 20180202358A1
• Time in Patent Office: 1,009 Days
• CPC Class Codes: F01C 1/22 of internal-axis type with equidirectional movement of co-operating members at the points of engagement, or with one of the co-operating members being stationary, the inner member having more teeth or tooth- equivalents than the outer member
• CPC Class Codes: F02C 5/02 characterised by the arrangement of the combustion chamber in the chamber in the plant combustion chambers per se F23R
• CPC Class Codes: F02C 5/06 the working fluid being generated in an internal-combustion gas generated of the positive-displacement type having essentially no mechanical power output internal-combustion engines with prolonged expansion using exhaust gas turbines F02B
• CPC Class Codes: F02C 7/185 Cooling means for reducing the temperature of the cooling air or gas
• 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: F02C 9/18 by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages F02C3/113 takes precedence
• CPC Class Codes: F02K 3/06 with front fan
• CPC Class Codes: F05D 2260/211 by intercooling, e.g. during a compression cycle
• CPC Class Codes: F05D 2260/40311 of the epicyclical, planetary or differential type
• CPC Class Codes: Y02T 10/12 Improving ICE efficiencies

Abstract

A turbofan engine assembly including an internal combustion engine in fluid communication between a compressor and a turbine, the internal combustion engine having an engine shaft, a bypass duct surrounding the internal combustion engine, and a fan drivingly engaged to the engine shaft via a gearbox, the gearbox configured to increase an output speed of the fan relative to an input speed of the engine shaft.

Claims

1. A turbofan engine assembly comprising:

an internal combustion engine in fluid communication between a compressor and a turbine, the internal combustion engine having an engine shaft;

a bypass duct surrounding the internal combustion engine; and

a fan drivingly engaged to the engine shaft via a gearbox, the gearbox configured to increase an output speed of the fan relative to an input speed of the engine shaft.

2. The assembly as defined in claim 1, wherein a compressor rotor of the compressor is drivingly engaged to the engine shaft via the gearbox so as to be rotatable at the rotational speed of the fan.

3. The assembly as defined in claim 1, wherein the turbine is compounded with the internal combustion engine.

4. The assembly as defined in claim 3, wherein the gearbox is a first gearbox and a turbine rotor of the turbine is drivingly engaged to the shaft of the internal combustion engine via a second gearbox.

5. The assembly as defined in claim 4, wherein the second gearbox is an accessory gearbox, the assembly further comprising at least one accessory drivingly engaged to the accessory gearbox.

6. The assembly as defined in claim 4, wherein the compressor is located between the internal combustion engine and the turbine, a compressor rotor of the compressor drivingly engaged to the shaft of the internal combustion engine via the second gearbox so as to be rotatable at a same rotational speed as the turbine rotor, the compressor is a centrifugal compressor, and the an inlet of the compressor is defined by a duct extending radially inwardly from the bypass duct.

7. The assembly as defined in claim 1, wherein the internal combustion engine is a Wankel rotary engine including an engine rotor having three apex portions mounted for eccentric revolutions within an internal cavity defined in a housing, the internal cavity having an epitrochoid shape with two lobes.

8. The assembly as defined in claim 1, further comprising a heat exchanger located in the bypass duct, the heat exchanger in fluid communication with a coolant system of the internal combustion engine.

9. The assembly as defined in claim 1, further comprising at least one additional internal combustion engine in fluid communication between the compressor and the turbine.

10. The assembly as defined in claim 1, wherein the turbine is a first turbine, the assembly further comprising a second turbine having an inlet in fluid communication with an outlet of the first turbine.

11. A turbofan engine assembly comprising:

a compressor;

a plurality of rotary internal combustion engines each including an engine rotor having three apex portions mounted for eccentric revolutions within an internal cavity defined in a housing, the internal cavity having an epitrochoid shape with two lobes, the rotary internal combustion engines having an inlet in fluid communication with an outlet of the compressor through at least one first passage of an intercooler;

a turbine having an inlet in fluid communication with an outlet of the rotary internal combustion engines;

a bypass duct surrounding the rotary internal combustion engines, compressor and turbine; and

a fan configured to propel air through the bypass duct and through an inlet of the compressor, the fan drivingly engaged to a shaft of the rotary internal combustion engines via a gearbox, the gearbox defining a speed ratio of a rotational speed of the shaft of the rotary internal combustion engines on a rotational speed of the fan, the speed ratio being smaller than 1 so that the gearbox defines a speed increase from the shaft of the rotary internal combustion engines to the fan.

12. The assembly as defined in claim 11, wherein a compressor rotor of the compressor is drivingly engaged to the shaft of the internal combustion via the gearbox so as to be rotatable at the rotational speed of the fan.

13. The assembly as defined in claim 11, wherein the turbine is compounded with the rotary internal combustion engines.

14. The assembly as defined in claim 13, wherein the gearbox is a first gearbox and a turbine rotor of the turbine is drivingly engaged to the shaft of the rotary internal combustion engines via a second gearbox.

15. The assembly as defined in claim 14, wherein the second gearbox is an accessory gearbox, the assembly further comprising at least one accessory drivingly engaged to the accessory gearbox.

16. The assembly as defined in claim 14, wherein the compressor is located between the rotary internal combustion engines and the turbine, a compressor rotor of the compressor drivingly engaged to the shaft of the rotary internal combustion engines via the second gearbox so as to be rotatable at a same rotational speed as the turbine rotor, the compressor is a centrifugal compressor, and the compressor inlet is defined by a duct extending radially inwardly from the bypass duct.

17. The assembly as defined in claim 11, further comprising a heat exchanger located in the bypass duct, the heat exchanger in fluid communication with a coolant system of the rotary internal combustion engines.

18. The assembly as defined in claim 11, wherein the turbine is a first turbine, the assembly further comprising a second turbine having an inlet in fluid communication with an outlet of the first turbine.

19. A method of driving a fan of a turbofan engine assembly, the method comprising:

rotating a shaft with an internal combustion engine of the turbofan engine assembly; and

driving the fan with the shaft of the internal combustion engine via a gearbox of the turbofan engine assembly, the gearbox configured so that the fan is rotated at a greater rotational speed than that of the shaft.

20. The method as defined in claim 19, wherein the internal combustion engine is a Wankel rotary engine including a rotor having three apex portions mounted for eccentric revolutions within an internal cavity defined in a housing, the internal cavity having an epitrochoid shape with two lobes.