Gas turbine engine with distributed fans

Patent metadata

Field	Value
Publication number	US-9650954-B2
Application number	US-201514597510-A
Country	US
Kind code	B2
Filing date	Jan 15, 2015
Priority date	Feb 7, 2014
Publication date	May 16, 2017
Grant date	May 16, 2017

Abstract

A gas generator has at least one compressor rotor, at least one gas generator turbine rotor and a combustion section. A fan drive turbine is positioned downstream of a path of the products of combustion having passed over the at least one gas generator turbine rotor. The fan drive turbine drives a shaft and the shaft engages gears to drive at least three fan rotors.

First claim

The invention claimed is:

1. A gas turbine engine comprising:
at least three fans rotors, wherein each of the at least three fan rotors is connected to a respective fan shaft;
a gas generator with at least one compressor rotor, at least one gas generator turbine rotor and a combustion section, and there being a fan drive turbine positioned downstream of a path of the products of combustion having passed over said at least one gas generator turbine rotor, said fan drive turbine driving a shaft and said shaft engaging at least three gears to drive respective said at least three fan rotors through said respective fan shaft,
wherein each one of the at least three fan rotors, the respective fan shaft and respective one of said three gears are enclosed in a respective fan casing and
wherein said at least three fan rotors, include at least two distinct diameters of fan rotors.

2. The gas turbine engine as set forth in claim 1 , wherein said gas generator includes at least two compressor rotors and at least two gas generator turbine rotors, with said fan drive turbine being positioned to be downstream of a path of the products of combustion having passed over each of said at least two gas generator turbine rotors.

3. The gas turbine engine as set forth in claim 1 , wherein an axis of rotation of said gas generator is generally perpendicular to an axis of rotation of said shaft.

4. The gas turbine engine as set forth in claim 1 , wherein an axis of rotation of said gas generator is generally coaxial with an axis of rotation of said shaft.

5. The gas turbine engine as set forth in claim 1 , wherein said shaft is generally hollow.

6. The gas turbine engine as set forth in claim 5 , wherein said shaft includes at least one flex coupling associated with a gear of said at least three gears for driving one of said at least three fan rotors.

7. The gas turbine engine as set forth in claim 6 , wherein each one of said at least three fan rotors is provided with a separately driven oil pump, oil supply and oil scavenge line.

8. The gas turbine engine as set forth in claim 5 , wherein each one of said at least three fan rotors is provided with a separately driven oil pump, oil supply and oil scavenge line.

9. The gas turbine engine as set forth in claim 1 , wherein each of said at least three fan rotors have a different diameter.

10. The gas turbine engine as set forth in claim 9 , wherein a gear ratio of said gears for driving respective said at least three fan rotors differs across at least two of said at least three fan rotors.

11. The gas turbine engine as set forth in claim 10 , wherein a pressure ratio provided across said at least three fan rotors differs across at least two of said at least three fan rotors.

12. The gas turbine engine as set forth in claim 9 , wherein a largest diameter fan rotor of said at least three fan rotors is positioned to be closer to said fan drive turbine.

13. The gas turbine engine as set forth in claim 12 , wherein a highest gear reduction ratio is provided on said largest diameter fan rotor.

14. The gas turbine engine as set forth in claim 1 , wherein a gear ratio of said gears for driving respective said at least three fan rotors differs across at least two of said at least three fan rotors.

15. The gas turbine engine as set forth in claim 1 , wherein said shaft includes at least one flex coupling associated with a gear of said at least three gears for driving one of said at least three fan rotors.

16. The gas turbine engine as set forth in claim 1 , wherein a pressure ratio provided across said at least three fan rotors differs across at least two of said at least three fan rotors.

17. The gas turbine engine as set forth in claim 16 , wherein a lowest fan pressure ratio is provided by a largest diameter fan rotor of said at least three fan rotors.

18. The gas turbine engine as set forth in claim 17 wherein said shaft is generally hollow.

19. The gas turbine engine as set forth in claim 1 , wherein adjacent ones of said at least three fan rotors are driven to rotate in opposed directions.

Assignees

• United Technologies Corp

Inventors

• Suciu Gabriel L
• Mccune Michael E
• Chandler Jesse M
• Epstein Alan H
• O'Flarity Steven M
• Hanlon Christopher J
• Schneider William F
• Staubach Joseph B
• Kenyon James A

Classifications

• F02C3/06

  the compressor comprising only axial stages (F02C3/10 takes precedence) · CPC title

• F02K3/077

  the plant being of the multiple flow type, i.e. having three or more flows · CPC title

• F02C7/36

  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 title

• F05D2250/312

  the axes being parallel to each other · CPC title

• F05D2220/36

  specially adapted for the fan of turbofan engines · CPC title