GAS TURBINE ENGINE WITH A COUNTER ROTATING FAN

• US 20130318999A1
• Filed: 05/31/2012
• Published: 12/05/2013
• Est. Priority Date: 05/31/2012
• Status: Abandoned Application

• Current Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Lucas, James L.
• Application Number:
  US13/485,035
• Publication Number:
  US 20130318999A1
• Time in Patent Office: Days
• US Class Current: 60/792
• CPC Class Codes: F02C 3/067 having counter-rotating rotors F02C3/073 takes precedence
• CPC Class Codes: F02C 3/107 with two or more rotors connected by power transmission
• 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: F02K 3/072 with counter-rotating , e.g. fan rotors
• CPC Class Codes: F05D 2250/313 the axes being perpendicular to each other
• CPC Class Codes: F05D 2260/532 of the bevelled or angled type

Abstract

An exemplary gas turbine engine includes a fan, a compressor section, a combustor in fluid communication with the compressor section and a turbine section in fluid communication with the combustor. The fan includes a first plurality of fan blades supported on a first fan support and a second plurality of fan blades supported on a second fan support. The first and second fan supports are rotatable about a fan axis independently of each other. A geared architecture includes at least one gear driven by the turbine section for rotating about a gear axis that is transverse to the fan axis. The gear drives the fan supports for rotating the respective pluralities of fan blades in opposite directions.

Claims

1. A gas turbine engine, comprising:

a fan including

a first plurality of fan blades supported on a first fan support that is rotatable about a fan axis, and

a second plurality of fan blades supported on a second fan support that is rotatable about the fan axis independent of the first plurality of fan blades;

a compressor section;

a combustor in fluid communication with the compressor section;

a turbine section in fluid communication with the combustor; and

a geared architecture including at least one gear configured to be driven by the turbine section for rotating about a gear axis that is transverse to the fan axis, the at least one gear being configured for driving the first fan support for rotating the first plurality of fan blades in a first direction, the at least one gear being configured for driving the second fan support for rotating the second plurality of fan blades in a second, opposite direction.

2. The gas turbine engine of claim 1, wherein the at least one gear comprises a bevel gear.

3. The gas turbine engine of claim 1, wherein the at least one gear comprises

a first gear situated for interacting with the turbine section, the first gear rotating about the gear axis,

a second gear spaced from the first gear and situated for interacting with the first and second fan supports, the second gear rotating about the gear axis, and

a gear shaft aligned with the gear axis, the first gear being coupled with the gear shaft near a first end of the gear shaft and the second gear being coupled with the gear shaft near a second, opposite end of the gear shaft such that the first and second gears and the gear shaft rotate together.

4. The gas turbine engine of claim 3, wherein

the turbine section comprises a geared component that is rotatable about the fan axis and

the first gear is rotatable about the gear axis responsive to rotation of the geared component.

5. The gas turbine engine of claim 4, wherein the geared component is associated with a low pressure spool that is rotatable with the turbine section.

6. The gas turbine engine of claim 3, comprising

a plurality of the first gears,

a corresponding plurality of the second gears, and

a corresponding plurality of gear shafts,

wherein the plurality of first gears are circumferentially spaced from each other about the fan axis.

7. The gas turbine engine of claim 3, wherein the first and second gears each comprise a bevel gear.

8. The gas turbine engine of claim 1, wherein

the compressor section comprises a first compressor and a second compressor,

the first compressor experiences a lower pressure than the second compressor,

there is a spacing between the first compressor and the second compressor in a direction parallel to the fan axis, and

the geared architecture is at least partially positioned in the spacing.

9. The gas turbine engine of claim 8, wherein the geared architecture comprises at least one gear component having a length extending along the gear axis in a radial direction relative to the fan axis.

10. The gas turbine engine of claim 1, wherein

the first fan support comprises a ring having at least one surface configured to interact with the at least one gear for rotation of the first fan support responsive to rotation of the at least one gear, and

the second fan support comprises a ring having at least one surface configured to interact with the at least one gear for rotation of the second fan support responsive to rotation of the at least one gear.

11. A gas turbine engine, comprising:

a fan that is rotatable about a fan axis;

a compressor section including

a first compressor that experiences a first pressure,

a second compressor that experiences a second pressure that is higher than the first pressure,

the first compressor being spaced from the second compressor along a direction parallel to the fan axis;

a combustor in fluid communication with the compressor section;

a turbine section in fluid communication with the combustor; and

a geared architecture for rotating the fan about the fan axis, the geared architecture including at least one gear configured to be driven by the turbine section for rotating about a gear axis that is transverse to the fan axis.

12. The gas turbine engine of claim 11, wherein the geared architecture is at least partially positioned between the first compressor and the second compressor.

13. The gas turbine engine of claim 11, wherein the geared architecture comprises at least one gear component having a length extending along the gear axis in a radial direction relative to the fan axis.

14. The gas turbine engine of claim 11, wherein the fan comprises

a first plurality of fan blades supported on a first fan support that is rotatable about the fan axis, and

a second plurality of fan blades supported on a second fan support that is rotatable about the fan axis independent of the first plurality of fan blades.

15. The gas turbine engine of claim 14, wherein

the at least one gear is configured to drive the first fan support for rotating the first plurality of fan blades in a first direction, and

the at least one gear is configured to drive the second fan support for rotating the second plurality of fan blades in a second, opposite direction.

16. The gas turbine engine of claim 15, wherein the at least one gear comprises

a first gear situated for interacting with the turbine section, the first gear rotating about the gear axis,

a second gear spaced from the first gear and situated for interacting with the first and second fan supports, the second gear rotating about the gear axis, and

a gear shaft aligned with the gear axis, the first gear being coupled with the gear shaft near a first end of the gear shaft and the second gear being coupled with the gear shaft near a second, opposite end of the gear shaft such that the first and second gears and the gear shaft rotate together.

17. The gas turbine engine of claim 16, comprising

a plurality of the first gears,

a corresponding plurality of the second gears, and

a corresponding plurality of gear shafts,

wherein the plurality of first gears are circumferentially spaced from each other about the fan axis.

18. The gas turbine engine of claim 16, wherein

the turbine section comprises a geared component that rotates about the fan axis and

the first gear rotates about the gear axis responsive to rotation of the geared component.

19. The gas turbine engine of claim 18, wherein the geared component is associated with a low pressure spool driven by the turbine section.

20. The gas turbine engine of claim 16, wherein the first and second gears each comprise a bevel gear.

21. The gas turbine engine of claim 14, wherein

the first fan support comprises a ring having at least one surface configured to interact with the at least one gear for rotation of the first fan support in a first direction responsive to rotation of the at least one gear, and

the second fan support comprises a ring having at least one surface configured to interact with the at least one gear for rotation of the second fan support in a second, opposite direction responsive to rotation of the at least one gear.