GEARED TURBOMACHINE FAN AND COMPRESSOR ROTATION

• US 20130186058A1
• Filed: 01/24/2012
• Published: 07/25/2013
• Est. Priority Date: 01/24/2012
• 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: Sheridan, William G., McCune, Michael E.
• Application Number:
  US13/356,940
• Publication Number:
  US 20130186058A1
• Time in Patent Office: Days
• US Class Current: 60/204
• CPC Class Codes: F01D 25/168 for axial load mainly
• 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 3/06 with front fan
• CPC Class Codes: F04D 29/522 especially adapted for elastic fluid pumps
• CPC Class Codes: F05D 2220/36 specially adapted for the fan of turbofan engines
• CPC Class Codes: F05D 2260/40311 of the epicyclical, planetary or differential type
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A high-bypass ratio geared turbomachine comprises a compressor section of a high-bypass ratio geared turbomachine. The compressor section provides at least a low-pressure compressor and a high-pressure compressor, wherein a rotor of the low-pressure compressor rotates together with a rotor of a fan.

Claims

1. A high-bypass ratio geared turbomachine, comprising:

a compressor section of a high-bypass ratio geared turbomachine, the compressor section providing at least a low-pressure compressor and a high-pressure compressor, wherein a rotor of the low-pressure compressor rotates together with a rotor of a fan.

2. The high-bypass ratio geared turbomachine of claim 1, wherein the rotor of the low pressure compressor and the rotor of the fan rotate at the same speed and in the same direction.

3. The high-bypass ratio geared turbomachine of claim 1, wherein the high-bypass ratio geared turbomachine has a fan bypass ratio greater than about 8.

4. The high-bypass ratio geared turbomachine of claim 1, wherein the high-bypass ratio geared turbomachine has an overall compression ratio greater than about 40.

5. The high-bypass ratio geared turbomachine of claim 1, wherein the high-pressure compressor has a pressure ratio greater than about 20.

6. The high-bypass ratio geared turbomachine of claim 1, wherein the fan includes a shaft that is rotatably supported by a plurality of tapered bearings.

7. The high-bypass ratio geared turbomachine of claim 1, including a turbine shaft that rotates a geared architecture to rotate the rotor of the low-pressure compressor and the rotor of the fan.

8. The high-bypass ratio geared turbomachine of claim 7, wherein at least one thrust bearing rotatably supports the turbine shaft, and the at least one thrust bearing is located axially between the geared architecture and a turbine secured to the turbine shaft.

9. The high-bypass ratio geared turbomachine of claim 8, wherein the at least one thrust bearing is a bi-directional tapered bearing.

10. The high-bypass ratio geared turbomachine of claim 7, wherein the shaft is a low-pressure turbine shaft.

11. The high-bypass ratio geared turbomachine of claim 7, wherein the geared architecture is a planetary geared architecture.

12. A high-bypass ratio turbomachine, comprising:

a fan rotor that rotates together with an compressor rotor at a first speed in a turbomachine having a high-bypass ratio, wherein the fan rotor and the compressor rotor are driven by a shaft that rotates at a second speed different than the first speed.

13. The high-bypass ratio turbomachine of claim 12, wherein the shaft rotates a geared architecture to rotate the fan rotor and the compressor rotor.

14. The high-bypass ratio turbomachine of claim 12, wherein the compressor rotor is axially forward of a fan frame extending radially across a fan bypass flow path.

15. The high-bypass ratio turbomachine of claim 12, wherein the fan rotor and the compressor rotor rotate at the same speed.

16. The high-bypass ratio turbomachine of claim 12, including a high-pressure turbine, a combustor section, and a low-pressure turbine arranged axially sequentially within the geared turbomachine.

17. The high-bypass ratio turbomachine of claim 12, wherein exclusively axial compressors provide compression in the geared turbomachine.

18. The high-bypass ratio turbomachine of claim 12, wherein the compressor is a low-pressure compressor.

19. A method of operating a high-bypass ratio turbomachine, comprising:

rotating a geared architecture with a first shaft;

rotating a second shaft with the geared architecture; and

rotating a fan rotor and a compressor rotor with the second shaft.

20. The method of claim 19, wherein the turbomachine has a fan bypass ratio greater than 8.