Gas turbine engine with fan-tied inducer section

• US 9,103,227 B2
• Filed: 02/28/2012
• Issued: 08/11/2015
• Est. Priority Date: 02/28/2012
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Kupratis, Daniel Bernard, Schwarz, Frederick M.
• Primary Examiner(s): Look, Edward
• Assistant Examiner(s): EASTMAN, AARON ROBERT
• Application Number:
  US13/406,819
• Publication Number:
  US 20130224003A1
• Time in Patent Office: 1,260 Days
• US Class Current: 1/1
• CPC Class Codes: F01D 15/12 Combinations with mechanical gearing driven by multiple engines F01D13/00
• CPC Class Codes: F02C 7/047 Heating to prevent icing
• 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 2260/40311 of the epicyclical, planetary or differential type

Abstract

A gas turbine engine includes a shaft, a speed change device driven by the shaft, and a fan including a fan rotor driven by the speed change device. At least one inducer stage is positioned aft of the fan and is coupled for rotation with the fan rotor.

Claims

1. A gas turbine engine comprising:

a shaft defining an axis of rotation;

a speed reduction device driven by the shaft;

a fan including a fan rotor driven by the speed reduction device; and

at least one inducer stage positioned aft of the fan and coupled for rotation with the fan rotor.

2. The gas turbine engine according to claim 1, wherein the at least one inducer stage comprises one or more inducer blades fixed for rotation with the fan rotor and a core inlet stator fixed to a non-rotating engine structure.

3. The gas turbine engine according to claim 2, wherein the core inlet stator is positioned axially between the fan and the inducer blades.

4. The gas turbine engine according to claim 2, wherein the core stator is positioned aft of the blades.

5. The gas turbine engine according to claim 2, wherein the core inlet stator is a variable vane.

6. The gas turbine engine according to claim 2, wherein the core inlet stator is heated for anti-icing.

7. The gas turbine engine according to claim 2, wherein the one or more inducer blades are heated for anti-icing.

8. The gas turbine engine according to claim 1, wherein the at least one inducer stage comprises a plurality of inducer stages coupled to the fan rotor.

9. The gas turbine engine according to claim 8, wherein each inducer state comprises one or more blades fixed for rotation with the fan rotor and a core stator fixed to a non-rotating engine structure.

10. The gas turbine engine according to claim 1, including a compressor comprising a plurality of compressor stages driven by the shaft.

11. The gas turbine engine according to claim 10, wherein the compressor is positioned immediately aft of the at least one inducer stage.

12. The gas turbine engine according to claim 10, wherein the at least one inducer stage is positioned forward of the speed reduction device.

13. The gas turbine engine according to claim 10, wherein the compressor comprises a low pressure compressor, and including a high pressure compressor positioned aft of the low pressure compressor and driven by a second shaft positioned radially outwardly relative to the shaft that drives the low pressure compressor.

14. The gas turbine engine according to claim 1, wherein the fan rotor turns in the same direction as the shaft.

15. The gas turbine engine according to claim 1, wherein the fan rotor turns in an opposite direction from the shaft.

16. The gas turbine engine according to claim 1 wherein the speed change device comprises a gearbox including a sun gear in meshing engagement with star gears and a ring gear in meshing engagement with the star gears, and wherein the ring gear at drives the fan.

17. The gas turbine engine according to claim 1 wherein the speed change device comprises a gearbox including a sun gear in meshing engagement with a plurality of planetary gears supported by a planet carrier and a ring gear in meshing engagement with the planet gears, and wherein the ring gear is fixed and the planet carrier provides input to the fan.

18. A gas turbine engine comprising:

a shaft defining an axis of rotation;

a speed change device driven by the shaft;

a fan section including at least one fan blade coupled to a fan rotor wherein the fan rotor is driven by the speed change device;

a compressor comprising a plurality of compressor stages driven by the shaft; and

at least one inducer stage positioned aft of the fan blade and coupled for rotation with the fan rotor about the axis of rotation.

19. The gas turbine engine according to claim 18, wherein the at least one inducer stage is positioned axially forward of the compressor.

20. The gas turbine engine according to claim 19, wherein the compressor comprises a low pressure compressor, and including a high pressure compressor positioned aft of the low pressure compressor and driven by a second shaft positioned radially outwardly relative to the shaft that drives the low pressure compressor.

21. The gas turbine engine according to claim 20, wherein the low pressure compressor is positioned aft of the speed change device.

22. The gas turbine engine according to claim 18, wherein the at least one inducer stage comprises one or more inducer blades fixed for rotation with the fan rotor and a core inlet stator fixed to a non-rotating engine structure.

23. The gas turbine engine according to claim 22, wherein the core inlet stator is positioned axially between the fan blades and the inducer blades.

24. The gas turbine engine according to claim 22, wherein the core inlet stator is positioned aft of the inducer blades.

25. The gas turbine engine according to claim 18, wherein the at least one inducer stage comprises a plurality of inducer stages coupled to the fan rotor, and wherein each inducer stage comprises one or more inducer blades fixed for rotation with the fan rotor and a core inlet stator fixed to a non-rotating engine structure.

26. The gas turbine engine according to claim 18, wherein the compressor is positioned aft of the at least one inducer stage.

27. The gas turbine engine according to claim 26, wherein the at least one inducer stage is positioned forward of the speed change device.