Gas turbine engine with fan-tied inducer section and multiple low pressure turbine sections

• US 8,915,700 B2
• Filed: 02/29/2012
• Issued: 12/23/2014
• Est. Priority Date: 02/29/2012
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Kupratis, Daniel Bernard, Schwarz, Frederick M.
• Primary Examiner(s): Kershteyn, Igor
• Application Number:
  US13/407,899
• Publication Number:
  US 20130223986A1
• Time in Patent Office: 1,028 Days
• Field of Search: 415/60, 415/66, 415/69, 415/122.1, 416/120, 416/122, 416/124, 416/126, 416/128, 416/170.R, 416/172
• US Class Current: 415/60
• 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 3/06 with front fan
• CPC Class Codes: F05D 2260/40311 of the epicyclical, planetary or differential type

Abstract

A gas turbine engine includes a first shaft defining an axis of rotation and a second shaft rotatable about the axis of rotation and spaced radially outwardly relative to the first shaft. A speed change mechanism is driven by the second shaft. A fan includes a fan rotor driven by the speed change mechanism such that the fan and the first shaft rotate at a slower speed than the second shaft. 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 first shaft defining an axis of rotation;

a second shaft rotatable about the axis of rotation and spaced radially outwardly relative to the first shaft;

a speed change mechanism driven by the second shaft;

a fan including a fan rotor driven by the speed change mechanism and the first shaft, wherein the fan and the first shaft rotate at a slower speed than the second shaft; 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 inlet stator is positioned aft of the inducer blades.

5. 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 with each inducer stage comprising one or more inducer blades fixed for rotation with the fan rotor and a core inlet stator fixed to a non-rotating engine structure.

6. The gas turbine engine according to claim 1, including a third shaft rotatable about the axis of rotation and spaced radially outwardly relative to the second shaft, and wherein the first shaft is driven by an aft low pressure turbine, the second shaft is driven by a mid-low pressure turbine, and the third shaft is driven by a high pressure turbine.

7. The gas turbine engine according to claim 6, wherein the aft low pressure turbine comprises one or two turbine stages, the mid-low pressure turbine comprises a plurality of turbine stages, and the high pressure turbine comprises one or two turbine stages.

8. The gas turbine engine according to claim 1, wherein the speed change mechanism comprises a geared architecture with a sun gear driven by the second shaft, a plurality of star gears in meshing engagement with the sun gear, and a ring gear in meshing engagement with the star gears, the ring gear providing driving output to the fan rotor.

9. The gas turbine engine according to claim 1, wherein the first shaft has a direct drive to the fan.

10. A gas turbine engine comprising:

a first shaft defining an axis of rotation;

a second shaft rotatable about the axis of rotation and spaced radially outwardly relative to the first shaft;

a speed change mechanism driven by the second 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 mechanism;

a first compressor section driven by the first shaft;

a second compressor section driven by the second 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.

11. The gas turbine engine according to claim 10, wherein the at least one inducer stage comprises a plurality of inducer stages.

12. The gas turbine engine according to claim 10, wherein a rotational speed of the second shaft is greater than the rotational speed of the first shaft.

13. The gas turbine engine according to claim 12, wherein the speed change mechanism comprises a geared architecture with a sun gear driven by the second shaft, a plurality of star gears in meshing engagement with the sun gear, and a ring gear in meshing engagement with the star gears, the ring gear providing driving output to the fan rotor.

14. The gas turbine engine according to claim 13, wherein the first shaft has direct drive to the fan.

15. The gas turbine engine according to claim 14, including a third shaft rotatable about the axis of rotation and spaced radially outwardly relative to the second shaft, and including a third turbine section driving the third shaft, wherein the second turbine section is positioned aft of the third turbine section and the first turbine section is positioned aft of the second turbine section.

16. The gas turbine engine according to claim 15, wherein the first turbine section comprises an aft low pressure turbine, the second turbine section comprises a mid-low pressure turbine, and the third turbine section comprises a high pressure turbine.

17. The gas turbine engine according to claim 11 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.

18. The gas turbine engine according to claim 17, wherein the core inlet stator is positioned axially between the fan blades and the inducer blades.

19. The gas turbine engine according to claim 17, wherein the core stator is positioned aft of the inducer blades.