Turbomachine with alternatingly spaced turbine rotor blades

Patent metadata

Field	Value
Publication number	US-10823000-B2
Application number	US-201715710138-A
Country	US
Kind code	B2
Filing date	Sep 20, 2017
Priority date	Sep 20, 2017
Publication date	Nov 3, 2020
Grant date	Nov 3, 2020

Abstract

A turbomachine includes a spool and a turbine section. The turbine section includes a turbine center frame and a turbine, with the turbine including a first plurality of turbine rotor blades and a second plurality of turbine rotor blades. The first plurality of turbine rotor blades and second plurality of turbine rotor blades are alternatingly spaced along the axial direction. The turbomachine also includes a gearbox aligned with, or positioned aft of, a midpoint of the turbine. The gearbox includes a first gear coupled to the first plurality of rotor blades, a second gear coupled to the second plurality of rotor blades, and a third gear coupled to the turbine center frame. The turbomachine also includes a support member, the first plurality of turbine rotor blades coupled to the spool through the support member, the support member extending aft of the gearbox.

First claim

What is claimed is:

1. A turbomachine defining a radial direction and an axial direction, the turbomachine comprising:
a spool;
a turbine section comprising a turbine center frame and a turbine, the turbine comprising a first plurality of turbine rotor blades and a second plurality of turbine rotor blades, each plurality positioned aft of the turbine center frame and forward of a turbine rear frame, the first plurality of turbine rotor blades and second plurality of turbine rotor blades alternatingly spaced along the axial direction, the turbine defining a midpoint along the axial direction;
a gearbox aligned with, or positioned aft of, the midpoint of the turbine, the gearbox comprising a first gear coupled to the first plurality of rotor blades, a second gear coupled to the second plurality of rotor blades, and a third gear coupled to and supported by the turbine center frame; and
a support member, the first plurality of turbine rotor blades coupled to the spool through the support member, the support member extending aft of the gearbox.

2. The turbomachine of claim 1 , wherein the support member is a first support member, wherein the turbomachine further comprises:
a bearing assembly; and
a second support member, the second plurality of turbine rotor blades supported by the second support member, wherein the spool and first support member are supported aft of the midpoint of the turbine through the bearing assembly, the bearing assembly positioned between the first support member and second support member.

3. The turbomachine of claim 1 , wherein the support member is a first support member, wherein the turbomachine further comprises:
a bearing assembly; and
a second support member, the second plurality of turbine rotor blades supported by the second support member, wherein the spool and first support member are supported within the turbine section through the bearing assembly, the bearing assembly positioned between the first support member and second support member.

4. The turbomachine of claim 3 , wherein the bearing assembly is positioned aft of the midpoint of the turbine.

5. The turbomachine of claim 3 , wherein the bearing assembly is a first bearing assembly, wherein the first bearing assembly comprises a first bearing and a second bearing, and wherein the turbomachine further comprises:
a second bearing assembly supporting the second support member.

6. The turbomachine of claim 5 , wherein the first bearing is configured as a roller bearing and the second bearing is configured as a ball bearing.

7. The turbomachine of claim 3 , wherein the bearing assembly is aligned with and positioned radially outward of the gearbox.

8. The turbomachine of claim 1 , wherein the first plurality of turbine rotor blades is configured as a plurality of low-speed turbine rotor blades, and wherein the second plurality of turbine rotor blades is configured as a plurality of high-speed turbine rotor blades.

9. The turbomachine of claim 8 , wherein the plurality of low-speed turbine rotor blades each extend between an inner end along the radial direction and an outer end along the radial direction, and wherein at least two of the plurality of low-speed turbine rotor blades are spaced from one another along the axial direction and coupled to one another at the outer ends.

10. The turbomachine of claim 8 , wherein the plurality of high-speed turbine rotor blades each extend between an inner end along the radial direction and an outer end along the radial direction, and wherein at least two of the plurality of high-speed turbine rotor blades are spaced from one another along the axial direction and coupled to one another at the inner ends.

11. The turbomachine of claim 8 , wherein the plurality of low-speed turbine rotor blades are configured to rotate in a first circumferential direction, and wherein the plurality of high-speed turbine rotor blades are configured to rotate in a second circumferential direction opposite the first circumferential direction.

12. A turbomachine defining a radial direction and an axial direction, the turbomachine comprising:
a spool;
a turbine section comprising a turbine center frame and a turbine, the turbine comprising a first plurality of turbine rotor blades and a second plurality of turbine rotor blades, each plurality positioned aft of the turbine center frame and forward of a turbine rear frame, the first plurality of turbine rotor blades and second plurality of turbine rotor blades alternatingly spaced along the axial direction;
a gearbox comprising a first gear coupled to the first plurality of rotor blades, a third gear coupled to and supported by the turbine center frame, and a second gear coupled to the second plurality of rotor blades;
a first support member, the first plurality of turbine rotor blades coupled to the spool through the first support member;
a second support member coupled to the second plurality of turbine rotor blades; and
a bearing assembly positioned between the first and second support members, the spool and the first plurality of turbine rotor blades supported within the turbine section through the bearing assembly.

13. The turbomachine of claim 12 , wherein the first support member extends around an aft end of the gearbox.

14. The turbomachine of claim 12 , wherein the bearing assembly is positioned aft of the midpoint of the turbine.

15. The turbomachine of claim 12 , wherein the bearing assembly comprises a first bearing and a second bearing.

16. The turbomachine of claim 15 , wherein the first bearing is configured as a roller bearing and the second bearing is configured as a ball bearing.

17. The turbomachine of claim 12 , wherein the bearing assembly is aligned with and positioned radially outward of the gearbox.

18. The turbomachine of claim 12 , wherein the first plurality of turbine rotor blades is configured as a plurality of low-speed turbine rotor blades, and wherein the second plurality of turbine rotor blades is configured as a plurality of high-speed turbine rotor blades.

19. The turbomachine of claim 18 , wherein the plurality of low-speed turbine rotor blades each extend between an inner end along the radial direction and an outer end along the radial direction, and wherein at least two of the plurality of low-speed turbine rotor blades are spaced from one another along the axial direction and coupled to one another at the outer ends, and wherein the plurality of high-speed turbine rotor blades each extend between an inner end along the radial direction and an outer end along the radial direction, and wherein at least two of the plurality of high-speed turbine rotor blades are spaced from one another along the axial direction and coupled to one another at the inner ends.

20. The turbomachine of claim 18 , wherein the plurality of low-speed turbine rotor blades is coupled to the first gear of the gearbox through a first flexible member, and wherein the plurality of high-speed turbine rotor blades is coupled to the second gear of the gearbox through a second flexible member.

21. The turbomachine of claim 1 , wherein the turbine center frame is positioned forward of the turbine.

Assignees

• Gen Electric

Inventors

• Pankaj Peeyush
• Puranik Shashank Suresh
• Zatorski Darek Tomasz
• Glynn Christopher Charles
• Schmidt Richard

Classifications

• F02C3/067

  having counter-rotating rotors (F02C3/073 takes precedence) · 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

• F05D2240/40

  Use of a multiplicity of similar components · CPC title

• F01D25/164

  Flexible supports; Vibration damping means associated with the bearing · CPC title

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title