Turbomachine with alternatingly spaced turbine rotor blades

Patent metadata

Field	Value
Publication number	US-10781717-B2
Application number	US-201715710191-A
Country	US
Kind code	B2
Filing date	Sep 20, 2017
Priority date	Sep 20, 2017
Publication date	Sep 22, 2020
Grant date	Sep 22, 2020

Abstract

A turbomachine includes a turbine frame and a turbine, the turbine including a first plurality of turbine rotor blades and a second plurality of turbine rotor blades alternatingly spaced along the axial direction and rotatable with one another. The turbomachine also includes a first support member assembly including a first support member supporting the first plurality of turbine rotor blades; a second support member assembly including a second support member supporting the second plurality of turbine rotor blades; a frame support member assembly including a frame support member coupled to and extending from the turbine frame; and a bearing assembly including a first bearing and a second bearing. The first bearing is positioned between the first support member and the second support member, and the second bearing is positioned between the frame support member and one of the first support member or the second support member.

First claim

What is claimed is:

1. A turbomachine defining a radial direction and an axial direction, the turbomachine comprising:
a turbine frame;
a turbine comprising 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 alternatingly spaced along the axial direction and rotatable with one another;
a first support member assembly comprising a first support member supporting the first plurality of turbine rotor blades;
a second support member assembly comprising a second support member supporting the second plurality of turbine rotor blades;
a frame support member assembly comprising a frame support member coupled to and extending from a center frame of the turbine frame, the center frame located forward of a midpoint of the turbine and the frame support member extending at least to the midpoint; and
a bearing assembly comprising a first bearing and a second bearing, the first bearing positioned between the first support member and the second support member, and the second bearing positioned between the frame support member and one of the first support member or the second support member.

2. The turbomachine of claim 1 , wherein the first bearing and the second bearing are each axially aligned with the first plurality of turbine rotor blades, the second plurality of turbine rotor blades, or both.

3. The turbomachine of claim 1 , wherein the first bearing is positioned inward of the second bearing along the radial direction.

4. The turbomachine of claim 1 , wherein the first bearing is aligned with the second bearing along the axial direction.

5. The turbomachine of claim 1 , wherein the second bearing is positioned between the turbine frame support member and the second support member.

6. The turbomachine of claim 1 , wherein the bearing assembly further comprises a third bearing and a fourth bearing, wherein the third bearing is positioned between the first support member and the second support member, and wherein the fourth bearing is positioned between the frame support member and one of the first support member or the second support member.

7. The turbomachine of claim 6 , wherein the fourth bearing is positioned between the frame support member and the second support member.

8. The turbomachine of claim 6 , wherein the first bearing, the second bearing, the third bearing, and the fourth bearing are each axially aligned with the first plurality of turbine rotor blades, the second plurality of turbine rotor blades, or both.

9. The turbomachine of claim 1 , further comprising:
a gearbox, wherein the first plurality of turbine rotor blades is rotatable with the second plurality of turbine rotor blades through the gearbox.

10. The turbomachine of claim 9 , further comprising:
a spool, wherein the turbine defines the midpoint along the axial direction, wherein the gearbox is aligned with, or positioned aft of, the midpoint of the turbine, wherein the first plurality of turbine rotor blades are coupled to the spool through the first support member assembly, and wherein the first support member assembly extends aft of the gearbox.

11. The turbomachine of claim 9 , wherein the gearbox comprises a first gear coupled to the first plurality of turbine rotor blades through the first support member assembly, a second gear coupled to the second plurality of turbine rotor blades through the second support member assembly, and a third gear coupled to the turbine frame through the frame support member assembly.

12. The turbomachine of claim 1 , wherein the turbine frame comprises the turbine center frame and a turbine rear frame.

13. 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.

14. The turbomachine of claim 13 , 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.

15. The turbomachine of claim 13 , 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.

16. A turbomachine defining a radial direction and an axial direction, the turbomachine comprising:
a turbine comprising a center frame located forward of a midpoint of the turbine, a frame support member coupled to the center frame and extending at least to the midpoint, 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 alternatingly spaced along the axial direction and rotatable with one another;
a first support member assembly comprising a first support member supporting the first plurality of turbine rotor blades;
a second support member assembly comprising a second support member supporting the second plurality of turbine rotor blades; and
a bearing assembly comprising a first bearing positioned between the first support member and the second support member, the first bearing axially aligned with the first plurality of turbine rotor blades, the second plurality of turbine rotor blades, or both.

17. The turbomachine of claim 16 , further comprising:
a turbine frame comprising the center frame and a rear frame; and
a frame support member assembly comprising the frame support member, wherein the bearing assembly further comprises a second bearing positioned between the frame support member and one of the first support member or the second support member.

18. The turbomachine of claim 17 , wherein the second bearing is positioned between the frame support member and the second support member.

19. The turbomachine of claim 16 , wherein the first bearing and the second bearing are axially aligned with the first plurality of turbine rotor blades, the second plurality of turbine rotor blades, or both.

20. The turbomachine of claim 16 , wherein the first bearing is positioned inward of the second bearing along the radial direction, and wherein the first bearing is substantially aligned with the second bearing along the axial direction.

Assignees

• Gen Electric

Inventors

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

Classifications

• F02K3/072

  with counter-rotating {, e.g. fan} rotors · CPC title

• F05D2260/40311

  of the epicyclical, planetary or differential type · CPC title

• F01D25/162

  Bearing supports · CPC title

• 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