Turbomachine with alternatingly spaced turbine rotor blades

Patent metadata

Field	Value
Publication number	US-11098592-B2
Application number	US-201715710164-A
Country	US
Kind code	B2
Filing date	Sep 20, 2017
Priority date	Sep 20, 2017
Publication date	Aug 24, 2021
Grant date	Aug 24, 2021

Abstract

A turbomachine includes a spool; and a turbine section including a turbine and a turbine center frame. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades alternatingly spaced along an axial direction and rotatable with one another. The turbomachine also includes a first support member, the first plurality of turbine rotor blades coupled to the spool through the first support member; a second support member, the second plurality of turbine rotor blades supported by the second support member; and a bearing assembly including a first bearing and a second bearing, the first bearing and the second bearing each rotatably supporting the second support member and each being supported by the turbine center frame.

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 and a turbine center frame located forward of a midpoint of the turbine, the 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 the second plurality of turbine rotor blades alternatingly spaced along the axial direction and rotatable with one another, the first plurality of turbine rotor blades and the second plurality of turbine rotor blades each arranged aft of the turbine center frame and supported by the turbine center frame via a support assembly;
a first support member, the first plurality of turbine rotor blades coupled to the spool through the first support member;
a second support member, the second plurality of turbine rotor blades supported by the second support member; and
a bearing assembly comprising a first bearing and a second bearing, the first bearing and the second bearing each rotatably supporting the second support member and each being supported by the turbine center frame via the support assembly,
wherein the support assembly comprises a frame support member coupled to the turbine center frame, the first bearing and the second bearing of the bearing assembly positioned between the frame support member and 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, of the second plurality of turbine rotor blades, or both.

3. The turbomachine of claim 2 , wherein the turbine defines the midpoint along the axial direction, wherein the first bearing is positioned forward of the midpoint, and wherein the second bearing is positioned aft of the midpoint.

4. The turbomachine of claim 1 , wherein the frame support member is an outer frame support member along the radial direction, and the support assembly further comprises an inner frame support member along the radial direction.

5. The turbomachine of claim 1 , wherein the first bearing and the second bearing each support the second support member at an inner side along the radial direction and are supported by the frame support member at an outer side along the radial direction.

6. 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.

7. The turbomachine of claim 6 , wherein the turbine defines the midpoint along the axial direction, and wherein the gearbox is aligned with, or positioned aft of, the midpoint of the turbine.

8. The turbomachine of claim 1 , wherein the turbine center frame is positioned forward of the turbine and a rear frame is positioned aft of the turbine along the axial direction.

9. A turbomachine defining a radial direction and an axial direction, the turbomachine comprising:
a spool;
a turbine section comprising a turbine and a turbine center frame located forward of a midpoint of the turbine, the 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 the second plurality of turbine rotor blades alternatingly spaced along the axial direction and rotatable with one another, the first plurality of turbine rotor blades and the second plurality of turbine rotor blades each arranged aft of the turbine center frame and supported by the turbine center frame via a support assembly;
a first support member, the first plurality of turbine rotor blades coupled to the spool through the first support member;
a second support member, the second plurality of turbine rotor blades supported by the second support member; and
a bearing assembly comprising a first bearing and a second bearing, the first bearing and the second bearing each rotatably supporting the second support member and each being supported by the turbine center frame via the support assembly, the bearing assembly further comprising a third bearing and a fourth bearing, wherein the third bearing and the fourth bearing each rotatably support the spool.

10. The turbomachine of claim 9 , 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.

11. The turbomachine of claim 10 , 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.

12. The turbomachine of claim 10 , 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.

13. The turbomachine of claim 9 , wherein the turbine section further comprises a turbine rear frame, wherein the third bearing is supported by the turbine center frame, and wherein the fourth bearing is supported by the turbine rear frame.

14. A turbomachine defining a radial direction and an axial direction, the turbomachine comprising:
a spool;
a turbine section comprising a turbine and a turbine center frame located forward of a midpoint of the turbine, the 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 the second plurality of turbine rotor blades alternatingly spaced along the axial direction and rotatable with one another, the first plurality of turbine rotor blades and the second plurality of turbine rotor blades each arranged aft of the turbine center frame and supported by the turbine center frame via a support assembly;
a first support member, the first plurality of turbine rotor blades coupled to the spool through the first support member;
a second support member, the second plurality of turbine rotor blades supported by the second support member; and
a bearing assembly comprising a first bearing and a second bearing, the first bearing and the second bearing each rotatably supporting the second support member and axially aligned with the first plurality of turbine rotor blades, the second plurality of turbine rotor blades, or both; and
wherein the support assembly comprises a frame support member coupled to the turbine center frame, the first bearing and the second bearing of the bearing assembly positioned between the frame support member and the second support member.

15. The turbomachine of claim 14 , 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.

16. The turbomachine of claim 15 , 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, wherein at least two of the plurality of low-speed turbine rotor blades are spaced from one another along the axial direction and

Assignees

• Gen Electric

Inventors

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

Classifications

• F02C3/067 Primary

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

• F01D25/164

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

• F05D2260/40311

  of the epicyclical, planetary or differential type · CPC title

• F05D2240/40

  Use of a multiplicity of similar components · CPC title

• F02C7/06

  Arrangements of bearings (bearings F16C); Lubricating ({of turbo machines F01D25/18; of machines or} engines in general F01M) · CPC title