System for coupling a segment to a rotor of a turbomachine

Patent metadata

Field	Value
Publication number	US-9109456-B2
Application number	US-201113282141-A
Country	US
Kind code	B2
Filing date	Oct 26, 2011
Priority date	Oct 26, 2011
Publication date	Aug 18, 2015
Grant date	Aug 18, 2015

Abstract

Embodiments of the present disclosure include a system having a turbine blade segment having a blade and a mounting segment coupled to the blade. The mounting segment is configured to couple to a slot in a rotor, and the mounting segment has a cavity extending radially into the mounting segment.

First claim

The invention claimed is:

1. A system, comprising:
a steam turbine blade segment comprising:
a blade;
a mounting segment coupled to the blade, wherein the mounting segment is configured to couple to a slot in a rotor; and
a multi-size cavity extending in a radial direction into the mounting segment to a depth in the steam turbine blade segment, wherein the multi-size cavity comprises a first portion followed by a second portion in the radial direction, the first portion has a first constant lateral cross-section along a first axis, the second portion has a second constant lateral cross-section along a second axis, the second constant lateral cross-section is sized less than the first constant lateral cross-section, the second axis extends along the first axis, and the second portion extends in the radial direction to a distal end of the multi-size cavity at the depth.

2. The system of claim 1 , wherein the mounting segment comprises a dovetail joint.

3. The system of claim 1 , wherein the multi-size cavity extends entirely through the mounting segment.

4. The system of claim 3 , wherein the multi-size cavity extends at least partially into the blade.

5. The system of claim 1 , comprising a steam turbine having the steam turbine blade segment.

6. The system of claim 1 , wherein the first constant lateral cross-section and the second constant lateral cross-section are disposed directly one after another in the radial direction.

7. The system of claim 1 , wherein the first portion is disposed in the mounting segment and the second portion is disposed in the blade.

8. The system of claim 1 , wherein the first constant lateral cross-section is circular and the second constant lateral cross-section is circular.

9. The system of claim 1 , wherein the multi-size cavity does not extend through an exterior surface of the blade.

10. The system of claim 1 , wherein the multi-size cavity is formed by a forging, machining, electrochemical, or electrical discharge process.

11. A system, comprising:
a turbine blade segment, comprising:
a blade;
a dovetail joint coupled to the turbine blade, wherein the dovetail joint is configured to couple the turbine blade to a rotor; and
a multi-size cavity extending in a radial direction into the dovetail joint to a depth in the turbine blade segment, wherein the cavity is configured to reduce stress on the turbine blade segment associated with rotation of the turbine blade segment, the multi-size cavity comprises a first portion followed by a second portion in the radial direction, the first portion has a first constant lateral cross-section along a first axis, the second portion has a second constant lateral cross-section along a second axis, the second constant lateral cross-section is sized less than the first constant lateral cross-section, the second axis extends along the first axis, and the second portion extends in the radial direction to a distal end of the multi-size cavity at the depth.

12. The system of claim 11 , wherein the turbine blade segment is a steam turbine blade segment.

13. The system of claim 11 , comprising the rotor or a turbine having the rotor, wherein the dovetail joint is configured to mount in a slot along the rotor, and the slot extends axially or circumferentially relative to a rotational axis of the rotor.

14. The system of claim 11 , wherein the multi-size cavity extends through the dovetail joint and into the turbine blade.

15. The system of claim 11 , wherein the dovetail joint has a plurality of lateral hooks.

16. The system of claim 11 , wherein the turbine blade segment has only a single one of the multi-size cavity extending in the radial direction into the dovetail joint, wherein the multi-size cavity is symmetrical about a radial axis of the dovetail joint.

17. A system, comprising:
a steam turbine blade segment, comprising:
a blade; and
a mounting base coupled to the blade, wherein the mounting base comprises a multi-size cavity extending one way in a radial direction into the mounting base to a depth without penetrating an exterior surface of the blade, the multi-size cavity comprises a first portion followed by a second portion in the radial direction, the first portion has a first constant lateral cross-section along a first axis, the second portion has a second constant lateral cross-section along a second axis, the second constant lateral cross-section is sized less than the first constant lateral cross-section, the second axis extends along the first axis, and the second portion extends in the radial direction to a distal end of the multi-size cavity at the depth.

18. The system of claim 17 , wherein the turbomachine blade segment is a steam turbine blade segment.

19. The system of claim 17 , wherein the multi-size cavity is configured to reduce stress on the turbomachine blade segment associated with rotation of the turbomachine blade segment.

20. The system of claim 17 , comprising a turbine or compressor having the turbomachine blade segment.

21. The system of claim 17 , wherein a first width of the first portion is between 30 to 80 percent of a second width of a neck of the mounting base.

22. The system of claim 17 , wherein the first constant lateral cross-section is circular and the second constant lateral cross-section is circular.

23. The system of claim 17 , wherein the turbomachine blade segment comprises only a single one of the multi-size cavity extending in the radial direction into the mounting base, wherein the multi-size cavity is symmetrical about a radial axis of the mounting base.

Assignees

• Joshi Manish
• Deallenbach Robert Edward
• Gen Electric

Inventors

• Joshi Manish
• Deallenbach Robert Edward

Classifications

• F01D5/3007 Primary

  of axial insertion type · CPC title

• F05D2220/31

  in steam turbines · CPC title

• F01D5/147

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title

• Y02T50/671

  Cross-Sectional Technologies · mapped topic

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title