Non-Integral Turbine Blade Platforms and Systems

• US 20100172760A1
• Filed: 01/06/2009
• Published: 07/08/2010
• Est. Priority Date: 01/06/2009
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (General Electric Company)
• Original Assignee: General Electric Company
• Inventors: Ammann, Luke J.
• Granted Patent: US 8,382,436 B2
• Time in Patent Office: Days
• US Class Current: 416/179
• CPC Class Codes: F01D 11/008 by spacer elements between the blades, e.g. independent interblade platforms
• CPC Class Codes: F01D 5/282 Selecting composite materials, e.g. blades with reinforcing filaments
• CPC Class Codes: F01D 5/284 Selection of ceramic materials
• CPC Class Codes: F01D 5/3015 with side plates
• CPC Class Codes: F05D 2300/6033 Ceramic matrix composites [CMC]
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft
• CPC Class Codes: Y10T 29/49316 Impeller making

Abstract

In one embodiment, a turbine blade platform may be disposed between two turbine blades. The platform may include a first exterior side configured to interface with a first turbine blade. The platform also may include a second exterior side disposed generally opposite the first exterior side and configured to interface with a second turbine blade.

Claims

1. A system, comprising:

a first turbine blade platform, comprising;

a first exterior side configured to interface with a first turbine blade disposed at a first angular position; and

a second exterior side disposed generally opposite the first exterior side and configured to interface with a second turbine blade disposed at a second angular position.

2. The system of claim 1, wherein the first turbine blade platform comprises a ceramic matrix composite material.

3. The system of claim 1, wherein the first turbine blade platform comprises an attachment mechanism configured to attach the first side of the turbine blade platform to an adjacent turbine blade platform.

4. The system of claim 1, wherein the first turbine blade platform comprises:

a pair of integral cover plates disposed generally opposite to each other and generally transverse to the first and second exterior sides; and

integral angel wings disposed on the integral cover plates.

5. The system of claim 1, comprising a second turbine blade platform adjoining the first exterior side of the first turbine blade platform, wherein the second turbine blade platform comprises a third exterior side corresponding to the second exterior side and wherein the third exterior side and the first exterior side form an opening configured to encircle the first turbine blade.

6. The system of claim 1, comprising a plurality of turbine blade platforms each corresponding to the first turbine blade platform and disposed in a circumferential arrangement to define a plurality of intermediate openings configured to encircle turbine blades.

7. The system of claim 6, comprising a rotor wheel with a plurality of circumferentially spaced openings configured to receive the turbine blades at angular positions around the rotor wheel, wherein the plurality of turbine blade platforms are radially positioned between the circumferentially spaced openings.

8. The system of claim 1, comprising a rotor, a turbine, a turbine engine, a compressor, a combustor, or combinations thereof.

9. A system, comprising:

a plurality of turbine blades circumferentially spaced about an axis; and

at least one turbine blade platform disposed between and supported by first and second turbine blades of the plurality of turbine blades, wherein the at least one turbine blade platform partially encircles each of the first and second turbine blades.

10. The system of claim 9, wherein each of the plurality of turbine blades comprises a concave pressure side and a convex suction side, and the at least one turbine blade platform comprises a convex exterior side contiguously disposed on the concave pressure side of the first turbine blade and a concave exterior side contiguously disposed on the convex suction side of the second turbine blade.

11. The system of claim 9, wherein each of the plurality of turbine blades comprises an airfoil, a shank, and a dovetail.

12. The system of claim 9, wherein each of the plurality of turbine blades comprises a contour configured to interface with the at least one turbine blade platform.

13. The system of claim 9, wherein the at least one turbine blade platform comprises a ceramic matrix composite and each of the plurality of turbine blades comprise a metal.

14. The system of claim 9, wherein the at least one turbine blade platform comprises:

a first side configured to generally conform to a suction side of the turbine blades; and

a second side configured to generally conform to a pressure side of the turbine blades.

15. The system of claim 9, comprising a plurality of turbine blade platforms disposed between and interfacing with each of the plurality of turbine blades.

16. The system of claim 9, comprising a turbine engine having the turbine blades and the at least one turbine blade platform.

17. A method, comprising:

positioning turbine blades into openings disposed circumferentially about a rotor wheel;

positioning turbine blade platforms between each of the turbine blades;

inserting the turbine blades into the rotor wheel to secure the turbine blades within the rotor wheel; and

setting the turbine blade platforms towards the rotor wheel such that each of the turbine blade platforms interfaces with an adjacent turbine blade platform to encompass one of the turbine blades.

18. The method of claim 17, wherein positioning turbine blades comprises partially inserting dovetails of the turbine blades into the openings.

19. The method of claim 17, wherein positioning turbine blade platforms comprises interfacing the turbine blade platforms with the turbine blades such that each of the turbine blade platforms is supported on opposite sides by the turbine blades.

20. The method of claim 17, wherein positioning turbine blade platforms comprises aligning a contoured side of the turbine blade platform with a turbine blade, wherein the contoured side interfaces with the turbine blade.