TURBINE ROTOR BLADE

• US 20160258301A1
• Filed: 03/04/2015
• Published: 09/08/2016
• Est. Priority Date: 03/04/2015
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (General Electric Company)
• Original Assignee: General Electric Company
• Inventors: Chouhan, Rohit, Jaiswal, Shashwat Swami
• Granted Patent: US 10,001,019 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: F01D 5/18 Hollow blades, i.e. blades with cooling or heating channels or cavities structure of hollow blades in general F01D5/147; Heating, heat-insulating or cooling means on blades
• CPC Class Codes: F01D 5/20 Specially-shaped blade tips to seal space between tips and stator F01D5/225 takes precedence
• CPC Class Codes: F02C 3/04 having a turbine driving a compressor power transmission arrangements F02C7/36; control of working fluid flow F02C9/16
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2240/307 related to the tip of a rotor blade
• CPC Class Codes: F05D 2240/35 Combustors or associated equipment
• CPC Class Codes: F05D 2250/121 square
• CPC Class Codes: F05D 2250/141 circular
• CPC Class Codes: F05D 2260/20 Heat transfer, e.g. cooling

Abstract

A turbine rotor blade includes a tip portion having a pressure tip wall and a suction tip wall, a tip leading edge and a tip trailing edge. Also included is a squealer cavity at least partially defined by the pressure tip wall and the suction tip wall. Further included is at least one hole defined by the suction tip wall, the at least one hole configured to bleed a cooling flow out of the squealer cavity into a hot gas path to reduce pressure within the squealer cavity. Yet further included is a main body having a suction side wall and a pressure side wall each extending from a root portion of the turbine rotor blade to the tip portion.

Claims

1. A turbine rotor blade comprising:

a tip portion having a pressure tip wall and a suction tip wall, a tip leading edge and a tip trailing edge;

a squealer cavity at least partially defined by the pressure tip wall and the suction tip wall;

at least one hole defined by the suction tip wall, the at least one hole configured to bleed a cooling flow out of the squealer cavity into a hot gas path to reduce pressure within the squealer cavity; and

a main body having a suction side wall and a pressure side wall each extending from a root portion of the turbine rotor blade to the tip portion.

2. The turbine rotor blade of claim 1, wherein the at least one hole is located proximate the tip leading edge.

3. The turbine rotor blade of claim 1, wherein the at least one hole comprises a plurality of holes.

4. The turbine rotor blade of claim 3, wherein the plurality of holes are arranged in a plurality of rows.

5. The turbine rotor blade of claim 3, wherein the plurality of holes are arranged in a single row.

6. The turbine rotor blade of claim 1, wherein the at least one hole comprises a geometry selected from a group consisting of a circle, a square, a rectangle, and an ellipse.

7. The turbine rotor blade of claim 1, wherein the suction tip wall and the pressure tip wall each extend fully to the tip trailing edge.

8. The turbine rotor blade of claim 1, wherein the suction tip wall partially extends toward the tip trailing edge.

9. The turbine rotor blade of claim 1, further comprising a tip plate that divides the tip portion from the main body.

10. The turbine rotor blade of claim 1, wherein the cooling flow is routed through the main body and expelled into the squealer cavity prior to being partially expelled through the at least one hole of the suction tip wall.

11. A turbine section of a turbine system comprising:

a plurality of turbine rotor blades forming a plurality of turbine stages, wherein each of the plurality of turbine rotor blades includes a main body having a leading edge, a trailing edge, a suction side wall and a pressure side wall;

a tip portion of at least one of the plurality of turbine rotor blades having a pressure tip wall and a suction tip wall, a tip leading edge and a tip trailing edge;

a squealer cavity at least partially defined by the pressure tip wall and the suction tip wall; and

at least one hole defined by the suction tip wall, the at least one hole configured to bleed a cooling flow out of the squealer cavity into a hot gas path to reduce pressure within the squealer cavity.

12. The turbine section of claim 11, wherein the at least one hole is located proximate the tip leading edge.

13. The turbine section of claim 11, wherein the at least one hole comprises a plurality of holes.

14. The turbine section of claim 13, wherein the plurality of holes are arranged in a plurality of rows.

15. The turbine section of claim 13, wherein the plurality of holes are arranged in a single row.

16. The turbine section of claim 11, wherein the at least one hole comprises a geometry selected from a group consisting of a circle, a square, a rectangle, and an ellipse.

17. The turbine section of claim 11, wherein the suction tip wall and the pressure tip wall each extend fully to the tip trailing edge.

18. The turbine section of claim 11, wherein the suction tip wall partially extends toward the tip trailing edge.

19. The turbine section of claim 11, further comprising a tip plate that divides the tip portion from the main body.

20. A gas turbine engine comprising:

a compressor section;

a combustion section; and

a turbine section comprising;

a tip portion having a pressure tip wall and a suction tip wall, a tip leading edge and a tip trailing edge;

a squealer cavity at least partially defined by the pressure tip wall and the suction tip wall; and

a plurality of holes defined by the suction tip wall and located proximate the tip leading edge, the plurality of holes configured to bleed a cooling flow out of the squealer cavity into a hot gas path to reduce pressure within the squealer cavity.