Rotor blade tip

• US 10,443,405 B2
• Filed: 05/10/2017
• Issued: 10/15/2019
• Est. Priority Date: 05/10/2017
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (General Electric Company)
• Original Assignee: General Electric Company
• Inventors: Subramaniyan, Moorthi, Fredmonski, Adam John
• Primary Examiner(s): Newton, J. Todd
• Application Number:
  US15/591,242
• Publication Number:
  US 20180328191A1
• Time in Patent Office: 888 Days
• Field of Search: 415115
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F01D 5/20 Specially-shaped blade tips to seal space between tips and stator F01D5/225 takes precedence
• CPC Class Codes: F01D 5/3007 of axial insertion type
• 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 2260/202 by film cooling
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A rotor blade includes an airfoil. The airfoil includes a leading edge and a trailing edge downstream of the leading edge. The airfoil also includes a radially outer tip with a pressure side tip rail and a suction side tip rail. A slot is formed in an aft portion of the suction side tip rail and an opening is positioned between the suction side tip rail and the pressure side tip rail at the trailing edge. Gas flows from the tip via the slot and the opening to inhibit formation of a vortex flow proximate to the suction side of the airfoil.

Claims

1. A rotor blade, comprising:

an airfoil, the airfoil comprising;

a leading edge;

a trailing edge downstream of the leading edge;

a root extending between the leading edge and the trailing edge;

a tip spaced radially outward from the root, the tip including a tip floor;

a pressure side wall extending between the root and the tip and extending between the leading edge and the trailing edge;

a suction side wall extending between the root and the tip and extending between the leading edge and the trailing edge, the suction side wall opposing the pressure side wall;

a pressure side tip rail that extends radially outwardly from the tip floor between the leading edge and the trailing edge along the pressure side wall;

a suction side tip rail that extends radially outwardly from the tip floor between the leading edge and the trailing edge along the suction side wall;

a tip cavity defined by the tip floor, the pressure side tip rail and the suction side tip rail, the tip cavity defining a radial extent outward of the tip floor;

a first slot formed in an aft portion of the suction side tip rail;

an opening between the suction side tip rail and the pressure side tip rail at the trailing edge; and

a second slot formed in the aft portion of the suction side tip rail, the second slot between the first slot and the opening;

wherein gas flows from the tip cavity via the slot and the opening, and the gas flow from the tip cavity inhibits formation of a vortex flow proximate to the suction side wall.

2. The rotor blade of claim 1, wherein the second slot is contiguous with the opening.

3. The rotor blade of claim 1, wherein gas flows over the top of the pressure side tip rail into the tip cavity.

4. The rotor blade of claim 1, wherein the first slot defines a height radially outward of the tip floor and the height of the first slot is less than the radial extent of the tip cavity.

5. The rotor blade of claim 1, wherein the aft portion of the suction side tip rail comprises half of the chordal extent of the suction side tip rail.

6. The rotor blade of claim 1, wherein the aft portion of the suction side tip rail comprises less than half of the chordal extent of the suction side tip rail.

7. The rotor blade of claim 1, wherein the aft portion of the suction side tip rail comprises twenty percent of the chordal extent of the suction side tip rail.

8. The rotor blade of claim 1, wherein the suction side tip rail does not extend fully to the trailing edge along the suction side wall.

9. The rotor blade of claim 1, wherein the suction side tip rail defines a thickness along a direction perpendicular to the radial extent of the tip cavity, the aft portion of the suction side tip rail having a maximum thickness proximate to the tip floor, the thickness decreasing over the radial extent of the tip cavity.

10. The rotor blade of claim 1, wherein the first slot forms an angle between about twenty-five degrees and about sixty-five degrees with the suction side wall.

11. The rotor blade of claim 1, wherein the first slot forms an angle of about ninety degrees with the suction side wall.

12. The rotor blade of claim 1, wherein the pressure side tip rail is continuous and uninterrupted along the pressure side wall, the pressure side tip rail defines a constant radial height, and the pressure side tip rail is continuous and uninterrupted over the constant radial height.

13. The rotor blade of claim 1, wherein the suction side tip rail consists of a forward portion and the aft portion, the forward portion of the suction side tip rail is continuous and uninterrupted along the suction side wall from the aft portion to the leading edge, the forward portion of the suction side tip rail defines a constant radial height, and the forward portion of the suction side tip rail is continuous and uninterrupted over the constant radial height.

14. A gas turbine, comprising;

a compressor;

a combustor disposed downstream from the compressor;

a turbine disposed downstream from the combustor, the turbine including a rotor shaft extending axially through the turbine, an outer casing circumferentially surrounding the rotor shaft to define a hot gas path therebetween and a plurality of rotor blades interconnected to the rotor shaft and defining a stage of rotor blades, wherein each rotor blade comprises;

a mounting portion including a mounting body, the mounting body being interconnectable with the rotor shaft; and

an airfoil coupled to the mounting portion, the airfoil comprising;

a leading edge;

a trailing edge downstream of the leading edge;

a root extending between the leading edge and the trailing edge;

a tip spaced radially outward from the root, the tip including a tip floor;

a pressure side wall extending between the root and the tip and extending between the leading edge and the trailing edge;

a suction side wall extending between the root and the tip and extending between the leading edge and the trailing edge, the suction side wall opposing the pressure side wall;

a pressure side tip rail that extends radially outwardly from the tip floor between the leading edge and the trailing edge along the pressure side wall;

a suction side tip rail that extends radially outwardly from the tip floor between the leading edge and the trailing edge along the suction side wall;

a tip cavity defined by the tip floor, the pressure side tip rail and the suction side tip rail, the tip cavity defining a radial extent outward of the tip floor;

a first slot formed in an aft portion of the suction side tip rail;

an opening between the suction side tip rail and the pressure side tip rail at the trailing edge; and

a second slot formed in the aft portion of the suction side tip rail, the second slot between the first slot and the opening;

wherein gas flows from the tip cavity via the slot and the opening, and the gas flow from the tip cavity inhibits formation of a vortex flow proximate to the suction side wall.

15. The gas turbine of claim 14, wherein the second slot of the airfoil of the rotor blade is contiguous with the opening of the airfoil of the rotor blade.

16. The gas turbine of claim 14, wherein the first slot defines a height radially outward of the tip floor and the height of the first slot is less than the radial extent of the tip cavity.

17. The gas turbine of claim 14, wherein the aft portion of the suction side tip rail comprises half of the chordal extent of the suction side tip rail.

18. The gas turbine of claim 14, wherein the aft portion of the suction side tip rail comprises less than half of the chordal extent of the suction side tip rail.

19. The gas turbine of claim 14, wherein the first slot forms an angle between about twenty-five degrees and about sixty-five degrees with the suction side wall.

20. The gas turbine of claim 14, wherein the first slot forms an angle of about ninety degrees with the suction side wall.