Turbomachine rotor blade

Patent metadata

Field	Value
Publication number	US-11060407-B2
Application number	US-201715630067-A
Country	US
Kind code	B2
Filing date	Jun 22, 2017
Priority date	Jun 22, 2017
Publication date	Jul 13, 2021
Grant date	Jul 13, 2021

Abstract

The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil and a tip shroud coupled to the airfoil. The tip shroud includes a side surface. The airfoil and the tip shroud define a first cooling passage. The tip shroud further defines a second passage in fluid communication with the first cooling passage. The second cooling passage extends from the first cooling passage to a first outlet defined by the side surface. The first outlet is configured to direct a flow of coolant onto a tip shroud fillet of a first adjacent rotor blade.

First claim

What is claimed is:

1. A rotor blade for a turbomachine, the rotor blade comprising:
an airfoil;
a tip shroud coupled to the airfoil, the tip shroud including a side surface, the side surface defining the outermost boundary of the tip shroud in an axial direction and a circumferential direction, the airfoil and the tip shroud defining a first cooling passage extending from an upstream end to a downstream end, the tip shroud further defining a second cooling passage intersecting and directly fluidly connected to the first cooling passage, the second cooling passage extending from an inlet at the downstream end of the first cooling passage to a first outlet defined on the side surface, the first outlet being configured to direct a coolant onto a tip shroud fillet of a first adjacent rotor blade, wherein the inlet defines a first diameter and the first outlet defines a second diameter, wherein the first diameter is equal to the second diameter, and wherein the first outlet is configured to expel the coolant at a sufficient velocity to traverse a gap between the first outlet and the tip shroud fillet such that the coolant impinges on the tip shroud fillet of the first adjacent rotor blade; and
a plug positioned in a radially outer end of the first cooling passage to direct the coolant flowing through the first cooling passage into the second cooling passage, the plug being positioned entirely radially outward from the second cooling passage.

2. The rotor blade of claim 1 , wherein the tip shroud entirely defines the second cooling passage.

3. The rotor blade of claim 1 , wherein the tip shroud comprises a seal rail extending outward from a radially outer surface of the tip shroud, the second cooling passage disposed radially inward from both the radially outer surface of the tip shroud and the seal rail, and wherein the second cooling passage extends parallel to the seal rail.

4. The rotor blade of claim 1 , wherein the airfoil and the tip shroud further define a third cooling passage, the tip shroud further defining a fourth cooling passage in fluid communication with the third cooling passage, the fourth cooling passage extending from the third cooling passage to a second outlet defined by the side surface, the second outlet being configured to direct the coolant onto a tip shroud fillet of a second adjacent rotor blade.

5. The rotor blade of claim 4 , wherein the first outlet is positioned on a pressure side of the tip shroud and the second outlet is positioned on a suction side of the tip shroud.

6. The rotor blade of claim 4 , wherein the tip shroud comprises a seal rail extending outward from a radially outer surface of the tip shroud, the second cooling passage being positioned forward of the seal rail and the fourth cooling passage being positioned aft of the seal rail.

7. The rotor blade of claim 4 , wherein the second cooling passage and the fourth cooling passage are substantially parallel.

8. A turbomachine, comprising:
a turbine section including a plurality of rotor blades, a first rotor blade of the plurality of rotor blades comprising:
an airfoil;
a tip shroud coupled to the airfoil, the tip shroud including a side surface, the side surface defining the outermost boundary of the tip shroud in an axial direction and a circumferential direction, the airfoil and the tip shroud defining a first cooling passage extending from an upstream end to a downstream end, the tip shroud further defining a second cooling passage extending from an inlet at the first cooling passage to a first outlet defined on the side surface, wherein the downstream end of the first cooling passage intersects and is directly fluidly connected to the inlet of the second cooling passage, the first outlet being configured to direct a coolant onto a tip shroud fillet of a second rotor blade of the plurality of rotor blades, wherein the inlet defines a first diameter and the first outlet defines a second diameter, wherein the first diameter is equal to the second diameter, and wherein the first outlet is configured to expel the coolant at a sufficient velocity to traverse a gap between the first outlet and the concave tip shroud fillet such that the coolant impinges on the tip shroud fillet of the first adjacent rotor blade; and
a plug positioned in a radially outer end of the first cooling passage to direct the coolant flowing through the first cooling passage into the second cooling passage, the plug being positioned entirely radially outward from the second cooling passage.

9. The turbomachine of claim 8 , wherein the tip shroud entirely defines the second cooling passage.

10. The turbomachine of claim 8 , wherein the tip shroud comprises a seal rail extending outward from a radially outer surface of the tip shroud, the second cooling passage extending along the seal rail.

11. The turbomachine of claim 8 , wherein the plug directs all of the coolant flowing through the first cooling passage into the second cooling passage.

12. The turbomachine of claim 8 , wherein the airfoil and the tip shroud further define a third cooling passage, the tip shroud further defining a fourth cooling passage in fluid communication with the third cooling passage, the fourth cooling passage extending from the third cooling passage to a second outlet defined by the side surface, the second outlet being configured to direct the coolant onto a tip shroud fillet of a third rotor blade of the plurality of rotor blades.

13. The turbomachine of claim 12 , wherein the first outlet is positioned on a pressure-side of the tip shroud and the second outlet is positioned on a suction-side of the tip shroud.

14. The turbomachine of claim 12 , wherein the tip shroud comprises a seal rail extending outward from a radially outer surface of the tip shroud, the second cooling passage being positioned forward of the seal rail and the fourth cooling passage being positioned aft of the seal rail.

15. The turbomachine of claim 12 , wherein the second cooling passage and the fourth cooling passage are substantially parallel.

16. A turbomachine, comprising:
a turbine section including a plurality of rotor blades, a first rotor blade of the plurality of rotor blades comprising:
an airfoil;
a tip shroud coupled to the airfoil, the tip shroud including a side surface having a convex tip shroud fillet, the side surface defining the outermost boundary of the tip shroud in an axial direction and a circumferential direction, the airfoil and the tip shroud defining a first cooling passage extending from an upstream end to a downstream end, the tip shroud further defining a second cooling passage intersecting and directly fluidly connected to the first cooling passage, the second cooling passage extending from an inlet at the downstream end of the first cooling passage to an outlet defined entirely on the side surface and disposed on the convex fillet, the outlet being configured to direct a coolant onto a concave tip shroud fillet of an adjacent second rotor blade, wherein the inlet defines a first diameter and the outlet defines a second diameter, wherein the first diameter is equal to the second diameter, and wherein the outlet is configured to expel the coolant at a sufficient velocity to traverse a gap between the outlet and the concave tip shroud fillet such that the coolant impinges on the concave tip shroud fillet of the adjacent second rotor blade; and
a plug positioned in a radially outer end of the first cooling passage to direct the coolant flowing through the first cooling passage into the second cooling passage, the plug being positioned entirely radially outward from

Assignees

• Gen Electric

Inventors

• Brittingham Robert Alan

Classifications

• F05D2260/20

  Heat transfer, e.g. cooling · CPC title

• F05D2240/307

  related to the tip of a rotor blade · CPC title

• F01D11/08

  for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) · CPC title

• F01D5/225 Primary

  by shrouding · CPC title

• F01D5/187 Primary

  Convection cooling · CPC title