Turbine blade having squealer tip

Patent metadata

Field	Value
Publication number	US-10890075-B2
Application number	US-201916294957-A
Country	US
Kind code	B2
Filing date	Mar 7, 2019
Priority date	Apr 4, 2018
Publication date	Jan 12, 2021
Grant date	Jan 12, 2021

Abstract

Disclosed is a turbine blade including a blade part having an airfoil in a cross section having a leading edge, a trailing edge, and a pressure surface and a suction surface connecting the leading edge and the trailing edge, the blade part extending radially from a platform part to a tip portion as a free end in the turbine blade, wherein a cavity through which cooling air flows is formed inside the turbine blade, wherein a squealer tip having a predetermined thickness protrudes along an edge of the tip portion so that a squealer pocket is formed on an inner side of the tip portion by the squealer tip, wherein the squealer tip is provided with a cooling hole communicating with the cavity along a radial direction of the turbine blade, and wherein an undercut is formed around the cooling hole of the squealer tip by cutting a part of the squealer tip in a circumferential direction.

First claim

The invention claimed is:

1. A turbine blade comprising:
a blade part having an airfoil in a cross section including a leading edge, a trailing edge, and a pressure surface and a suction surface connecting the leading edge and the trailing edge, the blade part extending radially from a platform part to a tip portion as a free end in the turbine blade,
wherein a cavity through which cooling air flows is formed inside the turbine blade,
wherein a squealer tip having a predetermined thickness protrudes along an edge of the tip portion so that a squealer pocket is formed on an inner side of the tip portion by the squealer tip,
wherein the squealer tip is provided with at least one cooling hole communicating with the cavity along a radial direction of the turbine blade,
wherein an undercut is formed around the at least one cooling hole of the squealer tip by cutting a part of the squealer tip in a circumferential direction, and
wherein the at least one cooling hole formed on the suction surface is formed in an inclined manner to discharge the cooling air in a direction toward the squealer pocket.

2. The turbine blade of claim 1 , wherein the at least one cooling hole of the squealer tip is formed on the pressure surface or the suction surface on the airfoil in the cross section.

3. The turbine blade of claim 2 , wherein the at least one cooling hole is formed on both the pressure surface and the suction surface on the airfoil in the cross section such that the at least one cooling hole respectively formed on the pressure surface and the suction surface is staggered so as not to overlap with each other with respect to the circumferential direction.

4. The turbine blade of claim 3 , wherein the at least one cooling hole formed on the suction surface is located along a line extending in a direction orthogonal to the pressure surface at an intermediate point of two adjacent cooling holes formed on the pressure surface.

5. The turbine blade of claim 3 , wherein the at least one cooling hole formed on the pressure surface is formed to discharge the cooling air in a direction parallel to the radial direction.

6. The turbine blade of claim 1 , wherein an edge forming a boundary between an upper surface of the squealer tip and the undercut is chamfered or a fillet-machined.

7. The turbine blade of claim 1 , wherein the squealer pocket is provided with a cooling hole communicating with the cavity along the radial direction of the turbine blade.

8. A turbine blade assembly comprising:
a blade part and a rotor disk, the blade part having an airfoil in a cross section including a leading edge, a trailing edge, and a pressure surface and a suction surface connecting the leading edge and the trailing edge, the blade part extending radially from a platform part to a tip portion as a free end in the turbine blade, the rotor disk circumferentially having a coupling slot through which a root part formed on a bottom surface of the platform part of the turbine blade is inserted,
wherein a cavity through which cooling air flows is formed inside the turbine blade,
wherein a squealer tip having a predetermined thickness protrudes along an edge of the tip portion so that a squealer pocket is formed on an inner side of the tip portion by the squealer tip,
wherein the squealer tip is provided with at least one cooling hole communicating with the cavity along a radial direction of the turbine blade,
wherein an undercut is formed around the at least one cooling hole of the squealer tip by cutting a part of the squealer tip in a circumferential direction, and
wherein the at least one cooling hole formed on the suction surface is formed in an inclined manner to discharge the cooling air in a direction toward the squealer pocket.

9. The turbine blade assembly of claim 8 , wherein the at least one cooling hole of the squealer tip is formed on the pressure surface or the suction surface on the airfoil in the cross section.

10. The turbine blade assembly of claim 9 , wherein the at least one cooling hole is formed on both the pressure surface and the suction surface on the airfoil in the cross section such that the at least one cooling hole respectively formed on the pressure surface and the suction surface is staggered so as not to overlap with each other with respect to the circumferential direction.

11. The turbine blade assembly of claim 10 , wherein the at least one cooling hole formed on the pressure surface is formed to discharge the cooling air in a direction parallel to the radial direction.

12. A gas turbine comprising:
a combustor mixing fuel with compressed air to provide a fuel-air mixture and combusting the fuel-air mixture to generate an expanding high-temperature combustion gas, and a turbine receiving the combustion gas generated in the combustor and converting a reaction force of the combustion gas to a rotary motion of a turbine blade,
wherein the turbine blade comprises a blade part having an airfoil in a cross section including a leading edge, a trailing edge, and a pressure surface and a suction surface connecting the leading edge and the trailing edge, the blade part extending radially from a platform part to a tip portion as a free end in the turbine blade,
wherein a cavity through which cooling air flows is formed inside the turbine blade,
wherein a squealer tip having a predetermined thickness protrudes along an edge of the tip portion so that a squealer pocket is formed on an inner side of the tip portion by the squealer tip,
wherein the squealer tip is provided with at least one cooling hole communicating with the cavity along a radial direction of the turbine blade,
wherein an undercut is formed around the at least one cooling hole of the squealer tip by cutting a part of the squealer tip in a circumferential direction, and
wherein the at least one cooling hole formed on the suction surface is formed in an inclined manner to discharge the cooling air in a direction toward the squealer pocket.

13. The gas turbine of claim 12 , wherein the at least one cooling hole of the squealer tip is formed on the pressure surface or the suction surface on the airfoil in the cross section.

14. The gas turbine of claim 13 , wherein the at least one cooling hole is formed on both the pressure surface and the suction surface on the airfoil in the cross section such that the at least one cooling hole respectively formed on the pressure surface and the suction surface is staggered so as not to overlap with each other with respect to the circumferential direction.

15. The gas turbine of claim 14 , wherein the at least one cooling hole formed on the pressure surface is formed to discharge the cooling air in a direction parallel to the radial direction.

Assignees

• Doosan Heavy Ind & Construction Co Ltd
• Doosan Heavy Ind Constr Co Ltd

Inventors

• Jung Sung Chul

Classifications

• F05D2260/20

  Heat transfer, e.g. cooling · CPC title

• F01D5/186

  Film cooling (F01D5/187 takes precedence) · CPC title

• F05D2240/307

  related to the tip of a rotor blade · CPC title

• F01D5/187 Primary

  Convection cooling · CPC title

• F01D5/20 Primary

  Specially-shaped blade tips to seal space between tips and stator {(F01D5/225 takes precedence)} · CPC title