Rotor-blade tip including cooling configuration

Patent metadata

Field	Value
Publication number	US-12345176-B2
Application number	US-202218559046-A
Country	US
Kind code	B2
Filing date	Apr 5, 2022
Priority date	May 11, 2021
Publication date	Jul 1, 2025
Grant date	Jul 1, 2025

Abstract

A turbine rotor having an improved rotor tip, which has at least one cooling channel in the rotor blade, the cooling channel, in the region of its cuspidal point, having at least one locally limited constriction that is caused by a thickened portion at the end of a partition of the cooling channel.

First claim

The invention claimed is:

1. A turbine blade, comprising:
a blade tip, comprising a first cooling channel and a second cooling channel in a blade airfoil,
wherein the first cooling channel is disposed between a leading edge of the turbine blade and the second cooling channel,
wherein the second cooling channel comprises an inflow limb leading to a reversal region, an outflow limb from the reversal region, and a divider wall between the inflow limb and the outflow limb,
wherein a thickening of an end of the divider wall causes a first narrowing of the second cooling channel at an entrance to the reversal region and a second narrowing of the second cooling channel in the outflow limb,
wherein the second cooling channel comprises at least one outlet opening in the reversal region and through an external wall of the turbine blade,
wherein the at least one outlet opening comprises a discharge opening in an external surface of the external wall,
wherein the at least one outlet opening comprises a conical transition that leads to the discharge opening, and
wherein the discharge opening and the conical transition that leads to the discharge opening are located on the inflow limb side of the divider wall.

2. The turbine blade as claimed in claim 1 ,
wherein a width of the inflow limb immediately before the reversal region is greater than a width of the outflow limb immediately after the reversal region.

3. The turbine blade as claimed in claim 1 , further comprising:
turbulators in the second cooling channel.

4. The turbine blade as claimed in claim 1 , the blade tip further comprising a third cooling channel:
wherein the third cooling channel comprises a third cooling channel inflow limb leading to a third cooling channel reversal region, a third cooling channel outflow limb from the third cooling channel reversal region, and a third cooling channel divider wall between the third cooling channel inflow limb and the third cooling channel outflow limb,
wherein a third cooling channel thickening of an end of the third cooling channel divider wall causes a first narrowing of the third cooling channel at an entrance to the third cooling channel reversal region and a second narrowing of the third cooling channel in the third cooling channel outflow limb, and
wherein the second cooling channel is disposed between the first cooling channel and the third cooling channel.

5. The turbine blade as claimed in claim 4 ,
wherein the third cooling channel comprises a third cooling channel outlet opening in the third cooling channel reversal region and through an external wall of the turbine blade, and
wherein the third cooling channel outlet opening comprises a third cooling channel discharge opening in an external surface of the external wall.

6. The turbine blade as claimed in claim 5 ,
wherein the third cooling channel outlet opening further comprises a third cooling conical transition, and
wherein the third cooling channel discharge opening and the conical transition are located on the inflow limb side of the divider wall.

7. A method for producing a turbine blade, comprising:
producing a turbine blade having a blade tip as claimed in claim 1 .

8. The method as claimed in claim 7 , further comprising:
applying the blade tip to a newly cast component or a component to be repaired.

9. The method as claimed in claim 7 ,
wherein an additive method, and/or a powder-bed method, is used.

10. The turbine blade as claimed in claim 1 ,
wherein the blade tip comprises two second cooling channels in the blade airfoil.

11. The turbine blade as claimed in claim 1 ,
wherein the blade tip comprises three cooling channels in the blade airfoil.

12. The turbine blade as claimed in claim 1 ,
wherein the inflow limb, the reversal region, and the outflow limb are free of any openings other than the at least one outlet opening through the external wall of the turbine blade.

13. The turbine blade as claimed in claim 1 ,
wherein the at least one outlet opening further comprises a channel with a constant cross section between the conical transition and the discharge opening.

14. The turbine blade as claimed in claim 1 ,
wherein the first cooling channel comprises a tubular form and is configured to be supplied with coolant originating from a blade root.

15. The turbine blade as claimed in claim 1 ,
wherein the first cooling channel comprises an outlet through the blade tip.

16. The turbine blade as claimed in claim 1 ,
wherein the first cooling channel is set apart from the second cooling channel by a wall disposed there between.

Assignees

• Siemens Energy Global Gmbh & Co Kg

Inventors

• Anders Björn
• Garske Constantin
• Krabiell Kay
• Lammers Heiko
• Lempke Markus
• Nilsson Ricardo
• Vöhringer Daniel

Classifications

• F05D2260/2214

  by increasing the heat transfer surface · CPC title

• F05D2250/185

  serpentine-like · CPC title

• F05D2240/307

  related to the tip of a rotor blade · CPC title

• F05D2230/80

  Repairing, retrofitting or upgrading methods · CPC title

• F01D5/20

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