Method for repairing a damaged leading or trailing edge region of a metallic turbine blade

Patent metadata

Field	Value
Publication number	US-11958150-B2
Application number	US-202118025901-A
Country	US
Kind code	B2
Filing date	Aug 6, 2021
Priority date	Sep 24, 2020
Publication date	Apr 16, 2024
Grant date	Apr 16, 2024

Abstract

A method for repairing a damaged leading or trailing edge region of a metallic turbine blade, which has a suction-side blade wall, a pressure-side blade wall and a leading edge and a trailing edge, includes: removing the damaged leading or trailing edge region, with a cutout being formed; providing a replacement part which can be inserted in form-fitting fashion into the cutout and which restores the intended geometry of the turbine blade; inserting the replacement part in form-fitting fashion into the cutout in a predetermined insertion direction, and cohesively connecting the replacement part to the turbine blade, wherein mechanical connection of the replacement part and turbine blade using separate fastening elements is performed in addition to the cohesive connection.

First claim

The invention claimed is:

1. A method for repairing a damaged leading or trailing edge region of a metallic turbine blade, which has a suction-side blade wall, a pressure-side blade wall and a leading edge and a trailing edge, comprising:
a) removing the damaged leading or trailing edge region, forming a cutout;
b) providing a replacement part which can be inserted by form fit into the cutout and which restores an intended geometry of the turbine blade;
c) inserting the replacement part by form fit into the cutout in a predetermined insertion direction, and
d) connecting the replacement part to the turbine blade by substance bonding,
wherein in step a), recesses without undercut relative to the insertion direction are formed in the blade walls, wherein the recesses of the suction-side blade wall are positioned offset to the recesses of the pressure-side blade wall when the turbine blade is viewed from the side,
wherein the replacement part provided in step b) has protrusions which in step c) are inserted by form fit in the recesses, wherein after insertion of the replacement part, the replacement part and the turbine blade have regions overlapping one another when the turbine blade is viewed from the side, and
wherein in step c), after insertion in the cutout, the replacement part is fixed to the turbine blade using fixing elements extending through mutually overlapping regions, such that this mechanical fixing blocks removal of the replacement part from the cutout against the predetermined insertion direction.

2. The method as claimed in claim 1 ,
wherein in step a), the cutout is produced using an erosion process, a vertical spark erosion process, and/or wire spark erosion process.

3. The method as claimed in claim 1 ,
wherein the fixing elements are pin-like and are guided through passage openings provided in the overlapping regions.

4. The method as claimed in claim 1 ,
wherein the replacement part is made by additive manufacturing.

5. The method as claimed in claim 1 ,
wherein the replacement part is a standard replacement part with standard dimensions, and the cutout is produced in step a) taking into account the standard dimensions.

6. The method as claimed in claim 5 ,
wherein the standard replacement part is machined before insertion in step c), so as to minimize deviations of a geometry of the standard replacement part from a geometry of the cutout.

7. The method as claimed in claim 1 ,
wherein abutting edges of the replacement part are provided with spacer protrusions which serve to set a predetermined joint width for a substance-bonded connection.

8. The method as claimed in claim 7 ,
wherein the substance-bonded connection of the replacement part to the turbine blade takes place using a soldering process, and/or using a narrow-gap soldering process.

9. A turbine blade, comprising:
a suction-side blade wall,
a pressure-side blade wall,
a leading edge, and
a trailing edge,
wherein a damaged leading or trailing edge region is repaired using a method as claimed in claim 1 .

Assignees

• Siemens Energy Global Gmbh & Co Kg

Inventors

• Anders Björn
• Anton Reiner
• Garske Constantin
• Krabiell Kay
• Lammers Heiko
• Nilsson Ricardo
• Vöhringer Daniel
• Ziege Jörg

Classifications

• B23P6/005 Primary

  using only replacement pieces of a particular form · CPC title

• B23K1/0018

  Brazing of turbine parts · CPC title

• F01D5/005 Primary

  Repairing methods or devices · CPC title

• B23K2101/001

  Turbines · CPC title

• B33Y80/00

  Products made by additive manufacturing · CPC title