METHODS FOR REPAIRING A GAS TURBINE COMPONENT

• US 20110099809A1
• Filed: 10/29/2010
• Published: 05/05/2011
• Est. Priority Date: 10/30/2009
• Status: Active Grant

• Current Assignee: General Electric Technology GmbH (GE Vernova, Inc.)
• Original Assignee: Alstom Technology Ltd. (Alstom SA)
• Inventors: Ambrosy, Günter, Hövel, Simone, Höbel, Matthias
• Granted Patent: US 8,978,249 B2
• Time in Patent Office: Days
• US Class Current: 29/888
• CPC Class Codes: B23P 6/005 using only replacement pieces of a particular form
• CPC Class Codes: F01D 5/005 Repairing methods or devices
• CPC Class Codes: F05D 2230/80 Repairing, retrofitting or upgrading methods
• CPC Class Codes: Y10T 29/49229 Prime mover or fluid pump making
• CPC Class Codes: Y10T 29/49318 Repairing or disassembling
• CPC Class Codes: Y10T 29/49336 Blade making
• CPC Class Codes: Y10T 29/49732 by attaching repair preform, e.g., remaking, restoring, or patching
• CPC Class Codes: Y10T 29/49734 and removing damaged material
• CPC Class Codes: Y10T 29/49771 Quantitative measuring or gauging

Abstract

A method for repairing a gas turbine component includes:

• • identifying on the gas turbine component (10) a worn out location, where the gas turbine component (10) is damaged;
  • removing the damaged location, thereby creating a missing zone (18);
  • manufacturing an insert, which fits into the missing zone (18);
  • putting the insert into the missing zone (18);
  • adjusting the insert in the gas turbine component (10); and
  • joining the adjusted insert to the gas turbine component (10).

A higher degree of precision and automation can be achieved, because

• • the worn out location is measured/scanned with a 3-D scanning/measuring system (20) to get the actual geometry of the missing zone (18), especially as a CAD data;
  • the nominal geometry for the insert is defined by the actual geometry of the worn out location, with respect to certain defined gap tolerances;
  • the actual geometry of the insert is measured during the manufacture of the insert;
  • the nominal geometry and the actual geometry of the insert are compared; and
  • an adaptive machining operation of the insert is carried out based on the results from the comparison between the actual and nominal geometries of the insert.

Claims

1. A method for repairing a gas turbine component comprising:

identifying on said gas turbine component a worn out location at which said gas turbine component is damaged;

removing said damaged location and creating a missing zone;

manufacturing an insert which fits into said missing zone;

putting said insert into said missing zone;

adjusting said insert in said gas turbine component;

joining said adjusted insert to said gas turbine component;

measuring the worn out location with a 3-D measuring system to determine the actual geometry of the missing zone;

wherein the nominal geometry for the insert is defined by said actual geometry of the worn out location with respect to predefined gap tolerances;

wherein measuring the actual geometry of the insert comprises measuring during said manufacturing an insert;

comparing the nominal geometry and the actual geometry of the insert; and

wherein manufacturing an insert comprises adaptive machining the insert based on said comparing.

2. The method according to claim 1, further comprising:

establishing a component-specific reference coordinate system using characteristic features of the damaged gas turbine component; and

wherein comparing the nominal geometry and the actual geometry of the insert comprises comparing using the component-specific reference coordinate system.

3. The method according to claim 2, further comprising:

creating reference marks on the damaged gas turbine component; and

wherein establishing the component-specific reference coordinate system comprises establishing in part based on said reference marks.

4. The method according to claim 3, wherein creating reference marks comprises laser engraving.

5. The method according to claim 1, wherein manufacturing an insert comprises CNC machining based on said comparing of the nominal geometry and the actual geometry of the insert.

6. The method according to claim 1, wherein said measuring of the actual geometry of the insert and said adaptive machining of the insert are performed in the same fixture.

7. The method according to claim 1, wherein said measuring of the actual geometry of the insert and said adaptive machining of the insert are performed in one machine tool.

8. The method according to claim 1, wherein the insert comprises features not needed for functionality of the insert in the repaired gas turbine component, the features being configured and arranged to allow clamping and assisting the adaptive machining operation.

9. The method according to claim 8, wherein said features comprise handles, pins, or stems.

10. The method according to claim 1, wherein manufacturing the insert comprises forming reference features configured and arranged to allow the measurement system to determine the position and orientation of the insert relative to the component-specific reference coordinate system.

11. The method according to claim 1, wherein the insert comprises additional geometrical fixation devices for said joining.

12. The method according to claim 1, wherein said joining comprises low heat input joining optimized to avoid distortion of the insert.

13. The method according to claim 12, wherein joining comprises brazing, laser welding, E-beam welding, or combinations thereof.

14. The method according to claim 1, further comprising:

recontouring the insert and gas turbine component after said joining.

15. The method according to claim 8, further comprising:

removing said features not needed for functionality of the insert by machining after said joining.

16. The method according to claim 1, wherein determining the actual geometry of the missing zone comprises generating CAD data.