Method for closing core printout holes in superalloy gas turbine blades

• US 6,454,156 B1
• Filed: 06/23/2000
• Issued: 09/24/2002
• Est. Priority Date: 06/23/2000
• Status: Active Grant

• Current Assignee: Siemens Energy Incorporated (Siemens AG)
• Original Assignee: Siemens Westinghouse Power Corporation
• Inventors: Taras, Michael A. Jr., Sabol, Stephen M.
• Primary Examiner(s): Elve, M. Alexandra
• Assistant Examiner(s): JOHNSON, JONATHAN J
• Application Number:
  US09/602,215
• Time in Patent Office: 823 Days
• Field of Search: 228/119-165, 228/161, 228/121, 228/171, 228/248.1, 228/124.7, 164/3, 298/891, 294/020.7, 294/020.8
• US Class Current: 228/165
• CPC Class Codes: B23K 20/16 with interposition of special material to facilitate connection of the parts, e.g. material for absorbing or producing gas
• CPC Class Codes: F01D 5/18 Hollow blades, i.e. blades with cooling or heating channels or cavities structure of hollow blades in general F01D5/147; Heating, heat-insulating or cooling means on blades
• CPC Class Codes: Y10T 29/49318 Repairing or disassembling

Abstract

A hole (3) formed in a superalloy turbine blade (12) is sealed by providing a superalloy plug (4), machining the hole to be of a configuration can receive the plug therein, and bonding the plug to the turbine blade. The plug can be of a threaded or unthreaded configuration and can be of a tapered or straight configuration. The plug is bonded to the hole by applying a bonding catalyst to one or both of the plug and the hole or by positioning the bonding catalyst therebetween, and providing appropriate treatment to the bonding catalyst, such as heating or other treatment, to cause the bonding catalyst to form a bond between the plug and the turbine blade to form a joint therebetween. Any of a variety of known bonds can be employed to form the joint. The plug additionally may be pre-cooled prior to insertion thereof into the hole in the turbine blade, or alternatively may be of a coefficient of thermal expansion that is greater than that of the turbine blade.

Claims

1. A method of closing a core printout hole in a superalloy turbine blade, the method comprising the steps of:

providing a superalloy plug having a given peripheral configuration;

forming the hole to have a configuration that is structured to cooperatively receive the plug therein and to form a mechanical lock therebetween;

receiving the plug in the hole; and

bonding the plug to the turbine blade.

2. The method as set forth in claim 1, in which the step of providing a superalloy plug includes the step of providing a superalloy plug having a threaded peripheral configuration.

3. The method as set forth in claim 2, in which the step of providing a superalloy plug includes the step of providing a superalloy plug having a tapered peripheral configuration with respect to a longitudinal axis of the plug with a gap distance of about 1-4 mils between the plug and turbine blade along at least a portion of the plug length.

4. The method as set forth in claim 1, in which the step of bonding includes the steps of applying a bonding catalyst to at least one of the plug and the turbine blade and heating the bonding catalyst.

5. The method as set forth in claim 4, in which the step of heating the bonding catalyst includes the steps of at least partially melting the bonding catalyst and causing the bonding catalyst to flow into a gap between the plug and the turbine blade.

6. The method as set forth in claim 1, in which the step of bonding the plug includes the steps of forming one of a diffusion braze joint, a liquid phase diffusion sintering joint, and a transient liquid phase joint between the plug and the turbine blade.

7. The method as set forth in claim 1, in which the turbine blade has a first coefficient of thermal expansion, and in which the step of providing a superalloy plug includes the step of providing a superalloy plug having a second coefficient of thermal expansion that is greater than the first coefficient of thermal expansion.

8. The method as set forth in claim 1, further comprising the step of pre-cooling the plug.

9. A method of closing a core printout hole in a superalloy turbine blade, the method comprising the steps of:

providing a superalloy plug having a threaded peripheral configuration;

forming the hole to have a threaded configuration that is structured to receive the plug therein;

receiving the plug in the hole;

applying a bonding catalyst to at least one of the plug and the turbine blade in the vicinity of the hole; and

forming a joint between the plug and the turbine blade.

10. The method as set forth in claim 9, in which the step of providing a superalloy plug having a threaded peripheral configuration includes the step of providing a superalloy plug having a tapered peripheral configuration with respect to a longitudinal axis of the plug.

11. The method as set forth in claim 9, which the turbine blade has a first coefficient of thermal expansion, and in which the step of providing a superalloy plug includes the step of providing a superalloy plug having a second coefficient of thermal expansion that is greater than the first coefficient of thermal expansion.

12. The method as set forth in claim 9, which the step of providing a superalloy plug includes the step of providing a superalloy plug having a tapered peripheral configuration with respect to a longitudinal axis of the plug.

13. The method as set forth in claim 12, in which the step of providing a superalloy plug having a tapered peripheral configuration includes the step of providing a superalloy plug having a non-circular cross-section with respect to a plane oriented perpendicular to the longitudinal axis of the plug.

14. The method as set forth in claim 12, in which the step of forming a joint includes at least one of the steps of heating the bonding catalyst and compressing the plug into the hole.

15. The method as set forth in claim 9, in which the step of bonding the plug includes the step of forming one of a braze joint, a diffusion braze joint, a liquid phase diffusion sintering joint, a transient liquid phase joint, and a diffusion bond joint between the plug and the turbine blade.

16. The method as set forth in claim 9, further comprising the step of pre-cooling the plug.

17. A method of closing a core printout hole in a superalloy turbine blade having a first coefficient of thermal expansion, the method comprising the steps of:

providing a superalloy plug having a tapered peripheral configuration with respect to the longitudinal axis of the plug and having a second coefficient of thermal expansion that is greater than the first coefficient of thermal expansion;

forming the hole to have a configuration that is structured to receive the plug therein;

receiving the plug in the hole; and

bonding the plug to the turbine blade.

18. The method as set forth in claim 17, in which the step of providing a superalloy plug having a tapered peripheral configuration includes the step of providing a superalloy plug having a non-circular cross-section with respect to a plane oriented perpendicular to the longitudinal axis of the plug.

19. The method as set forth in claim 17, in which the step of providing a superalloy plug includes the step of providing a superalloy plug having a threaded peripheral configuration.

20. The method as set forth in claim 17, in which the step of bonding includes the steps of applying a bonding catalyst to at least one of the plug and the turbine blade and heating the bonding catalyst.

21. The method as set forth in claim 17, in which the step of bonding the plug includes the step of forming one of a braze joint, a diffusion braze joint, a liquid phase diffusion sintering joint, a transient liquid phase joint, and a diffusion bond joint between the plug and the turbine blade.

22. A method of closing a core printout hole in a superalloy turbine blade, the method comprising the steps of:

providing a superalloy plug having a given peripheral configuration;

forming the hole to have a configuration that is structured to cooperatively receive the plug therein;

pre-cooling the plug to a temperature lower than that of the turbine blade;

receiving the plug in the hole; and

bonding the plug to the turbine blade.

23. The method as set forth in claim 22, in which the step of providing a superalloy plug includes the step of providing a superalloy plug having a tapered peripheral configuration with respect to a longitudinal axis of the plug.

24. The method as set forth in claim 23, in which the step of providing a superalloy plug having a tapered peripheral configuration includes the step of providing a superalloy plug having a non-circular cross-section section with respect to a plane oriented perpendicular to the longitudinal axis of the plug.

25. The method as set forth in claim 22, in which the step of bonding includes the steps of applying a bonding catalyst to at least one of the plug and the turbine blade and heating the bonding catalyst.

26. The method as set forth in claim 22, in which the step of bonding the plug includes the step of forming one of a braze joint, a diffusion braze joint, a liquid phase diffusion sintering joint, a transient liquid phase joint, and a diffusion bond joint between the plug and the turbine blade.