METHOD FOR EXTENDING AN ORIGINAL SERVICE LIFE OF GAS TURBINE COMPONENTS

• US 20140053403A1
• Filed: 08/22/2012
• Published: 02/27/2014
• Est. Priority Date: 08/22/2012
• Status: Abandoned Application

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Pawlowski, Joseph Vincent, Venkatappa, Srinivas, Sinha, Sudip Kumar
• Application Number:
  US13/591,726
• Publication Number:
  US 20140053403A1
• Time in Patent Office: Days
• US Class Current: 29/888.021
• CPC Class Codes: B23P 6/002 Repairing turbine components, e.g. moving or stationary blades, rotors, B23P6/045 takes precedence
• CPC Class Codes: F01D 21/003 Arrangements for testing or measuring for measuring vibrations G01H
• CPC Class Codes: F01D 5/005 Repairing methods or devices
• CPC Class Codes: Y10T 29/49238 Repairing, converting, servicing or salvaging

Abstract

A method for extending a service life of a gas turbine component includes identifying the service life for the component and comparing a characteristic of the component to a predetermined departure parameter. The method further includes refurbishing the component to a predetermined specification if the characteristic of the component satisfies the predetermined departure parameter and establishing an extended service life for the component.

Claims

1. A method for extending a service life of a gas turbine component, comprising:

a. identifying the service life for the component;

b. comparing a characteristic of the component to a predetermined departure parameter;

c. refurbishing the component to a predetermined specification if the characteristic of the component satisfies the predetermined departure parameter; and

d. establishing an extended service life for the component.

2. The method as in claim 1, wherein the service life for the component comprises at least one of operating hours, startup events, shut down events, or refurbishment events.

3. The method as in claim 1, wherein the predetermined departure parameter includes at least one of a location of the component, a repair history of the component, a dimension of the component, an operating history of the gas turbine, or a repair history of the gas turbine.

4. The method as in claim 1, wherein the refurbishing comprises at least one of removing deposits from the component, applying a coating to the component, annealing the component, or machining a dimension of the component.

5. The method as in claim 1, further comprising establishing a revised service life for the component based on the extended service life for a plurality of components.

6. The method as in claim 1, further comprising inspecting the component after the component exceeds the service life.

7. The method as in claim 6, further comprising establishing a revised service life for the component based on the inspection of the component after the component exceeds the service life.

8. The method as in claim 1, further comprising comparing a plurality of characteristics of the component to a plurality of predetermined departure parameters.

9. The method as in claim 8, further comprising refurbishing the component to the predetermined specification if all of the plurality of characteristics of the component satisfy the plurality of predetermined departure parameters.

10. A method for extending a service life of a gas turbine component, comprising:

a. identifying the service life for the component;

b. comparing a plurality of characteristics of the component to a plurality of predetermined departure parameters;

c. refurbishing the component to a predetermined specification if no more than one of the plurality of characteristics of the component fails to satisfy the plurality of predetermined departure parameters; and

d. establishing an extended service life for the component.

11. The method as in claim 10, wherein the service life for the component comprises at least one of operating hours, startup events, shut down events, or refurbishment events.

12. The method as in claim 10, wherein the plurality of predetermined departure parameters include at least two of a location of the component, a repair history of the component, a dimension of the component, an operating history of the gas turbine, or a repair history of the gas turbine.

13. The method as in claim 10, wherein the refurbishing comprises at least one of removing deposits from the component, applying a coating to the component, annealing the component, or machining a dimension of the component.

14. The method as in claim 10, further comprising establishing a revised service life for the component based on the extended service life for a plurality of components.

15. The method as in claim 10, further comprising inspecting the component after the component exceeds the service life.

16. The method as in claim 15, further comprising establishing a revised service life for the component based on the inspection of the component after the component exceeds the service life.

17. The method as in claim 10, further comprising refurbishing the component to the predetermined specification if all of the plurality of characteristics of the component satisfy the plurality of predetermined departure parameters.