TURBINE COMPONENT PATCH DELIVERY SYSTEMS AND METHODS

• US 20150174838A1
• Filed: 12/12/2014
• Published: 06/25/2015
• Est. Priority Date: 12/19/2013
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (GE Vernova, Inc.)
• Original Assignee: General Electric Company
• Inventors: Kittleson, Jacob John, Lipkin, Don Mark
• Granted Patent: US 10,022,921 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B23P 6/002 Repairing turbine components, e.g. moving or stationary blades, rotors, B23P6/045 takes precedence
• CPC Class Codes: B23P 6/04 Repairing fractures or cracked metal parts or products, e.g. castings
• CPC Class Codes: B23P 6/045 of turbine components, e.g. moving or stationary blades, rotors, etc.
• CPC Class Codes: B29C 73/025 fed under pressure
• CPC Class Codes: B29K 2103/04 Inorganic materials
• CPC Class Codes: B29L 2031/08 Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
• CPC Class Codes: F01D 5/005 Repairing methods or devices
• CPC Class Codes: F05D 2300/15 Rare earth metals, i.e. Sc, Y, lanthanides
• CPC Class Codes: Y10T 29/49318 Repairing or disassembling

Abstract

A turbine component patch delivery system can include a compressed gas source fluidly connected to a delivery line comprising a dispensing end. The turbine component patch delivery system can further include one or more turbine component patch carriers that can be projected out of the dispensing end of the delivery line by the compressed gas source, wherein each of the one or more turbine component patch carriers comprise a turbine component patch material housed within a breakaway shell.

Claims

1. A turbine component patch delivery system comprising:

a compressed gas source fluidly connected to a delivery line comprising a dispensing end; and

,

one or more turbine component patch carriers that can be projected out of the dispensing end of the delivery line by the compressed gas source, wherein each of the one or more turbine component patch carriers comprise a turbine component patch material housed within a breakaway shell.

2. The turbine component patch delivery system of claim 1, further comprising a support arm configured to support the delivery line.

3. The turbine component patch delivery system of claim 1, wherein each of the one or more turbine component patch carriers houses from about 1 mm³ to about 200 mm³ of turbine component patch material.

4. The turbine component patch delivery system of claim 1, further comprising an auxiliary patch application tool.

5. The turbine component patch delivery system of claim 4, wherein the auxiliary patch application tool comprises an optical system configured to provide an optical field of vision configured to include at least a portion of a projected path of the one or more turbine component patch carriers.

6. The turbine component patch delivery system of claim 4, wherein the auxiliary patch application tool further comprises an in-line laser configured to project a laser in the direction of the projected path of the one or more turbine component patch carriers.

7. The turbine component patch delivery system of claim 4, wherein the auxiliary patch application tool comprises a curing apparatus configured to cure the turbine component patch material disposed on the surface of the turbine component.

8. The turbine component patch delivery system of claim 1, wherein the turbine component patch material comprises:

one or more rare earth silicates;

wherein an inorganic composition of the environmentally resistant patch comprises, once cured, from about 80 mole percent to about 100 mole percent of a rare earth monosilicate and/or rare earth disilicate and from about 0 mole percent to about 20 mole percent of an inorganic additive; and

,

wherein the environmentally resistant patch has, once cured, an adhesive strength of at least about 3 MPa and a coefficient of thermal expansion of from about 3.5×

10<sup>−

6</sup>/°

C. to about 7.5×

10<sup>−

6</sup>/°

C.

9. The turbine component patch delivery system of claim 1, wherein the breakaway shell comprises at least one of a wax, gel, gelatin, denatured collagen, plasticizer or thermoplastic polymer.

10. The turbine component patch delivery system of claim 1, wherein the compressed gas source comprises compressed CO₂.

11. A turbine component patch delivery method comprising:

providing a compressed gas source fluidly connected to a delivery line comprising a dispensing end;

positioning a turbine component patch carrier in the delivery line, wherein the turbine component patch carrier comprises a turbine component patch material housed within a breakaway shell;

projecting the turbine component patch carrier through the delivery line and out the dispensing end towards a surface of a turbine component using the compressed gas source, wherein the breakaway shell breaks open to at least partially coat the surface of the turbine component with the turbine component patch material.

12. The turbine component patch delivery method of claim 11, wherein a support arm is configured to support the delivery line.

13. The turbine component patch delivery method of claim 11, wherein the turbine component patch carrier houses from about 1 mm³ to about 200 mm³ of turbine component patch material.

14. The turbine component patch delivery method of claim 11, further comprising using an auxiliary patch application tool connected to the delivery line.

15. The turbine component patch delivery method of claim 14, wherein the auxiliary patch application tool comprises an optical system configured to provide an optical field of vision configured to include at least a portion of a projected path of the turbine component patch carrier.

16. The turbine component patch delivery method of claim 14, wherein the auxiliary patch application tool further comprises an in-line laser configured to project a laser in the direction of the projected path of the turbine component patch carrier.

17. The turbine component patch delivery method of claim 14, wherein the auxiliary patch application tool comprises a curing apparatus configured to cure the turbine component patch material disposed on the surface of the turbine component

18. The turbine component patch delivery method of claim 11, wherein the turbine component patch material comprises:

one or more rare earth silicates;

wherein an inorganic composition of the environmentally resistant patch comprises, once cured, from about 80 mole percent to about 100 mole percent of a rare earth monosilicate and/or rare earth disilicate and from about 0 mole percent to about 20 mole percent of an inorganic additive; and

,

wherein the environmentally resistant patch has, once cured, an adhesive strength of at least about 3 MPa and a coefficient of thermal expansion of from about 3.5×

10<sup>−

6</sup>/°

C. to about 7.5×

10<sup>−

6</sup>/°

C.

19. The turbine component patch delivery method of claim 11, wherein the breakaway shell comprises at least one of a wax, gel, gelatin, denatured collagen, plasticizer or thermoplastic polymer.

20. The turbine component patch delivery method of claim 11, wherein the compressed gas source comprises at least one of CO₂, He, Ar, N₂ or air.