Peening coated internal surfaces of turbomachine components

Patent metadata

Field	Value
Publication number	US-10882158-B2
Application number	US-201916260768-A
Country	US
Kind code	B2
Filing date	Jan 29, 2019
Priority date	Jan 29, 2019
Publication date	Jan 5, 2021
Grant date	Jan 5, 2021

Abstract

A method of treating a substrate of a turbomachine component includes applying a coating to a surface of the substrate of the turbomachine component and peening the substrate after applying the coating to the surface by directing a peening force onto the coating whereby the peening force on the coating is transferred through the coating to the substrate. A method of treating an internal surface of a turbomachine component includes directing a peening force at the internal surface within a cooling passage of the turbomachine component.

First claim

What is claimed is:

1. A method of treating a substrate of a rotor blade for a turbomachine, the method comprising:
applying a coating to a surface of the substrate of the rotor blade, wherein the rotor blade is hollow and the surface is an internal surface of a cooling passage of the rotor blade;
applying a mask within the cooling passage at a location generally radially aligned with a platform of the rotor blade; and
peening the internal surface of the rotor blade after applying the coating to the internal surface by directing a peening force onto the coating whereby the peening force on the coating is transferred through the coating to the substrate and whereby the substrate exhibits residual compressive stress from the peening force transferred through the coating to the substrate, wherein the peening force is an impact force of a peening media, whereby the peening media is obstructed by the mask from entering a portion of the cooling passage within an airfoil portion of the rotor blade during peening, wherein peening the substrate comprises shot peening the substrate using a lance to direct the peening media onto the coating.

2. The method of claim 1 , wherein the rotor blade comprises a shank portion that extends radially inward from the platform, wherein an airfoil portion extends radially outward from the platform, and wherein the cooling passage extends within the shank portion, the airfoil portion, and the platform.

3. The method of claim 2 , further comprising removing the mask after peening.

4. The method of claim 1 , wherein applying the coating comprises heating the substrate.

5. The method of claim 1 , wherein applying the coating comprises applying an aluminide material to the substrate to form a diffusion aluminide coating.

6. The method of claim 1 , wherein applying the coating comprises applying the coating by chemical vapor deposition.

7. The method as in claim 1 , wherein an array of indents are formed in the substrate as a result of peening on the coating, and wherein no indents are formed on the coating as a result of peening on the coating.

8. The method as in claim 1 , wherein the applying the mask step is after the applying the coating step and prior to the peening step.

9. The method as in claim 1 , wherein the substrate comprises a superalloy material.

10. The method as in claim 1 , wherein applying the coating comprises heating the substrate to between about 800° C. to about 1,200° C.

11. The method as in claim 1 , wherein both the coating and the substrate do not exhibit readily observable effects of peening after the peening step.

12. The method of claim 1 , wherein the peening step results in a crystal lattice of the substrate exhibiting a grain misorientation, and wherein the grain misorientation is not observable to a naked eye.

13. The method as in claim 12 , further comprising identifying, by microscopic examination of the rotor blade using electron backscatter diffraction, the grain misorientation in an impact zone of the substrate.

14. A method of treating a rotor blade for a turbomachine, the method comprising:
applying a mask within a cooling passage defined within the rotor blade at a location generally radially aligned with a platform of the rotor blade;
directing a peening force at a coating on an internal surface of the cooling passage; and
whereby the peening force is transferred through the coating to the internal surface and whereby the internal surface exhibits residual compressive stress from the peening force transferred through the coating, wherein the peening force is an impact force of a peening media on the coating, and wherein the peening media comprises shot and directing the peening force at the coating on the internal surface comprises directing the peening media at the internal surface using a lance, whereby the peening media is obstructed by the mask from contacting a portion of the cooling passage within the airfoil portion of the rotor blade while directing the peening media at the coating on the internal surface.

15. The method of claim 14 , wherein the rotor blade comprises a substrate and the internal surface is a surface of the substrate.

16. The method of claim 15 , wherein applying the coating comprises applying an aluminide material to the substrate to form a diffusion aluminide coating.

17. The method of claim 15 , wherein applying the coating comprises applying the coating by chemical vapor deposition.

18. The method of claim 14 , wherein the rotor blade comprises a shank portion extending radially inward from the platform, wherein the airfoil portion extends radially outward from the platform, the cooling passage extending within the shank portion, the airfoil portion, and the platform, wherein the peening force is an impact force of a peening media directed at the coating on the internal surface.

19. The method of claim 18 , wherein the mask is one of a room temperature vulcanizing silicone or a wax, wherein the mask is injected into the rotor blade during the applying step, and wherein the method further comprises removing the mask after directing the peening media at the coating on the internal surface.

20. The method as in claim 14 , wherein the peening step is performed by one of water cavitation peening, laser peening, or explosion forming.

Assignees

• Gen Electric

Inventors

• Peck Arthur S
• Dellafera Gabriel
• Dimascio Paul Stephen
• Schaeffer Jon Conrad

Classifications

• F01D5/288

  Protective coatings for blades · CPC title

• F01D5/187

  Convection cooling · CPC title

• F01D5/005

  Repairing methods or devices · CPC title

• C23C10/50

  of ferrous surfaces · CPC title

• C23C10/02

  Pretreatment of the material to be coated (C23C10/04 takes precedence) · CPC title