Method for repairing a component for use in a turbine engine

Patent metadata

Field	Value
Publication number	US-9700941-B2
Application number	US-201213633999-A
Country	US
Kind code	B2
Filing date	Oct 3, 2012
Priority date	Oct 3, 2012
Publication date	Jul 11, 2017
Grant date	Jul 11, 2017

Abstract

A removed damaged portion of a fully consolidated turbine engine component is replaced with a powder coupon that includes powder particles that are at most partially sintered or are bonded together with a binder. A bonding agent is applied to the component and/or the powder coupon. The powder coupon is then positioned over the component and heat is applied to fully sinter the powder particles, thus causing the powder coupon to shrink onto the component. The heat also activates the bonding agent to bond the shrunken powder coupon to the component, but the heat does not sinter the material forming the fully consolidated component.

First claim

What is claimed is:

1. A method for replacing a removed damaged portion of a fully consolidated component for use in a turbine engine comprising:
providing a powder coupon comprising powder particles that are at most partially sintered or are bonded together with a binder;
applying a bonding agent to at least one of an outer mating surface of the component and an inner mating surface of the powder coupon;
positioning the powder coupon over the component such that the inner mating surface of the powder coupon is located adjacent to the outer mating surface of the component with the bonding agent therebetween so as to form a replacement assembly comprising the component, the powder coupon, and the bonding agent; and
applying heat to the replacement assembly, wherein the applied heat:
fully sinters the powder particles of the powder coupon so as to bind the powder particles together, thus causing the powder coupon to shrink onto the component; and
activates the bonding agent to bond the inner mating surface of the shrunken powder coupon to the outer mating surface of the component;

wherein applying heat to the replacement assembly does not sinter materials forming the fully consolidated component and the shrinking of the powder coupon by the sintering of the powder particles effects a width of the shrunken powder coupon being generally equal to a width of the component.

2. The method according to claim 1 , further comprising machining an outer surface of the component adjacent to the location of the removed damaged portion using a material removal procedure to form the outer mating surface.

3. The method according to claim 2 , wherein the outer mating surface of the component comprises a stepped surface with an adjacent portion of the outer surface of the component.

4. The method according to claim 3 , wherein the powder coupon comprises a rim that defines the inner mating surface and that is received by the stepped surface of the component when the shrunken powder coupon is bonded to the component.

5. The method according to claim 1 , wherein the inner and outer mating surfaces include features that effect a mechanical interlocking between the shrunken powder coupon and the component.

6. The method according to claim 1 , wherein the bonding agent comprises a melting point suppressant substance that lowers the melting point of the bonding agent.

7. The method according to claim 6 , wherein the melting point suppressant substance comprises at least one of boron, silicon, and germanium.

8. The method according to claim 1 , further comprising, before applying heat to the replacement assembly, cold working or peening at least one of the outer mating surface of the component and the inner mating surface of the powder coupon to create a storage of energy in the at least one of the component and the powder coupon, wherein the storage of energy effects a strengthening of the bond between the powder coupon and the component.

9. The method according to claim 1 , wherein the component comprises a turbine blade and the removed damaged portion of the component comprises a damaged blade tip.

10. The method according to claim 1 , wherein the applied heat also creates a rejuvenation treatment for the fully consolidated component by substantially restoring the original microstructure of the component.

11. A method for repairing a fully consolidated component for use in a turbine engine comprising:
removing a damaged portion of the component;
machining an outer surface of the component adjacent to the location of the removed damaged portion using a material removal procedure to form an outer mating surface comprising a stepped surface with an adjacent portion of the outer surface of the component;
providing a powder coupon comprising powder particles that are at most partially sintered or are bonded together with a binder;
applying a bonding agent to at least one of the outer mating surface of the component and an inner mating surface of the powder coupon;
positioning the powder coupon over the component such that the inner mating surface of the powder coupon is located adjacent to the outer mating surface of the component with the bonding agent therebetween so as to form a replacement assembly comprising the component, the powder coupon, and the bonding agent; and
applying heat to the replacement assembly, wherein the applied heat:
fully sinters the powder particles of the powder coupon so as to bind the powder particles together, thus causing the powder coupon to shrink such that the inner mating surface of the powder coupon is shrunken onto the outer mating surface of the component with the bonding agent therebetween; and
activates the bonding agent to bond the inner mating surface of the shrunken powder coupon to the outer mating surface of the component;

wherein the shrinking of the powder coupon onto the component exerts a pressure on the outer mating surface of the component so as to aid in the bonding process between the inner mating surface of the shrunken powder coupon and the outer mating surface of the component;
wherein applying heat to the replacement assembly does not sinter materials forming the fully consolidated component and the shrinking of the powder coupon by the sintering of the powder particles effects a width of the shrunken powder coupon being generally equal to a width of the component.

12. The method according to claim 11 , wherein the bonding agent comprises a melting point suppressant substance that lowers the melting point of the bonding agent, the melting point suppressant substance comprising at least one of boron, silicon, and germanium.

13. The method according to claim 11 , further comprising, before applying heat to the replacement assembly, cold working or peening at least one of the outer mating surface of the component and the inner mating surface of the powder coupon to create a storage of energy in the at least one of the component and the powder coupon, wherein the storage of energy effects a strengthening of the bond between the powder coupon and the component.

14. The method according to claim 11 , wherein the powder coupon comprises a rim that defines the inner mating surface and that is received by the stepped surface of the component when the shrunken powder coupon is bonded to the component.

15. The method according to claim 14 , wherein a height of the rim is at least about ⅓of an overall height of the powder coupon.

16. The method according to claim 14 , wherein a height of the rim is about 1/2 of an overall height of the powder coupon.

17. The method according to claim 11 , wherein the component comprises a turbine blade and the damaged portion of the component comprises a damaged blade tip.

18. The method according to claim 11 , further comprising forming at least one cooling feature in the powder coupon prior to applying heat to the replacement assembly.

19. The method according to claim 18 , wherein the at least one cooling feature comprises at least one of a cooling hole and a turbulating feature.

20. The method according to claim 11 , wherein the applied heat also creates a rejuvenation treatment for the fully consolidated component by substantially restoring the original microstructure of the component.

Assignees

• Siemens Energy Inc

Inventors

• James Allister W
• Abdo Zafir A M
• Kamel Ahmed

Classifications

• B23K35/02

  characterised by mechanical features, e.g. shape · CPC title

• F01D5/005

  Repairing methods or devices · CPC title

• B22F7/08

  with one or more parts not made from powder {(B22F7/062 takes precedence)} · CPC title

• F05D2240/307

  related to the tip of a rotor blade · CPC title

• B23K35/0244

  Powders, particles or spheres; Preforms made therefrom · CPC title