Component with a Filled Recess

• US 20080000063A1
• Filed: 09/21/2005
• Published: 01/03/2008
• Est. Priority Date: 11/22/2004
• Status: Abandoned Application

• Current Assignee: Siemens AG
• Original Assignee: Siemens AG
• Inventors: Pan, Ying, Dankert, Michael, Ahmad, Fathi, Teteruk, Rostislav
• Application Number:
  US11/791,101
• Publication Number:
  US 20080000063A1
• Time in Patent Office: Days
• US Class Current: 29/402.18
• CPC Class Codes: B23P 6/005 using only replacement pieces of a particular form
• CPC Class Codes: B23P 6/007 using only additive methods, e.g. build-up welding
• CPC Class Codes: B23P 6/045 of turbine components, e.g. moving or stationary blades, rotors, etc.
• CPC Class Codes: F01D 5/005 Repairing methods or devices
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft
• CPC Class Codes: Y10T 29/49746 by applying fluent material, e.g., coating, casting

Abstract

According to a prior art, components having a crack are repaired, wherein the thus produced elongated recess is filled with a solder material which nevertheless produces a weak point. The inventive component, in addition to the material filled recess, comprises an additional material filled recess which extends transversely to the longitudinal direction of the cavity.

Claims

1-16. -16. (canceled)

17. A process for repairing a component formed from a first material having a crack oriented in a direction of extent and of elongate shape, comprising:

machining a first recess along the extent of the crack;

machining a second recess at an angle with respect to the direction of extent; and

filling the first and second recesses with a second material.

18. The process as claimed in claim 17, wherein the second material is a solder material or a welding filler material.

19. The process as claimed in claim 17, wherein the first and second recesses form an L-shape.

20. The process as claimed in claim 17, wherein the first and second recesses form a T-shape.

21. The process as claimed in claim 20, wherein the T shape has a first T region and a second T region transverse to the direction of extent and having a first respective length greater than a second respective length if a first operative stress active in the first region during operation is greater than a second operative stress active in the second region during operation.

22. The process as claimed in claim 17, wherein the first and second recesses form an H-shape.

23. The process as claimed in claim 22, wherein the H shape, in a direction transverse with respect to the direction of extent, has:

a first H region having a first length and a first operative stress present during operation, and

a second H region having a second length in the transverse direction and a second operative stress present during operation, where the first length is greater than the second length if the first stress is greater than the second stress.

24. The process as claimed in claim 17, wherein the second recess is oriented at an angle of at least 45°

with respect to the direction of extent.

25. The process as claimed in claim 24, wherein the angle is at least 60°

.

26. The process as claimed in claim 24, wherein the angle is at least 75°

.

27. The process as claimed in claim 24, wherein the angle is at least or equal to 90°

.

28. The process as claimed claim 17, wherein the recess is formed at a location where a crack was present.

29. The process as claimed in claim 17, wherein the first and second materials are the same.

30. The process as claimed in claim 29, wherein the first material is a nickel, cobalt or iron based superalloy.

31. The process as claimed in claim 17, wherein the first material has a different microstructure than the second material.

32. The process as claimed in claim 17, wherein the first material is different than the second material.

33. The process as claimed in claim 17, wherein the component is a blade, vane or heat shield element of a gas turbine.