Weld-brazing techniques

Patent metadata

Field	Value
Publication number	US-11517969-B2
Application number	US-201916256340-A
Country	US
Kind code	B2
Filing date	Jan 24, 2019
Priority date	Jan 24, 2019
Publication date	Dec 6, 2022
Grant date	Dec 6, 2022

Abstract

A system includes a gas turbine component having a recessed portion with a recessed surface in a hard-to-weld (HTW) material. The system includes a plate disposed over the recessed portion. The plate has an easy-to-weld (ETW) material. The plate has an outer surface and an inner surface, and the inner surface faces the recessed portion. The system includes a braze material disposed within the recessed portion between the recessed surface and the inner surface of the plate. The braze material is configured to bond the recessed surface of the recessed portion with the inner surface of the plate when the braze material is heated to a brazing temperature. The system includes a filler material disposed on the outer surface of the plate disposed over the recessed portion. Application of the filler material to the outer surface of the plate is configured to heat the braze material to the brazing temperature.

First claim

The invention claimed is:

1. A system, comprising:
a gas turbine component comprising a recessed portion with a recessed surface, and an exterior surface disposed about the recessed portion;
a plate disposed over the recessed portion and at least a first portion of the exterior surface, wherein the plate comprises an outer perimeter, an outer surface and an inner surface, the plate comprises a plate material that is easier to weld than a component material of the gas turbine component, and the inner surface faces the recessed portion and the first portion of the exterior surface;
a braze material disposed within the recessed portion and extending an entire distance between the recessed surface and the inner surface of the plate, wherein the braze material bonds the recessed surface of the recessed portion with the inner surface of the plate; and
a metallic weld filler material disposed along a weld path within the outer perimeter on the outer surface of the plate disposed over the recessed portion, wherein the plate completely separates all of the metallic weld filler material on the outer surface of the plate from the gas turbine component, and the metallic weld filler material is oriented directly above the braze material disposed within the recessed portion.

2. The system of claim 1 , wherein the metallic weld filler material is welded to the outer surface of the plate above a recess area of the recessed portion, and the metallic weld filler material is welded along the weld path in a weld pattern having a plurality of weld beads oriented directly above the braze material disposed within the recessed portion.

3. The system of claim 1 , wherein the gas turbine component comprises a hot-gas-path component for a gas turbine.

4. The system of claim 1 , wherein an area of the plate is greater than a recess area of the recessed portion of the gas turbine component, wherein the area of the plate is predetermined when the plate is pre-formed separate from the gas turbine component.

5. The system of claim 1 , wherein the component material of the gas turbine component comprises a hard-to-weld material comprising at least one of an iron-based, martensitic stainless steel, a precipitated-hardening stainless steel, a chromium molybdenum steel, a high alloy steel, a tool steel, a non-ferrous alloy, a superalloy having a gamma-prime (γ′) between 0.4 and 1.0, a nickel-based superalloy, Hastelloy, Inconel, Waspaloy, GTD alloy, Rene alloy, nickel-aluminum intermetallics, and Oxide dispersion strengthened alloys.

6. The system of claim 5 , wherein the plate material of the plate comprises an easy-to-weld material comprising at least one of a steel, a stainless steel, a nickel-based superalloy different than the hard-to-weld material, a cobalt-based superalloy, a solid-solution strengthened alloy, Inconel 625, Inconel 617, Haynes 230, a precipitated strengthened alloy, GTD222, GTD262, GTD292, Rene 41, or an alloy having a gamma prime (γ′) less than 40 percent.

7. The system of claim 1 , wherein the gas turbine component comprises a machined surface extending at least partially into the metallic weld filler material on the plate.

8. The system of claim 1 , comprising a brazed joint of the braze material along the inner surface of the plate across an entire area of the recessed portion.

9. The system of claim 1 , wherein the braze material completely fills the recessed portion.

10. The system of claim 1 , wherein a second portion of the exterior surface is disposed directly about the first portion of the exterior surface directly adjacent to the plate, wherein the second portion extends flush with the first portion or the second portion extends below the first portion and the inner surface of the plate.

11. The system of claim 10 , wherein the metallic weld filler material protrudes above the outer surface of the plate and above the first and second portions of the exterior surface.

12. The system of claim 1 , wherein the plate completely separates the metallic weld filler material from the braze material, wherein the metallic weld filler material extends over only a portion of the outer surface of the plate.

13. A system, comprising:
a turbomachinery component comprising a defect and an exterior surface disposed about the defect;
a plate disposed over the defect and at least a first portion of the exterior surface, wherein the plate comprises an outer perimeter, an outer surface and an inner surface, and the inner surface faces the defect and the first portion of the exterior surface;
a braze material disposed over the defect and extending an entire distance between the defect and the inner surface of the plate, wherein the braze material bonds the defect with the inner surface of the plate; and
a metallic weld filler material disposed along a weld path within the outer perimeter on the outer surface of the plate disposed over the defect, wherein the plate completely separates all of the metallic weld filler material on the outer surface of the plate from the turbomachinery component, and the metallic weld filler material is oriented directly above the braze material disposed over the defect.

14. The system of claim 13 , wherein the defect comprises a recessed portion, and the weld path comprises a weld pattern.

15. The system of claim 13 , wherein a second portion of the exterior surface is disposed directly about the first portion of the exterior surface directly adjacent to the plate, and the second portion extends flush with the first portion or the second portion extends below the first portion.

Assignees

• Gen Electric

Inventors

• Cui Yan
• Arnett Michael
• Laylock Matthew
• Tollison Brian Lee

Classifications

• B23K35/24

  Selection of soldering or welding materials proper (B23K35/34 takes precedence) · CPC title

• F05D2230/235

  TIG or MIG welding · CPC title

• F05D2230/31

  Layer deposition · CPC title

• B23K1/20

  Preliminary treatment of work or areas to be soldered, e.g. in respect of a galvanic coating · CPC title

• B23P6/045

  of turbine components, e.g. moving or stationary blades, rotors, etc. · CPC title