Structural braze repair of superalloy component

Patent metadata

Field	Value
Publication number	US-10076811-B2
Application number	US-201514826366-A
Country	US
Kind code	B2
Filing date	Aug 14, 2015
Priority date	Nov 3, 2011
Publication date	Sep 18, 2018
Grant date	Sep 18, 2018

Abstract

Boron and silicon free braze alloys useful for structural repairs of superalloy gas turbine engine components. The braze alloy composition may contain only elements that are contained in the superalloy material to be repaired, and may have melting temperature ranges as low as 10° C. to facilitate producing a high strength homogenized braze joint during a solution heat treatment of the superalloy substrate material.

First claim

The invention claimed is:

1. A method comprising:
applying a boron and silicon free braze alloy to a superalloy substrate, the braze alloy consisting only of elemental constituents that are present in the superalloy substrate, the braze alloy composition containing an effective quantity of titanium as a melting point depressant so that the braze alloy composition has a melting temperature range of no more than 50° C. and inclusive of or below a solution heat treating temperature of the superalloy substrate; and
performing a solution heat treatment of the superalloy substrate effective to melt the braze alloy and to fuse and homogenize a braze joint,
applying the braze alloy composition consisting of:
Cr 12-16 wt. %;
Ti 13-16 wt. %;
Al 0-2.5 wt. %;
Co 2-4 wt. %;
W 3-5 wt. %;
Mo 0-2 wt. %;
Ta 0-2 wt. %;
balance Ni,
wherein the braze alloy composition is free of hafnium.

2. The method of claim 1 , further comprising applying the braze alloy as a powder into a discontinuity on a surface of the superalloy substrate so that the braze joint fills the discontinuity.

3. The method of claim 2 , further comprising applying a superalloy powder material into the discontinuity with the braze alloy.

4. The method of claim 3 , further comprising selecting a mesh size range of the braze alloy powder to be smaller than a mesh size range of the superally powder material.

5. A method comprising:
applying a boron and silicon free braze alloy to a superalloy substrate, the
braze alloy consisting only of elemental constituents that are present in the superalloy substrate, the braze alloy composition containing an effective quantity of titanium as a melting point depressant so that the braze alloy composition has a melting temperature range of no more than 50° C. and inclusive of or below a solution heat treating temperature of the superalloy substrate; and
performing a solution heat treatment of the superalloy substrate effective to melt the braze alloy and to fuse and homogenize a braze joint,
applying the braze alloy composition consisting of:
Cr 15-18 wt. %;
Ti 10-15 wt. %;
Al 0-2.5 wt. %;
Co 2-4 wt. %;
W 3-5 wt. %;
Mo 0-2 wt. %;
Ta 0-2 wt. %;
balance Ni.

6. The method of claim 5 , further comprising selecting the braze alloy composition to have a melting temperature range of 15° C., and selecting the superalloy substrate to be Alloy 247 or Rene 80.

7. A method comprising:
applying a boron and silicon free braze alloy to a superalloy substrate, the braze alloy consisting only of elemental constituents that are present in the superalloy substrate, the braze alloy composition containing an effective quantity of titanium as a melting point depressant so that the braze alloy composition has a melting temperature range of no more than 50° C. and inclusive of or below a solution heat treating temperature of the superalloy substrate; and
performing a solution heat treatment of the superalloy substrate effective to melt the braze alloy and to fuse and homogenize a braze joint
applying the braze alloy composition consisting of:

Cr 15-19 wt. %;
Ti 8-10 wt. %;
Al 0-2.5 wt. %;
Co 14-18 wt. %;
Mo 12-16 wt. %;
balance Ni.

8. A method comprising:
removing a superalloy gas turbine component from service;
applying a boron and silicon free braze alloy to a discontinuity on a surface of the component, the braze alloy consisting only of elemental constituents that are present in the component, the braze alloy containing an effective quantity of titanium as a melting point depressant so that the braze alloy composition has a melting temperature range of no more than 20° C.; and
heat treating the component with a temperature regiment effective to melt the braze alloy and to fuse and to homogenize a braze joint to repair the discontinuity,
applying the braze alloy composition consisting of:
Cr 15-18 wt. %;
Ti 10-16 wt. %;
Al 0-2.5 wt. %;
Co 2-4 wt. %;
W 3-5 wt. %;
Mo 0-2 wt. %;
Ta 0-2 wt. %;
balance Ni,
wherein the braze alloy composition is free of hafnium.

9. The method of claim 8 , further comprising selecting the braze alloy to have a melting temperature range of no more than 15° C.

10. The method of claim 8 , wherein the component comprises Rene 80 or Alloy 247 superalloy material, and further comprising selecting the braze alloy to have a liquidus temperature of no more than 1,215° C. and having a melting temperature range of no more than 20° C.

11. The method of claim 8 , further comprising cleaning a surface of the component proximate the discontinuity prior to the step of applying the braze alloy.

Assignees

• Siemens Energy Inc

Inventors

• Ozbaysal Kazim

Classifications

• F01D5/005

  Repairing methods or devices · CPC title

• B23K35/304

  with Cr as the next major constituent · CPC title

• C22F1/10 Primary

  of nickel or cobalt or alloys based thereon · CPC title

• C22C19/058

  without Mo and W · CPC title

• F05D2300/175

  Superalloys · CPC title