Method for producing a turbine engine part

Patent metadata

Field	Value
Publication number	US-2017320174-A1
Application number	US-201515526485-A
Country	US
Kind code	A1
Filing date	Nov 16, 2015
Priority date	Nov 14, 2014
Publication date	Nov 9, 2017
Grant date	—

Abstract

The production method comprises the steps for producing a preform by selective melting, the preform comprising an assembly surface to be brazed to the part to be repaired and containing a brazing material, and then assembling the preform to the turbine engine part by diffusion brazing. The thermal amplitude of the main transformation peak (A 1 ) of the brazing material used to make the preform must at least be twice that of each of the respective thermal amplitudes of the secondary transformation peaks (A 2 , A 3 ) of this brazing material.

First claim

1 . A method for repairing a turbine engine part, characterized in that it comprises the steps of:
producing a preform, layer by layer, by selectively melting a powder containing a base material identical or similar to that of the part, the preform having an assembly surface intended to be brazed to the part to be repaired and containing for this purpose a brazing material mixed with the base material, the brazing material being an alloy based on nickel, cobalt: 18 to 22%, silicon: 4 to 5%, boron: 2.7 to 3.15%, and carbon: 0 to 0.06%, all in percent by weight, said powder containing the mixture, upon heating to fusion generating heat fluxes, having a main transformation peak of the brazing material, with the greatest amplitude of heat flux, and secondary transformation peaks of the brazing material, with a lesser amplitude of heat flux; assembling the preform to the turbine engine part by diffusion brazing, wherein the amplitude of the heat flux of said main transformation peak of the brazing material used to make the preform is at least twice the amplitudes of the respective heat fluxes of the secondary transformation peaks of the brazing material, the brazing material further comprising chromium so as to limit the cracking of the parts when they are cooled.

2 . The method of claim 1 , wherein the quantity of chromium added ranges from 9% to 19% in percent by weight.

3 . The method of claim 1 , wherein the quantity of chromium added is equal to 14% in percent by weight.

4 . The repair method of claim 1 , wherein the chemical composition of the base material corresponds to a Ni, Co, Ti, or Fe-based superalloy and the chemical composition of the brazing material corresponds to a Ni and/or Co and/or Fe-based alloy, in which the melting element is Si and/or B.

5 . The repair method of claim 1 , wherein the preform is produced by selectively melting a base material powder and a brazing powder, the melting temperature of which is less than the melting temperature of the base material powder.

6 . The method of claim 1 , wherein the melting temperature of the brazing material is at most equal to 1,210° C.

7 . The method of claim 1 , wherein the base material is Astroloy (also known as NK17CDAT) having a chemical composition of nickel base with 16.9% cobalt, 14.8% chromium, 3.87% aluminium, 3.45% titanium, 5.1% molybdenum, and 0.015% carbon, all in percent by weight.

8 . A turbine engine part produced by executing the method of claim 1 .

Assignees

• Safran Aircraft Engines

Inventors

• Mottin Jean-Baptiste

Classifications

• B23P6/00

  Restoring or reconditioning objects (straightening or restoring form of sheet metal, metal rods, metal tubes, metal profiles, or specific articles made therefrom B21D1/00, B21D3/00; repairing defective or damaged objects by casting techniques B22D19/10) · CPC title

• B22F10/28

  Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM] · CPC title

• B23P6/007 Primary

  using only additive methods, e.g. build-up welding · CPC title

• B22F5/04 Primary

  of turbine blades · CPC title

• B22F10/34

  of powder characteristics, e.g. density, oxidation or flowability · CPC title