Protection against oxidation or corrosion of a hollow part made of a superalloy

Patent metadata

Field	Value
Publication number	US-12454891-B2
Application number	US-202118040767-A
Country	US
Kind code	B2
Filing date	Aug 5, 2021
Priority date	Aug 6, 2020
Publication date	Oct 28, 2025
Grant date	Oct 28, 2025

Abstract

A protection method, protects at least one hollow internal area of a turbine engine part made of a superalloy from oxidation and/or corrosion, wherein the at least one hollow inner area has been formed by means of at least one core made of a ceramic material limited by an external surface that surrounds it. Before bringing the superalloy around the core made of a ceramic material, the external surface is coated with a material that includes a nanometric layer of hafnium (Hf), and/or a micrometric layer of platinum (Pt), ormixture at least of hafnium and platinum.

First claim

The invention claimed is:

1 . A protection method, for protecting at least one hollow inner area of a turbine engine part made of a superalloy from oxidation and/or corrosion, said at least one hollow inner area having been formed by means of at least one core:
made of a material comprising a ceramic and/or metal or a metal and ceramic hybrid material, and limited by an external surface which surrounds the at least one core, the method comprising the steps of: before bringing the superalloy around the at least one core, coating said external surface with a coating material comprising hafnium (Hf), and/or platinum (Pt), and/or chromium (Cr) and/or silicon (Si) and/or Yttrium (Y), or a mixture thereof; before bringing the superalloy around the at least one core, diffusing said coating material in the at least one core between 800° C. and 1,250° C., under a pressure lower than 1 Pa; and after coating said external surface of the at least one core with the coating material, bringing the superalloy in a molten state in contact with said coated external surface.

2 . The protection method according to claim 1 , wherein the coating material with which said external surface is coated comprises:
a nanometric layer containing hafnium (Hf), or wherein hafnium is present between 0.3 and 15 w %, on an entire surface of the hollow inner area, in the superalloy.

3 . The protection method according to claim 2 , wherein:
the nanometric layer of or containing hafnium has a thickness between 50 nm and 800 nm, or hafnium is present between 0.3 and 5w % at the surface of the hollow inner area, in the superalloy.

4 . The protection method according to claim 1 , wherein bringing the superalloy around the at least one core comprises dissolving the superalloy, wherein the diffusing of the coating material in the at least one core is initiated when dissolving the superalloy.

5 . The protection method according to claim 1 , wherein the superalloy is nickel-based.

6 . The protection method according to claim 1 , wherein the coating material with which said external surface is coated comprises:
a micrometric layer containing platinum (Pt), or wherein platinum is present between 10 and 80 w %, on an entire surface of the hollow inner area, in the superalloy.

7 . The protection method according to claim 1 , wherein the coating material with which said external surface is coated comprises:
a mixture of at least hafnium (Hf) and platinum (Pt), across a micrometric thickness.

8 . The protection method according to claim 1 , wherein the coating material with which said external surface is coated comprises: at least one layer containing Cr and/or Si and/or Y across a nanometric thickness, or chromium is present between 2 and 30 w % at an entire surface of the superalloy of the hollow inner area of the turbine engine part, or silicon is present between 0.2 and 10 w % at the entire surface of the superalloy of the hollow inner area of the turbine engine part, or Yttrium is present between 0.3 and 15 w % at the entire surface of the superalloy of the hollow inner area of the turbine engine part.

9 . The protection method according to claim 6 , wherein:
the micrometric layer containing platinum has a thickness between 1 μm and 5 μm at the external surface of the at least one core, or platinum is present between 15 and 60 w % at an entire surface of the hollow inner area, in the superalloy, said at least one layer containing Cr and/or Si and/or Y and having a thickness comprised between 30 nm and 10 μm, or chromium is present between 4 and 10 w % at the surface of the superalloy of the hollow inner area of the turbine engine, or silicon is present between 0.2 and 2 w % at the surface of the superalloy of the hollow inner area of the turbine engine part.

Assignees

• Safran

Inventors

• Rame Jérémy
• Saboundji Amar
• Bechelany Mirna

Classifications

• B22D27/18

  Measures for using chemical processes for influencing the surface composition of castings, e.g. for increasing resistance to acid attack · CPC title

• B22C3/00

  Selection of compositions for coating the surfaces of moulds, cores, or patterns · CPC title

• F05D2300/222

  Silicon · CPC title

• F05D2300/175

  Superalloys · CPC title

• F05D2300/15

  Rare earth metals, i.e. Sc, Y, lanthanides · CPC title