Method for manufacturing a part coated with a protective coating

Patent metadata

Field	Value
Publication number	US-10619494-B2
Application number	US-201815985017-A
Country	US
Kind code	B2
Filing date	May 21, 2018
Priority date	Dec 3, 2014
Publication date	Apr 14, 2020
Grant date	Apr 14, 2020

Abstract

A part include a refractory alloy including a niobium matrix having metal silicide inclusions present therein, the surface of the part being coated by a protective coating, the protective coating including a phase having the following stoichiometry: (NbxTi1-x)3MβCrγSiδXε where M designates Fe, Co, or Ni, X designates one or more other elements that might be present, x lies in the range 0 to 1, x lies in the range 5 to 8.5, and the sum β+γ lies in the range 3 to 7; or Nb4M′ηSiθX′ε′ where M′ designates Fe, Co, or Ni, X′ designates one or more other elements that might be present, η lies in the range 3.2 to 4.8, and θ lies in the range 6 to 8.

First claim

The invention claimed is:

1. A part comprising a refractory alloy comprising a niobium matrix having metal silicide inclusions present therein, the surface of the part being coated by a protective coating, the protective coating comprising a phase having the following stoichiometry:
Nb 4 M′ η Si θ X′ ε ′ where M′ designates Ni, X′ designates one or more other elements that might be present, η lies in the range 3.2 to 4.8, and θ lies in the range 6 to 8, and when X′ is present, X′ is Al and/or Hf.

2. A turbine engine including a part according to claim 1 .

3. An aircraft including a turbine engine according to claim 2 .

4. The part according to claim 1 , wherein a thickness of the protective coating formed lies in the range from 15 μm to 50 μm.

5. The part according to claim 1 , wherein silicon is present in the phase at an atomic content lying in the range 45% to 49%.

6. The part according to claim 1 , wherein the part is a turbine engine blade.

7. The part according to claim 1 , wherein the part forms an integral portion of a combustion chamber or a turbine ring or nozzle.

8. The part according to claim 1 , wherein ε′ is less than or equal to 1.

9. The part according to claim 8 , wherein ε′ is less than equal to 0.5.

10. The part according to claim 8 , wherein ε′ is less than equal to 0.3.

Assignees

• Safran Aircraft Engines
• Univ De Lorraine

Inventors

• Knittel Stéphane
• Mathieu Stéphane
• Vilasi Michel

Classifications

• C23C16/32

  Carbides · CPC title

• C23C10/54

  Diffusion of at least chromium · CPC title

• F01D5/28

  Selecting particular materials; {Particular measures relating thereto;} Measures against erosion or corrosion · CPC title

• F01D5/288 Primary

  Protective coatings for blades · CPC title

• F05D2300/13

  Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W · CPC title