Method for producing a thermal barrier on a part of a turbomachine

Patent metadata

Field	Value
Publication number	US-11479873-B2
Application number	US-201816765657-A
Country	US
Kind code	B2
Filing date	Nov 20, 2018
Priority date	Nov 21, 2017
Publication date	Oct 25, 2022
Grant date	Oct 25, 2022

Abstract

A process for manufacturing a turbomachine part coated with a thermal barrier, includes manufacturing the part by additive manufacture; electrophoretic depositing the part of a layer including particles of a ceramic material; consolidating the layer by heat treatment to obtain a ceramic coating.

First claim

The invention claimed is:

1. A process for manufacturing a turbomachine part coated with a thermal barrier, the process comprising:
manufacturing the part by additive manufacturing;
electrophoretic depositing on the part of a layer comprising particles of a ceramic material, the electrophoretic depositing comprising dispersing the particles of the ceramic material in a sol-gel precursor monomer of said ceramic material which is liquid and polymerizing said sol-gel precursor monomer of said ceramic material to form said ceramic material; and
consolidating the layer by heat treatment in order to obtain a ceramic coating to form at least part of the thermal barrier, wherein a surface roughness of the ceramic coating is less than a surface roughness of an outer surface of the part on which the ceramic coating is formed.

2. The process according to claim 1 , further comprising depositing a bond coat on the part, the layer being deposited on said bond coat.

3. The process according to claim 2 , wherein the bond coat comprises MCrAlYRE, with RE denoting Hf, and/or Si, and/or Ta, and/or Re, and/or Pt, and/or Pd, and with M denoting Ni and/or Co, or wherein the bond coat comprises aluminide modified with Pt, and/or Hf, and/or Si.

4. The process according to claim 1 , wherein the heat treatment of the part to consolidate the ceramic coating is carried out by heating the part to a temperature above 700° C.

5. The process according to claim 4 , wherein the temperature is between 900° C. and 1100° C.

6. The process according to claim 1 , wherein the ceramic coating has a thickness between 10 μm and 300 μm.

7. The process according to claim 6 , wherein the thickness is between 50 μm and 150 μm.

8. The process according to claim 1 , wherein the ceramic material comprises Y 2 O 3 , Al 2 O 3 , TiO 2 , CeO 2 , and/or stabilized or partially stabilized zirconia of the type ZrO 2 -REO 1.5 and/or RE 2 Zr 2 O 7 , with RE denoting one or more rare earth elements, and/or yttriated zirconia.

9. The process according to claim 1 , wherein the part is a turbine air distributor comprising a plurality of blades, the ceramic coating being deposited on the blades.

10. The process according to claim 1 , wherein a maximum profile height Rmax of the surface roughness of the outer surface of the part is greater than or equal to 50 μm and a maximum profile height Rmax of the surface roughness of the ceramic coating is less than or equal to 20 μm.

Assignees

• Safran Helicopter Engines

Inventors

• Gurt Santanach Julien
• Danis Yann
• Crabos Fabrice

Classifications

• B22F10/66

  by mechanical means · CPC title

• B22F10/64

  by thermal means (control of energy beam parameters for post heating B22F10/364) · CPC title

• B22F10/62

  by chemical means · CPC title

• B22F10/28

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

• B33Y10/00

  Processes of additive manufacturing · CPC title