Turbine engine part coated in a thermal barrier, and a method of obtaining it

Patent metadata

Field	Value
Publication number	US-11466370-B2
Application number	US-201716348369-A
Country	US
Kind code	B2
Filing date	Oct 31, 2017
Priority date	Nov 9, 2016
Publication date	Oct 11, 2022
Grant date	Oct 11, 2022

Abstract

A turbine engine part coated in at least a first ceramic layer forming a thermal barrier and including a ceramic material with first ceramic fibers dispersed in the first layer. The first layer may have a chemical composition gradient between a material for forming a thermal barrier and a material for providing protection against calcium and magnesium aluminosilicates, which is present at a greater content in an outer zone of the first layer, and/or the first layer may be porous and may present a porosity gradient such that an outer portion of the first layer presents lower porosity.

First claim

The invention claimed is:

1. A turbine engine part coated in at least a first ceramic layer forming a thermal barrier and comprising a ceramic material with first ceramic fibers dispersed in said first ceramic layer, wherein
the first ceramic layer comprises a mixture of a first ceramic material for providing a thermal barrier and of a second ceramic material for providing protection against calcium and magnesium aluminosilicates, the first and second ceramic materials being different, said first ceramic layer presenting a first zone extending over a fraction of its thickness and presenting a non-zero first weight content of a second material, and a second zone extending over a fraction of its thickness and covering the first zone, the second zone presenting a second weight content of the second material that is strictly greater than the first weight content.

2. A part according to claim 1 , wherein the weight content of first ceramic fibers in the first ceramic layer lies in the range 30% to 90%.

3. A part according to claim 2 , wherein the weight content of first ceramic fibers in the first ceramic layer lies in the range 50% to 90%.

4. A part according to claim 1 , wherein the mean length of the first ceramic fibers is less than or equal to 50 μm.

5. A part according to claim 1 , wherein the first ceramic fibers are constituted by a material selected from the following: zirconia stabilized by a rare earth oxide; rare earth oxides; pyrochlore structures; rare earth zirconates; alumina; and mixtures thereof.

6. A part according to claim 1 , wherein the part is also coated in a second ceramic layer comprising a ceramic material for providing protection against calcium and magnesium aluminosilicates, the second ceramic layer being situated on the first ceramic layer and further comprising second ceramic fibers dispersed in said second ceramic layer.

7. A part according to claim 1 , wherein the ceramic material for providing protection against calcium and magnesium aluminosilicates is selected from the following: rare earth oxides, zirconium stabilized by an earth oxide; pyrochlore structures; rare earth zirconates;
alumina; and mixtures thereof.

8. A method of fabricating a part according to claim 1 , including at least one step of forming the first ceramic layer on the part by a wet process.

9. A method according to claim 8 , wherein the first ceramic layer is formed by a sol-gel process, by dip-coating, or by electrophoresis.

10. A part according to claim 1 , wherein the first layer is porous and comprises a first portion extending over a fraction of its thickness and presenting a first porosity, and a second portion extending over a fraction of its thickness and covering the first portion, the second portion presenting a second porosity that is strictly less than the first porosity.

Assignees

• Safran
• Safran Aircraft Engines
• Univ Toulouse 3 Paul Sabatier
• Centre Nat Rech Scient
• Univ Paul Sabatier—Toulouse Iii

Inventors

• Joulia Aurélien
• MALIE ANDRé HUBERT LOUIS
• Ansart Florence
• Delon Elodie Marie
• Duluard Sandrine

Classifications

• C04B41/87 Primary

  Ceramics · CPC title

• C04B41/009

  characterised by the material treated · CPC title

• F05D2300/614

  Fibres or filaments · CPC title

• C23C18/127

  Preformed particles · CPC title

• C04B41/5042

  Zirconium oxides or zirconates; Hafnium oxides or hafnates · CPC title