Turbine engine part coated with a protective ceramic coating, method for manufacturing and for using such a part

Patent metadata

Field	Value
Publication number	US-10301723-B2
Application number	US-201615754486-A
Country	US
Kind code	B2
Filing date	Oct 4, 2016
Priority date	Oct 7, 2015
Publication date	May 28, 2019
Grant date	May 28, 2019

Abstract

A turbine engine part includes at least a substrate, and present on the substrate, a ceramic coating for protection against calcium and magnesium aluminosilicates, the ceramic coating including Al2O3 at a molar content lying in the range 33% to 49%, Y3Al5O12 at a molar content lying in the range 21% to 53%, and yttria-stabilized zirconia at a molar content lying in the range 13% to 31%.

First claim

The invention claimed is:

1. A turbine engine part comprising at least a substrate, and present on the substrate, a ceramic coating for protection against calcium and magnesium aluminosilicates, the ceramic coating comprising:
Al 2 O 3 at a molar content lying in the range 33% to 49%;
Y 3 Al 5 O 12 at a molar content lying in the range 21% to 53%; and
yttria-stabilized zirconia at a molar content lying in the range 13% to 31%.

2. A part according to claim 1 , wherein the ceramic coating comprises:
Al 2 O 3 at a molar content lying in the range 37% to 45%;
Y 3 Al 5 O 12 at a molar content lying in the range 29% to 45%; and
yttria-stabilized zirconia at a molar content lying in the range 17% to 27%.

3. A part according to claim 1 , wherein the ceramic coating has a thickness lying in the range 50 μm to 200 μm.

4. A part according to claim 1 , wherein the substrate comprises a material selected from the following: a metal superalloy and a ceramic matrix composite material.

5. A part according to claim 1 , further comprising a thermal barrier layer present between the substrate and the ceramic coating.

6. A part according to claim 1 , wherein the substrate constitutes a part for an aviation turbine engine selected from among the following parts: a turbine blade; at least a portion of a turbine nozzle; and at least a portion of a turbine ring.

7. A method of fabricating a part according to claim 1 , the method comprising at least a step of forming the ceramic coating on the substrate, the ceramic coating comprising:
Al 2 O 3 at a molar content lying in the range 33% to 49%;
Y 3 Al 5 O 12 at a molar content lying in the range 21% to 53%; and
yttria-stabilized zirconia at a molar content lying in the range 13% to 31%.

8. A method according to claim 7 , wherein the ceramic coating is formed by sintering.

9. A method according to claim 7 , wherein the ceramic coating is formed on the substrate by directed solidification.

10. A method of using a part according to claim 1 , comprising a step of using the part at a temperature higher than 1000° C. in an oxidizing medium and in the presence of calcium and magnesium aluminosilicates.

Assignees

• Safran

Inventors

• Podgorski Michael
• Berthod Patrice
• Mathieu Stéphane
• Portebois Léo
• Vilasi Michel

Classifications

• F05D2300/506

  Hardness · CPC title

• F05D2240/24

  for turbines · CPC title

• C23C30/00 Primary

  Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process (C23C26/00, C23C28/00 take precedence) · CPC title

• C04B41/52

  Multiple coating or impregnating {multiple coating or impregnating with the same composition or with compositions only differing in the concentration of the constituents, is classified as single coating or impregnation} · CPC title

• C04B35/119

  with zirconium oxide · CPC title