Thermal barrier coating for gas turbine engine components

Patent metadata

Field	Value
Publication number	US-12344938-B2
Application number	US-202117359855-A
Country	US
Kind code	B2
Filing date	Jun 28, 2021
Priority date	Sep 5, 2012
Publication date	Jul 1, 2025
Grant date	Jul 1, 2025

Abstract

A component for a gas turbine engine according to an exemplary embodiment of the present disclosure can include a substrate, a thermal barrier coating deposited on at least a portion of the substrate, and an outer layer deposited on at least a portion of the thermal barrier coating. The outer layer can include a material that is reactive with an environmental contaminant that comes into contact with the outer layer to alter a microstructure of the outer layer.

First claim

What is claimed is:

1. A method of coating a component of a gas turbine engine, comprising:
applying a thermal barrier coating onto at least a portion of a substrate of the component; and
applying an outer layer onto at least a portion of the thermal barrier coating using the same application technique used to apply the thermal barrier coating, wherein the outer layer includes a material that is reactive with an environmental contaminant that comes into contact with the outer layer to alter a microstructure of the outer layer, wherein said thermal barrier coating includes a first priority in a range of approximately 20% to 28% by volume and said outer layer includes a second priority in a range of 40% to 60% by volume.

2. The method as recited in claim 1 , wherein each of the steps of applying include using a suspension plasma spray (SPS) technique.

3. A method of coating a component of a gas turbine engine, comprising:
applying a thermal barrier coating onto at least a portion of a substrate of the component; and

applying an outer layer onto at least a portion of the thermal barrier coating using the same application technique used to apply the thermal barrier coating, wherein the outer layer includes a material that is reactive with an environmental contaminant that comes into contact with the outer layer to alter a microstructure of the outer layer, wherein the thermal barrier coating includes a first porosity in a range of approximately 8% to 25% by volume and the outer layer includes a second porosity in a range of approximately 20% to 50% by volume.

4. The method as recited in claim 1 , comprising the step of:
shedding a solid portion formed within at least one porous region of the outer layer subsequent to the reaction between the material and the environmental contaminant.

5. The method as recited in claim 1 , wherein the steps of applying are performed using a suspension plasma spray technique that applies each of the thermal barrier coating and the outer layer in a plurality of individual coating passes, wherein a first coating pass of the plurality of individual coating passes includes a first material composition and a second coating pass of the plurality of individual coating passes includes a second material composition that is different from the first material composition.

6. The method as recited in claim 1 , wherein said outer layer includes a material that is reactive with an environmental contaminant that comes into contact with said outer layer to alter a microstructure of said outer layer, said material including gadolinia zirconia, hafnia, a lanthanide mixture, or a zirconia based ceramic material.

7. The method as recited in claim 6 , wherein said thermal barrier coating includes a first modulus of elasticity and said outer layer includes a second modulus of elasticity that is less than said first modulus of elasticity, and said thermal barrier coating includes a first density and said outer layer includes a second density that is less than said first density.

8. The method as recited in claim 7 , wherein said outer layer is comprised of a plurality of individual coating sublayers, and each of said plurality of individual coating sublayers includes its own unique material composition, porosity, density, and modulus of elasticity.

9. The method as recited in claim 8 , wherein an infiltrated portion is formed in at least one porous region of said second porosity in response to the reaction between said material and said environmental contaminant, said infiltrated portion absorbing and sequestering additional environmental contaminants, thereby preventing said additional environmental contaminants from infiltrating said thermal barrier coating.

10. The method as recited in claim 1 , wherein said outer layer includes a material including gadolinia zirconia configured to react with an environmental contaminant that comes into contact with said outer layer to alter a microstructure of said outer layer.

11. The method as recited in claim 10 , wherein an infiltrated portion is formed in said outer layer in response to the reaction between said material and said environmental contaminant, said infiltrated portion absorbing and sequestering additional environmental contaminants, thereby limiting infiltration of said additional environmental contaminants into said thermal barrier coating.

12. The method as recited in claim 11 , wherein at least a portion of said outer layer that includes said infiltrated portion is shed from said outer layer after the reaction with said environmental contaminant, said thermal barrier coating and said outer layer are both suspension plasma sprayed layers, and said outer layer is comprised of a plurality of individual coating sublayers, and each of said plurality of individual coating sublayers includes its own unique porosity, density, and modulus of elasticity.

13. The method as recited in claim 1 , wherein said outer layer includes a material including gadolinia zirconia that is configured to react with an environmental contaminant that comes into contact with said outer layer to alter a microstructure of said outer layer, wherein the reaction between said material and said environmental contaminant forms an infiltrated portion within at least one porous region of said outer layer, said infiltrated portion absorbing and sequestering additional environmental contaminants, thereby limiting infiltration of said additional environmental contaminants into said thermal barrier coating.

14. The method as recited in claim 13 , wherein said thermal barrier coating and said outer layer are both suspension plasma sprayed layers.

15. The method as recited in claim 14 , wherein said outer layer is comprised of a plurality of individual coating sublayers, and each of said plurality of individual coating sublayers includes its own unique porosity, density, and modulus of elasticity.

16. A method of coating a component of a gas turbine engine, comprising:
applying a thermal barrier coating onto at least a portion of a substrate of the component; and
applying an outer layer onto at least a portion of the thermal barrier coating by applying a plurality of individual coating sublayers, each individual coating sublayer having a thickness between 1 and 25 microns and formed with one of a plurality of individual coating passes of a suspension plasma spray device operated with a different set of spraying conditions from those used to form an adjacent individual coating sublayer, wherein the outer layer includes a material that is reactive with an environmental contaminant that comes into contact with the outer layer to alter a microstructure of the outer layer, and each of said plurality of individual coating sublayers includes its own unique porosity, density, and modulus of elasticity.

17. The method of claim 16 , wherein a first individual pass of the plurality of individual coating passes includes 7 wt % yttria stabilized zirconia (7YSZ) with a first set of spray conditions, and a second coating pass of the plurality of individual coating passes includes a second material different from 7 wt % yttria stabilized zirconia (7YSZ).

18. The method of claim 16 , wherein:
said thermal barrier coating includes a first porosity in a range of approximately 20% to 28% by volume and said outer layer includes a second porosity in a range of 40% to 60% by volume,
said thermal barrier coating includes a first modulus of elasticity and said outer layer includes a second modulus of elasticity that is less than said first modulus of elasticity, and s

Assignees

• Raytheon Tech Corp
• Rtx Corp

Inventors

• Strock Christopher W
• Maloney Michael J
• Litton David A
• Zimmerman Benjamin Joseph
• Hazel Brian T

Classifications

• F05D2300/514

  Porosity · CPC title

• C23C28/321

  with at least one metal alloy layer · CPC title

• C23C28/347

  with layers adapted for cutting tools or wear applications · CPC title

• F01D5/288

  Protective coatings for blades · CPC title

• C23C28/3215

  at least one MCrAlX layer · CPC title