Thermal barrier coating for gas turbine engine components

Patent metadata

Field	Value
Publication number	US-11047033-B2
Application number	US-201213603891-A
Country	US
Kind code	B2
Filing date	Sep 5, 2012
Priority date	Sep 5, 2012
Publication date	Jun 29, 2021
Grant date	Jun 29, 2021

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 component for a gas turbine engine, comprising:
a substrate;
a thermal barrier coating deposited on at least a portion of said substrate;
an outer layer deposited on at least a portion of said thermal barrier coating, 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 micro structure of said outer layer, said material including gadolinia zirconia, hafnia, a mixture of a lanthanide with one of Y, Sc, and Ce, or a zirconia-based ceramic material;
wherein said thermal barrier coating includes a first porosity and said outer layer includes a second porosity that is greater than said first porosity, and 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; and
wherein said outer layer is comprised of a plurality of individual coating sublayers, each having a thickness between 1 and 25 microns and formed with an individual pass of a suspension plasma spray device operated with a different set of spraying conditions from those used to form an adjacent individual coating sublayer, and each of said plurality of individual coating sublayers includes its own unique material composition, porosity, density, and modulus of elasticity,
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,
wherein said first porosity in the range of approximately 20% to 28% by volume and said second porosity in the range of 40% to 60% by volume.

2. The component as recited in claim 1 , wherein said material includes gadolinia zirconia.

3. The component as recited in claim 1 , wherein said thermal barrier coating includes a columnar microstructure that includes a dense vertically cracked structure.

4. The component as recited in claim 1 , wherein said environmental contaminant includes a calcium-magnesium-alumino-silicate (CMAS) infiltrants.

5. The component as recited in claim 1 , wherein at least a portion of said outer layer is shed from said outer layer after the reaction with said environmental contaminant.

6. The component as recited in claim 1 , wherein said outer layer is deposited over an entire surface area of said thermal barrier coating on an opposite side of said thermal barrier coating from said substrate.

7. A component for a gas turbine engine, comprising:
a substrate;
a thermal barrier coating deposited on at least a portion of said substrate;
an outer layer deposited on at least a portion of said thermal barrier coating, 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,
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,
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;
wherein said thermal barrier coating and said outer layer are both suspension plasma sprayed layers; and
wherein said outer layer is comprised of a plurality of individual coating sublayers, each having a thickness between 1 and 25 microns and formed with an individual pass of a suspension plasma spray device operated with a different set of spraying conditions from those used to form an adjacent individual coating sublayer, and each of said plurality of individual coating sublayers includes its own unique porosity, density, and modulus of elasticity,
wherein said thermal barrier coating includes a first porosity in the range of approximately 20% to 28% by volume and said outer layer includes a second porosity in the range of 40% to 60% by volume.

8. A component for a gas turbine engine, comprising:
a substrate;
a thermal barrier coating deposited on at least a portion of said substrate;
an outer layer deposited on at least a portion of said thermal barrier coating, 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;
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,
wherein said thermal barrier coating and said outer layer are both suspension plasma sprayed layers; and
wherein said outer layer is comprised of a plurality of individual coating sublayers, each having a thickness between 1 and 25 microns and formed with an individual pass of a suspension plasma spray device operated with a different set of spraying conditions from those used to form an adjacent individual coating sublayer, and each of said plurality of individual coating sublayers includes its own unique porosity, density, and modulus of elasticity,
wherein said thermal barrier coating includes a first porosity in the range of approximately 20% to 28% by volume and said outer layer includes a second porosity in the range of 40% to 60% by volume.

9. The component as recited in claim 1 , comprising a bond coat deposited between said thermal barrier coating and said substrate.

10. The component as recited in claim 9 , wherein said bond coat includes a metal-chromium-aluminum-yttrium layer (“MCrAlY”), or an aluminide or platinum aluminide.

11. The component as recited in claim 9 , wherein said bond coat includes a thermally grown oxide.

12. The component as recited in claim 9 , wherein said bond coat includes a NiAlCr based bond coat.

13. The component as recited in claim 9 , wherein said bond coat includes a thickness between 2 and 500 micrometers.

14. The component as recited in claim 9 , wherein said bond coat includes a thickness between 12 and 250 micrometers.

15. The component as recited in claim 9 , wherein said bond coat includes a thickness between 25 and 150 micrometers.

16. The component as recited in claim 1 , wherein a first individual coating sublayer of said plurality of individual coating sublayers includes a first material composition of 7 wt % yttria stabilized zirconia, and a second individual coating sublayer of said plurality of individual coating sublayers includes a second material composition that is different from said first material composition.

17. The component as re

Assignees

• Strock Christopher W
• Maloney Michael
• Litton David A
• Zimmerman Benjamin Joseph
• Hazel Brian T
• Raytheon Tech Corp

Inventors

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

Classifications

• F05D2300/514

  Porosity · CPC title

• F05D2300/13

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

• C23C4/02 Primary

  Pretreatment of the material to be coated, e.g. for coating on selected surface areas · CPC title

• C23C28/3215

  at least one MCrAlX layer · CPC title

• C23C28/347

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