Methods for manufacturing porous barrier coatings using air plasma spray techniques

Patent metadata

Field	Value
Publication number	US-11339671-B2
Application number	US-201916723110-A
Country	US
Kind code	B2
Filing date	Dec 20, 2019
Priority date	Dec 20, 2019
Publication date	May 24, 2022
Grant date	May 24, 2022

Abstract

A method for forming a porous barrier coating on a substrate without substantial chemical segregation includes the steps of providing or obtaining a barrier coating material in powdered form and spraying the barrier coating material onto the substrate using air plasma spraying. The air plasma spraying is performed using an average homologous surface temperature of the depositing particles in a range of about 1.25 to about 1.5 and a particle velocity in a range of about 300 m/s to about 500 m/s. The depositing particles are fully molten.

First claim

What is claimed is:

1. A method for forming a porous barrier coating on a substrate without substantial chemical segregation, the method comprising the steps of:
providing or obtaining a barrier coating material in powdered form; and spraying the barrier coating material onto the substrate using air plasma spraying to form the porous barrier coating,
wherein the air plasma spraying is performed using an average homologous surface temperature of the depositing particles in a range of about 1.25 to about 1.5 and a particle velocity in a range of about 300 m/s to about 500 m/s,
wherein the depositing particles are fully molten, and
wherein the porous barrier coating has a porosity of from about 10 to about 15%.

2. The method of claim 1 , wherein the substrate is a turbine engine component.

3. The method of claim 2 , wherein the substrate has been coated with an overlay coating or a combination of overlay coatings.

4. The method of claim 1 , wherein the barrier coating material is a thermal barrier coating material.

5. The method of claim 4 , wherein the thermal barrier coating material is a low-k thermal barrier coating material comprising a multi-component ceramic oxide with one or more rare-earth metals.

6. The method of claim 5 , wherein the thermal barrier coating material is elementally defined, by mole percent: about 8% to about 30% YO 1.5 ; about 8% to about 30% YbO 1.5 or GdO 1.5 or combination thereof; about 8% to about 30% TaO 2.5 ; about 0% to about 10% HfO 2 ; and a balance of ZrO 2 .

7. The method of claim 1 , wherein the average homologous surface temperature of the depositing particles is in a range of about 1.3 to about 1.45.

8. The method of claim 1 , wherein the porous barrier coating material is elementally defined, by mole percent: from about 8% to about 30% YO 1.5 ; from about 8% to about 30% YbO 1.5 or GdO 1.5 or combination thereof; from about 8% to about 30% TaO 2.5 ; from 0% to about 10% HfO 2 ; and a balance of ZrO 2 .

9. The method of claim 8 , wherein the particle velocity is in a range of about 325 m/s to about 475 m/s.

10. The method of claim 1 , wherein the particle velocity is in a range of about 325 m/s to about 475 m/s.

11. The method of claim 1 , wherein the particle velocity is in a range of about 300 m/s to about 350 m/s.

12. The method of claim 1 , wherein the particle velocity is in a range of about 350 m/s to about 400 m/s.

13. The method of claim 1 , utilizing as a secondary gas, hydrogen (H 2 ).

14. The method of claim 13 , wherein the H 2 gas has a flow rate of about 4 to about 20 normal liters/min.

15. A method for forming a porous low-k thermal barrier coating on a turbine engine substrate without substantial chemical segregation, the method comprising the steps of:
providing or obtaining a low-k thermal barrier coating material in powdered form, wherein the low-k thermal barrier coating material comprises a multi-component ceramic oxide with one or more rare-earth metals; and
spraying the low-k thermal barrier coating material onto the turbine engine substrate using air plasma spraying to form the porous low-k thermal barrier coating,
wherein the air plasma spraying is performed using an average homologous surface temperature of the depositing particles in a range of about 1.25 to about 1.5 and a particle velocity in a range of about 300 m/s to about 500 m/s, and
wherein the depositing particles are fully molten, and
wherein the porous low-k thermal barrier coating has a porosity of from about 10 to about 15%.

16. The method of claim 15 , wherein the average homologous surface temperature of the depositing particles is in a range of about 1.3 to about 1.45.

17. The method of claim 15 , wherein the porous low-k thermal barrier coating material is elementally defined, by mole percent: from about 8% to about 30% YO 1.5 ; from about 8% to about 30% YbO 1.5 or GdO 1.5 or combination thereof; from about 8% to about 30% TaO 2.5 ; from 0% to about 10% HfO 2 ; and a balance of ZrO 2 .

18. The method of claim 15 , wherein the particle velocity is in a range of about 325 m/s to about 475 m/s.

Assignees

• Honeywell Int Inc

Inventors

• Lutz Bradley
• Jorgensen David

Classifications

• F01D5/284

  Selection of ceramic materials · CPC title

• F05B2280/5002

  Thermal properties · CPC title

• C23C4/11 Primary

  Oxides · CPC title

• C23C4/134

  Plasma spraying · CPC title

• F05D2300/21

  Oxide ceramics · CPC title