Protective coating systems for gas turbine engine applications

Patent metadata

Field	Value
Publication number	US-11370717-B2
Application number	US-202016811726-A
Country	US
Kind code	B2
Filing date	Mar 6, 2020
Priority date	Jan 16, 2014
Publication date	Jun 28, 2022
Grant date	Jun 28, 2022

Abstract

A protective coating system includes a substrate that has an exterior surface exhibiting a degree of valley/hill surface irregularity including a plurality of hills and a plurality of valleys and a first coating layer formed directly on to the exterior surface of the substrate and that conforms to the exterior surface of the substrate such that the first coating layer has a non-uniform coating thickness over the substrate. The protective coating system further includes a second coating layer formed directly on to the exterior surface of the first coating layer. The second coating layer includes a plurality of pores within the second coating layer. Still further, the protective coating system includes a third coating layer formed within at least some of the plurality of pores within the second coating layer.

First claim

What is claimed is:

1. A protective coating system comprising:
a substrate formed of a ceramic matrix composite material, wherein the ceramic matrix composite material is a silicon carbide-silicon carbide (SiC-SiC) material, which includes a volume fraction of about 90% or more of SiC-based fibers; wherein the substrate has an exterior surface exhibiting a degree of valley/hill surface irregularity comprising a plurality of hills and a plurality of valleys;
a first coating layer deposited from a sol-gel material, wherein the first coating layer is formed directly on to the exterior surface of the substrate and conforms to the exterior surface of the substrate such that the first coating layer has a non-uniform coating thickness over the substrate wherein the first coating layer has a thickness within the plurality of valleys that is greater than its thickness over the plurality of hills;
a second, thermal barrier, porous coating layer formed directly on to the exterior surface of the first coating layer, wherein the second coating layer comprises a plurality of pores within the second coating layer, where the pores are at the surface and extending below the surface through various shapes and sizes; and
a third coating layer partially formed directly on to an exterior surface of the second coating layer and partially formed within at least some of the plurality of pores within the second coating layer, wherein the third coating layer coats walls of at least some of the plurality of pores but does not completely fill the at least some of the plurality of pores,
wherein:
there is a porosity gradient within the second coating layer, and
the porosity gradient is characterized by a relatively lesser degree of porosity adjacent to the exterior surface of the first coating layer and a relatively greater degree of porosity adjacent to the exterior surface of the second coating layer.

2. The protective coating system of claim 1 , wherein the first coating layer comprises a material including an element chosen from: aluminum, zirconium, titanium, yttrium, hafnium, and tantalum.

3. The protective coating system of claim 2 , wherein the first coating layer is a metal silicate.

4. The protective coating system of claim 1 , wherein the first coating layer has a variable thickness across the substrate of less than about 10 mils.

5. The protective coating system of claim 1 , wherein the second coating layer comprises a rare earth material.

6. The protective coating system of claim 5 , wherein the second coating layer consists of a silicate, aluminate, phosphate, or zirconate of a rare earth material.

7. The protective coating system of claim 1 , wherein the second coating layer has a thickness of about 10 mils to about 100 mils.

8. The protective coating system of claim 1 , wherein the third coating layer is chosen from: silicates, and phosphates of aluminum, silicon, zirconium, titanium, yttrium, hafnium, and tantalum.

9. The protective coating system of claim 1 , wherein the first coating layer comprises a metal silicate material including a metal element chosen from: aluminum, zirconium, titanium, yttrium, hafnium, and tantalum; wherein the second coating layer comprises a material that is chosen from: silicates, aluminates, phosphates, or zirconates of a rare earth material; and wherein the third coating layer comprises a material that is chosen from: silicates and phosphates of aluminum, silicon, zirconium, titanium, yttrium, hafnium, and tantalum.

10. The protective coating system of claim 1 , wherein the second coating layer comprises a porosity of about 10% to about 70%.

11. The protective coating system of claim 1 , wherein the third coating layer infiltrates the second coating layer to a depth of about 70% or less of a total thickness of the second coating layer.

12. The protective coating system of claim 1 , wherein the third coating layer creates a porosity gradient in the second coating layer.

13. The protective coating system of claim 1 , wherein about 30% or more of the total thickness of the second coating layer comprises pores that remain uncoated with the third coating layer.

14. The protective coating system of claim 1 , wherein the first coating layer is characterized as an oxygen barrier material, a compliance material, and/or a bonding material.

15. The protective coating system of claim 1 , wherein the second coating layer is characterized as a thermal barrier material.

16. A turbine blade comprising the protective coating system of claim 1 .

17. A protective coating system comprising:
a substrate that has an exterior surface exhibiting a degree of valley/hill surface irregularity comprising a plurality of hills and a plurality of valleys;
a first coating layer formed directly on to the exterior surface of the substrate and that conforms to the exterior surface of the substrate such that the first coating layer has a non-uniform coating thickness over the substrate wherein the first coating layer has a thickness within the plurality of valleys that is greater than its thickness over the plurality of hills;
a second, thermal barrier, coating layer formed directly on to the exterior surface of the first coating layer, wherein the second coating layer comprises a plurality of pores within the second coating layer, where the pores are at the surface and extending below the surface through various shapes and sizes; and
a third coating layer formed within at least some of the plurality of pores within the second coating layer, wherein the third coating layer coats walls of at least some of the plurality of pores but does not completely fill the at least some of the plurality of pores,
wherein:
there is a porosity gradient within the second coating layer, and
the porosity gradient is characterized by a relatively lesser degree of porosity adjacent to the exterior surface of the first coating layer and a relatively greater degree of porosity adjacent to the exterior surface of the second coating layer.

18. The protective coating system of claim 17 , wherein the third coating layer is further formed directly on to an exterior surface of the second coating layer.

Assignees

• Honeywell Int Inc

Inventors

• Oboodi Reza
• Passman Eric
• Jadidian Bahram

Classifications

• C04B41/89

  for obtaining at least two superposed coatings having different compositions · CPC title

• F05D2300/2261

  of silicon · CPC title

• Y10T428/24612

  Composite web or sheet · CPC title

• B05D7/5783

  No curing step for any layer · CPC title

• Y10T428/26

  Web or sheet containing structurally defined element or component, the element or component having a specified physical dimension · CPC title