Protective coating systems for gas turbine engine applications and methods for fabricating the same

Patent metadata

Field	Value
Publication number	US-10676403-B2
Application number	US-201414156502-A
Country	US
Kind code	B2
Filing date	Jan 16, 2014
Priority date	Jan 16, 2014
Publication date	Jun 9, 2020
Grant date	Jun 9, 2020

Abstract

Protective coating systems for gas turbine engine applications and methods for fabricating such protective coating systems are provided. An exemplary protective coating system includes a substrate formed of a ceramic matrix composite material, a first coating layer formed directly on to the substrate and comprising an oxygen barrier material, a compliance material, or a bonding material and a second coating layer formed directly on to the first coating layer and comprising a thermal barrier material. The exemplary protective coating optionally includes a third coating layer partially formed directly on to the second coating layer and partially formed within at least some of the plurality of pores of 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 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 and characterized as an oxygen barrier material, a compliance material, and/or a bonding 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, porous coating layer formed directly on to the exterior surface of the first coating layer and characterized as a thermal barrier material, wherein the second coating layer further comprises a plurality of pores within the second coating layer such that the second coating layer comprises a porosity of about 10% to about 70%; 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, and
wherein the third coating layer infiltrates the second coating layer to a depth of 70% or less of a total thickness of the second coating layer, thereby creating a porosity gradient in the second coating layer, and wherein 30% or more of the total thickness of the second coating layer comprises pores that remain uncoated.

2. The protective coating system of claim 1 , wherein the ceramic matrix composite material is a silicon carbide silicon carbide (SiC-SiC) material.

3. 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.

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

5. 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.

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

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

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

9. The protective coating system of claim 1 , wherein the porosity has a gradient within the second coating layer, wherein the 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.

10. 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.

11. 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.

12. A protective coating system comprising:
a substrate formed of a ceramic matrix composite material, 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 and characterized as an oxygen barrier material, a compliance material, and/or a bonding 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, porous coating layer formed directly on to the exterior surface of the first coating layer and characterized as a thermal barrier material, wherein the second coating layer further comprises a plurality of pores within the second coating layer; 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.

13. The protective coating system of claim 12 , wherein the second coating layer consists of a silicate, aluminate, phosphate, or zirconate of a rare earth material.

Assignees

• Honeywell Int Inc

Inventors

• Oboodi Reza
• Passman Eric
• Jadidian Bahram

Classifications

• Y10T428/24999

  Inorganic · CPC title

• Y02T50/672

  Cross-Sectional Technologies · mapped topic

• Y10T428/24364

  with transparent or protective coating · CPC title

• F01D5/284

  Selection of ceramic materials · CPC title

• F01D5/282

  Selecting composite materials, e.g. blades with reinforcing filaments · CPC title