Sintered-bonded high temperature coatings for ceramic turbomachine components

Patent metadata

Field	Value
Publication number	US-10801111-B2
Application number	US-201715608574-A
Country	US
Kind code	B2
Filing date	May 30, 2017
Priority date	May 30, 2017
Publication date	Oct 13, 2020
Grant date	Oct 13, 2020

Abstract

Methods for forming sintered-bonded high temperature coatings over ceramic turbomachine components are provided, as are ceramic turbomachine components having such high temperature coatings formed thereover. In one embodiment, the method includes the step or process of removing a surface oxide layer from the ceramic component body of a turbomachine component to expose a treated surface of the ceramic component body. A first layer of coating precursor material, which has a solids content composed predominately of at least one rare earth silicate by weight percentage, is applied to the treated surface. The first layer of the coating precursor material is then heat treated to sinter the solids content and form a first sintered coating layer bonded to the treated surface. The steps of applying and sintering the coating precursor may be repeated, as desired, to build a sintered coating body to a desired thickness over the ceramic component body.

First claim

What is claimed is:

1. A method for forming a spallation-resistant high temperature coating over a turbomachine component having a ceramic component body, the method comprising:
removing a surface oxide layer from the ceramic component body to expose a treated surface of the ceramic component body, the ceramic component body comprises a silicon-nitride material and the removing comprises contacting the surface oxide layer with molten sodium hydroxide (NaOH) over the silicon-nitride material and selectively removing silica scale and glass phases from the silicon-nitride material to produce a non-planar surface topography on the treated surface;
depositing a first layer of a coating precursor material over the treated surface, the coating precursor material infiltrating into the non-planar surface topography, the first layer of the coating precursor material having a solids content composed predominately of at least one rare earth silicate by weight percentage;
heat treating the first layer of the coating precursor material to sinter the solids content and form a first sintered coating layer bonded directly to the treated surface of the ceramic component body with a mechanical lock between the first sintered coating layer and the treated surface;
depositing a second layer of the coating precursor material over the first sintered coating layer;
heat treating the second layer of the coating precursor material to form a second sintered coating layer bonded to the first sintered coating layer; and
forming a top coating layer over the second sintered coating layer having a porosity less than a porosity of the second sintered coating layer, the top coating layer forming an outermost layer of the high temperature coating and the high temperature coating is spallation-resistant.

2. The method of claim 1 further comprising:
embedding organic particles in the second layer of coating precursor material; and
during heat treatment of the second layer of the coating precursor material, thermally decomposing the organic particles to impart the second sintered coating layer with an increased porosity relative to the first sintered coating layer.

3. The method of claim 2 further comprising selecting an amount, size, and shape of the organic particles to impart the second sintered coating layer with a porosity between about 20 and about 40 percent by volume.

4. The method of claim 2 further comprising forming at least one additional coating layer over the second sintered coating layer prior to forming the top coating layer, the additional coating layer having a porosity greater than the porosity of the second sintered coating layer.

5. The method of claim 1 wherein heat treating comprises:
performing an organic burnout phase during which the first layer of coating precursor material is heated to a first peak temperature within a first time period; and
after the organic burnout phase, performing a sintering phase during which the first layer of coating precursor material is heated to a second peak temperature within a second time period;
wherein the first peak temperature is less than the second peak temperature; and
wherein the first time period is greater than the second time period.

6. The method of claim 5 further comprising, during the sintering phase, heating the first layer of coating precursor material at a rate exceeding 300 degrees Celsius per minute to attain the second peak temperature.

7. The method of claim 1 further comprising maintaining the ceramic component body in non-oxidizing atmospheres for a period of time encompassing the steps of removing the surface oxide and heat treating the first layer of the coating precursor material.

8. The method of claim 1 wherein removing comprises imparting the treated surface with a surface roughness exceeding 0.1 micron.

9. The method of claim 1 wherein the steps of removing, depositing, and heat treating are performed such that the first sintered coating layer is bonded directly to and intimately contacts the treated surface of the ceramic component body.

10. The method of claim 1 further comprising selecting the solids content of the coating precursor material to comprise:
80% to 100% at least one rare earth silicate by weight; and
0% to 20% at least one glass sintering aid by weight.

11. The method of claim 10 further comprising selecting the at least one rare earth silicate to comprise ytterbium disilicate.

12. The method of claim 10 further comprising selecting the at least one glass sintering aid to comprise 1% to 10%, by weight, of a sintering glass aid selected from the group consisting of magnesioaluminosilicate, magnesia, and alumina.

13. The method of claim 1 wherein contacting the surface oxide layer with the molten sodium hydroxide (NaOH) further comprises submerging the ceramic component body in a bath of the molten sodium hydroxide (NaOH).

14. A method for forming a spallation-resistant high temperature coating over a turbomachine component having a silicon-nitride component body, the method comprising:
removing a surface oxide layer from the silicon-nitride component body to expose a treated surface of the silicon-nitride component body, the removing comprises contacting the surface oxide layer with molten sodium hydroxide (NaOH) over the silicon-nitride component body and selectively removing silica scale and glass phases from the silicon-nitride component body to produce a non-planar surface topography on the treated surface;
building-up a sintered coating body over the treated surface of the silicon-nitride component body by iteratively performing the steps of: (i) depositing coating precursor material layers containing rare earth silicate particles over the treated surface, and (ii) heat treating the coating precursor material layers to sinter the rare earth silicate particles and form a portion of the sintered coating body, the building-up including depositing a first layer of the coating precursor material over the treated surface and heat treating the first layer of the coating precursor material to sinter the rare earth silicate particles and form an innermost layer of the sintered coating body, with a mechanical lock formed between the innermost layer of the sintered coating body and the treated surface;
imparting the sintered coating body with a desired porosity that varies from the innermost layer of the sintered coating body to an outermost layer of the sintered coating body by: (i) adding organic particles to at least the first layer of coating precursor material layer included in the coating precursor material layers and, (ii) thermally decomposing the organic particles when heat treating the first layer of coating precursor material layer, the innermost layer directly bonded to the treated surface of the silicon-nitride component body and the outermost layer has a porosity that is greater than a porosity of the innermost layer; and
forming a top coating layer over the outermost layer of the sintered coating body having a porosity less than the porosity of the outermost layer of the sintered coating body, the top coating layer forming an outermost layer of the high temperature coating and the high temperature coating is spallation-resistant.

Assignees

• Honeywell Int Inc

Inventors

• Oboodi Reza
• Piascik James
• Olson Donald M
• Kruk Natalie
• Whalen Terence

Classifications

• C04B41/85 Primary

  with inorganic materials · CPC title

• Y10T428/249981

  Plural void-containing components · CPC title

• F05D2230/22

  by sintering · CPC title

• F05D2230/31

  Layer deposition · CPC title

• F05D2230/90

  Coating; Surface treatment · CPC title