Method of depositing abradable coatings under polymer gels

Patent metadata

Field	Value
Publication number	US-10508059-B2
Application number	US-201415102437-A
Country	US
Kind code	B2
Filing date	Dec 3, 2014
Priority date	Dec 12, 2013
Publication date	Dec 17, 2019
Grant date	Dec 17, 2019

Abstract

A method of depositing abradable coating on an engine component is provided wherein the engine component is formed of ceramic matrix composite and one or more layers, including at least one environmental barrier coating, may be disposed on the outer layer of the CMC. An outermost layer of the structure may further comprise a porous abradable layer that is disposed on the environmental barrier coating and provides a breakable structure which inhibits blade damage. The abradable layer may be gel-cast on the component and sintered or may be direct written by extrusion process and subsequently sintered.

First claim

What is claimed is:

1. A method of depositing an abradable coating on a gas turbine engine component, comprising:
forming a slurry mixture comprising at least bi-modal ceramic particulate with up to about 70% by volume of coarse particulate wherein said coarse particulate is at least one of Ln 2 Si 2 O 7 , Ln 2 SiO 5 , silica, barium strontium aluminosilicate (BSAS), monoclinic hafnium oxide, rare earth gallium garnet (Ln 2 Ga 2 O 9 ) where Ln is at least one of Scandium (Sc), Yttrium (Y), Lanthanum (La), Cerium (Ce), Praseodymium (Pr), Neodymium (Nd), Promethium (Pm), Samarium (Sm), Europium (Eu), Gadolinium (Gd), Terbium (Tb), Dysprosium (Dy), Holmium (Ho), Erbium (Er), Thulium (Tm), Ytterbium (Yb), Lutetium (Lu), and up to about 60% by volume of fine particulate, wherein said fine particulate includes at least one of Ln 2 Si 2 O 7 or Ln 2 SiO 5 where Ln is at least one of Sc, Y, La, Ce, Pr, Nd, Pm, Sm, Eu, Gd, Tb, Dy, Ho, Er, Tm, Yb, Lu, a dispersant for said ceramic particulate, and a monomer solution, a free-radical initiator compound, a low vapor pressure organic solvent and at least one sinter aid selected from the group consisting of iron, aluminum, titanium, cobalt, nickel, gallium, tin, indium, any compounds thereof, mixtures thereof, or mixtures of compounds thereof;
applying said slurry mixture to at least one of said gas turbine engine component and a mold;
gelling said slurry mixture by polymerizing and crosslinking said slurry mixture to form a firm irreversible gel matrix on said gas turbine component with said monomer solution and said free-radical initiator compound by heating said mold containing at least one of said gas turbine engine component and said slurry mixture to a first temperature between about 30° C.-80° C. before evaporation of said organic solvent;
drying said irreversible gel matrix at a second temperature of between 80° C. to 250° C. to affect a particulate on said gas turbine engine component one of within or removed from said mold; and
sintering said particulate of said dried irreversible gel matrix on said gas turbine engine component at a temperature greater than about 1204° C. and less than about 1357° C. forming a layer of said coating having a thickness greater than about 6 mils and a porosity of about 5 percent to about 50 percent, wherein said sintered layer comprises a doped rare earth disilicate where the sintering aid is a doping composition that dissolves into, and dopes the rare earth disilicate.

2. The method of claim 1 , wherein said coating is a porous, continuous abradable coating.

3. The method of claim 2 , further comprising inhibiting breakage of an adjacent component upon engagement with said abradable coating.

4. The method of claim 1 , wherein said coating is a solid abradable coating.

5. The method of claim 1 , wherein said coating is formed with a pattern.

6. The method of claim 1 , wherein said bi-modal ceramic particulate improves evaporation and reduces stress resulting in a substantially crack-free coating.

7. The method of claim 1 , wherein said coating includes a hermetic coating.

8. The method of claim 1 , wherein said gas turbine engine component is one of a blade or a shroud.

9. The method of claim 1 , wherein said irreversible gel matrix inhibits separation of said bi-modal ceramic particulate.

10. A gas turbine engine component, comprising:
a ceramic matrix composite (CMC) part forming one of a blade or shroud;
an environmental coating on an outer surface of said CMC part;
an abradable coating disposed on said environmental barrier coating;
said abradable coating comprising:
a bi-modal particulate including up to 70 percent by volume of a coarse particulate and up to 60 percent by volume of a fine particulate;
a free-radical initiator compound;
a low vapor pressure organic solvent;
at least one sintering aid selected from the group consisting of a iron, aluminum, titanium, cobalt, nickel, gallium, tin, indium, any compounds thereof, mixtures thereof, or mixtures of compounds thereof;
a gel-matrix spanning network formed by said bi-modal particulate being one of a monomer solution and polymer solution;
said gel matrix being dried and sintered on said CMC gas turbine engine component and having a thickness of at least about 5 mils.

11. The method of claim 10 , wherein said irreversible gel matrix inhibits settling of said coarse particulate.

Assignees

• Gen Electric

Inventors

• Kirby Glen Harold

Classifications

• C08K3/22

  of metals · CPC title

• F05D2300/228

  Nitrides · CPC title

• F05D2300/21

  Oxide ceramics · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• C04B41/89

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