High temperature tolerant ceramic matrix composites and environmental barrier coatings

Patent metadata

Field	Value
Publication number	US-10822998-B2
Application number	US-201414772883-A
Country	US
Kind code	B2
Filing date	Mar 4, 2014
Priority date	Mar 5, 2013
Publication date	Nov 3, 2020
Grant date	Nov 3, 2020

Abstract

High-temperature machine components, more particularly, articles capable of operating in high-temperature environments, including for example turbines of gas engines, may be formed of a high temperature ceramic matrix composite that includes a ceramic substrate including silicon; an environmental harrier coating system including a silicon containing bond coat; and a diffusion barrier layer of a carbide or a nitride between the substrate of the article and the silicon bond coat of the environmental barrier coating system. The diffusion harrier layer selectively prevents or reduces the diffusion of boron and impurities from the substrate to the bond coat of the environmental barrier coating system.

First claim

What is claimed is:

1. An article comprising:
a ceramic substrate comprising SiC fibers, a porous matrix of SiC, and melt infiltrated silicon and boron within at least some of the pores of the porous matrix;
an environmental barrier coating system comprising a silicon-containing bond coat, the silicon-containing bond coat comprising silicon and a silicide; and
a diffusion barrier layer of crystalline silicon nitride 1 micrometer to 150 micrometers thick between the ceramic substrate and the silicon-containing bond coat,
the diffusion barrier layer being in direct contact with the ceramic substrate and the silicon-containing bond coat being in direct contact with the diffusion barrier layer; and
wherein the diffusion barrier layer prevents or reduces diffusion of boron and impurities from the ceramic substrate to the silicon-containing bond coat.

2. The article of claim 1 , wherein the ceramic substrate is operable at temperatures of up to 2550 degrees F. without melting.

3. The article of claim 2 , wherein a total concentration of impurities other than boron in the silicon of the ceramic substrate is less than 1 atom percent.

4. The article of claim 1 , wherein the melt infiltrated silicon comprises about 10% of the ceramic substrate.

5. The article of claim 1 , wherein the boron is added intentionally to the melt infiltrated silicone.

6. The article of claim 1 , wherein the environmental barrier coating system further comprises at least one layer comprising a rare earth disilicate, the rare earth disilicate having the chemical formula RE 2 Si 2 O 7 , wherein RE is selected from among: Sc, Y, La, Ce, Pr, Nd, Pm, Sm, Eu, Gd, Tb, Dy, Ho, Er, Tm, Yb, and Lu.

7. The article of claim 1 , wherein the boron is added in a percentage concentration intentionally to the melt infiltrated silicon.

8. The article of claim 1 , wherein the melt infiltrated silicon and boron are added to the substrate in a melt infiltration process.

9. The article of claim 8 , wherein the melt infiltration process comprises silicon reacting with carbon in a porous matrix to form SiC and melt infiltrated silicon.

10. The article of claim 9 , wherein the melt infiltrated silicon comprises about 10% of the ceramic substrate.

11. The article of claim 8 , wherein at least a portion of the boron is added intentionally to the melt infiltrated silicon used in the melt infiltration process.

12. The article of claim 1 , wherein the article comprises a turbine engine component.

13. The article of claim 1 , wherein the surface of the environmental barrier coating system has a temperature limit of up to 2700 degrees F.

14. An article comprising:
a substrate comprising a ceramic matrix composite, the ceramic matrix composite comprising silicon carbide fibers, a porous matrix of silicon carbide, and melt infiltrated silicon and boron within at least some of the pores of the porous matrix, wherein the substrate has a concentration of impurities except boron of less than 1 atom percent;
an environmental barrier coating system comprising a silicon-containing bond coat disposed over the substrate, the silicon-containing bond coat comprising silicon and molybdenum silicide; and
a diffusion barrier layer of crystalline silicon nitride 1 micrometer to 150 micrometers thick between the substrate and the silicon-containing bond coat, the diffusion barrier layer being in direct contact with the substrate and the silicon bond coat being in direct contact with the diffusion barrier layer.

15. The article of claim 14 , wherein the environmental barrier coating system further comprises at least one layer comprising a rare earth disilicate, the rare earth disilicate having the chemical formula RE 2 Si 2 O 7 , wherein RE is selected from among: Sc, Y, La, Ce, Pr, Nd, Pm, Sm, Eu, Gd, Tb, Dy, Ho, Er, Tm, Yb, and Lu.

16. The article of claim 14 , wherein the melt infiltrated silicon and boron are added to the substrate in a melt infiltration process.

17. The article of claim 16 , wherein the melt infiltration process comprises silicon reacting with carbon in a porous matrix to form SiC and melt infiltrated silicon.

18. The article of claim 17 , wherein the melt infiltrated silicon comprises about 10% of the ceramic substrate.

19. The article of claim 16 , wherein at least a portion of the boron is added intentionally to the melt infiltrated silicon used in the melt infiltration process.

20. The article of claim 14 , wherein the article comprises a turbine engine component.

Assignees

• Gen Electric

Inventors

• Luthra Krishan Lal
• Lipkin Don M
• Wan Julin

Classifications

• C04B41/89 Primary

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

• F01D5/288

  Protective coatings for blades · CPC title

• F01D5/282

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

• C04B2235/428

  Silicon · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title