Ceramic materials comprising preceramic resin formulations, and related articles and methods

Patent metadata

Field	Value
Publication number	US-11634583-B2
Application number	US-202016916374-A
Country	US
Kind code	B2
Filing date	Jun 30, 2020
Priority date	Jul 17, 2017
Publication date	Apr 25, 2023
Grant date	Apr 25, 2023

Abstract

A preceramic resin formulation comprising a polycarbosilane preceramic polymer and an organically modified silicon dioxide preceramic polymer. A ceramic material comprising a reaction product of the polycarbosilane preceramic polymer and organically modified silicon dioxide preceramic polymer is also described. Articles comprising the ceramic material are also described, as are methods of forming the preceramic resin formulation and the ceramic material.

First claim

What is claimed is:

1. A ceramic material comprising a reaction product of a polycarbosilane preceramic polymer and an organically modified silicon dioxide preceramic polymer, the organically modified silicon dioxide preceramic polymer comprising monomers having the chemical structure of:

where each of R 3 and R 4 is independently a methyl (CH 3 ) group, a vinyl group (CH 2 ═CH) directly bonded to the silicon atom, or a vinyl group (CH 2 ═CH) bonded to the silicon atom by an alkyl linker, and n is an integer from 2 to 10,000.

2. The ceramic material of claim 1 , wherein the ceramic material is configured as at least a portion of a rocket motor nozzle or a rocket motor casing.

3. The ceramic material of claim 1 , wherein the ceramic material is configured as at least a portion of a turbine, a turbine blade, a turbine housing, a turbine engine vane, an insulating tile, a rotor blade, an insulation blanket, a compressor blade, a wing component, a fuselage skin, a landing gear, an exhaust nozzle, an engine exhaust duct, a nose cone, a re-entry shield, or a heat shield.

4. The ceramic material of claim 1 , wherein the ceramic material comprises an oxidative resistant coating on a rocket motor nozzle or other high temperature aerostructure, a high temperature adhesive, a mortar material, an insulation, a thermal protection material, a thermal ablation material, or a matrix material of a ceramic matrix composite.

5. The ceramic material of claim 1 , wherein the polycarbosilane preceramic polymer comprises a chemical structure of

where R 1 and R 2 of each monomer is independently a hydrogen (H) group, a methyl (CH 3 ) group, a vinyl group (CH 2 ═CH) directly bonded to the silicon atom, or a vinyl group (CH 2 ═CH) bonded to the silicon atom by an alkyl linker, and n is an integer from 2 to 10,000 and an organically modified silicon dioxide preceramic polymer.

6. The ceramic material of claim 1 , further comprising one or more of a filler and a pigment.

7. The ceramic material of claim 1 , wherein one or more of R 3 and R 4 in at least a portion of the monomers comprises the vinyl group directly bonded to the silicon atom or the vinyl group bonded to the silicon atom by the alkyl linker.

8. A method of forming a preceramic resin formulation, comprising:
combining a polycarbosilane preceramic polymer and an organically modified silicon dioxide preceramic polymer with a crosslinking agent to form the preceramic resin formulation, the organically modified silicon dioxide preceramic polymer comprising monomers having the chemical structure of:

where each of R 3 and R 4 is independently a methyl (CH 3 ) group, a vinyl group (CH 2 ═CH) directly bonded to the silicon atom, or a vinyl group (CH 2 ═CH) bonded to the silicon atom by an alkyl linker, and n is an integer from 2 to 10,000.

9. The method of claim 8 , wherein combining a polycarbosilane preceramic polymer and an organically modified silicon dioxide preceramic polymer with a crosslinking agent to form the preceramic resin formulation comprises combining the polycarbosilane preceramic polymer having a viscosity less than or equal to about 250 cP at a temperature of about 25° C. and the organically modified silicon dioxide preceramic polymer having a viscosity greater than or equal to about 2,500 cP at a temperature of about 25° C.

10. A method of forming a ceramic material, comprising:
forming a preceramic resin formulation comprising a polycarbosilane preceramic polymer, an organically modified silicon dioxide preceramic polymer, and a crosslinking agent;
reacting vinyl groups of the polycarbosilane preceramic polymer with silicon-hydrogen bonds of the organically modified silicon dioxide preceramic polymer to cure the preceramic resin formulation to form a cured preceramic resin formulation; and
ceramifying the cured preceramic resin formulation to form a ceramic material.

11. The method of claim 10 , wherein reacting vinyl groups of the polycarbosilane preceramic polymer with silicon-hydrogen bonds of the organically modified silicon dioxide preceramic polymer comprises exposing the preceramic resin formulation to a temperature of from about 0° C. to about 400° C.

12. The method of claim 10 , wherein ceramifying the cured preceramic resin formulation to form a ceramic material comprises forming the ceramic material at a ceramic yield of greater than about 70%.

13. The method of claim 10 , further comprising forming the preceramic resin formulation into a shape before curing the preceramic resin formulation.

14. The method of claim 13 , wherein forming the preceramic resin formulation into a shape before curing the preceramic resin formulation comprises forming the preceramic resin formulation into a component of a rocket motor nozzle before curing.

15. The method of claim 13 , wherein forming the preceramic resin formulation into a shape before curing the preceramic resin formulation comprises forming the preceramic resin formulation into a turbine or a heat shield before curing.

16. An article, comprising:
a reaction product of a polycarbosilane preceramic polymer and an organically modified silicon dioxide preceramic polymer, the article configured as a component of a rocket motor or of a high temperature aerostructure, the organically modified silicon dioxide preceramic polymer comprising monomers having the chemical structure of:

where each of R 3 and R 4 is independently a methyl (CH 3 ) group, a vinyl group (CH 2 ═CH) directly bonded to the silicon atom, or a vinyl group (CH 2 ═CH) bonded to the silicon atom by an alkyl linker and n is an integer from 2 to 10,000.

17. The article of claim 16 , wherein the article comprises at least a portion of a rocket motor nozzle or a rocket motor casing.

18. The article of claim 16 , wherein the article comprises at least a portion of a turbine, a turbine blade, a turbine housing, a turbine engine vane, an insulating tile, a rotor blade, an insulation blanket, a compressor blade, a wing component, a fuselage skin, a landing gear, an exhaust nozzle, an engine exhaust duct, a nose cone, a re-entry shield, a laminate structure, or a heat shield.

19. The article of claim 16 , wherein the article comprises an oxidative resistant coating on a rocket motor nozzle or other high temperature aerostructure, a high temperature adhesive, a mortar material, an insulation, a thermal protection material, a thermal ablation material, or a matrix material of a ceramic matrix composite.

20. The article of claim 16 , wherein the reaction product comprises a ceramic yield of greater than about 70%.

Assignees

• Northrop Grumman Systems Corp

Inventors

• Garcia Benjamin W C

Classifications

• F02C7/00

  Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants (controlling F02C9/00) · CPC title

• F01D5/284

  Selection of ceramic materials · CPC title

• C04B35/14

  based on silica · CPC title

• F02K9/00

  Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof · CPC title

• C08G77/60

  in which all the silicon atoms are connected by linkages other than oxygen atoms · CPC title