Methods for manufacturing coated composite materials

Patent metadata

Field	Value
Publication number	US-11845699-B2
Application number	US-202117468356-A
Country	US
Kind code	B2
Filing date	Sep 7, 2021
Priority date	Sep 7, 2021
Publication date	Dec 19, 2023
Grant date	Dec 19, 2023

Abstract

Composite materials and methods of manufacturing composite materials, such as for use in aerospace parts, are described herein. A representative method for manufacturing a coated composite material structure includes applying a plurality of material layers to a preform structure. The plurality of material layers can include at least one first material layer (including a first matrix precursor), and at least one second material layer (including a second matrix precursor and a coating precursor). The method can also include infusing the preform structure with the first and second matrix precursors and the coating precursor from the plurality of material layers. The method can further include heating the infused preform structure to concurrently form a composite material structure and a coating on at least a portion of the composite material structure.

First claim

We claim:

1. A method for manufacturing a coated composite material structure, the method comprising:
applying a plurality of material layers to a preform structure, the plurality of material layers including: at least one first material layer including a first matrix precursor, and at least one second material layer including a second matrix precursor and a coating precursor;
infusing the preform structure with the first matrix precursor, second matrix precursor, and the coating precursor from the plurality of material layers; and
heating the infused preform structure to concurrently form a composite material structure and a coating on at least a portion of the composite material structure.

2. The method of claim 1 , wherein infusing the preform structure with the first matrix precursor, second matrix precursor, and the coating precursor comprises:
heating the plurality of material layers to partially or fully liquify the first matrix precursor and the second matrix precursor,
wherein the first matrix precursor, the second matrix precursor, and coating precursor infuse into the preform structure.

3. The method of claim 2 , wherein the plurality of material layers is heated to a temperature from 50° C. to 250° C.

4. The method of claim 1 , wherein the infused preform structure is heated to a temperature of at least 1450° C.

5. The method of claim 1 , further comprising pre-treating the preform structure at least once by heating the preform structure prior to applying the plurality of material layers.

6. The method of claim 5 , wherein the preform structure is heated to a temperature of 1650° C. or less.

7. The method of claim 1 , wherein the first matrix precursor and second matrix precursor have a common chemical composition.

8. The method of claim 1 , wherein the first matrix precursor and second matrix precursor have a different chemical composition.

9. The method of claim 1 , wherein the first matrix precursor and the second matrix precursor each include a resin individually selected from the group consisting of polycarbosilane resins, polysilazane resins, benzoxazine resins, bismaleimide resins, cyanate ester resins, epoxy resins, phenolic resins, polybutadiene resins, polyester resins, polyimide resins, silicon oxycarbide resins, vinyl ester resins, and combinations thereof.

10. The method of claim 1 , wherein the coating precursor includes a carbide coating precursor.

11. The method of claim 10 , wherein the coating precursor is a carbide coating precursor.

12. The method of claim 1 , further comprising using the coated composite material structure as a component of a rocket engine.

13. The method of claim 1 , further comprising using the coated composite material structure as a component of a jet engine.

14. The method of claim 1 , further comprising using the coated composite material structure as a component of a power generator.

15. A method for manufacturing a carbide-coated ceramic matrix composite (CMC) structure, the method comprising:
applying at least one first resin film layer to a carbonized preform structure, the at least one first resin film layer including a first resin;
applying at least one second resin film layer to the at least one first resin film layer, the at least one second resin film layer including a second resin and a carbide coating precursor;
heating the carbonized preform structure, the at least one first resin film layer, and the at least one second resin film layer to a first temperature to infuse the carbonized preform structure with the first resin, the second resin, and the carbide coating precursor; and
heating the infused carbonized preform structure to a second temperature to concurrently form a CMC structure and a carbide coating on at least a portion of the CMC structure.

16. The method of claim 15 , further comprising pre-treating the carbonized preform structure at least once by heating the carbonized preform structure prior to applying the at least one first resin film layer.

17. The method of claim 16 , wherein the carbonized preform structure is heated to a temperature of 1650° C. or less.

18. The method of claim 15 , wherein the first temperature is 50° C. to 250° C.

19. The method of claim 15 , wherein the second temperature is at least 1450° C.

20. The method of claim 15 , wherein the first resin and the second resin have a common chemical composition.

21. The method of claim 15 , wherein the first resin and the second resin have a different chemical composition.

22. The method of claim 15 , wherein the first resin and the second resin are individually selected from the group consisting of polycarbosilane resins, polysilazane resins, benzoxazine resins, bismaleimide resins, cyanate ester resins, epoxy resins, phenolic resins, polybutadiene resins, polyester resins, polyimide resins, silicon oxycarbide resins, vinyl ester resins, and combinations thereof.

23. The method of claim 15 , further comprising curing the infused carbonized preform structure prior to heating the infused carbonized preform structure to the second temperature.

24. The method of claim 23 , wherein curing the infused carbonized preform structure comprises heating the infused carbonized preform structure to a temperature from 150° C. to 500° C.

25. The method of claim 15 , further comprising using the CMC structure as a component of a rocket engine.

26. The method of claim 15 , further comprising using the CMC structure as a component of a jet engine.

27. The method of claim 15 , further comprising using the CMC structure as a component of a power generator.

Assignees

• Blue Origin Llc

Inventors

• Ghabchi Arash
• Boyer Brendan

Classifications

• C04B35/78 Primary

  containing non-metallic materials · CPC title

• C04B35/622

  Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products · CPC title

• C04B35/80 Primary

  Fibres, filaments, whiskers, platelets, or the like · CPC title

• C04B2235/616

  Liquid infiltration of green bodies or pre-forms · CPC title

• C04B35/571

  obtained from {Si-containing} polymer precursors {or organosilicon monomers} · CPC title