Hybrid sandwich ceramic matrix composite

Patent metadata

Field	Value
Publication number	US-9850173-B2
Application number	US-201514593682-A
Country	US
Kind code	B2
Filing date	Jan 9, 2015
Priority date	Jan 9, 2015
Publication date	Dec 26, 2017
Grant date	Dec 26, 2017

Abstract

A hybrid sandwich ceramic matrix composite (CMC) may comprise a first facesheet, a second facesheet, and a core between and bonded to both of the first facesheet and the second facesheet. The first facesheet and the second facesheet may each include filaments in a ceramic matrix. The hybrid sandwich CMC may be configured for exposure to a thermal gradient in which the first facesheet is exposed to a higher temperature environment than the second facesheet. The first facesheet and the second facesheet may have at least closely matching coefficients of thermal expansion, and the first facesheet may have a higher compressive strength than the second facesheet.

First claim

What is claimed is:

1. A hybrid sandwich ceramic matrix composite (CMC), comprising:
a first facesheet including filaments in a ceramic matrix;
a second facesheet including filaments in a ceramic matrix; and
a core between and bonded to both of the first facesheet and the second facesheet, the hybrid sandwich CMC being configured for exposure to a thermal gradient in which the first facesheet is exposed to a higher temperature environment than the second facesheet, the first facesheet and the second facesheet having at least closely matching coefficients of thermal expansion, and the first facesheet having a higher compressive strength than the second facesheet, a diameter of the filaments in the first facesheet being greater than a diameter of the filaments in the second facesheet.

2. The hybrid sandwich CMC of claim 1 , wherein the second facesheet has a higher tensile strength than the first facesheet.

3. The hybrid sandwich CMC of claim 2 , wherein the first facesheet has a compressive strength that is about 1.5 times higher than a tensile strength of the first facesheet, and wherein the second facesheet has a tensile strength that is about 1.5 times higher than a compressive strength of the second facesheet.

4. The hybrid sandwich CMC of claim 1 , wherein the filaments of the first facesheet and the filaments of the second facesheet have a same chemical composition, wherein the ceramic matrix of the first facesheet and the ceramic matrix of the second facesheet have a same chemical composition, and wherein a volume fraction of the filaments in the first facesheet is equal to a volume fraction of the filaments in the second facesheet.

5. The hybrid sandwich CMC of claim 1 , wherein the hybrid sandwich CMC is cylindrical.

6. The hybrid sandwich CMC of claim 1 , wherein the first facesheet is more highly orthotropic than the second facesheet.

7. The hybrid sandwich CMC of claim 1 , wherein an interface strength between the filaments and the ceramic matrix of the first facesheet is stronger than an interface strength between the filaments and the ceramic matrix of the second facesheet.

8. The hybrid sandwich CMC of claim 1 , wherein a coefficient of thermal expansion of the first facesheet is lower than a coefficient of thermal expansion of the second facesheet.

9. The hybrid sandwich CMC of claim 1 , wherein the hybrid sandwich CMC is part of a component of an aircraft exhaust system, and wherein the first facesheet faces an exhaust gas flowpath of the aircraft exhaust system.

10. A hybrid sandwich ceramic matrix composite (CMC), comprising:
a first facesheet including filaments in a ceramic matrix;
a second facesheet including filaments in a ceramic matrix; and
a core between and bonded to both of the first facesheet and the second facesheet, the first facesheet and the second facesheet having at least closely matching coefficients of thermal expansion but differing in at least one of a diameter of the filaments, a chemistry of the filaments, a degree of orthotropy, and an interface strength between the filaments and the ceramic matrix, the hybrid sandwich CMC being configured for exposure to a thermal gradient in which the first facesheet is exposed to a higher temperature environment than the second facesheet, the first facesheet having a higher compressive strength than the second facesheet, an interface strength between the filaments and the ceramic matrix of the first facesheet being stronger than an interface strength between the filaments and the ceramic matrix of the second facesheet.

11. The hybrid sandwich CMC of claim 10 , wherein the second facesheet has a higher tensile strength than the first facesheet.

12. The hybrid sandwich CMC of claim 10 , wherein a diameter of the filaments of the first facesheet is greater than a diameter of the filaments of the second facesheet.

13. The hybrid sandwich CMC of claim 10 , wherein the first facesheet is more highly orthotropic than the second facesheet.

14. The hybrid sandwich CMC of claim 10 , wherein a coefficient of thermal expansion of the first facesheet is lower than a coefficient of thermal expansion of the second facesheet.

15. The hybrid sandwich CMC of claim 10 , wherein the hybrid sandwich CMC is cylindrical.

16. A method for fabricating a hybrid sandwich ceramic matrix composite (CMC), comprising:
laying up a first facesheet on a tool, the first facesheet including pre-preg layers of filaments in a ceramic matrix;
laying up a core on the first facesheet;
laying up a second facesheet on the core to provide a layup stack, the second facesheet including pre-preg layers of filaments in a ceramic matrix, the first facesheet and the second facesheet having at least closely matching coefficients of thermal expansion, the first facesheet having a higher compressive strength than the second facesheet, a diameter of the filaments in the first facesheet being greater than a diameter of the filaments in the second facesheet;
curing the layup stack at a first temperature; and
sintering the layup stack at a second temperature to provide the hybrid sandwich CMC, the hybrid sandwich CMC being configured for exposure to a thermal gradient in which the first facesheet is exposed to a higher temperature environment than the second facesheet.

17. A hybrid sandwich ceramic matrix composite (CMC), comprising:
a first facesheet including filaments in a ceramic matrix;
a second facesheet including filaments in a ceramic matrix; and
a core between and bonded to both of the first facesheet and the second facesheet, the hybrid sandwich CMC being configured for exposure to a thermal gradient in which the first facesheet is exposed to a higher temperature environment than the second facesheet, the first facesheet having more of the filaments oriented in the 0° and/or 90° directions than in other directions such that the first facesheet is more highly orthotropic than the second facesheet.

18. The hybrid sandwich CMC of claim 17 , wherein equivalent amounts of the filaments in the second facesheet are oriented in each of the 0°, 45°, −45°, and 90° directions.

Assignees

• Boeing Co

Inventors

• Keith William P

Classifications

• B64C1/00

  Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like · CPC title

• B32B18/00 Primary

  Layered products essentially comprising ceramics, e.g. refractory products · CPC title

• B32B1/08

  Tubular products · CPC title

• B32B2307/30

  having particular thermal properties · CPC title

• B32B9/005 Primary

  comprising one layer of ceramic material, e.g. porcelain, ceramic tile (layered products with at least two ceramic layers composed mainly of ceramic B32B18/00) · CPC title