Composite part with smooth outer face and manufacturing method thereof

Patent metadata

Field	Value
Publication number	US-11141960-B2
Application number	US-201916555575-A
Country	US
Kind code	B2
Filing date	Aug 29, 2019
Priority date	Aug 29, 2018
Publication date	Oct 12, 2021
Grant date	Oct 12, 2021

Abstract

A part for an aircraft turbojet engine nacelle is made of a composite material and includes at least one outer face (S1), a fibrous preform including fiber locks and having a surface(s) delimiting depressions between fiber locks, a covering material which at least partially covers the surface(s) of the fibrous preform and in particular the depressions, and a matrix which binds entirely the covering material and the fibrous preform. The covering material is a fibrous mat and the outer face (S1) is smooth. A method for manufacturing such a part includes manufacturing the fibrous preform, providing a fibrous mat, depositing the fibrous preform and fibrous mat in a mold, dispersing the matrix between the fibers of the preform and mat and consolidating the fibrous preform and mat.

First claim

What is claimed is:

1. A part for an aircraft turbojet engine nacelle, the part being made of a composite material and including at least one outer face, the part comprising:
a fibrous preform including fiber locks and a surface defining depressions between the fiber locks, the depressions having a height between one and two times a height of the fiber locks;
a covering material which at least partially covers the surface of the fibrous preform and the depressions; and
a matrix which binds the covering material and the fibrous preform,
wherein the covering material is an unwoven fibrous mat including at least one fiber extending substantially parallel to the at least one outer face of the part and above at least one of the depressions between the fiber locks of the fibrous preform, wherein the at least one outer face is smooth.

2. The part according to claim 1 , wherein a thickness of the unwoven fibrous mat is smaller than half a thickness of the fiber locks of the fibrous preform.

3. The part according to claim 1 , wherein a thickness of the unwoven fibrous mat is smaller than one fifth of a thickness of the fiber locks of the fibrous preform.

4. The part according to claim 1 , wherein the fibrous preform includes ceramic fibers.

5. The part according to claim 1 , wherein the fibrous preform includes ceramic fibers selected from the group consisting of carbides, borides, oxides, and silicides.

6. The part according to claim 1 , wherein the fibrous preform includes silicon carbide (SiC) fibers.

7. The part according to claim 1 , wherein the fibrous preform includes alumina or aluminosilicates-based fibers.

8. The part according to claim 1 , wherein the fibrous preform includes at least 60% alumina-based fibers.

9. The part according to claim 1 , wherein the matrix is a ceramic matrix.

10. The part according to claim 1 , wherein the matrix is a ceramic matrix selected from the group consisting of carbides, borides, oxides, and silicides.

11. The part according to claim 1 , wherein the matrix is a silicon carbide (SiC) matrix.

12. The part according to claim 1 , wherein the matrix is an alumina or aluminosilicates-based matrix.

13. The part according to claim 1 , wherein the matrix is at least 60% alumina-based matrix.

14. The part according to claim 1 , wherein the unwoven fibrous mat includes ceramic fibers.

15. The part according to claim 1 , wherein the unwoven fibrous mat includes ceramic fibers selected from the group consisting of carbides, borides, oxides, and silicides.

16. The part according to claim 1 , wherein the unwoven fibrous mat includes silicon carbide (SiC) fibers.

17. The part according to claim 1 , wherein the unwoven fibrous mat includes alumina-based fibers.

18. The part according to claim 1 , wherein the unwoven fibrous mat includes at least 60% alumina-based fibers.

19. A method for manufacturing a part according to claim 1 , the method comprising:
manufacturing the fibrous preform;
providing the unwoven fibrous mat;
depositing the fibrous preform and the unwoven fibrous mat between two faces of a mold;
dispersing the matrix between fibers of the fibrous preform and fibers of the unwoven fibrous mat; and
consolidating the fibrous preform and the unwoven fibrous mat, wherein the matrix dispersed between the fibers of the fibrous preform and the fibers of the unwoven fibrous mat is heat-treated.

20. The manufacturing method according to claim 19 , wherein the step of manufacturing the fibrous preform is performed in the mold.

21. The manufacturing method according to claim 19 , wherein the unwoven fibrous mat is deposited on at least one of the two faces of the mold, and the step of manufacturing the fibrous preform is carried out in the mold, on the unwoven fibrous mat.

22. The manufacturing method according to claim 21 , wherein the step of depositing the unwoven fibrous mat is repeated in the mold and on the fibrous preform such that the unwoven fibrous mat is on both faces of the fibrous preform.

23. The manufacturing method according to claim 19 , wherein the step of providing the unwoven fibrous mat is carried out by scattering cut fibers on at least one of the mold and the fibrous preform.

24. The manufacturing method according to claim 19 , wherein the consolidation step includes a thermomechanical treatment step.

Assignees

• Safran Nacelles
• Safran Ceram

Inventors

• Desjoyeaux Bertrand
• Silva De Vasconcellos Davi
• Planckeel Aline

Classifications

• B64C1/00

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

• C04B2235/5252

  having a specific pre-form · CPC title

• C04B2235/5228

  Silica and alumina, including aluminosilicates, e.g. mullite · CPC title

• C04B2235/5224

  Alumina or aluminates · CPC title

• C04B35/62852

  Alumina or aluminates · CPC title