Rear fairing for a turbojet engine pylon made of composite materials

Patent metadata

Field	Value
Publication number	US-11655044-B2
Application number	US-201916549359-A
Country	US
Kind code	B2
Filing date	Aug 23, 2019
Priority date	Feb 23, 2017
Publication date	May 23, 2023
Grant date	May 23, 2023

Abstract

An rear fairing for a pylon supporting an aircraft turbojet engine forms an aerodynamic surface covering the base of the pylon. The rear fairing is elongated in a longitudinal direction and includes a floor arranged opposite the hot gases exiting the turbojet engine and side walls constituting aerodynamic surfaces. The floor and the side walls include ceramic matrix composite materials made from preforms formed by layers of superimposed warp and weft yarns, the preforms have interlayer weaving yarns connecting the layers to one another.

First claim

What is claimed is:

1. A rear fairing for a pylon holding an aircraft turbojet engine and forming an aerodynamic surface covering a base of the pylon, the rear fairing extending in a longitudinal direction and comprising:
a floor facing a hot gas exiting the turbojet engine; and
lateral walls extending to the floor, the lateral walls forming aerodynamic surfaces,

wherein the floor and the lateral walls include ceramic matrix composite materials made from preforms formed of superimposed layers of warp or weft threads, the preforms having inter-layer weaving threads connecting the superimposed layers to each other,
wherein the preforms form, in one single piece, a structure in which the floor and the lateral walls meet each other at folds to form a Y-shaped section having a sharp edge turned outwards and configured to separate flow of the hot gas from a cold air flow.

2. The rear fairing according to claim 1 , wherein the warp or weft threads forming the preform are disposed in columns extending in the longitudinal direction, and the superimposed layers of the warp or weft threads forming the preform are connected to each other with different transversely disposed inter-layer weaving threads, which connect different columns of the warp or weft threads, along the longitudinal direction.

3. The rear fairing according to claim 1 , wherein:
the different superimposed layers of warp or weft threads forming the edges are connected to each other and the floor by transverse inter-layer weaving threads, and
the superimposed layers of warp or weft threads of the floor are connected to the superimposed layers of warp or weft threads of the lateral walls by inter-layer weaving threads such that the warp or weft threads of the floor, the lateral walls, and the edges form a single preform.

4. The rear fairing according to claim 1 further comprising transverse partitions fastened on the floor.

5. The rear fairing according to claim 4 , wherein the transverse partitions are made from a preform integrally formed with the preform of the floor.

6. The rear fairing according to claim 5 , wherein on a top of the preform of the floor includes transverse partitions, which are connected to the preform of the floor by transverse folding lines.

7. The rear fairing according to claim 1 , wherein the preforms form, in one single piece, the floor and the lateral walls which extend from each other by folds forming rounded edges.

8. The rear fairing according to claim 1 , wherein the preform of the floor includes, on each side outwardly of a folding line directly connecting the floor to the lateral wall, a protrusion made in continuity of the floor, below the lateral wall.

9. The rear fairing according to claim 1 further comprising, in the longitudinal direction, an assembly comprising the floor and the lateral walls, which is formed by several fairing portions attached together.

10. The rear fairing according to claim 9 , wherein a first fairing portion has a connection end setback inwardly of the first fairing portion and superimposed inside a second fairing portion.

11. The rear fairing according to claim 1 , wherein the aerodynamic surfaces include an acoustic processing.

12. The rear fairing according to claim 1 , wherein the preforms are woven of aluminum oxide fibers, aluminosilicates fibers, silicon carbide fibers, carbon fibers, or combinations thereof.

13. A turbojet engine nacelle for an aircraft, the turbojet engine nacelle comprising a rear fairing according to claim 1 covering a base of a pylon for connection with an aircraft.

14. A rear fairing for a pylon holding an aircraft turbojet engine and forming an aerodynamic surface covering a base of the pylon, the rear fairing extending in a longitudinal direction and comprising:
a floor facing a hot gas exiting the turbojet engine;
lateral walls extending to the floor, the lateral walls forming aerodynamic surfaces directing a cold air flow; and
a Y-shaped section including a leg extending from the floor and the lateral walls, the leg defining an edge turned outwards and configured to separate flow of the hot gas from the cold air flow,

wherein the floor and the lateral walls include ceramic matrix composite materials made from preforms formed of superimposed layers of warp or weft threads, the preforms having inter-layer weaving threads connecting the superimposed layers to each other.

Assignees

• Safran Nacelles

Inventors

• Desjoyeaux Bertrand
• Sentis Sylvain
• Delehouze Arnaud
• Taillard François

Classifications

• D03D1/00

  Woven fabrics designed to make specified articles · CPC title

• D03D15/275

  Carbon fibres · CPC title

• C04B2235/5244

  Silicon carbide · CPC title

• D10B2101/08

  Ceramic · CPC title

• D10B2505/02

  Reinforcing materials; Prepregs · CPC title