Aircraft turbofan having a cowl articulated in rotation and a system for deploying said cowl

Patent metadata

Field	Value
Publication number	US-2022106927-A1
Application number	US-202117488725-A
Country	US
Kind code	A1
Filing date	Sep 29, 2021
Priority date	Oct 2, 2020
Publication date	Apr 7, 2022
Grant date	—

Abstract

A turbofan having a fixed structure, a fan, a fan casing surrounding the fan, an outer cowl disposed around the fan casing and mounted so as to be articulated on the fixed structure, and a deployment system that moves the outer cowl from a closed position to an open position. The deployment system has a guide rail fastened around the fan casing, a slider that is able to move along the guide rail and has a shoe. An activation system of the deployment system moves the slider and the shoe alternately in one direction or the other along the guide rail. One end of an arm of the deployment system is mounted to be articulated on the shoe and another end is mounted to be articulated on the outer cowl. Such a motorized deployment system makes it possible to save space and mass in the turbofan.

First claim

1 . A turbofan for an aircraft, said turbofan comprising:
a longitudinal axis and having a fixed structure, a fan, a cylindrical fan casing surrounding the fan, at least one outer cowl disposed around the fan casing and mounted so as to be articulated on the fixed structure, and, for each outer cowl of the at least one outer cowl, a deployment system that moves the outer cowl from a closed position to an open position and vice versa, wherein each deployment system has:
a guide rail fastened along a part of a circumference of the fan casing,
a slider movable along the guide rail and having a shoe,
an activation system configured to move the slider and the shoe alternately in one direction or the other along the guide rail, and
an arm, one end of the arm being mounted to be articulated on the shoe and another end of the arm being mounted to be articulated on the outer cowl,
wherein the activation system has, for each slider, a motor that is fixed relative to the guide rail and of which a drive shaft is equipped with a gear and a rack that is realized on the slider and meshes with the gear.

2 . The turbofan according to claim 1 , wherein the guide rail is curved about the longitudinal axis.

3 . The turbofan according to claim 2 , wherein a section of the guide rail is formed as a U that is open towards the outside, a bottom of the U being fastened to the fan casing, and wherein the slider moves between U-walls of the guide rail.

4 . The turbofan according to claim 3 ,
wherein rollers having a groove on their circumference are distributed along each wall of the U constituting the guide rail and are mounted so as to be free to rotate about axes parallel to the longitudinal axis, and wherein the slider has ribs with a shape that is an inverse of that of the grooves of the rollers.

5 . The turbofan according to claim 3 ,
wherein the turbofan has two outer cowls, wherein the two guide rails are extensions of one another in the bottom part of the turbofan, wherein each slider is formed as an arc inscribed in a plane perpendicular to the longitudinal axis, and wherein the two planes are at a distance from one another.

6 . The turbofan according to claim 1 , wherein each outer cowl has a fixed cowl that is mounted in an articulated manner and a mobile cowl that is behind the fixed cowl and is mounted movable in translation on the fixed cowl between an advanced position and a retracted position.

7 . The turbofan according to claim 6 ,
wherein the turbofan has cascades secured to the mobile cowl, and wherein, in the advanced position, the cascades are housed between the fan casing and the fixed cowl and the guide rail is between the fan casing and the cascades.

8 . An aircraft having at least one turbofan according to claim 1 .

Assignees

• Airbus Operations Sas

Inventors

• Vilhes Corentin
• Vanderbauwede Simon
• Gaches Thierry
• Cazeaux Laurent
• Gardes Pascal
• Seguin Guillaume

Classifications

• F01D25/24

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title

• 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

• F02C3/04 Primary

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• B64D29/00

  Power-plant nacelles, fairings or cowlings · CPC title