Turbofan comprising a set of rotatable blades for blocking off the bypass flow duct

Patent metadata

Field	Value
Publication number	US-11105297-B2
Application number	US-202016745606-A
Country	US
Kind code	B2
Filing date	Jan 17, 2020
Priority date	Jan 24, 2019
Publication date	Aug 31, 2021
Grant date	Aug 31, 2021

Abstract

A turbofan having a nacelle comprising a slider translatable between an advanced position and a retracted position to open a window between a duct and the exterior, a plurality of blades, each one rotatable on the slider between a stowed position and a deployed position, and a maneuvering system that moves each blade and comprises, for each blade, a shaft rotatable on the slider and on which the blade is fixed, and a toothed sector fixed to the shaft, and a toothed arc rotatable on the slider about a longitudinal axis, where the teeth of the toothed arc mesh with the teeth of each toothed sector, a cam, as one with the toothed arc, and a groove, as one with a fixed structure, which receives the cam and where, when the slider moves, the cam follows the groove and rotates the toothed arc.

First claim

The invention claimed is:

1. A turbofan having a longitudinal axis and comprising a motor and a nacelle, surrounding the motor, which comprises a fan casing, in which a duct for a bypass flow is delimited between the nacelle and the motor and in which a flow of air flows in a flow direction, said nacelle comprising:
a fixed structure fixed to the fan casing,
a mobile assembly having a mobile cowl and a slider, the mobile cowl being fixed to the slider, the slider being mobile in translation, on the fixed structure, in a direction of translation between an advanced position in which the slider is positioned such that the mobile cowl is moved close to the fan casing and a retracted position in which the slider is positioned such that the mobile cowl is moved away from the fan casing so as to define, between the fan casing and the mobile cowl, an open window between the duct and the exterior of the nacelle,
a plurality of blades, each one comprising a first end mounted so as to be mobile in rotation on the slider about an axis of rotation, and where the plurality of blades are angularly offset from one to the next about the longitudinal axis, wherein each blade of the plurality of blades is mobile between a stowed position in which the plurality of blades are outside the duct and a deployed position in which the plurality of blades are across the duct,
an assembly of actuators causing the slider to move between the advanced position and the retracted position, and vice versa, and
a maneuvering system intended to move each blade from the stowed position to the deployed position and vice versa,
wherein the maneuvering system comprises:
for each blade, a shaft mounted so as to be mobile in rotation on the slider about the axis of rotation, and on which each respective blade is fixed,
for each blade, a toothed sector that is fixed to the shaft and is coaxial with the axis of rotation,
a toothed arc that is coaxial with the longitudinal axis, mounted so as to be mobile in rotation on the slider about the longitudinal axis, where the teeth of the toothed arc mesh with the teeth of each toothed sector,
a cam as one with the toothed arc, and
a groove, as one with the fixed structure, which receives the cam and wherein, when the mobile assembly moves, the cam follows the groove and rotates the toothed arc.

2. The turbofan according to claim 1 ,
wherein the mobile cowl comprises a U-shaped profile coaxial with the longitudinal axis and open towards the longitudinal axis,
wherein the plurality of blades are mounted mobile in rotation on the U-shaped profile,
wherein, in the stowed position, each blade is received in the U-shaped profile, and
wherein, in the deployed position, a second end of each blade leaves the U-shaped profile.

3. The turbofan according to claim 1 ,
wherein the groove has a proximal end where the cam is located when the slider is in the advanced position, and
wherein the groove has, at the proximal end, a straight portion parallel to the direction of translation.

4. The turbofan according to claim 1 , wherein the axis of rotation of each blade has an offset angle relative to the longitudinal axis, where the offset angle is large enough to avoid contact between the plurality of blades during movements, and small enough to avoid the blades moving apart from one another in the deployed position.

5. The turbofan according to claim 1 , wherein the maneuvering system comprises a plurality of rollers arranged below the toothed arc, wherein each roller is mounted so as to be mobile in rotation on the slider about an axis that is generally parallel to the longitudinal axis.

6. The turbofan according to claim 1 ,
wherein the maneuvering system comprises a second toothed arc, and
wherein the toothed arc and the second toothed arc move in opposite directions of rotation.

7. An aircraft comprising at least one turbofan according to claim 1 .

Assignees

• Airbus Operations Sas

Inventors

• Gardes Pascal
• Seguin Guillaume
• Tizac Laurent
• Menou Fabien
• Ridray Frédéric
• Orteu Benoit
• Cusset Romain

Classifications

• B64D29/02

  associated with wings · CPC title

• B64D29/06

  Attaching of nacelles, fairings or cowlings · CPC title

• F05D2250/411

  in rotation · CPC title

• F02K1/72 Primary

  the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow · CPC title

• B64D27/18 Primary

  within, or attached to, wings · CPC title