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

Patent metadata

Field	Value
Publication number	US-11220978-B2
Application number	US-201916699890-A
Country	US
Kind code	B2
Filing date	Dec 2, 2019
Priority date	Dec 13, 2018
Publication date	Jan 11, 2022
Grant date	Jan 11, 2022

Abstract

A turbofan having a nacelle comprising a slider mobile in translation between an advanced and a retracted position to open a window between a duct and the exterior, a plurality of blades, each one mobile in rotation on the slider between a stowed and a deployed position, where the blades are split into groups, where each group comprises a first blade, and a maneuvering system moving each blade and comprising a cam integral with the first blade of one of the groups and having a tooth, a groove receiving the tooth, a first transmission system transmitting the movement of the first blade bearing the cam to a first blade of each other group, and, for each group, a second transmission system transmitting the movement of the blade that bears the cam or is moved by the first transmission system to each of the other blades of the group.

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 them, an open window between the duct and an exterior of the nacelle,
a plurality of blades, each one comprising a first end mounted mobile in rotation on the slider about an axis of rotation generally parallel to the longitudinal axis, where each blade is mobile between a stowed position in which the blade is outside the duct and a deployed position in which the blade is across the duct, where said plurality of blades is split into groups, where each group comprises a first blade located furthest downstream, with respect to a direction of flow, compared to other blades of the same group, where, for each group, a blade of rank ‘n’ is located upstream of a blade of rank ‘n−1’ in the direction of flow and is offset angularly about the longitudinal axis with respect to the blade of rank ‘n−1’,
an assembly of actuators causing the slider to move between the advanced position and the retracted position, and vice versa, and
a maneuvering system configured to move each blade from the stowed position to the deployed position and vice versa, where the maneuvering system comprises:
a cam integral with the first blade of one of the groups and having a tooth,
a groove, integral with the fixed structure, which receives the tooth and where, when the mobile assembly moves, the tooth follows the groove and rotates said first blade,
a first transmission system which transmits a movement of the first blade bearing the cam to a first blade of each other group, and
for each group, a second transmission system which transmits the movement of the blade that bears the cam or is moved by the first transmission system to each of the other blades of said group.

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 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 tooth is located when the slider is in the advanced position, and wherein the groove has, at its proximal end, a straight portion parallel to the direction of translation.

4. The turbofan according to claim 1 , wherein the first transmission system comprises, for two first blades of two adjacent groups, a connecting rod mounted articulated between said two first blades, and wherein a point of articulation of the connecting rod to each first blade is off-center with respect to the axis of rotation of the first blade.

5. The turbofan according to claim 1 ,
wherein the second transmission system comprises, for each blade of a group, from the first blade to a penultimate blade, a peg integral with said blade, extending parallel to the longitudinal axis and projecting towards a blade of immediately superior rank, and
wherein the second transmission system comprises, for each blade of a group, from a second blade to a last blade, a groove created in said blade and arranged so as to receive a peg of a blade of immediately inferior rank.

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

Assignees

• Airbus Operations Sas

Inventors

• Gardes Pascal
• Goncalves José
• Sabathier Bastian

Classifications

• Y02T50/60

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

• F01D17/167

  of vanes moving in translation · CPC title

• B64D29/06 Primary

  Attaching of nacelles, fairings or cowlings · 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

• F05D2250/312

  the axes being parallel to each other · CPC title