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

Patent metadata

Field	Value
Publication number	US-11274633-B2
Application number	US-202016839437-A
Country	US
Kind code	B2
Filing date	Apr 3, 2020
Priority date	Apr 9, 2019
Publication date	Mar 15, 2022
Grant date	Mar 15, 2022

Abstract

A turbofan having a nacelle comprising a slider mobile in translation between advanced position and retracted positions to open a window between a duct and the exterior, a plurality of blades, each one being rotatably mobile on the slider between stowed and deployed positions, and a maneuvering system moving each blade and comprising for each blade, a shaft rotatably mobile on the slider and onto which the blade is fixed, for each shaft, a balance beam fixed to the shaft and having first and second ends, for three consecutive balance beams, two connecting rods where the first connecting rod is mounted articulated between the first balance beam and the second balance beam, and where the second connecting rod is mounted articulated between the second balance beam and the third balance beam, and an actuation system rotating one of the connecting rods in one direction and in the other.

First claim

The invention claimed is:

1. A turbofan having a longitudinal axis and comprising an engine core and a nacelle, surrounding the engine core, which comprises a fan casing, in which a duct for a bypass flow is delimited between the nacelle and the engine core 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 blade comprising a first end mounted mobile in rotation on the slider about an axis of rotation and where the blades are gradually offset angularly about the longitudinal axis, where each blade is mobile between a stowed position in which the respective blade is outside the duct and a deployed position in which the respective blade is 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, where the maneuvering system comprises:
for each blade, a shaft mounted mobile in rotation on the slider about the axis of rotation, and onto which the blade is fixed,
for each shaft, a balance beam fixed to the shaft and which has a first end and a second end which are disposed on opposite sides of said shaft,
for a first balance beam of the balance beams, a second balance beam of the balance beams and a third balance beam of the balance beams that are angularly consecutive, two connecting rods where a first rod of the two connecting rods has two ends, one end of which is mounted articulated on the second end of the first balance beam and the other end of which is mounted articulated on the second end of the second balance beam, and where the second rod of the two connecting rods has two ends, one end of which is mounted articulated on the first end of the second balance beam and the other end of which is mounted articulated on the first end of the third balance beam, and
an actuation system which produces rotation of one of the balance beams in two directions.

2. The turbofan according to claim 1 , wherein, for each of the connecting rods, the two ends are symmetrical with respect to the axis of rotation.

3. An aircraft comprising wings and at least one turbofan having a longitudinal axis and comprising an engine core and a nacelle, surrounding the engine core, which comprises a fan casing, in which a duct for a bypass flow is delimited between the nacelle and the engine core 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 blade comprising a first end mounted mobile in rotation on the slider about an axis of rotation and where the blades are gradually offset angularly about the longitudinal axis, where each blade is mobile between a stowed position in which the respective blade is outside the duct and a deployed position in which the respective blade is 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, where the maneuvering system comprises:
for each blade, a shaft mounted mobile in rotation on the slider about the axis of rotation, and onto which the blade is fixed,
for each shaft, a balance beam fixed to the shaft and which has a first end and a second end which are disposed on opposite sides of said shaft,
for a first balance beam of the balance beams, a second balance beam of the balance beams and a third balance beam of the balance beams that are angularly consecutive, two connecting rods where a first rod of the two connecting rods has two ends, one end of which is mounted articulated on the second end of the first balance beam and the other end of which is mounted articulated on the second end of the second balance beam, and where the second rod of the two connecting rods has two ends, one end of which is mounted articulated on the first end of the second balance beam and the other end of which is mounted articulated on the first end of the third balance beam, and
an actuation system which produces rotation of one of the balance beams in two directions.

Assignees

• Airbus Operations Sas

Inventors

• Gardes Pascal
• Sabathier Bastian
• Boudou Antoine

Classifications

• B64D27/18

  within, or attached to, wings · CPC title

• F05D2250/411

  in rotation · CPC title

• F05D2260/50

  Kinematic linkage, i.e. transmission of position · CPC title

• F05D2260/606

  Bypassing the fluid · 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