Jet engine comprising a nacelle equipped with reverser flaps provided with vortex-generating means

Patent metadata

Field	Value
Publication number	US-11215141-B2
Application number	US-201916431173-A
Country	US
Kind code	B2
Filing date	Jun 4, 2019
Priority date	Jun 26, 2018
Publication date	Jan 4, 2022
Grant date	Jan 4, 2022

Abstract

A turbofan comprising a motor and a nacelle, surrounding the motor, where a duct for a bypass flow is delimited between the nacelle and the motor and in which a flow of air flows. The nacelle comprises reverser flaps where each one is articulated between a stowed position in which it is not in the bypass duct and a deployed position in which it is across the bypass duct. The turbofan has at least one reverser flap with at least one leakage window configured to allow airflow in the deployed position. The at least one reverser flap has at least one fin extending across the leakage window.

First claim

The invention claimed is:

1. A turbofan comprising:
a motor and a nacelle, surrounding the motor,
wherein a duct for a bypass flow is delimited between the nacelle and the motor and in which a flow of air flows,
the nacelle comprising reverser flaps where each reverser flap is articulated between a stowed position in which the reverser flap is not positioned in the bypass duct and a deployed position in which the reverser flap extends across the bypass duct,
at least one reverser flap of the reverser flaps has at least one leakage window configured to allow airflow in the deployed position, and
wherein said at least one reverser flap has at least one fin extending across said at least one leakage window,
wherein the at least one leakage window comprises a hole passing through said at least one reverser flap, and
wherein the at least one fin has a form of a first plane and a second plane continuing from the first plane,
wherein the first plane is perpendicular to a plane of the at least one reverser flap and is bounded by forward-facing and rearward-facing perforated faces of the at least one reverser flap, and
wherein the second plane is inclined with respect to the plane of the at least one reverser flap and extends from and beyond the rearward-facing perforated face of the at least one reverser flap.

2. The turbofan according to claim 1 , wherein the at least one leakage window is formed as a notch which passes through said at least one reverser flap at a downstream edge of the at least one reverser flap.

3. The turbofan according to claim 1 , wherein the at least one leakage window is formed by a hole which passes through said at least one reverser flap at a central position of the at least one reverser flap.

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

Assignees

• Airbus Operations Sas

Inventors

• Gardes Pascal
• Ridray Frédéric
• Czapla Lionel

Classifications

• F02K1/763

  with actuating systems or actuating devices; Arrangement of actuators for thrust reversers · CPC title

• F05D2240/14

  Casings or housings protecting or supporting assemblies within · 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

• F02K1/70 Primary

  using thrust reverser flaps or doors mounted on the fan housing · CPC title

• F02K1/76

  Control or regulation of thrust reversers · CPC title