Membrane thrust inverter for an aircraft propulsion unit

Patent metadata

Field	Value
Publication number	US-11401887-B2
Application number	US-202016930524-A
Country	US
Kind code	B2
Filing date	Jul 16, 2020
Priority date	Jan 16, 2018
Publication date	Aug 2, 2022
Grant date	Aug 2, 2022

Abstract

An improved thrust reverser for an aircraft propulsion assembly includes redirection of the air flow for performing the thrust reversal by one or more closure membranes, i.e. by thin and flexible structures deployed across the propulsion assembly. The improved thrust reverser includes at least one closure membrane arranged to deflect at least one portion of the air flow in the direction of the evacuation structure when the thrust reverser is in the reverse jet position and an intermediate structure movable in rotation relative to the fixed structure.

First claim

What is claimed is:

1. A thrust reverser for an aircraft propulsion unit, comprising an evacuation structure comprising one or more openings, a movable structure and a fixed structure, the movable structure and the fixed structure delimiting a flow path capable of channeling an air flow in a longitudinal direction (D 1 ) when the thrust reverser is in a direct jet position, the movable structure being movable between the direct jet position and a reverse jet position providing a radial evacuation of at least one portion of the air flow through the evacuation structure, wherein the thrust reverser comprises at least one closure membrane arranged to deflect at least one portion of the air flow in a direction of the evacuation structure when the thrust reverser is in the reverse jet position and an intermediate structure movable in rotation relative to the fixed structure about an axis coincident with the longitudinal direction (D 1 ), a portion of the at least one closure membrane being fixed to the fixed structure, another portion of the at least one closure membrane being fixed to the intermediate structure.

2. The thrust reverser according to claim 1 , wherein the intermediate structure cooperates with the movable structure so that a displacement of the movable structure from the direct jet position to the reverse jet position drives the intermediate structure in rotation about the axis coincident with the longitudinal direction (D 1 ).

3. The thrust reverser according to claim 2 , comprising a rack system, the intermediate structure cooperating with the movable structure via the rack system.

4. The thrust reverser according to claim 1 , comprising an actuation device arranged to drive the intermediate structure in rotation about the axis coincident with the longitudinal direction (D 1 ).

5. The thrust reverser according to claim 1 , comprising one or more holding elements respectively secured to one or more portions of the at least one closure membrane, the one or more holding elements being movable in translation along a radial direction between a folded position, in which the at least one closure membrane does not close the flow path, and a closure position in which the at least one closure membrane is arranged to deflect the at least one portion of the air flow in the direction of the evacuation structure.

6. An aircraft propulsion unit comprising the thrust reverser according to claim 1 .

Assignees

• Safran Nacelles

Inventors

• Gonidec Patrick
• Kerbler Olivier
• Phi Alexandre
• Rami Jean-Paul
• Tirel Stephane
• Goulard Jean-Baptiste
• Vanderlinden Matthieu
• Carles-Espiteau Arnaud

Classifications

• F05D2250/411

  in rotation · CPC title

• F05D2200/25

  Hyperbolic trigonometric, e.g. sinh, cosh, tanh · CPC title

• F05D2300/501

  Elasticity · CPC title

• F05D2260/53

  using gears · CPC title

• B64D29/06

  Attaching of nacelles, fairings or cowlings · CPC title