Thrust reverser comprising movable cascades and a sealing membrane

Patent metadata

Field	Value
Publication number	US-12378930-B2
Application number	US-202318726923-A
Country	US
Kind code	B2
Filing date	Jan 6, 2023
Priority date	Jan 10, 2022
Publication date	Aug 5, 2025
Grant date	Aug 5, 2025

Abstract

A thrust reverser for an aircraft propulsion assembly, including at least one sealing membrane designed to deflect at least one portion of the secondary flow towards a set of cascades when the movable structure of the reverser is in the retracted thrust reversal position, the reverser also including a first flexible hook connecting a first end of the membrane to the fixed structure of the reverser, a second hook connecting a second end of the membrane to the fixed structure or to the movable structure, the second hook being fixed to the radially inner delimiting wall of the secondary vein, or guided by an internal guide fixed to the same radially inner delimiting wall.

First claim

The invention claimed is:

1. A thrust reverser for an aircraft propulsion unit, the thrust reverser comprising a fixed structure fitted with a radially inner delimiting wall of a secondary flow path of the propulsion unit intended to be passed through by a secondary flow, the thrust reverser also comprising a movable structure including at least one reverser cowl and at least one assembly of cascade vanes, said at least one assembly of vanes comprising a plurality of cascade vanes as well as a rear vane support structure to which a rear end of the plurality of cascade vanes is attached, and a front vane support structure to which a front end of the plurality of cascade vanes is attached, the movable structure being movable in translation relative to the fixed structure along a central longitudinal axis of the thrust reverser, between a forward direct thrust position and a rearward reverse thrust position,
wherein the thrust reverser comprises at least one sealing membrane designed to divert at least part of the secondary flow towards said at least one assembly of cascade vanes, when the movable structure is in the rearward reverse thrust position,
the thrust reverser also comprising, associated with said at least one sealing membrane:
first flexible attachment means connecting a first end of the membrane to the fixed structure of the thrust reverser,
second attachment means connecting a second end of the membrane, opposite the first end, to the fixed structure or to the movable structure, the second attachment means being fixed to the radially inner delimiting wall of the secondary flow path, or guided by internal guiding means fixed to said same radially inner delimiting wall,
the assembly formed by the membrane and the first and second attachment means being guided by front guiding means integral with the front vane support structure, and guided by rear guiding means integral with the rear vane support structure,
the thrust reverser being designed such that in the forward direct thrust position of the movable structure, at least part of the sealing membrane extends along the assembly of cascade vanes.

2. The thrust reverser according to claim 1 , wherein in the forward direct thrust position of the movable structure, the thrust reverser also being designed such that during at least part of the movement of the movable structure towards the rearward reverse thrust position, said assembly unfolds with the first flexible attachment means bearing on the front guiding means, and with the sealing membrane bearing on the rear guiding means.

3. The thrust reverser according to claim 1 , wherein the second attachment means comprise connecting rods, a first end of each of which is mounted on the radially inner delimiting wall of the secondary flow path.

4. The thrust reverser according to claim 3 , wherein each connecting rod is designed to move from a position projecting into the secondary flow path, adopted when the movable structure is in its forward direct thrust position, to a position folded back downstream, adopted when the movable structure is in its rearward reverse thrust position, and wherein elastic means push each connecting rod towards its folded back position.

5. The thrust reverser according to claim 1 , wherein the front, rear and internal guiding means comprise at least one roller, and/or at least one rotary cylinder, and/or at least one fixed shaft.

6. The thrust reverser according to claim 1 , wherein a plurality of the sealing membranes are associated with said plurality of cascade vanes, the membranes following one another in a circumferential direction of the thrust reverser.

7. A nacelle for an aircraft propulsion unit, comprising at least one fan cowl, as well as a thrust reverser according to claim 1 .

8. A propulsion unit for an aircraft, comprising a turbomachine and a nacelle according to claim 7 .

Assignees

• Safran Nacelles

Inventors

• Ferrier Gina
• Gonidec Patrick
• Chapelain Loïc
• Ramstein Edouard Marie Gabriel
• Boileau Patrick André

Classifications

• F05D2240/129

  Cascades, i.e. assemblies of similar profiles acting in parallel · CPC title

• F02K1/625

  the aft end of the engine cowling being movable to uncover openings for the reversed flow · CPC title

• F02K1/605

  the aft end of the engine cowling being movable to uncover openings for the reversed flow · CPC title

• F05D2300/50

  Intrinsic material properties or characteristics · CPC title

• F05D2260/50

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