Thrust reverser comprising means facilitating the mounting of a membrane for sealing off the secondary flow path

Patent metadata

Field	Value
Publication number	US-12429013-B2
Application number	US-202319111134-A
Country	US
Kind code	B2
Filing date	Sep 8, 2023
Priority date	Sep 20, 2022
Publication date	Sep 30, 2025
Grant date	Sep 30, 2025

Abstract

A thrust reverser including a sealing membrane designed to deflect at least one portion of a secondary flow towards a deflection cascade when a movable structure of the reverser is in the retracted reverse-thrust position, the reverser including a rear frame for supporting the deflection cascade. The reverser further includes an interface device between the sealing membrane and a rear cascade structure including the rear cascade support frame, the vanes located furthest back on the deflection cascade, and a bearing member via which the cascade bears against the rear cascade support frame. Moreover, the device forms an elastic clip mounted around the rear structure, and a rear clip portion whereof is arranged behind the structure.

First claim

The invention claimed is:

1. A thrust reverser for an aircraft propulsion unit, the reverser comprising a fixed structure equipped with a radially internal delimiting wall of a secondary flow path of the propulsion unit through which a secondary flow is intended to pass, the reverser also comprising a movable structure comprising at least one reverser cover equipped with a radially external wall and a radially internal wall forming a radially external delimitation of the secondary flow path, the movable structure being movable in translation with respect to the fixed structure along a longitudinal central axis of the reverser, between a forward direct-thrust position and a retracted reverse-thrust position, the reverser also including a deflection cascade and a sealing membrane to deflect at least one portion of the secondary flow toward the deflection cascade when the movable structure is in the retracted reverse-thrust position, the reverser also including a rear cascade support frame for supporting the deflection cascade,
wherein the reverser includes an interface device between the sealing membrane and a rear cascade structure comprising the rear cascade support frame, the vanes located furthest back on the deflection cascade, and a bearing member via which the cascade bears against the rear cascade support frame, the bearing member projecting behind the vanes located furthest back and also being fastened to the rear cascade support frame,
in that a first end of the sealing membrane is fastened to the interface device via first coupling means,
and wherein the interface device forms an elastic clip mounted around the rear structure, and a rear clip portion of the elastic clip is arranged behind the rear structure.

2. The thrust reverser according to claim 1 , wherein the interface device is equipped with anti-rotation means relative to the rear structure, the anti-rotation means being in contact with the rear cascade support frame and/or the bearing member of the deflection cascade.

3. The thrust reverser according to claim 1 , wherein the elastic clip includes a hook against any one of the following elements:
the rear cascade support frame;
the vanes located furthest back on the cascade; or
a clip latch itself bearing against the vanes located furthest back on the cascade.

4. The thrust reverser according to claim 3 , wherein the hook of the elastic clip is a clamping hook bearing against a front end of the rear cascade support frame, and wherein the elastic clip comprises a rear axial stop bearing against a rear portion of the rear structure, against a rear end of the rear cascade support frame, the clamping hook forcing the rear axial stop forward against the rear portion of the rear structure.

5. The thrust reverser according to claim 4 , wherein the elastic clip includes, between the clamping hook and the rear axial stop, flexible means making it possible, when they are moved to a predefined stress state, to disengage the hook from the rear cascade support frame, the flexible means comprising an axial tab.

6. The thrust reverser according to claim 5 , wherein the elastic clip also includes, at the end of the clamping hook, gripping means making it possible, under stress, to move the flexible means to said predefined stress state.

7. The thrust reverser according to claim 1 , wherein at least one portion of the first coupling means of the membrane is located in front of a rear end of the rear structure.

8. The thrust reverser according to claim 1 , wherein the deflection cascade belongs to the fixed structure of the reverser.

9. An aircraft propulsion unit, comprising a turbine engine and a nacelle including at least one fan cover, and a thrust reverser according to claim 1 .

10. A method for installing a sealing membrane of a thrust reverser according to claim 1 , wherein the sealing membrane comprises the following two steps, carried out in any order:
fastening the first end of the sealing membrane on the interface device, via the first coupling means,
moving the movable structure of the reverser to its retracted reverse-thrust position;
from outside the reverser, clipping the interface device onto the rear structure, and pushing the sealing membrane into the secondary flow path.

Assignees

• Safran Nacelles

Inventors

• Chandelier Julien
• Gonidec Patrick
• Bellet François
• Boileau Patrick André

Classifications

• D06C3/04

  Tentering clips · CPC title

• F05D2300/601

  Fabrics · CPC title

• F05D2260/38

  by a spring, i.e. spring loaded or biased towards a certain position · CPC title

• F05D2260/36

  by a form fit connection, e.g. by interlocking · 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