Blocker door for an aircraft thrust reverser

Patent metadata

Field	Value
Publication number	US-12595068-B2
Application number	US-202318873392-A
Country	US
Kind code	B2
Filing date	Jun 20, 2023
Priority date	Jun 22, 2022
Publication date	Apr 7, 2026
Grant date	Apr 7, 2026

Abstract

A blocker door for a thrust reverser includes: a structural frame which is configured to ensure the mechanical strength of the blocker door; an alveolar core; and an acoustically porous resistive skin which is intended to be located on the air flow side. The structural frame covers less than 50% of the surface of the resistive skin and is kept at a distance from the resistive skin. This separation between the structural frame and the resistive skin makes it possible to improve the impact behavior of the blocker door. The resistive skin and the alveolar core preferably form a one-piece subassembly into which the structural frame fits. The door may be devoid of a rear skin.

First claim

The invention claimed is:

1 . A blocker door for a thrust reverser, the blocker door comprising:
a structural frame configured to provide the mechanical strength of the blocker door, an alveolar core, an acoustically porous resistive skin intended to be located on the same side as a flow duct through which an air flow passes, wherein: the structural frame covers less than 50% of the surface of the resistive skin the structural frame is held at a distance from the resistive skin, said distance hereinafter being referred to as the decoupling distance.

2 . The blocker door according to claim 1 , wherein the decoupling distance is greater than or equal to 1 mm, preferably greater than or equal to 2 mm, or even greater than or equal to 5 mm.

3 . The blocker door according to claim 1 , wherein the resistive skin is pressed against the alveolar core and is secured thereto, the resistive skin and the alveolar core forming a single-piece subassembly , hereinafter referred to as an aero-acoustic box.

4 . The blocker door according to claim 1 , wherein the alveolar core includes partitions that extend projecting from the resistive skin in a direction, referred to as the radial direction, corresponding to a direction of the thickness of the blocker door.

5 . The blocker door according to claim 4 , wherein:
the structural frame comprises a body portion extending parallel to the resistive skin, and radial fins extending projecting from the body portion in the radial direction, the partitions of the alveolar core have notches for receiving fins of the structural frame, said notches having a bottom located at a distance from the resistive skin which, at every point on the notch, is greater than or equal to the decoupling distance, the structural frame thus fitting in the alveolar frame.

6 . The blocker door according to claim 1 , wherein the structural frame comprises:
two shackles extending projecting in the radial direction of the body portion, a housing provided in the body portion on the opposite side to the resistive skin, said housing receiving a connecting rod attachment, an aperture in said housing for a connecting rod controlling the blocker door to pass through.

7 . The blocker door according to claim 1 , wherein the structural frame and/or the alveolar core comprises, on the opposite side to the resistive skin, a direct-jet door stop.

8 . The blocker door according to claim 7 , wherein the structural frame has a roughly trapezoidal first part comprising:
a downstream plate, in which the housing receiving the connecting rod attachment and the aperture for the connecting rod controlling the blocker door to pass through are provided, two longitudinal ribs, each having a downstream end connected to said downstream plate and an upstream end located in proximity to an upstream edge of the blocker door, the two shackles being formed at the upstream ends of said longitudinal ribs.

9 . The blocker door according to claim 8 , wherein the structural frame also has two tabs on either side of the downstream plate, said tabs each having an end opposite to the downstream plate provided with a door stop in direct-jet mode.

10 . The blocker door according to claim 1 , wherein it has no rear skin.

11 . A nacelle comprising a thrust reverser of the type with screens and sliding cover, wherein the thrust reverser comprises blocker doors according to claim 1 .

Assignees

• Safran Nacelles

Inventors

• Valleroy Laurent Georges
• Desjoyeaux Bertrand Léon Marie
• Bellet François
• Mesmin Mattias
• Preau Mathieu François Eric

Classifications

• B64D2033/0206

  comprising noise reduction means, e.g. acoustic liners · CPC title

• F02K1/827

  Sound absorbing structures or liners · CPC title

• F02K1/625

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

• B64D29/00 Primary

  Power-plant nacelles, fairings or cowlings · 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