Thrust reverser comprising primary latches offset with respect to a plane of symmetry of the movable hood

Patent metadata

Field	Value
Publication number	US-12372047-B2
Application number	US-202017640112-A
Country	US
Kind code	B2
Filing date	Sep 2, 2020
Priority date	Sep 5, 2019
Publication date	Jul 29, 2025
Grant date	Jul 29, 2025

Abstract

A thrust reverser for an aircraft propulsion assembly, this reverser including an outer structure movable between a closed position and an open position of two primary latches configured to lock the movable outer structure in the closed position. The movable outer structure includes an output end that is oblique with respect to the longitudinal central axis so as to orient the thrust laterally. In order to compensate the tilting moment of the movable outer structure, which results from this lateral orientation of the thrust, the primary latches are offset with respect to a median longitudinal plane passing through the longitudinal central axis of the reverser.

First claim

The invention claimed is:

1. A thrust reverser for an aircraft propulsion unit, said reverser comprising:
a movable external structure having a central longitudinal axis, said external structure being movable between a closed position, wherein said external structure is configured to guide a flow of fluid in the propulsion unit so as to generate a thrust, and an open position wherein the movable external structure releases a radial opening configured to evacuate a portion of said flow of fluid from the propulsion unit so as to generate a counter-thrust,
a single actuator configured to move the movable external structure between the closed and open positions, and
first and second primary latches configured to latch the movable external structure in the closed position, wherein
said movable external structure is configured to direct the thrust-generating flow of fluid in an oblique direction with respect to the central longitudinal axis in the closed position, towards a first side of a first median longitudinal plane passing through the central longitudinal axis and extending in a vertical direction,
the movable external structure comprises an outlet end defining an oblique transverse plane with respect to the first median longitudinal plane so as to direct the flow of fluid generating the thrust in said oblique direction opposite the actuator so as to generate a force on the movable external structure for tilting the movable external structure around the vertical direction,
the movable external structure is a one-piece annular structure,
the first and second primary latches are both located in a latching plane on said first side of said first median longitudinal plane, the latching plane being parallel to the first median longitudinal plane, and
the actuator is located on a second side of the first median longitudinal plane, the first primary latch being located on one side of a second median longitudinal plane perpendicular to the first median longitudinal plane and extending laterally, the second primary latch being located on a second side of said second median longitudinal plane.

2. The thrust reverser according to claim 1 , wherein each of the first and second primary latches is positioned at an angular distance from the actuator comprised between 100° and 120°.

3. The thrust reverser according to claim 1 , wherein said actuator is configured to perform a movement without assistance from another actuator.

4. The thrust reverser according to claim 1 , wherein the actuator is traversed by the second median longitudinal plane.

5. The aircraft propulsion unit, said propulsion unit comprising the thrust reverser according to claim 1 .

6. The propulsion unit according to claim 5 , said propulsion unit comprising a pylon for attaching said propulsion unit to a fuselage of an aircraft, the pylon comprising a fairing sheltering said actuator.

7. An aircraft comprising at least one propulsion unit according to claim 5 .

8. The thrust reverser according to claim 1 , wherein
the first median longitudinal plane is parallel to a plane passing through a roll axis and a yaw axis of the thrust reverser, and
the central longitudinal axis is the roll axis of the thrust reverser.

9. The thrust reverser according to claim 1 , wherein the actuator includes a cylinder.

Assignees

• Safran Nacelles

Inventors

• Caruel Pierre Charles
• Charliac Fabien
• Bravin Fabien
• Chapelain Loïc

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F02K1/52

  Nozzles specially constructed for positioning adjacent to another nozzle or to a fixed member, e.g. fairing · CPC title

• F02K1/006

  within one plane only · CPC title

• F02K1/766 Primary

  with blocking systems or locking devices; Arrangement of locking devices for thrust reversers · 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