Thrust reverser for an aircraft turbojet engine nacelle

Patent metadata

Field	Value
Publication number	US-10001081-B2
Application number	US-201715706812-A
Country	US
Kind code	B2
Filing date	Sep 18, 2017
Priority date	Mar 17, 2015
Publication date	Jun 19, 2018
Grant date	Jun 19, 2018

Abstract

The present disclosure concerns a thrust reverser for an aircraft turbojet engine nacelle including at least one movable thrust reverser cowling, a means for locking the cowling, an outlet nozzle having a variable cross-section that is arranged in the downstream extension of said cowling and that is movable, and at least one actuator that includes an actuating rod capable of moving the variable nozzle and the movable cowling, remarkable in that the reverser is provided with a passive coupler.

First claim

What is claimed is:

1. A thrust reverser for an aircraft turbojet engine nacelle comprising:
a thrust reverser cowl movable in translation along a direction substantially parallel to a longitudinal axis (A) of the aircraft turbojet engine nacelle, between a direct jet position and a reverse jet position;
an outlet nozzle with a variable section which is arranged in a downstream extension of said cowl and which is movable between at least one reduced ejection section position, one increased ejection section position and one intermediate neutral position;
at least one actuator which comprises a body mounted on a fixed structure of the thrust reverser and an actuating rod, said rod being adapted to drive in displacement the variable section of the nozzle and the movable cowl; and
a passive coupler comprising:
a hollow housing secured to the thrust reverser cowl, and which delimits internally a cavity extending axially generally along an axis (B) of the actuating rod and which is delimited by a radial upstream wall and by a radial downstream wall;
a piston fastened on the actuating rod of the at least one actuator and which is slidably mounted in the housing of the passive coupler by hermetically dividing said cavity into two compartments comprising an upstream compartment located between the upstream wall and the piston and a downstream compartment located between the downstream wall and the piston, each compartment being filled with a fluid; and
a unidirectional flow limiter providing a fluid connection between the two compartments of the housing, said flow limiter limiting a fluid circulation rate in the direction of a fluid flow from the downstream compartment to the upstream compartment, and enabling a free circulation of the fluid in the direction of fluid flow from the upstream compartment to the downstream compartment.

2. The thrust reverser according to claim 1 , wherein, in the reduced ejection section position for the nozzle, the piston is in abutment against the downstream wall of the housing.

3. The thrust reverser according to claim 1 , wherein, in the increased ejection section position for the nozzle, the piston is in abutment against the upstream wall of the housing.

4. The thrust reverser according to claim 1 , wherein the flow limiter comprises a first pipe providing the fluid connection between the two compartments of the housing, a hydraulic device integrating on the first pipe a throttle valve.

5. The thrust reverser according to claim 4 , wherein the throttle valve is adjustable.

6. The thrust reverser according to claim 4 , wherein the flow limiter integrates on the first pipe a pressure regulator.

7. The thrust reverser according to claim 6 , wherein the pressure regulator is placed on the first pipe having its inlet in direct connection with the downstream compartment of the housing and having its outlet in direct connection with the throttle valve.

8. The thrust reverser according to claim 4 , wherein the flow limiter comprises a second pipe in parallel with the first pipe and providing the fluid connection between the two compartments of the housing, said flow limiter integrating on the second pipe a check valve inhibiting the circulation of the fluid in the second pipe in the direction of a fluid flow flowing from the downstream compartment to the upstream compartment.

9. An aircraft turbojet engine nacelle equipped with a thrust reverser according to claim 1 .

Assignees

• Safran Nacelles

Inventors

• Lerouvreur Mathieu
• Denis Rodolphe
• Lanfranchi Florent

Classifications

• F02K1/1261

  of one series of flaps hinged at their upstream ends on a substantially axially movable structure · 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

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F02K1/763

  with actuating systems or actuating devices; Arrangement of actuators for thrust reversers · CPC title

• F02K1/68

  Reversers mounted on the engine housing downstream of the fan exhaust section · CPC title