Nacelle thrust reverser and nacelle equipped with at least one reverser

• US 9,677,502 B2
• Filed: 05/22/2015
• Issued: 06/13/2017
• Est. Priority Date: 12/12/2012
• Status: Active Grant

• Current Assignee: Aircelle Ltd (Safran SA)
• Original Assignee: Aircelle Ltd (Safran SA)
• Inventors: Caruel, Pierre
• Primary Examiner(s): Nguyen, Andrew
• Application Number:
  US14/720,403
• Publication Number:
  US 20150260126A1
• Time in Patent Office: 753 Days
• CPC Class Codes: B64D 29/08 Inspection panels for power plants
• CPC Class Codes: F02K 1/56 Reversing jet main flow
• CPC Class Codes: F02K 1/72 the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
• CPC Class Codes: F02K 1/763 with actuating systems or actuating devices; Arrangement of actuators for thrust reversers
• CPC Class Codes: F05D 2230/72 Maintenance
• CPC Class Codes: F05D 2260/36 by a form fit connection, e.g. by interlocking

Abstract

The present disclosure relates to a turbojet engine nacelle equipped with at least one thrust reverser. The thrust reverser includes: two half-cowls forming an outer cowl which is articulated on hinges and translates between closed and open positions, a first actuator to translationally actuate a downstream frame, a second actuator to rotationally actuate each half-cowl, and a lock capable of locking or unlocking the half-cowls relative to one another. In particular, the thrust reverser includes cascades vanes supported at their upstream end by an upstream frame and at their downstream end by the downstream frame, and a connector between the downstream frame and the external cowl. The cascade vanes are enclosed in a shroud formed by a fan casing and a fan cowl.

Claims

1. A thrust reverser for a nacelle of a turbojet engine, comprising:

at least one outer cowl movable in translation from a closed position toward an open position, said at least one outer cowl made of two half-cowls hinged on hinges;

a first actuator for translationally actuating a downstream frame;

a second actuator for rotatably actuating each of the two half-cowls;

a lock for locking and unlocking the two half-cowls together;

cascade vanes supported at an upstream end thereof by an upstream frame and at a downstream end thereof by the downstream frame, the cascade vanes being enclosed in an envelope formed by a fan casing and a fan cowl; and

a connection between the downstream frame and said at least one outer cowl,

wherein the connection keeps said at least one outer cowl and the downstream frame secured together when actuating the first actuator and wherein, after unlocking the two half-cowls, the connection detaches said at least one outer cowl from the downstream frame when actuating the second actuator so as to provide access to an inside of the nacelle in one single manual unlocking operation.

2. The thrust reverser according to claim 1, wherein the connection comprises a spline secured to the downstream frame or to said at least one outer cowl and a knife respectively secured to the other of said at least one outer cowl or to the downstream frame, the spline and the knife cooperating so as to provide driving thereof during a translational movement and also detachment during a rotational movement of the knife relative to the spline.

3. The thrust reverser according to claim 2, wherein the spline is secured to the downstream frame and the knife is secured to said at least one outer cowl.

4. The thrust reverser according to claim 3, wherein the downstream frame and the spline form a single piece.

5. The thrust reverser according to claim 3, wherein the spline is secured to a junction piece, providing an aerodynamic continuity with a deflection edge of the fan casing.

6. The thrust reverser according to claim 5, wherein the junction piece carries a sealing gasket on an inner face thereof, the sealing gasket being in contact with the deflection edge of the fan casing.

7. The thrust reverser according to claim 6, wherein the sealing gasket includes a hollow tubular portion, enabling crushing of the sealing gasket on a wall of the deflection edge.

8. The thrust reverser according to claim 3, wherein the knife is fixed on an inter-panel frame secured to said at least one outer cowl.

9. The thrust reverser according to claim 1, wherein the second actuator includes opening control cylinders attached to the cascade vanes or to the downstream frame, and to said at least one outer cowl.

10. The thrust reverser according to claim 1, wherein an end of the cascade vanes cooperates with an engine pylon allowing a sliding of the cascade vanes along the engine pylon thereby enabling collaboration with an engine suspension positioned at the cascade vanes.

11. A nacelle for a turbojet engine comprising at least one thrust reverser according to claim 1.