THRUST REVERSER FOR A TURBOJET ENGINE NACELLE, COMPRISING CASCADES PARTIALLY INTEGRATED IN THE COWLS

• US 20160108852A1
• Filed: 12/22/2015
• Published: 04/21/2016
• Est. Priority Date: 07/01/2013
• Status: Active Grant

• Current Assignee: Aircelle (Safran SA)
• Original Assignee: Aircelle (Safran SA)
• Inventors: CARUEL, Pierre
• Granted Patent: US 10,669,971 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• 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: F16H 2025/2093 using conical gears
• CPC Class Codes: F16H 25/2204 with balls
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A thrust reverser for a turbojet engine nacelle includes movable cowls which move backward relative to a front frame under the action of an actuation system, thereby making flaps tilt, via a control mechanism, so as to substantially close the annular cold air flow path, and by opening cascades disposed around this flow path and which receive the cold air flow and return it forward. When the thrust reverser is closed, the cascades are partially integrated in the cowls, and the thrust reverser includes an actuation system which makes the cascades move backward along a stroke which is shorter than the stroke of the cowl.

Claims

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

movable cowls configured to move backward relative to a front frame under an action of an actuation system, thereby making flaps tilt, via a control mechanism, so as to substantially close an annular cold air flow path, and by opening cascades which are disposed around the annular cold air flow path and which receive the annular cold air flow to be returned forward, the cascades configured to be partially integrated in the movable cowls when the thrust reverser is closed,

wherein the thrust reverser comprises an actuation system configured to make the cascades move backward along a stroke which is shorter than a stroke of the movable cowls, and

wherein each flap is connected to the cascades via a guiding pin.

2. The thrust reverser according to claim 1, wherein each flap is connected to a corresponding movable cowl via a connecting rod comprising hinges at ends thereof.

3. The thrust reverser according to claim 2, wherein the cascades which lie above a flap, include a tab directed radially inward, and wherein the cascades protrude into the annular cold air flow path and are terminated by the guiding pin, a front hinge of the connecting rod being disposed radially outwardly relative to the guiding pin when the thrust reverser is closed.

4. The thrust reverser according to claim 2, wherein a rear hinge of the connecting rod is fastened on a support which is separated from the movable cowl by a radial movement outwardly of the movable cowl.

5. The thrust reverser according to claim 4, wherein the support is connected to the movable cowl via a positioning stud which is disposed radially and nests in a corresponding recess.

6. The thrust reverser according to claim 4, wherein the connection between the support and the movable cowl includes a gliders system sliding radially, and the gliders system maintains holding the support and the movable cowl in contact during opening of the movable cowl.

7. The thrust reverser according to claim 1, wherein the front frame includes sealing gaskets above and below a passage of the cascades, directed rearward, and wherein the sealing gaskets bear against corresponding flat faces which are fastened to the cascades when the thrust reverser is closed.

8. The thrust reverser according to claim 1, wherein the actuation system performs two different strokes of the movable cowls and the cascades, and the two strokes are proportional to each other.

9. The thrust reverser according to claim 8, wherein the actuation system includes two mechanical ball-screw cylinders, which perform two different strokes when driven by a same motorization.

10. The thrust reverser according to claim 9, wherein the actuation system includes a drive shaft which drives two pairs of bevel pinions, each of which rotates a screw of the two mechanical ball-screw cylinders disposed parallel to each other.

11. The thrust reverser according to claim 9, wherein the actuation system includes two concentric mechanical cylinders, comprising a screw which is provided with an external thread and an internal thread formed in a bore, for actuating each cylinder.

12. The thrust reverser according to claim 1, further comprising a motorization configured to drive, via a flexible shaft, several actuation systems distributed along a circumference of the turbojet engine nacelle.

13. A nacelle for a turbojet engine provided with the thrust reverser according to claim 1.