Thrust reverser for a turbojet engine nacelle, comprising cascades partially integrated in the cowls
First Claim
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1. A thrust reverser for a turbojet engine nacelle, comprising:
- an actuation system; and
movable cowls configured to move backward relative to a front frame under an action of the actuation system, thereby making flaps tilt, via a control mechanism, so as to close an annular cold air flow path, and by opening cascades which are disposed around the annular cold air flow path and which receive an 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 actuation system is configured to make the cascades move backward along a stroke which is shorter than a stroke of the movable cowls, andwherein each flap is connected to the cascades via a guiding pin and is connected to a corresponding one of the movable cowls via a connecting rod comprising hinges at ends thereof,wherein a rear one of the hinges of the connecting rod is fastened on a support, the support being separate from and movable relative to the corresponding one of the movable cowls in a radial direction, andwherein the support is removably connected to the corresponding one of the movable cowls via a positioning stud which is disposed radially and nests in a corresponding recess.
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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.
11 Citations
13 Claims
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1. A thrust reverser for a turbojet engine nacelle, comprising:
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an actuation system; and movable cowls configured to move backward relative to a front frame under an action of the actuation system, thereby making flaps tilt, via a control mechanism, so as to close an annular cold air flow path, and by opening cascades which are disposed around the annular cold air flow path and which receive an 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 actuation system is 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 and is connected to a corresponding one of the movable cowls via a connecting rod comprising hinges at ends thereof, wherein a rear one of the hinges of the connecting rod is fastened on a support, the support being separate from and movable relative to the corresponding one of the movable cowls in a radial direction, and wherein the support is removably connected to the corresponding one of the movable cowls via a positioning stud which is disposed radially and nests in a corresponding recess. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13)
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Specification