System driving the displaceable fairing of a turbojet-engine thrust reverser

  • US 6,592,074 B2
  • Filed: 03/08/2002
  • Issued: 07/15/2003
  • Est. Priority Date: 03/08/2001
  • Status: Active Grant
First Claim
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1. A thrust reverser of a turbojet engine having a stationary internal structure and an external pod supported by a strut extending from an aircraft wing, an internal surface of said pod defining with the stationary internal structure an annular duct through which passes a bypass flow from the turbojet engine, said pod including a stationary portion and at least one fairing movable between a deployed position, wherein said bypass flow of said jet engine is reversed, and a stowed position, said thrust reverser further comprising:

  • a plurality of guides each connected to the stationary portion of the pod and slidably mounted to one of said fairings, the guides arranged to translate the fairing relative to said stationary portion of the pod to thereby define a clearance therebetween when in said deployed position, wherein at least two guides are supported by and positioned along opposed sides of the strut;

    a plurality of drive devices each connected to the stationary portion of the pod and one of the guides, each drive device axially aligned along a central axis of each of said guides to linearly displace the at least one fairing between the deployed and stowed positions;

    a plurality of vane cascades connected to said stationary structure and extending along a portion of said annular duct; and

    at least one flap pivotably connected to said stationary structure and arranged to pivot across said annular duct when said at least one fairing is in said deployed position to thereby obstruct the bypass flow in the annular duct and cooperate with said plurality of cascades to deflect said bypass flow through said clearance.

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