Thrust reverser having a bypass vane-cascade and fitted with a stationary rear structure
Number of patents in Portfolio can not be more than 2000
United States of America Patent
Stats
-
May 14, 2002
Grant Date -
Aug 2, 2001
app pub date -
Jan 26, 2001
filing date -
Jan 27, 2000
priority date (Note) -
Expired
status (Latency Note)
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Abstract
A thrust reverser for a turbojet engine is provided with at least one displaceable assembly including a displaceable cowling portion and a flap. The displaceable cowling portion and the flap each subtend stationary upstream and downstream cowling portions such that the displaceable cowling portion forms a portion of the external engine cowling covering a reverse thrust opening and the flap forms a portion of the outer boundary of the gas flow in a forward thrust position. In a reverse thrust position, the reverse thrust opening is uncovered, and the displaceable cowling portion and the flap are displaced downstream such that the displaceable cowling portion extends downstream, parallel to the longitudinal engine axis and above, without interference, the downstream cowling portion. The flap engages in rolling contact with a plurality of rolling elements supported by an upstream end of the stationary downstream cowling portion and pivots and so as to block the gas flow duct and redirect the gas flow outward though the vane-cascades.
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