Turbojet-engine thrust reverser with scoop-doors of adjustable exhaust cross-section
Number of patents in Portfolio can not be more than 2000
United States of America Patent
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-
Dec 12, 2000
Grant Date -
N/A
app pub date -
Jun 16, 1999
filing date -
Jun 18, 1998
priority date (Note) -
Expired
status (Latency Note)
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Abstract
A bypass turbojet-engine thrust reverser comprises at least one hollow, pivoting door (3) with an inner conduit (10), defined between an outer structure (4) of the door (3) and an inner structure (5) of the door (3), which guides flow through the door (3) when the door (3) is in a reverse thrust position. At least a downstream part of the outer structure (4) of the door (3) is independent of and displaceable relative to the inner structure (5) of the door (3) and is driven in a centrifugal direction relative to the inner structure (5) by a mechanical drive system such that a downstream exhaust cross-section (S2) of the inner conduit (10), which is less than an intake cross-section (S1) of the inner conduit (10) when the door (3) is in a forward thrust position, is at least equal to the intake cross-section (S1) when the door (3) is in the reverse thrust position.
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