Specially configured deflection edge thrust reverser for jet engine
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United States of America Patent
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Feb 10, 1998
Grant Date -
N/A
app pub date -
Dec 14, 1995
filing date -
Dec 21, 1994
priority date (Note) -
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Abstract
The reverser includes a partition (28) exhibiting openings (19) and separating the cavity (16) which exists, when the doors (2) are in the closed position, between the front part (7) of the internal panel (11) of the door and the stream of gaseous flow (15) flowing in direct jet mode through the jet pipe CA, thus overcoming the aerodynamic losses which result from the presence of this cavity.
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