Gas turbine engine exhaust nozzle
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United States of America Patent
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Dec 6, 1994
Grant Date -
N/A
app pub date -
Jul 13, 1993
filing date -
Jul 13, 1993
priority date (Note) -
Expired
status (Latency Note)
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Abstract
The spherical portions of two gimbal (18) mounted convergent flaps (26,28) have hub structures (24) of concentric hubs (54,56). A piston (38) within each hub carries an annular seal (36) which is urged into sealing contact with the spherical static structure (10). The hub communicates air to a plenum between the convergent flaps to cool the convergent flaps.
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