Device for cooling the common nozzle of a turbojet pod
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United States of America Patent
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Oct 19, 2004
Grant Date -
Jul 31, 2003
app pub date -
Dec 31, 2002
filing date -
Jan 10, 2002
priority date (Note) -
Expired
status (Latency Note)
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Abstract
The invention relates to a dual flow turbojet comprising an engine of axis X housed completely inside a tubular pod whose inside wall co-operates with the case of said engine to define an annular passage for a secondary flow delivered by a fan, said pod having an air inlet upstream of the engine, thrust-reverser means in its middle section, and a common nozzle for ejecting both the primary flow and the secondary flow, the outlet of the nozzle being situated downstream from the engine, said thrust-reverser means being suitable for taking up an active position in which the secondary flow is diverted outwards and forwards from said pod, said nozzle having an enclosure defined by the inside and outside walls of said nozzle.
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