FLOW EVACUATION SYSTEM FOR AN AIRCRAFT ENGINE
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United States of America Patent
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Issued Date -
Nov 8, 2012
app pub date -
Mar 6, 2012
filing date -
Mar 7, 2011
priority date (Note) -
Abandoned
status (Latency Note)
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Abstract
A flow evacuation system for an aircraft engine including an engine nozzle that conveys the engine exhaust flow and an eductor receiving the engine exhaust flow and engine ventilation flow is disclosed. The engine nozzle has a final section in contact by its outer surface with the ventilation flow. The engine exhaust flow has a low swirl when the engine operates under design conditions and a high swirl when the engine operates out of design conditions. The engine nozzle includes a plurality of local flow conditioners placed in its inner surface in the final section for reducing the swirl of the engine exhaust flow at the exit of the engine nozzle.
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