COOLANT FLOW SWIRLER FOR A ROCKET ENGINE
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United States of America Patent
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Issued Date -
Oct 30, 2008
app pub date -
Apr 25, 2007
filing date -
Apr 25, 2007
priority date (Note) -
Abandoned
status (Latency Note)
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Abstract
A thrust chamber assembly cooling system includes a twisted ribbon/wire of any one of many variety of cross-sectional shapes located within a nozzle assembly cooling passage to direct the coolant to flow in a swirling manner which induces mixing and breaks up the boundary layer in the coolant passage to enhance the convective heat transfer.
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