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Aircraft Engine Combustor Simulation
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Recirculation Flow in an Aircraft Engine Combustor Simulation and visualization: Anthony C. Iannetti, NASA Glenn Research Center.
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The Low NOx Combustion team was awarded a Turning Goals Into Reality
Award for demonstrating a total NOx emissions reduction of 50% from the 1996
International Civil Aviation Organization standards for large and
regional size subsonic engines. New engines with this technology are expected to
start entering into service in the year 2002. The final goal is to reduce
the NOx emissions by a factor of 3 (or 70% reduction) from 1996 levels.
Lean Direct Injection (LDI) is a promising new concept for gas turbine
engine combustors which should reduce undesirable NOx emmissions by
50% to 70%. The NASA Glenn Research Center's Immersive Physics demo at
SC2000 will show, in 3D, the co-rotating discrete jet swirler of the combustor.
This jet swirler induces swirl by arrays of angled holes. The stream
tubes in the 3D environment will show the complex flow in the swirler flow
recirculation zones. The size of these zones is critical to the amount of
NOx produced, and the efficiency of the combustion process. This work is
part of the National Combustor Code, a joint NASA/industry effort to
develop an integrated system of computer codes for the design and
analysis of combustion systems.
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