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PRODID:-//Microsoft Corporation//Outlook MIMEDIR//EN
VERSION:1.0
BEGIN:VEVENT
DTSTART:20151117T190000Z
DTEND:20151117T195000Z
LOCATION:12AB
DESCRIPTION;ENCODING=QUOTED-PRINTABLE:ABSTRACT: Combustion in large industry gas turbine consists of complicated physics such as turbulence, multi-specie mixing, chemical reaction, and heat transfer.  The combustion process is highly turbulent and unsteady due to the interaction between the turbulence and the combustion.  The better understanding of the unsteady combustion will help to reduce the emission and enhance the durability of the gas turbine.   At the exit of the combustor, the first stage nozzle is critical for the durability of the turbine.  The cooling and hence the heat transfer in the first stage nozzle is of great importance.  In order to predict the heat transfer correctly, the upstream conditions form the combustor is needed.  In the traditional approach, the 2D exit temperature profile is derived from combustor model and used as inlet condition for the nozzle simulation.  However, the combustor exit flow is unsteady and 3 dimensional.  It is desired to model the combustor and first stage nozzle together.  In this study, a complete combustor can and nozzles of GE 9HA gas turbine are modeled using large eddy simulation (LES) method.  The model reveals the intricate details of the turbulent flame structures.  The unsteady flow field and the upstream conditions of the nozzles are studied too.
SUMMARY:System Level Large Eddy Simulation of a Large Gas Turbine Combustor
PRIORITY:3
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