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Fuel Burnup and Hot-Flow Modeling of Combustion Chambers
[Technical Report, Technical Report]
AIR FORCE SYSTEMS COMMAND WRIGHT-PATTERSON AFB OH
Pagination or Media Count:
To simplify the analysis of the combustion process taking place in gas turbines, it is recommended that the process be broken down into simplified stages. In the combustion of a liquid fuel, the process will consist of the following stages 1 preheating and evaporation of the fuel droplets 2 the mixing of the atomized fuel and its vapor with air and 3 the chemical reaction of the fuel vapor with oxygen. In selecting and comparing thermal loads, it is necessary to consider the burnout coefficient, pressure losses and temperature fields behind the chamber, maximum temperature of the flame tube wall, the combustion stability limits, and the fuel properties.
[A, Approved For Public Release]