On the aero-thermal characteristics of gasifier-fuelled gas turbine combustors with complex geometries

摘要: This paper describes the application of a mathematical model to predict aerodynamics, combustion,and NO emission performances gas turbine combustor. The numerical basis is specially constructed code that uses generalised nonorthogonal and boundary conforming coordinate system. component British Coal “Topping Cycle,” coal-fired fluidised-bed-based combined-cycle technology. A distinctive feature this study therefore fuel for produced from partial gasification coal. Since contains nitrogenous species derived fuel-bound nitrogen parent coal, there concern these might give rise high emissions In addition NO, prompt thermal are modelled. aerodynamic combustion combustor, Frame-9 unit, rather unusual found be generally good, with no indication flame stabilisation difficulties only relatively small temperature nonuniformity over exit plane. can traced products manage “skirt round” dilution jet flows. predicted level corresponds remarkably well measured. Most importantly, significant reduction N 2 by NH 3 occurs within primary zone, result Topping Cycle considerably diminished.