Reflection In Gas Turbine Combustor

1305 Words 6 Pages
When studing liquid fuel combustion in gas turbine combustor, complicated principals including reactive flow, spraying, turbulent flow, multiphase flow, convective and radiative heat transfer and their interactions should be considered. In recent 40 years combustion chambers have continuously improved structurally. Present combustion chambers are generally devided to three main groups: Can type, Can Annular type, and Annular type chambers. Combustion chambers consist of components such as swirler, injector, diffuser, liner, cooling holes, dilution holes and etc.
A gas turbine combustion chamber classically has three zones: primary zone, secondary zone, and dilution zone. In primary zone, which is located between injector and primary jets,
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They considered Methanol chemical details by 23 species and 168 Chemical reactions. Turbulence was modeled by standard k-ԑ. According to this study, the results of flamelet model with improved presumed β-PDF are close to results of transport PDF solution. They expressed that when chemical details are considered in combustion modelling, Pollutants and radicals are calculated better and more accurate.
Lee et al (2006) [7] evaluated the combustion and efficiency of cooling in annular aero gas turbine combustion chamber. In this work, they used SST model, ED combustion model and DO radiation model. In this work, Rozin–Romler distribution with 30 micrometer diameter is used. Their results show that cooling holes are suitable but injection of dilution holes is not appropriate. Improper injection causes the air does not have enough penetration. Thus, unsuitable air covering film is produced and as a result, distribution of exit temperature grow to
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The distinction of this study with previous research, is employing a geometry of combustion chamber model that all components such as swirler, airblast injector, primary and diulution holes are included. In the numerical simulation of reactive two-phase flow of this combustion chamber, the Realizable k-ε turbulence model, steady flamelet combustion model and discrete ordinates radiation model have been used. The spray and atomization of liquid fuel droplet is modeled by an Eulerian–Lagrangian method. The present study is performed for four different cases of air injection that, in the first case, boundary conditions are based on the laboratory conditions [11]. After validation of numerical results for the first case using experimental data, the subsequent cases are studied. The results of the present study, are comparison of velocity and temperature distributions, mass fraction percentage of the carbon dioxide, carbon monoxide and nitrogen oxide concentration at exit plane of combustion chamber for the above-mentioned four reactive flow cases and selection of the optimum

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