Numerical Analysis of An Annular Gas Turbine Combustor

Gandomi, Mohammad Hossein | 2012

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 43415 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Farshchi, Mohammad
  7. Abstract:
  8. The goal of this research is the simulation of the annular combustion chamber of the turbine engine utilized by liquid fuel. The achievement to this goal will lead to create numerical tools for parametric study, analysis and combustion chamber designing.For this reason simple geometry has been considered. This simplicity of geometry causes to facilitate in parametric study and decrease in saving time for modeling and meshing. This combustion chamber is a simplified model of engine CF6. In recent study, the k – ε realizable model has been used for turbulence modeling. For non-adiabatic condition, chemical reaction is dissolved by utilizing probability density function along with laminar flamelet. The fuel consumption is JET-A whose reaction will be simulated thorough mechanism 26 reaction and 17 species. The model of P1 is selected for heat transfer. Fuel spray is also modeled with discrete phase model. parametric study will be accomplished after expanding of numerical tools, equivalent ratio for operational parameter and swirl number for geometry parameter.The results show that in the constant equivalent ratio, the maximum of flame temperature is transferred to upstream in the case of increasing swirl number and the temperature and the products of CO_2, H_2 O are decreased in exit chamber. Increasing of equivalent ratio in the constant swirl number, causes to incline the maximum of flame temperature to the downstream of the chamber and also causes to increase the temperature and CO_2, H_2 O products in chamber exit.
  9. Keywords:
  10. Simulation ; Combustion Chamber ; Parametric Study

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