Computational Analysis of the Thermo Hydrodynamic Characteristics in a Can-Type Gas Turbine Combustor

The present work performs numerical simulations of a can-type gas turbine combustor. The fuel in the present study is taken as methane. The stoichiometric ratios for the correct amount of fuel–air mixture required in the combustor are calculated using a Python program. The number of fuel injector inlets is six, which are symmetric to the center of the combustor. The number of secondary air inlets is kept as four and symmetric to the center. The standard k − ε model is used because of the strong turbulence after the injector nozzle. This is also clearly observed from the findings that as we move along the length of the combustor toward the outlet, the profiles of velocity and static pressure and temperatures become symmetric and more uniform and steadier. Mass fractions of O2 and CH4 increase along the axis, and the overall pressure loss coefficient values reach nearly 5%.