Numerical analysis of a gas turbine combustor fueled by hydrogen in comparison with jet-A fuel

摘要

The interest in alternative fuels has increased in recent years. Because, the conventional fuels have the danger of extinction in the near future and these fuels harm the environment. Therefore, in this study, the availability of hydrogen as an alternative fuel has been investigated in the tubular combustion chamber of a gas turbine engine fueled by jet-A fuel. For this purpose, the combustion characteristics in the combustor of a Rolls-Royce Nene turbojet engine fueled by gas jet-A and hydrogen have been numerically studied at different excess air ratios (EAR) for a given thermal power values. Temperature distributions in the combustor, combustion efficiency, pressure drop and velocity change have been numerically analyzed at 1480 kW (10000 rpm), 2290 kW (11000 rpm) and 2980 kW (12000 rpm) thermal power in the combustion chamber. The RNG k-turbulence and eddy-dissipation combustion models have been used for 2D axisymmetric geometry with swirling flow.