Numerical Study on Combustion Characteristics of Hydrogen Gas Turbine Combustor using Cross flow Micro-mix System

Abstract

In response to the tight regulation of CO2 emissions, studies on gas turbines for aviation based on hydrogen fuel have recently become more important. Especially the Micro-mix combustion method is one of the promising combustion technologies that inherent safety against flash-back and low NOx emission due to a very short residence time of reactants in the flame region. In order to analyze the stability and low NOx emission characteristics of a gas turbine combustion system using hydrogen fuel and micro-mix technology, a series of numerical approach were performed in this study. The results show that, as the supplied fuel flow rate and the diameter of the fuel supply nozzle were increased, a stable hydrogen micro-mix combustion flame was formed.