The goal of the thesis is to investigate one of the possible solutions in the domain of emissions reduction and the process of decarbonization of aviation industry, by studying different configurations of novel combustors in aero gas turbine engines. In particular, the focus is on hydrogen combustion technology, replacing currently-used fossil fuels. After a consistent literature review on the state-of-art for hydrogen combustion, a hydrogen combustor typology is chosen and a specific geometry assessed for a first-approach study through computational fluid-dynamics simulations using the commercial software ANSYS Fluent. The geometry is placed in micromix combustors category, characterized by two main parts: an initial mixing zone and a combustion zone, with an overall length of seventy millimeters.