The civil aviation sector faces the crucial challenge of decarbonization, with hydrogen emerging as a key energy carrier for the future of sustainable propulsion. Although hydrogen combustion eliminates CO2 emissions, it introduces new criticalities, particularly the management of high flame temperatures which favor the production of nitrogen oxides (NOx). This thesis work aims to design and optimize a hydrogen-fueled annular combustor for a future-generation turbofan engine, with the primary objective of minimizing pollutant emissions while maintaining high operational performance. The developed methodology integrates parametric geometric modeling, high-fidelity Computational Fluid Dynamics (CFD) simulation, and advanced numerical optimization. A hybrid simulation strategy (Decoupled Detailed Chemistry) was defined and validated on the Sandia Hydrogen Flame experimental test case, combining the computational efficiency of the Flamelet model for the thermal field with the accuracy of detailed kinetic modeling for pollutant prediction.