Comparative analysis of hydrogen-ammonia blends and jet fuel in gas turbine combustors using well-stirred reactor model

This study compares hydrogen, ammonia-hydrogen fuel blends, and Jet-A2 fuel in gas turbine combustors using a well-stirred reactor model and validated MATLAB library, H2ools, to assess flame temperature, pollutant generation, combustion stability, and thermal efficiency. The aim is to address a significant deficiency in existing research, which frequently lacks standardized, turbine-related comparisons among new zero-carbon fuels. Quantitative data indicate that pure hydrogen attains the maximum adiabatic flame temperature (2552 Kelvin), laminar flame speed (7.73 meters per second), and heat generation (9.02 × 10 10 watts per cubic meter), while also demonstrating increased nitrogen oxide emissions (up to 6400 parts per million). Jet-A2 exhibits reduced flame temperatures (2429 Kelvin) and minimal nitrogen oxide emissions (1308 parts per million), whereas a 50% ammonia-hydrogen blend yields the maximum nitrogen oxide output (7022 parts per million) attributable to the nitrogen content in ammonia. Hydrogen generates the minimal nitrogen oxide emissions per unit of energy output—approximately 0.1 grams per kilowatt-hour at a residence time of five milliseconds. This study integrates reactor-level study with a high-fidelity modeling tool, providing insights for combustor design, fuel selection, and emissions control strategies in low-carbon aircraft and power systems.