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Abstract Within the context of future aircraft turbine engine development technology, hydrogen has fast become one of the most favored candidates as an alternative fuel due to the possibility of producing extremely low levels of pollutants in particular NOx. The principal component of such an engine technology is the hydrogen micromix combustor which provides a solution to safe hydrogen combustion which avoids auto-ignition and flashbacks by addressing novel methods of hydrogen-air mixing. The current design concepts include a typical injection manifold consisting of multiple concentric arrays of micromix combustors which produce hundreds of miniature low temperature diffusion flames at very low NOx levels. The present paper builds on previous studies of a typical micromix combustor which was evaluated using turbulent chemical interaction models by examining the effects on pollutant levels using laminar diffusion flamelets employing the Flamelet Generated Manifold model. Results for several different combustion kinetic mechanisms obtained with the latter method are compared with those obtained using the more classical turbulent chemical interaction models. The effects of the chosen segregated model for the convective fluxes and the adiabatic boundary conditions are also studied. The above methods are extended to simulations of combustion chamber fluxes at high pressures ranging from 15 to 20 atmospheres which are relevant to the development of future ultra-high bypass ratio engines which are envisaged to come into service around 2050. In line with these future developments, additional micromix combustor geometries are examined.
French et al. (Mon,) studied this question.