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The usage of alternative fuels in aircraft industry plays an important role of current aero engine research and development processes. The micromix burning principle allows a secure and low NO x combustion of gaseous hydrogen. The combustion principle is based on the fluid phenomenon of jet in cross-flow and achieves a significant lowering in NO x-formation by using multiple miniaturized flames. The paper highlights the development and the integration of a combustion chamber, based on the micromix combustion principle, into an Auxiliary Power Unit GTCP 36-300 with regard to the necessary modifications on the gas turbine and on the engine controller.

Development and integration of a scalable low NOx combustion chamber for a hydrogen-fueled aerogas turbine