Computational Characterization of Aeroengine Combustor/Augmentor Fuel Injectors

The work proposed for this project arises from the need for modeling a realistic fuel atomization process in a complex combustor/augmentor fuel injector. In a real gas turbine combustor or augmentor, the injected liquid fuel undergo atomization for fast evaporation, mixing and combustion. Furthermore, this atomization process occurs in the spatial regions adjacent to solid walls. Experimental studies have been limited to either simple injector geometries, or to far field measurements, after most of the atomization has occurred. Thus this project aims to study the computational characteristics of geometrically complex aeroengine combustor/augmentor fuel injector under realistic operating conditions. The overall objective of this project is to develop a computational tool capable of predicting the atomization of liquid injected trough geometrically complex injectors under realistic operating conditions. The approach will be integrating the Refined Level Set Grid (RLSG) method with the Cascade"s unstructured flow solver. The simulation results will then be validated with parallel experiments. The computational code development is performed by Cascade in collaboration with Dr. Marcus Herrmann, whereas Cascade's OEM partner, United Technologies Research Center (UTRC), will assist in validation with experimental conditions and results.