Ignition Modeling for Present and Future Combustors and Augmentors

The ability to predict the ignitibility potential of a combustor at various operating conditions is not practical at this time due to the complexity of this process. Ignition within a gas turbine combustor is dependent on various parameters; including spark (or plasma) energy, flow conditions, fuel/air ratio, and fuel spray density. All these parameters must be properly predicted in order to effectively model the ignition characteristics of a gas turbine combustor. In Phase I, the proof of concept to model ignition kernel growth and flame propagation of a jet fuel surrogate has been demonstrated. The objectives of Phase II can be broken into several developmental areas. First, improve and validate the models, including multi-dimensional turbulent ignition kernel growth models to include plasma ignition sources. Second, develop models for ignition kernel propagation and ignition mapping in combustors. Third, validate the ignition model against gas turbine combustor rig data. The detailed models must be validated in relevant environments in order to transition the technology to DoD programs. Thus, a detailed plan for this validation path must be designed and started.