Plasma Assisted Combustion for Enhanced Gas Turbine Combustor Stability

Plasma Assisted Combustion (PAC) has become an active area of research due to its potential as an electric means to enhance combustion performance and stability. Most published PAC work has involved feasibility demonstrations using laboratory Plasma Generators (PGs) and flames, or modeling work related to kinetics. To apply PAC in a practical combustor such as an aircraft gas turbine combustor, PGs with acceptable Size, Weight and Power (SWaP) characteristics are needed.  In addition, strategies or design rules for applying PGs in practical combustors are needed. In this project, we will move PAC technology from the laboratory towards application in practical military combustors such as gas turbine combustors, rotating detonation engines, or inter-turbine burners. Our approach involves a combination of empirical work utilizing advanced altitude test facilities, with parallel modeling. We propose to evaluate a range of PGs for PAC, considering the relative impact of thermal versus chemical enhancement, and the SWaP cost of a particular approach, including power electronics, relative to the combustion stability and performance benefit. Phase I will primarily involve design, analysis, and modeling, to prepare for PAC rig experiments in Phase II. In addition to developing PG technology for PAC, this program will seek to answer science questions such as: what mechanism (thermal or chemical) is most effective and efficient for PAC; what power electronics are needed to apply PGs in flight; and how should PGs be efficiently and effectively applied in a practical combustor.