Date of Award
Master of Science
Department of Aeronautics and Astronautics
Marc D. Polanka, PhD.
Previous research has been conducted showing significant benefits on combustion efficiency and stability by creating high centripetally accelerated, also known as g-loaded, combustion environments. Ultra Compact Combustor systems decrease size and weight of the overall engine by burning in a circumferential direction around a hybrid vane row where the high equivalence ratio cavity flow is quick quenched to lean by the core flow. The hybrid vane row integrates the compressor, combustor, and turbine for further length reduction and weight savings. Fuel and air are brought into the cavity and combusted in a high g-loaded environment driven by air injection at an angle tangent to the cavity outer diameter. The Air Force Research Lab and Air Force Institute of Technology have worked previously on compact combustor designs, and a new, high g-loaded, Ultra Compact Combustor has been designed to study flow characteristics in the cavity and core to help understand integration issues with engine systems.
DTIC Accession Number
Wilson, Jacob D., "Characterizing G-Loading, Swirl Direction and Rayleigh Losses in an Ultra Compact Combustor" (2013). Theses and Dissertations. 847.