Combustion Stability Innovations for Liquid Rocket

The proposed effort provides a unified modeling & simulation framework to substantially improve the capability for understanding, analyzing, and predicting the underlying mechanisms dictating the combustion stability characteristics of liquid-propellant rocket engines. Emphasis will be placed on the effects of atomization, mixing, and distributed combustion of liquid oxygen (LOX) and kerosene propellants under conditions representative of oxygen-rich preburner staged-combustion cycle (ORPSC) engines. New models and solution methodologies will be developed and validated, where necessary, to further enhance the solution accuracy and efficiency. The Phase II effort will focus on key elements of a simulation methodology that can capture flow evolution and flame dynamics in rocket engines.