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The paper considers the specifics of gasification, mixing and burnout processes for propellant components in a combustion chamber featuring coaxial bicentrifugal injectors and operating in the liquid/liquid mode employing oxygen and the T-1 and T-6 kerosene types. Numerical simulation revealed that when using the T6 fuel, the structure of recirculation zones appearing in the leading region of the combustion chamber may provide more efficient oxygen and kerosene mixing and burnout as compared to a chamber running on the T-1 fuel

Investigating the Specifics of Work Cycle Evolution in the Combustion Chamber of an Oxygen/Kerosene Liquid Rocket Engine