Combustor design and analysis using the ROCket Combustor Interactive Design (ROCCID) MethodologyThe ROCket Combustor Interactive Design (ROCCID) Methodology is a newly developed, interactive computer code for the design and analysis of a liquid propellant rocket combustion chamber. The application of ROCCID to design a liquid rocket combustion chamber is illustrated. Designs for a 50,000 lbf thrust and 1250 psi chamber pressure combustor using liquid oxygen (LOX)RP-1 propellants are developed and evaluated. Tradeoffs between key design parameters affecting combustor performance and stability are examined. Predicted performance and combustion stability margin for these designs are provided as a function of the combustor operating mixture ratio and chamber pressure.
Document ID
19900058639
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Klem, Mark D. (NASA Lewis Research Center Cleveland, OH, United States)
Pieper, Jerry L. (NASA Lewis Research Center Cleveland, OH, United States)
Walker, Richard E. (Aerojet TechSystems Sacramento, CA, United States)