Modeling and Simulation of the Stability of ORSC Main Combustion Chambers

The potential for combustion instability has historically been a hindrance in developing rocket engines, and nearly always represents the major technical risk in engine developments. This proposal addresses innovative approaches toward prediction of liquid rocket engine combustion instability, as well as innovations in full-scale engine stability verification. Specific objectives are to demonstrate modern experimental diagnostics for measuring combustion stability margin in conjunction with a three-level predictive approach comprising classical linear modeling, moderate-fidelity computational fluid dynamics, and high-fidelity hybrid RANS/LES simulations. This companion experimental/computational/analytical approach provides coupling between the experimental results and analyses at multiple levels of validation enabling a validated predictive tool for fullscale analysis. An existing oxidizer-rich preburner rated at 3600 psia is used to generate warm oxidizer for the experimental study of real-scale ORSC main chamber injectors. The final objective is to perform a stability analysis for a notional 250,000 lbf engine and define a protocol for stability verification of the full-scale engine. The end goals are to provide a revolutionary stability prediction methodology for demonstration during the IHPRPT Hydrocarbon Boost Engine project, and to provide the US propulsion community with a stability analysis methodology that takes full advantage of modern tools and commercial software.