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The combustion instability is investigated computationally for a ten-injectorrocket engine using the compressible flamelet progress variable (FPV) model anddetached eddy simulation (DES). An C++ code is developed based on OpenFOAM 4.1to apply the combustion model. Flamelet tables are generated for methane/oxygencombustion at the background pressure of 200 bar using a 12-species chemicalmechanism. The flames at this high pressure level are found having similarstructures as those at much lower pressures. A power law is determined torescale the reaction rate for the progress variable to address the pressureeffect. The combustion is also simulated by the one-step-kinetics (OSK) modelfor comparison with the FPV model. Premixed and diffusion flames are identifiedlocally for both the FPV and OSK models. Study of combustion instability showsthat a combined first longitudinal and first tangential mode of 3200 Hz isdominant for the FPV model while the OSK model favors a pure first tangentialmode of 2600 Hz. The coupling among pressure oscillation, unsteady transverseflow and helicity fluctuation is discussed. A preliminary study of theresonance in the injectors, which is driven by the acoustic oscillation in thecombustion chamber, is also presented.

Combustion Dynamics of Ten-injector Rocket Engine Using Flamelet Progress Variable