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Combustion dynamics of ten-injector rocket engine using flamelet progress variable
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DOI：10.1016/j.combustflame.2024.113538.png)
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Abstract
En 中文
Combustion instability is investigated computationally for a ten -injector rocket engine using a compressible flamelet progress variable (FPV) model and detached eddy simulation (DES). A C++ code is developed based on OpenFOAM 4.1 to apply the combustion model. Flamelet tables are generated for methane/oxygen combustion at the pressure of 200 bar using a 12 -species chemical mechanism. The flames at this high pressure level have similar structures as those at much lower pressures. A power law is determined to rescale the reaction rate for the progress variable to address the pressure effect. The combustion is also simulated by a one -step -kinetics (OSK) model for comparison with the FPV model. Premixed and diffusion flames are identified locally for both the FPV and OSK models. Study of combustion instability shows that a combined first -longitudinal and firsttangential mode of 3200 Hz is dominant for the FPV model while the OSK model favors a pure first -tangential mode of 2600 Hz. The coupling among pressure oscillation, unsteady transverse flow and helicity fluctuation is discussed. A preliminary study of the resonance in the injectors, which is driven by the acoustic oscillation in the combustion chamber, is also presented.
Keywords:
Combustion instability
Flamelet
Progress variable
Partially premixed flames
Turbulent combustion
Liquid rocket engine
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