Abstract
In the present work, results of attempts to capture the high-frequency combustion instability in a rocket combustor equipped with hydrogen (H2) / oxygen (O2) injector are shown. To enhance the coupling between heat release rate fluctuations and pressure oscillations, the injector element is installed at the off-center of the combustion chamber in the simulation. Two-dimensional simulations are conducted for a single-element combustor. The flow forcing by modulating the mass flow rate of O2 injection is attempted to excite the first transverse (1T) mode of chamber. The simulation results indicate that the amplitude of 1T mode is increased by the flow forcing. To clarify a driving mechanism for the growth of pressure oscillations, the simulation results are analyzed using the Rayleigh index. Simulations are then extended to three-dimensional LES for a combustor equipped with five shear-coaxial injector elements. The obtained results of pressure field and the Rayleigh index are compared with those of a single element combustor. The effects of multiple flames on the pressure field are examined.
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