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This study presented the numerical simulation of the tangential combustion instability in a hypergolic liquid bipropellant rocket thrust chamber, which applied fuel liquid film cooling method and unlike impinging injectors. The liquid spray was modeled using Lagrangian approach, while the gas was regarded as Euler phase. Stress-blended eddy simulation and finite rate/eddy–dissipation model were adopted to simulate the turbulent combustion process. Consistent with the experiment results, this work successfully simulated the transformation of tangential combustion instability from standing mode to spinning mode. The mean pressure, amplitude and frequency of limit cycle oscillation were in good agreement with the experiment. There was a detailed analysis about the flow field, Rayleigh index, and driving mechanism of the combustion instability. It was found that the oscillation began with hot spots of heat release rate due to the interaction between the spray of impinging injectors and cooling fuel jet. More than that, cooling fuel jet also contributed to drive the oscillation. In the standing mode, injectors in the inner and outer rings drive the oscillation together, while the spinning mode is mainly driven by injectors in the outer ring. The pressure wave is subsonic and its Mach number is close to 1. It was shown that the pressure wave contained a complex structure divided into three parts. This led to the in-phase of the pressure along the axial direction and the double-peak characteristic of the downstream pressure signal. Besides, a positive feedback closed-loop system associated with periodic oxidizer/fuel ratio was believed to sustain the combustion instability. The oscillation can be maintained when pressure, heat release and oxidizer/fuel ratio are coupled together. The analysis results indicate that rotating detonation is an implication to tangential combustion instability. [ABSTRACT FROM AUTHOR]

A numerical simulation is conducted to characterize the atomization process of like-doublet injector with two different impingement angles. Using thecoupled Level-Set/Volume-of-Fluid (CLSVOF) method for capturing the liquid/gas interfaces, liquid sheet characteristics were efficiently captured, and the simulations were found to agree well with experiment results for both breakup characteristics and Sauter Mean Diameter (D 32 ). This method combines the mass conservation properties of the volume-of-fluid method with the accurate surface reconstruction properties of the Level-Set method for a 3D atomization process simulation of the like-doublet injector. Since the velocity profiles around the stagnation point and impingement point greatly affects the sheet characteristics, the velocity profiles of different axial locations on the cross section for two different impingement angles cases are studied. It shows that the velocity difference caused by the impact of liquid jets is one of the important factors which directly affect the formation of surface wave and the breakup of sheet [ABSTRACT FROM AUTHOR]