Abstract
The numerical calculation of three-dimensional unsteady combustion for the combustion chamber of LOX/kerosene high pressure staged combustion rocket engine was carried out. By changing the offset ratio of oxygen mass flow rate in the edge area of the injector face, computational studies were conducted to investigate the effects of non-uniform distribution of oxidizer flow on combustion instability for a liquid-propellant rocket engine. The calculation results show that the offset ratio of oxygen mass flow rate changes the distribution of heat release in the combustion chamber. Within a certain range of offset ratio, the non-uniform distribution degree of oxidizer flow enhances the coupling between the pressure and heat release. As a result, it leads to an increase in the pressure oscillation amplitude in the combustion chamber. However, if the offset ratio is too large, the oxygen-fuel ratio will be too small in some regions, which will reduce coupling between the pressure and heat release and increase the damping of combustion instability.
Highlights
Almost every rocket engine in the development process encounters the problem of combustion instability
High frequency combustion instability in liquid propellant rocket engines is widely believed to result from a coupling of the complex and dynamic processes of injection, atomization, vaporization, mixing, and chemical reaction with a characteristic response of the gas dynamics in the combustion chamber [1]
It is considered that the combustion instability occurs when the pressure oscillation amplitude in the combustion chamber exceeds 10% of the average pressure [11]
Summary
Almost every rocket engine in the development process encounters the problem of combustion instability. High frequency combustion instability in liquid propellant rocket engines is widely believed to result from a coupling of the complex and dynamic processes of injection, atomization, vaporization, mixing, and chemical reaction with a characteristic response of the gas dynamics in the combustion chamber [1]. Understanding and predicting high-frequency combustion instability in liquid-propellant rocket engine continues to pose significant challenges due to the highly complex and nonlinear nature of turbulent combustion processes. It is of great practical significance to analyse the combustion instability of the LOX/kerosene staged combustion cycle rocket engine. Computational studies were conducted to investigate the effects of non-uniform distribution of oxygen mass flow on combustion instability for the LOX/kerosene high pressure staged combustion rocket engine
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