Abstract
The 3D flow filling process of LOX (Liquid Oxygen) dome is studied in a liquid oxygen/methane rocket engine. The volume, flow field pressure and velocity distributions of liquid oxygen at different time are determined. The flow property of propellant and the injection characteristic time of liquid oxygen are obtained. The results show that when the LOX dome has not been filled, the LOX flow state is disorder, and flows around the annular wall in the middle dome. The static pressure near the equalizing orifice near the liquid oxygen inlet is high and the velocity is slow. When the LOX filling is completed, the pressure at the outlet of each equalizing orifice is the same. The liquid oxygen flow is in a stable state, and the flow rate decreases. The overall velocity distribution is more uniform. In addition, in the filling process of LOX dome, the time of arrival in each area is different. There are different injection delays in each area on the injection panel, and the time of arrival of liquid oxygen in the opposite area of the inlet section of LOX dome is the latest. This result leads to the inhomogeneity of injection characteristic time and flow rate in thrust chamber.
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