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Numerical investigation of liquid oxygen filling process in liquid rocket engine by a multi-dimensional co-simulation method

Author

Listed:
  • Liu, Jiaxun
  • Liu, Gangyi
  • Zhou, Wenyuan
  • He, Xueqing
  • Yang, Qingchun
  • Xu, Xu

Abstract

The liquid oxygen filling process in the thermal component downstream of the valve directly affects the starting performance and working reliability of the liquid rocket engine. The filling process is reproduced with a multi-dimensional co-simulation method including one-dimensional system simulation and three-dimensional component simulation, the former provides dynamic flow data for the latter to calculate the filling process. The characteristics of the flow and evaporation and the phenomenon of gaseous oxygen residue are investigated. The results indicate that the simulated pressure value and tendency in the thermal component agree well with the experiment. The flow and evaporation reach a temporary equilibrium due to the flash boiling of the superheated liquid oxygen in the thermal component. The pressure in the combustion chamber downstream of the thermal component plays an important role in breaking the equilibrium and promoting the transition from superheat to supercool state of liquid oxygen. Additionally, the volume proportion of residue gaseous oxygen is 35 % at ignition time, which is far from the ideal state and affects the temperature measurement in the experiment. 26 % of the gaseous oxygen has not been discharged in time, leading to the injection instability in the injection region away from the inlet.

Suggested Citation

  • Liu, Jiaxun & Liu, Gangyi & Zhou, Wenyuan & He, Xueqing & Yang, Qingchun & Xu, Xu, 2024. "Numerical investigation of liquid oxygen filling process in liquid rocket engine by a multi-dimensional co-simulation method," Energy, Elsevier, vol. 308(C).
    • Handle: RePEc:eee:energy:v:308:y:2024:i:c:s0360544224026355
    DOI: 10.1016/j.energy.2024.132861
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