Droplet Motion Analysis in Space Rocket Engine Combustion Chamber Based on Gas Flow Similarity

Abstract

The previous research paid less attention to the similarity characteristics of gas liquid two-phase flow in space rocket engine thrust chamber, and the droplet motion analysis based on gas flow had never been carried out. In this paper, firstly a numerical analysis model about gas flow in thrust chamber is built and the gas flow similarity is deduced, then a dimensionless calculation expression is promoted to describe the gas flow velocity. Secondly, a numerical analysis model about droplet motion in thrust chamber is built, taking the gas flow as input. Lastly, the effects of the combustion length diameter ratio and outlet throat area ratio on the droplet trajectory and velocity are discussed. The analysis method, that is given in this paper and used to investigate into the droplet motion and gas flow in space rocket engine thrust chamber, has certain reference value for space rocket engine test and engineering design.