ロケットエンジン用推進剤の気液二相流計測に向けたボイド率計の開発

抄録

The use of nitrous oxide as a propellant is one of the most effective options for simplifying and improving the operability of rocket engines for launch vehicles and spacecrafts. On the other hand, when nitrous oxide is supplied with self-pressurization, a gas-liquid two-phase flow with strong unsteady characteristics is formed, and it is difficult to accurately predict the flow characteristics. In this paper, the outline of the newly developed capacitance void fraction meter was reported. The void fraction was successfully measured by calibrating the void fraction meter using the results of the subcooled nitrous oxide flow tests. As a result, in our test condition, it was found that the void fraction of the gas-liquid two-phase flow caused by self-pressurization was 0.2-0.6 and there was a tendency to increase unsteady.