Pressure Loss Characteristics of the Liquid Oxidizer Supply System for Rocket Engine

Abstract

Pressure loss characteristics of propellant supply system for rocket engine is analyzed in this paper. Gas generator(GG) is part of Gas Generator cycle Air Turbo Ram jet(GG-ATR) engine, which is under development at Muroran Institute of Tech. In order to accurately predict the flow rate for deciding mixing ratio at GG firing tests, it is necessary to calculate various pressure loss in propellant supply system from propellant flow tests. We found it is possible to predict pressure loss at propellant supply system between run tank and turbine flow meter.