Turbopumps for Gas Generator and Staged Combustion Cycle Rocket Engines

Abstract

The need to increase the engine specific impulse, lead design engineers to start development of closed cycle engines where gas is combusted in the main combustion chamber after passing through the Main Turbopump Assembly turbine. Trade-off study analysis for turbopumps of different cycles engines was performed for RD-0110 and RD-0124 LOX-kerosene engines, which have the same thrust range. The analysis included comparison of the parameters, design approaches, turbopumps design and development features for gas generator and stage combustion cycle engines.