Systematic Studies on Reusable Staged-Combustion Rocket Engine SLME for European Applications

Abstract

The full-flow staged combustion cycle rocket engine with a moderate 15 to 17 MPa range in nominal chamber pressure called SpaceLiner Main Engine (SLME) has been under investigation since several years. The baseline propulsion system for the reusable rocket-based multiple-mission launcher concept SpaceLiner is also used as a reference for closed cycle LOX-LH2-engines in several studies of future European RLV. A summary of these potential future applications and interesting regions of nozzle expansion ratios for 1st stage RLV or 2nd stages are presented. After completing the Mission Requirements Review, the SpaceLiner Main Engine (SLME) component definition is progressing at Phase A conceptual design level. Refinements are focusing on the turbo-machinery designed as an integrated power-head. The commercial AxSTREAM® software tool for turbomachinery analyses has been implemented. Consolidated size, mass, and performance data are available by this analysis and are integrated in the engine model. Further, the fuel-rich and the oxidizer-rich pre-burner have been investigated in a first series of numerical CFD-simulations.