Preliminary Component Definition of Reusable Staged-Combustion Rocket Engine

Abstract

Full-flow staged combustion cycle rocket engines with a moderate 15 to 17 MPa range in chamber pressure have been selected as the baseline propulsion system of DLR’s visionary fully reusable SpaceLiner concept. 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 and a suitable thrust-chamber lay-out. One key-objective is a light-weight, long-life, low-maintenance architecture. The paper describes the latest status of the SpaceLiner 7 propulsion system: • The reference vehicle’s preliminary design, • Main propulsion feed-and pressurization system definition and architectural lay-out, • Thrust chamber regenerative circuit, • Pre-design of different turbomachinery and attached preburners, Design solutions are traded and compared to other recent high-performance rocket engine developments based on available design data or reassessment.