Unified Low-Risk Single-Shaft Turbopump For Cryogenic Expander-Cycle Rocket Engines

This paper discusses a liquid rocket engine Single Shaft Turbopump (SSTP) developed jointly by Konstruktorskoe Buro Khimavtomatiky (KBKhA, Russia) and Pratt & Whitney Rocketdyne (PWR, USA) for an upper stage expander-cycle cryogenic engines. The SSTP developed may be used for multiple applications including in the RL10 engine for the Atlas V and Delta IV launch vehicles and in RL10 modifications providing thrust in the range of 50 156 kN (11 – 35 Klbf). With minimal modification, this SSTP is also capable of supporting the evolution of emerging methane architecture development. This paper discusses the SSTP final development,