Design of a kerosene-oxygen turbopump utilizing a conventional open-cycle system architecture sized to power a 5,000-lbf thrust chamber is described. A conservative design approach tolerant of low performance in return for reduced risk, ease of integration, and lower cost is utilized.
The conventional, single-shaft oxygen-kerosene-turbine arrangement is chosen, allowing substantial use of FASTRAC and F1 prior art, and operating speed is maintained well below the first critical speed.
