NASA NTRS · 19780010176
Tripropellant engine study
Abstract
Engine performance data, combustion gas thermodynamic properties, and turbine gas parameters were determined for various high power cycle engine configurations derived from the space shuttle main engine that will allow sequential burning of LOX/hydrocarbon and LOX/hydrogen fuels. Both stage combustion and gas generator pump power cycles were considered. Engine concepts were formulated for LOX/RP-1, LOX/CH4, and LOX/C3H8 propellants. Flowrates and operating conditions were established for this initial set of engine systems, and the adaptability of the major components of shuttle main engine was investigated.
Keep this discovery
Explore connections, maps & timelines
Wheeler, D. B.. 1978-02-09. Tripropellant engine study. https://ntrs.nasa.gov/citations/19780010176
Cite the original work for its findings. Save a collection to share your selection of sources.