File:Ssme schematic.svg

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Summary

Description
English: A functional diagram showing the flow of propellant through an RS-25 engine. Very high flow rates are needed in the main combustion chamber, so the energy to achieve this is generated in upstream combustion "pre-burner" chambers that generate a partial burn to drive the high pressure turbopumps on both the fuel and oxidizer sides. Pressure feeding the preburners is maintained by the low-pressure turbopumps. Routing fuel through the nozzle serves to both cool the nozzle as well as pre-heat the fuel.
Date
Source Main Propulsion System (MPS) (PDF). Shuttle Press Kit.com. Boeing, NASA & United Space Alliance (6 October 1998). Retrieved on 7 December 2011.
Author Jkwchui
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Date/TimeThumbnailDimensionsUserComment
current05:44, 24 December 2011Thumbnail for version as of 05:44, 24 December 2011800 × 571 (139 KB)wikimediacommons>Jkwchui(i) fixes lines in upper left; cleaned up lines (ii) added combustion zone to legend
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