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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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    українська
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Public domain This file is in the public domain in the United States because it was solely created by NASA. NASA copyright policy states that "NASA material is not protected by copyright unless noted". (See Template:PD-USGov, NASA copyright policy page or JPL Image Use Policy.)
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21 December 2011

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Date/TimeThumbnailDimensionsUserComment
current04:44, 24 December 2011Thumbnail for version as of 04:44, 24 December 2011800 × 571 (139 KB)Jkwchui(i) fixes lines in upper left; cleaned up lines (ii) added combustion zone to legend
10:33, 23 December 2011Thumbnail for version as of 10:33, 23 December 2011800 × 571 (210 KB)Jkwchui(i) fixed overlapping lines (ii) added rendering (iii) added legend
14:30, 21 December 2011Thumbnail for version as of 14:30, 21 December 2011800 × 600 (31 KB)Jkwchui

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