1. Shuttle Main Engine LOX System (typical of 3)
Oxidizer heat
exchanger
Liquid oxygen fuel tank
P = 100 psia
P = 422 psia
P = 4300 psia
P = 7420 psia
Preburner
Main combustion
chamber
Low pressure
oxidizer turbopump
(5150 RPM)
High pressure
oxidizer turbopump
(28,120 RPM)
Preburner pump
Main nozzle

2. Shuttle Main Engine Fuel (H2) System (typical of 3)
Liquid hydrogen fuel tank
P = 30 psia
P = 276 psia
P = 6515 psia
Hot gas manifold
Preburner
Main combustion
chamber
Low pressure
fuel turbopump
(16,185 RPM)
High pressure
fuel turbopump
(35,360 RPM)
Main nozzle