The components of this engine are an air intake, constant speed fan, diffuser section, low pressure seal, centrifugal propellant pump assembly, toroidal combustion chamber (TCC), and truncated aerospike ramp.
The idea is to admit air through the constant-speed fan, compress it to over 300 psi, and inject it into the TCC, where it is burned with LH2 and ejected onto the aerospike ramp.
The liquid hydrogen and oxygen are pressurized by rotation of the engine. The incoming subsonic air is pressurized by a diffuser section, and supersonic ram air is pressurized by ram air pressure.
The purpose of the diffuser section is to slow down and increase the pressure of ambient air prior to injection in the TCC. This will also raise its temperature, which will increase the combustion temperature and pressure, thus increasing the engine power.
The variable-pitch vanes in the constant-speed fan are necessary to minimize the drag of incoming air and increase the efficiency of the fan. This is the same idea as a constant-speed prop on some airplanes.
LH2 and LOX are delivered through "spokes" in the centrifugal propellant pump assembly. Air is delivered through an annular section containing a diffuser to slow down and pressurize the air. The air intake admits air at all speeds, from zero (Harrier-type takeoff and landing) to Mach 25.
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