Detail of the fuel return manifold and the flow vanes of the turbine exhaust manifold.
Fuel flows down two adjacent tubes, cooling the engine wall (known as
"regenerative cooling"). It reaches the fuel
return manifold (the silver ring at the exit plane of the thrust
chamber), where it returned through two "up" tubes, reaching the fuel manifold
and then being injected into
the combustion chamber.
Turbine exhaust flows through the heat
exchanger and then exit through the flow vanes on the aft end
of the turbine exhaust manifold, enter
the double-walled nozzle
extension, and finally enter the main exhaust flow through gaps in the shingles
comprising the nozzle extension inner wall and thus provide film cooling to the
nozzle extension.
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