FIELD: engines and pumps.
SUBSTANCE: invention relates to thrusters operating at gaseous hydrogen (H2) and oxygen (O2) as the actuators of control systems for rocket and space equipment. The mixing head has two centrifugal nozzles for supplying fuel and oxidant to the combustion chamber and fuel channels for cooling the wall of the combustion chamber and the nozzle. In order to supply fuel to the combustion chamber, a centrifugal nozzle with a large angle of the flow velocity vector and a coaxial centrifugal oxidant nozzle with a smaller velocity vector angle than the fuel are installed.
EFFECT: increased combustion completeness of gaseous hydrogen and oxygen in the engine.
1 dwg
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