FIELD: engines and pumps.
SUBSTANCE: invention relates to the field of low thrust engines (LTEs) operating on gaseous hydrogen (H2) and oxygen (O2) In outer space as executive bodies of control systems for rocket and space equipment. The engine comprises of a spark plug of surface discharge 1, a discharge space 2 of the spark plug, a diaphragm 3, channels 4 that connect the discharge space 2 of the spark plug and the first chamber 5, which receives hydrogen and combustion products flowing out of the diaphragm 3, the second chamber 6, which receives swirling oxygen and gas mixture from the first chamber 5, a centrifugal hydrogen nozzle 8, a centrifugal oxygen nozzle 10. The nozzles 8 and 10 form a two-component centrifugal gas injector. A centrifugal fuel injector 11 for internal cooling of a combustion chamber and a nozzle, the combustion chamber 12, a nozzle entrance 13. All axes of two-component centrifugal gas injectors are located at an angle to the axis of the engine, this angle can be 35-45°.
EFFECT: increased combustion efficiency of gaseous hydrogen and oxygen by preparing a mixture of hydrogen and oxygen capable of burning in the most complete way.
5 cl, 1 dwg
