FIELD: engines and pumps.
SUBSTANCE: invention relates to rocketry and can be used in units of industrial power generators. Liquid-propellant rocket engine mixing head comprises body, oxidiser feed unit, propellant feed unit and nozzles. Said nozzles are arranged inside mixing head in concentric circles and consist of several coaxial sleeves. Said sleeves make ring chambers for gaseous propellant and liquid oxidiser feed. Circular ledge is made at every inner sleeve wit grooves perpendicular to nozzle axis for feed of propellant into appropriate ring chamber and parallel grooves for feed of oxidiser into appropriate chamber. Ring chambers of fuel feed components on combustion chamber side are closed by spacer rings. Fuel feed holes are made in said spacer rings. Note here that all sleeves on side opposite the combustion zone are arranged right against each other.
EFFECT: higher combustion efficiency.
1 dwg
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