| 摘要 |
FIELD: engines; rocket science.SUBSTANCE: invention relates to rocket engineering, namely to the liquid chambers of rocket engines. Liquid-propellant rocket engine comprises a turbopump unit, a gas generator units supply and control chamber with the mixing head comprising an outer, middle and bottom of the fire, the nozzles are fastened together, pins, soldering and welding. Fuel and oxidant nozzles are located in the combustion bottom with the transition in the peripheral portion of the head to circumferentially spaced. Pins are arranged on the circumference in the peripheral zone of the mixing head. Located on the sides of the square in the central part of the mixing head nozzles and injectors, which are for each of the sides of the square in two rays extending from the periphery of the square, are made prominent in the firing chamber cavity of the bottom of the fire, forming anti-pulse partitions. Each nozzle peripheral to firing bottom is a fuel nozzle and located at the intersection of the circle with the specified location pins protruding rays location nozzles. Rays are an extension of the sides of the square and connect it to the top of the peripheral zone of the mixing head. Each pin holds at least three channels connecting the combustion chamber cavity with the cavity formed by the middle and fired bottoms, wherein the output portion of said channel is parallel to the axis of the combustion chamber.EFFECT: invention provides increase of specific impulse and high quality mixing.1 cl, 4 dwg |
