| 摘要 |
FIELD: engines and pumps. ^ SUBSTANCE: invention is related to aircraft power generating sets, namely to mixing heads of liquid propellant rocket engine chambers. Mixing head of liquid propellant rocket engine chamber comprising gas duct, oxidant unit, fuel unit with fire bottom, coaxial aligned jet nozzles, which consist of body with tip and bushing that embraces tip with annular gap, installed in units and connecting their cavities to cavity of combustion chamber, channels provided in fire bottom between peripheral nozzles and fire wall of combustion chamber and connecting cavity of fuel unit to cavity of combustion chamber, at that channels are arranged in the form of tubes, inlet part of which is located in fire bottom, and outlet part is located on the same axis with nozzle. Channels are arranged with length of (3-6)D, where D is internal diameter of oxidant tip. Channels are installed between peripheral nozzles, at that inlet part of channel is installed between nozzles, and outlet part is located on the same axis with nozzle. Outlet part of channel is arranged as profiled at the length of at least 2d, where d is internal diameter of tube. ^ EFFECT: more efficient protection of chamber internal wall and reduction of losses related to internal cooling. ^ 4 cl, 4 dwg |
