COMBUSTION CHAMBER OF CLOSED-LOOP LIQUID-PROPELLANT ROCKET ENGINE Russian patent published in 1999 - IPC

FIELD: liquid-propellant rocket engines. SUBSTANCE: combustion chamber includes gas duct head with two bottoms and doublet gas-and-liquid injectors made in form of cylinder of lesser diameter located at inlet and projecting into gas duct and cylinder of larger diameter located at outlet. Central duct of injectors has two rows of tangential orifices for delivery of liquid component which is located in area where lesser diameter changes into larger diameter. Length of mixing chamber is equal to (1.4 to 1.5) of outlet diameter of injector nozzle. Central duct has form of diffuser immediately before tangential orifices. Provision is made in invention for protection of dependences of inlet and outlet diameters of diffuser and parts of injectors projecting into gas duct. EFFECT: enhanced economical efficiency and stability of engine operating process. 4 dwg