FIELD: rocketry.
SUBSTANCE: liquid-propellant rocket engine comprising a combustion chamber with fuel injectors, a nozzle passing after the critical section into an expanding part, an insert is installed between the combustion chamber and the nozzle, structurally representing a nozzle, the diameter of the critical section of which is equal to the diameter of the critical section of the nozzle, and the diameter of the exit section of which is equal to the combustion chamber diameter.
EFFECT: increased engine thrust.
1 cl, 1 dwg
