The invention relates to rocket engine manufacturing, and may also be used in aircraft engine manufacturing.
A chamber comprises a casing, ignition means and a mixing head. The mixing head consists of an internal injector face, a middle bottom, an external bottom. Bipropellant injectors are fixed in the internal injector face and the middle bottom. A portion of the bipropellant injectors are mounted projecting from the internal injector face, while another portion are recessed in the internal injector face. The ignition means are made from jet injectors mounted in a structural casing behind the internal injector face. Axes of diverging ports of jet injectors are positioned at an acute angle to an outlet from the structural casing and deflected in a circle in a lateral plane from the longitudinal axis of the structural casing in an identical direction.
The chamber casing comprises a combustion chamber and a nozzle, made from an external structural envelope and an internal fire wall. A regenerative cooling passage is positioned between the external structural envelope and the internal fire wall. A ring-like slot of a gas-screen belt is made in the internal fire wall before the nozzle throat. The regenerative cooling passage of the chamber is made with a branched inlet. One of its branches communicates with the space of the chamber regenerative cooling passage between the nozzle throat and its scarf, a second branch - with the space of the chamber regenerative cooling passage before the nozzle throat, and a third - with the space of the chamber regenerative cooling passage before the ring-like slot of the gas-screen belt.