FIELD: rocket technics.
SUBSTANCE: invention relates to rocket engineering. Combustion chamber (CC) of liquid-propellant rocket engine (LPE) comprises housing 10 in the form of body of rotation with vertical generatrix and conjugated with profile 11 with outlet hole 12 in lower part CC, and also means for directed spraying of fuel and oxidizer for preliminary cooling of housing wall. Said means of directed spraying of fuel and oxidizer are made in the form of vortex-forming channels 20, 30 located on external side of wall of housing 10, passing around said housing. Output slots 21, 31 of said vortex-forming channels are tangentially inserted into inner volume of lower part of housing 10 CC in the direction providing vortex spiral motion of fuel and oxidant flows from bottom to top on inner side of said wall.
EFFECT: invention ensures complete combustion of fuel and efficient cooling of CC housing wall with considerable reduction of hydraulic resistance of CC fuel and oxidizer supply circuit.
1 cl, 3 dwg
