FIELD: rocketry and space engineering. SUBSTANCE: method consists in delivery of small portion of oxidizing generator gas to high pressure differential multistage turbine and then to supercritical section of nozzle where after-burning reducing boundary layer of gases created in combustion chamber and in nozzle is organized. Main portion of oxidizing gas is directed to low pressure differential turbine and then to combustion chamber through mixing head. Reducing generator gas at low rate may be directed to respective high pressure differential turbine which is then delivered in form of screen to supercritical section of nozzle; screen is formed in section or in sections before section or sections of oxidizing generator gas nozzle inlet. According to one version, oxidizing generator gas may be introduced in area of section of nozzle selected for separation of gas flow from wall for initiation and regulation of separation. Injection of this gas is regulated according to distribution of flow rates among strakes and total flow rate. EFFECT: enhanced thermal efficiency and increased specific impulse. 6 cl, 10 dwg
