ROCKET ENGINE (VERSIONS), ROTOR FOR ROCKET ENGINE (VERSIONS), METHOD OF EXECUTION OF WORKING PROCESSES IN ROCKET ENGINE (VERSIONS) AND METHOD OF COOLING OF ROCKET ENGINE Russian patent published in 2004 - IPC

FIELD: rocketry.

SUBSTANCE: proposed rocket engine contains first and second rotary nozzles for injection of propellant and oxidizing components of rocket propellant into first combustion chamber. Flow coming out of first combustion chamber sets into operation turbine which rotates the nozzles. Mixture of propellant in first combustion chamber is enriched with propellant to reduce temperature in combustion chamber. Getting out flow enriched with propellant is mixed in second combustion chamber with additional oxidizer injected by third rotary nozzle with creating of high temperature outgoing flow capable of providing engine thrust. To close transmission of relatively high pressure in combustion chamber into channels to deliver propellant under low pressure, rotary nozzles are provided with centrifugal hydraulic gates. Part of rich flow outgoing from first combustion chamber is directed through ring channels enclosing combustion chambers for effusive cooling of surfaces of second combustion chamber.

EFFECT: simplified design, improved reliability of proposed devices.

60 cl, 7 dwg