TWO-CHAMBER TURBOJET ENGINE (VERSIONS) Russian patent published in 2002 - IPC

FIELD: mechanical engineering; engines. SUBSTANCE: turbojet engine has intake device, compressor, turbine, main combustion chamber arranged between compressor and turbine, and ejector nozzle. Ejector nozzle has primary (inner) nozzle connected with compressor by channel accommodating additional combustion chamber, and secondary (outer) nozzle connected with turbine by channel accommodating reheat combustion chamber. Degree of pressure reduction across turbine is 2-2.5 times less than degree of air compression in compressor: 15-20. According to other design version, pressures in main and additional chambers of two-chamber turbojet engine are equal. Outer nozzle is made supersonic. Exit section of inner nozzle is located in widening part of outer nozzle. EFFECT: decreased specific mass of engine. 3 cl, 7 dwg