FIELD: engines and pumps.
SUBSTANCE: invention relates to rotor engines and compressors, and to aircraft gas turbine engines. The proposed turbo-rotor engine incorporates a compressor and engine, intake and exhaust openings, the 1st, 2nd and 3rd stage turbines. Both compressor and engine is made up of two rotors, one of them being an inner rotor with vanes directed outward, the other one, an outer rotor, features the vanes directed inside. The compressor and engine inner and outer rotors are interconnected. Each engine rotor has two roller couplings, one them provided with a fixed outer collar while the other furnished with outer coupling linked up with the rotor engine output shaft. The outer rotor vanes are furnished with differential valves, while the inner rotor vanes have ball-type slide valves. The axial chamber houses the combustion chamber with a nozzle. The fuel supply pipe with channels to feed fuel and oxidiser to two-component nozzle (with return valve) is arranged inside the turbo compressor shaft with openings linked up, via intensifier, with the rotor engine output shaft. The 1st stage turbine runs in bearings of the inner rotor shaft, right behind the exhaust openings. The 3rd stage turbine disk and shaft run in bearings of the turbo compressor shaft and those of fixed support. The disk coupling the 1st and 3rd stage turbines vanes accommodates the fan vanes in annular channel.
EFFECT: increased specific performances.
4 cl, 7 dwg
