YUGI'S TURBO-ROTOR ENGINE Russian patent published in 2009 - IPC F02C6/02 F02K5/00 F02B53/06 F02B53/08 F01C1/73 

FIELD: engines and pumps.

SUBSTANCE: invention relates to rotor engines and compressors and to aircraft gas turbine engines. The proposed turbo-rotor engine incorporates vane compressor and turbine, rotor compressor and engine made up of two coaxial vane rotors. The compressor and engine rotors are separated by an intermediate wall of outer rotor with cooling component feed and discharge channels. The engine inner rotor shaft bearings support the 1^st stage turbine. The 3^rs stage turbine disk and shaft run in the bearings of the 2^nd stage turbine and those of the fixed support. The disk that links up the 1^st and 3^rd stage turbine blades accommodates the fan vanes in the ring channel. The turbo rotor engine is furnished with a fluid cooling system provided with a pipe brought to the channels of shafts of both rotors. The fire tube features hollow vanes communicating with the double-wall fire tube chamber. Hollow vanes communicate the fire tube chamber with the steam rotor engine inlet manifold. The steam engine exhaust openings communicate with exhaust manifold that communicates, via appropriate channels, with the fan ring chamber. The second pipe is arranged on the manifold, right above the engine exhaust openings. There are a pipe arranged on the fairing, right behind the 1^st-, 2^nd and 3^rd-stage turbines communicating with the 2^nd and 4^th stage turbine shaft chambers, fan blade chambers and rotor engine shaft chamber, and a discharge pipe communicating with the 1^st and 2^nd pipes.

EFFECT: higher specific performances, reliability and longer life.

5 dwg