AIRCRAFT COUNTER ROTATION GAS-TURBINE ENGINE WITH COMPRESSOR WITH HIGH COMMON DEGREE OF PRESSURE RISE Russian patent published in 2007 - IPC F02K3/72 

FIELD: aircraft engineering.

SUBSTANCE: proposed aircraft gas-turbine engine contains high-pressure rotor including high-pressure turbine, low-pressure turbine with inner and outer low-pressure rotors, rotating in opposite direction. Low-pressure turbine includes rotating ring outer drum rotor with possibility of transmission of drive force, connected with first blade rim of fan and with first delivery compressor, and rotating ring inner drum rotor for transmitting drive force, connected with second blade rim of fan and second delivery compressor. First and second delivery compressors are arranged in axial direction between first and second blade rims of fan. Ratio of radius of inlet hub of fan to radius of blade tip is within 0.20 and 0.35. High-pressure compressor is made for providing common degree of pressure rise within 40 and 65. By-pass ratio within 5 and 15. Working degree of pressure rise provided by fan is within 1.4 and 2.5. Sum of working peripheral velocities of tip of fan blade of first and second blade rims of fan is within 1000 and 2500 feet per second.

EFFECT: reduced level of noise, weight, specific fuel consumption and cost.

21 cl, 10 dwg