THREE-SPOOL BYPASS TURBOJET ENGINE WITH HIGH BYPASS RATIO Russian patent published in 2009 - IPC F02K3/77 

FIELD: engines and pumps.

SUBSTANCE: three-spool bypass turbojet engine with high bypass ratio has front and back fans in front of intermediate body, which represents external bearing grid in flow of the second circuit and internal bearing grid in the main air flow. Fans have blades that stretch in radial direction outside to fan body. Fan body defines external side of the second circuit air flow. Turbojet engine also has low pressure compressor for compression of air coming to channel for the main air flow. Front and back fans rotate in straight direction and separately by means of two coaxial shafts. Low pressure compressor is installed in axial direction between blades of front fan and blades of back fan, and includes at least one ring of rotor blades stretching from periphery of ring, which is actuated by driving shaft of front fan, and at least two grids of stator blades installed in axial direction at every side of rotor blades ring and in radial direction inside grid bearing ring. Ring is supported by external grid, which is located in air flow of the second circuit. External grid is supported by fan body. Stator with alternating pitch is located downwards along the flow from external grid.

EFFECT: provision of acceptable matching of back fan with different speeds of engine.

6 cl, 1 dwg