DESIGN OF TURBOJET ENGINE WITH DOUBLED FAN IN FRONT PART Russian patent published in 2009 - IPC F02K3/06 

FIELD: engines and pumps.

SUBSTANCE: three-body double-circuit turbojet engine with high by-pass ratio comprises front fan and back fan in front part of intermediate tray equipped with external profile grate in circuit of secondary flow and internal profile grate in circuit of primary circuit. Fan blades are directed radially outside and reach fan tray, which limits secondary flow circuit outside. Engine also comprises low pressure compressor intended for compression of air coming to primary flow channel. Front and back fans are rotated directly and separately by means of two coaxial shafts. Blades of back fan are installed in secondary flow circuit, starting from disc joined with its driving shaft via back wheel of low pressure compressor movable blades. Low pressure compressor additionally comprises at least one front wheel of movable blades rotated by driving shaft of front fan, and external stator, in opening of which fixed blade grates are installed, which are inserted between wheels of movable blades. External stator is installed on fan tray via the second intermediate tray that comprises the second external profile grate in secondary flow circuit between blades of front fan and blades of back fan and the second internal profile grate in primary flow circuit. In the first intermediate circuit shaft is installed for rotation of back fan on axial thrust bearing together with driving shaft of front fan on intershaft bearing. Additional bearings are installed between intermediate tray and shafts.

EFFECT: reduction of turbine length and weight.

7 cl, 2 dwg