TURBO MACHINE, CONTAINING PLURALITY OF RADIAL BLADES, FIXED UPSTREAM FROM FAN Russian patent published in 2017 - IPC F01D17/16 F02K3/04 F04D29/56 

FIELD: machine engineering.

SUBSTANCE: double-circuit turbojet engine (1), in particular for an aircraft in which air streams are circulated downstream, at that the turbo machine (1) extending axially and comprising an inner body (11), an intercircuit body (12) and an outer body (13). They limit the primary circuit (V1) between the intercircuit body (12) and the inner body (11) and the secondary circuit (V2) between the intercircuit body (12) and the outer body (13). The rotary shaft (BP) includes an upstream movable fan (2) which comprises radial blades (20) having a free end opposite the outer body (13) of the turbo machine in such a way that compresses the air flow in at least secondary circuit (V2). A plurality of radial stator blades (5) with a variable installation angle are fixed upstream of the movable fan (2), so that the axial free air (F) is deflected before it is straightened by the movable fan (2) in the secondary circuit (V2). The engine (1) has no stator blades in the secondary circuit (V2) downstream from the moving fan.

EFFECT: reduced consumption, reduced weight, limited impact of sound vibrations.

10 cl, 11 dwg