TURBOJET ENGINE Russian patent published in 2016 - IPC F02K3/77 F02K3/75 

FIELD: engines.

SUBSTANCE: invention relates to aircraft turbojet engines, including engines for supersonic multi-mode aircraft. In turbojet engine on external side from external circuit channel there is a channel of a third circuit formed at engine inlet by intermediate flanges of fan inlet distributor and outer housing of engine and further downstream by separating flanges of working and straightening fan blades together with external housing of engine. Rear edge of inlet guide vane of fan in channel of third circuit can turn. Outer surface of separating flanges of straightening vanes is made on larger diameter relative to outer surface of separating flanges of working blades to form a ledge in flow part of channel of third circuit. Ratio of radial value h of ledge between separating flanges of working blade and straightening fan blade in channel of third circuit to axial clearance δ between separation flanges of working and straightening fan blades is within 0.5…1.5.

EFFECT: higher reliability of jet turbine engine.

1 cl, 4 dwg