DOUBLE-FLOW TURBINE JET ENGINE Russian patent published in 2020 - IPC F02C7/18 

FIELD: machine building.

SUBSTANCE: double-flow turbojet engine comprises fan 1, high pressure compressor 2, combustion chamber 3, high pressure turbine 4 and low pressure turbine 5. In order to solve the task of increasing the economy of a double-flow turbojet engine due to reduction of hydraulic losses in the annular channel of its outer contour, external housing 9 of the engine consists of external 13 and internal 14 coaxial annular walls, between which there are helical ribs 15 in number of not less than three pieces, which divide annular cavity between walls 13 and 14 on screw channels 16 for passage of air intended for cooling of high pressure turbine. Inlet of screw channels 16 is connected to holes 17 made in housing 18 of high pressure compressor 2, branch pipes 19 with openings 20. Outlet of screw channels 16 by branch pipes 21 with openings 22 is connected to holes 23 made in housing 24 of low pressure turbine 5, which are interconnected with holes 27 for passage of cooled air, made in housing of high pressure turbine.

EFFECT: broader functional capabilities.

1 cl, 3 dwg