BYPASS TURBOJET ENGINE OUTLET DEVICE Russian patent published in 2024 - IPC F02K1/04 F02K1/78 F02K1/82 

FIELD: aircraft engine building.

SUBSTANCE: invention relates to outlet devices of bypass turbojet engines. Outlet device of bypass turbojet engine comprises housing 1, annular partition wall 2, central turbine cowl 3 of turbine 4 with working blades 5. Channel of internal circuit 6, the inlet to which is located directly behind working blades 5 of turbine 4, is formed by the annular partition wall 2 and the central behind turbine cowl 3. Channel of external circuit 7 is formed by annular partition wall 2 and housing 1. Central turbine cowl 3 is made in the form of two cones: cone 8 with vertex facing towards outlet of exhaust gas flow, and cone 9 with truncated vertex facing turbine 4. Bases of cones 8 and 9 are conjugated with each other to form toroidal surface 10. Annular partition wall 2 is equipped with edge 11 overlapping the visibility of the inlet into the channel of internal circuit 6 and, accordingly, of working blades 5 of turbine 4.

EFFECT: providing low level of infrared radiation (IR) of bypass turbojet engines to rear hemisphere of aircraft due to exclusion of visibility of inlet into channel of inner contour and, accordingly, of working blades of turbine.

1 cl, 1 dwg