TAIL CONE FOR ROTARY GAS TURBINE ENGINE WITH MICRO-JETS Russian patent published in 2016 - IPC F02K1/34 

FIELD: engines.

SUBSTANCE: gas turbine engine rear casing, having primary stage, forming flow discharged by primary nozzle, is located downstream of primary stage and limits, on gas turbine engine inner side, channel through which primary flow passes downstream from primary nozzle. Rear casing comprises part, connected with pressurized gas supply system, and at least one pressurized gas into primary flow injection hole. Rear casing comprises fixed internal housing, intended for primary stage completion on its part, located downstream, said part, having hole, which is made with possibility of rotation on fixed inner housing, as well as said part rotation device about primary stage movable parts axis of rotation. Other inventions of group relate to gas turbine engine unit embodiments, including above mentioned rear casing and pressurized gas supply system, as well as to gas turbine engine equipped with such unit.

EFFECT: group of inventions enables reduced noise of gas turbine engine without considerable reduction of its characteristics.

8 cl, 3 dwg