DOUBLE-CIRCUIT GAS TURBINE FAN MOTOR Russian patent published in 2023 - IPC F02C7/47 F02K3/06 F01K23/06 F01D1/32 

FIELD: engine construction.

SUBSTANCE: invention is related in particular to aircraft turbojet fan engines. Steam generator 1, which is part of the liquid cooling system of the turbojet engine, cools combustion chamber 10. It is connected to receiver 2, in which a certain volume of steam with a certain pressure is concentrated. Steam is supplied to nozzles 3 located at the ends of propeller 4, which is located on the turbojet engine shaft. The diameter of screw 4 exceeds the diameter of fan 5 of the turbine so that the oncoming air flow formed by fan 5 does not intersect with the steam flow escaping from nozzles 3 of propeller 4. The steam jet creates additional torque for the turbine. After that, steam through special channel 6 enters the wings of the aircraft to heat them up and prevent icing. In the wings, steam is cooled, and condensate is formed. The wings are provided with a container for collecting condensate 7, as well as pump 8 for pumping condensate through nozzle 9 into steam generator 1. A closed cycle is supposed to be so organized. To simplify the design, the jet of steam from nozzle 3 after the work of rotating propeller 4 can simply be sent to combustion chamber 10 of the turbojet engine to increase thrust.

EFFECT: increase of efficiency of the engine and its consumption rate through the use of additional energy from the steam generated in the steam generator which is fed into jet nozzles located at the ends of the propeller.

1 cl, 1 dwg