TURBOSHAFT ENGINE Russian patent published in 2025 - IPC F02C6/06 F01C1/14 F01C3/08 F02C3/10 

FIELD: mechanical engineering.

SUBSTANCE: turboshaft engine with two output shafts, axes of which are located at an angle to each other, can be used in different types of transport: in caterpillar, in particular in armoured equipment, in aviation equipment (airplanes and helicopters), in machines and air-cushion ships, etc., where independent transfer of torque to different units of the vehicle is required. Its use is most promising in helicopters – synchrocopters. Turboshaft engine, like prototype, comprises compressor (2), combustion chamber (3) and compressor turbine (4) connected by shaft (5) with compressor, located in series in housing (1). Behind the turbine of compressor (4) there is guide nozzle (6) supplying the gas flow to free turbine (7). Free turbine (7) has two output shafts (13, 14) located at an angle to each other. In contrast to the prototype, free turbine (7) is made in the form of a gear rotary displacement machine with two conical screw rotors (8 and 9) with intersecting axes. Rotors are located in the conical bores of the housing, wherein the teeth of one of rotors (9) in the cross section are outlined by circular arcs (19), eccentrically displaced relative to the rotor axis, and teeth of the other rotor in the same section are outlined by sections of fronts (20) of cycloidal curves (21), forming eccentric-cycloidal (EC) engagement. Plane of the axes of rotors (13 and 14) is located inclined to the axis of the outlet hole of guide nozzle (6). In the preferred version of the invention, at the outlet of guide nozzle (6) there is divider (17) with a streamlined guide, which divides the flow into two.

EFFECT: considerable reduction of weight and dimensions of the engine; besides, load capacity and efficiency of free turbine are increased.

2 cl, 5 dwg