UNIVERSAL TURBOJET ENGINE “H” Russian patent published in 2018 - IPC F02K9/92 F02K7/16 

FIELD: machine building.

SUBSTANCE: invention relates to the fields of the jet power plants structures which, when operating as the LTJE or PATJE, creating the direction changing forward gas thrust, and, operating as a LPE, creating the rear gas thrust. Thus, according to the invention, the combustion chamber rear part with the turbine impeller is separated from the combustion chamber middle part by the annular gap. At that, the combustion chamber has of the combustion chamber female rear portion and the latter middle portion rear part support ring. At that, the latter, in its turn, has two through-cuts arranged diametrically and longitudinally in the latter middle and back portions side wall, and, in addition, has two through-cuts arranged diametrically and longitudinally in the support ring rear part rear section side wall. And, at that, the latter is immovably connected to the combustion chamber middle part by means of radial posts. Universal turbojet engine “H” also comprises rotary nozzle head, in which the inlet passage section is larger than the outlet flow cross-section, and the latter is larger than the combustion chamber rear portion outlet flow section. At that, the nozzle head has two semi-axes, located outside and opposite and stationary fixed on the front part side wall, in which the root parts diameter is larger than the middle and end parts diameter. And, at that, the support ring rear part rear portion cutouts walls cover their half-axes nozzle head middle parts with the gap. Universal turbojet engine “H” also contains two cover plates with the through circular hole each located on the support ring rear part outside and stationary fixed on the latter side wall. At that, the holes walls cover the nozzle head their semi-axes end parts with the gap. Universal turbojet engine “H” also contains two swivel elements: either cylindrical gear wheels, or sprockets. At that, the swivel elements are stationary fixed on their nozzle half-axes end parts. At that, the fuel injectors are stationary fixed in the combustion chamber side wall. Universal turbojet engine “H” also includes the front fuel oxidizing nozzles, circumferentially located in the combustion chamber middle in front of the spark plugs and stationary fixed in the combustion chamber side wall. Universal turbojet engine “H” also includes the rear fuel oxidizing nozzles, circumferentially located in the combustion chamber middle behind the spark plugs and stationary fixed in the combustion chamber side wall. Universal turbojet engine “H” also contains the front and rear rotary flaps, which have the form of biconvex disk, and with shafts. At that, the front flap is located in the combustion chamber front part and behind the fuel nozzles, and the front flap shaft is pivotally fixed in the combustion chamber side wall. Ans, at that, the rear flap is located in the combustion chamber middle part and behind the fuel oxidizing nozzles, and the rear flap shaft is pivotally fixed in the combustion chamber and support ring side walls. Invention also allows the electric current generation. For this, the universal turbojet engine “H” also comprises the electric current electromagnetic generator, located between the combustion chamber rear part and the support ring, in which rotor is fixedly connected to the combustion chamber rear part, and the stator is fixedly connected to the support ring. Furthermore, the invention is also characterized by the presence of a rotational element for gear or chain transmission. For this, the universal turbojet engine “H” also comprises the rolling bearing, located between the combustion chamber rear part and the support ring, in which the inner ring is fixedly connected to the combustion chamber rear part, and the outer ring is fixedly connected to the support ring. Universal turbojet engine “H” also comprises the rotational element located between the combustion chamber rear part and the support ring, and behind the bearing, either a spur gear or the sprocket. Moreover, the rotational element is stationary connected to the combustion chamber rear part.

EFFECT: invention allows to enable only the combustion chamber rear part rotation to reduce centrifugal loads, and also implements the rotary nozzle head for the front gas thrust direction changing, and, in addition, implements the front or rear gas thrust creation devices.

3 cl, 3 dwg