| 摘要 |
The invention relates to the jet engines and may be used at the wind-, thermo- and hydroelectric stations, in the mechanical engineering, in the earth, water and air transport. The jet engine contains a body, wherein there are installed with clearance a compressor and a turbine, coaxially mounted onto a common shaft, which is supported into the body in bearings, and placed correspondingly: the compressor - into a compression chamber, joined with an air intake, and the turbine - into a chamber for exhaust gas outlet, joined with a nozzle, and a combustion chamber, placed into the turbine and/or between the compressor and the turbine, or outside thereof, and wherein it is injected liquid or gaseous combustible. The compressor and the turbine contain at least two or more pairs of plates, symmetrically mounted onto the shaft about the transversal axes of the compressor and turbine correspondingly, and blades, having the form of an isosceles triangle with the vertex between the catheti oriented to the outside of the compressor and turbine, and the other two vertexes are correspondingly joined with the plates of the turbine and compressor, with that into the plates there are made one or several orifices. The result consists in increasing the engine torque, in sharply changing the displacement direction of the object equipped with the proposed engine. Claims: 10 |
