FIELD: aviation.
SUBSTANCE: invention relates to the field of aviation, in particular to designs of lifting engines, power plants of vertical take-off and landing aircraft. Vertically oriented turbojet comprises annular loop combustion chamber, turbine located outside combustion chamber. Turbine is connected with shaft above combustion chamber, or turbine shaft passes inside annular combustion chamber. Torque from turbine shaft to compressor is transmitted by reduction gear. Nozzle consists of two cone-shaped, interconnected static parts: one larger size, another smaller size located inside the first one with some gap. Cone-shaped nozzle has shape of discontinuous ring like horseshoe. Power plant of vertical take-off and landing aircraft consists of one or several vertically oriented (lifting) engines and one or several horizontally oriented turbojet engines with variable thrust vector.
EFFECT: high speed of horizontal flight, manoeuvrability and stability of aircraft in all modes of flight.
3 cl, 2 dwg
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