FIELD: transport.
SUBSTANCE: invention relates to aircraft engineering, particularly, to VTOL aircraft. Proposed aircraft comprises axially-symmetric airframe, fuel tank, instrumentation compartment, and gas turbine engine. Gas turbine engine comprises compressor, combustion chamber, turbine and jet nozzle. Engine is mounted along airframe vertical axis. Gas turbine engine multi-section combustion chamber incorporates fuel systems including fuel consumption controllers for every section and adjustable nozzle guide vanes. Turbine comprises turning nozzle vanes. Every said vane is furnished with drive. Said adjustable nozzle guide vanes are arranged behind the compressor. The number of nozzle vanes equals that of combustion chamber sections. Nozzle vanes are arranged between combustion chamber sections. Radial flow compressor has axial inlet and axial outlet. Fuel tank is arranged inside gas turbine engine. Emergency landing engine is mounted inside jet nozzle.
EFFECT: better controllability.
6 cl, 4 dwg
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