FIELD: machine building.
SUBSTANCE: axial gas turbine engine, such as a turbojet engine comprising a fan, a compressor equipped with a rotor with at least three annular rows of rotor blades, two rows of which are oppositely rotating rows, planetary step-down gearing connecting said fan with said compressor rotor and connecting said oppositely rotating rows. Axial gas turbine engine also comprises annular row of stator blades arranged between two rows of rotor blades, rotating in one direction, so as to straighten flow between said two rows of rotor blades. Each rotor blade is connected to the rotor by its inner end.
EFFECT: invention is aimed at optimization of compressor compression ratio and compactness, higher efficiency.
16 cl, 3 dwg
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