FIELD: engines and pumps.
SUBSTANCE: proposed engine comprises axial-flow compressor, combustion chamber, turbine and nozzle. One, several or all compressor stages comprise vanes that feature, in plan, triangular shape and/or height equal to boundary layer thickness. Via hollow vanes of stator or compressor or blade rim, pressure is equalised over compressor stage section by bypassing air from peripheral zone of increased pressure into circum-rotor zone with lower pressure. Hollow vane peripheral parts have holes or slots arranged on front edge or vane profile concave side, while circum-rotor part has holes or slots arranged on rear edge of vane profile convex side. Compressor and/or turbine vanes feature smoothly decreasing pitch on periphery and/or circum-rotor parts on the length that corresponds to boundary layer thickness. Turbine engine has additional rim or additional stage with vanes with height equal to boundary layer thickness.
EFFECT: higher anti-surge properties, engine response and reliability.
8 cl, 3 dwg
