FIELD: machine building.
SUBSTANCE: reduction system of vortex formation includes aerodynamic profile spread in the direction of profile span from end wall, rounding between aerodynamic profile and end wall, zone of front rounding edge near and about front edge of aerodynamic profile, as well as plasma generators. Plasma generators are spread in direction of profile span through rounding made in zone of front edge and provided with possibility of generating plasma spread above some part of rounding in the area of front edge. As per the other version, reduction system of vortex formation includes group of blades, which includes blade ring of gas-turbine engine, each of which has aerodynamic profile and is spread radially in the direction of profile span between radially internal and external bands. Each aerodynamic profile has external wall spread in the direction of chord between opposite front and rear edges, roundings between aerodynamic profile and internal and external bands, zones of front edge of roundings near and about front edge of aerodynamic profile, as well as plasma generators. Plasma generators are spread in profile span direction through rounding in zones of front edge. One more invention of the group refers to operating method of vortex formation reduction system, in compliance with which the power of plasma generators is switched on to generate plasma spread above some part of rounding in the zone of front edge of aerodynamic profile of gas-turbine engine.
EFFECT: inventions allow improving aerodynamic characteristics of gas-turbine engine blade.
12 cl, 9 dwg
