SYSTEM FOR REDUCTION OF SWIRLS ON REAR EDGE OF AERODYNAMIC SECTION OF GAS TURBINE ENGINE, AND ITS OPERATING METHOD Russian patent published in 2012 - IPC F01D5/14 

FIELD: engines and pumps.

SUBSTANCE: system for reduction of swirls on rear edge of aerodynamic section of gas turbine engine, which passes along chord between upper and rear edges and is continued in the direction of swing from bottom to tip, includes plasma generators. Aerodynamic section has positive and negative pressure sides which are continued along chord between upper and rear edges, as well as bottom of rear edge and area of rear edge, which includes bottom of rear edge. Plasma generators are installed on external wall of aerodynamic section and are continued at least partially in swing direction, along positive and/or negative pressure sides for formation of virtual elongation of rear edge in the rear edge area, which converges in downstream direction and is induced by plasma. The other invention of the group refers to the operating method of swirl reduction system on rear edge of aerodynamic section of gas turbine engine in which the above plasma generators are connected.

EFFECT: inventions allow increasing efficiency coefficient of gas turbine engine due to reducing the influence of thickness of read edge of aerodynamic section on its aerodynamic properties.

7 cl, 10 dwg