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A trailing edge vortex reducing system includes a gas turbine engine airfoil extending in a spanwise direction, one or more spanwise extending plasma generators in a trailing edge region around a trailing edge of the airfoil. The plasma generators may be mounted on an outer wall of the airfoil with

A trailing edge vortex reducing system includes a gas turbine engine airfoil extending in a spanwise direction, one or more spanwise extending plasma generators in a trailing edge region around a trailing edge of the airfoil. The plasma generators may be mounted on an outer wall of the airfoil with first and second pluralities of the plasma generators on pressure and suction sides of the airfoil respectively. The plasma generators may include inner and outer electrodes separated by a dielectric material disposed within a grooves in an outer hot surface of the outer wall of the airfoil. The plasma generators may be located at an aft end of the airfoil and the inner electrodes flush with the trailing edge base. A method for operating the system includes energizing one or more of plasma generators in steady state or unsteady modes.

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Accordingly, what is desired to be secured by Letters Patent of the United States is the invention as defined and differentiated in the following claims: 1. A trailing edge vortex reducing system comprising: a gas turbine engine airfoil extending in a chordwise direction between a leading edge and

Accordingly, what is desired to be secured by Letters Patent of the United States is the invention as defined and differentiated in the following claims: 1. A trailing edge vortex reducing system comprising: a gas turbine engine airfoil extending in a chordwise direction between a leading edge and a trailing edge of the airfoil and extending outwardly in a spanwise direction from an airfoil base to an airfoil tip, the airfoil having pressure and suction sides extending in the chordwise direction between the leading edge and the trailing edge, a trailing edge base at the trailing edge and a trailing edge region around the trailing edge and including the trailing edge base, and one or more plasma generators extending at least partway in the spanwise direction along the pressure side and/or the suction side in the trailing edge region. 2. A system as claimed in claim 1 further comprising the plasma generators being mounted on an outer wall of the airfoil. 3. A system as claimed in claim 2 further comprising a first plurality of the plasma generators on the pressure side of the airfoil and a second plurality of the plasma generators on the suction side of the airfoil. 4. A system as claimed in claim 2 further comprising a first one of the plasma generators on the pressure side of the airfoil and a second one of the plasma generators on the suction side of the airfoil. 5. A system as claimed in claim 1 further comprising the plasma generators including inner and outer electrodes separated by a dielectric material. 6. A system as claimed in claim 5 further comprising the plasma generators located at an aft end of the airfoil and the inner electrodes being flush with the trailing edge base. 7. A system as claimed in claim 5 further comprising the dielectric material being disposed within a groove in an outer hot surface of an outer wall of the airfoil. 8. A system as claimed in claim 7 further comprising a first plurality of the plasma generators on the pressure side of the airfoil and a second plurality of the plasma generators on the suction side of the airfoil. 9. A system as claimed in claim 7 further comprising a first one of the plasma generators on the pressure side of the airfoil and a second one of the plasma generators on the suction side of the airfoil. 10. A system as claimed in claim 7 further comprising a high pressure turbine nozzle vane including the airfoil extending radially in a spanwise direction between radially inner and outer bands. 11. A system as claimed in claim 7 further comprising a high pressure turbine blade including the airfoil extending radially outwardly from an airfoil base on a blade platform. 12. A trailing edge vortex reducing system comprising: a vane assembly including a row of circumferentially spaced apart and radially extending gas turbine engine vanes, each of the vanes having an airfoil extending radially in a spanwise direction between radially inner and outer bands, the airfoil having pressure and suction sides extending in a chordwise direction between the leading edge and the trailing edge, a trailing edge base at the trailing edge and a trailing edge region around the trailing edge and including the trailing edge base, and one or more plasma generators extending in the spanwise direction in the trailing edge region. 13. A system as claimed in claim 12 further comprising a first plurality of the plasma generators on the pressure side of the airfoil and a second plurality of the plasma generators on the suction side of the airfoil. 14. A system as claimed in claim 12 further comprising a first one of the plasma generators on the pressure side of the airfoil and a second one of the plasma generators on the suction side of the airfoil. 15. A system as claimed in claim 12 further comprising the plasma generators including inner and outer electrodes separated by a dielectric material and an AC power supply connected to the electrodes to supply a high voltage AC potential to the electrodes. 16. A system as claimed in claim 15 further comprising the plasma generators located at an aft end of the airfoil and the inner electrodes being flush with the trailing edge base. 17. A system as claimed in claim 15 further comprising the dielectric material being disposed within a grooves in an outer hot surface of an outer wall of the airfoil. 18. A system as claimed in claim 17 further comprising a first plurality of the plasma generators on the pressure side of the airfoil and a second plurality of the plasma generators on the suction side of the airfoil. 19. A system as claimed in claim 17 further comprising a first one of the plasma generators on the pressure side of the airfoil and a second one of the plasma generators on the suction side of the airfoil. 20. A trailing edge vortex reducing system comprising: a turbine assembly including a row of circumferentially spaced apart turbine blades, each of the turbine blades having a turbine airfoil extending radially outwardly in a spanwise direction from an airfoil base on a blade platform, the airfoil having pressure and suction sides extending in a chordwise direction between the leading edge and the trailing edge, a trailing edge base at the trailing edge and a trailing edge region around the trailing edge and including the trailing edge base, and one or more plasma generators extending in the spanwise direction in the trailing edge region. 21. A system as claimed in claim 20 further comprising a first plurality of the plasma generators on the pressure side of the airfoil and a second plurality of the plasma generators on the suction side of the airfoil. 22. A system as claimed in claim 20 further comprising a first one of the plasma generators on the pressure side of the airfoil and a second one of the plasma generators on the suction side of the airfoil. 23. A system as claimed in claim 20 further comprising the plasma generators including inner and outer electrodes separated by a dielectric material and an AC power supply connected to the electrodes to supply a high voltage AC potential to the electrodes. 24. A system as claimed in claim 23 further comprising the plasma generators located at an aft end of the airfoil and the inner electrodes being flush with the trailing edge base. 25. A system as claimed in claim 23 further comprising the dielectric material being disposed within a groove in an outer hot surface of an outer wall of the airfoil. 26. A system as claimed in claim 25 further comprising a first plurality of the plasma generators on the pressure side of the airfoil and a second plurality of the plasma generators on the suction side of the airfoil. 27. A system as claimed in claim 25 further comprising a first one of the plasma generators on the pressure side of the airfoil and a second one of the plasma generators on the suction side of the airfoil. 28. A method for operating a trailing edge vortex reducing system, the method comprising: energizing one or more spanwise extending plasma generators in a trailing edge region of a gas turbine engine airfoil, the airfoil extending in a chordwise direction between a leading edge and a trailing edge of the airfoil and extending outwardly in a spanwise direction from an airfoil base to an airfoil tip, the airfoil having pressure and suction sides extending in the chordwise direction between the leading edge and the trailing edge, a trailing edge base at the trailing edge, and the trailing edge region extending around the trailing edge and including the trailing edge base. 29. A method as claimed in claim 28 wherein the energizing further includes supplying an AC potential to inner and outer electrodes separated by a dielectric material of the plasma generator. 30. A method as claimed in claim 29 further comprising operating the plasma generator in steady state or unsteady modes. 31. A method as claimed in claim 29 further comprising operating the plasma generators located at an aft end of the airfoil and the inner electrodes being flush with the trailing edge base. 32. A method as claimed in claim 28 further comprising using a first plurality of the plasma generators mounted on the pressure side of the airfoil and a second plurality of the plasma generators mounted on the suction side of the airfoil. 33. A method as claimed in claim 28 further comprising using a first one of the plasma generators mounted on the pressure side of the airfoil and a second one of the plasma generators mounted on the suction side of the airfoil. 34. A method as claimed in claim 33 wherein the energizing further includes supplying an AC potential to inner and outer electrodes separated by a dielectric material of the plasma generator. 35. A method as claimed in claim 34 further comprising operating the plasma generator in steady state or unsteady modes. 36. A method for operating a trailing edge vortex reducing system, the method comprising: energizing one or more spanwise extending plasma generators in a trailing edge region of a gas turbine engine airfoil, the airfoil extending in a chordwise direction between a leading edge and a trailing edge of the airfoil and extending outwardly in a spanwise direction from an airfoil base to an airfoil tip, the airfoil extending radially in a spanwise direction between radially inner and outer bands, the airfoil having pressure and suction sides extending in the chordwise direction between the leading edge and the trailing edge, and the trailing edge region extending around the trailing edge and including a trailing edge base at the trailing edge. 37. A method as claimed in claim 36 wherein the energizing further includes supplying an AC potential to inner and outer electrodes separated by a dielectric material of the plasma generators. 38. A method as claimed in claim 37 further comprising operating the plasma generator in steady state or unsteady modes. 39. A method as claimed in claim 36 further comprising using a first plurality of the plasma generators mounted on the pressure side of the airfoil and a second plurality of the plasma generators mounted on the suction side of the airfoil. 40. A method as claimed in claim 36 further comprising using a first one of the plasma generators mounted on the pressure side of the airfoil and a second one of the plasma generators mounted on the suction side of the airfoil. 41. A method as claimed in claim 40 wherein the energizing further includes supplying an AC potential to inner and outer electrodes separated by a dielectric material of the plasma generator. 42. A method as claimed in claim 41 further comprising operating the plasma generator in steady state or unsteady modes.