Plasma induced virtual turbine airfoil trailing edge extension

Details Plasma induced virtual turbine airfoil trailing edge extension Plasma induced virtual turbine airfoil trailing edge extension

F - Mech Eng,Light,Heat,Weapons

02

C

F02C 7/00 (2006.01) F01D 5/14 (2006.01) F01D 9/02 (2006.01) F15D 1/12 (2006.01)

Patent

CA 2612533

A trailing edge vortex reducing system (11) includes a gas turbine engine airfoil (39) extending in a spanwise direction (SD), one or more spanwise extending plasma generators (2) in a trailing edge region (89) around a trailing edge (TE) of the airfoil (39). The plasma generators (2) may be mounted on an outer wall (26) of the airfoil (39) with first and second pluralities of the plasma generators (2) on pressure and suction sides (46, 48) of the airfoil (39) respectively. The plasma generators (2) may include inner and outer electrodes (3, 4) separated by a dielectric material (5) disposed within a grooves (6) in an outer hot surface (54) of the outer wall (26) of the airfoil (39). The plasma generators (2) may be located at an aft end of the airfoil (39) and the inner electrodes (3) flush with the trailing edge base (34). A method for operating the system (11) includes energizing one or more of plasma generators (2) in steady state or unsteady modes.

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