Airfoil leading edge end wall vortex reducing plasma

Details Airfoil leading edge end wall vortex reducing plasma Airfoil leading edge end wall vortex reducing plasma

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 2612810

A leading edge vortex reducing system (11) includes a gas turbine engine airfoil (39) extending in a spanwise direction (S) away from an end wall (88), one or more plasma generators (2) extending in the spanwise direction (S) through a fillet (34) between the airfoil (39) and the end wall (88) in a leading edge region (89) near and around a leading edge (LE) of the airfoil (39) and near the fillet (34). The plasma generators (2) being operable for producing a plasma (90) extending over a portion of the fillet (34) in the leading edge region (89). The plasma generators (2) may be mounted on an outer wall (26) of the airfoil (39) with a first portion of the plasma generators (2) on a pressure side (46) of the airfoil (39) and a second portion of the plasma generators (2) on a suction side (48) of the airfoil (39). A method for operating the system (11) includes energizing one or more plasma generators (2) to form the plasma (90) in steady state or unsteady modes.

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