Plasma lifted boundary layer gas turbine engine vane

Details Plasma lifted boundary layer gas turbine engine vane Plasma lifted boundary layer gas turbine engine vane

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 9/02 (2006.01) F15D 1/12 (2006.01)

Patent

CA 2607038

A plasma boundary layer lifting system (11) includes at least one gas turbine engine vane (32) having a spanwise extending airfoil (39) with an outer surface (54) extending in a chordwise direction (C) between opposite leading and trailing edges (LE, TE) and chordwise spaced apart plasma generators (2) for producing a plasma (90) extending in the chordwise direction (C) along the: outer surface (54). Each plasma generator (2) may include inner and outer electrodes (3, 4) separated by a dielectric material (5) disposed within a spanwise extending groove (6) in the outer surface (54). The airfoil (39) may be hollow having an outer wall (26) and the plasma generators (2) being mounted on the outer wall (26). A method for operating the system (11) includes forming a plasma (90) extending in the chordwise direction (C) along the outer surface (54) of the airfoil (39). The method may further include operating the plasma generators (2) in steady state or unsteady modes.

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