Airfoil with plasma generator at leading edge for vortex reduction and corresponding operating method Patent uri icon

abstract

  • 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.

author list (cited authors)

  • Lee, C. P., Wadia, A. R., Cherry, D. G., & Han, J. C.

complete list of authors

  • Lee, CP||Wadia, AR||Cherry, DG||Han, JC

publication date

  • June 2008