초록 ▼

A method for inhibiting radial transfer of core gas flow away from a center radial region and toward the inner and outer radial boundaries of a core gas flow path within a gas turbine engine is provided that includes the steps of: (1) providing a flow directing structure that includes an airfoil tha

A method for inhibiting radial transfer of core gas flow away from a center radial region and toward the inner and outer radial boundaries of a core gas flow path within a gas turbine engine is provided that includes the steps of: (1) providing a flow directing structure that includes an airfoil that abuts a wall surface, said airfoil having a leading edge, a pressure side, and a suction side; and (2) increasing the velocity of the core gas flow in the area where the leading edge of the airfoil abuts the wall. Increasing the velocity of the core gas flow in the area where the leading edge of the airfoil abuts the wall impedes the formation of a pressure gradient along the surface of the airfoil that forces core gas from the center region of the core gas toward the wall. The apparatus includes apparatus for diverting core gas flow away from the area where the airfoil abuts the wall.

대표청구항 ▼

1. A method for inhibiting radial transfer of core gas flow within a core gas flow path of a gas turbine engine, comprising the steps of:providing a flow directing structure having an airfoil that abuts a wall, said airfoil having a leading edge, a pressure side, a suction side; and increasing a vel

1. A method for inhibiting radial transfer of core gas flow within a core gas flow path of a gas turbine engine, comprising the steps of:providing a flow directing structure having an airfoil that abuts a wall, said airfoil having a leading edge, a pressure side, a suction side; and increasing a velocity of said core gas flow in an area where said leading edge of said airfoil abuts said wall with a fillet between said wall and said airfoil, said fillet extending generally from said leading edge of said airfoil and having a dividing plane aligned with a stagnation line of said airfoil; wherein increasing said core gas flow velocity in said area inhibits formation of a secondary flow of core gas flow in the direction of said wall.