GAS TURBINE ENGINE VANE COOLING CIRCUITS Russian patent published in 2010 - IPC F01D5/18 

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine vane central part has inner side and outer side cooling circuits. Inner side cooling circuit comprises at least one first and one second inner side spaces running radially and in direction of vane thickness from vane inner side to central wall passing radially and indirection of vane carcass. Central space runs radially and in direction of vane thickness from vane inner side to outer side. Air discharge hole is arranged on radial end of the inner side first space to feed air to inner side circuit. First passage communicates the other radial end of inner side first space with adjacent radial end of inner side second space. Second passage communicates the other radial end of inner side second space with adjacent radial end of inner side central space. Discharge holes start at central space to terminate at vane inner side. Outer cooling circuit comprises at least one first and one second spaces of inner side that pass radially and in direction of vane thickness from vane outer aide to vane inner side. Central space runs radially and in direction of vane thickness from vane inner side to outer side. Air discharge hole is arranged on radial end of the inner side first space to feed air to inner side circuit. First passage communicates the other radial end of inner side first space with adjacent radial end of inner side second space. Second passage communicates the other radial end of inner side second space with adjacent radial end of inner side central space. Discharge holes start at central space to terminate at vane inner side.

EFFECT: higher efficiency of cooling without deterioration in turbine aerodynamic characteristics.

10 cl, 5 dwg