A variable nozzle for a turbocharger, comprising: a generally annular nozzle ring defining a plurality of circumferentially spaced bearing apertures extending axially through an axially facing face of the nozzle ring; a nozzle wall defining a face axially spaced from and opposing the face of the nozzle ring, a nozzle flow path being defined between the opposing faces of the nozzle ring and nozzle wall; and a plurality of circumferentially spaced vanes disposed in the nozzle flow path, each vane comprising an axle defining a pivot axis for the vane, the axles of the vanes being respectively received in the bearing apertures of the nozzle ring and being rotatable therein about the respective pivot axes such that the vanes are adjustable in setting angle between a closed position and an open position, each vane including an aerodynamic airfoil portion having an outer airfoil surface, each airfoil portion being joined to the respective axle and extending along the pivot axis from a first end to an opposite second end, the first and second ends of each airfoil portion respectively defining first and second end faces that are substantially perpendicular to the pivot axis, clearances existing between the first end faces of the airfoil portions and the face of the nozzle ring and between the second end faces of the airfoil portions and the face of the nozzle wall; wherein at least the face of the nozzle ring includes a plurality of generally parallel spaced-apart grooves positioned proximate the respective end faces of the airfoil portions of the vanes, the grooves and the adjacent end face of each vane together defining a labyrinthine passage through which any leakage flow must pass. a generally annular nozzle ring defining a plurality of circumferentially spaced bearing apertures extending axially through an axially facing face of the nozzle ring; a nozzle wall defining a face axially spaced from and opposing the face of the nozzle ring, a nozzle flow path being defined between the opposing faces of the nozzle ring and nozzle wall; and a plurality of circumferentially spaced vanes disposed in the nozzle flow path, each vane comprising an axle defining a pivot axis for the vane, the axles of the vanes being respectively received in the bearing apertures of the nozzle ring and being rotatable therein about the respective pivot axes such that the vanes are adjustable in setting angle between a closed position and an open position, each vane including an aerodynamic airfoil portion having an outer airfoil surface, each airfoil portion being joined to the respective axle and extending along the pivot axis from a first end to an opposite second end, the first and second ends of each airfoil portion respectively defining first and second end faces that are substantially perpendicular to the pivot axis, clearances existing between the first end faces of the airfoil portions and the face of the nozzle ring and between the second end faces of the airfoil portions and the face of the nozzle wall; wherein at least the face of the nozzle ring includes a plurality of generally parallel spaced-apart grooves positioned proximate the respective end faces of the airfoil portions of the vanes, the grooves and the adjacent end face of each vane together defining a labyrinthine passage through which any leakage flow must pass. <EOS>