Method for constructing a fixed-vane ring for a nozzle of a turbocharger turbine

A method for constructing a fixed-vane ring for a nozzle of a turbocharger turbine, comprising the steps of:

• providing a nozzle ring comprising an annular flat disk, the nozzle ring having a first face and an opposite second face, an annular groove being formed in the second face;
• forming a plurality of circumferentially spaced circular bores extending through the nozzle ring from the first face to the second face, the bores being located within said annular groove in the second face of the nozzle ring;
• providing a plurality of vanes, each vane comprising an airfoil portion and a circular vane shaft extending from one end of the airfoil portion;
• inserting the vane shafts respectively into the bores in the nozzle ring from said first face thereof, each vane being oriented at a desired setting angle;
• and
• rigidly affixing the vane shafts to the nozzle ring to fix the vanes at the desired setting angles.