Abstract: The invention pertains to component-part manufacture for a turbine-nozzle assembly, to take the place of certain single-piece investment castings currently in use for such assemblies, intended primarily for gas-turbine application. The construction basically employs a blade element of desired airfoil-section development, and two base members, each locally recessed to define a locating socket or opening for the respective longitudinal ends of the blade. The invention is specifically concerned with apparatus and techniques whereby the recesses are carefully controlled in their location with respect to base-member geometry, to the end that the assembly may produce a given performance-class number for the resulting nozzle, once assembled and united into an integral whole, by welding, brazing, coating and the like finishing steps.