Abstract: A method for forming a nozzle segment for a turbine stage of a gas turbine engine to a specific measurement range for a throat area. The nozzle segment comprising an inner platform, and outer platform, and a plurality of airfoils between the inner platform and outer platform. A requested throat area measurement is obtained for the nozzle segment, and a starting stacking angle for a plurality of through holes and pockets corresponding to the airfoils for both the inner platform and outer platform is selected, which are then machined. The airfoils, inner platform, and outer platform are assembled to form a vane segment that is machined to obtain a finished throat area. The finished throat area is measured, and a determination is made if the measured finish throat area complies with the requested throat area.