Patent ID: 7658004

Claim:
A method for the finish machining of blade root structure of gas-turbine engine blades east in a brittle, light material, the structure including an airfoil and a platform, which upon removal from a casting mold is connected to a casting structure of feeders and runners, comprising: positioning the blade airfoil via reference points defined for subsequent machining and clamping the blade in this defined position, while the blade is in this defined position, producing a runner clamping surface on runner portions remaining on the platform of the blade and also producing conical recesses, and threaded holes originating at these conical recesses, into the runner portions from the runner clamping surface to form an auxiliary clamping structure, subsequently fixing the blade to a workpiece carrier via the clamping structure, the workpiece carrier position the blade via a flexible taper fit with the conical recesses and clamping the blade via an engagement with the threaded holes, machining a blade root structure while the blade is fixed to the workpiece carrier, and severing the auxiliary clamping structure from the machined blade.