An apparatus for machining a component is provided. The apparatus includes a fixation mechanism, wherein the fixation mechanism includes a first fixation member with a first fixation face and a second fixation member with a second fixation face, wherein the first fixation face and the second fixation face are arranged and configured such that different bearing surfaces of a plurality of different components can be fixed between the first fixation member and the second fixation member, wherein the apparatus further includes a machining device, and wherein the apparatus is configured to machine a machining surface of the respective component by means of the machining device and according to a predetermined accuracy. Further, a method of machining the component is presented.

A mounting for locking a turbine engine vane that includes a blade and at least one portion outside the blade is provided. The mounting can machine the outside portion on a machine tool and includes a stationary jaw for receiving the vane, the jaw including at least six points that form abutments and define a positioning reference system for the vane. The mounting also includes a movable jaw to ensure, during machining the outside portion, holding the vane against the stationary jaw by a clamping mechanism onto the vane blade. The movable jaw includes a first clamping mechanism exerting pressure on one of the surfaces of the blade, the pressure being substantially perpendicular to the surface. The stationary jaw includes a second clamping mechanism exerting pressure on the leading or trailing edge of the blade, the pressure being substantially oriented in the direction of the trailing or leading edge of the blade.

A method of removing material from an airfoil includes engaging a root of the airfoil within a root-securing fixture, engaging a tip of the airfoil within a tip-securing fixture, and removing material from the airfoil. The method further includes disengaging the tip of the airfoil from the tip-securing fixture to allow movement of the tip from a clamped state position to a free-state position. The method further includes reengaging the tip of the airfoil within the tip-securing fixture in the free-state position, and removing additional material from the airfoil.

A fixture for drilling a hole in a superalloy turbine blade includes a mount to selectively hold a root of the superalloy turbine blade with the superalloy turbine blade extending from the mount. The fixture may also include an actuator to apply a force to elastically deform at least a portion of the superalloy turbine blade when held by the mount from a relaxed, initial position to an elastically deformed position, the at least a portion of the superalloy turbine blade having a curvature in the elastically deformed position not present in the relaxed, initial position. The fixture may also include a drill guide configured to guide a drilling element into the superalloy turbine blade in the elastically deformed position.

A method includes applying a force to elastically deform at least a portion of a superalloy turbine blade from a relaxed, initial position to an elastically deformed position. The at least a portion of the superalloy turbine blade has a curvature in the elastically deformed position not present in the relaxed, initial position. A hole is drilled generally span-wise through the at least a portion of the superalloy turbine blade in the elastically deformed position, and when the force is released, the superalloy turbine blade returns to the relaxed, initial position and the hole takes on a hole curvature within the at least a portion of the superalloy turbine blade.

A method and system temporarily holds a workpiece, most suitably an aero engine turbine blade element during manufacture. The workholding system includes a support body with a contoured body surface, complementary to a workpiece surface, formed of a transparent material to define a bonding zone. The support body is supported by a base to form a workpiece shuttle, and a bond station receives the workpiece shuttle. Complementary zero-point locating elements on the shuttle and station assure accurate positioning. The bond station further has workpiece locating elements configured to accurately position the workpiece on the shuttle in a predetermined position relative to the zero-point locating elements of the shuttle, thereby compensating for shuttle-to-shuttle variance. An adhesive, such as a UV curable adhesive, is applied to the bonding zone and cured by UV through the transparent material, thereby fixing the workpiece in the predetermined position.

A turning fixture including a fixture insert attached to the turning fixture, the fixture insert comprising an upper portion having an upper portion body, the upper portion body includes a central span with a first arm and second arm opposite the first arm, a cavity is defined between the first arm and the second arm along the central span on an inner side of the upper portion body; the fixture insert including a lower portion having a lower portion body that includes a chamber located centrally between a first end and a second end; and a rod is insertable through the lower portion through the chamber, the rod being configured to apply a force to a compressor spindle vane inserted between the upper portion and the lower portion.

A turning fixture including a fixture insert attached to the turning fixture, the fixture insert comprising an upper portion having an upper portion body, the upper portion body includes a central span with a first arm and second arm opposite the first arm, a cavity is defined between the first arm and the second arm along the central span on an inner side of the upper portion body; the fixture insert including a lower portion having a lower portion body that includes a chamber located centrally between a first end and a second end; and a rod is insertable through the lower portion through the chamber, the rod being configured to apply a force to a compressor spindle vane inserted between the upper portion and the lower portion.

A method for mounting rotor blades on a rotor disk along a predetermined pitch circle diameter in such a way that adjacent rotor blades, when properly mounted on the rotor disk and in the cold state, are clamped against each other with a predetermined preload. A clamping device which performs such a method has a plurality of clamping elements which are arranged in a uniformly distributed manner around a central axis, the number of which corresponds to the number of rotor blades to be mounted on the rotor disk and which in each case are designed for the locating of a rotor blade, wherein the clamping elements are moveable radially, exerting a radially inwardly directed force.

A vane tip machining fixture assembly includes a first clamp ring mountable to a fixture, the first clamp ring includes a rigid back ring mounted to a resilient ring.