Various embodiments include a system for machining a hole in a turbine blade. The system can include: a mount for engaging a first side of a turbine rotor, the mount including: a drill plate for coupling with the first side of the turbine rotor, the drill plate having: a body; a feed opening on a first side of the body; a passage extending from the feed opening through the body; and a second opening on a second side of the body, the second opening coupled with the passage and positioned to align with the pre-formed hole in the turbine rotor; an alignment bushing for engaging the pre-formed hole in the rotor at a second side of the rotor; and a cutting device for extending through the body and alignment bushing, the cutting device for machining the hole in the blade, the cutting device aligned along a chamfer axis relative to a primary axis of the turbine rotor.

A method for checking a geometry of an electric discharge machining electrode is described. The method comprises the following steps: providing a file containing a native 3D-model of the electric discharge machining electrode; providing a manufactured electric discharge machining electrode based on the native 3D-model; light scanning a set of images of the manufactured electric discharge machining electrode in different positions and generating therewith a scanned 3D-model of the manufactured electric discharge machining electrode; comparing the native 3D-model and the scanned 3D-model and generating electrode compensation coordinates for an electric discharge machining apparatus, to correct an electrode path during electric discharge machining.

A method for checking a geometry of an electric discharge machining electrode is described. The method comprises the following steps: providing a file containing a native 3D-model of the electric discharge machining electrode; providing a manufactured electric discharge machining electrode based on the native 3D-model; light scanning a set of images of the manufactured electric discharge machining electrode in different positions and generating therewith a scanned 3D-model of the manufactured electric discharge machining electrode; comparing the native 3D-model and the scanned 3D-model and generating electrode compensation coordinates for an electric discharge machining apparatus, to correct an electrode path during electric discharge machining.

A gas path component for a gas turbine engine includes a film cooling hole disposed in the gas path component. The film cooling hole includes a metering section, a diffuser, and a tapered surface extending between the metering section and the diffuser. The tapered surface is oriented between twenty degrees and seventy degrees with respect to a centerline axis of the metering section. The tapered surface is oriented at an obtuse angle with respect to an immediately adjacent surface of the diffuser, the obtuse angle is open towards the centerline axis. The tapered surface is configured to mitigate flow separation in the diffuser.

A gas path component for a gas turbine engine includes a film cooling hole disposed in the gas path component. The film cooling hole includes a metering section, a diffuser, and a tapered surface extending between the metering section and the diffuser. The tapered surface is oriented between twenty degrees and seventy degrees with respect to a centerline axis of the metering section. The tapered surface is oriented at an obtuse angle with respect to an immediately adjacent surface of the diffuser, the obtuse angle is open towards the centerline axis. The tapered surface is configured to mitigate flow separation in the diffuser.

A turbine vane for a gas turbine engine having a plurality of cooling holes defined therein is provided. The plurality of cooling holes provide fluid communication to a surface of the turbine vane, the plurality of cooling holes including holes noted by the following coordinates: TVA, TVB, TVC, TVD and TVE of Table 1.

A turbine vane for a gas turbine engine having a plurality of cooling holes defined therein is provided. The plurality of cooling holes provide fluid communication to a surface of the turbine vane, the plurality of cooling holes including holes noted by the following coordinates: TVA, TVB, TVC, TVD and TVE of Table 1.

An electrode for electrical discharge machining (EDM) may comprise a diffuser portion and a tapered portion defining the tip of the electrode. A method for forming a film cooling hole may comprise moving a tool with respect to a film cooled gaspath component, forming a diffuser of the film cooling hole in response to the moving, and forming a tapered surface between a metering section and the diffuser of the film cooling hole.

An electrode for electrical discharge machining (EDM) may comprise a diffuser portion and a tapered portion defining the tip of the electrode. A method for forming a film cooling hole may comprise moving a tool with respect to a film cooled gaspath component, forming a diffuser of the film cooling hole in response to the moving, and forming a tapered surface between a metering section and the diffuser of the film cooling hole.

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.