An additive manufactured workpiece includes one or more cavities having an inner surface. A dielectric interface is formed in the cavity, and conforms to the inner surface. The additive manufactured workpiece further includes an in-situ electrode in the cavities. The dielectric interface is interposed between the in-situ electrode and the inner surface of the workpiece.

An additive manufactured workpiece includes one or more cavities having an inner surface. A dielectric interface is formed in the cavity, and conforms to the inner surface. The additive manufactured workpiece further includes an in-situ electrode in the cavities. The dielectric interface is interposed between the in-situ electrode and the inner surface of the workpiece.

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 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 apparatus for electrically machining including a rotatable shaft and an electrode for electrically machining is disclosed. The electrode is movably connected to the rotatable shaft. When the rotatable shaft is rotated, the electrode rotates together with the rotatable shaft and moves relative to the rotatable shaft under an action of centrifugal force. Further disclosed is a method for electrically machining including: movably connecting an electrode to a rotatable shaft; inserting the rotatable shaft into a hole in a workpiece, and keeping a gap between the electrode and the workpiece, wherein the hole has a first diameter; powering on the electrode and the workpiece; rotating the rotatable shaft in the hole to generate centrifugal force; and pushing the electrode relative to the rotatable shaft towards the workpiece under an action of the centrifugal force to remove a portion of a material of the hole.

An apparatus for electrically machining including a rotatable shaft and an electrode for electrically machining is disclosed. The electrode is movably connected to the rotatable shaft. When the rotatable shaft is rotated, the electrode rotates together with the rotatable shaft and moves relative to the rotatable shaft under an action of centrifugal force. Further disclosed is a method for electrically machining including: movably connecting an electrode to a rotatable shaft; inserting the rotatable shaft into a hole in a workpiece, and keeping a gap between the electrode and the workpiece, wherein the hole has a first diameter; powering on the electrode and the workpiece; rotating the rotatable shaft in the hole to generate centrifugal force; and pushing the electrode relative to the rotatable shaft towards the workpiece under an action of the centrifugal force to remove a portion of a material of the hole.

A core for gas turbine engine component comprises a body extending between first and second ends to define a length, and extending between first and second edges to define a width. A plurality of core extensions are formed as part of the body. The plurality of core extensions are positioned to be staggered relative to each other such that at least two adjacent core extensions are variable relative to each other in at least one dimension. A gas turbine engine component is also disclosed.