To provide a turbine blade, a manufacturing method for a turbine blade, and a gas turbine. In the turbine blade including a cooling passage provided along a blade height direction, the cooling passage includes: a first cooling hole including one end opening toward a front end, and having an inner diameter that is constant along the blade height direction; and a second cooling hole including one end communicating with the other end of the first cooling hole without a level difference, and having an inner diameter that is increased toward a base end. A length from the one end of the first cooling hole to a position where the first cooling hole and the second cooling hole are communicated with is 40% to 60% of a length from the one end of the first cooling hole to a gas path surface on the base end.

To provide a turbine blade, a manufacturing method for a turbine blade, and a gas turbine. In the turbine blade including a cooling passage provided along a blade height direction, the cooling passage includes: a first cooling hole including one end opening toward a front end, and having an inner diameter that is constant along the blade height direction; and a second cooling hole including one end communicating with the other end of the first cooling hole without a level difference, and having an inner diameter that is increased toward a base end. A length from the one end of the first cooling hole to a position where the first cooling hole and the second cooling hole are communicated with is 40% to 60% of a length from the one end of the first cooling hole to a gas path surface on the base end.

A system for forming features within composite components includes a tubular electrode extending along a longitudinal direction from a proximal end to a distal end. The distal end is, in turn, configured to be positioned relative to a machining surface of the composite component such that a spark gap is defined between the distal end and the machining surface. Furthermore, the tubular electrode further extends in a radial direction between an inner surface and an outer surface, with the inner surface defining a central passage configured to supply a dielectric fluid to the machining surface. The outer surface of the tubular electrode includes at least one a channel defined therein or a non-circular cross-sectional shape.

The present disclosure relates to an electrical discharge machining (EDM) device, and a method for machining a workpiece by the EDM device. The EDM device includes a spindle, a guide structure including a plurality of guideways, and a plurality of electrodes, the electrode coupled to the spindle via a flexible link, and slidably engaged with a respective one of the plurality of guideways.

A method for restoring a blade or vane platform of a gas turbine assembly configured for a power plant by: providing a blade or a vane having a platform with an edge deterioration zone; removing the deterioration zone by electro discharging machining technology; and rebuilding a removed zone by additive manufacturing technology. The removing can be performed to create a recessed plane along a platform edge, the recessed plane being connected to a platform plane by an enter inclined plane and an exit inclined plane arranged opposed along the platform edge.

A method for restoring a blade or vane platform of a gas turbine assembly configured for a power plant by: providing a blade or a vane having a platform with an edge deterioration zone; removing the deterioration zone by electro discharging machining technology; and rebuilding a removed zone by additive manufacturing technology. The removing can be performed to create a recessed plane along a platform edge, the recessed plane being connected to a platform plane by an enter inclined plane and an exit inclined plane arranged opposed along the platform edge.

A method for machining a blade and a blade for a turbomachine comprising a shroud which is positioned on a tip side of the blade. The shroud has an outer surface with at least one circumferential fin arranged thereon, whereby at least one section of the outer surface beside the at least one fin is processed in at least two manufacturing steps. At least one first section of the outer surface is processed to have a first shape and at least one second section of the outer surface is processed to have a second shape.

A method for machining a blade and a blade for a turbomachine comprising a shroud which is positioned on a tip side of the blade. The shroud has an outer surface with at least one circumferential fin arranged thereon, whereby at least one section of the outer surface beside the at least one fin is processed in at least two manufacturing steps. At least one first section of the outer surface is processed to have a first shape and at least one second section of the outer surface is processed to have a second shape.

The present disclosure relates to an electrical discharge machining (EDM) device, and a method for machining a workpiece by the EDM device. The EDM device includes a spindle, a guide structure including a plurality of guideways, and a plurality of electrodes, the electrode coupled to the spindle via a flexible link, and slidably engaged with a respective one of the plurality of guideways.

The invention provides a method for machining a shape such as slot or cavity or aperture using a plurality of first type holes (1) and second type holes (2), wherein during machining of first type holes (1) the hole circumference completely envelopes the respective portion of the electrode circumference.