A method of remanufacturing a turbine blade having a platform includes placing a puck against a surface of the platform. The method may include electrical discharge machining an interface between the puck and the platform and brazing the puck to the platform. A total radial thickness of a finally remanufactured platform of the remanufactured turbine blade is greater than an initial radial thickness of the platform before remanufacturing the turbine blade.

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.

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 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.

A method for the machining of workpieces (11) and inspection of the processed workpiece surface in a machine tool (1), preferably a die sinking electrical discharge machine. The method uses at least one machining process interruption during which the processed surface of the workpiece (11) is inspected. Within said machining process interruption, at least one image of the processed workpiece surface is captured on the machine tool (1) by means of a digital camera (12). The images are processed by one or two pattern recognition algorithm (PRA D, PRA S), which were previously trained to determine the surface characteristics such as roughness parameters, functional surface features and/or characteristic defects of the processed workpiece surface captured on that at least one image. The determined surface characteristics are used to resume the processing of the workpiece surface with or without adjusting the processing parameters.

The invention relates to a method for manufacturing an equipment part, comprising the following steps: providing a substrate, an upper face of which includes a large main surface; providing a computer model comprising spatial coordinates of said main surface and a second portion of the equipment part; then additive manufacturing of the second portion from the main surface, so as to secure said main surface and said second portion; then cutting in a thickness of the substrate to obtain a thin plate including the main surface secured to the second portion of the equipment part.

The invention relates to a method for manufacturing an equipment part, comprising the following steps: providing a substrate, an upper face of which includes a large main surface; providing a computer model comprising spatial coordinates of said main surface and a second portion of the equipment part; then additive manufacturing of the second portion from the main surface, so as to secure said main surface and said second portion; then cutting in a thickness of the substrate to obtain a thin plate including the main surface secured to the second portion of the equipment part.

A punch, such as a socket punch, with an angle on a portion of the punch and method of manufacturing a punch with an angle on a portion of the punch using wire EDM. A punch for a cold forming process includes a base portion adapted to be a structural backbone for the punch and a work portion extending from the base portion that performs a punching operation. In addition, grooves and a hex portion are formed in the working portion with an electric discharge machining (EDM) machine. Further, a cone point is machined on an end of the hex portion and a land area with an inwardly tapered angle formed between the hex portion and the cone point. The punch can be manufactured more quickly and from a CAD model, therefore removing the need for over-specialized equipment and improving manufacturing times.

A cable includes: a linear conductor; a plurality of resin hollow tubes which are disposed around the conductor so that an air layer is formed around the conductor and which extend in a longitudinal direction of the conductor; and an insulating protective member configured to protect the conductor and the plurality of hollow tubes.