The present disclosure is directed to a rotor blade and method for forming the rotor blade. The rotor blade includes a platform having a bottom side radially spaced from a top side and a leading edge portion axially spaced from a trailing edge portion. An airfoil extends radially outwardly from the top side of the platform and a shank extends radially inwardly from the bottom side of the platform. The shank includes a lip that extends axially outwardly from a forward wall of the shank. The lip defines a radially inward surface and a radially outward surface and a plurality of slots. Swirler vane inserts are disposed within respective slots of the plurality of slots. Each swirler vane insert extends radially inwardly from the inward surface of the lip and axially outwardly from the forward wall of the shank.

A turbine ring sector made of ceramic matrix composite material has a portion forming an annular base with an inner face for defining the inner face of a turbine ring when the ring sector is mounted on a ring support structure and an outer face from which there extends an attachment portion for attaching the ring sector to the ring support structure, the ring sector further including inter-sector faces, each for facing a neighboring ring sector when the ring sector is mounted on the ring support structure; wherein the inter-sector faces are coated in an environmental barrier that is doped with an electrically-conductive compound and that presents at least one slot.

A hollow portion is defined inside a stator blade, and a slit, extending in a height direction of the stator blade, opens to a surface of the stator blade and is in communication with the hollow portion. The slit is defined on the surface of the stator blade and includes a recess portion which is flat and has a longitudinal side extending in the height direction of the stator blade, and at least one through hole which opens to a bottom surface of the recess portion and to the hollow portion. In a projection plane to which a cross section of the slit is projected in the height direction of the stator blade, an area of an inlet opening of the through hole which opens to the bottom surface of the recess portion occupies a part of a projection width of the recess portion.

The gas turbine engine rotor assembly includes a rotor disc with a plurality of sealing tabs projecting radially out from a peripheral surface of the rotor disc in the rear end portion thereof. A said sealing tab is disposed at a tip portion of a fixing member of the disc, formed between pairs of blade root slots, adjacent a trailing edge of the rotor disc. The sealing tabs help to reduce the leakage of secondary air out the back of a blade pocket defined between adjacent blades mounted on the rotor disc.

An apparatus includes an electrode assembly comprising a carriage having a plurality of electrode holders, the electrode holders being respectively configured to detachably receive a plurality of electrodes, the electrodes include a plurality of first electrodes and a plurality of second electrodes. The first electrodes are configured for rough machining a workpiece by electric discharging or wire electric discharging to remove material from the workpiece, the second electrodes are configured for finish machining the rough machined workpiece by electric discharging to remove material from the rough machined workpiece.

A method for producing a cavity in a blade platform of a blade, in particular of a turbine blade, as part of a blade-platform cooling system, wherein the method has the steps of: producing a first bore from a first platform lateral face in the direction of an opposite second platform lateral face, with a first opening in the first platform lateral face being created, and expanding the first bore in a fan-like manner by an electrical discharge machining method, in particular using a wire- or bar-form electrode, such that the first opening, created in the first step, of the first bore represents the starting point of the fan-like expansion. A blade is produced in particular with such a method.

An apparatus and method relating to a film hole of a predetermined inner dimension in a component of a turbine engine that generates a hot combustion gas flow, and provides a cooling fluid flow, where a wall separates the hot combustion gas flow from the cooling fluid flow and defines a hot surface along which the hot combustion gas flows in a hot flow path and a cooled surface facing the cooling fluid flow including forming the hole in the component and applying a coating to the component such that the coating fills in portions of the film hole.

A vane cluster for a gas turbine engine includes an outer diameter platform and an inner diameter platform. A plurality of vanes span from the outer diameter platform to the inner diameter platform. At least one inbound region is defined between a first vane of the plurality of vanes and a second vane of the plurality of vanes. The first vane includes a suction side facing the inbound region. Each of the vanes includes a leading edge core passage and a trailing edge core passage. A plurality of electrical discharge machined (EDM) holes are disposed within at least 0.500 inches (12.7 mm) of a leading edge of the first vane. Each of the EDM holes connect a leading edge core passage of the vane to an exterior surface of the vane.

A system and method for improving sealing at a turbine blade tip shroud, while reducing weight associated with the improved sealing is disclosed. The gas turbine blade incorporates a tip shroud having one or more pockets located therein, where the one or more pockets remove weight from the shroud, thus reducing load on the blade attachment generated by additional sealing at the turbine blade shroud. Methods for incorporating the one or more tip shrouds in a new turbine blade or a repaired turbine blade are also disclosed.

A method of forming a film cooling hole in a component having an internal surface and an external surface is disclosed herein that includes forming the component with a first feature on the external surface, measuring a geometry of the external surface to determine a first placement of the first feature, and drilling the film cooling hole through the component at the first placement.