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.

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.

A tool for validating a wire-electric-discharge-machining (wEDM) operation to be performed using a wEDM machine comprises a body including an engagement feature shaped to removably hold a validation coupon to be machined in the wEDM operation, the validation coupon sized larger than a size of a cut-out to be made in a part using the wEDM machine. A method of manufacturing the tool and a wEDM machine assembly are also provided.

A method for modifying an aperture in a component, a system for modifying flow through a component, and a turbine component are disclosed. The method includes providing a substrate having at least one aperture having an electrically-conductive surface, providing a deposition device including an ESD torch, the ESD torch including an aperture penetrating electrode including a conductive material, inserting the aperture penetrating electrode at least partially into the aperture, and generating an arc between the aperture penetrating electrode and the electrically-conductive surface to deposit electrode material within the aperture. The system includes the ESD torch removably supported in an electrode holder. The turbine component includes at least one aperture having an electrospark deposited material along an electrically-conductive surface, the electrospark deposited material providing modified fluid flow through the turbine component.

A method for refurbishing an assembly having a first component and a second component is provided. The first component has a fore portion welded to the second component and a flared aft portion in proximity with the second component. The method includes processing the assembly such that the flared aft portion and a part of the fore portion proximal to the flared aft portion of the first component is subject to peening until the flared aft portion is plastically deformed from an initial position to a desired final position with respect to the second component.

Methods for forming airfoil, cores for forming airfoil, and airfoils for gas turbine engines are described. The methods include forming an airfoil body about a core assembly, the core assembly comprising at least one core structure having a radially extending purge slot protrusion extending from a portion of the at least one core structure, removing the core assembly from the airfoil body to form one or more internal cavities, wherein at least one internal cavity has a cavity extension define by the purge slot protrusion, and forming a squealer pocket in a tip of the formed airfoil body, wherein a cavity purge slot is formed at the cavity extension to fluidly connect the respect internal cavity with the squealer pocket. The radially extending protrusion has a radial height that is equal to or less than five times a width thereof.

A turbomachinery sealing apparatus including a first turbomachinery component having a first end face, and a seal extending away from the first end face, the seal being connected to a wall of the component by a tab extending between the wall and the seal.

The invention relates to a movable blade made of aluminum and titanium alloy, for a turbojet engine turbine comprising a vane and at least one root at a distal end of the vane. The root has at least one azimuthal contact surface with another directly adjacent blade. A hard abrasion-resistant material, called wear-resistant material, is deposited onto the at least one azimuthal contact surface. A cavity is produced in said at least one azimuthal contact surface, the wear-resistant material being deposited in the cavity.

Methods for forming airfoil, cores for forming airfoil, and airfoils for gas turbine engines are described. The methods include forming an airfoil body about a core assembly, the core assembly comprising at least one core structure having a radially extending purge slot protrusion extending from a portion of the at least one core structure, removing the core assembly from the airfoil body to form one or more internal cavities, wherein at least one internal cavity has a cavity extension define by the purge slot protrusion, and forming a squealer pocket in a tip of the formed airfoil body, wherein a cavity purge slot is formed at the cavity extension to fluidly connect the respect internal cavity with the squealer pocket. The radially extending protrusion has a radial height that is equal to or less than five times a width thereof.

Methods for forming airfoils, core assemblies, and airfoils for gas turbine engines are described. The methods include forming an airfoil body about a core assembly configured to define one or more internal cavities of the airfoil body, the core assembly comprising at least core structure having a purge slot protrusion extending from a portion of the core structure, removing the core assembly from the airfoil body to form one or more internal cavities, wherein at least one internal cavity has a cavity extension define by the purge slot protrusion, and forming a squealer pocket in a tip of the formed airfoil body, wherein a cavity purge slot is formed at the cavity extension to fluidly connect the respect internal cavity with the squealer pocket.