A closure element for an internal passage in a component, and a related method and turbine blade or nozzle are disclosed. The closure element includes a spherical body made of a first superalloy, and a plurality of extensions extending from a surface of the spherical body. The plurality of extensions made of the same, similar or different material other than the first superalloy. Subjecting the component to at least one thermal cycle causes a braze material to form a metallurgical bond with the spherical body, the plurality of extensions and the passage wall to seal the internal passage.

An airfoil for a gas turbine engine. The airfoil includes a unique cooling path for a coolant, routing the coolant through a cooling cavity, through a column of crossover passages and through a pin array near a trailing edge of the airfoil. The crossover passages produce impingement cooling and the pin array produces convective cooling. This combination of impingement cooling and convective cooling results in increased cooling of the airfoil and better aeromechanical life objectives.

The present disclosure generally relates to partial integrated core-shell investment casting molds that can be assembled into complete molds. Each section of the partial mold may contain both a portion of a core and portion of a shell. Each section can then be assembled into a mold for casting of a metal part. The partial integrated core-shell investment casting molds and the complete molds may be provided with filament structures corresponding to cooling hole patterns on the surface of the turbine blade or the stator vane, which provides a leaching pathway for the core portion after metal casting. The invention also relates to core filaments that can be used to supplement the leaching pathway, for example in a core tip portion of the mold.

An investment casting process for manufacturing a cast component is provided. The investment casting process includes forming a core, casting the cast component about the core such that a core positioning feature provides a location of an anticipated pilot hole in the cast component, removing the core from the cast component once the casting is completed, locating, forming and sizing a pilot hole to form a resized pilot hole that can receive a sealing plug and installing the sealing plug into the resized pilot hole.

A method includes casting a metallic material (56) in a mold (20) containing a core, the core having a substrate (40, 44) coated with a coating (42). A removing of the metallic material from the mold and decoring leaves a casting having a layer formed by the coating. The coating has a ceramic having a porosity in a zone (50) near the substrate less than a porosity in a zone (52) away from the substrate.

A production method for a component having integrated channels for internal fluid guidance, having a first region, which is connected to a second region, and wherein the channels extend both through the first region and through the second region. The geometry of the component is modified to the technological characteristics of both production methods. The first region is produced by a method for casting using lost models without undercuts, and proceeding from the first region, the second region is built up using an additive manufacturing method.

A method for manufacturing a blade, the method includes casting a nickel alloy blade precursor having an airfoil and a root. The airfoil and the root are solution heat treating differently from each other. After the solution heat treating, the root is wrought processed. After the wrought processing, an exterior of the root is machined.

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.

A method is provided for casting a component. Accordingly, a casting core is provided within a cavity of a component mold. The casting core defines an inner component shape and includes a core wall. The core wall defines a core outer surface and a core inner surface disposed opposite the core outer surface. The core inner surface defines a core cavity. The casting core also includes a removal facilitation feature. The component is cast within the cavity of the component mold with the casting core positioned therein. The cast component is removed from the component mold and the casting core is removed from the cast component.

The invention concerns a method for coating a core (1) for producing a turbomachine part (2) by isostatic compacting, for example a leading-edge shield of a blade, the coating method comprising the steps of:—S1: covering the core (1) by means of a first solution comprising a first refractory component configured to oppose the diffusion of species, the first component comprising a metal oxide,—S2: covering the core (1) by means of a second solution comprising a second component designed to bind the first component in such a way as to form a homogeneous layer, the second component comprising a mineral binder;—S3: applying a heat treatment to the covered core (1) in such a way as to dry the solution and solidify the coating.