A method for making a cooled component for a turbine engine includes casting an airfoil assembly having an airfoil with an airfoil cooling passage and extending from a platform with at least one platform cooling passage, and forming a connecting passage between the airfoil cooling air passage and the platform cooling air passage via a tool inserted into a breakout opening in a slashface of the platform.

A method and casting core for forming a landing for welding a baffle inserted into an airfoil are disclosed, wherein the baffle landing of the blade or vane is formed in investment casting by the casting core rather than by wax, reducing tolerances and variability in the location of the baffle inserted into the cooling cavity of airfoil when the baffle is welded to the baffle landing.

A core (1) for producing castings (100) in a modular mould; each casting (100) having at least one thermally activatable portion (102) shaped so that it can face a heat source (HS); each casting (100) having at least one duct (106) contained inside the portion (102); the duct (106) being fluid tight so that a fluid can flow through it; the core (1) having a suitable shape to form, in negative, the duct (106); the core (1) comprising at least one insert (20)(20′)(20″) shaped so as to define at least two passages (200)(200′) for the fluid inside the duct (106).

A method includes: forming a sand core including a main portion and core-head members connecting the main portion; applying a casting process to produce a frame casting having a first end, a first-end inner wall, a second end, a second-end inner wall, a closed water channel between the first-end inner wall and the second-end inner wall, a water inlet, a water outlet and sand-expelling holes at the first end; shaking the frame casting to have part of the sand core to leave the closed water channel via the water inlet, the water outlet and the sand-expelling holes; pressurizing a fluid into the closed water channel via the water inlet to carry the rest of the sand core to leave the closed water channel via the sand-expelling holes and the water outlet; and applying screw bolts to lock the sand-expelling holes to manufacture a closed-type and liquid-cooling motor frame.

A core shooting machine (1) for producing cores by a process of shooting a core sand mixture (21) into a at least one cavity (19) in a core box (18), the core shooting machine (1) having a source of compressed air (10) at an adjustable initial machine pressure (P.sub.0), a shooting head (13) fluidically coupled to the source of compressed air (10) by at least one conduit (12) that includes an electronically controlled shot valve (11), the shooting head (13) being configured for containing an amount of the core sand mixture (21), resulting in a filling degree of the shoot head (13), and a computing device (50,60) associated with the core shooting machine (1) and being configured to perform a simulation of the process.

An investment casting core (10) incorporates an alignment guide (24) extending through a body (12) of the core. The alignment guide (24) defines a coolant flow path (92) in a later-cast metal component (76) extending from a coolant outlet opening (90) in an impingement structure (88) to an impingement target area (86) of a cooling feature (84) formed on an impingement cooled surface (82) of the component (76). Methods of making the core (10) and using the core (10) in lost wax investment casting processes are also described.

Partial integrated core-shell investment casting molds that can be assembled into complete molds are provided herein. 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. Core filaments that can be used to supplement the leaching pathway, for example in a core tip portion of the mold are also provided herein.

An aircraft turbine engine blade includes at least one inner cavity for circulating a ventilation air flow and having a wall with first projecting elements oriented in a first direction and forming air flow disrupters, and at least a second projecting element oriented in a second direction different from the first direction. The second projecting element and at least one of the first projecting elements overlap each other in one area. At least one of the first projecting elements overlaps the second projecting element and has a height (H2, H4′) which is greater than that of the second projecting element in the area and greater than that of the other first projecting elements of the wall, in order to retain its disruptive function along the entire length thereof.

A casting core assembly is disclosed herein. The casting core assembly comprises a casting core and a bumper assembly. The bumper assembly is disposed on an outer surface of the casting core. The bumper assembly comprises a receptacle and a metal apparatus. The metal apparatus may be a pin, a sphere, or the like.

A tool is provided for positioning a core stabilizing pin into a preassigned hole of a plurality of holes formed in an additively manufactured mold. The tool has a main body, a pin cavity, and a standoff. When the tool is used to insert a core stabilizing pin, of a precise, controlled length, into a preassigned hole, and the core stabilizing pin is inserted until the mold engagement end contacts the outer surface of the mold, the angle of the preassigned hole and thickness of the mold precisely positions the core stabilizing pin to engage and stabilize the core.