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 method of forming a casting mold pattern that includes a core comprises mounting the core in a fixture such that the core is free of flexing imposed by the fixture. Material is removed from and/or added to a first and/or second mounting surface of the core. The core is then positioned in a die, and wax is conducted into the die to form the pattern. The amount of material removed from the first and/or second mounting surface is such that the core will be within a predetermined range of acceptable positions when the core is in the die with the first mounting surface engaging a first core locating surface of the die end with the second mounting surface engaging a second core locating surface of the die. The range of acceptable positions is determined relative to an ideal position of an ideal core.

A casting core containing a ceramic and having sufficient mechanical strength to withstand a casting process over a long period of time and good solubility in alkaline solutions. The casting core includes a core, a surface layer, and an intermediate layer between the core and the surface layer. The intermediate layer has a lower relative density than the surface layer and the core.

Provided is a multicore. The multicore includes a first core, being made of a water-insoluble material, having a hollow formed in the first core and, having an opening formed at both ends of the first core and connected to the hollow, a second core, being made of a water-soluble material and disposed inside the hollow, and a coating layer, being configured to surround the first core to prevent at least a portion of the first core and the second core from being exposed to an outside. Further, the first core includes a plurality of spaces to allow a fluid supplied to an interior of the first core to flow toward the second core.

A method of forming a cast heat exchanger plate includes forming at least one hot core plate defining internal features of a one piece heat exchanger plate and at least one first set of interlocking features. At least one cold core plate is formed defining external features of the heat exchanger plate and at least one second set of interlocking features. A core assembly is assembled wherein each hot core plate is directly interlocked to the at least one cold core plate. A wax pattern is formed with the core assembly. An external shell is formed over the wax pattern. The wax pattern is removed to form a space between the core assembly and the external shell. The space is filled with a molten material and cures the molten material. The external shell is removed. The core assembly is removed. A core assembly for a cast heat exchanger is also disclosed.

The present invention relates to a core for hollow product manufacture including a multilayer filling material, which may be used in forming a cooling water circulation channel through which a fluid such as cooling water may pass, and a method of manufacturing a hollow product using the core, and the core includes a pipe, having a hollow formed in the pipe and an opening formed at both ends of the pipe so that the hollow is exposed to the outside through the opening, a first support member, being disposed inside the hollow and having a space formed in the first support member, a second support member, being disposed in the space, and a melting bar, passing through the second support member in a longitudinal direction of the melting bar, wherein the melting bar melts and forms a space in the second support member when the melting bar is heated.

A core structure for a providing a cooling passage in a gas turbine engine includes a core body that has a first passage core. The first passage core has a first width in a chord-wise direction near a first wall. A second width in the chord-wise direction near a second wall. A third width in the chord-wise direction between the first and second walls. The third width being smaller than the first and second widths to form an hourglass shape.

A method for forming a wax model for the manufacture of turbine blades by lost-wax casting, in which a core is provided, a lower surface shell and an upper surface shell are positioned and bonded on either side of ducts of the core adjacent to the root, the core equipped with the lower surface shell and with the upper surface shell is positioned in an injection mold, wax is injected around the core equipped with the lower surface shell and with the upper surface shell, so as to form a wax model including a blade airfoil and a blade root including a fir tree, the lower surface shell and the upper surface shell being positioned around the core so as to form a portion of the fir tree of the wax model.

A core for the foundry of an aeronautical part such as a turbine blade, the core being intended to be disposed in an inner housing defined by a mold, the core comprising a body intended to form the internal shape of the turbine blade, an impact portion, disposed on at least a portion of the periphery of the body so as to break a fluid jet when filling the inner housing with the fluid, the impact portion comprising a top and at least one deflection wall converging towards the top.

Airfoils bodies having a first core cavity and a second core cavity located within the airfoil body that is adjacent the first core cavity. The second core cavity is defined by a first cavity wall, a second cavity wall, a first exterior wall, and a second exterior wall, wherein the first cavity wall is located between the second core cavity and the first core cavity and the first and second exterior walls are exterior walls of the airfoil body. The first cavity wall includes a first surface angled toward the first exterior wall and a second surface angled toward the second exterior wall. At least one first cavity impingement hole is formed within the first surface and a central ridge extends into the second core cavity from at least one of the first cavity wall and the second wall and divides the second core cavity into a two-vortex chamber.