Methods, structures, devices and systems are disclosed for fabricating and implementing nanoparticles with hollow core and sealable holes. In one aspect, a nanoparticle device can includes a shell structure including at least two layers including an internal layer and an external layer, the internal layer structured to enclose a hollow interior region and include one or more holes penetrating the internal layer, the external layer is of a porous material and formed around the internal layer and sealing the one or more holes, and a substance contained within the hollow interior region, the substance incapable of passing through the external layer.

The invention provides a device (200, 300, 400) for heating a continuous flow fluid. Said device (200, 300, 400) consists of a steel conduit (3, 3′, 3″) through which the fluid to be heated flows and of at least one sheathed resistor (2, 2c, 2d, 2e, 2f) that is parallel to the steel conduit (3, 3′, 3″) and that is in thermal contact therewith. The steel conduit (3, 3′, 3″) and the at least one heating element (2, 2c, 2d, 2e, 2f) are incorporated in a die-casting element made of an aluminium alloy.

A stack molding pattern and a shell for manufacturing aircraft turbine engine blades via lost wax casting. The stack molding shell includes a plurality of shell blade elements, each intended for producing a blade, wire elements being arranged within the shell blade elements; and a metal feeder including a plurality of metal outlets, each one radially open towards one of the shell blade elements and connected with the second end portion of the element. The shell includes a protective screen, associated with each second end portion and intended to protect a sensitive portion of the wire elements against the direct impact of a flow of metal from the feeder. The sensitive portion is located in the second end portion, downstream from the protective screen.

A method of manufacturing a crankshaft assembly includes configuring a crankshaft with a crankpin journal having a cavity extending at least partially from a first axial side to a second axial side of the crankpin journal, and opening at at least one of the first axial side and the second axial side. The method includes disposing a core plug in the cavity. The crankshaft has a first density and the core plug may have a second density which may be less than the first density. A crankshaft assembly includes the crankshaft and the core plug.

A die cast system in which an external shell and an internal core usable to form a component of a gas turbine engine are formed together is disclosed. In at least one embodiment, the external shell and internal core may be formed from at the same time via a selective laser melting process, thus eliminating the need for using the conventional lost-wax casting system. In at least one embodiment, the external shell and internal core may be formed a ceramic material that may support receiving molten metal to form a turbine component. Once formed, the external shell and internal core may be removed to reveal the turbine component.

To obtain an impact wave by generation of arc discharge between a high-voltage-side electrode 31 connected to a high-voltage-side terminal of a pulse power generating device and a low-voltage-side electrode 32 grounded or connected to a low-voltage-side terminal of the power source. One of the high-voltage-side electrode 31 or the low-voltage-side electrode 32 is an annular electrode formed in an annular shape, the other electrode is a core electrode arranged inside the annular electrode, and arc discharge is generated between an inner peripheral portion of the annular electrode and an outer peripheral portion of the core electrode.

A method for casting a turbine blade body comprises; providing a mold defining the external geometry of the blade body; providing a core defining an internal geometry of the blade body, the core comprising a main body defining an internal chamber of the blade body and having a root end and a tip end and a plurality of pedestals defining an array of cooling channels extending from the internal chamber; casting a molten material between the mold and the core; and removing the core after the molten material has solidified, wherein the pedestals are arranged in a single row starting from the root end to a mid-portion of the main body branching into multiple and divergent rows towards the tip end of the body.

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.

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.

A furnace for removing a molybdenum-alloy refractory metal core through sublimation comprising a retort furnace having an interior; a sublimation fixture insertable within the interior of the retort furnace, the sublimation fixture configured to receive at least one turbine blade having the molybdenum-alloy refractory metal core; a flow passage thermally coupled to the retort furnace configured to heat a fluid flowing through the flow passage and deliver the fluid to the molybdenum-alloy refractory metal core causing sublimation of the molybdenum-alloy refractory metal core.