A method for manufacturing a blade with a first portion and a second portion, the method includes forming the first portion that includes forming a model of the first portion from removable material, forming a first shell mould from the model of the first portion, and forming the single-crystal or columnar first portion m a first metal alloy in the first shell mould from a single-crystal seed, and forming the second portion in which the second portion is formed on the first portion, and in which the first portion and the second portion are made from different materials, the second portion being polycrystalline and formed from a second metal alloy. The blade includes a single-crystal or columnar first portion made from a first metal alloy and a polycrystalline second portion made from the second metal alloy different from the first metal alloy.

A medical scope device such as an endoscope is produced using a cast aluminum process including a molten casting aluminum alloy including a maximum of 0.2 - 0.3% Si and at least 5% Zn. The process includes providing an investment casting mold, casting the aluminum alloy in the mold to create a component and removing the mold from the component, post-machining the component to meet a desired specification, and after post-machining the component, performing surface finishing, such as centrifugal barrel finishing (CBF) sufficient to remove impurities on casting surfaces by 2 - 3 mils, then coating the component with a micro-crystalline aluminum anodic coating of at least 0.5 mil thickness. A medical scope and product-by-process is also provided employing such techniques.

A turbine blade including an airfoil portion having a leading edge, a trailing edge, and a pressure surface and a suction surface extending between the leading edge and the trailing edge. The airfoil portion internally forming a cooling passage, which includes first and second cooling passages, and a plurality of outflow passages each having one end which opens to a merging portion formed by connecting an end portion of the first cooling passage on a side of the trailing edge and an end portion of the second cooling passage on the side of the trailing edge, and another end which opens to the trailing edge. The first cooling passage and the second cooling passage are divided by a partition member disposed in the airfoil portion. The cooling passage includes pressure side pin fins in the first cooling passage, and suction side pin fins in the second cooling passage.

A refractory metal core (RMC) finishing method according to an exemplary aspect of the present disclosure includes, among other things, performing a plurality of finishing operations on a plurality of RMC samples, analyzing one or more properties of at least a portion of the plurality of RMC samples and selecting a combination of finishing operations for generating an RMC having desirable properties for manufacturing a part free from defects.

A refractory metal core (RMC) finishing method according to an exemplary aspect of the present disclosure includes, among other things, performing a plurality of finishing operations on a plurality of RMC samples, analyzing one or more properties of at least a portion of the plurality of RMC samples and selecting a combination of finishing operations for generating an RMC having desirable properties for manufacturing a part free from defects.

A method of forming a cast component and a method of forming a casting mold is described herein. The ceramic core-shell mold includes at least first core portion, a first shell portion, and at least one first cavity between the core portion and the first shell portion. The core-shell mold may be manufactured using an additive manufacturing process and may include an integrated ceramic filter. At least a portion of the ceramic core-shell mold and the wax gate component is coated with a second ceramic material. The wax gate component is then removed to form a second cavity in fluid communication with the first cavity.

A method for producing a flexible tooling liner for casting a ceramic core is presented. The method includes the steps of producing a three-dimensional (3D) reference object representative of a ceramic core to be cast, disposing the reference object into a containment vessel configured to receive a liquid flexible tooling material, filling the containment vessel with the liquid tooling material so that the reference object is encapsulated by the liquid tooling material on the surface whose topography is intended to be imparted, allowing the liquid tooling material to cure, and separating the cured flexible tooling along a parting surface into opposing portions and removing the reference the reference object.

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.

A manufacturing process for blades of a turbomachine, e.g. a gas turbine engine for an aircraft. In the process: a) a ceramic core piece that comprises at least two ceramic core elements and a clamping part that connects the ceramic core elements, is positioned in a wax forming device, subsequently; b) a molten wax material is applied to the outside of the ceramic core piece in the wax forming device and the wax is allowed to solidify, and subsequently; c) at least two turbomachine blades are cast using a crystallographically-oriented metal casting process and the wax and the ceramic core piece are removed.

A breathable salt core is provided that is placed in a cavity of a casting mold in order to mold a hollow part of a cast product and that is dissolved and removed after casting, the breathable salt core being formed by powder molding innumerable salt particles into a predetermined shape corresponding to the hollow part, wherein a gap that can retain a gas remaining in the cavity in a casting process is formed between the innumerable salt particles that have been powder molded. The breathable salt core thus manufactured assures that residual gas within the cavity pushed by the molten metal to enter the gap formed between salt particles of the salt core, thereby avoiding any incomplete filling of the molten metal, and which can be formed with a simple production process at a low cost.