A pitot tube includes a substantially cylindrical body portion having an interior defining a flow passage. A tip portion extends along a pitot tube axis from the body portion. The tip portion includes a high thermal conductive insert. The body portion and the tip portion including the high thermal conductive insert are integrally formed.

A method for manufacturing a cast product in which a core can be easily discharged from a casting roughly-shaped material is provided. A method for manufacturing a cast product according to the present disclosure includes: a step of hermetically sealing a casting roughly-shaped material formed by casting using a core in a container containing water; a step of heating the water contained in the container while keeping the casting roughly-shaped material hermetically sealed and thereby destroying the core while keeping a pressure inside the container at a pressure higher than an atmospheric pressure, and thereby forming core sand; and a step of discharging the core sand from the casting roughly-shaped material.

An inner band used on a turbine engine is disclosed herein. The inner band may include a core comprising polymeric materials and a shell comprising nanocrystalline metallic materials applied to the core to cover at least a portion of the core.

Casting core for the manufacture of hollow metal aeronautical parts, in particular high-pressure turbine parts by lost-wax casting, including a composite material including on the one hand a first phase of formula M.sub.n+1AlC.sub.n, where n=1 to 3 and M being a transition metal selected from the group consisting of titanium and/or niobium and/or molybdenum, the composite material including on the other hand a second phase of formula Al.sub.4C.sub.3.

Casting core for the manufacture of hollow metal aeronautical parts, in particular high-pressure turbine parts by lost-wax casting, including a composite material including on the one hand a first phase of formula M.sub.n+1AlC.sub.n, where n=1 to 3 and M being a transition metal selected from the group consisting of titanium and/or niobium and/or molybdenum, the composite material including on the other hand a second phase of formula Al.sub.4C.sub.3.

Molding core for manufacturing an OMC hollow aeronautical part, in particular a fan module part, including a composite material including on the one hand a first phase of formula M.sub.n+1AlC.sub.n, where n=1 to 3, and M being a transition metal selected from the group consisting of titanium, niobium, chromium or zirconium, the composite material including on the other hand a second phase of formula Al.sub.4C.sub.3

A core discharge device is provided for discharging a sand core from a cast material in which the sand core contains a binder having water glass. The core discharge device comprises a humidified gas supply device that supplies humidified gas, to which humidity has been added, to the sand core inside the cast molded article. The core discharge device

A method for manufacturing a cast product in which a core can be easily discharged from a casting roughly-shaped material is provided. A method for manufacturing a cast product according to the present disclosure includes: a step of hermetically sealing a casting roughly-shaped material formed by casting using a core in a container containing water; a step of heating the water contained in the container while keeping the casting roughly-shaped material hermetically sealed and thereby destroying the core while keeping a pressure inside the container at a pressure higher than an atmospheric pressure, and thereby forming core sand; and a step of discharging the core sand from the casting roughly-shaped material.

A method for demolding a casting from a casting mold having at least one casting core which images a passage opening in the casting connecting two outer sides of the casting and is produced from a molding material bound by a binder which decomposes under the influence of temperature, wherein the casting mold undergoes a heat treatment in a furnace for the demolding, during which it is heated to a temperature at which the binder loses its binding effect. In the furnace, hot gas is flowed through a passage formed in the casting core of the casting mold, the temperature of the hot gas corresponding at least to the temperature at which the binder of the molding material loses it binding effect such that the casting core decomposes into fragments or separate sand particles as a consequence of the influence of the hot gas.

A method for casting cast parts in which a casting mould is provided. The casting mould is enclosed in a housing, forming a filling space between an inner surface section of the housing and an associated outer surface section of the casting mould. The filling space is then filled with a free-flowing filling material and molten metal is poured in the casting mould. As a consequence a binder of the mould material begins to vaporise and combust disintegrating the casting mould. During the filling of the filling space, the filling material has a minimum temperature, starting out from which the temperature of the filling material rises, to beyond a boundary temperature at which the vaporising binder ignites and combusts.