Disclosed is a method for unpacking a component 11, produced by means of an additive manufacturing process, from a particulate material fill 9 of loose, unconsolidated particulate material, which is arranged together with the component 11 in a construction space 5 and surrounds the component 11. In order to unpack the component 11, the particulate material fill 9 surrounding the component 11 is transferred into a fluidized bed, so that the loose, unconsolidated particulate material is fluidized, and the fluidized, unconsolidated particulate material is drained downward off the construction space 5. In addition, a device for use in the method is described.

Disclosed is a method for unpacking a component 11, produced by means of an additive manufacturing process, from a particulate material fill 9 of loose, unconsolidated particulate material, which is arranged together with the component 11 in a construction space 5 and surrounds the component 11. In order to unpack the component 11, the particulate material fill 9 surrounding the component 11 is transferred into a fluidized bed, so that the loose, unconsolidated particulate material is fluidized, and the fluidized, unconsolidated particulate material is drained downward off the construction space 5. In addition, a device for use in the method is described.

A blade preform includes a strut connecting a plat-form to a blade root portion extending longitudinally in an upstream-downstream direction, an upstream web and a downstream web, which each extend in a direction substantially perpendicular to the longitudinal direction of the blade root and are formed at the upstream and downstream ends of the strut. The upstream and downstream webs connect the upstream and downstream ends of the plat-form to the upstream and downstream ends of the blade root. The blade root extends in a direction perpendicular to the longitudinal direction of the blade root over a distance smaller than that of the upstream and downstream webs and the side edges of each web are extended by walls that converge at the flanks of the blade root.

A blade preform includes a strut connecting a plat-form to a blade root portion extending longitudinally in an upstream-downstream direction, an upstream web and a downstream web, which each extend in a direction substantially perpendicular to the longitudinal direction of the blade root and are formed at the upstream and downstream ends of the strut. The upstream and downstream webs connect the upstream and downstream ends of the plat-form to the upstream and downstream ends of the blade root. The blade root extends in a direction perpendicular to the longitudinal direction of the blade root over a distance smaller than that of the upstream and downstream webs and the side edges of each web are extended by walls that converge at the flanks of the blade root.

A method is provided for making a mold for casting advanced turbine airfoils (e.g. gas turbine blade and vane castings) which can include complex internal and external air cooling features to improve efficiency of airfoil cooling during operation in the gas turbine hot gas stream. The method steps involve incorporating at least one fugitive insert in a ceramic material in a manner to form a core and at least a portion of an integral, cooperating mold wall wherein the core defines an internal cooling feature to be imparted to the cast airfoil and the at least portion of the mold wall has an inner surface that defines an external cooling feature to be imparted to the cast airfoil, selectively removing the fugitive insert, and incorporating the core and the at least portion of the integral, cooperating mold wall in a mold for receiving molten metal or alloy cast in the mold.

A method is provided for making a mold for casting advanced turbine airfoils (e.g. gas turbine blade and vane castings) which can include complex internal and external air cooling features to improve efficiency of airfoil cooling during operation in the gas turbine hot gas stream. The method steps involve incorporating at least one fugitive insert in a ceramic material in a manner to form a core and at least a portion of an integral, cooperating mold wall wherein the core defines an internal cooling feature to be imparted to the cast airfoil and the at least portion of the mold wall has an inner surface that defines an external cooling feature to be imparted to the cast airfoil, selectively removing the fugitive insert, and incorporating the core and the at least portion of the integral, cooperating mold wall in a mold for receiving molten metal or alloy cast in the mold.

A plurality of upper fins and a plurality of lower fins are each provided in an EGR passage so as to be adjacent to each other across a predetermined space in a direction perpendicular to an exhaust-gas flow direction. The upper fins and the lower fins are gradually narrowed in width toward their respective projection directions, so that both sides thereof in their width direction have inclined surfaces. A tilt angle of the inclined surfaces of the lower fins is made larger than a tilt angle of the inclined surfaces of the upper fins.

The device according to any of the preceding claims 13 to 19, characterized in that the device is further configured to carry out a method comprising the step of positioning the green sand mold (3), wherein the device is provided with levelling means configured to hold an upper side of the green sand mold (3) during step c in a parallel position in relation to a gravitationally horizontal plane.

A method for chemically pickling a cast metal part, including a metal envelope which delimits an inner space in which at least one porous ceramic core is housed, and an outer space, the ceramic core being in fluid communication with the outer space, which method including: filling the pores of the ceramic core with a liquid; and then chemically pickling the cast metal part. This chemical pickling method may be implemented in a method for manufacturing a metal part by investment casting. This method is applicable at least to manufacture of turbine blades for turbomachines and, especially, for aircraft turbojet engines.

A method for chemically pickling a cast metal part, including a metal envelope which delimits an inner space in which at least one porous ceramic core is housed, and an outer space, the ceramic core being in fluid communication with the outer space, which method including: filling the pores of the ceramic core with a liquid; and then chemically pickling the cast metal part. This chemical pickling method may be implemented in a method for manufacturing a metal part by investment casting. This method is applicable at least to manufacture of turbine blades for turbomachines and, especially, for aircraft turbojet engines.