The present disclosure relates to generation of forming instructions to form one or more three-dimensional (3D) objects. Generation of the forming instructions may include selection of one or more formation variables to form at least a portion of the one or more 3D objects. Generation of the forming instructions may include selection of a speed, feature, and/or an effect manifested in at least a portion of the formed one or more 3D objects. The forming variable(s) may be associated with a patch of a model of the 3D object.

A turbomachine includes a shroud and a hub spaced apart from the shroud to channel an airflow along a direction. The turbomachine includes a plurality of airfoils coupled between the shroud and the hub. At least one airfoil of the plurality of airfoils includes a leading edge spaced apart from a trailing edge in the direction of the airflow and a pressure side opposite a suction side. The turbomachine includes at least one local vortex generator array defined on the suction side so as to extend onto the hub or the shroud. The at least one local vortex generator array is defined downstream of the leading edge.

Inventive techniques for forming unique compositions of matter are disclosed, as well as various advantageous physical characteristics, and associated properties of the resultant materials. In particular, metal(s) (including various alloys, such as Inconel superalloys) are characterized by having carbon disposed within the metal lattice structure thereof. The carbon is primarily, or entirely, present at interstitial sites of the metal lattice, and may be present in amounts ranging from about 15 wt % to about 90 wt %. The carbon, moreover, forms non-polar covalent bonds with both metal atoms of the lattice and other carbon atoms present in the lattice. This facilitates substantially homogeneous dispersal of the carbon throughout the resultant material, conveying unique and advantageous properties such as strength-to-weight ratio, density, mechanical toughness, sheer strength, flex strength, hardness, anti-corrosiveness, electrical and/or thermal conductivity, etc. as described herein. In some approaches, the composition of matter may be powderized, or the powder may be pelletized.

Methods for creating an aircraft turbomachine vane using additive manufacturing include additively manufacturing a vane on a bed of powder using selective laser melting, the additive manufacturing being performed on a support plate so that first or second circumferential edges are manufactured first directly on the support plate, at least one temporary support member being produced simultaneously with the first or second edges. The methods also include removing the temporary support member by breaking its connection with the leading or trailing edge with a tool that is engaged in at least one recess thereof.

There is provided a cobalt-based alloy product comprising: in mass %, 0.08-0.25% C; 0.1% or less B; 10-30% Cr; 5% or less Fe and 30% or less Ni, the total amount of Fe and Ni being 30% or less; W and/or Mo, the total amount of W and Mo being 5-12%; at least one of Ti, Zr, Hf, V, Nb and Ta, the total amount of Ti, Zr, Hf, V, Nb and Ta being 0.5-2%; 0.5% or less Si; 0.5% or less Mn; 0.003-0.04% N; and the balance being Co and impurities. The product is a polycrystalline body of matrix phase crystal grains. In the matrix phase crystal grains, post-segregation cells with an average size of 0.13-2 μm are formed, wherein components constituting an MC type carbide phase comprising Ti, Zr, Hf, V, Nb and/or Ta are segregated along boundary regions of the post-segregation cells.

There is provided a cobalt-based alloy product comprising: in mass %, 0.08-0.25% C; 0.1% or less B; 10-30% Cr; 5% or less Fe and 30% or less Ni, the total amount of Fe and Ni being 30% or less; W and/or Mo, the total amount of W and Mo being 5-12%; at least one of Ti, Zr, Hf, V, Nb and Ta, the total amount of Ti, Zr, Hf, V, Nb and Ta being 0.5-2%; 0.5% or less Si; 0.5% or less Mn; 0.003-0.04% N; and the balance being Co and impurities. The product is a polycrystalline body of matrix phase crystal grains. In the matrix phase crystal grains, post-segregation cells with an average size of 0.13-2 μm are formed, wherein components constituting an MC type carbide phase comprising Ti, Zr, Hf, V, Nb and/or Ta are segregated along boundary regions of the post-segregation cells.

A system may include a powder source; a powder delivery device; an energy delivery device; and a computing device. The computing device may be configured to: control the powder source to deliver metal powder to the powder delivery device; control the powder delivery device to deliver the metal powder to a surface of an abrasive coating; and control the energy delivery device to deliver energy to at least one of the abrasive coating or the metal powder to cause the metal powder to be joined to the abrasive coating.

A method of reprocessing a metal product includes a welding step for welding a dummy member to the metal product, a reprocessing step for reprocessing the metal product in a state where the metal product is supported by a first support unit and the dummy member is supported by a second support unit, and a removal step for removing the dummy member from the metal product after the reprocessing step. The reprocessing of the metal product while the metal product is fixed is thus enabled without restriction from the shape of the metal product.

A component with a region to be cooled having a cooling channel which is arranged and designed so as to cool the region of the component during operation by a fluid flow, wherein the cooling channel is defined by a first channel side facing the region and by a second channel side facing away from the region. The first channel side forms a larger contact surface for the cooling channel than the second channel side. An additive manufacture process can produce the component.

A method for forming a component for a gas turbine engine may include forming a first portion of the component that includes a cast metal or metal alloy, forming a second portion of the component that includes presintered preform defining at least one support structure, positioning the second portion on the first portion to define an assembly such that the first portion and the second portion define at least one cooling channel therebetween, and heating the assembly to join the first portion and the second portion and form the component.