Patent classifications
B22C1/00
Gypsum composition for refractory moulds
The invention relates to a mineral composition for the preparation of foundry molds, comprising: (a) from 20% to 90% by weight of plaster, (b) from 10% to 80% by weight of a mineral component based on silica and/or alumina, and (c) from 0.5% to 4.8%, preferably from 1.5% to 4.5% and in particular between 2% and 4.5% by weight, of a mineral powder having a thermal conductivity (), at 20 C., of greater than 15 W/(m.Math.K) and a specific surface area of greater than 10 m.sup.2/g, these percentages being relative to the total weight of the sum of the components (a), (b) and (c).
Gypsum composition for refractory moulds
The invention relates to a mineral composition for the preparation of foundry molds, comprising: (a) from 20% to 90% by weight of plaster, (b) from 10% to 80% by weight of a mineral component based on silica and/or alumina, and (c) from 0.5% to 4.8%, preferably from 1.5% to 4.5% and in particular between 2% and 4.5% by weight, of a mineral powder having a thermal conductivity (), at 20 C., of greater than 15 W/(m.Math.K) and a specific surface area of greater than 10 m.sup.2/g, these percentages being relative to the total weight of the sum of the components (a), (b) and (c).
Additively manufactured casting articles for manufacturing gas turbine engine parts
A casting article according to an exemplary aspect of the present disclosure includes, among other things, a circuit forming portion and an interior channel formed inside of the circuit forming portion. The interior channel defines a leaching path that extends at least partially through the circuit forming portion.
Additively manufactured casting articles for manufacturing gas turbine engine parts
A casting article according to an exemplary aspect of the present disclosure includes, among other things, a circuit forming portion and an interior channel formed inside of the circuit forming portion. The interior channel defines a leaching path that extends at least partially through the circuit forming portion.
Dual investment shelled solid mold casting of reticulated metal foams
A method to manufacture reticulated metal foam via a dual investment, includes pre-investment of a precursor with a diluted pre-investment ceramic plaster then applying an outer mold to the encapsulated precursor as a shell-mold.
Dual investment shelled solid mold casting of reticulated metal foams
A method to manufacture reticulated metal foam via a dual investment, includes pre-investment of a precursor with a diluted pre-investment ceramic plaster then applying an outer mold to the encapsulated precursor as a shell-mold.
Three-dimensional manufacturing methods and systems for turbine components
The present application provides a method of producing a component. The method may include the steps of creating a dissolvable ceramic material mold in an additive manufacturing process, casting a metallic material in the dissolvable ceramic material mold, creating the component, and dissolving the dissolvable ceramic material. The component may be a turbine component.
Three-dimensional manufacturing methods and systems for turbine components
The present application provides a method of producing a component. The method may include the steps of creating a dissolvable ceramic material mold in an additive manufacturing process, casting a metallic material in the dissolvable ceramic material mold, creating the component, and dissolving the dissolvable ceramic material. The component may be a turbine component.
Foundry core for manufacturing a hollow metal aeronautical part
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.
Foundry core for manufacturing a hollow metal aeronautical part
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.