| 摘要 |
A method of making a component 110 & 120 from selectively sintered or melted powder layers 10 & 20 built upon a support plate 80, where first a plurality of columns 210 are built layer by layer on the support plate 80 and then the component 110 & 120 is built layer by layer on the columns 210. The non-solidified powder 220 located between the solidified columns 210 provides thermal insulation between the component 110 & 120 and the support plate 80 on which it is formed. The component 110 & 120 can be a turbine blade made from a nickel-based superalloy with the root 110 of the blade formed on the columns 210 and the airfoil 120 then formed on the root 110, or other components used in aviation which are made from a superalloy. |
