Method of making a pre-sintered preform
A method of making a pre-sintered preform, including forming a pre-sintered preform by a binder jet additive manufacturing technique. The binder jet additive manufacturing technique includes depositing a first powder layer including a first powder and a second powder followed by depositing a first binder at a pre-determined location of the first powder layer. The binder jet additive manufacturing technique also includes depositing a second powder layer over at least a portion of the first powder layer followed by depositing a second binder at a pre-determined location of the second powder layer. At least a portion of the first binder and at least a portion of the second binder is cured forming a green part. The green part is then densified to form a pre-sintered preform near net shape component.
1. A method of making a near net shape component, comprising in order:
forming a near net shape component by a binder jet additive manufacturing technique, the binder jet additive manufacturing technique including:
depositing a first powder layer including a first metal powder and a second metal powder, the second metal powder having a melting point at least 200° C. higher than the first metal powder;
depositing a first binder at a pre-determined location of the first powder layer;
depositing a second powder layer over at least a portion of the first powder layer;
depositing a second binder at a pre-determined location of the second powder layer; and
at least partially curing at least a portion of the first binder and at least a portion of the second binder to form a near net shape green part,
wherein the second metal powder is selected from the group consisting of GTD 111, GTD 222, HASTELLOY X, HAYNES 230, Inconel 600, Inconel 625, Inconel 718, Inconel 738, Inconel 939, MAR-M-247, René 108, René N5, FSX 414, HAYNES 188, MAR-M-509, and combinations thereof.
2. The method of claim 1 , further comprising densifying the green part to form a pre-sintered preform near net shape component of a turbine article.
3. A method of making a near net shape component, comprising in order:
forming a near net shape component by a binder jet additive manufacturing technique, the binder jet additive manufacturing technique including:
depositing a first powder layer including a first metal powder and a second metal powder, the second metal powder having a melting point at least 200° C. higher than the first metal powder;
depositing a first binder at a pre-determined location of the first powder layer;
depositing a second powder layer over at least a portion of the first powder layer;
depositing a second binder at a pre-determined location of the second powder layer; and
at least partially curing at least a portion of the first binder and at least a portion of the second binder to form a near net shape green part;
wherein the second binder is different from the first binder, and
wherein the second metal powder is selected from the group consisting of GTD 111, GTD 222, HASTELLOY X, HAYNES 230, Inconel 600, Inconel 625, Inconel 718, Inconel 738, Inconel 939, MAR-M-247, René 108, René N5, FSX 414, HAYNES 188, MAR-M-509, and combinations thereof.
4. The method of claim 3 , wherein the second powder layer includes a third powder; and wherein the third powder is different from the first metal powder and the second metal powder.
5. The method of claim 3 , further comprising densifying the green part to form a pre-sintered preform near net shape component of a turbine article.
6. A method of making a near net shape component, comprising in order:
forming a near net shape component by a binder jet additive manufacturing technique, the binder jet additive manufacturing technique including:
depositing a first powder layer including a first metal powder and a second metal powder, the second metal powder having a melting point at least 200° C. higher than the first metal powder;
depositing a first binder at a pre-determined location of the first powder layer;
depositing a second powder layer including a third powder over at least a portion of the first powder layer;
depositing a second binder at a pre-determined location of the second powder layer; and
at least partially curing at least a portion of the first binder and at least a portion of the second binder to form a near net shape green part;
wherein the third powder is different from the first metal powder and the second metal powder, and
wherein the second metal powder is selected from the group consisting of GTD 111, GTD 222, HASTELLOY X, HAYNES 230, Inconel 600, Inconel 625, Inconel 718, Inconel 738, Inconel 939, MAR-M-247, René 108, René N5, FSX 414, HAYNES 188, MAR-M-509, and combinations thereof.
7. The method of claim 6 , further comprising densifying the green part to form a pre-sintered preform near net shape component.
8. The method of claim 7 , further comprising assembling a turbine article, the assembling a turbine article including securing the pre-sintered preform near net shape component to a turbine article component to form the turbine article.
9. The method of claim 8 , wherein the turbine article is selected from the group consisting of a turbine bucket, a turbine nozzle, a turbine shroud, an airfoil, and combinations thereof.
10. The method of claim 8 , wherein the securing the pre-sintered preform near net shape component comprises welding, mechanical, brazing, laser welding, friction welding, ultrasonic welding, additive manufacturing, and combinations thereof.
11. The method of claim 7 , further comprising configuring the pre-sintered preform near net shape component to allow a fluid flow through the pre-sintered preform near net shape component.
12. The method of claim 7 , wherein the pre-sintered preform near net shape component is selected from the group consisting of a turbine bucket, a turbine nozzle, a turbine shroud, an airfoil, and combinations thereof.
13. The method of claim 7 , wherein densifying the green part includes sintering, solutionizing, aging, and combinations thereof.
14. The method of claim 13 , wherein the densifying includes sintering.
15. The method of claim 6 , further comprising infiltrating the green part with an infiltration material.
16. The method of claim 15 , wherein the infiltration material is selected from the group consisting of copper alloys, nickel alloys, cobalt alloys, and palladium alloys.
17. The method of claim 6 , further comprising heating the green part to a temperature above the melting point of the first metal powder and below the melting point of the second metal powder.
18. The method of claim 6 , wherein the first powder layer further includes carbon nanoparticles or ceramic fibers.
19. The method of claim 18 , wherein the first powder layer includes the carbon nanoparticles; and wherein the carbon nanoparticles include at least one of single wall carbon nanotubes, multi-wall carbon nanotubes, or carbon nanofibers.
20. The method of claim 18 , wherein the first powder layer includes the ceramic fibers; and wherein the ceramic fibers include at least one of silicon carbide, silicon nitride, alumina, aluminum nitride, titanium boride, titanium nitride, titanium carbide, or boron carbide.