# US 2014/0190649 A1 · Case corrosion-resistant liners in nozzles and case bodies to eliminate overlays > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2014/0190649 A1 - Document ID: US20140190649A1 - Status: Published application - Kind: A1 - Application number: 14/100,551 - Filed: 2013-12-09 - Published: 2014-07-10 - Earliest claimed: 2012-12-14 - Assignees: Dresser-Rand Company - Applicants: Dresser-Rand Company - Inventors: Byron L. Mohr - Web page: https://patentgrep.com/patent/US20140190649A1 ## CPC - B22D 19/16: for making compound objects cast of two or more different metals, e.g. for making rolls for rolling mills (casting compound ingots B22D7/02) - B22C 9/02: Sand moulds or like moulds for shaped castings - B22D: CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES (shaping of plastics or substances in a plastic state B29C; metallurgical processing, selection of substances to be added to metal C21, C22) - B22C: FOUNDRY MOULDING (moulding refractory materials in general B28B) ## Abstract A method for protecting a turbomachine from corrosion may include creating a first sand mold in a drag of a casting flask, coupling a cope of the casting flask to the drag, removing the runner pin and the at least one riser pin from the cope to expose a runner and at least one riser, respectively, and pouring a molten first material in the runner to cast a first component of the turbomachine. The method may further include removing the first sand mold, creating a second sand mold utilizing the first component in the drag, coupling the cope to the drag, removing the runner pin and the at least one riser pin from the cope to expose a runner and at least one riser, respectively, and pouring a molten second material in the runner to cast a second component of the turbomachine integral with the first component. ## Claims ### Claim 1 A method for protecting a turbomachine from corrosion, comprising: casting a first component of the turbomachine; and using the first component to cast a second component of the turbomachine integral with the first component, one of the first component and the second component being corrosion resistant. ### Claim 2 (depends on 1) The method of claim 1, wherein the first component is a nozzle and the second component is a corrosion-resistant liner. ### Claim 3 (depends on 2) The method of claim 2, wherein casting the nozzle comprises: creating a sand mold in a drag of a casting flask, the sand mold defining an in-gate and a hollow region; coupling a cope of the casting flask to the drag, the cope including a runner pin and at least one riser pin; removing the runner pin and the at least one riser pin to expose a runner and at least one riser, respectively; and pouring a molten nozzle material in the runner to cast the nozzle. ### Claim 4 (depends on 3) The method of claim 3, wherein the in-gate defines a depression and a passageway, and wherein the cope is coupled to the drag such that the runner aligns with the depression and the at least one riser aligns with the passageway. ### Claim 5 (depends on 3) The method of claim 3, further comprising: disposing a first core in the hollow region of the sand mold, wherein the molten nozzle material occupies a space between the first core and the sand mold. ### Claim 6 (depends on 3) The method of claim 3, wherein the hollow region is in a shape of the nozzle. ### Claim 7 (depends on 2) The method of claim 2, wherein casting the corrosion-resistant liner comprises: creating a sand mold in a drag of a casting flask, the sand mold including the nozzle and defining an in-gate; coupling a cope of the casting flask to the drag, the cope including a runner pin and at least one riser pin; removing the runner pin and the at least one riser pin to expose a runner and at least one riser, respectively; and pouring molten corrosion-resistant liner material in the runner to cast the corrosion-resistant liner integral with the nozzle. ### Claim 8 (depends on 7) The method of claim 7, further comprising: disposing a first core in the nozzle, wherein the molten corrosion-resistant liner material occupies a space formed between the nozzle and the first core. ### Claim 9 (depends on 7) The method of claim 7, wherein the in-gate defines a depression and a passageway, and wherein the cope is coupled to the drag such that the runner aligns with the depression and the at least one riser aligns with the passageway. ### Claim 10 (depends on 2) The method of claim 2, wherein the corrosion-resistant liner comprises one or more stainless steel alloys, one or more nickel alloys, one or more cobalt alloys, titanium, zirconium, or combinations thereof. ### Claim 11 (depends on 2) The method of claim 2, wherein the nozzle comprises carbon steel or alloy steel. ### Claim 12 (depends on 5) The method of claim 5, wherein the first core defines an outer surface of the corrosion-resistant liner. ### Claim 13 (depends on 8) The method of claim 8, wherein the first core defines an inner surface of the corrosion-resistant liner. ### Claim 14 A method for protecting a turbomachine from corrosion, comprising: creating a first sand mold in a drag of a casting flask, the first sand mold defining a first in-gate and a hollow region; pouring a molten first material in the first sand mold to cast a first component of the turbomachine; creating a second sand mold in the drag of the casting flask, the second sand mold utilizing the first component; and pouring a molten second material in the second sand mold to cast a second component of the turbomachine integral with the first component, one of the first component and the second component being corrosion-resistant. ### Claim 15 (depends on 14) The method of claim 14, wherein the molten first material is a molten nozzle material, the first component is a nozzle of the turbomachine, a molten second material is a molten corrosion-resistant liner material, and the second component is a corrosion-resistant liner. ### Claim 16 (depends on 15) The method of claim 15, further comprising: coupling a cope of the casting flask to the drag, the cope including a runner pin and at least one riser pin; and removing the runner pin and the at least one riser pin to expose a runner and at least one riser, respectively. ### Claim 17 (depends on 16) The method of claim 16, wherein: each of the first sand mold and the second sand mold defines a first in-gate and a second in-gate, respectively, each of the first in-gate and the second in-gate defining a depression and a passageway; and the cope is coupled to the drag such that the runner aligns with the depression and the at least one riser aligns with the passageway. ### Claim 18 (depends on 15) The method of claim 15, wherein creating the first sand mold comprises: placing the drag upside-down on a molding board; placing a pattern having dimensions of the nozzle on the molding board; filling the drag with sand such that the pattern is buried in the sand; placing a bottom board on the drag; flipping over an assembly including the molding board, the drag, and the bottom board; and removing the pattern. ### Claim 19 (depends on 15) The method of claim 15, wherein creating the second sand mold comprises: placing the drag upside-down on a molding board; placing the nozzle on the molding board; filling the drag with sand such that the cast nozzle is buried in the sand; placing a bottom board on the drag; and flipping over an assembly including the molding board, the drag, and the bottom board. ### Claim 20 A method for protecting a turbomachine from corrosion, comprising: creating a first sand mold in a drag of a casting flask; coupling a cope of the casting flask to the drag, the cope including a runner pin and at least one riser pin; removing the runner pin and the at least one riser pin to expose a runner and at least one riser, respectively; pouring a molten first material in the runner to cast a first component of the turbomachine; removing the first sand mold and creating a second sand mold in the drag, the second sand mold utilizing the first component; coupling the cope of the casting flask to the drag, the cope including the runner pin and the at least one riser pin; removing the runner pin and the at least one riser pin to expose a runner and at least one riser, respectively; and pouring a molten second material in the runner to cast a second component of the turbomachine integral with the first component, one of the first component and the second component being corrosion-resistant. ### Claim 21 (depends on 20) The method of claim 20, wherein the molten first material is a molten nozzle material, the first component is a nozzle, a molten second material is a molten corrosion-resistant liner material, and the second component is a corrosion-resistant liner. ### Claim 22 (depends on 21) The method of claim 21, wherein creating the first sand mold comprises: placing the drag upside-down on a molding board; placing a pattern having dimensions of the nozzle on the molding board; filling the drag with sand such that the pattern is buried in the sand; placing a bottom board on the drag; flipping over an assembly including the molding board, the drag, and the bottom board; and removing the pattern and carving a first in-gate. ### Claim 23 (depends on 21) The method of claim 21, wherein creating the second sand mold comprises: placing the drag upside-down on a molding board; placing the nozzle on the molding board; filling the drag with sand such that the cast nozzle is buried in the sand; placing a bottom board on the drag; flipping over an assembly including the molding board, the drag, and the bottom board; and carving a second in-gate.