# US 12,601,483 B2 · Additively manufactured combustion liner and axial fuel stage injector > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,601,483 B2 - Document ID: US12601483B2 - Status: Granted - Kind: B2 - Application number: 18/399,823 - Filed: 2023-12-29 - Published: 2025-07-03 - Granted: 2026-04-14 - Earliest claimed: 2023-12-29 - Assignees: GE Infrastructure Technology LLC - Applicants: GE Infrastructure Technology LLC - Inventors: Richard Martin DiCintio - Web page: https://patentgrep.com/patent/US12601483B2 ## CPC - F23R 3/002: {Wall structures (F23R3/02 and F23R3/007 take precedence)} - F02C 3/04: having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) - F23R 3/346: {for staged combustion} - F05D 2230/60: Assembly methods - F05D 2240/35: Combustors or associated equipment - F23R 2900/00018: Manufacturing combustion chamber liners or subparts - F23R: GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS (fluidised bed combustion apparatus specially adapted for operation at superatmospheric pressures F23C10/16) - F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract A combustor for a gas turbine system includes an additively manufactured (AM) combustor body including a one-piece member. The member includes a combustion liner including a cylindrical portion and a tapered transition portion at an aft end of the cylindrical portion; and at least one axial fuel stage (AFS) injector directed into the combustion liner. The member may also include at least one flow sleeve surrounding at least part of the combustion liner; and an aft frame at the aft end of the transition portion. The AM combustor body includes a plurality of parallel, sintered metal layers. A method of manufacturing such a combustor body is also provided. ## Claims ### Claim 1 A method, comprising: additively manufacturing a combustor body including a one-piece member including: a combustion liner including a cylindrical portion and a tapered transition portion, at least one axial fuel stage (AFS) injector directed into the combustion liner, at least one fuel passage defined within and enclosed by opposed exterior surfaces of the combustion liner and extending longitudinally from a forward end thereof to the at least one AFS injector, wherein the combustion liner is solid between the opposed exterior surfaces thereof apart from the at least one fuel passage defined therewithin, at least one cooling passage defined within and enclosed by the opposed exterior surfaces of the combustion liner and extending longitudinally within the combustion liner from the forward end thereof to an aft end thereof, and an aft frame at an aft end of the tapered transition portion of the combustion liner, wherein the AM combustor body includes a plurality of parallel, sintered metal layers; coupling a head end fuel nozzle assembly to a forward end of the combustor body; and coupling a turbine inlet to the aft frame. ### Claim 2 (depends on 1) The method of claim 1, wherein the at least one fuel passage includes a plurality of fuel passages disposed at a same radial distance in the combustion liner. ### Claim 3 (depends on 1) The method of claim 1, wherein the at least one fuel passage is at a first radial distance in the combustion liner and the at least one cooling passage is at a second radial distance in the combustion liner. ### Claim 4 (depends on 3) The method of claim 3, wherein the second radial distance is greater than the first radial distance. ### Claim 5 A combustor for a gas turbine system, the combustor comprising: an additively manufactured (AM) combustor body including a one-piece member including: a combustion liner including a cylindrical portion and a tapered transition portion, at least one axial fuel stage (AFS) injector directed into the combustion liner, at least one fuel passage defined within and enclosed by opposed exterior surfaces of the combustion liner and extending longitudinally within the combustion liner from a forward end thereof to the at least one AFS injector, wherein the combustion liner is solid between the opposed exterior surfaces thereof apart from the at least one fuel passage defined therewithin, and at least one cooling passage defined within and enclosed by the opposed exterior surfaces of the combustion liner and extending longitudinally within the combustion liner from the forward end thereof to an aft end thereof, wherein the AM combustor body includes a plurality of parallel, sintered metal layers. ### Claim 6 (depends on 5) The combustor of claim 5, wherein the at least one fuel passage comprises a plurality of fuel passages disposed at a same radial distance in the combustion liner. ### Claim 7 (depends on 5) The combustor of claim 5, wherein the at least one fuel passage is at a first radial distance in the combustion liner and the at least one cooling passage is at a second radial distance in the combustion liner. ### Claim 8 (depends on 7) The combustor of claim 7, wherein the second radial distance is greater than the first radial distance.