# US 12,215,868 B2 · Injector with disc for hydrogen-driven gas turbine engine > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,215,868 B2 - Document ID: US12215868B2 - Status: Granted - Kind: B2 - Application number: 18/423,649 - Filed: 2024-01-26 - Published: 2024-08-08 - Granted: 2025-02-04 - Earliest claimed: 2023-02-02 - Assignees: Pratt & Whitney Canada Corp. - Applicants: Pratt & Whitney Canada Corp. - Inventors: Tin Cheung John Hu - Web page: https://patentgrep.com/patent/US12215868B2 ## CPC - F23R 3/286: {having fuel-air premixing devices (F23R3/30 takes precedence)} - F02C 7/22: Fuel supply systems - F23D 14/70: Baffles or like flow-disturbing devices - F23R 2900/00002: Gas turbine combustors adapted for fuels having low heating value [LHV] - 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) - F23D: BURNERS ## Abstract An injector for a gas turbine engine includes an annular gas nozzle, a hydrogen feed conduit, and a disc. The annular gas nozzle is disposed along a central nozzle axis and includes a forward face, a frustoconical interior surface, and gas feed conduits that open at the frustoconical interior surface. The hydrogen feed conduit extends along the central nozzle axis through the annular gas nozzle. The hydrogen feed conduit and the frustoconical interior surface define there between an annular mixing chamber. The hydrogen feed conduit has an end portion that is axially displaced from the forward face. The end portion includes feed holes that open into the mixing chamber. The disc is disposed on the end portion and is diametrically larger than the end portion so as to form a forward boundary of the annular mixing chamber. The disc may have multiple teeth, serrated edges, single or multiple bleed holes that are normal or angularly drilled to enhance fuel and air mixing, and improve flame stability. ## Claims ### Claim 1 An injector for a gas turbine engine comprising: an annular gas nozzle disposed along a central nozzle axis and including a forward face, a frustoconical interior surface, and gas feed conduits opening at the frustoconical interior surface; a hydrogen feed conduit extending along the central nozzle axis through the annular gas nozzle, the hydrogen feed conduit and the frustoconical interior surface defining there between an annular mixing chamber, the hydrogen feed conduit having an end portion axially displaced from the forward face, the end portion including feed holes opening into the mixing chamber; and a disc disposed on the end portion of the hydrogen feed conduit, the disc being diametrically larger than the end portion of the hydrogen feed conduit. ### Claim 2 (depends on 1) The injector as recited in claim 1, wherein the disc is diametrically larger than the end portion by a factor of 1.2 to 2.5. ### Claim 3 (depends on 2) The injector as recited in claim 2, wherein the annular gas nozzle is diametrically larger than the disc by a factor of 2.0 to 4. ### Claim 4 (depends on 1) The injector as recited in claim 1, wherein the gas feed conduits are obliquely sloped with respect to the central nozzle axis. ### Claim 5 (depends on 1) The injector as recited in claim 1, wherein the gas feed conduits are pointed at the hydrogen feed conduit axially aft of the feed holes. ### Claim 6 (depends on 1) The injector as recited in claim 1, wherein the disc has a serrated outer edge. ### Claim 7 (depends on 1) The injector as recited in claim 1, wherein the disc has at least one hydrogen bleed hole. ### Claim 8 (depends on 1) The injector as recited in claim 1, wherein the disc forms a forward boundary of the annular mixing chamber. ### Claim 9 A gas turbine engine comprising: a combustor section having a combustion chamber; hydrogen source; and an injector for introducing hydrogen from the hydrogen source and gas into the combustion chamber, the injector including an annular gas nozzle disposed along a central nozzle axis and including a forward face, a frustoconical interior surface, and gas feed conduits opening at the frustoconical interior surface, a hydrogen feed conduit extending along the central nozzle axis through the annular gas nozzle, the hydrogen feed conduit and the frustoconical interior surface defining there between an annular mixing chamber, the hydrogen feed conduit having an end portion axially displaced from the forward face, the end portion including feed holes opening into the mixing chamber, and a disc disposed on the end portion of the hydrogen feed conduit, the disc being diametrically larger than the end portion of the hydrogen feed conduit. ### Claim 10 (depends on 9) The gas turbine engine as recited in claim 9, wherein the disc is diametrically larger than the end portion by a factor of 1.2 to 2.5. ### Claim 11 (depends on 10) The gas turbine engine as recited in claim 10, wherein the annular gas nozzle is diametrically larger than the disc by a factor of 2.0 to 4. ### Claim 12 (depends on 9) The gas turbine engine as recited in claim 9, wherein the gas feed conduits are obliquely sloped with respect to the central nozzle axis. ### Claim 13 (depends on 9) The gas turbine engine as recited in claim 9, wherein the gas feed conduits are pointed at the hydrogen feed conduit axially aft of the feed holes. ### Claim 14 (depends on 9) The gas turbine engine as recited in claim 9, including a compressor section providing gas to the combustor section, a turbine section in fluid communication with the combustor section, and a fan coupled to be driven by the turbine section. ### Claim 15 (depends on 9) The gas turbine engine as recited in claim 9, wherein the disc has a serrated outer edge. ### Claim 16 (depends on 9) The gas turbine engine as recited in claim 9, wherein the disc has at least one hydrogen bleed hole.