# US 2014/0150434 A1 · Fuel nozzle for a combustor of a 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 2014/0150434 A1 - Document ID: US20140150434A1 - Status: Published application - Kind: A1 - Application number: 13/705,443 - Filed: 2012-12-05 - Published: 2014-06-05 - Earliest claimed: 2012-12-05 - Assignees: General Electric Company - Applicants: General Electric Company - Inventors: Keith Cletus Belsom; Kevin Weston McMahan; Larry Lou Thomas - Web page: https://patentgrep.com/patent/US20140150434A1 ## CPC - F02C 7/222: {Fuel flow conduits, e.g. manifolds} - F23R 3/286: {having fuel-air premixing devices (F23R3/30 takes precedence)} - F23R 3/32: being tubular - 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) - 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) ## Abstract A fuel nozzle for a gas turbine generally includes a main body having an upstream end axially separated from a downstream end. The main body at least partially defines a fuel supply passage that extends through the upstream end and at least partially through the main body. A fuel distribution manifold is disposed at the downstream end of the main body. The fuel distribution manifold includes a plurality of axially extending passages that extend through the fuel distribution manifold. A plurality of fuel injection ports defines a flow path between the fuel supply passage and each of the plurality of axially extending passages. ## Claims ### Claim 1 A fuel nozzle for a gas turbine, comprising: a. a main body, the main body having an upstream end axially separated from a downstream end, the main body at least partially defining a fuel supply passage that extends through the upstream end and at least partially through the main body; b. a fuel distribution manifold disposed at the downstream end of the main body, the fuel distribution manifold having a plurality of axially extending passages that extend through the fuel distribution manifold; and c. a plurality of fuel injection ports, each fuel injection port defining a flow path between the fuel supply passage and a respective one of the plurality of axially extending passages. ### Claim 2 (depends on 1) The fuel nozzle as in claim 1, further comprising a plurality of axially extending tubes that extend downstream from the fuel distribution manifold, each tube being aligned with a respective one of the plurality of axially extending passages. ### Claim 3 (depends on 1) The fuel nozzle as in claim 1, further comprising a plurality of axially extending tubes that extend upstream from the fuel distribution manifold, each tube being aligned with a respective one of the plurality of axially extending passages. ### Claim 4 (depends on 1) The fuel nozzle as in claim 1, further comprising a plurality of axially extending tubes, each tube extending at least partially through a respective one of the plurality of axially extending passages. ### Claim 5 (depends on 4) The fuel nozzle as in claim 4, wherein each of the plurality of fuel injection ports extends through a respective one of the plurality of axially extending tubes. ### Claim 6 (depends on 1) The fuel nozzle as in claim 1, wherein the fuel distribution manifold and the main body are cast as a singular component. ### Claim 7 (depends on 1) The fuel nozzle as in claim 1, wherein the fuel distribution manifold further includes a fuel plenum that at least partially surrounds the plurality of axially extending passages. ### Claim 8 (depends on 7) The fuel nozzle as in claim 7, wherein the fuel plenum is in fluid communication with the fuel supply passage of the main body. ### Claim 9 (depends on 8) The fuel nozzle as in claim 8, further comprising a plurality of fuel injection ports, each fuel injection port defining a flow path between the fuel plenum and a respective one of the axially extending passages. ### Claim 10 A fuel nozzle for a gas turbine, comprising: a. a main body having an upstream end and a downstream end, the main body defining a fuel supply passage that extends through the upstream end and at least partially through the main body; b. a fuel distribution manifold that extends radially outward from the downstream end of the main body, the fuel distribution manifold defining a plurality of axially extending passages arranged in an annular array around the downstream end of the main body, the fuel distribution manifold further defining a fuel plenum that at least partially surrounds each of the plurality of axially extending passages; c. a flow path defined between the fuel supply passage of the main body and the fuel plenum of the fuel distribution manifold; and d. a plurality of fuel injection ports, each fuel injection port defining a flow path between the fuel plenum of the fuel distribution manifold and a respective one of the axially extending passages. ### Claim 11 (depends on 10) The fuel nozzle as in claim 10, further comprising a plurality of axially extending tubes that extend downstream from the fuel distribution manifold, each tube being aligned with a respective one of the plurality of axially extending passages. ### Claim 12 (depends on 10) The fuel nozzle as in claim 10, further comprising a plurality of axially extending tubes that extend upstream from the fuel distribution manifold, each tube being aligned with a respective one of the plurality of axially extending passages. ### Claim 13 (depends on 10) The fuel nozzle as in claim 10, further comprising a plurality of axially extending tubes, each tube extending at least partially through a respective one of the plurality of axially extending passages. ### Claim 14 (depends on 10) The fuel nozzle as in claim 10, wherein the fuel distribution manifold and the main body are cast as a singular component. ### Claim 15 (depends on 10) The fuel nozzle as in claim 10, further comprising a plurality of fuel injection ports, each fuel injection port defining a flow path between the fuel supply passage of the main body and a respective one of the plurality of axially extending passages. ### Claim 16 A gas turbine, comprising; a. a compressor, a combustor downstream from the compressor and a turbine downstream from the combustor, the combustor having an end cover connected to a compressor discharge casing that at least partially surrounds the combustor, the end cover having an inner surface; b. a plurality of fuel nozzles, each fuel nozzle extending downstream from the inner surface of the end cover, each fuel nozzle comprising: i. a main body having an upstream end and a downstream end, the main body defining a fuel supply passage that extends through the upstream end and at least partially through the main body; ii. a fuel distribution manifold that extends radially outward from the downstream end of the main body, the fuel distribution manifold defining a plurality of axially extending passages arranged in an annular array around the downstream end of the main body; and iii. at least one flow path defined between the fuel supply passage of the main body and a respective one of the plurality of axially extending passages of the fuel distribution manifold. ### Claim 17 (depends on 16) The gas turbine as in claim 16, wherein each fuel nozzle comprises a plurality of axially extending tubes that extend downstream from the fuel distribution manifold, each tube being aligned with a respective one of the plurality of axially extending passages. ### Claim 18 (depends on 16) The gas turbine as in claim 16, wherein each fuel nozzle comprises a plurality of axially extending tubes that extend upstream from the fuel distribution manifold, each tube being aligned with a respective one of the plurality of axially extending passages. ### Claim 19 (depends on 16) The gas turbine as in claim 16, wherein the fuel distribution manifold further defines a fuel plenum that circumferentially surrounds the plurality of axially extending passages, the fuel plenum being in fluid communication with the fuel supply passage of the main body. ### Claim 20 (depends on 19) The gas turbine as in claim 19, further comprising at least one flow path defined between the fuel plenum and a respective one of the plurality of axially extending passages.