# US 2014/0190168 A1 · Dual fuel nozzle tip assembly > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2014/0190168 A1 - Document ID: US20140190168A1 - Status: Published application - Kind: A1 - Application number: 14/077,557 - Filed: 2013-11-12 - Published: 2014-07-10 - Earliest claimed: 2013-01-10 - Assignees: General Electric Company - Applicants: General Electric Company - Inventors: Borys Borysovych Shershnyov; Leonid Yulyevich Ginessin - Web page: https://patentgrep.com/patent/US20140190168A1 ## CPC - F23R 3/283: {Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances} - F23R 3/14: by using swirl vanes - F23R 3/286: {having fuel-air premixing devices (F23R3/30 takes precedence)} - F23R 3/36: Supply of different fuels - F23R 2900/03044: Impingement cooled combustion chamber walls or subassemblies - 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 combustor includes a burner tube and a center nozzle assembly disposed within the burner tube. The center nozzle assembly includes a center body that at least partially defines a cooling air flow passage through the center nozzle assembly. A premix flow passage is defined between the burner tube and the center nozzle assembly. A tip assembly is disposed at a downstream end of the center body. The tip assembly includes an impingement plate, and a cap that is disposed downstream from the impingement plate. The impingement plate and the cap at least partially define a cooling plenum therebetween. An insert passage extends through the impingement plate and a cooling flow outlet extends through the cap. A plurality of cooling ports extends through the impingement plate to provide for fluid communication between the cooling air flow passage and the cooling plenum. ## Claims ### Claim 1 A fuel nozzle for a combustor, the fuel nozzle comprising: a. a burner tube component; b. a center nozzle assembly concentrically disposed within the burner tube component, the center nozzle assembly having center body that at least partially defines a cooling air flow passage through the center nozzle assembly, the center body having a downstream end; c. a premix flow passage defined between the burner tube component and the center nozzle assembly; d. a tip assembly disposed at the downstream end of the center body, the tip assembly having an impingement plate that extends radially across the downstream end of the center body, and a radially extending cap disposed downstream from the impingement plate, the impingement plate and the cap at least partially defining a cooling plenum therebetween; e. an insert passage that extends through the impingement plate; f. a cooling flow outlet that extends through the cap, the cooling flow outlet being coaxially aligned with the insert passage; and g. a plurality of cooling ports that extend through the impingement plate to provide for fluid communication between the cooling air flow passage and the cooling plenum. ### Claim 2 (depends on 1) The fuel nozzle as in claim 1, wherein the plurality of cooling ports are angled with respect to a longitudinal axis of the impingement plate within a plane defined between the longitudinal axis and a tangential axis of the impingement plate to impart swirl about the longitudinal axis to a compressed working fluid that passes therethrough. ### Claim 3 (depends on 2) The fuel nozzle as in claim 2, further comprising a plurality of swirler vanes that extend between the burner tube component and the center nozzle assembly within the premix flow passage, the swirler vanes being configured to impart swirl about a longitudinal axis of the fuel nozzle to a compressed working fluid that passes therethrough. ### Claim 4 (depends on 3) The dual fuel nozzle as in claim 3, wherein the plurality of cooling ports are angled to impart swirl that is opposite to the swirl imparted by the swirler vanes. ### Claim 5 (depends on 1) The fuel nozzle as in claim 1, wherein the cap includes a cool side and a hot side, the cooling flow outlet converging radially inward from the cool side towards the hot side of the cap. ### Claim 6 (depends on 1) The fuel nozzle as in claim 1, further comprising an annular heat shield concentrically disposed within the insert passage. ### Claim 7 (depends on 6) The fuel nozzle as in claim 6, further comprising a liquid fuel cartridge that extends through the heat shield, the liquid fuel cartridge having a fuel injection tip portion that extends through the heat shield and at least partially through the cooling flow passage of the cap. ### Claim 8 (depends on 7) The fuel nozzle as in claim 7, further comprising a cartridge tip cooling plenum that is at least partially defined between the heat shield and the fuel injection tip portion of the liquid fuel cartridge. ### Claim 9 (depends on 1) The fuel nozzle as in claim 1, further comprising a purge air bypass cartridge concentrically disposed within the insert passage of the impingement plate, the purge air bypass cartridge having a plurality of cooling air holes that are in fluid communication with the cooling plenum. ### Claim 10 A tip assembly for a fuel nozzle, comprising: a. an annular impingement plate, the impingement plate at least partially defining an insert passage that extends concentrically through the impingement plate along a longitudinal axis of the diffusion tip assembly; b. an annular cap disposed coaxially downstream from the impingement plate, the cap at least partially defining a cooling flow outlet, the cooling flow outlet being aligned with the insert passage, the cap having an outer portion that extends between the impingement plate and the cap, the outer portion, the cap and the impingement plate at least partially defining a cooling plenum therebetween; and c. a plurality of angled cooling ports extending through the impingement plate to provide fluid communication into the cooling plenum, the plurality of cooling ports being set at an angle with respect to the longitudinal axis of the impingement plate within a plane defined between the longitudinal axis and a tangential axis of the impingement plate. ### Claim 11 (depends on 10) The tip assembly as in claim 10, wherein the cap includes a cool side and a hot side, the cooling flow outlet converging radially inward from the cool side towards the hot side of the cap. ### Claim 12 (depends on 10) The tip assembly as in claim 10, further comprising an annular heat shield concentrically disposed within the insert passage. ### Claim 13 (depends on 12) The tip assembly as in claim 12, wherein the heat shield extends through the cap. ### Claim 14 (depends on 12) The tip assembly as in claim 12, further comprising a liquid fuel cartridge that extends through the heat shield, the liquid fuel cartridge having a fuel injection tip portion that extends through the heat shield and at least partially through the cooling flow passage of the cap. ### Claim 15 (depends on 14) The tip assembly as in claim 14, further comprising a cartridge tip cooling plenum that is at least partially defined between the heat shield and the fuel injection tip portion of the liquid fuel cartridge. ### Claim 16 (depends on 10) The tip assembly as in claim 10, further comprising a purge air bypass cartridge concentrically disposed within the insert passage of the impingement plate. ### Claim 17 A gas turbine comprising: a. a compressor at an upstream end of the gas turbine, a combustor positioned downstream from the compressor, and a turbine positioned downstream from the combustor, the combustor being in fluid communication with a fuel supply and a compressed air supply, the combustor having an end cover coupled to a casing, the casing at least partially surrounds the combustor, a fuel nozzle extends downstream from the end cover, the fuel nozzle comprising: i. a burner tube component; ii. a center nozzle assembly concentrically disposed within the burner tube component, the center nozzle assembly having an annular center body that at least partially defines a cooling air flow passage through the center nozzle assembly, the center body having a downstream end; iii. a premix flow passage defined between the burner tube component and the center body assembly; iv. a tip assembly disposed at the downstream end of the center body, the diffusion tip assembly having an impingement plate that extends radially across the downstream end of the center body and a radially extending cap disposed coaxially downstream from the impingement plate, the impingement plate and the cap at least partially defining a cooling plenum therebetween, the impingement plate at least partially defining an insert passage and the cap at least partially defining a cooling flow outlet that is aligned with the insert passage; and v. a plurality of angled cooling ports that extend through the impingement plate to provide for fluid communication between the cooling air flow passage and the cooling plenum. ### Claim 18 (depends on 17) The gas turbine as in claim 17, wherein the plurality of cooling ports of the impingement plate are arranged in an annular array around the insert passage. ### Claim 19 (depends on 17) The gas turbine as in claim 17, wherein the plurality of cooling ports of the impingement plate are angled with respect to a longitudinal axis of the impingement plate within a plane defined between the longitudinal axis and a tangential axis of the impingement plate to impart swirl about the longitudinal axis to a cooling medium that passes therethrough. ### Claim 20 (depends on 17) The gas turbine as in claim 17, wherein the tip further comprises an annular heat shield concentrically disposed within the insert passage and a liquid fuel cartridge that extends through the heat shield, the heat shield and the liquid fuel cartridge at least partially defining a cartridge tip cooling plenum therebetween.