# US 11,111,888 B2 · Fuel nozzles > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,111,888 B2 - Document ID: US11111888B2 - Status: Granted - Kind: B2 - Application number: 16/516,973 - Filed: 2019-07-19 - Published: 2019-11-07 - Granted: 2021-09-07 - Earliest claimed: 2015-03-31 - Assignees: Delavan Inc. - Applicants: Delavan Inc - Inventors: Lev A. Prociw - Web page: https://patentgrep.com/patent/US11111888B2 ## CPC - F02M 31/20: for cooling ({F02M31/005 takes precedence; use of cold F02M17/52;} cooling of charging-air or of scavenging-air F02B29/04) - F02C 7/22: Fuel supply systems - F23D 11/36: Details - F23R 3/14: by using swirl vanes - F23R 3/283: {Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances} - F02M: SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF - 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 - 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 nozzle includes a nozzle body defining a longitudinal axis. The nozzle body has an air passage, a fuel circuit radially outboard from the air passage with respect to the longitudinal axis, and a cooling circuit. The fuel circuit extends from a fuel circuit inlet to a fuel circuit annular outlet. The fuel circuit is defined between a fuel circuit inner wall and a fuel circuit outer wall. At least a portion of the fuel circuit outer wall is radially outboard from the fuel circuit inner wall with respect to the longitudinal axis. A cooling circuit is defined within at least one of the fuel circuit inner wall or the fuel circuit outer wall. The cooling circuit extends from an axial position proximate the fuel circuit inlet to an axial position proximate the fuel circuit outlet. ## Claims ### Claim 1 A nozzle, comprising: a nozzle body defining a longitudinal axis including: an air passage; a fuel circuit radially outboard from the air passage with respect to the longitudinal axis, the fuel circuit extending from a fuel circuit inlet to a fuel circuit annular outlet, wherein the fuel circuit is defined between a fuel circuit inner wall and a fuel circuit outer wall, wherein at least a portion of the fuel circuit outer wall is radially outboard from the fuel circuit inner wall with respect to the longitudinal axis; and a cooling circuit defined within at least one of the fuel circuit inner wall and the fuel circuit outer wall, wherein the cooling circuit extends from a first axial position proximate the fuel circuit inlet to a second axial position proximate the fuel circuit outlet; and a stem operatively connected to a fuel manifold of the nozzle body, wherein the stem includes three liquid channels for fluid communication with at least one of the fuel circuit or the cooling circuit, wherein one of the three liquid channels is a coolant-in channel in fluid communication with a distribution channel of the cooling circuit to provide coolant thereto, wherein one of the three liquid channels is a coolant-out channel in fluid communication with a collection channel of the cooling circuit to receive coolant therefrom, wherein the distribution channel and the collection channel are circumferentially spaced apart from one another. ### Claim 2 (depends on 1) The nozzle as recited in claim 1, further wherein one of the three liquid channels is a fuel channel in fluid communication with the fuel manifold to provide fuel to the fuel circuit inlet. ### Claim 3 (depends on 1) The nozzle as recited in claim 1, wherein the distribution channel and the collection channel are co-planar. ### Claim 4 (depends on 1) The nozzle as recited in claim 1, wherein the cooling circuit includes a pair of helical threads, wherein a first one of the helical threads begins at the distribution channel and extends to the second axial position proximate the fuel circuit outlet to provide cooling flow to a nozzle tip, and wherein a first end of a second one of the helical threads is connected to the first one of the helical threads proximate to the fuel circuit outlet and extends to the collection channel to provide a cooling flow exit to the coolant-out channel. ### Claim 5 (depends on 4) The nozzle as recited in claim 4, wherein the first end of the second one of the helical threads is connected to the first one of the helical threads through a short circuit segment. ### Claim 6 (depends on 1) The nozzle as recited in claim 1, wherein the nozzle body includes a pair of tubes defined through the air passage and though theft fuel manifold, wherein one of the tubes fluidly connects the distribution channel to the coolant-in channel and another one of the tubes fluidly connects the collection channel to the coolant-out channel. ### Claim 7 (depends on 6) The nozzle as recited in claim 6, wherein the air passage includes an annular inlet having radial swirl vanes circumferentially spaced apart from one another, wherein the tubes are defined within the radial swirl vanes. ### Claim 8 (depends on 1) The nozzle as recited in claim 1, wherein the air passage is defined between a backing plate and a jacket downstream from the backing plate, wherein at least a portion of the jacket is a conical shape that converges toward the longitudinal axis in a downstream direction. ### Claim 9 (depends on 1) The nozzle as recited in claim 1, wherein the air passage includes a radial swirler, a converging conical cross-section, and an annular inlet, wherein the radial swirler includes radial swirl vanes circumferentially spaced apart from one another about the annular inlet to induce swirl into air entering the annular inlet of the air passage. ### Claim 10 (depends on 1) The nozzle as recited in claim 1, wherein the nozzle body includes an outer air passage defined radially outboard of the fuel circuit with respect to the longitudinal axis. ### Claim 11 (depends on 10) The nozzle as recited in claim 10, wherein the outer air passage is defined between the fuel circuit outer wall and an outer air passage wall, and wherein the outer air passage is a converging non-swirling outer air passage. ### Claim 12 A nozzle, comprising: a nozzle body defining a longitudinal axis including: an air passage, wherein the air passage includes a radial swirler, a converging conical cross-section, and an annular inlet, wherein the radial swirler includes radial swirl vanes circumferentially spaced apart from one another about the annular inlet to induce swirl into air entering the annular inlet of the air passage; a fuel circuit radially outboard from the air passage with respect to the longitudinal axis, the fuel circuit extending from a fuel circuit inlet to a fuel circuit annular outlet, wherein the fuel circuit is defined between a fuel circuit inner wall and a fuel circuit outer wall, wherein at least a portion of the fuel circuit outer wall is radially outboard from the fuel circuit inner wall with respect to the longitudinal axis; and a cooling circuit defined within at least one of the fuel circuit inner wall and the fuel circuit outer wall, wherein the cooling circuit extends from a first axial position proximate the fuel circuit inlet to a second axial position proximate the fuel circuit outlet; and a stem operatively connected to a fuel manifold of the nozzle body, wherein the stem includes three liquid channels for fluid communication with at least one of the fuel circuit or the cooling circuit, wherein one of the three liquid channels is a coolant-in channel in fluid communication with a distribution channel of the cooling circuit to provide coolant thereto, wherein one of the three liquid channels is a coolant-out channel in fluid communication with a collection channel of the cooling circuit to receive coolant therefrom. ### Claim 13 (depends on 12) The nozzle as recited in claim 12, wherein one of the three liquid channels is a fuel channel in fluid communication with the fuel manifold to provide fuel to the fuel circuit inlet. ### Claim 14 (depends on 12) The nozzle as recited in claim 12, wherein the distribution channel and the collection channel are co-planar. ### Claim 15 (depends on 12) The nozzle as recited in claim 12, wherein the cooling circuit includes a pair of helical threads, wherein a first one of the helical threads begins at the distribution channel and extends to the second axial position proximate the fuel circuit outlet to provide cooling flow to a nozzle tip, and wherein a first end of a second one of the helical threads is connected to the first one of the helical threads proximate to the fuel circuit outlet and extends to the collection channel to provide a cooling flow exit to the coolant-out channel. ### Claim 16 (depends on 15) The nozzle as recited in claim 15, wherein the first end of the second one of the helical threads is connected to the first one of the helical threads through a short circuit segment. ### Claim 17 (depends on 12) The nozzle as recited in claim 12, wherein the nozzle body includes a pair of tubes defined through the air passage and though the fuel manifold, wherein one of the tubes fluidly connects the distribution channel to the coolant-in channel and another one of the tubes fluidly connects the collection channel to the coolant-out channel. ### Claim 18 (depends on 17) The nozzle as recited in claim 17, wherein the air passage includes an annular inlet having radial swirl vanes circumferentially spaced apart from one another, wherein the tubes are defined within the radial swirl vanes. ### Claim 19 (depends on 12) The nozzle as recited in claim 12, wherein the air passage is defined between a backing plate and a jacket downstream from the backing plate, wherein at least a portion of the jacket is a conical shape that converges toward the longitudinal axis in a downstream direction. ### Claim 20 (depends on 12) The nozzle as recited in claim 12, wherein the nozzle body includes an outer air passage defined radially outboard of the fuel circuit with respect to the longitudinal axis.