US20160201897A1 - Dual fuel nozzle system and apparatus - Google Patents
Dual fuel nozzle system and apparatus Download PDFInfo
- Publication number
- US20160201897A1 US20160201897A1 US14/913,056 US201414913056A US2016201897A1 US 20160201897 A1 US20160201897 A1 US 20160201897A1 US 201414913056 A US201414913056 A US 201414913056A US 2016201897 A1 US2016201897 A1 US 2016201897A1
- Authority
- US
- United States
- Prior art keywords
- gas
- fuel
- liquid
- fuel nozzle
- transition zone
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Abandoned
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/36—Supply of different fuels
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN A CARRIER GAS OR AIR
- F23C1/00—Combustion apparatus specially adapted for combustion of two or more kinds of fuel simultaneously or alternately, at least one kind of fuel being either a fluid fuel or a solid fuel suspended in a carrier gas or air
- F23C1/08—Combustion apparatus specially adapted for combustion of two or more kinds of fuel simultaneously or alternately, at least one kind of fuel being either a fluid fuel or a solid fuel suspended in a carrier gas or air liquid and gaseous fuel
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/46—Details, e.g. noise reduction means
- F23D14/48—Nozzles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
- F23D2900/11101—Pulverising gas flow impinging on fuel from pre-filming surface, e.g. lip atomizers
Definitions
- the present disclosure relates to radial fuel injection in fuel nozzles, and more specifically, to radial fuel injection in dual fuel nozzle to improve gaseous fuel dispersion and/or penetration.
- a gas turbine may generally include a fuel nozzle that is configured to supply one or more fuels to the combustor. This fuel may be mixed with air and/or pollution mitigation substances such as, for example, water. Dual fuel nozzles used in propulsion and energy production applications may comprise a radial fuel port. Dispersion and/or penetration of gas fuel may be affected by the location of the radial fuel port. Greater dispersion and/or penetration of gaseous fuel may increase the operating efficiency of a gas turbine.
- a gas turbine fuel nozzle may comprise a housing.
- the housing may define a mixing chamber including a transition zone.
- the housing may comprise an interior wall.
- the interior wall may comprise a shoulder.
- a fuel port may be defined in the shoulder.
- the fuel port may be configured to conduct a fuel into the mixing chamber. The fuel may propagate across a volume of the mixing chamber prior to reaching the transition zone.
- a dual fuel nozzle may comprise a gas supply, an interior wall, a housing, a liquid supply and a liquid supply channel.
- the interior wall may comprise a shoulder.
- the shoulder may include a gas port.
- the housing may define a gas discharge zone configured to receive a gas from the gas port.
- the gas discharge zone may comprise a transition zone.
- the liquid supply channel may be configured to conduct a liquid to the transition zone.
- a dual fuel distribution system may comprise a gas fuel supply, a housing, a liquid fuel supply, and a liquid distribution channel.
- the housing may comprise an interior wall defining a shoulder.
- the shoulder may define a plurality of gas ports. Gaseous fuel from the gas fuel supply may be conducted through the gas ports into a mixing chamber.
- the liquid distribution channel may be defined in the housing.
- the liquid distribution channel may be configured to conduct a liquid fuel from the liquid fuel supply to a transition zone.
- the transition zone may be a portion of the mixing chamber.
- FIG. 1A illustrates a perspective cross sectional view of a prior art dual fuel nozzle.
- FIG. 1B illustrates a gas fuel dispersion and/or penetration of a prior art dual fuel nozzle.
- FIG. 2A illustrates a perspective cross sectional view of a dual fuel nozzle, in accordance with various embodiments.
- FIG. 2B illustrates a gaseous fuel dispersion and/or penetration of a dual fuel nozzle, in accordance with various embodiments.
- FIG. 2C illustrates a perspective cross sectional view of a portion of a dual fuel nozzle, in accordance with various embodiments.
- any reference to singular includes plural embodiments, and any reference to more than one component or step may include a singular embodiment or step.
- any reference to attached, fixed, connected or the like may include permanent, removable, temporary, partial, full and/or any other possible attachment option.
- any reference to without contact (or similar phrases) may also include reduced contact or minimal contact.
- phrases such as “make contact with,” “coupled to,” “touch,” “interface with” and “engage” may be used interchangeably. Different surface shading may be used throughout the figures to denote different parts but not necessarily to denote the same or different materials.
- a gas turbine engine may comprise a dual fuel nozzle.
- the fuel nozzle may define one or more channels.
- One or more of these channels may be configured to receive a gas and/or a liquid.
- These channels may be operatively coupled and/or may be in fluid communication with one or more components of a gas turbine engine including, for example, the combustor.
- the liquid, gas, and/or air supplied through the one or more channels may be conducted or carried from the fuel nozzle to the combustor.
- the nozzle is configured to provide fuel in the form of a gas or a liquid to the combustor for starting or sustained operation of the gas turbine.
- the nozzle is configured to provide air, and/or water in either gaseous form or liquid form, or combinations thereof to the combustor for starting or sustained operation of the gas turbine.
- the gas turbine may be a gas turbine configured to provide power and/or a gas turbine configured to provide propulsion.
- the gas turbine may be installed or operated in a power plant environment where the gas turbine drives electricity generating devices and supplies power to a structure and/or a utility provider.
- the gas turbine may be installed on a vehicle such as, for example, an aircraft or other suitable machinery.
- a gas turbine may comprise a typical dual fuel nozzle comprising a housing 110 , a gas supply channel 112 and a liquid supply channel 118 .
- Housing 110 may define a gas distribution channel 114 and a liquid distribution channel 120 .
- Housing 110 may also define a mixing chamber 124 .
- Mixing chamber 124 may be in fluid communication with gas distribution channel 114 .
- Dual fuel nozzle 100 may further comprise a gas port 116 defined in an interior wall 117 of housing 110 .
- Gas port 116 may be located downstream of a shoulder 119 in interior wall 117 substantially near a transition zone 124 ′ of a mixing chamber 124 .
- gas e.g., a gaseous fuel
- the gas may be discharged through gas port 116 into mixing chamber 124 adjacent to transition zone 124 ′.
- liquid may be supplied through liquid supply channel 118 and conducted into liquid distribution channel 120 .
- the liquid may be disbursed through a lip 122 .
- Dual fuel nozzle 100 may further comprise an impeller 126 .
- Housing 110 may define an air supply channel 128 along a centerline A-A′ of dual fuel nozzle 100 .
- the impeller may be configured to conduct air through air supply channel 128 into a discharge zone 130 .
- the liquid, fuel and air may be mixed in discharge zone 130 .
- the liquid may be a liquid fuel and/or water. Where the dual fuel nozzle is installed in a power generation application, the liquid may be water that is used to mitigate or minimize carbon monoxide and/or mono-nitrogen oxide emissions (i.e., NO x ).
- Fuel mixing is shown as letter G.
- Fuel may be discharged through gas port 116 from fuel distribution channel 114 into mixing chamber 124 .
- Fuel distribution G generally shows that the fuel does not mix well into mixing chamber 124 , but rather, remains clustered (e.g., close to) near interior wall 117 as the fuel propagates from mixing chamber 124 to transition zone 124 ′. This clustering or lack of fuel dispersion and/or penetration may result in inefficient combustion of fuel G.
- the fluid velocity in mixing chamber 124 generally increases at transition zone 124 ′. This increase in fluid velocity may minimize fuel distribution G as the fuel propagates from mixing chamber 124 to transition zone 124 ′ causing the fuel to cluster along a portion of interior wall 117 adjacent to transition zone 124 ′.
- adjusting the position of fuel port 216 may increase fuel penetration (e.g., the distance the fuel travels into the mixing chamber 224 ) and dispersion (e.g., the spreading of a mass of fuel across a volume) . More specifically, moving fuel port 216 forward (e.g., in the direction associated with reference A of the A-A′ centerline) further away from transition zone 224 ′ may allow fuel discharged through fuel port 216 to further propagate into mixing chamber 224 . In this regard, the fluid velocity in mixing chamber 224 may be lower upstream of transition zone 224 ′, allowing for greater fuel penetration in mixing chamber 224 .
- fuel port 216 may be defined by interior wall 217 at shoulder 219 .
- fuel may be distributed or injected into mixing chamber 224 where the fluid velocity in the chamber is relatively low (e.g., the fluid velocity in an upstream portion of mixing chamber 224 may be lower than the fluid velocity in mixing chamber 224 near transition zone 224 ′).
- the fuel distribution G′ demonstrates greater fuel penetration as compared to fuel distribution G, as shown in FIG. 1B .
- fuel distribution G′ illustrates that the fuel propagates across the entire volume of mixing chamber 224 . This greater penetration provides for lower fuel density, a more suitable fuel-air mixture, and better ignition efficiency.
- the fuel distribution G′ illustrates that the fuel may propagate into the volume of mixing chamber 224 as opposed to clustering near interior wall 217 .
- the fuel may be conducted through the transition zone 224 ′, and mixed with air supplied through channel 228 , and a liquid supplied through channel 220 and lip 222 .
- This air, fuel, and water mixture may be further supplied to the combustor for ignition.
- the mixture gas (e.g., fuel), liquid (e.g., fuel and/or water), and/or air) may be conducted to the combustor.
- interior wall 217 may comprise a plurality of gas ports 216 .
- interior wall 217 may define 8 - 14 gas ports 216 around its diameter.
- interior wall 217 may define 12 gas ports 216 around its diameter.
- Gas ports 216 may be substantially aligned with one another around along a diameter of interior wall 217 .
- gas ports 216 may be equally spaced circumferentially around interior wall 217 .
- the holes may be of any suitable diameter (e.g., 0.090 inches-0.110 inches/0.2286 cm to 0.29784 cm) and/or pitch.
- the pitch may be a function of the shape and/or slope of shoulder 219 .
- the geometry of one or more gas ports 216 and/or number of gas ports may provide a Holdeman Parameter that is greater than the ratio of pitch to diameter.
- a liquid B may be supplied through liquid supply 218 and conducted to channel 220 and discharged through lip 222 as B′.
- a gas A may be supplied to gas distribution channel 212 through gas distribution channel 214 and out of gas port 216 into mixing chamber 224 as A′.
- Air C may be supplied along channel 228 as C′.
- gas A′ and liquid B′ may be mixed and supplied into channel 228 and mixed with air C′. The mixture is then conducted to a combustor for gas turbine operation, ignition and/or burning.
- references to “one embodiment”, “an embodiment”, “various embodiments”, etc. indicate that the embodiment described may include a particular feature, structure, or characteristic, but every embodiment may not necessarily include the particular feature, structure, or characteristic. Moreover, such phrases are not necessarily referring to the same embodiment. Further, when a particular feature, structure, or characteristic is described in connection with an embodiment, it is submitted that it is within the knowledge of one skilled in the art to affect such feature, structure, or characteristic in connection with other embodiments whether or not explicitly described. After reading the description, it will be apparent to one skilled in the relevant art(s) how to implement the disclosure in alternative embodiments.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
Description
- This application claims the benefit of provisional application Ser. No. 61/867,869, filed Aug. 20, 2013.
- The present disclosure relates to radial fuel injection in fuel nozzles, and more specifically, to radial fuel injection in dual fuel nozzle to improve gaseous fuel dispersion and/or penetration.
- A gas turbine may generally include a fuel nozzle that is configured to supply one or more fuels to the combustor. This fuel may be mixed with air and/or pollution mitigation substances such as, for example, water. Dual fuel nozzles used in propulsion and energy production applications may comprise a radial fuel port. Dispersion and/or penetration of gas fuel may be affected by the location of the radial fuel port. Greater dispersion and/or penetration of gaseous fuel may increase the operating efficiency of a gas turbine.
- In various embodiments, a gas turbine fuel nozzle may comprise a housing. The housing may define a mixing chamber including a transition zone. The housing may comprise an interior wall. The interior wall may comprise a shoulder. A fuel port may be defined in the shoulder. The fuel port may be configured to conduct a fuel into the mixing chamber. The fuel may propagate across a volume of the mixing chamber prior to reaching the transition zone.
- In various embodiments, a dual fuel nozzle may comprise a gas supply, an interior wall, a housing, a liquid supply and a liquid supply channel. The interior wall may comprise a shoulder. The shoulder may include a gas port. The housing may define a gas discharge zone configured to receive a gas from the gas port. The gas discharge zone may comprise a transition zone. The liquid supply channel may be configured to conduct a liquid to the transition zone.
- In various embodiments, a dual fuel distribution system may comprise a gas fuel supply, a housing, a liquid fuel supply, and a liquid distribution channel. The housing may comprise an interior wall defining a shoulder. The shoulder may define a plurality of gas ports. Gaseous fuel from the gas fuel supply may be conducted through the gas ports into a mixing chamber. The liquid distribution channel may be defined in the housing. The liquid distribution channel may be configured to conduct a liquid fuel from the liquid fuel supply to a transition zone. The transition zone may be a portion of the mixing chamber.
- The subject matter of the present disclosure is particularly pointed out and distinctly claimed in the concluding portion of the specification. A more complete understanding of the present disclosure, however, may best be obtained by referring to the detailed description and claims when considered in connection with the drawing figures, wherein like numerals denote like elements.
-
FIG. 1A illustrates a perspective cross sectional view of a prior art dual fuel nozzle. -
FIG. 1B illustrates a gas fuel dispersion and/or penetration of a prior art dual fuel nozzle. -
FIG. 2A illustrates a perspective cross sectional view of a dual fuel nozzle, in accordance with various embodiments. -
FIG. 2B illustrates a gaseous fuel dispersion and/or penetration of a dual fuel nozzle, in accordance with various embodiments. -
FIG. 2C illustrates a perspective cross sectional view of a portion of a dual fuel nozzle, in accordance with various embodiments. - The detailed description of exemplary embodiments herein makes reference to the accompanying drawings, which show exemplary embodiments by way of illustration and their best mode. While these exemplary embodiments are described in sufficient detail to enable those skilled in the art to practice the inventions, it should be understood that other embodiments may be realized and that logical, chemical and mechanical changes may be made without departing from the spirit and scope of the disclosure. Thus, the detailed description herein is presented for purposes of illustration only and not of limitation. For example, the steps recited in any of the method or process descriptions may be executed in any order and are not necessarily limited to the order presented.
- Furthermore, any reference to singular includes plural embodiments, and any reference to more than one component or step may include a singular embodiment or step. Also, any reference to attached, fixed, connected or the like may include permanent, removable, temporary, partial, full and/or any other possible attachment option. Additionally, any reference to without contact (or similar phrases) may also include reduced contact or minimal contact.
- As used herein, phrases such as “make contact with,” “coupled to,” “touch,” “interface with” and “engage” may be used interchangeably. Different surface shading may be used throughout the figures to denote different parts but not necessarily to denote the same or different materials.
- In various embodiments, a gas turbine engine may comprise a dual fuel nozzle. The fuel nozzle may define one or more channels. One or more of these channels may be configured to receive a gas and/or a liquid. These channels may be operatively coupled and/or may be in fluid communication with one or more components of a gas turbine engine including, for example, the combustor. The liquid, gas, and/or air supplied through the one or more channels may be conducted or carried from the fuel nozzle to the combustor. In this regard, the nozzle is configured to provide fuel in the form of a gas or a liquid to the combustor for starting or sustained operation of the gas turbine. The nozzle is configured to provide air, and/or water in either gaseous form or liquid form, or combinations thereof to the combustor for starting or sustained operation of the gas turbine.
- In various embodiments, the gas turbine may be a gas turbine configured to provide power and/or a gas turbine configured to provide propulsion. For example, in an embodiment where the gas turbine is configured to provide power, the gas turbine may be installed or operated in a power plant environment where the gas turbine drives electricity generating devices and supplies power to a structure and/or a utility provider. In an embodiment where the gas turbine is configured to provide propulsion, the gas turbine may be installed on a vehicle such as, for example, an aircraft or other suitable machinery.
- In various embodiments and with reference to
FIGS. 1A and 1B a gas turbine may comprise a typical dual fuel nozzle comprising ahousing 110, agas supply channel 112 and aliquid supply channel 118.Housing 110 may define agas distribution channel 114 and aliquid distribution channel 120.Housing 110 may also define amixing chamber 124. Mixingchamber 124 may be in fluid communication withgas distribution channel 114. -
Dual fuel nozzle 100 may further comprise agas port 116 defined in aninterior wall 117 ofhousing 110.Gas port 116 may be located downstream of ashoulder 119 ininterior wall 117 substantially near atransition zone 124′ of a mixingchamber 124. In this regard, gas (e.g., a gaseous fuel) may be conducted throughgas supply channel 112 andgas distribution channel 114. The gas may be discharged throughgas port 116 into mixingchamber 124 adjacent to transitionzone 124′. - In various embodiments, liquid may be supplied through
liquid supply channel 118 and conducted intoliquid distribution channel 120. The liquid may be disbursed through alip 122.Dual fuel nozzle 100 may further comprise animpeller 126.Housing 110 may define anair supply channel 128 along a centerline A-A′ ofdual fuel nozzle 100. The impeller may be configured to conduct air throughair supply channel 128 into adischarge zone 130. In various embodiments, the liquid, fuel and air may be mixed indischarge zone 130. - In various embodiments, the liquid may be a liquid fuel and/or water. Where the dual fuel nozzle is installed in a power generation application, the liquid may be water that is used to mitigate or minimize carbon monoxide and/or mono-nitrogen oxide emissions (i.e., NOx).
- In various embodiments and with specific reference to
FIG. 1B , fuel mixing is shown as letter G. Fuel may be discharged throughgas port 116 fromfuel distribution channel 114 into mixingchamber 124. Fuel distribution G generally shows that the fuel does not mix well into mixingchamber 124, but rather, remains clustered (e.g., close to) nearinterior wall 117 as the fuel propagates from mixingchamber 124 totransition zone 124′. This clustering or lack of fuel dispersion and/or penetration may result in inefficient combustion of fuel G. In this regard the fluid velocity in mixingchamber 124 generally increases attransition zone 124′. This increase in fluid velocity may minimize fuel distribution G as the fuel propagates from mixingchamber 124 totransition zone 124′ causing the fuel to cluster along a portion ofinterior wall 117 adjacent to transitionzone 124′. - In various embodiments and with reference to
FIGS. 2A-2C , adjusting the position offuel port 216 may increase fuel penetration (e.g., the distance the fuel travels into the mixing chamber 224) and dispersion (e.g., the spreading of a mass of fuel across a volume) . More specifically, movingfuel port 216 forward (e.g., in the direction associated with reference A of the A-A′ centerline) further away fromtransition zone 224′ may allow fuel discharged throughfuel port 216 to further propagate into mixingchamber 224. In this regard, the fluid velocity in mixingchamber 224 may be lower upstream oftransition zone 224′, allowing for greater fuel penetration in mixingchamber 224. - In various embodiments,
fuel port 216 may be defined byinterior wall 217 atshoulder 219. With specific reference toFIG. 2B , fuel may be distributed or injected into mixingchamber 224 where the fluid velocity in the chamber is relatively low (e.g., the fluid velocity in an upstream portion of mixingchamber 224 may be lower than the fluid velocity in mixingchamber 224 neartransition zone 224′). The fuel distribution G′ demonstrates greater fuel penetration as compared to fuel distribution G, as shown inFIG. 1B . In this regard, fuel distribution G′ illustrates that the fuel propagates across the entire volume of mixingchamber 224. This greater penetration provides for lower fuel density, a more suitable fuel-air mixture, and better ignition efficiency. - In various embodiments, the fuel distribution G′ illustrates that the fuel may propagate into the volume of mixing
chamber 224 as opposed to clustering nearinterior wall 217. The fuel may be conducted through thetransition zone 224′, and mixed with air supplied throughchannel 228, and a liquid supplied throughchannel 220 andlip 222. This air, fuel, and water mixture may be further supplied to the combustor for ignition. In this regard, the mixture (gas (e.g., fuel), liquid (e.g., fuel and/or water), and/or air) may be conducted to the combustor. - In various embodiments,
interior wall 217 may comprise a plurality ofgas ports 216. In various embodiments,interior wall 217 may define 8-14gas ports 216 around its diameter. In various embodiments,interior wall 217 may define 12gas ports 216 around its diameter.Gas ports 216 may be substantially aligned with one another around along a diameter ofinterior wall 217. Moreover,gas ports 216 may be equally spaced circumferentially aroundinterior wall 217. The holes may be of any suitable diameter (e.g., 0.090 inches-0.110 inches/0.2286 cm to 0.29784 cm) and/or pitch. The pitch may be a function of the shape and/or slope ofshoulder 219. In this regard, the geometry of one ormore gas ports 216 and/or number of gas ports may provide a Holdeman Parameter that is greater than the ratio of pitch to diameter. - In various embodiments and with reference to
FIG. 2C , a portion of the dual fuel nozzle illustrating particular flow channels is provided. A liquid B may be supplied throughliquid supply 218 and conducted to channel 220 and discharged throughlip 222 as B′. Similarly, a gas A may be supplied togas distribution channel 212 throughgas distribution channel 214 and out ofgas port 216 into mixingchamber 224 as A′. Air C may be supplied alongchannel 228 as C′. Attransition zone 224′, gas A′ and liquid B′ may be mixed and supplied intochannel 228 and mixed with air C′. The mixture is then conducted to a combustor for gas turbine operation, ignition and/or burning. - Benefits, other advantages, and solutions to problems have been described herein with regard to specific embodiments. Furthermore, the connecting lines shown in the various figures contained herein are intended to represent exemplary functional relationships and/or physical couplings between the various elements. It should be noted that many alternative or additional functional relationships or physical connections may be present in a practical system. However, the benefits, advantages, solutions to problems, and any elements that may cause any benefit, advantage, or solution to occur or become more pronounced are not to be construed as critical, required, or essential features or elements of the inventions. The scope of the inventions is accordingly to be limited by nothing other than the appended claims, in which reference to an element in the singular is not intended to mean “one and only one” unless explicitly so stated, but rather “one or more.” Moreover, where a phrase similar to “at least one of A, B, or C” is used in the claims, it is intended that the phrase be interpreted to mean that A alone may be present in an embodiment, B alone may be present in an embodiment, C alone may be present in an embodiment, or that any combination of the elements A, B and C may be present in a single embodiment; for example, A and B, A and C, B and C, or A and B and C. Different cross-hatching is used throughout the figures to denote different parts but not necessarily to denote the same or different materials.
- Systems, methods and apparatus are provided herein. In the detailed description herein, references to “one embodiment”, “an embodiment”, “various embodiments”, etc., indicate that the embodiment described may include a particular feature, structure, or characteristic, but every embodiment may not necessarily include the particular feature, structure, or characteristic. Moreover, such phrases are not necessarily referring to the same embodiment. Further, when a particular feature, structure, or characteristic is described in connection with an embodiment, it is submitted that it is within the knowledge of one skilled in the art to affect such feature, structure, or characteristic in connection with other embodiments whether or not explicitly described. After reading the description, it will be apparent to one skilled in the relevant art(s) how to implement the disclosure in alternative embodiments.
- Furthermore, no element, component, or method step in the present disclosure is intended to be dedicated to the public regardless of whether the element, component, or method step is explicitly recited in the claims. No claim element herein is to be construed under the provisions of 35 U.S.C. 112, sixth paragraph, unless the element is expressly recited using the phrase “means for.” As used herein, the terms “comprises”, “comprising”, or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
Claims (20)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US14/913,056 US20160201897A1 (en) | 2013-08-20 | 2014-08-19 | Dual fuel nozzle system and apparatus |
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US201361867869P | 2013-08-20 | 2013-08-20 | |
US14/913,056 US20160201897A1 (en) | 2013-08-20 | 2014-08-19 | Dual fuel nozzle system and apparatus |
PCT/US2014/051582 WO2015026760A1 (en) | 2013-08-20 | 2014-08-19 | Dual fuel nozzle system and apparatus |
Publications (1)
Publication Number | Publication Date |
---|---|
US20160201897A1 true US20160201897A1 (en) | 2016-07-14 |
Family
ID=52484086
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US14/913,056 Abandoned US20160201897A1 (en) | 2013-08-20 | 2014-08-19 | Dual fuel nozzle system and apparatus |
Country Status (3)
Country | Link |
---|---|
US (1) | US20160201897A1 (en) |
EP (1) | EP3036482B1 (en) |
WO (1) | WO2015026760A1 (en) |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20180363907A1 (en) * | 2017-06-16 | 2018-12-20 | General Electric Company | Liquid fuel cartridge unit for gas turbine combustor and method of assembly |
DE102022201182A1 (en) | 2022-02-04 | 2023-08-10 | Rolls-Royce Deutschland Ltd & Co Kg | Nozzle assembly with connecting pipe passing through a fuel pipe in a nozzle main body for air flow |
EP4310400A1 (en) | 2022-07-21 | 2024-01-24 | Rolls-Royce Deutschland Ltd & Co KG | Nozzle device for adding at least one gaseous fuel and a liquid fuel, set, supply system and gas turbine assembly |
EP4310304A1 (en) | 2022-07-21 | 2024-01-24 | Rolls-Royce Deutschland Ltd & Co KG | Connecting device for the flow connection between a fuel supply system and a nozzle device, nozzle device and gas turbine assembly |
EP4321804A1 (en) | 2022-08-10 | 2024-02-14 | Rolls-Royce Deutschland Ltd & Co KG | Combustor assembly for liquid and/or gaseous fuel operation, gas turbine assembly, and method |
EP4353958A1 (en) | 2022-10-13 | 2024-04-17 | Rolls-Royce Deutschland Ltd & Co KG | Propulsion system for an aircraft, aircraft having a propulsion system, and method for operating an aircraft |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10605459B2 (en) * | 2016-03-25 | 2020-03-31 | General Electric Company | Integrated combustor nozzle for a segmented annular combustion system |
Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6123273A (en) * | 1997-09-30 | 2000-09-26 | General Electric Co. | Dual-fuel nozzle for inhibiting carbon deposition onto combustor surfaces in a gas turbine |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP4683787B2 (en) * | 2001-03-09 | 2011-05-18 | 大阪瓦斯株式会社 | Burner device and gas turbine engine |
US20020162333A1 (en) * | 2001-05-02 | 2002-11-07 | Honeywell International, Inc., Law Dept. Ab2 | Partial premix dual circuit fuel injector |
US6895755B2 (en) * | 2002-03-01 | 2005-05-24 | Parker-Hannifin Corporation | Nozzle with flow equalizer |
US6871501B2 (en) * | 2002-12-03 | 2005-03-29 | General Electric Company | Method and apparatus to decrease gas turbine engine combustor emissions |
JP5472863B2 (en) * | 2009-06-03 | 2014-04-16 | 独立行政法人 宇宙航空研究開発機構 | Staging fuel nozzle |
US8661825B2 (en) * | 2010-12-17 | 2014-03-04 | General Electric Company | Pegless secondary fuel nozzle including a unitary fuel injection manifold |
US8925325B2 (en) * | 2011-03-18 | 2015-01-06 | Delavan Inc. | Recirculating product injection nozzle |
JP5772245B2 (en) * | 2011-06-03 | 2015-09-02 | 川崎重工業株式会社 | Fuel injection device |
-
2014
- 2014-08-19 US US14/913,056 patent/US20160201897A1/en not_active Abandoned
- 2014-08-19 EP EP14838205.4A patent/EP3036482B1/en active Active
- 2014-08-19 WO PCT/US2014/051582 patent/WO2015026760A1/en active Application Filing
Patent Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6123273A (en) * | 1997-09-30 | 2000-09-26 | General Electric Co. | Dual-fuel nozzle for inhibiting carbon deposition onto combustor surfaces in a gas turbine |
Non-Patent Citations (1)
Title |
---|
Forliti, D. "Trajectory and Mixing Scaling Laws for Confined and Unconfined Transverse Jets", 2012 May, Air Force Research Laboratory, All Pages * |
Cited By (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20180363907A1 (en) * | 2017-06-16 | 2018-12-20 | General Electric Company | Liquid fuel cartridge unit for gas turbine combustor and method of assembly |
US10578306B2 (en) * | 2017-06-16 | 2020-03-03 | General Electric Company | Liquid fuel cartridge unit for gas turbine combustor and method of assembly |
DE102022201182A1 (en) | 2022-02-04 | 2023-08-10 | Rolls-Royce Deutschland Ltd & Co Kg | Nozzle assembly with connecting pipe passing through a fuel pipe in a nozzle main body for air flow |
EP4310400A1 (en) | 2022-07-21 | 2024-01-24 | Rolls-Royce Deutschland Ltd & Co KG | Nozzle device for adding at least one gaseous fuel and a liquid fuel, set, supply system and gas turbine assembly |
EP4310304A1 (en) | 2022-07-21 | 2024-01-24 | Rolls-Royce Deutschland Ltd & Co KG | Connecting device for the flow connection between a fuel supply system and a nozzle device, nozzle device and gas turbine assembly |
DE102022207492A1 (en) | 2022-07-21 | 2024-02-01 | Rolls-Royce Deutschland Ltd & Co Kg | Nozzle device for adding at least one gaseous fuel and one liquid fuel, set, supply system and gas turbine arrangement |
DE102022207493A1 (en) | 2022-07-21 | 2024-02-01 | Rolls-Royce Deutschland Ltd & Co Kg | Connection device for flow connection between a fuel supply system and a nozzle device, nozzle device and gas turbine arrangement |
EP4321804A1 (en) | 2022-08-10 | 2024-02-14 | Rolls-Royce Deutschland Ltd & Co KG | Combustor assembly for liquid and/or gaseous fuel operation, gas turbine assembly, and method |
DE102022208339A1 (en) | 2022-08-10 | 2024-02-15 | Rolls-Royce Deutschland Ltd & Co Kg | Combustion chamber arrangement for operation with liquid and/or gaseous fuel, gas turbine arrangement and method |
EP4353958A1 (en) | 2022-10-13 | 2024-04-17 | Rolls-Royce Deutschland Ltd & Co KG | Propulsion system for an aircraft, aircraft having a propulsion system, and method for operating an aircraft |
DE102022210807A1 (en) | 2022-10-13 | 2024-04-18 | Rolls-Royce Deutschland Ltd & Co Kg | Propulsion system for an aircraft, aircraft with a propulsion system and method for operating an aircraft |
Also Published As
Publication number | Publication date |
---|---|
EP3036482A4 (en) | 2017-05-03 |
WO2015026760A1 (en) | 2015-02-26 |
EP3036482B1 (en) | 2020-10-21 |
EP3036482A1 (en) | 2016-06-29 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US20160201897A1 (en) | Dual fuel nozzle system and apparatus | |
JP6170438B2 (en) | Engine and combustion system | |
US9115896B2 (en) | Fuel-air mixer for use with a combustor assembly | |
JP6196868B2 (en) | Fuel nozzle and its assembly method | |
US8572981B2 (en) | Self-oscillating fuel injection jets | |
CN107923620B (en) | System and method for a multi-fuel premixing nozzle with integral liquid injector/evaporator | |
US10054314B2 (en) | Slotted injector for axial fuel staging | |
US20120058437A1 (en) | Apparatus and method for mixing fuel in a gas turbine nozzle | |
US9182124B2 (en) | Gas turbine and fuel injector for the same | |
JP6001848B2 (en) | Engraving trailing edge swirler combustion premixer and method | |
EP2481985B1 (en) | Fuel injector assembly | |
US20180355795A1 (en) | Rotating detonation combustor with fluid diode structure | |
US20160061452A1 (en) | Corrugated cyclone mixer assembly to facilitate reduced nox emissions and improve operability in a combustor system | |
US9279587B2 (en) | Device for mixing fuel and air of a jet engine | |
CN102721084B (en) | Burner flame tube interconnector | |
US10352570B2 (en) | Turbine engine fuel injection system and methods of assembling the same | |
RU2013125746A (en) | COMBUSTION CHAMBER (OPTIONS) AND GAS-TURBINE SYSTEM | |
RU98538U1 (en) | CONTINUOUS COMBUSTION CAMERA | |
JP2011226772A (en) | Coannular oil injection nozzle | |
WO2011056928A3 (en) | Micro-turbine combustor | |
US9121348B2 (en) | Hydrogen-rich gas combustion device | |
US9677766B2 (en) | Fuel nozzle for use in a turbine engine and method of assembly | |
CN111023150B (en) | Extension plate for combustion chamber | |
CN102620317A (en) | Fuel injector | |
KR101884694B1 (en) | Nozzle hub with fuel injection holes |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: UNITED TECHNOLOGIES CORPORATION, CONNECTICUT Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:SNYDER, TIMOTHY S;DAI, ZHONGTAO;SMITH, RANDOLPH J;AND OTHERS;SIGNING DATES FROM 20140808 TO 20140814;REEL/FRAME:037776/0098 |
|
STPP | Information on status: patent application and granting procedure in general |
Free format text: RESPONSE TO NON-FINAL OFFICE ACTION ENTERED AND FORWARDED TO EXAMINER |
|
STPP | Information on status: patent application and granting procedure in general |
Free format text: FINAL REJECTION MAILED |
|
STPP | Information on status: patent application and granting procedure in general |
Free format text: RESPONSE AFTER FINAL ACTION FORWARDED TO EXAMINER |
|
STCV | Information on status: appeal procedure |
Free format text: NOTICE OF APPEAL FILED |
|
STCV | Information on status: appeal procedure |
Free format text: APPEAL BRIEF (OR SUPPLEMENTAL BRIEF) ENTERED AND FORWARDED TO EXAMINER |
|
STPP | Information on status: patent application and granting procedure in general |
Free format text: NON FINAL ACTION MAILED |
|
STPP | Information on status: patent application and granting procedure in general |
Free format text: RESPONSE TO NON-FINAL OFFICE ACTION ENTERED AND FORWARDED TO EXAMINER |
|
STPP | Information on status: patent application and granting procedure in general |
Free format text: FINAL REJECTION MAILED |
|
STPP | Information on status: patent application and granting procedure in general |
Free format text: ADVISORY ACTION MAILED |
|
STPP | Information on status: patent application and granting procedure in general |
Free format text: DOCKETED NEW CASE - READY FOR EXAMINATION |
|
AS | Assignment |
Owner name: RAYTHEON TECHNOLOGIES CORPORATION, MASSACHUSETTS Free format text: CHANGE OF NAME;ASSIGNOR:UNITED TECHNOLOGIES CORPORATION;REEL/FRAME:054062/0001 Effective date: 20200403 |
|
STPP | Information on status: patent application and granting procedure in general |
Free format text: RESPONSE TO NON-FINAL OFFICE ACTION ENTERED AND FORWARDED TO EXAMINER |
|
AS | Assignment |
Owner name: RAYTHEON TECHNOLOGIES CORPORATION, CONNECTICUT Free format text: CORRECTIVE ASSIGNMENT TO CORRECT THE AND REMOVE PATENT APPLICATION NUMBER 11886281 AND ADD PATENT APPLICATION NUMBER 14846874. TO CORRECT THE RECEIVING PARTY ADDRESS PREVIOUSLY RECORDED AT REEL: 054062 FRAME: 0001. ASSIGNOR(S) HEREBY CONFIRMS THE CHANGE OF ADDRESS;ASSIGNOR:UNITED TECHNOLOGIES CORPORATION;REEL/FRAME:055659/0001 Effective date: 20200403 |
|
STPP | Information on status: patent application and granting procedure in general |
Free format text: FINAL REJECTION MAILED |
|
STPP | Information on status: patent application and granting procedure in general |
Free format text: RESPONSE AFTER FINAL ACTION FORWARDED TO EXAMINER |
|
STPP | Information on status: patent application and granting procedure in general |
Free format text: ADVISORY ACTION MAILED |
|
STCB | Information on status: application discontinuation |
Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION |