US20140033721A1 - Fuel nozzle assembly and methods of assembling same - Google Patents

Fuel nozzle assembly and methods of assembling same Download PDF

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Publication number
US20140033721A1
US20140033721A1 US13/566,459 US201213566459A US2014033721A1 US 20140033721 A1 US20140033721 A1 US 20140033721A1 US 201213566459 A US201213566459 A US 201213566459A US 2014033721 A1 US2014033721 A1 US 2014033721A1
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United States
Prior art keywords
tube
end portion
flow member
turbine engine
fuel
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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
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US13/566,459
Inventor
Elias Marquez
Lucas John Stoia
Oscar Flores
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General Electric Co
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General Electric Co
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Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Priority to US13/566,459 priority Critical patent/US20140033721A1/en
Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: STOIA, LUCAS JOHN, FLORES, Oscar, MARQUEZ, ELIAS
Publication of US20140033721A1 publication Critical patent/US20140033721A1/en
Application status is Abandoned legal-status Critical

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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F23N2235/26
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00017Assembling combustion chamber liners or subparts
    • YGENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10TTECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00Metal working
    • Y10T29/49Method of mechanical manufacture
    • Y10T29/494Fluidic or fluid actuated device making

Abstract

A fuel nozzle assembly for use with a turbine engine is provided. The fuel nozzle assembly includes a tube that is configured to channel at least a first type of fuel through the turbine engine. A flow member includes a first end portion and a second end portion that is removably coupled to the tube such that the flow member is severally removable from the tube to enable a plurality of different types of fuel to be channeled through the turbine engine for operation of the turbine engine.

Description

    BACKGROUND OF THE INVENTION
  • The field of the invention relates generally to turbine engines and, more particularly, to a fuel nozzle assembly for use with turbine engines.
  • At least some known turbine engines, such as gas turbine engines, are used in cogeneration facilities and power plants to generate power. At least some known gas turbine engines may have high specific work and power per unit mass flow requirements. To increase the operating efficiency, gas turbine engines may operate with increased combustion temperatures. Moreover, in at least some known gas turbine engines, engine efficiency increases as combustion gas temperatures increase.
  • However, operating with higher temperatures may also increase the generation of polluting emissions, such as oxides of nitrogen (NOx). In an attempt to reduce the generation of such emissions, at least some known gas turbine engines include improved combustion system designs. For example, at least some known combustion systems may include a plurality of fuel nozzles or fuel nozzle assemblies, wherein at least one of the fuel nozzles is a pre-mix nozzle. For example, known pre-mix nozzles enable substances to be mixed, such as diluents, gases, and/or air, with fuel to generate a fuel mixture for combustion. The mixed substances are discharged from a tube of the pre-mix nozzle through a flow member, such as a tertiary diffusion tip, that is integrally formed with the tube. More specifically, known flow members include a plurality of openings that enable the fuel to be discharged therefrom.
  • Various types of fuels may be used during operation of the gas turbine engine. However, each of the different types of fuel may require a specific size (i.e., diameter) of flow member openings. For example, while the size of the flow member openings may be sufficient for the passage of one type of fuel, those same openings may be too large or too small for a different type of fuel. As such, the flow member may need to be changed based on the type of fuel being used. However, in order to replace the flow member, the attached flow member may need to be cut from the tube prior to a new flow member being welded onto the tube. Such a process may time-consuming and/or labor intensive or relatively challenging.
  • BRIEF DESCRIPTION OF THE INVENTION
  • In one embodiment, a fuel nozzle assembly for use with a turbine engine is provided. The fuel nozzle assembly includes a tube that is configured to channel at least a first type of fuel through the turbine engine. A flow member includes a first end portion and a second end portion that is removably coupled to the tube such that the flow member is severally removable from the tube to enable a plurality of different types of fuel to be channeled through the turbine engine for operation of the turbine engine.
  • In another embodiment, a turbine engine is provided. The turbine engine includes a compressor. A combustion assembly is coupled to the compressor and the combustion assembly includes at least one combustor. At least one fuel nozzle assembly is coupled within the combustor. The fuel nozzle assembly includes a tube that is configured to channel at least a first type of fuel through the turbine engine. A flow member includes a first end portion and a second end portion that is removably coupled to the tube such that the flow member is severally removable from the tube to enable a plurality of different types of fuel to be channeled through the turbine engine for operation of the turbine engine.
  • In yet another embodiment, a method of assembling a fuel nozzle assembly for use with a turbine engine is provided. A tube that is configured to channel at least a first type of fuel through the turbine engine is provided. A flow member is coupled to the tube to enable the first type of fuel to be channeled through the turbine engine. The flow member is removed from the tube to enable a plurality of different types of fuel to be channeled through the turbine engine for operation of the turbine engine.
  • BRIEF DESCRIPTION OF THE DRAWINGS
  • FIG. 1 is a schematic cross-sectional view of an exemplary turbine engine;
  • FIG. 2 is a schematic cross-sectional view of a portion of an exemplary fuel nozzle that may be used with the turbine engine shown in FIG. 1 and taken from area 2;
  • FIG. 3 is an enlarged cross-sectional view of a portion of an exemplary fuel nozzle assembly that may be used with the fuel nozzle shown in FIG. 2 and taken from area 3;
  • FIG. 4 is a schematic cross-sectional view of a portion of an exemplary flow member that may be used with the fuel nozzle assembly shown in FIG. 3 and taken from area 4; and
  • FIG. 5 is a schematic cross-sectional view of a portion of the flow member shown in FIG. 4 and taken from area 5.
  • DETAILED DESCRIPTION OF THE INVENTION
  • The exemplary systems and methods described herein overcome at least some known disadvantages associated with at least some known combustion systems of turbine engines. More specifically, the embodiments described herein provide a fuel nozzle assembly that includes components that may relatively easily and/or efficiently removed and/or replaced for the various types of fuels being used with the turbine engine. For example, in the exemplary embodiment, the fuel nozzle assembly includes a flow member, such as a tertiary diffusion tip, that is removably coupled to a tube of the fuel nozzle assembly fuel to be channeled therethrough and to be easily removed and replaced if a different type of fuel is to be used to operate the turbine engine. Accordingly, in the exemplary embodiment, in order to replace the flow member, it no longer needs to be cut from the nozzle and welding is not required for attaching the flow member.
  • FIG. 1 illustrates an exemplary turbine engine 100. More specifically, turbine engine 100 is a gas turbine engine. While the exemplary embodiment illustrates a gas turbine engine, the present invention is not limited to any one particular engine, and one of ordinary skill in the art will appreciate that the current invention may be used in connection with other turbine engines.
  • Moreover, in the exemplary embodiment, turbine engine 100 includes an intake section 112, a compressor section 114 coupled downstream from intake section 112, a combustor section 116 coupled downstream from compressor section 114, a turbine section 118 coupled downstream from combustor section 116, and an exhaust section 120. It should be noted that, as used herein, the term “couple” is not limited to a direct mechanical, thermal, communication, and/or an electrical connection between components, but may also include an indirect mechanical, thermal, communication and/or electrical connection between multiple components.
  • In the exemplary embodiment, turbine section 118 is coupled to compressor section 114 via a rotor shaft 122. Combustor section 116 includes a plurality of combustors 124. Combustor section 116 is coupled to compressor section 114 such that each combustor 124 is positioned in flow communication with the compressor section 114. A plurality of fuel nozzles, such as fuel nozzles 126 and fuel nozzle 127, are coupled within each combustor 124. In the exemplary embodiment, fuel nozzles 126 are diffusion type nozzles and fuel nozzle 127 is a pre-mix nozzle. Alternatively, fuels nozzles 126 and 127 may be any suitable fuel nozzle that enables turbine engine 100 to function as described herein. Moreover, fuel nozzles 126 and 127 may be aligned substantially within a cap member (not shown) and/or fuel nozzles 126 and 127 may be integrally formed with the cap member.
  • In the exemplary embodiment, fuel nozzles 126 are spaced circumferentially about fuel nozzle 127 such that each fuel nozzle 127 is positioned within the center of the cap member. Alternatively, fuel nozzles 126 and 127 may be oriented in any orientation that enables turbine engine 100 to function as described herein. Moreover, as described in more detail below, fuel nozzle 127 includes a fuel nozzle assembly (not shown in FIG. 1) that includes components (not shown in FIG. 1) that can be relatively easily and efficiently removed and/or replaced from fuel nozzle 127. In the exemplary embodiment, while only fuel nozzle 127 includes the fuel nozzle assembly, other nozzles 126 may also include the fuel nozzle assembly.
  • Further, in the exemplary embodiment, turbine section 118 is coupled to compressor section 114 and to a load 128 such as, but not limited to, an electrical generator and/or a mechanical drive application. In the exemplary embodiment, each compressor section 114 and turbine section 118 includes at least one rotor disk assembly 130 that is coupled to a rotor shaft 122 to form a rotor assembly 132.
  • During operation, intake section 112 channels air towards compressor section 114 wherein the air is compressed to a higher pressure and temperature prior to being discharged towards combustor section 116. The compressed air is mixed with fuel and other fluids that are ignited to generate combustion gases that are channeled towards turbine section 118. More specifically, fuel, such as natural gas and/or fuel oil, air, diluents, and/or Nitrogen gas (N2) may be channeled into combustors 124, into the air flow, and into at least fuel nozzle 127. The blended mixtures are ignited to generate high temperature combustion gases that are channeled towards turbine section 118. Turbine section 118 converts the thermal energy from the gas stream to mechanical rotational energy, as the combustion gases impart rotational energy to turbine section 118 and to rotor assembly 132.
  • FIG. 2 is a schematic cross-sectional view of a portion of fuel nozzle 127 taken from area 2 (shown in FIG. 1). In the exemplary embodiment, fuel nozzle 127 includes a cylindrical tube assembly 202 that includes an inner cylindrical tube 204 and an outer cylindrical tube 206. More specifically, in the exemplary, outer tube 206 includes a channel 207 defined therein, and inner tube 204 is positioned within channel 207 such that outer tube 206 substantially circumscribes inner tube 204. Inner tube 204 also includes a channel 210 defined therein that is sized and oriented to channel fluids, such as various types of fuel, therethrough. In the exemplary embodiment, outer tube 206 includes an exterior portion 212, an interior portion 214, and a plurality of openings 216 that extend from exterior portion 212 to interior portion 214. Moreover, at least a first channel 220 is defined within interior portion 214 of outer tube 206 to channel fluids, such as various types of fuel, therethrough. For example, channel 220 may extend from at least one fuel source (not shown) to openings 216 such that fuel may be channeled through channel 220 and through each opening 216. Moreover, in some embodiments, channel 220 may also extend from opening 216 to an end portion 222 of fuel nozzle 127, wherein channel 220 is independent from fuel nozzle end portion 222.
  • In the exemplary embodiment, outer tube 206 and inner tube 204 may be integrally formed together such that tube assembly 202 is a unitary component. Alternatively, outer tube 206 and inner tube 204 may be separate structures that are coupled together. Moreover, tube assembly 202 may be formed via a variety of manufacturing processes known in the art, such as, but not limited to, molding process, drawing process or a machining process. One or more types of materials may be used to fabricate tube assembly 202 with the materials selected based on suitability for one or more manufacturing techniques, dimensional stability, cost, moldability, workability, rigidity, and/or other characteristic of the material(s). For example, tube assembly 202 may be fabricated from steel.
  • Moreover, in the exemplary embodiment, fuel nozzle 127 includes a plurality of pegs or fasteners 230 that are coupled to tube assembly 202. More specifically, fasteners 230 may be coupled to exterior portion 212 of outer tube 206. In the exemplary embodiment, each fastener 230 is coupled to outer tube 206 such that each fastener 230 extends radially outwardly from outer tube 206 and such that fasteners 230 are concentrically aligned with openings 216. Moreover, in the exemplary embodiment, each fastener 230 is substantially cylindrical. Alternatively, each fastener 230 may have any suitable shape that enables fuel nozzle 127 and/or turbine engine 100 to function as described herein.
  • In the exemplary embodiment, each fastener 230 includes an exterior portion 232 and an interior portion 234 that has a channel 236 defined therein such that various types of fuels may be channeled therethrough. Moreover, in the exemplary embodiment, each fastener 230 includes a plurality of openings 240 that extend from exterior portion 232 to interior portion 234. As such, fuel may be channeled from channel 220 to channel 236, and through openings 240 for use within combustor 124 (shown in FIG. 1). In the exemplary embodiment, openings 240 each have a predefined size (e.g., diameter) that is suitable to enable specific types of fuel to be channeled therethrough. Fasteners 230 may be removably coupled to tube assembly 202 or be integrally formed with tube assembly 202. In the exemplary embodiment, fasteners 230 and/or tube assembly 202 may be fabricated from the same material that enables fuel nozzle 127 and/or turbine engine 100 to function as described herein. Alternatively, fasteners 230 and/or tube assembly 202 may each be fabricated from different materials that enable fuel nozzle 127 and/or turbine engine 100 to function as described herein.
  • In the exemplary embodiment, fuel nozzle 127 includes a fuel nozzle assembly 250 at end portion 222 of fuel nozzle 127. Moreover, a second channel 254 defined within interior portion 214 of outer tube 206 is configured to channel fluids, such as various types of fuel, therethrough. For example, channel 254 may extend from at least one fuel source (not shown) to fuel nozzle assembly 250. As described in more detail below, fuel may be channeled through channel 254 and through fuel nozzle assembly 250.
  • FIG. 3 is an enlarged cross-sectional view of a portion of fuel nozzle assembly 250 taken from area 3 (shown in FIG. 2). FIG. 4 is a schematic cross-sectional view of a portion of a flow member 314 that may be used with fuel nozzle assembly 250 taken from area 4 (shown in FIG. 3). FIG. 5 is a schematic cross-sectional view of a portion of flow member 314 taken from area 5 (shown in FIG. 4). In the exemplary embodiment, fuel nozzle assembly 250 includes inner tube 204 that includes a first end portion 302, a second end portion 304, and a middle portion 306 that extends between first end portion 302 and second end portion 304. Tube 204 also includes an outer portion 308 and an opposite inner portion 310. Channel 210 is defined within inner portion 310, and channel 210 extends from first end portion 302 to second end portion 304.
  • A flow member 314 is removably coupled to tube 204. More specifically, in the exemplary embodiment, flow member 314 includes an exterior tube 320 having an outer portion 322 and an opposing inner portion 324 that defines a channel 326 therein. Flow member 314 also includes an interior tube 328 that is positioned within channel 326. Interior tube 328 includes an outer portion 330 that is adjacent to inner portion 324 of exterior tube 320, and an inner portion 332 that includes a channel 334 defined therein. Channel 334 is sized and shaped to channel various fluids, such as various types of fuels, therethrough. In the exemplary embodiment, when flow member 314 is coupled to tube 204, tube channel 210 is substantially concentrically aligned within flow member channel 334.
  • In the exemplary embodiment, exterior tube 320 and interior tube 328 of flow member 314 are integrally formed together such that flow member 314 is a unitary component. Alternatively, exterior tube 320 and interior tube 328 may be separate structures that are coupled together. Moreover, flow member 314 may be formed via a variety of manufacturing processes known in the art, such as, but not limited to, molding process, drawing process or a machining process. One or more types of materials may be used to fabricate flow member 314 with the materials selected based on suitability for one or more manufacturing techniques, dimensional stability, cost, moldability, workability, rigidity, and/or other characteristic of the material(s). For example, flow member 314 may be fabricated from steel. Further, flow member 314 and tube 204 may be fabricated from the same material(s) or each may be fabricated from different material(s).
  • In the exemplary embodiment, flow member exterior tube 320 has a first end portion 340 and a second end portion 342 that is coupled to second end portion 304 of tube 204. More specifically, in the exemplary embodiment, second end portion 342 includes a plurality of grooves 346 formed on outer portion 322 such that second end portion 342 is threaded. Second end portion 304 of tube 204 receives grooves 346 therein. For example, second end portion 304 may be keyed to receive grooves. Accordingly, second end portion 324 of exterior tube 320 of flow member 314 may be threadably coupled to second portion 304 of tube 204. Alternatively, second end portion 342 may not have grooves 346 and may be coupled to second end portion 304 of tube 204 in any suitable manner that enables fuel nozzle assembly 250 and/or turbine engine 100 to function as described herein.
  • Similar to exterior tube 320, interior tube 328 also includes a first end portion 350 and a second end portion 352. Moreover, in the exemplary embodiment, interior tube 328 includes a plurality of openings 360 that are defined between outer portion 330 and inner portion 332 of tube 328. Openings 360 also extend from first end portion 350 to second end portion 352 such that fluids, such as various types of fuels may be channeled therethrough.
  • Prior to operation of turbine engine 100, flow member 314 may be coupled to tube 204. More specifically, in the exemplary embodiment, second end portion 342 of exterior tube 320 may be threadably coupled to second end portion 304 of tube 204. When flow member 314 is securely coupled to tube 204, fuel, such as natural gas and/or fuel oil, air, diluents, and/or Nitrogen gas (N2) is channeled into fuel nozzle 127 (shown in FIG. 1). For example, in the exemplary embodiment, fuel may be channeled through channel 254 (shown in FIG. 2) of outer tube 206 (shown in FIG. 2) and fuel may be channeled through channel 210 (shown in FIG. 2). At the same time, fuel, such as gas fuel, may be channeled from channel 220 (shown in FIG. 2) to channel 236 (shown in FIG. 2) of each fastener 230 (shown in FIG. 2) and through fastener openings 240 (shown in FIG. 2).
  • Fuels from channels 254, 210, and 220 may then be channeled to end portion 222 (shown in FIG. 2) of fuel nozzle 127 and towards fuel nozzle assembly 250. More specifically, the fuel is channeled through channel 210 and through channel 334. Fuel is also channeled through openings 360 that are defined between outer portion 330 and inner portion 332 of tube 328 such that the fuel may be ignited to generate high temperature combustion gases that are channeled towards turbine section 118 (shown in FIG. 1).
  • A user of turbine engine 100 may change the type of fuels being used with turbine engine 100. However, the new type of fuel may not fit through fastener openings 360. As such, the user may remove flow member 314 from tube 204. More specifically, second end portion 342 of exterior tube 320 of flow member 314 may be removed from second end portion 304 of tube 204 and be replaced with a different flow member (not shown) having openings (not shown) that are suitable for the new type of fuel being used.
  • As compared to known turbine engines, the embodiments described herein provide a fuel nozzle assembly that enables the use of different types of fuels by providing a relatively easy and efficient solution to removing and replacing components of the fuel nozzle assembly. More specifically, the fuel nozzle assembly described herein includes a cylindrical tube that is configured to channel at least a first type of fuel through the turbine engine. A flow member includes a first end portion and a second end portion that is removably coupled to the cylindrical tube such that the flow member is severally removable from the tube to enable a plurality of different types of fuel to be channeled through the turbine engine for operation of the turbine engine. Accordingly, in the exemplary embodiment, in order to replace the flow member, it no longer needs to be cut from the nozzle and welding is not required for attaching the flow member.
  • Exemplary embodiments of the apparatus, systems, and methods are described above in detail. The apparatus, systems, and methods are not limited to the specific embodiments described herein, but rather, components of the apparatus, systems, and/or steps of the methods may be utilized independently and separately from other components and/or steps described herein. For example, the systems may also be used in combination with other systems and methods, and is not limited to practice with only the systems as described herein. Rather, the exemplary embodiment can be implemented and utilized in connection with many other applications.
  • Although specific features of various embodiments of the invention may be shown in some drawings and not in others, this is for convenience only. In accordance with the principles of the invention, any feature of a drawing may be referenced and/or claimed in combination with any feature of any other drawing.
  • This written description uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the invention is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they have structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal language of the claims.

Claims (20)

What is claimed is:
1. A fuel nozzle assembly for use with a turbine engine, said fuel nozzle assembly comprising:
a tube configured to channel at least a first type of fuel through the turbine engine; and
a flow member comprising a first end portion and a second end portion that is removably coupled to said tube such that said flow member is severally removable from said tube to enable a plurality of different types of fuel to be channeled through the turbine engine for operation of the turbine engine.
2. A fuel nozzle assembly in accordance with claim 1, wherein said flow member comprises an exterior tube and an interior tube that is integrally formed within said exterior tube.
3. A fuel nozzle assembly in accordance with claim 2, wherein said interior tube comprises an interior tube first end portion, an interior tube second end portion, and a plurality of openings extending from said interior tube first end portion to said interior tube second end portion.
4. A fuel nozzle assembly in accordance with claim 2, wherein said interior tube comprises a channel defined therein and is configured to channel fluid therethrough.
5. A fuel nozzle assembly in accordance with claim 4, wherein said tube comprises a channel defined therein, said interior tube channel is concentrically aligned with said tube channel when said flow member is coupled to said tube.
6. A fuel nozzle assembly in accordance with claim 1, wherein said flow member second end portion comprises a plurality of grooves.
7. A fuel nozzle assembly in accordance with claim 6, wherein said tube comprises a tube end portion that is configured to receive said plurality of grooves therein.
8. A turbine engine comprising:
a compressor;
a combustion assembly coupled to said compressor, wherein said combustion assembly comprises at least one combustor;
at least one fuel nozzle assembly coupled within said at least one combustor, said at least one fuel nozzle assembly comprises:
a tube that is configured to channel at least a first type of fuel through said turbine engine; and
a flow member comprising a first end portion and a second end portion that is removably coupled to said tube such that said flow member is severally removable from said tube to enable a plurality of different types of fuel to be channeled through said turbine engine for operation of said turbine engine.
9. A turbine engine in accordance with claim 8, wherein said flow member comprises an exterior tube and an interior tube that is integrally formed within said exterior tube.
10. A turbine engine in accordance with claim 9, wherein said interior tube comprises an interior tube first end portion, an interior tube second end portion, and a plurality of openings extending from said interior tube first end portion to said interior tube second end portion.
11. A turbine engine in accordance with claim 10, wherein said interior tube comprises a channel defined therein and is configured to channel fluid therethrough.
12. A turbine engine in accordance with claim 11, wherein said tube comprises a channel defined therein, said interior tube channel is concentrically aligned with said tube channel when said flow member is coupled to said tube.
13. A turbine engine in accordance with claim 8, wherein said flow member second end portion comprises a plurality of grooves.
14. A turbine engine in accordance with claim 13, wherein said tube comprises a tube end portion that is configured to receive said plurality of grooves therein.
15. A method of assembling a fuel nozzle assembly for use with a turbine engine, said method comprising:
providing a tube that is configured to channel at least a first type of fuel through the turbine engine;
coupling a flow member to the tube to enable the first type of fuel to be channeled through the turbine engine; and
removing the flow member from the tube to enable a plurality of different types of fuel to be channeled through the turbine engine for operation of the turbine engine.
16. A method in accordance with claim 15, wherein coupling a flow member further comprises coupling a flow member that includes an exterior tube and an interior tube integrally formed within the exterior tube.
17. A method in accordance with claim 15, wherein coupling a flow member further comprises coupling a flow member that includes an exterior tube and an interior tube that includes an interior tube first end portion, an interior tube second end portion, and a plurality of openings extending from the interior tube first end portion to the interior tube second end portion.
18. A method in accordance with claim 15, wherein coupling a flow member further comprises coupling a flow member that includes an exterior tube and an interior tube that includes a channel defined therein and is configured to channel fluid therethrough.
19. A method in accordance with claim 15, wherein coupling a flow member further comprises coupling a flow member that includes a first end portion and a second end portion that includes a plurality of grooves.
20. A method in accordance with claim 19, wherein coupling a flow member further comprises coupling the flow member second end portion to a tube end portion that is configured to receive the plurality of grooves therein.
US13/566,459 2012-08-03 2012-08-03 Fuel nozzle assembly and methods of assembling same Abandoned US20140033721A1 (en)

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PCT/US2013/053133 WO2014022617A1 (en) 2012-08-03 2013-08-01 Fuel nozzle assembly with removable fuel nozzle tip and method of assembling same

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US20150193768A1 (en) * 2014-01-09 2015-07-09 Capital One Financial Corporation Method and system for providing alert messages related to suspicious transactions
US10184403B2 (en) 2014-08-13 2019-01-22 Pratt & Whitney Canada Corp. Atomizing fuel nozzle

Citations (1)

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Publication number Priority date Publication date Assignee Title
US7690203B2 (en) * 2006-03-17 2010-04-06 Siemens Energy, Inc. Removable diffusion stage for gas turbine engine fuel nozzle assemblages

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Publication number Priority date Publication date Assignee Title
CA1259197A (en) * 1985-02-13 1989-09-12 Alan D. Bennett High reliability fuel oil nozzle for a gas turbine
US4850196A (en) * 1987-10-13 1989-07-25 Westinghouse Electric Corp. Fuel nozzle assembly for a gas turbine engine
US4891935A (en) * 1987-10-23 1990-01-09 Westinghouse Electric Corp. Fuel nozzle assembly for a gas turbine engine

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7690203B2 (en) * 2006-03-17 2010-04-06 Siemens Energy, Inc. Removable diffusion stage for gas turbine engine fuel nozzle assemblages

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150193768A1 (en) * 2014-01-09 2015-07-09 Capital One Financial Corporation Method and system for providing alert messages related to suspicious transactions
US10184403B2 (en) 2014-08-13 2019-01-22 Pratt & Whitney Canada Corp. Atomizing fuel nozzle

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Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:MARQUEZ, ELIAS;STOIA, LUCAS JOHN;FLORES, OSCAR;SIGNING DATES FROM 20120801 TO 20120803;REEL/FRAME:028721/0750

STCB Information on status: application discontinuation

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