• 专利附录
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  • 类似技术
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    • 专利摘要:
    Premix fuel nozzle assembly (100) includes a central body (110) including a sleeve (124) having an inner surface (126) and a pilot premix fuel nozzle assembly (200) extending axially through the central body (110) within the sleeve (124) and defines a pilot air passage (228) within the centerbody (110). The pilot premix fuel nozzle assembly (200) includes a premix tip (226) having a plurality of premix tubes (238) defining premix passages (254) in fluid communication with the pilot air passage (228). At least one of the premix tubes (238) includes a fuel port (256). The premix fuel nozzle assembly (100) further includes a pilot fuel flowpath (258) radially defined between the pilot premix fuel nozzle assembly (200) and the inner surface (126) of the sleeve (124) and a fuel plenum (262) at least partially disposed between the sleeve inner surface (126 ) and an outer surface of the premix tip (226). The fuel ports (256) provide fluid communication between the fuel plenum (262) and premixing passages (254).
    公开号:CH710425A2
    申请号:CH01699/15
    申请日:2015-11-20
    公开日:2016-05-31
    发明作者:Christopher Gibson Michael；Joseph Ouellet Dereck
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    FIELD OF THE INVENTION
    The present invention relates generally to a premix fuel nozzle assembly for a gas turbine combustor. More particularly, the invention relates to a dual fuel premix fuel nozzle assembly configured for gas only operation.
    BACKGROUND TO THE INVENTION
    [0002] Gas turbine combustors for power generation are generally available with fuel nozzles configured for either "dual fuel" or "gas only" operation. "Gas only" refers to a fuel nozzle that is responsive to the delivery of a gaseous fuel, such as gas. Natural gas, limited to combustion in a combustion chamber of the combustion chamber. "Dual fuel" refers to a fuel nozzle that may be configured to supply either a liquid fuel or a gaseous fuel for combustion during operation of the combustor. The combustor is typically operated with gaseous fuel, however, the liquid fuel may be used as a backup or alternative fuel in the event that the gaseous fuel becomes unavailable or the supply is limited. In certain configurations, a gas turbine combustor may be designed to accommodate a plurality of "dual fuel" fuel nozzles annularly disposed about a central fuel nozzle and / or about a common axial centerline.
    In a conventional "dual fuel" fuel nozzle, the liquid fuel is supplied through a liquid fuel nozzle or cartridge which extends axially within a center body portion of the fuel nozzle. The gaseous fuel is typically injected into a swirling flow of compressed air passing through an annular passage defined between the centerbody and an outer burner tube whereby the gaseous fuel is premixed with the compressed air before being directed into a combustion zone. which is defined downstream of the fuel nozzle. In certain configurations, a pilot premix nozzle or tip is disposed at a tip portion of the centerbody and concentrically aligned with the liquid fuel nozzle. During operation, the pilot premixing nozzle may be used to provide a substantially stabilized pilot flame during diffusion operation of the gas turbine, even at a low fuel-air ratio, thereby improving combustion chamber emissions performance.
    Although a gas turbine may include combustors having a "dual fuel" or "reserve fuel" capability, this may not be required by the operator or, in some cases, the liquid fuel may be unavailable and / or inefficient. On a gas turbine that is not required to have a reserve fuel capability, a gas only cartridge is provided in place of the liquid fuel nozzle, thereby converting the otherwise "dual fuel" fuel nozzle into a gas only fuel nozzle. Purge air is passed through the gas only cartridge to maintain cartridge tip temperatures within allowable limits during combustion chamber operation.
    Particularly in combustion chambers with premix pilot nozzles, the purge air flows from the gas-only cartridge and into a pilot flame provided by the premix pilot nozzle. As a result, the scavenging air can reduce the stability of the pilot flame, which can affect the performance of the combustion chamber. Therefore, an improved dual fuel premix fuel nozzle assembly, particularly one having a pilot premix nozzle and / or a gas only cartridge configured to reduce the effects of the purge air on the pilot flame provided by the pilot premix nozzle, would be useful.
    BRIEF DESCRIPTION OF THE INVENTION
    Aspects and advantages of the invention are set forth below in the description which follows, or may be obvious from the description, or may be learned by practice of the invention.
    One aspect of the present invention is a premix fuel nozzle assembly. The premix fuel nozzle assembly includes a central body at least partially defined by a sleeve having an inner surface. The premix fuel nozzle assembly further includes a pilot premix fuel nozzle assembly extending axially through the centerbody within the sleeve and defining a pilot air passage within the centerbody. The pilot premix fuel nozzle assembly includes a premix tip having a plurality of premix tubes, each premix tube defining a premix passage and a fuel port. The premix passage is in fluid communication with the pilot air passage. A pilot fuel flow path is defined radially between the pilot premix fuel nozzle assembly and the inner surface of the central body sleeve. A fuel plenum is defined at least partially between the sleeve inner surface and an outer surface of the premix tip. The fuel ports provide fluid communication between the fuel plenum and the premix passages.
    In the aforementioned premix fuel nozzle assembly, the pilot fuel flow path may extend axially between an intake passage and the fuel plenum.
    In one embodiment, the premix fuel nozzle may be a dual fuel premix fuel nozzle.
    In another embodiment, the pilot premix fuel nozzle assembly may include a stem, a coupling collar, a bellows, and a flow extension collar connected in series upstream of the premix tip.
    In the last-mentioned embodiment, the premix fuel nozzle assembly may further comprise a bushing surrounding the bellows along the circumference.
    In particular, the bellows and the bushing may at least partially define a collection space therebetween.
    In the premix fuel nozzle assembly of any type mentioned above, the plurality of premix tubes may be annularly disposed about the outer surface of the premix tip within the fuel plenum.
    In addition, or as an alternative, each premix tube of the plurality of premix tubes may extend radially outward from the outer surface of the premix tip within the fuel plenum.
    In one embodiment, the pilot premix fuel nozzle assembly may include one or more radial clearance features extending radially outward from one or more outer surfaces of the pilot premix fuel nozzle assembly within the premix fuel flow path.
    Another aspect of the present disclosure is a combustion chamber. The combustor includes an end cover and a plurality of premix fuel nozzle assemblies annularly disposed about a central fuel nozzle. Each of the premix fuel nozzle assemblies is a dual fuel type premix fuel nozzle assembly, each premix fuel nozzle assembly having a central body defined at least in part by a sleeve having an inner surface. A pilot premix fuel nozzle assembly extends axially through the centerbody within the sleeve and defines a pilot air passage within the centerbody. The pilot premix fuel nozzle assembly includes a premix tip having a plurality of premix tubes, each premix tube having an inlet end and an outlet end and a premix passage defined therebetween. Each premix tube contains at least one fuel port. The inlet end of the premix tube is in fluid communication with the pilot air passage. The premix fuel nozzle assembly further includes a pilot fuel flow path defined radially between the pilot premix fuel nozzle assembly and the inner surface of the sleeve of the centerbody and a fuel plenum defined at least partially between the sleeve inner surface and an outer surface of the premix tip. The fuel ports provide fluid communication between the fuel plenum and the premix passages.
    In the aforementioned combustor, the pilot fuel flow path may extend axially between an intake passage and the fuel plenum.
    Additionally or alternatively, the premix fuel nozzle assembly may be a dual fuel premix fuel nozzle.
    In one embodiment of the combustor, the pilot premix fuel nozzle assembly may include a stem, a coupling collar, a bellows, and a flow extension collar connected in series upstream of the premix tip.
    In this embodiment, the pilot premix fuel nozzle assembly may further include a bushing surrounding the bellows along the circumference.
    In addition, the bellows and the socket can at least partially define a collecting space therebetween.
    In an embodiment, the plurality of premix tubes of the pilot premix fuel nozzle assembly may be annularly disposed about the outside surface of the premix tip within the fuel plenum.
    In another embodiment, each premix tube of the plurality of premix tubes may extend radially outward from the outer surface of the premix tip within the fuel plenum.
    In yet another embodiment, the pilot premix fuel nozzle assembly may include one or more radial distance features extending radially outwardly from the one or more outer surfaces of the pilot premix fuel nozzle assembly within the premix fuel flow path.
    The combustion chamber of any kind mentioned above may be a component of a gas turbine.
    In one embodiment, the outlet ends of the premix tubes of the plurality of premix tubes may be annularly disposed about a fuel distribution disc portion of the premix tip.
    Those skilled in the art will better appreciate the features and aspects of such and other embodiments upon review of the specification.
    BRIEF DESCRIPTION OF THE DRAWINGS
    A full and enabling disclosure of the present invention, including its best mode, to those skilled in the art is set forth in particular in the remainder of the specification, including the accompanying drawings, in which:<Tb> FIG. 1 <SEP> is a functional block diagram of an exemplary gas turbine that may incorporate various embodiments of the present invention;<Tb> FIG. FIG. 2 is a side perspective view of an exemplary combustor as may include various embodiments of the present invention; FIG.<Tb> FIG. 3 <SEP> is a side perspective view of a portion of an exemplary combustor as may include one or more embodiments of the present invention;<Tb> FIG. 4 is a cross-sectional side view of an exemplary premix fuel nozzle assembly as may be included in the combustor shown in FIG. 3, in accordance with one or more embodiments of the present invention;<Tb> FIG. 5 is a side perspective view of an exemplary pilot premix fuel nozzle assembly as shown in FIG. 4 and as may be included in the combustor shown in FIG. 3, according to at least one embodiment;<Tb> FIG. FIG. 6 is an enlarged cross-sectional side view of a downstream portion of the exemplary pilot premix fuel nozzle assembly shown in FIG. 5, in accordance with one or more embodiments of the present invention; FIG.<Tb> FIG. 7 is a cross-sectional side view of the exemplary premix fuel nozzle assembly as shown in FIGS. 5 and 6, according to one or more embodiments of the present invention;<Tb> FIG. 8 is an enlarged cross-sectional side view of a portion of the premix fuel nozzle assembly as shown in FIG. 7 including a portion of a pilot premix fuel nozzle assembly, according to one or more embodiments of the present invention;<Tb> FIG. 9 is a perspective cross-sectional view of the premix fuel nozzle assembly as shown in FIGS. 3 and 7 according to various embodiments of the present invention;<Tb> FIG. 10 is an enlarged cross-sectional perspective view of a portion of the premix fuel nozzle assembly as shown in FIG. 9, according to at least one embodiment of the present invention;<Tb> FIG. 11 is an enlarged perspective cross-sectional side view of a tip portion of an air cartridge assembly as shown in FIG. 10, according to at least one embodiment of the present invention;<Tb> FIG. Fig. 12 is a perspective view of a tip portion of an air cartridge assembly as shown in Fig. 11, according to an embodiment of the present invention;<Tb> FIG. 13 <SEP> is a cross-sectional side view of the premix fuel nozzle assembly showing various flow paths of fuel and air or a purge medium through the premix fuel nozzle assembly as shown in FIG. 9, according to one or more embodiments of the present invention; and<Tb> FIG. 14 is a perspective view of a downstream end of a pilot premix flow nozzle assembly in pilot premix operation according to one embodiment of the present invention.
    DETAILED DESCRIPTION OF THE INVENTION
    Reference will now be made in detail to present embodiments of the invention, wherein one or more of the examples are illustrated in the accompanying drawings. The detailed description uses numerical and letter-based terms to refer to features in the figures. In the figures and the description, similar or similar terms are used to refer to the same or similar elements of the invention. As used herein, the terms "first," "second," and "third" may be used interchangeably to distinguish one component from another, and are not intended to indicate the location or meaning of the individual components. The terms "upstream" and "downstream" refer to the relative direction with respect to a flow direction in a flow path. For example, "upstream" refers to the direction from which a fluid flows, and "downstream" refers to the direction in which the fluid flows.
    Each example is given to illustrate the invention, not to limit the invention. Indeed, it will be apparent to one skilled in the art that modifications and variations of the present invention may be made without departing from the scope or spirit thereof. For example, features illustrated or described as part of one embodiment may be used in another embodiment to produce yet another embodiment. Thus, it is intended that the present invention cover such modifications and variations that fall within the scope of the appended claims and their equivalents. Although exemplary embodiments for the purpose of illustrating the present invention will be described essentially in the context of a premix fuel nozzle assembly, one skilled in the art will readily appreciate that the present invention can be applied to any type or type of combustor for a turbomachinery and not are limited to combustion chambers or combustion systems for land-based power generating gas turbines, unless it is specifically mentioned in the claims.
    Referring now to the drawings, wherein like reference numerals identify the same elements throughout the drawings, FIG. 1 is a functional block diagram of an exemplary gas turbine engine 10 that may incorporate various embodiments of the present invention. As shown, the gas turbine engine 10 generally includes an inlet section 12 that may include a number of filters, cooling coils, moisture separators, and / or other devices to clean and otherwise condition air 14 or other working fluids flowing into the gas turbine engine 10. The air 14 flows to a compressor section where a compressor 16 progressively transfers kinetic energy to the air to produce compressed air 18.
    The compressed air 18 is mixed with a fuel 20 from a fuel supply 22 to form a combustible mixture within one or more chambers 24. The combustible mixture is burned to produce combustion gases 26 having a high temperature, a high pressure and a high speed. The combustion gases 26 pass through a turbine 28 of the turbine section to perform work. The turbine 28 may e.g. be connected to a shaft 30 so that the rotation of the turbine 28 drives the compressor 16 to produce compressed air 18. Alternatively or additionally, the shaft 30 may connect the turbine 28 to a generator 32 for generating electricity. Exhaust gases 34 from the turbine 28 flow through an exhaust section 36 that connects the turbine 28 to an exhaust stack 38 downstream of the turbine 28. The exhaust section 36 may include, for example, a heat recovery steam generator (not shown) for purifying and extracting additional heat from the exhaust gases 34 prior to release to the environment.
    The combustor 24 may be a combustor of any type known in the art, and the present invention is not limited to any particular combustor design unless specifically stated in the claims. The combustion chamber 24 may be, for example, a tubular or an annular combustion chamber. FIG. 2 provides a side perspective view of a portion of an exemplary combustor 24 as may be included in the gas turbine engine 10 shown in FIG. 1 and how it may include one or more embodiments of the present invention.
    In an exemplary embodiment, as shown in Fig. 2, the combustion chamber 24 is at least partially surrounded by an outer housing 40. The outer housing 40 communicates with a source of compressed air, such as air. the compressor 16 (Figure 1) in fluid communication. The combustor 24 may include one or more sockets 42, such as those shown in FIG. a combustion chamber flame tube and / or a transition duct included, which at least partially defines a combustion chamber 44 within the outer housing 40. The bushing (s) 42 may also partially define a hot gas path 46 for directing the combustion gases 26 into the turbine 28. In certain configurations, one or more outer sleeves 48, such as e.g. a flow sleeve or an impact sleeve, at least partially surrounding the bushing (s) 44. The outer sleeve (s) 48 is radially spaced from the bushing (s) 42 to define an annular flow path 50 for directing a portion of the compressed air 18 toward a head end portion 52 of the combustion chamber. The head end portion 52 may be at least partially defined by an end cover 54 fixedly connected to the outer housing 40. In various embodiments, the combustor 24 includes a plurality of fuel nozzle assemblies 56 disposed within or encased within the outer housing 40.
    FIG. 3 shows a side perspective view of a portion of an exemplary combustor 24 as may include one or more embodiments of the present invention. As shown in FIG. 3, the fuel nozzle assemblies 56 may be annularly disposed about a common axial centerline 58 and / or central fuel nozzle assembly 60 that is substantially coaxially aligned with the centerline 58. In various embodiments, each fuel nozzle assembly 56 is connected at one end to the end cover 54. The fuel nozzle assemblies 56, 60 may be in fluid communication with the fuel source 22 (FIG. 2) via the end cover 54 and / or a fluid coupling (not shown).
    FIG. 4 shows a cross-sectional side view of an exemplary premix fuel nozzle assembly 100 as may be installed in the combustor 24 shown in FIG. 3, in accordance with one or more embodiments of the present invention. The premix fuel nozzle assembly 100 may be representative of any one or all of the fuel nozzle assemblies 56, 60 shown in FIGS. 2 and 3, and is not limited to any particular location or position along the end cover 54 or within the combustor 24, as shown in FIGS Claims not otherwise specified. The premix fuel nozzle assembly 100 is a "dual fuel" type premix fuel nozzle; as a result, the premix fuel nozzle assembly 100 as provided herein is a type of premix fuel nozzle that may be configured or modified to combust either a gaseous or a liquid fuel or to operate with either a gaseous or liquid fuel.
    As shown in Fig. 4, the premix fuel nozzle assembly 100 is substantially divided into two regions according to their functions. As shown in FIG. 4, premix fuel nozzle assembly 100 includes, in certain configurations, an inlet flow conditioner 102, a gas fuel injection air turbulizer assembly 104, and an annular fuel / air mixing passageway 106. As shown in FIG. 3, premix fuel nozzle assembly 100 includes, in various embodiments, a diffusion chamber. or pilot premix nozzle assembly 108. The pilot premix nozzle assembly 108 (FIG. 3) is mounted or deployed within a centerbody 110 (FIG. 4) of the premix fuel nozzle assembly 100. Although shown as part of the premix fuel nozzle assembly 100 in FIG. 4, the inlet conditioner 102 is not a necessary component of the premix fuel nozzle assembly 100 unless otherwise specified in the claims.
    As shown in FIG. 4, in certain embodiments, the annular fuel / air mixing passage 106 is substantially defined between an outer sleeve or burner tube 112 and the centerbody 110. The swirler assembly 104 includes swirler vanes 114 located between the centerbody 110 and an outer sleeve 116, such as an outer sleeve 116. the burner tube 112, extend. The centerbody 110 and the outer sleeve 116 define therebetween an annular passage 118 upstream of the annular fuel-air mixing passage 106. In certain configurations, one or more fuel injection ports 120 are formed along each turbulizer blade 114. The fuel injection ports 120 provide fluid communication between one or more fuel circuits 122 formed within the centerbody 110 and the annular passage 118. The centerbody 110 is at least partially defined by one or more annular sleeves 124. Each sleeve 124 includes an inner surface or surface 126 that is radially separated from an outer surface or surface 128.
    In operation, a portion of the compressed air 18 flows into the swirler assembly 104 of the premix fuel nozzle assembly 100 via the inlet flow conditioner 102 (if present). The swirler vanes 114 impart a twist to the compressed air 18 as it passes through the annular passage 118. A gaseous fuel, such as e.g. Natural gas is injected into the compressed air 18 via the injection ports 120. The gaseous fuel begins to mix with the compressed air 18 in the swirler assembly 104, and the fuel-air mixture is sealed in the annular passage 106. After the fuel-air mixture 62 flows out of the annular passage 106, it flows into the combustion chamber 44 or the reaction zone, where the combustion takes place.
    FIG. 5 shows a side perspective view of an exemplary pilot premix fuel nozzle assembly 200 as shown in FIG. 4 and as may be included in the combustor 24 shown in FIG. 3, in accordance with one or more embodiments of the present invention , 6 shows an enlarged cross-sectional side view of a downstream portion 202 of an exemplary pilot premix fuel nozzle assembly 200, as shown in FIG. 5, in accordance with one or more embodiments of the present invention. The exemplary pilot premix fuel nozzle assembly 200 may be representative of any or all of the pilot premix fuel nozzle assemblies 108 shown in FIG. 3 and is not limited to any particular premix fuel nozzle assembly 100 unless otherwise specified in the claims.
    In various embodiments, as shown in FIG. 5, the pilot premix fuel nozzle assembly 200 includes an annular shaft 204. A first or upstream end portion 206 of the shaft 204 is configured to engage with an opening of the end cover 54 (FIG. 3). to be connected and / or inserted within an opening of the end cover 54. The stem 204 may be in fluid communication with a pilot premix air supply (not shown). As shown in FIG. 5, in one embodiment, one or more alignment or spacing features 208 are formed or disposed along an outer surface 210 of the shaft 204. The alignment features 208 may be clocked or spaced along the circumference about the outer surface 210 of the shaft 204.
    As shown in Fig. 6, the downstream portion 202 is coupled or connected to a downstream end portion 212 of the shaft 204. As shown in FIG. 6, in one embodiment, the downstream portion 202 is coupled or connected to the downstream end portion 212 via a coupling collar 214. In one embodiment, one or more alignment or spacing features 216 are formed or disposed along an outer surface 218 of the coupling collar 214. The alignment features 216 may be clocked or spaced circumferentially around the outer surface 218 of the coupling collar 214.
    In various embodiments, the pilot premix fuel nozzle assembly 200 includes an annular bellows 220 coupled to an end of the downstream end portion 212 of the shaft 204 and / or to the coupling collar 214 and to an axial expansion end collar 222 at an axially opposite end. In certain embodiments, the stem 204, the coupling collar 214, the bellows 220, and the flow expansion collar 222 may be concentrically aligned with respect to an axial centerline 224 of the pilot premix fuel nozzle assembly 200.
    As shown in FIGS. 5 and 6, in various embodiments, the pilot premix fuel nozzle assembly 200 includes a premix tip 226 that extends axially downstream from the flow extension collar 222 with respect to the centerline 224. In certain embodiments, the premix tip 226 is concentrically aligned with one or more of the stem 204, the coupling collar 214, the bellows 220, and the flow extension collar 222 with respect to the centerline 224. The flow extension collar 222 extends axially between the bellows 220 and the premix tip 226. Each of the shaft 204, coupling collar 214, bellows 220, flow extension collar 222, and premix tip 226 at least partially define a pilot air passage 228 through the pilot premix fuel nozzle assembly 200 ,
    The pilot premix fuel nozzle assembly 200 includes, in certain embodiments, an annular sleeve or sleeve 230 surrounding the bellows 220 along the circumference. In one embodiment, the sleeve 230 engages the shaft 204 or coupling collar 214 at a first end 232 and engages the flow expansion collar 222 at a second end 234, thereby forming a plenum or cavity 236 between the bellows 220 and the sleeve 230 becomes. The bushing 230 may be fixedly engaged at the first or second end 232, 234 with the shaft 204, the coupling collar 214, or the flow extension collar 222, or may be slidably engaged.
    In one embodiment, sleeve 230 is fixedly engaged with shaft 204 or coupling collar 214 at first end 232 and slidably engaged with extension collar 222 at second end 234, thereby providing thermal expansion between shaft 204 and / or. or the coupling collar 214 and the premixing tip 226. In one embodiment, the sleeve 230 slidably engages the shaft 204 or coupling collar 214 at the first end 232 and firmly engages the extension collar 222 at a second end 234, thereby providing thermal expansion between the shaft 204 and / or the coupling collar 214 and premix tip 226. In one embodiment, the sleeve 230 is fixedly engaged on the first end 232 with shank 204 or coupling collar 214 and is fixedly engaged on the second end 234 with the extension collar 222, whereby the plenum or cavity 236 between the bellows 220 and the sleeve 230 is at least partially engaged is sealed.
    In various embodiments, as shown in FIGS. 5 and 6, premix tip 226 includes a plurality of premix tubes 238 annularly disposed on or about an outer surface 240 (FIG. 5) of premix tip 226. Each tube extends radially outwardly from the outer surface 240 (FIG. 5) of the premix tip 226. In certain embodiments, as shown in FIGS. 5 and 6, the premix tubes 238 extend axially with respect to a centerline 224 between the flow extension collar 222 and a fuel distribution disc or wall 242 of the premix tip 226. In certain embodiments, the outer surface 240 and / or the premix tubes are 238 of the premix tip 226 is radially inserted from a radially outer surface 244 of the flow extension collar 222 and / or a radially outer surface 246 of the fuel distribution disk 242. As shown in FIG. 5, in certain embodiments, a groove or groove 248 is formed or defined between each circumferentially adjacent premix tube 238.
    As shown in Figure 6, each premix tube 238 includes an inlet end 250 and an outlet end 252. In certain embodiments, each premix tube 238 defines a premix flow passage 254 through the premix tip 226. The inlet end 250 is in fluid communication with the pilot air passage 228. The outlet end 252 of each premix tube 238 provides fluid communication between the associated premix flow passage 254 and the combustion chamber or reaction zone 44 (Figure 2). In certain embodiments, each or each of at least some of the premix tubes 238 includes one or more fuel ports 256 that provide fluid communication into the associated premix passage 254.
    FIG. 7 shows a cross-sectional side view of the exemplary premix fuel nozzle assembly 100 with the pilot premix fuel nozzle assembly 200 as shown in FIGS. 5 and 6 deployed or secured within the centerbody 110, in accordance with one or more embodiments of the present invention. As shown in FIG. 7, the pilot premix fuel nozzle assembly 200 extends axially within the centerbody 110 with respect to the centerline 152 of the premix fuel nozzle assembly 100. In certain embodiments, the pilot premix fuel nozzle assembly 200 is concentric with the centerbody 110 with respect to the centerline 152. In certain embodiments, the pilot premix fuel nozzle assembly 200 may be fixedly connected at one end to the centerbody 110 at or near the fuel distribution disk 242 and may be unconnected or unfixed at the upstream end portion 206 of the stem 204, thereby providing thermal performance during operation of the combustor 24 Expansion, in particular an axial thermal expansion of the pilot premix fuel nozzle assembly 200 within the center body 110 via the bellows 220 is allowed.
    In various embodiments, a pilot fuel flow path 258, as shown in FIG. 7, is at least partially disposed between the inner surface (s) 126 of the sleeve (s) 124 of the centerbody 110 (FIG. 4) and at least a portion of FIG Pilot premix fuel nozzle assembly 200 defined. In one embodiment, a pilot fuel flowpath 258, as shown in FIG. 7, is between the inside or surface (s) 126 of the sleeve (s) 124 of the centerbody 110 and the stem 204, the coupling collar 214, the bellows 220 and / or the bellows bush 230 and the flow extension collar 222. In various embodiments, the pilot fuel flowpath 258 is defined radially inward of the one or more fuel circuits 122 formed within the centerbody 110 that provide or supply fuel to the fuel injection ports 120 formed within the swirler vanes 114. The pilot fuel flowpath 258 is generally supplied by an inlet passage 260 which provides fluid communication between the end cap 54 and / or a fuel source and the pilot fuel flow path 258.
    FIG. 8 shows an enlarged cross-sectional side view of a portion of premix fuel nozzle assembly 100 as shown in FIG. 7 including a portion of a pilot premix fuel nozzle assembly 200. In certain embodiments, a fuel plenum, as shown in FIGS. 7 and 8, is at least partially defined and / or formed between the inner surface 126 of the sleeve (s) 124 of the centerbody 110 and the premix tip 226. In certain embodiments, the fuel plenum 262 is at least partially defined or formed between the outer surfaces of the premix tubes 238 and / or the outer surface 240 (FIG. 5) of the premix tip 226 and the inner surface 126 of the sleeve (s) 124. The fuel plenum 262 is in fluid communication with the pilot fuel flowpath 258. In various embodiments, fuel ports 256 define a flow path between fuel plenum 262 and premix passages 254 of each associated premix tube 238. In certain embodiments, pilot fuel flowpath 258 provides a continuous fuel flow path between end cap 54 (FIG Combustion chamber 24.
    FIG. 9 shows a cross-sectional perspective side view of premix fuel nozzle assembly 100 as shown in FIGS. 3 and 7 according to various embodiments of the present invention. In certain embodiments, as shown in FIG. 9, the premix fuel nozzle assembly 100 includes a purge air cartridge assembly 300 for converting or modifying the premix fuel nozzle assembly 100 from a dual fuel premix fuel nozzle assembly 100 to a gas-only or gas-only configuration. The purge air cartridge assembly 300 extends generally axially with respect to the centerline 152. In certain embodiments, the purge air cartridge assembly 300 is concentrically disposed with the pilot premix fuel nozzle assembly 200 and / or the centerbody 110 with respect to the centerline 152. The purge air cartridge assembly 300 extends axially within the pilot air passage 228 through the shaft 204, coupling collar 214, bellows 220, flow extension collar 222, and premix tip 226, and at least partially through an opening 264 (Figs. 8 and 9) shown in Figs Fuel distribution disc 242 is defined or formed.
    The purge air cartridge assembly 300 generally includes a feed tube portion 302 and a tip portion 304. In certain embodiments, the feed tube portion 302 extends through an opening defined in the end cap 54. The purge air cartridge assembly 300, particularly the feed tube portion 302, is in fluid communication with the purge air supply (not shown). The purge air cartridge assembly 300 may be coupled or connected to the end cover 54 via bolts or other suitable attachment means (not shown). The feed tube portion 302 and the tip portion 304 generally define a purge air passage 308 through the purge air cartridge assembly 300. The purge air cartridge assembly 300 may be loaded from behind through the end cover 54. In various embodiments, the pilot air passage 228 is at least partially defined between an outer surface 306 of the purge air cartridge assembly 300 and the stem 204, the coupling collar 214, the bellows 220, the flow extension collar 222, and the premix tip 226 of the pilot premix fuel nozzle assembly 200.
    10 shows an enlarged perspective cross-sectional view of a portion of premix fuel nozzle assembly 100 that includes a portion of centerbody 110, premix tip 226 of pilot premix fuel nozzle assembly 200, and tip portion 304 of air cartridge assembly 300 according to at least one embodiment of the present invention. In various embodiments, the tip section 304 of the air cartridge assembly 300 includes a rear wall 310 as shown in FIG. 10. The rear wall 310 extends at or adjacent to a downstream end 314 of the tip section 304 radially and circumferentially with respect to an axial centerline 312 of the air cartridge assembly 300. A single opening 316 is formed through the rear wall 310. In one embodiment, the opening 316 is formed through the rear wall 310 concentric with the centerline 312. The opening 316 extends through the front face 318 and a rear side 320 of the rear wall 310 and provides fluid communication from the purging air passage 308 through the rear wall 310.
    11 shows an enlarged perspective cross-sectional side view of the tip section 304 of the air cartridge assembly 300 as shown in FIG. 10, according to at least one embodiment of the present invention. As shown in FIGS. 10 and 11, the air cartridge assembly 300 may include a baffle plate or impact insert 322. The baffle 322 extends radially and circumferentially with respect to the centerline 312 within the tip section 304 upstream of the inner side 318 of the rear wall 310. The baffle 322 is axially spaced from the inner side 316 of the rear wall 310 to define an impact collection space 324 therebetween. The baffle 322 includes a plurality of baffle holes 326 extending through an upstream side 328 and a downstream side 330 of the baffle 322. The baffle holes 326 provide fluid communication from the purging air passage 308 through the baffle plate 322 and into the crash collection space 324. The baffle holes 326 are substantially aligned and / or configured to direct a flow of purging air or air 332 from the purge media supply and purging air passage 308 against the front face 318 of the rear wall 310, thereby causing an impact during operation of the combustor 24 - or jet cooling of the rear wall 310 is achieved.
    As shown in FIG. 10, a radial gap or cavity 334 may be defined or formed between the tip portion 304 of the cartridge assembly 300 near the rear wall 310 and the opening 201 defined or formed in the fuel distribution disk 242. The cavity 334 may cause or result in the formation of a recirculation zone on the rear wall 310.
    Fig. 12 shows a perspective view of the tip portion 304 of the air cartridge assembly 300 as shown in Figs. 9-11, according to an embodiment of the present invention. In one embodiment, as shown in FIG. 12, multiple scavenging passages 336 are defined along the chamfered, chamfered or diverging sidewall portion 338 of the back wall 310. The purging passages 336 are aligned or adapted to allow a portion of the purging air 332 to flow radially outwardly from the impingement collection space 324 and / or purging air passage 308 and into the collection space 334 (FIG. 11) in a circumferential or tangential direction Operation of the combustion chamber 24, the formation of the recirculation zone is prevented.
    Fig. 13 shows a cross-sectional side view of premix fuel nozzle assembly 100 having various flow paths for fuel and purge medium, such as e.g. compressed air, through the premix fuel nozzle assembly 100, according to one or more embodiments of the present invention. During a pilot premix operation of the combustor 24, as shown and described in FIG. 13 and in various figures created herein, a gaseous fuel 400 is directed through an inlet passage 260 and into the pilot fuel flowpath 258. In certain embodiments, the alignment or spacing features 208, 216 maintain a desired radial gap between the pilot premix fuel nozzle assembly 200 and the inner surfaces 126 of the sleeve (s) 124 of the centerbody 110, thereby ensuring proper fuel flow of the gaseous fuel through the pilot fuel flowpath 258 is ensured.
    The gaseous fuel 400 enters the fuel collection chamber 262 and flows or circulates around the outer surface 240 of the premix tip 226 and / or within the grooves 248 formed or defined between all circumferentially adjacent premix tubes 238. The gaseous fuel 400 may achieve convection and / or conduction cooling of the premix tip 226 and / or the fuel distribution disk 242. The gaseous fuel 400 is then injected into the premix passage 254 of each premix tube 238 via the fuel port 256 and the fuel ports 256, respectively.
    At the same time, the pilot premix air 402 is directed through the pilot air passage 228. Pilot premix air 402 flows through shaft 204, coupling collar 214, and bellows 220 and into flow-through collar 222. A portion of the pilot premix air 402 flows through the inlet end 250 of each premix tube 238 and flows into the associated premix passage 254 upstream of the fuel port (s) 256. The gaseous fuel 400 and the pilot premix air 402 form a premix pilot fuel-air mixture 404 as they pass through the premix passage (s) 254 and exit through the respective outlet ends 252 of each premix tube 238. The premix pilot fuel-air mixture 404 flows into the combustion chamber 44 and / or a reaction zone 406 where the premix pilot fuel-air mixture 404 is burned as a pilot premix flame 408.
    In certain embodiments, a rinsing or cooling agent 410, such as e.g. compressed air, passed into the scavenging air passage 308 inside. In one or more embodiments, the purging medium 410 flows through the impingement passages 326 and impacts or impinges on the front face 318 of the back wall 310, thereby providing impact or jet cooling to the back wall 310. The purge medium 410 passes through the axially extending port 316 and enters the reaction zone 406 concentric with the pilot-operated premix flame 408. In one embodiment, a portion (i.e., less than 20 percent) of the purging medium 410 may be directed through the purging passages 336 to rinse the radial gap 334.
    FIG. 14 shows a perspective view of the spatial relationship between the purging medium 410 flowing through the axially extending port 316 and the pilot-operated premix flame 408 within the reaction zone 406. The axial flow direction of the purging medium 410 into the pilot-operated premix flame 408 reaction zone 406 increases premix pilot flame stability, which may result in extinction of piloted premix flame 408, as compared to conventional all-gas cartridges that generally allow the sweep medium to flow radially outward. Extinguishing the piloted premix flame 408 generally results in less than desirable or non-optimal interaction between the pilot flame and the cartridge purge air, less than optimal reaction rates at the pilot flame, thus affecting emissions performance and lower than optimal temperatures that the pilot flames surrounded, resulting in lower than optimal kinetic reaction rates can result.
    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 the manufacture and use of any devices and systems and the practice of any included method. The patentable scope of the invention is defined by the claims and may include other embodiments that will become apparent to those skilled in the art. Such other embodiments 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 languages of the claims.
    A premix fuel nozzle assembly includes a central body including a sleeve having an inner surface and a pilot premix fuel nozzle assembly extending axially through the central body within the sleeve and defining a pilot air passage within the central body. The pilot premix fuel nozzle assembly includes a premix tip having a plurality of premix tubes defining premix passages in fluid communication with the pilot air passage. At least one of the premix tubes contains a fuel port. The premix fuel nozzle assembly further includes a pilot fuel flow path defined radially between the pilot premix fuel nozzle assembly and the inner surface of the sleeve and a fuel plenum defined at least partially between the inner sleeve surface and an outer surface of the premix tip. The fuel ports provide fluid communication between the fuel plenum and the premix passages.
    LIST OF REFERENCE NUMBERS
    [0065]<Tb> 10 <September> Gas Turbine<Tb> 12 <September> inlet section<Tb> 14 <September> working fluid<Tb> 16 <September> compressor<tb> 18 <SEP> Compressed working fluid<Tb> 20 <September> Fuel<Tb> 22 <September> fuel source<Tb> 24 <September> combustion chamber<Tb> 26 <September> combustion gases<Tb> 28 <September> Turbine<Tb> 30 <September> wave<Tb> 32 <September> generator / motor<Tb> 34 <September> exhaust<Tb> 36 <September> exhaust section<Tb> 38 <September> exhaust stack<Tb> 40 <September> outer housing<Tb> 42 <September> high-pressure accumulator<Tb> 44 <September> end cover<Tb> 46 <September> fuel<Tb> 48 <September> lining<tb> 50 <SEP> downstream end<Tb> 52 <September> combustion chamber<Tb> 54 <September> hot gas path<Tb> 56 <September> tube / pipe<tb> 58 <SEP> Upstream End Section<tb> 60 <SEP> downstream end / tip section<Tb> 62 <September> fuel ports<Tb> 64 <September> swirler<Tb> 66 <September> fuel cartridges passage<tb> 67-99 <SEP> NOT USED<Tb> <September><tb> 100 <SEP> premix burner fabric nozzle assembly<Tb> 102 <September> inlet flow<Tb> 104 <September> swirler<Tb> 106 <September> fuel-air mixing passage<Tb> 108 <September> Pilotvormischdüsenanordnung<Tb> 110 <September> Central Body<Tb> 112 <September> burner tube<Tb> 114 <September> Verwirblerschaufel<Tb> 116 <September> outer sleeve<tb> 118 <SEP> Annular passage<Tb> 120 <September> fuel injection port<Tb> 122 <September> fuel cycle<Tb> 124 <September> Barrel<Tb> 126 <September> inside / Area<Tb> 128 <September> outside / Area<tb> 129-199 <SEP> NOT USED<Tb> <September><Tb> 200 <September> Pilotvormischbrennstoffdüsenanordnung<tb> 202 <SEP> Downstream section<Tb> 204 <September> End<tb> 206 <SEP> End section (shaft)<Tb> 208 <September> distance / alignment feature<tb> 210 <SEP> Outer surface (shaft)<tb> 212 <SEP> Downstream End Section (Shaft)<Tb> 214 <September> coupling collar<Tb> 216 <September> distance / alignment feature<tb> 218 <SEP> Outer surface (coupling collar)<Tb> 220 <September> bellows<Tb> 222 <September> Flow extension collar<tb> 224 <SEP> Axial Center Line (pilot premix nozzle)<Tb> 226 <September> Vormischspitze<Tb> 228 <September> pilot air passage<tb> 230 <SEP> Sleeve / Bushing (Bellows)<tb> 232 <SEP> First end (female)<tb> 234 <SEP> Second End (Socket)<Tb> 236 <September> collection chamber / cavity<Tb> 238 <September> premix<tb> 240 <SEP> Outer surface (premix tip)<Tb> 242 <September> fuel distribution disc<tb> 244 <SEP> Outer surface (flow extension collar)<tb> 246 <SEP> Outer surface (fuel distribution disk)<Tb> 248 <September> throat / groove<tb> 250 <SEP> inlet end (premix tube)<tb> 252 <SEP> outlet end (premix tube)<Tb> 254 <September> premixing<Tb> 256 <September> fuel port<Tb> 258 <September> pilot fuel flow path<Tb> 260 <September> inlet passage<Tb> 262 <September> fuel plenum<tb> 264 <SEP> opening (for cartridge)<tb> 265-299 <SEP> NOT USED<Tb> <September><Tb> 300 <September> Spülluftkartuschenanordnung<Tb> 302 <September> Zuführrohrabschnitt<Tb> 304 <September> tip portion<tb> 306 <SEP> Outer surface (purge air cartridge assembly)<Tb> 308 <September> Spülluftdurchgang<Tb> 310 <September> rear wall<Tb> 312 <September> centerline<tb> 314 <SEP> Downstream End (Top Section)<tb> 316 <SEP> Axial opening<tb> 318 <SEP> Front (back wall)<tb> 320 <SEP> Rear (back wall)<Tb> 322 <September> Flapper<Tb> 324 <September> impact plenum<Tb> 326 <September> impingement hole<tb> 328 <SEP> Upstream page<tb> 330 <SEP> Downstream page<Tb> 332 <September> impact media / air<tb> 334 <SEP> Radial gap / cavity<Tb> 336 <September> wash cycle<tb> 338 <SEP> beveled / beveled / diverging sidewall<tb> 339-399 <SEP> NOT USED<Tb> <September><tb> 400 <SEP> Gaseous fuel<Tb> 402 <September> Pilotvormischluft<Tb> 404 <September> Pilotvormisch fuel-air mixture<Tb> 406 <September> reaction zone<Tb> 408 <September> Pilotvormischflamme<Tb> 410 <September> flushing / cooling medium<tb> 411-499 <SEP> NOT USED
    权利要求:
    Claims (10)
    [1]
    A premix fuel nozzle assembly comprising:a central body at least partially defined by a sleeve having an inner surface;a pilot premix fuel nozzle assembly extending axially through the central body within the sleeve and defining a pilot air passage within the centerbody, the pilot premix fuel nozzle assembly including a premix tip with multiple premix tubes, each premix tube defining a premix passage and a fuel port, the premix passage communicating with the pilot air passage Fluid connection is;a pilot fuel flow path defined radially between the pilot premix fuel nozzle assembly and the inner surface of the sleeve of the centerbody; anda fuel plenum defined at least partially between the sleeve inner surface and an outer surface of the premix tip, the fuel ports providing fluid communication between the fuel plenum and the premix passages.
    [2]
    2. The premix fuel nozzle assembly of claim 1, wherein the pilot fuel flow path extends axially between an inlet passage and the fuel plenum.
    [3]
    A premix fuel nozzle assembly according to claim 1 or 2, wherein the premix fuel nozzle is a dual fuel premix fuel nozzle.
    [4]
    4. The premix fuel nozzle assembly of claim 1, wherein the pilot premix fuel nozzle assembly includes a stem, a coupling collar, a bellows, and a flow extension collar connected in series upstream of the premix tip.
    [5]
    5. The premix fuel nozzle assembly according to claim 4, further comprising a bushing surrounding the bellows along the circumference; wherein the bellows and the bushing preferably at least partially define a plenum therebetween.
    [6]
    The premix fuel nozzle assembly of any of the preceding claims, wherein the plurality of premix tubes are annularly disposed about the outer surface of the premix tip within the fuel plenum.
    [7]
    7. The premix fuel nozzle assembly of claim 1, wherein each premix tube of the plurality of premix tubes extends radially outwardly from the outer surface of the premix tip within the fuel plenum.
    [8]
    8. The premix fuel nozzle assembly of claim 1, wherein the pilot premix fuel nozzle assembly includes one or more radial distance features extending radially outward from one or more outer surfaces of the pilot premix fuel nozzle assembly within the premix fuel flow path.
    [9]
    9. combustion chamber comprising:an end cover;a plurality of premix fuel assemblies annularly disposed about a central fuel nozzle, each premix fuel nozzle assembly of the plurality of premix fuel nozzle assemblies and the central fuel nozzle fixedly connected to the end cover, each of the premix fuel nozzle assemblies being a dual fuel premix fuel nozzle assembly, each premix fuel nozzle assembly comprising;a central body at least partially defined by a sleeve having an inner surface;a pilot premix fuel nozzle assembly extending axially through the central body within the sleeve and defining a pilot air passage within the centerbody, the pilot premix fuel nozzle assembly including a premix tip with multiple premix tubes, each premix tube having an inlet end and an outlet end and a premix passage defined therebetween, wherein each premix tube a fuel port, wherein the inlet end of the premix tube is in fluid communication with the pilot air passage;a pilot fuel flow path defined radially between the pilot premix fuel nozzle assembly and the inner surface of the sleeve of the centerbody; anda fuel plenum defined at least partially between the sleeve inner surface and an outer surface of the premix tip, the fuel ports providing fluid communication between the fuel plenum and the premix passages.
    [10]
    10. A combustion chamber according to claim 9, wherein the combustion chamber is a component of a gas turbine; and orwherein the outlet ends of the premix tubes of the plurality of premix tubes are annularly arranged around a fuel distribution disc portion of the premix tip.
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    同族专利:
    公开号 | 公开日
    CH710425B1|2020-01-15|
    JP6849306B2|2021-03-24|
    US20160146459A1|2016-05-26|
    JP2016099107A|2016-05-30|
    DE102015119749A1|2016-06-02|
    US10030869B2|2018-07-24|
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    法律状态:
    2017-03-15| NV| New agent|Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH |
    2019-05-31| NV| New agent|Representative=s name: FREIGUTPARTNERS IP LAW FIRM DR. ROLF DITTMANN, CH |
    优先权:
    申请号 | 申请日 | 专利标题
    US14/555,074|US10030869B2|2014-11-26|2014-11-26|Premix fuel nozzle assembly|
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