• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    A system for utilizing cooling air (200) from a burner (24) includes a fuel nozzle having an axially extending central body, a burner tube circumferentially surrounding at least a portion of the central body, and a premixing channel (60) interposed between the central body and the burner tube is defined. The system further includes a burner cap assembly having a first cooling air plenum (124) formed between a cap plate (104) and a first partition plate (108), a second cooling air plenum (124) located upstream of the first cooling air plenum (124) between a second cooling air plenum (124) Partition plate and the first partition plate (108) is formed, and a tube (134) which provides a flow connection of the first cooling air collecting space (124), through the second cooling air collecting space and through the second partition plate.
    公开号:CH710574A2
    申请号:CH01846/15
    申请日:2015-12-16
    公开日:2016-06-30
    发明作者:Ashley Antoniono Carolyn；Han Chong Yon
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    FIELD OF THE INVENTION
    The invention generally relates to a burner for a gas turbine. More particularly, the invention relates to a system and method for utilizing cooling air in the burner.
    BACKGROUND OF THE INVENTION
    In an air-handling turbomachine (e.g., a gas turbine), air enters a compressor and is progressively compressed as it is directed toward a burner. The compressed air is premixed with a fuel and ignited in a reaction zone defined in the burner, so that hot combustion gases are formed. The combustion gases are then directed from the combustion chamber via a flame tube and / or a transition piece into a turbine section of the turbomachine where the combustion gases flow over alternating rows of stationary vanes and blades secured to a rotor shaft. As the combustion gases flow over the blades, kinetic and / or thermal energy is transferred to the blades so that the rotor shaft is rotated.
    In order to increase the turbine efficiency, modern burners are operated at high temperatures, which generate high thermal stresses on different mechanical components disposed in the burner. As a result, at least a portion of the compressed air supplied to the burner is used as cooling air to cool these components. For example, specific burners include a generally annular burner cap assembly that at least partially surrounds one or more fuel nozzles in the burner. Certain designs of burner cap assemblies include a cap plate disposed at a downstream end of the burner cap assembly. The fuel nozzles extend at least partially through the cap plate, which is usually disposed substantially adjacent to the combustion chamber. As a result, the cap plate is usually exposed to extremely high temperatures.
    One way to cool the cap plate is based on branching a portion of the compressed air as cooling air in the burner cap assembly and on an upstream side of the cap plate. The cooling air is then branched through a plurality of cooling or effusion openings which extend through the cap plate. The cooling air flows from the effusion ports into the reaction zone defined in the burner. This process is known in the industry as effusion cooling. However, the cooling air passing through the multiple cooling holes enters the reaction zone unmixed with the fuel and at a temperature substantially lower than the combustion flame temperatures. As a result, the generation of NOx and / or CO2 can be exacerbated and the overall efficiency of a turbine reduced. In addition, the cooling capacity of the cooling air is not fully optimized, with the result of a reduction in the cooling efficiency of the burner. An improved system and method for utilizing cooling air in the burner cap assembly would therefore be advantageous.
    BRIEF SUMMARY OF THE INVENTION
    Features and advantages of the invention are set forth below in the following description, or may be obvious from the description, or may be learned by practice of the invention.
    An embodiment of the present invention shows a system for utilizing cooling air in a burner. The system includes a fuel nozzle having an axially extending central body, a burner tube circumferentially surrounding at least a portion of the central body, and a premixing channel formed between the central body and the burner tube. The system further includes a burner cap assembly having a first cooling air plenum formed between a cap plate and a first partition plate, a second cooling air plenum formed upstream of the first cooling air plenum between a second partition plate and the first partition plate, and a tube having a second cooling air plenum provides fluid communication from the first cooling air plenum, through the second cooling air plenum and through the second splitting plate. The fuel nozzle extends axially in the burner cap assembly.
    The tube may provide a flow connection between the first cooling air plenum and the premixing channel.
    The fuel nozzle of each system mentioned above may include a scavenging air passage axially extending in the central body, the pipe providing a flow communication between the first cooling air plenum and the scavenging air passage.
    The tube of each system mentioned above may extend through the second cooling air plenum, which is substantially parallel to the fuel nozzle.
    At least part of the pipe in the second cooling air collecting space of each of the above-mentioned systems may be curved.
    The tube of each of the above-mentioned systems can isolate an outlet cooling air originating from the first cooling air collecting space in terms of flow from the second cooling air collecting space.
    The burner cap assembly of each of the above-mentioned systems may further include an outer support collar extending radially outwardly from an enclosure of the burner cap assembly, the outer support collar having a plurality of axially extending through holes adapted to provide compressed air passing therethrough through and toward a header portion of the burner.
    Another embodiment of the present invention is a burner. The burner contains an end cover, which is connected to an outer housing. The end cover and the outer housing form a high-pressure chamber and a head end of the burner. Further, the burner includes a fuel nozzle that extends axially downstream of the end cover and is in fluid communication with the head end. The fuel nozzle includes an axially extending central body, a burner tube circumferentially surrounding at least a portion of the central body, a premixing channel formed between the central body and the burner tube, and a purge air channel formed in the central body. The burner further includes a burner cap assembly surrounding at least a portion of the fuel nozzle circumferentially. The burner cap assembly includes a first cooling air plenum defined between a cap plate and a first splitting plate, a second cooling air plenum defined upstream of the first cooling air plenum between a second splitting plate and the first splitting plate, and a tube. The tube provides fluid communication from and / or out of the first cooling air plenum, through the second cooling air plenum and through the second splitting plate.
    The tube of the burner may provide a flow communication between the first cooling air plenum and the premixing channel.
    The tube of each burner mentioned above can provide a flow connection between the first cooling air collecting space and the scavenging air duct.
    The tube of each system mentioned above may extend through the second cooling air plenum, which is substantially parallel to the fuel nozzle.
    At least part of the pipe in the second cooling air collecting space of each of the above-mentioned systems may be curved.
    An outlet of the tube of each of the above-mentioned systems may be formed in proximity to at least one of a radial opening of the burner tube, an inlet to the premixing channel and an opening formed in the central body.
    The second cooling air plenum of each of the above-mentioned systems may be in fluid communication with the high pressure chamber, wherein the pipe isolates outlet cooling air from the first cooling air plenum fluidly from cooling air in the second cooling air plenum.
    Further, the burner cap assembly of each system mentioned above may include an outer support collar that extends radially outwardly from a shroud of the burner cap assembly toward the outer housing, the outer support sleeve having a plurality of axially extending through-holes.
    Another embodiment of the present invention includes a method of utilizing cooling air in a combustor, for example in a gas turbine combustor. The method includes directing cooling air from an annular flow passage defined in the combustor into a second cooling air plenum of a burner cap assembly. The annular flow channel is in fluid communication with a high pressure chamber. The method further includes directing the cooling air through a first divider plate and into a first cooling air plenum of the burner cap assembly such that the cooling air flows against a cold side of a cap plate of the burner cap assembly to cool it. The method further includes branching out exhaust cooling air from the first cooling air plenum to a header portion of the burner via a pipe. The tube extends from an opening formed in the first partition plate through the second cooling air plenum and through a second partition plate at least partially forming the second cooling air plenum.
    The method may further include directing the outlet cooling air into a scavenge air passage formed in a central body of a fuel nozzle that extends axially through the burner cap assembly.
    Further, each of the above-mentioned methods may include directing the outlet cooling air into a premixing channel defined by a fuel nozzle extending axially through the burner cap assembly.
    Each of the above-mentioned methods may further comprise directing compressed air into the head end via the annular flow channel and mixing the outlet cooling air with the compressed air.
    Each of the above-mentioned methods may further comprise fluidly isolating the outlet cooling air from the cooling air in the second cooling air plenum via the pipe.
    The person skilled in the art will understand the features and aspects of such and other embodiments after reading the description.
    BRIEF DESCRIPTION OF THE DRAWINGS
    A full and practicable description of the present invention, which includes the best mode for practicing the invention, will be more particularly described in the following description taken in conjunction with the accompanying drawings, in which:<Tb> FIG. 1 <SEP> illustrates a functional diagram of an exemplary gas turbine that may use at least one embodiment of the present invention;<Tb> FIG. 2 <SEP> is a cross-sectional side view of a portion of an exemplary combustor section of a gas turbine using an exemplary combustor, in accordance with one or more embodiments of the present invention;<Tb> FIG. FIG. 3 shows an enlarged cross-sectional perspective view of a portion of the burner as shown in FIG. 2, in accordance with one or more embodiments of the present invention; FIG.<Tb> FIG. 4 <SEP> illustrates in perspective view a portion of an exemplary burner cap assembly of the burner as shown in FIG. 3, according to one embodiment of the present invention;<Tb> FIG. 5 shows an enlarged cross-sectional perspective view of a portion of the burner as shown in FIG. 2, illustrating an operational flow diagram of the burner shown in FIG. 2, in accordance with one or more embodiments of the present invention; and<Tb> FIG. FIG. 6 shows a flowchart of an exemplary method of utilizing cooling air in the burner shown in FIG. 2, in accordance with one or more embodiments of the present invention.
    DETAILED DESCRIPTION OF THE INVENTION
    [0028] Reference will now be made in detail to the present embodiments of the invention, wherein one or more of the examples are illustrated in the accompanying drawings. The detailed description uses alphanumeric designations to refer to features in the figures. In the figures and in the description, similar or similar terms have been 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 not to define the location or meaning of the individual components.
    The terms "upstream" and "downstream" refer to the relative direction with respect to the fluid flow in a flow path. For example, "upstream" refers to the direction from which the fluid flows, and "downstream" refers to the direction in which the fluid flows. The term "radial" refers to the relative direction substantially perpendicular to and / or angular to an axial centerline of a particular component, and the term "axial" refers to the relative direction that is substantially parallel and / or coaxial aligned with an axial centerline of a particular component.
    All examples serve to illustrate the invention and are not intended to limit this. One skilled in the art will readily recognize that modifications and changes may be made to the present invention without departing from the scope or subject matter of the invention. For example, features that are illustrated or described as part of one embodiment may be applied to another embodiment to yield yet another embodiment. The present invention is therefore intended to cover such modifications and variations as fall within the scope of the appended claims and their equivalents. Although a burner for an industrial or land based gas turbine is shown and described herein, the present invention is not limited to a burner for a land-based and / or industrial gas turbine, unless otherwise specified in the claims. For example, the invention as described herein can be used in a burner for an aircraft gas turbine or marine gas turbine.
    Referring now to the drawings, wherein like elements are designated by like reference numerals, FIG. 1 shows a functional block diagram of an exemplary gas turbine engine 10 that may use different embodiments of the present invention. As shown, the gas turbine 10 generally includes an inlet section 12 that may include a series of filters, cooling coils, moisture separators, and / or other devices to clean a working fluid (eg, air) 14 entering the gas turbine engine 10 and to condition in any other way. The working fluid 14 flows to a compressor section where a compressor 16 progressively imparts kinetic energy 14 to the working fluid to produce compressed or pressurized air 18.
    The compressed air 18 is mixed with a fuel 20 from a fuel source 22, such as a fuel chute, to form an ignitable mixture in one or more burners 24. The ignitable mixture is burned to produce combustion gases 26 having high temperature, high pressure, and high velocity. The combustion gases 26 pass through a turbine 28 of a turbine section to perform work. For example, the turbine 28 may be connected to a shaft 30 such that rotation of the turbine 28 drives the compressor 16 to produce the compressed air 18. Alternatively, or in addition, the shaft 30 may connect the turbine 28 to a generator 32 to generate 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. For example, the outlet section 36 may include a heat recovery steam generator (not shown) for purifying the exhaust gases 34 and extracting additional heat from them before they are released into the environment.
    FIG. 2 shows a cross-sectional side view of a portion of an exemplary burner 24 in accordance with one or more embodiments of the present invention. As shown in FIG. 2, the burner 24 is at least partially surrounded by at least one outer housing 40, for example a compressor outlet housing. The outer housing 40 is in fluid communication with the compressor 16 (FIG. 1) to receive at least a portion of the compressed air 18 therefrom. In one construction, an end cover 42, as shown in FIG. 2, is connected to the outer housing 40. The outer housing 40 and / or the end cover 42 at least partially form a high-pressure chamber 44, which surrounds the burner 24 at least partially.
    At least one fuel nozzle 46 extends axially within the outer housing 40 with respect to an axial centerline of the combustor 24. In specific constructions, the combustor 24 may include a plurality of fuel nozzles 46 extending in the outer housing 40 in the axial direction. The fuel nozzle 46 may be connected to the end cover 42 at a first end. One or more flame tubes 48, such as a combustor wall or transition duct, extend downstream of the fuel nozzle 46 and may at least partially define a combustion reaction zone or chamber 50 within the outer housing 40. In addition, the flame tube 48 may at least partially define an annular flow channel 52 in the outer housing 40. In particular embodiments, the annular flow passage 52 may be further defined by the outer housing 40, the end cover 42, and / or other flame tubes or features formed in the outer housing 40. The annular flow passage 52 defines a fluid flow path for branching at least a portion of the compressed air 18 from the high pressure accumulator 44 and / or from the compressor 16 (FIG. 1) toward a header portion 54 of the end cover 42.
    In particular embodiments, the fuel nozzle 46 includes an outer sleeve or burner tube 56. The burner tube 56 circumferentially surrounds at least a portion of a central body or nozzle 58 to at least partially form an annular or premixing channel 60 therebetween. The burner tube 56 has an inlet 62 to the premixing channel 60 which is defined near the end cap 40 and is in fluid communication with the head end 54. The premix channel 60 is in fluid communication with the head end 54. In particular embodiments, the burner tube 56 includes and / or defines at least one radial opening 64. The radial opening 64 provides fluid communication through the burner tube 56 and into the annular flow channel 60 formed between the central body 58 and the burner tube 56.
    In particular constructions, the fuel nozzle 46 has a plurality of swirl vanes 66 extending radially outward from the central body 58 toward the burner tube 56 in the premix passage 60. All or some of the swirl vanes 66 may include one or more fuel injection ports (not shown). In operation, the swirl vanes 66 impart an angular swirl to a premix or combustion subset 68 of the compressed air 18 as it flows over the swirl vanes 66 and through the annular flow passage 60 to pre-mix fuel and premix subset 68 of the compressed air 18 upstream of the combustion zone 50 to refine. The radial opening 64 may be disposed at any axial position along the burner tube 56. For example, the radial opening 64 may be formed upstream, proximate or downstream of the swirl vanes 66.
    In particular constructions, the central body 58 at least partially forms a purge channel 70 for branching compressed air through the central body 58 for purge, cool, and / or controlled combustion operation. In one embodiment, the central body 58 has at least one opening 72. The one or more openings 72 provide fluid communication through the central body 58 into the purge or pilot air channel 70. In one embodiment, the one or more openings 72 provide a fluid communication between at least the premix channel 60 and / or the head end 54 and the purge or pilot air channel 70.
    In various embodiments, at least a portion of the fuel nozzle (s) 46 extends axially through a burner cap assembly 100. The fuel nozzle (s) 46 and the burner cap assembly 100 may be singular or as a system with regard to utilizing cool air and / or compressed air Air may be provided in the burner 24. 3 shows an enlarged side cutaway view of the burner 24 shown in FIG. 2 in accordance with one or more embodiments of the present invention. As shown in FIG. 3, the burner cap assembly 100 extends radially, circumferentially, and axially within the outer housing 40. The burner cap assembly 100 includes at least one annular shroud 102 circumferentially surrounding at least a portion of the fuel nozzle 46. The sheath 102 may be a single or one-piece sheath or based on multiple sheaths joined together at or near their respective ends by bolts, welds, or any other mechanical fastener to form a single annular sheath. In specific embodiments, the sheath 102 at least partially defines the annular flow channel 52 in the outer housing 40.
    In particular embodiments, the burner cap assembly 100 includes an effusion or capping plate 104, a first splitting plate 106 and a second splitting plate 108. The capping plate 104 extends axially, radially and circumferentially with respect to an axial centerline 112 of the burner cap assembly 100 a rear end 110 of the burner cap assembly 100. In specific embodiments, the cap plate 104 is generally solid or continuous. In particular embodiments, the cap plate 104 may include a plurality of cooling / effusion ports or passageways 114. In particular embodiments, the cap plate 104 may at least partially form one or more fuel nozzle passages 116 formed therein to receive the fuel nozzle (s) 46.
    In particular embodiments, the first divider plate 106 extends axially, radially, and circumferentially within the shroud 102 upstream of the cap plate 104 with respect to the centerline 112. The first divider plate 106 is axially spaced from the cap plate 104 and extends substantially parallel to the cap plate 104. The first partition plate 106 and the cap plate 104 at least partially form a first cooling air plenum 118 therebetween.
    In an embodiment, the first divider plate 106 may include and / or define one or more impingement orifices 120 provided for flow communication through the first divider plate 106 and into the first cooling air plenum 118. In various embodiments, the first divider plate 106 at least partially forms one or more fuel nozzle passages 122 to receive the fuel nozzle (s) 46. In particular embodiments, the one or more fuel nozzle passages 122 are aligned concentrically with the one or more fuel nozzle passages 116 of the cap plate 104.
    In particular embodiments, the second divider plate 108 extends axially, radially and circumferentially within the shroud 102 upstream of the first divider plate 106 with respect to the centerline 112. The second divider plate 108 is axially spaced from the first divider plate in the vicinity of the first divider plate Inlet 62 of the burner tube 56 is arranged. In particular embodiments, second partition plate 108 is substantially parallel to first partition plate 106. Second partition plate 108 and first partition plate 106 at least partially define a second cooling air plenum 124 therebetween. In various embodiments, second splitter plate 108 at least partially defines one or more fuel nozzle passages 126 for receiving the fuel nozzle (s) 46. In particular embodiments, the one or more fuel nozzle passages 126 are aligned concentrically with the one or more fuel nozzle passages 116 of the cap plate 104 and / or the one or more fuel nozzle passages 122 of the first splitting plate 106.
    In particular constructions, the burner cap assembly 100 includes an outer support collar 128. FIG. 4 shows a cross-sectional perspective view of a portion of the burner cap assembly 100 that includes a portion of the enclosure 102, the cap plate 104, the first partition plate 106, and the outer support collar 128 , in accordance with one or more embodiments of the present invention. As shown in Figures 3 and 4, the outer support collar 128 extends axially, radially and circumferentially from the shroud 102 toward the outer housing 40 (Figure 3) within the annular flow passage 52 (Figure 3).
    In one embodiment, as shown in FIG. 3, the outer support collar 128 connects the burner cap assembly 100 to the outer housing 40. In one embodiment, the outer support collar 128 is at least partially connected to one, as shown in FIGS. 3 and 4 or multiple passageways 130 formed. The one or more passageways 130 provide a flow path for fluid communication between the high pressure chamber 44 (FIG. 2) and the second cooling air plenum 124. As shown in FIGS. 3 and 4, the one or more passageways 130 may extend generally or substantially radially through the outer support collar 128 with respect to the centerline 112. In particular embodiments, the outer support collar 128 may be formed with a plurality of axially extending through holes 132. The through holes 132 may allow for flow conditioning of a portion of the compressed air 18 as it flows through the annular flow passage 52 toward the head end 54. For example, the through-holes 132 may reduce a pressure or flow rate at the head end 54.
    In various embodiments, the burner cap assembly 100 includes a plurality of tubes 134, as shown generally throughout FIGS. 3 and 4. Each tube 134 extends from a corresponding opening 136 formed within and / or through the first divider plate 106, through the second cooling air plenum 124, and toward the head end 54 (FIG. 3) of the burner 24. In specific embodiments As shown in FIG. 3, the tubes 134 extend through the second divider plate 108 toward the head end 54. Each tube 134 has an outlet 138.
    The tubes 134 provide fluid communication from the first cooling air plenum 118, through the second cooling air plenum 124, and to the top end 54 of the combustor 24, or at least in the direction thereof. The tubes 134 may substantially isolate a flow of a coolant, such as compressed air, from the cooling air plenum 124. The tubes 134 may extend substantially axially with respect to the centerline 112. In further embodiments, as illustrated by dashed lines in FIG. 3, the tubes 134 may be curved or otherwise non-rectilinear to define a tortuous flow path through the second cooling air plenum 124. Each tube 134 has an outlet.
    In particular embodiments, the outlet 138 of at least one of the tubes 134, as shown in dashed lines in Fig. 3, upstream and / or in the vicinity of the inlet 62 to the annular flow channel 60 of the burner tube 56 is arranged. In particular embodiments, the outlet 138 of at least one of the tubes 134, as shown in FIG. 3, is located upstream and / or near the radial opening 64 formed in the burner tube 56. In particular embodiments, the outlet 138 of at least one of the tubes 134, as shown in FIG. 3, is located upstream and / or near the opening (s) of the central body 58.
    FIG. 5 is an enlarged side elevational view of the combustor 24 illustrating a flow diagram of a portion of the combustor 24 in operation as described herein and illustrated in FIGS. 2, 3, and 4, in accordance with one or more embodiments of the present invention. In operation, part of the compressed air 18 as cooling air 200 at a first temperature (Ti) is branched from the high-pressure accumulation chamber 44 into the second cooling air accumulation chamber 124. Ti may be substantially equal to the temperature of the compressed air 18 in the high pressure chamber 44. In particular embodiments, the cooling air 200 is branched via the one or more passageways 130 into the second cooling air plenum 124.
    The cooling air 200 flows through the baffles 120 and into the first cooling air plenum 118. The baffles 120 may be configured or shaped to direct a jet or column of cooling air 200 against a front or cold side surface 140 of the cap plate 104 so as to provide at least impact / jet cooling and / or convective cooling to the cap plate 104. Thermal energy taken from the cap plate 104 raises the temperature of the cooling air 200 in the first cooling air plenum to a second temperature (T2).
    Outlet cooling air 202 flows through the tubes 134 from the first cooling air plenum 118 at a temperature T2. The tubes 134 branch the outlet cooling air 202 through the second cooling air plenum 124 and through the second splitting plate 108. In specific embodiments, the tubes 134 fluidly isolate the outlet cooling air 202 in the tubes from fresh cooling air 200 flowing from the high pressure plenum 44 into the second cooling plenum 124. The outlet cooling air 202 exits each corresponding outlet 138 of the tube 134 at a location located between the second divider plate 108 and the end cover 42 outside the second cooling air plenum 124, for example, at or near the top end 54 of the combustor 24.
    In one embodiment, at least a portion of the outlet cooling air 202 flows through the one or more radial openings 64 formed in the burner tube 56 and enters the premixing channel 60 of the fuel nozzle 46. The outlet cooling air 202 may enter the premixing passage 60 at any point along the burner tube 56, depending on the axial location of the radial passageway 66, for example, upstream, near or downstream of the swirl vanes 66. Thus, the outlet cooling air 202 may be utilized to purge the premix channel 60. In addition or in the alternative, the outlet cooling air 202 may be utilized at a temperature T2 higher than the temperature of a main portion 204 of the compressed air 18 flowing from the high-pressure accumulation space 44 to the head end at a third temperature (T3) To refine fuel-air pre-mixing in the premixing channel 60 so that the overall efficiency of the burner is increased.
    In one embodiment, the body portion 204 of the compressed air 18 flows through the through-holes 132 of the outer support sleeve 128 upstream of the head end 54, so that the flow rate or other flow characteristics of the main portion 204 of the compressed air 18 are conditioned or modified while moving in the direction of the head end 54 flows. At least a portion of the body portion 204 of the compressed air 18 may mix with the outlet cooling air 202 near and / or at the head end 54 of the burner 24.
    In one embodiment, at least a portion of the outlet cooling air 202 flows into the purge channel 70 via the one or more apertures 72 formed in the central body 58. Thus, the outlet cooling air 202 can be utilized to surround the central body 58 and / or can be used for pilot-assisted burner operation.
    The reintroduction of the outlet cooling air 202 into the premix channel 60 and / or into the purge or run air channel 70 increases the amount of compressed air available for combustion, cooling, and / or purge. As a result, a greater portion of the compressed air 18 from the high pressure accumulation space may be utilized to cool the one or more flame tubes 48 and / or other metal parts in the burners 24 and / or the turbine 28. In addition, reuse of the exhaust cooling air 202 for purging the purge air duct 70 may result in a reduction in engine emissions due to the fact that the exhaust cooling air is provided at a temperature T2 higher than Ti and T3.
    The various embodiments as described hereinabove and illustrated in FIGS. 2-5 provide a method 300 of utilizing the cooling air 200 in the combustor 24. FIG. 6 shows a flow chart of the method 300 according to one exemplary embodiment. In step 302, the method 300 includes directing the cooling air 200 from the annular flow passage 52 defined in the combustor 24 into the second cooling air plenum 124 with the annular flow passage 52 in fluid communication with the high pressure chamber 44. In step 304, the method 300 includes directing the cooling air 200 through the first divider plate 106 and into the first cooling air accumulation chamber 118 so that the cooling air 200 impacts the cold side 140 of the cap plate 104 of the burner cap assembly 100 to cool it. In step 306, the method 300 includes branching outlet cooling air 202 out of the first cooling air plenum 118 to the top end portion 54 of the combustor 24 via the pipe 134. The pipe 134 extends from an opening 136 formed in the first splitting plate 106. through the second cooling air plenum 124 and through the second partition plate 108, the second partition plate 108 at least partially forming the second cooling air plenum 124.
    In further embodiments, the method 300 includes directing the outlet cooling air 202 into the purge air channel 70 formed in the central body 58 of the fuel nozzle 46. In one embodiment, the method 300 further includes directing the outlet cooling air 202 into the premixing passage 60 of the fuel nozzle 46. In one embodiment, the method 300 includes directing the compressed air 18 from the high pressure accumulation space 44 into the head end 54 via the annular flow passage 52 and mixing the outlet cooling air 202 with the compressed air 18. In one embodiment, the method 300 includes, by means of the tube 134, fluidly isolating the outlet cooling air 202 from the cooling air 200 flowing into the second cooling air plenum 124. In further embodiments, the method 300 may include directing the outlet cooling air 202 into the premixing channel 60 upstream, near, or downstream of the swirl vanes 66.
    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 and systems, and to carry out any associated methods , The patentable scope of the invention is defined by the claims, and may include other examples of skill in the art. Such other examples are intended to be within the scope of the claims if they include structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements that differ only slightly from the literal language of the claims.
    A system for utilizing cooling air in a burner includes a fuel nozzle having an axially extending central body, a burner tube circumferentially surrounding at least a portion of the central body, and a premixing channel disposed between the central body and the burner tube is trained. The system further includes a burner cap assembly having a first cooling air plenum formed between a cap plate and a first partition plate, a second cooling air plenum formed upstream of the first cooling air plenum between a second partition plate and the first partition plate, and a tube having a second cooling air plenum provides fluid communication from the first cooling air plenum, through the second cooling air plenum and through the second splitting plate. The system provides a method of utilizing the cooling air in the burner.
    LIST OF REFERENCE NUMBERS
    [0059]<Tb> 10 <September> Gas Turbine<Tb> 12 <September> inlet section<Tb> 14 <September> working fluid / air<Tb> 16 <September> compressor<tb> 18 <SEP> Compressed air<Tb> 20 <September> Fuel<Tb> 22 <September> fuel source<Tb> 24 <September> burner<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> outlet<Tb> 38 <September> exhaust stack<Tb> 40 <September> outer housing<Tb> 42 <September> end cover<Tb> 44 <September> high-pressure accumulator<Tb> 46 <September> fuel<Tb> 48 <September> flame tube<Tb> 50 <September> combustion / reaction zone<tb> 52 <SEP> Annular flow channel<Tb> 54 <September> headboard<tb> 56 <SEP> Outer sleeve / burner tube<Tb> 58 <September> Body<Tb> 60 <September> Annular / premix<Tb> 62 <September> inlet<tb> 64 <SEP> Radial opening<Tb> 66 <September> swirl / turning vane<tb> 68 <SEP> Premix quantity of compressed air<Tb> 70 <September> rinsing / Zündluftkanal<tb> 72 <SEP> Opening - Body<Tb> <September><Tb> 100 <September> burner cap assembly<Tb> 102 <September> wrapping<Tb> 104 <September> effusion / cap plate<Tb> 106 <September> impingement plate<Tb> 108 <September> Distribution plate<tb> 110 <SEP> Rear end<Tb> 112 <September> centerline<Tb> 114 <September> cooling / effusion opening<Tb> 116 <September> fuel nozzle channel<Tb> 118 <September> impact plenum<Tb> 120 <September> Impact opening<Tb> 122 <September> fuel nozzle channel<Tb> 124 <September> Kühlluftsammelräum<Tb> 126 <September> fuel nozzle channel<tb> 128 <SEP> Outer Support Cuff<Tb> 130 <September> passageway<Tb> 132 <September> Through Hole<Tb> 134 <September> Pipe<Tb> 136 <September> opening<Tb> 138 <September> outlet<Tb> 140 <September> cold side<tb> 141-199 <SEP> NOT USED<Tb> <September><Tb> 200 <September> cooling air<Tb> 202 <September> Auslasskühlluft<tb> 204 <SEP> Primary subset of compressed air<tb> 205-299 <SEP> NOT USED<Tb> <September><Tb> 300 <September> Process<Tb> 302 <September> Step<Tb> 304 <September> Step<Tb> 306 <September> Step
    权利要求:
    Claims (10)
    [1]
    A system for utilizing cooling air in a burner, the system comprising:a fuel nozzle having an axially extending central body, a burner tube circumferentially surrounding at least a portion of the central body, and a premixing channel formed between the central body and the burner tube; anda burner cap assembly having a first cooling air plenum formed between a cap plate and a first partition plate, a second cooling air plenum formed upstream of the first cooling air plenum between a second partition plate and the first partition plate, and a pipe having a fluid communication therewith first cooling air plenum, through the second cooling air plenum and through the second partition plate, with the fuel nozzle extending axially in the burner cap assembly.
    [2]
    2. The system of claim 1, wherein the tube provides a flow connection between the first cooling air plenum and the premixing channel.
    [3]
    3. The system of claim 1, wherein the fuel nozzle has a scavenging air passage axially extending in the central body, the pipe providing a flow communication between the first cooling air plenum and the purge air passage.
    [4]
    4. The system of claim 1, wherein the tube extends through the second cooling air plenum, which is substantially parallel to the fuel nozzle.
    [5]
    5. The system of claim 1, wherein at least a portion of the tube is curved in the second cooling air plenum.
    [6]
    6. The system of claim 1, wherein the tube fluidly isolates an outlet cooling air from the first cooling air plenum from the second cooling air plenum.
    [7]
    The system of claim 1, wherein the burner cap assembly further includes an outer support collar extending radially outwardly from the envelope of the burner cap assembly, the outer support collar having a plurality of axially extending through holes configured to provide compressed air passing therethrough and flowing toward a header portion of the burner.
    [8]
    8. burner having:an end cover connected to an outer housing, the end cover and the outer housing forming a high pressure chamber and a head end of the burner;a fuel nozzle extending axially downstream of the end cover and in fluid communication with the head end, the fuel nozzle having an axially extending central body, a burner tube circumferentially surrounding at least a portion of the central body, a premix channel interposed between the central one Body and the burner tube is formed, and includes a scavenging air duct, which is formed in the central body;a torch cap assembly circumferentially surrounding at least a portion of the fuel nozzle, the torch cap assembly having a first cooling air plenum formed between a cap plate and a first splitting plate, a second cooling air plenum formed upstream of the first cooling air plenum between a second splitting plate and the first splitting plate; and providing a tube having fluid communication from the first cooling air plenum, through the second cooling air plenum and through the second splitting plate, the fuel nozzle extending through the burner cap assembly.
    [9]
    9. The burner of claim 8, wherein the tube provides a flow connection between the first cooling air plenum and the premixing channel; and / or wherein the tube provides a fluid communication between the first cooling air plenum and the purge air duct; and / or wherein the tube extends through the second cooling air plenum, which is substantially parallel to the fuel nozzle.
    [10]
    10. A method of using cooling air in a burner, comprising:Directing cooling air from an annular flow passage formed within the combustor into a second cooling air plenum of a burner cap assembly, the annular flow passage being in fluid communication with a high pressure chamber;Directing the cooling air from the second cooling air plenum through a first partition plate and into a first cooling air plenum of the burner cap assembly, the cooling air flowing against a cold side of a cap plate of the burner cap assembly to provide cooling therefor;Branching outlet cooling air from the first cooling air plenum to a header portion of the burner via a pipe, the pipe extending from an opening formed in the first partition plate through the second cooling air plenum and through a second partition plate at least partially the second one Cooling air collecting chamber forms.
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    同族专利:
    公开号 | 公开日
    CH710574B1|2020-09-30|
    DE102015121649A1|2016-06-23|
    JP6659344B2|2020-03-04|
    US9835333B2|2017-12-05|
    CN205746972U|2016-11-30|
    JP2016118201A|2016-06-30|
    US20160178202A1|2016-06-23|
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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 |
    2019-07-31| AZW| Rejection (application)|
    2020-05-29| AEN| Modification of the scope of the patent|Free format text: :DIE PATENTANMELDUNG WURDE AUFGRUND DES WEITERBEHANDLUNGSANTRAGS VOM 18.09.2019 REAKTIVIERT. |
    2021-07-30| PL| Patent ceased|
    优先权:
    申请号 | 申请日 | 专利标题
    US14/580,315|US9835333B2|2014-12-23|2014-12-23|System and method for utilizing cooling air within a combustor|
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