Gas Turbine Combustor

Abstract

To provide combustors for a gas-turbine engine.SOLUTION: Combustors (14), gas turbines (10) and associated methods of operation are provided. A method for operating a combustor (14) includes firing a bundled tube fuel nozzle assembly (100) within a combustion liner (36) of the combustor (14) to generate combustion gases (26) at a first temperature within a first combustion zone length (92). The method further includes firing a fuel injector (60) downstream from the bundled tube fuel nozzle assembly (100) within the combustion liner (36) of the combustor (14) to generate the combustion gases (26) at a second temperature within a second combustion zone length (94). The first combustion zone length (92) is less than the second combustion zone length (94). The combustion gases (26) travel through the first combustion zone length (92) in a first time period and through the second combustion zone length (94) in a second time period. The second time period is less than the first time period.SELECTED DRAWING: Figure 9

Description

[Technical Field]

[0001] FIELD OF THE DISCLOSURE This disclosure relates generally to combustors and, more particularly, to combustors for gas turbine engines. [Background technology]

[0002] Turbomachinery is used in various industries for the purpose of energy transmission. and For example, a gas turbine engine typically includes a compressor section, a combustion section, a turbine section, and an exhaust section. The compressor section gradually increases the pressure of a working fluid entering the gas turbine engine and supplies the compressed working fluid to the combustion section. and The fuel (e.g., natural gas) is mixed in the combustion section and burned in the combustion chamber to produce a high-temperature Pressure The combustion gases flow from the combustion section to the turbine section, Turbine Section Expand and work arising For example, the turbine section in The expansion of the combustion gases ( example Departure Electric machine ) to Connect This rotates the rotor shaft and generates electricity. Let The combustion gases are then discharged from the gas turbine through an exhaust section.

[0003] Many Publicly known In the combustion system, the mixed working fluid and The fuel is omitted It is ignited in the upstream portion, i.e., the combustion chamber, to produce the operating turbine operating temperatures. Ta The best job in the bin arising In order to Extremely high operating temperatures of combustion gases Maintained from the combustion chamber to the combustor exit death However, because nitrogen oxide (NOx) production is exponential with temperature and linear with time, maintaining high operating temperatures from the combustion zone to the combustor exit is a challenge for many. Publicly known Combustion system In Large contributor to emissions Tona do.

[0004] Therefore, improved combustors are in the art. in In particular, an improved combustor that optimally minimizes the amount of time the combustion gases spend at peak temperature is desirable. in It is desired. Summary of the Invention

[0005] Aspects and Benefits of the Disclosure About points ,below Detailed explanation However, the following detailed From the description Some may be self-evident, or This technology implementation through There may be something you can learn .

[0006] One embodiment So , combustor of offer vinegar The combustor has a forward end. definition Includes an end cover that supports the combustor. teeth , upstream end and Combustion liner having a downstream end too The combustor includes: collection It further includes a bundle-tube fuel nozzle assembly. collection The bundle-tube fuel nozzle assembly is fluidly coupled to the end cover at the upstream end of the combustion liner. However Extends to multiple outlets in the cap plate exists Multiple collection The cap plate includes a bundle-tube fuel nozzle. collection The diameter of the bundle-tube fuel nozzle assembly is definition The combustor is connected to a combustion liner. However Multiple collection Downstream of the bundle-tube fuel nozzle and The aft frame further includes a plurality of fuel injectors disposed upstream of the aft frame, the aft frame being coupled to a downstream end of the combustion liner. I'm The combustion liner defines the combustion zone between the outlets and the aft frame. defines a combustion zone through which the combustion gases take total time to travel. The combustion zone is formed between the outlets and the fuel injectors. definition The first combustion zone a first combustion zone through which combustion gases from the plurality of focus tube fuel nozzles flow for a first portion of the total time; The combustion zone is located between the fuel injectors and the rear frame. definition Second combustion zone a second combustion zone through which combustion gases from the plurality of focus tube fuel nozzles and the plurality of fuel injectors flow for a second portion of the total time; Further includes: time The second part of time It is about 30% to 50% of the total.

[0007] Another embodiment So , gas turbine of offer vinegar The gas turbine includes a compressor, a turbine, and a combustor located downstream of the compressor and upstream of the turbine. definition The combustor also includes an end cover that supports the upstream end. and The combustor includes a combustion liner having a downstream end. collection It further includes a bundle-tube fuel nozzle assembly. collection A bundle-tube fuel nozzle assembly is fluidly coupled to the end cover at the upstream end of the combustion liner and extends to a plurality of outlets in the cap plate. exists Multiple collection The cap plate includes a bundle-tube fuel nozzle. collection The diameter of the bundle-tube fuel nozzle assembly is definition The combustor is coupled to a combustion liner and includes a plurality of collection The combustion liner further includes a plurality of fuel injectors disposed downstream of the bundle-tube fuel nozzles and upstream of the aft frame, the aft frame being coupled to a downstream end of the combustion liner, the combustion liner defining a combustion zone between the plurality of outlets and the aft frame. defines a combustion zone through which the combustion gases take total time to travel. The combustion zone is formed between the outlets and the fuel injectors. definition The first combustion zone a first combustion zone through which combustion gases from the plurality of focus tube fuel nozzles flow for a first portion of the total time; The combustion zone is located between the fuel injectors and the rear frame. definition Second combustion zone a second combustion zone through which combustion gases from the plurality of focus tube fuel nozzles and the plurality of fuel injectors flow for a second portion of the total time; Further includes: time The second part of time It is about 30% to 50% of the total.

[0008] Another embodiment So , a method for operating a combustor of offer vinegar The method comprises: collection starting the bundle-tube fuel nozzle assembly. the result The combustion gases at the first temperature are generated within the first combustion zone length. collection Further including actuating a fuel injector assembly downstream of the bundle-tube fuel nozzle assembly. the result The combustion gases at the second temperature are generated within a second combustion zone length, the first combustion zone length being shorter than the second combustion zone length.

[0009] This system and Method The above Other features and aspects and advantage About is as follows: Detailed explanation and See claims By doing understanding You can deepen The accompanying drawings are indicative of the present specification. It is part of the contents of This technology Various Illustrative embodiments At the same time , Detailed Description of the Invention The principle of this technology will be explained together with the explanation. It is for .

[0010] Book Combustor and gas turbine In the following detailed description, reference is made to the accompanying drawings, in which: The present system and method Manufacturing and Best practices for use The disclosure, including the form of the invention, is sufficient to enable a person skilled in the art to carry out the invention. . [Brief explanation of the drawings]

[0011] [Figure 1] FIG. 1 is a functional block diagram of an exemplary gas turbine according to an embodiment of the present disclosure. [Figure 2] FIG. 1 is a simplified cross-sectional side view of an exemplary combustor according to an embodiment of the present disclosure. [Figure 3] FIG. 1 is a simplified cross-sectional side view of an exemplary combustor according to an embodiment of the present disclosure. [Figure 4] FIG. 2 is a close-up view of a simplified cross-sectional side view of an exemplary combustor according to an embodiment of the present disclosure. [Figure 5] FIG. 2 is a plan view of a focus tube fuel nozzle assembly looking upstream from the aft end of a combustor according to an embodiment of the present disclosure. [Figure 6] FIG. 10 is a plan view of a focus tube fuel nozzle assembly looking upstream from the aft end of a combustor according to another embodiment of the present disclosure. [Figure 7] FIG. 2 is a cross-sectional side view of a portion of a single focus tube fuel nozzle according to an embodiment of the present disclosure. [Figure 8] FIG. 1 is a perspective view of a portion of a combustor according to an embodiment of the present disclosure. [Figure 9] FIG. 1 illustrates a method of operating a combustor according to an embodiment of the present disclosure. DETAILED DESCRIPTION OF THE INVENTION

[0012] below ,This system and Method Various Embodiment The present invention will be described in detail with reference to one or more embodiments thereof illustrated in the drawings. . Each example is intended to be illustrative, not limiting, of the present technology. Indeed, it will be apparent to those skilled in the art that various modifications and variations can be made to the present technology without departing from the scope and spirit of the appended claims. For example, features illustrated or described as part of one embodiment can be used with another embodiment to yield a still further embodiment. Accordingly, the present disclosure covers modifications and variations that come within the scope of the appended claims and their equivalents.

[0013] The detailed description of the invention uses numerical and letter designations to refer to features depicted in the drawings. In the drawings and the detailed description of the invention, like or similar designations indicate like or similar components of the invention. In this specification, the terms "first," "second," and "third" are used interchangeably to distinguish one component from another and do not imply any position or importance of the individual components.

[0014] As used herein, the terms "upstream" and "downstream" refer to relative directions with respect to fluid flow in a fluid pathway. For example, "upstream" refers to the direction from which fluid flows and "downstream" refers to the direction to which fluid flows. The term "radial" refers to relative directions that are substantially perpendicular to the axial centerline of a part, the term "axial" refers to relative directions that are substantially parallel and / or coaxial with the axial centerline of a part, and the term "circumferential" refers to relative directions about the axial centerline of a part.

[0015] As used herein, approximate terms such as "approximately," "about," and "substantially" encompass ±10% of the stated numerical value. When used in reference to an angle or direction, such terms encompass within ±10 degrees of the stated angle or direction. For example, "approximately vertical" encompasses directions within 10 degrees of vertical in any direction (e.g., clockwise or counterclockwise).

[0016] The terms used herein are for the purpose of describing particular embodiments only and are not intended to limit the disclosure. As used herein, the singular "a," "an," or "an" includes the plural unless the context clearly dictates otherwise. As used herein, the terms "comprise" and / or "include" indicate the presence of stated features, integers, steps, operations, components, and / or parts, but do not exclude the presence or addition of one or more other features, integers, steps, operations, components, parts, and / or groups thereof.

[0017] Referring now to the drawings, Figure 1 illustrates a schematic diagram of an exemplary gas turbine 10. The gas turbine 10 generally includes a compressor 12, at least one combustor 14 disposed downstream from the compressor 12, and a turbine 16 disposed downstream from the combustor 14. Additionally, the gas turbine 10 includes a compressor 12 coupled to the turbine 16. End Including shaft 18 It Good too.

[0018] During operation, air 20 flows into compressor 12 where it is progressively compressed. handcompressed air or Compressed air 22 enters the combustor 14 supply At least a portion of the compressed air 22 is mixed with fuel 24 in the combustor 14 and combusted to generate combustion gases 26. The combustion gases 26 flow from the combustor 14 to the turbine 16, where they are converted into kinetic and / or Thermal energy is transferred from the combustion gases 26 to the rotor blades (not shown), causing the shaft 18 to rotate. The mechanical rotational energy is then transferred to the compressor 12. Drive salary and / or Used for various purposes, including power generation obtain The combustion gases 26 may then be exhausted from the gas turbine 10 .

[0019] 2 is a cross-sectional side view of an exemplary combustor that may incorporate various embodiments of the present disclosure. As shown, the combustor 14 has an axial A, radial R and Zhou Direction C definition Generally, the axial direction A extends parallel to the axial centerline 47 of the combustor 14. Exist The radial direction R extends substantially perpendicular to the axial center line 47. Exist , Zhou The direction C extends approximately concentrically around the axial centerline 47. exists As shown in FIG. 2, the combustor 14 is at least partially surrounded by an outer casing 28, such as a compressor discharge casing. It The outer casing 28 may accommodate various components of the combustor 14. parts a high pressure plenum 30 at least partially enclosing the definition The high-pressure plenum 30 is in fluid communication with the compressor 12 (FIG. 1) and may receive a portion of the compressed air 22 therefrom. An end cover 32 is coupled to the outer casing 28. obtain .

[0020] collection A bundle-tube fuel nozzle assembly 100 extends axially downstream from the end cover 32. There can be . collectionThe bundle-tube fuel nozzle assembly 100 is disposed upstream of the first combustion zone 38 and downstream of the end cover 32 relative to the axial centerline 47 of the combustor 14. and / or Located within outer casing 28 axially spaced from end cover 32 death In certain embodiments, the fuel nozzle assembly 100 includes: End The fuel supply 51 is in fluid communication with the fuel conduit 49. In certain embodiments, the fluid conduit 49 is fluidly coupled to the inner surface 33 of the end cover 32. and / or connection obtain . collection The bundle-tube fuel nozzle assembly 100 may be configured to provide a first mixture of fuel 24 and compressed air 22 to the first combustion zone 38 for ignition.

[0021] 1 End Combustion liner or Duct 36, 1 End of collection a first combustion chamber downstream of the bundle-tube fuel nozzle 34; or Zone 38 at least partially definition can be and / or a hot gas path 40 at least partially through the combustor 14 for directing the combustion gases 26 (FIG. 1) toward an inlet 42 of the turbine 16; definition In certain embodiments, the combustion liner 36 may include a or a unitary body having a forward end 44 or The combustion liner 36 may be formed from a unibody, and may be substantially cylindrical. or The combustion liner 36 is then or Non-circular shape near rear end 46 or A transition to a substantially rectangular cross-sectional shape can be achieved.

[0022] In certain embodiments, the aft end 46 of the combustion liner 36 may terminate in an aft frame 48. The aft frame 48 secures the combustion liner 36 to the outer casing 28. orIt can be used to attach to other support hardware, thereby securing the aft end 46 of the combustion liner 36. or Thus, the forward end 44 of the combustion liner 36 is axially constrained as the combustor 14 transitions through various thermal conditions associated with different modes of operation. collection axial expansion toward the bundle-tube fuel nozzle assembly 100 and It can be contracted.

[0023] In certain embodiments, the combustion liner 36 is at least partially enclosed by an outer sleeve 50. Zhou The outer sleeve 50 is surrounded by a single parts Formed as Alternatively, a flow sleeve and Formed by multiple sleeve segments, such as by impingement sleeves (not shown separately) You may The impingement sleeve is Flow Sleeve and the shaft may be slidably engaged to allow relative axial movement therebetween. or , the outer sleeve 50 is Flow Sleeve and the impingement sleeve are axially to Integrated with each other death Integrated body ( or "Unisleeve" structure It The outer sleeve 50 may be radially spaced from the combustion liner 36 to define a cooling flow annulus 56 therebetween. definition possible.

[0024] As shown in FIG. 2, in many embodiments, the cooling flow annulus 56 extends through the high pressure plenum. collection The outer sleeve 50 may be fluidly coupled to the bundle-tube fuel nozzle assembly 100. For example, the outer sleeve 50 may have a plurality of inlets that provide fluid communication from the high pressure plenum 30 to the cooling flow annulus 56. or hole (not shown) definition Alternatively, or Additionally, outer sleeve 50 includes an inlet 57 located at the aft end of combustor 14 that fluidly couples cooling flow annulus 56 to high pressure plenum 30. It Good too.

[0025] In many embodiments, the compressed air 22 from the high pressure plenum 30 passes through a cooling flow annulus 56 to the head end section of the combustor 14. or The compressed air 22 can flow upstream into the head-end volume 34. Within the head-end volume 34, the compressed air 22 reverses direction and collection The head end portion 34 may travel downstream through a bundle-tube fuel nozzle assembly 100 where the fuel 24 is introduced and a first mixture of the fuel 24 and compressed air 22 is provided to the combustion zone 38. The head end portion 34 may include an end cover 32 and a plurality of collection and a bundle-tube fuel nozzle 100, collection Compressed air 22 may be provided to the bundle-tube fuel nozzle assembly 100 .

[0026] In certain embodiments, the outer sleeve 50 is generally axially aligned with respect to the axial centerline 47 of the combustor 14 . or Thus, the outer sleeve 50 may be substantially unconstrained as the combustor 14 transitions through various thermal conditions. End of collection Towards the bundle tube fuel nozzle 34 and / or Expands axially toward rear frame 48 and It can be contracted.

[0027] Various embodiments So As shown in FIG. 2, the combustor 14 collection Axial offset from bundle-tube fuel nozzle assembly 100 It has , collection The bundle-tube fuel nozzle assembly 100 includes at least one fuel injector 60 disposed downstream. The fuel injector 60 includes an outer sleeve 50, a cooling passage 56, and Extending radially at least partially through the combustion liner 36 There can be In certain embodiments, the combustor 14 includes a combustion liner 36 and The outer sleeve 50 includes a plurality of fuel injectors 60 arranged annularly around the outer sleeve 50. Each fuel injector 60 extends along the circumference of the outer sleeve 50. ZhouSpaced apart in the direction obtain .

[0028] The plurality of fuel injectors 60 may be configured to provide a second mixture of fuel 24 and compressed air 22 to the second combustion zone 39 for ignition. The combustion gases 26 generated by the fuel injectors 60 in the second combustion zone 39 may mix with the combustion gases 26 of the first combustion zone 38 and may have a higher temperature than the first combustion zone 38. The second combustion zone 39 may include: collection Bundle-tube fuel nozzle 34 and / or Within the combustion liner 36 downstream of the first combustion zone 38 Definition In some embodiments, the second combustion zone 39 is located between the first combustion zone 38 and the aft frame 48. Can be defined In many embodiments, the second combustion zone 39 is located immediately downstream of the first combustion zone 38. Definition obtain.

[0029] Each fuel injector 60 may have an outlet that is substantially shaped as a geometric stadium, i.e., a rectangle with opposing circular ends. This shape advantageously allows each fuel injector to extend radially through the cooling flow annulus 56 without blocking a significant portion of the compressed air 22 traveling axially through the cooling flow annulus 56. exists This makes it possible to

[0030] Figure 3 and 4, the combustor 14 may include a first radial opening 62 and a second radial opening 64. The combustion liner 36 may include: collection A first radial opening 62 is formed downstream of the bundle-tube fuel nozzle assembly 100. definition The outer sleeve 50 may have a second radial opening 64. definition The first radial opening 62 and The second radial openings 64 are aligned with one another in both the radial direction R and the axial direction A. It Good too.

[0031] In addition, the first radial opening 62 and The second radial openings 64 may be of equal size, with each opening 62, 64 shaped as a geometric stadium, i.e., a rectangle with two semicircular ends opposite each other. and Each of the second radial openings 64 has a major axis 66 (as shown in FIG. 4). and The major axes 66 of both the first radial opening 62 and the second radial opening 64 may be the same length and aligned with one another. It Similarly, the minor axes 68 of both the first radial opening 62 and the second radial opening 64 may be the same length and aligned with one another. It The major axis 66 may be greater than the minor axis 68, and the major axis 66 may be aligned with the axial centerline 47 of the combustor 14. omitted The fuel injector 60 has a second radial opening 64 for delivering a second mixture of fuel and air to the second combustion zone 39. and Extending through the first radial opening 62 There can be .

[0032] As shown in FIG. 4, the first radial opening 62 and Each of the second radial openings 64 has a forward end 70 and The front end 70 may include a rear end 72. and The upstream most portions of the second radial openings 62, 64, respectively Can be defined Similarly, the rear end 72 is and The downstream most portions of the second radial openings 62, 64, respectively Can be defined First radial opening 62 and Each of the second radial openings 64 extends from a respective forward end 70 to a respective aft end 72. There can be .

[0033] Figure 5 and FIG. 6 shows a view of the combustor 14 looking upstream from the aft end. collection 1 is a plan view of an embodiment of a bundle-tube fuel nozzle assembly 100. As shown, collectionThe bundle-tube fuel nozzle assembly 100 may include a plurality of outer nozzles 104 arranged in an annular configuration around a central fuel nozzle 102 .

[0034] As shown in FIG. 5, the center nozzle 102 and Each outer nozzle 104 is round or The outer nozzles 104 are arranged around a central fuel nozzle 102 in a cap plate parallel to the end cover 32. Each fuel nozzle 102, 104 has a plurality of tubes 106. collection The plurality of tubes 106 extend through the fuel plenum toward the first combustion zone 38. exists Each of the plurality of tubes 106 is aligned with the axial centerline 47 of the combustor 14. Abbreviated as The cap plate may include a plurality of cooling holes to facilitate cooling of the cap plate.

[0035] 6, the central fuel nozzle 102 may be surrounded by multiple outer nozzles 150. Each fuel nozzle 102, 150 collectively supports a downstream cap plate. definition a unique rear plate for or A single cap plate (not shown) extends over the downstream end of the tubes 106 in each fuel nozzle 102, 104. There can be Each outer nozzle 150 is positioned adjacent to the center fuel nozzle 102 and has a truncated wedge shape that allows it to cover a majority of the head end area. Exist , first (radially inner) arcuate side surface 156 and defined as having a pair of radial sides 154 joined by a second (radially outer) arcuate side 158 death The radially outer side 158 of the fuel nozzle segment 150 and Collectively, the radially outer periphery of the head end or Diameter 90 definition do.

[0036] Figure (Fig. 5 andSpecific sizes, spacing, and other characteristics of the plurality of tubes 106 shown in FIG. 6 and The number is collection The bundle-tube fuel nozzles 102, 104, 150 are intended to be merely exemplary and are not intended to be limiting of specific sizes, spacing, or This book has several tubes. collection Further, nothing in this specification should be construed to limit bundle-tube fuel nozzles to having tubes that are a single tube diameter. collection It should not be construed as limiting bundle-tube fuel nozzles.

[0037] FIG. 7 illustrates a method for manufacturing a cellular telephone according to at least one embodiment of the present disclosure. Related A single example fuel nozzle assembly 100 shown in FIG. collection 1 provides a cross-sectional side view of a portion of a bundle-tube fuel nozzle 200. Various embodiments of the combustor 14 may include different arrangements of the fuel nozzle assembly 100, and the combustor 14 is not limited to a particular arrangement unless otherwise specified in the claims.

[0038] In at least one embodiment, as shown in FIG. 7, the fuel nozzle 200 includes a forward or An upstream plate 204, an aft plate 206 axially spaced from the forward plate 204, and a slit extending axially between the forward plate 204 and the aft plate 206. exists outer band or The fuel plenum includes a fuel plenum body having a shroud. teeth , within the fuel plenum body 202 definition In certain embodiments, the front plate 204, the rear plate 206, and The outer band 208 at least partially encloses the fuel plenum 210. definition In certain embodiments, the fluid conduit 49 extends through the front plate 204. Exist , fuel 24 may be provided to the fuel plenum 210. SoThe fuel nozzle assembly 200 includes a cap plate 212 axially spaced from the aft plate 206. A hot side 214 of the cap plate 212 generally abuts the first combustion zone 38. or The cap plate 212 may be unique to each fuel nozzle assembly 200. stone , or It may be common to all fuel nozzle assemblies 200 .

[0039] 7, the fuel nozzle assembly 200 can include a tube bundle 216 that includes a plurality of tubes 106. Each tube 106 is connected to a forward plate 204, a fuel plenum 210, an aft plate 206, and Extending through the cap plate 212 There can be The tube 106 is fixedly connected to the back plate 206 and / or or A seal is formed against the back plate 206. For example, the tube 218 may be welded, brazed, or otherwise attached to the back plate 206. or Each tube 106 may be connected in other ways. So At the upstream end 222 of each tube 106 definition an entrance 220; So At the downstream end 226 of each tube 106 definition Each tube 106 has a respective premix flow path 228 through the fuel nozzle 200. definition In certain embodiments, one of the plurality of tubes 106 End The tubes 106 have definition 1 End The fuel plenum 210 is in fluid communication with the fuel plenum 210 via the fuel ports 230 .

[0040] As shown in FIG. 8, the jacket portion 74 extends from the first radial opening 62 and The jacket portion 74 may have the same cross-sectional shape as the second radial opening 64. In many embodiments, the jacket portion 74 is spaced apart from the first radial opening 62 to form a passage for the outlet member of the fuel injector 60 to pass through. and Extending through the second radial opening 64 Exist hand ItFor example, the jacket portion 74 may have a stadium geometric cross-sectional area, i.e., a rectangle with rounded ends. exists Jacket portion 78, which extends through jacket portion 74, obstructs the flow of compressed air through annulus 56 (FIG. 2) between liner 36 and outer sleeve 50. Because the geometric stadium shape of jacket portion 78 creates less obstruction in annulus 56 than, for example, a jacket portion having a rounded shape, jacket portion 78 advantageously allows a fuel / air mixture to be introduced by fuel injector 60 in second combustion zone 39. An outlet member of fuel injector 60 extends through jacket portion 74. Exist , thereby forming a second radial opening 64 and Extending through the first radial opening 62 There can be In many embodiments, the fuel injector 60 may include an air passage 102. The air passage 102 may connect the fuel injector 60 to the high pressure plenum 30. and It may be fluidly coupled to a second combustion zone 39 (FIG. 2).

[0041] Here, one aspect of the present disclosure End In the embodiment of Related 2-4, which provide different views of the combustor 14. As shown, in some embodiments, the aft end of the fuel nozzle assembly 100 has a diameter 90 perpendicular to the axial centerline 47 of the combustor 14. definition In other embodiments, the diameter 90 may be greater than the diameter 90 at the aft end of the fuel nozzle assembly. definition The diameter 90 may be the inner diameter of the combustion liner 36. collection It may be the inside diameter of the combustion liner measured at the outlet 224 of the bundle-tube fuel nozzle assembly 100 .

[0042] As shown in FIGS. 2-4, the axial centerline 47 of the combustor 14 is substantially curved. or It may be arcuate and include a first portion 47a and a second portion 47b. ItThe hot gas path 40 may flow along and be aligned with the axial centerline of the combustor 14. The second portion 47b may be aligned with the axial centerline of the gas turbine 10 as the combustion gases 26 exit the aft end 46 of the combustor 14. omitted They may be parallel.

[0043] Figure 3 and 4 , in some embodiments, the combustor 14 also includes a first combustion zone length 92, a second combustion zone length 94, a total combustion zone length 96, and a total combustor length 98. The first combustion zone length 92 extends along a first portion 47a of the axial centerline 47. Definition In many embodiments, the first combustion zone length 92 is collection Between the outlet 224 of the bundle-tube fuel nozzle assembly 100 and the forward end 70 of the first radial opening 62 definition The first combustion zone length 92 can be collection It may be the distance that the mixture of fuel 24 and compressed air 22 exiting the bundle-tube fuel nozzle assembly 100 travels before reaching the second combustion zone 39 .

[0044] The second combustion zone length 94 is downstream of the first combustion zone 38. Definition In many embodiments, the second combustion zone length 94 is along the axial centerline 47 of the combustor 14 and extends between the forward end 70 of the first radial opening 62 and the aft frame 48. definition It is possible. or , the second combustion zone length 94 is between the forward end 70 of the second radial opening 64 and the aft frame 48 Can be defined The second combustion zone length 94 is the length of the air 22 introduced by the fuel injector 60. and It may be the distance that the combustion gases 26 produced by the fuel 24 travel within the combustion liner 36 before reaching the turbine 16 .

[0045] The total combustion zone length 96 may be the sum of the first combustion zone length 92 and the second combustion zone length 94. In many embodiments, the total combustion zone length 96 is collectionBetween the outlet 224 of the bundle-tube fuel nozzle assembly 100 and the aft frame 48 definition In many embodiments, the total combustion zone length 96 may be the total distance that the combustion gases 26 travel within the combustion liner 36 before reaching the turbine 16 .

[0046] As shown in FIG. 3, the overall length 98 of the combustor 14 is approximately 1 / 4" long along the axial centerline 47 of the combustor 14. definition In many embodiments, the overall length 98 is between the end cover 32 and the aft frame 48. definition Specifically, the total length 600 is the distance between the inner surface 33 of the end cover 32 and the rear frame 48. Definition The overall length 98 of the combustor 14 is along the axial centerline 47 definition Therefore, the total length 98 is along the curve as shown in Figure 3. definition can be measured accordingly.

[0047] With a plurality of fuel injectors 60 collection Utilizing the bundle-tube fuel nozzle assembly 100 advantageously provides an optimally minimized first combustion zone length 92 and A second combustion zone length 94 may be possible. collection The tubes 106 in the bundle-tube fuel nozzle 200 may be substantially parallel to one another and parallel to the axial centerline 47 of the combustor 14, such that collection The bundle-tube fuel nozzle assembly 100 does not impart any swirl to the fuel / air mixture entering the first combustion zone 38. Specifically, the fuel / air mixture exiting the outlet 224 of each tube 106 in the plurality of tubes 106 may travel axially without bulk swirl, relative to the axial centerline 47 of the combustor 14. omitted In many embodiments, collection The fuel / air mixture exiting the bundle-tube fuel nozzle assembly has a uniform velocity, fuel-air ratio and The temperature can be reduced, resulting in lower NOx emissions. collectionThe non-swirling flow of the fuel / air mixture exiting the bundle-tube fuel nozzle assembly 100 advantageously allows for a rapid burn time within the first combustion zone 38. Additionally, the relatively small diameter of each tube 106 results in a correspondingly small and relatively short flame length. Thus, the first combustion zone length 92 is reduced compared to head ends with conventional swirl fuel nozzles ("swozzles"). or The first combustion zone length 92 may be made more compact, thereby reducing the amount of time the combustion gases 26 spend at high temperatures within the combustor 14, which in turn significantly reduces overall nitrogen oxide (NOx) emissions. For example, in some embodiments, the ratio of the first combustion zone length 92 to the diameter 90 may be optimally minimized to reduce overall nitrogen oxide (NOx) emissions. In some embodiments, the first combustion zone length 92 and Diameter 90 is the primary collection Bundle-tube fuel nozzle operation alone (partial load), and Over a range of operating loads including operation of both the primary and secondary combustion stages (high loads), Emissions reduction can be optimized for

[0048] In some embodiments, first combustion zone length 92 may be between about 45% and about 80% of diameter 90. In many embodiments, first combustion zone length 92 may be between about 50% and about 70% of diameter 90. Various Embodiments So The first combustion zone length 92 may be between about 50% and about 80% of the diameter 90 .

[0049] In other embodiments, the ratio of the second combustion zone length 94 to the diameter 90 can be optimally minimized. In many embodiments, the second combustion zone length 94 and The diameter 80 is optimized for baseload NOx emissions, e.g., as small as possible to minimize NOx, but large enough to completely burn the fuel 24. death obtain.

[0050] For example, in some embodiments, the second combustion zone length 94 is: collectionThe second combustion zone length 94 may be between about 120% and about 180% of the diameter 90 of the bundle-tube fuel nozzle assembly 100. In many embodiments, the second combustion zone length 94 is collection The diameter 90 of the bundle-tube fuel nozzle assembly 100 may be between about 130% and about 180%. So , the second combustion zone length 94 is collection It may be about 150% to about 170% of the diameter 90 of the bundle-tube fuel nozzle assembly 100 .

[0051] FIG. 9 is a diagram of one embodiment of the present disclosure. End In an exemplary embodiment of Related A flowchart is provided that graphically illustrates an exemplary method 300 of operating a combustor, such as the combustor 14 described herein. As shown in FIG. 9 , the method 300 includes: collection The method may include step 302 of starting the bundle-tube fuel nozzle assembly 100. the result The combustion gases 26 at the first temperature are generated within the first combustion zone length 92. death In many embodiments, collection Starting the bundle-tube fuel nozzle assembly 100 may include injecting a first combustible mixture into the first combustion zone 38 and combusting the first combustible mixture within the first combustion zone 38 to generate combustion gases 26.

[0052] The method 300 also includes: collection The method may include step 304 of activating a fuel injector 60 downstream of the bundle-tube fuel nozzle assembly 100. the result The combustion gases 26 at the second temperature are generated within the second combustion zone length 94. death In some embodiments, actuating the fuel injector 60 includes injecting the second combustible mixture into a second combustion zone 39 downstream from the first combustion zone 38, where the second combustible mixture combusts in the second combustion zone 39 and mixes with the combustion gases 26 from the first combustion zone 38.

[0053] 4, in some embodiments, the first combustion zone length 92 may be shorter than the second combustion zone length 94. In some embodiments (not shown), the method 300 may also include providing the combustion gases 26 at the second temperature to the turbine 16 downstream of the combustor 14, where the combustion gases 26 Burning Move from the burner 14 to the turbine 16 But it takes time In addition, in some embodiments, the total time is the total combustion temperature in the first combustion zone length 92 time the first portion of the second combustion zone length 94 time and a second portion of time The second part of time In other embodiments, the total time The second part of time It may be about 35% to about 45% of the total.

[0054] With a plurality of fuel injectors 60 collection Utilizing the bundle-tube fuel nozzle assembly 100 advantageously optimally minimizes the time that the combustion gases 26 spend within the combustion zone. but For example, each collection The tubes 106 in the bundle-tube fuel nozzle 200 may be substantially parallel to one another and parallel to the axial centerline 47 of the combustor 14, such that collection The bundle-tube fuel nozzle assembly 100 does not impart any swirl to the fuel / air mixture entering the first combustion zone 38. Specifically, the fuel / air mixture exiting the outlet 224 of each tube 106 in the plurality of tubes 106 may have a laminar flow and may be oriented in a direction perpendicular to the axial centerline 47 of the combustor 14. omitted It can move axially. collection De-swirl of fuel / air mixture exiting bundle-tube fuel nozzle assembly 100 formula The laminar flow advantageously allows for a rapid combustion time within the first combustion zone 38. Therefore, the first combustion zone length 92 can be shortened. orThis allows for compactness, which reduces the amount of time the combustion gases 26 spend at high temperatures within the combustor 14, significantly reducing overall nitrogen oxide (NOx) emissions.

[0055] In addition, collection More fuel is delivered through multiple fuel injectors downstream of the bundle-tube fuel nozzle assembly 100. and By introducing air, the overall mass flow rate of the combustion gases 26 flowing through the second combustion zone 39 is increased. This increase in mass flow rate results in an increase in the overall velocity of the combustion gases moving through the second combustion zone, thereby allowing the combustion gases to accelerate quickly through the second combustion zone length 94. Minimizing the amount of time the combustion gases spend at peak temperature advantageously results in a significant reduction in overall nitrogen oxide (NOx) emissions.

[0056] This specification in teeth, The present invention The best form Including These examples have been provided to initially disclose and enable those skilled in the art to practice the invention, including making and using the devices or systems and practicing the methods. Patent of the invention have sexuality The range is: The scope of the claims also includes other examples that are obvious to those skilled in the art. Such other examples fall within the technical scope of the claims if they have parts that are not literal differences from the claims or equivalent parts that have only insubstantial differences from the claims. . [Explanation of symbols]

[0057] 10. Gas turbine 12 Compressor 14 Combustor 16 Turbine 18 shaft 20. Air 22 Pressurized air, compressed air 24 Fuel 26 Combustion Gas 28 outer casing 30 High Pressure Plenum 32 End cover 33 Inner 34 collection Bundle-tube fuel nozzle, head end section, volume section 36 Combustion liner, duct 38 First Combustion Zone 39 Second Combustion Zone 40 Hot Gas Path 42 Entrance 44 Front end, upstream end 46 Rear end, downstream end 47 Axial center line 47a First Part 47b Second part 48 Rear frame 49 Fluid conduit 50 Outer sleeve 51 Fuel supply source 56 Cooling flow annulus, cooling channel 57 Entrance 60 Fuel Injector 62 first radial opening 64 Second radial opening 66 Long axis 68 Short axis 70 Front end 72 Rear end 74 Jacket part 78 Jacket part 80 diameter 90 diameter 92 First combustion zone length 94 Secondary combustion zone length 96 Total combustion zone length 98 Total combustor length, total length 100 collection Bundle-tube fuel nozzle assembly 102 central fuel nozzle, collection Bundle tube fuel nozzle, air passage 104 outer nozzle, collection bundle-tube fuel nozzle 106 tube 150 outer nozzle, fuel nozzle segment, collection bundle-tube fuel nozzle 154 Radial side 156 first (radially inner) arcuate side 158 Second (radially outer) arcuate side 200 single collection Bundle-tube fuel nozzle, fuel nozzle assembly 202 Fuel plenum body 204 forward orUpstream plate, front wall 206 Rear plate, rear wall 208 Outer band, shroud 210 Fuel Plenum 212 Cap Plate 214 Hot Side 216 Tube bundle 218 tube 220 Entrance 222 Upstream end 224 Exit 226 Downstream end 228 Premixing channel 230 fuel port 300 ways

Claims

1. A combustor (14) for a gas turbine, the combustor (14) comprising: an end cover (32) defining a forward end of the combustor (14); a combustion liner (36) having an upstream end (44) and a downstream end (46); a focus tube fuel nozzle assembly (100) comprising a plurality of focus tube fuel nozzles (102, 104, 150, 200) fluidly coupled to the end cover (32) at an upstream end (44) of the combustion liner (36) and extending to a plurality of outlets (224) in a cap plate (212), the cap plate (212) defining a diameter (90) of the focus tube fuel nozzle assembly (100); a plurality of fuel injectors (60) coupled to the combustion liner (36) and positioned downstream of the plurality of focus tube fuel nozzles (102, 104, 150, 200) and upstream of an aft frame (48), the aft frame (48) being coupled to the downstream end (46) of the combustion liner (36); It is equipped with the combustion liner defines a first radial opening downstream of the plurality of focus tube fuel nozzles, a fuel injector of the plurality of fuel injectors extending through the first radial opening, the combustion liner defines a combustion zone between the plurality of outlets and the aft frame, the combustion zone having a total time for combustion gases to travel through the combustion zone, the combustion zone comprising: a first combustion zone (38) defined between the plurality of outlets (224) and the plurality of fuel injectors (60), through which combustion gases (26) from the plurality of focus tube fuel nozzles (102, 104, 150, 200) flow during a first portion of the total time, wherein a first combustion zone length (92) is defined between the plurality of outlets (224) and a forward end (70) of the first radial opening (62), and the first combustion zone length (92) is between 45% and 80% of a diameter (90) of the focus tube fuel nozzle assembly (100); a second combustion zone (39) defined between the plurality of fuel injectors (60) and the aft frame (48), through which combustion gases (26) from the plurality of focus tube fuel nozzles (102, 104, 150, 200) and the plurality of fuel injectors (60) flow during a second portion of the total time, wherein a second combustion zone length (94) is defined along an axial centerline (47) of the combustor (14) between a forward end (70) of the first radial opening (62) and the aft frame (48), and the second combustion zone length (94) is 120% to 180% of a diameter (90) of the focus tube fuel nozzle assembly (100); wherein the second portion of the total time is between 30% and 50% of the total time. A combustor (14).

2. 2. The combustor of claim 1, further comprising an outer sleeve surrounding at least a portion of the combustion liner, the outer sleeve defining a second radial opening, the second radial opening aligned with the first radial opening, and a fuel injector of the plurality of fuel injectors extending through the first radial opening and the second radial opening.

3. 3. The combustor of claim 2, wherein the first radial opening of the combustion liner and the second radial opening of the outer sleeve are shaped as a geometric stadium having a major axis and a minor axis, the major axis being parallel to an axial centerline of the combustor.

4. The combustor (14) of any preceding claim, wherein the first combustion zone length (92) is between 50% and 70% of the diameter (90) of the focus tube fuel nozzle assembly (100).

5. The combustor (14) of any preceding claim, wherein the second combustion zone length (94) is between 130% and 180% of the diameter (90) of the focus tube fuel nozzle assembly (100).

6. 6. The combustor (14) of claim 1, wherein each focus tube fuel nozzle of the plurality of focus tube fuel nozzles (102, 104, 150, 200) comprises a fuel plenum body (202) comprising a forward wall (204), an aft wall (206), and an outer band (208), a fuel plenum (210) defined within the fuel plenum body (202), and a plurality of tubes (106) extending through the forward wall (204), the fuel plenum (210), and the aft wall (206).

7. 7. The combustor (14) of claim 1, wherein each tube (106) of each focus tube fuel nozzle of the plurality of focus tube fuel nozzles (102, 104, 150, 200) is configured to be parallel to one another and to an axial centerline (47) of the combustor (14), such that a fuel / air mixture discharged from a respective outlet (224) of each tube (106) has a laminar flow and moves generally axially relative to the axial centerline (47) of the combustor (14) to discharge a non-swirling laminar flow of the fuel / air mixture from the focus tube fuel nozzle assembly (100).

8. A gas turbine (10), comprising: A compressor (12); a turbine (16); A combustor (14) according to any one of claims 1 to 7, disposed downstream of the compressor (12) and upstream of the turbine (16); A gas turbine (10) comprising:

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