Compact turbomachine combustors
The combustor design with multiple combustion zones and fuel injection strategies addresses the challenge of high-temperature operation in gas turbines, optimizing combustion efficiency and reducing NOx emissions by minimizing peak temperature exposure.
Patent Information
- Application Number
- JP2021033822
- Authority / Receiving Office
- JP · JP
- Patent Type
- Applications
- Current Assignee / Owner
- Priority Date
- 2020-03-30
- Filing Date
- 2021-03-03
- Publication Date
- 2025-07-29
- Estimated Expiration
- 2041-03-03
AI Technical Summary
Existing combustion systems face challenges in maintaining high operating temperatures for optimal turbine performance while minimizing the time combustion gases spend at peak temperatures to reduce NOx emissions.
A combustor design with a tube bundle fuel nozzle assembly and swirler fuel nozzle assembly, featuring multiple combustion zones, where combustion gases pass through a first zone with minimal swirl and a second zone with increased fuel injection, optimizing the time spent at high temperatures.
The design reduces NOx emissions by minimizing the time combustion gases spend at high temperatures and enhancing combustion efficiency, achieving rapid combustion with reduced emissions across varying operating loads.
Smart Images
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Abstract
Description
Technical Field
[0001] The present disclosure generally relates to combustors. More specifically, the present disclosure relates to combustors for gas turbine engines.
Background Art
[0002] Turbo machines are used in various industrial applications for energy transfer purposes. For example, a gas turbine engine generally includes a compressor section, a combustion section, a turbine section, and an exhaust section. The compressor section gradually increases the pressure of the working fluid entering the gas turbine engine and supplies this compressed working fluid to the combustion section. and The compressed working fluid and and fuel (e.g., natural gas) are mixed within the combustion section and burned within the combustion chamber to generate high static head temperature combustion gases. The combustion gases flow from the combustion section to the turbine section, turbine section expand therein, and do work occur For example, the expansion of the combustion gases in the turbine section in can cause a load ( such as will emit an electric machine ) to connect rotate a rotor shaft and generate electricity. make Subsequently, the combustion gases are discharged from the gas turbine through the exhaust section.
[0003] In many known combustion systems, the mixed working fluid and and fuel are ignited in the upstream portion of the combustor, i.e., within the combustion chamber, to generate the operating turbine temperature. approximate In order to do optimal work within the turbine, ta it is necessary to occur maintain a very high operating temperature of the combustion gas from the combustion chamber to the outlet of the combustor. make However, since the formation of nitrogen oxides (NOx) is exponential with respect to temperature and linear with respect to time, maintaining a high operating temperature from the combustion zone to the combustor outlet is a challenge in manyknown Combustion system in Major contributing factor to emissions become .
[0004] Therefore, an improved combustor is desired in the art in . In particular, an improved combustor that optimally minimizes the amount of time that combustion gases spend at peak temperature is desired in the art in . SUMMARY OF THE INVENTION
[0005] Aspects and advantages of the present disclosure will become apparent from the following regarding the point description detailed which will be described in detail below, but the following detailed will be made Some may be self-evident, or throughout implement this Some may be acquirable .
[0006] In one embodiment in , a combustor make is provided make . The combustor includes an end cover that covers the front end of the combustor draw . The combustor is includes a combustion liner having an upstream end and and a downstream end also . The combustor further includes collect a tube bundle fuel nozzle assembly collect . The tube bundle fuel nozzle assembly fluidly couples to the end cover at the upstream end of the combustion liner and and extends to a plurality of outlets within a cap plate exist . The tube bundle fuel nozzle assembly includes a plurality of collect tube bundle fuel nozzles collect . The cap plate defines the diameter of the tube bundle fuel nozzle assembly draw . The combustor further includes a plurality of fuel injectors disposed upstream of a rear frame downstream of the plurality of tube bundle fuel nozzles and . The rear frame couples to the downstream end of the combustion liner collect . The combustion liner defines a combustion zone between the plurality of outlets and the rear frame and . The combustion zone is between the plurality of outlets and the plurality of fuel injectors are doing . draw a combustion zone where the combustion gas passes through and moves, which takes a total time defineddraw a first combustion zone formed a first combustion zone where the combustion gas from a plurality of converging tube fuel nozzles passes through and flows, which takes a first part of the total time is included. The combustion zone is located between a plurality of fuel injectors and a rear frame draw a second combustion zone formed a second combustion zone where the combustion gas from a plurality of converging tube fuel nozzles and a plurality of fuel injectors passes through and flows, which takes a second part of the total time is further included. The total time second portion is about 30% to about 50% of the total time
[0007] Another embodiment in a gas turbine make is provided make which includes a compressor, a turbine, and a combustor disposed downstream of the compressor and upstream of the turbine. The combustor includes an end cover that covers the front end of the combustor draw and also includes a combustion liner having an upstream end and and a downstream end. The combustor further includes collect a swirler fuel nozzle assembly collect The swirler 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 within a cap plate exist and includes a plurality of collect swirler fuel nozzles. The cap plate defines collect the diameter of the swirler fuel nozzle assembly draw The combustor is coupled to the combustion liner and further includes a plurality of fuel injectors disposed downstream of the plurality of collect swirler fuel nozzles and upstream of the rear frame. The rear frame is coupled to the downstream end of the combustion liner. The combustion liner defines a combustion zone between the plurality of outlets and the rear frame draw a combustion zone where the combustion gas passes through and moves, which takes a total time The combustion zone is located between the plurality of outlets and the plurality of fuel injectors draw a first combustion zone formed a first combustion zone where the combustion gas from a plurality of converging tube fuel nozzles passes through and flows, which takes a first part of the total time is included. The combustion zone is located between the plurality of fuel injectors and the rear frame draw a second combustion zone formed a second combustion zone where the combustion gas from a plurality of converging tube fuel nozzles and a plurality of fuel injectors passes through and flows, which takes a second part of the total time is further included. The total time second portion is about 30% to about 50% of the total time
[0008] Another embodiment in a method of operating a combustormake Provided make is. The method includes starting a tube fuel nozzle assembly within a combustion liner of a combustor. collect Combustion gas at a first temperature is generated within a first combustion zone length. The method further includes starting a fuel injector assembly downstream of the tube fuel nozzle assembly within the combustion liner of the combustor. As a result Combustion gas at a second temperature is generated within a second combustion zone length. The first combustion zone length is shorter than the second combustion zone length. collect As a result
[0009] This system and of the method the above-mentioned that other features, aspects and advantages regarding are described in the following detailed description and with reference to the claims by doing for understanding. can be deepened as follows. The accompanying drawings illustrate embodiments of the present disclosure is part of the content of of the present technology various and, in conjunction with the description, explain the principles of the present technology. while doing detailed of the invention is for .
[0010] this Combustor and Gas turbine Regarding this, in the following detailed description, with reference to the accompanying drawings, of this system and method manufacture and best for use fully disclose so that those skilled in the art can implement, including the form .
Brief Description of the Drawings
[0011]
Figure 1
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Figure 3
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DETAILED DESCRIPTION OF THE INVENTION
[0012] The following , this system and of the method various embodiment will be described in detail, and one or more embodiments thereof will be shown in the drawings . Each embodiment is not intended to limit the present technology, but is for illustration purposes. In fact, it will be apparent to those skilled in the art that various modifications and changes can be made to the present technology without departing from the technical scope and technical idea described in the claims. For example, the features exemplified or described as part of one embodiment can be used in combination with another embodiment to form yet another embodiment. Therefore, the present disclosure includes modifications and changes that fall within the scope of the appended claims and their equivalents.
[0013] In the detailed description of the invention, reference signs consisting of numbers and letters are used to refer to the features described in the drawings. In the drawings and the detailed description of the invention, like or similar reference signs denote like or similar members of the invention. In this specification, the terms "first", "second", and "third" are used interchangeably to distinguish one component from another and do not mean the position or importance of individual components.
[0014] As used herein, the terms "upstream" and "downstream" indicate the relative directions of fluid flow in a fluid 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 direction" refers to a relative direction substantially perpendicular to the axial centerline of a component, the term "axial direction" refers to a relative direction substantially parallel and / or coaxial to the axial centerline of a component, and the term "circumferential direction" refers to a relative direction around the axial centerline of a component.
[0015] In this specification, approximate terms such as "substantially", "about", and "essentially" include ±10% of the recited numerical value. When used with respect to an angle or direction, such terms include within ±10 degrees of the recited angle or direction. For example, "substantially vertical" includes directions within 10 degrees in any direction (e.g., clockwise or counterclockwise) from vertical.
[0016] The terms used in this specification are for the purpose of describing particular embodiments only and do not limit the disclosure. In this specification, even if described in the singular, it means including the plural case unless otherwise apparent from the context. In this specification, the terms "comprising" and / or "including" indicate the presence of the recited features, integers, steps, operations, components, and / or parts, and 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, FIG. 1 shows a schematic view of an exemplary gas turbine 10. The gas turbine 10 generally includes a compressor 12, at least one combustor 14 disposed downstream of the compressor 12, and a turbine 16 disposed downstream of the combustor 14. In addition, the gas turbine 10 may include a shaft 18 that couples the compressor 12 to the turbine 16. Above including By .
[0018] During operation, air 20 flows into the compressor 12 where the air 20 is gradually compressed By Compressed air Or The pressurized air 22 is supplied to the combustor 14 Supply Thereof. At least a part of the compressed air 22 is mixed with the fuel 24 in the combustor 14 and burned to generate combustion gas 26. The combustion gas 26 flows from the combustor 14 to the turbine 16, where (kinetic And / Or thermal) energy is transferred from the combustion gas 26 to the rotor blades (not shown) to rotate the shaft 18. The mechanical rotational energy is then used for various purposes such as driving the compressor 12 Of the drive feed And / Or power generation, etc. Can . The combustion gas 26 can then be exhausted from the gas turbine 10.
[0019] FIG. 2 is a cross-sectional side view of an exemplary combustor incorporating various embodiments of the present disclosure. As shown, the combustor 14 has an axial direction A, a radial direction R And circumference and a circumferential direction C Defining . Generally, the axial direction A extends parallel to the axial center line 47 of the combustor 14 Exist , the radial direction R extends substantially perpendicular to the axial center line 47 Exist , Circumference and the circumferential direction C extends substantially concentrically around the axial center line 47 Exist . As shown in FIG. 2, the combustor 14 may be at least partially surrounded by an outer casing 28 such as a compressor discharge casing By . The outer casing 28 can at least partially surround a high-pressure plenum 30 that at least partially surrounds various components of the combustor 14 Component . The high-pressure plenum 30 is in fluid communication with the compressor 12 (FIG. 1) and can receive a portion of the compressed air 22 therefrom. An end cover 32 is coupled to the outer casing 28 Defining . Can .
[0020] Collect A bundled-tube fuel nozzle assembly 100 extends axially downstream from the end cover 32 Can exist . Collect The swirler fuel nozzle assembly 100 is disposed within an outer casing 28 that is axially spaced from the end cover 32, upstream of the first combustion zone 38, and downstream of the axis 47 of the combustor 14. And / Or and is axially spaced from the end cover 32. In certain embodiments, the fuel nozzle assembly 100 is in fluid communication with a fuel source 51 via a fluid conduit 49. In certain embodiments, the fluid conduit 49 is fluidly coupled to the inner surface 33 of the end cover 32. Do to obtain. In certain embodiments, the fuel nozzle assembly 100 is configured to provide a first mixture of fuel 24 and compressed air 22 to the first combustion zone 38 for ignition. Above A combustion liner duct 36 can at least partially define the first combustion zone 38 downstream of the swirler fuel nozzle 34 and can at least partially define a hot gas path 40 through the combustor 14 for directing combustion gases 26 (FIG. 1) toward the inlet 42 of the turbine 16. In certain embodiments, the combustion liner 36 can be formed from a single body having a forward end 44 upstream of the combustion liner 36 and is substantially cylindrical. The combustion liner 36 can then transition to a non-circular, substantially rectangular cross-sectional shape proximate the rearward end 46 of the combustion liner 36. And / Or connection Can . Collect The swirler fuel nozzle assembly 100 can be configured to provide a first mixture of fuel 24 and compressed air 22 to the first combustion zone 38 for ignition.
[0021] 1 Above of the combustion liner Or duct 36 is 1 Above of Collect at least partially defining the first combustion chamber Or zone 38 downstream of the swirler fuel nozzle 34 and can / Defining and at least partially define a hot gas path 40 through the combustor 14 for directing combustion gases 26 (FIG. 1) toward the inlet 42 of the turbine 16. In certain embodiments, the combustion liner 36 can be formed from a single body having a forward end 44 upstream of the combustion liner 36 and is substantially cylindrical. The combustion liner 36 can then transition to a non-circular, substantially rectangular cross-sectional shape proximate the rearward end 46 of the combustion liner 36. Or In certain embodiments, the rearward end 46 of the combustion liner 36 can terminate at a rearward frame 48. The rearward frame 48 secures the combustion liner 36 to the outer casing 28. Defining In certain embodiments, the combustion liner 36 can be formed from a single body having a forward end 44 upstream of the combustion liner 36 and is substantially cylindrical. The combustion liner 36 can then transition to a non-circular, substantially rectangular cross-sectional shape proximate the rearward end 46 of the combustion liner 36. Or forward end 44 and is substantially cylindrical. The combustion liner 36 can then transition to a non-circular, substantially rectangular cross-sectional shape proximate the rearward end 46 of the combustion liner 36. Or from a single body and is substantially cylindrical. Or round. The combustion liner 36 can then transition to a non-circular, substantially rectangular cross-sectional shape proximate the rearward end 46 of the combustion liner 36. Or non-circular Or proximate the rearward end 46 of the combustion liner 36.
[0022] In certain embodiments, the rearward end 46 of the combustion liner 36 can terminate at a rearward frame 48. The rearward frame 48 secures the combustion liner 36 to the outer casing 28. Or It can be used for attachment to other support hardware, thereby fixing the rear end portion 46 of the combustion liner 36 Or Axially restrain. Thus, as the front end portion 44 of the combustion liner 36 moves through various thermal conditions associated with different operating modes of the combustor 14, Collect Axially expand towards the swirler fuel nozzle assembly 100 And And contract.
[0023] In certain embodiments, the combustion liner 36 is at least partially Circumference Surrounded in the direction by the outer sleeve 50. The outer sleeve 50 is formed as a single Component Formed as May be, or a flow sleeve and Formed by a plurality of sleeve segments, such as by an impingement sleeve (not shown separately) May be . The impingement sleeve can Flow sleeve Engage slidably with them, allowing axial relative movement therebetween. Or , the outer sleeve 50 Flow sleeve With the impingement sleeve being axially To Integrated with each other Do To form an integral body ( Or , a "unisleeve") By May also have. The outer sleeve 50 is disposed radially spaced from the combustion liner 36, with a cooling flow annulus 56 therebetween Defining Obtained.
[0024] As shown in FIG. 2, in many embodiments, the cooling flow annulus 56 can fluidly couple the high pressure plenum Collect To the swirler fuel nozzle assembly 100. For example, the outer sleeve 50 can have a plurality of inlet Or Holes (not shown) providing fluid communication from the high pressure plenum 30 to the cooling flow annulus 56 Defining . Alternatively Or Additionally, the outer sleeve 50 can include an inlet 57 located at the rear end of the combustor 14 that fluidly couples the cooling flow annulus 56 to the high pressure plenum 30 By May also.
[0025] In many embodiments, compressed air 22 from the high-pressure plenum 30 can flow upstream through the cooling flow annulus 56 to the head-end portion of the combustor 14 Or to the volume portion 34. Within the head-end volume portion 34, the compressed air 22 can reverse direction and Collect move downstream through the tube bundle fuel nozzle assembly 100, where fuel 24 is introduced and a first mixture of fuel 24 and compressed air 22 is provided to the combustion zone 38. The head-end portion 34 can be positioned between the end cover 32 and the plurality of Collect tube bundle fuel nozzles 100 and Collect can provide compressed air 22 to the tube bundle fuel nozzle assembly 100.
[0026] In certain embodiments, the outer sleeve 50 may not be axially substantially constrained relative to the axial centerline 47 of the combustor 14. Thus, the outer sleeve 50 can expand and contract axially towards one Or tube bundle fuel nozzle 34 and Above of Collect towards the rear frame 48 as the combustor 14 transitions through various thermal conditions. And / Or axially towards the rear frame 48 And and contract.
[0027] In various embodiments In , as shown in FIG. 2, the combustor 14 includes at least one fuel injector 60 that is axially offset from the tube bundle fuel nozzle assembly 100 and Collect is disposed downstream of the tube bundle fuel nozzle assembly 100. The fuel injector 60 radially extends at least partially through the combustion liner 36 and Are present , Collect through the outer sleeve 50, the cooling flow path 56. And In certain embodiments, the combustor 14 includes a plurality of fuel injectors 60 that are annularly disposed around the combustion liner 36 Can exist around the outer sleeve 50. Each fuel injector 60 is along the periphery of the outer sleeve 50 And and Circumference Spaced apart in a direction Can .
[0028] The plurality of fuel injectors 60 can be configured to provide a second mixture of fuel 24 and compressed air 22 to the second combustion zone 39 for ignition. The combustion gas 26 generated by the fuel injectors 60 within the second combustion zone 39 can be mixed with the combustion gas 26 of the first combustion zone 38 and can have a higher temperature than the first combustion zone 38. The second combustion zone 39 is Collect a bundled tube fuel nozzle 34 And / Or within the combustion liner 36 downstream of the first combustion zone 38 Defining obtained. In some embodiments, the second combustion zone 39 is between the first combustion zone 38 and the rear frame 48 Can define . In many embodiments, the second combustion zone 39 is immediately downstream of the first combustion zone 38 Defining obtained.
[0029] Each fuel injector 60 can have an outlet substantially shaped as a geometric stadium, i.e., a rectangle having circular ends facing each other. This shape advantageously allows each fuel injector to extend radially through the cooling flow annulus 56 without blocking most of the compressed air 22 moving axially through the cooling flow annulus 56 Exist .
[0030] Figure 3 And In many embodiments as shown in Figure 4, the combustor 14 can include a first radially opening 62 and a second radially opening 64. The combustion liner 36 Collect can have the first radially opening 62 downstream of the bundled tube fuel nozzle assembly 100 Defining , and the outer sleeve 50 can have the second radially opening 64 Defining . The first radially opening 62 and The second radially opening 64 can be aligned with each other in both the radial direction R and the axial direction A with as well.
[0031] In addition, the first radial opening 62 and The second radial openings 64 may be of equal size, with each opening 62, 64 being 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. with 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. with 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. approximate 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 possible .
[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 drawable Similarly, the rear end 72 is and The downstream most portions of the second radial openings 62, 64, respectively drawable 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. possible .
[0033] Figure 5 and FIG. 6 shows a view of the combustor 14 looking upstream from the aft end. collect 1 is a plan view of an embodiment of a bundle-tube fuel nozzle assembly 100. As shown, collectThe bundled-tube fuel nozzle assembly 100 can include a plurality of outer nozzles 104 annularly arranged around a central fuel nozzle 102.
[0034] As shown in FIG. 5, the central nozzle 102 and Each outer nozzle 104 can be round or or circular. The plurality of outer nozzles 104 are arranged around the central fuel nozzle 102 within a cap plate parallel to the end cover 32. Each fuel nozzle 102, 104 can be a bundled-tube fuel nozzle. The plurality of tubes 106 can be parallel non-concentric mixing tubes extending through a fuel plenum towards a first combustion zone 38. Each of the plurality of tubes 106 can be parallel to the axial centerline 47 of the combustor 14. The cap plate can include a plurality of cooling holes to facilitate cooling of the cap plate. collect The bundled-tube fuel nozzle. The plurality of tubes 106 extend exist parallel non-concentric mixing tubes extending through a fuel plenum towards a first combustion zone 38. Each of the plurality of tubes 106 can be parallel to the axial centerline 47 approximate of the combustor 14. The cap plate can include a plurality of cooling holes to facilitate cooling of the cap plate.
[0035] As shown in FIG. 6, the central fuel nozzle 102 can be surrounded by a plurality of outer nozzles 150. Each fuel nozzle 102, 150 can include a unique rear plate that collectively forms a downstream cap plate, draw and a single cap plate (not shown) extends to cover the downstream ends of the tubes 106 at each fuel nozzle 102, 104. or Each outer nozzle 150 is positioned adjacent to the central fuel nozzle 102 and has a truncated wedge shape so as to be able to cover most of the head end area. The truncated wedge shape is defined as having a pair of radial sides 154 that extend in opposite directions and are joined by a first (radially inner) arcuate side 156 possible and a second (radially outer) arcuate side 158. The radially outer side 158 forms the exist collective radially outer perimeter of the head end of the fuel nozzle segment 150 and and has a diameter 90 do as defined. and collectively covering the radially outer perimeter of the head end [[ID=3(]]or of the fuel nozzle segment 150 draw and having a diameter 90.
[0036] FIG. (FIG. 5 andthe specific sizes, spacings, in the plurality of tubes 106 (including FIG. 6) and The numbers are collect intended to be merely examples of the clustered tube fuel nozzles 102, 104, 150, and should not be construed to limit the or clustered tube fuel nozzles to having a specific number of tubes. Further, the collect clustered tube fuel nozzles should not be construed to be limited to having tubes of a single tube diameter. collect
[0037] FIG. 7 provides a partial cross-sectional side view of a single related clustered tube fuel nozzle 200 in the exemplary fuel nozzle assembly 100 shown in FIG. 2. Various embodiments of the combustor 14 can 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. collect
[0038] In at least one embodiment, as shown in FIG. 7, the fuel nozzle 200 includes a fuel plenum body 202 having a forward or upstream plate 204, a rear plate 206 axially spaced from the forward plate 204, and an outer band exist shroud 208 extending axially between the forward plate 204 and the rear plate 206. A fuel plenum 210 or is disposed within the fuel plenum body 202. In certain embodiments, the forward plate 204, the rear plate 206, is and the outer band 208 can at least partially draw enclose the fuel plenum 210. In certain embodiments, the fluid conduit 49 extends through the forward plate 204 and and can provide fuel 24 to the fuel plenum 210. In various embodiments draw exist in, the fuel nozzle assembly 200 includes a cap plate 212 axially spaced from the rear plate 206. The hot side surface 214 of the cap plate 212 is generally adjacent to the first combustion zone 38 or and is disposed in close proximity. The cap plate 212 may be unique to each fuel nozzle assembly 200 exist , or or may be common to all fuel nozzle assemblies 200.
[0039] As shown in FIG. 7, the fuel nozzle assembly 200 can include a tube bundle 216 having a plurality of tubes 106. Each tube 106 passes through the front plate 204, the fuel plenum 210, the rear plate 206, and and the cap plate 212. possible The tubes 106 are fixedly connected to the rear plate 206 and / or form a seal with respect to the rear plate 206. For example, the tube 218 can be welded, brazed, or or otherwise connected to the rear plate 206. Each tube 106 has that an inlet 220 provided at the upstream end 222 of each respective tube 106 draw and an outlet 224 provided at the downstream end 226 of each respective tube 106. Each tube 106 defines a respective premixed flow path 228 through the fuel nozzle 200. that In a particular embodiment, one draw of the plurality of tubes 106 is in fluid communication with the fuel plenum 210 via one draw fuel port 230 provided within each respective tube 106. above draw above
[0040] and and exist As shown in FIG. 8, the jacket portion 74 can have the same cross-sectional shape as the first radial opening 62 and and the second radial opening 64. In many embodiments, the jacket portion 74 extends through the first radial opening 62 and and the second radial opening 64 to form a passage for the outlet member of the fuel injector 60 to pass through. exist through withThis is also possible. For example, the jacket portion 74 can have a geometric stadium cross-sectional area, i.e., a rectangle with circular ends. It extends to the liner 36 through the outer sleeve 50 exist The jacket portion 78 that extends through the outer sleeve 50 to the liner 36 impedes the flow of compressed air through the annulus 56 (FIG. 2) between the liner 36 and the outer sleeve 50. The geometric stadium shape of the jacket portion 78 reduces the blockage in the annulus 56 compared to, for example, a jacket portion having a round shape. Thus, the jacket portion 78 advantageously enables the fuel / air mixture to be introduced by the fuel injector 60 in the second combustion zone 39. The outlet member of the fuel injector 60 extends through the jacket portion 74 exist and thereby forms the second radial opening 64 and extending through the first radial opening possible 62. In many embodiments, the fuel injector 60 can include an air passage 102. The air passage 102 can fluidly couple the fuel injector 60 to the high-pressure plenum 30 and and the second combustion zone 39 (FIG. 2).
[0041] Here, referring again to FIGS. 2-4 that provide different views of the combustor 14 of one above embodiment of the present disclosure. As shown, in some embodiments, the rear end of the fuel nozzle assembly 100 can be perpendicular to the axial centerline 47 of the combustor 14 and have a diameter 90 related In other embodiments, the diameter 90 can be the inner diameter of the combustion liner 36 provided at the rear end of the fuel nozzle assembly draw Specifically, the diameter 90 can be the inner diameter of the combustion liner measured at the outlet 224 of the multi-tube fuel nozzle assembly 100 draw As shown in FIGS. 2-4, the axial centerline 47 of the combustor 14 can be substantially curved collect and bow-shaped, and can include a first portion 47a and a second portion 47b
[0042] as shown in FIGS. 2-4, the axial centerline 47 of the combustor 14 can be substantially curved or and bow-shaped, and can include a first portion 47a and a second portion 47b withThis is also acceptable. The high-temperature gas path 40 may flow along the axial centerline of the combustor 14 and may be aligned with the axial centerline. The second portion 47b may be parallel to the axial centerline of the gas turbine 10 when the combustion gas 26 is discharged from the rear end 46 of the combustor 14. approximate It may be parallel.
[0043] Figure 3 and As shown in Figure 4, in some embodiments, the combustor 14 may also include 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 may be obtained along the first portion 47a of the axial centerline 47. In many embodiments, the first combustion zone length 92 may be between the outlet 224 of the bundled-tube fuel nozzle assembly 100 and the front end 70 of the first radial opening 62. The first combustion zone length 92 may be the distance that the mixture of fuel 24 and compressed air 22 discharged from the bundled-tube fuel nozzle assembly 100 travels before reaching the second combustion zone 39. draw In many embodiments, the first combustion zone length 92 collect can be between the outlet 224 of the bundled-tube fuel nozzle assembly 100 and the front end 70 of the first radial opening 62. draw The first combustion zone length 92 collect can be the distance that the mixture of fuel 24 and compressed air 22 discharged from the bundled-tube fuel nozzle assembly 100 travels before reaching the second combustion zone 39.
[0044] The second combustion zone length 94 may be obtained downstream of the first combustion zone 38. In many embodiments, the second combustion zone length 94 may be along the axial centerline 47 of the combustor 14 and can be between the front end 70 of the first radial opening 62 and the rear frame 48. draw In many embodiments, the second combustion zone length 94 may be along the axial centerline 47 of the combustor 14 and can be between the front end 70 of the first radial opening 62 and the rear frame 48. draw It can be. or The second combustion zone length 94 can be between the front end 70 of the second radial opening 64 and the rear frame 48. drawable The second combustion zone length 94 can be the distance that the combustion gas 26 generated by the air 22 introduced by the fuel injector 60 and the fuel 24 travels within the combustion liner 36 before reaching the turbine 16. and The second combustion zone length 94 can be the distance that the combustion gas 26 generated by the air 22 introduced by the fuel injector 60 and the fuel 24 travels 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 collectBetween the outlet 224 of the swirler fuel nozzle assembly 100 and the aft frame 48 draw This can be done. In many embodiments, the total combustion zone length 96 can 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 can be along the axial centerline 47 of the combustor 14 draw This can be done, and in many embodiments, the overall length 98 can be between the end cover 32 and the aft frame 48 draw Specifically, the overall length 600 can be between the inner surface 33 of the end cover 32 and the aft frame 48 draw Obtainable. The overall length 98 of the combustor 14 can be along the axial centerline 47 draw Since this can be done, the overall length 98 can be along a curve as shown in FIG. 3 draw This can be done and can be measured accordingly.
[0047] Together with a plurality of fuel injectors 60 collect By utilizing the swirler fuel nozzle assembly 100, advantageously, an optimally minimized first combustion zone length 92 and Can enable a second combustion zone length 94. Each collect Each tube 106 within the swirler fuel nozzle 200 can be substantially parallel to each other and can be parallel to the axial centerline 47 of the combustor 14, so collect The swirler 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 discharged from each respective outlet 224 of the plurality of tubes 106 can move axially without bulk swirl and can move axially with respect to the axial centerline 47 of the combustor 14 approximate Axially. In many embodiments collect The fuel / air mixture discharged from the swirler fuel nozzle assembly can have a uniform velocity, fuel-air ratio and Temperature, and as a result, can result in less NOx generation. collectThe non-swirl flow of the fuel / air mixture discharged from the multi-tube fuel nozzle assembly 100 advantageously allows for a rapid combustion time within the first combustion zone 38. Further, the relatively small diameter of each tube 106 results in a correspondingly small and relatively short flame length. Accordingly, the first combustion zone length 92 is reduced compared to a head end having a conventional swirl fuel nozzle ("swirler"). or It can be compacted, thereby reducing the amount of time the combustion gases 26 spend at high temperatures within the combustor 14, and consequently significantly reducing the overall nitrogen oxide (NOx) emissions. For example, in some embodiments, the ratio of the first combustion zone length 92 to the diameter 90 can be optimally minimized to reduce the overall nitrogen oxide (NOx) emissions. In some embodiments, the first combustion zone length 92 and The diameter 90 is primary collect Operation of the multi-tube fuel nozzle alone (partial load), and Over a range of operating loads including operation of both the primary and secondary combustion stages (high load), emission reduction Can be optimized for.
[0048] In some embodiments, the first combustion zone length 92 may be from about 45% to about 80% of the diameter 90. In many embodiments, the first combustion zone length 92 may be from about 50% to about 70% of the diameter 90. In various embodiments in , the first combustion zone length 92 may be from about 50% to 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 the base load NOx emissions that are as small as possible to minimize NOx, but large enough to completely combust the fuel 24. do Obtained.
[0050] For example, in some embodiments, the second combustion zone length 94 is collectThe 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 collect The diameter 90 of the bundle-tube fuel nozzle assembly 100 may be between about 130% and about 180%. in , the second combustion zone length 94 is collect 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. above 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: collect The method may include step 302 of starting the bundle-tube fuel nozzle assembly 100. as a result The combustion gases 26 at the first temperature are generated within the first combustion zone length 92. do In many embodiments, collect 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: collect The method may include step 304 of activating a fuel injector 60 downstream of the bundle-tube fuel nozzle assembly 100. as a result The combustion gases 26 at the second temperature are generated within the second combustion zone length 94. do 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] As shown in FIG. 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), method 300 may also include providing combustion gas 26 at a second temperature to turbine 16 downstream of combustor 14, and the combustion gas 26 burn moves from combustor 14 to turbine 16 it takes a certain amount of time . Additionally, in some embodiments, the total time may include a first portion of the total time at the first combustion zone length 92 and a second portion of the total time at the second combustion zone length 94. In many embodiments, the second portion of the total time may be from about 30% to about 50% of the total time . In other embodiments, the second portion of the total time may be from about 35% to about 45% of the total time .
[0054] By utilizing the multi-tube fuel nozzle assembly 100 together with the plurality of fuel injectors 60, advantageously, the time that the combustion gas 26 spends within the combustion zone can be optimally minimized. For example, each tube 106 within each multi-tube fuel nozzle 200 can be substantially parallel to each other and parallel to the axial centerline 47 of the combustor 14, such that collect the multi-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 discharged from each respective outlet 224 of the plurality of tubes 106 can have a laminar flow and move axially with respect to the axial centerline 47 of the combustor 14 is . collect . collect The non-swirl approximate laminar flow of the fuel / air mixture discharged from the multi-tube fuel nozzle assembly 100 advantageously enables a rapid combustion time within the first combustion zone 38. Thus, the first combustion zone length 92 is shortened collect . formula . orIt can be compacted, thereby reducing the amount of time the combustion gas 26 spends at high temperatures in the combustor 14 and significantly reducing the overall nitrogen oxide (NOx) emissions.
[0055] In addition, collect more fuel is introduced through a plurality of fuel injectors downstream of the swirler fuel nozzle assembly 100 and By introducing air, the overall mass flow rate of the combustion gas 26 flowing through the second combustion zone 39 increases. This increase in mass flow rate results in an increase in the overall velocity of the combustion gas moving through the second combustion zone, thereby enabling the combustion gas to accelerate rapidly through the second combustion zone length 94. By minimizing the amount of time the combustion gas spends at the peak temperature, advantageously, a significant reduction in the overall nitrogen oxide (NOx) emissions is achieved.
[0056] This specification in is the present invention the best form including has been disclosed by way of example in order to enable those skilled in the art to make and use the apparatus or system and practice the method, and to enable them to carry out the present invention . The patent having the property scope of the present invention is defined by the claims, and other examples that are obvious to those skilled in the art are also included. Such other examples belong to the technical scope described in the claims if they have components that do not differ in language from the claims, or if they have equivalent components that have only non-essential differences from the language of the claims .
Explanation of Reference Numerals
[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 surface 34 collect Swirler fuel nozzle, head end portion, volume portion 36 Combustion liner, duct 38 First combustion zone 39 Second combustion zone 40 High-temperature gas path 42 Inlet 44 Front End, Upstream End 46 Rear End, Downstream End 47 Axial Centerline 47a First Portion 47b Second Portion 48 Rear Frame 49 Fluid Conduit 50 Outer Sleeve 51 Fuel Supply Source 56 Cooling Flow Annulus, Cooling Flow Path 57 Inlet 60 Fuel Injector 62 First Radial Opening 64 Second Radial Opening 66 Major Axis 68 Minor Axis 70 Front End 72 Rear End 74 Jacket Portion 78 Jacket Portion 80 Diameter 90 Diameter 92 First Combustion Zone Length 94 Second Combustion Zone Length 96 Total Combustion Zone Length 98 Total Combustor Length, Overall Length 100 collect Bundled Tube Fuel Nozzle Assembly 102 Central Fuel Nozzle, collect Bundled Tube Fuel Nozzle, Air Passage 104 Outer Nozzle, collect Bundled Tube Fuel Nozzle 106 Tube 150 Outer Nozzle, Fuel Nozzle Segment, collect Bundled Tube Fuel Nozzle 154 Radial Side 156 First (Radially Inner) Bowed Side 158 Second (Radially Outer) Bowed Side 200 Single collect Bundled Tube Fuel Nozzle, Fuel Nozzle Assembly 202 Fuel Plenum Body 204 Front orUpstream plate, front wall 206 Rear plate, rear wall 208 Outer band, shroud 210 Fuel plenum 212 Cap plate 214 High-temperature side 216 Tube bundle 218 Tube 220 Inlet 222 Upstream end 224 Outlet 226 Downstream end 228 Premixing flow path 230 Fuel port 300 Method
Claims
1. A combustor (14), 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 bundle-tube fuel nozzle assembly (100) fluidly coupled to the end cover (32) at the upstream end (44) of the combustion liner (36) and including a plurality of bundle-tube fuel nozzles extending to a plurality of outlets (224) in a cap plate (212), the cap plate (212) defining a diameter (90) of the bundle-tube fuel nozzle assembly (100); a plurality of fuel injectors (60) coupled to the combustion liner (36) and positioned downstream of the plurality of bundle-tube fuel nozzles and upstream of an aft frame (48), the aft frame (48) including a plurality of fuel injectors (60) coupled to the downstream end (46) of the combustion liner (36); Equipped with The combustion liner (36) defines a combustion zone between the plurality of outlets (224) and the aft frame (48) through which the combustion gases (26) travel over an entire period of time, 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 bundle-tube fuel nozzles flow during a first portion of the total time period; 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 bundle-tube fuel nozzles and the plurality of fuel injectors (60) flow during a second portion of the total period; Equipped with the second portion of the total period is between about 30% and about 50% of the total period; Combustor (14).
2. 2. The combustor of claim 1, further comprising an outer sleeve surrounding at least a portion of the combustion liner, the combustion liner defining a first radial opening downstream of the plurality of bundle-tube fuel nozzles, the outer sleeve defining a 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. 4. The combustor (14) of claim 2, wherein a first combustion zone length (92) is defined between the plurality of outlets (224) and the first radial opening (62), and a second combustion zone length (94) is defined between the first radial opening (62) and the aft frame (48).
5. The combustor (14) of claim 4, wherein the first combustion zone length (92) is between about 45% and about 75% of the diameter (90) of the bundle-tube fuel nozzle assembly (100).
6. 6. The combustor (14) of claim 4, wherein the second combustion zone length (94) is between about 120% and about 180% of the diameter (90) of the bundle-tube fuel nozzle assembly (100).
7. 7. The combustor (14) of claim 1, wherein each bundle-tube fuel nozzle of the plurality of bundle-tube fuel nozzles 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).
8. A gas turbine (10), comprising: A compressor (12); a turbine (16); a combustor (14) disposed downstream of the compressor (12) and upstream of the turbine (16), 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 bundle-tube fuel nozzle assembly (100) fluidly coupled to the end cover (32) at the upstream end (44) of the combustion liner (36) and including a plurality of bundle-tube fuel nozzles extending to a plurality of outlets (224) in a cap plate (212), the cap plate (212) defining a diameter (90) of the bundle-tube fuel nozzle assembly (100); a plurality of fuel injectors (60) coupled to the combustion liner (36) and positioned downstream of the plurality of bundle-tube fuel nozzles and upstream of an aft frame (48), the aft frame (48) including a plurality of fuel injectors (60) coupled to the downstream end (46) of the combustion liner (36); Equipped with The combustion liner (36) defines a combustion zone between the plurality of outlets (224) and the aft frame (48) through which the combustion gases (26) travel over an entire period of time, 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 bundle-tube fuel nozzles flow during a first portion of the total time period; 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 bundle-tube fuel nozzles and the plurality of fuel injectors (60) flow during a second portion of the total period; Equipped with the second portion of the total period is between about 30% and about 50% of the total period; Gas turbine (10).
9. 9. The gas turbine of claim 8, further comprising an outer sleeve surrounding at least a portion of the combustion liner, the combustion liner defining a first radial opening downstream of the plurality of bundle-tube fuel nozzles, the outer sleeve defining a 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.
10. 10. The gas turbine of claim 9, 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.
11. 11. The gas turbine (10) of claim 9, wherein a first combustion zone length (92) is defined between the plurality of outlets (224) and the first radial opening (62), and a second combustion zone length (94) is defined between the first radial opening (62) and the aft frame (48).
12. 12. The gas turbine (10) of claim 11, wherein the first combustion zone length (92) is between about 45% and about 75% of the diameter (90) of the bundle-tube fuel nozzle assembly (100).
13. 13. The gas turbine (10) of claim 11, wherein the second combustion zone length (94) is between about 120% and about 180% of the diameter (90) of the bundle-tube fuel nozzle assembly (100).