DE102014103083A1 - System and method for air conditioning at pipe level - Google Patents

Abstract

One system includes a multi-tube fuel nozzle. The multi-tube fuel nozzle contains several tubes. Each tube has a first end, a second end, and an annular wall disposed about a central passage. The first end is configured for placement around a fuel injector. Each tube also includes an air conditioning device having a plurality of air ports located adjacent the first end. The multiple air passage openings run through the wall into the central passage.

Description

GENERAL PRIOR ART

 The subject matter disclosed herein relates to pipe level air conditioning for turbine systems.

 Gas turbine systems generally include one or more combustors that burn a mixture of compressed air and fuel to produce hot combustion gases. Unfortunately, existing combustors may receive fuel and air at pressures and / or volumetric flows that vary due to various limitations of the combustors, fuel nozzles, and associated equipment. These variations in air and fuel can promote or cause fluctuations in the ratio of fuel to air, thereby increasing the chances of flame arrest, flashback, and / or increased emissions (e.g., oxides of nitrogen). Conventional systems may also be slower to achieve mixing, thereby reducing overall system efficiency. There is therefore a need for a system that can achieve faster and more uniform fuel-air mixing while at the same time being durable and easy to maintain.

BRIEF SUMMARY OF THE INVENTION

 Hereinafter, certain embodiments are summarized, the scope of which corresponds to the originally claimed invention. It is not intended that these embodiments limit the scope of the claimed invention, but rather these embodiments are intended to provide only a brief summary of possible forms of the invention. Indeed, the invention may encompass several different forms, which may be similar or different from the embodiments set forth below.

 According to a first embodiment, a system includes a multi-tube fuel nozzle. The multi-tube fuel nozzle includes several tubes. Each tube has a first end, a second end, and an annular wall disposed about a central passage. The first end is configured to be arranged around a fuel injector. Each tube also includes an air conditioning device having a plurality of air passage openings disposed adjacent to the first end. The plurality of air passage openings extend through the wall into the central passage.

 The plurality of air passage openings of the system may be circumferentially arranged around the annular wall.

 The plurality of air passage openings of any of the aforementioned systems may include a first set of air passage openings and a second set of air passage openings, the second set of air passage openings being located downstream of the first set of air passage openings relative to the first end.

 A first overall cross section of each air passage opening of the first set of air passage openings of a system mentioned above may be larger than a second total cross section of each air passage opening of the second set of air passage openings.

 The first set of air passage openings of any of the aforementioned systems may include a first row and a second row of air passage openings circumferentially disposed around the annular wall, and the first row of air passage openings offset in a circumferential direction from the second row of air passage openings.

 The second set of air passage openings of any of the aforementioned systems may include a third row and a fourth row of air passage openings arranged circumferentially around the annular wall, and the third row of air passage openings is offset in the circumferential direction from the fourth row of air passage openings.

 The first set of air passages of any of the aforementioned systems may be configured to direct the airflow in a radial direction into the central passageway.

 The second set of air passages of any of the aforementioned systems may be configured to guide the air with a swirling motion about a central axis of the central passage.

 The plurality of air vents of any of the aforementioned systems may have multiple sizes, shapes, angles, spacings, or any combination thereof.

 Each tube of the plurality of tubes of any of the aforementioned systems may be configured to obtain an equal distribution of air flow over the air conditioning device.

 The system of any type mentioned above may include a gas turbine or combustor with the multi-tube fuel nozzle.

According to a second embodiment, a system includes a Combustor end cover assembly and a multi-tube fuel nozzle coupled to the combustion chamber end cover assembly. The multi-tube fuel nozzle includes a retainer plate and a plurality of tubes disposed between the end cover assembly and the retainer plate. Each tube includes a first end adjacent the end cover assembly, a second end adjacent to the support plate, and an annular wall disposed about a central passage. The first end is configured to be arranged around a fuel injector. Each tube also includes an air conditioning device having a plurality of air passage openings disposed adjacent to the first end. The plurality of air passage openings extend through the wall into the central passage.

 Each tube of the plurality of tubes of any of the aforementioned systems may be configured to be individually removed from or interposed between the end cover assembly and the retainer plate.

 The retainer plate of any of the aforementioned systems may be configured to be removable from the multi-tube fuel nozzle after removal of the end cover assembly by sliding the retainer plate on the plurality of tubes from the first end to the second end of each tube.

 The plurality of air passage openings of any of the above-mentioned systems may be circumferentially arranged around the annular wall.

 The plurality of air passage openings of any of the aforementioned systems may include a first set of air passage openings and a second set of air passage openings, the second set of air passage openings being downstream of the first set of air passage openings relative to the first end.

 A first overall cross section of each air passage opening of the first set of air passage openings of any of the above-mentioned systems may be larger than a second total cross section of each air passage opening of the second set of air passage openings.

 The first set of air passages of any of the aforementioned systems may be configured to direct the airflow in a radial direction into the central passageway.

 The second set of orifices of any of the aforementioned systems may be configured to direct the air with a swirling motion about a central axis of the central passage.

 According to a third embodiment, a method of removing pipes from a multi-tube fuel nozzle includes removing the multi-tube fuel nozzle having a plurality of tubes disposed between a retainer plate and an end cover from a gas turbine. Each tube includes a first end disposed adjacent to the end cap and about a fuel injector, a second end disposed adjacent the plate, and an annular wall disposed about a central passage. The method also includes removing the end cap from the multi-tube fuel nozzle, removing the retainer plate from the multi-tube fuel nozzle by sliding the retainer plate along the plurality of tubes from the second end to the first end of each tube, and removing at least one tube from the multi-tube fuel nozzle.

 Accordingly, the system may include: a combustion chamber end cap assembly, a multi-tube fuel nozzle coupled to the combustor end cap assembly, comprising: a retainer plate and a tube disposed between the end cap assembly and the retainer plate, the tube having a first end adjacent the end cap assembly a second end adjacent the support plate, an annular wall disposed about a central passage, the first end configured to be disposed about a fuel injector, and an air conditioning device having a plurality of air passage openings disposed adjacent to the first end, the plurality of air passage openings through the wall into the central passage.

BRIEF DESCRIPTION OF THE DRAWINGS

 These and other features, aspects, and advantages of the present invention will become more apparent upon reading the following detailed description with reference to the accompanying drawings in which like reference characters represent like parts throughout the drawings. It shows:

1 10 is a block diagram of one embodiment of a gas turbine system having a multi-tube fuel nozzle within a combustor, with the tubes configured for uniform air distribution.

2 a cutaway side view of the embodiment of a gas turbine system of 1 .

3 a cut-away side view of an embodiment of the combustion chamber of 2 within the line 3-3, the one Multi-tube fuel nozzle coupled to an end cover assembly of the combustion chamber,

4 an exploded perspective view of the multi-tube fuel nozzle and end cover assembly according to 3 .

5 a side view, partially in cross section, of the combustion chamber of 3 illustrating multiple tubes and fuel injectors of the multi-tube fuel nozzle,

6 a side cross-sectional view of an embodiment of the first and second ends of a single tube and respective fuel injector of the multi-tube fuel nozzle of 5 .

7 3 is a perspective view of an embodiment of a single mixing tube illustrating an air conditioning device with air passage openings in the mixing tube,

8th a partial perspective view of an embodiment of the mixing tube of 7 within line 8-8, which illustrates details of an air conditioner having air passage openings at the first end of the mixing tube,

9 a partial side view of an embodiment of the first end of the mixing tube of 7 , which illustrates an air conditioning device with air passage openings,

10 a cross-sectional view of an embodiment of the mixing tube of 9 along line 10-10 through air passage openings of the air conditioning device,

11 a side cross-sectional view of an embodiment of the mixing tube of 9 along line 11-11 through air passage openings of the air conditioner,

12 a side cross-sectional view of an embodiment of the mixing tube of 9 along line 12-12 through air passage openings of the air conditioner and

13 - 16 a series of views of an embodiment of a multi-tube fuel nozzle and a combustion chamber end cover, illustrating a method for removing pipes of the multi-tube fuel nozzle.

DETAILED DESCRIPTION OF THE INVENTION

 Hereinafter, one or more specific embodiments of the present invention will be described. In an effort to provide a concise description of these embodiments, the specification may not describe all features of an actual implementation. It should be noted that in the development of such an actual implementation, as with any construction or design project, numerous implementation-specific decisions must be made in order to achieve the specific objectives of the designers, e.g. adherence to systemic and business-related constraints, which may vary with each implementation. It should be understood, therefore, that such a developmental project may be complex and time consuming, but would be a matter of routine for the person skilled in the art of this disclosure as to design, manufacture, and manufacture.

 In presenting elements of the various embodiments of the present invention, it is intended that the articles "a," "an," "the" and "the" mean that there are one or more of the elements. It is intended that the terms "comprising", "including" and "having" include, and signify that there may be additional elements besides the elements listed.

The present disclosure is directed to air conditioning systems within a multi-tube fuel nozzle of a turbine system. The turbine system may include one or more multi-tube fuel nozzles. Each multi-tube fuel nozzle includes a plurality of tubes (eg, premix tubes), each tube having an air conditioner and a fuel injector. In the multi-tube fuel nozzle, compressed air may enter each mixing tube through an air conditioning device, which may include a plurality of air passage openings passing through an annular wall of the mixing tube. The annular wall of each tube is arranged around a central passage. The individual mixing tubes are each configured to be arranged around a fuel injector which disperses fuel into the central passage of the mixing tube to provide the air-fuel mixture. The air passages of the air conditioners are configured to condition the air entering the mixing tubes to condition the air entering the mixing tubes for specific pressure drops and to more uniformly mix the air and fuel before passing them into the burning region. The air passage openings of each air conditioning device may be configured with various features to optimize airside system pressure drops and to best provide a uniform airflow. Accordingly, the air passage openings of each air conditioning device can be circumferentially around the annular wall to be used to exploit an air pressure profile, which is substantially uniform in the circumferential direction. The air conditioning device on each mixing tube may include a first set and a second set of air passage openings, the second set of air passage openings being downstream of the first set of air passage openings. The second set of air vents may have an overall cross-section greater than the cross-section of the first set of air vents to compensate for a region having a lower air-pressure cross-section downstream in the fuel nozzle air space. The air passage opening sets of each air conditioning device may include a plurality of rows offset from each other in a circumferential direction to more evenly distribute the air pressure as the compressed air moves downstream. The air passage openings of each air conditioning device may be configured to guide the airflow in a substantially radial direction into the mixing tubes, but in other embodiments, they could be configured to guide the airflow in a direction having different directional components (eg, radial, angled axially upstream, angled axially downstream, angled circumferentially clockwise, angled circumferentially counterclockwise, or any combination thereof). These angled air passages (eg, angled circumferentially clockwise or counterclockwise) can impart swirl to the air directed into the central passage of the mixing tubes, which can increase the uniformity of the fuel-air mixture. The tubes may each be configured based on their location within the multi-tube fuel nozzle to receive a substantially similar airflow distribution.

Now referring to the drawings and referring first to 1 Fig. 12 is a block diagram of one embodiment of a gas turbine system 10 illustrated. The gas turbine system 10 includes one or more fuel nozzles 12 (eg multi-tube fuel nozzles), a fuel supply 14 and a combustion chamber 16 , The fuel nozzle 12 he stops 18 compressed air from an air compressor 20 and fuel 22 from a fuel supply 14 , While the present embodiments are discussed in the context of air as an oxidant, the present embodiments may also utilize oxygen, oxygen-enriched air, oxygen-reduced air, oxygen mixtures, or any combination thereof. As will be discussed in more detail below, the fuel nozzle includes 12 several fuel injectors 24 (Eg 10 to 1000) and associated mixing tubes 26 (eg 10 to 1000), with each mixing tube 26 an air conditioning device 27 with air vents 28 (eg 1 to 100) for conducting and conditioning an air flow into the respective pipe 26 has and every mixing tube 26 a respective fuel injector 24 (eg, in a coaxial or concentric arrangement) for injecting fuel into the respective tube 26 Has. Every mixing tube 26 mixes the air and fuel along its length and then gives an air-fuel mixture 30 into the combustion chamber 16 out. In certain embodiments, the mixing tubes may 26 are described as micromixing tubes having diameters between about 0.5 to 2, 0.75 to 1.75 or 1 to 1.5 centimeters. The mixing tubes 26 may be arranged in one or more bundles (eg, 1, 2, 3, 4, 5, 6, 7, 8, 9, 10 or more) of closely spaced tubes generally in a parallel arrangement relative to each other. In this configuration, every mixing tube is 26 for mixing (eg micromixing) on a relatively small scale within each mixing tube 26 configured, then a fuel-air mixture 30 in the combustion chamber outputs. The air conditioning device 27 (eg with passage openings 28 ) of the disclosed embodiments provides air conditioning at tube level (ie, for each individual mixing tube) 26 ), allowing the flow and / or pressure of air into each pipe 26 and under the several pipes 26 can be controlled to give a better mixing of fuel and air.

The combustion chamber 16 ignites the fuel-air mixture 30 , whereby pressurized exhaust gases 32 generated in a turbine 34 stream. The pressurized exhaust gases 32 flow against and between the blades in the turbine 34 , being the turbine 34 to turn. The turbine blades are with a shaft 36 coupled, resulting in the escape of exhaust gases 32 into the combustion chamber 16 again also turns. The exhaust 32 of the combustion process leaves the turbine system 10 finally via an exhaust outlet 38 , Shovels inside the compressor 20 are in addition to the wave 36 coupled and rotate while the shaft 36 from the turbine 34 is driven to rotate. The rotation of the blades inside the compressor 20 compressed air 40 coming from an air intake 42 in the compressor 20 was pulled. The resulting compressed air 18 then enters the multi-tube fuel nozzle 12 the combustion chambers 16 fed, as discussed above, where they are fueled 22 is mixed and ignited, which creates a substantially self-sustaining process. Furthermore, the wave 36 with the load 44 be coupled. As can be seen, the load can 44 be any suitable device, via the rotary output of a turbine system 10 Generate energy, such as a power plant or an external mechanical load. The relationship between the composition of the fuel-air mixture 30 and the efficient operation of the gas turbine system can therefore be seen. The shape of the several mixing tubes 26 each having an air conditioning device 27 with several air vents 28 for the conditioning of air 18 will be discussed in more detail below.

2 shows a side sectional view of the embodiment of the gas turbine system 10 from 1 , As shown, the embodiment includes a compressor 20 Made with an annular array of combustion chambers 16 is coupled. Every combustion chamber 16 includes at least one fuel nozzle 12 (eg, a multi-tube fuel nozzle) containing the fuel-air mixture 30 one in each combustion chamber 16 located combustion chamber 46 supplies. As will be described in detail below, certain embodiments of the mixing tubes include 26 the fuel nozzle 12 unique features to the compressed air 18 to distribute more evenly, resulting in a more uniform fuel-air mixture 30 can arise. The uniformity of the fuel-air mixture 30 Ensures more efficient combustion, increasing performance and reducing emissions. The combustion of the fuel-air mixture 30 in the combustion chambers 16 as above regarding 1 mentions that the blades or blades within the turbine 24 when flowing through exhaust gases 22 (eg combustion gases) to an exhaust outlet 38 turn back. Throughout the discussion, reference is made to a set of axes throughout. These axes are based on a cylindrical coordinate system and point in an axial direction 48 , a radial direction 50 and a circumferential direction 52 , For example, the axial direction runs 48 on a longitudinal or longitudinal axis 54 the fuel nozzle 12 along, the radial direction 50 extends from the longitudinal axis 54 away and the circumferential direction 53 runs around the longitudinal axis 54 ,

3 is a cutaway side view of the combustion chamber 16 of the gas turbine system 10 from 2 and within line 3-3 of 2 taken. As shown, the combustion chamber includes 16 a headboard 56 and a combustion chamber 46 , The fuel nozzle 12 is inside the headboard 56 the combustion chamber 16 positioned. Inside the fuel nozzle 12 are the several mixing tubes 26 (eg air-fuel premix tubes) suspended. Illustrated is an embodiment of the mixing tubes 26 with air conditioners 27 with air vents 28 , the compressed air 18 Come in and fuel yourself 22 mix. The mixing tubes 26 generally extend axially between an end cover assembly 58 the combustion chamber 16 and a cap side assembly 60 the fuel nozzle 12 , The mixing tubes 26 can with the end cover assembly 58 and the cap side assembly 60 be coupled, as further described below. The end cover assembly 58 can a fuel inlet 62 and a fuel room 64 for supplying several fuel injectors 24 with fuel 22 include. As discussed above, every single fuel injector is 24 with a single mixing tube 26 coupled. During the combustion process, the fuel moves 22 axially through each of the mixing tubes 26 from the end cover assembly 58 (through the fuel injectors 24 ) through the cap side assembly 60 and to the combustion chamber 46 , The direction of this movement along the longitudinal axis 54 the fuel nozzle 12 along is called the downstream direction 66 designated. The opposite direction is called the upstream direction 68 designated.

As described above, the compressor compresses 20 from the air intake 42 preserved air 40 , The resulting stream of compressed air 18 will be the head end 56 the combustion chamber 16 lying fuel nozzles 12 fed. The air passes through air inlets 70 into the fuel nozzles 12 to be used in the combustion process. More specifically, the compressed air flows 18 from the compressor 20 in an upstream direction 68 through an annulus 72 that is between a lining 74 (eg, an annular liner) and a flow wrap 76 (Eg, an annular flow envelope) of the combustion chamber 16 is trained. At the end of this annulus 72 becomes the compressed air 18 in the air inlets 70 the fuel nozzle 12 forced and fills an airspace 78 inside the fuel nozzle 12 , The compressed air 18 in the airspace 78 then passes through the air vents 28 the air conditioning device 27 into the several mixing tubes 26 one. In addition to being the air 18 into the mixing tubes 26 can enter, the air vents 28 the air conditioning device 27 condition the air in several ways, as discussed further below. Inside the mixing tubes 26 gets the air 18 then with that of the fuel injectors 24 provided fuel 22 mixed. The fuel-air mixture 30 flows in a downstream direction 66 from the mixing tubes 26 in the combustion chamber 46 where it ignites and to make the combustion gases 22 (eg exhaust gases) is burned. The combustion gases 32 flow from the combustion chamber 46 in the downstream direction 66 to a transitional piece 80 , The combustion gases 22 then flow from the transition piece 80 to the turbine 34 where the combustion gases 22 the rotation of the blades inside the turbine 34 drive.

4 illustrates an exploded perspective view of the multi-tube fuel nozzle 12 within line 4-4 of 3 , This figure further illustrates the arrangement of the plurality of fuel injectors according to some embodiments 24 at the end cover 58 and their relationship with the several mixing tubes 26 , The fuel rooms 64 distribute the fuel 22 to the fuel injectors 24 , As described above, the mixing tubes are 26 arranged so that they are between the end cover assembly 58 and the cap side assembly 60 are arranged. The individual mixing tubes 26 are each with a single fuel injector 24 paired and arranged around this fuel injector 24 configured (eg in a coaxial or concentric arrangement). The air vents 28 are on this upstream 68 Side of the mixing tubes 26 closest to the fuel injectors 24 , In certain embodiments, the fuel injectors may 24 removable with the end cover assembly 58 be coupled.

Also illustrated 4 a support structure 82 (eg annular drum, fuel nozzle cap) of the fuel nozzle 12 , which are the mixing tubes 26 and other structures within the fuel nozzle 12 surrounds. The support structure 82 extends from the end cover assembly 58 to the cap side assembly 60 protects and supports those inside the fuel nozzle 12 positioned entities in general and defines the airspace 78 inside the fuel nozzle 12 , The air inlets 70 are located on the support structure 82 and direct the compressed air 18 radially into the airspace 78 on the inside of the fuel nozzle 12 , upstream 68 and closest to the removable cap side assembly 60 there is a holding plate 84 , In certain embodiments, the nozzle includes 12 one the air inlets 70 surrounding annular airflow conditioning diffuser 86 ,

5 is a side view, partially in cross section, of the combustion chamber 16 within line 5-5 of 3 , The head end 56 the combustion chamber 16 contains a part of the multi-tube fuel nozzle 12 , The support structure 82 surrounds the multi-tube fuel nozzle 12 and the several mixing tubes 26 , As discussed above, in some embodiments, each mixing tube may be 26 axially between the end cover assembly 58 and the cap side assembly 60 run. The mixing tubes 26 can also be through the cap side assembly 60 extend to the fuel-air mixture directly to the combustion chamber 46 supply. Every mixing tube 26 is positioned so that it has a fuel injector 24 surrounds (eg coaxial or concentric arrangement) so that the injector 24 fuel 22 from the fuel room 64 get and the fuel into the pipe 26 passes. The fuel room 64 is with in the fuel inlet 62 that attaches to the end cover assembly 58 is fed by incoming fuel.

As described above, compressed air occurs 18 through the air inlets 70 coming from a diffuser 86 can be surrounded in the fuel nozzle 12 one. The diffuser 86 can be annular and for preconditioning and distribution of compressed air through the mixing tubes 26 in different directions in the fuel nozzle 12 be configured. The direction of the air flow inside the fuel nozzle 12 is essentially radially inward 88 but may be an upstream one 68 Component or downstream 66 Have component. The air flow varies over the mixing tubes 26 extending radially further out 90 located within the fuel nozzle 12 , closer to the air inlets 70 , are located. After entering the fuel nozzle 12 through the air inlet 70 and moving over the mixing tubes 26 enters the compressed air 18 through one or more air passage openings 28 an air conditioning device 27 in every mixing tube 26 one. In certain embodiments, the configuration is air vents 28 the air conditioning device 27 under individual mixing tubes 26 based on their radial 50 Location within the airspace 78 the fuel nozzle different. This specific adaptation can reduce the fluctuations of air pressure and movement across the mixing tubes 26 namely, the pressure drop going in the radially inward direction 88 Direction takes place, compensate. In certain embodiments, the axial 48 Positions of air vents 28 along the mixing tubes 26 be different to axial 48 To compensate for air pressure fluctuations. For additional regulation of the compressed air flow 18 can the air vents 28 the air conditioning device 27 be configured to have various shapes, sizes and arrangements, as further discussed below. In some embodiments, as well as in 5 shown, the retaining plate 84 and / or a baffle plate 92 inside the fuel nozzle 12 be positioned, which is the downstream 66 End of the mixing tubes 26 generally closest to the cap side assembly 60 surrounds. The flapper 92 may include multiple impingement cooling recesses, the air jets impacting a rear surface of the cap side assembly 60 can steer to provide impingement cooling.

In 6 is a cross-sectional view of a single mixing tube 26 and fuel injector 24 within line 6-6 of 5 illustrated. The central part of the pipe 26 was omitted to get more details of the first and second end 94 and 96 to show. The fuel injector 24 can generally be within a central passage 98 at the first end 94 (eg upstream 68 End) of each mixing tube 26 be positioned. This first end 94 is located on the upstream 68 Side of the multi-tube fuel nozzle 12 adjacent to the end cover assembly 58 , In certain embodiments, the air passage openings are located 28 the air conditioning device 27 at or near this first end 94 generally closest to the fuel injector 24 , In other embodiments, the air passages are located 28 the air conditioning device 27 in places upstream 68 or downstream 66 from the fuel injector 24 , The location of the air vents 28 Can be configured to take the air 28 to conduct selectively in different ways, depending on the flow of fuel 22 and compressed air 28 at a specific location within the fuel nozzle 12 , In some embodiments, the retaining plate 84 a second end 96 the mixing tubes 26 support, located on the downstream 66 Page is located. In certain embodiments, the retaining plate 84 also for fixing the second end 96 the mixing tubes 26 at the flapper 82 contribute.

6 also illustrates an embodiment of the spatial relationship among the mixing tubes 26 , the cap side assembly 60 and / or the end cover assembly 58 , In some embodiments, the mixing tubes may 26 with various fasteners or joints, such as weld, braze joints, brackets, threaded fasteners, snap fits, connectors or other connections, to components within the head end 56 the combustion chamber 16 be attached, such as the cap side assembly 60 , the retaining plate 84 and / or the baffle plate 92 , In other embodiments, the mixing tubes 26 are held in a floating configuration and are only supported by one or more of the cap side assembly 60 , the retaining plate 84 , the flapper 92 , various springs or other support structures worn. Such floating configurations can advantageously thermal expansion of the mixing tubes 18 and other components of the combustion chamber 14 take up. Floating configurations also allow for easier customization and configuration of mixing tubes 26 with various configurations of air vents 28 , If it is determined that fuel-air mixtures 20 are not uniform, can easily single pipes 26 removed and through pipes 26 be replaced, the other configurations of the air vents 28 (eg air conditioning device 27 ), the air pressure fluctuations in the fuel nozzle 12 better balance. The floating configurations can also be achieved by installing an axial spring 100 be implemented to resilient axial 48 Support and restriction of the movement of the mixing tubes 26 provide. According to the illustrated embodiment, the axial spring 100 between a holding plate 84 and a flapper 92 be positioned. Furthermore, a radial spring 102 between the fuel injector 24 and the first end 94 of the mixing tube 26 lie and can have a resilient radial 50 limiting the movement and thermal expansion of the mixing tube 26 provide. It may further include features such as additional springs, channels and / or guides for blocking movement of the mixing tubes 26 in the circumferential direction 52 give.

As further in 6 The fuel injector has illustrated 24 an annular wall 103 around an internal fuel passage 104 leading to one or more fuel ports 106 in a beveled part 108 of the fuel injector 24 that leads inside the mixing tube 26 is arranged (eg in a coaxial or concentric arrangement). In operation leaves the fuel injector 24 fuel 22 from the fuel room 64 over the one or more fuel ports 106 downstream 66 to a region inside the mixing tube 26 stream. In certain embodiments, the fuel passage openings 106 relative to the air passage (s) 28 axially upstream 69 , axially downstream 66 be positioned axially aligned with or in a combination thereof. In the illustrated embodiment, the fuel passage openings are located 106 at the beveled part 108 that has a linear or curved slope in the downstream direction 66 may have. For example, the chamfered part 108 as a conical wall, an inwardly curved annular wall (eg inwardly towards the axis of the injector 24 curved), an outwardly curved annular wall (eg from the axis of the injector 24 curved outward) or a combination thereof. In the illustrated embodiment, the chamfered part extends 108 from a first position upstream 68 the air passage openings 28 to a second position downstream 66 the air passage openings 28 of the mixing tube 26 , As illustrated, the diameter of the chamfered part decreases 108 of the fuel injector 24 in the downstream direction 66 gradually (ie, it converges), reducing the cross-sectional area between the fuel injector 24 and the mixing tube 26 in the downstream direction 66 is gradually increased. In this way, the illustrated embodiment provides a gradual pressure drop between the fuel injector 24 and the mixing tube 26 , which contributes to improving the flow and mixing of fuel and air. In the illustrated embodiment, the air conditioners are 27 (eg air vents 28 ) on the mixing tube 26 along and the fuel passage openings 106 at the fuel injector 24 (eg beveled part 108 ) both upstream of a tip 109 of the fuel injector 24 arranged so that the air and the fuel adhere to the decreasing cross-sectional area between the fuel injector 24 and the mixing tube 26 at least partially mix. Furthermore, the illustrated air passage openings 28 upstream of the fuel passage openings 106 arranged to the pressure upstream of the fuel passage openings 106 to increase.

In certain embodiments, the fuel passage openings 106 and the Air passage openings 28 (eg axes of the openings) in the radial direction 50 , the axial direction 48 , an axially upstream angle, an axially downstream angle, the circumferential direction 52 (eg clockwise or counterclockwise) or a combination thereof. Furthermore, the fuel and air passage openings 106 and 28 be aligned in the same direction and / or in different directions. For example, the fuel passage openings 106 be aligned radially outward while the air passage openings 28 may be aligned radially outward, and the fuel passage openings 106 can in the same and / or opposite circumferential direction 52 like the air vents 28 be aligned. The circumferential direction of the openings 28 and 106 can be used to allow a swirl flow. The orientation of the fuel ports 106 and air vents 28 can also be in the circumferential direction 52 around each tube 26 , axially on each tube 26 vary along or in a combination thereof. Furthermore, the orientation of the fuel passage openings 106 and the air vents 28 under the several mixing tubes 26 from a pipe 26 to another pipe 26 to be different. In this way, the orientation of the fuel passage openings 106 and the air vents 28 used to mix the fuel and air in each tube 26 improve while flow and pressure fluctuations within the multi-tube fuel nozzle 12 be compensated. This ability, the orientation of openings 28 and 106 , especially the air vents 28 To change, allows tube-based air conditioning under the multiple mixing tubes 26 ,

The number, size and / or shape of the fuel ports 106 and the air vents 27 may be the same and / or different from each other. In certain embodiments, the air passage openings 28 Have hole diameters that are as large as, greater than and / or smaller than the hole diameter of the fuel passage openings 106 are. For example, the air vents 28 a diameter of 0.1 to 10 times, 0.2 to 5 times, 0.3 to 4 times, 0.4 to 3 times or 0.5 to 2 times the diameter of the fuel passage openings 106 to have. In certain embodiments, the number of air vents 28 as large as, greater than and / or less than the number of fuel ports 106 be. By way of example, the number of air vents may be about 0.5 to 50 times, 0.5 to 25 times, 1 to 10 times, or 2 to 5 times the number of fuel ports 106 be. As an example, the air conditioner 27 every mixing tube 26 5 to 500, 10 to 100 or 15 to 50 air vents 28 to have. In certain embodiments, the shape of the fuel passage openings 106 and the air vents 28 circular openings, rectangular openings, oval openings, triangular openings, polygonal openings, or any combination thereof. Along with the variation of orientation, number, size and / or shape, the fuel ports may be 106 and air vents 28 also in the circumferential direction 52 around each tube 26 , axially on each tube 26 be different along or in a combination thereof. Furthermore, the number, size and / or shape of the fuel passage openings 106 or air vents 28 also from a pipe 26 to another pipe 26 under the several mixing tubes 26 to be different. In this way, the number, size and / or shape of the fuel passage openings 106 and the air vents 28 used to mix the fuel and air in each tube 26 improve while flow and pressure fluctuations within the multi-tube fuel nozzle 12 be compensated. This ability, the number, size and / or shape of the openings 28 and 106 , especially the air vents 28 To change, allows tube-based air conditioning under the multiple mixing tubes 26 ,

7 is an illustration of a single, from the fuel nozzle 12 separate mixing tube 26 , In certain embodiments, the mixing tubes may 26 for repair, inspection or replacement of the fuel nozzle 12 be expandable. As discussed above, the mixing tubes can 26 inside mixing tubes, the other configurations of air vents 28 have the pressure drops inside the fuel nozzle 12 possibly better offset, selectively removed and replaced. A method for removing and replacing the mixing tubes 26 will be discussed in more detail below. 7 also illustrates a complete mixing tube 26 with a first end 94 in which, in some embodiments, generally the air passage openings 28 lie, and a second end 96 where the mixing tube 26 with the cap side assembly 60 , a holding plate 84 and / or a baffle plate 92 is coupled. Every mixing tube 26 may also have any of various shapes and sizes. In some embodiments, each mixing tube 26 have a generally cylindrical shape and may, for example, have a generally circular cross-section. In addition, the mixing tube 26 in some embodiments have a diameter of about 5 to 20 mm, 5 to 10 mm, 10 to 15 mm and all subgroups in between. For example, a mixing tube 26 have a diameter of 5, 10, 15 or 20 millimeters or another diameter. In certain embodiments, the mixing tube 26 a diameter of about 6.35 Have millimeters. It should be noted that all mixing tubes 26 inside the combustion chamber 16 may have a substantially similar diameter, but that in certain embodiments it may be advantageous when the mixing tubes 26 have different diameters. Furthermore, every mixing tube 26 have an axial length of about 10 to 300 cm, 20 to 200 cm, 30 to 150 cm or an arbitrary incremental length or area within these ranges. For example, every mixing tube 26 have an axial length of 10, 15, 20, 35, 30, 75, 80, 85, 90 or 150 cm or any other length. In certain embodiments, the mixing tubes may 26 inside the combustion chamber 16 have substantially similar lengths, although the mixing tubes 26 in some embodiments may have two or more different lengths. Furthermore, the air conditioning device 27 (eg air vents 28 ) at any axial part of each tube 26 along within 0 to 10, 0 to 20, 0 to 30, 0 to 40, or 0 to 50 percent of the length of each tube 26 , measured from the upstream end 94 of the pipe 26 , The air conditioning device 27 may also include one or more groups of closely spaced air passage openings 28 at one or more axial regions on each tube 26 along.

8th is a detailed view of the first end 94 of the mixing tube 26 from 7 showing an embodiment of the air conditioning device 27 (eg air vents 28 ) on a mixing tube 26 illustrated. As discussed below, the air vents 28 have different shapes, sizes, orientations, numbers and configurations. 8th illustrates a two-set configuration 110 and 112 elliptical air vents 28 in the circumferential direction 52 around the mixing tube 26 are arranged, the first sentence 110 Air passage openings 28 axially upstream 68 of the second sentence 112 Air passage openings 28 lies. In this embodiment, the individual air passage openings 28 of the first sentence 110 a cross-sectional area 114 that is substantially larger than the cross-sectional area 114 the air passage openings 28 of the second sentence 112 is. The larger cross section 114 the further downstream air passage openings 28 can compensate for the downstream pressure drop across the pipes 26 within the airspace 78 is experienced. In other embodiments, the air passage openings 28 have a circular, teardrop-shaped or rectangular cross-sectional shape or any other shape. Each illustrated sentence 110 and 112 Air passage openings 28 includes several rows 116 and 118 (eg two rows) of air vents 28 in the circumferential direction 52 around the mixing tube 26 are arranged uniformly spaced from each other, wherein the air passage openings 28 the first row 116 in the axial direction 48 and the circumferential direction 52 from the air vents 28 in the second row 118 offset (eg staggered) are. In some embodiments, subsequent rows 118 not in the circumferential direction 52 can be staggered (eg staggered) but instead can be circumferentially aligned with previous rows 116 of air vents 28 aligned (eg in an axial line). In other embodiments, subsequent rows 118 be partially offset from each other. In some embodiments, the air passage openings 28 a cross section 114 in a range of about 1 mm ² to 100 mm ² , 10 mm ² to 50 mm ² , 25 mm ² to 75 mm ² or any subgroup in between. For example, the individual air vents 28 have a cross section of 1, 5, 10, 15, 20, 25, 30, 75, 80, 85, 90, 95 or 100 square millimeters or any other cross section. In the illustrated embodiment, the air conditioner includes 27 two rows 116 and 118 of air vents 28 in two sentences 110 and 112 Air passage openings 28 , In other embodiments, the air conditioning device 27 1 to 1000, 2 to 500, 3 to 250, 4 to 100 or 5 to 25 or more sets and rows of air vents 28 with different sizes, shapes, orientations, patterns or a combination thereof. For example, the air conditioning device 27 1 to 100 sets of different sized air vents 28 each set comprising 1 to 100 rows of equally or differently spaced, angled or formed air passage openings 28 Has. Further, for example, the size, the number and / or the angle of the air passage openings 28 be the same, in the axial direction 48 and / or the circumferential direction 52 on each mixing tube 26 increase and / or decrease. In certain embodiments, the diameter of the air passage openings 28 gradually from one row to another on the mixing tube 26 increase or decrease (or alternate).

9 is an embodiment of the air conditioning device 27 (eg air vents 28 ) at the first end 94 a mixing tube 26 , wherein the air passage openings 28 essentially the same shape and cross-sectional area 114 to have. An embodiment of air passage openings 28 how this can take advantage of a cross section, in which in the axial 48 or circumferential direction 52 an insignificant pressure drop is expected. The air vents 28 this embodiment are in six rows 116 arranged. The axial 48 Distance between the rows 116 is the same and the air vents 28 every row 116 are in the circumferential direction 52 around the mixing tube 26 equally spaced from each other. Besides, every row is 116 in the circumferential direction 52 from the next row 118 completely offset, ie staggered.

10 is a cross section of the mixing tube 26 from 9 by line 10-10 of 9 , As illustrated, the air vents are 28 directly inward towards a central axis 119 of the mixing tube 26 aligned, whereby an air injection radially inwardly into the mixing tube 26 is enabled as indicated by the arrows. As discussed above, the compressed air occurs 18 over the airspace 78 the fuel nozzle 12 into the mixing tubes 26 one. The air 18 is from a diffuser 86 and an air intake 70 in a substantially radial inward direction 74 in the airspace 78 directed. When entering the air 18 into the mixing tubes 26 carry the air vents 28 the air conditioning device 27 for conducting, distributing and generally conditioning the flow of air into the mixing tube 26 to improve the mixing with the fuel 22 from the fuel injector 24 at. In this embodiment, the air passage openings 28 to the radial axis 48 parallel and thus lend into the mixing tubes 26 entering air 18 no twisting movement.

11 is a cross section of the mixing tube 26 from 9 through line 11-11 of 9 , The air vents 28 are, as illustrated by the arrows, radially inward toward the central axis 119 of the mixing tube 26 but offset, aligned. That is, the air vents 28 are generally relative to the radial axis 50 angled, as if from an angle 120 is hinted, so that the air vents 28 in the circumferential direction 52 around the central axis 119 of the pipe 26 impart a swirl flow. As illustrated, the angle is 120 the air passage opening 28 with respect to the radial axis 50 greater than zero. The angle 120 individual air vents 28 may be in the range between about 0 and 45 degrees, 0 and 30 degrees, 15 and 45 degrees, 15 and 30 degrees, or any subgroup in between. For example, the angle 120 some air vents 28 5, 10, 15, 20, 25, 30, 35, 40 or 45 degrees or any other angle and the angle 120 other air vents 28 can be 5, 10, 15, 20, 25, 30, 40, or 45 degrees, or any other angle. In some embodiments, the air passage openings 28 be configured to impart swirling air clockwise while leaving other air vents 28 can be configured to impart the air counterclockwise twist. This variation may be based on the circumferential position of the single mixing tube 26 in terms of the air intake 70 the fuel nozzle 12 done to the stream of compressed air 18 in the airspace 78 the fuel nozzle 12 better to grasp.

12 is a cross section of the mixing tube 26 from 9 by line 12-12 of 9 , As illustrated by the arrows, the air vents are 28 radially inward toward the central axis 119 of the mixing tube 26 but offset, aligned. That is, the air vents 28 are generally relative to the radial axis 50 angled, as from the angle 120 is hinted, so that the air vents 28 in the circumferential direction 52 around the central axis 119 of the pipe 26 impart a swirl flow. In contrast to 11 is the angle 120 the air passage openings 28 in 12 larger to provide a stronger swirl current. That is, the angle 120 the air passage opening 28 with respect to a radial axis 50 is a greater value than the angle 120 in 11 , For example, the angle 120 the air passage openings 28 range between about 45 and 90 degrees, 60 and 90 degrees, 45 and 75 degrees or 60 and 75 degrees, or any subgroup in between. It is also discussed that individual air vents 28 within a set of air vents 28 with different angles 120 can be configured to control the flow of compressed air 18 inside the fuel nozzle 12 to adapt specifically. For example, mixing tubes can 26 in some embodiments, within the fuel nozzle 12 are installed at locations that are radially outward and closer to the air inlet 70 lie, be configured so that they have air vents 28 have, the larger angles 120 as the air vents on mixing tubes 26 that are within the radially inward locations within the fuel nozzle 12 , further from the air intake 70 away, lie. In some embodiments, air passage openings 28 at the mixing tubes 26 be angled so that they air in directions with an axial 48 Direct component. That is, the air passage opening 28 Can for even greater control over the flow of compressed air 18 inside the mixing tubes 26 Be configured to direct the compressed air in one direction with a downstream one 66 or upstream 68 Component conducts. These variations in the angular configuration of the air vents 28 may be fluctuations in the flow of compressed air within the mixing tube 26 , Fluctuations in the fine distribution of injected fuel 22 from the fuel injectors 24 or other varying conditions of the environment within the fuel nozzle 12 compensate for the uniformity of the fuel-air mixture 30 can affect.

The 13 - 16 are perspective views of the fuel nozzle 12 showing a series of steps of a method for removing at least one mixing tube 26 according to certain embodiments. As in 13 Illustrated is the multi-tube fuel nozzle 12 from head 56 the combustion chamber 16 removed and with the end cover assembly 58 coupled. The end cover assembly 58 with fuel inlet 62 is with the support structure 82 and the cap side assembly 60 coupled illustrated. To the mixing tubes 26 to expose, as in 14 is shown, the end cover assembly 58 from the supporting structure 82 and the cap side assembly 60 separated. 14 shows the fuel injectors 24 on that with the end cover assembly 58 the fuel nozzle 12 are coupled. Next, as in 15 shown the retaining plate 84 from the cap side assembly 60 removed by holding plate 84 in an upstream direction 68 from the second end 96 to the first end 94 the mixing tubes 26 at the mixing tubes 26 pushed along. As in 16 can then be shown the mixing tubes 26 from their location on the cap side assembly 60 be removed. The removal of one or more mixing tubes 26 It may allow inspection, replacement, repair or any other purpose during the manufacture, assembly and operation of the fuel nozzle 12 demonstrate. The installation of mixing tubes 26 By following in the 13 to 16 Steps achieved in reverse order. The one or more mixing tubes 26 can namely on the cap side assembly 60 ( 16 ) can be used in their desired position, then the holding plate 84 by sliding over the mixing tubes 26 from the first end 94 to the second end 96 until the pipes 26 with the cap side assembly 60 and / or the baffle plate 92 ( 15 ) are flush mounted. The support structure 82 then comes with the end cover assembly 58 coupled by the mixing tubes 26 on their respective fuel injectors 24 ( 14 ). The assembled fuel nozzle 12 ( 13 ) can then be in the headboard 56 the combustion chamber 12 to be built in.

Technical results of the disclosed embodiments include systems and methods for improving the mixing of air and fuel within multi-tube fuel nozzles 12 a gas turbine system. Special is the fuel nozzle 12 with several mixing tubes 26 equipped, the air vents 28 (eg air conditioning device 27 ), through which compressed compressed air 18 in the fuel nozzle 12 enters, is directed and fueled 22 mixed, that of several fuel injectors 24 is injected. The air vents 28 can be configured with different shapes, sizes, spatial arrangements and configured to direct the air at different angles. The fluctuating pressures of air 18 and fuel 22 among the several fuel injectors 24 in the multi-tube fuel nozzle 12 Balancing, this specific adjustment increases the mixing and uniformity. The increased mixing of the air 18 and fuel 22 increases flame stability within the combustion chamber 16 and reduces the amount of undesirable adjacent combustion products. The procedure for removing and installing the individual mixing tubes 26 enables cost-effective and efficient repair of the fuel nozzle 12 ,

 Although some typical sizes and dimensions are provided above in the present disclosure, it should be understood that the various components of the described combustor may be scaled up or down and may also be customized to various types of combustors and various applications. This written description uses examples to disclose embodiments of the invention, including the best mode of execution, and also to enable any person skilled in the art to practice the invention, including making and using any devices or systems and performing integrated methods. The patentable scope of the invention is defined by the claims, and may include other examples that will occur to those skilled in the art. It is intended that such further examples fall within the scope of the claims if they have structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal languages of the claims.

 One system includes a multi-tube fuel nozzle. The multi-tube fuel nozzle includes several tubes. Each tube has a first end, a second end, and an annular wall disposed about a central passage. The first end is configured to be arranged around a fuel injector. Each tube also includes an air conditioning device having a plurality of air passage openings disposed adjacent to the first end. The plurality of air passage openings pass through the wall into the central passage.

LIST OF REFERENCE NUMBERS

10

 Gas Turbine System

12

 fuel nozzle

14

 fuel supply

16

 combustion chamber

18

 compressed air

20

 compressor

22

 fuel

24

 fuel injector

26

 mixing tubes

27

 type air conditioner

28

 Air passage opening

30

 Fuel-air mixture

32

 pressurized exhaust gases

34

 turbine

36

 wave

38

 exhaust outlet

40

 air

42

 air inlet

44

 load

46

 combustion chamber

48

 axial

50

 radial

52

 in the circumferential direction

54

 longitudinal axis

56

 head

58

 end cover

60

 Cap side assembly

62

 Fuel inlet in the end cover

64

 Fuel chamber in the end cover

66

 Downstream direction

68

 Upstream direction

70

 air intake

72

 annulus

74

 lining

76

 flow envelope

78

 airspace

80

 Transition piece

82

 support structure

84

 Retaining plate

86

 diffuser

88

 radially inward direction

90

 radially outward

92

 flapper

94

 first end of the mixing tube

96

 second end of the mixing tube

98

 central mixing tube passage

100

 axial spring

102

 radial spring

103

 annular wall of the fuel injector

104

 internal fuel passage of the fuel injector

106

 Fuel passage openings on the fuel injector

108

 bevelled part

109

 Tip of the fuel injector

110

 first set of air vents

112

 second set of air vents

114

 Air passage opening cross-section

116

 first row of air vents

118

 second row of air vents

120

 angle

Claims (10)

 System comprising: a multi-tube fuel nozzle, comprising: several tubes, each tube having: a first end, a second end, an annular wall disposed about a central passage, the first end configured to be disposed about a fuel injector, and an air conditioning device having a plurality of air passage openings disposed adjacent to the first end, the plurality of air passage openings extending through the wall into the central passage.  The system of claim 1, wherein the plurality of air passage openings are circumferentially disposed around the annular wall and / or wherein the plurality of air passage openings comprises a first set of air passage openings and a second set of air passage openings, the second set of air passage openings being relative to the first end downstream of the first set Air outlet is located.  The system of claim 2, wherein a first total cross section of each air passage opening of the first set of air passage openings is larger than a second total cross section of each air passage opening of the second set of air passage openings.  The system of claim 1, wherein the first set of air passage openings includes a first row and a second row of air passage openings circumferentially disposed around the annular wall and the first row of air passage openings offset in a circumferential direction from the second row of air passage openings and / or wherein the first set of air passage openings is configured to direct the airflow in a radial direction into the central passageway.  The system of claim 1, wherein the second set of air passage openings comprises a third row and a fourth row of air passage openings circumferentially disposed around the annular wall, and the third row of air passage openings offset in the circumferential direction from the fourth row of air passage openings , and / or wherein the second set of air passage openings is configured to guide the air with a swirling motion about a central axis of the central passage.  The system of claim 1, wherein the plurality of air vents have multiple sizes, shapes, angles, pitches, or any combination thereof.  The system of claim 1, wherein each tube of the plurality of tubes is configured to obtain an equal distribution of the airflow over the air conditioning device. The system of claim 1, comprising a gas turbine or combustor with the multi-tube fuel nozzle.  System comprising: a combustor end cover assembly, a multi-tube fuel nozzle coupled to the combustor end cover assembly, comprising: a holding plate and a plurality of tubes disposed between the end cover assembly and the support plate, each tube having: a first end adjacent to the end cover assembly, a second end adjacent to the retaining plate, an annular wall disposed about a central passage, the first end configured to be disposed about a fuel injector, and an air conditioning device having a plurality of air passage openings disposed adjacent to the first end, the plurality of air passage openings extending through the wall into the central passage.  The system of claim 9, wherein each tube of the plurality of tubes is configured to be individually removed from or installed between the end cover assembly and the retainer plate, and / or wherein the retainer plate is configured to be removed from the multi-tube fuel nozzle after removal of the end cover assembly be moved by the holding plate on the plurality of tubes along the first end to the second end of each tube.

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