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    • 专利摘要:
    A downstream nozzle (45) for use in a combustor includes an inner radial wall (24) defining a combustion zone (23) downstream of a primary nozzle and an outer radial wall (25) surrounding the inner radial wall (24) so as to form a flow annulus (28) therebetween. The downstream nozzle (45) includes: an injector tube (54) extending between the outer radial wall (25) and the inner radial wall (24); a first plenum (61) adjacent to the injector tube (54); and, inside a ceiling (65), a bottom (66) disposed between the inner radial wall (24) and the outer radial wall (25). A supply passage (62) connects the first collection space (61) to an inlet formed externally of the outer radial wall (25), and baffles (63) are formed through the bottom (66) of the first collection space (61).
    公开号:CH709993A2
    申请号:CH01163/15
    申请日:2015-08-13
    公开日:2016-02-15
    发明作者:Christopher Paul Willis；William Michael Poschel；Lucas John Stoia；Patrick Benedict Melton；Vaibhav Nadkarni；Chandrasekhar Pushkaran
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    The present invention relates to combustion systems in gas turbines, and more particularly to apparatus and systems related to nozzles or fuel injectors disposed downstream of primary nozzles in certain types of combustors.
    For staged combustion in combustion turbines (also called "gas turbines") there are several designs, but most are complicated arrangements consisting of multiple pipelines and interfaces. As will be appreciated, one type of staged combustion system commonly used in gas turbines is referred to as late lean-mix injection systems that include injectors located downstream of the primary nozzles of the combustor. In this type of system, late fuel injection fuel injectors are located downstream of the primary nozzle. These injectors may be positioned toward the rear of the combustion zone. As one of ordinary skill in the art will appreciate, combustion of a fuel-air mixture at this downstream location may be used to improve NOx emission performance. NOx, or nitrogen oxides, is one of the major undesirable air pollutant emissions generated by gas turbines burning conventional hydrocarbon fuels. Late lean-mixture systems may also function as an air bypass, which may also be used to reduce carbon monoxide or CO emissions during a "shutdown" or light load operation. Systems for late lean-mix injection may also bring other operational benefits.
    Conventional late lean mix injection arrangements are expensive for new gas turbine engine manufacturing units and are difficult to retrofit in existing units. One of the reasons for this is the complexity of conventional late lean-mix injection systems, particularly those components of the systems associated with fuel and air supply. The many parts associated with these systems must be designed to withstand the extreme thermal and mechanical stresses of the turbine environment, significantly increasing manufacturing and installation costs. Conventional late lean-mix injection arrangements have a high risk of fuel leakage, which can lead to autoignition, flame holding, unit damage, and safety issues.
    [0004] In addition, these systems require injector tubes to guide a fuel and / or air mixture across the flow annulus so that the mixture can be injected into a rearward portion of the combustion zone. Specifically, such injector tubes halve the flow annulus, thereby creating significant obstacles to the flow of compressed air that moves through it, which, as will be appreciated, can adversely affect performance in a variety of ways. For example, downstream vortices or downstream vortices caused by the injector tubes interfere with flow through the annulus and may result in uneven distribution of flow characteristics. As the compressed air moves toward the front portion of the combustion chamber to introduce the fuel within the primary nozzles, uneven flow can adversely affect the resulting combustion. This can reduce the efficiency of the turbine as well as affect the emission levels. As will be appreciated, the levels of undesirable emissions typically decrease when compressed air is supplied to the primary nozzle having uniform characteristics, while non-uniform properties causing nonuniform combustion result in increased levels of emissions. As a result, there is a need for downstream injection devices and systems that reduce the formation of such flow disturbances that are typical in conventional designs.
    In addition, the wake flow or vortex flow, which forms downstream of the injector tubes, negatively affect the cooling in the area. It will be appreciated that the air moving through the flow annulus creates cooling for the inner radial wall defining the combustion zone. This cooling allows the inner radial wall to withstand the high temperatures that allow more efficient turbines. The downstream wake flow associated with the injector tubes interrupts this flow, particularly with respect to the region on the inner radial wall that is located just downstream of an injector tube. More specifically, the injector tube interrupts the portion of the air flowing through the flow annulus, which was otherwise provided for convective cooling of the area. To the extent that this problem can be mitigated, the life of a combustor part can be extended. Accordingly, there is a need for novel and innovative designs for downstream injectors that avoid affecting annulus cooling in this manner.
    BRIEF DESCRIPTION OF THE INVENTION
    The present application thus describes a downstream nozzle for use in a combustion chamber which includes an inner radial wall defining a combustion zone downstream of the primary nozzle and an outer radial wall surrounding the inner radial wall so as to provide a flow annulus to train in between. The downstream nozzle may include: an injector tube extending between the outer radial wall and the inner radial wall; a first plenum adjacent to the injector tube and, internally from the ceiling, a bottom disposed between the inner radial wall and the outer radial wall. A supply passage may connect the first collection space to an inlet formed externally of the outer radial wall, and impact openings may be formed through the bottom of the first collection space.
    In a preferred embodiment of the aforementioned downstream nozzle, the injector tube may include an upstream side and a downstream side defined with respect to an expected flow through the flow annulus during operation of the combustion turbine, with a downstream portion of the first collection chamber adjacent is disposed downstream of the injector tube and may include at least a plurality of the baffles and wherein across the flow annulus an outer surface of the inner radial wall of an inner surface of the outer radial wall is disposed opposite.
    In addition, the supply passage may extend through the outer radial wall between an inlet disposed outwardly from the outer radial wall and an outlet disposed inwardly of the outer radial wall, and adapted to communicate with first collecting space to be in fluid communication.
    Further additionally or as an alternative, the outer surface of the inner radial wall may include a target region that is just downstream of and adjacent to and adjacent to the injector tube, and the plurality of impact ports within the downstream portion of the first plenum may be established to direct a pressurized fluid ejected therefrom toward the target area.
    In the downstream nozzle of the latter type, the downstream portion of the first plenum may include at least 8 of the impingement ports, wherein the at least 8 impingement ports may be uniformly spaced so as to correspond to the target region.
    In a preferred embodiment of the downstream nozzle of any kind mentioned above, the first collection space may have a cantilevered structure in which a downstream portion of the first collection space protrudes from the downstream side of the injector tube, a target area being the outer surface of the inner radial wall may be overhanged by the projecting downstream portion of the first plenum, and wherein the downstream portion of the first plenum may have a plurality of impact openings directed to the target area.
    Additionally, or as an alternative, the first plenum may be configured to overhang a target region defined on the outer surface of the inner radial wall, wherein the target region is located just downstream of the injector tube, wherein the impingement orifices are of a construction can adjust each to the target region, and wherein the bottom of the first collection space may have a planar structure which is aligned substantially parallel to the outer surface of the inner radial wall, and wherein the bottom of the first collection space approximately in the middle between the outer surface of the inner radial wall and the inner surface of the outer radial wall may be arranged.
    In the downstream nozzle of the last-mentioned type, the ceiling of the first plenum may be located slightly outboard from the outer radial wall, wherein the impingement openings may be oriented substantially perpendicular to a direction of flow through the flow annulus, the downstream nozzle having a plurality may include the supply channels, wherein the plurality of supply channels include at least two supply channels, which are arranged on substantially opposite sides of the downstream nozzle.
    In the preferred embodiment of the downstream nozzle of any kind mentioned above, a compressor outlet housing may define a compressor outlet cavity around the combustion chamber, wherein the inlet of the supply channel may be configured to be in fluid communication with the compressor outlet cavity.
    Additionally or as an alternative, the first plenum may form an annulus around the injector tube, wherein the impingement ports may be distributed over the bottom of the first plenum so as to have a concentration within the downstream portion of the first plenum.
    Further additionally or as a further alternative, the upstream side of the injector tube may have an aerodynamic nose feature.
    In the downstream nozzle of the latter type, the aerodynamic nose feature may constrict to a sharp point directed in a downstream direction relative to the expected flow through the flow annulus, the aerodynamic nose feature having an inboard position with respect to the first collection space can.
    In the preferred embodiment of the downstream nozzle of any of the aforementioned types, a compressor outlet housing may define a compressor outlet cavity around the combustion chamber, the downstream nozzle may further include an air shield, the air shield including a wall extending from an injector footprint, The air shield is configured to substantially separate the interior of the downstream nozzle from the compressor outlet cavity, wherein the supply channel may be configured to extend through the air shield so as to be in fluid communication with the compressor outlet cavity.
    The preferred embodiment of the downstream nozzle of any kind mentioned above may further comprise a fuel plenum formed around the injector tube, the fuel plenum containing longitudinally within the outer radial wall a connection to a fuel supply passage, and a mixing plenum having thereto is arranged to include an air supply and fuel injection ports, which are respectively connected to the fuel plenum, wherein the mixed collection space may be connected to a first end of the injector tube and wherein a second end of the injector can be connected through the inner radial wall with the combustion zone, and wherein between the outer radial wall and the inner radial wall, the injector tube may have a separation structure configured to move a flow moving through the injector tube from that through the flow annulus h to separate moving flow.
    In addition, the inner radial wall may have a lining, and the outer radial wall may comprise a flow sleeve.
    As an alternative to this, the inner radial wall may have a transition piece, and the outer radial wall may comprise a baffle sleeve.
    As a further alternative or further in addition, the downstream nozzle may include a late lean mixture injection system configured to inject a mixture of fuel and air within a rearward end of the combustion zone defined by the liner Flow annulus may be configured to guide an incoming compressed air toward a cap assembly disposed at a forward end of the combustor within which the primary nozzle is housed.
    In the downstream nozzle of any of the aforementioned types, the opening may have a slot formed through the bottom of the first plenum, which slot may have a tapered profile that narrows as the slot extends downstream.
    In addition, the slot may include a screen formed on a downstream wall, which screen may include a plurality of openings and a slot opening formed in proximity and approximately parallel to the inner radial wall of the combustion chamber.
    In a further aspect of the invention, there is provided a late lean injection injector in a combustor of a gas turbine, the combustor including a liner defining a combustion zone downstream of a primary nozzle and a flow sleeve surrounding the liner so as to provide a liner Forming flow annulus between them. The late lean injection injector has an injector tube extending between the outer radial wall and the inner radial wall, a first plenum forming an annulus around the injector tube, the first plenum being a ceiling and, internally from the ceiling, a floor with the bottom disposed between the inner radial wall and the outer radial wall, a feed channel connecting the first plenum with an inlet formed externally of the outer radial wall, and baffles opening through the bottom of the first Are formed through collection space. The baffles are distributed over the bottom of the first plenum so as to have a concentration within the downstream portion of the first plenum. The outer surface of the inner radial wall includes a target region defined just downstream of and adjacent to the injector tube, wherein the concentration of the impingement ports within the downstream portion of the first plenum is directed to the target region.
    These and other features of the present application will become apparent upon review of the following detailed description of preferred embodiments in conjunction with the drawings and appended claims.
    BRIEF DESCRIPTION OF THE DRAWINGS
    These and other features of this invention will be more fully understood from a study of the following more detailed description of exemplary embodiments of the invention, taken in conjunction with the accompanying drawings, in which:<Tb> FIG. Figure 1 shows a sectional view of a gas turbine in which embodiments of the present application may be used.<Tb> FIG. Figure 2 shows a sectional view of a conventional combustor in which embodiments of the present invention may be used.<Tb> FIG. FIG. 3 shows an enlarged sectional view of a combustor having a downstream or injector for late lean-mix injection according to a conventional structure. FIG.<Tb> FIG. Figure 4 shows a cross-sectional view of a downstream fuel injector incorporating aspects of the present invention.<Tb> FIG. 5 <SEP> is a perspective cross-sectional view of a downstream fuel injector according to embodiments of the present invention.<Tb> FIG. FIG. 6 shows a perspective view of a portion of a downstream fuel injector according to certain embodiments of the present invention. FIG.<Tb> FIG. FIG. 7 shows a simplified cross-sectional profile view of a downstream fuel injector according to embodiments of the present invention. FIG.<Tb> FIG. 8 shows a perspective view of a portion of a downstream fuel injector according to an alternative embodiment of the present invention.<Tb> FIG. 9 <SEP> is a plan view of the embodiment shown in FIG. 8.<Tb> FIG. 10 shows a perspective view of a portion of a downstream fuel injector according to an alternative embodiment of the present invention.<Tb> FIG. 11 <SEP> is a plan view of the embodiment shown in FIG.
    DETAILED DESCRIPTION OF THE INVENTION
    In the text below, certain terms have been chosen to describe the present invention. Wherever possible, these terms have been selected based on the industry standard terminology. However, it will be appreciated that such terms are often subjected to different interpretations. For example, what may be described herein as a single component may be referred to in other context as consisting of multiple components, or what may be described herein as comprising a plurality of components may be referred to elsewhere as a single component. Thus, with the understanding of the scope of the present invention, attention should be given not only to the specific terminology but also to the accompanying description and context, as well as the structure, structure, function and / or use of the component to which reference is made and which is described, including the manner in which the term refers to the various figures, as well as, of course, the precise use of the terminology in the appended claims.
    As some descriptive terms are used regularly in the description of the components and systems within the turbines, it should be helpful to define these terms at the beginning of this section. Accordingly, unless otherwise specified, these terms and their definitions are as follows. Without further specification, the terms "up" and "down" refer to directions with respect to the orientation of the gas turbine. That "Front" refers to the front or compressor end of the turbine and "rear" refers to the turbine's rear or turbine end. It will be appreciated that each of these terms can be used to refer to a movement or relative position within the turbine. The terms "downstream" and "upstream" are used to refer to a position within a specified channel with respect to the general direction of the flow moving therethrough. (It will be appreciated that these terms refer to a direction with respect to expected flow during normal operation, which should be readily apparent to one of ordinary skill in the art.) The term "downstream" corresponds to the direction in which a fluid flows through the specified channel while refers to "upstream" in the opposite direction.
    For example, the primary flow of the working fluid through a turbine consisting of the air passing through the compressor and subsequently becoming combustion gases within and beyond the combustion chamber may thus begin as at an upstream location at an upstream end of the compressor and terminating at a downstream location at a downstream end of the turbine. With regard to the description of the flow direction within a combustor of common type, as described in more detail below, it will be appreciated that the compressor exit air typically enters the combustor through impingement orifices (with respect to the longitudinal axis of the combustor and the compressor / turbine positioning described below , which defines the difference between front and rear) to focus against the rear end of the combustion chamber. Once in the combustion chamber, the compressed air is guided from a flow annulus formed around an inner chamber toward the front end of the combustion chamber where the air flow enters the inner chamber and its flow direction reverses toward the rear end the combustion chamber flows. The coolant through cooling passages can be treated in the same way.
    With the given means of the compressor and turbine around a common axis as well as the cylindrical structure common to many types of combustors, terms describing a position with respect to an axis are used. In this regard, it will be appreciated that the term "radial" refers to a movement or position perpendicular to an axis. Related to this, it may be necessary to describe a relative distance to the central axis. In this case, when a first component is closer to the central axis than a second component, it is defined herein that the first component is "radially inward of" or "within" the second component. On the other hand, if the first component is farther away from the central axis than the second component, it will be determined herein that the first component is "radially outward of" or "outside" the second component. In addition, it will be appreciated that the term "axial" refers to a movement or position parallel to an axis. Finally, the term "circumferentially" or "circumferentially" refers to a movement or position about an axis. As noted, although these terms may be applied to a common centerline extending through the compressor and turbine sections of the engine, these terms may also be applied to other components or subsystems of the turbine. For example, in the case of a cylindrically shaped combustor common to many turbines, the axis which gives these terms the relative meaning may be the longitudinal center axis extending through the center of the cylindrical cross-sectional shape which is first cylindrical but one more circular profile shape as it approaches the turbine.
    The following description provides examples of both conventional technology and of the present invention, as well as, in the case of the present invention, some examples of implementation and illustrative embodiments. It will be appreciated, however, that the following examples are not intended to be exhaustive of all possible applications of the invention. Further, while the examples below are illustrated with respect to a particular type of turbine, the technology of the present invention may also be applicable to other types of turbine, as one skilled in the relevant technology would understand.
    Fig. 1 is a cross-sectional view of a conventional gas turbine 10 in which the embodiments of the present invention may be used. As shown, the gas turbine 10 generally includes a compressor 11, one or more combustors 12, and a turbine 13. It will be appreciated that a flow path is defined by the gas turbine 10. During normal operation, air may flow into the gas turbine engine 10 through an inlet section and is then conveyed to a compressor 11. The plurality of axially stacked stages of rotating blades within the compressor 11 compress the air flow to produce a supply of compressed air. The compressed air flows through a nozzle into the combustion chamber 12, within which it is mixed with a fuel supply, so as to form an air-fuel mixture. The air-fuel mixture is burned within the combustion zone portion of the combustion chamber, so that a high-energy flow of hot gases is generated. This energetic flow of hot gases then becomes the working fluid which expands through the turbine 13 which deprives it of energy.
    Fig. 2 illustrates an exemplary combustor 12 in which embodiments of the present invention may be used. As one of ordinary skill in the art will appreciate, the combustor 12 is defined by a forward end, which is typically referred to as the head end 15, and a rear end that may be defined by a rear frame 16 that defines the combustor 12 with the turbine 13 connects. A primary nozzle 17 may be disposed toward the front end of the combustion chamber 12. The primary nozzle 17 is the component that brings together and mixes most of the fuel and air that are combusted within the combustor 12. As illustrated, the head end 15 generally provides the various manifolds, devices and / or fuel lines 18 that supply the fuel to the nozzle 17. The head end 15 may also include an end cap 19 forming the front axial boundary of the large cavity formed within the combustion chamber 12 through which the flow path of the working fluid is defined.
    As illustrated, the interior of the combustor may be divided into a number of smaller chambers configured to direct the working fluid along a desired path. These may include a first chamber typically defined within a component referred to as a cap assembly 21. The cap assembly 21 receives and supports structurally the primary nozzle 17 which, as illustrated, may be disposed at its rear end. The cap assembly 21 generally extends rearwardly from a joint that makes it to the end cap 19 and is surrounded by a combustor shell 29 formed therearound. It will be appreciated that the cap assembly 21 and combustor housing 29 form an annular space flow path therebetween that may continue in a rearward direction, as described in more detail below. This flow path is referred to herein as an annulus flow path 28. As illustrated, a second chamber may be located just behind the primary nozzle 17. Within the second chamber, a combustion zone 23 is defined, in which the combined in the nozzle 17, fuel-air mixture is burned. The combustion zone 23 may be defined circumferentially by a liner 24. The second chamber may extend from the liner 24 through a transition section toward the connection that establishes the combustor 12 with the turbine 13. Although other configurations within this transition section are also possible, the cross-sectional area of the second chamber transitions from a circular shape of the combustion zone 23 to a more circular shape required for injection of the combustion gases into the turbine 13.
    Around the liner 24 around a flow sleeve 25 is arranged. The liner 24 and the flow sleeve 25 may have a cylindrical shape and be arranged in a concentric cylindrical configuration. In this way, the flow annulus 28 formed between the cap assembly 21 and the combustor shell 29 continues in a rearward direction. Similarly, as illustrated, an impingement sleeve 27 may surround the transition piece 26 so that the flow annulus 28 extends further rearwardly. According to the example provided, the flow annulus 28 may extend approximately from the end cap 19 to the rear frame 29. The flow sleeve 25 and / or the baffle sleeve 27 may include a plurality of baffles 32 which allow a flow of compressed air external to the combustion chamber 12 to enter the flow annulus 28. It will be appreciated that, as illustrated, a compressor discharge housing 34 may define approximately at least a portion of the combustion chamber 12 and the compressor discharge cavity 35. The user outlet cavity 35 may be configured to receive a supply of compressed air from the compressor 11 such that the supply of compressed air then enters the flow annulus 28 of the combustor 12 through the impingement openings 32. At least some of the impingement ports 32 may be configured to impinge the airflow against the liner 24 and / or the transition piece 26, thereby achieving efficient convective cooling of that region. In particular, the impinged flow serves to convectively cool the outer surfaces of the liner 24 and / or the transition piece 26. Once in the flow annulus 28, the compressed air is directed toward the forward end of the combustor 12. Then, the compressed air is directed via the inlets 31 in the cap assembly 21 into the interior of the cap assembly 21 and conveyed towards the primary nozzle 17, where it is mixed with a fuel.
    It will be appreciated that the pairings cap assembly 21 / combustion chamber housing 29, lining 24 / flow sleeve 25 and transition piece 26 / impact sleeve 27 expand the flow annulus 28 along almost the entire length of the combustion chamber 12. As used herein, the term "flow annulus 28" may generally be used to refer to that entire annulus or any of its sections. Specific portions of the flow annulus 28 may be more particularly referred to herein with the following terminology: a forward annulus portion 36 is defined as the portion formed between the cap assembly 21 and the combustor shell 29; a middle annulus portion 37 is defined as the portion formed between the liner 24 and the flow sleeve 25; and a rear annular space portion 38 is defined as the portion formed between the transition piece 26 and the impact sleeve 27.
    It will be appreciated that the cap assembly 21 and the combustion zone 23 defined by the liner 24 and / or the transition piece 26 may be described as forming axially stacked chambers, referred to herein as first and second chambers, respectively becomes. As shown, these first and second chambers are separated at the primary nozzle 17. In addition, the concentrically disposed cylindrical walls forming the flow annulus 28 may be referred to herein as inner and outer radial walls.
    The primary nozzle 17 represents the primary fuel supply component within the combustor 12 and may be located at the rear end of the cap assembly 21, as illustrated. It will be appreciated that the manner in which primary nozzle 17 combines and mixes the input fuel with the supplied air may include many different configurations. For example, the primary nozzle 17 may include mixing tubes, swirl nozzle configurations, micromixing technologies, etc. The primary nozzle 17 may further include an array of fuel injectors supplied by a plurality of fuel lines 18. The fuel may be, for example, natural gas, although other types of fuel are also possible.
    As also indicated in Fig. 2, a plurality of guide vanes 41 may be provided within the flow annulus 28. The vanes 41 may take various forms. The vanes 41 typically have a wing profile shape or a narrow profile and extend between a joint formed with the inner radial wall and a joint formed with an outer radial wall. The vanes 41 may be circumferentially spaced around the circumference of the cap assembly 21. In this way, the blades 41 provide structural support for the cap assembly 21 and the primary nozzles 17 contained therein.
    FIG. 3 provides a cross-sectional view of a liner 25 / flow sleeve 26 assembly including a downstream injection system 44 (referred to as a late lean-mix injection system) in accordance with certain aspects of the present invention. As used herein, a "downstream injection system" is a system for injecting a mixture of fuel and air into the flow of the working fluid at a point downstream of the primary nozzle 17 and upstream of the turbine 13. One of the goals of downstream injection systems generally comprises Enabling fuel combustion to take place downstream of primary combustors / primary combustion zone. This type of operation can be used to improve NOx emission performance. As shown, the late fuel injection system 44 includes a downstream nozzle 45 within which the supply of fuel and air are combined and, as indicated, injected into a downstream portion of the combustion zone 23. The system 44 may also include a fuel passageway 47 defined within the flow sleeve 26. The fuel passageway 47 may connect an upstream end to a fuel manifold 48 which, as indicated, may be present within a flow sleeve flange, although other configurations are also possible. The fuel passageway 47 may extend from the fuel manifold 48 to a fuel plenum 49 formed within the downstream nozzle 45.
    As indicated in Fig. 4, the downstream nozzle 45 may include a fuel injector 51 containing a fuel plenum 52 which supplies a number of fuel ports 53 disposed within the downstream nozzle 45 so as to supply the fuel with an air supply which is taken from the flow annulus 20 or from another location to mix. A transfer or injector tube 54 may then convey the fuel-air mixture through the entire flow annulus 28 for injection into the combustion zone 23. More specifically, the injector tube 54 provides a conduit for directing the fuel-air mixture through the entire flow annulus 28 where it can then be injected into the flow of a hot gas within the liner 24 for combustion. As shown, a cover or air shield 55 may be provided so as to form a chamber 56 within which the fuel-air mixture may be merged for mixing. It will be appreciated that the air shield 55 also serves to substantially isolate the downstream nozzle 45 from the surrounding compressor outlet cavity 35.
    It will be appreciated that the downstream nozzle 45 may be installed in a similar manner also at locations further forward or rearward in the combustor 12 than those shown in the various figures, or actually at any location there is a flow assembly having the same basic configuration as that described for the liner 24 / flow sleeve 25 assembly described above. For example, using the same base components, the downstream nozzle 45 may also be disposed within the transition piece 26 / impact sleeve 27 assembly. As one of ordinary skill in the art will recognize, this design may be advantageous in providing certain criteria and operator preferences. While the various created figures are directed to an exemplary embodiment within the liner 24 / flow sleeve 25 assembly, it will be appreciated that this is not meant to be limiting. Accordingly, as the following description refers to an "outer radial wall," it will be appreciated that this could refer to a flow sleeve 25, an impact sleeve 27, or similar component, unless otherwise described. And, when the following description refers to an "inner radial wall", it will be appreciated that this could refer to the liner 24, the transition piece 25, or a similar component, unless otherwise described.
    A particular problem relating to the use of such downstream nozzles 45 is the negative effect of the wake flow caused by the injector tube 54 within the flow annulus 28. As noted, the wake flow may result in poorly mixed flow at the head end that adversely affects combustion and NOx emissions. The wake flow may also adversely affect the cooling of the inner radial wall just downstream of the injector tube 54, to which reference is made, as indicated in FIG. 4, as the "target area 59". In particular, the "dead zone", which results just downstream of the injector tube 54, affects the cooling of the target area by interrupting the flow and thereby adversely affecting the heat transfer coefficient.
    Figures 5-7 provide embodiments of downstream fuel nozzles 40 that may be used in accordance with the present invention to mitigate the adverse effects associated with the injector tube 54 and disrupt the flow annulus 28. As described in more detail below, generally a collection space 52 is provided within the flow annulus 28 that is supplied with a supply of compressed air from the compressor discharge cavity 35, and a flow from the collection space 52 is directed through a plurality of impingement openings 63 into an area where the wake-up flow occurs to reduce it while at the same time providing additional cooling to the target area. The plenum 61 and baffles 63 may be sized so as to provide adequate cooling while at the same time providing sufficient air to "top up" the wake flow location downstream of the injector tube 54 so as to eliminate any head end distribution problems. In addition, an upstream nose feature 68 may be provided on the upstream side of the injector tube 54 to enhance the aerodynamic profile of the injector tube, thereby reducing the resulting shaft. By providing a uniform air distribution to the head end, the primary nozzle 17 will receive a uniform air distribution, thereby providing a uniform fuel-air mixture which will allow the head end to operate at maximum power, thereby maximizing output while simultaneously emitting emissions be minimized. The cooling of the target area 69 prolongs the part life of the liner, which increases the time between combustion intervals and reduces repair costs associated with damaged components.
    The downstream nozzle 45 may include an injector tube 54 extending between the outer radial wall and the inner radial wall. Between the outer radial wall and the inner radial wall, the injector tube 54 may include a solid structure configured to separate a flow moving through the injector tube 54 from the flow through the flow annulus. As before, depending on the axial location of the downstream nozzle 45, the outer radial wall may include the combustor housing 29, the flow sleeve 25, or the impingement sleeve 27. Accordingly, the inner radial wall may include the cap assembly 21, the liner 14 or the transition piece 26. In a preferred embodiment, as illustrated in FIG. 3, the outer radial wall is the flow sleeve 25, and the inner radial wall is the liner 44. As shown, a plenum 61 (referred to herein as the "first plenum 61" can be formed) adjacent to the injector 54 may be formed. The first collection space 61 may include a ceiling 65 and a floor 66. As used herein, the blanket 65 is the outer radial boundary of the first collection space 61, while the bottom 66 is the inner radial boundary. According to preferred embodiments, the bottom 66 is disposed between the inner radial wall and the outer radial wall. As shown, one or more supply passages 62 are provided to connect the first plenum 61 to an inlet formed externally of the outer radial wall. The downstream nozzle 45 also includes baffles 63 formed through the bottom 66 in such a manner that a compressed fluid within the first collection space 61 can be expelled into the flow annulus 28.
    According to the present invention, the configuration of the first annulus 61 can be varied. As illustrated, a preferred embodiment includes at least a portion of the first plenum 61 disposed adjacent to a downstream side of the injector tube 54. It will be appreciated that when defined with respect to an expected flow through the flow annulus 28 during operation, the injector tube 54 may be described as having an upstream side and a downstream side. As described, compressed air from the compressor 11 is supplied to the combustor outlet cavity 35 formed around the combustor during operation. The compressed air then flows into the flow annulus 28 through the apertures 32 formed within the impingement sleeve 27 and the flow sleeve 25 to develop a fast moving flow through the annulus 28 that is toward the forward end of the combustor 12 is directed. Accordingly, in providing this flow direction through the annulus 28, the downstream side of the injector tube 54 is the forward side (i.e., the side facing the head end 15 of the combustor 12). In an alternative embodiment, the first plenum 61 is formed adjacent to only this downstream side of the injector tube 54. According to a preferred embodiment, as shown, the first plenum 61 is formed as an annular space around the injector tube 54. In this case, the impact holes 63 may be distributed on the bottom 66 of the first plenum 61 so as to be concentrated or formed only in the downstream portion of the first plenum 61.
    The target region 59 is a region on the outer surface of the inner radial wall that occurs just downstream and adjacent to the injector tube 54. The target area 59 is, as mentioned, the area most affected by the wake, which is formed downstream of the injector tube 54. That is, the injector tube 54 interrupts the flow through the annulus 28 and adversely affects the convective cooling of the target region 59 by the flow. According to the preferred embodiments, the baffle openings 63 may be arranged inside the downstream portion of the first collection space 61 to direct a compressed fluid ejected from the first collection space 61 toward the target area 59. It will be appreciated that this additional coolant flow may be used to address the cooling imperfections within the target area 59 caused by the wake flow of the injector tube 54. The outflow of air through the baffles 63 also acts to "top up" the air that has been separated by the injector tube 54, thereby minimizing disruption and maximizing uniformity within the flow as it is supplied to the primary nozzle 17. According to a preferred embodiment, the downstream portion of the first plenum 61 includes at least 8 of the impingement orifices 63. The eight impingement orifices 63 may be uniformly spaced in a manner corresponding to the target region 59. As best illustrated in FIG. 7, the first plenum 61 may have a cantilevered configuration in which a downstream portion of the first plenum 61 protrudes from the downstream side of the injector tube 54. In such cases, the target area 59 may be defined as the outer surface of the inner radial wall overhung by the downstream portion of the first plenum 61. The impact openings 63 may be aligned substantially perpendicular to a flow direction through the flow annulus.
    The bottom 66 of the first plenum 61 may be disposed in proximity to the outer surface of the inner radial wall to thereby enhance the cooling effect exhibited by the flow through the impingement ports. The ceiling 65 of the first plenum 61 may be located near the outer radial wall. The bottom 66 of the first plenum 61 may have a planar configuration that is substantially parallel to the outer surface of the inner radial wall. According to a preferred embodiment, the bottom 66 of the first plenum 61 may be located approximately midway between the outer surface of the inner radial wall and the inner surface of the outer radial wall. The ceiling 65 of the first plenum 61 may be located slightly outboard from the outer radial wall. According to an alternative embodiment, the ceiling 65 of the first collecting space 61 can be arranged just inside from the outer radial wall.
    As illustrated, the supply channel 62 may be configured to pass through the outer radial wall between an inlet disposed outwardly from the outer radial wall and an outlet internally disposed from the outer radial wall , to extend therethrough and may be adapted to be in fluid communication with the plenum 61. As described, a compressor outlet housing 34 defines a compressor outlet cavity around the combustion chamber. As illustrated, the inlet of the feed channel 62 may be configured to be in fluid communication with the compressor outlet cavity 35. According to an alternative embodiment, several of the feed channels 62 may be provided. As illustrated in FIGS. 5 and 7, two feed channels 62 may be provided and arranged on substantially opposite sides of the downstream nozzle 45.
    The downstream nozzle may further include an air shield 55 as shown. The air shield may include a wall extending outboard from an injector footprint defined on an outer surface of the outer radial wall. The air shield 55 may be configured to substantially separate the interior of the downstream nozzle 45 from the compressor outlet cavity 35. In a preferred embodiment, the supply channel 62 is configured to extend through the air shield 55 so as to be in fluid communication with the compressor outlet cavity 35. It will be appreciated that the supply of the first plenum 61 in this manner provides a flow of sufficient pressure to effectively cool the target region 59 while preventing any possible backflow from the annulus 28.
    The upstream side of the injector tube 54 may include an aerodynamic nose feature 68, as illustrated in FIG. 6. The aerodynamic nose feature 68 may include an aerodynamic profile that mitigates the formation of wakeful flow downstream of the injector tube 54. In a preferred embodiment, the aerodynamic nose feature 68, as illustrated, may include a narrow profile that includes a sharp point at an upstream end. The aerodynamic nose feature may have an inboard position with respect to the first plenum 61.
    Similar to the downstream nozzle 45 shown in FIG. 4, the downstream nozzle 45 according to FIGS. 5 to 7 may include a fuel injector 51 in which a fuel plenum 52 formed around the injector pipe 54 has a number of fuel ports 53 which are designed to inject fuel into a supply of compressed air which is directed into the injector tube 54. In a preferred embodiment, the first plenum 52 communicates with a fuel passageway formed within the outer radial wall. Other configurations for fuel delivery are also possible. As illustrated, the downstream nozzle 45 may also include a mixing plenum or mixing chamber 56 to merge the fuel and air before the mixed flow is directed into the injector tube 54. It will be appreciated that the chamber 56 is connected to a first end of the injector tube 54, while a second end of the injector tube 54 is connected to the combustion zone through the inner radial wall of the combustor 12. The downstream nozzle 45 may be included within a late lean-mix injection system configured to inject a mixture of fuel and air within a rearward end of the combustion zone defined by the liner. Such systems may include various downstream nozzles 45 arranged circumferentially around the combustion zone 23.
    Figures 8 to 11 illustrate an alternative embodiment in which the baffles 63 are replaced by a slot 71 formed through the downstream portion of the bottom 66 of the first collection space 61. When so configured, the slot 71 may be used to direct a greater volume of air to the wake flow area that forms, as described, just downstream of the injector tube 54. This volume of air flowing through the first plenum 61 and injected into the wake flow area may be adjusted by varying the size of the slot 71 so that disturbance of the annulus flow just downstream of the injector tube 54 is minimized. With reference to Figure 9, the slot 71 may have a profile with side walls 72 which narrows the opening while the slot extends in the downstream direction. It will be appreciated that with this profile, the airflow from the first plenum can be concentrated in the area most affected by the flow interruption by the injector tube 54. The tapered flow area of the tapered profile also increases the velocity of the flow, which improves its cooling properties.
    Referring to Figures 10 and 11, an alternative embodiment may include the slot 71 described above, which is combined with a screen 73. As shown, the screen 73 may include a number of screen openings 75 that are aligned approximately parallel to the flow through the annulus. The screen openings 75 may serve to condition the flow of air injected into the annulus flow path, thereby limiting aerodynamic losses. The screen openings 75 can also be used to measure the flow in this area. As shown, the screen 73 may also include a slot opening 77 disposed along the inner radial edge of the screen 73. The slot opening 77 may be aligned approximately parallel to the inner radial wall or lining 24, as shown. The slot opening 75 may be used to thereby concentrate a flow of coolant along the outer surface of the liner 24. The slit opening 77 may be another way by which the flow from the first plenum 61 is sized to thereby improve performance. It will be appreciated that the screen openings 75 condition the flow being injected, thereby mitigating the aerodynamic disturbance downstream of the injector tube 54, while the slot opening 77 may be used to cope especially with the frequent cooling problems.
    Although the invention has been described in conjunction with what is presently considered to be the most practical and preferred embodiment, it should be understood that the invention is not limited to the disclosed embodiment, but on the contrary, various modifications and equivalent arrangements It is intended to cover, to the extent that they come within the scope and scope of the appended claims.
    A downstream nozzle for use in a combustion chamber includes an inner radial wall defining a combustion zone downstream of a primary nozzle and an outer radial wall surrounding the inner radial wall so as to form a flow annulus between them. The downstream nozzle may include: an injector tube extending between the outer radial wall and the inner radial wall; a first plenum adjacent to the injector tube, and, inside a ceiling, a bottom disposed between the inner radial wall and the outer radial wall. A supply passage may connect the first collection space to an inlet formed externally of the outer radial wall, and baffle openings may be formed through the bottom of the first collection space.
    权利要求:
    Claims (10)
    [1]
    A downstream nozzle in a combustion chamber of a combustion turbine, the combustion chamber including an inner radial wall defining a combustion zone downstream of a primary nozzle, and an outer radial wall surrounding the inner radial wall to form a flow annulus therebetween, the downstream ones Nozzle comprises:an injector tube extending between the outer radial wall and the inner radial wall;a first plenum adjacent to the injector tube, the first plenum containing a ceiling and a floor interior from the ceiling, the floor being disposed between the inner radial wall and the outer radial wall;a supply passage connecting the first collection space to an inlet formed outside of the outer radial wall; andan opening formed through the bottom of the first collection space.
    [2]
    2. The downstream nozzle of claim 1, wherein the injector tube includes an upstream side and a downstream side defined relative to an expected flow through the flow annulus during operation of the combustion turbine;wherein a downstream portion of the first plenum is disposed adjacent to the downstream side of the injector tube and includes at least a plurality of the impingement ports; andwherein an outer surface of the inner radial wall across the flow annulus faces an inner surface of the outer radial wall;wherein the supply passage preferably extends through the outer radial wall between an inlet located outside of the outer radial wall and an outlet located inside of the outer radial wall, and configured to communicate with the first collection space in To be fluid connection.
    [3]
    3. The downstream nozzle of claim 2, wherein the outer surface of the inner radial wall includes a target region defined just downstream of and adjacent to the injector tube; andwherein the plurality of impingement openings are arranged within the downstream portion of the first plenum to direct a pressurized fluid ejected therefrom toward the target area;the downstream portion of the first plenum preferably having at least 8 of the impingement openings; andwherein the at least 8 baffles are preferably equally spaced so as to correspond to the target area.
    [4]
    The downstream nozzle according to claim 2 or 3, wherein the first collection space has a cantilever configuration in which a downstream portion of the first collection space protrudes from the downstream side of the injector tube;a target area having the outer surface of the inner radial wall overhanging the cantilevered downstream portion of the first plenum; andwherein the downstream portion of the first collection space has a plurality of the baffles facing the target area.
    [5]
    5. The downstream nozzle of claim 2 or 3, wherein the first plenum is configured to overhang a target area defined on the outer surface of the inner radial wall, the target area being located just downstream of the injector tube;the baffles having a configuration that adjusts each baffle opening to the target area; andthe bottom of the first plenum having a planar configuration substantially parallel to the outer surface of the inner radial wall; andwherein the bottom of the first plenum is located approximately midway between the outer surface of the inner radial wall and the inner surface of the outer radial wall;wherein the ceiling of the first collection space is preferably located just outside of the outer radial wall;wherein the baffles are preferably aligned substantially perpendicular to a direction of flow through the flow annulus; andthe downstream nozzle preferably including a plurality of the supply channels, the plurality of supply channels including at least two supply channels arranged on substantially opposite sides of the downstream nozzle.
    [6]
    6. A downstream nozzle according to any of claims 2-5, wherein a compressor outlet housing defines a compressor outlet cavity around the combustion chamber;wherein the inlet of the supply channel is adapted to be in fluid communication with the compressor outlet cavity; and orfurther comprising an air shield, the air shield including a wall extending outwardly from an injector footprint defined on an outer surface of the outer radial wall, the air shield configured to substantially surround an interior of the downstream nozzle from the compressor outlet cavity to separate; wherein the supply channel is configured to extend through the air shield so as to be in fluid communication with the compressor outlet cavity.
    [7]
    7. A downstream nozzle according to any of claims 2-6, wherein the first plenum forms an annulus around the injector tube; the baffles being distributed over the bottom of the first plenum so as to have a concentration within the downstream portion of the first plenum; and orwherein the downstream side of the injector tube has an aerodynamic nose feature; wherein the aerodynamic nose feature preferably narrows to a sharp point directed in a downstream direction relative to the expected flow through the flow annulus; and wherein the aerodynamic nose feature preferably has an inboard position with respect to the first plenum.
    [8]
    The downstream nozzle of any of claims 2-7, wherein the downstream nozzle further comprises:a fuel plenum formed around the injector tube, the fuel plenum containing a connection to a longitudinal fuel supply passage within the outer radial wall; anda mixed collection space configured to contain air supply and fuel injection ports respectively connected to the fuel collection space;wherein the mixing plenum is connected to a first end of the injector tube; andwherein a second end of the injector tube is connected to the combustion zone through the inner radial wall; andwherein between the outer radial wall and the inner radial wall, the injector tube has a separation structure configured to separate a flow moving through the injector tube from the flow moving through the flow annulus.
    [9]
    A downstream nozzle according to any one of the preceding claims, wherein the opening has a slot formed through the bottom of the first plenum, the slot having a tapered profile which narrows with the downstream extent of the slot;the slot preferably including a screen formed on a downstream wall, the screen including a plurality of openings and a slot opening formed proximate and approximately parallel to the inner radial wall of the combustion chamber.
    [10]
    A late lean injection injector in a combustion chamber of a combustion turbine, wherein the combustion chamber includes a liner defining a combustion zone downstream of a primary nozzle and a flow sleeve surrounding the liner so as to form a flow annulus therebetween, the late lean injection injector having:an injector tube extending between the outer radial wall and the inner radial wall;a first plenum forming an annulus around the injector tube, the first plenum including a ceiling and a floor interior from the ceiling, the floor being disposed between the inner radial wall and the outer radial wall;a supply passage connecting the first collection space to an inlet formed outwardly from the outer radial wall; andBaffle openings formed through the bottom of the first collection space;wherein the impingement openings are distributed over the bottom of the first plenum such that they have a concentration within a downstream portion of the first plenum; andwherein the outer surface of the inner radial wall includes a target region defined just downstream of and adjacent to the injector tube, and wherein the concentration of the impingement ports within the downstream portion of the first plenum is directed to the target region.
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    同族专利:
    公开号 | 公开日
    US20160047317A1|2016-02-18|
    CN105371300A|2016-03-02|
    JP2016041929A|2016-03-31|
    CN105371300B|2020-12-11|
    DE102015112767A1|2016-02-18|
    JP6708380B2|2020-06-10|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    EP3220054A1|2016-03-15|2017-09-20|General Electric Company|Staged fuel and air injectors in combustion systems of gas turbiines|JPS5618577U|1979-07-18|1981-02-18|
    JPH01123068U|1988-02-15|1989-08-22|
    US5402635A|1993-09-09|1995-04-04|Westinghouse Electric Corporation|Gas turbine combustor with cooling cross-flame tube connector|
    US6557350B2|2001-05-17|2003-05-06|General Electric Company|Method and apparatus for cooling gas turbine engine igniter tubes|
    JP2004317008A|2003-04-15|2004-11-11|Toshiba Corp|Gas turbine combustor|
    DE10336530B3|2003-08-05|2005-02-17|Leinemann Gmbh & Co.|Flame arrester|
    FR2926329B1|2008-01-15|2013-01-04|Snecma|ARRANGEMENT OF A SEMICONDUCTOR TYPE CANDLE IN A COMBUSTION CHAMBER OF A GAS TURBINE ENGINE.|
    JP4797079B2|2009-03-13|2011-10-19|川崎重工業株式会社|Gas turbine combustor|
    US8381532B2|2010-01-27|2013-02-26|General Electric Company|Bled diffuser fed secondary combustion system for gas turbines|
    US8863525B2|2011-01-03|2014-10-21|General Electric Company|Combustor with fuel staggering for flame holding mitigation|
    US8407892B2|2011-08-05|2013-04-02|General Electric Company|Methods relating to integrating late lean injection into combustion turbine engines|
    EP2742291B1|2011-08-11|2020-07-08|General Electric Company|System for injecting fuel in a gas turbine engine|
    JP5393745B2|2011-09-05|2014-01-22|川崎重工業株式会社|Gas turbine combustor|
    WO2013043076A1|2011-09-22|2013-03-28|General Electric Company|Combustor and method for supplying fuel to a combustor|
    US20130104553A1|2011-11-01|2013-05-02|General Electric Company|Injection apparatus|
    US9170024B2|2012-01-06|2015-10-27|General Electric Company|System and method for supplying a working fluid to a combustor|
    US20130213046A1|2012-02-16|2013-08-22|General Electric Company|Late lean injection system|
    US9097424B2|2012-03-12|2015-08-04|General Electric Company|System for supplying a fuel and working fluid mixture to a combustor|
    US9310078B2|2012-10-31|2016-04-12|General Electric Company|Fuel injection assemblies in combustion turbine engines|
    US9400113B2|2014-06-12|2016-07-26|Kawasaki Jukogyo Kabushiki Kaisha|Multifuel gas turbine combustor|US10060629B2|2015-02-20|2018-08-28|United Technologies Corporation|Angled radial fuel/air delivery system for combustor|
    US9945294B2|2015-12-22|2018-04-17|General Electric Company|Staged fuel and air injection in combustion systems of gas turbines|
    US20170268785A1|2016-03-15|2017-09-21|General Electric Company|Staged fuel and air injectors in combustion systems of gas turbines|
    US20170268783A1|2016-03-15|2017-09-21|General Electric Company|Axially staged fuel injector assembly mounting|
    US10228135B2|2016-03-15|2019-03-12|General Electric Company|Combustion liner cooling|
    US10260424B2|2016-03-24|2019-04-16|General Electric Company|Transition duct assembly with late injection features|
    US10415831B2|2016-10-27|2019-09-17|General Electric Company|Combustor assembly with mounted auxiliary component|
    US10739002B2|2016-12-19|2020-08-11|General Electric Company|Fluidic nozzle assembly for a turbine engine|
    US10718523B2|2017-05-12|2020-07-21|General Electric Company|Fuel injectors with multiple outlet slots for use in gas turbine combustor|
    US10690349B2|2017-09-01|2020-06-23|General Electric Company|Premixing fuel injectors and methods of use in gas turbine combustor|
    US11174792B2|2019-05-21|2021-11-16|General Electric Company|System and method for high frequency acoustic dampers with baffles|
    US11156164B2|2019-05-21|2021-10-26|General Electric Company|System and method for high frequency accoustic dampers with caps|
    法律状态:
    2017-03-15| NV| New agent|Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH |
    2019-05-31| AZW| Rejection (application)|
    优先权:
    申请号 | 申请日 | 专利标题
    US14/459,397|US20160047317A1|2014-08-14|2014-08-14|Fuel injector assemblies in combustion turbine engines|
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