• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
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    • 专利摘要:
    A fuel nozzle for a gas turbine includes: an elongate centerbody; an axially elongated peripheral wall formed about the central body to define a primary flow annulus therebetween; a primary fuel supply and a primary air supply in the primary flow annulus; and a pilot nozzle (40). The pilot nozzle (40) has a downstream portion of the centerbody and includes: axial elongated mixing tubes defined within a centerbody wall; a fuel port disposed on the mixing tubes for connection to each of a secondary fuel supply; and a secondary air supply configured to communicate with an inlet of each of the mixing tubes in fluid communication. Several of the mixing tubes are formed as inclined mixing tubes (41) adapted to induce a swirling downstream flow, while a plurality of the mixing tubes are axial mixing tubes.
    公开号:CH710573A2
    申请号:CH01831/15
    申请日:2015-12-14
    公开日:2016-06-30
    发明作者:Thurman Stewart Jason；Cole Wilson Charlotte；Marshall Washam Roy
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    BACKGROUND OF THE INVENTION
    The present invention relates generally to a gas turbine combusting an air-mixed hydrocarbon fuel to produce a high temperature gas stream that drives turbine blades to rotate a shaft connected to the blades. In particular, but not by way of limitation, the invention relates to combustor fuel jets containing pilot nozzles which premix a fuel and air to achieve lower nitrogen oxide levels.
    Gas turbines are widely used to produce power for many applications. A conventional gas turbine includes a compressor, a combustor and a turbine. In a typical gas turbine, the compressor introduces compressed air to the combustion chamber. The entering into the combustion chamber air is mixed with fuel and burned. Hot combustion gases are exhausted from the combustion chamber and flow into the blades of the turbine to rotate the turbine shaft connected to the blades. Part of this mechanical energy of the rotating shaft drives the compressor and / or other mechanical systems.
    Since government regulations disapprove of the release of nitrogen oxides in the atmosphere, it is desirable to keep their production as by-products of the operation of gas turbines below allowable levels. One approach to meeting such regulations is to switch from diffusion flame combustors to combustors that use lean fuel-air mixtures in a fully premixed mode of operation to control emissions of, for example, nitrogen oxides (commonly denoted NOx) and carbon monoxide (CO). to reduce. These combustors are variously known in the art as dry low NOx (DLN) (dry low NO x), dry low emission (DLE) (dry low emission) or lean premixed (LPM) (lean premix) combustion systems.
    Fuel-air mixing affects both the levels of nitrogen oxides produced in the hot combustion gases of a gas turbine and machine performance. A gas turbine may utilize one or more fuel nozzles to receive air and fuel to assist in fuel-air mixing in the combustion chamber. The fuel nozzles may be disposed in a head end of the combustion chamber and may be configured to receive an airflow that is mixed with a fuel input. Each fuel nozzle may typically be internally supported by a centerbody disposed within the fuel nozzle, and a pilot nozzle may be disposed at the downstream end of the centerbody. For example, as described in US Pat. No. 6,438,961, which is incorporated herein by reference in its entirety for all purposes, a so-called swozzle (integrated swirler with nozzle) may be secured to the outside of the centerbody and located upstream of the pilot nozzle , The swozzle has curved vanes which extend radially from the centerbody over an annular flow channel and from which fuel is introduced into the annular flow channel to be entrained in an air stream which is swirled by the vanes of the swozzle.
    Various parameters describing the combustion process in the gas turbine correlate with the generation of nitrogen oxides. Higher gas temperatures in the combustion reaction zone are responsible, for example, for the generation of higher amounts of nitrogen oxide. One way to reduce these temperatures is to premix the fuel-air mixture and reduce the ratio of fuel to air that is burned. When the ratio of fuel to air that is burned is reduced, the amount of nitrogen oxides is also reduced. However, there is a trade-off in the performance of the gas turbine. For, if the ratio of fuel to air that is burned is reduced, there is an increased tendency for the flame of the fuel nozzle to go out, thus making the operation of the gas turbine unstable. A diffuser flame type pilot nozzle has been used for better flame stabilization in a combustor, but its use increases NOx emissions. Thus, there remains a need for improved pilot nozzle arrangements that provide flame stabilization benefits while also minimizing NOx emissions generally associated with pilot nozzles.
    BRIEF DESCRIPTION OF THE INVENTION
    The present application thus describes a fuel nozzle for a gas turbine. The fuel nozzle may include: an axially elongated centerbody; an axially elongated peripheral wall formed about the centerbody to define a primary flow annulus therebetween; a primary fuel supply and a primary air supply in fluid communication with an upstream end of the primary flow annulus; and a pilot nozzle. The pilot nozzle may be formed in the centerbody including: axially elongate mixing tubes defined within a centerbody wall, each of the mixing tubes being defined between an inlet defined by an upstream surface of the pilot nozzle and an outlet defined by a downstream one Surface of the pilot nozzle is formed, extends; a fuel port disposed between the inlet and the outlet of each of the mixing tubes for communicating each of the mixing tubes with a secondary fuel supply; and a secondary air supply configured to be in fluid communication with the inlet of each of the mixing tubes. Several of the mixing tubes may be formed as inclined mixing tubes which are adapted to induce a swirling flow around the central axis in a common outlet therefrom.
    In the aforementioned fuel nozzle, the slanted mixing tubes may be tangentially inclined with respect to the center axis of the fuel nozzle, the common outlet having a combined fuel and air outlet from the plurality of slanted mixing tubes; wherein the tilted mixing tubes may be configured such that the swirling flow of the common outlet swirls in the same direction as a swirling flow caused by swirling vanes of the primary flow annulus, and wherein the axial mixing tubes may be from the mixing tubes that are relative to the central axis the fuel nozzle are aligned in parallel.
    [0008] In a preferred embodiment, the mixing tubes may each comprise an outlet portion having an axially narrow downstream portion of the mixing tube located adjacent to the outlet, the outlet portion thereby defining a central axis, wherein the inclined mixing tubes may be configured such that a continuation of the center axis of the outlet portion has an acute tangential exit angle with respect to a downstream continuation of the center axis of the fuel nozzle, and wherein the axial mixing tubes may be configured so that a continuation of the center axis of the outlet portion has an exit angle of about 0 ° with respect to a downstream continuation of the center axis of the Has fuel nozzle.
    In the last-mentioned embodiment, the inclined mixing tubes each of the pilot nozzle may have a parallel arrangement with respect to each other, wherein the tangential exit angle of the inclined mixing tubes may have an angle between 10 ° and 70 °.
    Additionally or alternatively, the centerbody may include axially stacked sections including a forward section having a secondary fuel supply and a secondary air supply; and a rear portion configured as the pilot nozzle, wherein the front portion of the center body may include an axially extending central supply line and a secondary flow annulus formed around the central supply line extending axially between a connection made to an air source and in the direction of a is provided at the upstream end of the center body, and extends the upstream surface of the pilot nozzle, and wherein the center body wall defining an outer wall of the center body and may define an outer boundary of the secondary flow annulus.
    Further, the primary flow annulus may include a swozzle that may include a plurality of swirler vanes that may extend radially across the entire primary flow annulus; and fuel passages extending through the swirler vanes for connecting the fuel ports formed by an outer surface of the swirler vanes to a fuel plenum, the swirler vanes having a tangentially angled orientation with respect to the central axis to cause downstream flow thereof; which swirls around the central axis in a first direction.
    In the latter variant, the fuel port of each of the inclined mixing tubes and the axial mixing tubes may have a side fuel hole for injecting fuel through an opening formed in a side wall, wherein the fuel port for each of the inclined mixing tubes and the axial mixing tubes an upstream position may have relative to an air flow therethrough.
    Additionally or alternatively, the canted mixing tubes and each of the axial mixing tubes may include a plurality of fuel ports, wherein the plurality of fuel ports may have an upstream concentration relative to an air flow therethrough.
    Additionally or alternatively, as an alternative, the inclined mixing tubes and the axial mixing tubes may be configured to receive air flow through the inlet and fuel flow through the fuel aperture to dispense a mixture thereof through the outlet, the outlet can be in fluid communication with a combustion chamber of the combustion chamber.
    In each fuel nozzle having a side fuel opening, the axial mixing tubes may each have a mixing length defined between an upstream fuel opening and the outlet, wherein the mixing length of the axial mixing tube may have a linear configuration.
    In addition, the inclined mixing tubes may each have a mixed length defined between an upstream fuel port and the outlet, wherein, in terms of mixing length, the inclined mixing tubes each have a segmented configuration, including an upstream segment and a downstream segment on each side Compound that marks a change of direction for the inclined mixing tube may have.
    Further, the inclined mixing tubes may each have a configuration in which the upstream segment is linear and the downstream portion is curved.
    Still further, the inclined mixing tubes may each have a configuration in which the upstream segment is linear and axially aligned and the downstream segment is curved and spirally formed about the center axis of the fuel nozzle, the upstream portion being less than half the mixing length may have the inclined mixing tubes.
    In any fuel nozzle having a mixed length, as mentioned above, the tangential exit angle of the inclined mixing tubes may have an angle between 20 ° and 55 °.
    Additionally or alternatively, the inclined mixing tubes may be configured such that the swirling flow of the common outlet swirls in the first direction as defined by the direction of the swirling downstream flow created by the swirler vanes of the primary flow annulus becomes.
    In the latter variant, the pilot nozzle may have between five and twenty five of the inclined mixing tubes and between five and twenty five of the axial mixing tubes, wherein the inclined mixing tubes may be circumferentially spaced within the central body wall at regular intervals and wherein the axial mixing tubes are within the Center body wall may be spaced at regular intervals in the circumferential direction.
    Further, the plurality of inclined mixing tubes may have a relation to the plurality of axial mixing tubes outboard position.
    Still further, the plurality of tilted mixing tubes may have an internal position relative to the plurality of axial mixing tubes.
    Still further, the plurality of inclined mixing tubes and the plurality of axial mixing tubes may have the same number of mixing tubes.
    In a variant of the last-mentioned embodiment of the fuel nozzle, the downstream surface of the pilot nozzle may have an arrangement of the outputs in which the outputs of the inclined mixing tubes are angularly clocked with respect to the outputs of the axial mixing tubes, wherein the angular clocking of the arrangement of outputs can be that the outputs of the inclined mixing tubes are angularly offset with respect to the outputs of the axial mixing tubes.
    In a further variant, the downstream surface of the pilot nozzle may have an arrangement of the outputs in which the outputs of the inclined mixing tubes are angularly clocked with respect to the outputs of the axial mixing tubes, wherein the angular timing of the arrangement of the outlets may have the outlets the inclined mixing tubes are arranged such that they coincide angularly with the outlets of the axial mixing tubes.
    In each embodiment having between five and twenty five of the inclined mixing tubes and between five and twenty five of the axial mixing tubes, the inclined mixing tubes may be radially inclined with respect to the center axis of the fuel nozzle, the inclined mixing tubes being radially outward of the Fuel nozzle can be made at an angle between 0.1 ° and 20 ° obliquely.
    As an alternative, the inclined mixing tubes may be made radially inclined with respect to the center axis of the fuel nozzle, wherein the inclined mixing tubes may be inclined to an inward direction of the fuel nozzle at an angle between 0.1 ° and 20 °.
    BRIEF DESCRIPTION OF THE DRAWINGS
    [0029]<Tb> FIG. 1 <SEP> illustrates a block diagram of an exemplary gas turbine in which embodiments of the present invention may be used;<Tb> FIG. FIG. 2 is a cross-sectional view of an exemplary combustor as may be used in the gas turbine shown in FIG. 1; FIG.<Tb> FIG. FIG. 3 includes a view, partially in perspective and partially in cross section, showing an exemplary combustor nozzle according to certain aspects of the present invention; FIG.<Tb> FIG. 4 <SEP> illustrates a more detailed cross-sectional view of the combustor nozzle of FIG. 3;<Tb> FIG. 5 <SEP> illustrates an end view cut along the lines of sight marked 5-5 in FIG. 4;<Tb> FIG. 6 <SEP> contains a simplified side view of a mixing tube that can be used in a pilot nozzle;<Tb> FIG. Figure 7 illustrates a simplified side view of an alternative mixing tube having an inclined configuration according to certain aspects of the present invention;<Tb> FIG. 8 shows a cross-sectional view depicting an exemplary pilot nozzle having tilted mixing tubes in accordance with certain aspects of the present invention;<Tb> FIG. FIG. 9 illustrates a side view of inclined mixing tubes according to an exemplary embodiment of the present invention; FIG.<Tb> FIG. 10 <SEP> contains a perspective view of the mixing tube of FIG. 9;<Tb> FIG. Figure 11 illustrates a side view of inclined mixing tubes according to an alternative embodiment of the present invention;<Tb> FIG. Figure 12 shows a side view of a tilted mixing tube according to another alternative embodiment of the present invention;<Tb> FIG. Fig. 13 illustrates a side view of another embodiment in which linear mixing tubes are combined with inclined mixing tubes;<Tb> FIG. 14 <SEP> contains a perspective view of the mixing tubes of FIG. 13;<Tb> FIG. Fig. 15 <SEP> shows an inlet view of the mixing tubes of Fig. 13;<Tb> FIG. 16 <SEP> illustrates an outlet view of the mixing tubes of FIG. 13;<Tb> FIG. Figure 17 illustrates a side view of another embodiment including counter-rotating spiral mixing tubes in accordance with certain other aspects of the present invention;<Tb> FIG. 18 <SEP> contains a perspective view of the mixing tubes of FIG. 17;<Tb> FIG. Fig. 19 <SEP> shows an inlet view of the mixing tubes of Fig. 17;<Tb> FIG. 20 <SEP> illustrates an outlet view of the mixing tubes of FIG. 17;<Tb> FIG. 21 <SEP> illustrates an outlet view of an alternative embodiment of the mixing tubes that includes a component that is exterior to the exit direction;<Tb> FIG. Figure 22 illustrates an outlet view of an alternative embodiment of the mixing tubes that includes a component internal to the exit direction;<Tb> FIG. 23 <SEP> schematically illustrates the results of a directional flow analysis of mixing tubes that have a linear or axial orientation; and<Tb> FIG. 24 <SEP> schematically illustrates the results of a directional flow analysis of mixing tubes that have a tangentially skewed orientation.
    DETAILED DESCRIPTION OF THE INVENTION
    Aspects and advantages of the invention are set forth below in the following description, or may be obvious from the description, or may be learned by practice of the invention. Reference will now be made in detail to the present embodiments of the invention, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses terms in the form of numbers and letters to refer to features in the drawings. The same or similar terms in the drawings and the description may be used to refer to the same or similar parts of the invention.
    As will be appreciated, each example is provided to illustrate the invention, not for the purpose of limiting the invention. In fact, it will be apparent to those skilled in the art that modifications and changes may be made to the present invention without departing from the scope or scope thereof. For example, features that are illustrated or described as part of one embodiment may be used in another embodiment to yield a still further embodiment. Thus, it is intended that the present invention cover such modifications and changes as fall within the scope of the appended claims and their equivalents. It is understood that the ranges and limitations mentioned herein include all sub-ranges that are within the prescribed limits, including the limits themselves, unless otherwise specified.
    In addition, certain terms have been selected to describe the present invention and its component subsystems and parts. Wherever possible, these terms have been selected based on common terminology in the technology field. 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, in understanding 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. Further, while the following examples are described with respect to a particular type of turbine, the technology of the present invention may be applicable to other types of turbines, as one skilled in the art would understand in the relevant technological field.
    Taking into account the nature of turbine operation, some descriptive terms throughout this application may be used to explain the operation of the machine and / or some subsystems or components contained therein, and it may prove advantageous to use these terms at the beginning of this application Section to define. Accordingly, unless otherwise specified, these terms and their definitions are as follows. Without further specification, the terms "front" and "rear" refer to directions with respect to the orientation of the gas turbine. That is, "front" refers to the front or compressor end of the gas turbine, and "rear" refers to the rear or turbine end of the gas turbine. 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 location within a specified conduit 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 skilled in the art.) The term "downstream" corresponds to the direction in which a fluid flows through the specified conduit during refers to "upstream" in the opposite direction. For example, the primary flow of working fluid through a turbine consisting of the air flowing through the compressor and subsequently becoming combustion gases within and beyond the combustion chamber may thus begin as an upstream location toward an upstream or forward end of the compressor and terminating at a downstream location to a downstream or aft 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 discharge air typically enters the combustor through impingement ducts (in relation 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 directed from a flow annulus formed around an inner chamber toward the forward end of the combustion chamber where the air flow enters the inner chamber and changes its direction of flow in the direction of the rear end of the combustion chamber flows. In still another context, coolant flows may be treated by cooling passages in the same manner.
    In addition, given the configuration of a compressor and turbine around a common centerline as well as the cylindrical configuration common to many types of combustors, terms describing a position relative to an axis may be used herein. 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 from the central axis. In this case, when a first component is closer to the central axis than a second component, it is described herein that the first component is "radially inboard" or "inboard" with respect to 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 described herein that the first component is "radially outward of" or "outboard" with respect to 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, which is common to many turbines, the axis, which gives these terms relative importance, may be the longitudinal reference axis extending through the center of the cylindrical cross-sectional shape, which is first cylindrical but a more annular Profile goes over when approaching the turbine.
    Referring to Figure 1, a simplified drawing of some portions of a gas turbine system 10 is illustrated. The turbine system 10 may be liquid or gaseous fuel, e.g. Natural gas and / or a hydrogen-rich synthesis gas, use to operate the turbine system 10. As shown, a plurality of fuel-air nozzles (or, as referred to herein "fuel nozzles 12vx) of the type described in more detail below receive a fuel supply 14, mix the fuel with an air supply, and direct the fuel-air mixture into one for combustion Combustion chamber 16 into it. The combusted fuel-air mixture generates hot pressurized exhaust gases that may be directed through a turbine 18 toward an exhaust outlet 20. As the exhaust gases pass through the turbine 18, the gases force one or more turbine blades to rotate a shaft 22 along an axis of the turbine system 10. As illustrated, the shaft 22 may be connected to various components of the turbine system 10, including a compressor 24. The compressor 24 also includes blades that may be connected to the shaft 22. As the shaft 22 rotates, the blades within the compressor 24 also revolve, thereby compressing air from an air inlet 26 through the compressor 24 and into the fuel nozzles 12 and / or the combustion chamber 16. The shaft 22 may also be connected to a load 28 which may be a vehicle or a stationary load such as a truck. may be an electric generator in a power plant or a propeller on an aircraft. As will be understood, the load 28 may include any suitable device that is capable of being driven by the rotational output of the turbine system 10.
    Fig. 2 shows a simplified drawing of cross-sectional views of some portions of the gas turbine system 10, which is shown schematically in Fig. 1. As schematically shown in FIG. 2, the turbine system 10 includes one or more fuel nozzles 12 disposed in a head end 27 of the combustor 16 in the gas turbine engine 10. Each illustrated fuel nozzle 12 may include a plurality of fuel nozzles grouped together and / or a standalone fuel nozzle, each illustrated fuel nozzle 12 being based at least substantially or entirely on internal structural support (e.g., load bearing fluid channels). Referring to Fig. 2, the system 10 includes a compressor section 24 for pressurizing a gas, e.g. Air entering the system 10 via an air inlet 26. In operation, air enters the turbine system 10 through the air inlet 26 and may be pressurized in the compressor 24. It should be understood that while gas is referred to herein as air, the gas may be any gas suitable for use in a gas turbine system 10. Compressed air exhausted from the compressor section 24 flows into a combustor section 16 generally characterized by a plurality of combustors 16 (only one of which is illustrated in Figs. 1 and 2) arranged in an annular array about an axis of the system 10 are arranged around. The air flowing into the combustion chamber section 16 is mixed with the fuel and combusted within the combustion chamber 32 of the combustion chamber 16. For example, the fuel nozzles 12 may inject a fuel-air mixture into the combustion chamber 16 in a fuel-to-air ratio of fuel suitable for optimal combustion, optimum emission output, fuel economy, and power output. The combustion produces hot pressurized exhaust gases, which then flow from each combustor 16 to a turbine section 18 (FIG. 1) to drive the system 10 and produce power. The hot gases drive one or more blades (not shown) within the turbine 18 to rotate the shaft 22 and thus the compressor 24 and the load 28. The rotation of the shaft 22 causes the blades 30 within the compressor 24 to circulate and draw and compress air received through the inlet 26. However, it should be readily appreciated that a combustor 16 need not be configured as described above and illustrated herein, and that it may generally be of any configuration that allows compressed air to be mixed with fuel, combusted, and delivered to a turbine section 18 of the system 10 is transmitted.
    Referring now to FIGS. 3-5, an exemplary configuration of a premixing pilot nozzle 40 (or simply "pilot nozzle 40") according to certain aspects of the present invention is illustrated. The pilot nozzle 40 may include some mixing tubes 41 within which a fuel-air mixture for combustion within the combustion chamber 32 is generated. FIGS. 3 to 5 illustrate an arrangement by which fuel and air can be supplied to different mixing tubes 41 of the pilot nozzle 40. Another such air-fuel delivery configuration is provided with respect to Figure 8, and it should be appreciated that other fuel-air delivery arrangements are also possible, and that these examples should not be construed as limiting unless otherwise specified in the appended set of claims is displayed.
    As shown in Figs. 3, 4 and 5, the mixing tubes 41 may have a linear and axial configuration. In such cases, each mixing tube 41 may be configured to discharge fluid flow therefrom in one direction (or as used herein, include an "exit direction") parallel to the central axis 36 of the fuel nozzle 12, or alternatively at least the tangentially inclined one Alignment with respect to the central axis 36 of the fuel nozzle does not have. As used herein, such mixing tubes 41 may be referred to as "axial mixing tubes". Accordingly, an axial mixing tube 41 may be oriented to be substantially parallel to the central axis 36 of the fuel nozzle 12, or alternatively, the axial mixing tube 41 may be aligned to contain a radially skewed alignment with respect to the central axis 36 as long as the mixing tube Tangent inclined component is missing. Other mixing tubes 41, referred to as "slanted mixing tubes", may include this tangentially angled orientation such that each of them releases the mixture of fuel and air in a direction that is skewed with respect to the center axis 36 of the fuel nozzle 12 or is tilted tangentially. As described below, this type of configuration can be used to generate a swirl pattern within the combustion zone after release, which improves certain performance aspects of the pilot nozzle 40 and thereby the performance of the fuel nozzle 12.
    As illustrated, the fuel nozzle 12 may include an axially elongated peripheral wall 50 defining an outer shell of the component. The peripheral wall 50 of the fuel nozzle 12 has an outer surface and an inner surface which is oriented in the opposite direction to the outer surface and which defines an axially elongated inner cavity. As used herein, a center axis 36 of the nozzle 12 is defined as the center axis of the fuel nozzle 12, which in this example is defined as the center axis of the peripheral wall 50. The fuel nozzle 12 may further include a hollow, axially elongated central body 52 disposed within the cavity defined by the peripheral wall 50. Given the concentric arrangement shown between the peripheral wall 50 and the centerbody 52, the central axis 36 may be common to each component. The centerbody 52 may be axially defined by a wall defining an upstream end and a downstream end. A primary air flow channel 51 may be defined in the annular space between the peripheral wall 50 and the outer surface of the centerbody 52.
    The fuel nozzle 12 may further include an axially elongate, hollow fuel supply conduit, referred to herein as the "central supply conduit 54" extending through the center of the centerbody 52. Defined between the central supply line 54 and the outer wall of the centerbody 52, an elongate inner passage or secondary flow annulus 53 may extend axially from a forward position adjacent the head end 27 toward the pilot nozzle 40. The central supply conduit 54 may similarly extend axially between the forward end of the centerbody 52, being able to communicate with a fuel source (not shown) through the headend 27. The central supply line 54 may have a downstream end disposed at the rear end of the centerbody 52 and may provide a supply of fuel that is ultimately injected into the mixing tubes 41 of the pilot nozzle 40.
    The primary fuel supply of the fuel nozzle 12 may be directed to the combustion chamber 32 of the combustor 16 by a plurality of swirler vanes 56 which, as illustrated in FIG. 3, may be fixed vanes extending across the primary flow annulus 51. In accordance with aspects of the present invention, the swirler vanes 56 may define a so-called "swozzle" type fuel nozzle in which a plurality of vanes 56 extend radially between the centerbody 52 and the peripheral wall 50. As shown schematically in Figure 3, each of the swirler vanes 56 of the swozzle may desirably be provided with internal fuel channels 57 terminating in fuel injection ports 58 from which the primary fuel supply (whose flow is indicated by arrows) is introduced into the primary air stream. which is passed through the primary flow annulus 51. As this primary airflow is directed against the swirler vanes 56, a swirl pattern is provided which, as will be appreciated, aids in the mixing of the air and fuel feeds within the primary flow annulus 51. Downstream of the swirler vanes 56, the swirling air and fuel feeds which have been brought together within the flow annulus 51 can continuously mix before being discharged into the combustion chamber 32 for combustion. As used herein, as distinguished from the pilot nozzle 40, the primary flow annulus 51 may be referred to as a "parent nozzle" and the fuel-air mixture brought together within the primary flow annulus 51 may be referred to as inside the "parent nozzle" are taken from. When using these designations, it will be appreciated that the fuel nozzle 12 includes a primary nozzle and a pilot nozzle and that each of these injects separate fuel-air mixtures into the combustion chamber.
    The centerbody 52 may be described as including axially stacked sections, with the pilot nozzle 40 being the axial section located at the downstream or rearward end of the centerbody 52. According to the exemplary embodiment shown, the pilot nozzle 40 includes a fuel plenum 64 located at a downstream end of the central supply line 54. As illustrated, the fuel plenum 64 may be in fluid communication with the central supply line 54 via one or more fuel ports 61. The fuel can thus flow through the supply line 54 in order to flow into the fuel collecting space 64 via the fuel openings 61. The pilot nozzle 40 may further include an annular shaped center body wall 63 disposed radially outward of the fuel plenum 64, and desirably concentric with respect to the central axis 36.
    As described, the pilot nozzle 40 may include a plurality of axially elongated, hollow mixing tubes 41 that are located just outboard with respect to the fuel plenum 64.The pilot nozzle 40 may be axially defined by an upstream end surface 71 and a downstream end surface 72. As illustrated, the mixing tubes 41 may extend axially through the centerbody wall 63. A plurality of fuel ports 75 may be formed within the centerbody wall 63 for supplying fuel from the fuel plenum 64 into the mixing tubes 41. Each of the mixing tubes 41 may extend axially between an inlet 65 formed through the upstream end surface 71 of the pilot nozzle 40 and an outlet 66 formed through the downstream end surface 72 of the pilot nozzle 40. Arranged in this manner, airflow into the inlet 65 of each mixing tube 41 may be directed out of the secondary flow annulus 53 of the centerbody 52. Each mixing tube 41 may include at least one fuel port 75 in fluid communication with the fuel plenum 64 such that a fuel stream exiting the fuel plenum 64 flows into each mixing tube 41. A resulting fuel-air mixture may then flow downstream in each mixing tube 41 and may then be injected into the combustion chamber 32 from the outlets 66 formed through the downstream end face 72 of the pilot nozzle 40. As will be appreciated, given the predetermined linear configuration and axial orientation of the mixing tubes 41 shown in FIGS. 3-5, the fuel-air mixture exiting the outlets 66 is directed in a direction that in FIG Aligned substantially parallel to the central axis 36 of the fuel nozzle 12. While the fuel-air mixture, after being injected into the combustion chamber 32, has a tendency to spread radially from each mixing tube 41, Applicants have found that the radial spread is negligible. Indeed, studies have shown that the equivalence ratio (ie, the air / fuel ratio) at the portion of the combustion exit plane 44 located immediately downstream of the outlet 66 of each mixing tube 41 can be almost twice the equivalence ratio is present at the portion of the combustion exit plane 44 which is located immediately downstream of the central axis 36. High equivalence ratios at a location immediately downstream of the outlet 66 of each mixing tube 41 can continuously and effectively ignite the fuel-air mixture through the superordinate nozzle and can thereby be used to stabilize the flame, even if the Flame near the condition for lean-blow-out, "LBO") is operated.
    Figures 6 and 7 include a simplified side view comparing various orientations of a single mixing tube 41 within a pilot nozzle 40 with respect to the center axis 36 of the fuel nozzle 12 (i.e., as it may be defined by the peripheral wall 50). FIG. 6 shows a mixing tube 41 having an axial configuration which is the configuration described above with reference to FIGS. 3 to 5. As indicated, the mixing tube 41 is oriented substantially parallel to the central axis 36 so that the fuel-air mixture discharged therefrom (ie, from the outlet 66) has a direction of exit ("exit direction") 80 approximately parallel to a downstream continuation of the central axis 36 of the fuel nozzle 12 extends.
    As illustrated in Fig. 7, the mixing tube 41 according to an alternative embodiment of the present invention at a downstream end of an inclined outlet portion 79 which is angled nozzle 12 with respect to the central axis 36 of the fuel or employed at an angle oblique. As established in this manner, the fuel-air mixture flowing out of the outlet 66 has an exit direction 80 that extends from and follows the tangentially skewed orientation of the inclined outlet portion 79. As used herein, the inclined outlet portion 79 may be defined with respect to the acute tangential angle 81 that it forms relative to the downstream direction of the axial reference line 82 (which, as used herein, is defined as a reference line parallel to the central axis 36). ,
    As described in more detail below, performance advantages for the pilot nozzle 40 can be achieved by arranging the various mixing tubes to contain such slanted orientations. Typically, each of the mixing tubes 41 may be similarly configured and arranged in parallel, although certain embodiments described in more detail below include exceptions thereto. The extent to which the inclined outlet portions 79 of the mixing tubes 41 are tangentially angled, i. the size of the tangential angle 81 formed between the exit direction 80 and the axial reference line 82 may vary. As will be appreciated, the tangential angle 81 may depend on various criteria. Further, although the results may be optimal at certain values, different levels of desired performance advantages over a wide range of values for the tangential angles 81 may be achieved. Applicants have been able to determine some preferred embodiments, which will now be disclosed. According to one embodiment, the tangential angle 81 of the inclined mixing tube 41 includes a range between 10 ° and 70 °. According to another embodiment, the tangential angle 81 includes a range between 20 ° and 55 °.
    Although the simplified version shown in Fig. 7 only shows a mixing tube 41, each of the mixing tubes 41 may have a similar configuration and may be aligned parallel to each other. If the angled orientation is consistently applied to each of the plurality of mixing tubes 41 contained within the pilot nozzle 40, it will be appreciated that the tangential alignment of the exit direction just downstream of the downstream end face 72 of the pilot nozzle 40 creates a swirling flow. As discovered by the present applicants, this swirling flow can be used to achieve certain performance benefits, which are described in more detail below. According to an exemplary embodiment, the mixture discharged from the mixing tubes 41 may be caused to "spin in-phase" with the swirling fuel-air mixture exiting the primary flow annulus 51 (ie, in cases where the primary flow annulus 51 is the swirler vanes) 56 contains).
    As described with reference to some alternative embodiments provided below, the mixing tubes 41 may be configured to achieve this tangentially angled exit direction 80 in various ways. For example, For example, mixing tubes 41 containing linear segments that are connected at arcs or elbows (as in FIG. 7) may be used to angled the exit direction. In other cases, as shown below, the mixing tubes 41 may be curved and / or spiraled to achieve the desired exit direction. In addition, combinations of linear segments and curved or spiral segments, as well as any other geometry that allows the exiting flow from the mixing tubes 41 to exit at a tangential angle with respect to the central axis 36 of the primary flow annulus 51 may be used.
    Figures 8 through 12 illustrate exemplary embodiments that include a mixing tube 41 having angled or tilted configurations in accordance with the present invention. FIG. 8 shows an exemplary helical configuration for the mixing tubes 41 and is also provided to illustrate an alternative preferred arrangement by which fuel and air may be supplied to the mixing tubes 41 of the pilot nozzle 40. In this case, an outboard fuel passage 85 is disposed within the centerbody wall 63 and extends axially from an upstream connection provided with a fuel conduit 57 which, as illustrated in Figures 3 and 4, also supplies fuel to the orifices 58 of the swirler vanes 56 supplies. In the given configuration of FIG. 8, the fuel per se is supplied from the fuel passage 85, which is located slightly outboard of the mixing tubes 41, rather than the fuel being supplied from a fuel plenum located radially inward of the mixing tube 41.
    As will be appreciated, the outer fuel passage 85 may be formed as an annular passage or as a plurality of individual tubes formed around the circumference of the center body 52 so as to desirably coincide with the locations of the mixing tubes 41. One or more fuel ports 75 may be formed to fluidly connect the outboard fuel passage 85 to each of the mixing tubes 41. In this way, an upstream end of each of the mixing tubes 41 may be connected to a fuel source. As further illustrated, the secondary flow annulus 53 may be formed within and axially extend through the centerbody 52 to provide a supply of air to each of the inlets 65 of the mixing tubes 41. It will be appreciated that, unlike the embodiment of FIGS. 3 and 4, the centrally located central supply conduit 54 of the centerbody 52 is not used to supply fuel to the mixing tubes 41. Even then, the central supply line 54 may be included to provide or facilitate other types of fuel for the fuel nozzle 12. In any case, the inner passage or the secondary flow annulus 53 may be formed as an elongate passage defined between a central structure, such as a central one. the outer surface of the central supply line 54 and an inner surface of the center body wall 63 is defined. Other configurations are also possible.
    Similar to the configuration illustrated in FIG. 7, each of the mixing tubes 41 may include an inclined outlet portion 79 which is tangentially angled with respect to the central axis 36 of the fuel nozzle 12. In this way, the exit direction 80 for the fuel-air mixture moving through the mixing tubes 41 may be tilted similarly to the center axis 36 of the fuel nozzle 12. According to the preferred embodiments of FIGS. 8-10, each of the mixing tubes 41 includes an upstream linear portion 86 that merges into a downstream spiral portion 87 that curves about the central axis 36, as indicated. In one embodiment, the fuel ports 74 are disposed in the upstream linear section 86, and the downstream spiral section 87 promotes mixing of fuel and air, thereby causing the components within the mixing tube 41 to change direction. It has been found that this change in direction produces secondary flows and turbulence which promote mixing between fuel and air flowing therethrough so that a well mixed fuel-air mixture comes out of the mixing tubes 71 in the desired angled exit direction.
    According to preferred embodiments, a plurality of mixing tubes 41 are provided around the periphery of the pilot nozzle 40. For example, between ten and fifteen tubes may be defined within the centerbody wall 63. The mixing tubes 41 may be spaced at regular intervals. The exit direction 80 defined by the slanted outlet portion 79 may be configured to coincide with or point in the same direction as the direction of swirl generated within the primary flow annulus 51 by the swirler vanes 56. In particular, according to a preferred embodiment, the inclined outlet portion 79 may be angled in the same direction as the swirler vanes 56 to create a flow that swirls about the central axis 36 in the same direction.
    A further exemplary embodiment is shown in Fig. 11, which includes mixing tubes 41, which contains a curved spiral formation for the entire mixing length of the mixing tubes 41. As used herein, the mixing length of a mixing tube 41 is the axial length between the location of the initial (i.e., the most upstream) fuel port 75 and the outlet 66. As will be appreciated, each of the mixing tubes 41 may include at least one fuel port 75. According to alternative embodiments, each mixing tube 41 may include a plurality of fuel ports 75. The fuel openings 75 may be axially spaced along the mixing length of the mixing tube 41. However, in a preferred embodiment, the fuel ports 75 are located or concentrated toward the upstream end of the mixing tube 41, causing fuel and air to be brought together early so that greater mixing can occur before the combined flow from the outlets 66 in FIG the combustion chamber 32 is injected.
    According to another embodiment, as shown in Fig. 12, the inclined portion of the mixing tube 41 may be limited only to a downstream portion of the mixing tube 41, which, as shown, an axially small length, which is adjacent to the outlet 66 is located. With this configuration, the beneficial results can still be achieved because the desired swirl pattern can still be produced within the common outlet from the mixing tubes 41. However, the degree of fuel-air mixing within the mixing tube 41 may be less than optimal.
    Figs. 13 to 16 illustrate additional embodiments in which linear and spiral mixing tubes 41 are combined. Figures 13 and 14 respectively illustrate a side view and a perspective view of a preferred manner in which linear axial mixing tubes 41 (ie, extending parallel to the central axis 36) are disposed with slanted mixing tubes 41 within the central body wall 63 of the nozzle 40 can. As shown, the inclined mixing tubes 41 may be formed spirally. As will be appreciated, the slanted mixing tubes 41 may also be formed with a linear segmented configuration including a kink or elbow-like connection between segments, such as the example of FIG. 12, between the segments. As can be seen, FIG. 15 provides an inlet view showing the inlets 65 of the axial and inclined mixing tubes 41 on the upstream end face 71 of the pilot nozzle 40. FIG. 16 provides an exhaust view showing a representative arrangement of the outlets 66 of the axial and inclined mixing tubes 41 at the downstream end face 72 of the pilot nozzle 40. According to alternative embodiments, the inclined mixing tubes 41 may be adapted to swirl in the same direction, i. around the center axis 36 in the same direction as the swirling mixture of the parent nozzle of the primary flow annulus 51.
    The axial and inclined mixing tubes can both be supplied by the same air and fuel sources. Alternatively, each of the different types of mixing tubes may be supplied from different supply leads so that the proportion of fuel and air reaching the mixing tubes is either significantly different or controllable. In particular, as will be appreciated, the supply of each type of pipe with its own controllable air and fuel feeds allows for flexibility in engine operation that may allow for adjustment or adjustment of the fuel-air or equivalence ratio within the combustion chamber. Different settings may be used across the entire range of loads or operating levels, which, as discovered by the Applicants of the disclosure, provides a way to address certain problem areas that may occur at various load levels.
    For example, in a part load mode of operation, when the combustion temperatures are low relative to the base load, CO is the primary emission problem. In such cases, equivalence ratios may be increased to increase peak zone temperatures for improved CO burnout. That is, because the tilted mixing tubes act to attract the reactants of the parent nozzle back to the nozzle tip, the temperature in the tip zone (i.e., the tip of the nozzle) may remain cooler than if the tubes were not tangentially angled. In some cases, this can lead to excess CO in the emissions of the combustion chamber. However, by adding or increasing the axial momentum as a result of the addition of the axial mixing tubes (as illustrated in Figs. 13-16), the amount of recirculation flow may be adjusted, limited or controlled, thus providing a means for controlling peak zone temperature. This method may thus serve as an additional way to improve combustion characteristics and emission levels when operating the engine in certain modes.
    According to other embodiments, the present invention includes, for example, the use of conventional control systems and methods for manipulating air flow levels between the two different types of mixing tubes. According to one embodiment, the air flow to the axial mixing tubes 41 can be increased to prevent cooler reactant products from the parent nozzle from being drawn back into the tip zone of the pilot nozzle 40. This can be used to raise the temperature of the tip zone, which can reduce CO levels.
    In addition, the combustion dynamics can have a strong correlation to the shear in the reaction zones. By adjusting the amount of air passing through each of the different types of mixing tubes (i.e., the inclined and axial), the amount of shear can be tuned to a level that positively affects combustion. This can be achieved by establishing throttle openings to deliver unequal amounts of air to various types of mixing tubes. Alternatively, active control devices may be installed and operated via conventional methods and systems to vary the air supply levels during operation. Further, a control logic and / or a closed loop control loop may be generated such that the control of the devices is responsive to an operating mode or a measured operating parameter. As mentioned, this can lead to varying control settings according to the operating mode of the machine, e.g. - when operating at full load or at reduced load levels or in response to measured operator parameter readings. Such systems may also include the same types of control method of varying the amount of fuel supplied to the different types of mixing tubes. This can be achieved by pre-set component configurations, i. Aperture size and the like, or by more active real-time control. As will be appreciated, operating parameters such as e.g. Temperatures within the combustion chamber, acoustic variations, reactance flow patterns, and / or other parameters related to combustor operation may be used as part of a feedback loop in such a control system.
    As will be appreciated, these types of control methods and systems may also be applicable to other embodiments described herein, including all those involving the combination of mixing tubes in the same pilot nozzle having different configurations or directions of turbulence (including, for example, contra-rotating Whirling embodiments described with reference to Figures 17 to 20 or the embodiments of Figures 21 and 22 illustrating ways in which a subset of flow tubes may be configured to have exit directions containing radial components). Furthermore, these types of control methods and systems may be applicable to other embodiments discussed herein, including any of those involving the combination of mixing tubes in the same pilot nozzle having different configurations or swirl directions (such as those described with reference to FIGS. 17 to 20) Embodiments with opposing vertebrae).
    In addition, such methods and systems can be applied to pilot nozzle configurations in which all of the mixing tubes are set up in the same way and are aligned parallel to each other. In these cases, the control systems may be operated to control combustion processes by varying air and / or fuel distributions between the parent nozzle and the pilot nozzle to affect combustion characteristics. According to other embodiments, the control methods and systems may be configured to vary fuel and / or air supply levels unevenly around the circumference of the pilot nozzle, which may be used, for example, to break certain flow patterns or prevent the generation of harmful acoustics. Such measures may be taken prospectively or in response to a detected abnormality. For example, the fuel and air supply may be increased or decreased to a particular subset of the mixing tubes. This action may be taken on a predefined periodic basis in response to measured operating parameters or other conditions.
    FIGS. 17 through 20 illustrate additional exemplary embodiments in which slanted mixing tubes 41 having counter-rotating configurations are defined within the centerbody wall 63. Figures 17 and 18 illustrate a side view and a perspective view, respectively, of a representative arrangement of counter-rotating spiral mixing tubes 41 within the centerbody wall 63. As can be seen, Figure 19 provides an inlet view of the pilot nozzle 40 which provides a representative arrangement of the inlets 65 of the counter-rotating spiral mixing tubes 41 at the upstream end face 71 of the pilot nozzle 40 is illustrated. FIG. 20 provides an outlet view of the pilot nozzle 40 illustrating a preferred manner in which the outlets 66 of the counter-rotating spiral mixing tubes 41 may be disposed on the downstream end face 72 of the pilot nozzle 40. As will be appreciated, the addition of the counter-swirling inclined mixing tubes 41 may be used in the manner described above to control the temperature at the tip zone of the nozzle. In addition, the counter-swirling, inclined mixing tubes promote greater mixing in the peak zone region due to increased shear caused by the counter-swirling pilot streams, which may be advantageous for certain operating conditions.
    Figs. 21 and 22 illustrate alternative embodiments in which a radial component is added to the exit direction of the mixing tubes 41. As will be appreciated, Figure 21 illustrates an outlet view of an alternative embodiment of the mixing tubes which includes an exterior component with respect to the exit direction. In contrast, Figure 22 illustrates an outlet view of an alternative embodiment of the mixing tubes that includes an internal component with respect to the exit direction. In this way, the inclined mixing tubes of the present invention may be configured to have both a radial component and a tangential component in the exit direction. According to an alternative embodiment, the mixing tubes may be arranged to have an outlet direction which has a radial component but no component in the circumferential direction. Thus, the inboard and outboard radial components may be added to the axial or slanted mixing tubes. According to exemplary embodiments, the angle of the inner and / or the outer radial component may include a range between 0.1 ° and 20 °. As described above, the radial component may be included in a subset of the mixing tubes and thereby may be used to manipulate the shear action of the pilot nozzle so as to favorably control recirculation.
    Fig. 23 schematically illustrates the results of a directional flow analysis of a pilot nozzle 40 having axial mixing tubes 41 containing an axial outlet section, while Fig. 24 schematically illustrates the results of a directional flow analysis of inclined mixing tubes 41 having an inclined outlet section , Axial mixing tubes 41, as shown, can counteract the reverse flow created by the spin caused by the parent nozzles, which can compromise flame stability and increase the likelihood of lean flash flame blowing. In contrast, the inclined outlet portion may be configured to swirl the pilot reactants about the fuel nozzle axis in the same direction as the swirl generated in the primary or superordinate nozzle. As the results show, the swirling flow proves to be advantageous because the pilot nozzle now works together with the parent nozzle to create and / or enhance a central recirculation zone. As illustrated, the recirculation zone associated with the tilted mixing tubes contains a much more pronounced and centralized recirculation that causes reactants to be brought from a far downstream position back to the outlet of the fuel nozzle. As will be appreciated, the central recycle zone forms the basis for turbulence stabilized combustion because the products of combustion are drawn back to the nozzle outlet and exposed to fresh reactants so as to ensure the ignition of these reactants and thereby continue the process. The tilted mixing tubes can thus be used to enhance recirculation and thereby further stabilize the combustion that can be used to further stabilize lean fuel-air mixtures that may allow lower NOx emission levels. In addition, pilot nozzles, which, as mentioned, have tilted mixing tubes, can provide performance benefits associated with CO emission levels. This is achieved due to an enrichment circuit that creates a locally hot zone at the outlet of the fuel nozzle, which binds the nozzle flames and allows for further CO burnout. In addition, the pronounced recirculation produced by the inclined mixing tubes of the present invention can assist in CO burn-out by mixing the products and CO generated during combustion back into the central recirculation zone, thus likelihood that CO escapes unburned, minimizing.
    In this written description, examples are used to disclose the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, including making and using devices and systems and carrying them out Method. The patentable scope of the invention is defined by the claims, and may include other examples to which the person skilled in the art thinks. These other examples are intended to be 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.
    A fuel nozzle for a gas turbine includes: an elongate center body; an elongated peripheral wall formed about the central body to define a primary flow annulus therebetween; a primary fuel supply and a primary air supply in the primary flow annulus; and a pilot nozzle. The pilot nozzle may be formed in the centerbody and include: axial elongated mixing tube defined within a centerbody wall; a fuel port disposed on the mixing tubes for connection to each of a secondary fuel supply; and a secondary air supply configured to communicate with an inlet of each of the mixing tubes in fluid communication. Several of the mixing tubes may be formed as inclined mixing tubes adapted to produce a swirling downstream flow, while a plurality of the mixing tubes may be axial mixing tubes.
    权利要求:
    Claims (15)
    [1]
    1. A fuel nozzle for a combustion chamber of a gas turbine, wherein the fuel nozzle comprises:an axially elongate central body;an axially elongated peripheral wall formed about the central body to define a primary flow annulus space therebetween, the peripheral wall defining a central axis of the fuel nozzle;a primary fuel supply and a primary air supply in fluid communication with an upstream end of the primary flow annulus; anda pilot nozzle having a downstream portion of the centerbody, the pilot nozzle including:axially elongated mixing tubes defined within a central body wall, each of the mixing tubes extending between an inlet defined by an upstream end face of the pilot nozzle and an outlet formed by a downstream end face of the pilot nozzle;a fuel port disposed between the inlet and the outlet of each of the mixing tubes for communicating each of the mixing tubes with a secondary fuel supply; anda secondary air supply configured to be in fluid communication with the inlet of each of the mixing tubes;the mixing tubes containing a plurality of inclined mixing tubes and a plurality of axial mixing tubes;wherein the inclined mixing tubes are of the mixing tubes angled relative to the central axis of the fuel nozzle to produce a downstream swirling flow in a common outlet therefrom.
    [2]
    2. The fuel nozzle according to claim 1, wherein the inclined mixing tubes are tangentially inclined with respect to the central axis of the fuel nozzle;wherein the common outlet has a combined fuel and air outlet from the plurality of inclined mixing tubes;wherein the inclined mixing tubes are arranged such that the swirling flow of the common outlet swirls in the same direction as a swirling flow caused by swirling vanes of the primary flow annulus; andwherein the axial mixing tubes are of the mixing tubes which are parallel with respect to the center axis of the fuel nozzle.
    [3]
    3. A fuel nozzle according to claim 1 or 2, wherein the mixing tubes each have an outlet portion having an axially narrow downstream portion of the mixing tube, which is located adjacent to the outlet, wherein the outlet portion defines a central axis therethrough;wherein the inclined mixing tubes are arranged such that a continuation of the central axis of the outlet section has an acute tangential exit angle relative to a downstream continuation of the center axis of the fuel nozzle; andwherein the axial mixing tubes are arranged such that a continuation of the central axis of the outlet portion has an exit angle of about 0 ° relative to a downstream continuation of the center axis of the fuel nozzle.
    [4]
    4. The fuel nozzle according to claim 3, wherein all of the inclined mixing tubes of the pilot nozzle have a parallel arrangement with respect to each other; andwherein the tangential exit angle of the inclined mixing tubes has an angle between 10 ° and 70 °.
    [5]
    A fuel nozzle according to claim 3 or 4, wherein the center body has axially stacked portions including: a front portion having a secondary fuel supply and a secondary air supply; and a rear portion configured as the pilot nozzle;wherein the front portion of the centerbody has an axially extending central supply line and a secondary flow annulus formed around the central supply line extending axially between a connection made with an air source formed toward the upstream end of the centerbody and a second extending upstream face of the pilot nozzle; andwherein the central body wall defines an outer wall of the central body and defines an outer boundary of the secondary flow annulus.
    [6]
    6. The fuel nozzle according to claim 5, wherein the primary flow annulus has a swozzle containinga plurality of swirler vanes extending radially across the primary flow annulus; andFuel passages extending through the swirler vanes to connect fuel ports formed by an outer surface of the swirler vane to a fuel plenum;the swirler vanes having a tangentially angled orientation with respect to the central axis to cause a downstream flow therefrom that swirls about the central axis in a first direction.
    [7]
    7. The fuel nozzle according to claim 6, wherein the fuel port of each of the inclined mixing tubes and the axial mixing tubes has a side fuel hole for injecting fuel through an opening formed through a side wall; andwherein the fuel opening for each of the inclined mixing tubes and the axial mixing tubes has an upstream position relative to an air flow therethrough.
    [8]
    8. A fuel nozzle according to claim 6 or 7, wherein each of the inclined mixing tubes and the axial mixing tubes comprises a plurality of the fuel ports, and wherein the plurality of fuel ports have an upstream concentration relative to an air flow therethrough; and orwherein each of the inclined mixing tubes and the axial mixing tubes is configured to receive air flow through the inlet and a fuel flow through the fuel opening to dispense a mixture thereof through the outlet, and wherein the outlet is in fluid communication with a combustion chamber of the combustion chamber.
    [9]
    A fuel nozzle according to claim 7 or 8, wherein the axial mixing tubes each have a mixing length defined between an upstream fuel port and the outlet, the mixing length of the axial mixing tube having a linear configuration; and orwherein the inclined mixing tubes each have a mixing length defined between an upstream fuel opening and the outlet, wherein, with respect to the mixing length, the inclined mixing tubes each have a segmented configuration including an upstream segment and a downstream segment to each side of a connection forming a Direction change marked for the inclined mixing tube.
    [10]
    10. A fuel nozzle according to claim 9, wherein the inclined mixing tubes each have a configuration in which the upstream segment is linear and the downstream portion is curved;wherein the inclined mixing tubes are each preferably of a configuration in which the upstream segment is linear and axially aligned and the downstream segment is curved and spirally formed about the central axis of the fuel nozzle, and wherein the upstream portion is preferably less than half the mixing length of the inclined ones Has mixing tubes.
    [11]
    11. The fuel nozzle according to claim 9 or 10, wherein the tangential exit angle of the inclined mixing tubes has an angle between 20 ° and 55 °; and orwherein the inclined mixing tubes are arranged such that the swirling flow of the common outlet swirls in the first direction as defined by the direction of the swirling downstream flow created by the swirler vanes of the primary flow annulus.
    [12]
    12. The fuel nozzle according to claim 11, wherein the pilot nozzle has between five and twenty five of the inclined mixing tubes and between five and twenty five of the axial mixing tubes;wherein the inclined mixing tubes are circumferentially spaced within the centerbody wall at regular intervals; andwherein the axial mixing tubes are circumferentially spaced within the centerbody wall at regular intervals.
    [13]
    13. A fuel nozzle according to claim 12, wherein the plurality of inclined mixing tubes have a relation to the plurality of axial mixing tubes outboard position; orwherein the plurality of inclined mixing tubes have an internal position relative to the plurality of axial mixing tubes;wherein the plurality of inclined mixing tubes and the plurality of axial mixing tubes preferably have the same number of mixing tubes.
    [14]
    14. The fuel nozzle according to claim 13, wherein the downstream end face of the pilot nozzle has an arrangement of the outlets in which the outputs of the inclined mixing tubes are angularly clocked with respect to the outputs of the axial mixing tubes, and wherein the angular clocking of the array of outputs has the outputs the inclined mixing tubes are angularly offset with respect to the outputs of the axial mixing tubes; orwherein the downstream end face of the pilot nozzle has an arrangement of the outlets, in which the outlets of the inclined mixing tubes are angularly clocked with respect to the outlets of the axial mixing tubes, and wherein the angular timing of the arrangement of the outlets means that the outlets of the inclined mixing tubes are arranged such that they coincide angularly with the outlets of the axial mixing tubes.
    [15]
    15. The fuel nozzle according to any one of claims 12-14, wherein the inclined mixing tubes are radially inclined with respect to the central axis of the fuel nozzle and wherein the inclined mixing tubes radially to an outward direction of the fuel nozzle at an angle between 0.1 ° and 20 ° obliquely are employed; orwherein the inclined mixing tubes are radially inclined with respect to the center axis of the fuel nozzle, and wherein the inclined mixing tubes are inclined to an inward direction of the fuel nozzle at an angle between 0.1 ° and 20 °.
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    同族专利:
    公开号 | 公开日
    JP2016186414A|2016-10-27|
    DE102015121653A1|2016-06-30|
    US20160186663A1|2016-06-30|
    CN205481129U|2016-08-17|
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    法律状态:
    2017-03-15| NV| New agent|Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH |
    2019-03-15| AZW| Rejection (application)|
    优先权:
    申请号 | 申请日 | 专利标题
    US14/585,837|US20160186663A1|2014-12-30|2014-12-30|Pilot nozzle in gas turbine combustor|
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