CN205717331U - Fuel nozzle in gas turbine combustor - Google Patents
Fuel nozzle in gas turbine combustor Download PDFInfo
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- CN205717331U CN205717331U CN201521145541.XU CN201521145541U CN205717331U CN 205717331 U CN205717331 U CN 205717331U CN 201521145541 U CN201521145541 U CN 201521145541U CN 205717331 U CN205717331 U CN 205717331U
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Abstract
A kind of fuel nozzle in gas turbine combustor, including: the centrosome of elongation；The peripheral wall of elongation, it is formed at around centrosome to limit main stream annulus therebetween；Main fuel supply and major air supply, itself and the main upstream extremity fluid communication flowing annulus；And directional nozzle.Directional nozzle may be formed in centrosome, and includes: the mixing tube axially extended, and it is limited in the body wall of center；Fuel port, it is positioned on mixing tube for each is connected to auxiliary fuel supply；And auxiliary air supply, its entrance being configured to each in mixing tube fluidly connects.Multiple mixing tubes are formed as oblique mixing tube, and it is configured at the eddy current causing central axis in its common ejection.
Description
Technical field
This utility model relates generally to gas-turbine unit, and the hydrocarbon fuel that its burning mixes with air is to produce high temperature gas flow, and this high temperature gas flow drives turbo blade so that the axle being attached to blade rotates.More particularly, but the mode of not-go end, this utility model relates to the combustor fuel nozzle including directional nozzle, and this directional nozzle pre-mixed fuel and air are to obtain lower nitrogen oxides.
Background technology
Gas-turbine unit is widely used for producing power and applies for many.Conventional gas turbogenerator includes compressor, burner and turbine.In typical gas-turbine unit, compressor provides compressed air to burner.The air entering burner mixes with fuel and burns.The hot gas of burning discharges and flow into the blade of turbine from burner so that the turbine wheel shaft being connected to blade rotates.Some mechanical energy of rotary shaft drives compressor and/or other mechanical systems.
Not agreeing with due to government regulation discharging into the atmosphere nitrogen oxides, the formation of by-product as operation of gas-turbine unit is tried hard to maintain can be below tolerable injury level.The approach meeting this regulation is to forward to use poor fuel and the burner of air mixture from diffusion flame burners, and it uses fully premixed closing operation pattern to reduce such as nitrogen oxides (being typically expressed as NOx) and the discharge of nitric oxide (CO).These burners are referred to variously as dry low NOx (DLN) combustion system, dry low emissions thing (DLE) combustion system or lean premixing (LPM) combustion system in the art.
The level of the nitrogen oxides produced in the hot gas of the burning of Fuel-air mixed influence gas-turbine unit and the performance of electromotor.Gas-turbine unit can use one or more fuel nozzle to suck air and fuel, to promote that the Fuel-air in burner mixes.Fuel nozzle can be located at the head end of burner, and may be configured to suck the air stream treating to mix with fuel input.Typically, each fuel nozzle can be by being positioned at the centrosome of the inside of fuel nozzle in inner support, and guide may be installed the downstream end of centrosome.Such as described in U.S. Patent No. 6438961, so-called swirl nozzle (swozzle) may be mounted to the outside of centrosome and is positioned at the upstream of guide, and this patent is quoted by this and is incorporated herein for various purposes with entire contents.Swirl nozzle has zigzag grain boundary, and it crosses annularly flow path radially from centrosome, and fuel introduces annularly flow path from zigzag grain boundary to be entrained to by the air stream of the stator blade vortex of swirl nozzle.
The various parameters of the combustion process in description gas-turbine unit are relevant to the generation of nitrogen oxides.Such as, the higher fuel gas temperature in combustion zone is the reason producing larger amount of nitrogen oxides.The method reducing these temperature is by pre-mixed fuel-air mixture and to reduce the fuel of burning and the ratio of air.When the fuel of burning reduces with the ratio of air, the amount of nitrogen oxides also reduces.But, there is the compromise of the performance to gas-turbine unit.Because when the fuel of burning reduces with the ratio of air, the tendency of the fray-out of flame of fuel nozzle increases, and thus results in the fluctuation of service of gas-turbine unit.Used diffusion flame guide for flame stabilization more preferable in burner, it is done so that increase NOx.Therefore, still there are the needs for the directional nozzle assembly improved, the directional nozzle assembly of this improvement provides the benefit of flame stabilization, but also makes the NOx emission being generally associated with directional nozzle the fewest.
Utility model content
Therefore the application describes the fuel nozzle for gas-turbine unit.This fuel nozzle comprises the steps that the centrosome axially extended；The peripheral wall axially extended, it is formed at around centrosome to limit main stream annulus therebetween；Main fuel supply and major air supply, itself and the main upstream extremity fluid communication flowing annulus；And directional nozzle.Directional nozzle may be formed in centrosome, comprising: the mixing tube axially extended, it is limited in the body wall of center, and each in mixing tube is extended between the entrance limited by the upstream face of directional nozzle and the outlet formed by the downstream face of directional nozzle；Fuel port, between the entrance and exit of its each being positioned in mixing tube, for each in mixing tube is connected to auxiliary fuel supply；And, auxiliary air supply, its entrance being configured to each in mixing tube fluidly connects.Multiple mixing tubes are formed as oblique (canted) mixing tube, and it is configured at the eddy current causing central axis in its common ejection.
Accompanying drawing explanation
Fig. 1 is shown in which to use the block diagram of the exemplary gas turbine of embodiment of the present utility model；
Fig. 2 be such as can in FIG shown in gas turbine in the cross sectional view of exemplary burner that uses；
Fig. 3 includes that fragmentary perspective and part are the view in cross section, which depict according to the exemplary burner nozzle in terms of some of the present utility model；
Fig. 4 shows the more detailed cross sectional view of the burner nozzle of Fig. 3；
Fig. 5 shows and is labeled as the end-view that the sight line of 5-5 intercepts in Fig. 4；
Fig. 6 includes the simplified side view of the mixing tube that can use in directional nozzle；
Fig. 7 illustrates the simplified side view of alternative blended pipe, and it has according to the oblique configuration in terms of some of the present utility model；
Fig. 8 illustrates the cross sectional view describing exemplary directional nozzle, and it has according to the oblique mixing tube in terms of some of the present utility model；
Fig. 9 illustrates the side view of the oblique mixing tube according to exemplary embodiment of the present utility model；
Figure 10 includes the perspective view of the mixing tube of Fig. 9；
Figure 11 illustrates the side view of the oblique mixing tube according to alternative of the present utility model；
Figure 12 illustrates the side view of the oblique mixing tube according to another alternative embodiment of the present utility model；
Figure 13 illustrates the side view of another embodiment, and wherein linear hybrid pipe combines with oblique mixing tube；
Figure 14 includes the perspective view of the mixing tube of Figure 13；
Figure 15 illustrates the portal view of the mixing tube of Figure 13；
Figure 16 illustrates the outlet view of the mixing tube of Figure 13；
Figure 17 illustrates the side view of another embodiment, and it includes according to some otherwise counter-rotating thread mixing pipe of the present utility model；
Figure 18 includes the perspective view of the mixing tube of Figure 17；
Figure 19 illustrates the portal view of the mixing tube of Figure 17；
Figure 20 illustrates the outlet view of the mixing tube of Figure 17；
Figure 21 illustrates the outlet view of the alternative of mixing tube, and it includes the outside component of discharge direction；
Figure 22 illustrates the outlet view of the alternative of mixing tube, and it includes the inner side component of discharge direction；
Figure 23 schematically shows the result of the direction flow analysis of the mixing tube with linear or axial orientation；And
Figure 24 schematically shows the result of the direction flow analysis of the mixing tube with the most oblique orientation.
Detailed description of the invention
State in the following description below aspect of the present utility model and advantage, or can be from this description it is clear that or can be instructed by practice of the present utility model.Embodiment of the present utility model will be carried out now referring in detail to, its one or more example is shown in the drawings.Describe in detail and use numeral labelling to come with reference to the feature in accompanying drawing.Accompanying drawing can be used for the similar or similar part with reference to embodiment of the present utility model with similar or similar labelling in description.
It will be appreciated that, each example is by explaining this utility model rather than limiting mode of the present utility model and provide.It is true that the skilled person will be apparent that, without departing from the scope with spirit in the case of, modifications and variations can be made in this utility model.Such as, the feature that the part as an embodiment illustrates or describes can be used in another embodiment, to produce further embodiment.Therefore, it is intended that make this utility model cover this modifications and variations in the range of claims and equivalent thereof.Should be appreciated that scope mentioned herein and limit all subranges of the limit including being positioned at regulation, unless stated otherwise, otherwise including limit itself.
It addition, selected some term to describe this utility model and component subsystem thereof and part.These terms are as much as possible based on the selection of terms that this technical field is conventional.It will be appreciated, however, that these terms generally have different explanations.Such as, can be referenced as elsewhere being made up of multiple components herein with reference to the key element for single component, or, can be herein with reference to for including that the key element of multiple component can be referenced as single component elsewhere.When understanding scope of the present utility model, not only should be noted that used particular term, but also should be noted that adjoint description and situation, and referenced and the structure of component, configuration, function and/or the usage of description, including the mode that this term is relevant to some accompanying drawings, and certainly, the definite usage of term in the following claims.Although additionally, the example below illustrates about certain form of turbogenerator, but technology of the present utility model can apply also for other kinds of turbogenerator, as understood by those of ordinary skill in correlative technology field.
In view of the character of turbine engine operation, run through this application can use some illustrative terms to explain electromotor and/or including subsystem or the function of component, and at the beginning of this chapter, define these terms may prove useful.Correspondingly, unless stated otherwise, these terms and being defined as follows.Term " forward " and " backward ", in the case of there is no more particularity, refer to the direction of the orientation relative to gas turbine.That is, refer to " forward " front end or the compressor end of electromotor, and " backward " refers to rear end or the turbine end of electromotor.It will be appreciated that, each in these terms may be used to indicate in-engine movement or relative position.Term " downstream " and " upstream " are for indicating the position of the interior general direction relative to the stream being moved through it of particular conduit.(it will be appreciated that, these terms are with reference to relative to expecting the direction of flowing in the normal operation period, and it should be the most apparent to any those of ordinary skill in this area.) term " downstream " refers to fluid along its flowing by the direction of particular conduit, and " upstream " refers to opposite to that direction.Therefore, such as, can be described as the upstream position in the front end towards upstream or compressor by the main stream (it starts the air for being moved through compressor and then becomes the burning gases in burner and in farther place) of the working fluid of turbogenerator to start, and the downstream position in the rear end towards downstream or turbine terminates.About the direction in the burner describing common type, as discussed in more detail below, it will be appreciated that, compressor air-out enters burner typically via impact port, and impact port is concentrated towards the rear end (relative to the longitudinal axis of burner and the above-mentioned compressor/turbine location that limits front/rear difference) of burner.The most in the burner, compressed air flows the annulus front end guidance towards burner by be formed at around internal chamber, and air stream enters internal chamber there and reverses its flow direction, advances in the rear end towards burner.But in another situation, can be processed in the same manner by the coolant stream of cooling channel.
Additionally, it is contemplated that compressor and turbine configuration around the common axis line of center, and the cylindrical configuration that many burner types are commonly used, describing can be used herein relative to the term of the position of axis.In this regard, it will be appreciated that term " radially " refers to be perpendicular to the movement of axis or position.Related to this, in order to be sufficiently accurate it may be desired to describe the relative distance away from central axis.In this case, such as, if the first component is put closer to central axis than second component, then the first component will be described as about second component " radial inward " or in " inner side " of second component.On the other hand, if the first component is put further from central axis than second component, then the first component will be described herein as about second component " radially " or in " outside " of second component.Additionally, it will be appreciated that term " axially " refers to be parallel to the movement of axis or position.Finally, term " circumferential " refers in the movement of axis or position.As described, although these terms can about extending through the common central axis application of the compressor section of electromotor and turbine, but these terms also can use about other components of electromotor or subsystem.Such as, in the situation of cylindrical burner (this is conventional to many gas turbine machineries), the axis giving these term relative meanings is longitudinal center's axis at the center extending through cross sectional shape, this cross sectional shape is initially cylindrical, but is as it and is transitioned into more annular profile close to turbine.
With reference to Fig. 1, it is shown that if the simplification figure of the stem portion of combustion gas turbine systems 10.Turbine system 10 can use liquid or gaseous fuel, and such as natural gas and/or hydrogen enriched syngas, to run turbine system 10.As described, multiple Fuel-air nozzles of type more fully described below (or, as being previously mentioned in this article, " fuel nozzle 12 ") suck fuel supply 14, fuel is mixed with air supply, and guides fuel-air mixture interior for burning to burner 16.The fuel-air mixture of burning produces hot pressure exhaust, and it can guide by turbine 18 towards air exit 20.When aerofluxus is by turbine 18, gas forces one or more turbo blade to make axle 22 rotate along the axis of turbine system 10.As it can be seen, axle 22 may be connected to the various components of turbine system 10, including compressor 24.Compressor 24 also includes the blade that can be connected to axle 22.When axle 22 rotates, the blade in compressor 24 also rotates, thus compresses the air from air inlet 26 and by compressor 24 and enter fuel nozzle 12 and/or burner 16.Axle 22 is also connected to load 28, and it can be vehicle or stationary load, such as, and the such as electromotor in power facility or propeller on board the aircraft.It will be appreciated that, load 28 can include can be by any appropriate device rotating output driving of turbine system 10.
If Fig. 2 is the simplification figure of the cross sectional view of the stem portion of the combustion gas turbine systems 10 of schematic description in Fig. 1.As schematically show in fig. 2, turbine system 10 includes one or more fuel nozzle 12 in the head end 27 of burner 16 being positioned in gas-turbine unit 10.Each diagram fuel nozzle 12 can include integrating groups of multiple fuel nozzle and/or independent fuel nozzle together, wherein, the fuel nozzle 12 of each diagram the most substantially or completely depends on interior structural support (such as, the fluid passage of carry load).With reference to Fig. 2, system 10 includes compressor section 24, for gas (such as air) pressurization flowing in system 10 via air inlet 26.In operation, air is entered turbine system 10 by air inlet 26 and can be pressurizeed in compressor 24.It is to be understood that, although this gas can context means that air, but this gas can be any gas being suitable in combustion gas turbine systems 10 using.The forced air discharged from compressor section 24 flows into combustor section 16, and its general characteristics is to be arranged to multiple burners 16 (only one illustrates in fig. 1 and 2) of annular array at the axis of system 10.The air entering combustor section 16 mixes with fuel and burns in the combustor 32 of burner 16.Such as, suitable fuel-air ratio that fuel-air mixture exports for best combustion, discharge, fuel consumption and power can be ejected in burner 16 by fuel nozzle 12.Burning produces hot pressure exhaust, and then it flow to turbine 18 (Fig. 1) from each burner 16 and with drive system 10 and produce power.Hot gas drives one or more blade (not shown) in turbine 18 so that axle 22 and therefore compressor 24 and load 28 rotate.The rotation of axle 22 causes the blade 30 in compressor 24 to rotate, and sucks the air that also supercharging is received by air inlet 26.But, it should be readily understood that, burner 16 constructs as need not as described above and illustrating herein, and could generally have any configuration that permission forced air mixes, burns and transfer to the turbine 18 of system 10 with fuel.
Turning now to Fig. 3 to Fig. 5, the exemplary configuration (or " directional nozzle 40 " simply) of premixing directional nozzle 40 is proposed according to some aspect of the present utility model.Directional nozzle 40 can include some mixing tubes 41, and fuel and air mixture is formed therein that to burn in combustor 32.Fig. 3 to Fig. 5 illustrates a kind of configuration, and fuel and air can be fed to some mixing tubes 41 of directional nozzle 40 by this configuration.Another kind of such Fuel-air transport arrangement provides about Fig. 8, and is to be understood that other fuel and air supply configuration are also possible, and these examples are not construed as limiting, unless concentrated instruction in claims.
As described in Fig. 3, Fig. 4 and Fig. 5, mixing tube 41 can have linear and axial arrangement.In these cases, each mixing tube 41 be configured so to from its fluid stream along be parallel to fuel nozzle 12 central axis 36 (or, as used in this article, including " discharge direction ") discharge, or alternatively, the direction along the tangential oblique orientation at least without the central axis 36 relative to fuel nozzle is discharged.As used in this article, this mixing tube 41 can be described as " axial backmixing pipe ".Correspondingly, axial backmixing pipe 41 may be oriented so that it is roughly parallel to the central axis of fuel nozzle 12 36, or alternatively, axial backmixing pipe 41 can be oriented to include relative to the oblique orientation of the radial direction of central axis 36, as long as mixing tube does not has tangential oblique component.Other mixing tubes 41 being referred to as " oblique mixing tube " can include this tangentially angled or oblique orientation so that each discharges fuel and the mixture of air along central axis 36 deflection or the most oblique direction relative to fuel nozzle 12.As described hereinafter, the configuration of the type can be used for producing in combustion zone upon discharge swirl pattern, which improves some aspect of performance of directional nozzle 40, and thus improves the performance of fuel nozzle 12.
As it can be seen, fuel nozzle 12 can include the peripheral wall 50 axially extended, it limits the outer envelope of component.The peripheral wall 50 of fuel nozzle 12 has outer surface and inner surface, and inner surface is in the face of outer surface and limits the inner chamber axially extended.As it is used in the present context, the central axis 36 of nozzle 12 is defined to the central axis of fuel nozzle 12, it is defined to the central axis of peripheral wall 50 in this example.Fuel nozzle 12 may also include the centrosome 52 of the axial elongation of hollow, and it is arranged in the intracavity formed by peripheral wall 50.Considering the concentric arrangement illustrated between peripheral wall 50 and centrosome 52, central axis 36 can be that each component is total.Centrosome 52 axially can limit by limiting the wall of upstream extremity and downstream.Major air circulation road 51 can be limited in the annular space between the outer surface of centrosome 52 and peripheral wall 50.
Fuel nozzle 12 may also include the hollow fuel supply lines axially extended, and it will be referred to herein as " central supply pipeline 54 ", and it extends through the central authorities of centrosome 52.Internal path or the auxiliary flow annulus 53 of elongation are limited between the outer wall of centrosome 52 and central supply pipeline 54, and it axially can extend towards directional nozzle 40 from the anterior position of neighbouring head end 27.Central supply pipeline 54 can axially extend similarly between the front end of centrosome 52, and wherein, it can be formed and by the connection of the fuels sources (not shown) of head end 27.Central supply pipeline 54 can have downstream, and it is arranged in the rear end of centrosome 52, and can provide the supply of fuel in the mixing tube 41 being finally ejected into directional nozzle 40.
The main fuel supply of fuel nozzle 12 can be directed to the combustor 32 of burner 16 by multiple cyclone stator blades 56, and as shown in Figure 3, it can be to extend across the main fixing stator blade flowing annulus 51 to the plurality of cyclone stator blade 56.According to aspect of the present utility model, cyclone stator blade 56 can limit so-called " swirl nozzle " type fuel nozzle, wherein, multiple stator blades 56 between centrosome 52 and peripheral wall 50 radially.As schematically show in figure 3, each cyclone stator blade 56 of swirl nozzle can desirably be provided with internal fuel pipe 57, it terminates in fuel injection port 58, and main fuel supply (its flowing is indicated by an arrow) is incorporated into from this fuel injection port 58 in guiding the main air stream by main stream annulus 51.Owing to this main air stream guides relative to cyclone stator blade 56, so giving swirl pattern, it will be appreciated that swirl pattern promotes air and the fuel supply mixing in main stream annulus 51.In the downstream of cyclone stator blade 56, the air of the vortex gathered together in stream annulus 51 and fuel supply can continue mixing in being discharged to combustor 32 before burning.As used in this article, when distinguishing with directional nozzle 40, main stream annulus 51 can be described as " female nozzle ", and the fuel-air mixture gathered together in main stream annulus 51 can be described as coming from " female nozzle ".When using these labellings, it will be appreciated that fuel nozzle 12 includes female nozzle and directional nozzle, and single fuel and air mixture is ejected in combustor by each in these.
Centrosome 52 can be described as including axially stacked section, and wherein, directional nozzle 40 is the axial section of downstream part or the rear end being arranged in centrosome 52.According to shown exemplary embodiment, directional nozzle 40 includes the fuel plenum 64 being arranged in around the downstream of central supply pipeline 54.As it can be seen, fuel plenum 64 can be in fluid communication with central supply pipeline 54 via one or more fuel port 61.Therefore, fuel can be advanced through supply line 54, in order to enters fuel plenum 64 via fuel port 61.Directional nozzle 40 may also include annular center body wall 63, and it is radially arranged from fuel plenum 64 and desirably concentric about central axis 36.
As described, directional nozzle 40 can include multiple hollow mixing tube 41 axially extended, and it is arranged in the positive outside of fuel plenum 64.Directional nozzle 40 axially can be limited by upstream face 71 and downstream face 72.As it can be seen, mixing tube 41 can extend axially through center body wall 63.Multiple fuel port 75 are fed in mixing tube 41 from fuel plenum 64 for by fuel in may be formed at center body wall 63.Each in mixing tube 41 axially can extend between entrance 65 and outlet 66, and entrance 65 is formed by the upstream face 71 of directional nozzle 40, and outlet 66 is formed by the downstream face 72 of directional nozzle 40.Being constructed so as to, air stream can be directed in the entrance 65 of each mixing tube 41 from the auxiliary flow annulus 53 of centrosome 52.Each mixing tube 41 can have at least one fuel port 75, and it is in fluid communication with fuel plenum 64 so that the fuel left from fuel plenum 64 is streamed in each mixing tube 41.Then the fuel-air mixture of gained can downstream advance in each mixing tube 41, and then can be ejected in combustor 32 from the outlet 66 formed by the downstream face 72 of directional nozzle 40.It will be appreciated that, it is considered to the linear configurations of the mixing tube 41 shown in Fig. 3 to Fig. 5 and axial orientation, from the fuel-air mixture of outlet 66 discharge, the direction along the central axis 36 being roughly parallel to fuel nozzle 12 guides.Although fuel-air mixture tends to from each mixing tube 41 radial diffusion after being ejected in combustor 32, but applicant have discovered that radial diffusion is the most notable.In fact, research has shown that, equivalent proportion (that is, air/fuel ratio) at the section of the Combustion outlet plane 44 at the positive downstream of the outlet 66 being positioned at each mixing tube 41 can be the almost twice of the equivalent proportion left at the section of the Combustion outlet plane 44 at the positive downstream being positioned at central axis 36.At the high equivalent weight of position of positive downstream of outlet 66 of each mixing tube 41 than the fuel-air mixture can lighted continuously and effectively by female nozzle, and such that it is able to even it is used for when flame operates fuel-lean blowout (" LBO ") state near stablizing flame.
Fig. 6 and Fig. 7 includes the single mixing tube 41 comparing in directional nozzle 40 simplified side view being differently directed relative to the central axis 36 (that is, as limited) of fuel nozzle 12 by peripheral wall 50.Fig. 6 illustrates the mixing tube 41 with axial arrangement, and it is the configuration discussed above in connection with Fig. 3 to Fig. 5.As noted, mixing tube 41 is roughly parallel to central axis 36 and is directed at, so that the fuel-air mixture discharged (that is, from outlet 66) therefrom has the direction (" discharge direction ") 80 of the discharge of the downstream continuity of the central axis 36 being approximately parallel to fuel nozzle 12.
As shown in Figure 7, according to alternative of the present utility model, mixing tube 41 is included in the oblique exit zone 79 of downstream end, and it is angled or the most oblique relative to the central axis 36 of fuel nozzle 12.Constructing in this manner, the tangential oblique orientation having from oblique exit zone 79 from the fuel-air mixture of outlet 66 flowing extends and follows the discharge direction 80 of this orientation.As used in this article, oblique exit zone 79 can limit about the triangular angular 81 of acute angle, and this angle is formed relative to the downstream direction of axial reference line 82 (as it is used in the present context, it is defined as parallel to the reference line of central axis 36).
As discussed in further detail below, the feature performance benefit for directional nozzle 40 can include that this oblique orientation realizes by being configured to by some mixing tubes.Typically, mixing tube 41 can each be similarly constructed and configure abreast, but specific embodiment discussed more fully below includes the exception for this situation.The tangentially angled scope of the oblique exit zone 79 of mixing tube 41, i.e. be formed at can vary in size of the triangular angular 81 between discharge direction 80 and axial reference line 82.It will be appreciated that, triangular angular 81 can be depending on some standards.Although additionally, result can be optimal at some value, but the broad range that can cross the value for triangular angular 81 realizes the expected performance benefit of various level.Applicant has been able to determine disclosed some preferred embodiments now.According to an embodiment, the triangular angular 81 of oblique mixing tube 41 is included in the scope between 10 ° and 70 °.According to another embodiment, triangular angular 81 is included in the scope between 20 ° and 55 °.Finally, according to last embodiment, mixing tube 41 preferably construct make triangular angular 81 be about 40 ° to 50 ° between.
Although the simple version that figure 7 illustrates only illustrates a mixing tube 41, but each in mixing tube 41 can have similar configuration, and relative to each other can parallel orientation.When angularly orienting each being applied uniformly in the multiple mixing tubes 41 being included in directional nozzle 40, it will be appreciated that the tangential orientation of discharge direction forms eddy current at the positive downstream of the downstream face 72 of directional nozzle 40.As applicants have discovered that, this eddy current can be used for some feature performance benefit realizing will be described in more detail below.According to an exemplary embodiment, the swirl-air mixture " common-vortex " (during mainly stream annulus 51 includes the situation of cyclone stator blade 56 i.e., wherein) that the mixture discharged from mixing tube 41 can be made with leave from main stream annulus 51.
As describe about the some alternatives being provided below, mixing tube 41 may be configured to realize this tangential angularly discharge direction 80 in a number of ways.Such as, the mixing tube 41 (as in the figure 7) being included in the linear segments that elbow connects can be used for making discharge direction be at an angle of.In other situations, as provided below, mixing tube 41 bends and/or is spirally formed, in order to realize desired discharge direction.It addition, linear segments and bending or the combination of spiral sections can be used, and allow mixing tube 41 leave any other geometry discharged with the central axis 36 tangentially angle relative to main stream annulus 51 that flows.
Fig. 8 to Figure 12 illustrates the exemplary embodiment included according to the mixing tube 41 with angled or angled construction of the present utility model.Fig. 8 illustrates that the Exemplary helical for mixing tube 41 configures, and is also configured to illustrate that alternative preferred disposition, fuel and air can pass through its mixing tube 41 being transported to directional nozzle 40.In this case, in outside fuel channel 85 is arranged in center body wall 63 and axially extending from the upstream connecting portion with fuel channel 57, as shown in Figures 3 and 4, fuel channel 57 also supplies fuel to the port 58 of cyclone stator blade 56.Accordingly, it is considered to the configuration of Fig. 8, replacing fuel from the fuel plenum conveying positioned relative to mixing tube 41 radial inward, the fuel fuel channel 85 from the positive outside being arranged in mixing tube 41 carries.
It will be appreciated that, outside fuel channel 85 be formed as centrosome 52 circumference formed some discontinuous pipe or annular channels, in order to desirably the position with mixing tube 41 is consistent.One or more fuel port 75 can be formed so that outside fuel channel 85 is fluidly connected to each in mixing tube 41.In this manner, the upstream extremity of each of mixing tube 41 may be connected to fuels sources.As further illustrated, in auxiliary flow annulus 53 may be formed at centrosome 52 and pass axially through it and extend so that air supply is transported in each of entrance 65 of mixing tube 41.Different from the embodiment of Fig. 3 and Fig. 4, it will be appreciated that the centrally arranged central supply pipeline 54 of centrosome 52 is not used in and delivers the fuels to mixing tube 41.Nonetheless, it may include central supply pipeline 54 is to provide or be allowed for other fuel types of fuel nozzle 12.In any case, internal path or auxiliary flow annulus 53 are formed as the path of elongation, and it is limited between division center (the such as outer surface of central supply pipeline 54) and the inner surface of center body wall 63.Other structures are also possible.
Being similar in Fig. 7 the configuration of teaching, each in mixing tube 41 can include oblique exit zone 79, and it is tangentially at an angle of relative to the central axis 36 of fuel nozzle 12.In this manner, the discharge direction 80 of the fuel-air mixture for being moved through mixing tube 41 can be the most oblique relative to the central axis 36 of fuel nozzle 12.According to the preferred embodiment of Fig. 8 to Figure 10, each in mixing tube 41 includes the upstream linear segments 86 being transitioned into downstream helical segments 87, and it bends as noted around central axis 36.In one embodiment, fuel port 74 is positioned in upstream linear segments 86, and downstream helical segments 87 promotes the mixing of fuel and air, thus causes component to change direction in mixing tube 41.Having been found that the change of the direction forms auxiliary flow and turbulent flow, it promotes the mixing being moved through between its Fuel-air so that the fuel-air mixture of good mixing occurs from mixing tube 71 with desired angled discharge direction.
According to preferred embodiment, multiple mixing tubes 41 are arranged on the circumference of directional nozzle 40.Such as, in the pipe between ten and 15 can be limited to center body wall 63.Mixing tube 41 can be with regular circumferentially-spaced spaced apart.It is consistent with the direction of the vortex formed in main stream annulus 51 by cyclone stator blade 56 or in same direction that the discharge direction 80 limited by oblique exit zone 79 is configured so to it.More specifically, according to preferred embodiment, oblique exit zone 79 can be at an angle of along the direction identical with cyclone stator blade 56, in order to produce the stream along the equidirectional vortex about central axis 36.
Another exemplary embodiment provides in fig. 11, it mixing tube 41 including having the bending spiral form of the whole mixing length for mixing tube 41.As it is used in the present context, the mixing length of mixing tube 41 is the axial length between the position and outlet 66 of initial (that is, furthest upstream) fuel port 75.It will be appreciated that, each in mixing tube 41 can include at least one fuel port 75.According to alternative, each mixing tube 41 can include multiple fuel port 75.Fuel port 75 can be axially spaced along the mixing length of mixing tube 41.But, according to preferred embodiment, fuel port 75 positions towards the upstream extremity of mixing tube 41 or concentrates, and it causes fuel and air to flock together very early, then at combination stream, more mixing can occur before outlet 66 is ejected in combustor 32.
According to another embodiment, as shown in Figure 12, the oblique part of mixing tube 41 can be limited to the positive downstream section of mixing tube 41, and it represents the narrowest length of neighbouring outlet 66 as shown in the figure.Utilize this configuration, still can realize useful result, since it is desirable that rotary mode still can cause in the common ejection of mixing tube 41.But, the Fuel-air mixed-level in mixing tube 41 can be not as good as optimal.
Figure 13 to Figure 16 illustrates the wherein linear and Additional examples of composition of thread mixing pipe 41 combination.Figure 13 and Figure 14 respectively illustrates side view and the perspective view of the optimal way that wherein linear axial mixing tube 41 (that is, be parallel to central axis 36 extend those) can be arranged in the center body wall 63 of nozzle 40 together with oblique mixing tube 41.As it can be seen, oblique mixing tube 41 can spirally be formed.It will be appreciated that, oblique mixing tube 41 may also be formed as configuring with linear segmented, its bending section being included between sections or elbow joint, the example of such as Figure 12.It will be appreciated that, Figure 15 provides portal view, the entrance 65 of its axial and oblique mixing tube 41 being shown on the upstream face 71 of directional nozzle 40.Figure 16 provides outlet view, the representative configuration of the outlet 66 of its axial and oblique mixing tube 41 being shown on the downstream face 72 of directional nozzle 40.According to alternative, oblique mixing tube 41 may be configured to jointly rotate, i.e. along the direction vortex identical with the vortex mixed of female nozzle of main stream annulus 51 around central axis 36.
Axial and oblique mixing tube all can be from identical air and fuels sources supply.Alternately, can be from different supply feeding supplies each of in different types of mixing tube so that the level of the fuel of mixing tube and air of arriving is significantly different or can control.More particularly, it will be appreciated that, controllable air and fuel supply for each tubing type supply their own realize mechanically operated motility, and it can allow the fuel-air ratio in combustor or the adjustment of equivalent proportion or regulation.The scope running through load or operation level can use different settings, and it is such as found by the applicant of the disclosure, it is provided that solves the approach of the specific Focus Area that can occur in different engine loading levels.
Such as, in load down running operation pattern, when ignition temperature is lower relative to baseline load, CO is the emission being primarily upon.In these cases, equivalent proportion can increase to increase tip region Wen Yidu for improving CO burning.This is because oblique mixing tube works so that female nozzle reactant backs into nozzle tip, tip region (that is, the tip of nozzle) if temperature colder when can keep the most tangentially being at an angle of than pipe.In some cases, the excessive CO during this can promote the emission of burner.But, by adding or increase axial momentum via adding axial backmixing pipe (as shown in Figure 13 to Figure 16), can change, limit or control the amount of recirculation flow, and therefore, it is achieved for controlling the device of tip region temperature.Therefore the method can be used as improving the additional ways of combustion characteristics and emission level when electromotor operates in some pattern.
According to other embodiments, such as, this utility model includes using classical control system and method for the air flow horizontal handled between two distinct types of mixing tube.According to an embodiment, the air-flow to axial backmixing pipe 41 can increase to prevent the colder product from female nozzle to be introduced back in the tip region of directional nozzle 40.This temperature that can be used for increasing tip region, it can reduce the level of CO.
It addition, burning dynamically can have strong correlation to the shearing in reaction zone.By adjusting the amount guided by the air of each in different types of mixing tube (that is, oblique and axial), the amount of shearing can be adjusted to the level of actively (positively) impact burning.This can be by structure dip hatch to be transported to different types of mixing tube by uneven air capacity and realizing.Alternately, active control device can be installed via conventional method and system and actuate, in order to change the air level of supply during operation.Control logic additionally, can create and/or control feedback circuit so that the control of equipment is in response to operator scheme or the operating parameter of measurement.As mentioned, this operator's parameter readings that may result in measured by the operator scheme (such as when operation under the load level loaded completely or reduce) according to electromotor or response changes control setting.These systems may also include the control method about the same type changing the fuel quantity being fed to different types of mixing tube.This can be by pre-configured component structure (that is, port size etc.) or by more initiative real-time control realization.It will be appreciated that, operating parameter (temperature in such as combustor, sound variation, reagent flow pattern) and/or relate to other parameters of operation of combustors and can be used as the part of the feedback circuit in these control systems.
It will be appreciated that, the control method of these types and system could be applicable to other embodiments discussed herein, it is included in identical directional nozzle any one in those embodiments relating to combined hybrid pipe, these compound tubes have different structures or swirl direction (includes, such as, the reverse vortex embodiment discussed about Figure 17 to Figure 20, or the embodiment of Figure 21 and Figure 22, the subset which illustrates wherein flow duct may be configured with the mode of the discharge direction including radial component).In addition, the control method of these types and system are applicable to other embodiments discussed herein, being included in identical directional nozzle any one in those embodiments relating to combined hybrid pipe, these compound tubes have different structures or swirl direction (the reverse vortex embodiment such as discussed) about Figure 17 to Figure 20.
Construct in the same manner and the directional nozzle structure of alignment parallel to each other it addition, these method and systems may be used on each in wherein mixing tube.In these cases, control system is operable to be separated controlled combustion process to affect combustion characteristics by the air between the female nozzle of change and directional nozzle and/or fuel.Being configured so to change fuel and/or air level of supply unevenly at the circumference of directional nozzle according to other embodiments, control method and system, this such as can be used for interrupting some flow pattern, or for preventing the sound being harmful to from producing.These measures can be taked on the basis of preferential or in response to the exception detected.Such as, the particular subset of mixing tube can be increased or reduce by fuel and air supply.This action can be on the basis of predetermined period, take in response to measuring operating parameter or other states.
Figure 17 to Figure 20 illustrates extra exemplary embodiment, and wherein, oblique mixing tube 41 has the reverse swirl formation being limited in center body wall 63.Figure 17 and Figure 18 respectively illustrates side view and the perspective view of the representative configuration of the thread mixing pipe 41 of the reverse vortex in center body wall 63.It will be appreciated that, Figure 19 provides the portal view of directional nozzle 40, which illustrates the representative configuration of the entrance 65 of the thread mixing pipe 41 of reverse vortex on the upstream face 71 of directional nozzle 40.Figure 20 provides the outlet view of directional nozzle 40, and the outlet 66 which illustrates the wherein thread mixing pipe 41 of reverse vortex is configurable on the optimal way on the downstream face 72 of directional nozzle 40.It will be appreciated that, the interpolation of the oblique mixing tube 41 of reverse vortex can use to control the temperature of the tip region of nozzle under mode discussed herein above.It addition, the oblique mixing tube of reverse vortex due to by reverse vortex guide that stream causes increase shearing and promote the bigger mixing in periphery, this is favourable for some mode of operation.
Figure 21 and Figure 22 illustrates alternative, and wherein radial component adds the discharge direction of mixing tube 41 to.It will be appreciated that, Figure 21 shows the outlet view of the alternative of mixing tube, and it includes the outside component of discharge direction.Comparatively speaking, Figure 22 shows the outlet view of the alternative of mixing tube, and it includes the inner side component of discharge direction.In these modes, oblique mixing tube of the present utility model may be configured to have radial component and tangential component in discharge direction.According to alternative, mixing tube may be configured with such discharge direction, and but it has radial component does not has circumferential component.Therefore, in any one during inner side and outer side radial component can add axial and oblique mixing tube to.According to exemplary embodiment, the angle of inner side and/or outer radial component may be included in the scope between 0.1 ° and 20 °.As mentioned above, radial component may be included in the subset of mixing tube and thus can be used for handling the shearing effect of directional nozzle advantageously to control recirculation.
Figure 23 schematically shows the result of the direction flow point analysis of the directional nozzle 40 with the axial backmixing pipe 41 including axial exit zone, and Figure 24 schematically shows the result that the direction flow point of the oblique mixing tube 41 with oblique exit zone is analysed.As it can be seen, axial backmixing pipe 41 can be contrary with the reverse flow that the vortex caused by female nozzle is formed, this can damage flame holding and increase the probability of oil-poor extinguishing.Comparatively speaking, oblique exit zone may be configured to make directed response thing along the direction vortex identical with the vortex formed in main or female nozzle around fuel nozzle axis.As result indicates, this eddy current proves useful, because directional nozzle with creation and/or strengthens central recirculation zone with female nozzle cooperation work now.As it can be seen, the recirculation zone being associated with oblique mixing tube includes recirculation that is many more significant and that concentrate, it causes the reactant carried position downstream at a distance to return to the outlet of fuel nozzle.It will be appreciated that, center recirculation zone is the basis stably burnt for whirlpool, because the product of burning backs into jet expansion and introduces fresh reactant, in order to guarantee the igniting of those reactants, and thus continue this process.Therefore, oblique mixing tube can be used for improving recirculation and thus the most stably burn, its lean fuel-air that can be used for the most stably allowing lower NOx emission level.It addition, as discussed, the directional nozzle with oblique mixing tube can allow to relate to the performance benefit of CO emission level.This is that it adheres to nozzle flame and allows further CO after-flame owing to realizing in the enrichment of the formation local hot spots, exit of fuel nozzle circulation.Additionally, the notable recirculation produced by oblique mixing tube of the present utility model can help CO after-flame, its return to central recirculation zone by the product produced during making burning and CO mixing in so that the chance making CO escape in the case of unburned is the least and realize.
This written description uses examples to disclose this utility model, including its optimal mode, and also makes any person skilled in the art can put into practice this utility model, including manufacturing and using any device or system and perform any method comprised.This utility model patentable scope is defined by the claims, and can include other examples that those skilled in the art expect.If these other examples have not different from the literal language of claim structural details, if or they include the equivalent structural elements without essence difference of the literal language with claim, then these other examples are intended within the scope of the claims.
Claims (22)
1. the fuel nozzle in gas turbine combustor, described fuel nozzle includes:
The centrosome axially extended；
The peripheral wall axially extended, it is formed at around described centrosome to limit main stream annulus therebetween, and wherein said peripheral wall limits the central axis of described fuel nozzle；
The main fuel supply being in fluid communication with the upstream extremity of described main stream annulus and major air supply；And
Including the directional nozzle of the downstream section of described centrosome, described directional nozzle includes:
The mixing tube axially extended, it is limited in the body wall of center, the elongation between the entrance limited by the upstream face of described directional nozzle and the outlet formed by the downstream face of described directional nozzle of each in described mixing tube；
Fuel port, between described entrance and the described outlet of its each being positioned in described mixing tube, is connected to auxiliary fuel supply for by each in described mixing tube；And
Auxiliary air is supplied, and its described entrance being configured to each in described mixing tube fluidly connects；
Plurality of described mixing tube includes oblique mixing tube, and it is angled relative to the described central axis of described fuel nozzle to cause downstream turbulent in its common ejection.
Fuel nozzle the most according to claim 1, it is characterized in that, in the described exit formed by the described downstream face of described directional nozzle, described oblique mixing tube each includes the tangential angularly orientation of the described central axis relative to described fuel nozzle；
Wherein, described common ejection includes fuel and the air ejection of the combination from the plurality of described oblique mixing tube；And
Wherein, described oblique mixing tube is configured so that the described eddy current of described common ejection is along the direction vortex identical with the eddy current caused by the cyclone stator blade of described main stream annulus.
Fuel nozzle the most according to claim 1, it is characterized in that, described oblique mixing tube each includes exit zone, it includes the narrowest downstream section being positioned at neighbouring described outlet of described oblique mixing tube, and described exit zone is configured to discharge direction gives the fuel from it and the ejection of air；
Wherein said oblique mixing tube is configured so that described discharge direction limits the tangential discharge angle of acute angle of the downstream continuity of the described central axis relative to described fuel nozzle；And
Wherein tangential discharge angle is included in the angle between 10 ° to 70 °.
Fuel nozzle the most according to claim 1, it is characterised in that described mixing tube each includes exit zone, it includes the axial narrow downstream section being positioned at neighbouring described outlet of described mixing tube, the described exit zone restriction central axis by it；And
Wherein said oblique mixing tube is configured so that the continuity of the described central axis of described exit zone includes the tangential discharge angle of acute angle of the downstream continuity of the described central axis relative to described fuel nozzle.
Fuel nozzle the most according to claim 4, it is characterised in that each in the described mixing tube of described directional nozzle includes described oblique mixing tube and the layout being parallel with respect to each other；
Wherein said peripheral wall and described center body wall each include cylinder form, and wherein said peripheral wall is arranged concentrically about at described center body wall；And
Wherein said tangential discharge angle is included in the angle between 10 ° to 70 °.
Fuel nozzle the most according to claim 4, it is characterised in that described centrosome includes axially stacked section, comprising: include described auxiliary fuel supply and the front section of described auxiliary air supply；And it is configured to the rear section of described directional nozzle；
The described front section of wherein said centrosome includes: the central supply pipeline axially extended；And, it being formed at the auxiliary flow annulus around described central supply pipeline, described auxiliary flow annulus axially extends between the connecting portion to air source and the described upstream face of described directional nozzle formed towards the upstream extremity of described centrosome；And
Wherein said center body wall limits the outer wall of described centrosome and limits the outer boundaries of described auxiliary flow annulus.
Fuel nozzle the most according to claim 6, it is characterised in that described main stream annulus includes swirl nozzle, comprising:
Cross described main stream annulus multiple cyclone stator blades radially；And
Fuel passage, it extends through described cyclone stator blade so that the fuel port formed by the outer surface of described cyclone stator blade is connected to fuel plenum；
Wherein, described cyclone stator blade includes the most angularly orienting for causing the downstream from it to flow in the first direction at described central axis vortex relative to described central axis；And
The described fuel port of each in wherein said oblique mixing tube includes that lateral fuel port is for via the opening injection fuel formed by the sidewall of described oblique mixing tube.
Fuel nozzle the most according to claim 7, it is characterised in that the connecting portion formed from described oblique mixing tube, described fuel port extends along lateral direction to be connected with described auxiliary fuel supply；And
Wherein said auxiliary fuel supply includes the fuel channel just formed in the described oblique outside cutting mixing tube and described center body wall.
Fuel nozzle the most according to claim 8, it is characterised in that described fuel plenum is arranged on the inner side of described cyclone stator blade；And
Described downstream face that wherein said fuel channel extends axially to described directional nozzle from the connecting portion that described fuel plenum is formed and the connecting portion of described fuel port included between which to described oblique mixing tube.
Fuel nozzle the most according to claim 7, it is characterised in that the connecting portion formed from described mixing tube, described fuel port extends along direction, inner side to be connected with the fuel pressure chamber formed at described central supply line downstream end；And
Wherein the described fuel port of each in described oblique mixing tube includes the upstream position of the air stream with respect to it.
11. fuel nozzles according to claim 7, it is characterised in that each in described oblique mixing tube includes multiple described fuel port；And
Wherein said multiple fuel port includes that the upstream of the air stream with respect to it is concentrated.
12. fuel nozzles according to claim 7, it is characterised in that each in described oblique mixing tube is configured to accept the air stream by described entrance and the fuel stream by described fuel port and discharges its mixture for by described outlet；
Connect the combustion chamber fluid of wherein said outlet and described burner,
Wherein said oblique mixing tube each includes the mixing length being limited between upstream fuel port and described outlet；And
Wherein, for described mixing length, described oblique mixing tube each includes that segmented configuration, described segmented configuration include upstream sections and the downstream sections of the every side to joint, and described joint mark changes for the direction of described oblique mixing tube.
13. fuel nozzles according to claim 12, it is characterised in that described oblique mixing tube each include wherein said upstream sections be linear and described downstream section be bending configuration.
14. fuel nozzles according to claim 12, it is characterised in that described oblique mixing tube each include wherein said upstream sections be linear and described downstream section be linear configuration.
15. fuel nozzles according to claim 12, it is characterised in that described oblique mixing tube each include wherein said upstream sections be bending and described downstream section be linear configuration.
16. fuel nozzles according to claim 12, it is characterised in that described oblique mixing tube each includes the configuration that wherein said upstream sections is bending and described downstream section is bending.
17. fuel nozzles according to claim 12, it is characterized in that, described oblique mixing tube each includes a kind of configuration, and wherein said upstream sections is linear and is axially directed, and described downstream sections is bending and is formed spirally at the described central axis of described fuel nozzle；And
Wherein said upstream zone includes the mixing length of the half of the described mixing length less than described oblique mixing tube.
18. fuel nozzles according to claim 7, it is characterised in that described oblique mixing tube each includes the mixing length being limited between upstream fuel port and described outlet；And
Wherein, for described mixing length, described oblique mixing tube each includes that non-sections configures, and wherein said mixing tube keeps constant form in described mixing length.
19. fuel nozzles according to claim 7, it is characterised in that described tangential discharge angle is included in the angle between 20 ° to 55 °.
20. fuel nozzles according to claim 19, it is characterised in that relative to each other, described oblique mixing tube includes parallel orientation so that relative to each other, and the described tangential discharge angle of described oblique mixing tube includes parallel configuration.
21. fuel nozzles according to claim 20, it is characterized in that, described oblique mixing tube be configured so that the described eddy current of described common ejection along by by as described in main stream annulus as described in cyclone stator blade produce as described in the direction of vortex downstream stream limit as described in first direction vortex.
22. fuel nozzles according to claim 21, it is characterised in that described directional nozzle is included in the described oblique mixing tube between five and 25；And
Wherein said oblique mixing tube is circumferentially spaced with regular intervals in the body wall of described center.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521145541.XU CN205717331U (en) | 2015-12-31 | 2015-12-31 | Fuel nozzle in gas turbine combustor |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521145541.XU CN205717331U (en) | 2015-12-31 | 2015-12-31 | Fuel nozzle in gas turbine combustor |
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| CN205717331U true CN205717331U (en) | 2016-11-23 |
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| CN201521145541.XU Active CN205717331U (en) | 2015-12-31 | 2015-12-31 | Fuel nozzle in gas turbine combustor |
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Effective date of registration: 20240109 Address after: Swiss Baden Patentee after: GENERAL ELECTRIC CO. LTD. Address before: New York, United States Patentee before: General Electric Co. |
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