CN105972642A - Air shield for a fuel injector of a combustor - Google Patents

Abstract

An air shield (100, 200) for an injector (32) of a combustor is provided, and includes a first section (102) that extends axially from a first end (101) to a second end (103), and a channel (112) defined by the air shield. The channel includes at least one inlet proximate to the second end. The at least one inlet is configured to receive a channel airflow (144) that is a portion of a surrounding airflow (44). The channel (112) is configured to control a distribution of the channel airflow (144) to the injector (32).

Description

Airhood for the fuel injector of burner

Technical field

The field of the invention relates generally to the fuel of a kind of burner for rotary machinery Ejector, and relate more specifically to a kind of for controlling the air flowing to fuel injector Airhood.

Background technology

At least some known burner being used together with rotary machinery, such as combustion gas turbine Including at least one of commonly referred to " late lean injection device " being positioned at primary fuel nozzle downstream Secondary fuel ejector.The lean ejector of at least some known delay by fuel supply with such as from The air supply mixing of compressor air-discharging cylinder.But, this air supply is in certain operations condition Under may be the most stable or uniformly, and there is a small amount of fuel by postponing Lean ejector spills into the probability of combustor external.

Summary of the invention

On the one hand, the present invention provides the airhood of a kind of ejector for burner.Described sky Gas hood includes the first section axially extending to the second end from the first end, and by described air The passage that cover limits.Described passage includes at least one entrance of neighbouring described second end.Institute Stating at least one entrance to be configured to receive channel airflow, described channel airflow is surrounding flow A part.Described passage is arranged for controlling for the distribution to described ejector of the described channel airflow.

On the other hand, the present invention provides a kind of burner for combustion gas turbine.Described burning Device includes the bushing pipe limiting primary combustion zone, and the sleeve pipe substantially around described bushing pipe.Institute State burner and be additionally included in described first downstream, combustion zone secondary in flow communication combustion Burn region, and be connected to the ejector of described sleeve pipe in described secondary combustion region upstream.Described Ejector includes at least one transfer tube being in fluid communication with described primary combustion zone.Described combustion Burner farther includes airhood.Described airhood includes axially extending to second from the first end First section of end, and the passage limited by described airhood.Described passage includes neighbouring institute State at least one entrance of the second end.At least one entrance described is configured to receive passage gas Stream, described channel airflow is a part for the surrounding flow of burner.Described passage is configured to Control the distribution to described ejector of the described channel airflow.

Wherein, described first section includes the cervical region of neighbouring described second end and from described cervical region A pair shoulder regions extended, at least one entrance described is positioned at described cervical region and described shoulder district In at least one in territory.It is each that at least one entrance described is included in described shoulder regions Respective apertures near individual.Wherein said passage is configured to further around described ejector The periphery of entrance essentially homogeneously distributes described channel airflow.

Wherein, described airhood farther includes the annular domed district of neighbouring described first end Territory, described annular domed region includes being positioned on the edge of the described entrance of described ejector Summit.Described airhood farther includes the scrollwork region of neighbouring described first end, described Scrollwork region is limited by radius, and described radius is along the arc of the described entrance around described ejector Shape path reduces generally.Described airhood farther includes transitional region, described transitional region Be shaped as described channel airflow is converted to ejector described in convergence with described ejector The speed that described entrance is the most tangent.

Wherein, described airhood is configured to be closed to the fuel supply lines of described ejector At least partially.Described airhood farther includes the second section, and described first section is described Second end includes that telescopable portion, described telescopable portion are configured to exist at least in part Extend on described second section.Wherein said airhood is configured to along described burner circumference The ultimate range extended is about a times to about three times of the diameter of described ejector.

Accompanying drawing explanation

Fig. 1 is the schematic diagram of exemplary gas turbine；

Fig. 2 is the exemplary burner can being used together with the exemplary gas turbine of Fig. 1 Schematic section；

Fig. 3 is the first exemplary embodiment of the airhood of the exemplary burner being connected to Fig. 2 Perspective view；

Fig. 4 is the first embodiment of the ejector being covered lid by first exemplary air of Fig. 3 Schematic section；

Fig. 5 is another perspective view of the first exemplary air cover shown in Fig. 3 and Fig. 4；

Fig. 6 is to be connected to the burner shown in Fig. 2 and cover the second embodiment of ejector The perspective view of the second exemplary embodiment of airhood；

Fig. 7 is the second exemplary air cover of the second exemplary sparger shown in coverage diagram 6 Schematic section；And

Fig. 8 is to assemble for combustion gas turbine, all exemplary gas turbines as shown in Figure 1 The flow chart of the illustrative methods of the burner of machine.

Detailed description of the invention

Illustrative methods described in this specification and system overcome with for Clothoid type machinery At least some in the shortcoming that the lean ejector of known delay of burner is associated.In this specification The embodiment described includes a kind of airhood being configured to cover late lean injection device.Described sky Gas hood limits passage, and described passage controls the distribution of the air-flow to late lean injection device.Such as, Described airhood can be shaped as distribution air stream in the channel and postpone lean spray to promote to arrive Symmetrical flowing in the entrance of emitter, thus promote the fuel of the improvement in late lean injection device/ Air mixing and flow uniformity.Additionally, described airhood can be closed to late lean injection device Fuel supply lines at least some of.

Fig. 1 is the exemplary gas turbine 10 of the embodiment of the airhood that can use the present invention Schematic diagram.In the exemplary embodiment, combustion gas turbine 10 includes air inlet section 12, connection It is connected on the compressor section 14 in air inlet section 12 downstream, is connected in compressor section 14 downstream Combustor section 16 and be connected in the turbine 18 in combustor section 16 downstream.

Turbine 18 is connected to compressor section 14 via armature spindle 17.Note that such as this Used in the description, term " couples " be not limited between parts the most mechanical, electric And/or communication connection, but can also include between multiple parts indirectly machinery, electricity and/ Or communication connection.At combustion gas turbine 10 run duration, air inlet section 12 by air towards pressure Contracting machine section 14 carries.Air is compressed into and is in elevated pressures and temperature by compressor section 14, And compressed air is discharged towards combustor section 16.In combustor section 16, compression Air mixes with fuel and lights to generate the burning gases towards turbine 18 conveying.More Specifically, combustor section 16 includes at least one burner 20, at least one burner In 20, fuel, such as natural gas and/or fuel oil are injected in air stream, and fuel is empty Gas mixture is combusted to generate the high-temperature combustion gas towards turbine 18 conveying.

It is connected to armature spindle 17 extremely in turbine 18 when rotational is given by burning gases During a few rotor blade 19, the heat energy of turbine 18 spontaneous combustion gas stream in the future is converted into Mechanical rotation energy.Armature spindle 17 can be connected to drive such as, but not limited to electromotor and/or machinery The load (not shown) of dynamic application.The burning gases discharged leave turbine 18.

Fig. 2 is the exemplary enforcement of the burner 20 can being used together with combustion gas turbine 10 The schematic section of example.Although with reference to burner 20 embodiments of the invention will describe, but In alternate embodiment, burner 20 may be such that embodiments of the invention can be such as this explanation Any suitable burner worked described in book.In the embodiment shown, burner 20 include head end 22.Bushing pipe 24 relative to the longitudinal axis 40 of burner 20 axially from head end 22 Extend to contrary tail end 46.Bushing pipe 24 is substantially by sleeve pipe 26 cincture.It addition, sleeve pipe 26 adjacent to head end 22 anteriorly 45 by socket case 30 cincture.Bushing pipe 24 is also about the longitudinal axis 40 extend circumferentially over upon to limit primary combustion zone 23 generally.Secondary combustion region 33 is one Downstream, secondary combustion zone 23 extends, and in flow communication.

Head end 22 includes that multiple primary fuel nozzle 21, the plurality of primary fuel nozzle 21 are joined Put for fuel combination in any suitable manner and air to enter in primary fuel district 23 Row burning.Fuel and the burning of the mixture of air in primary combustion zone 23 produce burning Gas, in described combustion gas flow to secondary combustion region 33 and towards turbine 18 (figure 1 illustrates) carries.

Burner 20 also includes at least one secondary injection device or late lean injection device 32.Institute Showing in embodiment, at least one late lean injection device 32 each is in secondary combustion region 33 upstream It is connected to sleeve pipe 26.In certain embodiments, at least one late lean injection device 32 is around The circumferentially spaced multiple late lean injection devices 32 of bushing pipe 24.At least one late lean injection each Device 32 receives fuel from corresponding fuel supply lines 29.In one embodiment, every fuel Supply line 29 is generally along the radially-outer surface of socket case 30 and the radial direction of sleeve pipe 26 Outer surface axially extends to corresponding late lean injection device 32.In alternative embodiments, fuel supply Pipeline 29 can be at least partially defined at least one in socket case 30 and sleeve pipe 26 In.10008 additionally or alternatively, fuel supply lines 29 can be at least in part from quill housing At least one in body 30 and sleeve pipe 26 radially outward offsets.

At least one late lean injection device 32 each is configured to mixing from fuel supply lines 29 Deliver fuel and from around the air-flow 44 of burner 20 extraction air.Implement at some In example, surrounding flow 44 is the compression supplied from compressor section 14 (figure 1 illustrates) Air stream.Additionally, at least one late lean injection device 32 each includes and primary combustion zone 23 At least one transfer tube 34 of fluid communication.At least one late lean injection device 32 is configured to By at least one transfer tube 34, fuel and the air of mixing are ejected into primary combustion zone 23 In.The fuel sprayed by least one late lean injection device 32 obtains in secondary combustion region 33 With burning.

At least one late lean injection device 32 each can have so that burner 20 can be such as this Any suitable design worked described in the specificationly.Such as but not with the side limited Formula, at least one late lean injection device 32 can be horn mouth ejector, tube-in-tube ejector, At least one in swirl injector, dense catalyzed injector and sprinkler head type multitube ejector.

Fig. 3 is the saturating of the first exemplary embodiment of the airhood 100 being connected to burner 20 View.It will be appreciated that the purpose that the shown specific embodiment of burner 20 is merely cited for, and And airhood 100 can be used together with any suitable replacement burner.In illustrated embodiment In, at least one late lean injection device 32 is multiple circumferentially spaced late lean injection devices 32, And corresponding multiple circumferentially spaced airhoods 100 are connected to burner 20 so that each air The corresponding late lean injection device 32 of cover 100 covering.In the embodiment shown, each airhood 100 Formed by translucent plastic material.In alternative embodiments, airhood 100 can be by any Suitably material is formed.

Each airhood 100 includes the first section 102, and described first section 102 is from being configured to The first end 101 that neighbouring corresponding late lean injection device 32 is arranged axially extends to and is configured to neighbour The second end 103 that nearly socket case 30 is arranged.In certain embodiments, each airhood 100 is the straight of corresponding late lean injection device 32 along the ultimate range that burner 20 is circumferentially extending About one times of footpath Dao about three times.In a particular embodiment, each airhood 100 is along combustion The circumferentially extending ultimate range of burner 20 is about the two of the diameter of corresponding late lean injection device 32 Times.In alternative embodiments, each airhood 100 is circumferentially extending along burner 20 Big distance is more than about three times of the diameter of corresponding late lean injection device 32.

When airhood 100 is connected to burner 20, airhood 100 limits passage 112.Logical Road 112 is configured to receive channel airflow 144 and be configured to channel airflow 144 points Being fitted on late lean injection device 32, described channel airflow 144 is a part for surrounding flow 44. Additionally, airhood 100 limits passage 112 to control channel airflow 144 in a desired manner Distribution to late lean injection device 32.

Such as, passage 112 is configured to from the surrounding flow 44 adjacent to the second end 103 It not that the surrounding flow 44 from neighbouring first end 101 receives most channel airflow 144. In certain embodiments, compared with the surrounding flow 44 of neighbouring first end 101, neighbouring the The surrounding flow 44 of two ends 103 is dynamically relatively weak.Therefore, each passage 112 It is configured to relatively uniform air-flow 144 is assigned to corresponding multiple lean sprays of circumferentially spaced delay Each in emitter 32.

In the embodiment shown, the first section 102 is connected to sleeve pipe 26, and airhood 100 Also include the second section 104 being connected to socket case 30.Second section 104 and the first section 102 fluid communication.In alternative embodiments, the second section 104 can omit.And institute Showing in embodiment, the first section 102 includes the cervical region 106 of neighbouring second end 103 and from neck A pair shoulder regions 108 that portion 106 extends.First section 102 also includes neighbouring first end The annular domed region 110 of 101 so that annular domed region 110 is configured to be arranged on delay The radially outer of lean ejector 32.The cervical region 106 of airhood 100, a pair shoulder regions 108 Passage 112 is limited further to control logical in a desired manner with annular domed region 110 Road air-flow 144 is to the distribution of late lean injection device 32, as will be referred to described by Fig. 4 and Fig. 5 's.

Fig. 4 is the of the late lean injection device 32 covered by airhood 100 as shown in Figure 3 The schematic section of one specific embodiment.In the embodiment shown, except central core shaft entrance 146 Outside, late lean injection device 32 also includes horn mouth air intake 114.Channel airflow 144 exists From the second end 103 convergence horn mouth air intake 114 in passage 112.If ignoring annular The effect of dome area 110, then the channel airflow 144 of disproportionate part will tend to The upstream of the side nearest from the second end 103 at the edge 118 of horn mouth air intake 114 Dynamic, this will be prone to the asymmetric empty aerodynamic flow through late lean injection device 32.This The flowing of kind of asymmetric air will tend to cause fuel and air in late lean injection device 32 Mix the most effective.

As can be seen in Figure 4, the annular domed region 110 of airhood 100 limits further Routing 112 is to control the channel airflow 144 distribution to late lean injection device 32.More precisely Ground, annular domed region 110 is substantially centrally located on late lean injection device 32, and And the summit 116 being sized such that annular domed region 110 in annular domed region 110 It is positioned on the edge 118 of horn mouth air intake 114.Therefore, with not there is airhood The late lean injection device of 100 is compared, limited by annular domed region 110 one of passage 112 Point it is configured to the periphery around horn mouth air intake 114 essentially homogeneously by channel airflow 144 are assigned in late lean injection device 32, so that through the air-flow of late lean injection device 32 More symmetrical.It will be appreciated that airhood 100 can be with any suitable late lean injection device 32 It is used together, and is not limited to and the specific embodiment of the late lean injection device 32 shown in Fig. 4 It is used together.Such as, although the periphery at summit 116 and edge 118 in the embodiment shown The most circular, it is to be understood that the periphery at summit 116 and edge 118 can have Other suitable shapes.The most such as, although late lean injection device 32 wraps in the embodiment shown Include mandrel entrance 146, but other embodiments of some of late lean injection device 32 do not include core Axle entrance 146.

Fig. 5 is airhood 100 another illustrating at least one entrance 120 leading to passage 112 One perspective view.At least one entrance 120 is configured to receive a part for surrounding flow 44 Using as channel airflow 144 (figure 3 illustrates).At least one entrance 120 each is overall Upper neighbouring second end 103 positions.In the embodiment shown, at least one entrance 120 each It is positioned at least one in cervical region 106 and shoulder regions 108.

In the embodiment shown, at least one entrance 120 includes side window 122.Each side window 122 Limit along corresponding shoulder regions 108 through the sidewall of the first section 102 of airhood 100. At least one entrance 120 can also include at least one top limited through the roof of cervical region 106 Window 124.Additionally, at least one entrance 120 can include through each shoulder regions 108 Roof limit multiple apertures 126, and can include through cervical region 106 roof limit Multiple apertures 128.At least one entrance 120 may further include through the second section 104 Wall limit aperture or window 130.Such as, in the embodiment shown, aperture 130 around Limited opening, fuel supply lines 29 is extended in passage 112 by described opening.Additionally Ground or alternately, at least one entrance 120 can include any other suitable window, hole Mouthful, passage or lead to the other kinds of entrance of passage 112.

It will be appreciated that in the case of without departing substantially from the scope of the present invention, entering of any type or position Mouth 120 can use in conjunction with the entrance 120 of any other type or position.Such as, specific In embodiment, at least one entrance 120 includes side window 122 and roof window 124, and does not include hole Mouth 126,128 and 130.The most such as, in alternative embodiments, at least one entrance 120 wraps Include side window 122 and aperture 126 and 128, and do not include roof window 124 and aperture 130.One For as, the type of entrance 120 and quantity can be selected so that the most in a desired manner Control the channel airflow 144 distribution to late lean injection device 32 (figure 3 illustrates).Such as, Aperture 126 may be used near shoulder regions 108 input other channel airflow 144 so that Compensate the tendency that channel airflow 144 separates near shoulder regions 108.Similarly, roof window 124 May be used for being pushed to from airhood channel airflow 144 with at least one in aperture 128 The sidewall of 100 closer to.Again for example, it is possible to relative in roof window 124 and aperture 128 at least The size of the size Selection side window 122 of, in order to reduce channel airflow 144 convergence and postpone lean The non axial component of the channel airflow 144 during ejector 32.

In certain embodiments, airhood 100 is configured to capture from late lean injection device 32 Any fuel of loss.More properly, passage 112 is arranged so that channel airflow 144 produces Towards the speed of late lean injection device 32, described speed be enough to back blow the fuel of loss Enter in primary combustion zone 23 through late lean injection device 32.The speed of channel airflow 144 Degree prevents the fuel of loss by least one entrance 120 leaving channel 112.

In the embodiment shown, the first section 102 includes telescoping section at the second end 103 Points 134, described telescopable portion 134 be configured at least in part the second section 104 it Upper extension.More properly, telescopable portion 134 be configured on the second section 104, It is parallel to the square upward sliding of the longitudinal axis 40 (figure 2 illustrates) on the whole so that airhood 100 adapt to be parallel between sleeve pipe 26 and socket case 30 relative motion of the longitudinal axis 40.Such as, In certain embodiments, when the operation of combustion gas turbine 10 starts, sleeve pipe 26 is relative to set Tube shell 30 towards head end 22 axially extending/expand.Owing to the first section 102 is connected to sleeve pipe 26, the first section 102 moves towards the second section 104.Telescopable portion 134 is in the secondth district Slide to maintain the integrity of passage 112 towards head end 22 on section 104.Work as gas turbine When running abort of machine 10, sleeve pipe 26 is from socket case 30 axial retraction and scalable Part 134 slides to maintain the complete of passage 112 away from head end 22 on the second section 104 Whole property.In alternative embodiments, the first section 102 does not include telescopable portion 134.

With reference to Fig. 3 and Fig. 5, in the embodiment shown, airhood 100 be configured to close right Answer at least some of of fuel supply lines 29.In certain embodiments, airhood 100 is joined Put for protect fuel supply lines 29 avoid burner transport, install and safeguard During at least one impaired.Such as, airhood 100 can have suitable strength and stiffness with Absorb the accidental shock that may damage fuel supply lines 29 the most potentially.Replacing For in embodiment, airhood 100 is not configured to close corresponding fuel supply lines 29 At least partially.

Fig. 6 is to be connected to burner 20 and cover the second specific reality of late lean injection device 32 Execute the perspective view of the second exemplary embodiment of the airhood 200 of example, and Fig. 7 is its signal Cross sectional view.As described above, at least one late lean injection device 32 can be multiple week To the late lean injection device 32 at interval, and corresponding multiple circumferentially spaced airhoods 200 are permissible It is connected to burner 20 so that each airhood 200 covers corresponding late lean injection device 32. Each airhood 200 has and the axial and circumferential scope described for airhood 100 generally Similar axial and circumferential scope.

With reference to Fig. 6 and Fig. 7, airhood 200 is substantially similar to airhood 100 at some aspects, And similar characteristics will be given by same reference numbers.Such as, airhood 200 is from the first end End 101 extends to the second end 103, limits passage 112, and described passage 112 is configured to Receiving channel airflow 144, described channel airflow 144 is a part for surrounding flow 44, and Described passage 112 is configured to from neighbouring second end 103 rather than from neighbouring second end The surrounding flow 44 of 101 receives most channel airflow 144.It addition, airhood 200 wraps Include the first section 102 being connected to sleeve pipe 26, and optionally include being connected to socket case Second section 104 of 30.In the embodiment shown, the first section 102 includes neighbouring second end End 103 cervical region 106, from cervical region 106 extend a pair shoulder regions 108, at least one Entrance 120, and optionally include telescopable portion 134.In the embodiment shown, at least One entrance 120 includes side window 122 and roof window 124, but in alternative embodiments, permissible Use any suitable combination of entrance 120, as above for described by airhood 100.Class As, in the embodiment shown, airhood 200 is configured to close corresponding fuel supply lines 29 at least some of, but in alternative embodiments, airhood 200 not be configured to envelope Close at least some of of corresponding fuel supply lines 29.

As described above, late lean injection device 32 is configured at least one transfer tube Fuel and the air of mixing are ejected in primary combustion zone 23 (figure 2 illustrates) by 34. In the illustrated embodiment of Fig. 6 and Fig. 7, in addition to mandrel entrance 246, late lean injection Device 32 also includes cyclone inlet 214.Cyclone inlet 214 includes around cyclone inlet The circumferentially spaced multiple stators 216 of central axial line 220 of 214.Central axial line 220 is defined Become to be perpendicular to the surface of sleeve pipe 26 when airhood 200 is connected to burner 20.Each stator 216 are orientated to have relative to the RADIAL 222 extending through stator from central axial line 220 and lead Leaf angle 226 so that cyclone inlet 214 is arranged to make to connect from channel airflow 144 The air received is around central axial line 220 turn.In certain embodiments, by cyclone inlet 214 The turn given improves the mixing carried out fuel and air by late lean injection device 32.

In the embodiment shown, airhood 200 includes the scrollwork region of neighbouring first end 101 232 so that scrollwork region (scroll region) 232 is configured to be arranged on late lean injection device 32 Radially outer.Airhood 200 also includes being arranged on scrollwork region 232 and the second end 103 Between transitional region 230.Scrollwork region 232 is by the radius 234 measured from central point 236 Limiting, central point 236 is configured to when airhood 200 is connected to burner 20 centrally located On axis 220.Radius 234 subtracts generally along the curved path around cyclone inlet 214 Little, as in Fig. 6 shown in some representative locations.In the embodiment shown, radius 234 The maximum of the position intersected with transitional region 230 from neighbouring scrollwork region 232 generally subtracts Little.At scrollwork region 232, transitional region 230, cervical region 106 and a pair shoulder regions 108 In fluid communication, and limit passage 112 to control channel airflow 144 in a desired manner To the distribution of late lean injection device 32, as in this specification by described in.

Channel airflow 144 in passage 112 from the second end 103 convergence cyclone inlet 214. If ignoring the effect in scrollwork region 232, then the channel airflow 144 of disproportionate part will Tend to the angular range significantly to change relative to guide vane angle 226 and collide multiple stators 216 In certain some, this makes the entrance velocity of the periphery around cyclone inlet 214 show by tending to Write change and produce the asymmetric air flowing through late lean injection device 32.This The flowing of asymmetric air will tend to cause the mixed of fuel and air in late lean injection device 32 Close the most effective.

As in fig. 6 it can be seen that radius 234 is along the arc around cyclone inlet 214 The overall reduction in path tends to make the pre-turn of channel airflow 144.Therefore, scrollwork region 232 It is shaped as the change reducing the angle that air-flow 144 collides each stator 216.Additionally, institute Showing in embodiment, transitional region 230 is shaped as channel airflow 144 from neighbouring second end The speed-shifting generally axially of 103 to convergence late lean injection device 32 and cyclone inlet 214 the most tangent speed.Therefore, transitional region 230 and scrollwork region 232 cooperate with Reduce the change that air-flow 144 collides the angle of each stator 216.

In the embodiment shown, stator 216 has guide vane angle 226, guide vane angle 226 quilt It is oriented to so that cyclone inlet 214 is arranged to give counterclockwise around central axial line 220 Turn/eddy current, and the most counterclockwise along around cyclone inlet 214 of radius 234 Path reduces, in order to make the most pre-turn of channel airflow 144.Additionally, transition Region 230 is oriented to promote channel airflow 144 is converted to tangential velocity counterclockwise.Replacing For in embodiment (not shown), stator 216 has the guide vane angle 226 of opposed orientation, makes Obtain cyclone inlet 214 to be arranged to give turn/whirlpool clockwise around central axial line 220 Stream, radius 234 reduces along the most clockwise path around cyclone inlet 214, To make the most pre-turn of channel airflow 144, and transitional region 230 is taken To promote channel airflow 144 is converted to tangential velocity clockwise.

Therefore, compared with the late lean injection device without airhood 200, passage 112 is by whirlpool The part that volume region 232 (and the most also by transitional region 230) limits is configured to Channel airflow 144 is essentially homogeneously assigned to postpone by the periphery around cyclone inlet 214 In lean ejector 32, so that the air-flow through late lean injection device 32 is more symmetrical.Ying Liao Solving, airhood 200 can be used together with any suitable late lean injection device 32, and not It is limited to be used together with the specific embodiment of the late lean injection device 32 shown in Fig. 6 and Fig. 7.

Shown in Fig. 8 assemble for combustion gas turbine, such as combustion gas turbine 10 burner, The illustrative methods 800 of such as burner 20.Referring also to Fig. 1-7, method 800 includes: adjacent Nearly ejector, such as late lean injection device 32 arrange 802 airhoods (such as airhood 100 Or airhood 200) the first end, such as the first end 101.Method 800 also includes: Second end (such as the second end 103) of airhood is arranged 804 in the first end upstream. Method 800 farther includes: airhood couples 806 to sleeve pipe, such as sleeve pipe 26 so that Limit passage, such as passage 112.Described passage is arranged for controlling for the passage gas of ejector Stream, the distribution of such as channel airflow 144.Described passage has neighbouring described second end extremely Few entrance, such as at least one entrance 120.At least one entrance described is configured to connect Receive a part for the surrounding flow of burner, such as channel airflow 44 using as channel airflow.

In certain embodiments, airhood connection 806 is farther included to sleeve pipe: by air Cover couples 808 one-tenth and passage is further configured for around the entrance of ejector, such as loudspeaker The periphery of mouth air intake 114 or cyclone inlet 214 essentially homogeneously distributes passage gas Stream.Airhood can have neighbouring the annular domed region of the first end, such as annular domed district Territory 110, and method 800 may further include: by the summit in annular domed region, all As summit 116 positions 810 on the edge of the entrance of ejector, such as edge 118.Can Alternately or in addition, airhood can include neighbouring the scrollwork region of the first end, such as whirlpool Volume region 232, and airhood connection 806 be may further include to sleeve pipe: by air Cover couples 812 one-tenth radius curved paths along the entrance around ejector making scrollwork region Reduce generally.In certain embodiments, airhood connection 806 is farther included to sleeve pipe: By at least some of envelope to the fuel supply lines of ejector, such as fuel supply lines 29 Close 814 in airhood.

Above-detailed is configured to the airhood of the late lean injection device of covering burner Exemplary embodiment.Embodiment provides in terms of the distribution of the air-flow of control to late lean injection device Advantage.Such as, described airhood can be shaped as and promote in the entrance of late lean injection device Symmetrical flowing, thus promote fuel/air mixture mixing and the flowing of the improvement in late lean injection device Uniformity.Embodiment also provides for advantages below, i.e. airhood can close fuel supply lines At least partially with promote such as burner transport, install and safeguard during protect fuel to supply Answer pipeline.

Method and system described in this specification is not limited to the tool described in this specification Body embodiment.Such as, the parts of every kind of system and/or the step of every kind of method can be relative to these Miscellaneous part described in this description and/or step are independently used alone and/or put into practice.Separately Outward, each parts and/or step can also be used together with other assemblies and method and/or put into practice.

The although present invention describes with regard to each specific embodiment, but the technology of art Personnel are it will be recognized that can make the present invention and repairing in the spirit and scope of claims Change.Although the specific features of each embodiment of the present invention may illustrate in some drawings and not Illustrate in the other drawings, but this is only in order at and considers easily.Additionally, it is right in above description The reference of " embodiment " is not intended as being construed to get rid of exist comprising described feature equally Additional embodiment.According to the principle of the present invention, any feature in accompanying drawing can be any in conjunction with other Any feature of accompanying drawing is come with reference to and/or proposes claim.

Claims (10)

1., for an airhood for burner ejector, described airhood includes:

First section, described first section axially extends to the second end from the first end；And

Passage, described passage is limited by described airhood, and described passage includes neighbouring described second end At least one entrance of end, at least one entrance described is configured to receive channel airflow, described Channel airflow is a part for surrounding flow, and described passage is arranged for controlling for described channel airflow Distribution to described ejector.

Airhood the most according to claim 1, wherein said first section includes neighbouring institute State the cervical region of the second end and a pair shoulder regions from described neck extension, described at least one Entrance is positioned at least one in described cervical region and described shoulder regions.

Airhood the most according to claim 2, at least one entrance wherein said is included in Each neighbouring respective apertures in described shoulder regions.

Airhood the most according to claim 1, wherein said passage is configured to further Periphery around the entrance of described ejector essentially homogeneously distributes described channel airflow.

Airhood the most according to claim 4, wherein said airhood farther includes neighbour The annular domed region of the most described first end, described annular domed region includes being configured to location Summit on the edge of the described entrance of described ejector.

Airhood the most according to claim 4, wherein said airhood farther includes neighbour The scrollwork region of the most described first end, described scrollwork region is limited by radius, described radius edge The curved path the described inlet ambient being configured to be positioned at described ejector reduces generally.

Airhood the most according to claim 6, wherein said airhood farther included Crossing region, described transitional region is shaped as and is converted to described channel airflow described in convergence spray The speed the most tangent with the described entrance of described ejector of device.

Airhood the most according to claim 1, wherein said airhood is configured to close Fuel supply lines at least some of to described ejector.

Airhood the most according to claim 1, wherein said airhood farther includes Two sections, described first section includes telescopable portion in described second end, described stretches Contracting part is configured to extend on described second section at least in part.

Airhood the most according to claim 1, wherein said airhood is configured to along institute State that the circumferentially extending ultimate range of burner is the diameter of described ejector one times to three times.