CN101235969B - Reverse current jet mechanism with coaxial fuel-air passageway - Google Patents
Reverse current jet mechanism with coaxial fuel-air passageway Download PDFInfo
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- CN101235969B CN101235969B CN200710087945.1A CN200710087945A CN101235969B CN 101235969 B CN101235969 B CN 101235969B CN 200710087945 A CN200710087945 A CN 200710087945A CN 101235969 B CN101235969 B CN 101235969B
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Abstract
The invention relates to a system according to some embodiments, comprising a fuel-air injection mechanism which comprises fuel and air passages which are coaxial and open to fuel and air injection orifices (70, 72, 156, 157, 210, 211). The fuel and air injection orifices (70, 72, 156, 157, 210, 211) are arranged at the position deviated from the axial line of a gas-turbine combustor (30), and the injection direction of the fuel and air injection orifices (70, 72, 156, 157, 210, 211) is positioned without being in the direction on the same straight line of air flow which flows from the combustion turbine combustor (30) to a turbine (22).
Description
Background technology
Wish to introduce to reader in this part the various aspects of technology that may be relevant to the each aspect of the present invention that the following describes and/or require.Believe that this discussion contributes to provide background information to reader, thereby make reader have to various aspects of the present invention better understanding.Therefore, while reading these explanations, should be appreciated that, they are in this connection, and do not think the accreditation to prior art.
Combustor, for example gas turbine, can produce various pollutant effulents.For example, pollutant effulent generally includes oxycarbide (COx), nitrogen oxide (NOx), oxysulfide (SOx) and particulate matter (PM).Be strictly controlled in the U.S. and other local these pollutant effulents.The NOx that gas turbine is discharged can reduce by premixed fuel and air.Regrettably, premix can produce and be difficult to make its unstable flame stopping, and best premixing system can not reach the discharge index of NOx now.Another kind method is the NOx SCR (SCR) being undertaken by spraying ammonia.Regrettably, the cost of SCR method is relatively high.
Therefore, need a kind of pollutant emission that reduces gas turbine burner, for example the improvement technology of NOx discharge.
Summary of the invention
Set forth the more corresponding aspects of invention scope with primitive request below.Should be appreciated that, introduce the brief overview of these aspects just to some forms of the present invention is provided to reader may takes, do not wish that these aspects limit the scope of the invention.Certainly, the present invention can comprise the multiple aspect that may not set forth below.
According to the embodiment of some, a kind of system comprises fuel-air injection equipment, described fuel-air injection equipment comprises the coaxial fuel and the air duct that lead to fuel and air jet, fuel and air jet are arranged on the position of departing from gas turbine burner axis, and the injection direction of fuel and air jet is oriented to not the direction in alignment with the air-flow that flows to turbine from gas turbine burner.
According to other embodiment, system comprises gas turbine burner, and described gas turbine burner comprises combustion liner, and described combustion liner has the longitudinal axis of flow of cardinal principle that extends to turbine nozzle from stagnant area.Gas turbine burner also has adverse current fuel-air ejector, and described adverse current fuel-air ejector is arranged on one or more centre positions of combustion liner, between stagnant area and turbine nozzle.Described adverse current fuel-air ejector comprises coaxial fuel and air duct, and described fuel and air duct extend to fuel and air jet, and not in alignment with the flow direction from stagnant area to turbine nozzle.
According to embodiment further, a kind of method: be included in respect to the cardinal principle longitudinal stream moving axis of the turbine nozzle from stagnant area to gas turbine burner to become in the direction of adverse current substantially, fuel and air coaxially flow towards adverse current fuel-air ejector.
The various refinements of above-mentioned feature are present in different aspect of the present invention.More feature also can be incorporated in these different aspects.These refinements and additional feature can exist separately or in any combination.For example, the following various features relevant to one or more illustrated embodiments can be attached to separately or in any combination in any above-mentioned aspect of the present invention.Secondly, above-mentioned brief overview is only intended to allow reader be familiar with aspects more of the present invention and scope, and does not limit desired theme.
Brief description of the drawings
While reading detail specifications below by reference to accompanying drawing, will have better understanding to these and other features of the present invention, aspect and advantage, wherein the same tag in institute's drawings attached represents identical parts, wherein:
Fig. 1 is according to some embodiment of this technology, has the structure chart of the canonical system of the gas turbine being connected with load;
Fig. 2 is longitudinal sketch of the representative burner of gas turbine shown in Fig. 1, has further described according to some embodiment of this technology, has multiplely to become fuel-air of circumference to spray the upstream injection devices of salient angle along the solid inner casing of burner;
Fig. 3 is the horizontal sketch of the embodiment of burner shown in Fig. 2, has further described the multiple fuel-air being arranged in along multiple radial positions of solid inner casing circumference and has sprayed salient angle;
Fig. 4 is longitudinal sketch of the alternate embodiment of burner shown in Fig. 1 and 2, further described have along the solid inner casing of burner become circumference arranged radially flush fuel-air jeting area;
Fig. 5 is longitudinal sketch of the alternate embodiment of burner shown in Fig. 1 and 2, further described and had the upstream injection mechanism that becomes inside cantilevered fuel-air injection component of the arranged radially of circumference along the solid inner casing of burner, wherein each inside cantilevered fuel-air injection component has multiple coaxial fuel-air scoops that are positioned to cardinal principle longitudinally and become adverse current with respect to burner longitudinal stream moving axis;
Fig. 6 is the horizontal sketch of the embodiment of burner shown in Fig. 5, has further described the inside cantilevered fuel-air injection component being arranged on along the arranged radially in multiple radial positions of solid inner casing circumference;
Fig. 7 is the inside cross sectional view of the embodiment of cantilevered fuel-air injection component shown in a Fig. 5, further described substantially longitudinally and become with respect to burner longitudinal stream moving axis fuel and the air coaxial flow of adverse current;
Fig. 8 is longitudinal sketch of the alternate embodiment of burner shown in Fig. 5, and wherein each inside cantilevered fuel-air injection component further comprises multiple coaxial fuel-air scoops that are positioned to cardinal principle laterally and become adverse current with respect to burner longitudinal stream moving axis.
Fig. 9 is the horizontal sketch of the embodiment of burner shown in Fig. 8, has further described the inside cantilevered fuel-air injection component being arranged on along the arranged radially in multiple radial positions of solid inner casing circumference;
Figure 10 is the cross sectional view of the embodiment of inside cantilevered fuel-air injection component shown in a Fig. 8, further describe substantially longitudinally and become with respect to burner longitudinal stream moving axis fuel and the air coaxial flow of adverse current, also described in two substantially horizontal relative directions and become fuel and the air coaxial flow of adverse current with respect to burner longitudinal stream moving axis;
Figure 11 is longitudinal sketch of another embodiment of burner shown in Fig. 1, further described and had the unidirectional interior cantilevered fuel-air injection component being arranged on turbine nozzle place or near the solid inner casing of burner, wherein inwardly cantilevered fuel-air injection component has multiple coaxial fuel-air scoops that are positioned to substantially longitudinally and become adverse current with respect to burner longitudinal stream moving axis;
Figure 12 is according to some embodiment of this technology, has the schematic diagram at the typical fuel-air ejector of identical coaxial fuel longitudinally or axially and air stream;
Figure 13 is the schematic diagram with fuel-air ejector alternate embodiment of coaxial fuel and air stream, and wherein fuel flow arrives horizontal or in the radial direction outside with respect to air flow redirection;
Figure 14 is another alternate embodiment that has central shaft air stream and point to the fuel-air ejector of the external fuel stream of horizontal or outside radial direction with respect to air stream; And
Figure 15 has coaxial fuel and air stream and comprises the figure for another alternate embodiment of the fuel-air ejector of the swirl-flow devices of fuel and air stream.
Detailed description of the invention
One or more specific embodiment of the present invention will be described below.For the brief description of these embodiment can be provided as possible, all features of actual enforcement can not described in description.Should be appreciated that, in the development of any so actual enforcement, as in any engineering or design object, a lot of concrete making of decision of implementing must be the specific purposes in order to realize developer, for example adapt to the restriction of related system and relative commercial, certain one may be different from the object of another enforcement.In addition, should be appreciated that, such development plan may be complicated and consuming time, but benefits from those of ordinary skill of the present disclosure for those, will remain conventional design, manufacture and a production task.
Fig. 1 is the structure chart of example system 10, and it comprises for according to the gas turbine 12 of the application 14 of some embodiment of this technology.In certain embodiments, system 10 can comprise aircraft, ship, locomotive, electricity generation system or its combination.Therefore, application 14 can comprise generator, propeller or its combination.Shown in gas turbine 12 comprise air approach section 16, compressor 18, burner section 20, turbine 22 and discharge section 24.Turbine 22 by axle 26 transmissions be connected in compressor 18.As discussed in further detail below, disclosed burner section 20 embodiment comprise various adverse current fuel-air jet systems, and they contribute to the mixing of burner section fuel, air and hot combustion product.More specifically, disclosed adverse current fuel-air jet system is burner oil and air in the reverse or reverse one or more directions of total stream common and by gas turbine 12, especially burner section 20 simultaneously.
As arrow indication, air is through approach section 16 and flow into compressor 18, thereby compressed before entering burner section 20.Shown in burner section 20 comprise around axle 26 with one heart or ring-type be arranged on the burner housing 28 between compressor 18 and turbine 22.In burner housing 28 inside, burner section 20 comprises the multiple burners 30 that are arranged on around in the circle of axle 26 or multiple radial positions of circular structure.As discussed in further detail below, enter each burner 30 from the compressed air of compressor 18, subsequently with burner 30 separately in fuel mix burning, to drive turbine 22.
In certain embodiments, burner 30 can be configured to multistage burner, and wherein fuel injector is positioned at along on burner 30 length directions separately not at the same level.As selection, burner 30 can be configured to single stage burner, and wherein fuel injector is placed in single burning Ji Huo district.In the following discussion, burner 30 is described as single stage burner, but disclosed embodiment also can apply single-stage or multistage burner within the scope of the present invention.
The embodiment of disclosed burner 30 comprises multiple adverse current fuel-air jet systems, and it is spraying air and fuel with total the stream in substantially reverse one or more directions through burner 30.For example, adverse current fuel-air jet system can comprise the fuel-air ejector of multiple longitudinal sensings, laterally fuel-air ejector of pointing to or the inclination fuel-air ejector simultaneously with vertical and horizontal directed section.Fuel-the air ejector longitudinally pointing to can be conventionally burner 30 longitudinally on arrange, and the fuel-air ejector laterally pointing to can become laterally with respect to the longitudinal stream of burner 30 or axis, intersection or arranged radially.Fuel-the air ejector tilting can be with respect to the longitudinal stream moving axis of burner 30 or inner surface direction in an acute angle location.This acute angle direction generally includes the directed section that maybe can resolve into vertical and horizontal.These longitudinally, laterally and acute angle direction can be defined as countercurrent direction.
As discussed in further detail below, adverse current fuel-air jet system sprays into the opposite end of burner 30, like this fuel and air just a stagnant area in mixed combining combustion by fuel and air at these on away from the countercurrent direction of turbine 22.The stagnant area that is positioned at burner 30 opposite ends is improved stability and the stationarity of burner 30 flames conventionally.Be folded to turbine 22 with the after heat combustion product adverse current fuel-air jet system of flowing through.In addition, adverse current fuel-air jet system contributes to mixing of fuel and air and hot combustion product.Flow to turbine 22 with after heat combustion product through nozzle 32.These hot combustion products drive turbine 22, thus by the load 34 of axle 26 drive compression machines 18 and application 14.Discharge via discharging section 24 with after heat combustion product.
Fig. 2 is longitudinal sketch of the exemplary embodiments of burner 30 shown in Fig. 1, wherein according to some embodiment of this technology, burner 30 comprises upstream injection device 50, and upstream injection device 50 comprises that the multiple fuel-air being arranged on around the different radial positions of burner inner liner 54 inner peripherys sprays salient angle 52.Shown in burner inner liner 54 comprise the solid inner casing 56 being surrounded by porous shell 58.That is to say, burner inner liner 54 has the wall construction of a hollow, and it has a common continuous interval between interior and shell 56 and 58.Burner inner liner 54 can comprise pottery, cermet or other suitable materials.Fuel-air sprays salient angle 52 and is conventionally formed by solid inner casing 56, or is connected on solid inner casing 56.In the embodiment shown, fuel-air sprays salient angle wheel 52 and is arranged in multiple radial positions of solid inner casing 56, and with respect to burner 30 center longitudinal axis 62 in lengthwise position 60.So, shown in burner 30 be configured to a single stage burner.But other embodiment of burner 30 can have the fuel-air being arranged in multiple lengthwise positions with respect to axis 62 and spray salient angle 52.
Shown in upstream injection device 50 comprise and the fuel injection component 64 of air injection components 66 adjacent settings.In certain embodiments, fuel and air injection components 64 and 66 abut one another layout.Fuel injection component 64 comprises multiple fuel injectors 68 with microscler spray tip 70.Air injection components 66 comprises multiple being arranged on around the acutangulate air duct 72 of the different radial positions of solid inner casing 56 inner peripherys.In certain embodiments, microscler spray tip 70 can arrange near air duct 72.For example, in embodiment illustrated in fig. 2, microscler spray tip 70 is conventionally coaxial or concentric with air duct 72.Microscler spray tip 70 and air duct 72 run through the lobe formation 74 being positioned at around the different radial positions of solid inner casing 56 inner peripherys.That is to say, each fuel-air sprays salient angle 52 and comprises the microscler spray tip 70 and the air duct 72 that are arranged in a lobe formation 74.As described in, lobe formation 74 comprises lug boss 76 and the recess 78 of the longitudinal opposite side that is positioned at position 60.In certain embodiments, each lobe formation 74 has the circle of being generally or annular structure (for example, near-ring shape), and wherein this geometry gradually changes between lug boss 76 and recess 74.
In embodiment illustrated in fig. 2, microscler spray tip 70 and air duct 72 that each fuel-air sprays salient angle 52 are positioned at in the contrary or reverse direction of total stream 80 cardinal principles of the gas turbine 12 through discussing above with reference to Fig. 1.For example, microscler spray tip 70 can arrange with respect to 62 one-tenth corresponding angles 82 and 84 of the axis of burner 30 with air duct 72.Angle 82 can be substantially the same or different with 84.Angle 82 and 84 also can change between 0 and 90 degree, and this is determined by burner inner liner 54 or other factors.For example, angle 82 becomes 5,10,15,20,25,30,35,40,45,50,55,60,65,70,75,80 or 85 degree angles with 84 with respect to axis 62 or solid inner casing 56 inner surfaces.And fuel-air sprays the microscler spray tip 70 of salient angle 52 and air duct 72 can point to the stagnant area 86 in the close rear 88 of solid inner casing 56 in the mode substantially converging.Stagnant area 86 is improved near flame holding and the stationarity of close rear 88 of burner 30 conventionally.
Be in operation, burner 30 shown in Fig. 2, as the direction of arrow 92 indications, receives the compressed air from compressor 18 via the hole 90 in porous shell 58.Compressed air rests on the annular space between solid inner casing 56 and porous shell 58 after entering burner inner liner 54 through porous shell 58.That is to say, burner inner liner 54 has the hollow wall being limited by inner casing and shell 56 and 58, as the annular of hollow or cylindrical wall.Advantageously, burner inner liner 54 guides compressed air to spray salient angle 52 as arrow 94 directions flow to multiple fuel-air along solid inner casing 56.By this method, air stream 94 had helped solid inner casing 56 cooling before spraying into burner 30 inside via air duct 72.
Spray salient angle 52 places at fuel-air, microscler spray tip 70 is accompanied by the air stream 98 that air duct 72 sprays and ejects fuel flow 96.In the embodiment shown, fuel and air stream 96 and 98 are coaxially to each other or with one heart.Especially, due to the concentric or coaxial configuration of air duct 72 inner elongated spray tip 70, air stream 98 and the concentric setting of fuel flow 96.In addition, microscler spray tip 70 and air duct 72 arrange with corresponding angle 82 and 84, thereby make fuel flow to axis 62 and stagnant area 86 with angle 82 and 84 one-tenth ethods of remittance with air stream 96 at least in the early stage with 98.Coaxial or the concentric structure of fuel like this ,-air injection salient angle 52 and resultant current 96 and 98 contribute to mixing instead of the premix of burner 30 fuels-air.In addition, the relation of converging of fuel-air injection salient angle 52 contributes to the mixing of stagnant area 86 fuels and air, flowing/mixing as arrow 100 indications.As described in, stream 100 comprises inside sensing axis 62 and outwards points to the U-shaped stream of the wall of solid inner casing 56.That is to say, when stream 100 sprays salient angle 52 while flowing to close rear 88 with countercurrent direction from fuel-air, stream 100 oppositely points to the walls of axis 62 and solid inner casing 56 conventionally simultaneously in U-shaped mode.A kind of similarly type of flow appears in other embodiment discussed below.Fuel-air mixture 100 is burning in the stagnant area 86 of contiguous close rear 88, thereby stagnant area 86 can advantageously keep or fixing flame improves the stability of burner 30 interior flames.
Then, hot combustion product as shown in arrow 102 from stagnant area 86 along burner 30 longitudinal streams to nozzle 32.Like this, hot combustion product 102 is just to flow through gas turbine 12 with the roughly the same direction of total flow path direction 80, and fuel-air sprays fuel and normally adverse current of air stream 96 and 98 that salient angle 52 is sprayed.In addition, adverse current can be longitudinally, with respect to 56 one-tenth of axis 62 or solid inner casings laterally or to there is the acute angle of vertical and horizontal directed section, point to stagnant area 86.So, upstream injection device 50 has promoted burner 30 fuels and air together with the mixing of combustion heat product, burns and has reduced the pollutant emission that burner 30 produces (for example, NOx discharge) thereby improved.Equally, lobe formation 74 is offset the inner periphery of microscler spray tip 70 solid inner casing 56 relative to air duct 72 slightly, makes thus the injection of fuel and air stream 96 and 98 slightly away from inner periphery, thereby has improved the mixing of fuel, air and hot combustion product.
Fig. 3 is the horizontal sketch of the embodiment of burner 30 shown in Fig. 2, further according to some embodiment of this technology, illustrated in the multiple radial positions 110,112,114,116,118,120,122 around solid inner casing 56, and the fuel of upstream injection device 50 on 124-air sprays the radial configuration of salient angle 52.As discussed with reference to figure 2 above, fuel and air stream 96 and 98 that multiple fuel and air spray salient angle 52 converge at axis 62 in 86 inside, stagnant area conventionally.In certain embodiments, fuel and air stream 96 and 98 can converge at center as dotted line 110,112,114,116,118,120,122 and 124 indications, i.e. axis 62 conventionally.
In other embodiments, fuel-air sprays salient angle 52 can be positioned to point to stagnant area 86 to gather to the mode of axis 62, and as shown in dotted arrow 126, axis 62 has at least a bit eccentric relatively simultaneously.Because fuel-air sprays the ethod of remittance of this bias of salient angle 52, the eddy flow that fuel and air stream 96 and 98 can produce as shown in dotted arrow 128.In any structure, the fuel-air relation of converging between salient angle 52 of spraying contributes to the mixing (also have with hot combustion product mix) of stagnant area 86 fuels and air.But, stagnant area 86 inward eddies 128 add the mixing and burning that can further promote burner 30 fuels-air.In certain embodiments, fuel-air sprays salient angle 52 can all be positioned to produce a clockwise eddy flow or a counterclockwise eddy flow.As selection, fuel-air sprays salient angle 52 can interlock to produce clockwise and counterclockwise eddy flow simultaneously.For example, odd number fuel-air (for example sprays salient angle 52, in radial position 110,114,118 and 122) can be positioned to produce clockwise eddy flow, even number fuel simultaneously-air injection salient angle 52 (for example,, in radial position 112,116,120 and 124) can be configured to produce counterclockwise eddy flow.In addition, shown in some embodiment of burner 30 can in the multiple lengthwise positions along axis 62, comprise that the fuel shown in Fig. 3-air sprays the annular array of salient angle 52, for example, in multistage burner 30 as above.
Fig. 4 is longitudinal sketch of the alternate embodiment of burner 30 shown in Fig. 1-3, and wherein according to some embodiment of this technology, what upstream injection device 50 comprised arranged radially or layout flushes fuel-air jeting area 140.As shown, the microscler spray tip 70 of fuel and air injection components 64 and 68 and air duct 72 extend to the position substantially flushing with the solid inner casing 56 of burner inner liner 54.That is to say, the inner surface 142 of microscler spray tip 70 and air duct 72 recessed solid inner casings 56, but inner casing 56 does not have projection near microscler spray tip 70 and air duct 72.Like this, contrary with fuel shown in Fig. 2 and 3-air injection salient angle 52, the fuel-air jeting area 140 that flushes of the arranged radially shown in Fig. 4 does not stretch into burner 30 inside and exceeds solid inner casing 56.But in certain embodiments, microscler spray tip 70 can be positioned to partly stretch out the inner surface 142 of solid inner casing 56.As selection, microscler spray tip 70 can retraction air duct 72, as further described and describe with reference to figure 12 below.In addition the mode that, upstream injection device 50 is configured to substantially converge as shown in Figure 4 guides fuel and air stream 96 and 98 to flow to stagnant area 86 against the total stream 80 through gas turbine 12.Then, hot combustion product is from stagnant area 86, the arranged radially of flowing through flush fuel-air jeting area 140, then flow out burner 30 via nozzle 32.
Fig. 5 is longitudinal sketch of another alternate embodiment of burner shown in Fig. 1, wherein according to some embodiment of this technology, burner 30 comprises upstream injection device 150, and upstream injection device 150 has along inside cantilevered fuel-air injection component 152 of the solid inner casing 56 inner arranged radiallys that arrange.In the embodiment shown, fuel-air injection component 152 inwardly stretches to from the solid inner casing 56 of burner inner liner 54, but does not arrive the central longitudinal axis 62 of burner 30.That is to say, fuel-air injection component 150 is cantilevered, and off-axis 62.
Shown in fuel-air injection component 152 have that band arranges along edge 158 and towards the concurrent kinetoplast 154 of the coaxial fuel-air scoop 156 and 157 of stagnant area 86.In the embodiment shown, coaxial fuel-air scoop 156 comprises three mouths 156 parallel with axis 62 cardinal principles, coaxial fuel air scoop 157 comprises a mouth 157 simultaneously, and mouth 157 is angled inside sensing (or converging at) axis 62 in the countercurrent direction of pointing to stagnant area 86.In optional embodiment, fuel-air scoop 156 and 157 can comprise the mouth to expect that interval arranges along concurrent kinetoplast 156 of any other quantity or layout.Coaxial fuel-air scoop 156 and petrolift or injector 160 and air duct 162 are communicated with, and wherein air duct 162 extends to the space between solid inner casing 56 and the porous shell 58 of burner inner liner 54.
So, fuel-air injection component 152 receives fuel and air by concurrent kinetoplast 154 simultaneously, subsequently concurrent kinetoplast 154 by the concurrent of fuel and air from coaxial fuel-air scoop 156 and 157, direction with substantially longitudinal sensing stagnant area 86 sprays into burner 30, as shown in arrow 164 and 165.In the embodiment shown, the longitudinal stream 164 of fuel and air is conventionally parallel with the axis 62 of burner 40, and stream 165 converges at axis 62 conventionally.But in other embodiment, coaxial fuel-air scoop 156 can be positioned to converge angle or the angle of divergence with respect to 62 one-tenth, axis conventionally.In addition, coaxial fuel-air scoop 156 and 157 can point to conventionally around the clockwise angle of axis 62 or counterclockwise angle, so just can be at the inner eddy flows that produce of burner 30, as discussed with reference to figure 3 above.
Be in operation, similar to the embodiment of Fig. 2, burner 30 receives through porous shell 58 and points to the compressed air of upstream injection device 150 along solid inner casing 56, as shown in arrow 92 and 94.After arriving upstream injection device 150, compressed air enters concurrent kinetoplast 154 through air duct 162, and fuel enters concurrent kinetoplast 154 from petrolift or injector 160 simultaneously.Fuel-air injection component 152 sprays into solid inner casing 56 inside by the concurrent of fuel and air from mouth 156 and 157 subsequently, as shown in arrow 164 and 165.Have, these concurrents 164 and 165 are arranged on multiple radiuss of a circle position of off-axis 62 again.In addition, concurrent 164 and 165 is positioned to flow into stagnant area 86 with the direction contrary or reverse with total stream 80 cardinal principles of passing gas turbine 12.So, the concurrent 164 and 165 of fuel-air contributes to the mixing of fuel-air, burns and has reduced the pollutant emission in burner 40 thereby improved.In stagnant area 86, the mixture 100 of fuel-air burns, and turns back with after heat combustion product, the upstream injection device 150 of flowing through, and arrive forward nozzle 32, as shown in arrow 102.Have, the concurrent 164 of fuel-air flows 102 one-tenth adverse currents with respect to hot combustion product conventionally with 165 again.So this adverse current has further promoted the mixing together with hot combustion product of burner 30 fuels and air, as discussed in detail above.
Fig. 6 is the horizontal sketch of burner 30 shown in Fig. 5, and it has illustrated inside cantilevered fuel-air injection component 152 of the arranged radially of upstream injection device 150 further according to some embodiment of this technology.The embodiment of Fig. 6 is slightly different from the embodiment of Fig. 5.Specifically, the quantity of mouth 156 is four instead of three, and Length Ratio Fig. 5's of concurrent kinetoplast 154 is relatively shorter.But the quantity of mouth 156 and 157 can increase or reduce according to the needs of particular burner 30.In addition, the length of body 154 can increase to extend to and approaches axis 62.And, each mouthfuls 156 and 157 can be inwardly and axis 62 at angle.
In the embodiment shown, fuel-air injection component 152 is arranged in the inner periphery of solid inner casing 56 or multiple radial positions of periphery, as shown in dotted line 166,168,170,172,174,176,178 and 180.In addition, fuel-air injection component 152 aligns or centering with axis 62 conventionally.But inwardly the inner of cantilevered fuel-air injection component 152 or free end departs from conventionally or offset axis 62, as shown in arrow 182.In certain embodiments, fuel-air injection component 152 can with axis 62 at angle, produce thus counterclockwise or clockwise eddy flow in the downstream of stagnant area 86.For example, fuel-air injection component 152 can be in an acute angle with solid inner casing 56 inner surfaces, instead of perpendicular.In the embodiment shown, upstream injection device 150 comprises into 8 fuel-air injection components 152 of circumference-radial configuration, as illustrated in Figures 5 and 6.But other embodiment of upstream injection device 150 can comprise fuel-air injection component 152 of other right quantities.
Fig. 7 is the cross sectional view of the exemplary embodiments of the injection component of fuel-air shown in Fig. 5 and 6 152, and it further illustrates the co-flow passage of concurrent kinetoplast 154 inside according to some embodiment of this technology.As shown, concurrent kinetoplast 154 has aerodynamic shape or airfoil structure conventionally.In addition, concurrent kinetoplast 154 comprises multiple side fuel injection passages 184, and side fuel injection passages 184 is extended from or conventional fuel service duct 186 for example, with the longitudinal axis (, vertical with accompanying drawing) of concurrent kinetoplast 154 longitudinally corresponding.These passages 184 and 186 conventionally by upper and lower support component 188 and 190 and one or more lateral support structure 192 with passage 184 support.Concurrent kinetoplast 154 also comprises one or more air ducts 194,196 and 198.Shown in fuel injection passages 184 and air duct 194,196 and 198 lead to coaxial fuel-air scoop 156 and 157 along edge 158, as described above.Especially, as shown in Figure 7, coaxial fuel-air scoop 156 and 157 comprises the concentric or annular air mouth 202 of side fuel injection passages 184 center fuel port 200 and air duct 194,196 and 198.So, be in operation, the fuel fuel-air injection component 152 of flowing through as shown in arrow 204, simultaneously the air fuel-air injection component 152 of flowing through as shown in arrow 206.
The alternate embodiment of burner 30 shown in Fig. 5-7 has been described in Fig. 8-10, wherein, according to some embodiment of this technology, inside cantilevered fuel-air injection component 152 of arranged radially comprises along the additional coaxial fuel-air scoop 210 and 211 of the upper and lower side of concurrent kinetoplast 154.First referring to Fig. 8, this figure is longitudinal sketch of burner 30, and it has described a series of coaxial fuel-air scoops 156 along edge 158 and 157 and a series of coaxial fuel-air scoop 210 and 211 along concurrent kinetoplast 154 fronts.As discussed with reference to figure 5 above, coaxial fuel-air scoop 156 is conventionally with respect to 62 one-tenth longitudinal registers of axis of burner 30, thereby produces fuel as shown in arrow 164 and the coaxial flow of air.Have, these coaxial flows 164 can be arranged in parallel with axis 62 conventionally again, or axis 62 converges relatively, or axis 62 is dispersed relatively.But, these common longitudinal sensing stagnant areas 86 along burner 30 of coaxial flows 164.Similarly, coaxial fuel-air scoop 157 (with stream 165) is positioned to point to stagnant area 86 along burner 30 length directions.But as mentioned above, coaxial fuel-air scoop 157 (with stream 165) converges at axis 62 conventionally in the countercurrent direction of pointing to stagnant area 86.
On the contrary, coaxial fuel-air scoop 210 laterally points at a certain distance with respect to axis 62.That is to say, coaxial fuel-air scoop 210 is positioned to conventionally produce the stream vertical with Fig. 8.Coaxial fuel-air scoop 211 also laterally points to respect to 62 one-tenth, axis.But different from coaxial fuel-air scoop 210, coaxial fuel-air scoop 211 radially inwardly points to axis 62 in the mode directly converging, as shown in arrow 167.That is to say, the whole straight lines of coaxial fuel-air scoop 211 point to axis 62, resemble the spoke of wheel or the ray of the sun.So, fuel-air injection component 152 just produces longitudinal stream and cross-current simultaneously, to promote the mixing of burner 30 fuels and air.
Fig. 9 is the horizontal sketch of burner 30 shown in Fig. 8, and it is according to some embodiment of this technology, further illustrates the fuel and the air cross-current 214 and 216 that are sprayed by the coaxial fuel-air scoop 210 being arranged on the opposite face 212 and 218 of concurrent kinetoplast 154.Have, the embodiment of Fig. 9 is slightly different from the embodiment of Fig. 8 again.Specifically, the quantity of mouth 156 and 210 is 4 instead of 3, and Length Ratio Fig. 8's of concurrent kinetoplast 154 is relatively shorter.But the quantity of mouth 156,157,210 and 211 can increase or reduce according to the needs of particular burner 30.In addition, the length of body 154 can increase to extend to and approaches axis 62.And each mouthful 156,157,210 and 211 can inwardly angularly point to axis 62.
As shown in Figure 9, strengthen gradually the common off-axis 62 of coaxial flow 214 and 216 by making to the distance of the solid inner casing 56 of burner inner liner 54 from the free end of concurrent kinetoplast 154.In addition, concurrent 214 is positioned to clockwise conventionally around axis 62, and concurrent 216 is positioned to conventionally counterclockwise around axis 62.So, concurrent 214 and 216 can produce reverse rotation stream or the swirling flow as shown in arrow 220 and 222 respectively.In addition, coaxial flow 165 and 167 converges at axis 62 conventionally, to such an extent as to coaxial flow 165 is conventionally vertical or horizontal with 216 one-tenth with respect to coaxial flow 214 with 167.
Figure 10 is the cross sectional view of the injection component of fuel-air shown in Fig. 8 and 9 152, and it has further described and led to the inner passage that is arranged on the coaxial fuel-air scoop 210 and 211 on surface 212 and 218 according to some embodiments of the present invention.Have again, similar to the embodiment of Fig. 7, concurrent kinetoplast 154 has aerodynamic shape or airfoil structure conventionally, multiple side fuel feed passage 184 from the longitudinal axis 154 (for example, vertical with accompanying drawing) corresponding first of concurrent kinetoplast 154 longitudinally or conventional fuel service duct 186 extend.Concurrent kinetoplast 154 also comprises one or more air ducts 194,196 and 198.Shown in fuel injection passages 184 and air duct 194,196 and 198 lead to coaxial fuel-air scoop 156 and 157 along edge 158, as mentioned above.Especially, as shown in Figure 7, coaxial fuel-air scoop 156 and 157 comprises the concentric or annular air mouth 202 of side fuel injection passages 184 center fuel port 200 and air duct 194,196 and 198.
Except the feature of Fig. 7 embodiment, the upper and lower support component 188 and 190 of Figure 10 comprise by second longitudinally or conventional fuel service duct 186 lead to respectively the upper and lower fuel injection passages 230 and 232 of the fuel injection orifice 234 and 236 on opposite face 212 and 218.That is to say, illustrated embodiment comprises two independently fuel feed passage 186, and mouth 156 and 157 is just independent of mouthful 210 and 211 burner oils like this.In alternate embodiment, single fuel feed passage 186 can be for all mouths 156,157,210 and 211.In another alternate embodiment, independently fuel feed passage 186 can be for each group mouth 156,157,210 and 211.Coaxial fuel-air scoop 210 and 211 also comprises or the annular air jet 238 and 240 that arrange concentric around fuel injection orifice 234 and 236 respectively.So, being in operation, fuel and air are as the arrow 204 and 206 fuel-air injection component 152 of flowing through.
Figure 11 is longitudinal sketch of 30 embodiment of another burner shown in Fig. 5, and wherein according to some embodiment of this technology, upstream injection device 150 has and is arranged on nozzle 32 places, near or inner unidirectional interior cantilevered fuel-air injection component 152.As shown, in list, stretch out from a side of solid inner casing 56 to the concurrent kinetoplast 154 of cantilevered fuel-air injection component 152, and extend through the essential part of its diameter at nozzle 32 places.Therefore, in this embodiment, concurrent kinetoplast 154 extends through the central longitudinal axis 62 of burner 30 at nozzle 32 places.Coaxial fuel-air scoop 156 is arranged through the both sides of axis 62, and fuel-air injection component 152 just provides the coaxial flow 164 of fuel and air at bias or deviation post with respect to axis 62 like this.In the embodiment shown, one of them fuel-air scoop 156 62 is arranged or alignment conventionally vertically, thereby fuel and an air coaxial flow 164 that converges at axis 62 is provided.In certain embodiments, fuel-air injection component 152 may further include coaxial fuel-air scoop 210, and for example those are at the mouth shown in the embodiment of Fig. 8-10.In addition, it should be noted that the length of burner 30 can be than Fig. 2,4,5 relative shorter with 8 embodiment because upstream injection device 150 be arranged on nozzle 32 places or near, instead of centre position between blind end 88 and the nozzle 32 of burner 30.
Figure 12-15th, the sketch of the different alternative embodiments of description fuel-air jet system, for example fuel-air sprays salient angle 52, flushes fuel-air jeting area 140 and inside cantilevered fuel-air injection component 152, as discussed in detail with reference to figure 2-11 above.First referring to the embodiment of Figure 12, this figure has illustrated the coaxial fuel-air jet system 260 according to some embodiment of this technology.As shown, coaxial fuel-air jet system 260 comprises the concentric or outer ring air duct 266 arranging with one heart along axis 264 center fuel channel 262 with around center fuel channel 262.In the embodiment shown, the end 268 of center fuel channel 262 arranges with an offset distance 270 and 272 intervals, end of concentric or outer ring air duct 266.Especially, the end 268 of center fuel channel 262 is recessed into one heart or the end 272 of outer ring air duct 266.But in other embodiment of coaxial fuel-air jet system 260, end 268 and 272 can flush substantially each other, or the end 268 of center fuel channel 262 can be outwardly from the end 272 of concentric or outer ring air duct 266.Be in operation, coaxial fuel-air jet system 260 produces the center fuel flow 274 being surrounded by annular air stream 276, and this has promoted the mixing of burner 30 fuels-air.
Figure 13 is the typical radial-axial fuel-air jet system 280 according to some embodiment of this technology, and it has radial flow and the axial flow of colliding each other the mixing that promotes fuel-air.In the embodiment shown, radial-axial fuel-air jet system 280 comprise along axis 284 center fuel channel 282 and arrange around center fuel channel 282 with one heart or outer ring air duct 286.In addition, center fuel channel 282 comprises one or more radial port 288 vertical with axis 284 conventionally.Center fuel channel 282 also has the conical section or the end 290 that are positioned at radial port 288 downstreams.Be in operation, air passes the concentric or outer ring air duct 286 around center fuel channel 282 along the direction of axis 284, as shown in arrow 292.In addition, fuel flows through center fuel channel 282 along the direction of the axis 284 shown in arrow 294.After arriving radial port 288, fuel radially outward sprays into air stream 292 from axis 284, as shown in arrow 296.Like this, air is conventionally intersected with each other or vertical with 296 with fuel flow 292, just to promote the mixing of radial-axial fuel-air jet system 280 fuels and air before spraying into burner 30.In addition, radial-axial fuel-air jet system 280 contributes to the mixing of burner 30 fuels-air, instead of the premix of fuel and air.
Figure 14 is the alternative radial-axial fuel-air jet system 300 according to some embodiment of this technology.As shown, the outer wall 304 of fuel injection device 302Yu center air duct 306 connects.Shown in fuel injection device 302 comprise multiple radial fuel mouths 308 that run through outer wall 304.In addition, air flows through center air duct 306 along the direction 310 of axis 312.On the contrary, fuel with respect to axis 312 substantially radially or on horizontal 314 through radial fuel mouth 308.So, air and fuel flow 310 and 314 collision each other in radial-axial fuel-air jet system 300.The collision of air and fuel flow 310 and 314 has promoted the mixing of injection apparatus 300 fuels-air.In addition, radial-axial fuel-air jet system 300 contributes to the mixing of burner 30 fuels-air, instead of the premix of fuel and air.
Figure 15 is the alternative coaxial fuel-air swirl injection apparatus 320 according to some embodiment of this technology.As shown, swirling jet unit 320 comprises the center fuel channel 322 extending along axis 324 and the concentric or outer ring air duct 326 arranging around center fuel channel 322.In addition, center fuel channel 322 comprises and is arranged on fuel outlet or mouthful 330 places or near fuel swirl device 328.Concentric or outer ring air duct 326 also comprises one or more air swirl devices 332 that are arranged on fuel outlet or mouthful 330 downstreams.Be in operation, fuel flows through central passage 322 along the direction 334 of axis 324.After arriving fuel swirl device 328, fuel flow obtains one clockwise or is rotated counterclockwise or turn, as shown in arrow 336.Similarly, air stream flows through with one heart or outer ring air duct 326 vertically, as shown in arrow 338.After arriving air swirl device 332, air stream obtains a clockwise or counterclockwise rotation, as shown in arrow 340.So, the fuel of rotation or turn and air stream 336 and 340 have promoted the mixing of swirling jet unit 320 fuels and air.
In certain embodiments, fuel and the air stream 336 and 340 of rotation or turn have common direction of rotation, for example clockwise or counterclockwise.But in other embodiments, fuel and the air stream 336 and 340 of rotation or turn can have contrary direction of rotation, for example, clockwise with counterclockwise, or vice versa.In addition, some embodiment of swirling jet unit 320 can only include air swirl device 332 and not comprise fuel swirl device 328, or only include fuel swirl device 328 and do not comprise air swirl device 332.Other embodiment can comprise continuously or the additional fuel or the air swirl device 328 and 332 that are set parallel to each other.Have, these swirl-flow devices 328 and 332 contribute to the mixing of swirling jet unit 320 fuels and air again.And coaxial fuel-air swirl injection apparatus 320 contributes to the mixing of burner 30 fuels-air, instead of the premix of fuel and air.
The present invention shows as an example in the accompanying drawings specific embodiment, and in this article they has been described in detail, although can easily have various amendments and replacement form.But, will be appreciated that and do not wish that the present invention is limited to disclosed concrete form.On the contrary, the present invention falls into covering all modifications, equivalent and the alternative in the spirit and scope of following additional invention that claim defines.
Parts catalogue
10 systems
12 gas turbines
14 application
16 air approach sections
18 compressors
20 burner sections
22 turbines
24 discharge section
26 axles
28 burner shells
30 burners
32 nozzles
34 loads
40 burners
50 upstream injection devices
52 fuel-air sprays salient angle
54 burner inner liners
56 solid inner casings
58 porous shells
60 lengthwise positions
62 center longitudinal axis
64 fuel injection components
66 air injection components
68 fuel injectors
70 spray tip
72 acute angle air ducts
74 lobe formation
76 protuberances
78 recess
80 always flow
82 jiaos
84 jiaos
86 stagnant areas
88 close rear
90 holes
92 arrows
94 arrows
96 fuel flows
98 air streams
100 streams/mixing arrow
102 arrows
110 radial positions
112 radial positions
114 radial positions
116 radial positions
118 radial positions
120 radial positions
122 radial positions
124 radial positions
126 dotted arrows
128 dotted arrows
140 flush fuel-air jeting area
142 inner surfaces
150 injection apparatus
152 fuel-air injection component
154 concurrent kinetoplasts
156 mouthfuls
157 mouthfuls
158 edges
160 petrolifts or injector
162 air ducts
164 arrows
165 arrows
166 dotted lines
167 arrows
168 dotted lines
170 dotted lines
172 dotted lines
174 dotted lines
176 dotted lines
178 dotted lines
180 dotted lines
182 arrows
184 fuel injection passages
186 fuel feed passage
188 support components
190 support components
192 supporting constructions
194 air ducts
196 air ducts
198 air ducts
200 center fuel ports
202 air scoops
204 arrows
206 arrows
210 coaxial fuels-air scoop
211 coaxial fuels-air scoop
212 surfaces
214 coaxial flows
216 coaxial flows
218 surfaces
220 arrows
222 arrows
230 fuel injection passages
232 fuel injection passages
234 fuel injection orifices
236 fuel injection orifices
238 air jets
240 air jets
260 coaxial fuels-air jet system
262 center fuel channels
264 axis
266 annular air channel
268 ends
270 offset distances
272 ends
274 fuel flows
276 air streams
280 radial-axial fuel-air jet systems
282 fuel channels
284 fuel channels
286 air ducts
288 radial port
290 conical sections or end
292 arrows
294 arrows
296 arrows
300 radial-axial fuel-injection apparatus
302 fuel injection devices
304 outer walls
306 center air ducts
308 radial fuel mouths
310 is axial
312 axis
314 radially or laterally
320 coaxial fuels-air swirl injection apparatus
322 center fuel channels
324 axis
326 air ducts
328 fuel swirl devices
330 fuel outlets or mouth
332 air swirl devices
334 is axial
336 arrows
338 arrows
340 arrows
Claims (11)
1. a gas turbine engine systems, comprising:
Gas turbine burner (30), described gas turbine burner (30) comprising:
Combustion liner (54), its stagnant area (86) with the close rear (88) from being positioned at described burner (30) extends to the longitudinal axis of flow of cardinal principle of turbine (22); With
Inwardly cantilevered adverse current fuel-air injection equipment (50,150), it comprises the coaxial fuel and the air duct that lead to fuel and air jet,
It is characterized in that:
Fuel and air jet are arranged on the position of departing from gas turbine burner (30) axis, and the injection direction of fuel and air jet is oriented to not with in alignment to the flow direction of turbine (22) by gas turbine burner (30).
2. gas turbine engine systems as claimed in claim 1, is characterized in that: fuel and air jet are coaxial setting each other substantially.
3. gas turbine engine systems as claimed in claim 1, is characterized in that: fuel and air jet depart from each other along the common axis line of coaxial fuel and air duct.
4. gas turbine engine systems as claimed in claim 1, is characterized in that: fuel and air jet are oriented to intersected with each other.
5. gas turbine engine systems as claimed in claim 4, is characterized in that: fuel injection orifice is arranged in the circle wall (304) of the air duct (306) in coaxial fuel and air duct.
6. gas turbine engine systems as claimed in claim 4, is characterized in that: fuel injection orifice is arranged in the circle wall of the fuel channel (282) in coaxial fuel and air duct.
7. gas turbine engine systems as claimed in claim 1, is characterized in that: coaxial fuel and air duct comprise fuel swirl mechanism (328), or air swirl mechanism (332), or their combination.
8. gas turbine engine systems as claimed in claim 1, is characterized in that: coaxial fuel and air duct comprise reverse eddy flow mechanism.
9. gas turbine engine systems as claimed in claim 1, is characterized in that: comprise the multiple described fuel-air injection equipment (50,150) in multiple radial positions along circumference.
10. a gas turbine engine systems, comprising:
Gas turbine burner (30), described gas turbine burner (30) comprising:
Combustion liner (54), the stagnant area (86) with the close rear (88) from being positioned at described burner (30) extends to the longitudinal axis of flow of cardinal principle of turbine (22); With
Inwardly cantilevered adverse current fuel-air ejector (50,150), it is arranged on and on combustion liner (54), is positioned at the one or more centre positions between stagnant area (86) and turbine (22), wherein adverse current fuel-air ejector (50,150) comprise coaxial fuel and air duct, described fuel and air duct extend to not with from stagnant area (86) to the flow direction of turbine (22) fuel and air jet in alignment.
11. 1 kinds of minimizings, according to the method for the pollutant emission of the burner of the gas turbine engine systems described in any one in claim 1-9, comprising:
Make fuel and air coaxially flow to described inside cantilevered adverse current fuel-air ejector (50,150), it is directed in the direction that becomes cardinal principle adverse current with respect to described cardinal principle longitudinal stream moving axis (62).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200710087945.1A CN101235969B (en) | 2007-01-31 | 2007-01-31 | Reverse current jet mechanism with coaxial fuel-air passageway |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200710087945.1A CN101235969B (en) | 2007-01-31 | 2007-01-31 | Reverse current jet mechanism with coaxial fuel-air passageway |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101235969A CN101235969A (en) | 2008-08-06 |
| CN101235969B true CN101235969B (en) | 2014-11-26 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200710087945.1A Expired - Fee Related CN101235969B (en) | 2007-01-31 | 2007-01-31 | Reverse current jet mechanism with coaxial fuel-air passageway |
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| CN (1) | CN101235969B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102607025A (en) * | 2011-12-06 | 2012-07-25 | 上海诺特飞博燃烧设备有限公司 | Gas back-jetting pre-mixing low-NOx combustion apparatus and combustion method of combustion apparatus |
| US9200808B2 (en) * | 2012-04-27 | 2015-12-01 | General Electric Company | System for supplying fuel to a late-lean fuel injector of a combustor |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2635426A (en) * | 1949-06-29 | 1953-04-21 | A V Roe Canada Ltd | Annular vaporizer |
| GB726538A (en) * | 1953-01-14 | 1955-03-23 | Lucas Industries Ltd | Liquid fuel vaporisers |
| US3290880A (en) * | 1964-02-21 | 1966-12-13 | Rolls Royce | Combustion equipment for a gas turbine engine |
| US3531937A (en) * | 1968-09-24 | 1970-10-06 | Curtiss Wright Corp | Fuel vaporizer for gas turbine engines |
| CN1037957A (en) * | 1988-05-05 | 1989-12-13 | 巴布考克和威尔科斯公司 | The modified burner of coal combustion, oil or gas |
| US4922840A (en) * | 1988-03-28 | 1990-05-08 | Avco Research Laboratory, Inc. | Sulfur equilibrium desulfurization of sulfur containing products of combustion |
| CN1209521A (en) * | 1997-08-25 | 1999-03-03 | Abb研究有限公司 | Burner for heat generator |
| US6148604A (en) * | 1998-06-30 | 2000-11-21 | Rolls-Royce Plc | Combustion chamber assembly having a transition duct damping member |
-
2007
- 2007-01-31 CN CN200710087945.1A patent/CN101235969B/en not_active Expired - Fee Related
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2635426A (en) * | 1949-06-29 | 1953-04-21 | A V Roe Canada Ltd | Annular vaporizer |
| GB726538A (en) * | 1953-01-14 | 1955-03-23 | Lucas Industries Ltd | Liquid fuel vaporisers |
| US3290880A (en) * | 1964-02-21 | 1966-12-13 | Rolls Royce | Combustion equipment for a gas turbine engine |
| US3531937A (en) * | 1968-09-24 | 1970-10-06 | Curtiss Wright Corp | Fuel vaporizer for gas turbine engines |
| US4922840A (en) * | 1988-03-28 | 1990-05-08 | Avco Research Laboratory, Inc. | Sulfur equilibrium desulfurization of sulfur containing products of combustion |
| CN1037957A (en) * | 1988-05-05 | 1989-12-13 | 巴布考克和威尔科斯公司 | The modified burner of coal combustion, oil or gas |
| CN1209521A (en) * | 1997-08-25 | 1999-03-03 | Abb研究有限公司 | Burner for heat generator |
| US6148604A (en) * | 1998-06-30 | 2000-11-21 | Rolls-Royce Plc | Combustion chamber assembly having a transition duct damping member |
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| CN101235969A (en) | 2008-08-06 |
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