CN102809176A

CN102809176A - Aerodynamic fuel nozzle

Info

Publication number: CN102809176A
Application number: CN2012101792348A
Authority: CN
Inventors: J·M·海恩斯
Original assignee: General Electric Co
Current assignee: General Electric Co
Priority date: 2011-04-22
Filing date: 2012-04-20
Publication date: 2012-12-05
Also published as: EP2515042A3; US20120266602A1; EP2515042A2

Abstract

The present application and the resultant patent provide a combustor (100) for a turbine engine (10). The combustor (100) may include a number of fuel nozzles (110) with one or more of the fuel nozzles (110) including a swirler assembly (130). The swirler assembly (130) may include a number of stages (140) with a number of fueled structures (245) and a number of unfueled structures (250).

Description

The aerodynamic force fuel nozzle

Technical field

The present invention relates in general to gas-turbine unit, and relates more particularly to be used to the aerodynamic force fuel nozzle that postpones thin injection and turn down the three swirler device of (turndown) a kind of having.

Background technology

Dry low NOx technology can be used for utilizing the emission control of gas fuel combustion of the industry gas turbine of annular firing system etc.These known dry low NOx combustion systems provide the premix of fuel and air, are used to have the burning velocity unanimous on the whole of constant relatively reaction zone temperature.Through meticulous air administrative, these reaction zone temperatures can be optimized to produce considerably less nitrogen oxide (" NOx "), carbon monoxide (" CO "), unburned hydrocarbon (" UHC "), and the emission of not expecting of other types.Specifically, when changing the fuel input that gets into turbine, the adjusting of center premixed fuel nozzle keeps constant relatively and can enlarge opereating specification with corresponding reaction speed through the fuel-air ratio that allows outer nozzle.

Fuel staging allows to have the higher turbine-entry temperature of balanced heat release.Axially staged system adopts along a plurality of fuel of burner runner usually sprays the plane.Though making progress aspect material and the heat-transferring method, under full-load conditions, producing low discharged nitrous oxides, current burner design is still challenged.Likewise, the carbon monoxide emission under the sub-load condition is forming challenge aspect the reduction combustion ignition temperature.Through only lighting selected nozzle, contiguous unignited nozzle possibly suppress this reaction and produce carbon monoxide.Thereby this nozzle of lighting also possibly cause the remarkable thermal stress in the combustion liner to shorten component life.

Therefore exist for the feasible demand that reduces the fuel temperature peak value of the method for improved fuel nozzle and burner design and/or classification fuel wherein.This type of improved design should keep sufficient system's output and efficient with the corresponding low yield of nitrogen oxide, carbon monoxide and other types emission.

Summary of the invention

Therefore the application and resulting patent provide a kind of burner that is used for turbogenerator.This burner can comprise a plurality of fuel nozzles, and one of fuel nozzle or more comprise a kind of swirler assembly more.This swirler assembly can comprise a plurality of levels, and these grades have structure and a plurality of structure of not supplying with fuel of a plurality of supply fuel.

The application and resulting patent also provide a kind of method that is used to postpone the burner of thin injection of operating.This method can may further comprise the steps: provide air to flow to fuel nozzle; The structure of fuel stream through one or more supply fuel of swirler assembly is provided; Make a plurality of grades air stream and fuel stream eddy flow through swirler assembly; Be formed for the fuel nozzle main recirculating zone on every side of low emission, and the auxilliary recirculating zone that is formed for the fuel nozzle downstream of high temperature.

The application and resulting patent also provide a kind of swirler assembly of using with burner of being used for.This swirler assembly can comprise a plurality of levels, a plurality of blades, and a plurality of.Each level can comprise one or more multiple-blade and/or piece.

After combining some accompanying drawings and accompanying claims to check the following specific embodiment, these of the application and resulting patent will become obvious with other characteristics and improvement for those of ordinary skills.

Description of drawings

Fig. 1 is the sketch map of known gas-turbine unit.

Fig. 2 is the schematic cross sectional view of known burner.

Fig. 3 is end cap and the schematic elevational view of fuel nozzle assembly of the burner of Fig. 2.

Fig. 4 is that have can be like the part side sectional view of the fuel nozzle of cyclone described herein.

Fig. 5 is that have can be like the part side sectional view of the fuel nozzle of the alternative of cyclone described herein.

Fig. 6 is the front plan view of radial embodiment of cyclone of the fuel nozzle of Fig. 4.

Fig. 7 is the sketch map of piece embodiment of cyclone of the fuel nozzle of Fig. 4.

Fig. 8 is the part side view of piece embodiment of the cyclone of Fig. 7.

List of parts

10 gas-turbine units

15 compressors

20 air stream

25 burners

30 fuel stream

35 burning gases stream

40 turbines

45

50 loads

55 shells

60 end caps

65 outer nozzles

70 central nozzles

75 combustion zones

80 shells

85 stream sleeves

90 runners

95 transition pieces

100 burners

110 fuel nozzles

120 center fuel nozzles

130 swirler assemblies

140 grades

150 first order

160 second level

170 third level

180 axial directions

190 circumferential direction

200 radial blades

210

220 fixed blocks

230 movable blocks

240 jets

245 supply with fuel

250 do not supply with fuel

260 enrichment recirculating zones

270 thin recirculating zones

The specific embodiment

Referring now to accompanying drawing,, wherein runs through the similar similar parts of numeral indication of some views.Fig. 1 has shown the sketch map of turbomachinery, and this turbomachinery is such as can be gas-turbine unit 10 described herein.This gas-turbine unit 10 can comprise compressor 15.Compressor 15 compressions get into air stream 20.This compressor 15 carries air compressed stream 20 to burner 25.Burner 25 mixes the fuel stream 30 of air compressed stream 20 and compression and lights this mixture to produce burning gases stream 35.Though only shown single burner 25, gas-turbine unit 10 can comprise the burner 25 of arbitrary number.Burning gases stream 35 is transported to turbine 40 again.Burning gases stream 35 drives turbine 40 so that produce mechanical power.The mechanical power that in turbine 40, produces is through axle 45 Driven Compressor 15 and external loadings 50, for example generator etc.

Gas-turbine unit 10 can use natural gas, various types of synthesis gas, and/or the fuel of other type.Gas-turbine unit 10 can be any one in many different gas-turbine units, those gas-turbine units that for example provided by the General Electric Co. Limited of New York Si Kanaitadi etc.Gas-turbine unit 10 can have different structures and can use the parts of other type.The gas-turbine unit of other type also can be used here.A plurality of gas-turbine units, the turbine of other types, and the generating equipment of other types also can be together with here.

Fig. 2 and 3 has shown an instance of known burner 25.In general, burner comprises shell 55.Shell 55 can be by bolt to the turbine 40 or otherwise attached.One end of shell 55 can be surrounded by end cap 60.End cap 60 is admitted supply pipe, collector and the relevant valve that is used for supply gas fuel, liquid fuel, empty G&W.This end cap 60 supports a plurality of outer fuel nozzles 65 around central nozzle 70.Can use other parts and other structures here.

Combustion zone 75 can be positioned in the shell 55 and

fuel nozzle

65,70 in end cap 60 downstream.Combustion zone 75 can be surrounded by combustion liner 80.Stream sleeve 85 can and limit runner 90 betwixt around combustion liner 80.From the air of compressor reducer 15 stream 20 this runner 90 of flowing through, around end cap 60, turn to, and flow into fuel nozzle 65,70.Transition piece 95 can extend around the downstream of shell 55.Transition piece 95 can be communicated with turbine 10, is used for guiding burning gases stream 35 to the there.Can use other parts and other structure here.

Burner 25 can compatiblely postpone thin injection.Postponing the thin burner that sprays compatibility can be to have to exceed about 2; 500 degrees Fahrenheits (about 1; 371 degrees centigrade) outlet temperature, perhaps handle and have ratio such as methane has more reactivity, have any burner greater than the fuel of the component of about 10 milliseconds hot junction residence time.The instance that postpones thin injection compatible burner comprises DLN-1 (" dry-low NOx ") burner, DLN-2 burner and the DLN-2.6 burner that the General Electric Co. Limited by New York Si Kanaitadi provides.Can use the thin injection compatible burner of delay of other type here.This type of postpones thin injection compatible burner has and is positioned at around the transition piece 95 or other position is used for a plurality of fuel injector (not shown) of fuel staging etc.Yet these downstream fuel injectors possibly increase the overall complexity of burner 25.Can use other parts and other structure here.

Fig. 4 shows the instance of the part of burner 100 that can be as described herein.Burner 100 comprises a plurality of fuel nozzles 110.Can use the fuel nozzle 110 of any amount.In this example, at least one central nozzle 120 can comprise swirler assembly 130.Swirler assembly 130 can be the cyclone with three levels 140.Therefore three levels 140 comprise the first order 150, the second level 160 and the third level 170.Can use the level 140 of any amount here.Level 140 can be as shown in Figure 4 180 location in axial direction, as shown in Figure 5 along circumferential direction 190 location, perhaps along their integrated positioning.Outer cyclone can have whirlpool and count S3＞0.6, and interior cyclone can have, and whirlpool is counted S2＞S3 and whirlpool is counted S1＞S3.The whirlpool numerical table is levied the burner backflow that has greater than the whirlpool several 0.6 of expression good reflux.Can use other parts and other structure here.

The level 140 of swirler assembly 130 can be taked multiple multi-form.For example, cyclone 130 can comprise a plurality of radial blades 200 as shown in Figure 6, as shown in Figure 7 a plurality of 210, and/or their combination.Also can adopt other shape here.In the piece embodiment of Fig. 7, can adopt a plurality of fixed blocks 220 and a plurality of movable blocks 230, so that a kind of variable cyclone is provided.In arbitrary embodiment, can adopt a plurality of jets 240 as shown in Figure 8 for the structure 245 of supplying with fuel.Jet 240 can be radially, axially and/or on the circumferential direction locate.For example, in the blade 200 of Fig. 7, can use three directions that (3) are different.This blade 200 also can be a structure 250 of not supplying with fuel with piece 210.Can use other structure and other parts here.

The combination of blade 200 and piece 210 can be used together.Specifically, can use to have dissimilar blade 200 piece 210, or the dissimilar cyclones of other shape here.Following chart shows some instances of the different embodiment of swirler assembly 130:

Instance shown in this paper is not an exclusiveness.As understandable, can use the various combination of arbitrary number that is supplied to fuel or does not supply with blade 200 and the piece 210 of fuel herein.

Therefore fuel nozzle 110 forms near the main recirculating zone 260 of nozzle 120 and the auxilliary recirculating zone 270 in downstream.The thin spraying of Along with delayed, main recirculating zone 260 are operated near flammability limit (approximately Phi～2.5 or approximately Phi～0.4) and combustion product moves downstream and do not form a large amount of nitrogen oxide or other emission.In auxilliary recirculating zone 270, core and third level air mix under the condition of overall lean and the bulk temperature of rising hot combustion gas, so that reduce fuel staging through pneumatic mode.

Turn down for height, main recirculating zone 260 can be at thin temperature (approximately Phi～0.5 to the 0.6) down-firing of appropriateness.This can realize good fuel after-flame and keep low emission.In downstream more, inner product and the 3rd stream mix so that make mixture reach the condition of overall lean in auxilliary recirculating zone 270.Thereby fuel nozzle 110 can form and turn down, and when having unlit nozzle, keeps low CO simultaneously.

Therefore nozzle 110 makes it possible to do not having under the situation of obvious hardware change, postpones thin jet performance raising combustion ignition temperature and does not increase nitrogen oxide through carrying out effectively.Nozzle 110 makes it possible to also to carry out that high burning is turned down and the carbon monoxide that do not produce the level of signifiance.Nozzle 110 can be used in combination with existing nozzle, and existing nozzle can keep unignited and not influence the low CO performance.

Therefore the use that has the swirler assembly 130 of central nozzle 120 provides fuel staging, so that produce air downstream classification flame.So the fuel staging here can maximize.And this type of fuel staging can suppress the dynamic change of burning.

Obviously, above-mentioned some embodiment that only relates to the application and resulting patent.Many variations and improvement can be made under situation about not deviating from claim and its marrow of the present invention that equivalent limited and scope those of ordinary skills.

Claims

1. burner (100) that is used for turbogenerator (10) comprising:

A plurality of fuel nozzles (110); With

One or more swirler assembly (130) that comprises of said a plurality of fuel nozzle (110) more;

Wherein said swirler assembly (130) comprises a plurality of levels (140); And

Wherein said a plurality of levels (140) comprise structure (245) and a plurality of structure (250) of not supplying with fuel of a plurality of supply fuel.

2. burner as claimed in claim 1 (100) is characterized in that, said a plurality of fuel nozzles (110) comprise center fuel nozzle (120).

3. burner as claimed in claim 1 (100) is characterized in that, said a plurality of levels (140) comprise the first order (150), the second level (160), and the third level (170).

4. burner as claimed in claim 1 (100) is characterized in that, said a plurality of levels (140) go up at axial direction (180) extends.

5. burner as claimed in claim 1 (100) is characterized in that, said a plurality of levels (140) go up in circumferential direction (190) extends.

6. burner as claimed in claim 1 (100) is characterized in that, said a plurality of levels (140) comprise a plurality of radial blades (200).

7. burner as claimed in claim 1 (100) is characterized in that, said a plurality of levels (140) comprise a plurality of (210).

8. burner as claimed in claim 7 (100) is characterized in that, said a plurality of (210) comprise a plurality of fixed blocks (220) and a plurality of movable block (230).

9. burner as claimed in claim 1 (100) is characterized in that, the structure of said a plurality of supply fuel (245) comprises a plurality of radial blades (200) and a plurality of (210).

10. burner as claimed in claim 1 (100) is characterized in that, the structure of said a plurality of supply fuel (245) comprises a plurality of jets (240).

11. burner as claimed in claim 10 (100) is characterized in that, said a plurality of jets (240) comprise axial direction (180) and/or circumferential direction (190).

12. burner as claimed in claim 1 (100) is characterized in that, said burner also comprises said a plurality of fuel nozzle (110) the main recirculating zone (260) on every side and the auxilliary recirculating zone (270) in said a plurality of fuel nozzle (110) downstream.

13. burner as claimed in claim 1 (100) is characterized in that, the structure of said a plurality of supply fuel (245) comprises a plurality of blades (200).

14. burner as claimed in claim 1 (100) is characterized in that, the structure of said a plurality of supply fuel (245) comprises a plurality of movable blocks (230).

15. an operation is used to postpone the method for the burner (100) of thin injection, comprising:

Air stream (20) to fuel nozzle (110) is provided;

One or the more structure (245) of supplying with fuel of fuel stream (30) through swirler assembly (130) are provided more;

Make said air stream (20) and said fuel stream (30) a plurality of level (140) eddy flows through said swirler assembly (130);

Be formed for said fuel nozzle (110) the main recirculating zone (260) on every side of low emission; With

Be formed for the auxilliary recirculating zone (270) in said fuel nozzle (110) downstream of high temperature.