CN107466354A - Cyclone, burner and burner for gas-turbine unit - Google Patents
Cyclone, burner and burner for gas-turbine unit Download PDFInfo
- Publication number
- CN107466354A CN107466354A CN201680020973.9A CN201680020973A CN107466354A CN 107466354 A CN107466354 A CN 107466354A CN 201680020973 A CN201680020973 A CN 201680020973A CN 107466354 A CN107466354 A CN 107466354A
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- China
- Prior art keywords
- cyclone
- counterbore
- hole
- hand
- gaseous fuel
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 239000000446 fuel Substances 0.000 claims abstract description 112
- 239000000203 mixture Substances 0.000 claims abstract description 19
- 239000007789 gas Substances 0.000 claims description 27
- 239000000463 material Substances 0.000 claims 1
- 230000002035 prolonged effect Effects 0.000 claims 1
- 239000003570 air Substances 0.000 description 77
- 238000002485 combustion reaction Methods 0.000 description 16
- 238000002347 injection Methods 0.000 description 14
- 239000007924 injection Substances 0.000 description 14
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 10
- 239000003344 environmental pollutant Substances 0.000 description 5
- 231100000719 pollutant Toxicity 0.000 description 5
- 230000001419 dependent effect Effects 0.000 description 3
- 239000007788 liquid Substances 0.000 description 3
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 2
- 229910002091 carbon monoxide Inorganic materials 0.000 description 2
- 239000004215 Carbon black (E152) Substances 0.000 description 1
- GQPLMRYTRLFLPF-UHFFFAOYSA-N Nitrous Oxide Chemical class [O-][N+]#N GQPLMRYTRLFLPF-UHFFFAOYSA-N 0.000 description 1
- 239000012080 ambient air Substances 0.000 description 1
- 230000000295 complement effect Effects 0.000 description 1
- 239000004020 conductor Substances 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 229930195733 hydrocarbon Natural products 0.000 description 1
- 150000002430 hydrocarbons Chemical class 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- JTJMJGYZQZDUJJ-UHFFFAOYSA-N phencyclidine Chemical class C1CCCCN1C1(C=2C=CC=CC=2)CCCCC1 JTJMJGYZQZDUJJ-UHFFFAOYSA-N 0.000 description 1
- 230000001869 rapid Effects 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
- F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN A CARRIER GAS OR AIR
- F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
- F23C2900/07001—Air swirling vanes incorporating fuel injectors
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Pre-Mixing And Non-Premixing Gas Burner (AREA)
Abstract
The present invention relates to the cyclone in a kind of burner for gas-turbine unit,Including the circumferentially staggered arrangement according to circular,Multiple passages essentially radially to extend internally,Each passage has a radially outer arrival end,One inner radial port of export,First and second lateral surfaces essentially radially to extend internally,And primary surface and top surface,In the use of cyclone,Fuel and air march to its port of export along these passages from the arrival end of these passages,To create eddy flow fuel/air mixture near the port of export,At least one surface of wherein at least one passage includes at least one gaseous fuel hand-hole,It is characterized in that,Surface with gaseous fuel hand-hole includes at least one counterbore,At least one counterbore radially surrounds gas fuel orifice,Wherein gaseous fuel hand-hole is disposed in the base portion of counterbore.
Description
Technical field
It is all the present invention relates to the cyclone in a kind of burner for gas-turbine unit, including according to circular
To interlaced arrangement, multiple passages essentially radially to extend internally, there is each passage radially outer arrival end, inner radial to go out
Mouth end, the first and second lateral surfaces essentially radially to extend internally and primary surface and top surface, in the use of cyclone
In, fuel and air march to the port of export of these passages along passage from the arrival end of these passages, so as to attached in the port of export
Near to create eddy flow fuel/air mixture, wherein at least one surface includes at least one gaseous fuel hand-hole.
In addition, the present invention relates to a kind of burner for gas-turbine unit.
In addition, the present invention relates to a kind of burner for gas-turbine unit.
Background technology
Gas-turbine unit includes ambient air feed pipe road, compressor, burner, expanding machine (i.e. turbine) and row
Feed channel.
It is expected the disposal of pollutants of reduction gas-turbine unit, particularly nitrogen oxides (NOx), carbon monoxide (CO), not
Hydrocarbon (UHC), smog and the particulate emission of after-flame.
Reducing a kind of mode of disposal of pollutants is：One is provided for the burner in the burner of gas-turbine unit
Cyclone.Compressed air is supplied to the combustion chamber of burner via burner, by a passage, and the cyclone is then
It is disposed in this passage.Cyclone is connected to gas-fuel feeder.Cyclone provides one for the air supplied
The individual tangential direction for making flow rotation, i.e. provide rotational flow air flowing to combustion chamber.Meanwhile gaseous fuel is by being arranged
In cyclone, multiple internal gas fuel channels and be introduced into air.Rotational flow air/gaseous fuel mixture is supplied to
To the combustion chamber of burner.The eddy flow of air/gas fuel mixture causes the air/gas fuel of height homogeneous to mix
Thing, this air/gas fuel mixture have lean gas gaseous fuel mixture form.Compared with rich gas gaseous fuel mixture, this
Kind lean gas fuel mixture burns under relatively low ignition temperature.Especially, the reduction of ignition temperature can cause nitrogen oxides to be arranged
The reduction put.
The Al of EP 1 867 925 disclose a kind of burner, and particularly a kind of gas turbine combustor, it includes at least one
Individual cyclone.Cyclone has at least one air entry apertures, at least one air outlet slit opening and at least one cyclone
Air duct, at least one air outlet slit opening are positioned in the downstream of air entry apertures, and at least one cyclone is empty
Gas passage extends at least one air outlet slit opening from least one air entry apertures, and by swirler air passage wall Lai
Delimit.Air passage wall includes：Multiple downstream wall sections of adjacent at least one air outlet slit opening；An and fuel injection system
System, the fuel injection system include the multiple fuel injection opening being disposed at least one swirler air passage wall, with
Just inject fuel into swirler air passage；At least tract of one of air passage wall is undulatory.
US2010/011770 Al disclose a kind of premixer for gas turbine combustion device, including an axial direction
Cyclone, the axial swirler include multiple steering stator blades and at least one fuel injection position, and multiple stator blades that turn to are by eddy flow
Speed is assigned by the axial air flow of premixer, at least one fuel injection position allow fuel to in premixer
Air stream mixing.Fuel injection position, which terminates at one, pit hole.It is this to there is pit hole to improve mixing efficiency, and enhance
Flash back (flashback)/flame stabilization (flameholding) resistance.
US2012/0111015A1 discloses a kind of burner with radial vortex type burner, wherein air/
Before fuel mixture burns in main burning device room, vortex is converted into by cyclone.Radial swirler includes quiet
One annular array of leaf, wherein forming air duct between these stator blades.Air duct, which is supplied into the substantially radially, upcountry to be arranged, with
Create vortex.Fuel mixes in these passages with air.
The content of the invention
The purpose of the present invention is the further reduction disposal of pollutants associated with the operation of gas-turbine unit, is particularly
Discharged nitrous oxides.
The purpose is realized by independent claims.Advantageous embodiment has been disclosed in the dependent claims, has passed through list
Solely consider these dependent claims or be combined these dependent claims each other, may relate to the one of the present invention
Individual aspect.
According to the present invention a kind of burner for gas-turbine unit in cyclone, including according to circle and
Circumferentially staggered arrangement, the multiple passage essentially radially to extend internally, each passage have a radially outer arrival end, one
The lateral surface and primary surface and top surface that the inner radial port of export, first and second essentially radially extend internally, in eddy flow
Device in use, fuel and air march to the port of export of these passages along these passages from the arrival end of these passages, with
Just eddy flow fuel/air mixture is created near the port of export, at least one surface of wherein at least one passage is included at least
One gaseous fuel hand-hole, wherein the surface with gaseous fuel hand-hole includes at least one counterbore, this is at least one heavy
Hole radially surrounds gas fuel orifice, and wherein gaseous fuel hand-hole is disposed in the base portion of the counterbore.
According to the present invention, gaseous fuel hand-hole is not the table that passage is placed directly as being conventionally known
Face, but be disposed in the counterbore on the surface, this counterbore limits a cavity in the surface.In this way,
A low velocity region is created at cavity (i.e. in counterbore), leaves what the gaseous fuel of gaseous fuel hand-hole sprayed to reduce
Momentum.Thus, entering the crossflow in cavity will mix with the local recirculation stream in the cavity, so as to strengthen air
With the mixing of gaseous fuel.This enhanced or adjusted mixing can bring less disposal of pollutants.In addition, it is this enhanced or
Adjusted mixing causes the number of focus to reduce, so as to further reduce disposal of pollutants.
Especially, surface of the compressed air along the passage for including counterbore has a cross-flow velocity, the lateral flow
Speed reduces the gaseous fuel flow for leaving gaseous fuel hand-hole by having the air of low pressure to recycle in the counterbore
Momentum.In this way, the aerodynamics for enabling gaseous fuel and air to mix improves.
By contrast, it is known that cyclone include multiple passages, wherein not being provided with the counterbore of the present invention, but for example
Gaseous fuel hand-hole is directly arranged at lateral surface, wherein the lateral surface by cyclone a stator blade a side
Limited to surface plane.So, the gaseous fuel flow from gaseous fuel hand-hole is not mixing what is effectively influenceed by this
In the case of, just the expansion area towards the combustion chamber of burner is advanced, and thus causes the mixing of gaseous fuel and air to have
It is more inefficient and/or be not easy controlled.
The cyclone of the present invention can have the one or more passages designed according to the present invention.Especially, cyclone
All passages can be designed accordingly.The cross section of at least one passage can be rectangle, square, circular, ellipse
Round or the like shape.
Two or more gaseous fuel hand-holes can be had according to the surface of at least one swirler passages of the present invention.
Each gaseous fuel hand-hole connects with least one internal gas feed path of cyclone.At least one surface can be flat
Smooth shape, inclined, facet shape, curved shape or the like shape.
Counterbore can be optimised in terms of itself mixed characteristic.For example, the size (its depth, diameter etc.) of counterbore can
To be changed, to adapt to the specifically used of cyclone, to optimize the mixed characteristic of cyclone.
Preferably, counterbore is rectangular shape, oval shape, elliptical shape or round-shaped.It is heavy with other shapes
Hole can also improve the mixed characteristic of counterbore.
Preferably, at least one surface includes：At least two gaseous fuel hand-holes and at least one counterbore, the counterbore footpath
To two gaseous fuel hand-holes are surrounded, wherein gaseous fuel hand-hole is disposed in the base portion of counterbore.According to this mode, one
The all gas injection hole on individual surface can be disposed in the shared single counterbore on the surface.
Preferably, wherein at least one surface includes：At least two gaseous fuel hand-holes and at least two counterbores, wherein
Each gaseous fuel hand-hole is radially surrounded by the counterbore of oneself and is disposed in the base portion of the counterbore.According to the embodiment,
More than one counterbore is disposed on a single surface of swirler passages, and each counterbore surrounds at least one gaseous fuel note
Enter hole.
Preferably, the surface for having at least one gaseous fuel hand-hole and at least one counterbore is a lateral surface.
The lateral surface can be limited by the lateral surface of the stator blade of cyclone.
Preferably, the surface for having at least one gaseous fuel hand-hole and at least one counterbore is primary surface.
Included according to the burner for gas-turbine unit of the present invention：It is at least one according in previous embodiment
Any one or its any combination of cyclone.Accordingly, it is above-mentioned to be also the advantages of relevant and burner of the invention with cyclone
The advantages of relevant.
Included according to the burner for gas-turbine unit of the present invention：According at least one burning of the present invention
Device.Accordingly, above-mentioned the advantages of with cyclone being also relevant with the burner of the present invention the advantages of relevant.
Brief description of the drawings
By reference to reference to following description of the accompanying drawing to the embodiment of the present invention, mentioned above the present invention attribute, other
Feature, advantage and realize that their mode will be apparent, and be better understood with the present invention itself, wherein
Fig. 1 illustrates the part of turbogenerator with section,
Fig. 2 shows the longitudinal cross-section of the burner of turbogenerator,
Fig. 3 shows the stereogram of the cyclone of the invention of burner,
Fig. 4 shows the perspective view of the embodiment details of the cyclone of the present invention,
Fig. 5 shows the sectional view of the cyclone shown in Fig. 4,
Fig. 6 shows the perspective view of the details of the further embodiment of the cyclone of the present invention,
Fig. 7 shows the perspective view of the details of the further embodiment of the cyclone of the present invention, and
Fig. 8 shows the perspective view of the details of the further embodiment of the cyclone of the present invention.
Embodiment
Fig. 1 is the schematic illustration of the general arrangement of gas-turbine unit 10, and gas-turbine unit 10 has entrance
12nd, compressor 14, burner system 16, turbine system 18, discharge line 20 and twin shaft arrangement 22,24.Gas turbine starts
Machine 10 is overall to be arranged around axis 26, and axis 26 is the pivot center for rotating building block.These arrangements 22,24 can have phase
Same or opposite rotation direction.
Combustion system 16 includes an annular array with multiple burner units (that is, burner 36), in figure only
A burner being shown in which.In one example, there are six burners 36 being evenly spaced apart around generator 10.
Turbine system 18 includes a high-pressure turbine 28, and the high-pressure turbine 28 arranges 22,24 first axle 22 by twin shaft
Compressor 14 is connected in a driving manner.Turbine system 18 also includes a low-pressure turbine 30, and the low-pressure turbine 30 is via double
Second axle 24 of axle arrangement, load (not shown) is connected in a driving manner.
Term " axial direction " is for axis 26.Term " upstream " and " downstream " are with respect to engine 10
Gas flowing general direction for, as shown in figure 1, generally from left to right.
Compressor 14 includes：The axially series of install in a conventional manner, stator stator blade and rotor movable vane.Stator is calmed the anger
Machine stator blade can be fixed, or can have geometry-variable, to be improved on downstream rotor or gas compressor moving blade
Air-flow.
Each turbine 28,30 includes：, should via the axially series of installed by rotor disk, stator stator blade and rotor movable vane
Rotor disk is arranged and operated in a conventional manner.Rotor assembly includes：The circular array of rotor movable vane or movable vane and rotor disk
Row.
In operation, air 32 is inhaled into engine 10 by entrance 12, and is entered in compressor 14, in compressor 14
The continuous level of place, stator blade and movable vane is compressed to air, is then delivered compressed air in combustion system 16.It is in burning
In the combustion chamber of system 16, the mixture of compressed air and fuel is ignited.Resulting hot working gas travels are imported into high pressure
Turbine 28, expand and drive high-pressure turbine 28, the high-pressure turbine 28 and then drive compressor 14 via first axle 22.Passing through
After high-pressure turbine 28, hot working gas travels are imported into low-pressure turbine 30, and the low-pressure turbine 30 drives via the second axle 24
Load.
Low-pressure turbine 30 can also be referred to as power turbine, and the second axle 24 can also be referred to as line shaft.Typically,
Load is the generator for generating, or the machine such as pump or technological process compressor.Other known loads can be with
Driven via low-pressure turbine 30.Fuel can be in the form of gaseous state and/or liquid.
The turbogenerator 10 that reference picture 1 shows and described only is the multiple engines or turbine that the present invention can be incorporated into that
An example.This engine can be gas engine or steam engine, and including applying Yu Haiyang, industry and boat
Single shaft, twin shaft and three shaft generators in empty field.
Fig. 2 shows a longitudinal cross-section of the burner 100 of gas-turbine unit.According to flow direction order, combustion
Burning device 100 includes：Burner 131, transition piece or precombustion chamber 103 and main chamber 104, the burner 131 have cyclone
Part 102 and the burner head part 101 for being attached to cyclone part 102.The diameter of main chamber 104 is more than precombustion chamber 103
Diameter.Main chamber 104 is connected to precombustion chamber 103 via dome part 110, and the dome part 110 includes dome plate
111 and along from precombustion chamber 103 to the directional divergence of main chamber 104.Generally, precombustion chamber 103 may be implemented as
A part towards combustion chamber 104 for burner 101 continues, a part towards burner 101 for combustion chamber 104 prolongs
A continuous or individual components between burner 101 and combustion chamber 104.Burner and combustion-chamber assembly are big around longitudinal axis S
Cause symmetrical.
Fuel conductor 105 is arranged for guiding gaseous state or liquid fuel to burner, and the gas or liquid fuel will
Mixed in cyclone 102 with leaked-in air.Then, fuel/towards primary combustion zone 109 guides air mixture 107, empty
Gas mixture 107 burns to form hot pressure exhaust at primary combustion zone 109, and the hot pressure exhaust is in arrow direction indication
108 flow upwardly to the turbine of gas-turbine unit.
It is shown in greater detail according to the exemplary cyclone 102 of the present invention in Fig. 3.It is quiet that cyclone 102 includes cyclone
The annular array of leaf 112, and in this example, 12 cyclones are disposed with cyclone stator blade support member 113 or plate
Stator blade 112.
Air duct 114 is formd between neighbouring swirler stator blade 112.These air ducts 114 are opened in air intake
Extend between mouth 116 and air outlet slit opening 118.These air ducts 114 by neighbouring swirler stator blade 112 relative side
120th, 122 and the surface 124 of cyclone stator blade plate 113 limit.Side 120,122 and the table of cyclone stator blade plate 113
Face forms air passage wall, and these air passage walls limit these air ducts 114.Another plate or another of burner
Part be located at cyclone stator blade, with supporting plate opposite end surface, and therefore realizing the restriction to air duct 114.
Side 120,122 is undulatory in their tract, to form mixing tab on cyclone stator blade 112
123.The ripple of relative side 120,122 is complementary, to cause additional rapids in the fuel/air mixture of flowing
Stream, and it is controlled make it that the fuel in the exit of air duct is placed.In other examples, cyclone stator blade 112
Downstream or trailing edge can be straight.
Fuel injection opening 126a, 126b are disposed in side 120.In addition, fuel injection opening 128 is arranged in eddy flow
In device support member 113.Fuel injection opening 126a, 126b, 128 are guide as known in the art and main fuel injector.
During the operation of burner, air is flowed in air duct 114 by air entry apertures 116.In air duct 114, lead to
Cross using fuel injection opening 126a, 126b, 128, and inject fuel into the air of flowing.Then, fuel/air mixture mixes
Thing leaves air duct 114 by air outlet slit opening 118, flows through the central opening 130 of cyclone stator blade array, goes forward side by side
Enter in precombustion chamber 103.Fuel/air mixture flows out from precombustion chamber 103, enters in the combustion zone 109 of main chamber 104, and
Burnt at combustion zone 109.As shown in Figure 4, two the first fuel notes are disposed with the side 120 of cyclone stator blade 112
Enter opening, to limit bottom and top first fuel injection opening 126a.The alternative location such as 126b of fuel injection opening
It is shown.
Fig. 4 shows the details of the embodiment of cyclone 1 of the invention used in the burner of gas-turbine unit
Perspective view.
Cyclone 102 includes multiple passages 114 essentially radially to extend internally, and these passages 114 are according to circular and circumferential
Alternately arrange, illustrate only one of passage 114 in Fig. 4.The air duct 114 extended radially inwardly can also be retouched
State for：It is arranged tangentially to the radius using the axis S of cyclone as the center of circle.Known cyclone is a radial swirler, and
These air ducts 114 of the cyclone are arranged such that their durection component in radial directions.Each passage 114 has
There are radially outer arrival end 116 and the inner radial port of export 118, as shown in Figure 3.Each passage 114 is limited by surface 3, in Fig. 4
In illustrate only one of surface 3.The surface 3 can be lateral or side surface 120,122, primary surface 124 or top surface.
Cyclone 1 in use, the arrival end of fuel and air along passage 114 from these passages 114 marches to these passages 114
The port of export, to generate eddy flow fuel/air mixture near the port of export.
Surface 3 includes two gaseous fuel hand-holes 5, the inside gas of the two gaseous fuel hand-holes 5 and cyclone 102
Fluid fuel feed path 4 connects.In addition, surface 3 includes counterbore 6, the counterbore 6 radially surrounds gaseous fuel hand-hole 5, and should
Counterbore 6 is rectangular shape, especially for box-shape.Gaseous fuel hand-hole 5 is disposed in the base portion 38 of counterbore 6.Therefore,
This shared counterbore 6 radially surrounds two gaseous fuel hand-holes 5.Arrow 7 indicates that gaseous fuel is supplied by gaseous fuel
The flowing of passage 4.
Fig. 5 shows the sectional view of the cyclone 102 shown in Fig. 3.Arrow 8 indicates the air flowed along surface 3.Spiral shape
The line 9 of shape indicates how air circulates in the counterbore 6, thus reduces gaseous fuel and jets away from gaseous fuel hand-hole 5
Momentum.It will be mixed into the crossflow in counterbore 6 with these local recirculation streams in counterbore 6, thereby enhance air
With the mixing of gaseous fuel.
What the embodiment of the counterbore 6 shown in Fig. 4 and Fig. 5 was generally rectangular, and with depth D of the surface below 3,
Perpendicular to the width W in the direction of the air flow 8 and length L substantially on the direction of air flow 8.Gaseous fuel hand-hole 5
With diameter d.In this embodiment, it is as follows relative to diameter d, preferred parameter：Length L is at least 4d, and width W is at least 3d,
And depth D is at least 2d.These known minimum relative sizes can provide advantages described below.
Fig. 6 shows the perspective view of the details of 102 another embodiment of cyclone of the present invention.In the embodiment and Fig. 4
The embodiment shown the difference is that only that counterbore 6 is oval shape.
The embodiment of the counterbore 6 shown in Fig. 6 is generally of ovoid shape, and wherein major axis dimension a is substantially in air flow 8
On direction.Minor axis dimension b is generally perpendicular to the direction of air flow 8 and major axis dimension a.Counterbore 6 has the depth on surface below 3
D.A diameter of d of gaseous fuel hand-hole 5.In this embodiment, it is as follows relative to diameter d, preferred parameter：Major axis dimension a is extremely
It is 4d less, minor axis dimension W is at least 3d, and depth D is at least 2d.These known minimum relative sizes can provide following institute
The advantages of stating.
Fig. 7 shows the perspective view of the details of another embodiment of the cyclone 102 of the present invention.The embodiment and Fig. 4
In the embodiment that shows the difference is that only that counterbore 6 is round-shaped.
In embodiment shown in Fig. 7, with round-shaped counterbore 6, counterbore 6 has the depth on surface below 3
D, and there is diameter L.Gaseous fuel hand-hole 5 has diameter d.In this embodiment, it is as follows relative to diameter d, preferred parameter：
Diameter L is at least 4d, and depth D is at least 2d.These known minimum relative sizes can provide advantages described below.
Fig. 8 shows the perspective view of the details of another embodiment of the cyclone 102 of the present invention.The embodiment and Fig. 4
Difference to embodiment illustrated in fig. 7 is：Surface 3 includes two gaseous fuel hand-holes 5 and two counterbores 6, wherein often
Individual gaseous fuel hand-hole 5 is radially surrounded and is disposed at the base portion 38 of the counterbore 6 by the counterbore 6 of oneself.
In the counterbore 6 of circle, rectangle or oval shape that each counterbore in two counterbores 6 can be described above
Any one.However, in this embodiment, it is as follows relative to diameter d, preferred parameter：Diameter L (or major axis dimension L) is at least
2d, and depth D is at least 2d.In addition, the spacing X between counterbore 6 is at least 2d.
In the embodiments described, these gaseous fuel hand-holes 5 are relative to the air flow side flowed along surface 3
It is arranged in a row to (being indicated with arrow 8).As an alternative, gaseous fuel hand-hole 5 can be relative to the stream
Dynamic direction and it is diagonally disposed.
Be related to the embodiment of above-mentioned counterbore and position of these counterbores on the side surface of cyclone stator blade 112 have it is multiple
Advantage, these advantages include：By improving the mixing of fuel and air and improving fuel placement, to reduce hot localised points, subtract
Few NOx emission.Because the fuel momentum in counterbore is reduced locally, so improving fuel and air across side surface flowing
Mixing.Therefore, compared with other fuel injection devices, local burnup-air ratio that these counterbores are provided is closer local
Chemical equivalent Hybrid analysis.
Although describe in detail and describe the present invention relevantly with preferred embodiment, it is noted that the present invention is not
It is limited to disclosed embodiment.Those skilled in the art can export guarantor of other changes without departing from the present invention from these embodiments
Protect scope.
Claims (11)
1. the cyclone (102) that one kind is used in the burner of gas-turbine unit (10),
The cyclone (102) has an axis (S), and an annular array including cyclone stator blade (112), described
Cyclone stator blade (112), which is arranged and at least partially defined out around the axis (S), multiple essentially radially inwardly to be prolonged
The passage (114) stretched, the multiple passage (114) essentially radially to extend internally are arranged to establishment and surround the axis (S)
, the vortex of fuel and air,
Each passage (114) has a radially outer arrival end (116), an inner radial port of export (118), first and the
Two lateral surfaces essentially radially to extend internally (3),
In the cyclone (102) in use, the arrival end row of fuel and air along the passage (114) from the passage
The port of export of the passage is proceeded to, to create eddy flow fuel/air mixture near the port of export,
Wherein at least one lateral surface (3) includes at least one gaseous fuel hand-hole (5), it is characterised in that has described
The surface (3) of gaseous fuel hand-hole (5) includes at least one counterbore (6), and at least one counterbore (6) radially surrounds
The gas fuel orifice (5).
2. cyclone (102) according to claim 1, wherein the counterbore (6) is rectangular shape, oval shape, ellipse
Shape is round-shaped.
3. cyclone (102) according to claim 1 or 2, wherein at least one surface (3) fire including at least two gases
Material hand-hole (5) and at least one counterbore (6), the counterbore (6) radially surround two gaseous fuel hand-holes (5), wherein institute
State base portion (38) place that gaseous fuel hand-hole (5) is disposed in the counterbore (6).
4. cyclone (102) according to claim 3, two of which counterbore (6) X spaced apart, and the distance X
At least 2d, wherein d are the diameters of gaseous fuel hand-hole (5).
5. cyclone (102) according to claim 4, wherein the counterbore (6) has size L and L is at least 2d, and
And the depth D of the counterbore (6) is at least 2d.
6. cyclone (102) according to claim 1 or 2, wherein at least one surface (3) fire including at least two gases
Expect hand-hole (5) and at least two counterbores (6), wherein each gaseous fuel hand-hole (5) by the gaseous fuel hand-hole (5) oneself
Oneself counterbore (6) radially surrounds and is disposed in base portion (38) place of this counterbore (6).
7. the cyclone (102) according to any one of claim 1 to 6, wherein being fired with least one gas
The surface (3) for expecting hand-hole (5) and at least one counterbore (6) is lateral surface (3).
8. the cyclone (102) according to any one of claim 1 to 6, wherein being fired with least one gas
The surface (3) for expecting hand-hole (5) and at least one counterbore (6) is primary surface (3).
9. the cyclone (102) according to any one of claim 1 to 8,
Wherein described counterbore (6) has：In the depth D of the surface (3) below, the air perpendicular to the leap surface (3)
Flow the width W and the length L substantially on the air flow (8) direction in (8) direction, the gaseous fuel hand-hole
(5) there is diameter d；
Wherein described length L is at least 4d, and/or the width W is at least 3d, and/or the depth D is at least 2d.
10. one kind is used for the burner (36) of gas-turbine unit (10),
It is characterized in that at least one cyclone (102) according to any one of preceding claims.
11. one kind is used for the burner of gas-turbine unit (10), including according to claim 10 at least one
Burner (36).
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP15162154.7A EP3076081A1 (en) | 2015-04-01 | 2015-04-01 | Swirler, burner and combustor for a gas turbine engine |
| EP15162154.7 | 2015-04-01 | ||
| PCT/EP2016/055802 WO2016156055A1 (en) | 2015-04-01 | 2016-03-17 | Swirler, burner and combustor for a gas turbine engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107466354A true CN107466354A (en) | 2017-12-12 |
Family
ID=52780484
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201680020973.9A Pending CN107466354A (en) | 2015-04-01 | 2016-03-17 | Cyclone, burner and burner for gas-turbine unit |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US20180045414A1 (en) |
| EP (2) | EP3076081A1 (en) |
| CN (1) | CN107466354A (en) |
| RU (1) | RU2690598C2 (en) |
| WO (1) | WO2016156055A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| TWI811711B (en) * | 2020-06-26 | 2023-08-11 | 日商三菱動力股份有限公司 | Fuel injector, combustor including the fuel injector, and gas turbine including the combustor |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10837643B2 (en) | 2018-08-06 | 2020-11-17 | General Electric Company | Mixer assembly for a combustor |
| GB2593123A (en) | 2019-06-25 | 2021-09-22 | Siemens Ag | Combustor for a gas turbine |
| GB2585025A (en) | 2019-06-25 | 2020-12-30 | Siemens Ag | Combustor for a gas turbine |
| US11280495B2 (en) * | 2020-03-04 | 2022-03-22 | General Electric Company | Gas turbine combustor fuel injector flow device including vanes |
| CN111911960A (en) * | 2020-08-11 | 2020-11-10 | 新奥能源动力科技（上海）有限公司 | Low nitrogen oxide emission combustion chamber for gas turbine and gas turbine |
| US11761632B2 (en) * | 2021-08-05 | 2023-09-19 | General Electric Company | Combustor swirler with vanes incorporating open area |
| CN115388428B (en) * | 2022-07-29 | 2023-06-16 | 北京航空航天大学 | Main combustion stage swirler, combustor nozzle and combustor with improved radial temperature distribution |
| US20240263785A1 (en) * | 2023-02-02 | 2024-08-08 | Pratt & Whitney Canada Corp. | Combined air swirler and fuel distributor |
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| WO2008049678A1 (en) * | 2006-10-25 | 2008-05-02 | Siemens Aktiengesellschaft | Burner, in particular for a gas turbine |
| EP1921376A1 (en) * | 2006-11-08 | 2008-05-14 | Siemens Aktiengesellschaft | Fuel injection system |
| EP1995521A1 (en) * | 2007-05-24 | 2008-11-26 | Siemens Aktiengesellschaft | Swirler vane |
| CN101466980A (en) * | 2006-06-12 | 2009-06-24 | 西门子公司 | Burner |
| CN101644436A (en) * | 2008-07-21 | 2010-02-10 | 通用电气公司 | Gas turbine premixer with cratered fuel injection sites |
| CN102414513A (en) * | 2009-05-05 | 2012-04-11 | 西门子公司 | Swirler, combustion chamber, and gas turbine with improved mixing |
| CN102538012A (en) * | 2010-11-08 | 2012-07-04 | 通用电气公司 | Self-oscillating fuel injection jets |
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|---|---|---|---|---|
| GB2337102A (en) * | 1998-05-09 | 1999-11-10 | Europ Gas Turbines Ltd | Gas-turbine engine combustor |
| EP2629008A1 (en) * | 2012-02-15 | 2013-08-21 | Siemens Aktiengesellschaft | Inclined fuel injection of fuel into a swirler slot |
| RU2511992C2 (en) * | 2012-06-27 | 2014-04-10 | Николай Борисович Болотин | Injector unit of gas-turbine engine combustion chamber |
-
2015
- 2015-04-01 EP EP15162154.7A patent/EP3076081A1/en not_active Withdrawn
-
2016
- 2016-03-17 WO PCT/EP2016/055802 patent/WO2016156055A1/en active Application Filing
- 2016-03-17 RU RU2017134597A patent/RU2690598C2/en not_active IP Right Cessation
- 2016-03-17 CN CN201680020973.9A patent/CN107466354A/en active Pending
- 2016-03-17 US US15/559,557 patent/US20180045414A1/en not_active Abandoned
- 2016-03-17 EP EP16710218.5A patent/EP3278029A1/en not_active Withdrawn
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101466980A (en) * | 2006-06-12 | 2009-06-24 | 西门子公司 | Burner |
| WO2008049678A1 (en) * | 2006-10-25 | 2008-05-02 | Siemens Aktiengesellschaft | Burner, in particular for a gas turbine |
| EP1921376A1 (en) * | 2006-11-08 | 2008-05-14 | Siemens Aktiengesellschaft | Fuel injection system |
| EP1995521A1 (en) * | 2007-05-24 | 2008-11-26 | Siemens Aktiengesellschaft | Swirler vane |
| CN101644436A (en) * | 2008-07-21 | 2010-02-10 | 通用电气公司 | Gas turbine premixer with cratered fuel injection sites |
| CN102414513A (en) * | 2009-05-05 | 2012-04-11 | 西门子公司 | Swirler, combustion chamber, and gas turbine with improved mixing |
| CN102538012A (en) * | 2010-11-08 | 2012-07-04 | 通用电气公司 | Self-oscillating fuel injection jets |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| TWI811711B (en) * | 2020-06-26 | 2023-08-11 | 日商三菱動力股份有限公司 | Fuel injector, combustor including the fuel injector, and gas turbine including the combustor |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2016156055A1 (en) | 2016-10-06 |
| EP3076081A1 (en) | 2016-10-05 |
| US20180045414A1 (en) | 2018-02-15 |
| RU2690598C2 (en) | 2019-06-04 |
| RU2017134597A3 (en) | 2019-04-05 |
| RU2017134597A (en) | 2019-04-05 |
| EP3278029A1 (en) | 2018-02-07 |
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Application publication date: 20171212 |