CN106662328A - Burner comprising a fluidic oscillator, for a gas turbine, and a gas turbine comprising at least one such burner - Google Patents
Burner comprising a fluidic oscillator, for a gas turbine, and a gas turbine comprising at least one such burner Download PDFInfo
- Publication number
- CN106662328A CN106662328A CN201580033859.5A CN201580033859A CN106662328A CN 106662328 A CN106662328 A CN 106662328A CN 201580033859 A CN201580033859 A CN 201580033859A CN 106662328 A CN106662328 A CN 106662328A
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- China
- Prior art keywords
- burner
- fuel
- room
- reciprocation
- fuel nozzle
- 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.)
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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
- F23R3/28—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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
- F23D11/36—Details, e.g. burner cooling means, noise reduction means
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- 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
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
- F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
- F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means
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- 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
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- 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
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gas Burners (AREA)
- Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
- Nozzles For Spraying Of Liquid Fuel (AREA)
- Pre-Mixing And Non-Premixing Gas Burner (AREA)
Abstract
The invention relates to a burner comprising a pre-mixing passage (68) that is delimited radially outwardly by a wall and, in operation, is used to mix fuel and air, a burner lance (72, 94) and a plurality of fuel injectors being arranged in said pre-mixing passage, and said injectors extending from the burner lance (72) in the direction of the wall and comprising fuel nozzles (80, 80a, 80b). During operation, the burner allows pollutant emissions and pressure pulsations to be reduced. According to the invention, said fuel supply arrangement comprises at least one fluidic oscillator (85) that has an interaction chamber (26), an inlet (28) to said interaction chamber being connected to a fuel channel (82) of the fuel supply arrangement, a first outlet channel (86) of said interaction chamber extending at least to a first fuel nozzle (80a) and a second outlet channel (88) extending at least to a second fuel nozzle (80b), said fluidic oscillator comprising one feedback line (38a, 38b) for each outlet channel, one end of the feedback line terminating into the respective outlet channel in the region downstream of the at least one fuel nozzle, and the other end thereof terminating into an inlet region (30) of said interaction chamber.
Description
Technical field
The present invention relates to a kind of combustor for a gas, the burner has the burner axis in central authorities and extremely
Partially surround the pre-mixing passages of the burner axis.Thus pre-mixing passages have following channel cross-section, described
Channel cross-section stretches around burner axis.The burner axis in central authorities are imaginary, endless lines.Channel cross-section example
If being annularly disposed or being arranged around the full circle of burner axis.In other words, pre-mixing passages and burner axle
Line coaxially stretches (identical pivot center).Ring or whole diameter of a circle can change along burner axis section.Especially
Ground, pre-mixing passages can be at least partially constituted as annular chamber passage (cross section is annular), the annular chamber passage energy
Enough transition are pre-mixing passages section, and the cross section of the pre-mixing passages section is configured to full circle.
Background technology
Pre-mixing passages are radially outward by wall gauge.Pre-mixing passages operationally can be flowed by compressor air.It is described
Pre-mixing passages are used for fuel combination and air, wherein being provided with burner spear or burner hub in pre-mixing passages
With multiple fuel injectors.The fuel injector extended towards wall from burner spear/hub and burned device at least in part
The fuel delivery means that spear/hub is surrounded are fluidly connected and with fuel nozzle.Fuel injector for example can not only be wrapped
Include the fuel nozzle for fuel gas and the fuel nozzle run for oil can be included.This is equally applicable to following burning
Device spear/hub, the burner spear/hub can also be configured to do not have fuel nozzle as an alternative.
Burner spear can also be referred to as within the scope of this invention burner hub.
Burner spear can be centrally disposed in pre-mixing passages.Burner spear can extend into from upstream
In pre-mixing passages so that passage is only partially radially-inwardly by burner spear gauge.In this case, it is pre-mixed logical
Road can for example have the cross section of wholecircle shape in burner spear downstream.But, burner spear also can be substantially
Extend up to the outlet of pre-mixing passages.
Used as alternative, pre-mixing passages can radially-inwardly at least in part by the combustion being centrally disposed in passage
Burner hub gauge, the burner hub has the surface of substantially truncated cone shell-like, and the surface is radially-inwardly from upstream up to hub
End regions to pre-mixing passages gauge.Pre-mixing passages can be the premixing that cross section is wholecircle shape in hub downstream transition
Region.Thus, pre-mixing passages have the channel cross-section of annular along hub, and the diameter of the channel cross-section can be along stream
Dynamic direction reduces.Especially, other pre-mixing passages can be provided with burner hub or central authorities are for example provided with
Igniter.
Pre-mixing passages can also be referred to as within the scope of this invention premixing duct.Fuel is sprayed into via fuel injector
Can mix in pre-mixing passages and with the compressor air stream of percolation pre-mixing passages setting up to pre-mixing passages
In the outlet in downstream so that premix burner is in its exit provides fuel/air mixture to be discharged to combustion chamber.Except this
Outside, fuel also can be sprayed into via the fuel nozzle being set directly in burner spear.
By means of burner of the invention, it is devoted to harmful substance burning as few as possible and avoids heat in burning
Acoustic instability.Especially, although premix burner is easier to operationally with low discharge of poisonous waste to this
Form pressure pulse.
The content of the invention
The purpose of the present invention is to propose a kind of burner for starting proposition type for gas turbine, by means of described
Burner realizes the reduction of discharge of poisonous waste when burner runs or realizes the reduction of pressure pulse.
According to the present invention, the purpose is realized in the following way in the burner for starting to propose type：Fuel is conveyed
Device includes at least one fluidic oscillator, and the fluid oscillator has reciprocation room, the wherein entrance of reciprocation room
It is connected on the fuel channel of fuel delivery means, and the first effuser road of reciprocation room at least extends up to the first combustion
Material nozzle, and the second effuser road at least extends up to the second fuel nozzle, and wherein fluidic oscillator is for each effuser
Road includes feedback pipe, and wherein feedback pipe is being passed through by means of its one end in the region at least one fuel nozzle downstream
It is corresponding to flow out in pipeline, and be passed through in the inflow region of reciprocation room by means of the other end.
At least the first fuel nozzle and at least the second fuel nozzle or first group and second group of fuel nozzle for example can
Enough be arranged on common fuel injector and for as far as possible uniform distribution of the fuel in pre-mixing passages along
Radial direction is arranged in a distributed manner.At least the first fuel nozzle for example also can be arranged in suction side and at least the second fuel
Fuel injector that nozzle is constituted in which can for example be arranged on swirl vane shape is on the pressure side gone up.First group and second group of fuel spray
Mouth for example also can be arranged on different fuel injectors.For example, it is arranged on putting in burning spear substantially opposite
Fuel injector in.
Fluidic oscillator is already as fluid control elements, it is known that the fluid control elements are without expensive valve
In the case of be also enough.Fluidic oscillator for example in the boundary layer for delivering air to loading end with avoid boundary layer take off
Fall.
Fluidic oscillator is run by means of fluid stream be applied on its entrance and under pressure.The fluid stream exists
Vibration is entered in reciprocation room so that at least one outlet of the room is alternately loaded with the jet for leaving.Thus, pulse
The fluid stream of formula is left from the flow pass of fluidic oscillator, wherein flow pass alternately ejecting fluid.From the prior art
The known fluidic oscillator with feedback pipe, the feedback pipe in order to stablize reciprocation room in vibration by reciprocation
The region of flowing out of room is connected with the inflow region of reciprocation room.The feedback pipe of prior art is being handed over respectively by means of its one end
The near exit of interaction room be passed through in reciprocation room and by means of its other end in outlet upstream in reciprocation room
Entrance is passed through in reciprocation room.If corresponding outlet is loaded with fluid stream in oscillatory operation, then this causes instead
The pressure of the raising of the end of feedback pipeline, the pressure continues to be directed in following region by the pipeline on inflow region,
At the region, stream is abutted on the side wall of reciprocation room just.Thus, the stream of vibration tends to from side wall depart from.This
Cause reciprocation room flow out between region and inflow region it is pressure ratio, stable feedback is carried out to vibration.
It is currently proposed according to the present invention：Feedback pipe is unlike the stream that can be passed through reciprocation room in the prior art
In going out region, but it is passed through positioned at the area of at least one fuel nozzle or fuel nozzle group downstream in each outflow pipeline
In domain, the flow pass extends to the fuel nozzle group.This is according to present invention realization：Pressure ratio in pre-mixing passages exists
Can flow into together in feedback signal in the pre-mixing passages region of fuel nozzle upstream.Flow pass can be in fuel
Nozzle or fuel nozzle group downstream have end pieces, and feedback channel is passed through in the end pieces.
If the static pressure in pre-mixing passages is higher in the region of fuel nozzle group, then less fuel flowing
It is relatively low through flowing out pipeline and flowing out the dynamic pressure in pipeline.Thus, in the structure of the invention of feedback pipe
Into in scheme, feedback signal is lower, and the feelings contrary with the pressure ratio in the fuel nozzle upstream positioned at effuser road
Compare in pre-mixing passages under condition, fuel flows longerly in pipeline is flowed out.If the static pressure in premixing duct
It is relatively low in the region of fuel nozzle group, then more The fuel streams when loading to the outlet belonging to reciprocation room
It is higher to move through affiliated flowing out pipeline and flow out the dynamic pressure in pipeline.Because positioned at least the one of outflow pipeline
The affiliated feedback pipe in individual fuel nozzle downstream is passed through in outflow pipeline, so anti-in being passed through the end regions for flowing out pipeline
Pressure in feedback pipeline is side wall of the higher and affiliated fuel spray quickly from the inflow region of reciprocation room
Place departs from and to next outlet loading fuel.Thus, vibration of the fuel spray in reciprocation room is for longer periods to such as
Lower effuser road loads fuel, and at least one fuel nozzle of the outflow pipeline is passed through in the following region of pre-mixing passages,
There is higher pressure in this region.Thus balanced following effect：Generally less fuel leaves from fuel nozzle, described
Fuel nozzle is passed through in the higher region of channel pressure, or more fuel are injected into the low region of pressure.By this
It is kind balanced, fuel concentration evenly can be produced in pre-mixing passages according to the present invention.Thus, the penetrating of fuel is by extremely
, from main regulation, the control without adding sets for few two fuel nozzle groups being connected on fluidic oscillator or fuel nozzle
It is standby.The distribution evenly of the produced fuel concentration in pre-mixing passages causes the reduction of discharge of poisonous waste.Pass through
Spray into the fuel of fluctuation on place in time, the fuel and the compressed air for flowing through sprayed from fuel nozzle group is caused in addition
Good mixing.According to the present invention, because the fuel of the fluctuation caused because of fluidic oscillator is sprayed into, also cause prolonging for burner
Late time graph is broadening, thus reduces the reciprocation of burner and flame and reduction evokes thermoacoustic vibration.
In order to illustrate that term thermoacoustic is vibrated and time delay, it is noted that：Heat can be caused in a combustion chamber to discharge
In acoustic vibration and fluctuation reciprocation.When in such as lower frequency, these acoustic vibrations and fluctuation can mutually be promoted, described
Frequency is consistent with the so-called natural mode of gas turbine.The size and configuration phase of these natural modes and corresponding gas turbine
Close.This thermoacoustic vibration can cause the significant damage at component in gas turbine operation and force equipment to cut off.
In order to avoid exciting for thermoacoustic vibration, the operationally set time delay curve of burner can to the greatest extent may be used
Can be wide, wherein time delay is the following time, and the time is needed for the fluid up to arrival flame left from fuel nozzle
The time wanted.
Burner by fluidic oscillator supply fuel fuel nozzle or fuel nozzle group due to the outlet in nozzle
Place not only in time but also on place pulsed fuel spray and there is the fuel concentration in the compressed air for flowing through
The fluctuation of curve, this broadening time delay curve due to burner and improve thermoacoustic stability again --- it is for example relative
In the burner with traditional pressure eddy current spraying nozzle or full jet nozzle.The frequency of the penetrating of the pulsed of fuel for example can
It is enough to be arranged by the size of reciprocation room.Burner can include multiple fluidic oscillators, the fluidic oscillator difference
Pipeline supply fuel is flowed out at least two, the outflow pipeline has respectively at least one fuel nozzle or fuel nozzle group.
Known different types of fluidic oscillator, the fluidic oscillator is different in terms of its construction.The present invention does not limit to
In the particular type of these fluidic oscillators.All these types all have something in common, i.e., these types all have interaction
Application chamber, the fluid beam under pressure is entered into the reciprocation room through entrance.Beam is periodically abutted in
On the different side wall of reciprocation room or sidewall areas, enabling the referred to as reciprocation of the side wall of beam and room, its
In evoke the vibration of beam so that beam periodically flows through room so as to the cycle in region is flowed out on different paths
Property ground leave the reciprocation room or leave reciprocation in different directions through the different outlet of reciprocation room
The central outlets of room.Thus beam at least periodically abuts in two opposite sidewall areas or departs from again, this
Caused due to the delay flowed.
The operation principle of fluidic oscillator is prior art so that fluidic oscillator here is only simply illustrated.In the accompanying drawings
Some type of fluidic oscillator is shown in addition.The present invention is uncorrelated to the type for being used of fluidic oscillator.The present invention is excellent
With following fluidic oscillator as starting point, the fluidic oscillator is due to the side of the diverging in the inflow region of reciprocation room for choosing
Wall and cause to evoke the vibration of the beam of inflow.Especially, the present invention is preferably with the substantially rotational symmetric of reciprocation room
Composition scheme is starting point, and the reciprocation room is with the end in room around the entrance of pivot center and with least one
The outflow region of the individual outlet for arranging oppositely.In order to evoke vibration, in this kind of reciprocation room, reciprocation room is at least
Widen towards outflow regional diffusion device shape in the inflow region of room.The operation principle of feedback pipe has been described above explaining
State.
The favourable design of the present invention below with illustrate in dependent claims, its feature can apply individually
Or the application in the way of arbitrary combination each other.
Can advantageously propose：First effuser road extends up to first group of fuel nozzle and the second effuser road extends
Until second group of fuel nozzle, wherein feedback pipe are passed through stream in the region positioned at the downstream of the fuel nozzle of respective sets respectively
In going out pipeline.
First group and second group of fuel nozzle or the first fuel nozzle and the second fuel nozzle for example can be arranged on jointly
Fuel injector in.The fuel injector for example can be the swirl vane of vortex generator.Because in pre-mixing passages
In blade suction side and on the pressure side on there are different pressure, so the first fuel nozzle or first group of fuel nozzle energy
Enough it is arranged in the suction side of swirl vane and second group of fuel nozzle or fuel nozzle group can be arranged on swirl vane
On the pressure side go up.According to the present invention, the fuel thus, it is possible to spray into approximate equivalent on the both sides of blade.
Also can be considered as advantageously, feedback pipe is at least one fuel nozzle downstream connection to outflow pipeline.
Flowing out pipeline and feedback pipe here can have different diameters.
Also can be considered as advantageously, at least the first fuel nozzle and at least the second fuel nozzle is arranged on different fuel
In injector.
Especially, can be considered as advantageously, the two fuel injectors are substantially opposite to be arranged on burner lance with putting
On shape part.
Thus, the fuel concentration in pre-mixing passages can be balanced against others at least the two opposite regions, although
Pressure ratio in this region is different.
Also can be considered as advantageously, at least two fuel nozzles or at least two fuel nozzle groups are arranged on common combustion
In material ejector and it is radially arranged difference in pre-mixing passages so that although in the close burner of pre-mixing passages
Spear is different with the pressure ratio in the region away from fuel spear but fuel concentration can be balanced along radial direction.Fluid
Oscillator can be arranged in burner hub or also can arrange within the fuel injector.
Advantageously, it is furthermore possible to propose：Burner include from fluidic oscillator connection, in different fuel injectors
In the fuel nozzle more than two groups.
This realizes the equilibrium of the fuel concentration in pre-mixing passages in different fuel injector downstreams.
Another favourable design of the present invention can be proposed：Different fuel injectors are arranged circumferentially at burner
Flow out in spear and accordingly pipeline to be arranged circumferentially on reciprocation room.
But can also be considered as advantageously, at least one fuel injector includes matrix, be surrounded by fuel injector
Fuel nozzle is arranged on the matrix, wherein the swirl vane of matrix especially vortex generator.
Furthermore it is possible to advantageously propose：Reciprocation room is in one end thereof including entrance in opposite end
It is upper to include flowing out region and being extended up to from the entrance of room by side wall or sidewall areas gauge, the side wall or sidewall areas
The outflow region of outlet is surrounded, side wall that wherein at least two is arranged oppositely or sidewall areas are at least in inflow region
Towards outlet diverging.
Of the invention this of vibration of the fuel spray entered into reciprocation room through entrance under pressure sets
Meter scheme is evoked by the way that alternately beam is applied in the sidewall areas for divergently constituting.Make in interaction of the invention
With in room, evoking for vibration is based on the delay in flow caused by the side wall/sidewall areas for dissipating in inflow region.
Also can be considered as advantageously, at least two side walls for arranging oppositely are in the inflow region of reciprocation room
To dissipate towards outlet into the angle more than 7.5 degree relative to the inflow direction of the entrance of reciprocation room.
The unlimited angle for being suitable for evoking vibration of reciprocation room is known from the prior art.Relative to inflow direction into extremely
Few 7.5 degree angle has proven to be especially advantageous.
Can advantageously propose：Reciprocation room is substantially symmetrically constituted, and wherein reciprocation room is at least in stream
Enter in region and divergently widened towards outlet.
By the rotational symmetric construction of fluidic oscillator, obtain：To what is started in the outflow region of reciprocation room
Flow out pipeline and circumferentially load fuel.
Fluidic oscillator for example can be centrally disposed in burner spear and to rotationally in an orbiting manner
At least one outflow pipeline difference of the fuel injector supply fuel being arranged in burner spear, wherein fluidic oscillator
Extend to each one group of fuel nozzle of fuel injector.Circular fuel injector can jointly include two fuel-grades.It is right
For each level, unique fluidic oscillator is provided with.
It is another object of the present invention to, a kind of burner apparatus with multiple burners are proposed,
- wherein main burner is arranged in the circle that one or more are arranged concentrically with each other, by means of the circle, in burning
The reduction that discharge of poisonous waste is realized during device plant running or the reduction for realizing pressure pulse.
In this regard, at least one burner is constituted according to any one of claim 1 to 11.
What burner was for example capable of burner apparatus is the igniter that middle ground is arranged.According to another embodiment, as attached
Plus scheme or alternative, the main burner of burner apparatus also can constitute according to any one of claim 1 to 11.
Even if burner of the invention or burner apparatus of the invention are especially in operation at part load
Realize especially stable burning.
It is another object of the present invention to, a kind of combustion chamber for gas turbine and a kind of gas turbine are proposed, by means of
The combustion chamber and the gas turbine, operationally realize the reduction of discharge of poisonous waste or realize pressure arteries and veins in combustion chamber
The reduction of punching.
In this regard, combustion chamber includes at least one burner and combustion gas according to any one of claim 1 to 12
Turbine includes at least one combustion chamber according to claim 13.
Description of the drawings
Other suitable designs and advantage of the present invention are that the diagram of refer to the attached drawing is retouched to embodiments of the invention
The object stated, wherein identical reference have represented the component of phase same-action.
It is shown in which：
Fig. 1 schematically shows the sectional side elevation of the gas turbine of prior art,
The sectional side elevation that Fig. 2,3 schematically show two kinds of fluidic oscillator according to prior art,
Fig. 4 schematically illustrates a part for the combustion chamber 10 of prior art in sectional side elevation,
Fig. 5 is shown schematically in the sectional side elevation of the main burner of the burner apparatus illustrated in Fig. 4,
Fig. 6 schematically shows the sectional side elevation of the burner of the invention of first embodiment of the invention, with
And
Fig. 7 schematically shows the sectional side elevation of burner of the invention according to the second embodiment of the present invention.
Specific embodiment
Fig. 1 illustrates the sectional view of the gas turbine 1 according to prior art in schematic simplification view.Gas turbine 1
Have in its inside and rotor 3 and the axle 4 installed is rotated around pivot center 2, the rotor is also referred to as turbine rotation part.Suction
Housing 6, compressor 8, the combustion system 9 with multiple combustion chambers 10, turbine 14 and waste gas housing 15 are arranged successively along rotor 3
Row, the combustion chamber includes that respectively the burner apparatus with burner 11, (unshowned) fuel for burner are supplied
System and housing 12.Combustion chamber 10 for example can be toroidal combustion chamber.But gas turbine can also include tubular type combustion chamber, institute
State tubular type combustion chamber to be for example annularly disposed at turbine inlet.
Combustion system 9 is communicated with for example annular hot gas duct.In this place, multiple stage of turbines being sequentially connected form turbine
14.Each stage of turbine is formed by blade ring.Observe along the flow direction of working media, in the row formed by guide vane 17
Hot channel in arrange the row formed by rotor blade 18.The here of guide vane 17 is fixed on the inner housing of stator 19, and
One row's rotor blade 18 is for example placed on rotor 3 by means of the turbine disk.(unshowned) generator is for example coupled in rotor 3
On.
During gas turbine operation, aspirated and compressed air through suction housing 6 by compressor 8.In the whirlpool of compressor 8
The compressor air L provided on the end of wheel side " is guided along burner collection chamber 7 towards combustion system 9, and in this place
Import in the region of burner apparatus in burner 11, and mix with fuel in the burner and/or in burner
Fuel is rich in 11 outflow region.Fuel delivery system here supplies fuel to burner.Mixture or compressor air and
Fuel is imported in combustion chamber 10 from burner 11, and is burnt in the combustion zone inside the burning chamber shell 12 of combustion chamber,
To form the working air current of heat.Working air current is from this along hot gas duct in guide vane 17 and the by-pass flow of rotor blade 18.
Working air current is reduced pressure on rotor blade 18 in the way of transmission pulse so that rotor blade 18 drives rotor 3 and the rotor
Driving is coupled to generator (not shown) thereon.
Fig. 2 illustrates the sectional side elevation of the fluidic oscillator of the first kind according to prior art.
Oscillator 24a includes reciprocation room 26, and the reciprocation room has entrance 28, and the entrance has inflow area
Domain 30, and the reciprocation room has the outflow region 32 of opposite setting, and the outflow region has first outlet
34 and second outlet 36.For the feedback pipe 38 that each outlet arranges relatively thin, the feedback pipe is by inflow region and flows out
Region connects.
Sidewall areas 40 are towards outlet diverging so that reciprocation room 26 has the vertical section of triangle.Oscillator 24a is not
It is symmetrically to construct, and is perpendicular to figure layer and there is constant vertical section.
Fig. 3 illustrates the vertical section of the fluidic oscillator 24b of the Second Type according to prior art.Oscillator 24b is equally not
It is symmetrically to construct, and is perpendicular to figure layer and there is constant vertical section.Inside center of the entrance 28 in guiding mechanism 42
Be arranged in reciprocation room 26 so that the jet for occurring under stress is pro directed at opposite side wall 44.Jet is left
Right alternately flow direction flows out region 32 and here alternately provides mouth 34 and 36 plus carrying object at guiding mechanism so that jet
Alternately pass through one outlet and another outlet is left with such as lower frequency from room, the frequency is big by reciprocation room 26
Little determination.
Fig. 4 schematically shows a part for the combustion chamber 10 of prior art, cephalic par of the combustion chamber in combustion chamber
Place has burner apparatus 48.Combustion chamber includes chamber wall, and the chamber wall has the He of flame tube 50 for including combustion zone
The transition piece 52 being connected on flame tube, the transition piece extends up to the turbine inlet of gas turbine.In order that operationally
The thermoacoustic vibration decay of appearance, resonator 54 is arranged on chamber wall on the height of flame.Burner apparatus 48 include
The igniter 56 in central authorities, the igniter has the igniter spear 58 and igniter pre-mixing passages 60 in central authorities.Igniter
56 include the starting taper 62 conically widened along flow direction.Igniter of the circular main burner 64 around central authorities is arranged.It is main
Burner 64 has respectively burner axis 66 and the pre-mixing passages 68 being coaxially disposed with burner axis, wherein being pre-mixed
Passage 68 radially outward by the gauge of wall 70, and operationally can be by compressor air L " percolation, and for fuel combination and
Air L ", wherein being provided with the burner spear 72 and multiple fuel injectors in central authorities, the combustion in pre-mixing passages 68
Material ejector extends from burner spear towards wall 70, and with the fuel delivery means stream surrounded by burner spear 72
Body connects, and with fuel nozzle.Fuel injector is configured to the swirl vane of vortex generator 74, and wherein fuel nozzle sets
Put on swirl vane.
Fig. 5 schematically shows the sectional side elevation of the main burner 64 of the burner apparatus of Fig. 4.Burner 64 has central authorities
Burner axis 66 and at least partly surround the pre-mixing passages 68 of burner axis, wherein pre-mixing passages radially outward by
The gauge of wall 70 and operationally can be by compressor air L " flow and for fuel combination and air.In pre-mixing passages 68
In be provided with central authorities burner spear 72 and multiple fuel injectors 79.Fuel injector 79 includes being arranged on premix respectively
The matrix 71 in passage is closed, described matrix is configured to the swirl vane 76 of vortex generator 74.Fuel injector 79 includes fuel
Nozzle 80, the fuel nozzle is opened on the surface of swirl vane 76 towards pre-mixing passages 68.Fuel nozzle 80 is for quilt
Supply fuel and fluidly connect with fuel delivery means 73.Fuel delivery means 73 are included in the combustion stretched in burner spear
Pipe material 82 and fuel tube 78, the fuel tube extends up to corresponding fuel nozzle in swirl vane 76
80。
First embodiment of the invention, Fig. 6 schematically shows the sectional side elevation of burner of the invention 84.With
Differently, fuel delivery means 73 have at least one fluidic oscillator 85 to the burner 64 of the prior art that figure 5 illustrates,
The entrance 28 that the fluidic oscillator has reciprocation room 26, wherein reciprocation room is connected to the combustion of fuel delivery means 73
On pipe material 82.Reciprocation room 26 has outflow region 32, the outflow region and the phase of inflow region 30 with entrance 28
It is opposed and with two outlet 34 and 36.First effuser road 86 is extended up in the first fuel injector 79a from outlet 34
First group of fuel nozzle 80a.Second effuser road 88 extends up to the fuel injector 79b in opposite setting from outlet 36
In second group of fuel nozzle 80b, wherein fluidic oscillator 85 for each outflow pipeline include feedback pipe 38a, 38b, its
Middle feedback pipe 38a, 38b are passed through corresponding stream by its one end in fuel nozzle 80a, 80b downstreams surrounded by outflow pipeline
In going out pipeline 86,88, and it is passed through in the inflow region 30 of reciprocation room 26 by its other end.
If the entrance 28 of fluidic oscillator 85 is used by means of fuel channel 82 when burner runs and is loaded with pressure
The fuel stream is supplied, then because the side wall dissipated in inflow region 30 promotes The fuel stream oscillatory type ground in reciprocation room 26
Abut on the side wall of room so that The fuel stream alternately provides the supply fuel of mouth 34 and 36.Fuel is through outflow pipeline 86,88
It flow to corresponding fuel nozzle group so that the The fuel stream of pulsed is injected in pre-mixing passages 68 from the fuel nozzle group.
Fuel nozzle for example can be full jet nozzle or pressure eddy current spraying nozzle.Feedback pipe 38a is in fuel nozzle 80a downstream connections
Inflow region 30 of the pressure feedback on the end flowed out on pipeline 86 and will be present in outflow pipeline to reciprocation room
On.Be present in pressure here on the end for flowing out pipeline by pre-mixing passages located immediately at fuel nozzle 80a upstreams
Pressure influence so that in this region pressure height in the case of with pressure it is low in this case compared with, fuel supply quilt
More slowly it is switched on second group of fuel nozzle 80b.Thus, this group of nozzle injects fuel into the pressure for flowing through with the longer time
In contracting machine air stream so that even if in the case where the exit of burner is different in pressure ratio the two of burner spear 72
Fuel concentration evenly is also provided with side, wherein in the nozzle upstream, the pressure in pre-mixing passages is higher.This is supported
Disappear pressure pulse evokes and reduces the generation of discharge of poisonous waste.
Fig. 7 schematically shows according to the second embodiment of the present invention burner of the invention 90.Burner 90 has
The pre-mixing passages 92 and middle ground of the annular cavity-like that the burner axis 66 and burner axis 66 for having central authorities stretch with one heart
The burner hub 94 of setting, the pre-mixing passages are outwards by the gauge of wall 70.Diagonal grid is provided with pre-mixing passages 92
96, the diagonal grid is the compressor air L flowed in pre-mixing passages " apply vortex.Diagonal grid is surrounded by multiple
The fuel injector 98 that hub is arranged is constituted, and the matrix of the fuel injector is the compressor air L for flowing through " apply to point to passage
The velocity component of ring circumferential direction, described matrix is arranged in pre-mixing passages.Stretching in burner hub 94 has at least one combustion
Pipe material 82, the fuel channel can circumferentially be constituted and via the combustion of fuel injector 98 in the cone of burner hub
Material nozzle 80,80a, 80b is fueled.According to the embodiment, at least two outflows of (unshowned) fluidic oscillator
Pipeline is extended at least one fuel injector 100.Fluidic oscillator is fluidly disposed in fuel channel 82 and at least one
Between first group and second group of fuel nozzle, described first group and second group of fuel nozzle Jing in fuel injector 100
Pipeline is flowed out by (unshowned) first and second of fluidic oscillator to be fueled.First group of fuel nozzle is represented with 80a
And it is arranged on fuel injector in hub side, wherein second group of fuel nozzle is represented and diametrically more externally with 80b
Inject fuel into pre-mixing passages on fuel injector.The embodiment is realized：Even if in the outside of pre-mixing passages
In hub side region flowing velocity or pressure ratio difference in the case of, also pre-mixing passages exit obtain in radial direction
Upper uniform fuel concentration.
Claims (14)
1. (56,64,84), the burner has the burner axis in central authorities and at least partly surrounds described a kind of burner
Burner axis pre-mixing passages (60,68,92), wherein the pre-mixing passages radially outward by wall (70) gauge and
Can be flowed by compressor air during operation and for fuel and air to be mixed, wherein arranging in the pre-mixing passages
Have burner spear (58,72,94) or burner hub and multiple fuel injectors (79,79a, 79b, 98, it is 100), described
Fuel injector extends towards the wall (70) from the burner spear or burner hub and fills with conveying with fuel
The fuel nozzle (80,80a, 80b) that (73) fluidly connect is put, the fuel delivery means are at least in part by the burner lance
Shape part or burner hub are surrounded,
Characterized in that,
Including at least one fluidic oscillator, (24a, 24b, 85), the fluidic oscillator has the fuel delivery means (73)
Reciprocation room (26), wherein the entrance (28) of the reciprocation room is connected to the fuel channel of the fuel delivery means
(82) on, and the first effuser road (86) of the reciprocation room at least extend to the first fuel nozzle (80a) and second
Flow out pipeline (88) and at least extend to the second fuel nozzle (80b), wherein the fluidic oscillator is for each outflow pipeline
(86,88) including feedback pipe (38,38a, 38b), wherein the feedback pipe is being located at described at least one by its one end
During the corresponding outflow pipeline is passed through in the region in fuel nozzle downstream, and the reciprocation room is passed through by the other end
(26) in inflow region (30).
2. burner according to claim 1 (56,64,84),
Characterized in that,
The first effuser road (86) extends up to first group of fuel nozzle (80a), and the second effuser road (88) extends
Until second group of fuel nozzle (80b), wherein the feedback pipe (38a, 38b) is respectively in the fuel nozzle positioned at respective sets
During the corresponding outflow pipeline is passed through in the region in the downstream of (80,80a, 80b).
3. burner according to claim 1 and 2,
Characterized in that,
The feedback pipe (38a, 38b) at least one fuel nozzle (80a, 80b) downstream connection to the outflow pipeline
(86,88) on.
4. burner according to any one of claim 1 to 3,
Characterized in that,
At least described first fuel nozzle and at least described second fuel nozzle be arranged on different fuel injector (79a,
In 79b).
5. the burner according to the next item up claim,
Characterized in that,
The two fuel injectors (79a, 79b) are substantially opposite to be arranged on the burner spear (72) with putting.
6. the burner according to claim 4 or 5,
Characterized in that,
The burner different fuel injectors (79a, 79b) include it is being connected with the fluidic oscillator, more than two
The fuel nozzle (80a, 80b) of group.
7. burner according to claim 6,
Characterized in that,
The different fuel injectors (79a, 79b) is arranged circumferentially on the burner spear (72), and affiliated
The outflow pipeline (86,88) be arranged circumferentially on the reciprocation room (26).
8. the burner according to any one of the claims,
Characterized in that,
Fuel injector described at least one (79) includes matrix (71), is provided with the matrix by the fuel injector
The fuel nozzle (80) for surrounding, the wherein swirl vane (76) of described matrix especially vortex generator (74).
9. the burner according to any one of the claims,
Characterized in that,
The reciprocation room includes on one end entrance (28) and includes flowing out region on its opposite one end
(32) and by side wall or sidewall areas (40) gauge, the side wall or sidewall areas extend up to from the entrance of the room
Including the outlet (34, the outflow region (32) 36), side wall or sidewall region that wherein at least two is arranged oppositely
Domain (40) is at least towards the outflow regional divergence in the inflow region (30).
10. the burner according to any one of the claims,
Characterized in that,
At least two sidewall areas for arranging oppositely (40) are in the inflow region of the reciprocation room with relative
Regional divergence is flowed out in the inflow direction of the entrance of the reciprocation room into the angle direction more than 7.5 degree.
11. burners according to any one of the claims,
Characterized in that,
The reciprocation room is substantially symmetrically constituted, wherein the reciprocation room (26) is at least in the inflow area
Widen towards the outflow regional diffusion device formula in domain.
A kind of 12. burner apparatus (48), it has multiple burners,
- wherein main burner (64) is arranged in the circle that one or more are arranged concentrically with each other,
Characterized in that,
At least one burner (56,64) constituted according to any one of claim 1 to 11.
A kind of 13. combustion chambers (10) for gas turbine (1),
Characterized in that,
The combustion chamber include at least one according to the burner of any one of claim 1 to 12 (11,48,56,64).
A kind of 14. gas turbines, it has at least one combustion chamber,
Characterized in that,
The combustion chamber is constituted according to claim 13.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE102014218288.3 | 2014-09-12 | ||
| DE102014218288 | 2014-09-12 | ||
| PCT/EP2015/070355 WO2016037966A1 (en) | 2014-09-12 | 2015-09-07 | Burner comprising a fluidic oscillator, for a gas turbine, and a gas turbine comprising at least one such burner |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106662328A true CN106662328A (en) | 2017-05-10 |
Family
ID=54140423
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201580033859.5A Pending CN106662328A (en) | 2014-09-12 | 2015-09-07 | Burner comprising a fluidic oscillator, for a gas turbine, and a gas turbine comprising at least one such burner |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US20170254541A1 (en) |
| EP (1) | EP3134677B1 (en) |
| JP (1) | JP6321282B2 (en) |
| CN (1) | CN106662328A (en) |
| WO (1) | WO2016037966A1 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110449309A (en) * | 2019-08-16 | 2019-11-15 | 中国航空发动机研究院 | A kind of fluidic oscillator array and its frequency synchronization method |
| WO2022237223A1 (en) * | 2021-05-13 | 2022-11-17 | 中国航空发动机研究院 | Afterburner structure based on self-excited sweep oscillating fuel nozzle |
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|---|---|---|---|---|
| EP3062019B1 (en) * | 2015-02-27 | 2018-11-21 | Ansaldo Energia Switzerland AG | Method and device for flame stabilization in a burner system of a stationary combustion engine |
| US10386074B2 (en) * | 2016-12-09 | 2019-08-20 | Solar Turbines Incorporated | Injector head with a resonator for a gas turbine engine |
| US11156162B2 (en) * | 2018-05-23 | 2021-10-26 | General Electric Company | Fluid manifold damper for gas turbine engine |
| KR102142140B1 (en) * | 2018-09-17 | 2020-08-06 | 두산중공업 주식회사 | Fuel nozzle, combustor and gas turbine having the same |
| US11174792B2 (en) | 2019-05-21 | 2021-11-16 | General Electric Company | System and method for high frequency acoustic dampers with baffles |
| US11156164B2 (en) | 2019-05-21 | 2021-10-26 | General Electric Company | System and method for high frequency accoustic dampers with caps |
| CN114856827B (en) * | 2022-05-12 | 2023-06-30 | 中国航发四川燃气涡轮研究院 | Detachable fan-shaped nozzle capable of adjusting nozzle position and spraying direction |
| KR20240003230A (en) * | 2022-06-30 | 2024-01-08 | 두산에너빌리티 주식회사 | Jet nozzle, combustor and gas turbine including same |
| CN117960415A (en) * | 2024-03-28 | 2024-05-03 | 箭牌家居集团股份有限公司 | Oscillator unit and water outlet device |
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- 2015-09-07 JP JP2017504403A patent/JP6321282B2/en active Active
- 2015-09-07 EP EP15763533.5A patent/EP3134677B1/en not_active Not-in-force
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| CN110449309B (en) * | 2019-08-16 | 2020-06-26 | 中国航空发动机研究院 | Fluid oscillator array and frequency synchronization method thereof |
| WO2022237223A1 (en) * | 2021-05-13 | 2022-11-17 | 中国航空发动机研究院 | Afterburner structure based on self-excited sweep oscillating fuel nozzle |
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Also Published As
| Publication number | Publication date |
|---|---|
| EP3134677A1 (en) | 2017-03-01 |
| EP3134677B1 (en) | 2018-03-07 |
| JP6321282B2 (en) | 2018-05-09 |
| WO2016037966A1 (en) | 2016-03-17 |
| JP2017527765A (en) | 2017-09-21 |
| US20170254541A1 (en) | 2017-09-07 |
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