CN1878986B - Device for stabilizing combustion in gas turbine engines - Google Patents
Device for stabilizing combustion in gas turbine engines Download PDFInfo
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- CN1878986B CN1878986B CN2004800328006A CN200480032800A CN1878986B CN 1878986 B CN1878986 B CN 1878986B CN 2004800328006 A CN2004800328006 A CN 2004800328006A CN 200480032800 A CN200480032800 A CN 200480032800A CN 1878986 B CN1878986 B CN 1878986B
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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
- F23R3/28—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
- 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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/46—Details, e.g. noise reduction means
- F23D14/72—Safety devices, e.g. operative in case of failure of gas supply
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/46—Details, e.g. noise reduction means
- F23D14/72—Safety devices, e.g. operative in case of failure of gas supply
- F23D14/74—Preventing flame lift-off
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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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2209/00—Safety arrangements
- F23D2209/20—Flame lift-off / stability
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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)
- Pre-Mixing And Non-Premixing Gas Burner (AREA)
Abstract
Disclose is a burner for a gas turbine combustor that uses a central bluff body flame holder and a quarl to shape the recirculation zone in order to stabilize the combustion process. The burner includes, among other elements, a cylindrical main body and a flame holder. The flame holder is disposed within a fuel-air mixing chamber and includes a base portion and an elongated bluff body. The base portion engages with the main body of the burner in a supporting manner and the elongated bluff body extends in an axially downstream direction from the base portion through the internal mixing chamberso as to position a combustion ignition point downstream of the internal mixing chamber. In a representative embodiment, the burner further includes a quarl device disposed adjacent to the downstreamend portion of the burner main body. The quarl device defines an interior recirculation chamber and a burner exit. The interior recirculation chamber is adapted for receiving precumbustion gases fromthemixing chamber and for recirculating a portion of the combustion product gases in an upstream direction so as to aid in stabilizing combustion.
Description
Technical field
The burner of the present invention for using about gas turbine, the relevant especially burner that is suitable for stablizing engine combustion, more relevant in conjunction with spout device and utilize the burner of central bluff body flameholder with the smooth combustion process.
Background technology
The application of gas turbine has many-side, comprises generating, military affairs and commercial flight, pipeline transmission, reaches sea transport etc.In gas turbine engine, fuel and air are supplied with the combustion chamber, and at this fuel combination and air and with flame ignition, thereby take fire.Gas turbine engine has some technical problem underlying relevant with combustion process.These problems comprise, for example, the thermal efficiency of burner (burner/combustor), fuel and air suitable mixes, the eliminating of stable, the pulse of flame and noise, reach control, the especially nitrogen oxide (NO of disposal of pollutants
X).Flame stable be refer to flame in the fixed combustion device the position with intensity so that elimination pulse and noise-decreasing and reach other purpose.
The smooth combustion of gas turbine engine needs the cyclic program of combustion product (also instant heating and free radical), wherein heat and free radical pass back the upstream to the flame starting point to promote process of combustion.
At present knownly can be provided with rotational flow air (swirled air) or give eddy flow fuel air mixture, thereby make combustion process stable to fuel air mixture in order to promote the stable of flame.Thereby the swirl stabilized combustion fluids near the burner center line, produce adverse current with heat and free radical pass back the upstream to the fuel air mixture of not combustion to promote burning.
The burner of making charcoal that discloses in U.S. of people such as Monroe the 5th, 131, No. 334, the 5th, 365, No. 865 and the 5th, 415, No. 114 patents all contains gives the flameholder of eddy flow to fuel air mixture.This flameholder comprises the flabellum assembly on a plurality of spaced radials and the fixing circular element on the center fuel supply pipe on the throne.The shape of flabellum becomes to provide the downstream of rotational flow air to fuel supply pipe with azimuth design.
Generally speaking the 5th, 477, No. 685 patents of the U.S. that are included in this Samuelson as a reference are to disclose the swirl stabilized lean burn syringe (lean burninjector) that is used in gas turbine burner.Exemplify in the specific embodiment at it, fuel air mixture leaves the nozzle of position in central authorities via a plurality of radially the outlet.One air cyclone and a spout device are to be attached to the downstream of the wrong gloomy syringe of Sa (Samuelson injector) to promote recirculation flow.With the fuel air mixture that radially leaves nozzle for because of air cyclone so meet with the air of the axial conduct syringe of spiral path.Spout device is use recycles hot combustion product with reinforcement and change at Industrial Boiler and stove a shape.
Utilize the conventional burners of eddy flow, for example go up the those shown, enough swirl strengths need be arranged so that recirculation produces near center line, as shown in Figure 1 with smooth combustion.As above-mentioned, in swirl stabilized burning, when the heat that produces in combustion process upstream is transmitted back to recirculation zone with free radical and mixes with unreacted fuel air mixture still and when taking fire, burning side stablizes.The stable utmost point of burning is dependent on the recirculation that these hot combustion products are back to the upstream.Moreover when the speed increase of recycle burning product, the flux of the combustion product that the heat of upstream and chemistry are lived also increases, and combustion process will be tending towards more stable at wider operating conditions.
Swirl strength has intense influence to size, shape and the intensity of hot combustion product recirculation zone.Swirl strength is weighed it with a dimensionless quantity number (nondimensional number), and it is defined as the ratio of the axial flux of angular momentum to the axial flux of axial momentum.Usually, swirling number was less than 0.4 o'clock, and recirculation zone can't produce.When increasing, can cause swirling number stagnation pressure reduction at preceding stagnation point.Shown in Figure 1, preceding stagnation point be combustion product upstream flow along center line with from burner air downstream axial flow junction part, all speed are all zero herein.Typically, swirling number can produce a low-pressure area at preceding stagnation point greater than about 0.6 o'clock.This low-pressure area is to make combustion product upstream flow to the preceding stagnation point that pressure reduces by the higher burner downstream of burner internal pressure.This is the machine-processed (see figure 1) that causes main recirculation zone to form.
Increase swirling number (S
n) tend to lower preceding stagnation pressure and increase submedial upstream recirculation rate.The upstream flow of the combustion product of this increase has increased and has flow to the hot gas of preceding stagnation point that can open the beginning active combustion and the flux of chemically reactive substance.(0.4＜S just when swirling number is low
n＜0.6), the pressure of the preceding stagnation point pressure of stagnation point behind the recirculation zone only.Thereby, passed back the heat of upstream and the low and instability of burning of flux of chemism combustion product, especially more right when burning is thin.
Swirling number has other influence to recirculation zone.For example, S
nIncrease will lower and further toward a upstream at the low-pressure of preceding stagnation point and a back stagnation point and make recirculation zone shorter.Moreover, with S
nIncrease and the circumferential force of increase, also cause the enlarged-diameter of recirculation zone.
Spout device is to use in Industrial Boiler and stove to lower the influence of swirling number size to recirculation zone length and diameter.Spout device is also allowed is not increasing S
nFollowing to the diameter of the enlarged-diameter of recirculation zone to the spout device outlet.Moreover when using spout device, recirculation zone length is more insensitive to swirling number, and presents the length that is about 2 to 2.5 times of spout device outlet diameters.
Spout device is allowed the high S of use
nAnd the large diameter recirculation zone of unlikely generation.Yet the burner that uses spout device is when strong swirl strength, and flame tends to upstream move and gos deep into burner in and then the part of damage burner.Moreover when burning is initially at lean side on the stoichiometry, denseer mixture will increase flame speed.The increase of this flame speed also impel flame further up the trip move in the burner.Except that the hardware of damaging burner, go deep in the burner and uncontrolled flame moves the discharging that more can cause high nitrogen oxide.
In addition, when the fuel/air mixture ratio changed, it is great that stability problem can become.When thin premixed combustion became very thin, flame speed became very responsive to the change of fuel/air mixture ratio.The flame speed that continue to change often causes the displacement of flame location and causes the vibration and the noise of combustion pressure.
In flame enters burner, cause the fuel/air mixture ratio Shi Yineng that thickens combustion instability is taken place, and flame is more goed deep in the burner.Denseer fuel/air mixture goes up mat attenuating swirl strength than the typical case and offsets.Yet this will cause the cyclic process of flame turnover burner.This universal instability problem can cause the very pulse of high pressure and the rising of discharged nitrous oxides.This unstability belongs to typical low frequency instability, usually between 80 to 150 hertz (Hz).The amplitude of its pressure pulse can be disruptive to gas turbine engine up to 0.1 crust (bar).Moreover, during the dense unstable cyclic part that burns, can produce a large amount of nitrogen oxide.
The shortcoming of known techniques in view of the above needs a kind ofly through improved burner in fact, and it not only promotes the stable of flame, the also discharging of the pulse that can reduce pressure, noise and nitrogen oxide.
Summary of the invention
The burner that the relevant a kind of gas turbine burner of the application's case is used, it utilizes central bluff body flameholder and spout device with the smooth combustion process.This burner comprises cylindrical body, flameholder and other assembly.
This burner body comprises axially relative upstream and downstream end, at least one fuel inlet channel and at least one air inlet passage form wherein.Fuel and air inlet passage are to build to be set to respectively fuel supplying and air to being formed on the downstream end mixing chamber.Mixing chamber has a plurality of its inside and hoop surfaces at interval that are formed on so that make the fuel that is supplied to mixing chamber with air generation eddy flow and mix.
Flameholder is configured in the mixing chamber, comprises pedestal part and long bluff body.Pedestal part is to be connected burner body with supporting way, and long bluff body then extends the combustion ignition point is put the downstream part in the internal mix chamber with the axial downstream direction through the internal mix chamber from pedestal part.
Burner also comprises the spout device that adjoins downstream end.Spout device is for defining interior recirculation chamber and burner outlet.Interior recirculation chamber is to be set as in order to receive from the gas before the burning of mixing chamber with in order to combustion product gas the stablizing with auxiliary combustion at the updrift side recycle sections.
The bluff body of imagination flameholder is for putting at the mixing chamber center, and has a taper upstream zone and an essence cylinder cusp field.Under the ideal state, the axial length of flameholder is to reach the S greater than about 0.6
nAnd design.Swirling number is the ratio of tangent line momentum to axial momentum, and it flows through combustion air amount that burner rotates to leave the ratio of the combustion air amount of burner with the axial flow condition for definition.The mathematical definition of swirling number as seen in the 5th, 365, No. 865 patents of the U.S. of Monroe, generally speaking quote at this by its definition.
In a demonstration specific embodiment, have an air inlet passage at least for forming with radially inner in fact direction, fuel then enters the mixing chamber of main body with axial direction in fact.Under the ideal state, air adds all air by burner for the direction with tangent line and radial inward enters air intake with eddy flow, and this is that design is in order to reach the S greater than about 0.6
n
Those skilled in the art can understand the present invention immediately and can be applicable to any type of combustion chamber or burner, for example solid fuel burner or stove.
Description of drawings
Know for making the personnel of technology can know from experience how to make and use the application's case immediately under the application's case, can be with reference to following graphic:
Fig. 1 is the cross-sectional perspective view of the swirl stabilized combustion device of known techniques;
Fig. 2 contains the cross-sectional perspective view of the swirl stabilized combustion device of bluff body flameholder for the present invention;
Fig. 3 is the sectional view of Fig. 2 burner, the eddy flow of its explanation in burner flows, before the main recirculation zone stagnation point grappling and at the other flame front of central bluff body flameholder;
Fig. 4 a is the sectional view according to the burner of preferred embodiment of the present invention institute construction, and its explanation flame stabilization is at the central bluff body flameholder;
Fig. 4 b is the sectional view of burner of the no central bluff body flameholder of known techniques, and its explanation flame is in the backfire position;
Fig. 4 c is the sectional view of Fig. 4 b burner, and its explanation flame position closely exports at the burner downstream end; And
Fig. 4 d is the sectional view of Fig. 4 b burner, and its explanation flame position is outside burner outlet.
The component symbol simple declaration:
100 burners, 198 flames
20 flameholders, 22 pedestal part
24 long bluff body 26 taper upstream zone
27 post grooves, 28 downstream neck regions
200 burners, 260 mixed zones
298 flames
End, 50 main bodys, 52 upstream
54 downstream ends, 56 fuel inlet channels
58 air inlet passage
60 mixing chambers, 62 surfaces
Stagnation point before 75
80 spout devices, 82 recirculation chamber
Inner surperficial 84 burner outlets of 82a
90 main recirculation zone 92 outer recirculation zone
94 combustion initiation point, 98 conical flames
The specific embodiment
Know this technical staff and will understand above-mentioned and other feature of the burner of the application's case easily by the detailed description of following preferred embodiment.In following reference was graphic, the similar framework of the present invention was all with similar element numbers sign.In Fig. 2, the burner that gas turbine burner is used is generally and is denoted as element numbers 100.Burner 100 is for using central bluff body flameholder 20 and spout device 80 with the smooth combustion process.Burner 100 comprises cylindrical body 50, flameholder 20, spout device 80 and other assembly.Main body 50 and flameholder 20 can be attached mutually with traditional approach, or are retained on together in the close-fitting mode, or mechanically chain live.
Fuel and air inlet passage 56 and 58 are to build up with putting with fuel supplying and air respectively to the mixing chamber 60 that is formed on downstream end.Mixing chamber 60 has a plurality of its inside and hoop surface 62 or turbine leaves at interval of being formed on, in order to the fuel and the air that are supplied to mixing chamber 60 are given swirling motion and given mixing chamber.
Flameholder 20 contains a pedestal part 22 and a long bluff body 24 for putting in mixing chamber 60.Pedestal part 22 is the main body 50 that is connected burner 100 with supporting way, and long bluff body 24 then extends so that combustion ignition point (combustion ignition point) or preceding stagnation point (forward stagnation point) 75 (referring to Fig. 3) are put the downstream part in internal mix chamber 60 with the axial downstream direction through internal mix chamber 60 from pedestal part 22.Long bluff body 24 still has a plurality of to be formed on the outer and axially extended post groove 27 in its surface, with the scale of turbulent flow in the definition burner 100.
The bluff body part 24 of flameholder 20 is for putting at mixing chamber 60 centers and a taper upstream zone 26 being arranged and have a downstream neck regions 28 of radially amplifying head.The shape of neck regions can be set as stable with further recirculation that improves combustion product and flame.Sun selects the axial length of flameholder 20 so that with greater than about 0.6 but be not more than 2.0 swirling number and come the grappling recirculation zone.As previously mentioned, swirling number is to be defined as the combustion air amount of rotation of the burner of flowing through to leave the ratio of the combustion air amount of burner with the axial flow condition.
In fact flameholder 20 stops flame to enter mixing chamber 60 along burner 100 center line backfire.Enter mixing chamber 60 by stoping along the center line backfire, fuel-air mixture can have the swirl component of higher tangential direction.Increase swirl strength and do not have backfire for making spout device more efficient during towards the upstream recirculation of hot gas, and make whole combustion process more stable in enhancing.Increase upstream heat re-circulated and can make thinner fuel-air mixture flameholding.This will provide bigger elasticity and robustness in engine operation, keep low engine emissions simultaneously.
Keeping little recirculation zone is of value to the chemism that keeps hot combustion gas, and allows that faster Yu more stable burning is initial, and especially at low combustion temperature, this often occurs in low NOx NO
X(nitric oxide NO and nitrogen dioxide NO
2) when engine is lower than 1700K.Raise and ignition temperature decline with combustion pressure, the low residence time in recirculation becomes more important to the chemism combustion product.Under high pressure, chemically-reactive substance (or claim free radical that quick incipient combustion is benefited to some extent) is releived apace to balanced level under affected by high.The life-span that is higher than the free radical of balanced level shortens with the increase of pressure.When ignition temperature low, for example at low NO
XIn the engine,, apparent more important to effective utilization of the high lack of balance level of these free radicals because of free radical is that balanced level is lower when the low temperature.
Fig. 3 is the sectional view of swirl stabilized combustion device 100, and its recirculation of describing the past upstream of combustion product is to keep combustion process.The upstream of burner 100 and downstream are its reference marker with " U " and " D " respectively.As shown in the figure, mobile different zones, the just main recirculation zone 90 and outer recirculation zone 92 of being separated into of combustion product.
As previously mentioned, moving program generally is used to smooth combustion so that combustion product is up vacillated to make the fuel-air mixture eddy flow.In the burner 100 that discloses, bluff body flameholder 20 is anchored on a fixed position to main recirculation zone 90.The combustion initiation point 94 of flame front or premix fluid produces along the outer surface of main recirculation zone 90, at outer surface, and heat is mixed with free radical and initial unreacted is crossed premixed fuel and air.Flame initial at flameholder 20 end and toward downstream side to being extended to cone shape.
Even the ratio of fuel-air mixture has very remarkable change, burner 100 is still kept the end 24 of the position of flame at flameholder 20.When thin premixed combustion became very thin, flame speed became very responsive to the fuel/air mixture ratio.The change of this flame speed often causes the displacement of flame location, and may cause the vibration of combustion pressure.By coming the grappling flame location with central bluff body flameholder 20 and avoiding flame to move, can prevent the vibration of pressure.
The sectional view explanation of the burner 100 that Fig. 4 a is provided is anchored on the conical flame 98 of flameholder 20.Fig. 4 b to 4d is depicted as the burner 200 that does not contain the centerbody flameholder.In burner 200, strong when swirl strength, or the fuel/air mixture ratio of premix is when dense, and flame 298 tendencies move and go deep in it toward burner, shown in Fig. 4 b.When burning during, make that mixture is denseer will to increase flame speed for the lean side on the stoichiometry.It is moving that the flame speed that increases can make flame further up vacillate.Increasing swirl strength also can produce and make the flame moving same tendency of further up vacillating.Do not wish that generally flame 298 enters in the burner mixed zone 260, shown in Fig. 4 b.Go deep in the burner 200 and uncontrolled flame moves the discharging that can damage the hardware of burner and cause high nitrogen oxide.Install central bluff body flameholder 20 additional and can be anchored on the preceding stagnation point 96 of main recirculation zone 90 end of flameholder 20, enter mixing chamber 60 to prevent main recirculation zone 90 and flame in the spout device modified burner.For stagnation point 96 before can ordering about originally go deep in the burner 100 or towards outlet 84 or even all swirl strengths of burner outside, the central bluff body flameholder is for being fixed on preceding stagnation point 96 (referring to Fig. 3) end of flameholder 20.Hereat, central bluff body flameholder 20 is anchored on single position to preceding stagnation point 96 and flame 198 it is unlikelyly ceaselessly moved with the change of swirl strength.
Central bluff body flameholder 20 has an optimum position, and at this, swirling number can increase and decrease in the same manner and preceding stagnation point 96 continues to be attached on the flameholder 20 with flame 198.If swirl strength continues to successively decrease, flame 198 jumps out of flameholder and is stabilized in the downstream quite at a distance or outside burner outlet 84 until last flame continuing to be attached to flameholder 20.From identical optimum swirl number and central bluff body flameholder position, increasing swirl strength can not influence flame location, and until at a certain critical swirl strength the time, flame location is jumped flameholder 20 ends that swallow up toward the upstream in the main recirculation zone.As long as operating condition remains in the zone of reasonableness of swirl strength and fuel/air mixture ratio, flame location will stay put, and will be as the same even engine conditions changes to some extent.These scopes have proved quite big, and this is the positive characteristic of burner 100.
The mobile of flame location is a significant problem for the combustion system of operating with very thin condition.Is to produce at the thinnest fuel/air mixture ratio and/or minimum swirl strength at Fig. 4 c with the flame 198 shown in Fig. 4 d.When burning was very thin, it is very unstable that swirl stabilized combustion can become.Yet, lower NO
XBurning is thin to be brought down below diatomic nitrogen and oxygen (N to flame temperature in order to make to discharge the method for tool effect
2With O
2) decompose and be combined into NO and NO again
2Temperature.If the air and the fuel mix of nearly twice are arranged, the inert material that the air that has more then heats as burned process before the fuel and air mixture burning.As long as have abundance or more air to supply with combustion process, the energy size that combustion process discharges is only to be decided by spent fuel quantity.Exceed the size that the required air of burning does not influence combustion process and released energy, but then remain unchanged the temperature of flame and combustion product thereby attenuating because of the binding capacity of fuel and air increases in the energy that discharges.The attenuating of flame temperature also reduces NO
X(NO and NO
2) synthetic.These are several to be present all low NO
XThe principle of the gas turbine engine institute foundation of discharging.
As above-mentioned, install central bluff body flameholder 20 additional and allow the increase of swirl strength and do not cause flame to flash back in the mixing chamber 60 at burner 100.The ability order that increases swirl strength increases the adverse current that hot combustion product is back to the upstream.The increase of hot combustion product is flowed provides more heat and free radical, and makes burning more sturdy and difficult unstable.
If flame front is begun outward by burner, at the fixed pressure drop across burner, burner will have a maximum airflow rate.If some disturbance causes flame to jump in the burner, will reduce through the air mass flow rate (mass flow rate) of burner, this is will make the volume flow rate that air is expanded to be increased through burner outlet because of heat that combustion process produces.This increase at the volume flow rate of fixed pressure drop will cause the minimizing through the air mass flow rate of burner.For most of gas turbine engine, use 6 to 100 burners calmly according to the power rating of engine.If flame is jumped into some burner, but non-whole, then have the burner of flame and will burn stronglyer in inside.This is on average to supply with each burner because of identical fuel via the common fuel menifold.Because the burning of burner outlet inside causes the volume flow rate increase and causes air mass flow rate to reduce, so flame burns denselyer at interior burner.When burning is initially when thin, the result of denser burning is for increasing flame speed.The increase of flame speed allows that flame more gos deep in the burner.This will increase the also extra minimizing air mass flow rate of volume flow rate and make burning more dense.In case enter inside, flame might rest in some burners, rests on simultaneously outside other burner.If this takes place, when the turbine inlet that enters corresponding to denser burner, will cause high NO
XAnd focus appears.
Combustion process in burner also will influence the characteristic of eddy flow, and it can cause the reverse of the previous program in the burner that flame is drawn in.In the time of in flame is drawn into burner, the mass flowrate of air will reduce.Atmospheric density by cyclone does not change and causes the lower speed and the attenuating of swirl strength.The attenuating of swirl strength easily makes the preceding stagnation point of main recirculation down vacillate moving.Combustion process itself also has the tendency that lowers swirl strength, and this is the flow that enlarges all directions because of combustion process fifty-fifty.Can cause instability when causing the fuel/air mixture ratio to thicken in flame moves into burner, this will make flame more go deep in the burner.The denseer fuel/air mixture of offsetting the generation higher flame speed is than the decline that is swirl strength.This will form the cyclic process of flame turnover burner.And this universal instability problem can cause the very pulse and the NO of high pressure
XThe rising of discharging.This unstability is general low frequency instability, usually between 80 to 150 hertz.The amplitude of its pressure pulse can reach 0.1 the crust pressure oscillation and disruptive to gas turbine engine.Moreover, in the dense cyclic part that burns, can produce a large amount of NO
XUse the central bluff body flameholder and make flame location insensitive, and allow the fixed position of flame stabilization at the flameholder end for the change of swirl strength and fuel/air mixture ratio in invention based on the burner of spout device.So can eliminate and lead because of the pressure oscillation of moving and the NO of rising in flame
XDischarging.
The present invention encyclopaedizes to preferred embodiment, those skilled in the art can understand the disclosed content of utilization easily can do different changes and/or modification, and unlikely disengaging such as spirit of the present invention and technology category that appending claims defined.
Swirling number is the ratio of tangent line momentum to axial momentum, and the combustion air flow that its definition is rotated through burner leaves the ratio of the combustion air flow of burner for flowing vertically.
Claims (16)
1. burner that gas-turbine combustion chamber is used comprises:
A) cylindrical body, have at axial relative upstream and downstream end, this main body has at least one fuel inlet channel and is formed on wherein at least one air inlet passage, these passages are applicable to that fuel supplying and air are to the mixing chamber of this downstream end that is defined in this main body respectively, and this mixing chamber is configured to make the fuel that is supplied to this mixing chamber to produce eddy flow with air and it is mixed; And
B) flameholder, be configured in this mixing chamber, and comprise the pedestal part that engages with this burner body, and from this pedestal part through the internal mix chamber vertically downstream direction extend to control the long bluff body of this internal mix chamber combustion ignition point downstream position, wherein, this long bluff body comprises taper upstream zone and downstream neck regions, and the diameter of this taper upstream zone reduces along downstream direction, and this neck regions comprises the cusp field that radially amplifies.
2. burner as claimed in claim 1 also comprises:
Spout device, adjoin at this downstream end of this burner body and arrange, this spout device defines interior recirculation chamber and burner outlet, this interior recirculation chamber is useful in the pre-burning gas of reception from this mixing chamber, and along the combustion product gas of updrift side recycle sections, with auxiliary smooth combustion.
3. burner as claimed in claim 1, wherein, the bluff body of this flameholder is configured in the axial centre place in this mixing chamber.
4. burner as claimed in claim 1, wherein, the axial length of this flameholder is set as in order to reach the swirl number per min greater than about 0.6.
5. burner as claimed in claim 1, wherein, this at least one air inlet passage is along the direction formation of radial inward in fact.
6. burner as claimed in claim 1, wherein, fuel edge axial direction in fact enters this mixing chamber of this main body.
7. burner as claimed in claim 1, wherein, this at least one fuel inlet channel that is formed on this burner body comprises and is used in the spire of giving angular momentum to fuel.
8. burner as claimed in claim 1, wherein, this flameholder bluff body has many and is formed on its outer surface and axially extended groove.
9. burner that gas-turbine combustion chamber is used comprises:
A) cylindrical body, have at axial relative upstream and downstream end, this main body has at least one fuel inlet channel and is formed on wherein at least one air inlet passage, these passages are useful in that fuel supplying and air are to the mixing chamber of this downstream end that is defined in this main body respectively, and this mixing chamber is configured to make the fuel that is supplied to this mixing chamber to produce eddy flow with air and it is mixed; And
B) flameholder, be configured in this mixing chamber, and comprise the pedestal part that engages with this burner body, and from this pedestal part through the internal mix chamber vertically downstream direction extend to control the long bluff body of this internal mix chamber combustion ignition point downstream position, wherein, this long bluff body comprises taper upstream zone and downstream neck regions, and the diameter of this taper upstream zone reduces along downstream direction, and this neck regions comprises the cusp field that radially amplifies; And
C) spout device, adjoin at this downstream end of this burner body and arrange, this spout device defines interior recirculation chamber and burner outlet, this interior recirculation chamber is suitable for receiving the pre-burning gas from this mixing chamber, and along the combustion product gas of updrift side recycle sections, with auxiliary smooth combustion.
10. burner as claimed in claim 9, wherein, this bluff body of this flameholder is configured in the axial centre place in this mixing chamber.
11. burner as claimed in claim 9, wherein, the axial length of flameholder is suitable for making the swirl number per min of main recirculation to be stabilized in about 0.6 and about 2.0 scopes.
12. burner as claimed in claim 9, wherein, this at least one air inlet passage is along the direction formation of radial inward in fact.
13. burner as claimed in claim 9, wherein, fuel edge axial direction in fact enters this mixing chamber of this main body.
14. burner as claimed in claim 9, wherein, this at least one fuel inlet channel that is formed on burner body comprises and is used in the spire of giving angular momentum to fuel.
15. burner as claimed in claim 9, wherein, this flameholder bluff body has many and is formed on its outer surface and axially extended groove.
16. the burner that gas-turbine combustion chamber is used comprises:
A) cylindrical body, have axially relative upstream and downstream end, this main body has at least one fuel inlet channel and formation at least one air inlet passage wherein, these passages are useful in respectively fuel supplying and air to the mixing chamber that is defined in downstream end, and the fuel that this mixing chamber is configured to be supplied to mixing chamber produces eddy flow and it is mixed with air; And
B) be configured in the mixing chamber and be used in the device of control internal mix combustion ignition point downstream position, wherein, this device comprises taper upstream zone and downstream neck regions, and, the diameter of this taper upstream zone reduces along downstream direction, and this neck regions comprises the cusp field that radially amplifies.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US50051703P | 2003-09-05 | 2003-09-05 | |
| US60/500,517 | 2003-09-05 | ||
| PCT/US2004/028768 WO2005040682A2 (en) | 2003-09-05 | 2004-09-03 | Device for stabilizing combustion in gas turbine engines |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1878986A CN1878986A (en) | 2006-12-13 |
| CN1878986B true CN1878986B (en) | 2010-04-28 |
Family
ID=34519984
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2004800328006A Expired - Fee Related CN1878986B (en) | 2003-09-05 | 2004-09-03 | Device for stabilizing combustion in gas turbine engines |
Country Status (9)
| Country | Link |
|---|---|
| US (1) | US20050106520A1 (en) |
| EP (1) | EP1668295A2 (en) |
| JP (1) | JP4767851B2 (en) |
| KR (1) | KR101178195B1 (en) |
| CN (1) | CN1878986B (en) |
| BR (1) | BRPI0413966A (en) |
| CA (1) | CA2537949C (en) |
| RU (1) | RU2407950C2 (en) |
| WO (1) | WO2005040682A2 (en) |
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- 2004-09-03 CN CN2004800328006A patent/CN1878986B/en not_active Expired - Fee Related
- 2004-09-03 RU RU2006110986/06A patent/RU2407950C2/en not_active IP Right Cessation
- 2004-09-03 KR KR1020067004626A patent/KR101178195B1/en not_active IP Right Cessation
- 2004-09-03 US US10/933,887 patent/US20050106520A1/en not_active Abandoned
- 2004-09-03 BR BRPI0413966-6A patent/BRPI0413966A/en not_active Application Discontinuation
- 2004-09-03 EP EP04809669A patent/EP1668295A2/en not_active Withdrawn
- 2004-09-03 WO PCT/US2004/028768 patent/WO2005040682A2/en active Application Filing
- 2004-09-03 JP JP2006525479A patent/JP4767851B2/en not_active Expired - Fee Related
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| US6145450A (en) * | 1996-02-06 | 2000-11-14 | Foster Wheeler Corporation | Burner assembly with air stabilizer vane |
Also Published As
| Publication number | Publication date |
|---|---|
| CA2537949A1 (en) | 2005-05-06 |
| JP4767851B2 (en) | 2011-09-07 |
| CA2537949C (en) | 2011-01-11 |
| US20050106520A1 (en) | 2005-05-19 |
| BRPI0413966A (en) | 2006-10-31 |
| EP1668295A2 (en) | 2006-06-14 |
| RU2407950C2 (en) | 2010-12-27 |
| KR101178195B1 (en) | 2012-08-30 |
| WO2005040682A2 (en) | 2005-05-06 |
| RU2006110986A (en) | 2006-07-27 |
| KR20060086358A (en) | 2006-07-31 |
| CN1878986A (en) | 2006-12-13 |
| JP2007504429A (en) | 2007-03-01 |
| WO2005040682A3 (en) | 2005-08-11 |
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Owner name: SIEMENS AKTIENGESELLSCHAFT Free format text: FORMER OWNER: DELAVAN INC. Effective date: 20140801 Free format text: FORMER OWNER: SIEMENS INDUSTRIAL TURBINE MACHINERY COMPANY Effective date: 20140801 |
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Address after: Iowa Patentee after: Delavan Inc. Patentee after: SIEMENS industrial Turbomachinery Address before: Iowa Patentee before: Delavan Inc. Patentee before: Demag Delaval Ind Turbomachine |
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