CN101625130A - Flameless combustion organizational structure and flameless combustion chamber for realizing structure - Google Patents
Flameless combustion organizational structure and flameless combustion chamber for realizing structure Download PDFInfo
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
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Abstract
The invention discloses a flameless combustion organizational structure used in a combustion chamber of a gas turbine. In the structure, a plurality of coaxial ejector nozzles are evenly arranged at one end of the cylinder-shaped combustion chamber in a ring shape; the center of the ejector nozzles evenly arranged in the ring shape is provided with a cylinder-shaped reflux structure; secondary air does not take part in combustion in the cylinder-shaped combustion chamber; the air taking part in the reaction enters from one end provided with the ejector nozzles arranged on the cylinder-shaped combustion chamber, and a large amount of reflux high-temperature fume is mixed with the fresh air according to the position relationship between the nozzle evenly arranged in the ring shape and the cylinder-shaped reflux structure arranged in the center of the nozzles, so that the air temperature is increased, and the air is diluted; and the diluted high-temperature air spontaneously combusts when exposed to the fuel to form a high-temperature dispersing reaction area, so that the flameless combustion is achieved in the combustion chamber of the gas turbine. The invention simultaneously discloses the flameless combustion chamber for realizing the flameless combustion organizational structure. The flameless combustion organizational structure and the flameless combustion chamber realize flameless combustion and achieve the aims of extremely low pollutant emission and stable combustion of the combustion chamber of the gas turbine.
Description
Technical field
The present invention relates to the gas turbine technology field, relate in particular to a kind of flameless combustion institutional framework that is applied to gas-turbine combustion chamber, and the Flameless combuster of realizing this flameless combustion institutional framework.
Background technology
The environmental issue that present China is brought based on the energy resource structure of coal has faced increasing international pressure, is badly in need of the breakthrough and the innovation of clean coal technology.Efficient heat such as integrated gasification combined cycle plants (IGCC), coal co-generation system, the direct preparing hydrogen, generating power of the coal system-merit transfer process that with advanced gas turbine is core is because in efficient, economic competitiveness, pollutant emission control, especially at CO
2Many-sided great development potentiality such as reduction of discharging are the important component parts of following main flow generation technology.These systems medium powers are produced core cells---and low heat value hydrogen-rich fuel during the fuel of gas turbine is, therefore development is to be one of basic technology of using of the advanced power cycle of core with the gas turbine at the ultralow pollution combustion technology of hydrogen-rich fuel.
Gas turbine hangs down NO at present
XCombustion technology mainly comprises dilution, diffusion and combustion, poor fuel premix, portly-chilling-poor attitude (Rich-burn, Quick-quench, Lean burn, RQL) burning, catalytic combustion etc.
The dilution, diffusion and combustion technology is the low NO at middle low heat value hydrogen-rich fuel that is widely used in heavy duty gas turbine
XCombustion technology.Its characteristics adopt the inert gas dilution hydrogen-rich fuel exactly, reduce fuel value; Or diluent air, the oxygen concentration when reducing burning reaches reduction diffusion combustion adiabatic flame temperature and reduces NO
XThe purpose of discharging.In the IGCC system, adopt the empty high pressure N that produces that divides
2As the diluent of hydrogen-rich fuel have reduce investment outlay, the characteristics of pressure recovery potential energy.The thermal value range of the fuel gas that low calorie fuels gas diffusion dilution combustion chamber can be used in the GE company is from 5MJ/Nm
3To 12MJ/Nm
3, NO
XEmission level generally is reduced to 40ppm (@15%O
2) below, adopt multiinjector low-noise combustion chamber (Multi nozzle quiet combustor, type MNQC) even be lower than 10ppm (@15%O individually
2).But this technology is difficult to obtain extremely low NO
XDischarging, because excessive dilution can cause the CO of combustion instability, combustion chamber and UHC discharging to increase, efficiency of combustion descends, as adopts stable combustion technology on duty, has increased NO again
XDischarging further reduces NO so the dilution, diffusion and combustion technology is difficult to reach gas turbine of future generation
XBe discharged into the requirement of 3ppm.
Poor fuel premix technology has obtained successful Application on the gas turbine of gas-firing, as the F level and the H level heavy duty gas turbine of GE company, current NO
XEmission level can reach 25ppm (@15%O
2), indivedual types are lower than 10ppm (@15%O
2).The problem that this technology exists is easy to generate thermal acoustic oscillation and tempering exactly.In order to obtain extremely low NO
XDischarging just need make fuel burn under poorer condition, and can further strengthen hugging like this.For hydrogen-rich fuel owing to contain a large amount of H
2, H
2High activity and high flame propagation velocity can make tempering and thermal acoustic oscillation problem more serious.Therefore the commercial gas turbine of existing burning hydrogen-rich fuel does not all adopt poor fuel premix technology.
The RQL combustion technology is nitrogenous (as NH in order to reduce at first
3) NO of fuel
XDischarging and propose is characterized in that burning is divided into two districts and carries out, and the nitrogen major part in fuel-rich regions fuel is converted into N
2Rather than NO, use air quenching then, form poor premixed combustion.In recent years, this technology conception was further development of the two-region combustion model, and fuel enters Liang Qu respectively, and seed region wherein is positioned at the next door, primary zone, not with load change, becomes the point of safes burning things which may cause a fire disaster.There is TVC (Trap Vortex Combustor) combustion chamber based on this conception of species, AVC (Advanced Vortex Combustor) etc., and the characteristics of this class combustion technology are flame stabilizations, adapt to bigger load change, NO
XAlso can drop to below the 10ppm, but still be in conceptual phase at present.
Catalytic combustion also still is in conceptual phase at present, has the problem of the too complicated and poor reliability of chamber structure.This technology makes chemical reaction to carry out under very low temperature, has therefore avoided the high-temperature region, can guarantee low-down NO
XEmission level.The major defect of this method be exactly under hot conditions the life-span of catalyst and effecting reaction face limited, and they cost an arm and a leg.
Summary of the invention
(1) technical problem that will solve
In view of this, main purpose of the present invention is at the low NO of low heat value hydrogen-rich fuel in existing
XThe deficiency of combustion technology, a kind of flameless combustion institutional framework that is applied to gas-turbine combustion chamber is provided, and the Flameless combuster of realizing this flameless combustion institutional framework, to realize flameless combustion, reach the utmost point low pollution emission and the smooth combustion of gas-turbine combustion chamber.
(2) technical scheme
For achieving the above object, the invention provides a kind of flameless combustion institutional framework that is applied to gas-turbine combustion chamber, this structure is evenly arranged a plurality of coaxial jet nozzles an end ring shape of cannular combustion chamber, and center arrangement tubular return-flow structure at the even a plurality of jet nozzles arranged of this annular, no auxiliary air participates in burning in the cannular combustion chamber, the air that participates in reaction arranges that from cannular combustion chamber an end of jet nozzle enters, position relation between the nozzle that the utilization annular is evenly arranged and the tubular return-flow structure of center arrangement, form a large amount of backflow high-temperature flue gas and fresh air blending, improve the temperature of air and air is diluted, this diluted high temperature air runs into fuel generation spontaneous combustion, form the high degree of dispersion reaction zone, in gas-turbine combustion chamber, realize flameless combustion.
In the such scheme, air and fuel are injected at a high speed in the combustion chamber by a plurality of coaxial jet nozzles, do not adopt air cyclone and fuel swirl device, guarantee jet penetration, make the reactant high-speed jet go into the combustion zone of cannular combustion chamber.
In the such scheme, utilize even nozzle of arranging of annular and the relative position relation between the tubular return-flow structure, reaction finishes the back high-temperature flue gas and refluxes along the center line of cannular combustion chamber, and near air enters the cannular combustion chamber air intake radially to external diffusion, with reactant generation blending.
In the such scheme, because the tubular return-flow structure exists, flame stabilization is in the zone of distance nozzle certain distance, and concrete distance size depends on the laminar flame spread speed of effluxvelocity and fuel gas.
In the such scheme, flame region is a monoblock type distribution flame, does not have obvious flame front, does not have obvious high-temperature area, does not need to take the design of auxiliary air, and the air that participates in reaction all arranges that from cannular combustion chamber an end of jet nozzle enters.
The present invention also provides a kind of Flameless combuster of realizing the flameless combustion institutional framework, and this Flameless combuster comprises:
Be positioned at dismountable fuel air chamber that this Flameless combuster one end is used to provide fuel;
The air air chamber of fixedlying connected with this fuel air chamber;
End is positioned at the fuel air chamber, and front end is positioned at cannular combustion chamber, and runs through evenly a plurality of coaxial jet nozzles of layout of this air air chamber, annular;
The tubular return-flow structure of the center arrangement of a plurality of jet nozzles of evenly arranging in this annular;
The cannular combustion chamber of fixedlying connected with this air air chamber;
Be used for the design air blending hole, the research dilution air is for the influence of exit flow field, and the afterbody blending section of fixedlying connected with this cannular combustion chamber.
In the such scheme, described cannular combustion chamber adopts the double-layer flame barrel structure, and this double-layer flame barrel structure inside is reaction zone, is air duct between two-layer, a cooling effect.
In the such scheme, described tubular return-flow structure is replaceable, in order to capacity of returns and recirculation zone size in the control cannular combustion chamber.
In the such scheme, described coaxial jet nozzle is 12, and internal diameter equals 12mm, is evenly distributed on around the tubular return-flow structure, and riding position is at cannular combustion chamber one end, apart from cannular combustion chamber center line 38mm place.
In the such scheme, described coaxial jet nozzle is pre-mix nozzle or divergent nozzle, the perforate of premix nozzle head sealing long tube wall, and fuel gas is in air air chamber and air blending; Divergent nozzle is the coaxial jet form, the sealing of head perforate long tube wall, and head stays 5mm and jet air blending to enter cannular combustion chamber then at a high speed.
In the such scheme, described tubular return-flow structure is replaceable, utilizes the burner inner liner cover plate of cannular combustion chamber and the gap between the air air chamber to fix, and need not welding, this tubular return-flow structure head recirculation zone internal diameter Φ 50mm, and length is respectively 30mm, 50mm, 70mm.
In the such scheme, air enters between the double-layer flame barrel structure from the cannular combustion chamber rear portion by four holes, through entering air chamber by trench structure behind the burner inner liner zone between the double-layer flame barrel structure inside and outside wall, by annular oriffice the head recirculating zone structure that stretches in the air chamber is impacted cooling then, enter cannular combustion chamber by air nozzle.
(3) beneficial effect
From technique scheme as can be seen, the present invention has following beneficial effect:
1, the present invention proposes around cannular combustion chamber inlet uniform nozzle, head of combustion chamber and settle the burning institutional framework of tubular recirculating zone, center, and propose the model combustion chamber in addition structure realize.The model combustion chamber is except that replaceable head recirculation zone structure, and the burner inner liner mid portion uses the double-layer flame barrel structure and utilizes counter-flow air to be cooled off, and fuel nozzle adopts diffusion/premix exchangeable nozzle structure.By this institutional framework and the combustion chamber of realizing this structure, effectively realize flameless combustion, thereby reach the utmost point low pollution emission and the smooth combustion of gas-turbine combustion chamber.
2, the present invention has high stability, extremely oligosaprobic characteristics for the burning of low heat value hydrogen-rich fuel in the gas-turbine combustion chamber has proposed effective solution.Avoided simultaneously present main flow combustion with reduced pollutants mode be applied in deficiency on the low heat value hydrogen-rich fuel, be that a kind of burning organizational form and structure thereof of novel combustion chamber realizes.
3, therefore the present invention has avoided the tempering problem of premixed combustion owing to adopt high effluxvelocity; Owing to adopt the monoblock type burning, also avoided the thermal acoustic oscillation problem.
Description of drawings
Fig. 1 is the flow process schematic diagram of fluid in the model combustion chamber;
Fig. 2 is the three-dimensional half sectional view of Flameless combuster;
Fig. 3 is a nonflame model combustion chamber rear view;
Fig. 4 is the structural representation of replaceable head return-flow structure;
Fig. 5 is an air air chamber structure schematic diagram;
Fig. 6 is a fuel gas air chamber structure schematic diagram;
Fig. 7 is the schematic diagram of replaceable fuel nozzle arrangements;
Fig. 8 is diffusion scheme computation structure figure of the present invention;
Fig. 9 is premix scheme computation structure figure of the present invention;
Figure 10 is a divergent nozzle of the present invention velocity contour vertically;
Figure 11 is the pre-mix nozzle of a present invention velocity contour vertically;
Figure 12 is a high temperature gases recirculating situation head temperature dyeing trace distribution map of the present invention;
Figure 13 is divergent nozzle structure temperature distribution cross-sectional distribution figure;
Figure 14 is premix nozzle arrangements Temperature Distribution cross-sectional distribution figure.
The specific embodiment
At first, flameless combustion is described in detail.
Flameless combustion is a kind of the rise the nineties, at high temperature, low oxygen concentration, low fuel air equivalent than producing invisible flame burning technology under the condition.This technology is to adopt a large amount of high-temperature flue gas and ozone blending that reflux, the temperature that will improve on the one hand air make it to surpass fuel from ignition temperature, reach the purpose of dilution oxidant, reduction oxygen concentration on the other hand, make fuel generation spontaneous combustion after this high temperature air through dilution runs into fuel.Because combustion reaction at this moment is simultaneous in certain spatial dimension, form the reaction zone of high degree of dispersion, do not exist to resemble tangible flame front diffusion combustion or the premixed combustion.Though very high with the air themperature after the flue gas blending, because dilution back oxygen concentration is very low, therefore the flame temperature that obtains is very low.As long as make flame temperature be lower than 1800K by the reflux ratio of adjusting flue gas, just can obtain extremely low NO
XDischarging.
When adopting flameless combustion technology, can be so that fuel and air infeed the combustion chamber respectively, and can adopt very high fuel jet speed, tempering can not take place therefore; In this high degree of dispersion reaction zone that flameless combustion forms, there is not the flame propagation process, therefore hardly the thermal acoustic oscillation problem can takes place.Aphlogistic these characteristics are particularly suitable for the hydrogen-rich fuel that burns, and not only can obtain very low NO
XDischarging can also solve tempering and thermal acoustic oscillation problem.
Flameless combustion also has the height flame holding, does not need to adopt steady flame technology such as cyclone or bluff body, even at very low O
2Also can smooth combustion under concentration and the equivalent proportion condition.In addition, flameless combustion also has very high efficiency of combustion, and this makes flameless combustion also can be applied to the fuel of ultra-low heat value again, solves problems such as flame stabilization and efficiency of combustion are low.
Than the combustion technology that background parts is mentioned, flameless combustion technology has following advantage in the hydrogen-rich fuel burning:
1, do not need extra auxiliary equipment or other supplies (catalytic combustion or dilute combustion), there is higher reliability the combustion chamber like this.
2, compare with fractional combustion, realize the simple in structure of flameless combustion technology, and NO
XBe emitted on lower level, reason is that flameless combustion technology has only one simply to utilize the moving air combustion zone, does not produce a large amount of NO
xPremixed flame on duty
3, have better security, avoided tempering and thermal acoustic oscillation problem (poor premixed combustion).
4, need not be divided into richness-poor two districts (RQL) on physical arrangement, it does not need special cooling yet.
In order to achieve the above object, form flameless combustion, an end that the present invention proposes by arrange nozzle at cannular combustion chamber increases the recirculation zone structure, evenly arrange the coaxial jet nozzle at this recirculation zone structure periphery, forming the high-temperature flue gas inside center refluxes, make high-temperature flue gas and do not fire the mutual blending of fresh product, form aphlogistic burning institutional framework.
This flameless combustion institutional framework that is applied to gas-turbine combustion chamber provided by the invention, end ring shape at cannular combustion chamber is evenly arranged a plurality of coaxial jet nozzles, and center arrangement tubular return-flow structure at the even a plurality of jet nozzles arranged of this annular, no auxiliary air participates in burning in the cannular combustion chamber, the air that participates in reaction arranges that from cannular combustion chamber an end of jet nozzle enters, position relation between the nozzle that the utilization annular is evenly arranged and the tubular return-flow structure of center arrangement, form a large amount of backflow high-temperature flue gas and fresh air blending, improve the temperature of air and air is diluted, this diluted high temperature air runs into fuel generation spontaneous combustion, form the high degree of dispersion reaction zone, in gas-turbine combustion chamber, realize flameless combustion.
In this flameless combustion institutional framework that is applied to gas-turbine combustion chamber provided by the invention, air and fuel are injected in the combustion chamber at a high speed by a plurality of coaxial jet nozzles, do not adopt air cyclone and fuel swirl device, guarantee jet penetration, make the reactant high-speed jet go into the combustion zone of cannular combustion chamber.
In this flameless combustion institutional framework that is applied to gas-turbine combustion chamber provided by the invention, utilize even nozzle of arranging of annular and the relative position relation between the tubular return-flow structure, reaction finishes the center line backflow of back high-temperature flue gas along cannular combustion chamber, and near air enters the cannular combustion chamber air intake radially to external diffusion, with reactant generation blending.
In this flameless combustion institutional framework that is applied to gas-turbine combustion chamber provided by the invention, because the tubular return-flow structure exists, flame stabilization is in the zone of distance nozzle certain distance, and concrete distance size depends on the laminar flame spread speed of effluxvelocity and fuel gas.
In this flameless combustion institutional framework that is applied to gas-turbine combustion chamber provided by the invention, flame region is a monoblock type distribution flame, there is not obvious flame front, there is not obvious high-temperature area, do not need to take the design of auxiliary air, the air that participates in reaction all arranges that from cannular combustion chamber an end of jet nozzle enters.
The present invention also provides a kind of Flameless combuster of realizing above-mentioned flameless combustion institutional framework, and this Flameless combuster comprises:
Be positioned at dismountable fuel air chamber that this Flameless combuster one end is used to provide fuel;
The air air chamber of fixedlying connected with this fuel air chamber;
End is positioned at the fuel air chamber, and front end is positioned at cannular combustion chamber, and runs through evenly a plurality of coaxial jet nozzles of layout of this air air chamber, annular;
The tubular return-flow structure of the center arrangement of a plurality of jet nozzles of evenly arranging in this annular;
The cannular combustion chamber of fixedlying connected with this air air chamber;
Be used for the design air blending hole, the research dilution air is for the influence of exit flow field, and the afterbody blending section of fixedlying connected with this cannular combustion chamber.
This Flameless combuster has been considered situation about cooperating with other gas turbines, air enters between the double-layer flame barrel structure from the cannular combustion chamber rear portion by four holes, through entering air chamber by trench structure behind the burner inner liner zone between the double-deck inside and outside wall, by annular oriffice the head recirculating zone structure that stretches in the air chamber is impacted cooling then, enter cannular combustion chamber by air nozzle.The effect of this reverse-flow air mainly comprises: 1) primary zone is cooled off; 2) make that to enter in the air chamber air flow field more even.
Settle annular oriffice in the air air chamber, the air that enters from sleeve pipe passes air air chamber head orifice plate, passes annular oriffice in the air air chamber head recirculating zone structure that stretches in the air air chamber is impacted cooling.
Described cannular combustion chamber adopts double-layer flame barrel structure (this double-layer flame barrel structure also can be called the double-layer flame barrel structure), and this double-layer flame barrel structure inside is reaction zone, is air duct between two-layer, a cooling effect.In the double-layer flame barrel structure, the internal diameter of outer layer sleeve is 146mm, and the internal diameter of inner layer sleeve is 100mm.Described coaxial jet nozzle is generally 12, also can be for a plurality of.The internal diameter of coaxial jet nozzle equals 12mm, is evenly distributed on around the tubular return-flow structure, and riding position is at cannular combustion chamber one end, apart from cannular combustion chamber center line 38mm place.This coaxial jet nozzle can be premix nozzle or divergent nozzle, the perforate of premix nozzle head sealing long tube wall, and fuel gas is in air air chamber and air blending; Divergent nozzle is the coaxial jet form, the sealing of head perforate long tube wall, and head stays 5mm and jet air blending to enter cannular combustion chamber then at a high speed.
In cannular combustion chamber, air is injected in the cannular combustion chamber at a high speed by 12 jet pipes that are periphery, the burner inner liner head center is a tubular recirculation zone structure, because the existence of tubular recirculation zone, product refluxes from the center, near nozzle, be blended into and do not fire in the reactant, make it reach the fuel self-ignition temperature.The reactant of dilution high temperature is after the self-ignition time delay through fuel, and the even layout formula that forms no obvious flame front at the rear portion, combustion chamber is burnt.
Described tubular return-flow structure is replaceable, and in order to capacity of returns and recirculation zone size in the control cannular combustion chamber, the head recirculating zone structure of different length can change backflow blending amount, thereby in the size of controlling the recirculating zone.This tubular return-flow structure utilizes the burner inner liner cover plate of cannular combustion chamber and the gap between the air air chamber to fix, and need not welding, this tubular return-flow structure head recirculation zone internal diameter Φ 50mm, and length is respectively 30mm, 50mm, 70mm.
Fuel nozzle can be changed, thereby carries out the even blending of nozzle exit fuel and air (premixed combustion) respectively, fuel and air part blending (diffusion combustion) different flameless combustion experiment in main reaction region.
Below in conjunction with specific embodiment, and with reference to accompanying drawing, the present invention is described in more detail.
Fig. 1 is the flow process schematic diagram of fluid in the model combustion chamber.5 is the burner inner liner profile of cannular combustion chamber, and different with traditional burner inner liner is, there is tubular recirculation zone structure in head, and the nozzle annular is evenly arranged in around the head tubular recirculation zone.1 is the air flow trace, and counter-flow air enters burner inner liner after at first combustion chamber wall surface being cooled off; 2 is the fuel flow trace, and fuel and air enter burner inner liner at same position, and fuel and air enter the mode of burner inner liner can use the premix mode, can adopt diffusion way, and these all do not have influence to the flameless combustion institutional framework.3 is the flow trace of main flow combustion gas in the combustion chamber, and 4 are the flow trace of backflow combustion gas, and the backflow combustion gas forms the gaseous mixture of the poor fuel of high temperature in inlet vicinity blending track 3, behind a segment distance, form flameless combustion at the beginning of 4 tracks.
Fig. 2 partly cuts open schematic diagram for the Flameless combuster three-dimensional.The model combustion chamber mainly is made up of four parts: 8 are the detachable fuel air chamber; 7 is the air air chamber, and 23 fuel nozzles pass 8 and enter in 7; 6 is the burner inner liner part, and air enters in the air air chamber 7 by the double-layer flame barrel structure of burner inner liner part 6, then in the inner layer sleeve that enters burner inner liner part 6; 9 are the blending section, and the design air blending hole can be studied the influence of dilution air for exit flow field.
Fig. 3 is a nonflame model combustion chamber rear view, and burner inner liner is made up of three parts, and 11 is outer wall, and internal diameter is 146mm; 12 is inner layer tube wall, and internal diameter is 100mm; 13 is burner inner liner head cover plate; Air enters cannular combustion chamber from 4 holes shown in the label 10, bore dia Φ 10mm.
Fig. 4 is the structural representation of replaceable head return-flow structure.14 is the tubular return-flow structure.Tubular return-flow structure 14 can be changed, and length is respectively 30mm, 50mm, 70mm.Tubular return-flow structure 14 is clipped in the middle by burner inner liner head cover plate 13 and air air chamber head cover plate 15, does not adopt welding procedure.
Fig. 5 is the structural representation of air air chamber, and the air air chamber adopts stainless steel material, the argon arc welding.The air air chamber is made up of with air nozzle 19 air air chamber head cover plate 15, air air chamber rear portion cover plate 16, air gas chamber outer wall 17, impact cooling orifice plate 18.Air impacts cooling by 18 pairs of tubular return-flow structures 14 of orifice plate after entering from air air chamber head cover plate 15, enters in the burner inner liner part 6 by air nozzle 19 then.
Fig. 6 is the structural representation of fuel air chamber, and the fuel air chamber is mainly by fuel gas room cover plate 21, the outdoor wall 20 of fuel gas, and the indoor wall 22 of fuel gas is formed.Wherein, have 6 screwed holes on the outdoor wall 20 of fuel gas, be used for fixing with air air chamber 7, whole fuel air chamber can dismounting and change.
Fig. 7 is the schematic diagram of exchangeable nozzle structure, and 23 is the replaceable fuel nozzle.If the employing diffusion scheme, the long tube wall sealing of nozzle 23, head perforate; If adopt the premix scheme, the long tube wall of nozzle 23 is opened a series of apertures, and head is shut.Fuel mixes in advance with air in air air chamber 7 like this, and air air chamber 7 has in fact just become pre-mixing chamber.
Use the flameless combustion CFD analog result of the inventive method: in order to check the design achievement of this invention, respectively numerical simulation has been carried out in diffusion and two kinds of operating modes of premix in this combustion chamber, assess the cost in order to save, calculate 1/12 of Flameless combuster, adopt periodic boundary condition, so still can simulate the working condition of whole combustion chamber.
Fig. 8, Fig. 9 are respectively the computation structure schematic diagrames of diffusion structure of the present invention, pre-mixed configuration.24 are the fuel gas inlet, and 25 is air intake, and 27 are premix gas inlet, and 26 and 28 is computational fields.Computational fields 26 and 28 side wall surface adopt periodic boundary condition.Numerical simulation and dimensional structure ratio of the present invention are 1: 1.
Figure 10, Figure 11 are respectively axial VELOCITY DISTRIBUTION isopleth profile under two kinds of nozzle situations, can see, because the existence of head return-flow structure, the center has produced tangible recirculation zone, in this zone, high temperature gases recirculating is realized flameless combustion thereby reach ignition temperature with the mutual blending of fresh product of not firing near nozzle.
Figure 12 is a high temperature gases recirculating situation head temperature dyeing trace distribution map of the present invention, being used for the surface distributes near the fluid trace the nozzle, can see that smoke backflow with the mixture that does not fire the blending phenomenon has taken place near jet expansion, this explanation, the structure that the present invention proposes can effectively realize flameless combustion.
Figure 13, Figure 14 are two kinds of axial temperature profile figure under the burner scheme.Can see that Temperature Distribution is obviously different with the diffusion combustion premixed combustion, flame has produced the lifting phenomenon, and has formed monoblock type flame, and maximum temperature also descends to some extent.
The present invention has also calculated the situation of pollutant, through calculating, though the divergent nozzle scheme, premix burner scheme, NO
XDischarging all below 10ppm, is lower than the diffusion combustion form.Owing to high effluxvelocity, also avoided the tempering problem of premixed combustion simultaneously; Owing to be the monoblock type burning, also avoided the thermal acoustic oscillation problem.
In sum, the present invention has high stability, extremely oligosaprobic characteristics for the burning of low heat value hydrogen-rich fuel in the gas-turbine combustion chamber has proposed effective solution.Avoided simultaneously present main flow combustion with reduced pollutants mode be applied in deficiency on the low heat value hydrogen-rich fuel, be that a kind of burning institutional framework and structure thereof of novel combustion chamber realizes.
Above-described specific embodiment; purpose of the present invention, technical scheme and beneficial effect are further described; institute is understood that; the above only is specific embodiments of the invention; be not limited to the present invention; within the spirit and principles in the present invention all, any modification of being made, be equal to replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (12)
1, a kind of flameless combustion institutional framework that is applied to gas-turbine combustion chamber, it is characterized in that, this structure is evenly arranged a plurality of coaxial jet nozzles an end ring shape of cannular combustion chamber, and center arrangement tubular return-flow structure at the even a plurality of jet nozzles arranged of this annular, no auxiliary air participates in burning in the cannular combustion chamber, the air that participates in reaction arranges that from cannular combustion chamber an end of jet nozzle enters, position relation between the nozzle that the utilization annular is evenly arranged and the tubular return-flow structure of center arrangement, form a large amount of backflow high-temperature flue gas and fresh air blending, improve the temperature of air and air is diluted, this diluted high temperature air runs into fuel generation spontaneous combustion, form the high degree of dispersion reaction zone, in gas-turbine combustion chamber, realize flameless combustion.
2, the flameless combustion institutional framework that is applied to gas-turbine combustion chamber according to claim 1, it is characterized in that, air and fuel are injected in the combustion chamber at a high speed by a plurality of coaxial jet nozzles, do not adopt air cyclone and fuel swirl device, guarantee jet penetration, make the reactant high-speed jet go into the combustion zone of cannular combustion chamber.
3, the flameless combustion institutional framework that is applied to gas-turbine combustion chamber according to claim 1, it is characterized in that, utilize even nozzle of arranging of annular and the relative position relation between the tubular return-flow structure, reaction finishes the center line backflow of back high-temperature flue gas along cannular combustion chamber, and near air enters the cannular combustion chamber air intake radially to external diffusion, with reactant generation blending.
4, the flameless combustion institutional framework that is applied to gas-turbine combustion chamber according to claim 1, it is characterized in that, because the tubular return-flow structure exists, flame stabilization is in the zone of distance nozzle certain distance, and concrete distance size depends on the laminar flame spread speed of effluxvelocity and fuel gas.
5, the flameless combustion institutional framework that is applied to gas-turbine combustion chamber according to claim 1, it is characterized in that, flame region is a monoblock type distribution flame, there is not obvious flame front, there is not obvious high-temperature area, do not need to take the design of auxiliary air, the air that participates in reaction all arranges that from cannular combustion chamber an end of jet nozzle enters.
6, a kind of Flameless combuster of realizing the described flameless combustion institutional framework of claim 1 is characterized in that, this Flameless combuster comprises:
Be positioned at dismountable fuel air chamber that this Flameless combuster one end is used to provide fuel;
The air air chamber of fixedlying connected with this fuel air chamber;
End is positioned at the fuel air chamber, and front end is positioned at cannular combustion chamber, and runs through evenly a plurality of coaxial jet nozzles of layout of this air air chamber, annular;
The tubular return-flow structure of the center arrangement of a plurality of jet nozzles of evenly arranging in this annular;
The cannular combustion chamber of fixedlying connected with this air air chamber;
Be used for the design air blending hole, the research dilution air is for the influence of exit flow field, and the afterbody blending section of fixedlying connected with this cannular combustion chamber.
7, Flameless combuster according to claim 6 is characterized in that, described cannular combustion chamber adopts the double-layer flame barrel structure, and this double-layer flame barrel structure inside is reaction zone, is air duct between two-layer, a cooling effect.
8, Flameless combuster according to claim 6 is characterized in that, described tubular return-flow structure is replaceable, in order to capacity of returns and recirculation zone size in the control cannular combustion chamber.
9, Flameless combuster according to claim 6 is characterized in that, described coaxial jet nozzle is 12, internal diameter equals 12mm, be evenly distributed on around the tubular return-flow structure, riding position is at cannular combustion chamber one end, apart from cannular combustion chamber center line 38mm place.
10, Flameless combuster according to claim 6 is characterized in that, described coaxial jet nozzle is pre-mix nozzle or divergent nozzle, the perforate of premix nozzle head sealing long tube wall, and fuel gas is in air air chamber and air blending; Divergent nozzle is the coaxial jet form, the sealing of head perforate long tube wall, and head stays 5mm and jet air blending to enter cannular combustion chamber then at a high speed.
11, Flameless combuster according to claim 6, it is characterized in that, described tubular return-flow structure is replaceable, utilize the burner inner liner cover plate of cannular combustion chamber and the gap between the air air chamber to fix, need not welding, this tubular return-flow structure head recirculation zone internal diameter Φ 50mm, length is respectively 30mm, 50mm, 70mm.
12, Flameless combuster according to claim 6, it is characterized in that, air enters between the double-layer flame barrel structure from the cannular combustion chamber rear portion by four holes, through entering air chamber by trench structure behind the burner inner liner zone between the double-layer flame barrel structure inside and outside wall, by annular oriffice the head recirculating zone structure that stretches in the air chamber is impacted cooling then, enter cannular combustion chamber by air nozzle.
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| CN200810116374A CN101625130A (en) | 2008-07-09 | 2008-07-09 | Flameless combustion organizational structure and flameless combustion chamber for realizing structure |
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| CN200810116374A CN101625130A (en) | 2008-07-09 | 2008-07-09 | Flameless combustion organizational structure and flameless combustion chamber for realizing structure |
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| CN102384473A (en) * | 2010-08-25 | 2012-03-21 | 中国科学院工程热物理研究所 | Flameless trapped vortex burner for gas turbine |
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| CN105465831A (en) * | 2016-01-12 | 2016-04-06 | 西北工业大学 | Gas turbine combustion chamber provided with double flame tubes and flame holder |
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| CN112815357A (en) * | 2020-12-24 | 2021-05-18 | 北航（四川）西部国际创新港科技有限公司 | Flame tube structure of combustion chamber and combustion chamber |
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| CN102384473B (en) * | 2010-08-25 | 2013-07-31 | 中国科学院工程热物理研究所 | Flameless trapped vortex burner for gas turbine |
| CN102384473A (en) * | 2010-08-25 | 2012-03-21 | 中国科学院工程热物理研究所 | Flameless trapped vortex burner for gas turbine |
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| CN103062804B (en) * | 2011-10-21 | 2016-05-18 | 通用电气公司 | Formula nozzle and method are penetrated in expansion for hypoxemia fuel nozzle assembly |
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| CN107576502B (en) * | 2017-08-10 | 2019-11-12 | 中国北方发动机研究所(天津) | A kind of turbocharger test platform combustion chamber with mixing section |
| CN109238722B (en) * | 2018-09-30 | 2023-11-21 | 中国科学院工程热物理研究所 | Multi-head test piece test bed for combustion chamber of gas turbine |
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| CN111059573A (en) * | 2019-12-31 | 2020-04-24 | 新奥能源动力科技（上海）有限公司 | Gas turbine combustion chamber and gas turbine |
| CN112815357A (en) * | 2020-12-24 | 2021-05-18 | 北航（四川）西部国际创新港科技有限公司 | Flame tube structure of combustion chamber and combustion chamber |
| CN113671875A (en) * | 2021-08-20 | 2021-11-19 | 中国联合重型燃气轮机技术有限公司 | IGCC and method of controlling IGCC |
| CN113671875B (en) * | 2021-08-20 | 2023-05-12 | 中国联合重型燃气轮机技术有限公司 | IGCC and control method of IGCC |
| CN113983496A (en) * | 2021-09-23 | 2022-01-28 | 中国联合重型燃气轮机技术有限公司 | Nozzle, combustion chamber and gas turbine |
| CN115628449A (en) * | 2022-12-20 | 2023-01-20 | 中国空气动力研究与发展中心超高速空气动力研究所 | Gas-liquid coaxial centrifugal nozzle in assembly structure |
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