CN104266226B - A kind of porous spray combustion system of poor fuel - Google Patents

A kind of porous spray combustion system of poor fuel Download PDF

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Publication number
CN104266226B
CN104266226B CN201410361344.5A CN201410361344A CN104266226B CN 104266226 B CN104266226 B CN 104266226B CN 201410361344 A CN201410361344 A CN 201410361344A CN 104266226 B CN104266226 B CN 104266226B
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fuel
propellant spray
combustion
nozzle
main burner
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CN201410361344.5A
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CN104266226A (en
Inventor
李珊珊
井文明
吕煊
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China United Heavy Gas Turbine Technology Co Ltd
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Beijing Huatsing Gas Turbine and IGCC Technology Co Ltd
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Abstract

The invention belongs to gas turbine field, discloses a kind of porous spray combustion system of poor fuel, including:Nozzle on duty, annular positioned at combustion system center are evenly arranged in multiple main burners on the outside of nozzle on duty and the cap and guide bushing that are arranged on the outside of multiple main burners, the inlet and outlet of multiple main burners are sector, propellant spray device is equipped with multiple main burners, propellant spray hole is equipped with the propellant spray device;The inner or outer side of the equally distributed multiple main burners of annular is provided with fuel supply channel, and the fuel supply channel is connected with multiple propellant spray devices respectively, and at least one fuel nozzle is connected with the fuel supply channel.The present invention effectively solves the problem in terms of topology layout, Cooling Design in the prior art;Equivalent proportion distribution curve is changed, reduces the scope in burner inner liner overtemperature area, enhances the combustibility of main burner.

Description

A kind of porous spray combustion system of poor fuel
Technical field
The present invention relates to gas turbine technology field, more particularly to a kind of porous spray combustion system of poor fuel.
Background technology
Fig. 1 is a kind of typical head of combustion chamber structure, and arrangement of nozzles on duty is in center, the uniform cloth of multiple main burner annulars It is placed on the outside of nozzle on duty.Nozzle on duty sets the steady flame plate of taper, mesh using diffusion or premixed combustion mode, nozzle downstream on duty The flame stability for being to strengthen whole head of combustion chamber, nozzle on duty undertake igniting and main flame stabilization function.From end cap Multiple fuel nozzles are drawn, main burner axis region is deeply corresponded to respectively, radial propellant spray is set on fuel nozzle Device and cyclone 34, spray fuel simultaneously strengthen blending.When main burner uses this constructional device, equivalent proportion is typically along main burner Axis is symmetrical, during primary nozzle design, if high (such as Fig. 2 a) close to nozzle equivalent proportion on duty, close to burner inner liner wall The equivalent proportion increase in region, causes burner inner liner wall area overtemperature;If the equivalent proportion close to nozzle on duty is low (such as Fig. 2 b), value Class nozzle the firing action of main burner is not easy to realize, cause main burner burning it is insufficient;Fig. 2 c are ideal equivalent proportions Distribution, but such case generally requires to strengthen blending by way of the swirl strength for increasing nozzle, and increase nozzle eddy flow is strong Degree, can cause the recirculating zone in nozzle downstream, and then cause discharged nitrous oxides to increase.
Fig. 3 is that a kind of main burner outlet is circular structure, and this structure has the problem of cooling difficulty is larger.Fig. 4 is A kind of main burner outlet is fan-shaped structure, and the structure cooling range is less, also needs to set at main burner in terms of structure design One circle fan group section.
In the prior art, the main burner outlet equivalent proportion close to combustion system axis region is relatively low, and combustibility is poor, Ignition temperature is low, can not light laterally, causes the flow burning close to burner inner liner wall area insufficient, pollutant concentration compared with It is high.
The content of the invention
(1) technical problems to be solved
The technical problem to be solved in the present invention is:It is not reasonable to solve existing combustion system nozzle equivalent proportion distribution, to Light outside and be not easy to realize, cause outside to be burnt the problem of insufficient, pollutant concentration is higher.
(2) technical scheme
In order to solve the above-mentioned technical problem, the invention provides a kind of porous spray combustion system of poor fuel, including:It is located at The nozzle on duty at combustion system center, annular are evenly arranged in multiple main burners on the outside of nozzle on duty and are arranged on multiple Cap and guide bushing on the outside of main burner, the inlet and outlet of multiple main burners are sector, in multiple main burners Provided with propellant spray device, propellant spray hole is equipped with the propellant spray device;The equally distributed multiple main burners of annular Inner or outer side be provided with fuel supply channel, the fuel supply channel is connected with multiple propellant spray devices respectively, At least one fuel nozzle is connected with the fuel supply channel.
Wherein, the propellant spray hole includes being radially distributed in the multipair small of propellant spray device both sides along combustion system Hole, the diameter of each pair aperture are identical;Along combustion system radial direction from inside to outside, the diameter of aperture is along gradually increase.
Wherein, N number of propellant spray hole, N number of propellant spray hole edge combustion are equipped with each propellant spray device Burning system radially outward, is designated as 1,2 ... N, the corresponding region 1 that N number of propellant spray hole control be present, 2 ... N, often successively The equivalent proportion for arranging propellant spray hole control area is φ12…φn
Main burner average equivalent ratio is
Wherein, φ1Compare φaverHigh 5%~15%, φnCompare φaverLow 5%~15%;From φ1To φn, the equivalent proportion Stairway degression.
Wherein, multiple main burners include at least two layers, and every layer includes multiple main burners, and adjacent two layers main burner interlocks Arrangement.
Wherein, every layer of main burner is equipped with fuel supply channel, and one or more is connected with the fuel supply channel Fuel nozzle.
Wherein, adjacent two layers main burner is connected on same fuel supply channel, is connected with the fuel supply channel One or more fuel nozzle.
Wherein, after the fuel supply channel of adjacent two layers main burner is converged by pipeline, it is connected with fuel nozzle, the combustion Material jet pipe includes one or more.
(3) beneficial effect
Above-mentioned technical proposal has the following advantages that:A kind of porous spray combustion system of poor fuel of the present invention, by duty Annular region between nozzle and main burner sets primary nozzle fuel jet pipe, avoids the occurrence of along the centrosymmetric eddy flow area of main burner Domain;Main burner import is arranged to fan-shaped, and the annular compartment structure formed with nozzle on duty and cap is engaged, convenient layout;It is main Jet expansion is arranged to fan-shaped, reduces the area for needing cooled region, simultaneously because the structural integrity that import is fan-shaped, simplifies The design of main burner inlet and outlet group section;Main burner equivalent proportion gradually reduces along nozzle radial direction on duty, there is provided in rank The main burner outlet equivalent proportion distribution of ladder distribution, can be by main burner layer by layer when nozzle on duty has igniting with flame stabilization function Light, improve the combustibility of main burner;Main burner facilitates nozzle point on duty close to the region equivalent proportion highest of nozzle on duty Fire main burner;Main burner is minimum close to the region equivalent proportion of burner inner liner wall, and ignition temperature is minimum, reduces the overtemperature model of burner inner liner Enclose.
Brief description of the drawings
Fig. 1 is the head of combustion chamber structural representation of prior art;
Fig. 2 a are the common equivalent proportion distribution map one of main burner in the prior art;
Fig. 2 b are the common equivalent proportion distribution map two of main burner in the prior art;
Fig. 2 c are the common equivalent proportion distribution map three of main burner in the prior art;
Fig. 3 is the main burner export structure schematic diagram one of prior art;
Fig. 4 is the main burner export structure schematic diagram two of prior art;
Fig. 5 is the main burner schematic cross-section of the embodiment of the present invention one;
Fig. 6 is the main burner schematic rear view of the embodiment of the present invention one;
Fig. 7 a are the design equivalent proportion distribution map of the main burner of the embodiment of the present invention one;
Fig. 7 b are the true equivalent proportion distribution map one of the main burner of the embodiment of the present invention one outlet;
Fig. 7 c are the true equivalent proportion distribution map two of the main burner of the embodiment of the present invention one outlet;
Fig. 8 is the main burner export structure schematic diagram of the embodiment of the present invention two.
Wherein, 1, propellant spray hole;2nd, nozzle on duty;3rd, main burner;31st, fuel nozzle;32nd, fuel supply channel;33、 Propellant spray device;34th, cyclone;35th, main burner exports;4th, cap;5th, guide bushing.
Embodiment
With reference to the accompanying drawings and examples, the embodiment of the present invention is described in further detail.Implement below Example is used to illustrate the present invention, but is not limited to the scope of the present invention.
Embodiment one:
As shown in Figure 5 and Figure 6, a kind of porous spray combustion system of poor fuel of the present invention includes:Positioned at combustion system center Nozzle on duty 2, annular is evenly arranged in multiple main burners 3 in the outside of nozzle on duty 2 and is arranged on outside multiple main burners 3 Cap 4, guide bushing 5 and the burner inner liner of side;Nozzle 2 on duty is set using diffusion or premixed combustion mode, the downstream of nozzle 2 on duty The steady flame plate of taper is put, undertakes igniting and main flame stabilization function;The inlet and outlet of multiple main burners 3 are sector, with master The circular geometry that nozzle 3 is imported and exported is adapted, convenient layout;Propellant spray device is equipped with multiple main burners 3 33, propellant spray hole 1 is equipped with the propellant spray device 33;Between the nozzle on duty 2 and main burner 3 or main burner 3 Be provided with fuel supply channel 32 in annular region between cap 4, the fuel supply channel 32 respectively with multiple combustions Material injection device 33 is connected, and at least one fuel nozzle 31 is connected with the fuel supply channel 32;Fuel nozzle 31 is from poor The end cap of the porous spray combustion system of fuel is drawn.
Annular region adverse current flow upstream of the air between cap 4 and guide bushing 5, enter through the import of main burner 3 In main burner 3, fuel introduces from the end cap of combustion system, the fuel supply channel 32 in downstream is entered through fuel nozzle 31, then The propellant spray device 33 being connected with fuel supply channel 32 is flowed into, is sprayed by propellant spray hole 1, with flowing through propellant spray dress The air mixing in 33 main burner 3 is put, gaseous mixture is formed in the passage of main burner 3, main burner 3 is flowed out, by nozzle point on duty Combustion.
The propellant spray hole 1 includes being radially distributed in the multipair small of the both sides of propellant spray device 33 along combustion system Hole, the diameter of each pair aperture are identical;Along combustion system radial direction from inside to outside, the diameter of aperture gradually increases.
Preferably, the injection device that burns is 4~12, and the both sides of each downstream direction of propellant spray device 33, which are opened, waits directly The propellant spray hole 1 in footpath, the number per side propellant spray hole 1 is between 4~8,1 a diameter of 1mm~2mm of propellant spray hole, Ensure to mix with air more uniform with the higher depth of penetration when fuel sprays burning injection device;Fuel nozzle 31 Number is arranged to 4~8, to ensure fuel gas stream uniformity;The number of fuel nozzle 31 is consistent with the number of main burner 3, ensures The uniformity in fuel gas stream direction;Fuel supply channel 32 is arranged at identical axial location with propellant spray device 33.
By controlling the aperture in propellant spray hole 1 on the porous spray combustion system main burner 3 of the poor fuel, regulation often row's combustion The equivalent proportion of annular ring cavity where expecting spray orifice 1;The equivalent proportion of main burner 3 gradually reduces along combustion system radial direction;Specifically Process is as follows:
N number of propellant spray hole 1 is set on each propellant spray device 33 of main burner 3, and N number of propellant spray hole 1 is along combustion Burning system radially outward, is designated as 1,2 ... N successively, corresponding region 1,2 ... the N that N number of propellant spray hole 1 controls to be present,
Wherein, i-th of propellant spray hole 1 is a diameter ofArea isDischarge coefficient isDensity isFuel injection speed isThe corresponding control area i of propellant spray hole 1 ventilation area isFlow Coefficient isDensity isFuel injection speed isThe then hole control area of i-th of propellant spray hole 1 Equivalent proportion be
Wherein,(F/A)stoicFor the chemical equivalent oil-gas ratio of fuel, it is fixed into for one kind Point the fuel value be definite value, such as CH4 (F/A)stoic=0.58.When fuel characteristic and the timing of 3 structure of main burner one, lead to The equivalent proportion for often arranging teasehole control area can be controlled by crossing the area (diameter) in control propellant spray hole 1, often arrange propellant spray The equivalent proportion of the control area of hole 1 is φ12…φn
The average equivalent ratio of main burner 3 is
Wherein, φ1Compare φaverHigh 5%~15%, φnCompare φaverLow 5%~15%, and from φ1To φn, equivalent proportion rank Ladder successively decreases, final to ensure that overall average equivalent proportion is constant.Fig. 7 a are design equivalent proportion distribution, due in the premixed channel of main burner 3, Each layer fuel blending diffusion, Fig. 7 b, 7c are that true main burner 3 exports the distribution of 35 equivalent proportions.
In the prior art, main burner 3 export 35 equivalent proportions it is relatively low close to combustion system axis region, combustibility compared with Difference, ignition temperature are low, it is impossible to and outside fuel is lighted laterally, causes the flow burning close to burner inner liner wall area insufficient, Pollutant concentration is higher.
Main burner 3 of the present invention exports 35 equivalent proportions and is distributed in iridescent type, i.e., main burner 3 is divided into N layers region, every layer of region Equivalent proportion gradually reduces, and in specific works, nozzle 2 on duty is ignited (being lighted by other external equipments, such as igniter) first, so Nozzle 2 on duty successively lights main burner 3 afterwards, and main burner 3 facilitates nozzle 2 on duty close to the region equivalent proportion highest of nozzle 2 on duty Light main burner 3;The equivalent proportion of main burner 3 gradually reduces, and ensures that the internal layer fuel quantity close to ignition point does not have relatively low be not easy The region lighted, ensure that the every layer of fuel of main burner 3 can be ignited and stable burning, burning fully, improve main burner 3 Efficiency of combustion, significantly reduce pollutant concentration.
Embodiment two:
The present embodiment and embodiment one are essentially identical, and difference is:The main burner 3 includes at least two layers, and every layer includes The main burner 3 of multiple annular spreads, the outlet interlaced arrangement (such as Fig. 8) of adjacent two layers main burner 3.Every layer of main burner 3 is equipped with Fuel supply channel 32, one or more fuel nozzle 31 is connected with the fuel supply channel 32, when the total chi of combustion system When very little larger, such layout type can be used, the oversized of main burner 3 is avoided, is unfavorable for processing and installs.
Embodiment three:
The present embodiment and embodiment two are essentially identical, and difference is:Adjacent two layers main burner 3 is connected to same by pipeline On fuel supply channel 32, one or more fuel nozzle 31 is connected with the fuel supply channel 32, this layout type can Effectively to solve the problems, such as insufficient space between main burner, structural complexity is reduced.
Example IV:
The present embodiment and embodiment two are essentially identical, and difference is:The fuel supply channel 32 of adjacent two layers main burner 3 is logical After piping convergence, it is connected with fuel nozzle 31, the fuel nozzle 31 includes one or more, and this layout type can be reduced The number of plies of fuel nozzle 31, excessive fuel nozzle 31 is avoided to bring inconvenience installation.
As can be seen from the above embodiments, the present invention around nozzle 2 on duty by setting multiple main burners 3, main burner 3 It is divided into N layers region, every layer of region equivalent proportion gradually reduces, and nozzle 2 on duty successively lights main burner 3, ensures every layer of main burner 3 The burning that fuel can be stablized, burning is abundant, significantly reduces pollutant concentration;By nozzle 2 on duty and main burner 3 it Between annular region set the fuel nozzle 31 of main burner 3, avoid the occurrence of along the centrosymmetric eddy flow region of main burner;Main burner 3 Import is arranged to fan-shaped, and the annular compartment structure formed with nozzle 2 on duty and cap 4 is engaged, convenient layout;Main burner 3 goes out Mouth 35 is arranged to fan-shaped, reduces the area for needing cooled region, simultaneously because the structural integrity that import is fan-shaped, simplifies master Nozzle 3 imports and exports the design of group section;The equivalent proportion of main burner 3 gradually reduces along the radial direction of nozzle 2 on duty, there is provided in ladder The main burner 3 of distribution exports the distribution of 35 equivalent proportions, can be 3 layers by main burner when nozzle 2 on duty has igniting with flame stabilization function Layer is lighted, and improves the combustibility of main burner 3;Main burner 3 facilitates on duty close to the region equivalent proportion highest of nozzle 2 on duty Nozzle 2 lights main burner 3;Main burner 3 is minimum close to the region equivalent proportion of burner inner liner wall, and ignition temperature is minimum, reduces flame The overtemperature scope of cylinder.
The present invention effectively solves the problem in terms of topology layout, Cooling Design in the prior art;Change equivalent proportion distribution Curve, the scope in burner inner liner overtemperature area is reduced, enhance the combustibility of main burner 3.
Described above is only the preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art For member, without departing from the technical principles of the invention, some improvement and replacement can also be made, these improve and replaced Also it should be regarded as protection scope of the present invention.

Claims (6)

1. a kind of porous spray combustion system of poor fuel, including:Nozzle on duty (2), annular positioned at combustion system center are uniformly The multiple main burners (3) being arranged on the outside of nozzle on duty (2) and the cap (4) being arranged on the outside of multiple main burners (3) and lead Flow bushing (5), it is characterised in that the inlet and outlet of multiple main burners (3) are sector, in multiple main burners (3) Provided with propellant spray device (33), propellant spray hole (1), the propellant spray hole are equipped with the propellant spray device (33) (1) the multipair aperture for being radially distributed in propellant spray device (33) both sides along combustion system, the diameter phase of each pair aperture are included Together;Along combustion system radial direction from inside to outside, the diameter of aperture gradually increases;The equally distributed multiple main burners (3) of annular Inner or outer side is provided with fuel supply channel (32), the fuel supply channel (32) respectively with multiple propellant spray devices (33) connect, at least one fuel nozzle (31) is connected with the fuel supply channel (32).
2. the porous spray combustion system of poor fuel as claimed in claim 1, it is characterised in that each propellant spray device (33) N number of propellant spray hole (1) is equipped with, N number of propellant spray hole (1) radially outward, is remembered successively along combustion system For 1,2 ... N, the corresponding region 1 that N number of propellant spray hole (1) control be present, 2 ... N, propellant spray hole (1) control zone is often arranged The equivalent proportion in domain is followed successively by φ12…φn
Main burner (3) average equivalent ratio is
Wherein, φ1Compare φaverHigh 5%~15%, φnCompare φaverLow 5%~15%;From φ1To φn, the equivalent proportion ladder Successively decrease;ρfFor the fuel density of i-th of propellant spray hole (1), UfFor the fuel injection of i-th of propellant spray hole (1) Speed, AfFor the fuel circulation area of i-th of propellant spray hole (1), CdfFor the combustion of i-th of propellant spray hole (1) Stream coefficient of discharge;ρAirFor the atmospheric density of i-th of propellant spray hole (1), UAirFor i-th of propellant spray hole (1) Air injection rate, AAirFor corresponding propellant spray hole (1) control area i ventilation area, CdAirFor i-th of institute State the air mass flow coefficient in propellant spray hole (1), (F/A)stoicFor the chemical equivalent oil-gas ratio of fuel;
Wherein,DfFor the diameter of i-th of propellant spray hole (1).
3. the porous spray combustion system of poor fuel as claimed in claim 2, it is characterised in that multiple main burner (3) bags Include at least two layers, every layer includes multiple main burners (3), adjacent two layers main burner (3) interlaced arrangement.
4. the porous spray combustion system of poor fuel as claimed in claim 3, it is characterised in that every layer of main burner (3) is equipped with Fuel supply channel (32), one or more fuel nozzle (31) is connected with the fuel supply channel (32).
5. the porous spray combustion system of poor fuel as claimed in claim 3, it is characterised in that adjacent two layers main burner (3) is even It is connected on same fuel supply channel (32), one or more fuel nozzle is connected with the fuel supply channel (32) (31)。
6. the porous spray combustion system of poor fuel as claimed in claim 3, it is characterised in that adjacent two layers main burner (3) After fuel supply channel (32) is converged by pipeline, be connected with fuel nozzle (31), the fuel nozzle (31) include one or More.
CN201410361344.5A 2014-07-25 2014-07-25 A kind of porous spray combustion system of poor fuel Active CN104266226B (en)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3228939B1 (en) * 2016-04-08 2020-08-05 Ansaldo Energia Switzerland AG Method for combusting a fuel, and combustion appliance
JP6934359B2 (en) * 2017-08-21 2021-09-15 三菱パワー株式会社 Combustor and gas turbine with the combustor

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1464959A (en) * 2001-06-07 2003-12-31 三菱重工业株式会社 Combustor
CN101023302A (en) * 2004-09-10 2007-08-22 三菱重工业株式会社 Gas turbine combustor
CN102345879A (en) * 2010-07-30 2012-02-08 通用电气公司 Fuel nozzle and assembly and gas turbine comprising the same
CN102444911A (en) * 2010-10-11 2012-05-09 通用电气公司 Combustor with lean pre-nozzle fuel injection system
CN204114995U (en) * 2014-07-25 2015-01-21 北京华清燃气轮机与煤气化联合循环工程技术有限公司 A kind of poor fuel porous spray combustion system

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH06137559A (en) * 1992-10-26 1994-05-17 Mitsubishi Heavy Ind Ltd Combustor for gas turbine
JP3300754B2 (en) * 1998-02-09 2002-07-08 三菱重工業株式会社 Combustor

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1464959A (en) * 2001-06-07 2003-12-31 三菱重工业株式会社 Combustor
CN101023302A (en) * 2004-09-10 2007-08-22 三菱重工业株式会社 Gas turbine combustor
CN102345879A (en) * 2010-07-30 2012-02-08 通用电气公司 Fuel nozzle and assembly and gas turbine comprising the same
CN102444911A (en) * 2010-10-11 2012-05-09 通用电气公司 Combustor with lean pre-nozzle fuel injection system
CN204114995U (en) * 2014-07-25 2015-01-21 北京华清燃气轮机与煤气化联合循环工程技术有限公司 A kind of poor fuel porous spray combustion system

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Patentee before: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd.