EP2629011A1 - Buse de combustible - Google Patents

Buse de combustible Download PDF

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Publication number
EP2629011A1
EP2629011A1 EP13002599.2A EP13002599A EP2629011A1 EP 2629011 A1 EP2629011 A1 EP 2629011A1 EP 13002599 A EP13002599 A EP 13002599A EP 2629011 A1 EP2629011 A1 EP 2629011A1
Authority
EP
European Patent Office
Prior art keywords
fuel
nozzle
flower
synthesis gas
tube
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP13002599.2A
Other languages
German (de)
English (en)
Inventor
Giacomo Colmegna
Ulrich Wörz
Jaap Van Kampen
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from EP08017127A external-priority patent/EP2169307A1/fr
Priority claimed from EP08017128A external-priority patent/EP2169308A1/fr
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP13002599.2A priority Critical patent/EP2629011A1/fr
Publication of EP2629011A1 publication Critical patent/EP2629011A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • 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
    • F23D14/20—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone
    • F23D14/22—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone with separate air and gas feed ducts, e.g. with ducts running parallel or crossing each other
    • 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
    • F23D14/48—Nozzles
    • F23D14/58—Nozzles characterised by the shape or arrangement of the outlet or outlets from the nozzle, e.g. of annular configuration
    • 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

Definitions

  • the invention relates to a fuel nozzle, comprising a nozzle tube and a nozzle outlet opening, wherein the nozzle tube is in communication with a fuel supply line for supplying a fuel into the nozzle tube, wherein the fuel from the nozzle outlet opening is injected into an air flow, which surrounds the fuel nozzle substantially annular , And a reaching to the nozzle outlet opening first nozzle tube section is formed flower-shaped in such a way that a substantially coaxial injection of the fuel in the air flow is feasible, wherein the nozzle outlet opening has a closed, conical flower scar.
  • synthesis gas can in principle be made from solid, liquid and gaseous educts.
  • synthesis gas can in principle be made from solid, liquid and gaseous educts.
  • coal gasification biomass gasification
  • coke gasification
  • premix combustion is becoming increasingly important also in the combustion of low calorific gases.
  • Premix burners typically include a premix zone in which air and fuel are mixed before passing the mixture into a combustion chamber. There, the mixture burns, producing a hot gas under elevated pressure. This hot gas is forwarded to the turbine. In connection with the operation of Vormischbrennern it comes Above all, it is important to keep the nitrogen oxide emissions low and to avoid a flashback.
  • Synthesis gas premix burners are characterized by the fact that synthesis gases are used as fuel in them. Compared with the traditional turbine fuels natural gas and petroleum, which consist essentially of hydrocarbon compounds, the combustible components of the synthesis gas are essentially carbon monoxide and hydrogen. Depending on the gasification process and the overall plant concept, the calorific value of the synthesis gas is about 5 to 10 times smaller than that of natural gas.
  • the quality of mixing between synthesis gas and combustion air at the flame front is an important influencing variable for avoiding temperature peaks and thus for minimizing the formation of thermal nitrogen oxides.
  • a spatially good mixture of combustion air and synthesis gas is particularly difficult due to the high volume flows of required synthesis gas and the correspondingly large spatial extent of the mixing area.
  • the lowest possible production of nitrogen oxides is an essential requirement for combustion, in particular for combustion in the gas turbine plant of a power plant.
  • the formation of nitrogen oxides increases exponentially rapidly with the combustion flame temperature. In an inhomogeneous mixture of fuel and air results in a certain distribution of flame temperatures in the combustion area. The maximum temperature of such a distribution determined by the said exponential relationship of nitrogen oxide formation and flame temperature significantly the amount of undesirable nitrogen oxides formed.
  • the object of the invention is to provide a fuel nozzle, in particular for the supply of synthesis gas, which leads to a lower nitrogen oxide formation during combustion.
  • a fuel nozzle comprising a nozzle tube and a nozzle outlet opening, wherein the nozzle tube is in communication with a fuel supply line for supplying a fuel into the nozzle tube, wherein the fuel from the nozzle outlet opening into an air stream, which the fuel nozzle substantially annular surrounds, is injected, and a reaching to the nozzle outlet opening first nozzle tube section is shaped like a flower in such a way that a substantially coaxial injection of the fuel in the air flow is feasible, wherein the nozzle outlet opening has a closed, conical flower scar.
  • the invention is based on the fact that, especially for large volume flows of fuel such as synthesis gas, large injection sequences must be made available, which is associated with high pressure losses. Furthermore, however, in order to achieve good NOx values, especially the premix mode with a good mixing is necessary. However, the swirling elements used in the prior art and the inflow of the fuel stream transverse to the air flow lead to a significantly undesirable pressure loss, which in turn leads to poor NOx values.
  • the invention is based on the recognition that an increase in the contact area between the synthesis gas stream causes a significant improvement in the mixing. This effect is particularly important if the fuel flow and the air flow have different flow velocity. Due to the flower-shaped design of first nozzle pipe section this is caused. Due to the flower-shaped configuration of the first nozzle pipe section, a second flow field, ie desired calculable turbulences, is additionally formed on the profile trailing edges, which in turn improves mixing. This is also particularly advantageous if the fuel flow and the air flow have different flow velocity.
  • the flower-shaped embodiment according to the invention of the first nozzle tube section further enables coaxial injection of the fuel into the air flow. As a result, undesirably high pressure losses are avoided. This allows operation of the nozzle in the premix mode, even at high volume flows of fuel, such as this is the case with synthesis gas.
  • the nozzle outlet opening of the fuel nozzle now has a closed, conically formed flower scar.
  • the flower scar which is arranged symmetrically around the center of the designed as a flower nozzle orifice, a continuous area mixing of the fuel and the air is enforced. This is especially for the fuel, which would be passed through the central region of the nozzle exit opening, an advantage.
  • Due to the design of the nozzle outlet opening with a flower hub quasi the contact surface between fuel and air is further increased, which has a positive effect on the mixing.
  • the flower scar preferably runs pointedly in the direction of flow.
  • the flower scar is double-conical.
  • boundary layer separation can be avoided and reduce the risk of flashback by return areas.
  • the flower scar has notches. These notches are attached to the flower hub in correspondence with the individual petals or in correspondence with the profile trailing edges. These notches essentially serve to provide a smooth passage for the fuel, i. the exit of the fuel from the fuel nozzle takes place without unwanted and unpredictable turbulence. Thus, boundary layer separation can be avoided and the risk of flashback by return areas can be reduced.
  • the notches are applied in a straight line in the direction of flow and / or twisted.
  • a swirl during the injection can be impressed on the air flow or the fuel flow.
  • the first nozzle pipe section preferably tapers in the flow direction. As a result, an increase in the flow rate of the fuel is achieved.
  • the flower shape of the first nozzle tube section is sawtooth-like. Predictable turbulences are formed in the flow field by the saw teeth, which causes a better mixing of the fuel with the air flow. However, since coaxial injection continues to be assured, no increase in pressure loss occurs in this embodiment of the fuel nozzle.
  • a second nozzle tube section may be present, to which the first nozzle tube section adjoins in the flow direction, wherein the second nozzle tube section tapers in the flow direction.
  • the sawtooth-like first nozzle tube section connects in the horizontal direction to the second nozzle tube section.
  • the sawtooth-like first nozzle tube section adjoins the second nozzle tube section inclined relative to the horizon. This increases the flow rate of the fuel.
  • the flower scar is connected to a substantially coaxial to the nozzle tube extending pipe for the supply of high calorific fuel and has at least one tangential and / or axial inlet opening.
  • the arrangement, the number, and the diameter of the inlet openings can vary. Since the high calorie fuel feed within the synthesis gas feed (high calorie fuel feed is annularly surrounded by the synthesis gas feed), these are preferably tangential and axial inlet ports, i. Holes.
  • both the inlet openings for high-calorie fuel and the feed itself only require a small diameter, since the volume flow of the high-calorie fuel is substantially lower than that of the synthesis gas. This fact contributes to the supply of high calorific fuel causing little or no disturbance in the air stream during synthesis gas operation.
  • the at least one tangential inlet opening is arranged on the flower web between two petals of the flower-shaped synthesis gas injection.
  • the fuel nozzle is present in a burner.
  • a burner This is in particular a synthesis gas burner operated in a premix mode.
  • the burner can be designed as a two- or multi-fuel burner, which can also be operated with, for example, natural gas in Vormischmodus.
  • the burner is present in a gas turbine.
  • the synthesis gas can in principle be made from solid, liquid and gaseous educts.
  • the coal gasification should be mentioned.
  • Coal is converted in a mixture of partial oxidation and gasification with water vapor to a mixture of CO and hydrogen.
  • the use of other solids such as biomass and coke should be mentioned in principle.
  • Different crude oil distillates can be used as the liquid reactants for synthesis gas.
  • the most important gaseous educt is natural gas.
  • Fig. 1 shows a fuel nozzle. This has a nozzle tube 2 and a nozzle outlet opening 10.
  • the nozzle tube 2 is in communication with a fuel supply line (not shown) which supplies fuel to the nozzle tube 2.
  • the fuel is injected from the nozzle outlet opening 10 into an air stream 8, which surrounds the fuel nozzle in an annular manner.
  • the reaching to the nozzle outlet opening 10 first nozzle tube section 4 is formed like a flower 6 and although such that a substantially coaxial injection of the fuel into the air stream 4 is feasible.
  • the synthesis gas is guided inside the nozzle tube 2.
  • Fig. 2 shows a cross section of such a nozzle outlet opening 10 with six individual flowers.
  • the number of flowers is mainly dependent on the individual burner types or gas turbine types and may vary.
  • the nozzle tube section 4 and the nozzle outlet opening 10 provide by their inventive flower-shaped configuration 6 a larger contact area between synthesis gas stream and air stream 8 ago.
  • an improved mixing between synthesis gas and air stream 8 is achieved without increased pressure loss.
  • This embodiment is particularly advantageous if the air stream 8 and the synthesis gas stream have different flow velocities.
  • this flower-shaped embodiment 6 has the significant advantage that a second flow field is formed, in particular at the profile trailing edges of the individual flowers. Here vortex structures are formed. This also contributes significantly to improving the mixing, especially when there is a significant difference in the flow rates of the synthesis gas and the air stream 8.
  • Fig. 3 shows by way of example as a diagram, the improved interference of a flower-shaped fuel nozzle, here in the FIG. 3 indicated at b, as compared to a fuel nozzle, here for example an annular, tapered nozzle tube according to the prior art (in FIG. 3 indicated with a).
  • the non-mixing degree is indicated on the y-axis.
  • the flower-shaped fuel nozzle has a higher mixing, but due to the coaxial injection with lower pressure loss.
  • Fig. 4 shows an embodiment of a fuel nozzle according to the invention. This has at the flower-shaped nozzle outlet opening 10 centrally a conical flower hub 14.
  • the flower hub 14 may be single conical or double conical be educated. This has the advantage that a smooth transition of the two streams is ensured in each other. Furthermore, this embodiment prevents a boundary layer separation or the formation of return flow areas, which can cause a flashback.
  • notches 16 can be made in the conical flower hub 14. These are advantageously on the one hand in their radial extension and attachment in accordance with the individual flowers attached, that is, the notch 16 and the flowers face each other. This achieves a smooth exit surface for the synthesis gas. On the other hand, further indentations 16 are provided, which lie opposite the profile trailing edges 20 and in their radial width essentially coincide with them. These achieve a smooth exit surface for the air flow 8.
  • the notches 16 may be rectilinear in the flow direction or wound so as to achieve a turbulence of the air or the fuel.
  • Fig. 5 shows an alternative fuel nozzle in which the flower shape has 8 tapered flowers, that is essentially formed like a sawtooth.
  • these saw teeth 22 are attached to a first pipe section 4.
  • This first pipe section 4 may have a constant pipe diameter in the flow direction (ie, the saw teeth 22 are substantially horizontal) or in Flow direction is tapered (ie the saw teeth 22 are inclined relative to the horizon line 26, Fig. 6 ).
  • a second pipe section 24, to which the first pipe section 4 adjoins in the flow direction, can be tapered in the direction of flow for better injection.
  • the design of the fuel nozzle with saw teeth 22 desired turbulence in the flow field to be generated, which in turn improves the mixing between synthesis gas and air stream 8.
  • Fig. 7 An embodiment of the inventive fuel nozzle with a second fuel supply is shown. Since the synthesis gas inlet openings must ensure a large volume flow, the fuel nozzle is formed in the shape of a flower 6 with respect to the synthesis gas according to the invention.
  • Tangential natural gas inlet openings 16 are placed between two petals 18.
  • the point of contact or the line of contact of two petals 18 with each other is referred to below as flower spike 19.
  • Fig. 7 has six tangential natural gas inlet openings 16 and an axial natural gas inlet openings 17. Depending on the burner and gas turbine, both the number and the arrangement may vary.
  • the natural gas inlet openings 16, 17 are essentially round, and can be produced by means of bores.
  • the synthesis gas supply and the flower-shaped synthesis gas inlet opening 6 as well as the natural gas supply 30 with the natural gas inlet 16,17 are designed so that a Pressure loss below 25 dp / p is achieved with the same heat input in terms of synthesis and natural gas.
  • Fig. 8 schematically shows the natural gas supply 30. Since the volume flow of natural gas is much lower than that for synthesis gas, the diameter of the natural gas supply 30 is substantially lower than the synthesis gas supply. In order to switch from synthesis gas to natural gas operation or vice versa, it is only necessary to interrupt the synthesis gas or natural gas supply 30. This can be achieved without hardware changes.
  • any other high-calorie burner material can be used, for example fuel oil.
  • the flower shape 6 of the synthesis gas inlet port is merely an example, other forms for syngas inlet port are also conceivable.
  • synthesis gas burners should be operable not only with a fuel, but possibly with different fuels, such as oil, natural gas and / or coal gas optional or even in combination to increase security of supply and flexibility in operation.
  • synthesis gas burners should be operable not only with a fuel, but possibly with different fuels, such as oil, natural gas and / or coal gas optional or even in combination to increase security of supply and flexibility in operation.
  • this invention it is possible to use the same nozzle for natural gas (or diluted natural gas) or synthesis gas. This simplifies the design of the burner and significantly reduces component components.
  • the fuel nozzle presented here is not limited only to the operation with synthesis gas, but it can be operated advantageously with any fuel. To emphasize this advantage especially with high-volume fuel flow.
  • the fuel nozzle according to the invention is particularly suitable in premix operation.

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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)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
EP13002599.2A 2008-09-29 2009-09-25 Buse de combustible Withdrawn EP2629011A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP13002599.2A EP2629011A1 (fr) 2008-09-29 2009-09-25 Buse de combustible

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
EP08017127A EP2169307A1 (fr) 2008-09-29 2008-09-29 Buse à combustible
EP08017128A EP2169308A1 (fr) 2008-09-29 2008-09-29 Alimentation en carburant et procédé d'injection du carburant
EP13002599.2A EP2629011A1 (fr) 2008-09-29 2009-09-25 Buse de combustible
EP09783434.5A EP2329189B1 (fr) 2008-09-29 2009-09-25 Buse à combustible

Related Parent Applications (2)

Application Number Title Priority Date Filing Date
EP09783434.5A Division-Into EP2329189B1 (fr) 2008-09-29 2009-09-25 Buse à combustible
EP09783434.5 Division 2009-09-25

Publications (1)

Publication Number Publication Date
EP2629011A1 true EP2629011A1 (fr) 2013-08-21

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EP13002599.2A Withdrawn EP2629011A1 (fr) 2008-09-29 2009-09-25 Buse de combustible
EP09783434.5A Not-in-force EP2329189B1 (fr) 2008-09-29 2009-09-25 Buse à combustible

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP09783434.5A Not-in-force EP2329189B1 (fr) 2008-09-29 2009-09-25 Buse à combustible

Country Status (6)

Country Link
US (1) US8959922B2 (fr)
EP (2) EP2629011A1 (fr)
JP (2) JP5312599B2 (fr)
CN (1) CN102165258B (fr)
RU (1) RU2506497C2 (fr)
WO (1) WO2010034819A1 (fr)

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US20130244187A1 (en) * 2012-03-19 2013-09-19 Honeywell International Inc. HIGH EFFICIENCY LOW NOx EMISSION BURNER APPARATUS
US9200808B2 (en) * 2012-04-27 2015-12-01 General Electric Company System for supplying fuel to a late-lean fuel injector of a combustor
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US20140144141A1 (en) * 2012-11-26 2014-05-29 General Electric Company Premixer with diluent fluid and fuel tubes having chevron outlets
FR3007801B1 (fr) * 2013-07-01 2018-01-05 Arianegroup Sas Element d'injection
US20160061452A1 (en) * 2014-08-26 2016-03-03 General Electric Company Corrugated cyclone mixer assembly to facilitate reduced nox emissions and improve operability in a combustor system
US20170328568A1 (en) * 2014-11-26 2017-11-16 Siemens Aktiengesellschaft Fuel lance with means for interacting with a flow of air and improve breakage of an ejected liquid jet of fuel
CN104566467B (zh) * 2014-12-31 2018-02-23 北京华清燃气轮机与煤气化联合循环工程技术有限公司 一种防回火型喷嘴
CN104764016A (zh) * 2015-04-01 2015-07-08 深圳智慧能源技术有限公司 文丘里混合器的喷嘴结构
CN104791788B (zh) * 2015-04-01 2017-12-08 深圳智慧能源技术有限公司 高效文丘里燃烧器
US10392284B2 (en) * 2015-04-16 2019-08-27 Praxair Technology, Inc. Combustion method for low velocity reactant streams
CN105757716B (zh) * 2016-02-22 2019-04-30 中国科学院工程热物理研究所 一种用于预混燃烧的喷嘴、喷嘴阵列和燃烧器
JP6634909B2 (ja) * 2016-03-18 2020-01-22 三浦工業株式会社 ベンチュリノズル及び該ベンチュリノズルを備える燃料供給装置
CN105698172B (zh) * 2016-04-11 2017-11-28 徐州科融环境资源股份有限公司 一种花瓣形分级燃烧燃气低氮燃烧器
CN106402857A (zh) * 2016-08-31 2017-02-15 北京北机机电工业有限责任公司 一种用于喷射装置的点火喷嘴
CN107023828B (zh) * 2017-05-22 2024-04-16 北京醇能科技有限公司 一种用于气态燃料混合器的喷嘴
US10927804B2 (en) 2017-06-07 2021-02-23 Ford Global Technologies, Llc Direct fuel injector
US20190056108A1 (en) * 2017-08-21 2019-02-21 General Electric Company Non-uniform mixer for combustion dynamics attenuation
CN107843467A (zh) * 2017-11-16 2018-03-27 南京航空航天大学 适用于安全检查的射流式气体感应系统及方法
CN107957066B (zh) * 2017-12-22 2024-07-02 上海齐耀热能工程有限公司 点火枪
CN110801948A (zh) * 2018-08-05 2020-02-18 大连理工大学 一种带扭转式8字形喷孔的喷嘴
EP3689818A1 (fr) * 2019-01-31 2020-08-05 Casale Sa Réacteur et procédé d'oxydation partielle
CN111442266A (zh) * 2020-05-08 2020-07-24 中国科学院工程热物理研究所 一体化设计的富氢燃烧室头部
DE102020003357B4 (de) 2020-06-03 2024-06-27 SDT Industrial Technology UG (haftungsbeschränkt) Die Vorrichtung zur Luft-Desinfektion

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Publication number Priority date Publication date Assignee Title
WO2016068922A1 (fr) * 2014-10-30 2016-05-06 Siemens Aktiengesellschaft Veilleuse et procédé pour la stabilisation d'une flamme de veilleuse dans une chambre de combustion soumise à une dynamique de combustion
WO2017003649A1 (fr) * 2015-06-30 2017-01-05 General Electric Company Ensemble injecteur de carburant
US10458655B2 (en) 2015-06-30 2019-10-29 General Electric Company Fuel nozzle assembly

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EP2329189B1 (fr) 2016-01-13
JP2012504219A (ja) 2012-02-16
RU2011117317A (ru) 2012-11-10
JP5312599B2 (ja) 2013-10-09
WO2010034819A1 (fr) 2010-04-01
CN102165258A (zh) 2011-08-24
EP2329189A1 (fr) 2011-06-08
JP5487280B2 (ja) 2014-05-07
US20110232289A1 (en) 2011-09-29
US8959922B2 (en) 2015-02-24
RU2506497C2 (ru) 2014-02-10
JP2013040769A (ja) 2013-02-28
CN102165258B (zh) 2014-01-22

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