EP2169307A1 - Buse à combustible - Google Patents

Buse à combustible Download PDF

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Publication number
EP2169307A1
EP2169307A1 EP08017127A EP08017127A EP2169307A1 EP 2169307 A1 EP2169307 A1 EP 2169307A1 EP 08017127 A EP08017127 A EP 08017127A EP 08017127 A EP08017127 A EP 08017127A EP 2169307 A1 EP2169307 A1 EP 2169307A1
Authority
EP
European Patent Office
Prior art keywords
nozzle
fuel
flower
fuel nozzle
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Withdrawn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
EP08017127A
Other languages
German (de)
English (en)
Inventor
Giacomo Colmegna
Ulrich Wörz
Jaap Dr. 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
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP08017127A priority Critical patent/EP2169307A1/fr
Priority to PCT/EP2009/062460 priority patent/WO2010034819A1/fr
Priority to US13/121,461 priority patent/US8959922B2/en
Priority to CN200980138271.0A priority patent/CN102165258B/zh
Priority to EP13002599.2A priority patent/EP2629011A1/fr
Priority to EP09783434.5A priority patent/EP2329189B1/fr
Priority to JP2011528347A priority patent/JP5312599B2/ja
Priority to RU2011117317/06A priority patent/RU2506497C2/ru
Publication of EP2169307A1 publication Critical patent/EP2169307A1/fr
Priority to JP2012259959A priority patent/JP5487280B2/ja
Withdrawn legal-status Critical Current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
    • F23D14/02—Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone
    • F23D14/04—Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone induction type, e.g. Bunsen burner
    • F23D14/08—Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone induction type, e.g. Bunsen burner with axial outlets at the burner head
    • 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
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00002—Gas turbine combustors adapted for fuels having low heating value [LHV]

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 in an annular manner.
  • 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 premix burners, it is particularly 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 classic turbine fuels natural gas and petroleum, which are essentially hydrocarbon compounds The flammable 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.
  • An inhomogeneous mixture of fuel and air results in a certain distribution of the flame temperatures in the combustion region. 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 in an air flow, which the fuel nozzle substantially annular surrounds injected, wherein 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 into the air stream is feasible.
  • 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. This is caused by the flower-shaped configuration of the first nozzle pipe section according to the invention. Due to the flower-shaped configuration of the first nozzle pipe section according to the invention, a second flow field, ie the desired calculable turbulence, is additionally formed on the profile trailing edges, which in turn improves the thorough mixing. This is also particularly advantageous if the fuel flow and the air flow have different flow velocity.
  • the flower-shaped embodiment of the first nozzle tube section according to the invention further allows coaxial injection of the fuel into the airflow. As a result, the undesirable in the prior art 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 to a closed flower scar.
  • the flower scar preferably runs pointedly in the direction of flow.
  • 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 is 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. However, it is still possible coaxial inflow of the fuel into the air flow, whereby only a negligible pressure loss arises despite the improved mixing.
  • 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, ie, the exit of the fuel from the fuel nozzle takes place without unwanted and unpredictable Verwirblept. 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 pipe section is present, to which the first nozzle pipe section adjoins in the flow direction, wherein the second nozzle pipe section tapers in the flow direction.
  • the sawtooth-like first nozzle pipe section connects in the horizontal direction to the second nozzle pipe 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 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 also with, for example, natural gas in Vormischmodus can be operated.
  • 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 according to the invention.
  • 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 shaped like a flower 6 in such a way 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 when the air stream 8 and the synthesis gas stream have different flow rates.
  • 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 fuel nozzle according to the invention, here in the FIG. 3 with b as compared with a prior art fuel nozzle, here, for example, an annular prior art tapered nozzle tube (shown in Figs FIG. 3 indicated with a).
  • the non-mixing degree is indicated on the y-axis.
  • the fuel nozzle according to the invention has a higher mixing, but due to the coaxial injection with lower pressure loss.
  • Fig. 4 shows a further 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 simple-conical or double-conical. This has the advantage that a smooth transition between the two streams is ensured. 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 notches 16 are mounted, which are opposite the profile trailing edges 20 and in their Radial width substantially coincident with these. 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 a 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 tapered in the flow direction (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 is of considerable advantage, since thus desired turbulences are generated in the flow field, which in turn improves the mixing between synthesis gas and air stream 8.
  • 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.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
EP08017127A 2008-09-29 2008-09-29 Buse à combustible Withdrawn EP2169307A1 (fr)

Priority Applications (9)

Application Number Priority Date Filing Date Title
EP08017127A EP2169307A1 (fr) 2008-09-29 2008-09-29 Buse à combustible
PCT/EP2009/062460 WO2010034819A1 (fr) 2008-09-29 2009-09-25 Buse à combustible
US13/121,461 US8959922B2 (en) 2008-09-29 2009-09-25 Fuel nozzle with flower shaped nozzle tube
CN200980138271.0A CN102165258B (zh) 2008-09-29 2009-09-25 燃料喷嘴
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
JP2011528347A JP5312599B2 (ja) 2008-09-29 2009-09-25 燃料ノズル
RU2011117317/06A RU2506497C2 (ru) 2008-09-29 2009-09-25 Топливная форсунка
JP2012259959A JP5487280B2 (ja) 2008-09-29 2012-11-28 燃料ノズル

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08017127A EP2169307A1 (fr) 2008-09-29 2008-09-29 Buse à combustible

Publications (1)

Publication Number Publication Date
EP2169307A1 true EP2169307A1 (fr) 2010-03-31

Family

ID=40056380

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08017127A Withdrawn EP2169307A1 (fr) 2008-09-29 2008-09-29 Buse à combustible

Country Status (1)

Country Link
EP (1) EP2169307A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104368463A (zh) * 2014-11-25 2015-02-25 天津大学 一种能够增强射流混合效果的喷嘴
US9435537B2 (en) 2010-11-30 2016-09-06 General Electric Company System and method for premixer wake and vortex filling for enhanced flame-holding resistance

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB173901A (fr) *
US2121948A (en) * 1935-05-11 1938-06-28 Western Electric Co Burner
WO1999006767A1 (fr) * 1997-07-31 1999-02-11 Siemens Aktiengesellschaft Brûleur
US20040146821A1 (en) * 2003-01-29 2004-07-29 Joshi Mahendra Ladharam Slotted injection nozzle and low NOx burner assembly
US20050097889A1 (en) * 2002-08-21 2005-05-12 Nickolaos Pilatis Fuel injection arrangement
EP1645807A1 (fr) 2004-10-11 2006-04-12 Siemens Aktiengesellschaft Brûleur pour gas à faible capacité calorifique et méthode d'utilisation d'un tel brûleur
EP1892472A1 (fr) * 2006-08-14 2008-02-27 Siemens Aktiengesellschaft Système de combustion en particulier pour une turbine à gaz

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB173901A (fr) *
US2121948A (en) * 1935-05-11 1938-06-28 Western Electric Co Burner
WO1999006767A1 (fr) * 1997-07-31 1999-02-11 Siemens Aktiengesellschaft Brûleur
US20050097889A1 (en) * 2002-08-21 2005-05-12 Nickolaos Pilatis Fuel injection arrangement
US20040146821A1 (en) * 2003-01-29 2004-07-29 Joshi Mahendra Ladharam Slotted injection nozzle and low NOx burner assembly
EP1645807A1 (fr) 2004-10-11 2006-04-12 Siemens Aktiengesellschaft Brûleur pour gas à faible capacité calorifique et méthode d'utilisation d'un tel brûleur
EP1892472A1 (fr) * 2006-08-14 2008-02-27 Siemens Aktiengesellschaft Système de combustion en particulier pour une turbine à gaz

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9435537B2 (en) 2010-11-30 2016-09-06 General Electric Company System and method for premixer wake and vortex filling for enhanced flame-holding resistance
CN104368463A (zh) * 2014-11-25 2015-02-25 天津大学 一种能够增强射流混合效果的喷嘴

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