EP2116769A1 - Brennstofflanze für einen Brenner - Google Patents

Brennstofflanze für einen Brenner Download PDF

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Publication number
EP2116769A1
EP2116769A1 EP08155968A EP08155968A EP2116769A1 EP 2116769 A1 EP2116769 A1 EP 2116769A1 EP 08155968 A EP08155968 A EP 08155968A EP 08155968 A EP08155968 A EP 08155968A EP 2116769 A1 EP2116769 A1 EP 2116769A1
Authority
EP
European Patent Office
Prior art keywords
lance
burner
fuel
shaft
nozzle
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Withdrawn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
EP08155968A
Other languages
English (en)
French (fr)
Inventor
Richard Carroni
Madhavan Narasimhan Poyyapakkam
Michal Tadeusz Bialkowski
Mark Andrew Willetts
Jian-xin CHEN
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Priority to EP08155968A priority Critical patent/EP2116769A1/de
Publication of EP2116769A1 publication Critical patent/EP2116769A1/de
Withdrawn legal-status Critical Current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
    • F23D14/46—Details, e.g. noise reduction means
    • F23D14/62—Mixing devices; Mixing tubes
    • F23D14/64—Mixing devices; Mixing tubes with injectors
    • 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
    • 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
    • F23R3/34—Feeding into different combustion zones
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07021—Details of lances

Definitions

  • the present invention relates to a lance for the introduction of fuel into a burner, in particular into a premix burner, of a second combustion chamber of a gas turbine plant with sequential combustion having a first and a second combustion chamber.
  • the invention relates, moreover, to a burner equipped with a lance of this type.
  • a lance may be provided for the introduction of gaseous and/or liquid fuel, for example for pilot operation or for stabilizing the combustion in a combustion space of the combustion chamber.
  • a lance of this type as kwon for example from the DE4326802 may have a base and a shaft projecting perpendicularly from the latter. With the lance installed in the burner, the base extends perpendicularly with respect to a main flow direction prevailing in the burner, while the shaft runs parallel to this main flow direction.
  • the shaft is equipped with at least one nozzle.
  • a plurality of nozzles arranged in a row along the shaft in the circumferential direction may be provided, which are in each case configured such that they have for the fuel a main injection direction which is radial with respect to the main flow direction of the burner.
  • the lance shaft usually has a cylindrical configuration.
  • a fuel gas containing hydrogen gas in a conventional burner, it is usually natural gas which is injected as gaseous fuel with the aid of the lance, in modern burners there is provision for using a fuel gas containing hydrogen gas.
  • a fuel gas of this type may be produced, for example, from long-chain hydrocarbons by means of partial oxidation. This artificially produced fuel gas may therefore also be designated as synthesis gas or syngas.
  • a fuel gas containing hydrogen gas also additionally contains carbon monoxide gas.
  • Such a fuel gas is distinguished, as compared with conventional natural gas, by a significantly increased reactivity which leads to higher reaction temperatures, lower ignition temperatures and higher flame velocities.
  • the invention as characterized in the claims, is concerned with the problem of specifying for a lance of the type initially mentioned or for a burner equipped with it an improved embodiment which is distinguished, in particular, in that it can be operated with a fuel gas containing hydrogen gas or syngas and at the same time has improved intermixing and increased operating reliability.
  • the invention is based on the general idea of configuring an axial portion of the lance conically, specifically such that the shaft portion tapers with an increasing distance from the base. It has been shown that, with the aid of such a conical portion, the mixing behavior of fuel and oxidizer gas in the burner can be influenced positively.
  • the fuel can be introduced in a directed manner axially, radially and in the circumferential direction in the region of the conical portion, this likewise being advantageous for intensive intermixing.
  • An embodiment is particularly expedient, therefore, in which the at least one nozzle, in particular each nozzle, is arranged on the conical portion.
  • the respective nozzle By the respective nozzle being mounted on the conical portion, the respective nozzle, which typically is formed only by an outlet orifice, possesses a main injection direction which is no longer solely oriented radially, as in the case of a cylindrical shaft, but also has an axial direction component. Since the main injection direction is thus inclined toward the main flow direction of the burner, the risk of a contacting of the fuel gas with a burner wall can be reduced, which would lead to an enrichment of fuel gas in the region of the burner wall. Correspondingly, this measure leads to an improved intermixing of fuel gas and oxidizer gas.
  • the at least one nozzle has an annular orifice extending as a slit-shaped opening around the conical part of the shaft.
  • a plurality of nozzles may be arranged, distributed, on the conical portion. It is conceivable, for example, to have a row or a plurality of rows of nozzles or outlet orifices arranged next to one another in the circumferential direction. Additionally or alternatively, a plurality of nozzles may also be arranged, spaced apart from one another axially, on the conical portion. With nozzles or outlet orifices spaced apart from one another in the axial direction, the conicity of the conical portion brings about a variation in the distance between the respective outlet orifice and a longitudinal mid-axis of the shaft. If only because of this, an improved three-dimensional propagation of the fuel can be achieved within the burner.
  • the lance may be equipped with an introduction device, with the aid of which an inert protective gas can be introduced into the burner.
  • a protective gas of this type which, for example, may be nitrogen, early contacting between the fuel gas and oxidizer gas can be avoided, with the result that the ignition timepoint can be delayed. The propagation of the fuel over the entire throughflow cross section of the burner can thereby be assisted.
  • additional injection means for injection of the liquid fuel have to be provided.
  • these means are nozzles for the injection of liquid fuel, which are arranged in the lance and for example inject fuel in the main flow direction from the downstream end of the shaft, as known for example from the DE4326802 .
  • a burner 1 comprises a burner wall 2 which laterally delimits a mixing space 3.
  • an oxidizer gas flow in particular an air flow, enters the burner 1 or the mixing space 3.
  • a gas flow leaves the burner 1 or the mixing space 3 and can enter a combustion space of a combustion chamber, not shown.
  • the burner 1 forms an integral part of said combustion chamber which itself forms an integral part of a gas turbine plant.
  • the burner 1 has a lance 6, with the aid of which a gaseous fuel can be introduced into the burner 1 or into the mixing space 3.
  • the fuel gas is preferably a fuel gas containing a hydrogen gas.
  • the shaft 8 is positioned preferably centrally in the burner 1 or in the mixing space 3 with the aid of the base 7, specifically such that a longitudinal mid-axis 9 of the shaft 8 extends at least approximately parallel to a main flow direction 10 which, when the burner 1 is in operation, is established by virtue of the flow of oxidizer gas through it.
  • the shaft 8 projects from the base 7 essentially at right angles.
  • the base 7 extends essentially perpendicularly with respect to the main flow direction 10.
  • an inclined installation in the flow direction or opposite to the flow direction may also be envisaged.
  • the lance 6 is fastened to the burner wall 2.
  • the shaft 8 has a conical portion 11 which tapers with an increasing distance from the base 7.
  • the lance 6 or the shaft 8 has at least one nozzle 12, through which the gaseous fuel can be injected into the mixing space 3.
  • the respective nozzle is formed in each case by its outlet orifice 13 incorporated into the conical portion 11.
  • Forming the respective nozzle 12 on the conical portion 11 necessarily results for the respective nozzle 12 in a main injection direction which has both a radial and an axial component.
  • the respective nozzle 12 forms a conical spray jet, the longitudinal mid-axis of which defines the main injection direction.
  • the oxidizer gas flow By the main injection directions being inclined, as compared with a purely radial orientation, the oxidizer gas flow, even at higher flow velocities, can give rise for the injected fuel to a sufficient deflection of the fuel flow toward the main flow direction 10. A concentration of fuel gas in the region of the burner wall 2 can thereby be avoided.
  • the measures shown thus assist an intensive intermixing between the fuel gas and the oxidizer gas.
  • the conical portion 11 may have a plurality of nozzles 12 or a plurality of outlet orifices 13 which are arranged, distributed, on the conical portion 11.
  • at least one row 14 on the conical portion 11 may be formed, which has a plurality of nozzles 12 or outlet orifices 13 arranged next to one another in the circumferential direction and which extends annularly and coaxially with respect to the longitudinal mid-axis 9 of the shaft 8.
  • the plurality of such rows 14 spaced apart axially from one another may be formed on the conical portion 11.
  • the fuel can be injected, staged, into the burner 1.
  • the nozzles 12 or their outlet orifices 13 within the respective rows 14 are located on different radii or at different distances with respect to the longitudinal mid-axis 9. As a result, as uniform a distribution of the fuel as possible can be achieved within a throughflow cross section of the burner 1 or of the mixing space 3.
  • a multiplicity of nozzles 12 may be arranged, distributed over a large area, on the conical portion 11.
  • the outlet orifices 13 of these nozzles 12 may in this case possess comparatively small cross sections.
  • the lance 6 may be equipped here with micronozzles 12, in which the diameters of the outlet orifices 13 are in the order of a millimeters. Penetration into the oxidizer flow of the fuel jet from these small nozzles is limited. As a result the region of the burner into which fuel can be injected with these nozzles depends on the radius on the tapered section of the lance from which they inject fuel.
  • the nozzles 12 or their outlet orifices 13 are preferably dimensioned such that the fuel stream is reliably freed from the outer surface of the lance 6 and can be picked up by the oxidizer flow.
  • two rows of nozzles 12 or outlet orifices 13 are formed on the shaft 8 or on its conical portion 11.
  • the upstream row 14 exhibits a circumferentially irregular arrangement of adjacent nozzles 12 or outlet orifices 13.
  • individual adaption to varying flow ratios in the circumferential direction can be implemented within the burner 1.
  • the burner 1 is per se expediently configured symmetrically, as a result of which as homogeneous a flow profile as possible is to be achieved within the mixing space 3.
  • the base 7 of the lance 6 forms a significant flow obstacle, the wake of which impairs the symmetry within the flow profile.
  • the arrangement of the individual nozzles 12 or of the individual outlet orifices 13 may be coordinated with the wake such that a concentration of fuel in the wake subjected to a less pronounced throughflow is avoided.
  • Fig. 4 it is likewise possible to equip the conical portion 11 with nozzles 12 which differ from one another in terms of their outlet orifices 13.
  • an outlet orifice 13' which is arranged approximately centrally within the conical portion 11 and which obviously has a larger cross-sectional area than the other outlet orifices 13 of the other nozzles 12.
  • an individual adaptation of the fuel injection to the flow profile in the burner 1 can be implemented.
  • the possibilities described, and other possibilities, for adapting the fuel injection to the flow profile of the burner 1 serve in each case the purpose of achieving within the mixing space 3, over the entire throughflow cross section of the burner 1, as uniform and as even a distribution of the fuel gas in the oxidizer gas as possible.
  • Fig. 5 shows a further embodiment in which at least one nozzle 12 with an annular outlet orifice 13 is arranged on the conical portion 11.
  • two nozzles 12 of this type with annular outlet orifices 13 are arranged, spaced apart axially from one another, on the conical portion 11.
  • the conical portion 11 in each case is truncated, with the truncated end called top 15, remote from the base 7, of the shaft 8. In this case, therefore, the conical portion 11 extends essentially completely from the base 7 as far as the top 15.
  • the conical portion 11 has a frustoconical configuration, so that, here, the top 15 lies in a plane which extends perpendicularly with respect to the longitudinal mid-axis 9.
  • the top 15 may have a convex configuration, particularly in the manner of a spherical segment. Pointed cones without truncation are also conceivable.
  • the top 15 of the shaft 8 is free of nozzles 12 for gaseous fuel and free of outlet orifices 13 gaseous fuel.
  • a nozzle incorporated into the conical portion has to be understood to be a nozzle in or on the conical surface of the conical and not as nozzle in or on the top of the conical portion.
  • liquid fuel is typically injected from a nozzle arranged in the center of the top 15 of the conical portion 11, which forms the downstream end of the lance.
  • a fuel feed 16 which is indicated here by an arrow, is provided for the introduction of fuel via the lance 6.
  • This fuel feed 16 guides the gaseous fuel to the lance 6 and, within the lance 6, to the outlet orifices 13 of the individual nozzles 12.
  • a protective gas feed 17, likewise indicated by an arrow, may be provided. This feeds to the burner 1 or the lance 6 an inert protective gas which leads within the lance 6 to at least one outlet orifice of a nozzle.
  • the first row 14 upstream with respect to the main flow direction 10 or a plurality of upstream rows 14 to the protective gas feed 17, while the other, downstream rows 14 are assigned to the fuel gas feed 16.
  • the nozzles assigned to the protective gas feed 17 are expediently arranged and/or configured such that the protective gas delays the intermixing of the fuel gas with oxidizer gas and therefore the spontaneous ignition of the mixture.
  • the protective gas is introduced by the nozzles into the burner 1 expediently such that the oxidizer gas flowing in the burner 1 first impinges onto the inert protective gas before it impinges onto the fuel gas.
  • This can for example realized by a concentric arrangement of nozzles, where the fuel gas is injected in the center nozzle and inert gas is injected by an annular nozzle, which surrounds the fuel nozzle.
  • this is realized by injecting protective gas through a nozzle upstream of the fuel injection nozzle.
  • the direct contact between oxidizer gas and fuel in the stagnation region on the upstream side of the fuel jets can be avoided for example by well directed inert protective gas injected directly into this region.
  • the momentum of the inert gas can be used to increase the fuel penetration into the oxidizer gas flow.
  • a suitable inert protective gas is, for example, nitrogen gas (N 2 ).
  • N 2 nitrogen gas
  • the burner 1 proposed here and the lance 6 proposed here are especially suitable for use with a fuel gas containing hydrogen gas, since they allow for the particular features of this highly reactive fuel gas, such as, for example, a higher reaction temperature, lower spontaneous ignition temperature and higher flame velocity.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
EP08155968A 2008-05-09 2008-05-09 Brennstofflanze für einen Brenner Withdrawn EP2116769A1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP08155968A EP2116769A1 (de) 2008-05-09 2008-05-09 Brennstofflanze für einen Brenner

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08155968A EP2116769A1 (de) 2008-05-09 2008-05-09 Brennstofflanze für einen Brenner

Publications (1)

Publication Number Publication Date
EP2116769A1 true EP2116769A1 (de) 2009-11-11

Family

ID=40342799

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EP08155968A Withdrawn EP2116769A1 (de) 2008-05-09 2008-05-09 Brennstofflanze für einen Brenner

Country Status (1)

Country Link
EP (1) EP2116769A1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013139914A1 (en) * 2012-03-23 2013-09-26 Alstom Technology Ltd Combustion device
CN109654537A (zh) * 2018-12-07 2019-04-19 中国航发沈阳发动机研究所 一种中心燃料喷嘴
EP3486570A1 (de) * 2017-11-15 2019-05-22 Ansaldo Energia Switzerland AG Sekundäre brennkammerphase für eine sequentielle gasturbinenbrennkammer

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4326802A1 (de) 1993-08-10 1995-02-16 Abb Management Ag Brennstofflanze für flüssige und/oder gasförmige Brennstoffe sowie Verfahren zu deren Betrieb
EP0769657A2 (de) * 1995-10-19 1997-04-23 General Electric Company Vormischbrenner für eine Gasturbinenbrennkammer mit niedriger Schadstoffemission
US6357237B1 (en) * 1998-10-09 2002-03-19 General Electric Company Fuel injection assembly for gas turbine engine combustor
US6543235B1 (en) * 2001-08-08 2003-04-08 Cfd Research Corporation Single-circuit fuel injector for gas turbine combustors
US20040006991A1 (en) * 2002-07-15 2004-01-15 Peter Stuttaford Fully premixed secondary fuel nozzle with improved stability and dual fuel capability
WO2007051698A1 (de) * 2005-11-04 2007-05-10 Alstom Technology Ltd Brennerlanze

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4326802A1 (de) 1993-08-10 1995-02-16 Abb Management Ag Brennstofflanze für flüssige und/oder gasförmige Brennstoffe sowie Verfahren zu deren Betrieb
EP0769657A2 (de) * 1995-10-19 1997-04-23 General Electric Company Vormischbrenner für eine Gasturbinenbrennkammer mit niedriger Schadstoffemission
US6357237B1 (en) * 1998-10-09 2002-03-19 General Electric Company Fuel injection assembly for gas turbine engine combustor
US6543235B1 (en) * 2001-08-08 2003-04-08 Cfd Research Corporation Single-circuit fuel injector for gas turbine combustors
US20040006991A1 (en) * 2002-07-15 2004-01-15 Peter Stuttaford Fully premixed secondary fuel nozzle with improved stability and dual fuel capability
WO2007051698A1 (de) * 2005-11-04 2007-05-10 Alstom Technology Ltd Brennerlanze

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013139914A1 (en) * 2012-03-23 2013-09-26 Alstom Technology Ltd Combustion device
US9568198B2 (en) 2012-03-23 2017-02-14 General Electric Technology Gmbh Combustion device having a distribution plenum
EP3486570A1 (de) * 2017-11-15 2019-05-22 Ansaldo Energia Switzerland AG Sekundäre brennkammerphase für eine sequentielle gasturbinenbrennkammer
CN109654537A (zh) * 2018-12-07 2019-04-19 中国航发沈阳发动机研究所 一种中心燃料喷嘴

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