EP1336800B1 - Verfahren zur Verminderung verbrennungsgetriebener Schwingungen in Verbrennungssystemen sowie Vormischbrenner zur Durchführung des Verfahrens - Google Patents

Verfahren zur Verminderung verbrennungsgetriebener Schwingungen in Verbrennungssystemen sowie Vormischbrenner zur Durchführung des Verfahrens Download PDF

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Publication number
EP1336800B1
EP1336800B1 EP03405031.0A EP03405031A EP1336800B1 EP 1336800 B1 EP1336800 B1 EP 1336800B1 EP 03405031 A EP03405031 A EP 03405031A EP 1336800 B1 EP1336800 B1 EP 1336800B1
Authority
EP
European Patent Office
Prior art keywords
burner
lance
combustion
fuel
end region
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.)
Expired - Lifetime
Application number
EP03405031.0A
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German (de)
English (en)
French (fr)
Other versions
EP1336800A1 (de
Inventor
Ephraim Gutmark
Christian Oliver Paschereit
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
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Filing date
Publication date
Application filed by Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP1336800A1 publication Critical patent/EP1336800A1/de
Application granted granted Critical
Publication of EP1336800B1 publication Critical patent/EP1336800B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • 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
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F23D11/40—Mixing tubes or chambers; Burner heads
    • F23D11/402—Mixing chambers downstream of the nozzle
    • 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
    • F23D14/72—Safety devices, e.g. operative in case of failure of gas supply
    • F23D14/74—Preventing flame lift-off
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D17/00—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel
    • F23D17/002—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel gaseous or liquid fuel
    • 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
    • F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2210/00—Noise abatement
    • 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
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators

Definitions

  • the invention relates to a premix burner for reducing combustion-driven vibrations within a combustion system, in particular one with low acoustic damping, as is frequently encountered in combustion chambers of flow engines.
  • turbomachinery such as gas turbine plants
  • combustion-driven thermoacoustic oscillations arise at the burner as fluid mechanical Instabilticianswellen and lead to eddies that greatly affect the entire combustion process and lead to unwanted periodic heat releases within the combustion chamber.
  • pressure fluctuations of high amplitude can lead to undesirable effects, such as a high mechanical load of the combustion chamber, increased NO x emissions by inhomogeneous combustion or even to extinguishment of the flame within the combustion chamber.
  • Thermoacoustic oscillations are based, at least in part, on flow instabilities of the burner flow, which manifest themselves in coherent flow structures, and which influence the mixing processes between combustion air and fuel.
  • thermoacoustic oscillations for example.
  • a cooling air film which is passed over the combustion chamber walls or by an acoustic coupling of so-called Helmholtz damper in the combustion chamber or in the region of the cooling air.
  • thermoacoustic vibration amplitudes involves the disadvantage that the injection of fuel at the head stage is accompanied by an increase in the emission of NO x .
  • thermoacoustic vibrations have shown that often flow instabilities lead to these instabilities.
  • shear layers forming between two mixing flows which initiate waves perpendicular to the direction of flow (Kevin Helmholtz waves).
  • These instabilities on shear layers in combination with the ongoing combustion process are mainly responsible for the thermoacoustic oscillations caused by reaction rate fluctuations.
  • These largely coherent waves result in a burner of the aforementioned type under typical operating conditions to vibrations at frequencies in the range of 100 Hz.
  • thermoacoustic oscillations pose a problem following publications: Oster & Wygnanski 1982, "The forced mixing layer between parallel streams", Journal of Fluid Mechanics, Vol. 123, 91-130 ; Paschereit et al. 1995, “Experimental investigation of subharmonic resonance in an axisymmetric jet", Journal of Fluid Mechanics, Vol. 283, 365-407 ; Paschereit et al., 1998, "Structure and Control of Thermoacoustic Instabilities in a Gas Turbine Burner, Combustion, Science & Technology, Vol. 138, 213-232 ).
  • Premixed flames require low velocity zones to be stabilized.
  • To stabilize the flame backflow zones which are generated either by the lag behind sturgeons, so-called flame holders, or by aerodynamic methods (vortex breakdown).
  • the stability of the backflow zone is another criterion for the stability of the combustion and the avoidance of thermoacoustic instabilities.
  • US 5325660 describes embodiments of burners of the former category.
  • a flow-influencing body is arranged downstream of the premixing zone of the burner such that a backflow zone forms downstream.
  • the flame sits directly behind the flame holder.
  • Such designed burners are not well suited for operation in connection with fluid power engines, such as gas turbines.
  • the flame holders are subject to high wear due to their exposed position and the enormous thermal and chemical stresses. Waste parts would have devastating effects on the downstream turbine. In modern gas turbine plants such burners are therefore no alternative.
  • EP 321 809 B1 discloses a premix burner with a return flow zone forming downstream of the burner exit which stabilizes the flame without the need for a mechanical flame holder.
  • This burner consists of at least two hollow, nested Operakegel Sciencesn whose longitudinal axes are offset from each other such that tangential slots for supplying the combustion air form, which flows like a spiral through an enclosed by the part cone bodies, conically expanding premixing zone to the burner outlet.
  • Centrally arranged in the premixing lance for fuel injection is arranged.
  • WO 01/96785 discloses a generic same premix burner, which is characterized by a stable operation in the partial load range and thermoacoustic instabilities, which can lead to a complete extinction of the flame, especially in the part-load range, reduced. This is accomplished by a locally variable fuel injection into the premix zone via at least a first group and at least a second group of fuel supply means.
  • the burner lance should preferably be equipped with more than one group of fuel supply and extend relatively far into the premixing zone.
  • a number of premix zones for supplying a fuel-air mixture are coupled to the combustion chamber.
  • the premix zones each consist of a cylindrical jacket tube with an inner cylindrical central body, so they have an annular cross-section.
  • the central body ends shortly before the outlet of the premixing zone in the combustion chamber.
  • At the entrance of the premixing zone are vortex elements for the combustion air and from the central body radially outgoing, projecting into the combustion air flow lances for injecting fuel into the flowing combustion air.
  • the premixing zone Starting from the jacket pipe or the central body protrude at the combustion chamber side outlet the premixing zone includes a plurality of, approximately two to six, flow elements radially into the annular premixing zone which interfere with the formed flow patterns and thus inhibit the formation of coherent structures.
  • the invention has for its object to provide a premix burner for reducing combustion-driven thermoacoustic oscillations within a combustion system, in particular one with a low acoustic damping, which further reduces the formation of coherent flow instabilities at the burner outlet and which is to create with little equipment.
  • the object is achieved by a premix burner of the type mentioned in the independent claim.
  • the basic idea of the invention is to further stabilize the central backflow zone forming downstream of the burner outlet, within which the fuel / air mixture ignites. Due to the stabilization of the backflow zone and the reduction of the formation of coherent vortex structures at the burner outlet, the periodic heat releases within the combustion chamber which cause the occurrence of thermoacoustic oscillations are largely prevented.
  • the fluidic stabilization of the remindströmzone according to the invention is carried out by providing the central fuel nozzle in the form of a burner lance, as is commonly used for pilot gas supply, wherein the burner lance has a length downstream of the burner head in a length of 60 to 80% in the burner protrudes, is arranged centrally to the burner axis and in her
  • the fuel discharge takes place by at least one fuel nozzle opening attached to the end of the lance in such a way that the fuel discharged into the interior of the burner mixes finely distributed with incoming air and is at the same time swirled.
  • the wake at the end of the lance provides further stabilization of the aerodynamically generated return flow zone.
  • the lance is equipped in a manner known per se with means which allow an independent supply of two fluid media.
  • Such a design makes it possible to introduce additional fuel air into the burner interior in addition to a fuel injection. By a known modulated supply of this additional air combustion chamber vibrations thus can be additionally counteracted.
  • the measure according to the invention carries a partial fuel injection via the central fuel lance pushed into the interior space and having an expanding cross section in the end region to stabilize the flame forming within the backflow zone.
  • FIG. 1 is shown in longitudinal section a premix burner 1, as in its basic structure, for example, from the EP 0 321 809 evident.
  • the premix burner 1 consists of two half-shell-shaped, conically widening partial bodies 1 a and 1 b, which are arranged axially parallel and offset from one another such that they form tangential gaps in two overlapping areas lying opposite each other in mirror image.
  • the resulting from the displacement of the longitudinal axes of the body part 1 a and 1 b column serve as inlet channels through which the combustion air 7 flows tangentially into the burner interior 2 in the burner operation.
  • injection openings through which a preferably gaseous Fuel 8 is injected into the passing combustion air 7.
  • this abovementioned type of burner has in a central arrangement in the starting region of the burner interior 2 a nozzle for introducing further, preferably liquid fuel.
  • a nozzle for introducing further, preferably liquid fuel.
  • combustion air 7 and fuel 8 pass through the burner interior 2 with intensive mixing.
  • the swirl flow 6 breaks down to form a backflow zone 5 with an effect stabilizing the flame front acting there. Further details of the structure and operation of this burner 1 are shown in the aforementioned EP document and other sources of information known to those skilled in the art.
  • a burner lance 3 protrudes parallel to the burner axis into the burner interior 2 as an extension of the mentioned central fuel nozzle.
  • thermoacoustic oscillations open out in the region of the end of the lance.
  • This air, as well as the fuel can be fed modulated.
  • the in a swirl flow 6 through the burner interior 2 in the combustion chamber 4 propagating fuel / air mixture is able to stabilize within the combustion chamber 4 forming remindströmzone 5, especially since the vortex of the fuel / air mixture before and during ignition the vortex decay within the combustion chamber. 4 favors, whereby the remindströmzone 5 is stabilized. This can prevent the remindströmzone 5 changes its position periodically, which is ultimately the cause of propagating within the combustion system thermoacoustic oscillations.
  • FIG. 2 is a diagram representation illustrating the effect of inventively designed burner lance 3 on the suppression of instabilities in the form of pressure oscillations in the 120 Hz range.
  • the pulsations measured in pressure values (Pa) along the ordinate in FIG. 2 are plotted as a function of the position of the lance end in the burner 1.
  • the ratio I / L is plotted, ie the ratio of the length of the burner lance 3 to the total axial extent L of the burner.
  • FIG. 3 Diagram representation shown is with the in FIG. 2 comparable.
  • FIG. 4 the evaluation of the individual interfering geometries with regard to the nitrogen oxide emission is shown.
  • the burner lance interspersed with a multiplicity of fuel outlets proves to be particularly advantageous FIG. 5 is shown.
  • FIG. 5 The illustrated interference geometry as well as the geometries shown in the following figures can be formed, for example, as threaded screw tops, which are screwed into the burner head and in particular can be easily exchanged for test purposes.
  • burner lance 3 is equipped with a plurality of the shell laterally penetrating fuel outlet openings 9.
  • the injection takes place preferably in the region of the second lance half, as viewed in the direction of flow.
  • FIG. 6 shows a star-shaped Lanzenendgeometrie
  • FIG. 7 a conically shaped Lanzenendgeometrie, wherein the fuel discharge from the lance 3 by axially aligned outlet openings 12, 32 takes place, as it were the lance geometry in FIG. 8 showing a burner lance to which a plate 13 is attached.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Gas Burners (AREA)
EP03405031.0A 2002-02-13 2003-01-24 Verfahren zur Verminderung verbrennungsgetriebener Schwingungen in Verbrennungssystemen sowie Vormischbrenner zur Durchführung des Verfahrens Expired - Lifetime EP1336800B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10205839A DE10205839B4 (de) 2002-02-13 2002-02-13 Vormischbrenner zur Verminderung verbrennungsgetriebener Schwingungen in Verbrennungssystemen
DE10205839 2002-02-13

Publications (2)

Publication Number Publication Date
EP1336800A1 EP1336800A1 (de) 2003-08-20
EP1336800B1 true EP1336800B1 (de) 2013-11-27

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US (1) US6918256B2 (ja)
EP (1) EP1336800B1 (ja)
JP (1) JP2003240242A (ja)
DE (1) DE10205839B4 (ja)

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Publication number Publication date
JP2003240242A (ja) 2003-08-27
DE10205839A1 (de) 2003-08-14
DE10205839B4 (de) 2011-08-11
US6918256B2 (en) 2005-07-19
EP1336800A1 (de) 2003-08-20
US20030150217A1 (en) 2003-08-14

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