EP1654496A1 - Bruleur et procede pour faire fonctionner une turbine a gaz - Google Patents

Bruleur et procede pour faire fonctionner une turbine a gaz

Info

Publication number
EP1654496A1
EP1654496A1 EP04763360A EP04763360A EP1654496A1 EP 1654496 A1 EP1654496 A1 EP 1654496A1 EP 04763360 A EP04763360 A EP 04763360A EP 04763360 A EP04763360 A EP 04763360A EP 1654496 A1 EP1654496 A1 EP 1654496A1
Authority
EP
European Patent Office
Prior art keywords
fuel
burner
premixing channel
inlet
inlet devices
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.)
Granted
Application number
EP04763360A
Other languages
German (de)
English (en)
Other versions
EP1654496B1 (fr
Inventor
Malte Blomeyer
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
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to EP04763360.7A priority Critical patent/EP1654496B1/fr
Publication of EP1654496A1 publication Critical patent/EP1654496A1/fr
Application granted granted Critical
Publication of EP1654496B1 publication Critical patent/EP1654496B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

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
    • F23D14/62—Mixing devices; Mixing tubes
    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • 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
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00008—Burner assemblies with diffusion and premix modes, i.e. dual mode burners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/14—Special features of gas burners
    • F23D2900/14004—Special features of gas burners with radially extending gas distribution spokes

Definitions

  • the invention relates to a burner with an annular premixing channel into which fuel can be introduced in a radially distributed manner.
  • the invention also relates to a method for operating a gas turbine with a burner which has an annular premixing channel.
  • Combustion air and fuel are combined in a burner, mixed, ignited and burned in a flame. It is usually of great importance that pollutant emissions such as carbon monoxide or nitrogen oxide are kept low.
  • pollutant emissions such as carbon monoxide or nitrogen oxide are kept low.
  • the possibility of low-nitrogen oxide combustion exists in particular through a so-called premix combustion, in which the fuel and combustion air are first mixed as homogeneously as possible before they are fed into the combustion zone.
  • a premix burner is disclosed in WO 02/095293 AI. This burner shows an annular premixing channel which surrounds a central diffusion burner. In the premixing channel, swirl vanes are arranged clearly upstream of the combustion zone in a swirl grid extending over the entire cross section of the premixing channel. Such a swirl grid serves to stabilize the flame.
  • the swirl vanes of the disclosed swirl grille are hollow, openings on the surface of the swirl vanes extending in the radial direction with swirl vanes. From these openings, fuel is let into the premixing channel, which was previously fed to the hollow swirl blades. In this way, an even introduction of fuel into the combustion air flowing through the premix channel is achieved over the radial height of the premix channel. At the same time, an even distribution of fuel in the circumferential direction of the premixing channel is also achieved by the inlet of the fuel from all swirl vanes. This has a high homogeneity of the then in according to the combustion air / fuel mixture flowing in the combustion zone. Such homogeneity is desirable for low nitrogen oxide emissions because the formation of nitrogen oxide increases exponentially with the flame temperature.
  • the object of the invention is to provide a burner with an annular premixing channel which, with regard to its combustion stability, can be set as a function of the prevailing operating conditions.
  • Another object of the invention is to provide a method for operating a gas turbine, in which a burner is set depending on the operating state of the gas turbine so that the highest possible flame stability and the lowest possible pollutant emissions result.
  • the object directed at a burner is achieved according to the invention by a burner directed along an axis. with an annular premixing channel into which fuel can be introduced in a radially distributed manner, the radial distribution of the fuel being adjustable during operation of the burner.
  • the radial distribution of the fuel is the distribution of the fuel along a line perpendicular to the axis of the burner.
  • the invention it is proposed for the first time to make the radial distribution of the fuel adjustable so that it is possible to react to different operating conditions. So far, only static fuel distributions have been realized using the geometry and inlet positions of fuel and combustion air.
  • the invention is based on the knowledge that pollutant emissions and combustion stabilities can be influenced favorably by changing the radial distribution of the fuel under different operating conditions of the burner. For example, in full-load operation, the aim is generally for fuel to be distributed as homogeneously as possible in the combustion air in order to keep nitrogen oxide emissions low.
  • Distribution profile of the fuel inlet can interrupt this positive feedback and thus suppress the combustion oscillation.
  • inlet devices are preferably provided distributed over the circumference of the premixing channel, for a radial inlet of fuel lying at the respective circumferential position by means of inlet openings arranged in the radial direction with a respective opening cross section, with the opening cross sections in the direction of the first part of the inlet devices Increase the axis and decrease the opening cross-sections in a second part of the inlet devices.
  • Such a configuration makes it possible, depending on the inlet of fuel, to set a desired radial distribution of the fuel inlet on the one hand from the first part of the inlet devices and on the other hand from the second part of the inlet devices by changing the opening cross sections in opposite directions.
  • the inlet devices of the first part and the second part are preferably arranged alternately along the circumference of the premixing channel.
  • the inlet devices of the first and the second part are thus alternately distributed next to one another over the circumference.
  • the inlet devices of the first part and of the second part preferably follow in the axial direction of the premixing device. channel to each other.
  • z For example, fuel is first let into the premixing channel from the inlet devices of the first part and then fuel is subsequently flowed in from the inlet devices of the second part in the flow direction.
  • fuel can be let in uniformly distributed both from the inlet devices of the first part and from the inlet devices of the second part with the circumference of the premixing channel.
  • the superposition of the fuel inlet from the two parts gives the desired radial distribution for the entire fuel inlet.
  • a first and a second fuel feed line running around the axis of the burner are preferably provided, with a pressure difference of the fuel pressure in the two
  • Fuel feed lines can be adjusted to one another depending on the operating state of the burner.
  • the first part of the inlet device is further preferably connected to the first fuel feed line and the second part of the inlet device is connected to the second fuel feed line.
  • the pressure required for the desired distribution is set in the first and second fuel feed lines. Depending on the pressure difference, there are therefore different amounts of fuel which are admitted via the first or the second inlet device, so that the entire fuel inlet is adjusted according to the desired distribution.
  • the inlet devices are preferably tubes protruding radially into the premixing channel, into the interior of which the fuel is supplied. From these tubes, the fuel is then admitted into the premixing channel from the inlet openings.
  • the inlet devices are preferably swirl vanes which protrude radially into the premixing channel and to the interior of which the fuel is supplied.
  • the inlet openings are arranged on the surface of the swirl blades, preferably in the vicinity of a blade leading edge.
  • the swirl vanes thus fulfill a dual function in that they impart the swirl necessary for combustion stabilization and at the same time act as an inlet device for the fuel.
  • the first part of the inlet devices is preferably formed from tubes projecting radially into the premixing channel and the second part of the inlet devices is formed from swirl vanes projecting radially into the premixing channel. Both the first part and the second part of the inlet devices can be arranged upstream of the other part in the premixing channel.
  • the tubes are advantageously arranged upstream of the swirl vanes, which leads to a greater mixing of fuel and combustion air when passing through the swirl grille. With increased security against a flashback, however, it may be cheaper to arrange the tubes downstream of the swirl blades.
  • the burner is preferably a gas turbine burner, in particular for a stationary gas turbine with an output greater than 50 MW.
  • a gas turbine has a compressor that compresses air and supplies it to the burner.
  • the burner opens into a gas turbine combustion chamber in which the burner flame is enclosed.
  • the hot exhaust gas generated in the combustion chamber then flows into a turbine part in which hot gas flows around turbine blades. Blades arranged on a turbine shaft, driven by the hot gas, set the turbine shaft in rotation.
  • Large stationary gas turbines in particular have strict requirements with regard to low pollutant emissions and a low tendency to form combustion vibrations.
  • the burner preferably has a central diffusion burner enclosed by the premixing channel.
  • the object directed to a method is achieved according to the invention by specifying a method for operating a gas turbine with a burner for combusting a fuel in air, which burner has an annular premixing channel into which the fuel is introduced in a radial distribution, the radial distribution being dependent is set by the operating state of the gas turbine.
  • a radial distribution is preferably set such that a region of a local maximum is formed in the radial distribution of the fuel concentration in the fuel-air mixture.
  • a radial distribution is preferably set such that a homogeneous mixture concentration of fuel and air results.
  • the radial distribution is preferably changed when a combustion oscillation occurs with an amplitude that exceeds a predetermined limit value.
  • FIG. 1 shows a gas turbine
  • FIG. 2 shows a premix burner according to the prior art
  • FIG. 3 shows a longitudinal section through a premixing channel of a premixing burner according to the prior art
  • FIG. 4, 5 a section of a longitudinal section through a premixing channel
  • FIG. 6 shows a longitudinal section through a premixing channel
  • FIG. 8 shows a section of a cross section through a premixing channel
  • Figure 9 shows a detail of a longitudinal section through a premixing channel.
  • FIG. 1 shows a gas turbine 1.
  • the gas turbine 1 has a compressor 3 and a turbine part 7 arranged on a common turbine shaft 8.
  • An annular combustion chamber 5 is connected between the compressor 3 and the turbine part 7.
  • a number of premix burners 9 open into the annular combustion chamber 5 distributed around the circumference.
  • the premix burners 9 are supplied with highly compressed air 11 from the compressor 3.
  • Fuel 13 is also fed to the premix burner 9. Air 11 and fuel 13 are mixed and introduced via the premix burner 9 into the combustion chamber 5, where they are burned to a hot gas 15.
  • FIG. 2 shows a premix burner 9. This is directed along an axis 10.
  • the premix burner 9 has an annular premix channel 21.
  • the premixing channel 21 surrounds a central diffusion burner 23.
  • the premixing channel 21 has an annular central surface 22 which forms an angle to the burner axis 10 in cross section.
  • the premixing channel 21 has a radially outer surface 18 and a radially inner surface 20.
  • an annular swirl grid 25 extends, which is constructed from individual swirl blades 26.
  • fuel inlet tubes 27 protrude into the premixing channel 21 in the radial direction.
  • the fuel inlet tubes 27 are hollow and have inlet openings 29.
  • air 11 is passed through the premixing channel 21.
  • the air 11 flows past the fuel inlet tube 27.
  • the fuel inlet tube 27 is fed into the interior of fuel 13, which exits into the air 11 from the inlet openings 29.
  • the air 11 is given a swirl via the swirl blades 26 in the swirl grille 25, which serves to stabilize the combustion.
  • the swirl blades 26 are designed such that fuel 13 can also be supplied to them. Via inlet openings, not shown, on the surface of the
  • fuel 13 is also introduced into the air 11 in the premixing channel 21.
  • Fuel 13 and air 11 are mixed in the premixing channel 21 to form a fuel / air mixture 28 which emerges from the premix burner 9 and is burned there in a combustion zone.
  • a premix combustion tends to cause instabilities in the flame, that is to say fluctuations or even an extinguishing of the flame.
  • the central diffusion burner 21, to which air 11 and fuel 13 are likewise fed, is often used to stabilize this combustion. However, these are essentially only mixed with one another in the combustion zone, with a richer mixture being selected.
  • the premix combustion can be stabilized with the flame of the diffusion burner 23.
  • substance 13 introduced into the premixing channel 21 in a fixed, static distribution.
  • Figure 3 shows a section of a longitudinal section through a premixing channel according to the prior art.
  • a section through a swirl vane 26 of the swirl grille 25 is shown.
  • An annular fuel feed line 41 is arranged in the area of the inner surface 20 of the premixing channel 21.
  • Fuel 13 is supplied to the swirl blades 26 from this annular fuel feed line 41.
  • the swirl blades 26 all have the same arrangement and the same opening cross section at their inlet openings 29.
  • FIG. 4 shows, in a section of a longitudinal section through the premixing channel 21, an arrangement which has been changed compared to FIG. 3 and which becomes clear together with FIG. 4 and 5 each show a section through two adjacent swirl blades 26, ie FIG. 4 shows a first swirl blade 26 and FIG. 5 shows an adjacent swirl blade 26.
  • the opening cross sections of the inlet openings 29, and the opening cross sections in the direction of the inner surface 20 of the premixing channel 21, ie in the direction of the axis 10, not shown here become larger.
  • the opening cross sections of the inlet openings 29 of the swirl vane 26 shown in FIG. 5 become smaller in the same direction.
  • the opening cross sections of the inlet openings 29 thus change in the opposite direction, that is to say that one vane 26 is followed by inlet openings 29 enlarging in the direction of the axis 10, each with a swirl vane 26 with inlet openings 29, the opening cross sections of which reduce in the direction of axis 10.
  • the swirl blades 26 of FIG. 4 form a first part 31 of inlet devices for the inlet of fuel 13 into the premixing channel 21.
  • the swirl blades 26 of FIG. the second part 33 of inlet devices for the inlet of fuel 13 into the premixing channel 21.
  • FIGS. 6 and 7 show how the inlet devices 31, 33 are supplied with the fuel 13.
  • the first part 31 of the inlet devices is supplied from an annular fuel feed line 43 which is arranged between the diffusion burner 23 and the premixing channel 21.
  • the second part 33 is supplied with fuel 13 by a second, independent annular fuel feed line 45.
  • the second annular fuel feed line 45 is arranged directly adjacent to the first fuel feed line 43.
  • the second part of the inlet devices are supplied with more fuel, which leads to a more homogeneous distribution of fuel 13 in the premixing channel 21.
  • the inlet openings 29 widening in the direction of the outer surface 18 of the premixing channel 21 include mass flow of air 11 in the radially outer part in the direction of the outer surface 18 in the premixing channel 21, so that a radial distribution of fuel 13 in the premixing channel 21 is set by this increasing opening cross-section, which results in a mixture of fuel 13 and air 11 which is as homogeneous as possible.
  • the radial distribution of the fuel 13 could also be changed if a combustion oscillation occurs in the combustion chamber 5 that exceeds a certain limit amplitude.
  • Such combustion vibrations may be formed by flame instabilities and a feedback of 'pressure variations and density fluctuations in fuel-air mixture.
  • this feedback mechanism can be interrupted and the combustion vibrations can thereby be suppressed.
  • FIG. 8 shows again in a section of a cross section through the premixing channel 21 the alternating arrangement of the first part 31 of inlet devices and the second part 33 of inlet devices, each designed as swirl vanes 26 in the swirl grille 25.
  • the opposite change in the opening cross section of the inlet openings 29 in can be seen radial direction.
  • FIG. 9 shows a further possible configuration of the arrangement of the first part 31 and the second part 33 of the inlet devices.
  • a section through a longitudinal section through the premixing channel 21 shows the first part 31 and the second part 33 of the inlet devices arranged one behind the other in the flow direction of the air 11.
  • the first part 31 is formed here from tubes which protrude into the premixing channel 21.
  • the second part 33 is formed from swirl blades 26.
  • the opening cross sections of the inlet openings 29 in turn change in opposite directions, that is to say in the direction of the axis 10 or in the direction of the inner surface 20 the inlet openings 29 of the first part 31 of the inlet devices enlarge, while the opening cross sections of the inlet openings 29 of the second part 33 of the inlet device reduce in the direction of axis 10.
  • fuel 13 can also be introduced very uniformly in the premixing channel 21 in the circumferential direction.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)

Abstract

L'invention concerne un brûleur (9) comportant un canal de prémélange (21) annulaire dans lequel un combustible (13) peut être introduit en étant réparti radialement. La répartition radiale du combustible (13) peut être, pendant le fonctionnement du brûleur (9), réglée par le fait que du combustible (13) peut être, par l'intermédiaire de conduites d'amenée de combustible (41, 43, 45), conduit à une première et une seconde partie (31 ; 33) de dispositifs d'admission présentant des ouvertures d'admission (29) dont les sections varient radialement en sens contraire, cette amenée se faisant de façon indépendante pour lesdites parties. L'invention concerne également un procédé pour faire fonctionner une turbine à gaz, procédé selon lequel la répartition radiale de combustible est réglée dans un canal de prémélange (21) d'un brûleur (9).
EP04763360.7A 2003-08-13 2004-07-20 Bruleur et procede pour faire fonctionner une turbine a gaz Expired - Lifetime EP1654496B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP04763360.7A EP1654496B1 (fr) 2003-08-13 2004-07-20 Bruleur et procede pour faire fonctionner une turbine a gaz

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP03018408A EP1507119A1 (fr) 2003-08-13 2003-08-13 Brûleur et méthode de fonctionnement d'une turbine à gaz
EP04763360.7A EP1654496B1 (fr) 2003-08-13 2004-07-20 Bruleur et procede pour faire fonctionner une turbine a gaz
PCT/EP2004/008115 WO2005019733A1 (fr) 2003-08-13 2004-07-20 Bruleur et procede pour faire fonctionner une turbine a gaz

Publications (2)

Publication Number Publication Date
EP1654496A1 true EP1654496A1 (fr) 2006-05-10
EP1654496B1 EP1654496B1 (fr) 2015-08-26

Family

ID=33560792

Family Applications (2)

Application Number Title Priority Date Filing Date
EP03018408A Withdrawn EP1507119A1 (fr) 2003-08-13 2003-08-13 Brûleur et méthode de fonctionnement d'une turbine à gaz
EP04763360.7A Expired - Lifetime EP1654496B1 (fr) 2003-08-13 2004-07-20 Bruleur et procede pour faire fonctionner une turbine a gaz

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP03018408A Withdrawn EP1507119A1 (fr) 2003-08-13 2003-08-13 Brûleur et méthode de fonctionnement d'une turbine à gaz

Country Status (6)

Country Link
US (1) US7654090B2 (fr)
EP (2) EP1507119A1 (fr)
JP (1) JP4430074B2 (fr)
CN (1) CN100545517C (fr)
ES (1) ES2551440T3 (fr)
WO (1) WO2005019733A1 (fr)

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JP4418442B2 (ja) * 2006-03-30 2010-02-17 三菱重工業株式会社 ガスタービンの燃焼器及び燃焼制御方法
EP1843098A1 (fr) * 2006-04-07 2007-10-10 Siemens Aktiengesellschaft Chambre de combustion pour turbine à gaz
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US9163841B2 (en) * 2011-09-23 2015-10-20 Siemens Aktiengesellschaft Cast manifold for dry low NOx gas turbine engine
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WO2013128572A1 (fr) 2012-02-28 2013-09-06 三菱重工業株式会社 Brûleur, et turbine à gaz
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CN113757719B (zh) * 2021-09-18 2023-05-05 北京航空航天大学 燃烧室燃烧振荡的控制方法及燃烧室
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Publication number Priority date Publication date Assignee Title
DE102018205874A1 (de) 2018-04-18 2019-10-24 Siemens Aktiengesellschaft Brenner mit selektiver Anpassung des Bohrungsmusters für die Gaseindüsung
WO2019201577A1 (fr) 2018-04-18 2019-10-24 Siemens Aktiengesellschaft Brûleur comprenant une adaptation sélective du gabarit de perçage pour l'injection de gaz

Also Published As

Publication number Publication date
WO2005019733A1 (fr) 2005-03-03
US7654090B2 (en) 2010-02-02
CN1860333A (zh) 2006-11-08
US20070031771A1 (en) 2007-02-08
JP4430074B2 (ja) 2010-03-10
EP1654496B1 (fr) 2015-08-26
JP2007501926A (ja) 2007-02-01
CN100545517C (zh) 2009-09-30
ES2551440T3 (es) 2015-11-19
EP1507119A1 (fr) 2005-02-16

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