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WO2009019114A2 - Combustible pour une chambre de combustion d'un turbogroupe - Google Patents

Combustible pour une chambre de combustion d'un turbogroupe Download PDF

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Publication number
WO2009019114A2
WO2009019114A2 PCT/EP2008/059350 EP2008059350W WO2009019114A2 WO 2009019114 A2 WO2009019114 A2 WO 2009019114A2 EP 2008059350 W EP2008059350 W EP 2008059350W WO 2009019114 A2 WO2009019114 A2 WO 2009019114A2
Authority
WO
WIPO (PCT)
Prior art keywords
burner
lance
channel
combustion chamber
outlet opening
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.)
Ceased
Application number
PCT/EP2008/059350
Other languages
German (de)
English (en)
Other versions
WO2009019114A3 (fr
Inventor
Jaan Hellat
Adnan Eroglu
Jan Cerny
Douglas Anthony Pennell
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.)
GE Vernova 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
Publication of WO2009019114A2 publication Critical patent/WO2009019114A2/fr
Publication of WO2009019114A3 publication Critical patent/WO2009019114A3/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

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
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • 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 
    • 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
    • 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
    • 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
    • F23D2900/00015—Pilot burners specially adapted for low load or transient conditions, e.g. for increasing stability

Definitions

  • the present invention relates to a burner for a combustion chamber of a turbo group, in particular in a power plant.
  • Such burners have a swirl generator, which encloses a burner interior on the input side and which has at least one air inlet tangential to a longitudinal central axis of the burner. Furthermore, such a burner comprises a mixer, which surrounds the burner interior on the output side and which has an outlet opening open to a combustion chamber of the combustion chamber. In addition, such a burner may be equipped with a lance for introducing pilot fuel into the combustion chamber. The lance is arranged coaxially to the longitudinal central axis of the burner and extends from a burner head, starting in the burner inside.
  • the invention deals with the problem of providing a burner of the type mentioned in an improved embodiment, which is characterized in particular by an increased stability of the combustion process in the combustion chamber.
  • the invention is based on the general idea of constructing the lance from a plurality of tubes arranged concentrically with one another in order to be able to independently supply air, liquid fuel and gaseous fuel.
  • Pilot operation can be better adapted to current operating conditions of the combustion chamber, whereby the combustion reaction can be stabilized in the combustion chamber. For example, when starting or starting up the combustion chamber, a pilot operation with exclusively liquid pilot fuel can be carried out. In the transition to the nominal operating state, which usually no
  • Pilot fuel is supplied via the lance, gaseous pilot fuel can be increasingly supplied. At the same time, the supply of the liquid pilot fuel can be reduced successively. Finally, the supply of gaseous pilot fuel can be successively reduced. Likewise, it is conceivable to supply the supply of pilot fuel for a short-term increase in output of the combustion chamber, wherein here also, depending on various parameters, such as temperature and pressure, liquid or gaseous pilot fuel or any combination thereof can be introduced. Due to the increased variability of the supply of different pilot fuels, the stability of the combustion reaction in the combustion chamber can be improved.
  • an inner annular channel to supply air is advantageous in several ways.
  • the lance can be cooled with the air.
  • the air prevents the penetration of the flames in the unused central channel and in the unused at least one outer channel, whereby a flushing of the respective channel is dispensable in the event that either only liquid pilot fuel or only gaseous pilot fuel is supplied.
  • the lance may be designed so that it extends at least in the pilot operation of the burner as far into the burner inside, that a flame front of a running in the combustion chamber combustion reaction at least partially into an enclosed by an outlet end portion of the mixer end portion of the burner interior extends into it.
  • the pilot operation is simplified due to the reduced distance between the free-standing lance end and the flame front.
  • the stability of the flame front can be increased.
  • the flame front, at least in the part running within the respective burner is largely decoupled from interactions which, in the case of a combustion chamber equipped with a plurality of burners, are caused by the other burners via the common combustion chamber come. The reduction of such interactions stabilizes the flame front.
  • this design makes it easier to transfer results from a single-burner test bench system to an industrial plant that is regularly equipped with multiple burners.
  • FIG. 2 is a view as in Fig. 1, but in another embodiment,
  • FIGS. 1 and 2 are views as in FIGS. 1 and 2, but with the lance extended
  • FIGS. 1 and 2 are views as in FIGS. 1 and 2, but with a more detailed representation of the lance,
  • Fig. 5 is a view as in Fig. 4, but in another embodiment of the lance. Ways to carry out the invention
  • a burner 1 comprises a swirl generator 2, a mixer 3 and a lance 4.
  • the burner 1 forms in the mounted state a component of a combustion chamber, not shown here, of a turbo group, which is arranged in particular in a power plant.
  • the swirl generator 2 encloses an input-side section of a burner interior 5 and has at least one air inlet 6, which extends tangentially with respect to a longitudinal central axis 7 of the burner 1.
  • the swirl generator 2 is configured conical.
  • the respective air inlet 6 forms a longitudinal slot along the cone sheath.
  • a plurality of such air inlets 6 are arranged distributed in the circumferential direction. As a result, the air can penetrate tangentially into the burner interior 5, whereby it is acted upon by a twist.
  • the swirl generator 2 also has a fuel inlet 8, via which gaseous fuel can be introduced into the burner interior 5.
  • this fuel inlet 8 consists of several, along the generatrix of the conical swirl generator 2 extending rows of individual inlet openings through which the fuel gas can enter the burner interior 5.
  • the fuel inlet 8 may be aligned tangentially to increase the swirl effect.
  • the fuel inlet 8 may generate some radial component to enhance mixing with the air.
  • the mixer 3 encloses an output-side section of the burner interior 5 and has an outlet opening 9, which leads to a combustion chamber 10 of FIG Combustion chamber is open.
  • the mixer 3 comprises, for example, a tubular body 11, which is connected via a tubular transition piece 12 to the swirl generator 2 and which carries an outlet flange 13 with the outlet opening 9.
  • the burner 1 can be connected to the combustion chamber.
  • the mixer 3 is cylindrically shaped.
  • the lance 4 is used for introducing pilot fuel into the combustion chamber 10.
  • the lance 4 is arranged coaxially to the longitudinal central axis 7. Furthermore, at least in a pilot operation of the burner 1, the lance 4 extends into the burner interior 5 from a burner head 14, which essentially forms the tip of the conical swirl generator 2. The lance 4 thus starts from the burner head 14 and ends with a lance end 15 freestanding in the burner interior. 5
  • a part of a flame front 16 is also shown, which forms during operation of the combustion chamber by the combustion reaction taking place in the combustion chamber 10.
  • part of this flame front 16 projects into the burner interior 5, into an end section of the burner interior 5, which is enclosed by an outlet-side end region of the mixer 3.
  • the flame front 16 remains within the section of the burner interior 5 enclosed by the outlet flange 13.
  • Such a course of the flame front 16, in which a part of the flame front 16 projects through the outlet opening 9 into the burner interior 5, is characterized by a particular embodiment and / or or arrangement of the lance 4 reached.
  • the lance 4 extends with its free-standing end 15 comparatively far into the burner interior 5, namely to the extent that a part of the flame front 16 extends into the burner interior 5 inside.
  • the lance 4 so deep in the Burner interior 5 may protrude in the direction of the outlet opening 9, the lance 4 must be designed accordingly so that it has the required axial length.
  • the lance 4 is positioned in the burner 1 so that its free-standing end 15 is located in a portion of the burner interior 5 enclosed by the mixer 3. In other words, the lance 4 extends into the mixer 3.
  • the lance 4 with its free-standing end 15 in the axial direction to about half of the mixer 3 or even beyond in the mixer 3 extend into it.
  • a distance 17 entered in FIG. 2, which the freestanding lance end 15 has from the outlet opening 9 is greater than 25% or less than 50% of a distance 18 that an outlet end 19 of the swirl generator 2 has from the outlet opening 9.
  • the distance 17 between outlet opening 9 and lance end 15 is preferably in a range of 25% to 50% of the distance 18 prevailing between outlet opening 9 and outlet-side end 19.
  • an inlet tube 20 which extends coaxially with the lance 4, can be arranged on the burner head 14.
  • This inlet tube 20 projects in the axial direction into a portion of the burner interior 5 enclosed by the swirl generator 2.
  • This inlet tube 20 may be an annular
  • the inlet channel 21 has at least one axially oriented outlet opening 22.
  • the liquid fuel can enter the burner interior 5 substantially in the axial direction, as indicated by arrows 48.
  • the burner 1 can thus be operated with fuel gas and / or with liquid fuel.
  • a plurality of such axial outlet openings 22 are arranged at the end of the inlet tube 20 ending in the burner interior 5.
  • the lance 4 may be arranged in the axial direction adjustable on the burner head 14.
  • the axial position of the free-standing lance end 15 within the burner interior 5 is adjustable. In particular, this allows the position of the part of the flame front 16 projecting into the burner interior 5 to be adjusted.
  • the burner 1 can be adapted to operating parameters of the combustion chamber, which allows stabilization of the combustion process.
  • the lance 4 can thus be retracted more or less deep into the burner interior 5, depending on demand, or extend more or less far out of the burner interior 5.
  • Fig. 3 shows a situation in which the lance 4 is largely extended from the burner interior 5.
  • the lance end 15 expediently ends at the inside of the burner head 14 facing the burner interior 5.
  • the lance 4 is fully extended for a simplified illustration. It can be retracted according to an arrow 23 back into the burner interior 5.
  • the flame front 16 is arranged completely outside the burner interior 5 and is located downstream of the outlet opening 9 with respect to the flow direction of the burner 1.
  • Fig. 3 is a simplified velocity profile 24 is shown, the
  • Distribution of the flow velocity along the cross section of the burner 1 within the mixer 3 represents. Visible, the flow has a significant maximum in the absence of lance 4 in the center. By retracting the lance 4 into the described area within the mixer 3, the flow velocity in the center of the cross section of the mixer 3 is inevitably reduced. At the same time, the speed is correspondingly increased outside the lance 4, ie in the edge region of the cross section, in order to ensure a constant volume flow. The reduction of the central flow velocity allows the flame front 16 to hike upstream. With appropriate positioning and configuration of the lance 4, the flame front 16 projects partially into the burner interior 5, as shown in FIG.
  • Figs. 4 and 5 the lance 4 is also shown cut.
  • the following detailed description of the lance 4 applies in particular to the embodiments of FIGS. 1 to 3.
  • the lance 4 has a plurality of concentrically arranged tubes, namely a central inner tube 25 and an outer tube 26.
  • the inner tube 25 includes a central channel 27 and has at least the free-standing lance end 15 axially oriented outlet opening 28.
  • the central channel 27 serves to supply liquid fuel to the at least one outlet opening 28.
  • the inner tube 25 is in the region of the outlet opening 28 with a nozzle-shaped
  • Cross-sectional constriction 29 equipped, which allows the formation of an intense liquid jet.
  • This liquid fuel jet is indicated in FIGS. 4 and 5 by an arrow 32.
  • the outer tube 26 is sized so that it surrounds the inner tube 25 to form an inner annular channel 30.
  • This inner annular channel 30 is axially open at the end of the lance 15 and thus opens into the burner interior 5.
  • the inner annular channel 30 serves to guide air, which can emerge from the inner annular channel 30 in the axial direction according to an arrow 31.
  • the outer tube 26 is configured hollow-walled, that is, the outer tube 26 has a hollow wall 33 with an inner wall 34 and a radially spaced outer wall 35.
  • the outer tube 26 includes at least one outer channel 36 (Fig 37 ( Figure 5).
  • This at least one outer channel 36, 37 serves to supply gaseous fuel.
  • the outer channel 36, 37 may be configured as an annular channel, which is simply formed between the two walls 34, 35 of the wall 33. According to FIG. 4, this outer annular channel 36 or 37 can have at least one axially oriented outlet opening 38 on the lance end 15, as a result of which an essentially axially oriented injection of fuel gas can be achieved in accordance with an arrow 39. Additionally or alternatively, in an in Fig.
  • an array of a plurality of radial outlet openings 41 may be provided.
  • These radial outlet openings 41 are preferably formed in the outer wall 35 of the hollow wall 33 of the outer tube 26.
  • a corresponding control can be provided which, for example, operates with a sleeve-shaped control element which lies in a first position in front of the radial outlet openings 41. while it locks in a second position, the at least one axial outlet opening 38.
  • a plurality of circumferentially distributed axial outlet openings 38 are arranged at the axial end of the outer tube 26.
  • first outer channel 36 may be formed, which leads at the lance end 15 to the at least one axial outlet opening 38.
  • at least one second outer channel 37 may be formed which leads to at least one of the radial outlet openings 41 formed in the lance end section 40.
  • FIG. 4 shows a section through the first outer channels 36
  • FIG. 5 shows a section through the second outer channels 37.
  • the first and second outer channels 36, 37 may be connected on the input side to various, independently operable supply devices or control devices.
  • the inner tube 25 projects axially beyond the outer tube 26. In this way, a certain separation of media during operation of the lance 4 for injecting the liquid fuel and for injecting the fuel gas can be achieved. This media separation can also be assisted by the injected air 31.
  • the inlet pipe 20 arranged at the burner head 14 is hollow-walled, so that it has a hollow wall 43 with an inner wall 44 and an outer wall 45.
  • the hollow-walled inlet tube 20 is here also dimensioned so that it encloses the lance 4 and the outer tube 26 to form an axially open annular channel 46. Through this annular channel 46 47 air can be injected into the burner interior according to an arrow. In this way, an effective cooling of the lance in the region of the burner head 14 can be achieved.
  • the inlet channel 21, which serves to introduce the liquid fuel according to arrows 48, is formed in the hollow wall 43 and may in particular also be designed annular. Figs. 4 and 5 show another feature.
  • a wall 49 of the mixer 3 is provided with a film cooling 50.
  • a film cooling 50 is realized for example by means of a plurality of cooling holes 51 which pass through the corresponding wall 49 and can be flowed through by coolant, which applies to the side of the wall 49 facing the burner interior 5 and thereby generates a cooling film protecting the wall 49.
  • coolant is usually air.
  • the cooling holes 51 may be set in the main flow direction of the burner 1 as shown here to enhance the formation of a cooling film.

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

Abstract

L'invention concerne un brûleur (1) pour une chambre de combustion d'un turbogroupe, comprenant un générateur de torsion (2), un mélangeur (3) et une lance (4) destinée à déposer le combustible pilote dans une chambre de combustion (10). Pour pouvoir mieux stabiliser la combustion, la lance (4) comprend plusieurs tubes (25, 26) disposés concentriquement : un tube interne central (25) contenant un canal central (27) pour le combustible liquide et présentant à l'extrémité de lance (15) au moins un orifice de sortie axial (28) ; un tube externe à paroi creuse (26) entourant le tube interne (25) en formant un canal annulaire interne (30) et contenant dans sa paroi creuse (33) au moins un canal externe (36, 37) pour le combustible gazeux, le canal annulaire interne (30) s'ouvrant axialement à l'extrémité de la lance (15) et servant à guider l'air.
PCT/EP2008/059350 2007-08-07 2008-07-17 Combustible pour une chambre de combustion d'un turbogroupe Ceased WO2009019114A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102007037290 2007-08-07
DE102007037290.8 2007-08-07

Publications (2)

Publication Number Publication Date
WO2009019114A2 true WO2009019114A2 (fr) 2009-02-12
WO2009019114A3 WO2009019114A3 (fr) 2009-06-11

Family

ID=40341803

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2008/059350 Ceased WO2009019114A2 (fr) 2007-08-07 2008-07-17 Combustible pour une chambre de combustion d'un turbogroupe

Country Status (1)

Country Link
WO (1) WO2009019114A2 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2199674A1 (fr) * 2008-12-19 2010-06-23 ALSTOM Technology Ltd Brûleur d'une turbine à gaz
CN102914164A (zh) * 2012-09-26 2013-02-06 金川集团股份有限公司 一种提高了使用寿命的镍富氧顶吹浸没式喷枪
DE102015222661A1 (de) * 2015-11-17 2017-05-18 Siemens Aktiengesellschaft Strömungshülse für Brennstoffeindüsung mit Zeitverzögerung

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH674561A5 (fr) * 1987-12-21 1990-06-15 Bbc Brown Boveri & Cie
DE4435266A1 (de) * 1994-10-01 1996-04-04 Abb Management Ag Brenner
DE10334228A1 (de) * 2002-08-19 2004-03-04 Alstom (Switzerland) Ltd. Verfahren zum Betrieb eines Vormischbrenners sowie Vorrichtung zur Durchführung des Verfahrens
DE10345137B4 (de) * 2003-09-29 2014-02-13 Alstom Technology Ltd. Verfahren zum Betrieb einer Brennstoffeinspritzvorrichtung sowie eine Brennstoffeinspritzvorrichtung zur Durchführung des Verfahrens
US6935117B2 (en) * 2003-10-23 2005-08-30 United Technologies Corporation Turbine engine fuel injector
WO2006042796A2 (fr) * 2004-10-18 2006-04-27 Alstom Technology Ltd Bruleur pour turbine a gaz
DE102005015152A1 (de) * 2005-03-31 2006-10-05 Alstom Technology Ltd. Vormischbrenner für eine Gasturbinenbrennkammer

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2199674A1 (fr) * 2008-12-19 2010-06-23 ALSTOM Technology Ltd Brûleur d'une turbine à gaz
US8938968B2 (en) 2008-12-19 2015-01-27 Alstom Technology Ltd. Burner of a gas turbine
CN102914164A (zh) * 2012-09-26 2013-02-06 金川集团股份有限公司 一种提高了使用寿命的镍富氧顶吹浸没式喷枪
DE102015222661A1 (de) * 2015-11-17 2017-05-18 Siemens Aktiengesellschaft Strömungshülse für Brennstoffeindüsung mit Zeitverzögerung

Also Published As

Publication number Publication date
WO2009019114A3 (fr) 2009-06-11

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