EP0481111B1 - Chambre de combustion pour turbine à gaz - Google Patents

Chambre de combustion pour turbine à gaz Download PDF

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Publication number
EP0481111B1
EP0481111B1 EP90119900A EP90119900A EP0481111B1 EP 0481111 B1 EP0481111 B1 EP 0481111B1 EP 90119900 A EP90119900 A EP 90119900A EP 90119900 A EP90119900 A EP 90119900A EP 0481111 B1 EP0481111 B1 EP 0481111B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
burners
premix burners
combustion
burner
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
EP90119900A
Other languages
German (de)
English (en)
Other versions
EP0481111A1 (fr
Inventor
Jakob Dr. Keller
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.)
ABB Asea Brown Boveri Ltd
ABB AB
Original Assignee
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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 ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Priority to EP90119900A priority Critical patent/EP0481111B1/fr
Priority to DE59009353T priority patent/DE59009353D1/de
Priority to AT90119900T priority patent/ATE124528T1/de
Priority to PL29190291A priority patent/PL291902A1/xx
Priority to US07/775,603 priority patent/US5274993A/en
Priority to CA002053587A priority patent/CA2053587A1/fr
Priority to JP26918891A priority patent/JP3179154B2/ja
Publication of EP0481111A1 publication Critical patent/EP0481111A1/fr
Application granted granted Critical
Publication of EP0481111B1 publication Critical patent/EP0481111B1/fr
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
    • F23R3/36—Supply of different fuels
    • 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
    • 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
    • F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising 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
    • F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners

Definitions

  • the present invention relates to a combustion chamber of a gas turbine according to the preamble of claim 1.
  • premix burners With regard to the prescribed, extremely low NOx, CO and UHC emissions when operating a gas turbine, many manufacturers are adopting premix burners.
  • One of the disadvantages of premix burners is that they extinguish at a ⁇ of approx. 2, even at very low air numbers, depending on the temperature downstream of the compressor of the gas turbine group.
  • "lean premix combustion" in the low load range of a combustion chamber leads to poor combustion efficiency and correspondingly high NOx, CO and UHC emissions. This problem becomes particularly critical in multi-shaft machines because the combustion chamber pressure there is typically very low when idling. For this reason, the air temperature after the compressor is very low.
  • the document EP-A1-0 387 532 describes an annular combustion chamber which has a number of premix burners on the inflow side in the circumferential direction.
  • the large premix burners which are the main burners of the ring combustion chamber, and the small premix burners, which are the pilot burners, are placed alternately and at a uniform distance from one another. Both the pilot burner and the main burner open into a single annular front wall.
  • a combustion chamber is installed downstream of this front wall. In the entire load range of the combustion chamber, the pilot burners work as independent premix burners, whereby the air ratio remains almost constant.
  • the invention seeks to remedy this.
  • the invention as characterized in the claims, is based on the object of maximizing the efficiency and minimizing the various pollutant emissions in a combustion chamber of the type mentioned at part-load operation.
  • a pilot burner likewise designed on the basis of premix burner, between two main burners designed on the basis of premix burners, the pilot burners being combined with a pre-combustion chamber.
  • the main burners are related to the pilot burners in relation to the size of the burner air flowing through them, which is determined on a case-by-case basis.
  • the combination pilot burner / pre-combustion chamber is then operated in "rich primary mode". In this way, with the help of the fuel-rich combustion in the pre-combustion chamber, both the evaporation of the liquid fuel and the burnout of liquid or gaseous fuel can be decisively improved.
  • the main burner system is then switched on and the pilot burners are then operated in "lean primary mode".
  • main burners and the pilot burners consist of so-called double-cone burners of different sizes, and if these burners are integrated into an annular combustion chamber.
  • Fig. 1 shows a section of a sector of an annular combustion chamber A along the front wall 10 thereof. This shows the placement of the individual main burners B and pilot burners C. These are placed along the front wall 10 at a uniform distance from one another, with an alternating distribution.
  • the size difference shown between main burner B and pilot burner C is only of a qualitative nature.
  • the effective size of the individual burners B and C and their distance from one another primarily depends on the size and performance of the respective combustion chamber.
  • the size ratio between pilot burners C and main burners B is selected such that approximately 23% of the burner air flows through the pilot burners C and approximately 77% through the main burners B.
  • the pilot burners C are each supplemented with a pre-combustion chamber C1, the configuration of which will be explained in more detail in FIG. 2.
  • Fig. 2 is a schematic axial section through the annular combustion chamber in the plane of the burners B and C; both the main burner B and the pilot burner C all open same height in the uniform front wall 10 to the subsequent combustion chamber of the combustion chamber: the main burners B directly because of their outflow opening, the pilot burners C, however, via the pre-combustion chamber C1 downstream of the burner part in the outflow direction.
  • the schematic representation of FIG. 2 already shows that both the main burners B and the pilot burners C are designed as premix burners, ie they do not need the otherwise usual premix zone. Of course, with such a design, it must always be ensured that backfire in the premixing zone of the respective burner, upstream of the front wall 10, is excluded.
  • the size ratio between the main burner B and the pilot burner C to a certain extent also indicates the operating mode with regard to the load range: At low partial load, only the pilot burner C (one or more stages) is supplied with fuel in such a configuration. "Lean premix combustion" leads to poor combustion efficiency in the low load range of a combustion chamber and correspondingly high NOx, CO and HC emissions. Where multi-shaft machines are used, for example, this problem becomes particularly critical because the combustion chamber pressure is typically very low when idling. For this reason, the air temperature after the compressor is also very low, which does not result in optimal premixing of this compressor air with the fuel used.
  • FIG. 3 which can be both main burner B and pilot burner C in structure, consists of two half hollow partial cone bodies 1, 2 which are radially offset from one another with respect to their longitudinal axis of symmetry.
  • the offset of the respective longitudinal axis of symmetry 1b, 2b to each other creates a tangential air inlet slot 19, 20 on both sides of the partial cone body 1, 2 in the opposite inflow arrangement (see FIGS. 4-6) through which the combustion air 15 enters the interior of the burner , ie flows in the cone cavity 14 formed by the two partial cone bodies 1, 2.
  • the cone shape of the ge showed partial cone body 1, 2 in the flow direction has a certain fixed angle.
  • the partial cone bodies 1, 2 can have a progressive or degressive taper in the direction of flow.
  • the two last-mentioned embodiments are not included in the drawing, since they can easily be reread. Which form is ultimately preferred essentially depends on the combustion parameters specified in each case.
  • the two partial cone bodies 1, 2 each have a cylindrical initial part 1a, 2a, which, analogous to the partial cone bodies 1, 2, are offset from one another, so that the tangential air inlet slots 19, 20 are present throughout the entire burner.
  • a nozzle 3 is accommodated in this cylindrical starting part 1a, 2a, the fuel injection 4 of which coincides with the narrowest cross section of the conical cavity 14 formed by the two partial cone bodies 1, 2.
  • the size of this nozzle 3 depends on the type of burner, ie whether it is a pilot burner C or main burner B. Of course, the burner can be made purely conical, that is to say without cylindrical starting parts 1a, 2a.
  • Both partial cone bodies 1, 2 each have a fuel line 8, 9 provided with openings 17, through which a gaseous fuel 13 is fed, which in turn is admixed to the combustion air 15 flowing into the cone cavity 14 through the tangential air inlet slots 19, 20.
  • the fuel lines 8, 9 should preferably be provided at the end of the tangential inflow, immediately before entering the cone cavity 14, in order to achieve an optimal speed-related admixture 16 between fuel 13 and inflowing combustion air 15. Of course, mixed operation with both fuels 12, 13 is possible .
  • the outlet opening of the burner B / C merges into a front wall 10, in which bores, which are not shown in the drawing, proceed can be seen, this in order to be able to supply dilution air or cooling air to the front part of the combustion chamber if required.
  • the liquid fuel 12, which preferably flows through the nozzle 3, is injected into the cone hollow body 14 at an acute angle, in such a way that the most homogeneous conical spray pattern is obtained in the burner outlet plane, which is only possible if the inner walls of the partial cone bodies 1, 2 through the Fuel injection 4, which can be an air assisted or pressure atomization, are not wetted.
  • the tapered liquid fuel profile 5 is enclosed by the combustion air 15 flowing in tangentially and a further combustion air flow 15a brought in axially.
  • the concentration of the liquid fuel 12 is continuously reduced by the mixed-in combustion air 15.
  • gaseous fuel 13 is used via the fuel lines 8, 9, the mixture formation with the combustion air 15 takes place, as has already been briefly explained above, directly in the area of the air inlet slots 19, 20, at the inlet into the hollow cone body 14
  • the injection of the liquid fuel 12 is achieved in the area of the vortex, ie in the area of the backflow zone 6, the optimal homogeneous fuel concentration over the cross section.
  • the ignition takes place at the tip of the return flow zone 6. Only at this point can a stable flame front 7 arise.
  • a flashback of the flame into the interior of the burner B, C as can potentially always be the case with known premixing sections, while there is a remedy with complicated flame holders, there is no fear here.
  • an accelerated, holistic evaporation of the liquid fuel 12 occurs before the point at the outlet of the burner B, C is reached, at which the ignition of the mixture can take place.
  • the degree of evaporation is of course dependent on the size of the Burner B, C, depending on the drop size of the injected fuel and on the temperature of the combustion air streams 15, 15a. Minimized pollutant emission levels occur when full evaporation can be provided before entering the combustion zone.
  • the axial speed can also be influenced by the axial supply of combustion air 15a.
  • the design of the burner is particularly suitable, given the given length of the burner, to change the size of the tangential air inlet slots 19, 20 by pushing the partial cone bodies 1, 2 towards or away from each other, whereby the distance between the two central axes 1b, 2b is reduced or respectively. enlarged, the gap size of the tangential air inlet slots 19, 20 also changes accordingly, as can be seen particularly well from FIGS. 4-6.
  • the partial cone bodies 1, 2 can also be displaced relative to one another in another plane, as a result of which even an overlap thereof can be controlled.
  • 4-6 now shows the geometric configuration of the guide plates 21a, 21b. They have flow introduction functions, whereby, depending on their length, they extend the respective end of the partial cone bodies 1, 2 in the direction of flow of the combustion air 15.
  • the channeling of the combustion air 15 into the cone cavity 14 can be optimized by opening or closing the guide plates 21a, 21b around a pivot point 23 placed in the area of the entry into the cone cavity 14, this is particularly necessary if the original gap size of the tangential air inlet slots 19, 20 is changed.
  • the burner B, C can of course also be operated without baffles, or other aids can be provided for this.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
  • Combustion Of Fluid Fuel (AREA)

Claims (8)

  1. Chambre de combustion d'une turbine à gaz qui, du côté de l'admission, est équipée d'un certain nombre de brûleurs à prémélange (B, C) et présente une zone de combustion (22) succédant aux brûleurs à prémélange dans le sens de l'écoulement, dans laquelle les brûleurs à prémélange (B, C) sont disposés l'un à côté de l'autre et sont de taille différente en ce qui concerne le courant d'air de combustion qui peut les traverser, et dans laquelle un petit brûleur à prémélange (C) est chaque fois placé entre deux gros brûleurs à prémélange (B), caractérisée en ce que les petits brûleurs à prémélange (C) présentent une chambre de précombustion (C1) en aval de leur plus grande ouverture de sortie.
  2. Chambre de combustion suivant la revendication 1, caractérisée en ce que la chambre de combustion (A) est une chambre de combustion annulaire, en ce que la chambre de combustion annulaire présente une paroi frontale annulaire (10) en amont de la zone de combustion (22), en ce que les gros brûleurs à prémélange (B) et les petits brûleurs à prémélange (C) sont disposés en alternance l'un avec l'autre le long de la paroi frontale, en ce que les gros brûleurs à prémélange (B) et la chambre de précombustion (C1) des petits brûleurs à prémélange (C) débouchent dans la paroi frontale (10).
  3. Chambre de combustion suivant la revendication 1, caractérisée en ce que les gros brûleurs à prémélange (B) sont les brûleurs principaux et en ce que les petits brûleurs à prémélange (C) sont les brûleurs pilotes de la chambre de combustion (A).
  4. Chambre de combustion suivant la revendication 1, caractérisée en ce que le brûleur à prémélange (B, C) se compose, dans le sens de l'écoulement, d'au moins deux corps partiels coniques creux (1, 2), disposés l'un sur l'autre, dont les axes de symétrie longitudinaux (1b, 2b) sont décalés radialement l'un par rapport à l'autre, en ce que les axes de symétrie longitudinaux (1b, 2b) décalés donnent naissance à des fentes d'entrée tangentielles (19, 20), ayant un sens d'écoulement opposé, pour un courant d'air de combustion (15), en ce que, dans la zone conique creuse (14) formée par les corps partiels coniques (1, 2), est placé au moins un gicleur à combustible (3), dont l'injection (4) du combustible (12) est située au milieu de la distance entre les axes de symétrie longitudinaux (1b, 2b) décalés l'un par rapport à l'autre des corps partiels coniques (1, 2).
  5. Chambre de combustion suivant la revendication 4, caractérisée en ce que, dans la région des fentes d'entrée tangentielles (19, 20) se trouvent d'autres gicleurs (17) d'un autre combustible (13).
  6. Chambre de combustion suivant la revendication 4, caractérisée en ce que les corps partiels (1, 2) s'évasent en cône dans le sens de l'écoulement, avec un angle fixe.
  7. Chambre de combustion suivant la revendication 4, caractérisée en ce que les corps partiels (1, 2) présentent une conicité progressive dans le sens de l'écoulement.
  8. Chambre de combustion suivant la revendication 4, caractérisée en ce que les corps partiels (1, 2) présentent une conicité dégressive dans le sens de l'écoulement.
EP90119900A 1990-10-17 1990-10-17 Chambre de combustion pour turbine à gaz Expired - Lifetime EP0481111B1 (fr)

Priority Applications (7)

Application Number Priority Date Filing Date Title
EP90119900A EP0481111B1 (fr) 1990-10-17 1990-10-17 Chambre de combustion pour turbine à gaz
DE59009353T DE59009353D1 (de) 1990-10-17 1990-10-17 Brennkammer einer Gasturbine.
AT90119900T ATE124528T1 (de) 1990-10-17 1990-10-17 Brennkammer einer gasturbine.
PL29190291A PL291902A1 (en) 1990-10-17 1991-10-02 Gas turbine combustion chamber and method of operating a burner in such chamber
US07/775,603 US5274993A (en) 1990-10-17 1991-10-15 Combustion chamber of a gas turbine including pilot burners having precombustion chambers
CA002053587A CA2053587A1 (fr) 1990-10-17 1991-10-16 Chambre de combustion d'une turbine a gaz
JP26918891A JP3179154B2 (ja) 1990-10-17 1991-10-17 ガスタービンの燃焼室

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP90119900A EP0481111B1 (fr) 1990-10-17 1990-10-17 Chambre de combustion pour turbine à gaz

Publications (2)

Publication Number Publication Date
EP0481111A1 EP0481111A1 (fr) 1992-04-22
EP0481111B1 true EP0481111B1 (fr) 1995-06-28

Family

ID=8204623

Family Applications (1)

Application Number Title Priority Date Filing Date
EP90119900A Expired - Lifetime EP0481111B1 (fr) 1990-10-17 1990-10-17 Chambre de combustion pour turbine à gaz

Country Status (7)

Country Link
US (1) US5274993A (fr)
EP (1) EP0481111B1 (fr)
JP (1) JP3179154B2 (fr)
AT (1) ATE124528T1 (fr)
CA (1) CA2053587A1 (fr)
DE (1) DE59009353D1 (fr)
PL (1) PL291902A1 (fr)

Families Citing this family (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2694799B1 (fr) * 1992-08-12 1994-09-23 Snecma Chambre de combustion annulaire conventionnelle à plusieurs injecteurs.
FR2695460B1 (fr) * 1992-09-09 1994-10-21 Snecma Chambre de combustion de turbomachine à plusieurs injecteurs.
DE4336096B4 (de) * 1992-11-13 2004-07-08 Alstom Vorrichtung zur Reduktion von Schwingungen in Brennkammern
DE19502796B4 (de) * 1995-01-30 2004-10-28 Alstom Brenner
DE19510743A1 (de) * 1995-02-20 1996-09-26 Abb Management Ag Brennkammer mit Zweistufenverbrennung
JPH09119641A (ja) * 1995-06-05 1997-05-06 Allison Engine Co Inc ガスタービンエンジン用低窒素酸化物希薄予混合モジュール
DE19548853A1 (de) * 1995-12-27 1997-07-03 Abb Research Ltd Kegelbrenner
DE19619873A1 (de) * 1996-05-17 1997-11-20 Abb Research Ltd Brenner
SE9802707L (sv) * 1998-08-11 2000-02-12 Abb Ab Brännkammaranordning och förfarande för att reducera inverkan av akustiska trycksvängningar i en brännkammaranordning
DE19948674B4 (de) * 1999-10-08 2012-04-12 Alstom Verbrennungseinrichtung, insbesondere für den Antrieb von Gasturbinen
US6360776B1 (en) 2000-11-01 2002-03-26 Rolls-Royce Corporation Apparatus for premixing in a gas turbine engine
DE10108560A1 (de) * 2001-02-22 2002-09-05 Alstom Switzerland Ltd Verfahren zum Betrieb einer Ringbrennkammer sowie eine diesbezügliche Ringbrennkammer
JP4134311B2 (ja) * 2002-03-08 2008-08-20 独立行政法人 宇宙航空研究開発機構 ガスタービン燃焼器
US6968699B2 (en) * 2003-05-08 2005-11-29 General Electric Company Sector staging combustor
DE102006051286A1 (de) * 2006-10-26 2008-04-30 Deutsches Zentrum für Luft- und Raumfahrt e.V. Brennervorrichtung
GB2455289B (en) * 2007-12-03 2010-04-07 Siemens Ag Improvements in or relating to burners for a gas-turbine engine
US8122700B2 (en) * 2008-04-28 2012-02-28 United Technologies Corp. Premix nozzles and gas turbine engine systems involving such nozzles
EP2434222B1 (fr) * 2010-09-24 2019-02-27 Ansaldo Energia IP UK Limited Méthode d'opération d'une chambre de combustion
US8479521B2 (en) * 2011-01-24 2013-07-09 United Technologies Corporation Gas turbine combustor with liner air admission holes associated with interspersed main and pilot swirler assemblies
US9689571B2 (en) * 2014-01-15 2017-06-27 Delavan Inc. Offset stem fuel distributor
CN106482154A (zh) * 2016-10-31 2017-03-08 南京航空航天大学 一种主级带喷溅式雾化的贫油预混预蒸发低污染燃烧室

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Publication number Priority date Publication date Assignee Title
US4194358A (en) * 1977-12-15 1980-03-25 General Electric Company Double annular combustor configuration
EP0210462B1 (fr) * 1985-07-30 1989-03-15 BBC Brown Boveri AG Chambre de combustion double
CH678757A5 (fr) * 1989-03-15 1991-10-31 Asea Brown Boveri
CH680084A5 (fr) * 1989-06-06 1992-06-15 Asea Brown Boveri

Also Published As

Publication number Publication date
JPH04260722A (ja) 1992-09-16
JP3179154B2 (ja) 2001-06-25
DE59009353D1 (de) 1995-08-03
EP0481111A1 (fr) 1992-04-22
ATE124528T1 (de) 1995-07-15
CA2053587A1 (fr) 1992-04-18
PL291902A1 (en) 1992-04-21
US5274993A (en) 1994-01-04

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