WO2015067482A1 - Brûleur de turbine à gaz présentant des niveaux de combustible réglables séparément dans des déflecteurs de brûleur pilotes - Google Patents

Brûleur de turbine à gaz présentant des niveaux de combustible réglables séparément dans des déflecteurs de brûleur pilotes Download PDF

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Publication number
WO2015067482A1
WO2015067482A1 PCT/EP2014/072827 EP2014072827W WO2015067482A1 WO 2015067482 A1 WO2015067482 A1 WO 2015067482A1 EP 2014072827 W EP2014072827 W EP 2014072827W WO 2015067482 A1 WO2015067482 A1 WO 2015067482A1
Authority
WO
WIPO (PCT)
Prior art keywords
fuel
burner
air duct
swirl vanes
annular air
Prior art date
Application number
PCT/EP2014/072827
Other languages
English (en)
Inventor
Andreas Böttcher
Boris Ferdinand Kock
Tobias Krieger
Jürgen MEISL
William R. Ryan
Daniel Vogtmann
Ulrich Wörz
Original Assignee
Siemens Aktiengesellschaft
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 Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Publication of WO2015067482A1 publication Critical patent/WO2015067482A1/fr

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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
    • 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
    • F23D11/38—Nozzles; Cleaning devices therefor
    • F23D11/383—Nozzles; Cleaning devices therefor with swirl means
    • 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
    • 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
    • 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
    • F23C2900/07001—Air swirling vanes incorporating fuel injectors
    • 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
    • F23D2900/14021—Premixing burners with swirling or vortices creating means for fuel or air

Definitions

  • the invention relates to a burner arrangement for a combus ⁇ tion chamber, in particular a gas turbine combustion chamber, for burning fluidic fuels.
  • a combustion air-fuel mixture in a combustion chamber in particular in a combustion chamber of a gas turbine, emission limit values (NO x and CO) and the humming behavior, caused by thermo-acoustic vibrations in the region of the combustion chamber, are always important top- ics .
  • the object which is di ⁇ rected toward a burner arrangement is achieved by means of a burner arrangement for a combustion chamber, in particular a gas turbine combustion chamber, for burning fluidic fuels, having a main burner and a pilot burner, arranged centrally therein, which serves to ignite and/or stabilize the combus ⁇ tion of the main burner,
  • the main burner comprising a first annular air duct for supplying combustion air and first fuel nozzles for injecting a fuel into the first annular air duct
  • the pilot burner comprising a second annular air duct for supplying combustion air and second fuel nozzles for inject ⁇ ing a fuel into the second annular air duct, in which the se ⁇ cond fuel nozzles are provided as first and second fuel stag ⁇ es .
  • the invention therefore provides for integrating a second fuel stage into the pilot burner.
  • each fuel stage has an in- dividual fuel supply, where appropriate with a distributor duct.
  • This embodiment allows both stages to be controlled in ⁇ dependently of one another.
  • the first and second fuel stages are pre- mixed fuel stages.
  • the first annu ⁇ lar air duct has first swirl vanes and the first fuel nozzles are arranged in the first swirl vanes.
  • the second annular air duct has second swirl vanes and at least some of the second fuel nozzles are arranged in the second swirl vanes.
  • a bore pattern of the second fuel nozzles is chosen such that, in operation, different ra ⁇ dial fuel distributions can be set via the first and the se ⁇ cond fuel stage.
  • the radial distribution of fuel can be actively influenced in operation and emissions and combustion stability can be influenced. It is hereby pos- sible to broaden the corridors which must be navigated when starting up and shutting down the machine, and the emissions behavior and stability behavior, most importantly in the par ⁇ tial load range (currently of considerable interest) , can be improved .
  • Burner arrangements having only one fuel stage in the pilot burner are known. It is therefore advantageous if, in the case of a pilot burner which has a central diffusion gas pas ⁇ sage, a pipe is provided, wherein an annular duct for the fuel supply to the second fuel stage is formed between an in ⁇ ner wall of the diffusion gas passage and a pipe outer wall. In this manner, the diffusion gas passage already present in the burner is used for the fuel supply of the second stage and sealed by means of a pipe-in-pipe construction which for example is unloaded by means of a compensator.
  • the figure shows, schematically, a section through a part of a burner arrangement 1 according to the invention.
  • the burner arrangement 1 is substantially radially symmetrical about the central axis 21 and comprises a main burner 2 and a pilot burner 3 arranged centrally therein which serves to ignite and/or stabilize the combustion of the main burner 2.
  • the main burner 2 comprises a first annular air duct 4 for supplying combustion air 5 and first fuel nozzles 6 for injecting a fuel 7 into the first annular air duct 4.
  • the pilot burner 3 comprises a second annular air duct 8 for supplying combustion air 5 and second fuel nozzles 9 for injecting a fuel 7 into the second annular air duct 8.
  • the second fuel nozzles 9 are now provided as first and second fuel stages 10, 11, wherein each fuel stage 10, 11 has an individual fuel supply 12, 13 and in the example of the figure is a premixed fuel stage.
  • the first annular air duct 4 has first swirl vanes 14 in which the first fuel nozzles 6 are arranged.
  • the second annular air duct 8 has second swirl vanes 15, wherein at least some of the second fuel nozzles 9 are arranged in the second swirl vanes 15, wherein in particular all of the second fuel nozzles 9 are arranged in the second swirl vanes 15 and all of the second swirl vanes 15 have second fuel noz ⁇ zles 9 of the first 10 and second fuel stage 11.
  • different radial fuel distributions can be set, when the burner arrangement 1 is in operation, via the first 10 and the second fuel stage 11.
  • the separations between the bores or, in addition, the opening diameter of the latter may vary radially.
  • the pilot burner 3 has a central diffusion gas passage 16 in which a pipe 17 is arranged, wherein an annular duct 20 for the fuel supply 13 to the second fuel stage 11 is formed be ⁇ tween an inner wall 18 of the diffusion gas passage 16 and a pipe outer wall 19.
  • This pipe-in-pipe construction is unload ⁇ ed by means of a compensator 22.

Landscapes

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

Abstract

La présente invention concerne un agencement de brûleur (1) pour une chambre de combustion, en particulier une chambre de combustion de turbine à gaz, pour la combustion de combustibles liquides, présentant un brûleur principal (2) et un brûleur pilote (3), disposé de manière centrale à l'intérieur de ce dernier, qui sert à déclencher et/ou à stabiliser la combustion du brûleur principal (2), le brûleur principal (2) comprenant un premier conduit d'air annulaire (4) permettant de fournir de l'air de combustion (5) et des premiers gicleurs de combustible (6) permettant d'injecter un combustible (7) dans le premier conduit d'air annulaire (4), le brûleur pilote (3) comprenant un second conduit d'air annulaire (8) permettant de fournir l'air de combustion (5) et des seconds gicleurs de combustible (9) permettant d'injecter un combustible (7) dans le second conduit d'air annulaire (8), les seconds gicleurs de combustible (9) étant utilisés comme premier et second niveaux de combustibles (10, 11).
PCT/EP2014/072827 2013-11-08 2014-10-24 Brûleur de turbine à gaz présentant des niveaux de combustible réglables séparément dans des déflecteurs de brûleur pilotes WO2015067482A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201361901569P 2013-11-08 2013-11-08
US61/901,569 2013-11-08

Publications (1)

Publication Number Publication Date
WO2015067482A1 true WO2015067482A1 (fr) 2015-05-14

Family

ID=51866134

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2014/072827 WO2015067482A1 (fr) 2013-11-08 2014-10-24 Brûleur de turbine à gaz présentant des niveaux de combustible réglables séparément dans des déflecteurs de brûleur pilotes

Country Status (1)

Country Link
WO (1) WO2015067482A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015165680A1 (fr) * 2014-04-30 2015-11-05 Siemens Aktiengesellschaft Brûleur à profil de combustible radial réglable
WO2016162248A1 (fr) * 2015-04-08 2016-10-13 Siemens Aktiengesellschaft Ensemble brûleur
WO2017052547A1 (fr) * 2015-09-24 2017-03-30 Siemens Aktiengesellschaft Buse pilote à ailettes bi-étagée

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009038845A1 (de) * 2009-08-26 2011-03-03 Siemens Aktiengesellschaft Drallschaufel, Brenner und Gasturbine
EP2503240A1 (fr) * 2011-03-22 2012-09-26 Siemens Aktiengesellschaft Brûleur de turbine à gaz

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009038845A1 (de) * 2009-08-26 2011-03-03 Siemens Aktiengesellschaft Drallschaufel, Brenner und Gasturbine
EP2503240A1 (fr) * 2011-03-22 2012-09-26 Siemens Aktiengesellschaft Brûleur de turbine à gaz

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015165680A1 (fr) * 2014-04-30 2015-11-05 Siemens Aktiengesellschaft Brûleur à profil de combustible radial réglable
WO2016162248A1 (fr) * 2015-04-08 2016-10-13 Siemens Aktiengesellschaft Ensemble brûleur
WO2017052547A1 (fr) * 2015-09-24 2017-03-30 Siemens Aktiengesellschaft Buse pilote à ailettes bi-étagée

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