EP1534997A2 - Bruleur - Google Patents

Bruleur

Info

Publication number
EP1534997A2
EP1534997A2 EP03794901A EP03794901A EP1534997A2 EP 1534997 A2 EP1534997 A2 EP 1534997A2 EP 03794901 A EP03794901 A EP 03794901A EP 03794901 A EP03794901 A EP 03794901A EP 1534997 A2 EP1534997 A2 EP 1534997A2
Authority
EP
European Patent Office
Prior art keywords
burner
fuel
longitudinal axis
channel
radial direction
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
EP03794901A
Other languages
German (de)
English (en)
Other versions
EP1534997B1 (fr
Inventor
Peter Berenbrink
Malte Blomeyer
Werner Krebs
Bernd Prade
Holger Streb
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 EP03794901.3A priority Critical patent/EP1534997B1/fr
Publication of EP1534997A2 publication Critical patent/EP1534997A2/fr
Application granted granted Critical
Publication of EP1534997B1 publication Critical patent/EP1534997B1/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
    • 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
    • F23R3/02—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
    • 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 burner according to the preamble of claims 1 and 2.
  • Such combustion instabilities can be suppressed actively, for example by increasing the power of the pilot flame, or passively, for example by resonators.
  • FIG. 2 shows an enlarged detail from FIG. 1,
  • FIG. 3 shows a swirl vane for a burner designed according to the invention
  • FIG. 4 shows a swirl vane for a burner designed according to the invention
  • Figure 5 velocity vectors of a flowing fuel air-gas mixture
  • FIG. 1 shows a burner 1, in particular a premix burner 1, in particular for a gas turbine.
  • the burner 1 has a burner longitudinal axis 46.
  • a diffusion or pilot burner 43 is arranged centrally along the longitudinal axis 46 of the burner. In the premix mode, the pilot burner 43 is operated to support the burner 1.
  • fuel 7 and / or air 4 is fed to a premixing section 10 and / or a combustion chamber 19 via a channel 13 (FIG. 6) that is annular, for example, to the longitudinal axis 46.
  • a channel 13 annular, for example, to the longitudinal axis 46.
  • oxygen or another gas can also be supplied, which together with fuel 7 results in a combustible fuel-gas mixture.
  • air 4 is first supplied to channel 13 and then fuel 7.
  • the air 4 flows in the channel 13, for example, at least on one
  • the swirl blades 16 are arranged, for example, in a ring shape, in particular equidistantly, around the longitudinal axis 46 of the burner (FIG. 6).
  • the air 4 and the fuel 7 mix in the premixing section 10, which is indicated by dashed lines.
  • FIG. 2 shows the radial end 49 of the diffusion / pilot burner 43 with the annular channel 13.
  • the fuel 7 is fed to the channel 13 via at least two fuel nozzles 31 and flows there in a flow direction 88.
  • the fuel is preferably supplied via fuel nozzles 31 which are arranged in the swirl vane 16.
  • the fuel 7 can also be supplied to the channel 13 via other distribution units.
  • the combustion instabilities result from a distribution of the fuel concentration 58 according to the prior art.
  • the concentration of the fuel is approximately the same.
  • the operating range for burner 1 can thus be expanded.
  • the fuel concentration changes, for example, in a radial direction
  • Fuel concentration for example, linearly from or to.
  • FIG. 3 shows a swirl vane 16 with which this can be achieved.
  • the operating range can also be expanded if a discharge angle ⁇ of a medium, ie the angle between the resulting speed and peripheral speed (FIG. 5), for example the air / fuel / 7 mixture, has a distribution similar to the concentration of the fuel 7 has, ie seen from the burner longitudinal axis 46, the outflow angle ⁇ decreases, for example, in a radial direction 55 from a maximum value to a minimum value or vice versa. This is done, for example, by twisting the swirl blade 16 as described in FIG. 4.
  • the outflow angle ⁇ is also the angle between the flow direction of the medium flowing in the channel (air, oxygen, fuel, mixtures thereof) and a plane whose normal is the burner longitudinal axis 46.
  • the distribution 52 of the fuel concentration and the outflow angle ⁇ can also be combined with one another in order to expand and improve the operating range of the burner 1.
  • FIG. 3 shows a swirl vane 16 for a burner 1 according to the invention.
  • the swirl vane 16 has a leading edge 67 and a trailing edge 70.
  • the medium flows in in channel 13
  • Flow direction 88 first past the leading edge 67 and then past the trailing edge 70.
  • FIG. 4 shows a further swirl vane 16 for a burner 1 according to the invention.
  • the swirl vane 16 is designed, for example, with respect to the size and distribution of the fuel nozzles 31, like the swirl vane in FIG. 3.
  • the airfoil 61 can still be wound around a winding axis 76.
  • the winding axis 76 forms a non-zero cutting angle with the flow direction 88 and is in particular 90 °.
  • ⁇ 1 At one end of the swirl vane 16 in the region of the trailing edge 70, a different outflow angle ⁇ 1 is generated than at the other end, an outflow angle ⁇ 2 (not equal to ⁇ l), viewed in the direction of a longitudinal axis of the feed 64.
  • the outflow angle ⁇ decreases linearly. There may also be a non-linear increase or decrease.
  • This distribution in the radial direction 55 of the outflow angle ⁇ likewise suppresses combustion instabilities, so that the operating range for the burner 1 is expanded.
  • the flowing medium on the swirl vane 16 with the flow direction 88 in the channel 13 forms the outflow angle ⁇ .
  • the swirl vane 16 can be both twisted and have different diameters for the fuel nozzles.
  • FIG. 5 shows the arrangement of the different flow vectors of the gas flowing in the channel 13.
  • the vector 79 represents the meridional speed component.
  • the vector 82 represents the peripheral speed, so that a resulting speed sector 85 results.
  • the angle between the resulting speed 85 and the peripheral speed 82 represents the outflow angle ⁇ .
  • the angle 90 ° - ⁇ is the complementary angle.
  • the outflow angle ⁇ is also the angle between the direction of flow of the flowing medium and a plane which is perpendicular to the longitudinal axis 46 of the burner.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Spray-Type Burners (AREA)
  • Air Supply (AREA)

Abstract

Les brûleurs habituels présentent des instabilités de combustion dans certains modes de fonctionnement, ce qui limite la gamme d'applications. Sur le brûleur selon l'invention (1), le combustible (1) présente une distribution de concentration, la concentration du combustible (7) diminuant dans le sens radial (55), de l'intérieur vers l'extérieur.
EP03794901.3A 2002-09-02 2003-08-20 Brûleur d'une turbine à gaz Expired - Lifetime EP1534997B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP03794901.3A EP1534997B1 (fr) 2002-09-02 2003-08-20 Brûleur d'une turbine à gaz

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
EP02019530 2002-09-02
EP02019530A EP1394471A1 (fr) 2002-09-02 2002-09-02 Brûleur
PCT/EP2003/009222 WO2004025183A2 (fr) 2002-09-02 2003-08-20 Bruleur
EP03794901.3A EP1534997B1 (fr) 2002-09-02 2003-08-20 Brûleur d'une turbine à gaz

Publications (2)

Publication Number Publication Date
EP1534997A2 true EP1534997A2 (fr) 2005-06-01
EP1534997B1 EP1534997B1 (fr) 2015-07-29

Family

ID=31197882

Family Applications (2)

Application Number Title Priority Date Filing Date
EP02019530A Withdrawn EP1394471A1 (fr) 2002-09-02 2002-09-02 Brûleur
EP03794901.3A Expired - Lifetime EP1534997B1 (fr) 2002-09-02 2003-08-20 Brûleur d'une turbine à gaz

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP02019530A Withdrawn EP1394471A1 (fr) 2002-09-02 2002-09-02 Brûleur

Country Status (6)

Country Link
US (1) US7753677B2 (fr)
EP (2) EP1394471A1 (fr)
JP (2) JP4369370B2 (fr)
CN (1) CN100432531C (fr)
ES (1) ES2550096T3 (fr)
WO (1) WO2004025183A2 (fr)

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JP4476176B2 (ja) * 2005-06-06 2010-06-09 三菱重工業株式会社 ガスタービンの予混合燃焼バーナー
US20070269755A2 (en) * 2006-01-05 2007-11-22 Petro-Chem Development Co., Inc. Systems, apparatus and method for flameless combustion absent catalyst or high temperature oxidants
US20080078182A1 (en) * 2006-09-29 2008-04-03 Andrei Tristan Evulet Premixing device, gas turbines comprising the premixing device, and methods of use
KR100820233B1 (ko) * 2006-10-31 2008-04-08 한국전력공사 연소기 및 이를 포함하는 멀티 연소기, 그리고 연소방법
EP1992878A1 (fr) * 2007-05-18 2008-11-19 Siemens Aktiengesellschaft Distributeur de combustible
US9016601B2 (en) 2007-05-18 2015-04-28 Siemens Aktiengesellschaft Fuel distributor
EP2042807A1 (fr) * 2007-09-25 2009-04-01 Siemens Aktiengesellschaft Etage de prémélange pour brûleur de turbine à gaz
JP5172468B2 (ja) * 2008-05-23 2013-03-27 川崎重工業株式会社 燃焼装置および燃焼装置の制御方法
EP2312215A1 (fr) * 2008-10-01 2011-04-20 Siemens Aktiengesellschaft Brûleur et procédé de fonctionnement d'un brûleur
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DE102009045950A1 (de) * 2009-10-23 2011-04-28 Man Diesel & Turbo Se Drallerzeuger
US9163841B2 (en) * 2011-09-23 2015-10-20 Siemens Aktiengesellschaft Cast manifold for dry low NOx gas turbine engine
CN104471317B (zh) * 2012-08-06 2016-09-07 西门子公司 在带有具有在外部区域内交叉的叶片端部的旋流生成器的燃烧器内的空气和燃料混合的局部改进
EP2728260A1 (fr) * 2012-11-06 2014-05-07 Alstom Technology Ltd Dispositif de tourbillonnement axial
US20150316266A1 (en) 2014-04-30 2015-11-05 Siemens Aktiengesellschaft Burner with adjustable radial fuel profile
EP2966350B1 (fr) * 2014-07-10 2018-06-13 Ansaldo Energia Switzerland AG Dispositif de tourbillonnement axial
CN107514636B (zh) * 2017-10-10 2023-09-08 安徽科达洁能股份有限公司 一种悬浮焙烧炉用烧嘴及其应用
DE102018205874A1 (de) * 2018-04-18 2019-10-24 Siemens Aktiengesellschaft Brenner mit selektiver Anpassung des Bohrungsmusters für die Gaseindüsung
PT3794283T (pt) * 2018-05-15 2024-04-11 Air Prod & Chem Sistema e procedimento para melhoramento da estabilidade de combustão numa turbina a gás
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EA039073B1 (ru) * 2020-09-07 2021-11-30 Некоммерческое Акционерное Общество "Алматинский Университет Энергетики И Связи Имени Гумарбека Даукеева" Двухъярусная горелка
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Also Published As

Publication number Publication date
CN100432531C (zh) 2008-11-12
ES2550096T3 (es) 2015-11-04
US7753677B2 (en) 2010-07-13
US20060035188A1 (en) 2006-02-16
JP4369370B2 (ja) 2009-11-18
EP1394471A1 (fr) 2004-03-03
JP2008256357A (ja) 2008-10-23
WO2004025183A3 (fr) 2005-01-20
EP1534997B1 (fr) 2015-07-29
CN1678871A (zh) 2005-10-05
JP4841587B2 (ja) 2011-12-21
WO2004025183A2 (fr) 2004-03-25
JP2006507466A (ja) 2006-03-02

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