EP0851172A2 - Brûleur pour la mise en oeuvre d'une chambre de combustion avec un combustible liquide ou gazeux - Google Patents

Brûleur pour la mise en oeuvre d'une chambre de combustion avec un combustible liquide ou gazeux Download PDF

Info

Publication number: EP0851172A2
Authority: EP; European Patent Office
Prior art keywords: burner; flow; zone; air; burner according
Prior art date: 1996-12-23
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

EP97810838A

Other languages

German (de)

English (en)

Other versions

EP0851172A3 (fr

EP0851172B1 (fr

Inventor

Thomas Dr. Sattelmayer

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.)

General Electric Switzerland GmbH

Original Assignee

ABB Research Ltd Switzerland

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.)

1996-12-23

Filing date

1997-11-07

Publication date

1998-07-01

1997-11-07 Application filed by ABB Research Ltd Switzerland filed Critical ABB Research Ltd Switzerland

1998-07-01 Publication of EP0851172A2 publication Critical patent/EP0851172A2/fr

1999-06-09 Publication of EP0851172A3 publication Critical patent/EP0851172A3/fr

2003-07-16 Application granted granted Critical

2003-07-16 Publication of EP0851172B1 publication Critical patent/EP0851172B1/fr

2017-11-07 Anticipated expiration legal-status Critical

Status Expired - Lifetime legal-status Critical Current

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Classifications

- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D17/00—Burners for combustion simultaneously or alternately of gaseous or liquid or pulverulent fuel
- F23D17/002—Burners for combustion simultaneously or alternately of gaseous or liquid or pulverulent fuel gaseous or liquid fuel
- 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
- 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
- F23D—BURNERS
- F23D2209/00—Safety arrangements
- F23D2209/10—Flame flashback

Definitions

the present invention relates to a burner according to the preamble of claim 1.
Step on the outer boundary of the swirl flow field particularly low speeds because at constant Total pressure in the arrangement of the static pressure from the inside to the outside, causing the dynamic pressure caused by the absolute speed is represented with increasing Radius is getting smaller. These low speeds may no longer be able to prevent the flame from the combustion chamber, along the boundary layer, into the burner reproduces and can then overheat and destroy it.
the invention seeks to remedy this.
the invention how it is characterized in the claims, the task lies based on precautions for a burner of the type mentioned to meet those who are capable of a flashback to prevent safely.
the main advantage of the invention is that that this additional device of the simplest design is, and be installed as required in the burner mentioned can intervene without changing the basic concept of the same to have, with which such a burner, which is at medium compressor pressure ratios already well proven has, also for the further development stages of Gas turbines can be taken over and used.
additional air is injected along made of the burner walls, preferably in the downstream half of the burner.
This additional air forms a film along the wall and mixes it then slowly with the fuel-enriched main flow.
the essential improvement in security against one Backfire is based on two principles.
the mixture is diluted with weight. There the burner is operating near its lean extinguishing limit weak local dilution of the mixture results along the walls to the desired loss of flammability of the mixture along the walls.
this additional air is injected so that the axial speed is increased along the wall, which is also convenient affects the operation of such a burner.
the pulse density ratio between film air and main flow in the range of 1 since both flows are common be accelerated from the same total pressure. Other impulses are also easily conceivable, they have striven for Effect no negative effects.
Fig. 1 shows a burner in perspective.
Fig. 2 For a better understanding of the subject, it is advantageous if at the same time when studying Fig. 1 based on the description Fig. 2 is also used.
Partial bodies 1, 2 which are nested offset from one another are.
the offset of the respective central axis or Longitudinal axis of symmetry of the partial bodies 1, 2 to one another creates on both sides, in mirror image Arrangement, each having a tangential air inlet duct 5, 6 free, through which the combustion air 7 in the interior of the Brenner, i.e.
the two tapered Partial bodies 1, 2 each have a cylindrical initial part 9, 10, which also, analogously to the aforementioned partial bodies 1, 2, offset to each other, so that the tangential Air inlet channels 5, 6 over the entire length of the Brenners are present.
a nozzle 11 for preferably atomizing a liquid fuel 12 housed such that their injection approximately with the narrowest cross section of the the partial body 1, 2 formed conical cavity 8 coincides.
the injection capacity and the operating mode of this Nozzle 11 depends on the given parameters of the respective Brenners.
the fuel injected through the nozzle 11 12 can be enriched with a recirculated exhaust gas if necessary will; then it is also possible to pass through the nozzle 11 to provide the complementary injection of a quantity of water.
the burner can be purely conical, that is, without cylindrical starting parts 9, 10 may be formed.
the partial body 1, 2 each have a fuel line 13, 14, which along the tangential inlet channels 5, 6 arranged and provided with injection openings 15, through which preferably a gaseous fuel 16 in the combustion air 7 flowing there is injected, as this is symbolized by arrows 16, these Injection at the same time the fuel injection level (see Fig. 3, item 22) of the system.
These fuel lines 13, 14 are preferably at the latest at the end of the tangential inflow, before entering the cone cavity 8, placed this to ensure an optimal air / fuel mixture.
the burner On the combustion chamber side, the burner has an anchor for the partial body 1, 2 serving front panel 18 with a number Bores 19 through which a mixing or Cooling air 20 or the front part of the combustion chamber 17 Wall is fed.
Liquid fuel 12 is used to operate the burner the central nozzle 11 is used, this is under one acute angle in the cone cavity 8 or in the combustion chamber 17 injected. A nozzle is thus formed from the nozzle 11 Fuel profile 23, which flows in from the tangential rotating combustion air 7 is enclosed. In axial Direction is the concentration of the injected fuel 12 continuously through the incoming combustion air 7 an optimal mixture degraded. If the burner with a operated gaseous fuel 16, this can in principle also happen via the fuel nozzle 11, preferably but this happens via the injection openings 15, whereby the formation of this fuel / air mixture right at the end the air inlet channels 5, 6 comes about.
a backflow zone also forms there or backflow bladder 24 (vortex breakdown) with one opposite the flame front 25 acting there stabilizing Effect one, in the sense that the backflow zone 24 has the function of a disembodied flame holder.
the optimal fuel concentration across the cross-section is only in the area of vertebral bursting, i.e. in the area the backflow zone 24 reached. Only at this point then a stable flame front 25.
the flame stabilizing Effect results from that in the cone cavity 8 forming swirl number in the direction of flow along the cone axis. The flame strikes back inside the burner therefore occurs due to this fluidic specification not on.
the flow opening is minimized of the tangential air inlet ducts 6, 7 is predestined is the backflow zone 24 from the end of the premixing section to build.
the construction of the burner is suitable furthermore excellent, the flow opening of the tangential To change air inlet channels 5, 6 as required, with what a relative without changing the overall length of the burner large operational bandwidth can be captured.
the partial body 1, 2 in another Plane can be shifted towards each other, which even overlaps opposite the air inlet plane into the cone cavity 8 (See FIG. 2, item 21) of the same in the area of the tangential Air inlet channels 5, 6, as shown in Fig. 2, accomplished can be. It is then also possible that Partial body 1, 2 by a counter-rotating movement to nest in a spiral.
Fig. 2 shows the same burner according to Fig. 1 but from a different one Perspective and in a simplified form.
This figure 2 mainly wants the disposition of the two conical ones Show part body 1, 2 and their offset to each other.
the Displacement of the respective central axis 3, 4 of the two partial bodies to each other, based on the main central axis 26 of the Burner, which is the main axis of the central fuel nozzle 11 corresponds to the respective size of the flow openings the tangential air inlet ducts 5, 6.
the central axes 3, 4 run parallel to each other here.
Zone 27 in which the placements of Means for the injection of additional air takes place.
FIGS. 4 and 5 show a development 28 of a conical partial body, which schematically shows zone 27 within which has a specific configuration of injection openings for additional air, which ensure a reignition lock, is taken as a basis.
the orientation of the injection openings 29 as well as their number and size will be the respective Flow conditions in the burner adjusted.
the final Purpose is primarily aimed at the reignition barrier.
the individual oblique lines 30 want the placement of the symbolize individual rows of the injection openings 29.
the arrows 31 point to the outflow direction of the Additional air indicate that is at right angles to the Level 30 of the injection openings 29 runs. This outflow direction can, however, range from purely axial to direction the main flow vary. For better understanding are in this processing 28 a single row and one Double row of injection openings 29 shown. The corresponding cuts are then shown in FIGS. 4 and 5.
Fig. 4 shows the design of a simple row of injection openings 29.
the additional air 32 is here under one injected acute angle with respect to the swirl flow 7a flat to the inner wall of the corresponding partial body 2, this around improve film production.
FIG. 5 shows a double row of injection openings 29. Basically, the same precautions are taken here as described in Fig. 3.
the injection openings 33 run in the area the inner wall of the corresponding partial body 2 fan-shaped, as shown in Fig. 7, which is a plan view.

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)

EP97810838A 1996-12-23 1997-11-07 Brûleur et méthode pour la mise en oeuvre d'une chambre de combustion avec un combustible liquide et/ou gazeux Expired - Lifetime EP0851172B1 (fr)

Applications Claiming Priority (2)

Application Number	Priority Date	Filing Date	Title
DE19654116		1996-12-23
DE19654116A DE19654116A1 (de)	1996-12-23	1996-12-23	Brenner zum Betrieb einer Brennkammer mit einem flüssigen und/oder gasförmigen Brennstoff

Publications (3)

Publication Number	Publication Date
EP0851172A2 true EP0851172A2 (fr)	1998-07-01
EP0851172A3 EP0851172A3 (fr)	1999-06-09
EP0851172B1 EP0851172B1 (fr)	2003-07-16

Family

ID=7816084

Family Applications (1)

Application Number	Title	Priority Date	Filing Date
EP97810838A Expired - Lifetime EP0851172B1 (fr)	1996-12-23	1997-11-07	Brûleur et méthode pour la mise en oeuvre d'une chambre de combustion avec un combustible liquide et/ou gazeux

Country Status (3)

Country	Link
US (1)	US5921770A (fr)
EP (1)	EP0851172B1 (fr)
DE (2)	DE19654116A1 (fr)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
EP0959298A3 (fr) *	1998-05-18	2000-02-23	United Technologies Corporation	Injecteur de combustible à prémélange et son procédé de mise en oeuvre
EP1001214B1 (fr) *	1998-11-09	2004-09-15	ALSTOM Technology Ltd	Brûleur
EP1002992B1 (fr) *	1998-11-18	2004-09-29	ALSTOM Technology Ltd	Brûleur
EP0987491B1 (fr) *	1998-09-16	2005-07-20	ALSTOM Technology Ltd	Procédé pour prévenir les instabilités d'écoulement dans un brûleur
EP2423597A2 (fr)	2010-08-27	2012-02-29	Alstom Technology Ltd	Brûleur à prémélange pour une turbine à gaz
EP2685161A1 (fr)	2012-07-10	2014-01-15	Alstom Technology Ltd	Agencement de chambre de combustion, en particulier pour turbine à gaz
EP2685163A1 (fr)	2012-07-10	2014-01-15	Alstom Technology Ltd	Brûleur de prémélange du type multi-cônes destiné à une turbine à gaz
EP2685162A1 (fr)	2012-07-10	2014-01-15	Alstom Technology Ltd	Brûleur de prémélange du type multi-cônes destiné à une turbine à gaz et procédé de fonctionnement d'un tel brûleur
EP2685160A1 (fr)	2012-07-10	2014-01-15	Alstom Technology Ltd	Brûleur de prémélange du type multi-cônes destiné à une turbine à gaz
EP3299720A1 (fr)	2016-09-22	2018-03-28	Ansaldo Energia IP UK Limited	Ensemble avant de chambre de combustion pour turbine à gaz

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
RU2168460C2 (ru) *	1999-07-14	2001-06-10	Кубиков Валентин Борисович	Коаксиальный смесительный элемент-горелка типа "газ-газ" для камер сгорания высокопроизводительных генераторов синтез-газа
DE10051221A1 (de) *	2000-10-16	2002-07-11	Alstom Switzerland Ltd	Brenner mit gestufter Brennstoff-Eindüsung
WO2006058843A1 (fr) *	2004-11-30	2006-06-08	Alstom Technology Ltd	Procede et dispositif de combustion d'hydrogene dans un bruleur a premelange
EP2257736B1 (fr)	2008-03-07	2015-11-25	Alstom Technology Ltd	Procédé de production de gaz chaud
JP5453322B2 (ja)	2008-03-07	2014-03-26	アルストムテクノロジーリミテッド	バーナ装置並びにバーナ装置の使用
GB2512894A (en) *	2013-04-10	2014-10-15	David Thomas Bell	Inward firing multiple zoned gas burner
KR101990767B1 (ko)	2017-08-09	2019-06-20	한국기계연구원	이중 원추형 가스터빈용 버너 및 이 버너에 공기를 공급하는 방법
DE102018005192B3 (de)	2018-07-02	2019-12-05	Truma Gerätetechnik GmbH & Co. KG	Brennervorrichtung
US11852319B2 (en) *	2021-02-26	2023-12-26	Armando Parra	Control means for vortex flame device

Citations (2)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
EP0321809B1 (fr)	1987-12-21	1991-05-15	BBC Brown Boveri AG	Procédé pour la combustion de combustible liquide dans un brûleur
EP0704657A2 (fr)	1994-10-01	1996-04-03	ABB Management AG	Brûleur

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
FR758974A (fr) *	1933-07-28	1934-01-26	Indugas Ind U Gasofen Bauges M	Brûleur à gaz à longueur de flamme réglable
US2665748A (en) *	1949-05-27	1954-01-12	Frank H Cornelius	Fuel burner
US3951584A (en) *	1974-05-23	1976-04-20	Midland-Ross Corporation	Self-stabilizing burner
US3975141A (en) *	1974-06-25	1976-08-17	The United States Of America As Represented By The Secretary Of The Army	Combustion liner swirler
US3958416A (en) *	1974-12-12	1976-05-25	General Motors Corporation	Combustion apparatus
CH680157A5 (fr) *	1989-12-01	1992-06-30	Asea Brown Boveri
DE4330083A1 (de) *	1993-09-06	1995-03-09	Abb Research Ltd	Verfahren zum Betrieb eines Vormischbrenners
DE4409918A1 (de) *	1994-03-23	1995-09-28	Abb Management Ag	Brenner zum Betrieb einer Brennkammer
DE19545036A1 (de) *	1995-12-02	1997-06-05	Abb Research Ltd	Vormischbrenner
DE19545310B4 (de) *	1995-12-05	2008-06-26	Alstom	Vormischbrenner

1996
- 1996-12-23 DE DE19654116A patent/DE19654116A1/de not_active Withdrawn
1997
- 1997-11-07 DE DE59710441T patent/DE59710441D1/de not_active Expired - Lifetime
- 1997-11-07 EP EP97810838A patent/EP0851172B1/fr not_active Expired - Lifetime
- 1997-11-20 US US08/975,301 patent/US5921770A/en not_active Expired - Fee Related

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
EP0321809B1 (fr)	1987-12-21	1991-05-15	BBC Brown Boveri AG	Procédé pour la combustion de combustible liquide dans un brûleur
EP0704657A2 (fr)	1994-10-01	1996-04-03	ABB Management AG	Brûleur

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
EP0959298A3 (fr) *	1998-05-18	2000-02-23	United Technologies Corporation	Injecteur de combustible à prémélange et son procédé de mise en oeuvre
EP0987491B1 (fr) *	1998-09-16	2005-07-20	ALSTOM Technology Ltd	Procédé pour prévenir les instabilités d'écoulement dans un brûleur
EP1001214B1 (fr) *	1998-11-09	2004-09-15	ALSTOM Technology Ltd	Brûleur
EP1002992B1 (fr) *	1998-11-18	2004-09-29	ALSTOM Technology Ltd	Brûleur
EP2423597A2 (fr)	2010-08-27	2012-02-29	Alstom Technology Ltd	Brûleur à prémélange pour une turbine à gaz
CH703655A1 (de) *	2010-08-27	2012-02-29	Alstom Technology Ltd	Vormischbrenner für eine gasturbine.
EP2423597A3 (fr) *	2010-08-27	2012-08-15	Alstom Technology Ltd	Brûleur à prémélange pour une turbine à gaz
US9170022B2 (en)	2010-08-27	2015-10-27	Alstom Technology Ltd	Premix burner for a gas turbine
EP2685163A1 (fr)	2012-07-10	2014-01-15	Alstom Technology Ltd	Brûleur de prémélange du type multi-cônes destiné à une turbine à gaz
EP2685162A1 (fr)	2012-07-10	2014-01-15	Alstom Technology Ltd	Brûleur de prémélange du type multi-cônes destiné à une turbine à gaz et procédé de fonctionnement d'un tel brûleur
EP2685160A1 (fr)	2012-07-10	2014-01-15	Alstom Technology Ltd	Brûleur de prémélange du type multi-cônes destiné à une turbine à gaz
US8950187B2 (en)	2012-07-10	2015-02-10	Alstom Technology Ltd	Premix burner of the multi-cone type for a gas turbine
RU2551706C2 (ru) *	2012-07-10	2015-05-27	Альстом Текнолоджи Лтд	Горелка предварительного смешивания многоконусного типа для газовой турбины
RU2561767C2 (ru) *	2012-07-10	2015-09-10	Альстом Текнолоджи Лтд	Горелка многоконусного типа предварительного смешивания для газовой турбины
EP2685161A1 (fr)	2012-07-10	2014-01-15	Alstom Technology Ltd	Agencement de chambre de combustion, en particulier pour turbine à gaz
RU2573090C2 (ru) *	2012-07-10	2016-01-20	Альстом Текнолоджи Лтд.	Узел камеры сгорания, в частности для газовой турбины
US9441837B2 (en)	2012-07-10	2016-09-13	General Electric Technology Gmbh	Premix burner of the multi-cone type for a gas turbine
US9933163B2 (en)	2012-07-10	2018-04-03	Ansaldo Energia Switzerland AG	Combustor arrangement with slidable multi-cone premix burner
EP3299720A1 (fr)	2016-09-22	2018-03-28	Ansaldo Energia IP UK Limited	Ensemble avant de chambre de combustion pour turbine à gaz

Also Published As

Publication number	Publication date
DE59710441D1 (de)	2003-08-21
EP0851172A3 (fr)	1999-06-09
EP0851172B1 (fr)	2003-07-16
US5921770A (en)	1999-07-13
DE19654116A1 (de)	1998-06-25

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2002-10-02	RTI1	Title (correction)	Free format text: BURNER AND METHOD FOR OPERATING A COMBUSTION CHAMBER WITH A LIQUID AND/OR GASEOUS FUEL
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Publication	Publication Date	Title
EP0851172B1 (fr)	2003-07-16	Brûleur et méthode pour la mise en oeuvre d'une chambre de combustion avec un combustible liquide et/ou gazeux
DE4426351B4 (de)	2006-04-06	Brennkammer für eine Gasturbine
EP0704657B1 (fr)	2001-11-07	Brûleur
EP0387532B1 (fr)	1994-11-30	Chambre de combustion d'une turbine à gaz
EP0401529B1 (fr)	1994-06-29	Chambre de combustion d'une turbine à gaz
EP0777081B1 (fr)	2003-03-05	Brûleur à prémélange
EP0718561B1 (fr)	2001-03-14	Brûleur
EP0481111B1 (fr)	1995-06-28	Chambre de combustion pour turbine à gaz
EP0918190A1 (fr)	1999-05-26	Brûleur pour la mise en oeuvre d'un générateur de chaleur
DE19757189B4 (de)	2008-05-08	Verfahren zum Betrieb eines Brenners eines Wärmeerzeugers
EP0780630A2 (fr)	1997-06-25	Brûleur pour un générateur de chaleur
EP0521325B1 (fr)	1996-09-25	Chambre de combustion
EP0775869A2 (fr)	1997-05-28	Brûleur à prémélange
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