EP1207350A2 - Chambre de combustion et procédé de fonctionnement associé - Google Patents

Chambre de combustion et procédé de fonctionnement associé Download PDF

Info

Publication number: EP1207350A2
Authority: EP; European Patent Office
Prior art keywords: combustion chamber; fuel; mixing zone; supporting air; lance
Prior art date: 2000-11-14
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

EP01126841A

Other languages

German (de)

English (en)

Other versions

EP1207350A3 (fr

EP1207350B1 (fr

Inventor

Marcel Stalder

Daniel Burri

Urs Benz

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 Schweiz AG

Alstom Power NV

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.)

2000-11-14

Filing date

2001-11-12

Publication date

2002-05-22

Family has litigation

First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=7663158&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=EP1207350(A2) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.

2001-11-12 Application filed by Alstom Schweiz AG, Alstom Power NV filed Critical Alstom Schweiz AG

2002-05-22 Publication of EP1207350A2 publication Critical patent/EP1207350A2/fr

2002-07-24 Publication of EP1207350A3 publication Critical patent/EP1207350A3/fr

2008-08-06 Application granted granted Critical

2008-08-06 Publication of EP1207350B1 publication Critical patent/EP1207350B1/fr

2021-11-12 Anticipated expiration legal-status Critical

Status Expired - Lifetime legal-status Critical Current

Images

Classifications

- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/46—Details
- F23D14/62—Mixing devices; Mixing tubes
- F23D14/64—Mixing devices; Mixing tubes with injectors
- 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
- F23D11/40—Mixing tubes; 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
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices

Definitions

the invention is a combustion chamber according to the Preamble of claim 4 or a method for operating the Combustion chamber according to the preamble of claim 1.
combustion chamber Ignition there is a combustion chamber Ignition known.
a Fuel lance fuel and supporting air introduced into a hot gas stream, mixed there and the mixture in a downstream Combustion zone burned.
the fuel lance is in one Mixing zone and is centrally located there. It is for about 10% of the Total volume flow through the channel dimensioned, the fuel can be injected transversely or in the direction of the flow.
the injected fuel is combined with a portion of supporting air several radial openings entrained by the vertebrae injected upstream and mixed with the main flow.
the injected fuel follows helical course of the vertebrae and is downstream in the chamber equally distributed. This reduces the risk of impact rays on the opposite channel wall as well as the formation of "hot spots", such as this is the case with an undisturbed flow.
the aim of this invention is to avoid the disadvantages mentioned.
the Invention solves the problem of a combustion chamber and a method of operation to create this combustion chamber with which it is possible to disrupt the To minimize hot gas flow in the mixing zone of the combustion chamber. This should happen with less cooling of the fuel lance and it should improve the behavior of the combustion chamber in all load ranges will achieve.
this is the case with a method according to the preamble of claim 1 achieved in that the fuel of at least one Side wall of the mixing zone of the combustion chamber is injected and it is at the combustion chamber according to the preamble of claim 4 thereby achieved that the at least one fuel lance in a side wall of the Mixing zone of the combustion chamber is embedded.
support air is also injected through this fuel lance.
An advantage of such a lateral, asymmetrical injection of the Fuel is in particular that only one through the fuel lance little flow disturbance is caused, which is this disturbance only on the side wall of the mixing zone and no longer centrally in the Main flow is located. It is also advantageous if at least a fuel lance in the form of a ball or one in Main flow direction extending ellipsoids in the side wall of the Combustion chamber is inserted and in the interior of the mixing zone Combustion chamber protrudes.
the mixing zone as a venturi channel or any additional internals (radial or circumferential) can increase the speed and thus improve it Mixing of hot gas and fuel / supporting air can be achieved. Trail areas behind the fuel lance, in which fuel can accumulate are practical due to this type of arrangement locked out.
the area of the seal between the sidewall of the Mixing zone and fuel lance is also advantageously small and in held advantageous shape.
An advantageous embodiment of the method according to the invention lies in that the fuel and any supporting air present in various fuel / supporting air mixture jets in the mixing zone of the Combustion chamber to be injected, the different Fuel / supporting air mixture jets in different directions or in different sectors directed within the mixing zone of the combustion chamber are.
This embodiment is particularly advantageous because depending on Utilization of the combustion chamber beams can be switched on or off.
This is also in combination with the internals mentioned above advantageous because with the targeted feeding of different sectors through the jets, the fuel at different pressures in different Areas within the mixing zone can be transported.
FIG. 1 shows a combustion chamber 1 according to the invention, which as one annular combustion chamber arranged around a shaft axis 9.
the Combustion chamber 1 consists of a vortex generator 14, a mixing zone 11 and from a combustion zone 12.
Such ring burner chambers are suitable very well in order to be operated as a self-igniting combustion chamber 1, the combustion chamber 1 then not between two, in the single figure shown turbines is placed.
the mixing zone 11, as shown in FIG. 1, is a venturi channel designed.
Another form of Cross section changes can be chosen as long as this is the improved Acceleration and mixing of fuel 4 and hot gases 5 is used.
the fuel lance 2 is in a side wall 6 of the Mixing zone 11 let in. The distribution of the fuel 3 and the supporting air 2 thus takes place asymmetrically with respect to the cross section of the mixing zone 11.
An advantage of such a lateral, asymmetrical injection of the Fuel 3 is in particular that the fuel lance 2 only one represents little disturbance of the flow, this disturbance merely being the side wall 6 of the mixing zone 11 and no longer centrally in the Main flow is located.
the Fuel lance 2 in the form of a ball or one in Main flow direction of the hot gas 5 extending ellipsoids in the Side wall 6 of the combustion chamber 1 embedded and protrudes into the interior of the Mixing zone 11 of the combustion chamber 1.
An advantageous embodiment of the method according to the invention lies in that the fuel 3 and any supporting air 4 in various fuel / supporting air mixture jets 7 into the mixing zone 11 the combustion chamber 1 are injected, the various Fuel / supporting air mixture jets 7 in different sectors or in different target spaces within the mixing zone 11 of the combustion chamber 1 are directed.
Figure 2 shows a section along the line II-II of the figure 1. There is the alignment of the rays 7 in different areas of the Mixing zone 11 clearly visible.
FIG. 3 also shows section III of FIG Figure 2 closer.
the supporting air 4 surrounds the fuel 3 in a jacket shape, the fuel jets as a plain jet be injected into the mixing zone. By choosing different Channels can use different types of fuel (gaseous / liquid) become.
Such an injection principle is in principle from the Publication EP-A1-1,030,109 known.
the use of different nozzle geometries is suitable for this purpose.
the embodiment of the beams 7 is therefore particularly advantageous since, depending on the load on the combustion chamber, beams 7 can be switched on or off. This means that the beams 7 are fed individually. Overall, the entire operating range can be increased from minimum to maximum fuel quantity. An improved part-load behavior is thus achieved, which has a positive effect with regard to pollutant behavior, i.e. formation of CO, NO x , UHC, etc.
the arrangement of the fuel lances 2 according to the invention is therefore also advantageous because trailing areas behind the fuel lance 2, in which Fuel 3 can accumulate, are practically completely excluded.
the cross section of the mixing zone 11 for example as Venturi channel or any additional internals (radial or in Circumferential direction) within the mixing zone 11 can increase the Speed and thus an improved mixing of hot gas 5 and fuel 3 / supporting air 4 can be reached.
This is also in combination with the built-in components mentioned are therefore advantageous because with the targeted feed of different sectors through the rays 7, the fuel 3 at same pressure can be transported in different sectors.

Landscapes

Engineering & Computer Science (AREA)
Chemical & Material Sciences (AREA)
Combustion & Propulsion (AREA)
Mechanical Engineering (AREA)
General Engineering & Computer Science (AREA)
Fluidized-Bed Combustion And Resonant Combustion (AREA)
Pre-Mixing And Non-Premixing Gas Burner (AREA)

EP01126841A 2000-11-14 2001-11-12 Chambre de combustion et procédé de fonctionnement associé Expired - Lifetime EP1207350B1 (fr)

Applications Claiming Priority (2)

Application Number	Priority Date	Filing Date	Title
DE10056243		2000-11-14
DE10056243A DE10056243A1 (de)	2000-11-14	2000-11-14	Brennkammer und Verfahren zum Betrieb dieser Brennkammer

Publications (3)

Publication Number	Publication Date
EP1207350A2 true EP1207350A2 (fr)	2002-05-22
EP1207350A3 EP1207350A3 (fr)	2002-07-24
EP1207350B1 EP1207350B1 (fr)	2008-08-06

Family

ID=7663158

Family Applications (1)

Application Number	Title	Priority Date	Filing Date
EP01126841A Expired - Lifetime EP1207350B1 (fr)	2000-11-14	2001-11-12	Chambre de combustion et procédé de fonctionnement associé

Country Status (4)

Country	Link
US (1)	US6688111B2 (fr)
EP (1)	EP1207350B1 (fr)
JP (1)	JP2002162037A (fr)
DE (2)	DE10056243A1 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
EP1400752A1 (fr) *	2002-09-20	2004-03-24	Siemens Aktiengesellschaft	Brûleur à prémélange avec un écoulement d'air profilé
WO2004025183A2 (fr)	2002-09-02	2004-03-25	Siemens Aktiengesellschaft	Bruleur
EP1512912A2 (fr)	2003-09-04	2005-03-09	Rolls-Royce Deutschland Ltd & Co KG	Mélange homogène obtenu par injection tourbillonnaire du carburant
WO2009109448A1 (fr) *	2008-03-07	2009-09-11	Alstom Technology Ltd	Ensemble brûleur et son utilisation
US8057224B2 (en) *	2004-12-23	2011-11-15	Alstom Technology Ltd.	Premix burner with mixing section
CN115899763A (zh) *	2022-11-30	2023-04-04	南京航空航天大学	一种加力或冲压燃烧室尾缘剪切强化火焰稳定器

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
DE10348604A1 (de) *	2003-10-20	2005-07-28	Rolls-Royce Deutschland Ltd & Co Kg	Kraftstoffeinspritzdüse mit filmartiger Kraftstoffplatzierung
EP1730447A1 (fr) *	2004-03-31	2006-12-13	Alstom Technology Ltd	Brûleur
DE102006051286A1 (de) *	2006-10-26	2008-04-30	Deutsches Zentrum für Luft- und Raumfahrt e.V.	Brennervorrichtung
NO326633B1 (no) *	2006-12-28	2009-01-26	Age Jorgen Skomsvold	Fremgangsmate og anordning for motor- og kompresjonsprosess
DE102007043626A1 (de) *	2007-09-13	2009-03-19	Rolls-Royce Deutschland Ltd & Co Kg	Gasturbinenmagerbrenner mit Kraftstoffdüse mit kontrollierter Kraftstoffinhomogenität
EP2116767B1 (fr) *	2008-05-09	2015-11-18	Alstom Technology Ltd	Brûleur avec lance
EP2211110B1 (fr) *	2009-01-23	2019-05-01	Ansaldo Energia Switzerland AG	Brûleur pour turbine à gaz
US8667800B2 (en) *	2009-05-13	2014-03-11	Delavan Inc.	Flameless combustion systems for gas turbine engines
ES2462974T3 (es) *	2010-08-16	2014-05-27	Alstom Technology Ltd	Quemador de recalentamiento
CN104204680B (zh) *	2012-03-23	2016-01-06	阿尔斯通技术有限公司	燃烧装置
US9677766B2 (en)	2012-11-28	2017-06-13	General Electric Company	Fuel nozzle for use in a turbine engine and method of assembly
US9599343B2 (en)	2012-11-28	2017-03-21	General Electric Company	Fuel nozzle for use in a turbine engine and method of assembly
US12159497B2 (en)	2014-12-02	2024-12-03	Carrier Corporation	Remote programming for access control system with virtual card data
WO2016089837A1 (fr)	2014-12-02	2016-06-09	Carrier Corporation	Capture d'intention d'utilisateur lors d'une interaction avec une pluralité de commandes d'accès
EP3228107B1 (fr)	2014-12-02	2021-03-24	Carrier Corporation	Système de commande d'accès avec des données de carte virtuelle
ES2923690T3 (es)	2014-12-02	2022-09-29	Carrier Corp	Sistema de control de acceso con traspaso de servicio de acreditación móvil automático

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DE4417538A1 (de)	1994-05-19	1995-11-23	Abb Management Ag	Brennkammer mit Selbstzündung
EP1030109A1 (fr)	1999-02-15	2000-08-23	ABB Alstom Power (Schweiz) AG	Injecteur de combustible pour l'injection de combustibles liquides et/ou gazeux dans une chambre de combustion

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GB2012415B (en) *	1978-01-04	1982-03-03	Secr Defence	Fuel mixers
US4420929A (en) *	1979-01-12	1983-12-20	General Electric Company	Dual stage-dual mode low emission gas turbine combustion system
EP0358437B1 (fr) *	1988-09-07	1995-07-12	Hitachi, Ltd.	Dispositif de prémélange air-carburant pour une turbine à gaz
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EP0577862B1 (fr) *	1992-07-03	1997-03-12	Abb Research Ltd.	Dispositif de post-combustion
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GB9321505D0 (en) *	1993-10-19	1993-12-08	Europ Gas Turbines Ltd	Fuel injector
DE4408256A1 (de) *	1994-03-11	1995-09-14	Abb Management Ag	Verfahren und Vorrichtung zur Flammenstabilisation von Vormischbrennern
DE4426351B4 (de) *	1994-07-25	2006-04-06	Alstom	Brennkammer für eine Gasturbine
DE19510743A1 (de) *	1995-02-20	1996-09-26	Abb Management Ag	Brennkammer mit Zweistufenverbrennung
DE19527453B4 (de) *	1995-07-27	2009-05-07	Alstom	Vormischbrenner
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AU7357298A (en) *	1997-03-26	1998-10-20	San Diego State University Foundation	Fuel/air mixing device for jet engines
US5850732A (en) *	1997-05-13	1998-12-22	Capstone Turbine Corporation	Low emissions combustion system for a gas turbine engine
EP0919768B1 (fr) *	1997-11-25	2003-02-05	Alstom	Brûleur pour la mise en oeuvre d'un générateur de chaleur
DE19859829A1 (de) *	1998-12-23	2000-06-29	Abb Alstom Power Ch Ag	Brenner zum Betrieb eines Wärmeerzeugers

2000
- 2000-11-14 DE DE10056243A patent/DE10056243A1/de not_active Ceased
2001
- 2001-11-12 DE DE50114185T patent/DE50114185D1/de not_active Expired - Lifetime
- 2001-11-12 EP EP01126841A patent/EP1207350B1/fr not_active Expired - Lifetime
- 2001-11-13 US US09/987,117 patent/US6688111B2/en not_active Expired - Lifetime
- 2001-11-14 JP JP2001349121A patent/JP2002162037A/ja active Pending

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Publication number	Priority date	Publication date	Assignee	Title
DE4417538A1 (de)	1994-05-19	1995-11-23	Abb Management Ag	Brennkammer mit Selbstzündung
EP1030109A1 (fr)	1999-02-15	2000-08-23	ABB Alstom Power (Schweiz) AG	Injecteur de combustible pour l'injection de combustibles liquides et/ou gazeux dans une chambre de combustion

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
WO2004025183A2 (fr)	2002-09-02	2004-03-25	Siemens Aktiengesellschaft	Bruleur
WO2004025183A3 (fr) *	2002-09-02	2005-01-20	Siemens Ag	Bruleur
US7753677B2 (en)	2002-09-02	2010-07-13	Siemens Aktiengesellschaft	Burner
EP1400752A1 (fr) *	2002-09-20	2004-03-24	Siemens Aktiengesellschaft	Brûleur à prémélange avec un écoulement d'air profilé
EP1512912A2 (fr)	2003-09-04	2005-03-09	Rolls-Royce Deutschland Ltd & Co KG	Mélange homogène obtenu par injection tourbillonnaire du carburant
EP1512912A3 (fr) *	2003-09-04	2010-10-27	Rolls-Royce Deutschland Ltd & Co KG	Mélange homogène obtenu par injection tourbillonnaire du carburant
US8057224B2 (en) *	2004-12-23	2011-11-15	Alstom Technology Ltd.	Premix burner with mixing section
WO2009109448A1 (fr) *	2008-03-07	2009-09-11	Alstom Technology Ltd	Ensemble brûleur et son utilisation
CN115899763A (zh) *	2022-11-30	2023-04-04	南京航空航天大学	一种加力或冲压燃烧室尾缘剪切强化火焰稳定器

Also Published As

Publication number	Publication date
US6688111B2 (en)	2004-02-10
DE10056243A1 (de)	2002-05-23
JP2002162037A (ja)	2002-06-07
US20030093997A1 (en)	2003-05-22
EP1207350A3 (fr)	2002-07-24
DE50114185D1 (de)	2008-09-18
EP1207350B1 (fr)	2008-08-06

Publication	Publication Date	Title
EP1207350A2 (fr)	2002-05-22	Chambre de combustion et procédé de fonctionnement associé
DE19615910B4 (de)	2006-09-14	Brenneranordnung
EP0675322B1 (fr)	1999-04-28	Brûleur à prémélange
DE69412572T2 (de)	1999-04-29	Hybridbrenner einer Gasturbine
EP0781967B1 (fr)	2003-04-02	Chambre de combustion annulaire pour turbine à gaz
DE3222347C2 (fr)	1988-06-01
EP0687860B1 (fr)	2001-02-28	Chambre de combustion à allumage automatique
EP1723369B1 (fr)	2007-07-18	Bruleur a premelange et procede pour bruler un gaz pauvre
DE69918744T2 (de)	2005-07-21	Gasturbinenbrennkammer
DE60037850T2 (de)	2009-01-22	Flüssigbrennstoffeinspritzdüse für Gasturbinenbrenner
DE19502796B4 (de)	2004-10-28	Brenner
DE69525920T2 (de)	2002-09-19	Brennstoffeinspritzeinrictung für mit gasförmigem oder flüssigem Brennstoff betriebene Turbine
EP0924470B1 (fr)	2003-06-18	Chambre de combustion à prémélange pour turbine à gaz
EP0694740A2 (fr)	1996-01-31	Chambre de combustion
DE102010037412B4 (de)	2022-07-28	Zweibrennstoffdüse für eine Turbomaschine
DE3029095A1 (de)	1981-02-12	Doppelbrennstoffinjektor fuer gasturbinentriebwerke
DE4415315A1 (de)	1995-11-09	Kraftwerksanlage
DE19510744A1 (de)	1996-09-26	Brennkammer mit Zweistufenverbrennung
EP1828684A1 (fr)	2007-09-05	Bruleur de premelange dote d'un parcours de melange
DE4113681A1 (de)	1992-09-17	Brenner fuer eine vormischverbrennung eines fluessigen und/oder gasfoermigen brennstoffes
EP0718561A2 (fr)	1996-06-26	Brûleur
DE4446611A1 (de)	1996-06-27	Brennkammer
EP0777081A2 (fr)	1997-06-04	Brûleur à prémélange
EP0394800B1 (fr)	1993-11-18	Brûleur à mélange préalable pour la génération de gaz chaud
EP0775869A2 (fr)	1997-05-28	Brûleur à prémélange

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