EP0683356A2 - Procédé de fonctionnement d'une chambre de combustion - Google Patents

Procédé de fonctionnement d'une chambre de combustion Download PDF

Info

Publication number: EP0683356A2
Authority: EP; European Patent Office
Prior art keywords: fuel; zone; combustion chamber; lances; combustion
Prior art date: 1994-05-19
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

EP95810290A

Other languages

German (de)

English (en)

Other versions

EP0683356A3 (fr

EP0683356B1 (fr

Inventor

Rolf Dr. Althaus

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 Management AG

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.)

1994-05-19

Filing date

1995-05-03

Publication date

1995-11-22

1995-05-03 Application filed by ABB Management AG filed Critical ABB Management AG

1995-11-22 Publication of EP0683356A2 publication Critical patent/EP0683356A2/fr

1997-06-18 Publication of EP0683356A3 publication Critical patent/EP0683356A3/fr

2001-01-17 Application granted granted Critical

2001-01-17 Publication of EP0683356B1 publication Critical patent/EP0683356B1/fr

2015-05-03 Anticipated expiration legal-status Critical

Status Expired - Lifetime legal-status Critical Current

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Images

Classifications

- 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
- F23C5/00—Disposition of burners with respect to the combustion chamber or to one another; Mounting of burners in combustion apparatus
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D23/00—Assemblies of two or more burners
- 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

Definitions

the present invention relates to a method according to the preamble of claim 1. It also relates to a combustion chamber for carrying out the method.
the invention seeks to remedy this.
the object of the invention is to minimize, in particular, the CO and UHC emissions in the critical range between auto-ignition and a temperature of approximately 1100 ° C. in a method and a combustion chamber of the type mentioned at the outset .
the burners should be divided into at least two groups.
the individual groups are run in series from the auto-ignition point to at least 1100 ° C.
the group of burners used is supplied on average with a larger amount of fuel during the starting phase; the individual burners can thus be operated more stably. If all burner groups up to a temperature level of approx. 1100 ° C have been retightened, they are then raised in parallel from this temperature level to the desired operating temperature.
annular combustion chamber 1 shows, as can be seen from the shaft axis 16, an annular combustion chamber 1, which essentially has the shape of a coherent annular or quasi-annular cylinder.
a combustion chamber can also consist of a number of axially, quasi-axially or helically arranged and individually closed combustion chambers.
Such ring combustion chambers are excellently suited to be operated as self-igniting combustion chambers which are placed in the flow direction between two turbines mounted on a shaft. If such an annular combustion chamber 1 is operated on self-ignition, the upstream turbine 2 is only designed for partial relaxation of the hot gases 3, so that the exhaust gases 4 downstream of this turbine 2 still flow into the inflow zone 5 of the annular combustion chamber 1 at a very high temperature.
This inflow zone 5 is equipped on the inside and in the circumferential direction of the channel wall 6 with a series of vortex-generating elements 100, hereinafter only called vortex generators.
the exhaust gases 4 are swirled by the vortex generators 100 such that no recirculation areas occur in the wake of the vortex generators 100 mentioned in the subsequent premixing section 7.
this premixing section 7 which is designed as a Venturi channel, a plurality of fuel lances 8 are arranged, which take over the supply of a fuel 9 and supporting air 10. These fuel lances 8 are discussed in more detail below. These media can be supplied to the individual fuel lances 8, for example, via a ring line (not shown).
the swirl flow triggered by the vortex generators 100 provides for a large-scale distribution of the introduced fuel 9, and possibly also the admixed supporting air 10. Furthermore, the swirl flow ensures a homogenization of the mixture of combustion air and fuel.
the fuel 9 injected into the exhaust gases 4 by the fuel lance 8 triggers self-ignition if these exhaust gases 4 have the specific temperature which the fuel-dependent auto-ignition is capable of triggering. If the ring combustion chamber 1 is operated with a gaseous fuel, a temperature of the exhaust gases 4 above approx. 850 ° C. must be present for the initiation of self-ignition. With such a combustion, as already appreciated above, there is a risk of a flashback. This problem is remedied by, on the one hand, designing the premixing zone 7 as a venturi channel and, on the other hand, disposing the injection of the fuel 9 in the region of the largest constriction within the premixing zone 7.
a combustion zone 11 follows the relatively short premixing zone 7.
the transition between the two zones is formed by a radial cross-sectional jump 12, which initially induces the flow cross-section of the combustion zone 11.
the cross-sectional jump 12 is also a flame front. In order to prevent the flame from reigniting into the interior of the premixing zone 7, the flame front must be kept stable.
the vortex generators 100 are designed such that no recirculation takes place in the premixing zone 7; only after the sudden widening of the cross section is the burst of the swirl flow desired.
the swirl flow supports the rapid re-application of the flow behind the cross-sectional jump 12, so that a high burn-out with a short overall length can be achieved by utilizing the volume of the combustion zone 11 as fully as possible.
a flow-like edge zone is formed during operation, in which vortex detachments occur due to the prevailing negative pressure, which then lead to stabilization of the flame front.
the exhaust gases 4 processed into combustion gases 11 into hot gases 14 subsequently act on a further turbine 14 acting downstream.
the exhaust gases 15 can then be used to operate a steam cycle, in which case the system is a combination system.
FIG. 2 shows a diagram in which the stepped mode of operation of the burners can be seen during the starting phase.
the abscissa 17 intends to symbolize the development of the burners arranged next to one another, while the ordinate 18 shows the first temperature levels approached during the starting phase.
the staged procedure consists in that the burners, ie the fuel lances from FIG. 1, are supplied with fuel in series during the starting phase.
the fuel lances 8a, 8c, etc. are put into operation and are first brought up to approximately 1100 ° C.
the remaining fuel lances 8b, 8d, etc. are also drawn up to the above-mentioned temperature level of approx. 1100 ° C.
this driving style has the additional advantage that CO and UHC emissions in particular can be significantly reduced in the critical range between 1000 ° C and 1100 ° C.
the staged driving style during the starting phase is not limited to 2 groups of burners.
the abscissa 22 shows the load range, zero being the temperature level at which the self-ignition of the mixture takes place, that is to say from about 850 ° C. in our case.
the ordinate 23 shows the degree of pollutant emissions.
Curve 24 shows the course of the pollutant emissions in a conventional, non-stepped driving style. The tip symbolizes the CO and UHC emissions in the interval between approx. 1000 ° C and approx. 1100 ° C.
the stepped driving style is different, as curve 25 shows.
a two-hump curve is recognizable here, corresponding to the stepped mode of operation with two burner groups.
the staged driving style can achieve emission values that are more than half smaller than the conventional driving style.

Landscapes

Engineering & Computer Science (AREA)
Chemical & Material Sciences (AREA)
Combustion & Propulsion (AREA)
Mechanical Engineering (AREA)
General Engineering & Computer Science (AREA)
Combustion Of Fluid Fuel (AREA)

EP95810290A 1994-05-19 1995-05-03 Procédé de fonctionnement d'une chambre de combustion et chambre de combustion Expired - Lifetime EP0683356B1 (fr)

Applications Claiming Priority (2)

Application Number	Priority Date	Filing Date	Title
DE4417536		1994-05-19
DE4417536A DE4417536A1 (de)	1994-05-19	1994-05-19	Verfahren zum Betrieb einer Brennkammer

Publications (3)

Publication Number	Publication Date
EP0683356A2 true EP0683356A2 (fr)	1995-11-22
EP0683356A3 EP0683356A3 (fr)	1997-06-18
EP0683356B1 EP0683356B1 (fr)	2001-01-17

Family

ID=6518481

Family Applications (1)

Application Number	Title	Priority Date	Filing Date
EP95810290A Expired - Lifetime EP0683356B1 (fr)	1994-05-19	1995-05-03	Procédé de fonctionnement d'une chambre de combustion et chambre de combustion

Country Status (5)

Country	Link
US (1)	US5609017A (fr)
EP (1)	EP0683356B1 (fr)
JP (1)	JPH07318008A (fr)
CN (1)	CN1116697A (fr)
DE (2)	DE4417536A1 (fr)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
DE19545311B4 (de) *	1995-12-05	2006-09-14	Alstom	Verfahren zur Betrieb einer mit Vormischbrennern bestückten Brennkammer
EP1096201A1 (fr) *	1999-10-29	2001-05-02	Siemens Aktiengesellschaft	Brûleur
JP4508474B2 (ja) *	2001-06-07	2010-07-21	三菱重工業株式会社	燃焼器
CN100434796C (zh) *	2006-11-13	2008-11-19	中国第一冶金建设有限责任公司	蓄热式加热炉炉墙内的烧嘴、空气通道、煤气通道施工方法
CN102175085A (zh) *	2010-12-29	2011-09-07	天津二十冶建设有限公司	具有蓄热式烧嘴的加热炉炉墙整体浇筑施工方法
EP3081862B1 (fr) *	2015-04-13	2020-08-19	Ansaldo Energia Switzerland AG	Agencement de génération de vortex pour un brûleur à pré-mélange d'une turbine à gaz et turbine à gaz avec un tel agencement de génération de vortex
CN104896511B (zh) *	2015-05-29	2017-03-22	北京航空航天大学	一种用于低排放燃烧室的燃油预混装置

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
US2716863A (en) *	1950-07-04	1955-09-06	Onera (Off Nat Aerospatiale)	Continuous flow and internal combustion engines, and in particular turbojets or turbo-props
DE1277639B (de) *	1966-01-28	1968-09-12	M A N Turbo G M B H	Zusatzverbrennungsvorrichtung fuer die Aufheizung der Gase eines Turbinenstrahltriebwerkes
US3600891A (en) *	1969-12-18	1971-08-24	United Aircraft Corp	Variable area nozzle
US3691762A (en) *	1970-12-04	1972-09-19	Caterpillar Tractor Co	Carbureted reactor combustion system for gas turbine engine
US3958416A (en) *	1974-12-12	1976-05-25	General Motors Corporation	Combustion apparatus
FR2392231A1 (fr) *	1977-05-23	1978-12-22	Inst Francais Du Petrole	Turbine a gaz comportant une chambre de combustion entre les etages de la turbine
US4215535A (en) *	1978-01-19	1980-08-05	United Technologies Corporation	Method and apparatus for reducing nitrous oxide emissions from combustors
US4246757A (en) *	1979-03-27	1981-01-27	General Electric Company	Combustor including a cyclone prechamber and combustion process for gas turbines fired with liquid fuel
US4373325A (en) *	1980-03-07	1983-02-15	International Harvester Company	Combustors
DE3534268A1 (de) *	1985-09-26	1987-04-02	Deutsche Forsch Luft Raumfahrt	Zur vermeidung von stroemungsabloesungen ausgebildete oberflaeche eines umstroemten koerpers
CH674561A5 (fr) *	1987-12-21	1990-06-15	Bbc Brown Boveri & Cie
JP2772955B2 (ja) *	1988-07-08	1998-07-09	株式会社日本ケミカル・プラント・コンサルタント	燃焼器用の燃料混合器
JPH0579629A (ja) *	1991-09-19	1993-03-30	Hitachi Ltd	燃焼器およびその運転方法
US5263325A (en) *	1991-12-16	1993-11-23	United Technologies Corporation	Low NOx combustion
CH687269A5 (de) *	1993-04-08	1996-10-31	Abb Management Ag	Gasturbogruppe.
US5487274A (en) *	1993-05-03	1996-01-30	General Electric Company	Screech suppressor for advanced low emissions gas turbine combustor
GB9325708D0 (en) *	1993-12-16	1994-02-16	Rolls Royce Plc	A gas turbine engine combustion chamber

1994
- 1994-05-19 DE DE4417536A patent/DE4417536A1/de not_active Withdrawn
1995
- 1995-04-24 US US08/427,590 patent/US5609017A/en not_active Expired - Fee Related
- 1995-05-03 EP EP95810290A patent/EP0683356B1/fr not_active Expired - Lifetime
- 1995-05-03 DE DE59508963T patent/DE59508963D1/de not_active Expired - Fee Related
- 1995-05-17 JP JP7118690A patent/JPH07318008A/ja active Pending
- 1995-05-18 CN CN95106318A patent/CN1116697A/zh active Pending

Also Published As

Publication number	Publication date
EP0683356A3 (fr)	1997-06-18
DE59508963D1 (de)	2001-02-22
DE4417536A1 (de)	1995-11-23
US5609017A (en)	1997-03-11
CN1116697A (zh)	1996-02-14
JPH07318008A (ja)	1995-12-08
EP0683356B1 (fr)	2001-01-17

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2000-05-17	RAP1	Party data changed (applicant data changed or rights of an application transferred)	Owner name: ABB ALSTOM POWER (SCHWEIZ) AG
2000-05-24	RTI1	Title (correction)	Free format text: METHOD FOR OPERATING A COMBUSTION CHAMBER AND COMBUSTION CHAMBER
2000-06-28	RTI1	Title (correction)	Free format text: METHOD FOR OPERATING A COMBUSTION CHAMBER AND COMBUSTION CHAMBER
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