EP0964206A1 - Brennkammer einer Gasturbine mit verstellbarer Geometrie - Google Patents

Brennkammer einer Gasturbine mit verstellbarer Geometrie Download PDF

Info

Publication number: EP0964206A1
Authority: EP; European Patent Office
Prior art keywords: combustion chamber; combustion; injection; chamber according; oxidant
Prior art date: 1998-06-11
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

EP99401204A

Other languages

English (en)

French (fr)

Other versions

EP0964206B1 (de

Inventor

Guy Grienche

Gérard Schott

Jean-Hervé Le Gal

Gérard Martin

Patrice Laborde

Raphael Spagne

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.)

IFP Energies Nouvelles IFPEN

Safran Helicopter Engines SAS

Original Assignee

IFP Energies Nouvelles IFPEN

Turbomeca SA

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.)

1998-06-11

Filing date

1999-05-18

Publication date

1999-12-15

1999-05-18 Application filed by IFP Energies Nouvelles IFPEN, Turbomeca SA filed Critical IFP Energies Nouvelles IFPEN

1999-12-15 Publication of EP0964206A1 publication Critical patent/EP0964206A1/de

2004-12-08 Application granted granted Critical

2004-12-08 Publication of EP0964206B1 publication Critical patent/EP0964206B1/de

2019-05-18 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
- 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
- F23R3/346—Feeding into different combustion zones for staged 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
- F23R3/26—Controlling the air flow

Definitions

the present invention relates to the field of gas turbines and more particularly combustion chambers associated with such turbines.
One of the problems at the origin of the present invention relates to the pollution caused by the operation of these turbines. More specifically, emissions of nitrogen oxides (NOx) and carbon monoxide carbon (CO) should be reduced as these are the most harmful to the environment.
NOx nitrogen oxides
CO carbon monoxide carbon
Nitrogen oxides are mainly thermal nitrogen oxides which form at high temperature, that is to say beyond 1700 K in combustion chambers of gas turbines where the fumes have times of stay generally between 2 and 10 milliseconds.
Carbon monoxide (CO) is formed at a lower temperature ( ⁇ 1600 K), by incomplete combustion of the fuel.
Figure 1 illustrates, by curves (CO and NOx), the respective emissions carbon monoxide and nitrogen oxides as a function of temperature T (in K) under the operating conditions of a combustion of a gas turbine.
NO x and CO emissions are thus directly linked to the richness of the air-fuel mixture in the combustion chamber; that is, the ratio between the air flow and the fuel flow. Knowing that the richness of the mixture must be imposed, if one seeks to operate within a certain temperature range. such as that mentioned above, the adiabatic flame temperature of the mixture will vary approximately in proportion to the richness.
the fuel flow is the only parameter to control the operating regime of the turbine. It follows that for a given fuel flow, the air flow is perfectly set to a value depending only on the characteristics of the machine and in particular of the passage sections in the hearth. Through wealth is then completely determined.
Another concept for obtaining operating combustion chambers over a determined temperature range consists of equipping it with a set of shutters. valves or other sealing means allow check the air flow in the fireplace.
the command and actuation of such elements is complex, delicate to implement. The assembly is also expensive.
the present invention therefore aims to provide a reliable, simple solution to the problem of wealth regulation in a combustion of a gas turbine.
the object of this control is to be able to carry out combustion in an optimal temperature range with regard in particular to carbon monoxide, and nitrogen oxides.
the present invention thus allows automatic regulation of the combustion air flow.
a mechanical servo is advantageously achieved thanks to a very limited number of parts mechanical.
the subject of the invention is a gas turbine combustion chamber comprising at least one so-called pilot injection zone in which lead to at least a first pilot fuel injection means and a first means of injecting associated oxidizer; a combustion zone main which leads to at least a second plea main fuel injection and a second injection means of associated oxidizer, the assembly being maintained under a pressure P1 to inside an enclosure.
said combustion chamber further comprises a mechanical means for regulating the second oxidant flow, which reacts to the pressure difference between the interior (P1) and the pressure atmospheric (Po) outside the enclosure, said pressure difference being directly linked to the engine speed.
said regulating means comprises at least one obturation element which more or less blocks the second air inlets in the combustion chamber, several connecting rods between the elements shutter and a support element, a compression element, a sealing bellows placed around the delimiting compression element with the support element the volume at atmospheric pressure (Po) opposite of the pressure vessel (P1).
first fuel injection means and the first oxidant injection means are arranged substantially at proximity to the longitudinal axis (XX ') of the combustion chamber.
the second means main fuel injection and the second means of injecting oxidizer are arranged on a circumference, downstream of the pilot combustion relative to the direction of flame propagation.
the combustion chamber according to the invention comprises a third means of injecting oxidizer which opens into the combustion, downstream of the second oxidant injection means relative to the direction of flame propagation.
the means for regulating the second oxidizer flow rate allows the flow rate of the third air injection means to be regulated (function of bypass).
the compression member may include a stack of washers or springs.
the room comprises three areas for grouping the second main means of injection of fuel (7) and main oxidant injection (8), each zone being angularly spaced 120 ° C.
the hearth 1 is delimited by an internal ferrule 2 which presents here two different diameters: the smallest diameter contains the pilot combustion area 11 while the larger diameter area 12 is that where the main combustion takes place.
Pilot combustion zone 11 ensures idling combustion and combustion can be maintained there during the other regimes of operation.
injectors 3 of fuel such as for example natural gas and injectors or air inlets 4.
a bottom 5 is provided to delimit zone 11. Arrivals from fuel 3 and air 4 are located near the bottom 5, circumferentially, and not far from the longitudinal axis XX 'of the chamber.
the pilot combustion zone 11 is a flame stability zone, where a flame exists whatever the operating conditions.
Air rotation fins 6 can be provided at the air intake level 4.
the fuel injectors 3 can be installed in these fins without departing from the scope of the invention.
Zone 12 therefore has a larger diameter than that of the zone 11: this is where the main combustion takes place.
a second fuel injection means 7 is arranged at the boundary between zones 11 and 12.
a second injection means air 8 is located near the second fuel injector 7.
Des fins 9 can also be arranged at the level of injectors 8.
the means 7, 8 and 9 are located on a circumference of the shell 2, and several groupings can be provided. Here three groups are planned, each angularly spaced 120 °.
so-called “dilution” air that is to say that does not participate in the combustion or cooling of the walls can be introduced into the shell 2, downstream of the combustion zone 12, via suitable orifices 22.
the general air supply is through an annular space 13 delimited by the ferrule 2 and an outer envelope 14.
a pressure P2 reign in this space; this pressure is slightly higher than the pressure P1, the difference being due to the pressure losses created by the different air inlet ports.
the present invention provides a means flow control, which reacts to the pressure difference between the space annular (P2) and the outside of the enclosure 14 or a pressure Po prevails (Atmosphérique atmospheric pressure).
the regulating means comprises a ferrule 15 capable of sliding along the axis XX 'in front of the openings 8 (preferably equipped with fins 9) and therefore allowing a variation of the air passage section.
the ferrule 15 is fixed, by any means known per se, to the end lower of several rods 16. At their other end, the rods 16 carry a support plate 17 which is itself linked to a compression element 18. A stack of conical washers or springs can be provided for this purpose.
a bellows 19 or other sealing means is also provided. around the compression element 18.
the bellows 19 is a separation between the interior volume of the combustion chamber, where the pressures P2 and P1, and the external volume where the pressure Po prevails.
ferrule 15 can be provided with additional openings which connect the space 13 and an annular space 21 inside the ferrule 2.
an additional ferrule 20, coaxial with the ferrule 2 is provided over part of the height of ferrule 2.
the ferrule 20 may have a height which corresponds to the zone 12 combustion. On this height, the air coming from the openings 10 and which passes in the annular space 21, will make it possible to reject air downstream of the combustion zone 12 while cooling the walls of said combustion zone combustion 12. It is thus possible to maintain an acceptable richness within the main focus regardless of the diet.
the main effect of bypass 21 is to limit the decrease in wealth in household 1, especially at diet partial.
the openings 10 are designed so that at full load, no air passes through them (case of figure 4), while at load partial or weak, air passes into space 21 in order to be rejected downstream of the combustion zone 12 while cooling the wall of the shell 2.
the openings 10 are rather largely open from so that air can pass through the space 21 and cool the wall 20, without participate in combustion in zone 12. It is thus possible to maintain a acceptable richness in it and avoid high CO emissions.
combustion chamber according to the invention does does not require a specific mechanical device for regulating arrivals of air. Regulation takes place here by itself, by the relative pressure in the combustion chamber and therefore depending on the engine speed.

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

EP99401204A 1998-06-11 1999-05-18 Brennkammer einer Gasturbine mit verstellbarer Geometrie Expired - Lifetime EP0964206B1 (de)

Applications Claiming Priority (2)

Application Number	Priority Date	Filing Date	Title
FR9807409		1998-06-11
FR9807409A FR2779807B1 (fr)	1998-06-11	1998-06-11	Chambre de combustion de turbine a gaz a geometrie variable

Publications (2)

Publication Number	Publication Date
EP0964206A1 true EP0964206A1 (de)	1999-12-15
EP0964206B1 EP0964206B1 (de)	2004-12-08

Family

ID=9527308

Family Applications (1)

Application Number	Title	Priority Date	Filing Date
EP99401204A Expired - Lifetime EP0964206B1 (de)	1998-06-11	1999-05-18	Brennkammer einer Gasturbine mit verstellbarer Geometrie

Country Status (5)

Country	Link
US (1)	US6263663B1 (de)
EP (1)	EP0964206B1 (de)
JP (1)	JP4435331B2 (de)
DE (1)	DE69922437T2 (de)
FR (1)	FR2779807B1 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
EP1777459A2 (de) *	2005-10-24	2007-04-25	Kawasaki Jukogyo Kabushiki Kaisha	Gasturbinenbrennkammer
US11242992B2 (en)	2017-04-11	2022-02-08	Office National D'etudes Et De Recherches Aerospatiales	Self-adapting gas turbine firebox with variable geometry

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
US7788897B2 (en) *	2004-06-11	2010-09-07	Vast Power Portfolio, Llc	Low emissions combustion apparatus and method
JP4670035B2 (ja) *	2004-06-25	2011-04-13	独立行政法人宇宙航空研究開発機構	ガスタービン燃焼器
US8915086B2 (en)	2006-08-07	2014-12-23	General Electric Company	System for controlling combustion dynamics and method for operating the same
GB0815761D0 (en) *	2008-09-01	2008-10-08	Rolls Royce Plc	Swirler for a fuel injector
US8099941B2 (en) *	2008-12-31	2012-01-24	General Electric Company	Methods and systems for controlling a combustor in turbine engines
US8276386B2 (en) *	2010-09-24	2012-10-02	General Electric Company	Apparatus and method for a combustor
US9316155B2 (en) *	2013-03-18	2016-04-19	General Electric Company	System for providing fuel to a combustor
US9803555B2 (en) *	2014-04-23	2017-10-31	General Electric Company	Fuel delivery system with moveably attached fuel tube
WO2022079523A1 (en) *	2020-10-14	2022-04-21	King Abdullah University Of Science And Technology	Adjustable fuel injector for flame dynamics control
GB202112641D0 (en) *	2021-09-06	2021-10-20	Rolls Royce Plc	Controlling soot
CN116592391A (zh) *	2022-02-07	2023-08-15	通用电气公司	具有可变初级区燃烧室的燃烧器
CN115031260B (zh) *	2022-05-30	2023-08-22	中国人民解放军空军工程大学	一种旋转爆震燃烧室出口喉道位置固定的可调喷管
WO2024079656A1 (en) *	2022-10-11	2024-04-18	Ecospectr Llc	Two-stage burner with two-layer vortex countercurrent flow

Citations (7)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
US3691761A (en) *	1967-11-10	1972-09-19	Squire Ronald Jackson	Apparatus for regulation of airflow to flame tubes for gas turbine engines
US3765171A (en) *	1970-04-27	1973-10-16	Mtu Muenchen Gmbh	Combustion chamber for gas turbine engines
US3869246A (en) *	1973-12-26	1975-03-04	Gen Motors Corp	Variable configuration combustion apparatus
FR2270448A1 (en) *	1974-05-10	1975-12-05	Bennes Marrel	Gas turbine combustion chamber - has spring loaded bellows controlling annular air flow control membrane
US4296599A (en) *	1979-03-30	1981-10-27	General Electric Company	Turbine cooling air modulation apparatus
EP0281961A1 (de) *	1987-03-06	1988-09-14	Hitachi, Ltd.	Gasturbinenbrennkammer und Verbrennungsverfahren dafür
US5159807A (en) *	1990-05-03	1992-11-03	Societe Nationale D'etude Et De Construction De Motors D'aviation "S.N.E.C.M.A."	Control system for oxidizer intake diaphragms

1998
- 1998-06-11 FR FR9807409A patent/FR2779807B1/fr not_active Expired - Lifetime
1999
- 1999-05-18 DE DE69922437T patent/DE69922437T2/de not_active Expired - Lifetime
- 1999-05-18 EP EP99401204A patent/EP0964206B1/de not_active Expired - Lifetime
- 1999-06-08 JP JP16130699A patent/JP4435331B2/ja not_active Expired - Lifetime
- 1999-06-11 US US09/330,199 patent/US6263663B1/en not_active Expired - Lifetime

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
US3691761A (en) *	1967-11-10	1972-09-19	Squire Ronald Jackson	Apparatus for regulation of airflow to flame tubes for gas turbine engines
US3765171A (en) *	1970-04-27	1973-10-16	Mtu Muenchen Gmbh	Combustion chamber for gas turbine engines
US3869246A (en) *	1973-12-26	1975-03-04	Gen Motors Corp	Variable configuration combustion apparatus
FR2270448A1 (en) *	1974-05-10	1975-12-05	Bennes Marrel	Gas turbine combustion chamber - has spring loaded bellows controlling annular air flow control membrane
US4296599A (en) *	1979-03-30	1981-10-27	General Electric Company	Turbine cooling air modulation apparatus
EP0281961A1 (de) *	1987-03-06	1988-09-14	Hitachi, Ltd.	Gasturbinenbrennkammer und Verbrennungsverfahren dafür
US5159807A (en) *	1990-05-03	1992-11-03	Societe Nationale D'etude Et De Construction De Motors D'aviation "S.N.E.C.M.A."	Control system for oxidizer intake diaphragms

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
EP1777459A2 (de) *	2005-10-24	2007-04-25	Kawasaki Jukogyo Kabushiki Kaisha	Gasturbinenbrennkammer
EP1777459A3 (de) *	2005-10-24	2009-10-07	Kawasaki Jukogyo Kabushiki Kaisha	Gasturbinenbrennkammer
US11242992B2 (en)	2017-04-11	2022-02-08	Office National D'etudes Et De Recherches Aerospatiales	Self-adapting gas turbine firebox with variable geometry

Also Published As

Publication number	Publication date
DE69922437T2 (de)	2005-12-08
JP4435331B2 (ja)	2010-03-17
JP2000009319A (ja)	2000-01-14
US6263663B1 (en)	2001-07-24
DE69922437D1 (de)	2005-01-13
FR2779807A1 (fr)	1999-12-17
EP0964206B1 (de)	2004-12-08
FR2779807B1 (fr)	2000-07-13

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Publication	Publication Date	Title
EP0964206B1 (de)	2004-12-08	Brennkammer einer Gasturbine mit verstellbarer Geometrie
FR2674317A1 (fr)	1992-09-25	Chambre de combustion de turbomachine comportant un reglage du debit de comburant.
EP2954183B1 (de)	2018-03-14	Anordnung zum führen von abgas
CH641284A5 (fr)	1984-02-15	Dispositif regulateur de la pression d'un fluide.
FR2627229A1 (fr)	1989-08-18	Systeme de purge pour le dispositif d'injection de carburant d'un moteur a turbine et ce moteur
EP0496659B1 (de)	1995-07-26	Gasturbinenbrennkammer mit verstellbarer Wand
EP0031770B1 (de)	1984-03-07	Aufgeladene Brennkraftmaschine, insbesondere Dieselmotor
CA2498242A1 (fr)	2005-08-24	Procede d'amelioration des performances d'allumage de dispositif de post-combustion pour turboreacteur double flux et dispositif de post-combustion a performance d'allumage amelioree
EP1658419A1 (de)	2006-05-24	Vorrichtung zur wärmeregelung von abgas
EP0499535B1 (de)	1995-01-04	Brennkammer einer Gasturbine mit niedrigem Auspuff-Schadstoffgehalt
EP0301950B1 (de)	1992-01-02	Aufgeladene Brennkraftmaschine mit einem Hilfsverbrennungsraum.
WO2008043932A1 (fr)	2008-04-17	Ligne d'echappement munie d'un injecteur de carburant et de moyens d'homogeneisation des gaz brules
EP0569300B1 (de)	1996-07-03	Brennkammer mit verstellbaren Primärluftzufuhrbohrungen
CA2204591A1 (fr)	1997-11-09	Systeme d'injection a geometrie variable adoptant un debit d'air en fonction du regime moteur
EP0577451A1 (de)	1994-01-05	Vorrichtung zum Kontrollieren der pneumatischen Einspritzung eines Gemisches für eine Zweitaktbrennkraftmaschine und ihre Verwendung
FR2704628A1 (fr)	1994-11-04	Chambre de combustion comportant un système d'injection de comburant à géométrie variable.
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EP0162761B1 (de)	1988-07-06	Brenner mit Schaufeln und ausgeglichener Zweitluftzufuhr
FR2743111A1 (fr)	1997-07-04	Dispositif d'admission pour moteur a combustion interne
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