EP0964206A1 - Chambre de combustion de turbine à gaz à geométrie variable - Google Patents
Chambre de combustion de turbine à gaz à geométrie variable Download PDFInfo
- Publication number
- EP0964206A1 EP0964206A1 EP99401204A EP99401204A EP0964206A1 EP 0964206 A1 EP0964206 A1 EP 0964206A1 EP 99401204 A EP99401204 A EP 99401204A EP 99401204 A EP99401204 A EP 99401204A EP 0964206 A1 EP0964206 A1 EP 0964206A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- combustion chamber
- combustion
- injection
- chamber according
- oxidant
- 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
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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)
Abstract
- La présente invention concerne une chambre de combustion de turbine à gaz comprenant au moins une zone (11) dite de combustion-pilote dans laquelle débouchent au moins un premier moyen (3) d'injection de carburant pilote et un premier moyen (4) d'injection de comburant associé ; une zone (12) de combustion principale dans laquelle débouchent au moins un deuxième moyen (7) d'injection principale de carburant et un deuxième moyen (8) d'injection de comburant associé, l'ensemble étant maintenu sous une pression P1 à l'intérieur d'une enceinte (14).
- Conformément à l'invention, ladite chambre comprend en outre un moyen mécanique (15-19) de régulation du deuxième débit de comburant, qui réagit à la différence de pression entre l'intérieur (P1) et la pression atmosphérique (Po) à l'extérieur de l'enceinte (14), ladite différence de pression étant directement liée au régime-moteur.
Description
- La figure 3 est une coupe longitudinale d'une chambre de combustion selon un mode de réalisation de l'invention;
- La figure 4 est une coupe longitudinale de la chambre de combustion de la figure 3, dans une autre position de fonctionnement.
Claims (9)
- Chambre de combustion de turbine à gaz comprenant au moins une zone (11) dite de combustion-pilote dans laquelle débouchent au moins un premier moyen (3) d'injection de carburant pilote et un premier moyen (4) d'injection de comburant associé ; une zone (12) de combustion principale dans laquelle débouchent au moins un deuxième moyen (7) d'injection principale de carburant et un deuxième moyen (8) d'injection de comburant associé, l'ensemble étant maintenu sous une pression P1 à l'intérieur d'une enceinte (14), caractérisée en ce qu'elle comprend en outre un moyen mécanique (15, 16, 17, 18, 19) de régulation du deuxième débit de comburant, qui réagit à la différence de pression entre l'intérieur (P1) et la pression atmosphérique (Po) à l'extérieur de l'enceinte (14), ladite différence de pression étant directement liée au régime-moteur.
- Chambre de combustion selon la revendication 1, caractérisée en ce que ledit moyen de régulation comprend au moins un élément d'obturation (15) qui obture plus ou moins les deuxièmes arrivées de comburant (8) dans la chambre de combustion, plusieurs tiges de liaison (16) entre les éléments d'obturation et un élément de support (17), un élément de compression (18), un soufflet d'étanchéité (19) placé autour de l'élément de compression (18) et délimitant avec l'élément de support (17) le volume à pression atmosphérique (Po) vis-à-vis de l'enceinte sous pression (P1).
- Chambre de combustion selon l'une quelconque des revendications précédentes, caractérisée en ce que le premier moyen d'injection de carburant (3) et le premier moyen d'injection de comburant (4) sont disposés sensiblement à proximité de l'axe longitudinal (XX') de la chambre de combustion.
- Chambre de combustion selon l'une quelconque des revendications précédentes, caractérisée en ce que le deuxième moyen (7) d'injection principale de carburant et le deuxième moyen (8) d'injection de comburant sont disposés sur une circonférence, en aval de la zone (11) d'injection pilote relativement au sens de propagation de la flamme.
- Chambre de combustion selon l'une quelconque des revendications précédentes, caractérisée en ce qu'elle comprend en outre un troisième moyen d'injection de comburant qui débouche dans la chambre de combustion en aval du deuxième moyen (8) d'injection de comburant relativement au sens de propagation de la flamme.
- Chambre de combustion selon la revendication 5, caractérisée en ce que le moyen (15) de régulation du deuxième débit de comburant permet en outre de réguler le débit du troisième moyen d'injection de comburant.
- Chambre de combustion selon l'une quelconque des revendications 2 à 6, caractérisée en ce que l'élément de compression (18) comprend un empilage de rondelles coniques.
- Chambre de combustion selon l'une quelconque des revendications 2 à 6, caractérisée en ce que l'élément de compression (18) comprend au moins un ressort.
- Chambre de combustion selon l'une quelconque des revendications précédentes, caractérisée en ce qu'elle comprend trois zones de regroupement des deuxième moyen d'injection principal de carburant (7) et d'injection principal de comburant (8), chaque zone étant angulairement espacée de 120°C.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR9807409A FR2779807B1 (fr) | 1998-06-11 | 1998-06-11 | Chambre de combustion de turbine a gaz a geometrie variable |
FR9807409 | 1998-06-11 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0964206A1 true EP0964206A1 (fr) | 1999-12-15 |
EP0964206B1 EP0964206B1 (fr) | 2004-12-08 |
Family
ID=9527308
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP99401204A Expired - Lifetime EP0964206B1 (fr) | 1998-06-11 | 1999-05-18 | Chambre de combustion de turbine à gaz à géométrie variable |
Country Status (5)
Country | Link |
---|---|
US (1) | US6263663B1 (fr) |
EP (1) | EP0964206B1 (fr) |
JP (1) | JP4435331B2 (fr) |
DE (1) | DE69922437T2 (fr) |
FR (1) | FR2779807B1 (fr) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1777459A2 (fr) * | 2005-10-24 | 2007-04-25 | Kawasaki Jukogyo Kabushiki Kaisha | Chambre de combustion pour turbine à gaz |
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)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2005124231A2 (fr) * | 2004-06-11 | 2005-12-29 | Vast Power Systems, Inc. | Appareil et procede de combustion a faibles emissions |
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 |
US12044174B2 (en) * | 2020-10-14 | 2024-07-23 | 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 (fr) * | 2022-10-11 | 2024-04-18 | Ecospectr Llc | Brûleur par tout ou peu à écoulement à contre-courant tourbillonnaire à deux couches |
Citations (7)
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 (fr) * | 1987-03-06 | 1988-09-14 | Hitachi, Ltd. | Chambre de combustion pour turbine à gaz et méthode de combustion |
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 EP EP99401204A patent/EP0964206B1/fr not_active Expired - Lifetime
- 1999-05-18 DE DE69922437T patent/DE69922437T2/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)
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 (fr) * | 1987-03-06 | 1988-09-14 | Hitachi, Ltd. | Chambre de combustion pour turbine à gaz et méthode de combustion |
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)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1777459A2 (fr) * | 2005-10-24 | 2007-04-25 | Kawasaki Jukogyo Kabushiki Kaisha | Chambre de combustion pour turbine à gaz |
EP1777459A3 (fr) * | 2005-10-24 | 2009-10-07 | Kawasaki Jukogyo Kabushiki Kaisha | Chambre de combustion pour turbine à gaz |
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 |
JP2000009319A (ja) | 2000-01-14 |
FR2779807B1 (fr) | 2000-07-13 |
JP4435331B2 (ja) | 2010-03-17 |
DE69922437D1 (de) | 2005-01-13 |
US6263663B1 (en) | 2001-07-24 |
FR2779807A1 (fr) | 1999-12-17 |
EP0964206B1 (fr) | 2004-12-08 |
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