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EP0964206A1 - Variable geometry gas turbine combustor chamber - Google Patents

Variable geometry gas turbine combustor chamber Download PDF

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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
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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
Application number
EP99401204A
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German (de)
French (fr)
Other versions
EP0964206B1 (en
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
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Publication of EP0964206A1 publication Critical patent/EP0964206A1/en
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Publication of EP0964206B1 publication Critical patent/EP0964206B1/en
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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

The combustion chamber has pilot (11) and main (12) combustion zones with separate injectors (3,7;4,8) for fuel and oxidant, the assembly being held under pressure (P1) inside a housing (14). The system incorporates a regulating mechanism for the main oxidant flow which reacts to the pressure difference between the internal pressure (P1) and the atmospheric pressure outside the housing.

Description

La présente invention concerne le domaine des turbines à gaz et plus particulièrement des chambres de combustion associées à de telles turbines.The present invention relates to the field of gas turbines and more particularly combustion chambers associated with such turbines.

L'un des problèmes à l'origine de la présente invention a trait à la pollution engendrée par le fonctionnement de ces turbines. Plus précisément, les émissions d'oxydes d'azote (NOx) et de monoxyde de carbone (CO) doivent être réduites car ce sont les plus nocives pour l'environnement.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.

Par ailleurs des normes assez sévères, sont ou vont être en vigueur dans la plupart des pays industrialisés.In addition, fairly strict standards are or will be in force in most industrialized countries.

Les oxydes d'azote (NOx) sont surtout des oxydes d'azote thermiques qui se forment à haute température, c'est-à-dire au-delà de 1700 K dans des chambres de combustion de turbines à gaz où les fumées ont des temps de séjour généralement compris entre 2 et 10 millisecondes.Nitrogen oxides (NOx) 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.

Le monoxyde de carbone (CO) est, quant à lui, formé à plus basse température (< 1600 K), par combustion incomplète du carburant.Carbon monoxide (CO) is formed at a lower temperature (<1600 K), by incomplete combustion of the fuel.

Ainsi, la plage de température optimale pour avoir des émissions réduites à la fois en NOx et en CO se situe entre environ 1650 K et 1750 K. La figure 1 illustre, par des courbes (CO et NOx) les émissions respectives de monoxyde de carbone et d'oxydes d'azote en fonction de la température T (en K) dans les conditions de fonctionnement d'une chambre de combustion d'une turbine à gaz.So the optimal temperature range for emissions reduced in both NOx and CO is between about 1650 K and 1750 K. 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.

Les émissions de NOx et de CO sont ainsi directement reliées à la richesse du mélange air-carburant dans la chambre de combustion ; c'est-à-dire au rapport entre le débit d'air et le débit de carburant. Sachant que la richesse du mélange doit être imposée, si l'on cherche à opérer dans une certaine plage de températures. telle que celle évoquée ci-dessus, la température adiabatique de flamme du mélange variera approximativement proportionnellement à la richesse.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.

De façon connue et conventionnelle, le débit de carburant est le seul paramètre permettant de contrôler le régime de fonctionnement de la turbine. Il s'ensuit que pour un débit de carburant donné, le débit d'air est parfaitement fixé à une valeur dépendant uniquement des caractéristiques de la machine et en particulier des sections de passage dans le foyer. Par suite, la richesse est totalement déterminée.In a known and conventional manner, 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.

Cependant, la plage de richesses permettant de respecter la plage de température définie ci-dessus ne correspond pas toujours à la richesse imposée par la courbe de fonctionnement de la machine.However, the wealth range allowing to respect the range of temperature defined above does not always correspond to the richness imposed by the machine operating curve.

Plusieurs concepts sont envisageables pour remédier à ce problème.Several concepts can be envisaged to remedy this problem.

L'un consiste à réaliser une combustion sur plusieurs étages, allumés successivement. Cette solution connue est illustrée par la figure 2 où l'on voit une chambre de combustion ayant un étage pilote suivi de deux autres étages ayant chacun une entrée d'air et une entrée de carburant tel que du gaz naturel par exemple. Il s'agit alors de réaliser la combustion sur chaque étage successivement, et en fonction de la puissance totale demandée. La combustion-pilote est quant à elle, réalisée quel que soit le régime. Cette solution permet théoriquement d'obtenir des richesses acceptables dans les étages allumés, pour chaque régime moteur, si l'on dispose d'un nombre d'étages suffisant. L'inconvénient majeur est qu'elle nécessite un circuit d'alimentation en carburant complexe, d'où des problèmes de fiabilité, de régulation et surtout de coût.One consists in carrying out a combustion on several stages, lit successively. This known solution is illustrated in Figure 2 where we see a combustion chamber having a pilot stage followed by two others stages each having an air inlet and a fuel inlet such as natural gas for example. It is then a question of carrying out the combustion on each stage successively, and according to the total power requested. The pilot combustion is carried out regardless of the speed. This solution theoretically allows to obtain acceptable wealth in lit stages, for each engine speed, if a number is available sufficient floors. The major drawback is that it requires a circuit complex fuel supply, resulting in reliability problems, regulation and especially cost.

Un autre concept pour obtenir des chambres de combustion opérant sur une plage de température déterminée, consiste à l'équiper d'un ensemble de volets. clapets ou autres moyens d'obturation permettent de contrôler le débit d'air dans le foyer. Bien entendu, la commande et l'actionnement de tels éléments est complexe, délicat à mettre en oeuvre. L'ensemble est en outre coûteux.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. Of course, the command and actuation of such elements is complex, delicate to implement. The assembly is also expensive.

La présente invention vise donc à proposer une solution fiable, simple au problème de la régulation de la richesse dans une chambre de combustion d'une turbine à gaz.The present invention therefore aims to provide a reliable, simple solution to the problem of wealth regulation in a combustion of a gas turbine.

L'objet de ce contrôle est de pouvoir réaliser une combustion dans une plage de température optimale vis-à-vis notamment des émissions de monoxyde de carbone, et d'oxydes d'azote.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.

La présente invention permet ainsi une régulation automatique du débit d'air de combustion. Un asservissement mécanique est avantageusement réalisé grâce à un nombre très limité de pièces mécaniques.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.

L'invention a pour objet une chambre de combustion de turbine à gaz comprenant au moins une zone dite d'injection-pilote dans laquelle débouchent au moins un premier moyen d'injection de carburant pilote et un premier moyen d'injection de comburant associé ; une zone de combustion principale dans laquelle débouchent au moins un deuxième moyen d'injection principale de carburant et un deuxième moyen d'injection de comburant associé, l'ensemble étant maintenu sous une pression P1 à l'intérieur d'une enceinte.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.

Selon l'invention, ladite chambre de combustion comprend en outre un moyen mécanique 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, ladite différence de pression étant directement liée au régime-moteur. According to the invention, 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.

Plus précisément, ledit moyen de régulation comprend au moins un élément d'obturation qui obture plus ou moins les deuxièmes arrivées d'air dans la chambre de combustion, plusieurs tiges de liaison entre les éléments d'obturation et un élément de support, un élément de compression, un soufflet d'étanchéité placé autour de l'élément de compression délimitant avec l'élément de support le volume à pression atmosphérique (Po) vis-à-vis de l'enceinte sous pression (P1).More specifically, 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).

De façon particulière, le premier moyen d'injection de carburant et le premier moyen d'injection de comburant sont disposés sensiblement à proximité de l'axe longitudinal (XX') de la chambre de combustion.In particular, the first fuel injection means and the first oxidant injection means are arranged substantially at proximity to the longitudinal axis (XX ') of the combustion chamber.

Selon un arrangement spécifique de l'invention, le deuxième moyen d'injection principale de carburant et le deuxième moyen d'injection de comburant sont disposés sur une circonférence, en aval de la zone de combustion pilote relativement au sens de propagation de la flamme.According to a specific arrangement of the invention, 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.

En outre, la chambre de combustion selon l'invention comprend un troisième moyen d'injection de comburant qui débouche, dans la chambre de combustion, en aval du deuxième moyen d'injection de comburant relativement au sens de propagation de la flamme.In addition, 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.

Par ailleurs, le moyen de régulation du deuxième débit de comburant permet de réguler le débit du troisième moyen d'injection d'air (fonction de by-pass).Furthermore, 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).

L'élément de compression peut comprendre un empilage de rondelles ou bien des ressorts.The compression member may include a stack of washers or springs.

Selon un mode de réalisation de l'invention, la chambre 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.According to one embodiment of the invention, 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.

L'invention sera mieux comprise, d'autres avantages, particularités et détails apparaítront à la lecture de la description qui va suivre, faite à titre illustratif et nullement limitatif en référence aux dessins annexés sur lesquels :

  • 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.
The invention will be better understood, other advantages, particularities and details will appear on reading the description which follows, given by way of illustration and in no way limitative with reference to the appended drawings in which:
  • Figure 3 is a longitudinal section of a combustion chamber according to an embodiment of the invention;
  • Figure 4 is a longitudinal section of the combustion chamber of Figure 3, in another operating position.

Sur la figure 3, le foyer 1 est délimité par une virole interne 2 qui présente ici deux diamètres différents : le plus petit diamètre renferme la zone de la combustion-pilote 11 tandis que la zone de plus grand diamètre 12 est celle où se développe la combustion principale.In FIG. 3, 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.

La zone 11 de combustion-pilote assure la combustion au ralenti et la combustion peut y être maintenue pendant les autres régimes de fonctionnement.Pilot combustion zone 11 ensures idling combustion and combustion can be maintained there during the other regimes of operation.

Au niveau de la zone 11 débouchent respectivement des injecteurs 3 de carburant tel que par exemple du gaz naturel et des injecteurs ou des entrées d'air 4.At the level of the zone 11 respectively emerge injectors 3 of fuel such as for example natural gas and injectors or air inlets 4.

Un fond 5 est prévu pour délimiter la zone 11. Les arrivées de carburant 3 et d'air 4 sont situées près du fond 5, circonférentiellement, et non loin de l'axe longitudinal XX' de la chambre. La zone de combustion-pilote 11 est une zone de stabilité de la flamme, où une flamme existe quelles que soient les conditions de fonctionnement. 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.

Des ailettes 6 de mise en rotation de l'air peuvent être prévues au niveau des arrivées d'air 4.Air rotation fins 6 can be provided at the air intake level 4.

Les injecteurs de carburant 3 peuvent être implantés dans ces ailettes sans sortir du cadre de l'invention.The fuel injectors 3 can be installed in these fins without departing from the scope of the invention.

A l'intérieur de la zone 11 règne une pression donnée P1, de même que dans la zone 12.Inside zone 11 there is a given pressure P1, likewise than in zone 12.

La zone 12 présente donc un diamètre plus grand que celui de la zone 11 : c'est là qu'est opérée la combustion principale.Zone 12 therefore has a larger diameter than that of the zone 11: this is where the main combustion takes place.

Ainsi un deuxième moyen d'injection de carburant 7 est disposé à la limite entre les zones 11 et 12. De même un deuxième moyen d'injection d'air 8 est situé à proximité du deuxième injecteur de carburant 7. Des ailettes 9 peuvent en outre être disposées au niveau des injecteurs 8. Les moyens 7, 8 et 9 sont situés sur une circonférence de la virole 2, et plusieurs groupements peuvent être prévus. Ici trois groupements sont prévus, chacun angulairement espacé de 120°.Thus a second fuel injection means 7 is arranged at the boundary between zones 11 and 12. Similarly, 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 °.

En outre de l'air dit "de dilution" c'est-à-dire ne participant pas à la combustion ni au refroidissement des parois peut être introduit dans la virole 2, en aval de la zone de combustion 12, via des orifices appropriés 22.In addition, 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.

L'alimentation générale en air se fait par un espace annulaire 13 délimité par la virole 2 et une enveloppe extérieure 14. Une pression P2 règne dans cet espace ; cette pression est légèrement supérieure à la pression P1, la différence étant due aux pertes de charge créés par les différents orifices d'entrée d'air.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.

Au niveau des arrivées d'air 8, la présente invention prévoit un moyen de régulation du débit, qui réagit à la différence de pression entre l'espace annulaire (P2) et l'extérieur de l'enceinte 14 ou règne une pression Po (∼ pression atmosphérique).At the air inlets 8, 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).

Lorsque le régime de la turbine augmente, la pression P2 augmente et la pression Po ne varie pas ; de la sorte, la différence de pression (P2-Po) augmente et le moyen de régulation réagit en autorisant une plus grande ouverture des arrivées d'air 8.When the turbine speed increases, the pressure P2 increases and the pressure Po does not vary; so the pressure difference (P2-Po) increases and the regulating means reacts by authorizing greater opening of air inlets 8.

Plus précisément, le moyen de régulation comprend une virole 15 susceptible de coulisser selon l'axe XX' devant les ouvertures 8 (préférentiellement équipées d'ailettes 9) et permettant donc une variation de la section de passage de l'air.More specifically, 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.

Des ouvertures correspondantes sont prévues dans la virole 15, en regard des ouvertures 8 de la virole 2.Corresponding openings are provided in the shell 15, in look of the openings 8 of the shell 2.

La virole 15 est fixée, par tout moyen connu en soi, à l'extrémité inférieure de plusieurs tiges 16. A leur autre extrémité, les tiges 16 portent une plaque-support 17 qui est elle-même liée à un élément de compression 18. Un empilement de rondelles coniques ou des ressorts peuvent être prévus à cet effet.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.

Un soufflet 19 ou autre moyen d'étanchéité est par ailleurs prévu autour de l'élément de compression 18. Le soufflet 19 est une séparation entre le volume intérieur de la chambre de combustion, où règne les pressions P2 et P1, et le volume extérieur où règne la pression Po.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.

Par ailleurs, la virole 15 peut être munie d'ouvertures additionnelles qui mettent en communication l'espace 13 et un espace annulaire 21 intérieur à la virole 2. Pour ce faire une virole additionnelle 20, coaxiale à la virole 2 est prévue sur une partie de la hauteur de la virole 2. Furthermore, the ferrule 15 can be provided with additional openings which connect the space 13 and an annular space 21 inside the ferrule 2. To do this, an additional ferrule 20, coaxial with the ferrule 2 is provided over part of the height of ferrule 2.

La virole 20 peut présenter une hauteur qui correspond à la zone 12 de combustion. Sur cette hauteur, l'air issu des ouvertures 10 et qui transite dans l'espace annulaire 21, va permettre de rejeter de l'air en aval de la zone de combustion 12 tout en refroidissant les parois de ladite zone de combustion 12. On peut ainsi maintenir une richesse acceptable au sein du foyer principal quel que soit le régime. L'effet principal du by-pass 21 est de limiter la décroissance de la richesse dans le foyer 1, notamment à régime partiel.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.

Ainsi, les ouvertures 10 sont conçues de telle sorte qu'à pleine charge, aucun air ne les traverse (cas de la figure 4), tandis qu'à charge partielle ou faible, de l'air passe dans l'espace 21 afin d'être rejeté en aval de la zone de combustion 12 tout en refroidissant la paroi de la virole 2.Thus, 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.

Le fonctionnement de l'ensemble qui vient d'être décrit peut être résumé de la façon suivante, en comparant respectivement les figures 3 et 4.The operation of the assembly which has just been described can be summarized as follows, comparing Figures 3 and 4.

En effet, sur la figure 3 la position des différents éléments correspond à un fonctionnement à environ 50 % de la puissance maximale. Sur la figure 4, est schématisé l'appareil tel qu'il fonctionne à 100 % de sa puissance.Indeed, in Figure 3 the position of the different elements corresponds at operation at around 50% of maximum power. On the face 4, is shown schematically the device as it operates at 100% of its power.

Lorsqu'une puissance faible est requise (régimes de ralenti), la pression relative (P2- Po) entre l'espace annulaire 13 et l'extérieur de la virole 14, permet une ouverture limitée des arrivées d'air 8.When low power is required (idle speed), the relative pressure (P2-Po) between the annular space 13 and the outside of the ferrule 14, allows limited opening of the air inlets 8.

Simultanément, les ouvertures 10 sont plutôt largement ouvertes de sorte que de l'air peut traverser l'espace 21 et refroidir la paroi 20, sans participer à la combustion dans la zone 12. On peut ainsi maintenir une richesse acceptable dans celle-ci et éviter de fortes émissions de CO. Simultaneously, 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.

Lorsque la turbine fonctionne à pleine charge, la pression relative (P2-Po) est plus importante que dans le cas qui vient d'être évoqué, de sorte que la virole 15 est soulevée et découvre plus largement les ouvertures 8. Un important débit d'air peut alors pénétrer dans la chambre de combustion 12. Simultanément les ouvertures 10 sont fermées ce qui empêche l'air de venir dans l'espace annulaire 21. Une grande quantité d'air est ainsi injectée directement dans la zone de combustion principale 12, ce qui limite la richesse maximale et évite la formation de NOx.When the turbine is operating at full load, the relative pressure (P2-Po) is greater than in the case which has just been mentioned, so that the shell 15 is lifted and more widely discovers the openings 8. A large flow d air can then enter the combustion chamber 12. Simultaneously the openings 10 are closed which prevents air from coming into the annular space 21. A large quantity of air is thus injected directly into the main combustion zone 12 , which limits the maximum richness and prevents the formation of NO x .

Ainsi il apparaít que la chambre de combustion selon l'invention ne nécessite pas de dispositif mécanique spécifique de régulation des arrivées d'air. La régulation se fait ici d'elle-même, par la pression relative dans la chambre de combustion et donc en fonction du régime-moteur.Thus it appears that the 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.

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.Gas turbine combustion chamber comprising at least a pilot combustion zone (11) into which at least open out a first means (3) of pilot fuel injection and a first means (4) injection of associated oxidizer; a main combustion zone (12) into which open at least a second injection means (7) main fuel and a second means (8) for injecting oxidant associated, the assembly being maintained under a pressure P1 inside a enclosure (14), characterized in that it further comprises means mechanical (15, 16, 17, 18, 19) regulating the second flow of oxidizer, which reacts to the pressure difference between the interior (P1) and the atmospheric pressure (Po) outside the enclosure (14), said difference pressure being directly linked to the engine speed. 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).Combustion chamber according to claim 1, characterized in that said regulating means comprises at least one element shutter (15) which more or less seals the second arrivals of oxidizer (8) in the combustion chamber, several connecting rods (16) between the closure elements and a support element (17), a compression element (18), a sealing bellows (19) placed around the compression element (18) and delimiting with the support element (17) the volume at atmospheric pressure (Po) with respect to the pressure vessel (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. Combustion chamber according to any one of the claims previous, characterized in that the first means of injecting fuel (3) and the first oxidant injection means (4) are arranged substantially close to the longitudinal axis (XX ') of the chamber 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.Combustion chamber according to any one of the claims previous, characterized in that the second injection means (7) main fuel and second means (8) for injecting oxidant are arranged on a circumference, downstream of the pilot injection zone (11) relative to the direction of flame propagation. 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.Combustion chamber according to any one of the claims previous, characterized in that it further comprises a third oxidizer injection means which opens into the combustion downstream of the second oxidant injection means (8) relative to the direction of flame propagation. 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.Combustion chamber according to claim 5, characterized in what the means (15) for regulating the second oxidant flow allows in addition to regulate the flow rate of the third oxidant injection means. 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.Combustion chamber according to any one of the claims 2 to 6, characterized in that the compression element (18) comprises a stacking of conical washers. 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.Combustion chamber according to any one of the claims 2 to 6, characterized in that the compression element (18) comprises at minus a spring. 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.Combustion chamber according to any one of the claims previous, characterized in that it comprises three zones of grouping of the second main fuel injection means (7) and main oxidant injection (8), each zone being angularly spaced 120 ° C apart.
EP99401204A 1998-06-11 1999-05-18 Variable geometry gas turbine combustor chamber Expired - Lifetime EP0964206B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9807409 1998-06-11
FR9807409A FR2779807B1 (en) 1998-06-11 1998-06-11 VARIABLE GEOMETRY GAS TURBINE COMBUSTION CHAMBER

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EP0964206A1 true EP0964206A1 (en) 1999-12-15
EP0964206B1 EP0964206B1 (en) 2004-12-08

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US (1) US6263663B1 (en)
EP (1) EP0964206B1 (en)
JP (1) JP4435331B2 (en)
DE (1) DE69922437T2 (en)
FR (1) FR2779807B1 (en)

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US11242992B2 (en) 2017-04-11 2022-02-08 Office National D'etudes Et De Recherches Aerospatiales Self-adapting gas turbine firebox with variable geometry

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JP4670035B2 (en) * 2004-06-25 2011-04-13 独立行政法人 宇宙航空研究開発機構 Gas turbine combustor
US8915086B2 (en) 2006-08-07 2014-12-23 General Electric Company System for controlling combustion dynamics and method for operating the same
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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
FR2779807B1 (en) 2000-07-13
US6263663B1 (en) 2001-07-24
FR2779807A1 (en) 1999-12-17
JP4435331B2 (en) 2010-03-17
DE69922437T2 (en) 2005-12-08
EP0964206B1 (en) 2004-12-08
JP2000009319A (en) 2000-01-14
DE69922437D1 (en) 2005-01-13

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