EP0933594A1 - Gas turbine combustion chamber for liquid fuel - Google Patents

Gas turbine combustion chamber for liquid fuel Download PDF

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Publication number
EP0933594A1
EP0933594A1 EP99400141A EP99400141A EP0933594A1 EP 0933594 A1 EP0933594 A1 EP 0933594A1 EP 99400141 A EP99400141 A EP 99400141A EP 99400141 A EP99400141 A EP 99400141A EP 0933594 A1 EP0933594 A1 EP 0933594A1
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Prior art keywords
air
combustion chamber
fuel
enclosure
chamber according
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EP99400141A
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German (de)
French (fr)
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EP0933594B1 (en
Inventor
Jean-Hervé Le Gal
Patrick Flament
Gérard Martin
Guy Grienche
Gérard Schott
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IFP Energies Nouvelles IFPEN
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    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/44—Combustion chambers comprising a single tubular flame tube within a tubular casing
    • 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 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
    • F23C7/004—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion using vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F23D11/38—Nozzles; Cleaning devices therefor
    • 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
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • 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
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/58—Cyclone or vortex type combustion chambers

Definitions

  • the present invention relates to the field of combustion of gas turbines powered by liquid fuel.
  • Such gas turbines can be illustrated by the system shown in Figure 3.
  • This assembly includes a compressor (20) the outlet of which is connected to the inlet of the combustion chamber (1) where a liquid fuel (fuel oil or kerosene) is injected.
  • a liquid fuel fuel oil or kerosene
  • the gases burned in this chamber are then expanded in a turbine (30) which thereby provides the desired power to the main shaft which itself drives the compressor (20).
  • thermodynamic cycle of the machine In gas turbine combustion chambers, combustion at flame level is usually performed around stoichiometry as this ensures good flame stability. Wealth however global imposed by the conditions of the thermodynamic cycle of the machine is very low, on the order of 0.15 to 0.3, depending on the conditions of operation. Operating locally in or around rich conditions stoichiometry, with air preheated by the compressor, leads to locally very high temperatures in the room (around 2000 to 2500 K). The measurements showed that under these conditions, the majority of the nitrogen oxide formed was "thermal NO".
  • the so-called dry processes generally aim to achieve combustion a lean premix of air and fuel produced beforehand.
  • the Patent application EP-A2-0 769 657 illustrates a system of this type.
  • the stability of combustion and ignition of the main premix are ensured by a pilot flame of small power whose role is also to ensure the machine running at idle speed.
  • the wealth in the chamber being fixed by the respective proportions of air and fuel premixed, it is possible to limit the flame temperatures and therefore thermal nitrogen oxide.
  • premixed combustion technologies do not not give satisfactory results with liquid fuel.
  • this technique requires the implementation of a pilot burner allowing to ensure the stability of the flame, especially in poor conditions.
  • This burner ensuring the operation of the machine during the phases of idling, it passes a fuel flow of up to almost a third of the total flow. For some applications, it works under conditions operating close to stoichiometry so under conditions unfavorable procedures from the point of view of oxide production nitrogen.
  • the present invention makes it possible in particular to resolve all of the problems discussed above. It is an alternative solution to combustion chambers operating in premix or in processes damp as mentioned above.
  • the present invention aims to achieve a diffusion flame by combining certain conditions of injection of air and liquid fuel.
  • the present invention relates to a combustion chamber of gas turbine operating on liquid fuel, comprising an enclosure tubular having at least one air inlet, a means for injecting liquid fuel located on or near the longitudinal axis of the enclosure tubular, one outlet to the turbine, at least two types of air inlets under pressure located close to each other: the first introducing air helically around the longitudinal axis of the combustion chamber, the second inlet introduces air tangentially to the enclosure to create around the fuel jets counter-rotating flows intended for improve the mixture between said fuel and air.
  • the first air inlet allows the introduction of 30% to 70% of the total amount of pressurized air entering the combustion chamber, the rest being injected through the second inlets pressurized air.
  • said injection means has between 5 and 12 orifices intended for the injection of liquid fuel, preferably between 6 and 10 ports.
  • the injection means comprises a central disc located on the longitudinal axis of the tubular enclosure, around which is arranged a ring pierced with said orifices, the surface of the ring being a truncated cone.
  • the tangential entry includes a set of inserts distributed around the periphery of the enclosure, which direct the air tangentially to the enclosure wall with a direction of rotation opposite to that of flow main.
  • the air inlets can be dimensioned so that the air speed inside the combustion chamber is between 20 and 120 m / s.
  • the angle at the top of the injection cone is preferably between 35 ° and 45 °.
  • the combustion chamber according to the invention illustrated schematically in Figure 1, includes a tubular outer casing 1 and an inner enclosure 2 coaxial with the casing 1.
  • envelopes 1 and 2 are closed at one end where they delimit a functional space 3.
  • envelopes 1 and 2 define between they an annular space 4 for the circulation of pressurized air before to enter the combustion chamber proper.
  • the actual combustion chamber, 5, is defined by the interior volume of the enclosure 2.
  • a means for injecting fuel 6 which preferably comprises a central disc 61 located on or in the immediate vicinity of the longitudinal axis XX 'of the enclosure 2.
  • the injection means 6 comprises a set of orifices 62 arranged on a truncated cone ring.
  • from 5 to 12 jets can be created; preferably between 6 and 10. These jets are separated from each other from others and located along the generatrices of a corner cone at the top a between 30 ° and 60 °, preferably between 35 ° and 45 °.
  • the injection means 6 can operate with assistance additional air; we then obtain medium diameter droplets less than 50 micrometers.
  • the number of jets is also important. If this one is too important, there is an effect of blocking the flow by the jets of combustible. This results in an air-depleted area behind the jets, which leads to rich combustion conditions, therefore at high temperature. Yes there are too few jets, the interactions between jets decrease and we found in the case of n independent axial flames.
  • the first type introduces air helically into enclosure 2, around the longitudinal axis of the enclosure.
  • This entry 7 is here a ring around the injection means 6.
  • Fins 71 can be arranged in the ring to print to this air a quantity of tangential movement.
  • the second type of air intake includes peripheral inlets 8 which allow the air to be injected tangentially to the wall of the enclosure 2. A this effect of the inserts 81 as shown in FIG. 2 can be planned.
  • the inserts 81 direct the air tangentially and in the opposite direction to the first type of flow. This increases the shear between the two flows and therefore accelerate the mixing between the air and the fuel droplets.
  • the air flow at inlet 7 is between 30 and 70% air used for combustion, preferably between 40 and 50%.
  • Well heard the air flow passing through the tangential inlets 8 is the 100% complement.
  • Dilution air is introduced if necessary downstream of the combustion zone 5, through orifices made in the enclosure 2.
  • the means injection 6 advantageously comprises a central disc 61.
  • the latter allows, in combination with the rotation of the flow, generate a small internal recirculation according to the arrows A in Figure 1, at level of the injector nose 6.
  • the zone 10 delimited by this recirculation is rather rich in fuel and it partly ensures the stability of the combustion.
  • the majority of the fuel is burned in poor conditions since the overall wealth in the combustion chamber 5 is between 0.4 and 0.8.
  • a separate flame burner operates around stoichiometry or with a slight excess of air.
  • thermodynamic cycle of this imposes operation under pressure which can vary from approximately 2 to approximately 30 bars.
  • the residence times in the combustion chamber 5 according to the invention are commonly less than 50 milliseconds, which leads to heating densities of between 50 and 200 MW / m 3 .
  • the heating densities in the field of boiler burners are rather less than 1 MW / m 3 , with residence times of the order of a second.
  • the figure 3 shows in longitudinal section a turbo-compressor assembly likely to implement the invention; this figure was commented on in description head.

Abstract

The tubular combustion chamber (2) has at least one air intake, a liquid fuel injector (6) situated on or close to its lengthwise axis (X-X'), and an outlet towards the turbine. The injector has a series of orifices (62) designed to give separate jets of fuel along the generating lines of a cone with a summit angle of 30 - 60 degrees. The chamber has two types of air intake situated close to one another - one (7) introducing an air flow in a spiral about the lengthwise axis, and the other (8) a tangential flow.

Description

La présente invention concerne le domaine des chambres de combustion de turbines à gaz fonctionnant au carburant liquide.The present invention relates to the field of combustion of gas turbines powered by liquid fuel.

De telles turbines à gaz peuvent être illustrées par le système représenté sur la figure 3. Cet ensemble comprend un compresseur (20) dont la sortie est reliée à l'entrée de la chambre de combustion (1) où un carburant liquide (fioul ou kérosène) est injecté. Les gaz brûlés dans cette chambre sont ensuite détendus dans une turbine (30) qui fournit ainsi la puissance souhaitée à l'arbre principal qui lui-même entraíne le compresseur (20).Such gas turbines can be illustrated by the system shown in Figure 3. This assembly includes a compressor (20) the outlet of which is connected to the inlet of the combustion chamber (1) where a liquid fuel (fuel oil or kerosene) is injected. The gases burned in this chamber are then expanded in a turbine (30) which thereby provides the desired power to the main shaft which itself drives the compressor (20).

De façon connue, la combustion dans ce type de turbines à gaz amène à la formation d'oxydes d'azote qui ont diverses origines :

  • le "prompt" NO résulte de réactions rapides complexes entre le fuel et l'azote de l'air. Il est formé en un temps très court généralement bien inférieur à la milliseconde.
  • Le "fuel" NO est produit par des réactions entre l'azote contenu dans le carburant sous forme N et l'oxygène de l'air. Ce type d'oxyde d'azote est principalement formé en milieu pauvre, lorsque l'air est en excès par rapport au carburant.
  • L'oxyde d'azote thermique est produit à haute température, à partir de l'azote de l'air N2. L'oxyde d'azote est couramment produit à des températures supérieures à 1500°C, compte tenu des temps de séjour dans la chambre de combustion, qui est alors de l'ordre de quelques dizaines de millisecondes. La vitesse des réactions conduisant à l'azote thermique croít exponentiellement en fonction de la température.
In known manner, combustion in this type of gas turbine leads to the formation of nitrogen oxides which have various origins:
  • the "prompt" NO results from complex rapid reactions between the fuel and the nitrogen in the air. It is formed in a very short time, generally much less than a millisecond.
  • NO fuel is produced by reactions between the nitrogen contained in the fuel in N form and the oxygen in the air. This type of nitrogen oxide is mainly formed in a lean environment, when the air is in excess relative to the fuel.
  • Thermal nitrogen oxide is produced at high temperature from nitrogen in the air N2. Nitrogen oxide is commonly produced at temperatures above 1500 ° C, taking into account the residence times in the combustion chamber, which is then of the order of a few tens of milliseconds. The speed of the reactions leading to thermal nitrogen increases exponentially as a function of temperature.

C'est ce dernier type d'azote qui pose problème, comme il va être exposé ci-après. It is the latter type of nitrogen that is the problem, as it will be set out below.

Dans les chambres de combustion de turbine à gaz, la combustion au niveau de la flamme est généralement réalisée autour de la stoechiométrie car cela assure une bonne stabilité de la flamme. Cependant la richesse globale imposée par les conditions du cycle thermodynamique de la machine est très faible, de l'ordre de 0,15 à 0,3, selon les conditions de fonctionnement. Le fait d'opérer localement en conditions riches ou autour de la stoechiométrie, avec de l'air préchauffé par le compresseur, conduit à des températures localement très élevées dans la chambre (de l'ordre de 2000 à 2500 K). Les mesures ont montré que dans ces conditions, la majorité de l'oxyde d'azote formé était du "NO thermique".In gas turbine combustion chambers, combustion at flame level is usually performed around stoichiometry as this ensures good flame stability. Wealth however global imposed by the conditions of the thermodynamic cycle of the machine is very low, on the order of 0.15 to 0.3, depending on the conditions of operation. Operating locally in or around rich conditions stoichiometry, with air preheated by the compressor, leads to locally very high temperatures in the room (around 2000 to 2500 K). The measurements showed that under these conditions, the majority of the nitrogen oxide formed was "thermal NO".

Plusieurs solutions sont connues pour diminuer les émissions d'oxydes d'azote. On peut globalement les classer en deux grands types :

  • les procédés humides basés sur l'injection de vapeur ou d'eau dans la chambre de combustion.
  • les procédés dits secs qui sont basés sur une amélioration des conditions de combustion.
Several solutions are known to reduce emissions of nitrogen oxides. We can broadly classify them into two main types:
  • wet processes based on the injection of steam or water into the combustion chamber.
  • the so-called dry processes which are based on an improvement of the combustion conditions.

Les procédés humides donnent des résultats assez satisfaisants du point de vue technique mais sont souvent plus complexes, plus difficiles à mettre en oeuvre, que les procédés secs.The wet processes give fairly satisfactory results from the from a technical point of view but are often more complex, more difficult to implement, than dry processes.

En outre il sont plus coûteux que les procédés secs à cause de la vapeur d'eau nécessairement injectée soit dans le liquide soit dans la phase gazeuse.In addition, they are more expensive than dry processes because of the water vapor necessarily injected either in the liquid or in the phase carbonated.

Les procédés dits secs visent généralement à réaliser la combustion d'un prémélange pauvre d'air et de carburant réalisé préalablement. La demande de brevet EP-A2-0 769 657 illustre un système de ce type. La stabilité de la combustion et l'allumage du prémélange principal sont assurés par une flamme pilote de petite puissance dont le rôle est aussi d'assurer le fonctionnement de la machine au régime de ralenti. La richesse dans la chambre étant fixée par les proportions respectives d'air et de carburant prémélangées, il est possible de limiter les températures de flamme et donc l'oxyde d'azote thermique.The so-called dry processes generally aim to achieve combustion a lean premix of air and fuel produced beforehand. The Patent application EP-A2-0 769 657 illustrates a system of this type. The stability of combustion and ignition of the main premix are ensured by a pilot flame of small power whose role is also to ensure the machine running at idle speed. The wealth in the chamber being fixed by the respective proportions of air and fuel premixed, it is possible to limit the flame temperatures and therefore thermal nitrogen oxide.

Cette technologie peut être mise en oeuvre assez facilement avec un carburant gazeux. Dans le cas d'un carburant liquide, le problème est plus complexe puisqu'il est nécessaire de le vaporiser avant son mélange avec l'air. L'évaporation peut être réalisée en évaporant un film liquide sur une paroi chaude ou en injectant le carburant sous forme de spray dans un conduit où il se mélange avec l'air : c'est le cas du document européen précité.This technology can be implemented quite easily with a gaseous fuel. In the case of liquid fuel, the problem is more complex since it is necessary to vaporize it before mixing with the air. Evaporation can be carried out by evaporating a liquid film on a hot wall or by injecting fuel as a spray into a duct where it mixes with air: this is the case of the European document cited above.

Actuellement, les technologies de combustion avec prémélange ne donnent pas de résultats satisfaisants avec du carburant liquide. De plus, cette technique nécessite la mise en oeuvre d'un brûleur pilote permettant d'assurer la stabilité de la flamme notamment dans des conditions pauvres. Ce brûleur assurant le fonctionnement de la machine durant les phases de ralenti, il y passe un débit de carburant pouvant atteindre près du tiers du débit total. Pour certaines applications, il fonctionne dans des conditions opératoires proches de la stoechiométrie donc dans des conditions opératoires défavorables du point de vue de la production des oxydes d'azote.Currently, premixed combustion technologies do not not give satisfactory results with liquid fuel. Moreover, this technique requires the implementation of a pilot burner allowing to ensure the stability of the flame, especially in poor conditions. This burner ensuring the operation of the machine during the phases of idling, it passes a fuel flow of up to almost a third of the total flow. For some applications, it works under conditions operating close to stoichiometry so under conditions unfavorable procedures from the point of view of oxide production nitrogen.

La présente invention permet de résoudre notamment l'ensemble des problèmes évoqués ci-dessus. Il s'agit d'une solution alternative aux chambres de combustion fonctionnant en prémélange ou aux procédés humides tels qu'évoqués ci-avant. The present invention makes it possible in particular to resolve all of the problems discussed above. It is an alternative solution to combustion chambers operating in premix or in processes damp as mentioned above.

La présente invention vise à réaliser une flamme de diffusion en combinant certaines conditions d'injection de l'air et du carburant liquide.The present invention aims to achieve a diffusion flame by combining certain conditions of injection of air and liquid fuel.

Il existe déjà des flammes de diffusion dans d'autres domaines techniques que celui des chambres de combustion de turbines à gaz. Les brûleurs pour chaudières tels que décrits par exemple dans le brevet FR 2 656 676 permettent de créer des flammes de diffusion. De même le brevet US 5 562 437 divulgue ce type de structure adapté toutefois à un brûleur de chaudière.Diffusion flames already exist in other areas techniques than that of gas turbine combustion chambers. The burners for boilers as described for example in the patent FR 2 656 676 allow the creation of diffusion flames. Likewise the US Patent 5,562,437 discloses this type of structure, however suitable for a boiler burner.

Cependant dans ce type de combustion, les conditions opératoires sont fondamentalement différentes.

  • Les richesses sont beaucoup plus fortes dans les brûleurs que dans les turbines. Les brûleurs opèrent autour de la stoechiométrie ou avec un léger excès d'air alors que la richesse globale dans les chambres de turbines est habituellement comprise entre 0,15 et 0,35.
  • La combustion est opérée sous pression (celle de la sortie du compresseur) alors que les brûleurs fonctionnent à la pression atmosphérique.
  • Par ailleurs les densités de chauffe sont largement supérieures dans les chambres de combustion de turbines, couramment plusieurs dizaines de fois supérieures.
However, in this type of combustion, the operating conditions are fundamentally different.
  • The wealth is much higher in the burners than in the turbines. The burners operate around stoichiometry or with a slight excess of air while the overall richness in the turbine chambers is usually between 0.15 and 0.35.
  • Combustion is carried out under pressure (that of the compressor outlet) while the burners operate at atmospheric pressure.
  • Furthermore, the heating densities are much higher in the combustion chambers of turbines, usually several tens of times higher.

On connaít aussi des techniques de flammes élémentaires dans le domaine des brûleurs pour essais de puits pétroliers. Là encore les conditions de fonctionnement sont très différentes notamment la pression qui est ici la pression atmosphérique. La demande de brevet français FR 2 741 424 décrit un brûleur de ce type. We also know elementary flame techniques in the field of burners for oil well testing. Again the operating conditions are very different including the pressure which here is atmospheric pressure. French patent application FR 2 741 424 describes a burner of this type.

Ces conditions de fonctionnement différentes imposent des contraintes et donc des structures spécifiques adaptées à ces fonctions particulières.These different operating conditions impose constraints and therefore specific structures adapted to these functions particular.

La présente invention a pour objet une chambre de combustion de turbine à gaz fonctionnant au carburant liquide, comprenant une enceinte tubulaire ayant au moins une entrée d'air, un moyen d'injection de combustible liquide situé sur ou à proximité de l'axe longitudinal de l'enceinte tubulaire, une sortie vers la turbine, au moins deux types d'entrées d'air sous pression situées à proximité l'une de l'autre : la première introduisant l'air hélicoïdalement autour de l'axe longitudinal de la chambre de combustion, la deuxième entrée introduit l'air tangentiellement à l'enceinte afin de créer autour des jets de combustible des écoulements contra-rotatifs destinés à améliorer le mélange entre ledit combustible et l'air.The present invention relates to a combustion chamber of gas turbine operating on liquid fuel, comprising an enclosure tubular having at least one air inlet, a means for injecting liquid fuel located on or near the longitudinal axis of the enclosure tubular, one outlet to the turbine, at least two types of air inlets under pressure located close to each other: the first introducing air helically around the longitudinal axis of the combustion chamber, the second inlet introduces air tangentially to the enclosure to create around the fuel jets counter-rotating flows intended for improve the mixture between said fuel and air.

Selon l'invention :

  • Ledit moyen d'injection de carburant comprend un ensemble d'orifices disposés de façon à créer des jets séparés de combustible, lesdits jets étant situés suivant les génératrices d'un cône d'angle au sommet compris entre 30° et 60°;
l'ensemble fonctionnant à une pression comprise entre 2 et 30 bars et à une richesse comprise entre environ 0,4 et environ 0,8, et le temps de séjour des fluides à l'intérieur de l'enceinte est inférieur à 50 millisecondes.According to the invention:
  • Said fuel injection means comprises a set of orifices arranged so as to create separate jets of fuel, said jets being located along the generatrices of a cone with an angle at the apex between 30 ° and 60 °;
the assembly operating at a pressure between 2 and 30 bars and at a richness between about 0.4 and about 0.8, and the residence time of the fluids inside the enclosure is less than 50 milliseconds.

De façon particulière, la première entrée d'air permet d'introduire de 30% à 70% de la quantité totale d'air sous pression qui entre dans la chambre de combustion, le reste étant injecté à travers les secondes entrées d'air sous pression. In particular, the first air inlet allows the introduction of 30% to 70% of the total amount of pressurized air entering the combustion chamber, the rest being injected through the second inlets pressurized air.

Conformément à l'invention, ledit moyen d'injection présente entre 5 et 12 orifices destinés à l'injection du combustible liquide, de préférence entre 6 et 10 orifices.According to the invention, said injection means has between 5 and 12 orifices intended for the injection of liquid fuel, preferably between 6 and 10 ports.

Par ailleurs, les entrées d'air et le moyen d'injection sont disposés de telle sorte que le nombre de swirl N est compris entre 0,2 et 0,4, N étant défini par:

Figure 00060001
où :

  • R1 et R2 sont respectivement les rayons intérieur et extérieur de l'entrée d'air (7), exprimés en mètres;
  • ρ est la masse volumique de l'air en kg/m3;
  • Vax est la vitesse axiale du fluide à la sortie de l'entrée (7);
  • Vtg est la vitesse tangentielle du fluide à la sortie de l'entrée (7) ; les vitesses étant exprimées en m/s.
    • Furthermore, the air inlets and the injection means are arranged so that the number of swirls N is between 0.2 and 0.4, N being defined by:
    Figure 00060001
    or :
  • R 1 and R 2 are the interior and exterior radii of the air inlet (7), respectively, expressed in meters;
  • ρ is the density of air in kg / m 3 ;
  • Vax is the axial speed of the fluid at the outlet of the inlet (7);
  • V tg is the tangential speed of the fluid at the outlet of the input (7); the speeds being expressed in m / s.

    • Selon une particularité de l'invention, le moyen d'injection comprend un disque central situé sur l'axe longitudinal de l'enceinte tubulaire, autour duquel est disposé un anneau percé desdits orifices, la surface de l'anneau étant un tronc de cône.According to a feature of the invention, the injection means comprises a central disc located on the longitudinal axis of the tubular enclosure, around which is arranged a ring pierced with said orifices, the surface of the ring being a truncated cone.

    Spécifiquement, l'entrée tangentielle comprend un ensemble d'inserts répartis sur la périphérie de l'enceinte, qui dirigent l'air tangentiellement à la paroi de l'enceinte avec un sens de rotation contraire à celui de l'écoulement principal. Specifically, the tangential entry includes a set of inserts distributed around the periphery of the enclosure, which direct the air tangentially to the enclosure wall with a direction of rotation opposite to that of flow main.

    Les entrées d'air peuvent être dimensionnées de façon à ce que la vitesse de l'air à l'intérieur de la chambre de combustion soit comprise entre 20 et 120 m/s.The air inlets can be dimensioned so that the air speed inside the combustion chamber is between 20 and 120 m / s.

    Par ailleurs, l'angle au sommet du cône d'injection est préférentiellement compris entre 35° et 45°.Furthermore, the angle at the top of the injection cone is preferably between 35 ° and 45 °.

    D'autres caractéristiques, détails, avantages de l'invention apparaítront mieux à la lecture de la description faite ci-après à titre illustratif et nullement limitatif en référence aux dessins annexés sur lesquels :

    • La figure 1 est une coupe longitudinale simplifiée d'une chambre de combustion selon l'invention;
    • La figure 2 est une coupe schématique d'un détail de l'invention selon II de la figure 1; et
    • La figure 3 est une coupe longitudinale simplifiée d'un turbo-compresseur mettant en oeuvre l'invention.
    Other characteristics, details and advantages of the invention will appear better on reading the description given below by way of illustration and in no way limitative with reference to the appended drawings in which:
    • Figure 1 is a simplified longitudinal section of a combustion chamber according to the invention;
    • Figure 2 is a schematic section of a detail of the invention according to II of Figure 1; and
    • Figure 3 is a simplified longitudinal section of a turbo-compressor implementing the invention.

    La chambre de combustion selon l'invention, illustrée schématiquement par la figure 1, comprend un carter extérieur tubulaire 1 et une enceinte intérieure 2 coaxiale au carter 1.The combustion chamber according to the invention, illustrated schematically in Figure 1, includes a tubular outer casing 1 and an inner enclosure 2 coaxial with the casing 1.

    Les deux enveloppes sont fermées à une extrémité où elles délimitent un espace fonctionnel 3. En outre, les enveloppes 1 et 2 définissent entre elles un espace annulaire 4 pour la circulation de l'air sous pression avant d'entrer dans la chambre de combustion proprement dite.The two envelopes are closed at one end where they delimit a functional space 3. In addition, envelopes 1 and 2 define between they an annular space 4 for the circulation of pressurized air before to enter the combustion chamber proper.

    La chambre de combustion proprement dite, 5, est définie par le volume intérieur de l'enceinte 2. The actual combustion chamber, 5, is defined by the interior volume of the enclosure 2.

    Au fond de la chambre 5 est disposé un moyen d'injection de carburant 6 qui comprend préférentiellement un disque central 61 situé sur ou à proximité immédiate de l'axe longitudinal XX' de l'enceinte 2. Par ailleurs le moyen d'injection 6 comprend un ensemble d'orifices 62 disposés sur un anneau en tronc de cône. Avantageusement, de 5 à 12 jets peuvent être créés ; préférentiellement entre 6 et 10. Ces jets sont séparés les uns des autres et situés selon les génératrices d'un cône d'angle au sommet a compris entre 30° et 60°, préférentiellement entre 35° et 45°.At the bottom of the chamber 5 is disposed a means for injecting fuel 6 which preferably comprises a central disc 61 located on or in the immediate vicinity of the longitudinal axis XX 'of the enclosure 2. By elsewhere the injection means 6 comprises a set of orifices 62 arranged on a truncated cone ring. Advantageously, from 5 to 12 jets can be created; preferably between 6 and 10. These jets are separated from each other from others and located along the generatrices of a corner cone at the top a between 30 ° and 60 °, preferably between 35 ° and 45 °.

    Le moyen d'injection 6 peut fonctionner avec une assistance supplémentaire en air ; on obtient alors des gouttelettes de diamètre moyen inférieur à 50 micromètres.The injection means 6 can operate with assistance additional air; we then obtain medium diameter droplets less than 50 micrometers.

    L'intérêt de réaliser une flamme à jets séparés est multiple. Cette flamme ne se comporte pas comme plusieurs flammes axiales indépendantes. Il y a tout d'abord des interactions de type thermique entre les différents jets avec une modification des écoulements entre les jets et donc des conditions stoechiométriques locales. Ces conditions dépendent bien évidemment de l'angle existant entre les jets.The advantage of making a flame with separate jets is multiple. This flame does not behave like several axial flames independent. First there are thermal interactions between the different jets with a modification of the flows between the jets and therefore local stoichiometric conditions. These conditions depend obviously the angle between the jets.

    Plus cet angle est petit, plus la flamme se rapproche d'une flamme axiale de diffusion, dont on sait que les performances du points de vue des émissions de Nox sont mauvaises puisque le carburant se mélange mal avec l'air.The smaller this angle, the closer the flame is to a flame axial diffusion, which we know that the performances from the point of view of Nox emissions are bad since the fuel mixes badly with the air.

    Si l'angle augmente trop, le risque est de projeter des gouttelettes le long des parois. Il peut en résulter la formation de coke ou formation d'imbrûlés et de CO dans le cas où les parois sont refroidies et donc les températures basses.If the angle increases too much, the risk is of projecting droplets the along the walls. This can result in the formation of coke or formation unburnt and CO in the case where the walls are cooled and therefore the low temperatures.

    Le nombre de jets a aussi son importance. Si celui-ci est trop important, on observe un effet de blocage de l'écoulement par les jets de combustible. Il en résulte une zone appauvrie en air derrière les jets, ce qui conduit à des conditions de combustion riches, donc à haute température. Si les jets sont trop peu nombreux, les interactions entre jets diminuent et on se retrouve dans le cas de n flammes axiales indépendantes.The number of jets is also important. If this one is too important, there is an effect of blocking the flow by the jets of combustible. This results in an air-depleted area behind the jets, which leads to rich combustion conditions, therefore at high temperature. Yes there are too few jets, the interactions between jets decrease and we found in the case of n independent axial flames.

    Par ailleurs, deux types d'entrée d'air sous pression sont prévus, situés tous deux du côté de l'espace fonctionnel 3.In addition, two types of pressure air inlet are provided, both located on the side of functional space 3.

    Le premier type introduit de l'air hélicoïdalement dans l'enceinte 2, autour de l'axe longitudinal de l'enceinte. Cette entrée 7 est ici un anneau autour du moyen d'injection 6. On parle d'air "swirlé axial". Des ailettes inclinées 71 peuvent être disposées dans l'anneau afin d'imprimer à cet air une quantité de mouvement tangentielle.The first type introduces air helically into enclosure 2, around the longitudinal axis of the enclosure. This entry 7 is here a ring around the injection means 6. We speak of "axial swirled" air. Fins 71 can be arranged in the ring to print to this air a quantity of tangential movement.

    Le deuxième type d'entrée d'air comprend des arrivées périphériques 8 qui permettent d'injecter l'air tangentiellement à la paroi de l'enceinte 2. A cet effet des inserts 81 telles que montrés sur la figure 2 peuvent être prévus.The second type of air intake includes peripheral inlets 8 which allow the air to be injected tangentially to the wall of the enclosure 2. A this effect of the inserts 81 as shown in FIG. 2 can be planned.

    Les inserts 81 dirigent l'air tangentiellement et en sens contraire du premier type d'écoulement. Ceci permet d'augmenter le cisaillement entre les deux écoulements et donc d'accélérer le mélange entre l'air et les gouttelettes de combustible.The inserts 81 direct the air tangentially and in the opposite direction to the first type of flow. This increases the shear between the two flows and therefore accelerate the mixing between the air and the fuel droplets.

    Pour obtenir une flamme stable dans de bonnes conditions de richesse, le débit d'air au niveau de l'entrée 7 est compris entre 30 et 70% de l'air servant à la combustion, préférentiellement entre 40 et 50%. Bien entendu le débit d'air passant par les entrées tangentielles 8 est le complément à 100%. L'air de dilution est introduit si nécessaire en aval de la zone de combustion 5, à travers des orifices pratiqués dans l'enceinte 2. To obtain a stable flame under good conditions of richness, the air flow at inlet 7 is between 30 and 70% air used for combustion, preferably between 40 and 50%. Well heard the air flow passing through the tangential inlets 8 is the 100% complement. Dilution air is introduced if necessary downstream of the combustion zone 5, through orifices made in the enclosure 2.

    Concernant la stabilité de la flamme de combustion, le moyen d'injection 6 comprend avantageusement un disque central 61. Celui-ci permet, en combinaison avec la mise en rotation de l'écoulement, de générer une petite recirculation interne selon les flèches A de la figure 1, au niveau du nez de l'injecteur 6. La zone 10 délimitée par cette recirculation, est plutôt riche en combustible et elle assure en partie la stabilité de la combustion. Toutefois, comme énoncé plus haut, la majorité du carburant est brûlé dans des conditions pauvres puisque la richesse globale dans la chambre de combustion 5 est comprise entre 0,4 et 0,8. Il est ici rappelé qu'un brûleur à flammes séparées opère autour de la stoechiométrie ou avec un léger excès d'air.Regarding the stability of the combustion flame, the means injection 6 advantageously comprises a central disc 61. The latter allows, in combination with the rotation of the flow, generate a small internal recirculation according to the arrows A in Figure 1, at level of the injector nose 6. The zone 10 delimited by this recirculation, is rather rich in fuel and it partly ensures the stability of the combustion. However, as stated above, the majority of the fuel is burned in poor conditions since the overall wealth in the combustion chamber 5 is between 0.4 and 0.8. Here it is recalled that a separate flame burner operates around stoichiometry or with a slight excess of air.

    Les entrées d'air 7, 8 et le moyen d'injection 6 sont disposés de telle sorte que le nombre de swirl, N, est préférentiellement compris entre 0,2 et 0,4. Le nombre de swirl, N, étant défini par

    Figure 00100001
    où :

  • R1 et R2 sont respectivement les rayons intérieur et extérieur de l'entrée d'air (7), exprimés en mètres;
  • ρ est la masse volumique de l'air en kg/m3;
  • Vax est la vitesse axiale du fluide à la sortie de l'entrée (7);
  • Vtg est la vitesse tangentielle du fluide à la sortie de l'entrée (7) ; Les vitesses sont exprimées en m/s.
    • The air inlets 7, 8 and the injection means 6 are arranged so that the number of swirls, N, is preferably between 0.2 and 0.4. The number of swirls, N, being defined by
    Figure 00100001
    or :
  • R 1 and R 2 are the interior and exterior radii of the air inlet (7), respectively, expressed in meters;
  • ρ is the density of air in kg / m 3 ;
  • Vax is the axial speed of the fluid at the outlet of the inlet (7);
  • V tg is the tangential speed of the fluid at the outlet of the input (7); The speeds are expressed in m / s.

    • La chambre de combustion 5 selon l'invention étant adaptée à fonctionner avec une turbine, le cycle thermodynamique de celle-ci impose un fonctionnement sous une pression qui peut varier d'environ 2 à environ 30 bars.The combustion chamber 5 according to the invention being adapted to operate with a turbine, the thermodynamic cycle of this imposes operation under pressure which can vary from approximately 2 to approximately 30 bars.

    Vis-à-vis d'un brûleur fonctionnant à la pression atmosphérique, ceci modifie la masse volumique de l'air et donc le rapport des masses volumiques entre l'air et le carburant, rapport qui peut être multiplié par dix. Les conditions de mélange et d'évaporation sont de ce fait notablement différentes.Opposite a burner operating at atmospheric pressure, this changes the density of air and therefore the mass ratio between air and fuel, which can be multiplied by ten. The mixing and evaporation conditions are therefore considerably different.

    En outre, les temps de séjour dans la chambre de combustion 5 selon l'invention sont couramment inférieurs à 50 millisecondes, ce qui conduit à des densités de chauffe comprises entre 50 et 200 MW/m3.In addition, the residence times in the combustion chamber 5 according to the invention are commonly less than 50 milliseconds, which leads to heating densities of between 50 and 200 MW / m 3 .

    A titre de comparaison, les densités de chauffe dans le domaine des brûleurs de chaudière sont plutôt inférieures à 1 MW/m3, avec des temps de séjour de l'ordre de la seconde.By way of comparison, the heating densities in the field of boiler burners are rather less than 1 MW / m 3 , with residence times of the order of a second.

    Les conditions particulières de fonctionnement de la présente invention conduisent à des vitesses de l'air comprises entre 20 et 120 m/s vu le dimensionnement des première et deuxième entrées d'air.The specific operating conditions of this invention lead to air speeds between 20 and 120 m / s seen the dimensioning of the first and second air inlets.

    Afin de mieux illustrer une application préférée de l'invention, la figure 3 montre en coupe longitudinale un ensemble turbo-compresseur susceptible de mettre en oeuvre l'invention ; cette figure a été commentée en tête de la description.In order to better illustrate a preferred application of the invention, the figure 3 shows in longitudinal section a turbo-compressor assembly likely to implement the invention; this figure was commented on in description head.

    Claims (8)

    Chambre de combustion de turbine à gaz fonctionnant au carburant liquide, comprenant une enceinte tubulaire (2) ayant au moins une entrée d'air, un moyen (6) d'injection de combustible liquide situé sur ou à proximité de l'axe longitudinal XX' de l'enceinte tubulaire, une sortie vers la turbine, au moins deux types d'entrées d'air sous pression situées à proximité l'une de l'autre, la première (7) introduisant l'air hélicoïdalement autour de l'axe longitudinal de la chambre de combustion, la deuxième entrée (8) introduisant l'air tangentiellement à l'enceinte (2) afin de créer autour des jets de combustible des écoulements contra rotatifs destinés à améliorer le mélange de l'air et dudit combustible, caractérisé en ce que ledit moyen (6) d'injection de combustible comprend un ensemble d'orifices disposés de façon à créer des jets séparés de combustible, lesdits jets étant situés suivant les génératrices d'un cône d'angle au sommet compris entre 30° et 60°; en ce que l'ensemble fonctionne à une pression comprise entre 2 et 30 bars et avec une richesse comprise entre environ 0,4 et environ 0,8 et en ce que le temps de séjour des fluides à l'intérieur de l'enceinte (2) est inférieur à 50 millisecondes.Fuel turbine gas turbine combustion chamber liquid, comprising a tubular enclosure (2) having at least one inlet air, a means (6) of injecting liquid fuel located on or near from the longitudinal axis XX 'of the tubular enclosure, an outlet to the turbine, at at least two types of pressurized air inlets located near one of the other, the first (7) introducing the air helically around the axis longitudinal of the combustion chamber, the second inlet (8) introducing air tangentially to the enclosure (2) to create around the jets fuel from counter-rotating flows intended to improve the mixture of air and said fuel, characterized in that said means (6) fuel injection system comprises a set of orifices arranged so as to create separate fuel jets, said jets being located along the generatrices of a cone of angle at the summit between 30 ° and 60 °; in that the assembly operates at a pressure between 2 and 30 bars and with a richness between about 0.4 and about 0.8 and in this that the residence time of the fluids inside the enclosure (2) is less than 50 milliseconds. Chambre de combustion selon la revendication 1, caractérisée en ce que la première entrée d'air (7) permet d'introduire de 30% à 70% de la quantité totale d'air sous pression utilisé pour la combustion, le reste étant injecté à travers les deuxièmes entrées d'air sous pression (8).Combustion chamber according to claim 1, characterized in what the first air inlet (7) allows to introduce from 30% to 70% of the total amount of pressurized air used for combustion, the remainder being injected through the second pressurized air inlets (8). Chambre de combustion selon l'une quelconque des revendications 1 ou 2, caractérisée en ce que ledit moyen d'injection (6) présente entre 5 et 12 orifices (62) destinés à l'injection du combustible liquide, de préférence entre 6 et 10 orifices. Combustion chamber according to any one of the claims 1 or 2, characterized in that said injection means (6) has between 5 and 12 orifices (62) intended for the injection of liquid fuel, preferably between 6 and 10 holes. Chambre de combustion selon l'une quelconque des revendications précédentes, caractérisée en ce que les entrées d'air (7, 8) et le moyen d'injection (6) sont disposés de telle sorte que le nombre de swirl N est compris entre 0,2 et 0,4 ; N étant défini par :
    Figure 00130001
    où : R1 et R2 sont respectivement les rayons intérieur et extérieur de l'entrée d'air (7), exprimés en mètres; ρ est la masse volumique de l'air en kg/m3; Vax est la vitesse axiale du fluide à la sortie de l'entrée (7); Vtg est la vitesse tangentielle du fluide à la sortie de l'entrée (7) ; les vitesses étant exprimées en m/s.     Combustion chamber according to any one of the preceding claims, characterized in that the air inlets (7, 8) and the injection means (6) are arranged so that the number of swirl N is between 0 , 2 and 0.4; N being defined by:
    Figure 00130001
    or : R 1 and R 2 are the interior and exterior radii of the air inlet (7), respectively, expressed in meters; ρ is the density of air in kg / m 3 ; Vax is the axial speed of the fluid at the outlet of the inlet (7); V tg is the tangential speed of the fluid at the outlet of the input (7); the speeds being expressed in m / s.     Chambre de combustion selon la revendication 3, caractérisée en ce que le moyen d'injection (6) comprend un disque central (61) situé sur l'axe longitudinal XX' de l'enceinte tubulaire, autour duquel est disposé un anneau percé desdits orifices (62), la surface de l'anneau étant un tronc de cône.Combustion chamber according to claim 3, characterized in that the injection means (6) comprises a central disc (61) located on the longitudinal axis XX 'of the tubular enclosure, around which a ring pierced with said orifices (62), the surface of the ring being a trunk of cone. Chambre de combustion selon l'une quelconque des revendications précédentes, caractérisée en ce que l'entrée tangentielle (8) comprend un ensemble d'inserts répartis sur la périphérie de l'enceinte (2), qui dirigent l'air tangentiellement à la paroi de l'enceinte (2), avec un sens de rotation contraire à celui de l'écoulement principal.Combustion chamber according to any one of the claims previous, characterized in that the tangential entry (8) comprises a set of inserts distributed around the periphery of the enclosure (2), which direct the air tangentially to the wall of the enclosure (2), with a direction of rotation contrary to that of the main flow. Chambre de combustion selon l'une quelconque des revendications précédentes, caractérisée en ce que les entrées d'air sont dimensionnées de façon à ce que la vitesse de l'air à l'intérieur de la chambre de combustion soit comprise entre 20 et 120 m/s.Combustion chamber according to any one of the claims previous, characterized in that the air inlets are dimensioned so that the air speed inside the combustion chamber is between 20 and 120 m / s. Chambre de combustion selon la revendication 1, caractérisée en ce que l'angle au sommet du cône d'injection est préférentiellement compris entre 35° et 45°.Combustion chamber according to claim 1, characterized in what the angle at the top of the injection cone is preferably understood between 35 ° and 45 °.
    EP99400141A 1998-01-28 1999-01-21 Method of operating a gas turbine combustion chamber for liquid fuel Expired - Lifetime EP0933594B1 (en)

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    FR9800932A FR2774152B1 (en) 1998-01-28 1998-01-28 COMBUSTION CHAMBER OF GAS TURBINE OPERATING ON LIQUID FUEL
    FR9800932 1998-01-28

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    US8621870B2 (en) 2007-12-19 2014-01-07 Alstom Technology Ltd. Fuel injection method
    NL2005381C2 (en) * 2010-09-21 2012-03-28 Micro Turbine Technology B V Combustor with a single limited fuel-air mixing burner and recuperated micro gas turbine.
    WO2012039611A1 (en) * 2010-09-21 2012-03-29 Micro Turbine Technology Bv Combustor with a single limited fuel-air mixing burner and recuperated micro gas turbine

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    DE69922559T2 (en) 2005-05-12
    FR2774152B1 (en) 2000-03-24
    EP0933594B1 (en) 2004-12-15
    FR2774152A1 (en) 1999-07-30
    US20020050139A1 (en) 2002-05-02
    DE69922559D1 (en) 2005-01-20
    JPH11270852A (en) 1999-10-05
    US6378310B1 (en) 2002-04-30

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