EP0224397A1 - Sectoral fuel injection head - Google Patents

Sectoral fuel injection head Download PDF

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Publication number
EP0224397A1
EP0224397A1 EP86402290A EP86402290A EP0224397A1 EP 0224397 A1 EP0224397 A1 EP 0224397A1 EP 86402290 A EP86402290 A EP 86402290A EP 86402290 A EP86402290 A EP 86402290A EP 0224397 A1 EP0224397 A1 EP 0224397A1
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EP
European Patent Office
Prior art keywords
sectors
bowl
holes
combustion chamber
air
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
EP86402290A
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German (de)
French (fr)
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EP0224397B1 (en
Inventor
Gérard Yves Georges Barbier
Gérard Joseph Pascal Bayle-Laboure
Michel André Albert Desaulty
Rodolphe Martinez
Jérome Perigne
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.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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Publication of EP0224397A1 publication Critical patent/EP0224397A1/en
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Publication of EP0224397B1 publication Critical patent/EP0224397B1/en
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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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/26—Controlling the air flow
    • 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
    • F23C7/008—Flow control devices
    • 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

Definitions

  • the invention relates to the supply of fuel and primary air to a combustion chamber, in particular for a turbomachine.
  • Traditional combustion chambers generally have a high-rich primary zone and a dilution zone.
  • part of the primary air flow is injected, on the one hand by means of internal and external turbulence tendrils intended to create a cone for spraying the fuel leaving the injector, on the other hand by means orifices of the chamber bottom and the internal and external walls of the combustion chamber.
  • the choice of the fraction of air to be injected into the primary zone results from a compromise between the performance of the combustion chamber at full gas: emission of smoke, thermal resistance of the walls, distribution of temperatures and performance in idle mode : yield, stability.
  • aerodynamic bowl injectors such as those described in the applicant's prior patents have been developed: FR 2 357 738 and FR 2 391 359. These injectors are mounted on the chamber bottom with the interposition of a part intermediate called bowl comprising a frustoconical part flared downstream and pierced with a multiplicity of small diameter holes through which air at high pressure enters the sprayed fuel cone. By the turbulence it creates and the intimate mixing it produces, this bowl completes the role of the injector, acts on the mixing composition and allows the creation of a mini primary zone in slow motion.
  • the present invention aims to improve these types of aerodynamic injectors with intermediate bowl by shaping them so that they contribute, on the one hand, to improving the cooling of the walls of the combustion chamber and, on the other hand on the other hand, to improve the efficiency at idle, in particular when they are mounted in annular combustion chambers on the bottom of which they are regularly distributed, this making best use of the localized recirculation zones existing between the adjacent injectors.
  • the subject of the invention is a device for injecting air and fuel into a combustion chamber, in particular of a turbomachine, comprising at least one fuel injector, an external swirl spin for the passage of atomizing air.
  • fuel equipped with a diaphragm for modulating the air inlet flow rate, a bowl-shaped body comprising a downstream web flared in the direction of flow and provided with a row of bowl holes for the injection of air into the sprayed fuel cone and an impact cooling chamber formed by the downstream web, an intermediate ring and an outer skirt having air inlet orifices.
  • the chamber is divided into four equal sectors, diametrically opposite two by two and separated by radial partitions, two first sectors having small diameter bowl holes and two second sectors having large diameter bowl holes.
  • the diameter of the holes of the first sectors is calculated for an optimized operation of the combustion chamber at idle and the diameter of the holes of the second sectors for an optimized yield at full gas speed.
  • the injection device comprises a diaphragm for modulating the air flow rate of the large diameter bowl holes of the second sectors.
  • the bowls are oriented so that the first sectors of each bowl are arranged side by side while the second sectors of the bowls having large diameter holes are oriented towards the internal and external walls of the combustion chamber to improve cooling at full gas speed.
  • Figure 1 is shown in longitudinal half-section an annular combustion chamber 1 for a turbomachine comprising the injection system according to the invention.
  • Chamber 1 is between an external casing 2 and an internal ferrule 3 which delimit the stream of compressed gases.
  • a fraction F1 of the upstream air coming from the compressor (not shown) is guided through the injection system 4 for the formation of the fuel mixture. This passes into the primary zone 5 where the combustion reactions take place, then the gases produced are diluted in the dilution zone 6 and cooled in the downstream secondary zone 7 and are distributed to the turbine, not shown, which they train.
  • the injector of which only the body 8 is shown in dotted lines in FIG. 1 is connected to the bottom 9 of the combustion chamber by an intermediate bowl 10 whose particular structure is the subject of the invention.
  • the injection system comprises, in known manner, an internal turbulence spin (not shown) which can be either of the radial type, or of the centripetal axial type intended to project the fuel from the injector forming a tapered jet flared downstream.
  • the injector 8 provided with its internal swirl spin is surrounded by a cap 11 forming the upstream wall of the intermediate bowl 10.
  • the cap 11 comprises downstream a frustoconical part lla extended upstream by a cylindrical bearing llb and finally by a radial wall llc delimiting with the radial wall 12c of an intermediate ring 12 a radial channel provided with inclined blades 13 forming an external swirling swirl for the injection system.
  • the intermediate ring 12 has a cylindrical part 12b and is extended by tightening downstream by a frustoconical bearing 12a, the cap 11 and the ring 12 forming an axial-centripetal annular channel for the air coming from the swirl of external turbulence 13.
  • the external turbulence spin 13 can be diaphragmed by a cylindrical ring 22 movable in rotation and having air intake orifices in number equal to that of the passages of the spin 13.
  • the rotation of the diaphragm 22 takes place by means of an operating lever 23 (shown diagrammatically in FIG. 1) connected to a control system external to the casing 2 and not shown.
  • the external spin 13 can be closed at idle speed and opened continuously until full opening at full gas in order to optimize the air-fuel mixture conditions (air-fuel percentages, volume distribution, spraying) at all operating speeds, which is permitted because the external spin has an important axial component at full throttle conditions and low at idle, this being due to the fact that the spin is diaphragmed upstream and that, the section at the neck of the bowl being constant, the speed of delivery, axial at this level, is directly proportional to the air flow and is therefore increasing from idle to full throttle.
  • the ring 12 is extended downstream by a frustoconical downstream web 14 flared downstream and forming the bowl proper.
  • the latter is connected to the combustion chamber by an external cylindrical skirt 15 attached to its downstream edge and comprising a thread allowing a nut, not shown, to come to grip in a known manner a cup cut out in the bottom 9 of the combustion chamber.
  • the ring 12, the downstream web 14 and the outer skirt 15 form an annular cooling chamber 16 by impact of the web 14.
  • the skirt 15 has radial openings 17 regularly distributed around its periphery, allowing the supply of chamber 16 in upstream air.
  • the chamber 16 is divided into four equal, diametrically opposite sectors 16a, 16b, separated by radial partitions 21.
  • the downstream web 14 regularly has bowl holes distributed over its periphery allowing the upstream air introduced into the sectors 16a, 16b of the chamber 16 escape from said chamber by fulfilling a spraying function of the conical sheet 18 of fuel formed between the air jets from the two tendrils of external and internal turbulence.
  • the first two sectors 16a of the chamber 16 comprise on the parts of the downstream web 14 which are associated with them small diameter bowl holes 19 while the second sectors 16b comprise on the corresponding parts of the downstream web of bowl 20 of large diameter.
  • the first sectors 16a and the second sectors 16b are supplied separately with upstream air through the radial openings 17, the partitions 21 completely isolating them from each other.
  • the openings 17, supplying the second sectors with large-diameter bowl holes can be diaphragmed by two perforated cylindrical extensions 22a of the ring 22 forming the diaphragm of the external turbulence spin 13, in order to modulate the flow bowl hole outlet 20.
  • the diaphragms 22 and 22a thus secured are operated simultaneously towards opening or closing and it is immediately seen that, at idle, the large-diameter bowl holes 20 of the second sectors are not supplied and that they can be supplied up to full flow by the gradual opening of the diaphragm 22a until it is fully open to full gas, while the bowl holes 19 of the first two sectors remain supplied with upstream air throughout the operating life of the turbomachine.
  • Figure 5 shows the arrangement and orientation of the bowls according to the invention applied to an annular combustion chamber. In this figure, without showing the totality of each bowl, there are adjacent bowls 10 seen in a section similar to that of FIG. 4.
  • the combustion chamber 1 comprises a number of injectors connected to the chamber bottom by as many intermediate bowls regularly distributed in a ring.
  • the adjacent bowls are oriented so that their first sectors permanently supplied with upstream air are face to face while the second sectors diaphragmed at idle and delivering at full throttle are oriented facing the internal 3 and external walls. 2 of the combustion chamber to ensure maximum cooling at full gas.
  • This arrangement is chosen, in addition to the cooling needs of the walls at full gas speed, because we realized by tests of hydraulic analogy then by measurements of cold laser velocimetry that there was a zone of localized recirculation between the adjacent injectors where the flame is localized just before extinction and that it was important to keep a constant supply of carbureted air from this zone at idle in order to improve the flame stability in this operating configuration.
  • the diameter of the bowl holes 20 of the sectors 16b is calculated in order to make the operation of the injection device at full gas speed optimal, with the diaphragms open.
  • the optimal efficiency at idle and in full throttle was obtained with ten holes of two millimeters in diameter for each first sector of five holes of four millimeters in diameter for each second sector.
  • Another calculation element taken into account in determining the number and dimensions of the holes in each sector consists of the percentage of air admitted in the combustion chamber, respectively by the internal and external swirl tendrils, by the bowl and by the other air intake orifices of the chamber (primary orifices 24 and dilution orifices 25, devices for cooling the walls by impact, by convection or by wall film).
  • This arrangement combined with the orientation of the adjacent bowls with respect to each other and the variation in swirl angle of the external spin obtained by the upstream arrangement of the diaphragm 22, makes it possible to vary between idle and full throttle the volumetric distribution of the air-fuel mixture in the reaction zone and thereby improving the flame stability at idle and the combustion efficiency at full gas and achieving continuous modulation of these parameters throughout the operating range of the combustion chamber.

Abstract

L'invention concerne un dispositif d'injection d'air et de carburant dans une chambre de combustion de turbomachine. Le dispositif d'injection comprend un bol d'entrée d'air possédant une chambre de refroidissement par impact divisée en quatre secteurs égaux (16a, 16b) opposés deux à deux et séparés par des cloisons radiales (21) deux premiers secteurs (16a) comprenant des trous de bol de faible diamètre et deux seconds secteurs comportant des trous de bols de gros diamètre, pouvant être diaphragmés.The invention relates to a device for injecting air and fuel into a combustion chamber of a turbomachine. The injection device comprises an air inlet bowl having an impact cooling chamber divided into four equal sectors (16a, 16b) opposite in pairs and separated by radial partitions (21) two first sectors (16a) comprising small diameter bowl holes and two second sectors comprising large diameter bowl holes, which can be diaphragmed.

Description

L'invention concerne l'alimentation en carburant et en air primaire d'une chambre de combustion notamment pour turbomachine.The invention relates to the supply of fuel and primary air to a combustion chamber, in particular for a turbomachine.

Les chambres de combustion traditionnelles comportent généralement une zone primaire à richesse élevée et une zone de dilution. Dans la zone primaire, est injectée une partie du débit d'air primaire, d'une part au moyen de vrilles de turbulences internes et externes destinées à créer un cône de pulvérisation du carburant sortant de l'injecteur, d'autre part au moyen d'orifices du fond de chambre et des parois internes et externes de la chambre de combustion. Le choix de la fraction d'air à injecter dans la zone primaire résulte d'un compromis entre les performances de la chambre de combustion au plein gaz : émission de fumées, tenue thermique des parois, répartition des températures et les performances en régime de ralenti : rendement, stabilité.Traditional combustion chambers generally have a high-rich primary zone and a dilution zone. In the primary zone, part of the primary air flow is injected, on the one hand by means of internal and external turbulence tendrils intended to create a cone for spraying the fuel leaving the injector, on the other hand by means orifices of the chamber bottom and the internal and external walls of the combustion chamber. The choice of the fraction of air to be injected into the primary zone results from a compromise between the performance of the combustion chamber at full gas: emission of smoke, thermal resistance of the walls, distribution of temperatures and performance in idle mode : yield, stability.

En raison de l'accroissement des performances demandées aux chambres de combustion des moteurs modernes, le compromis entre performances au ralenti et au plein gaz est de plus en plus difficile à trouver. Pour y parvenir, une première solution a consisté à réaliser des chambres à deux modules : l'un adapté au régime de plein gaz et l'autre au régime de ralenti. Les chambres lourdes, car volumineuses, et coûteuses, car elles nécessitent le doublement des points d'injection, posent également des problèmes de régulation aux régimes intermédiaires.Due to the increased performance demanded from the combustion chambers of modern engines, the compromise between performance at idle and at full throttle is increasingly difficult to find. To achieve this, a first solution consisted in producing chambers with two modules: one adapted to the full throttle regime and the other to the idle regime. Heavy chambers, because they are bulky, and expensive, since they require the injection points to be doubled, also pose problems of regulation for intermediate regimes.

Pour éviter les problèmes rencontrés avec les chambres de combustion initiales et les chambres à deux modules dont il vient d'être question, une autre voie a été abordée qui consiste à adapter de manière .continue la répartition du débit d'air en fonction du régime au moyen de volets mobiles aptes à diaphragmer plus ou moins les entrées d'air de la chambre, ce qui permet une optimisation continue du fonctionnement de la chambre, donc une réduction importante du volume de combustion et ainsi de l'encombrement de la chambre. Une première approche de cette solution est montrée dans les brevets français 2 491 139 et 2 491 140 qui divulguent des diaphragmes adaptés à une vrille de turbulence externe radiale ou axiale d'un dispositif d'injection par ailleurs totalement traditionnel. Ces dispositifs ont pour inconvénients un mauvais guidage de l'air à l'entrée des vrilles ainsi que la génération de sillages importants à l'intérieur de la chambre de combustion.To avoid the problems encountered with the initial combustion chambers and the two-module chambers which have just been mentioned, another route has been approached which consists in adapting .continuously the distribution of the air flow according to the speed by means of movable shutters capable of more or less diaphragming the air intakes of the chamber, which allows continuous optimization of the operation of the chamber, therefore a significant reduction in the combustion volume and thus in the size of the chamber. A first approach to this solution is shown in French patents 2,491,139 and 2,491,140 which disclose diaphragms adapted to a spin of external radial or axial turbulence of an otherwise completely traditional injection device. These devices have the disadvantages of poor air guidance at the entry of the tendrils and the generation of large wakes inside the combustion chamber.

D'autre part, ont été développés des injecteurs aérodynamiques à bol tels que ceux décrits dans les brevets antérieurs de la demanderesse : FR 2 357 738 et FR 2 391 359. Ces injecteurs sont montés sur le fond de chambre avec interposition d'une pièce intermédiaire appelée bol comportant une partie tronconique évasée vers l'aval et percée d'une multiplicité de trous de faible diamètre par lesquels de l'air à forte pression pénètre dans le cône de carburant pulvérisé. Par les turbulences qu'il crée et le mélange intime qu'il réalise, ce bol complète le rôle de l'injecteur, agit sur la composition de mélange et permet la création d'une mini zone primaire au ralenti.On the other hand, aerodynamic bowl injectors such as those described in the applicant's prior patents have been developed: FR 2 357 738 and FR 2 391 359. These injectors are mounted on the chamber bottom with the interposition of a part intermediate called bowl comprising a frustoconical part flared downstream and pierced with a multiplicity of small diameter holes through which air at high pressure enters the sprayed fuel cone. By the turbulence it creates and the intimate mixing it produces, this bowl completes the role of the injector, acts on the mixing composition and allows the creation of a mini primary zone in slow motion.

Pour améliorer ces injecteurs aérodynamiques à bol intermédiaire, on a doté leur vrille de turbulence externe ainsi que l'admission d'air des trous de bolide diaphragme permettant d'en moduler le débit de sortie pour adapter la richesse du mélange air-carburant en sortie de bol à toutes les conditions de fonctionnement de la chambre de combustion et ainsi adapter cette richesse à tous les régimes intermédiaires entre le ralenti et le plein gaz. Une telle disposition est prévue par la demande de brevet français n" 84.16536 au nom de la demanderesse déposée le 30 octobre 1984.To improve these aerodynamic injectors with intermediate bowl, we have equipped their external swirl swirl as well as the air intake of the diaphragm bolide holes allowing to modulate the output flow to adapt the richness of the air-fuel mixture at the output. from bowl to all the operating conditions of the combustion chamber and thus adapt this richness to all the intermediate speeds between idling and full throttle. Such a provision is provided for by French patent application No. 84.16536 in the name of the applicant filed on October 30, 1984.

La présente invention a pour but d'améliorer ces types d'injecteurs aérodynamiques à bol intermédiaires en les conformant de telle sorte qu'ils contribuent, d'une part, à améliorer le refroidissement des parois de la chambre de combustion et, d'autre part, à améliorer le rendement au ralenti, notamment lorsqu'ils sont montés dans des chambres de combustion annulaires sur le fond desquelles ils sont régulièrement répartis, ceci en utilisant au mieux les zones de recirculation localisées existant entre les injecteurs adjacents.The present invention aims to improve these types of aerodynamic injectors with intermediate bowl by shaping them so that they contribute, on the one hand, to improving the cooling of the walls of the combustion chamber and, on the other hand on the other hand, to improve the efficiency at idle, in particular when they are mounted in annular combustion chambers on the bottom of which they are regularly distributed, this making best use of the localized recirculation zones existing between the adjacent injectors.

Pour ce faire, l'invention a pour objet un dispositif d'injection d'air et de carburant dans une chambre de combustion notamment de turbomachine comprenant au moins un injecteur de carburant, une vrille de turbulence externe pour le passage d'air de pulvérisation du carburant, équipée d'un diaphragme de modulation de débit d'entrée d'air, un corps en forme de bol comportant un voile aval évasé dans le sens de l'écoulement et pourvu d'une rangée de trous de bol pour l'injection d'air dans le cône de carburant pulvérisé et une chambre de refroidissement par impact formée par le voile aval, une bague intermédiaire et une jupe externe possédant des orifices d'entrée d'air.To do this, the subject of the invention is a device for injecting air and fuel into a combustion chamber, in particular of a turbomachine, comprising at least one fuel injector, an external swirl spin for the passage of atomizing air. fuel, equipped with a diaphragm for modulating the air inlet flow rate, a bowl-shaped body comprising a downstream web flared in the direction of flow and provided with a row of bowl holes for the injection of air into the sprayed fuel cone and an impact cooling chamber formed by the downstream web, an intermediate ring and an outer skirt having air inlet orifices.

Selon l'invention, la chambre est divisée en quatre secteurs égaux, diamétralement opposés deux à deux et séparés par des cloisons radiales, deux premiers secteurs comportant des trous de bol de faible diamètre et deux seconds secteurs comportant des trous de bol de gros diamètre.According to the invention, the chamber is divided into four equal sectors, diametrically opposite two by two and separated by radial partitions, two first sectors having small diameter bowl holes and two second sectors having large diameter bowl holes.

Selon une particularité de l'invention, le diamètre des trous des premiers secteurs est calculé pour un fonctionnement optimisé de la chambre de combustion au ralenti et le diamètre des trous des seconds secteurs pour un rendement optimisé au régime plein gaz.According to a feature of the invention, the diameter of the holes of the first sectors is calculated for an optimized operation of the combustion chamber at idle and the diameter of the holes of the second sectors for an optimized yield at full gas speed.

Selon une autre particularité de l'invention, le dispositif d'injection comporte un diaphragme de modulation du débit d'air des trous de bol de gros diamètre des seconds secteurs.According to another feature of the invention, the injection device comprises a diaphragm for modulating the air flow rate of the large diameter bowl holes of the second sectors.

Dans le cas où l'invention est appliquée à une chambre de combustion annulaire comportant plusieurs injecteurs adjacents les uns aux autres, répartis en couronne sur le fond de la chambre de combustion, on oriente les bols de telle sorte que les premiers secteurs de chaque bol soient disposés côte à côte tandis que les seconds secteurs des bols possédant des trous de gros diamètre sont orientés vers les parois interne et externe de la chambre de combustion pour en améliorer le refroidissement au régime plein gaz.In the case where the invention is applied to an annular combustion chamber comprising several injectors adjacent to each other, distributed in a crown on the bottom of the combustion chamber, the bowls are oriented so that the first sectors of each bowl are arranged side by side while the second sectors of the bowls having large diameter holes are oriented towards the internal and external walls of the combustion chamber to improve cooling at full gas speed.

D'autres caractéristiques de l'invention seront explicitées en regard des planches de dessins représentant de façon non limitative des modes de réalisation de l'invention.Other characteristics of the invention will be explained with reference to the drawing boards showing, without limitation, embodiments of the invention.

  • La figure 1 montre, en coupe longitudinale, une chambre de combustion équipée d'un dispositif d'injection selon l'invention.Figure 1 shows, in longitudinal section, a combustion chamber equipped with an injection device according to the invention.
  • La figure 2 montre, en demi-coupe longitudinale, un mode de réalisation de l'invention, sans le corps de l'injecteur de carburant proprement dit.Figure 2 shows, in longitudinal half-section, an embodiment of the invention, without the body of the fuel injector itself.
  • La figure 3 montre une coupe du bol de l'invention selon une coupe III-III de la figure 2.FIG. 3 shows a section of the bowl of the invention according to a section III-III of FIG. 2.
  • La figure 4 montre une coupe IV-IV de la figure 2.Figure 4 shows a section IV-IV of Figure 2.
  • La figure 5 schématise l'orientation des dispositifs selon l'invention appliqués à une chambre de combustion annulaire.FIG. 5 shows diagrammatically the orientation of the devices according to the invention applied to an annular combustion chamber.

Sur la figure 1 est représentée en demi-coupe longitudinale une chambre de combustion annulaire 1 pour turbomachine comprenant le système d'injection selon l'invention. La chambre 1 est comprise entre un carter externe 2 et une virole interne 3 qui délimitent la veine de gaz comprimés. Une fraction F1 de l'air amont provenant du compresseur (non représenté) est guidée à travers le système d'injection 4 pour la formation du mélange carburé. Celui-ci passe dans la zone primaire 5 où ont lieu les réactions de combustion, puis les gaz produits sont dilués dans la zone de dilution 6 et refroidis dans la zone secondaire aval 7 et sont distribués vers la turbine, non représentée, qu'ils entraînent.In Figure 1 is shown in longitudinal half-section an annular combustion chamber 1 for a turbomachine comprising the injection system according to the invention. Chamber 1 is between an external casing 2 and an internal ferrule 3 which delimit the stream of compressed gases. A fraction F1 of the upstream air coming from the compressor (not shown) is guided through the injection system 4 for the formation of the fuel mixture. This passes into the primary zone 5 where the combustion reactions take place, then the gases produced are diluted in the dilution zone 6 and cooled in the downstream secondary zone 7 and are distributed to the turbine, not shown, which they train.

L'injecteur dont seul le corps 8 est figuré en pointillé à la figure 1 est relié au fond 9 de la chambre de combustion par un bol intermédiaire 10 dont la structure particulière fait l'objet de l'invention. Le système d'injection comporte de façon connue une vrille de turbulence interne (non représentée) pouvant être soit de type radial, soit de type axial centripète destinée à projeter le carburant issu de l'injecteur en formant un jet tronconique évasé vers l'aval.The injector of which only the body 8 is shown in dotted lines in FIG. 1 is connected to the bottom 9 of the combustion chamber by an intermediate bowl 10 whose particular structure is the subject of the invention. The injection system comprises, in known manner, an internal turbulence spin (not shown) which can be either of the radial type, or of the centripetal axial type intended to project the fuel from the injector forming a tapered jet flared downstream.

L'injecteur 8 muni de sa vrille de turbulence interne est entouré par un chapeau 11 formant la paroi amont du bol intermédiaire 10. Le chapeau 11 comporte en aval une partie lla tronconique prolongée vers l'amont par une portée cylindrique llb et enfin par une paroi radiale llc délimitant avec la paroi radiale 12c d'une bague intermédiaire 12 un canal radial doté d'aubages 13 inclinés formant une vrille de turbulence externe pour le système d'injection. La bague intermédiaire 12 comporte une partie cylindrique 12b et se prolonge en se resserrant vers l'aval par une portée tronconique 12a, le chapeau 11 et la bague 12 formant un canal annulaire axialo-centripète pour l'air provenant de la vrille de turbulence externe 13.The injector 8 provided with its internal swirl spin is surrounded by a cap 11 forming the upstream wall of the intermediate bowl 10. The cap 11 comprises downstream a frustoconical part lla extended upstream by a cylindrical bearing llb and finally by a radial wall llc delimiting with the radial wall 12c of an intermediate ring 12 a radial channel provided with inclined blades 13 forming an external swirling swirl for the injection system. The intermediate ring 12 has a cylindrical part 12b and is extended by tightening downstream by a frustoconical bearing 12a, the cap 11 and the ring 12 forming an axial-centripetal annular channel for the air coming from the swirl of external turbulence 13.

De façon connue, la vrille de turbulence externe 13 peut être diaphragmée par une bague cylindrique 22 mobile en rotation et comportant des orifices d'entrée d'air en nombre égal à celui des passages de la vrille 13. La mise en rotation du diaphragme 22 s'effectue par l'intermédiaire d'un levier de manoeuvre 23 (schématisé à la figure 1) relié à un système de commande externe au carter 2 et non représenté. Par ce moyen, on peut obturer la vrille externe 13 au régime de ralenti et l'ouvrir continuellement jusqu'à pleine ouverture au plein gaz afin d'optimiser les conditions de mélange air-carburant (pourcentages air-carburant, répartition volumique, pulvérisation) à tous les régimes de fonctionnement, ce qui est permis parce que la vrille externe possède une composante axiale importante aux conditions pleins gaz et faible au ralenti, ceci étant dû au fait que la vrille est diaphragmée en amont et que, la section au col du bol étant constante, la vitesse débitante, axiale à ce niveau, est directement proportionnelle au débit d'air et est donc croissante du ralenti au plein gaz.In known manner, the external turbulence spin 13 can be diaphragmed by a cylindrical ring 22 movable in rotation and having air intake orifices in number equal to that of the passages of the spin 13. The rotation of the diaphragm 22 takes place by means of an operating lever 23 (shown diagrammatically in FIG. 1) connected to a control system external to the casing 2 and not shown. By this means, the external spin 13 can be closed at idle speed and opened continuously until full opening at full gas in order to optimize the air-fuel mixture conditions (air-fuel percentages, volume distribution, spraying) at all operating speeds, which is permitted because the external spin has an important axial component at full throttle conditions and low at idle, this being due to the fact that the spin is diaphragmed upstream and that, the section at the neck of the bowl being constant, the speed of delivery, axial at this level, is directly proportional to the air flow and is therefore increasing from idle to full throttle.

La bague 12 est prolongée vers l'aval par un voile aval tronconique 14 évasé vers l'aval et formant le bol proprement dit. Celui-ci est relié à la chambre de combustion par une jupe externe 15 cylindrique rapportée à son bord aval et comportant un filetage permettant à un écrou non représenté de venir enserrer de façon connue une coupelle découpée dans le fond 9 de la chambre de combustion.The ring 12 is extended downstream by a frustoconical downstream web 14 flared downstream and forming the bowl proper. The latter is connected to the combustion chamber by an external cylindrical skirt 15 attached to its downstream edge and comprising a thread allowing a nut, not shown, to come to grip in a known manner a cup cut out in the bottom 9 of the combustion chamber.

La bague 12, le voile aval 14 et la jupe externe 15 forment une chambre annulaire de refroidissement 16 par impact du voile 14. Pour obtenir ce refroidissement, la jupe 15 comporte des ouvertures radiales 17 régulièrement réparties sur son pourtour, permettant l'alimentation de la chambre 16 en air amont.The ring 12, the downstream web 14 and the outer skirt 15 form an annular cooling chamber 16 by impact of the web 14. To obtain this cooling, the skirt 15 has radial openings 17 regularly distributed around its periphery, allowing the supply of chamber 16 in upstream air.

Selon l'invention, la chambre 16 est divisée en quatre secteurs 16a, 16b égaux, diamétralement opposés, séparés par des cloisons radiales 21. Le voile aval 14 comporte régulièrement répartis sur sa périphérie des trous de bol permettant à l'air amont introduit dans les secteurs 16a, 16b de la chambre 16 de s'échapper de ladite chambre en remplissant une fonction de pulvérisation de la nappe conique 18 de carburant formée entre les jets d'air issus des deux vrilles de turbulence externe et interne. Selon l'invention, les deux premiers secteurs 16a de la chambre 16 comportent sur les parties du voile aval 14 qui leur sont associées des trous de bol de petit diamètre 19 tandis que les seconds secteurs 16b comportent sur les parties correspondantes du voile aval des trous de bol 20 de gros diamètre.According to the invention, the chamber 16 is divided into four equal, diametrically opposite sectors 16a, 16b, separated by radial partitions 21. The downstream web 14 regularly has bowl holes distributed over its periphery allowing the upstream air introduced into the sectors 16a, 16b of the chamber 16 escape from said chamber by fulfilling a spraying function of the conical sheet 18 of fuel formed between the air jets from the two tendrils of external and internal turbulence. According to the invention, the first two sectors 16a of the chamber 16 comprise on the parts of the downstream web 14 which are associated with them small diameter bowl holes 19 while the second sectors 16b comprise on the corresponding parts of the downstream web of bowl 20 of large diameter.

Les premiers secteurs 16a et les seconds secteurs 16b sont alimentés séparément en air amont par les ouvertures radiales 17, les cloisons 21 les isolant totalement les uns des autres. Selon l'invention, les ouvertures 17, alimentant les seconds secteurs à trous de bol de gros diamètre, peuvent être diaphragmées par deux prolongements cylindriques ajourés 22a de la bague 22 formant le diaphragme de la vrille de turbulence externe 13, afin de moduler le débit de sortie des trous de bol 20.The first sectors 16a and the second sectors 16b are supplied separately with upstream air through the radial openings 17, the partitions 21 completely isolating them from each other. According to the invention, the openings 17, supplying the second sectors with large-diameter bowl holes, can be diaphragmed by two perforated cylindrical extensions 22a of the ring 22 forming the diaphragm of the external turbulence spin 13, in order to modulate the flow bowl hole outlet 20.

Les diaphragmes 22 et 22a ainsi solidaires sont manoeuvrés simultanément vers l'ouverture ou la fermeture et l'on voit immédiatement que, au ralenti, les trous de bol 20 à gros diamètre des seconds secteurs ne sont pas alimentés et qu'ils peuvent être alimentés jusqu'à plein débit par l'ouverture progressive du diaphragme 22a jusqu'à sa pleine ouverture au plein gaz, alors que les trous de bol 19 des deux premiers secteurs restent alimentés en air amont pendant toute la durée de fonctionnement de la turbomachine.The diaphragms 22 and 22a thus secured are operated simultaneously towards opening or closing and it is immediately seen that, at idle, the large-diameter bowl holes 20 of the second sectors are not supplied and that they can be supplied up to full flow by the gradual opening of the diaphragm 22a until it is fully open to full gas, while the bowl holes 19 of the first two sectors remain supplied with upstream air throughout the operating life of the turbomachine.

La figure 5 montre la disposition et l'orientation des bols selon l'invention appliqués à une chambre de combustion annulaire. Sur cette figure, sans représenter la totalité de chaque bol, on a des bols adjacents 10 vus selon une coupe similaire à celle de la figure 4.Figure 5 shows the arrangement and orientation of the bowls according to the invention applied to an annular combustion chamber. In this figure, without showing the totality of each bowl, there are adjacent bowls 10 seen in a section similar to that of FIG. 4.

La chambre de combustion 1 comporte un certain nombre d'injecteurs reliés au fond de chambre par autant de bols intermédiaires régulièrement répartis en couronne. Selon l'invention, les bols adjacents sont orientés de façon à ce que leurs premiers secteurs alimentés en permanence en air amont soient face à face tandis que les seconds secteurs diaphragmés au ralenti et débitant au plein gaz soient orientés face aux parois interne 3 et externe 2 de la chambre de combustion afin d'en assurer le refroidissement maximum au plein gaz.The combustion chamber 1 comprises a number of injectors connected to the chamber bottom by as many intermediate bowls regularly distributed in a ring. According to the invention, the adjacent bowls are oriented so that their first sectors permanently supplied with upstream air are face to face while the second sectors diaphragmed at idle and delivering at full throttle are oriented facing the internal 3 and external walls. 2 of the combustion chamber to ensure maximum cooling at full gas.

Cette disposition est choisie, outre les besoins de refroidissement des parois au régime plein gaz, parce que l'on s'est rendu compte par des essais d'analogie hydraulique puis par des mesures de vélocimétrie laser à froid qu'il existait une zone de recirculation localisée entre les injecteurs adjacents où se localise la flamme juste avant l'extinction et qu'il importait de garder une alimentation constante en air carburé de cette zone au ralenti afin d'améliorer la stabilité de flamme dans cette configuration de fonctionnement.This arrangement is chosen, in addition to the cooling needs of the walls at full gas speed, because we realized by tests of hydraulic analogy then by measurements of cold laser velocimetry that there was a zone of localized recirculation between the adjacent injectors where the flame is localized just before extinction and that it was important to keep a constant supply of carbureted air from this zone at idle in order to improve the flame stability in this operating configuration.

La séparation du bol en secteurs alimentés en air indépendamment, dont les secteurs 16a en regard sont alimentés constamment en air amont, permet d'obtenir ce résultat, d'autant mieux que le diamètre des trous de bol 19 des secteurs 16a est calculé de telle sorte que le rendement au ralenti du dispositif d'injection soit optimal avec les diaphragmes 22, 22a fermés.The separation of the bowl into sectors supplied with air independently, the opposite sectors 16a of which are constantly supplied with upstream air, makes it possible to obtain this result, all the better since the diameter of the bowl holes 19 of the sectors 16a is calculated in such a way so that the idling performance of the injection device is optimal with the diaphragms 22, 22a closed.

Parallèlement, le diamètre des trous de bol 20 des secteurs 16b est calculé afin de rendre optimal, diaphragmes ouverts, le fonctionnement du dispositif d'injection au régime plein gaz. Ainsi, pour un bol expérimental réalisé, le rendement optimal au ralenti et en plein gaz a été obtenu avec dix trous de deux millimètres de diamètre pour chaque premier secteur de cinq trous de quatre millimètres de diamètre pour chaque second secteur.At the same time, the diameter of the bowl holes 20 of the sectors 16b is calculated in order to make the operation of the injection device at full gas speed optimal, with the diaphragms open. Thus, for an experimental bowl made, the optimal efficiency at idle and in full throttle was obtained with ten holes of two millimeters in diameter for each first sector of five holes of four millimeters in diameter for each second sector.

Un autre élément de calcul pris en compte dans la détermination du nombre et des dimensions des trous de chaque secteur consiste dans le pourcentage d'air admis dans la chambre de combustion, respectivement par les vrilles de turbulence interne et externe, par le bol et par les autres orifices d'admission d'air de la chambre (orifices primaires 24 et de dilution 25, dispositifs de refroidissement des parois par impact, par convection ou par film pariétal).Another calculation element taken into account in determining the number and dimensions of the holes in each sector consists of the percentage of air admitted in the combustion chamber, respectively by the internal and external swirl tendrils, by the bowl and by the other air intake orifices of the chamber (primary orifices 24 and dilution orifices 25, devices for cooling the walls by impact, by convection or by wall film).

Ainsi, selon l'invention, les dimensions et le nombre des trous de bol et des vrilles sont tels que le débit d'admission d'air dans la chambre par le système d'injection (vrille interne + vrille externe + trous de bol) varie de 5% à 22% du débit d'air total admis dans la chambre de combustion et plus particulièrement que les débits respectifs par rapport au débit d'air total de la chambre varient depuis le ralenti jusqu'au plein gaz :

  • - de 1% à 13% pour la vrille de turbulence externe,
  • - de 0% à 4% pour les trous de bol 20 des seconds secteurs,

tandis que les débits de la vrille interne et des trous de bol 19 des premiers secteurs sont constants pendant tout le fonctionnement de la turbomachine, respectivement de 3% et de 2% du débit total d'air admis dans la chambre de combustion.Thus, according to the invention, the dimensions and the number of bowl holes and tendrils are such that the rate of admission of air into the chamber by the injection system (internal twist + external twist + bowl holes) varies from 5% to 22% of the total air flow admitted into the combustion chamber and more particularly that the respective flows relative to the total air flow of the chamber vary from idle to full gas:
  • - from 1% to 13% for the external swirl spin,
  • - from 0% to 4% for the bowl holes 20 of the second sectors,

while the flow rates of the internal spin and the bowl holes 19 of the first sectors are constant during the entire operation of the turbomachine, respectively of 3% and 2% of the total air flow admitted into the combustion chamber.

Cette disposition, combinée avec l'orientation des bols adjacents les uns par rapport aux autres et la variation d'angle de swirl de la vrille externe obtenue par la disposition amont du diaphragme 22, permet de faire varier entre le ralenti et le plein gaz la répartition volumétrique du mélange air-carburant dans la zone de réaction et de ce fait d'améliorer la stabilité de flamme au ralenti et le rendement de combustion au plein gaz et réalisant une modulation continue de ces paramètres tout au long de la plage de fonctionnement de la chambre de combustion.This arrangement, combined with the orientation of the adjacent bowls with respect to each other and the variation in swirl angle of the external spin obtained by the upstream arrangement of the diaphragm 22, makes it possible to vary between idle and full throttle the volumetric distribution of the air-fuel mixture in the reaction zone and thereby improving the flame stability at idle and the combustion efficiency at full gas and achieving continuous modulation of these parameters throughout the operating range of the combustion chamber.

Ces avantages rendent l'invention particulièrement adaptée aux turboréacteurs d'aviation à faible niveau de pollution.These advantages make the invention particularly suitable for aviation turbojets with low pollution levels.

Claims (6)

1. Dispositif d'injection d'air et de carburant dans une chambre de combustion notamment de turbomachine, comprenant au moins un injecteur de carburant, une vrille de turbulence externe pour le passage d'air de pulvérisation du carburant, équipée d'un diaphragme de modulation de débit d'entrée d'air, un corps en forme de bol comportant un voile aval évasé dans le sens de l'écoulement et pourvu d'une rangée de trous de bol pour l'injection d'air dans le cône de carburant pulvérisé et une chambre de refroidissement par impact (16) formée par le voile aval, une bague intermédiaire et une jupe externe possédant des orifices d'entrée d'air, caractérisé en ce que la chambre est divisée en quatre secteurs égaux (16a, 16b), diamétralement opposés deux à deux et séparés par des cloisons radiales (21), deux premiers secteurs (16a) comportant des trous de bol de faible diamètre (19) et deux seconds secteurs (16b) comportant des trous de bol de gros diamètre (20).1. Device for injecting air and fuel into a combustion chamber, in particular of a turbomachine, comprising at least one fuel injector, an external swirl swirl for the passage of fuel spray air, equipped with a diaphragm of air inlet flow modulation, a bowl-shaped body comprising a downstream web flared in the direction of flow and provided with a row of bowl holes for injecting air into the cone of pulverized fuel and an impact cooling chamber (16) formed by the downstream web, an intermediate ring and an outer skirt having air inlet orifices, characterized in that the chamber is divided into four equal sectors (16a, 16b), diametrically opposite two by two and separated by radial partitions (21), two first sectors (16a) having small diameter bowl holes (19) and two second sectors (16b) having large diameter bowl holes (20). 2. Dispositif d'injection selon la revendication 1, caractérisé en ce que le diamètre des trous (19) des premiers secteurs (16a) est calculé pour un fonctionnement optimisé de la chambre de combustion au ralenti et le diamètre des trous (20) des seconds secteurs (16b) pour un rendement optimisé au régime plein gaz.2. An injection device according to claim 1, characterized in that the diameter of the holes (19) of the first sectors (16a) is calculated for an optimized operation of the combustion chamber at idle and the diameter of the holes (20) of the second sectors (16b) for an optimized yield at full gas speed. 3. Dispositif d'injection selon la revendication 2, caractérisé en ce qu'il comporte un diaphragme (22a) de modulation du débit d'air des trous de bol de gros diamètre (20) de chacun des seconds secteurs (16b).3. Injection device according to claim 2, characterized in that it comprises a diaphragm (22a) for modulating the air flow rate of the large diameter bowl holes (20) of each of the second sectors (16b). 4. Dispositif d'injection selon la revendication 3, caractérisé en ce que le diaphragme (22) de la vrille de turbulence externe et celui (22a) des orifices de bol des seconda secteurs (16b) sont solidaires et manoeuvrables simultanément vers l'ouverture au régime plein gaz ou la fermeture au ralenti.4. Injection device according to claim 3, characterized in that the diaphragm (22) of the tendril external turbulence and that (22a) of the bowl orifices of the second sectors (16b) are integral and maneuverable simultaneously towards opening at full throttle speed or closing at idle. 5. Dispositif d'injection selon l'une quelconque des revendications 1 à 3, pour chambre de combustion annulaire comportant plusieurs injecteurs adjacents les uns aux autres, répartis en couronne sur le fond de la chambre de combustion, caractérisé en ce que les premiers secteurs (16a) des bols adjacents sont disposés face à face, les seconds secteurs (16b) des bols possédant les trous de gros diamètre (20) étant orientés vers les parois (2, 3) de la chambre de combustion pour assurer son refroidissement au régime plein gaz.5. An injection device according to any one of claims 1 to 3, for annular combustion chamber comprising several injectors adjacent to each other, distributed in a crown on the bottom of the combustion chamber, characterized in that the first sectors (16a) adjacent bowls are arranged face to face, the second sectors (16b) of the bowls having the large diameter holes (20) being oriented towards the walls (2, 3) of the combustion chamber to cool it at speed full throttle. 6. Dispositif d'injection selon la revendication 5, caractérisé en ce que les trous de bol (20) des seconds secteurs (16b) ont un débit global variant entre 0% au ralenti et 4% au plein gaz par rapport au débit total d'entrée d'air dans la chambre de combustion, le débit des trous de bol (19) des premiers secteurs (16a) étant de 2% constant et le débit de la vrille externe (13) variant entre 1% au ralenti et 13% aux pleins gaz.6. Injection device according to claim 5, characterized in that the bowl holes (20) of the second sectors (16b) have an overall flow varying between 0% at idle and 4% at full throttle relative to the total flow d air inlet into the combustion chamber, the flow rate of the bowl holes (19) of the first sectors (16a) being 2% constant and the flow rate of the external spin (13) varying between 1% at idle and 13% at full throttle.
EP86402290A 1985-10-18 1986-10-15 Sectoral fuel injection head Expired EP0224397B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8515925A FR2588919B1 (en) 1985-10-18 1985-10-18 SECTORIZED BOWL INJECTION DEVICE
FR8515925 1985-10-18

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EP0224397A1 true EP0224397A1 (en) 1987-06-03
EP0224397B1 EP0224397B1 (en) 1988-12-14

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US (1) US4696157A (en)
EP (1) EP0224397B1 (en)
JP (1) JPH0637977B2 (en)
DE (1) DE3661440D1 (en)
FR (1) FR2588919B1 (en)

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Also Published As

Publication number Publication date
US4696157A (en) 1987-09-29
JPH0637977B2 (en) 1994-05-18
DE3661440D1 (en) 1989-01-19
FR2588919A1 (en) 1987-04-24
EP0224397B1 (en) 1988-12-14
JPS62106223A (en) 1987-05-16
FR2588919B1 (en) 1987-12-04

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