EP2856036B1 - Turbomachine combustion chamber shell ring - Google Patents

Turbomachine combustion chamber shell ring Download PDF

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Publication number
EP2856036B1
EP2856036B1 EP13728462.6A EP13728462A EP2856036B1 EP 2856036 B1 EP2856036 B1 EP 2856036B1 EP 13728462 A EP13728462 A EP 13728462A EP 2856036 B1 EP2856036 B1 EP 2856036B1
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EP
European Patent Office
Prior art keywords
shell ring
holes
inserts
dilution
shell
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EP13728462.6A
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German (de)
French (fr)
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EP2856036A2 (en
Inventor
Denis Jean Maurice Sandelis
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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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
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03042—Film cooled combustion chamber walls or domes
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies
    • 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
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing

Definitions

  • the present invention relates to a turbomachine combustion chamber shell.
  • the ferrule in question here delimits a flame tube where the combustion takes place, and which is therefore subjected to a significant heating on its inner face, while its outer face is traversed by a flow of fresh gas, originating from the compressors of the turbomachine and which mixes with the combustion gases downstream of the shell before passing into the turbines.
  • Such a ferrule is traversed by several kinds of drilling, including relatively large diameter dilution holes intended to let part of the external flow into the flame tube to improve the composition of the combustion mixture, and holes finer ventilation, more numerous and distributed over most of the surface of the ferrule, to also allow an air inlet of the external flow, but whose effect is to protect the ferrule from heating, by forming a grazing flow downstream on the inner face of the shell and therefore a boundary layer cooler than the combustion gases.
  • This boundary layer is reformed badly immediately downstream of the large diameter holes, which break the grazing flow, and that the corresponding parts of the ferrule, subjected almost entirely to heating, are subject to deformations and stresses resulting from dilations. differentials, which can give rise to creeks.
  • the document FR 2 892 180 A1 which relates to a combustion chamber shell comprising primary bores, dilution bores, ventilation bores, and where the lack of ventilation downstream of the large bores is remedied by a fourth category of bores regularly located on the circumferences.
  • the ferrule passing immediately downstream of the large holes; as well as the document FR 2 404 110 A1 , which describes a ferrule composed of two separate layers and joined at the same time by ribs.
  • the dilution bores can be provided with a cylindrical ring which passes through them and comprises an upper rim. The ring makes it possible to obtain favorable characteristics of the ventilation flow; the upper rim is therefore hollowed out, or completely interrupted; but this document does not suggest interrupting ventilation holes under the wafer to create a room where the air breath stays for a moment.
  • a turbomachine combustion chamber shell comprising dilution bores and ventilation bores surrounding the dilution holes and finer and more numerous than them, characterized in that it comprises platelets extending over and around the dilution bores on an outer face of the ferrule, the ferrule is devoid of ventilation holes at portions above the platelets, the plates each comprising a flange for attachment to the ferrule and an orifice extending over one of the respective dilution bores, and the wafers are pierced by bores directed towards said portions of the ferrule.
  • the essential effect obtained is that the pressure that prevails around the ferrule causes air to penetrate through the holes of the wafer, in jets that strike the outer face of the ferrule and produce at this point the desired cooling, with a greater intensity than ventilation holes arranged through the shell, that the air passes very quickly. Instead, the air sucked under the wafer flows over the outer face of the ferrule after reaching it, moving towards the dilution piercing, and this flow time causes greater heat removal. .
  • the rather low speed with which it is then animated can allow it to take up quite easily a tangent direction downstream, which will help to restore the boundary layer on the inner face of ferrule and will further improve ventilation.
  • the platelets may be parallel to or inclined to the shell in an axial direction of the shell.
  • the piercings of the platelets are advantageously perpendicular to the ferrule, but they can also be placed obliquely; all these arrangements are to be decided in each design.
  • the wafers it is advantageous for the wafers to extend more in the downstream direction of the shell than in other directions from the centers of the dilution bores, since the portions of the ferrule which are subjected to intense heating are precisely downstream of the ferrule. these holes.
  • the platelets may, however, undergo shrinkage in this downstream direction of the ferrule, since the boundary layer is reconstituted in the same form, bypassing the dilution bores.
  • the plates each comprise an inner rim surrounding the respective orifice and extending towards the respective dilution passage, which allows to channel both the air sucked directly by the dilution holes passing. through the orifice of the wafer, and the air sucked by the holes of the wafer and blowing on the shell, which then passes around this inner edge.
  • Another aspect of the invention is a turbomachine combustion chamber comprising such a ferrule.
  • a turbomachine combustion chamber where the invention may be present is schematically represented in FIG. Figure 1 . It will be recalled that these combustion chambers are annular around an axis of the turbomachine, so that the figure 1 is only half a cut along the axis.
  • a fairing 1 comprises an outer shell 2, an inner shell 3, both generally conical and concentric with each other, and an annular chamber bottom 4 joining the ferrules 2 and 3.
  • the internal volume of the combustion chamber, forming a tube with flame 16 is delimited by the ferrules 2 and 3 and the chamber bottom 4 and opens on the opposite side to the chamber bottom 4 by an opening 5.
  • the combustion chamber is surrounded by an outer casing 6 and an inner casing 7 which delimit a flow vein 10 that the fairing 1 separates in two outer vein portions 8 and 9 which circumvent and run along the fairing 1.
  • the air flow stream 10 comes from a nozzle 11 located opposite an opening 12 formed between rear fairings 13 and 14 of the ferrules 2 and 3 (in this description, "back” and “front” are considered with reference to the direction of the airflow).
  • Fuel injectors 15 extend through the outer casing 6, the opening 12 and the chamber bottom 4 into the flame tube 16. Candles 17 also pass through the outer casing 6 at the front of the fuel injectors 15 and also through the outer shell 1 to flush in the flame tube 16. The largest part of the air flow thus borrows the veins 8 and 9, even if a portion penetrates under the shrouds 13 and 14 by the opening 12.
  • the ferrules 2 and 3 are traversed by numerous holes, including ventilation holes 38 thin and numerous and diluting holes 39 of larger diameter, less numerous and distributed over a circle or a small number of circles.
  • ventilation holes 38 thin and numerous and diluting holes 39 of larger diameter, less numerous and distributed over a circle or a small number of circles.
  • the common effect of these holes is to let air from the veins 8 and 9 into the flame tube 16 at lower pressure for various purposes.
  • the invention can be implemented on one or the other of the ferrules 2 and 3.
  • Platelets 40 are disposed on the outer face of ferrule 2 or 3 and around dilution holes 39. They each comprise a main portion 41 extending above ferrule 2 or 3, an outer flange 42 surrounding the portion main 41 and attached to the ferrule 2 or 3, an orifice 43 extending in front of the respective dilution bore 39 but smaller radius, an inner rim 44 surrounding the orifice 43 and extending into most of the the depth of the dilution bore 39, and the holes 45 passing through the main portion 41 and opening in front of a portion facing the ferrule 2 or 3, which is devoid of the ventilation holes 38 there.
  • the plate 40 thus delimits a chamber 49 almost closed in front of the ferrule 2 or 3 of the respective dilution bore 39.
  • the wafer 40 is generally triangular in shape, extending further in the downstream direction of the flow while becoming narrower and narrower, so as to correspond as much as possible to the zone of ferrule 2 or 3 where the cracks can appear.
  • the dilution piercing 39 is provided with fixing sectors 46 projecting towards the center of said bore, which come to touch and grip the inner rim 44.
  • This inner rim 44 and the attachment sectors 46 delimit airflow sectors having through the holes 45 of the plates 40, including here two lateral sectors 47 symmetrical with respect to an axial direction of the shell 2 or 3 and a downstream sector 48.
  • the centers O1 and O2 of the inner flange 44 and drilling 39 are axially offset, so that the sectors 47 or 48 have an irregular shape and the downstream sector 48 is wider, which promotes the flow of the chamber 49 by the downstream sector 48 and the reconstruction of a ventilation limit layer downstream of dilution drilling 39.
  • the specific flow provided by the wafer 40 is as follows. Air from the flow of the vein 8 or 9 under excess pressure is blown into the chamber 49 through the holes of the plates 45 and refreshes the ferrule 2 or 3 around the respective dilution bore 39, and in particular the downstream portion. of it, by its outer face. This air then flows into the flame tube 16 through the flow sectors 47 and 48 and in particular through the latter. Upon entering the flame tube 16, its flow can quickly become axial downstream of the combustion chamber and reconstitute a boundary layer in the aforementioned zone of the shell 2 or 3 downstream of the dilution bore 38 and further contributes to protect her.
  • the main portions 41 of the plates 40 may or may not be parallel to the portion facing the shell 2 or 3, and the holes 45 perpendicular or otherwise to this portion.
  • the main portions 41 may in particular be inclined in the axial direction of the shell 2 or 3, according to the contour 41 ', to better intercept the flow air by creating a larger obstacle.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)

Description

L'invention présente se rapporte à une virole de chambre de combustion de turbomachine.The present invention relates to a turbomachine combustion chamber shell.

La virole dont il est ici question délimite un tube à flamme où la combustion a lieu, et qui est donc soumise à un échauffement important sur sa face intérieure, alors que sa face extérieure est parcourue par un écoulement de gaz frais, originaire des compresseurs de la turbomachine et qui se mêle aux gaz de combustion en aval de la virole avant de passer dans les turbines.The ferrule in question here delimits a flame tube where the combustion takes place, and which is therefore subjected to a significant heating on its inner face, while its outer face is traversed by a flow of fresh gas, originating from the compressors of the turbomachine and which mixes with the combustion gases downstream of the shell before passing into the turbines.

Une telle virole est traversée par plusieurs genres de perçages, dont des perçages de dilution de relativement gros diamètre destinés à laisser entrer une partie de l'écoulement extérieur dans le tube à flamme afin d'améliorer la composition du mélange de combustion, et des perçages de ventilation plus fins, plus nombreux et répartis sur la plus grande partie de la superficie de la virole, pour permettre aussi une entrée d'air de l'écoulement extérieur, mais dont l'effet est de protéger la virole de l'échauffement, en formant un écoulement rasant vers l'aval sur la face intérieure de la virole et donc une couche limite plus fraîche que les gaz de combustion.Such a ferrule is traversed by several kinds of drilling, including relatively large diameter dilution holes intended to let part of the external flow into the flame tube to improve the composition of the combustion mixture, and holes finer ventilation, more numerous and distributed over most of the surface of the ferrule, to also allow an air inlet of the external flow, but whose effect is to protect the ferrule from heating, by forming a grazing flow downstream on the inner face of the shell and therefore a boundary layer cooler than the combustion gases.

Cette couche limite se reforme mal immédiatement en aval des perçages de gros diamètres, qui rompent l'écoulement rasant, et que les parties correspondantes de la virole, soumises intégralement ou presque à l'échauffement, sont sujettes à des déformations et contraintes découlant de dilatations différentielles, qui peuvent faire naître des criques.This boundary layer is reformed badly immediately downstream of the large diameter holes, which break the grazing flow, and that the corresponding parts of the ferrule, subjected almost entirely to heating, are subject to deformations and stresses resulting from dilations. differentials, which can give rise to creeks.

Le document EP-A-1 703 207 décrit une chambre de combustion sur laquelle l'invention peut être implantée. Et les problèmes ci-dessus sont mentionnés dans la demande de brevet français enregistrée sous le numéro 11 53232 qui expose une modification de l'agencement classique de la virole pour reformer la couche limite immédiatement en aval des perçages de gros diamètre et soulager ainsi la virole. Une autre solution est toutefois proposée avec la présente invention.The document EP-A-1,703,207 discloses a combustion chamber on which the invention can be implanted. And the above problems are mentioned in the French patent application registered under the number 11 53232 which exposes a modification of the conventional arrangement of the ferrule for reforming the boundary layer immediately downstream of the large-diameter bores and thus relieving the ferrule . Another solution is however proposed with the present invention.

On citera encore le document FR 2 892 180 A1 , qui est relatif à une virole de chambre de combustion comprenant des perçages primaires, des perçages de dilution, des perçages de ventilation, et où on remédie au manque de ventilation en aval des perçages larges par une quatrième catégorie de perçages situés régulièrement sur les circonférences de la virole, passant immédiatement en aval des perçages larges ; ainsi que le document FR 2 404 110 A1 , qui décrit une virole composée de deux épaisseurs séparées et réunies à la fois par des nervures. Les perçages de dilution peuvent être munis d'une bague cylindrique qui les traverse et comprend un rebord supérieur. La bague permet d'obtenir des caractéristiques favorables de l'écoulement de ventilation ; le rebord supérieur est pour cela évidé, ou complètement interrompu ; mais ce document ne suggère pas d'interrompre des perçages de ventilation sous la plaquette afin de créer une chambre où l'air soufflé séjourne un moment.We will still quote the document FR 2 892 180 A1 , which relates to a combustion chamber shell comprising primary bores, dilution bores, ventilation bores, and where the lack of ventilation downstream of the large bores is remedied by a fourth category of bores regularly located on the circumferences. the ferrule, passing immediately downstream of the large holes; as well as the document FR 2 404 110 A1 , which describes a ferrule composed of two separate layers and joined at the same time by ribs. The dilution bores can be provided with a cylindrical ring which passes through them and comprises an upper rim. The ring makes it possible to obtain favorable characteristics of the ventilation flow; the upper rim is therefore hollowed out, or completely interrupted; but this document does not suggest interrupting ventilation holes under the wafer to create a room where the air breath stays for a moment.

Sous une forme générale, elle concerne une virole de chambre de combustion de turbomachine, comprenant des perçages de dilution et des perçages de ventilation environnant les perçages de dilution et plus fins et plus nombreux qu'eux, caractérisée en ce qu'elle comprend des plaquettes s'étendant au-dessus et autour des perçages de dilution sur une face extérieure de la virole, la virole est dépourvue des perçages de ventilation à des portions situées au-dessus des plaquettes, les plaquettes comprenant chacune un rebord de fixation à la virole et un orifice s'étendant au-dessus d'un des perçages de dilution respectifs, et les plaquettes sont traversées des perçages dirigés vers lesdites portions de la virole.In a general form, it relates to a turbomachine combustion chamber shell, comprising dilution bores and ventilation bores surrounding the dilution holes and finer and more numerous than them, characterized in that it comprises platelets extending over and around the dilution bores on an outer face of the ferrule, the ferrule is devoid of ventilation holes at portions above the platelets, the plates each comprising a flange for attachment to the ferrule and an orifice extending over one of the respective dilution bores, and the wafers are pierced by bores directed towards said portions of the ferrule.

L'effet essentiel obtenu est que la surpression qui règne autour de la virole fait pénétrer de l'air à travers les perçages de la plaquette, en jets qui viennent frapper la face extérieure de la virole et produire à cet endroit le rafraîchissement souhaité, avec une intensité plus grande que des perçages de ventilation disposés à travers la virole, que l'air traverse très rapidement. Au lieu de cela, l'air aspiré sous la plaquette s'écoule sur la face extérieure de la virole après l'avoir atteinte, en se dirigeant vers le perçage de dilution, et cette durée d'écoulement occasionne un enlèvement de chaleur plus important. Quand l'air est entré dans le perçage de dilution, la vitesse assez faible dont il est alors animé peut permettre qu'il reprenne assez facilement une direction tangente vers l'aval, ce qui contribuera à rétablir la couche limite sur la face intérieure de la virole et améliorera encore la ventilation.The essential effect obtained is that the pressure that prevails around the ferrule causes air to penetrate through the holes of the wafer, in jets that strike the outer face of the ferrule and produce at this point the desired cooling, with a greater intensity than ventilation holes arranged through the shell, that the air passes very quickly. Instead, the air sucked under the wafer flows over the outer face of the ferrule after reaching it, moving towards the dilution piercing, and this flow time causes greater heat removal. . When the air has entered the dilution bore, the rather low speed with which it is then animated can allow it to take up quite easily a tangent direction downstream, which will help to restore the boundary layer on the inner face of ferrule and will further improve ventilation.

Selon les besoins, les plaquettes peuvent être parallèles à la virole ou inclinées par rapport à elle dans une direction axiale de la virole. Les perçages des plaquettes sont avantageusement perpendiculaires à la virole, mais ils peuvent être aussi placés obliquement ; tous ces aménagements sont à décider dans chaque conception.As required, the platelets may be parallel to or inclined to the shell in an axial direction of the shell. The piercings of the platelets are advantageously perpendicular to the ferrule, but they can also be placed obliquely; all these arrangements are to be decided in each design.

Il est avantageux que les plaquettes s'étendent plus dans la direction aval de la virole que dans d'autres directions à partir des centres des perçages de dilution, puisque les portions de la virole qui sont soumises à un échauffement intense sont précisément en aval de ces perçages. Les plaquettes peuvent toutefois subir un étrécissement dans cette direction aval de la virole, puisque la couche limite se reconstitue suivant la même forme, en contournant les perçages de dilution.It is advantageous for the wafers to extend more in the downstream direction of the shell than in other directions from the centers of the dilution bores, since the portions of the ferrule which are subjected to intense heating are precisely downstream of the ferrule. these holes. The platelets may, however, undergo shrinkage in this downstream direction of the ferrule, since the boundary layer is reconstituted in the same form, bypassing the dilution bores.

Une autre caractéristique favorable est obtenue si les plaquettes comprennent chacune un rebord intérieur entourant l'orifice respectif et s'étendant vers le passage de dilution respectif, ce qui permet de canaliser à la fois l'air aspiré directement par les perçages de dilution en passant par l'orifice de la plaquette, et l'air aspiré par les perçages de la plaquette et soufflant sur la virole, qui passe alors autour de ce rebord intérieur.Another favorable feature is obtained if the plates each comprise an inner rim surrounding the respective orifice and extending towards the respective dilution passage, which allows to channel both the air sucked directly by the dilution holes passing. through the orifice of the wafer, and the air sucked by the holes of the wafer and blowing on the shell, which then passes around this inner edge.

Une bonne cohésion est obtenue si le rebord intérieur est serré entre des secteurs de fixation situés dans le perçage de dilution respectif, des secteurs d'écoulement étant délimités dans ledit perçage de dilution respectif par le rebord intérieur et entre les secteurs de fixation. Afin de favoriser la poursuite de l'écoulement du côté aval du perçage de dilution, il est encore plus avantageux alors que le perçage de dilution et le rebord intérieur aient des centres décalés dans une direction axiale de la virole, de sorte que les secteurs d'écoulement ont une superficie principale en aval du rebord intérieur.Good cohesion is obtained if the inner flange is clamped between attachment sectors in the respective dilution boring, with flow sectors being delimited in said respective dilution boring by the inner flange and between the fastening sectors. In order to promote the continuation of the flow on the downstream side of the dilution bore, it is even more advantageous while the dilution bore and the inner rim have centers offset in an axial direction of the ferrule, so that the flow have a main area downstream of the inner rim.

Un autre aspect de l'invention est une chambre de combustion de turbomachine comprenant une telle virole.Another aspect of the invention is a turbomachine combustion chamber comprising such a ferrule.

L'invention sera maintenant décrite en liaison aux figures suivantes :

  • la figure 1 est une vue générale d'une chambre de combustion de turbomachine et de sa virole ; et
  • les figures 2 et 3 exposent l'invention plus précisément.
The invention will now be described with reference to the following figures:
  • the figure 1 is a general view of a turbomachine combustion chamber and its ferrule; and
  • the Figures 2 and 3 expose the invention more precisely.

Une chambre de combustion de turbomachine où l'invention peut être présente est représentée schématiquement à la Figure 1. On rappellera que ces chambres de combustion sont annulaires autour d'un axe de la turbomachine, de sorte que la figure 1 est seulement une demi-coupe le long de l'axe. Un carénage 1 comprend une virole extérieure 2, une virole intérieure 3, toutes deux globalement coniques et concentriques entre elles, et un fond de chambre 4 annulaire joignant les viroles 2 et 3. Le volume interne de la chambre de combustion, formant un tube à flamme 16, est délimité par les viroles 2 et 3 et le fond de chambre 4 et s'ouvre du côté opposé au fond de chambre 4 par une ouverture 5. La chambre de combustion est entourée par un carter extérieur 6 et un carter intérieur 7 qui délimitent une veine d'écoulement 10 que le carénage 1 sépare en deux portions de veine extérieure 8 et 9 qui contournent et longent le carénage 1. L'air de la veine d'écoulement 10 provient d'une tuyère 11 située en face d'une ouverture 12 ménagée entre des carénages arrière 13 et 14 des viroles 2 et 3 (dans cette description, « arrière » et « avant » sont considérés en référence au sens de l'écoulement d'air). Des injecteurs de carburant 15 s'étendent à travers le carter extérieur 6, l'ouverture 12 et le fond de chambre 4 jusque dans le tube à flamme 16. Des bougies 17 traversent aussi le carter extérieur 6 à l'avant des injecteurs de carburant 15 et traversent aussi la virole extérieure 1 pour affleurer dans le tube à flamme 16. La plus grande partie de l'écoulement d'air emprunte donc les veines 8 et 9, même si une portion pénètre sous les carénages 13 et 14 par l'ouverture 12.A turbomachine combustion chamber where the invention may be present is schematically represented in FIG. Figure 1 . It will be recalled that these combustion chambers are annular around an axis of the turbomachine, so that the figure 1 is only half a cut along the axis. A fairing 1 comprises an outer shell 2, an inner shell 3, both generally conical and concentric with each other, and an annular chamber bottom 4 joining the ferrules 2 and 3. The internal volume of the combustion chamber, forming a tube with flame 16, is delimited by the ferrules 2 and 3 and the chamber bottom 4 and opens on the opposite side to the chamber bottom 4 by an opening 5. The combustion chamber is surrounded by an outer casing 6 and an inner casing 7 which delimit a flow vein 10 that the fairing 1 separates in two outer vein portions 8 and 9 which circumvent and run along the fairing 1. The air flow stream 10 comes from a nozzle 11 located opposite an opening 12 formed between rear fairings 13 and 14 of the ferrules 2 and 3 (in this description, "back" and "front" are considered with reference to the direction of the airflow). Fuel injectors 15 extend through the outer casing 6, the opening 12 and the chamber bottom 4 into the flame tube 16. Candles 17 also pass through the outer casing 6 at the front of the fuel injectors 15 and also through the outer shell 1 to flush in the flame tube 16. The largest part of the air flow thus borrows the veins 8 and 9, even if a portion penetrates under the shrouds 13 and 14 by the opening 12.

Les viroles 2 et 3 sont traversées par de nombreux perçages, dont des perçages de ventilation 38 fins et nombreux et des perçages de dilution 39 de plus gros diamètre, moins nombreux et répartis sur un cercle ou un petit nombre de cercles. L'effet commun de ces perçages est de laisser entrer de l'air des veines 8 et 9 dans le tube à flamme 16 à pression plus faible pour des buts variés.The ferrules 2 and 3 are traversed by numerous holes, including ventilation holes 38 thin and numerous and diluting holes 39 of larger diameter, less numerous and distributed over a circle or a small number of circles. The common effect of these holes is to let air from the veins 8 and 9 into the flame tube 16 at lower pressure for various purposes.

L'invention pourra être mise en oeuvre sur l'une ou l'autre des viroles 2 et 3.The invention can be implemented on one or the other of the ferrules 2 and 3.

On passe maintenant au commentaire des figures 2 et 3. Des plaquettes 40 sont disposées sur la face extérieure de la virole 2 ou 3 et autour des perçages de dilution 39. Elles comprennent chacune une partie principale 41 s'étendant au-dessus de la virole 2 ou 3, un rebord extérieur 42 entourant la partie principale 41 et fixé à la virole 2 ou 3, un orifice 43 s'étendant devant le perçage de dilution 39 respectif mais de plus petit rayon, un rebord intérieur 44 entourant l'orifice 43 et s'étendant jusque dans la plus grande partie de la profondeur du perçage de dilution 39, et des perçages 45 traversant la partie principale 41 et débouchant devant une portion en regard de la virole 2 ou 3, qui est dépourvue des perçages de ventilation 38 là. La plaquette 40 délimite donc une chambre 49 presque fermée devant la virole 2 ou 3 du perçage de dilution 39 respectif. On voit à la figure 3 que la plaquette 40 a une forme générale à peu près triangulaire, s'étendant plus dans la direction aval de l'écoulement tout en devenant de plus en plus étroite, de manière à correspondre autant que possible à la zone de la virole 2 ou 3 où les criques peuvent apparaître. Le perçage de dilution 39 est muni de secteurs de fixation 46 saillants vers le centre dudit perçage, qui viennent toucher et enserrer le rebord intérieur 44. Ce rebord intérieur 44 et les secteurs de fixation 46 délimitent des secteurs d'écoulement de l'air ayant traversé les perçages 45 des plaquettes 40, dont, ici, deux secteurs latéraux 47 symétriques par rapport à une direction axiale de la virole 2 ou 3 et un secteur aval 48. On remarquera que les centres O1 et O2 du rebord intérieur 44 et du perçage de dilution 39 sont décalés axialement, de sorte que les secteurs 47 ou 48 ont une forme irrégulière et que le secteur aval 48 est plus large, ce qui favorise l'écoulement de la chambre 49 par ce secteur aval 48 et la reconstruction d'une couche limite de ventilation en aval du perçage de dilution 39.We now move on to the commentary Figures 2 and 3 . Platelets 40 are disposed on the outer face of ferrule 2 or 3 and around dilution holes 39. They each comprise a main portion 41 extending above ferrule 2 or 3, an outer flange 42 surrounding the portion main 41 and attached to the ferrule 2 or 3, an orifice 43 extending in front of the respective dilution bore 39 but smaller radius, an inner rim 44 surrounding the orifice 43 and extending into most of the the depth of the dilution bore 39, and the holes 45 passing through the main portion 41 and opening in front of a portion facing the ferrule 2 or 3, which is devoid of the ventilation holes 38 there. The plate 40 thus delimits a chamber 49 almost closed in front of the ferrule 2 or 3 of the respective dilution bore 39. We see at the figure 3 that the wafer 40 is generally triangular in shape, extending further in the downstream direction of the flow while becoming narrower and narrower, so as to correspond as much as possible to the zone of ferrule 2 or 3 where the cracks can appear. The dilution piercing 39 is provided with fixing sectors 46 projecting towards the center of said bore, which come to touch and grip the inner rim 44. This inner rim 44 and the attachment sectors 46 delimit airflow sectors having through the holes 45 of the plates 40, including here two lateral sectors 47 symmetrical with respect to an axial direction of the shell 2 or 3 and a downstream sector 48. It will be noted that the centers O1 and O2 of the inner flange 44 and drilling 39 are axially offset, so that the sectors 47 or 48 have an irregular shape and the downstream sector 48 is wider, which promotes the flow of the chamber 49 by the downstream sector 48 and the reconstruction of a ventilation limit layer downstream of dilution drilling 39.

L'écoulement spécifique procuré par la plaquette 40 est le suivant. De l'air de l'écoulement de la veine 8 ou 9 en surpression est soufflé dans la chambre 49 à travers les perçages des plaquettes 45 et rafraîchit la virole 2 ou 3 autour du perçage de dilution 39 respectif, et notamment la portion en aval de celui-ci, par sa face extérieure. Cet air s'écoule ensuite dans le tube à flamme 16 par les secteurs 47 et 48 d'écoulement et notamment à travers ce dernier. En arrivant dans le tube à flamme 16, son écoulement peut redevenir rapidement axial vers l'aval de la chambre de combustion et reconstituer une couche limite dans la zone susmentionnée de la virole 2 ou 3 en aval du perçage de dilution 38 et contribue encore à la protéger.The specific flow provided by the wafer 40 is as follows. Air from the flow of the vein 8 or 9 under excess pressure is blown into the chamber 49 through the holes of the plates 45 and refreshes the ferrule 2 or 3 around the respective dilution bore 39, and in particular the downstream portion. of it, by its outer face. This air then flows into the flame tube 16 through the flow sectors 47 and 48 and in particular through the latter. Upon entering the flame tube 16, its flow can quickly become axial downstream of the combustion chamber and reconstitute a boundary layer in the aforementioned zone of the shell 2 or 3 downstream of the dilution bore 38 and further contributes to protect her.

Les parties principales 41 des plaquettes 40 peuvent être ou non parallèles à la portion en regard de la virole 2 ou 3, et les perçages 45 perpendiculaires ou non à cette portion. Les parties principales 41 peuvent notamment être inclinées en se dressant en direction axiale de la virole 2 ou 3, selon le contour 41', pour intercepter mieux de l'air d'écoulement en créant un obstacle plus important.The main portions 41 of the plates 40 may or may not be parallel to the portion facing the shell 2 or 3, and the holes 45 perpendicular or otherwise to this portion. The main portions 41 may in particular be inclined in the axial direction of the shell 2 or 3, according to the contour 41 ', to better intercept the flow air by creating a larger obstacle.

Claims (10)

  1. Turbomachine combustion chamber shell ring, comprising dilution holes (39) and ventilation holes (38) surrounding the dilution holes (39) and finer and more numerous than said holes, characterised in that it comprises inserts (40) extending over and around the dilution holes (39) on an outer face of the shell ring (2, 3), the shell ring is devoid of ventilation holes (38) at portions situated beneath the inserts, the inserts each comprising an edge (42) for attaching to the shell ring and an orifice (43) extending over one of the respective dilution holes, and the inserts are traversed by holes (45) directed towards said portions of the shell ring.
  2. Shell ring according to claim 1, characterised in that main portions (41) of the inserts (40) are parallel with the shell ring.
  3. Shell ring according to claim 1, characterised in that main portions (41') of the inserts are inclined in relation to the shell ring in an axial direction of the shell ring.
  4. Shell ring according to any of claims 1 to 3, characterised in that the holes of the inserts are perpendicular to the shell ring.
  5. Shell ring according to any of claims 1 to 4, characterised in that the inserts extend more in the downstream direction of the shell ring than in other directions from the centres of the dilution holes.
  6. Shell ring according to claim 5, characterised in that the inserts taper in the downstream direction of the shell ring.
  7. Shell ring according to any of claims 1 to 6, characterised in that the inserts each comprise an inner edge (44) surrounding the respective orifice (43) and extending towards the respective dilution passage.
  8. Shell ring according to claim 7, characterised in that the inner edge is enclosed between attachment sectors (46) projecting in the respective dilution hole (39), flow sectors (47) being defined in said respective dilution hole by the inner edge and the attachment sectors.
  9. Shell ring according to claim 8, characterised in that the dilution holes (39) and the inner edges (44) have centres (01, 02) offset in an axial direction of the shell ring, such that the flow sectors have a main surface area downstream from the inner edges.
  10. Turbomachine combustion chamber comprising a shell ring, according to any one of the previous claims.
EP13728462.6A 2012-05-25 2013-05-23 Turbomachine combustion chamber shell ring Active EP2856036B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1254847A FR2991028B1 (en) 2012-05-25 2012-05-25 TURBOMACHINE COMBUSTION CHAMBER VIROLE
PCT/FR2013/051117 WO2013175126A2 (en) 2012-05-25 2013-05-23 Turbomachine combustion chamber shell ring

Publications (2)

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EP2856036A2 EP2856036A2 (en) 2015-04-08
EP2856036B1 true EP2856036B1 (en) 2018-09-12

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EP13728462.6A Active EP2856036B1 (en) 2012-05-25 2013-05-23 Turbomachine combustion chamber shell ring

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US (1) US9377200B2 (en)
EP (1) EP2856036B1 (en)
CN (1) CN104520647B (en)
BR (1) BR112014027018B1 (en)
CA (1) CA2871923C (en)
FR (1) FR2991028B1 (en)
IN (1) IN2014DN08528A (en)
RU (1) RU2626876C2 (en)
WO (1) WO2013175126A2 (en)

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DE102012022259A1 (en) 2012-11-13 2014-05-28 Rolls-Royce Deutschland Ltd & Co Kg Combustor shingle of a gas turbine and process for its production
EP3087266B1 (en) * 2013-12-23 2019-10-09 United Technologies Corporation Multi-streamed dilution hole configuration for a gas turbine engine and relating method of operation
EP3018417B8 (en) * 2014-11-04 2021-03-31 Raytheon Technologies Corporation Low lump mass combustor wall with quench aperture(s)
US10386072B2 (en) * 2015-09-02 2019-08-20 Pratt & Whitney Canada Corp. Internally cooled dilution hole bosses for gas turbine engine combustors
US20180283689A1 (en) * 2017-04-03 2018-10-04 General Electric Company Film starters in combustors of gas turbine engines
US11187412B2 (en) 2018-08-22 2021-11-30 General Electric Company Flow control wall assembly for heat engine

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FR1052475A (en) * 1952-03-15 1954-01-25 Snecma Combustion chambers particularly suitable for gas turbines
GB777782A (en) 1955-06-24 1957-06-26 Ici Ltd Purification of terephthalic acid
US4132066A (en) * 1977-09-23 1979-01-02 United Technologies Corporation Combustor liner for gas turbine engine
US4875339A (en) * 1987-11-27 1989-10-24 General Electric Company Combustion chamber liner insert
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FR2855249B1 (en) * 2003-05-20 2005-07-08 Snecma Moteurs COMBUSTION CHAMBER HAVING A FLEXIBLE CONNECTION BETWEEN A BOTTOM BED AND A BEDROOM
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FR2881813B1 (en) * 2005-02-09 2011-04-08 Snecma Moteurs TURBOMACHINE COMBUSTION CHAMBER FAIRING
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CN104520647A (en) 2015-04-15
RU2626876C2 (en) 2017-08-02
US20150059344A1 (en) 2015-03-05
RU2014152849A (en) 2016-07-20
WO2013175126A2 (en) 2013-11-28
WO2013175126A3 (en) 2014-04-24
CA2871923A1 (en) 2013-11-28
US9377200B2 (en) 2016-06-28
FR2991028B1 (en) 2014-07-04
CN104520647B (en) 2016-02-24
EP2856036A2 (en) 2015-04-08
IN2014DN08528A (en) 2015-05-15
CA2871923C (en) 2020-02-11
FR2991028A1 (en) 2013-11-29
BR112014027018B1 (en) 2021-05-25
BR112014027018A2 (en) 2017-06-27

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