EP0950859A1 - Separator for combustion chamber with two burner heads - Google Patents

Separator for combustion chamber with two burner heads Download PDF

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Publication number
EP0950859A1
EP0950859A1 EP99400918A EP99400918A EP0950859A1 EP 0950859 A1 EP0950859 A1 EP 0950859A1 EP 99400918 A EP99400918 A EP 99400918A EP 99400918 A EP99400918 A EP 99400918A EP 0950859 A1 EP0950859 A1 EP 0950859A1
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EP
European Patent Office
Prior art keywords
tiles
sectors
combustion chamber
walls
heads
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Granted
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EP99400918A
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German (de)
French (fr)
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EP0950859B1 (en
Inventor
Alexandre Forestier
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Safran Aircraft Engines SAS
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Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones

Definitions

  • the two heads are delimited in the back of the room, by a ring called separator and thus form two concentric ferrules.
  • This separator is a critical element in the design of the room because it is subjected to longitudinal stresses and tangential during operation of the chamber.
  • the separator ring is consisting of a plurality of sectors arranged circumferentially at some distance from each other.
  • the external walls of the separator are subject to very high temperatures, moreover, intersections circumferential of these separators are favorable for recirculation hot gases between the two heads.
  • the object of the invention is to thermally protect the outer walls of the sectors and prevent recirculation of gases between the two heads.
  • the invention therefore relates to an annular combustion chamber comprising two concentric heads offset radially one by relative to each other and delimited in the back of the room by a ring gas separator, one of the heads, called the pilot head, operating at idle and full throttle, and the other head, called the take-off head, operating at full gas speed, said separator ring comprising a plurality of elementary sectors disposed circumferentially at a certain distance from each other and fixed on sheets from the bottom of chamber, each sector being shaped into an elongated hollow body, cooled by air circulation from upstream from the bottom of chamber, entering said sector and escaping in both heads through the walls of said sector by a plurality of orifices.
  • This combustion chamber is characterized by the fact that said areas are thermally protected by two sets of tiles covering respectively the upper and lower walls of said sectors, the tiles of said series being arranged astride two adjacent areas and away from said walls to allow air cooling circulate in the space thus created, orifices being formed in said tiles to allow the escape of air from cooling in both heads.
  • the drawing shows a combustion chamber 1 of a combustion with two gas turbine heads, delimited by a wall external annular and an internal annular wall, symmetrical of revolution around a common axis, as well as through a chamber bottom 2 connecting the downstream ends of the two annular walls and partially mounted on figure 1.
  • the bottom of chamber 2 is equipped with two groups of injectors fuel distributed over concentric annular rings, different diameters.
  • the injectors of the external group pass through holes 3 of axis Y1 formed in the chamber bottom 2 and cooperate for the fueling of the fuel with air passages passing through the bottom 2 and the walls of enclosure 1.
  • These fuel injectors closest to the wall external are intended to function, being alone in service, with the mode idling speed, and constitute fuel injectors for the pilot head.
  • Internal group injectors also pass through holes 4 of axis Y2 formed in the bottom of chamber 2 and are intended for operate at full throttle or takeoff on an equipped aircraft of said gas turbine.
  • a gas separator assembly 10 of generally annular shape, fixed on the bottom of chamber 2, is interposed between the two groups injectors. This separator assembly 10 constitutes a projection the interior of the combustion chamber 1 relative to the chamber bottom 2.
  • the separator assembly 10 gas consists of a plurality of elementary hollow sectors 11, of elongated shape, which are arranged circumferentially at a certain distance x from each other and which are each fixed on sheets 12, 13 of the chamber bottom 2 by fixing means 14 distinct from those from other sectors.
  • the sheets 12 and 13 of the chamber bottom 2 are put in forms so as to form, on the side of the combustion chamber 1, a annular groove 15 of U-shaped section reversed 90 °, and in the bottom of which is engaged the upstream part 16 of each elementary sector 11.
  • Each elementary sector 11 has, in addition to the part upstream 16, of inverted U section, which engages in the bottom of the groove 15 of the chamber bottom 2, an upper wall 17 and a wall lower 18 which are connected at their downstream ends 19, so as to form a corner in the combustion chamber 1, and the ends of which respective upstream 20 and 21 are connected to the wings of the upstream part 16, by connecting walls 22 and 23 which form recesses in such a way that the upstream parts of the walls upper 17 and lower 18 are separated from the sheets 12 respectively and 13 and delimit therewith annular spaces 24, 25.
  • the upper wall 17 has in the annular space 24 a external rib 26 parallel to the connecting wall 22 and which forms with the connection wall 22 and the sheet 12 a groove 27.
  • the bottom wall 18 has in the annular space 25 an external rib 28 parallel to the connecting wall 23 and which defines with the latter and the sheet 13 a groove 29.
  • the downstream end 19 for connection of the upper wall 17 and of the bottom wall 18 also has an open groove 30 in the opposite direction to the chamber bottom 2.
  • Two side walls 31, 32 close off the ends of each elementary sector 11.
  • the upstream part 16 of each elementary sector 11 and the sheets 12 and 13 of the chamber bottom 2 have corresponding holes 33 for the removal of cooling air upstream from the bottom of chamber 1, this cooling air circulating inside the sector 11 and discharging through a plurality of orifices 34 formed in the walls upper 17 and lower 18 to the combustion chamber 1.
  • the upper walls 17 of the elementary sectors 11 are thermally protected by a first series of tiles 40 arranged each straddling two adjacent tiles 11a, 11b as is visible in Figure 2.
  • the lower walls 18 of the sectors elementary 11 are covered by a second series of tiles 41 each arranged astride two adjacent tiles 11a, 11b.
  • the tiles 40 and 41 each have at their downstream end a hook respectively 42, 43 directed towards the chamber bottom.
  • the hooks 42, 43 of two tiles 40, 41 straddling the same sectors 11a, 11b are intended to accommodate with play, being arranged one on the other in the grooves 30 formed at the downstream ends of these two sectors 11a, 11b.
  • the tiles 40 and 41 also have at their upstream ends ribs 44, 45 arranged on their internal faces and which are intended to be fitted respectively in grooves 27 and 29 provided at the bottom of the annular external 24 and internal 25 grooves.
  • the heights of the ribs 26 and 44, 28 and 45, and the thicknesses of the walls of tiles 40 and 41 are calculated in such a way that the upstream ends of tiles 40 and 41 are sandwiched between the sheets 12, 13 and the elementary sectors 11.
  • the internal faces of the tiles 40, 41 are maintained spaced from the upper 17 and lower 18 walls by a distance substantially equal to the thickness of the outer ribs 26, 28 for allow the cooling air which escapes through the orifices 34 to circulate in the spaces 46, 47 formed between the tiles 40, 41 and the walls 17, 18 of the elementary sectors 11.
  • This cooling air then escapes through orifices 48, 49 formed in the tiles 40, 41 as well as by a multi-perforation 50 made in the thickness of the tiles 40, 41.
  • the spaces 46, 47 are closed in the circumferential direction by tile returns 51, 52 which are supported on the external faces of the upper 17 and lower 18 walls of adjacent sectors 11a, 11b.
  • Zirconate is deposited on the tiles 40, 41 so to create a thermal barrier.
  • the upstream part of the assembly thus produced is embedded in the groove 15 of the chamber bottom 2, formed by the sheets 12 and 13 and therein fixed by the fixing means 14.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Portable Nailing Machines And Staplers (AREA)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The combustion chamber separator (10) is made up of a series of sectors (11) fastened to the chamber base sheet metal components (12,13). Each sector is in the form of an elongated hollow body cooled by circulated air from the front of the chamber base which penetrates the sectors and passes into the two heads through holes (34) in the upper and lower walls (17,18).

Description

La conception des nouvelles turbomachines aéronautiques conduit, pour obtenir des taux de pollution réduits, à envisager l'adoption de chambres de combustion annulaires à deux têtes, l'une fonctionnant aux régimes ralenti et plein gaz, appelée tête pilote, l'autre au régime plein gaz, appelée tête de décollage.The design of new aeronautical turbomachines leads, to obtain reduced pollution rates, to consider the adoption of annular combustion chambers with two heads, one operating at idle and full throttle, called the pilot head, the other at full throttle, called the take-off head.

Dans le volume global de la chambre, les deux têtes sont délimitées dans le fond de chambre, par un anneau appelé séparateur et forment ainsi deux viroles concentriques.In the overall volume of the chamber, the two heads are delimited in the back of the room, by a ring called separator and thus form two concentric ferrules.

Ce séparateur constitue un élément critique dans la conception de la chambre, car il est soumis à des contraintes longitudinales et tangentielles lors du fonctionnement de la chambre.This separator is a critical element in the design of the room because it is subjected to longitudinal stresses and tangential during operation of the chamber.

Dans le but d'annuler ces contraintes, l'anneau séparateur est constitué d'une pluralité de secteurs disposés circonférentiellement à une certaine distance les uns des autres.In order to overcome these constraints, the separator ring is consisting of a plurality of sectors arranged circumferentially at some distance from each other.

Chaque secteur et refroidi par une circulation d'air, provenant dans les secteurs et s'échappant dans les têtes au travers des parois par une pluralité d'orifices.Each sector and cooled by an air circulation, coming in the sectors and escaping in the heads through the walls by a plurality of orifices.

En fonctionnement, les parois externes du séparateur sont soumises à des températures très élevées, de plus, les intersections circonférentielles de ces séparateurs sont favorables à une recirculation des gaz chauds entre les deux têtes.In operation, the external walls of the separator are subject to very high temperatures, moreover, intersections circumferential of these separators are favorable for recirculation hot gases between the two heads.

L'invention s'est donné pour but de protéger thermiquement les parois externes des secteurs et d'empêcher la recirculation des gaz entre les deux têtes.The object of the invention is to thermally protect the outer walls of the sectors and prevent recirculation of gases between the two heads.

L'invention concerne donc une chambre de combustion annulaire comprenant deux têtes concentriques décalées radialement l'une par rapport à l'autre et délimitées dans le fond de chambre par un anneau séparateur de gaz, l'une des têtes, appelée tête pilote, fonctionnant aux régimes ralenti et plein gaz, et l'autre tête, appelée tête de décollage, fonctionnant au régime plein gaz, ledit anneau séparateur comprenant une pluralité de secteurs élémentaires disposés circonférentiellement à une certaine distance les uns des autres et fixés sur des tôles du fond de chambre, chaque secteur étant conformé en un corps allongé creux, refroidi par une circulation d'air provenant de l'amont du fond de chambre, pénétrant dans ledit secteur et s'échappant dans les deux têtes au travers des parois dudit secteur par une pluralité d'orifices. The invention therefore relates to an annular combustion chamber comprising two concentric heads offset radially one by relative to each other and delimited in the back of the room by a ring gas separator, one of the heads, called the pilot head, operating at idle and full throttle, and the other head, called the take-off head, operating at full gas speed, said separator ring comprising a plurality of elementary sectors disposed circumferentially at a certain distance from each other and fixed on sheets from the bottom of chamber, each sector being shaped into an elongated hollow body, cooled by air circulation from upstream from the bottom of chamber, entering said sector and escaping in both heads through the walls of said sector by a plurality of orifices.

Cette chambre de combustion est caractérisée par le fait que lesdits secteurs sont protégés thermiquement par deux séries de tuiles recouvrant respectivement les parois supérieures et inférieures desdits secteurs, les tuiles desdites séries étant disposées à cheval sur deux secteurs adjacents et à distance desdites parois afin de permettre à l'air de refroidissement de circuler dans l'espace ainsi créé, des orifices étant ménagés dans lesdites tuiles pour permettre l'échappement de l'air de refroidissement dans les deux têtes.This combustion chamber is characterized by the fact that said areas are thermally protected by two sets of tiles covering respectively the upper and lower walls of said sectors, the tiles of said series being arranged astride two adjacent areas and away from said walls to allow air cooling circulate in the space thus created, orifices being formed in said tiles to allow the escape of air from cooling in both heads.

Les avantageuses dispositions suivantes sont en outre adoptées :

  • chaque secteur présente à son extrémité aval une rainure et au voisinage de l'extrémité amont de ses parois supérieure et inférieure une nervure externe qui délimite une rainure avec les tôles du fond de chambre ;
  • chaque tuile présente un crochet à son extrémité aval et une nervure interne à son extrémité amont, ledit crochet et ladite nervure étant destinés à loger dans les rainures des secteurs ;
  • les extrémités amont des tuiles sont interposés entre les parois des secteurs et les tôles du fond de chambre, ces dernières étant conformées en conséquence ;
  • les nervures des secteurs comportent des évidements dans lesquels s'engagent des crans formés sur les faces internes des tuiles, afin d'assurer le maintien circonférentiel des tuiles par rapport aux secteurs ;
  • un jeu est laissé entre les crochets des tuiles et les fonds des rainures des extrémités aval des secteurs pour permettre le déplacement axial des éléments en présence ;
  • un dépôt de zirconate est effectué sur les tuiles de manière à créer une barrière thermique.
The following advantageous provisions are also adopted:
  • each sector has a groove at its downstream end and in the vicinity of the upstream end of its upper and lower walls an external rib which defines a groove with the sheets of the chamber bottom;
  • each tile has a hook at its downstream end and an internal rib at its upstream end, said hook and said rib being intended to be housed in the grooves of the sectors;
  • the upstream ends of the tiles are interposed between the walls of the sectors and the sheets of the chamber bottom, the latter being shaped accordingly;
  • the ribs of the sectors include recesses in which engage notches formed on the internal faces of the tiles, in order to ensure the circumferential maintenance of the tiles with respect to the sectors;
  • a clearance is left between the hooks of the tiles and the bottoms of the grooves of the downstream ends of the sectors to allow the axial displacement of the elements present;
  • a deposit of zirconate is carried out on the tiles so as to create a thermal barrier.

D'autres avantages et caractéristiques de l'invention ressortiront à la lecture de la description suivante faite à titre d'exemple et en référence au dessin annexé dans lequel :

  • la figure 1 est une demi-coupe axiale de la partie médiane d'un fond de chambre d'une chambre de combustion à deux têtes, conforme à l'invention ;
  • la figure 2 montre en développé une coupe du séparateur selon la ligne II-II de la figure 1.
    • Other advantages and characteristics of the invention will emerge on reading the following description given by way of example and with reference to the appended drawing in which:
  • Figure 1 is an axial half-section of the middle part of a chamber bottom of a combustion chamber with two heads, according to the invention;
  • FIG. 2 shows an enlarged section of the separator along line II-II of FIG. 1.

    • Le dessin montre une enceinte de combustion 1 d'une chambre de combustion à deux têtes de turbine à gaz, délimitée par une paroi annulaire externe et une paroi annulaire interne, symétriques de révolution autour d'un axe commun, ainsi que par un fond de chambre 2 reliant les extrémités aval des deux parois annulaires et partiellement montée sur la figure 1.The drawing shows a combustion chamber 1 of a combustion with two gas turbine heads, delimited by a wall external annular and an internal annular wall, symmetrical of revolution around a common axis, as well as through a chamber bottom 2 connecting the downstream ends of the two annular walls and partially mounted on figure 1.

    Le fond de chambre 2 est équipé de deux groupes d'injecteurs de carburant répartis sur des couronnes annulaires concentriques, de diamètres différents.The bottom of chamber 2 is equipped with two groups of injectors fuel distributed over concentric annular rings, different diameters.

    Les injecteurs du groupe externe traversent des trous 3 d'axe Y1 ménagés dans le fond de chambre 2 et coopèrent pour la carburation du carburant avec des passages d'air traversant le fond 2 et les parois de l'enceinte 1. Ces injecteurs de carburant les plus proches de la paroi externe sont destinés à fonctionner, en étant seuls en service, au régime de ralenti, et constituent des injecteurs de carburant de la tête pilote.The injectors of the external group pass through holes 3 of axis Y1 formed in the chamber bottom 2 and cooperate for the fueling of the fuel with air passages passing through the bottom 2 and the walls of enclosure 1. These fuel injectors closest to the wall external are intended to function, being alone in service, with the mode idling speed, and constitute fuel injectors for the pilot head.

    Les injecteurs du groupe interne traversent également des trous 4 d'axe Y2 ménagés dans le fond de chambre 2 et sont destinés à fonctionner au régime de pleins gaz ou de décollage d'un avion équipé de ladite turbine à gaz.Internal group injectors also pass through holes 4 of axis Y2 formed in the bottom of chamber 2 and are intended for operate at full throttle or takeoff on an equipped aircraft of said gas turbine.

    Un ensemble 10 séparateur de gaz, de forme générale annulaire, fixé sur le fond de chambre 2, est interposé entre les deux groupes d'injecteurs. Cet ensemble 10 séparateur constitue une saillie à l'intérieur de l'enceinte de combustion 1 par rapport au fond de chambre 2.A gas separator assembly 10, of generally annular shape, fixed on the bottom of chamber 2, is interposed between the two groups injectors. This separator assembly 10 constitutes a projection the interior of the combustion chamber 1 relative to the chamber bottom 2.

    Ainsi que cela ressort des dessins, l'ensemble 10 séparateur de gaz est constitué par une pluralité de secteurs élémentaires 11 creux, de forme allongée, qui sont disposés circonférentiellement à une certaine distance x les uns des autres et qui sont fixés chacun sur des tôles 12, 13 du fond de chambre 2 par des moyens de fixation 14 distincts de ceux des autres secteurs.As can be seen from the drawings, the separator assembly 10 gas consists of a plurality of elementary hollow sectors 11, of elongated shape, which are arranged circumferentially at a certain distance x from each other and which are each fixed on sheets 12, 13 of the chamber bottom 2 by fixing means 14 distinct from those from other sectors.

    A cet effet les tôles 12 et 13 du fond de chambre 2 sont mises en forme de manière à former, du côté de l'enceinte de combustion 1, une rainure annulaire 15 de section en U renversé de 90°, et dans le fond de laquelle est engagée la partie amont 16 de chaque secteur élémentaire 11. For this purpose the sheets 12 and 13 of the chamber bottom 2 are put in forms so as to form, on the side of the combustion chamber 1, a annular groove 15 of U-shaped section reversed 90 °, and in the bottom of which is engaged the upstream part 16 of each elementary sector 11.

    Chaque secteur élémentaire 11 présente, en plus de la partie amont 16, de section en U renversé, qui s'engage dans le fond de la rainure 15 du fond de chambre 2, une paroi supérieure 17 et une paroi inférieure 18 qui se raccordent à leurs extrémités aval 19, de manière à former un coin dans l'enceinte de combustion 1, et dont les extrémités respectives amont 20 et 21 sont raccordées aux ailes de la partie amont 16, par des parois de raccordement 22 et 23 qui forment des décrochements de telle manière que les parties amont des parois supérieure 17 et inférieure 18 sont écartées respectivement des tôles 12 et 13 et délimitent avec ces dernières des espaces annulaires 24, 25.Each elementary sector 11 has, in addition to the part upstream 16, of inverted U section, which engages in the bottom of the groove 15 of the chamber bottom 2, an upper wall 17 and a wall lower 18 which are connected at their downstream ends 19, so as to form a corner in the combustion chamber 1, and the ends of which respective upstream 20 and 21 are connected to the wings of the upstream part 16, by connecting walls 22 and 23 which form recesses in such a way that the upstream parts of the walls upper 17 and lower 18 are separated from the sheets 12 respectively and 13 and delimit therewith annular spaces 24, 25.

    La paroi supérieure 17 comporte dans l'espace annulaire 24 une nervure externe 26 parallèle à la paroi de raccordement 22 et qui forme avec la paroi de raccordement 22 et la tôle 12 une rainure 27.The upper wall 17 has in the annular space 24 a external rib 26 parallel to the connecting wall 22 and which forms with the connection wall 22 and the sheet 12 a groove 27.

    De même, la paroi inférieure 18 comporte dans l'espace annulaire 25 une nervure externe 28 parallèle à la paroi de raccordement 23 et qui délimite avec cette dernière et la tôle 13 une rainure 29.Similarly, the bottom wall 18 has in the annular space 25 an external rib 28 parallel to the connecting wall 23 and which defines with the latter and the sheet 13 a groove 29.

    L'extrémité aval 19 de raccordement de la paroi supérieure 17 et de la paroi inférieure 18 présente également une rainure 30 ouverte dans la direction opposée au fond de chambre 2.The downstream end 19 for connection of the upper wall 17 and of the bottom wall 18 also has an open groove 30 in the opposite direction to the chamber bottom 2.

    Deux parois latérales 31, 32 obturent les extrémités circonférentielles de chaque secteur élémentaire 11.Two side walls 31, 32 close off the ends of each elementary sector 11.

    La partie amont 16 de chaque secteur élémentaire 11 et les tôles 12 et 13 du fond de chambre 2 comportent en correspondance des trous 33 pour le prélèvement d'un air de refroidissement en amont du fond de chambre 1, cet air de refroidissement circulant à l'intérieur du secteur 11 et s'évacuant par une pluralité d'orifices 34 ménagées dans les parois supérieure 17 et inférieure 18 vers l'enceinte de combustion 1.The upstream part 16 of each elementary sector 11 and the sheets 12 and 13 of the chamber bottom 2 have corresponding holes 33 for the removal of cooling air upstream from the bottom of chamber 1, this cooling air circulating inside the sector 11 and discharging through a plurality of orifices 34 formed in the walls upper 17 and lower 18 to the combustion chamber 1.

    Les parois supérieures 17 des secteurs élémentaires 11 sont protégées thermiquement par une première série de tuiles 40 disposées chacune à cheval sur deux tuiles adjacentes 11a, 11b ainsi que cela est visible sur la figure 2.The upper walls 17 of the elementary sectors 11 are thermally protected by a first series of tiles 40 arranged each straddling two adjacent tiles 11a, 11b as is visible in Figure 2.

    De la même manière, les parois inférieures 18 des secteurs élémentaires 11 sont recouvertes par une deuxième série de tuiles 41 disposées chacune à cheval sur deux tuiles adjacentes 11a, 11b.Likewise, the lower walls 18 of the sectors elementary 11 are covered by a second series of tiles 41 each arranged astride two adjacent tiles 11a, 11b.

    Les tuiles 40 et 41 comportent, chacune à leur extrémité aval, un crochet respectivement 42, 43 dirigé vers le fond de chambre. Les crochets 42, 43 de deux tuiles 40, 41 à cheval sur les mêmes secteurs 11a, 11b sont destinés à loger avec jeu, en étant disposés l'un sur l'autre dans les rainures 30 ménagées aux extrémités aval de ces deux secteurs 11a, 11b.The tiles 40 and 41 each have at their downstream end a hook respectively 42, 43 directed towards the chamber bottom. The hooks 42, 43 of two tiles 40, 41 straddling the same sectors 11a, 11b are intended to accommodate with play, being arranged one on the other in the grooves 30 formed at the downstream ends of these two sectors 11a, 11b.

    Les tuiles 40 et 41 comportent en outre à leurs extrémités amont des nervures 44, 45 disposées sur leurs faces internes et qui sont destinées à venir s'encastrer respectivement dans les rainures 27 et 29 prévues au fond des rainures annulaires externe 24 et interne 25.The tiles 40 and 41 also have at their upstream ends ribs 44, 45 arranged on their internal faces and which are intended to be fitted respectively in grooves 27 and 29 provided at the bottom of the annular external 24 and internal 25 grooves.

    Les hauteurs des nervures 26 et 44, 28 et 45, et les épaisseurs des parois des tuiles 40 et 41 sont calculées de telle manière que les extrémités amont des tuiles 40 et 41 sont prises en sandwich entre les tôles 12, 13 et les secteurs élémentaires 11.The heights of the ribs 26 and 44, 28 and 45, and the thicknesses of the walls of tiles 40 and 41 are calculated in such a way that the upstream ends of tiles 40 and 41 are sandwiched between the sheets 12, 13 and the elementary sectors 11.

    En outre, les faces internes des tuiles 40, 41 sont maintenues écartées des parois supérieure 17 et inférieure 18 d'une distance sensiblement égale à l'épaisseur des nervures externes 26, 28 pour permettre à l'air de refroidissement qui s'échappe par les orifices 34 de circuler dans les espaces 46, 47 ménagées entre les tuiles 40, 41 et les parois 17, 18 des secteurs élémentaires 11. Cet air de refroidissement s'échappe ensuite par des orifices 48, 49 ménagés dans les tuiles 40, 41 ainsi que par une multiperforation 50 réalisée dans l'épaisseur des tuiles 40, 41. Les espaces 46, 47 sont fermées dans le sens circonférentiel par des retours de tuile 51, 52 qui sont en appui sur les faces externes des parois supérieures 17 et inférieures 18 des secteurs adjacents 11a, 11b.In addition, the internal faces of the tiles 40, 41 are maintained spaced from the upper 17 and lower 18 walls by a distance substantially equal to the thickness of the outer ribs 26, 28 for allow the cooling air which escapes through the orifices 34 to circulate in the spaces 46, 47 formed between the tiles 40, 41 and the walls 17, 18 of the elementary sectors 11. This cooling air then escapes through orifices 48, 49 formed in the tiles 40, 41 as well as by a multi-perforation 50 made in the thickness of the tiles 40, 41. The spaces 46, 47 are closed in the circumferential direction by tile returns 51, 52 which are supported on the external faces of the upper 17 and lower 18 walls of adjacent sectors 11a, 11b.

    Un dépôt de zirconate est effectué sur les tuiles 40, 41 de manière à créer une barrière thermique.Zirconate is deposited on the tiles 40, 41 so to create a thermal barrier.

    Le maintien circonférentiel des tuiles 40, 41 par rapport aux secteurs 11 est réalisé par des crans 53, 54 solidaires des parois internes des tuiles 40, 41 qui viennent s'engager dans des évidements, non représentés sur les dessins, usinés dans les nervures externes 26, 28 des secteurs 11.The circumferential maintenance of the tiles 40, 41 relative to the sectors 11 is produced by notches 53, 54 integral with the internal walls tiles 40, 41 which engage in recesses, not shown in the drawings, machined in the outer ribs 26, 28 of sectors 11.

    Le montage des tuiles 40, 41 s'effectue de la manière suivante :

    • les secteurs 11 du séparateur sont positionnés circonférentiellement sur un outillage de montage ;
    • les tuiles 40, 41 sont alors présentées axialement, de façon à engager les crochets 42, 43 dans la rainure aval 30 des secteurs 11 et les crans 53, 54 dans les évidements externes 26, 28 des secteurs 11. Les nervures 44, 45 des tuiles 40, 41 viennent par élasticité s'encastrer dans les rainures 27, 29 des secteurs 11.
    The mounting of the tiles 40, 41 is carried out as follows:
    • the sectors 11 of the separator are positioned circumferentially on an assembly tool;
    • the tiles 40, 41 are then presented axially, so as to engage the hooks 42, 43 in the downstream groove 30 of the sectors 11 and the notches 53, 54 in the external recesses 26, 28 of the sectors 11. The ribs 44, 45 of the tiles 40, 41 come by elasticity to be embedded in the grooves 27, 29 of the sectors 11.

    La partie amont de l'ensemble ainsi réalisé est encastré dans la rainure 15 du fond de chambre 2, formée par les tôles 12 et 13 et y est fixé par les moyens de fixation 14.The upstream part of the assembly thus produced is embedded in the groove 15 of the chamber bottom 2, formed by the sheets 12 and 13 and therein fixed by the fixing means 14.

    La présence des tuiles 40, 41 sur les secteurs 11 du séparateur de gaz permet d'améliorer l'efficacité du refroidissement du séparateur de gaz, et leur disposition à cheval sur deux secteurs adjacents assure l'étanchéité aux gaz entre les secteurs 11 composant le séparateur de gaz 10.The presence of tiles 40, 41 on sectors 11 of the separator of gas improves the cooling efficiency of the separator gas, and their arrangement straddling two adjacent sectors ensures gas tightness between the sectors 11 making up the gas separator 10.

    Claims (6)

    Chambre de combustion annulaire comprenant deux têtes concentriques décalées radialement l'une par rapport à l'autre et délimitées dans le fond de chambre (2) par un anneau séparateur (10) de gaz, l'une des têtes, appelée tête pilote, fonctionnant aux régimes ralenti et plein gaz, et l'autre tête, appelée tête de décollage, fonctionnant au régime plein gaz, ledit anneau séparateur (10) comprenant une pluralité de secteurs élémentaires (11) disposés circonférentiellement à une certaine distance (x) les uns des autres et fixés sur des tôles (12, 13) du fond de chambre (2), chaque secteur (11) étant conformé en un corps allongé creux, refroidi par une circulation d'air provenant de l'amont du fond de chambre (2), pénétrant dans ledit secteur et s'échappant dans les deux têtes au travers des parois (17, 18) dudit secteur par une pluralité d'orifices (34),
    caractérisée par le fait que lesdits secteurs (11) sont protégés thermiquement par deux séries de tuiles (40, 41) recouvrant respectivement les parois supérieures (17) et inférieures (18) desdits secteurs, les tuiles (40, 41) desdites séries étant disposées à cheval sur deux secteurs adjacents (11a, 11b) et à distance desdites parois (17, 18) afin de permettre à l'air de refroidissement de circuler dans l'espace (46, 47) ainsi créé, des orifices (48, 49, 50) étant ménagés dans lesdites tuiles (40, 41) pour permettre l'échappement de l'air de refroidissement dans les deux têtes.    Annular combustion chamber comprising two concentric heads offset radially with respect to each other and delimited in the chamber bottom (2) by a gas separator ring (10), one of the heads, called the pilot head, operating at idle and full throttle speeds, and the other head, called take-off head, operating at full throttle speed, said separating ring (10) comprising a plurality of elementary sectors (11) arranged circumferentially at a certain distance (x) from each other of the others and fixed to sheets (12, 13) of the chamber bottom (2), each sector (11) being shaped as an elongated hollow body, cooled by a circulation of air coming from upstream from the chamber bottom ( 2), penetrating into said sector and escaping in the two heads through the walls (17, 18) of said sector through a plurality of orifices (34),
    characterized by the fact that said sectors (11) are thermally protected by two series of tiles (40, 41) respectively covering the upper (17) and lower (18) walls of said sectors, the tiles (40, 41) of said series being arranged straddling two adjacent sectors (11a, 11b) and at a distance from said walls (17, 18) in order to allow the cooling air to circulate in the space (46, 47) thus created, orifices (48, 49 , 50) being arranged in said tiles (40, 41) to allow the escape of the cooling air in the two heads.         Chambre de combustion selon la revendication 1, caractérisée par le fait que chaque tuile (40, 41) présente un crochet (42, 43) à son extrémité aval et une nervure interne (44, 45) à son extrémité amont, par le fait que les secteurs (11) présentent à leurs extrémités aval une rainure (30) dans laquelle logent les crochets (42, 43) des tuiles (40, 41), et au voisinage des extrémités amont de leurs parois supérieures (17) et inférieures (18) des nervures externes (26, 28) qui délimitent avec les tôles (12, 13) du fond de chambre (2) des rainures (27, 28) dans lesquelles logent les nervures internes (44, 45) des tuiles (40, 41).Combustion chamber according to claim 1, characterized by the fact that each tile (40, 41) has a hook (42, 43) at its downstream end and an internal rib (44, 45) at its upstream end, by the fact that the sectors (11) have at their downstream ends a groove (30) in which the hooks (42, 43) of the tiles (40, 41), and in the vicinity of the upstream ends of their upper walls (17) and lower (18) external ribs (26, 28) which delimit with the sheets (12, 13) of the chamber bottom (2) of the grooves (27, 28) in which house the internal ribs (44, 45) of the tiles (40, 41). Chambre de combustion selon la revendication 2, caractérisée par le fait que les extrémités amont des tuiles (41, 41) sont interposées entre les parois des secteurs (17, 18) et les tôles (12, 13) du fond de chambre (2), ces dernières étant conformées en conséquence.Combustion chamber according to claim 2, characterized by the fact that the upstream ends of the tiles (41, 41) are interposed between the walls of the sectors (17, 18) and the sheets (12, 13) of the chamber bottom (2), the latter being shaped accordingly. Chambre de combustion selon l'une quelconque des revendications 2 ou 3, caractérisée par le fait que les nervures externes (26, 28) des secteurs (11) comportent des évidements dans lesquels s'engagent des crans (53, 54) formés sur les faces internes des tuiles (40, 41).Combustion chamber according to any one of claims 2 or 3, characterized in that the external ribs (26, 28) of the sectors (11) have recesses in which notches (53, 54) formed on the internal faces of the tiles (40, 41). Chambre de combustion selon l'une quelconque des revendications 2 à 4, caractérisée par le fait que les crochets (42, 43) des tuiles (40, 41) logent avec jeu dans les rainures (30) des extrémités aval des secteurs (11).Combustion chamber according to any one of Claims 2 to 4, characterized in that the hooks (42, 43) of the tiles (40, 41) fit with play in the grooves (30) of the downstream ends sectors (11). Chambre de combustion selon l'une quelconque des revendications 2 à 5, caractérisée par le fait que les tuiles (40, 41) sont recouvertes d'une couche de zirconate.Combustion chamber according to any one of Claims 2 to 5, characterized in that the tiles (40, 41) are covered with a layer of zirconate.
    EP99400918A 1998-04-16 1999-04-15 Separator for combustion chamber with two burner heads Expired - Lifetime EP0950859B1 (en)

    Applications Claiming Priority (2)

    Application Number Priority Date Filing Date Title
    FR9804704A FR2777634B1 (en) 1998-04-16 1998-04-16 SEPARATOR FOR TWO-HEADED COMBUSTION CHAMBER
    FR9804704 1998-04-16

    Publications (2)

    Publication Number Publication Date
    EP0950859A1 true EP0950859A1 (en) 1999-10-20
    EP0950859B1 EP0950859B1 (en) 2004-06-30

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    EP (1) EP0950859B1 (en)
    JP (1) JPH11324712A (en)
    DE (1) DE69918352T2 (en)
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    FR2856468B1 (en) * 2003-06-17 2007-11-23 Snecma Moteurs TURBOMACHINE ANNULAR COMBUSTION CHAMBER
    GB2420614B (en) * 2004-11-30 2009-06-03 Alstom Technology Ltd Tile and exo-skeleton tile structure
    DE102007062699A1 (en) * 2007-12-27 2009-07-02 Rolls-Royce Deutschland Ltd & Co Kg combustion liner
    US8015817B2 (en) * 2009-06-10 2011-09-13 Siemens Energy, Inc. Cooling structure for gas turbine transition duct
    US10101029B2 (en) * 2015-03-30 2018-10-16 United Technologies Corporation Combustor panels and configurations for a gas turbine engine

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    US5421158A (en) * 1994-10-21 1995-06-06 General Electric Company Segmented centerbody for a double annular combustor
    GB2297830A (en) * 1995-02-07 1996-08-14 Rolls Royce Radially staged annular combustor

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    EP0564170A1 (en) * 1992-03-30 1993-10-06 General Electric Company Segmented centerbody for a double annular combustor
    US5421158A (en) * 1994-10-21 1995-06-06 General Electric Company Segmented centerbody for a double annular combustor
    GB2297830A (en) * 1995-02-07 1996-08-14 Rolls Royce Radially staged annular combustor

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    DE69918352T2 (en) 2005-08-25
    FR2777634B1 (en) 2000-05-19
    US6155055A (en) 2000-12-05
    FR2777634A1 (en) 1999-10-22
    JPH11324712A (en) 1999-11-26
    DE69918352D1 (en) 2004-08-05
    EP0950859B1 (en) 2004-06-30

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