EP1965027B1 - High-pressure turbine of a turbomachine - Google Patents

High-pressure turbine of a turbomachine Download PDF

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Publication number
EP1965027B1
EP1965027B1 EP08151865A EP08151865A EP1965027B1 EP 1965027 B1 EP1965027 B1 EP 1965027B1 EP 08151865 A EP08151865 A EP 08151865A EP 08151865 A EP08151865 A EP 08151865A EP 1965027 B1 EP1965027 B1 EP 1965027B1
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EP
European Patent Office
Prior art keywords
annular
turbomachine
guide vane
radially
upstream
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EP08151865A
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German (de)
French (fr)
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EP1965027A2 (en
EP1965027A3 (en
EP1965027A8 (en
Inventor
Mathieu Dakowski
Claire Dorin
Alain Dominique Gendraud
Vincent Philippot
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Safran Aircraft Engines SAS
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SNECMA SAS
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators

Definitions

  • the present invention relates to a high-pressure turbine in a turbomachine such as in particular an airplane turbojet or turboprop.
  • a turbomachine high-pressure turbine comprises at least one stage comprising a distributor formed of an annular row of stationary vanes for rectification and a rotor wheel rotatably mounted downstream of the distributor in a cylindrical or frustoconical assembly of ring sectors arranged circumferentially butt ( US Patent 4,023,919 , US Patent 4,485,620 , EP 0 083 896 and US Patent 3,314,648 ). These ring sectors comprise at their upstream and downstream ends hooking means on an annular support which is fixed to an outer casing of the turbine by suspension means.
  • the radial clearances between the moving blades of the wheel and the ring sectors must be minimized to improve the efficiency of the turbomachine while avoiding friction of the ends of the blades on the ring sectors, which would result in wear of these parts. extremes and degradation of the efficiency of the turbomachine at all operating speeds.
  • the distributor of the high-pressure turbine comprises two coaxial walls of revolution which extend one inside the other and which are interconnected by the fixed vanes of recovery. It is fixed in the turbomachine by its inner wall of revolution which comprises an annular flange for attachment to an inner casing of the turbine. Sealing means are further provided at the upstream and downstream ends of the revolution walls of the distributor to limit leakage of gases flowing in the turbine.
  • the hot gases leaving the combustion chamber of the turbomachine flow on the vanes of the distributor and exert on them an axial thrust which solicits the distributor towards the downstream.
  • the external periphery of the dispenser then tends to axially bear on the annular attachment support of the ring sectors and push it downstream, resulting in random and uncontrolled variations of the radial clearances between the rotor blades of the wheel and the ring sectors , and therefore a decrease in the performance of the turbomachine.
  • the invention aims in particular to provide a simple, effective and economical solution to this problem.
  • a turbomachine comprising a high-pressure turbine comprising at least one distributor formed of an annular row of fixed vanes rectifying and a rotor wheel rotatably mounted downstream of the distributor and inside a set of ring sectors arranged circumferentially end to end and carried by an annular support suspended on an outer casing, the dispenser comprising at its radially inner end means for fixing on an inner casing and at its radially outer end of the support means axial on a fixed element which is suspended from the outer casing independently of the annular support of the ring sectors, characterized in that the annular plate comprises on a radially inner portion an annular groove oriented axially upstream and intended to receive a cylindrical rim an outer wall of a combustion chamber arranged upstream of the distributor.
  • this fixed element comprises an annular sheet which extends radially between the distributor and the outer casing and which has at its radially outer end an annular clamping flange on the outer casing.
  • This annular sheet may also comprise at its radially inner end a radial annular support flange of the distributor.
  • the sheet comprises on a radially inner portion an annular groove oriented axially upstream and intended to receive a cylindrical rim of an outer wall of the combustion chamber located upstream.
  • the radially outer portion of this sheet may also include ventilation air passage orifices regularly distributed around its axis of revolution.
  • the distributor comprises an annular radial flange extending outwardly and forming axial bearing means on the fixed element of the turbine.
  • This radial flange may comprise a cylindrical rib axial support on the fixed element of the turbine.
  • this radial flange is located substantially to the right of the leading edges of the vanes of the dispenser.
  • the invention also relates to an annular sheet for a turbomachine as described above, characterized in that it comprises a frustoconical wall extending between a radially outer annular flange and a radial annular flange.
  • the frustoconical wall comprises, on a radially outer portion, ventilation air passage orifices regularly distributed around the axis of revolution of the wall, and on a radially inner portion, an annular groove.
  • the figure 1 schematically represents a portion of a turbomachine such as a turbojet or an airplane turboprop comprising a high-pressure turbine 10 arranged downstream of a combustion chamber 12, and upstream of a low-pressure turbine 14 of the turbomachine.
  • a turbomachine such as a turbojet or an airplane turboprop comprising a high-pressure turbine 10 arranged downstream of a combustion chamber 12, and upstream of a low-pressure turbine 14 of the turbomachine.
  • the combustion chamber 12 comprises a wall of internal revolution 48 and an outer wall of revolution 50 extending one inside the other.
  • the inner wall 48 is connected at its downstream end to a radially outer end of a frustoconical wall 52 whose radially inner end has an annular flange 54 fixed to an inner casing 56 of the combustion chamber.
  • the outer wall 50 of the chamber is connected at its downstream end to a radially inner end of a frustoconical wall 58 which has at its radially outer end a radially outer annular flange 60 for attachment to a corresponding annular flange 62 of an outer casing 64 of the room.
  • the high-pressure turbine 10 comprises a single turbine stage comprising a distributor 16 formed of an annular row of stationary vanes for rectification, and a vane wheel 18 rotatably mounted downstream of the distributor 16.
  • the low-pressure turbine 14 comprises several turbine stages, each of these stages also comprising a distributor and a paddle wheel, only the distributor 47 of the upstream low-pressure stage being visible in FIG. figure 1 .
  • the impeller 18 of the high-pressure turbine 10 rotates within a substantially cylindrical assembly of ring sectors 20 which are circumferentially disposed end-to-end and suspended from a turbine casing 22 via a support 24.
  • This annular support 24 comprises at its inner periphery means 26 for hooking ring sectors 20 and comprises a frustoconical wall 28 which extends upstream and outwards and is connected at its end. radially external to a radially outer annular flange 30 for fixing on a corresponding annular flange 32 of the turbine casing 22.
  • This flange 30 is interposed axially between the flange 60 of the frustoconical wall 58 and the flange 32 of the turbine casing 22 and is clamped axially between these flanges by appropriate means of the flange. screw-nut type.
  • the annular support 24 comprises at its inner periphery two radial annular walls 34, 36, respectively upstream and downstream, which are connected to one another by a cylindrical wall 38.
  • the radial walls 34, 36 comprise at their radially internal ends downstream cylindrical flanges 40 which cooperate with circumferential hooks 42, 44 provided at the upstream and downstream ends of the ring sectors 20.
  • An annular locking member 46 with a C-section is engaged axially from downstream on the downstream cylindrical rim 40 of the support and on the downstream hooks 44 of the ring sectors to ensure the locking of the assembly.
  • the frustoconical wall 28 of the annular support 24 defines with the frustoconical wall 58 of the chamber an annular enclosure 80 which is supplied with ventilation and cooling air through orifices 82 formed in the frustoconical wall 58.
  • Orifices 84 are formed in the wall radial upstream 34 of the annular support 24 to establish a fluid communication between the enclosure 80 and an annular cavity 86 for cooling the ring sectors 20 delimited externally by the cylindrical wall 38 of the annular support.
  • the distributor 16 of the high-pressure turbine 10 is formed of two coaxial walls of revolution 66, 68 which extend one inside the other and which are interconnected by the fixed vanes of recovery.
  • the inner wall 68 of the dispenser comprises an annular flange 70 which extends radially inwardly from its inner surface and which is secured by suitable means to a corresponding flange 72 provided at the downstream end of the inner casing 56 of the chamber
  • the upstream and downstream ends of the inner wall 68 of the distributor cooperate to seal with the downstream end of the inner wall 48 of the combustion chamber and with the upstream end of the platforms of the blades of the wheel 18, respectively, to prevent the passage of gas from the annular flow vein of the turbine radially inwardly of the inner wall 68.
  • the outer wall 66 of the distributor comprises at each of its upstream and downstream ends an annular groove 74 opening radially outwards.
  • Annular sealing gaskets 76 are housed in these grooves 74 and cooperate with cylindrical ribs 78 formed on the frustoconical wall 58 and on the upstream radial wall 34 of the annular support 24, respectively, to prevent the passage of gas from the flow duct.
  • the turbine radially outwardly of the outer wall 66, and conversely, the passage of air from the enclosure 80 radially inward in the vein of the turbine.
  • the distributor 16 In operation of the turbomachine, the distributor 16 is biased downstream by the flow of gas in the turbine and its outer periphery which is not rigidly connected to a fixed element of the turbine moves slightly downstream until the radially outer end of the outer wall 66 of the distributor comes to bear axially on an upstream face of the upstream radial wall 34 of the annular support 24. The distributor 16 then exerts an axial force directed downstream on the support that is deformed and causes a displacement of the ring sectors 20 and a change of the radial clearances between the blades of the wheel 18 and the ring sectors.
  • the invention makes it possible to provide a simple solution to this problem by means of the axial support of the external periphery of the distributor 16 on another fixed element of the turbine which is suspended from the outer casing 22 independently of the support 24 for securing the heating sectors. 'ring.
  • the forces applied to the distributor are thus taken up by the fixed element and are therefore not transmitted to the support 24.
  • this fixed element is formed by an annular plate 90 which extends radially around the axis of the turbine and around the distributor 16.
  • This plate 90 has a substantially frustoconical shape and comprises at its radially outer end a radially outer annular flange 92 which is axially clamped between the flange 62 of the outer casing 64 and the flange. 30 of the annular support 24.
  • the radially inner end of the sheet comprises a radial annular flange 94 which defines on the upstream side a bearing face of the distributor 16.
  • the radially inner end of the sheet also comprises an annular groove 96 opening axially upstream.
  • the outer wall 50 of the chamber is connected at its downstream end to a frustoconical wall 58 'which has a smaller radial dimension than the wall 58 of the figure 1 and which has at its radially outer end a cylindrical rim 98 facing downstream and engaged in the groove 96 of the sheet 90.
  • the reduction of the radial dimension of the frustoconical wall 58 ' makes it possible to reduce the temperature differences between the ends radially inner and outer wall and thus increase its life.
  • the sheet 90 further comprises orifices 100 of ventilation air passage for the air supply of the annular enclosure 80, these orifices 100 being evenly distributed around the axis of the turbine.
  • the distributor 16 of the figure 2 includes internal 68 and outer 66 ferrules similar to those of the figure 1 , the outer ring 66 of the dispenser further comprising at its upstream end a radial annular flange 102 extending outwardly from its outer surface.
  • This radial flange 102 comprises on the downstream side a cylindrical rib 104 bearing axially on the radial flange 94 of the sheet 90.
  • the flange 102 extends substantially to the right of the attacking edges of the blades of the distributor .
  • the distributor which is urged downstream by the hot gases leaving the combustion chamber transmits a portion of the forces to which it is subjected to the annular plate 90 by axial support of its radial flange 102 on the flange 94 of the sheet.
  • the sheet may possibly deform elastically to ensure the resumption of efforts to which the distributor is subject.
  • the flange 94 of the sheet is at a sufficient axial distance from the support 24 so as not to come into contact with the latter during operation. This support 24 is therefore no longer biased downstream by the distributor 16, which makes it possible to maintain constant radial clearances between the moving blades and the ring sectors 20.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

La présente invention concerne une turbine haute-pression dans une turbomachine telle en particulier qu'un turboréacteur ou un turbopropulseur d'avion.The present invention relates to a high-pressure turbine in a turbomachine such as in particular an airplane turbojet or turboprop.

Une turbine haute-pression de turbomachine comprend au moins un étage comportant un distributeur formé d'une rangée annulaire d'aubes fixes de redressement et une roue à aubes montée rotative en aval du distributeur dans un ensemble cylindrique ou tronconique de secteurs d'anneau disposés circonférentiellement bout à bout ( US-A-4,023,919 , US-A-4,485,620 , EP 0 083 896 et US-A-3,314,648 ). Ces secteurs d'anneau comprennent à leurs extrémités amont et aval des moyens d'accrochage sur un support annulaire qui est fixé à un carter externe de la turbine par des moyens de suspension.A turbomachine high-pressure turbine comprises at least one stage comprising a distributor formed of an annular row of stationary vanes for rectification and a rotor wheel rotatably mounted downstream of the distributor in a cylindrical or frustoconical assembly of ring sectors arranged circumferentially butt ( US Patent 4,023,919 , US Patent 4,485,620 , EP 0 083 896 and US Patent 3,314,648 ). These ring sectors comprise at their upstream and downstream ends hooking means on an annular support which is fixed to an outer casing of the turbine by suspension means.

Les jeux radiaux entre les aubes mobiles de la roue et les secteurs d'anneau doivent être minimisés pour améliorer le rendement de la turbomachine tout en évitant un frottement des extrémités des aubes sur les secteurs d'anneau, qui se traduirait par une usure de ces extrémités et par une dégradation du rendement de la turbomachine à tous les régimes de fonctionnement.The radial clearances between the moving blades of the wheel and the ring sectors must be minimized to improve the efficiency of the turbomachine while avoiding friction of the ends of the blades on the ring sectors, which would result in wear of these parts. extremes and degradation of the efficiency of the turbomachine at all operating speeds.

Le distributeur de la turbine haute-pression comprend deux parois de révolution coaxiales qui s'étendent l'une à l'intérieur de l'autre et qui sont reliées entre elles par les aubes fixes de redressement. Il est fixé dans la turbomachine par sa paroi de révolution interne qui comporte une bride annulaire de fixation sur un carter interne de la turbine. Des moyens d'étanchéité sont en outre prévus aux extrémités amont et aval des parois de révolution du distributeur pour limiter les fuites des gaz s'écoulant dans la turbine.The distributor of the high-pressure turbine comprises two coaxial walls of revolution which extend one inside the other and which are interconnected by the fixed vanes of recovery. It is fixed in the turbomachine by its inner wall of revolution which comprises an annular flange for attachment to an inner casing of the turbine. Sealing means are further provided at the upstream and downstream ends of the revolution walls of the distributor to limit leakage of gases flowing in the turbine.

En fonctionnement, les gaz chauds sortant de la chambre de combustion de la turbomachine s'écoulent sur les aubes du distributeur et exercent sur celles-ci une poussée axiale qui sollicite le distributeur en direction de l'aval. La périphérie externe du distributeur a alors tendance à venir en appui axial sur le support annulaire d'accrochage des secteurs d'anneau et à le pousser vers l'aval, ce qui entraîne des variations aléatoires et non maîtrisées des jeux radiaux entre les aubes mobiles de la roue et les secteurs d'anneau, et donc une diminution des performances de la turbomachine.In operation, the hot gases leaving the combustion chamber of the turbomachine flow on the vanes of the distributor and exert on them an axial thrust which solicits the distributor towards the downstream. The external periphery of the dispenser then tends to axially bear on the annular attachment support of the ring sectors and push it downstream, resulting in random and uncontrolled variations of the radial clearances between the rotor blades of the wheel and the ring sectors , and therefore a decrease in the performance of the turbomachine.

L'invention a notamment pour but d'apporter une solution simple, efficace et économique à ce problème.The invention aims in particular to provide a simple, effective and economical solution to this problem.

Elle propose à cet effet une turbomachine, comprenant une turbine haute-pression comportant au moins un distributeur formé d'une rangée annulaire d'aubes fixes de redressement et une roue à aubes montée rotative en aval du distributeur et à l'intérieur d'un ensemble de secteurs d'anneau disposés circonférentiellement bout à bout et portés par un support annulaire suspendu à un carter externe, le distributeur comprenant à son extrémité radialement interne des moyens de fixation sur un carter interne et à son extrémité radialement externe des moyens d'appui axial sur un élément fixe qui est suspendu au carter externe indépendamment du support annulaire des secteurs d'anneau, caractérisée en ce que la tôle annulaire comporte sur une partie radialement interne une rainure annulaire orientée axialement vers l'amont et destinée à recevoir un rebord cylindrique d'une paroi externe d'une chambre de combustion agencée en amont du distributeur.It proposes for this purpose a turbomachine, comprising a high-pressure turbine comprising at least one distributor formed of an annular row of fixed vanes rectifying and a rotor wheel rotatably mounted downstream of the distributor and inside a set of ring sectors arranged circumferentially end to end and carried by an annular support suspended on an outer casing, the dispenser comprising at its radially inner end means for fixing on an inner casing and at its radially outer end of the support means axial on a fixed element which is suspended from the outer casing independently of the annular support of the ring sectors, characterized in that the annular plate comprises on a radially inner portion an annular groove oriented axially upstream and intended to receive a cylindrical rim an outer wall of a combustion chamber arranged upstream of the distributor.

En fonctionnement, les efforts appliqués au distributeur de la turbine haute-pression sont repris par l'élément fixe suspendu au carter externe indépendamment du support des secteurs d'anneau, et ne sont donc plus transmis au support des secteurs d'anneau de sorte que les efforts subis par ce distributeur n'ont plus d'influence sur les jeux radiaux entre les aubes mobiles de la roue et les secteurs d'anneau. Ces jeux radiaux peuvent ainsi être optimisés de manière plus efficace pour améliorer les performances de la turbine.In operation, the forces applied to the distributor of the high-pressure turbine are taken up by the fixed element suspended from the outer casing independently of the support of the ring sectors, and are therefore no longer transmitted to the support of the ring sectors so that the forces undergone by this distributor no longer have any influence on the radial clearances between the moving blades of the wheel and the ring sectors. These radial clearances can thus be optimized more effectively to improve the performance of the turbine.

Selon une autre caractéristique de l'invention, cet élément fixe comprend une tôle annulaire qui s'étend radialement entre le distributeur et le carter externe et qui comporte à son extrémité radialement externe une bride annulaire de fixation sur le carter externe. Cette tôle annulaire peut également comprendre à son extrémité radialement interne un flasque annulaire radial d'appui du distributeur.According to another characteristic of the invention, this fixed element comprises an annular sheet which extends radially between the distributor and the outer casing and which has at its radially outer end an annular clamping flange on the outer casing. This annular sheet may also comprise at its radially inner end a radial annular support flange of the distributor.

La tôle comporte sur une partie radialement interne une rainure annulaire orientée axialement vers l'amont et destinée à recevoir un rebord cylindrique d'une paroi externe de la chambre de combustion située en amont. La partie radialement externe de cette tôle peut également comporter des orifices de passage d'air de ventilation régulièrement répartis autour de son axe de révolution.The sheet comprises on a radially inner portion an annular groove oriented axially upstream and intended to receive a cylindrical rim of an outer wall of the combustion chamber located upstream. The radially outer portion of this sheet may also include ventilation air passage orifices regularly distributed around its axis of revolution.

Le distributeur comprend un rebord annulaire radial s'étendant vers l'extérieur et formant des moyens d'appui axial sur l'élément fixe de la turbine. Ce rebord radial peut comprendre une nervure cylindrique d'appui axial sur l'élément fixe de la turbine. Préférentiellement, ce rebord radial est situé sensiblement au droit des bords d'attaque des aubes du distributeur.The distributor comprises an annular radial flange extending outwardly and forming axial bearing means on the fixed element of the turbine. This radial flange may comprise a cylindrical rib axial support on the fixed element of the turbine. Preferably, this radial flange is located substantially to the right of the leading edges of the vanes of the dispenser.

L'invention concerne encore une tôle annulaire pour une turbomachine telle que décrite ci-dessus, caractérisée en ce qu'elle comprend une paroi tronconique s'étendant entre une bride annulaire radialement externe et un flasque annulaire radial. La paroi tronconique comporte, sur une partie radialement externe, des orifices de passage d'air de ventilation régulièrement répartis autour de l'axe de révolution de la paroi, et sur une partie radialement interne, une rainure annulaire.The invention also relates to an annular sheet for a turbomachine as described above, characterized in that it comprises a frustoconical wall extending between a radially outer annular flange and a radial annular flange. The frustoconical wall comprises, on a radially outer portion, ventilation air passage orifices regularly distributed around the axis of revolution of the wall, and on a radially inner portion, an annular groove.

L'invention sera mieux comprise et d'autres caractéristiques, détails et avantages de celle-ci apparaîtront plus clairement à la lecture de la description qui suit, faite à titre d'exemple non limitatif et en référence aux dessins annexés dans lesquels :

  • la figure 1 est une demi vue schématique partielle en coupe axiale d'une turbine haute-pression de turbomachine selon la technique antérieure à l'invention ;
  • la figure 2 est une demi vue schématique partielle en coupe axiale d'une turbine haute-pression de turbomachine selon l'invention.
The invention will be better understood and other characteristics, details and advantages thereof will appear more clearly on reading the description which follows, given by way of nonlimiting example and with reference to the accompanying drawings in which:
  • the figure 1 is a partial diagrammatic partial view in axial section of a turbomachine high-pressure turbine according to the prior art to the invention;
  • the figure 2 is a partial schematic half view in axial section of a turbomachine high-pressure turbine according to the invention.

La figure 1 représente de manière schématique une partie d'une turbomachine telle qu'un turboréacteur ou un turbopropulseur d'avion comprenant une turbine haute-pression 10 agencée en aval d'une chambre de combustion 12, et en amont d'une turbine basse-pression 14 de la turbomachine.The figure 1 schematically represents a portion of a turbomachine such as a turbojet or an airplane turboprop comprising a high-pressure turbine 10 arranged downstream of a combustion chamber 12, and upstream of a low-pressure turbine 14 of the turbomachine.

La chambre de combustion 12 comprend une paroi de révolution interne 48 et une paroi de révolution externe 50 s'étendant l'une à l'intérieur de l'autre. La paroi interne 48 est reliée à son extrémité aval à une extrémité radialement externe d'une paroi tronconique 52 dont l'extrémité radialement interne comporte une bride annulaire 54 fixée sur un carter interne 56 de la chambre de combustion. La paroi externe 50 de la chambre est reliée à son extrémité aval à une extrémité radialement interne d'une paroi tronconique 58 qui comporte à son extrémité radialement externe une bride annulaire radialement externe 60 de fixation sur une bride annulaire 62 correspondante d'un carter externe 64 de la chambre.The combustion chamber 12 comprises a wall of internal revolution 48 and an outer wall of revolution 50 extending one inside the other. The inner wall 48 is connected at its downstream end to a radially outer end of a frustoconical wall 52 whose radially inner end has an annular flange 54 fixed to an inner casing 56 of the combustion chamber. The outer wall 50 of the chamber is connected at its downstream end to a radially inner end of a frustoconical wall 58 which has at its radially outer end a radially outer annular flange 60 for attachment to a corresponding annular flange 62 of an outer casing 64 of the room.

La turbine haute-pression 10 comprend un seul étage de turbine comportant un distributeur 16 formé d'une rangée annulaire d'aubes fixes de redressement, et une roue à aubes 18 montée rotative en aval du distributeur 16.The high-pressure turbine 10 comprises a single turbine stage comprising a distributor 16 formed of an annular row of stationary vanes for rectification, and a vane wheel 18 rotatably mounted downstream of the distributor 16.

La turbine basse-pression 14 comprend plusieurs étages de turbine, chacun de ces étages comportant également un distributeur et une roue à aubes, seul le distributeur 47 de l'étage basse-pression amont étant visible en figure 1.The low-pressure turbine 14 comprises several turbine stages, each of these stages also comprising a distributor and a paddle wheel, only the distributor 47 of the upstream low-pressure stage being visible in FIG. figure 1 .

La roue 18 de la turbine haute-pression 10 tourne à l'intérieur d'un ensemble sensiblement cylindrique de secteurs d'anneau 20 qui sont disposés circonférentiellement bout à bout et suspendus à un carter de turbine 22 par l'intermédiaire d'un support annulaire 24. Ce support annulaire 24 comprend à sa périphérie interne des moyens 26 d'accrochage des secteurs d'anneau 20 et comprend une paroi tronconique 28 qui s'étend vers l'amont et vers l'extérieur et qui est reliée à son extrémité radialement externe à une bride annulaire radialement externe 30 de fixation sur une bride annulaire 32 correspondante du carter de turbine 22. Cette bride 30 est intercalée axialement entre la bride 60 de la paroi tronconique 58 et la bride 32 du carter de turbine 22 et est serrée axialement entre ces brides par des moyens appropriés du type vis-écrou.The impeller 18 of the high-pressure turbine 10 rotates within a substantially cylindrical assembly of ring sectors 20 which are circumferentially disposed end-to-end and suspended from a turbine casing 22 via a support 24. This annular support 24 comprises at its inner periphery means 26 for hooking ring sectors 20 and comprises a frustoconical wall 28 which extends upstream and outwards and is connected at its end. radially external to a radially outer annular flange 30 for fixing on a corresponding annular flange 32 of the turbine casing 22. This flange 30 is interposed axially between the flange 60 of the frustoconical wall 58 and the flange 32 of the turbine casing 22 and is clamped axially between these flanges by appropriate means of the flange. screw-nut type.

Le support annulaire 24 comprend à sa périphérie interne deux parois annulaire radiales 34, 36, respectivement amont et aval, qui sont reliées l'une à l'autre par une paroi cylindrique 38. Les parois radiales 34, 36 comprennent à leurs extrémités radialement internes des rebords cylindriques 40 orientés vers l'aval qui coopèrent avec des crochets circonférentiels 42, 44 prévus aux extrémités amont et aval des secteurs d'anneau 20. Un organe annulaire de verrouillage 46 à section en C est engagé axialement depuis l'aval sur le rebord cylindrique aval 40 du support et sur les crochets aval 44 des secteurs d'anneau pour assurer le verrouillage de l'ensemble.The annular support 24 comprises at its inner periphery two radial annular walls 34, 36, respectively upstream and downstream, which are connected to one another by a cylindrical wall 38. The radial walls 34, 36 comprise at their radially internal ends downstream cylindrical flanges 40 which cooperate with circumferential hooks 42, 44 provided at the upstream and downstream ends of the ring sectors 20. An annular locking member 46 with a C-section is engaged axially from downstream on the downstream cylindrical rim 40 of the support and on the downstream hooks 44 of the ring sectors to ensure the locking of the assembly.

La paroi tronconique 28 du support annulaire 24 définit avec la paroi tronconique 58 de la chambre une enceinte annulaire 80 qui est alimentée en air de ventilation et de refroidissement par des orifices 82 formés dans la paroi tronconique 58. Des orifices 84 sont formés dans la paroi radiale amont 34 du support annulaire 24 pour établir une communication fluidique entre l'enceinte 80 et une cavité annulaire 86 de refroidissement des secteurs d'anneau 20 délimitée extérieurement par la paroi cylindrique 38 du support annulaire.The frustoconical wall 28 of the annular support 24 defines with the frustoconical wall 58 of the chamber an annular enclosure 80 which is supplied with ventilation and cooling air through orifices 82 formed in the frustoconical wall 58. Orifices 84 are formed in the wall radial upstream 34 of the annular support 24 to establish a fluid communication between the enclosure 80 and an annular cavity 86 for cooling the ring sectors 20 delimited externally by the cylindrical wall 38 of the annular support.

Le distributeur 16 de la turbine haute-pression 10 est formé de deux parois de révolution 66, 68 coaxiales qui s'étendent l'une à l'intérieur de l'autre et qui sont reliées entre elles par les aubes fixes de redressement.The distributor 16 of the high-pressure turbine 10 is formed of two coaxial walls of revolution 66, 68 which extend one inside the other and which are interconnected by the fixed vanes of recovery.

La paroi interne 68 du distributeur comprend une bride annulaire 70 qui s'étend radialement vers l'intérieur depuis sa surface intérieure et qui est fixée par des moyens appropriés sur une bride 72 correspondante prévue à l'extrémité aval du carter interne 56 de la chambre de combustion 12. Les extrémités amont et aval de la paroi interne 68 du distributeur coopèrent à étanchéité avec l'extrémité aval de la paroi interne 48 de la chambre de combustion et avec l'extrémité amont des plateformes des aubes mobiles de la roue 18, respectivement, pour empêcher le passage de gaz depuis la veine annulaire d'écoulement de la turbine radialement vers l'intérieur de la paroi interne 68.The inner wall 68 of the dispenser comprises an annular flange 70 which extends radially inwardly from its inner surface and which is secured by suitable means to a corresponding flange 72 provided at the downstream end of the inner casing 56 of the chamber The upstream and downstream ends of the inner wall 68 of the distributor cooperate to seal with the downstream end of the inner wall 48 of the combustion chamber and with the upstream end of the platforms of the blades of the wheel 18, respectively, to prevent the passage of gas from the annular flow vein of the turbine radially inwardly of the inner wall 68.

La paroi externe 66 du distributeur comprend à chacune de ses extrémités amont et aval une rainure annulaire 74 débouchant radialement vers l'extérieur. Des garnitures annulaires d'étanchéité 76 sont logés dans ces rainures 74 et coopèrent avec des nervures cylindriques 78 formées sur la paroi tronconique 58 et sur la paroi radiale amont 34 du support annulaire 24, respectivement, pour empêcher le passage de gaz depuis la veine de la turbine radialement vers l'extérieur de la paroi externe 66, et inversement, le passage d'air depuis l'enceinte 80 radialement vers l'intérieur dans la veine de la turbine.The outer wall 66 of the distributor comprises at each of its upstream and downstream ends an annular groove 74 opening radially outwards. Annular sealing gaskets 76 are housed in these grooves 74 and cooperate with cylindrical ribs 78 formed on the frustoconical wall 58 and on the upstream radial wall 34 of the annular support 24, respectively, to prevent the passage of gas from the flow duct. the turbine radially outwardly of the outer wall 66, and conversely, the passage of air from the enclosure 80 radially inward in the vein of the turbine.

En fonctionnement de la turbomachine, le distributeur 16 est sollicité vers l'aval par l'écoulement des gaz dans la turbine et sa périphérie externe qui n'est pas reliée rigidement à un élément fixe de la turbine se déplace légèrement vers l'aval jusqu'à ce que l'extrémité radialement externe de la paroi externe 66 du distributeur vienne en appui axial sur une face amont de la paroi radiale amont 34 du support annulaire 24. Le distributeur 16 exerce alors un effort axial dirigé vers l'aval sur le support qui se déforme et entraîne un déplacement des secteurs d'anneau 20 et une modification des jeux radiaux entre les aubes mobiles de la roue 18 et les secteurs d'anneau.In operation of the turbomachine, the distributor 16 is biased downstream by the flow of gas in the turbine and its outer periphery which is not rigidly connected to a fixed element of the turbine moves slightly downstream until the radially outer end of the outer wall 66 of the distributor comes to bear axially on an upstream face of the upstream radial wall 34 of the annular support 24. The distributor 16 then exerts an axial force directed downstream on the support that is deformed and causes a displacement of the ring sectors 20 and a change of the radial clearances between the blades of the wheel 18 and the ring sectors.

L'invention permet d'apporter une solution simple à ce problème grâce à l'appui axial de la périphérie externe du distributeur 16 sur un autre élément fixe de la turbine qui est suspendu au carter externe 22 indépendamment du support 24 de fixation des secteurs d'anneau. Les efforts appliqués au distributeur sont ainsi repris par l'élément fixe et ne sont donc pas transmis au support 24.The invention makes it possible to provide a simple solution to this problem by means of the axial support of the external periphery of the distributor 16 on another fixed element of the turbine which is suspended from the outer casing 22 independently of the support 24 for securing the heating sectors. 'ring. The forces applied to the distributor are thus taken up by the fixed element and are therefore not transmitted to the support 24.

Dans un mode de réalisation de l'invention représenté en figure 2, cet élément fixe est formé par une tôle annulaire 90 qui s'étend radialement autour de l'axe de la turbine et autour du distributeur 16. Cette tôle 90 a une forme sensiblement tronconique et comprend à son extrémité radialement externe une bride annulaire radialement externe 92 qui est serrée axialement entre la bride 62 du carter externe 64 et la bride 30 du support annulaire 24.In one embodiment of the invention shown in figure 2 this fixed element is formed by an annular plate 90 which extends radially around the axis of the turbine and around the distributor 16. This plate 90 has a substantially frustoconical shape and comprises at its radially outer end a radially outer annular flange 92 which is axially clamped between the flange 62 of the outer casing 64 and the flange. 30 of the annular support 24.

L'extrémité radialement interne de la tôle comprend un flasque annulaire radial 94 qui définit du côté amont une face d'appui du distributeur 16. L'extrémité radialement interne de la tôle comprend également une rainure annulaire 96 débouchant axialement vers l'amont.The radially inner end of the sheet comprises a radial annular flange 94 which defines on the upstream side a bearing face of the distributor 16. The radially inner end of the sheet also comprises an annular groove 96 opening axially upstream.

La paroi externe 50 de la chambre est reliée à son extrémité aval à une paroi tronconique 58' qui a une dimension radiale inférieure à la paroi 58 de la figure 1 et qui comporte à son extrémité radialement externe un rebord cylindrique 98 orienté vers l'aval et engagé dans la rainure 96 de la tôle 90. La réduction de la dimension radiale de la paroi tronconique 58' permet de diminuer les écarts de température entre les extrémités radialement interne et externe de cette paroi et ainsi d'augmenter sa durée de vie.The outer wall 50 of the chamber is connected at its downstream end to a frustoconical wall 58 'which has a smaller radial dimension than the wall 58 of the figure 1 and which has at its radially outer end a cylindrical rim 98 facing downstream and engaged in the groove 96 of the sheet 90. The reduction of the radial dimension of the frustoconical wall 58 'makes it possible to reduce the temperature differences between the ends radially inner and outer wall and thus increase its life.

La tôle 90 comporte en outre des orifices 100 de passage d'air de ventilation pour l'alimentation en air de l'enceinte annulaire 80, ces orifices 100 étant régulièrement répartis autour de l'axe de la turbine.The sheet 90 further comprises orifices 100 of ventilation air passage for the air supply of the annular enclosure 80, these orifices 100 being evenly distributed around the axis of the turbine.

Le distributeur 16 de la figure 2 comprend des viroles interne 68 et externe 66 similaires à celles de la figure 1, la virole externe 66 du distributeur comprenant en outre à son extrémité amont un rebord annulaire radial 102 s'étendant vers l'extérieur depuis sa surface extérieure. Ce rebord radial 102 comprend du côté aval une nervure cylindrique 104 en appui axial sur le flasque radial 94 de la tôle 90. Dans l'exemple représenté, le rebord 102 s'étend sensiblement au droit des bords d'attaques des aubes fixes du distributeur.The distributor 16 of the figure 2 includes internal 68 and outer 66 ferrules similar to those of the figure 1 , the outer ring 66 of the dispenser further comprising at its upstream end a radial annular flange 102 extending outwardly from its outer surface. This radial flange 102 comprises on the downstream side a cylindrical rib 104 bearing axially on the radial flange 94 of the sheet 90. In the example shown, the flange 102 extends substantially to the right of the attacking edges of the blades of the distributor .

En fonctionnement, le distributeur qui est sollicité vers l'aval par les gaz chauds sortant de la chambre de combustion transmet une partie des efforts auquel il est soumis à la tôle annulaire 90 par appui axial de son rebord radial 102 sur le flasque 94 de la tôle. La tôle peut éventuellement se déformer élastiquement pour assurer la reprise des efforts auquel est soumis le distributeur. Le flasque 94 de la tôle est à une distance axiale suffisante du support 24 pour ne pas venir en contact avec ce dernier en fonctionnement. Ce support 24 n'est donc plus sollicité vers l'aval par le distributeur 16 ce qui permet de conserver des jeux radiaux constants entre les aubes mobiles et les secteurs d'anneau 20.In operation, the distributor which is urged downstream by the hot gases leaving the combustion chamber transmits a portion of the forces to which it is subjected to the annular plate 90 by axial support of its radial flange 102 on the flange 94 of the sheet. The sheet may possibly deform elastically to ensure the resumption of efforts to which the distributor is subject. The flange 94 of the sheet is at a sufficient axial distance from the support 24 so as not to come into contact with the latter during operation. This support 24 is therefore no longer biased downstream by the distributor 16, which makes it possible to maintain constant radial clearances between the moving blades and the ring sectors 20.

Claims (9)

  1. A turbomachine comprising a combustion chamber (12) and a high-pressure turbine comprising at least one upstream guide vane element (16) formed of an annular array of fixed stator blades and an impeller (18) mounted so as to rotate downstream of the upstream guide vane element and inside an assembly of ring sectors (20) placed circumferentially end-to-end and supported by an annular support (24) suspended from an outer casing (22), the upstream guide vane element comprising, at its radially inner end, means for attachment to an inner casing (56), and, at its radially outer end means for pressing axially on a fixed element (90) that is suspended from the outer casing independently of the annular support of the ring sectors, characterized in that the fixed element (90) comprises, on a radially inner portion, an annular groove (96) oriented axially in the upstream direction and designed to receive a cylindrical rim (98) of an outer wall (58') of the combustion chamber (12) arranged upstream of the upstream guide vane element.
  2. The turbomachine as claimed in claim 1, characterized in that the fixed element is an annular metal sheet (90) which extends radially between the upstream guide vane element (16) and the outer casing (22).
  3. The turbomachine as claimed in claim 2, characterized in that annular metal sheet (90) comprises, at its radially outer end, an annular flange (92) for attachment to the outer casing (22).
  4. The turbomachine as claimed in claim 2 or 3, characterized in that the annular metal sheet (90) comprises, at its radially inner end, a radial annular endpiece for pressing on the upstream guide vane element.
  5. The turbomachine as claimed in one of claims 2 to 4, characterized in that the radially outer portion of the annular metal sheet (90) comprises orifices (100) evenly distributed about its axis of revolution for the passage of ventilation air.
  6. The turbomachine as claimed in one of the preceding claims, characterized in that the upstream guide vane element (16) comprises a radial annular rim (102) extending outward and forming means for pressing axially on the fixed element (90) of the turbine.
  7. The turbomachine as claimed in claim 6, characterized in that the radial rim (102) comprises a cylindrical rib for pressing axially on the fixed element of the turbine.
  8. The turbomachine as claimed in claim 6 or 7, characterized in that the radial rim is situated substantially level with the leading edges of the blades of the upstream guide vane element.
  9. An annular metal sheet (90) for a turbomachine as claimed in one of claims 1 to 8, comprising a frustoconical wall extending between a radially outer annular flange (92) intended to be fixed to an outer casing (22) and a radial annular endpiece (94) defining an abutment face of the guide vane element (16) of the high-pressure turbine, characterized in that the frustoconical wall comprises orifices (100) evenly distributed about its axis over a radially outer portion and an annular groove (96) over a radially inner portion intended to receive a cylindrical rim of an outer wall (58') of a combustion chamber (12).
EP08151865A 2007-02-28 2008-02-25 High-pressure turbine of a turbomachine Active EP1965027B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0701427A FR2913050B1 (en) 2007-02-28 2007-02-28 HIGH-PRESSURE TURBINE OF A TURBOMACHINE

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EP1965027A2 EP1965027A2 (en) 2008-09-03
EP1965027A8 EP1965027A8 (en) 2008-10-29
EP1965027A3 EP1965027A3 (en) 2011-01-26
EP1965027B1 true EP1965027B1 (en) 2012-01-25

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US20080267768A1 (en) 2008-10-30
CA2622116C (en) 2015-08-11
CA2622116A1 (en) 2008-08-28
US8133018B2 (en) 2012-03-13
FR2913050B1 (en) 2011-06-17
EP1965027A2 (en) 2008-09-03
EP1965027A3 (en) 2011-01-26
EP1965027A8 (en) 2008-10-29
FR2913050A1 (en) 2008-08-29

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