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EP2504529B1 - Insulation of a circumferential edge of an outer casing of a turbine engine from a corresponding ring sector - Google Patents

Insulation of a circumferential edge of an outer casing of a turbine engine from a corresponding ring sector Download PDF

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Publication number
EP2504529B1
EP2504529B1 EP10805261.4A EP10805261A EP2504529B1 EP 2504529 B1 EP2504529 B1 EP 2504529B1 EP 10805261 A EP10805261 A EP 10805261A EP 2504529 B1 EP2504529 B1 EP 2504529B1
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EP
European Patent Office
Prior art keywords
annular
bottom wall
outer casing
ring sector
turbine stage
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Application number
EP10805261.4A
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German (de)
French (fr)
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EP2504529A1 (en
Inventor
Fabrice Marcel Noël GARIN
Alain Dominique Gendraud
Gilles Jeannin
Sébastien Jean Laurent Prestel
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA Services SA
SNECMA SAS
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Publication date
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Publication of EP2504529A1 publication Critical patent/EP2504529A1/en
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Publication of EP2504529B1 publication Critical patent/EP2504529B1/en
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Classifications

    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements

Definitions

  • the present invention relates to a turbine stage of a turbomachine, such as an airplane turbojet or turboprop.
  • a turbomachine low-pressure turbine comprises several stages each comprising a distributor formed of an annular row of stationary vanes carried by an outer casing and of a rotor wheel rotatably mounted downstream of the distributor in a cylindrical or frustoconical envelope formed by ring sectors circumferentially attached end to end on the outer casing.
  • Pressurized hot gases leaving the combustion chamber of the turbomachine pass between the vanes of the distributors and flow on the blades of the turbine wheels, which has the effect of raising the temperature of the envelopes formed by the sectors of the turbine. 'ring.
  • the outer casing has at least one circumferential hooking flange of the downstream ends of the ring sectors.
  • each ring sector has a downstream end formed with an annular cavity delimited by an upstream annular abutment, a downstream annular abutment and a bottom wall and this cavity is engaged on the circumferential rim of the casing, the sector ring being held in axial position on the flange by the annular abutments of the cavity.
  • the invention aims in particular to provide a simple, effective and economical solution to this problem.
  • a turbine stage of a turbomachine comprising a rotor wheel mounted inside a sectored ring carried by an outer casing, each ring sector having a downstream end formed with an annular cavity. defined by an upstream annular abutment, a downstream annular abutment and a bottom wall, the outer casing having at least one circumferential flange housed in this cavity for attachment of the downstream end of the ring sector, the bottom wall of the the annular cavity of the ring sector remaining spaced radially from the circumferential rim of the outer casing, so as to provide a thermally insulating space between them and comprises radial positioning means on the circumferential rim.
  • the radial positioning means comprise at least two studs formed projecting on the bottom wall of the annular cavity.
  • the contact surface between the ring sector and the circumferential flange is thus limited to the surface of the end of the pads.
  • the studs are located at the circumferential ends of the bottom wall.
  • the pads are located at a distance from the median axial plane of the bottom wall, so as to ensure a good radial positioning of the ring sector.
  • the pads are located between the median axial plane and the circumferential ends of the bottom wall, so as to limit the wear of the aforementioned elements in contact.
  • each annular abutment has a radial surface extending over the entire circumference of the ring sector, the circumferential rim of the outer casing being mounted without clearance between these surfaces of the annular abutments of the ring sector.
  • the pads may be parallelepipedic.
  • circumferential rim of the outer casing is also advantageous for the circumferential rim of the outer casing to be axially constrained between the annular abutments so as to guarantee the correct positioning of the ring sector on the outer casing.
  • the ratio between the contact surface of the pads and the bottom surface of the annular cavity is between 0.1 and 0.25.
  • the invention further relates to a turbomachine such as a turbojet or an airplane turboprop, characterized in that it comprises a low pressure turbine stage according to the invention.
  • the Figures 1 to 3 represent a turbomachine low-pressure turbine 1 of the prior art, comprising a plurality of stages each comprising a stationary nozzle distributor 2 carried by an outer casing 4 of the turbine, and a rotor wheel 5 mounted downstream of the distributor 2 and rotating in a substantially frustoconical envelope formed by ring sectors 6 carried circumferentially end to end by the casing 4 of the turbine.
  • the distributors 2 comprise walls of internal (not visible) and external revolution 7 which delimit between them an annular stream 8 of gas flow in the turbine and which are radially connected by the blades 3.
  • the rotor wheels 2 are integral with a turbine shaft, not shown, and each comprise outer and inner rings 9 (not visible), the outer ring 9 comprising external radial ribs 10 externally surrounded with a small clearance by the sectors ring 6.
  • Each ring sector 6 comprises a frustoconical wall 11 and a block of abradable material 12 fixed by soldering and / or welding on the radially inner surface of the frustoconical wall 11, this block 12 being of the honeycomb type and being intended to wear by friction on the ribs 10 of the wheel 5 to minimize the radial clearances between the wheel 5 and the ring sectors 6.
  • the frustoconical wall 11 of the ring sector has a downstream end 13 formed with an annular cavity open towards the outside and delimited by an upstream annular abutment 14, a downstream annular abutment 15 and a bottom wall 16.
  • Each annular abutment 14, 15 comprises a surface extending over the entire circumference of the ring sector 6.
  • the bottom wall 16 further has a downstream annular groove 17 and an upstream annular groove 18, allowing the cavity to be machined (see FIG. figure 3 ).
  • each ring sector 6 is engaged in an annular space 19 delimited between two annular flanges of the outer wall 7 of the downstream distributor 2, respectively a radially inner flange 20 and a radially outer flange 21, oriented upstream.
  • the outer casing 4 comprises an inner circumferential rim 22 whose cross section has the shape of a hook facing downstream, engaged in the cavity of the frustoconical wall 11 of the ring sector and held therein by the rim radially. external 21 of the distributor 2.
  • the circumferential flange 22 of the outer casing 4 is axially constrained, between the annular abutments 14, 15 of the ring sector 6, this stress remaining in all phases of operation of the turbomachine.
  • said flange 22 having a radially outer annular surface bearing against the radially outer flange 21 of the distributor and a radially inner annular surface bearing against the bottom wall 16 of the ring sector.
  • An axial clearance j1 is provided between the upstream end of the radially outer flange 21 and the connection zone 23 between the flange 22 and the outer casing 4. This clearance makes it possible to compensate for the effects of expansion and can become almost zero during the operation of the flange. the turbomachine.
  • the ring sector 6 is thus locked, at its downstream end 13, on the circumferential rim 22 of the housing by the distributor 2, the seal between the circumferential flange 22 and the ring sector 6 being provided by the axial stops 14 , And by the bottom wall 16.
  • the ring sector 6 is also hooked at its upstream end on the housing by means whose structure will not be detailed here.
  • the gases from the combustion chamber heat the ring sectors 6, the heat then being transmitted by conduction to the circumferential rim 22 of the housing.
  • the conduction surface or contact surface between the ring sector 6 and the circumferential rim 22 is important, so that in practice the temperature of the rim 22 can reach a limit value, for example 730.degree. is the maximum acceptable for the material conventionally used.
  • FIGS. Figures 4 to 6 A ring sector according to the invention is illustrated in FIGS. Figures 4 to 6 . It differs from that described above in that the bottom wall 16 of the annular cavity comprises at least two studs 24 projecting radially outwardly, the ends of which form bearing surfaces 25 on the circumferential edge 22.
  • the pads 24 are preferably arranged near the upstream stop 14 of the ring sector 6.
  • the ratio between the contact surface of the pads 24 and the bottom surface 16 is between 0.1 and 0.25.
  • such a structure reduces by approximately 40 ° C the temperature of the circumferential rim 22 during operation of the turbomachine.
  • the studs 24 are of parallelepipedal shape and located at the circumferential ends of the bottom wall 16.
  • the studs 24 are located at a distance from a median axial plane P of the bottom wall 16, on either side of it and are located between the median axial plane P and one of the circumferential ends of the bottom wall 16.
  • each ring sector is immobilized circumferentially on the casing by means located in its median plane P, it expands relative to to the housing on either side of the median plane P.
  • the bringing of the pads 24 of the plane P thus reduces their friction on the circumferential rim 22 of the housing.
  • Positioning them at a distance from the plane P ensures a good radial positioning of the ring sector on the circumferential flange 22, avoiding any risk of tilting of the ring sector on one side or the other of the median plane P.
  • the studs 24 could have any other desired shape, for example square, cylindrical, frustoconical, etc.

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

Description

La présente invention concerne un étage de turbine d'une turbomachine, telle qu'un turboréacteur ou un turbopropulseur d'avion.The present invention relates to a turbine stage of a turbomachine, such as an airplane turbojet or turboprop.

Une turbine basse pression de turbomachine comprend plusieurs étages comportant chacun un distributeur formé d'une rangée annulaire d'aubes fixes portées par un carter externe et d'une roue à aubes montée rotative en aval du distributeur dans une enveloppe cylindrique ou tronconique formée par des secteurs d'anneau fixés circonférentiellement bout à bout sur le carter externe.A turbomachine low-pressure turbine comprises several stages each comprising a distributor formed of an annular row of stationary vanes carried by an outer casing and of a rotor wheel rotatably mounted downstream of the distributor in a cylindrical or frustoconical envelope formed by ring sectors circumferentially attached end to end on the outer casing.

Des gaz chaud sous pression sortant de la chambre de combustion de la turbomachine passent entre les aubes des distributeurs et s'écoulent sur les aubes des roues de la turbine, ce qui a pour effet d'élever la température des enveloppes formées par les secteurs d'anneau.Pressurized hot gases leaving the combustion chamber of the turbomachine pass between the vanes of the distributors and flow on the blades of the turbine wheels, which has the effect of raising the temperature of the envelopes formed by the sectors of the turbine. 'ring.

Comme décrit par exemple dans le document FR 2 899 273 ou FR 2887920 au nom du Demandeur, le carter externe comporte au moins un rebord circonférentiel d'accrochage des extrémités aval des secteurs d'anneau.As described for example in the document FR 2 899 273 or FR 2887920 in the name of the Applicant, the outer casing has at least one circumferential hooking flange of the downstream ends of the ring sectors.

De manière connue en soi, chaque secteur d'anneau présente une extrémité aval formée avec une cavité annulaire délimitée par une butée annulaire amont, une butée annulaire aval et une paroi de fond et cette cavité est engagée sur le rebord circonférentiel du carter, le secteur d'anneau étant maintenu en position axiale sur le rebord par les butées annulaires de la cavité.In a manner known per se, each ring sector has a downstream end formed with an annular cavity delimited by an upstream annular abutment, a downstream annular abutment and a bottom wall and this cavity is engaged on the circumferential rim of the casing, the sector ring being held in axial position on the flange by the annular abutments of the cavity.

La surface de contact entre le rebord circonférentiel du carter et chaque secteur d'anneau étant importante, une grande partie de la chaleur de l'anneau est conduite vers le carter externe, par l'intermédiaire de ce rebord circonférentiel. En fonctionnement, ce dernier peut atteindre une température de l'ordre de 730 °C, qui est la limite tolérée pour le matériau utilisé.As the contact area between the circumferential rim of the housing and each ring sector is large, a large part of the heat of the ring is directed towards the outer casing, via this circumferential rim. In operation, the latter can reach a temperature of the order of 730 ° C, which is the limit tolerated for the material used.

Il en résulte des risques importants de dégradation du rebord circonférentiel et du carter externe.This results in significant risks of degradation of the circumferential rim and the outer casing.

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.

A cet effet, elle propose un étage de turbine d'une turbomachine, comprenant une roue de rotor montée à l'intérieur d'un anneau sectorisé porté par un carter externe, chaque secteur d'anneau ayant une extrémité aval formée avec une cavité annulaire délimitée par une butée annulaire amont, une butée annulaire aval et une paroi de fond, le carter externe comportant au moins un rebord circonférentiel logé dans cette cavité pour l'accrochage de l'extrémité aval du secteur d'anneau, la paroi de fond de la cavité annulaire du secteur d'anneau restant écartée radialement du rebord circonférentiel du carter externe, de façon à ménager un espace thermiquement isolant entre eux et comporte des moyens de positionnement radial sur ce rebord circonférentiel.For this purpose, it proposes a turbine stage of a turbomachine, comprising a rotor wheel mounted inside a sectored ring carried by an outer casing, each ring sector having a downstream end formed with an annular cavity. defined by an upstream annular abutment, a downstream annular abutment and a bottom wall, the outer casing having at least one circumferential flange housed in this cavity for attachment of the downstream end of the ring sector, the bottom wall of the the annular cavity of the ring sector remaining spaced radially from the circumferential rim of the outer casing, so as to provide a thermally insulating space between them and comprises radial positioning means on the circumferential rim.

De cette manière, la surface de contact entre le rebord circonférentiel et chaque secteur d'anneau est fortement réduite, limitant ainsi l'échauffement du rebord circonférentiel et, plus généralement, du carter externe.In this way, the contact area between the circumferential flange and each ring sector is greatly reduced, thus limiting the heating of the circumferential flange and, more generally, of the outer casing.

Selon l'invention, les moyens de positionnement radial comprennent au moins deux plots formés en saillie sur la paroi de fond de la cavité annulaire.According to the invention, the radial positioning means comprise at least two studs formed projecting on the bottom wall of the annular cavity.

La surface de contact entre le secteur d'anneau et le rebord circonférentiel est ainsi limitée à la surface de l'extrémité des plots.The contact surface between the ring sector and the circumferential flange is thus limited to the surface of the end of the pads.

Avantageusement, les plots sont situés aux extrémités circonférentielles de la paroi de fond.Advantageously, the studs are located at the circumferential ends of the bottom wall.

Ceci permet d'assurer un bon positionnement du secteur d'anneau vis-à-vis du rebord circonférentiel. Toutefois, la dilatation circonférentielle de l'anneau étant plus importante que celle du rebord circonférentiel, il se produit un déplacement relatif entre les plots et le rebord circonférentiel lors du fonctionnement de la turbomachine, entraînant un frottement et une usure de ceux-ci.This ensures a good positioning of the ring sector vis-à-vis the circumferential edge. However, the circumferential expansion of the ring being greater than that of the circumferential rim, there is a relative displacement between the pads and the circumferential rim when the operation of the turbomachine, causing friction and wear thereof.

Selon une autre caractéristique de l'invention, les plots sont situés à distance du plan axial médian de la paroi de fond, de façon à assurer un bon positionnement radial du secteur d'anneau.According to another characteristic of the invention, the pads are located at a distance from the median axial plane of the bottom wall, so as to ensure a good radial positioning of the ring sector.

De façon préférée, les plots sont situés entre le plan axial médian et les extrémités circonférentielles de la paroi de fond, de façon à limiter l'usure des éléments précités en contact.Preferably, the pads are located between the median axial plane and the circumferential ends of the bottom wall, so as to limit the wear of the aforementioned elements in contact.

Il est avantageux également que chaque butée annulaire comporte une surface radiale s'étendant sur toute la circonférence du secteur d'anneau, le rebord circonférentiel du carter externe étant monté sans jeu entre ces surfaces des butées annulaires du secteur d'anneau.It is also advantageous that each annular abutment has a radial surface extending over the entire circumference of the ring sector, the circumferential rim of the outer casing being mounted without clearance between these surfaces of the annular abutments of the ring sector.

On assure de cette manière l'étanchéité entre le rebord circonférentiel et le secteur d'anneau.This ensures the sealing between the circumferential rim and the ring sector.

Les plots peuvent être parallélépipédiques.The pads may be parallelepipedic.

Il est avantageux également que le rebord circonférentiel du carter externe soit contraint axialement entre les butées annulaires, de façon à garantir le bon positionnement du secteur d'anneau sur le carter externe.It is also advantageous for the circumferential rim of the outer casing to be axially constrained between the annular abutments so as to guarantee the correct positioning of the ring sector on the outer casing.

Préférentiellement, le rapport entre la surface de contact des plots et la surface de fond de la cavité annulaire est compris entre 0,1 et 0,25.Preferably, the ratio between the contact surface of the pads and the bottom surface of the annular cavity is between 0.1 and 0.25.

L'invention concerne en outre une turbomachine telle qu'un turboréacteur ou un turbopropulseur d'avion, caractérisée en ce qu'elle comprend un étage de turbine basse pression selon l'invention.The invention further relates to a turbomachine such as a turbojet or an airplane turboprop, characterized in that it comprises a low pressure turbine stage according to the invention.

L'invention sera mieux comprise et d'autres détails, caractéristiques et avantages de l'invention apparaîtront à la lecture de la description suivante faite à titre d'exemple non limitatif en référence aux dessins annexés dans lesquels :

  • la figure 1 est une vue schématique partielle en coupe axiale d'une turbine basse pression de l'art antérieur ;
  • la figure 2 est une vue agrandie d'une partie de la figure 1 ;
  • la figure 3 est une vue agrandie de la figure 2, représentant le montage de l'extrémité aval d'un secteur d'anneau sur un rebord circonférentiel du carter externe ;
  • la figure 4 est une vue correspondant à la figure 3 et illustrant l'invention ;
  • la figure 5 est une vue partielle et en perspective, d'un secteur d'anneau selon l'invention ;
  • figure 6 est une vue, en perspective, du secteur d'anneau de la figure 5.
The invention will be better understood and other details, characteristics and advantages of the invention will appear on reading the following description given by way of non-limiting example with reference to the accompanying drawings in which:
  • the figure 1 is a partial schematic view in axial section of a low pressure turbine of the prior art;
  • the figure 2 is an enlarged view of some of the figure 1 ;
  • the figure 3 is an enlarged view of the figure 2 , showing the mounting of the downstream end of a ring sector on a circumferential rim of the outer casing;
  • the figure 4 is a view corresponding to the figure 3 and illustrating the invention;
  • the figure 5 is a partial view in perspective of a ring sector according to the invention;
  • figure 6 is a perspective view of the ring sector of the figure 5 .

Les figures 1 à 3 représentent une turbine basse pression 1 de turbomachine de l'art antérieur, comprenant plusieurs étages comportant chacun un distributeur 2 à aubes fixes 3 porté par un carter externe 4 de la turbine, et une roue de rotor 5 montée en aval du distributeur 2 et tournant dans une enveloppe sensiblement tronconique formée par des secteurs d'anneau 6 portés circonférentiellement bout à bout par le carter 4 de la turbine.The Figures 1 to 3 represent a turbomachine low-pressure turbine 1 of the prior art, comprising a plurality of stages each comprising a stationary nozzle distributor 2 carried by an outer casing 4 of the turbine, and a rotor wheel 5 mounted downstream of the distributor 2 and rotating in a substantially frustoconical envelope formed by ring sectors 6 carried circumferentially end to end by the casing 4 of the turbine.

Les distributeurs 2 comprennent des parois de révolution interne (non visible) et externe 7 qui délimitent entre elles une veine annulaire 8 d'écoulement des gaz dans la turbine et qui sont reliées radialement par les aubes 3.The distributors 2 comprise walls of internal (not visible) and external revolution 7 which delimit between them an annular stream 8 of gas flow in the turbine and which are radially connected by the blades 3.

Les roues de rotor 2 sont solidaires d'un arbre de turbine, non représenté, et comprennent chacune des viroles externes 9 et internes (non visible), la virole externe 9 comprenant des nervures radiales externes 10 entourées extérieurement avec un faible jeu par les secteurs d'anneau 6.The rotor wheels 2 are integral with a turbine shaft, not shown, and each comprise outer and inner rings 9 (not visible), the outer ring 9 comprising external radial ribs 10 externally surrounded with a small clearance by the sectors ring 6.

Chaque secteur d'anneau 6 comporte une paroi tronconique 11 et un bloc de matière abradable 12 fixé par brasage et/ou soudage sur la surface radialement interne de la paroi tronconique 11, ce bloc 12 étant du type en nid d'abeille et étant destiné à s'user par frottement sur les nervures 10 de la roue 5 pour minimiser les jeux radiaux entre la roue 5 et les secteurs d'anneaux 6.Each ring sector 6 comprises a frustoconical wall 11 and a block of abradable material 12 fixed by soldering and / or welding on the radially inner surface of the frustoconical wall 11, this block 12 being of the honeycomb type and being intended to wear by friction on the ribs 10 of the wheel 5 to minimize the radial clearances between the wheel 5 and the ring sectors 6.

La paroi tronconique 11 du secteur d'anneau présente une extrémité aval 13 formée avec une cavité annulaire ouverte vers l'extérieur et délimitée par une butée annulaire amont 14, une butée annulaire aval 15 et une paroi de fond 16. Chaque butée annulaire 14, 15 comporte une surface s'étendant sur toute la circonférence du secteur d'anneau 6. La paroi de fond 16 présente en outre une gorge annulaire aval 17 et une gorge annulaire amont 18, permettant l'usinage de la cavité (voir figure 3).The frustoconical wall 11 of the ring sector has a downstream end 13 formed with an annular cavity open towards the outside and delimited by an upstream annular abutment 14, a downstream annular abutment 15 and a bottom wall 16. Each annular abutment 14, 15 comprises a surface extending over the entire circumference of the ring sector 6. The bottom wall 16 further has a downstream annular groove 17 and an upstream annular groove 18, allowing the cavity to be machined (see FIG. figure 3 ).

L'extrémité aval 13 de chaque secteur d'anneau 6 est engagée dans un espace annulaire 19 délimité entre deux rebords annulaires de la paroi externe 7 du distributeur 2 situé en aval, respectivement un rebord radialement interne 20 et un rebord radialement externe 21, orientés vers l'amont.The downstream end 13 of each ring sector 6 is engaged in an annular space 19 delimited between two annular flanges of the outer wall 7 of the downstream distributor 2, respectively a radially inner flange 20 and a radially outer flange 21, oriented upstream.

Le carter externe 4 comporte un rebord circonférentiel interne 22 dont la section a la forme d'un crochet tourné vers l'aval, engagé dans la cavité de la paroi tronconique 11 du secteur d'anneau et maintenu dans celle-ci par le rebord radialement externe 21 du distributeur 2. Le rebord circonférentiel 22 du carter externe 4 est contraint axialement, entre les butées annulaires 14, 15 du secteur d'anneau 6, cette contrainte subsistant dans toutes les phases de fonctionnement de la turbomachine.The outer casing 4 comprises an inner circumferential rim 22 whose cross section has the shape of a hook facing downstream, engaged in the cavity of the frustoconical wall 11 of the ring sector and held therein by the rim radially. external 21 of the distributor 2. The circumferential flange 22 of the outer casing 4 is axially constrained, between the annular abutments 14, 15 of the ring sector 6, this stress remaining in all phases of operation of the turbomachine.

Plus particulièrement, ledit rebord 22 présentant une surface annulaire radialement externe venant en appui contre le rebord radialement externe 21 du distributeur et une surface annulaire radialement interne en appui contre la paroi de fond 16 du secteur d'anneau.More particularly, said flange 22 having a radially outer annular surface bearing against the radially outer flange 21 of the distributor and a radially inner annular surface bearing against the bottom wall 16 of the ring sector.

Un jeu axial j1 est ménagé entre l'extrémité amont du rebord radialement externe 21 et la zone de raccordement 23 entre le rebord 22 et le carter externe 4. Ce jeu permet de compenser les effets de dilatation et peut devenir quasiment nul lors du fonctionnement de la turbomachine.An axial clearance j1 is provided between the upstream end of the radially outer flange 21 and the connection zone 23 between the flange 22 and the outer casing 4. This clearance makes it possible to compensate for the effects of expansion and can become almost zero during the operation of the flange. the turbomachine.

Le secteur d'anneau 6 est ainsi verrouillé, à son extrémité aval 13, sur le rebord circonférentiel 22 du carter par le distributeur 2, l'étanchéité entre le rebord circonférentiel 22 et le secteur d'anneau 6 étant assurée par les butées axiales 14, 15 et par la paroi de fond 16.The ring sector 6 is thus locked, at its downstream end 13, on the circumferential rim 22 of the housing by the distributor 2, the seal between the circumferential flange 22 and the ring sector 6 being provided by the axial stops 14 , And by the bottom wall 16.

Le secteur d'anneau 6 est également accroché, à son extrémité amont, sur le carter par des moyens dont la structure ne sera pas détaillée ici.The ring sector 6 is also hooked at its upstream end on the housing by means whose structure will not be detailed here.

En fonctionnement, les gaz issus de la chambre de combustion chauffent les secteurs d'anneau 6, la chaleur étant ensuite transmise par conduction au rebord circonférentiel 22 du carter.In operation, the gases from the combustion chamber heat the ring sectors 6, the heat then being transmitted by conduction to the circumferential rim 22 of the housing.

Or, la surface de conduction ou surface de contact entre le secteur d'anneau 6 et le rebord circonférentiel 22 est importante, de sorte qu'en pratique la température du rebord 22 peut atteindre une valeur limite, par exemple de 730°C, qui est le maximum acceptable pour le matériau classiquement utilisé.However, the conduction surface or contact surface between the ring sector 6 and the circumferential rim 22 is important, so that in practice the temperature of the rim 22 can reach a limit value, for example 730.degree. is the maximum acceptable for the material conventionally used.

Un secteur d'anneau selon l'invention est illustré aux figures 4 à 6. Il diffère de celui décrit précédemment en ce que la paroi de fond 16 de la cavité annulaire comprend au moins deux plots 24 en saillie radialement vers l'extérieur, dont les extrémités forment des surfaces d'appui 25 sur le rebord circonférentiel 22. Les plots 24 sont préférentiellement disposés à proximité de la butée amont 14 du secteur d'anneau 6.A ring sector according to the invention is illustrated in FIGS. Figures 4 to 6 . It differs from that described above in that the bottom wall 16 of the annular cavity comprises at least two studs 24 projecting radially outwardly, the ends of which form bearing surfaces 25 on the circumferential edge 22. The pads 24 are preferably arranged near the upstream stop 14 of the ring sector 6.

De cette manière, la surface de contact entre le rebord circonférentiel 22 et le secteur d'anneau 6 est réduite et une lame d'air isolante est formée entre la paroi de fond 16 et la paroi interne du rebord circonférentiel 22.In this way, the contact surface between the circumferential flange 22 and the ring sector 6 is reduced and an insulating air plate is formed between the bottom wall 16 and the inner wall of the circumferential flange 22.

Le rapport entre la surface de contact des plots 24 et la surface de fond 16 est compris entre 0,1 et 0,25.The ratio between the contact surface of the pads 24 and the bottom surface 16 is between 0.1 and 0.25.

En pratique, une telle structure permet de réduire d'environ 40°C la température du rebord circonférentiel 22 lors du fonctionnement de la turbomachine.In practice, such a structure reduces by approximately 40 ° C the temperature of the circumferential rim 22 during operation of the turbomachine.

Dans la forme de réalisation des figures 5 et 6, les plots 24 sont de forme parallélépipédique et situés aux extrémités circonférentielles de la paroi de fond 16.In the embodiment of the Figures 5 and 6 , the studs 24 are of parallelepipedal shape and located at the circumferential ends of the bottom wall 16.

De préférence, les plots 24 sont situés à distance d'un plan axial médian P de la paroi de fond 16, de part et d'autre de celui-ci et se trouvent entre le plan axial médian P et l'une des extrémités circonférentielles de la paroi de fond 16. En effet, comme chaque secteur d'anneau est immobilisé circonférentiellement sur le carter par des moyens situés dans son plan médian P, il se dilate par rapport au carter de part et d'autre du plan médian P. Le fait de rapprocher les plots 24 du plan P réduit donc leurs frottements sur le rebord circonférentiel 22 du carter. Les situer à distance du plan P assure un bon positionnement radial du secteur d'anneau sur le rebord circonférentiel 22 en évitant tout risque de basculement du secteur d'anneau d'un côté ou de l'autre du plan médian P.Preferably, the studs 24 are located at a distance from a median axial plane P of the bottom wall 16, on either side of it and are located between the median axial plane P and one of the circumferential ends of the bottom wall 16. Indeed, since each ring sector is immobilized circumferentially on the casing by means located in its median plane P, it expands relative to to the housing on either side of the median plane P. The bringing of the pads 24 of the plane P thus reduces their friction on the circumferential rim 22 of the housing. Positioning them at a distance from the plane P ensures a good radial positioning of the ring sector on the circumferential flange 22, avoiding any risk of tilting of the ring sector on one side or the other of the median plane P.

Par ailleurs, les plots 24 pourraient avoir toute autre forme souhaitée, par exemple carrée, cylindrique, tronconique, etc.Moreover, the studs 24 could have any other desired shape, for example square, cylindrical, frustoconical, etc.

Claims (9)

  1. A turbine stage (1) of a turbine engine, the stage comprising a rotor wheel (5) mounted inside a sectorized ring carried by an outer casing (4), each ring sector (6) having a downstream end (13) formed with an annular cavity defined by an upstream annular abutment (14), a downstream annular abutment (15), and a bottom wall (16), the outer casing (4) having at least a circumferential rim (22) housed in said annular cavity in order to attach the downstream end (13) of the ring sector (6), the bottom wall (16) of the annular cavity of the ring sector (6) remaining radially spaced apart from the circumferential rim (22) of the outer casing (4) so as to provide a thermally insulating space between them and including radial positioning means (24) acting on the circumferential rim (22), characterized in that the radial positioning means (24) are formed by at least two studs (24) projecting from the bottom wall (16) of the annular cavity.
  2. A turbine stage (1) according to claim 1, characterized in that the studs (24) are situated at the circumferential ends of the bottom wall (16).
  3. A turbine stage (1) according to claim 1, characterized in that the studs (24) are situated at a distance from the axial midplane (P) of the bottom wall (16).
  4. A turbine stage (1) according to claim 3, characterized in that the studs (24) are situated between the axial midplane (P) and the circumferential ends of the bottom wall (16).
  5. A turbine stage (1) according to any one of claims 1 to 4, characterized in that each annular abutment (14, 15) includes a radial surface extending over the entire circumference of the annular sector, the circumferential rim (22) of the outer casing (4) being mounted without clearance between the radial surfaces of the annular abutments (14, 15) of the ring sector (6).
  6. A turbine stage (1) according to claim 5, characterized in that the circumferential rim (22) of the outer casing (4) is axially stressed between the annular abutments (14, 15).
  7. A turbine stage (1) according to any one of claims 1 to 6, characterized in that the studs (24) are of rectangular shape.
  8. A turbine stage (1) according to any one of claims 1 to 7, characterized in that the ratio between the contact area of the studs (24) and the area of the bottom wall (16) of the annular cavity lies in the range 0.1 to 0.25.
  9. A turbine engine such as an airplane turboprop or turbojet, the turbine engine being characterized in that it includes a turbine stage (1) according to any one of claims 1 to 8.
EP10805261.4A 2009-11-25 2010-11-24 Insulation of a circumferential edge of an outer casing of a turbine engine from a corresponding ring sector Active EP2504529B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0905657A FR2952965B1 (en) 2009-11-25 2009-11-25 INSULATING A CIRCONFERENTIAL SIDE OF AN EXTERNAL TURBOMACHINE CASTER WITH RESPECT TO A CORRESPONDING RING SECTOR
PCT/FR2010/052495 WO2011064496A1 (en) 2009-11-25 2010-11-24 Insulation of a circumferential edge of an outer casing of a turbine engine from a corresponding ring sector

Publications (2)

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EP2504529A1 EP2504529A1 (en) 2012-10-03
EP2504529B1 true EP2504529B1 (en) 2013-10-09

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EP10805261.4A Active EP2504529B1 (en) 2009-11-25 2010-11-24 Insulation of a circumferential edge of an outer casing of a turbine engine from a corresponding ring sector

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EP (1) EP2504529B1 (en)
JP (1) JP5771217B2 (en)
CN (1) CN102630268B (en)
BR (1) BR112012012393B1 (en)
CA (1) CA2781936C (en)
FR (1) FR2952965B1 (en)
RU (1) RU2548535C2 (en)
WO (1) WO2011064496A1 (en)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10344621B2 (en) * 2012-04-27 2019-07-09 General Electric Company System and method of limiting axial movement between components in a turbine assembly
ES2620482T3 (en) * 2012-08-09 2017-06-28 MTU Aero Engines AG Waterproofing the flow channel of a turbomachine machine
JP6233578B2 (en) * 2013-12-05 2017-11-22 株式会社Ihi Turbine
US10648362B2 (en) 2017-02-24 2020-05-12 General Electric Company Spline for a turbine engine
US10655495B2 (en) 2017-02-24 2020-05-19 General Electric Company Spline for a turbine engine
US20180347399A1 (en) * 2017-06-01 2018-12-06 Pratt & Whitney Canada Corp. Turbine shroud with integrated heat shield
FR3071273B1 (en) * 2017-09-21 2019-08-30 Safran Aircraft Engines TURBINE SEALING ASSEMBLY FOR TURBOMACHINE
US10982559B2 (en) * 2018-08-24 2021-04-20 General Electric Company Spline seal with cooling features for turbine engines
FR3096395B1 (en) * 2019-05-21 2021-04-23 Safran Aircraft Engines Turbine for a turbomachine, such as a turbojet or an aircraft turboprop
FR3100838B1 (en) * 2019-09-13 2021-10-01 Safran Aircraft Engines TURBOMACHINE SEALING RING
FR3109402B1 (en) * 2020-04-15 2022-07-15 Safran Aircraft Engines Turbine for a turbomachine

Family Cites Families (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4687413A (en) * 1985-07-31 1987-08-18 United Technologies Corporation Gas turbine engine assembly
FR2635562B1 (en) * 1988-08-18 1993-12-24 Snecma TURBINE STATOR RING ASSOCIATED WITH A TURBINE HOUSING BINDING SUPPORT
US5553999A (en) * 1995-06-06 1996-09-10 General Electric Company Sealable turbine shroud hanger
US5641267A (en) * 1995-06-06 1997-06-24 General Electric Company Controlled leakage shroud panel
JP3592932B2 (en) * 1998-05-22 2004-11-24 三菱重工業株式会社 Contact structure between gas turbine vane and blade ring
DE19938443A1 (en) 1999-08-13 2001-02-15 Abb Alstom Power Ch Ag Fastening and fixing device
US6435820B1 (en) * 1999-08-25 2002-08-20 General Electric Company Shroud assembly having C-clip retainer
FR2800797B1 (en) * 1999-11-10 2001-12-07 Snecma ASSEMBLY OF A RING BORDING A TURBINE TO THE TURBINE STRUCTURE
DE10122464C1 (en) * 2001-05-09 2002-03-07 Mtu Aero Engines Gmbh Mantle ring for low pressure turbine stage of gas turbine uses segments each having seal carrier and relatively spaced security element with minimum contact between them
US6733235B2 (en) * 2002-03-28 2004-05-11 General Electric Company Shroud segment and assembly for a turbine engine
US6902371B2 (en) * 2002-07-26 2005-06-07 General Electric Company Internal low pressure turbine case cooling
US20040219011A1 (en) 2003-05-02 2004-11-04 General Electric Company High pressure turbine elastic clearance control system and method
US7186078B2 (en) * 2003-07-04 2007-03-06 Ishikawajima-Harima Heavy Industries Co., Ltd. Turbine shroud segment
JP4200846B2 (en) * 2003-07-04 2008-12-24 株式会社Ｉｈｉ Shroud segment
JP4269829B2 (en) * 2003-07-04 2009-05-27 株式会社Ｉｈｉ Shroud segment
US6942203B2 (en) * 2003-11-04 2005-09-13 General Electric Company Spring mass damper system for turbine shrouds
FR2867224B1 (en) * 2004-03-04 2006-05-19 Snecma Moteurs AXIAL AXIS HOLDING DEVICE FOR RING OF A TURBOMACHINE HIGH-PRESSURE TURBINE
US7217089B2 (en) * 2005-01-14 2007-05-15 Pratt & Whitney Canada Corp. Gas turbine engine shroud sealing arrangement
FR2887920B1 (en) * 2005-06-29 2010-09-10 Snecma DEVICE FOR FASTENING RING SECTIONS ON A TURBINE HOUSING
FR2899275A1 (en) * 2006-03-30 2007-10-05 Snecma Sa Ring sector fixing device for e.g. turboprop of aircraft, has cylindrical rims engaged on casing rail, where each cylindrical rim comprises annular collar axially clamped on casing rail using annular locking unit
FR2899273B1 (en) * 2006-03-30 2012-08-17 Snecma DEVICE FOR FASTENING RING SECTIONS ON A TURBINE HOUSING OF A TURBOMACHINE
FR2931197B1 (en) * 2008-05-16 2010-06-18 Snecma LOCKING SECTOR OF RING SECTIONS ON A TURBOMACHINE CASING, COMPRISING AXIAL PASSAGES FOR ITS PRETENSION

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RU2548535C2 (en) 2015-04-20
JP2013512382A (en) 2013-04-11
BR112012012393B1 (en) 2020-11-10
EP2504529A1 (en) 2012-10-03
CN102630268A (en) 2012-08-08
CA2781936A1 (en) 2011-06-03
FR2952965A1 (en) 2011-05-27
FR2952965B1 (en) 2012-03-09
WO2011064496A1 (en) 2011-06-03
US8961117B2 (en) 2015-02-24
RU2012126095A (en) 2013-12-27
CA2781936C (en) 2017-12-12
US20120288362A1 (en) 2012-11-15
CN102630268B (en) 2015-07-08
JP5771217B2 (en) 2015-08-26
BR112012012393A2 (en) 2016-04-12

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