EP1847686B1 - Device for fixing ring sectors on the casing of a jet engine - Google Patents

Device for fixing ring sectors on the casing of a jet engine Download PDF

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Publication number
EP1847686B1
EP1847686B1 EP07290301A EP07290301A EP1847686B1 EP 1847686 B1 EP1847686 B1 EP 1847686B1 EP 07290301 A EP07290301 A EP 07290301A EP 07290301 A EP07290301 A EP 07290301A EP 1847686 B1 EP1847686 B1 EP 1847686B1
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EP
European Patent Office
Prior art keywords
turbine
annular
locking member
ring sectors
casing
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EP07290301A
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German (de)
French (fr)
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EP1847686A1 (en
Inventor
Didier Durand
Dominique Gehan
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Safran Aircraft Engines SAS
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SNECMA SAS
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Publication of EP1847686A1 publication Critical patent/EP1847686A1/en
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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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • 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

Definitions

  • the present invention relates to a device for fixing ring sectors on a turbine casing in a turbomachine, such as in particular an airplane turbojet or turboprop engine.
  • a turbomachine turbine comprises a plurality of stages, each comprising a distributor formed of an annular row of stationary vanes carried by a casing of the turbine and a rotatably mounted wheel downstream of the distributor in a cylindrical or frustoconical envelope formed by ring sectors. circumferentially attached end-to-end on the turbine casing.
  • the ring sectors comprise at their upstream ends circumferential means such as cylindrical flanges engaged with a small axial clearance in a radially inner annular groove of an annular housing rail and held radially in this groove by an annular locking member to C section which is engaged axially from upstream on the casing rail and on the cylindrical edges of the ring sectors. These sectors are held axially by their cylindrical flanges engaged in the groove of the crankcase rail (see for example the document US 2005/002779 A1 ).
  • EP-A-1 079 076 discloses ring sectors comprising at their upstream and downstream ends means for hooking on a casing of a turbine.
  • edges of the ring sectors are "convergecambrés" relative to the crankcase rail and the locking member, that is to say that the edges of the ring sectors have a radius of curvature greater than that of the crankcase rail and the locking member, which makes it possible to mount the rims of the ring sectors with a certain radial prestressing between the bottom of the groove of the rail and the locking member and thus to limit the axial displacements of the edges of the ring areas in the gorge.
  • the edges of the ring sectors can, by moving downstream in the groove, disengage from the locking member, which results in a tilting of the ring sectors to the axis of the turbine and a risk of contact between the ring sectors and the turbine wheel, may cause destruction of the ring sectors and the wheel.
  • the invention aims in particular to provide a simple, effective and economical solution to this problem.
  • a turbomachine turbine comprising at least one distributor formed of an annular row of stationary vanes carried by a casing of the turbine, and a rotatably mounted wheel downstream of the distributor in a substantially frustoconical casing formed by ring sectors circumferentially fixed end-to-end only at their upstream ends on the turbine casing, the ring sectors comprising at their upstream ends circumferential fastening means which are engaged on a casing rail and which are held by an annular locking member of C section axially engaged on the housing rail and on the hooking means of the ring sectors, characterized in that the attachment means of the ring sectors are interposed axially between the body locking and crankcase rail and axially clamped on the crankcase rail by the locking member.
  • the attachment means of the ring sectors are axially immobilized on the casing rail by the locking member, which prevents the attachment means from frictionally rubbing the casing rail and their prohibited from exiting the locking member.
  • the attachment means of the ring sectors are also immobilized radially on the casing rail by the locking member.
  • the device according to the invention also has the advantage of allowing attachment of the ring sectors on a casing rail regardless of the wear thereof.
  • the attachment means comprise an annular flange extending radially outwardly to the upstream end of each ring sector.
  • each ring sector is preferably formed at the upstream end of a cylindrical rim of the ring sector, and is for example axially clamped between a radial wall of the annular locking member and an upstream end of the ring sector. crankcase rail.
  • the locking member is of C-section and its radial wall is connected at its ends to cylindrical walls extending downstream and engaged respectively outside the casing rail and inside the cylindrical rim of each ring sector.
  • the locking member is interposed axially between the flanges of the ring sectors and an outer annular wall of a distributor of the turbine, so as to exert on the annular flanges an axial force downstream when the distributor is itself even urged downstream by the flow of gas passing through the turbine.
  • This axial force exerted by the locking member is sufficient to axially immobilize the flanges of the upstream edges of the ring sectors on the casing rail.
  • the invention also relates to a turbomachine, such as an airplane turbojet or turboprop, comprising a turbine as described above.
  • the first stage or upstream stage of the low-pressure turbine 10 partially shown in FIG. figure 1 comprises a distributor 12, 13 formed of an annular row of fixed blades 14 carried by a housing 16 of the turbine, and a wheel 18 mounted downstream of the distributor 12, 13 and rotating in a substantially frustoconical casing formed by sectors of ring 20 carried circumferentially end to end by the casing 16 of the turbine.
  • the distributor 12, 13 comprises walls of external revolution 22 and internal (not visible), respectively, which delimit between them the annular flow vein of the gas in the turbine and between which radially extend the blades 14.
  • the means of attachment of the distributor comprise at least one outer cylindrical rim 24 oriented upstream and intended to be engaged in an annular groove 26 facing downstream of the housing 16.
  • the wheel 18 is carried by a turbine shaft (not shown) and comprises external and internal (not visible) ferrules 28, the outer ferrule 28 comprising external annular ribs 30 externally surrounded with a small clearance by the ring sectors 20 .
  • Each ring sector 20 comprises a frustoconical wall 32 and a block 34 of abradable material fixed by soldering and / or welding on the radially inner surface of the wall 32, this block 34 being of the honeycomb type and intended for wear by friction on the ribs 30 of the wheel to minimize the radial clearances between the wheel and the ring sectors 20.
  • the downstream ends of the ring sectors 20 are engaged from upstream in an annular space 36 delimited by a cylindrical rim 38 facing upstream of the outer wall 22 of the distributor 13 located downstream of the ring sectors, a part, and a cylindrical rim 40 of the housing on which is attached this distributor, on the other hand.
  • the ring sectors 20 are held radially at their downstream ends by radial support towards the outside of their walls 32 on a radially inner cylindrical face of the flange 40 of the casing, and by radial support towards the inside of their blocks 34 of material abradable on a radially outer cylindrical face of the cylindrical rim 38 of the distributor.
  • the walls 32 of the ring sectors each comprise at their downstream ends a tab 42 extending axially downstream and intended to be engaged in a corresponding cavity 44 of the downstream distributor 13 to immobilize in rotation the ring sectors 20 around of the turbine axis.
  • the frustoconical walls 32 of the ring sectors 20 comprise at their upstream ends cylindrical rims 46 facing upstream which are engaged with a small axial clearance in a radially inner annular groove 48 of an annular rail 50 of the casing 16.
  • the flanges 46 are held radially in this groove by means of a locking member 52 formed of a split ring C or U section axially engaged from upstream on the annular rail 50 of the housing and on the upstream edges 46 of the ring sectors.
  • the locking member 52 comprises two cylindrical walls 54 and 56 extending downstream, radially outer and radially inner respectively, which are connected together at their upstream ends by a radial wall 58, and which are engaged respectively to the outside the rail 50 and inside the cylindrical flanges 46 of the ring sectors 20.
  • the radial wall 58 of the locking member 52 is interposed axially between the upstream end of the casing rail 50 and an outer annular wall 60 of the distributor 12 located upstream of the sectors. ring 20, to prevent the locking member 52 from moving axially upstream and disengage from the housing rail 50 and flanges 46 of the ring sectors.
  • the radius of curvature of the locking member 52 and the rail 50 is smaller than that of the flanges 46 of the ring sectors 20, which makes it possible to mount with a certain radial prestress the flanges 46 of the ring sectors in the groove. 48 of the rail, these ring sectors being locally in radial support on the bottom of the groove 48 and on the radially inner wall 56 of the locking member, respectively.
  • the flanges 46 of the ring sectors 20 vibrate axially and frictionally use the upstream and downstream faces of the groove 46 of the rail.
  • the flanges 46 can move downstream to slide on the radially inner wall 56 of the locking member and disengage from the locking member, which can cause at least the destruction of the blocks 34 of abradable material ring sectors which come into contact with the annular ribs 30 of the wheel 18.
  • the invention makes it possible to provide a simple solution to this problem by axially immobilizing the flanges of the ring sectors on the casing rail by the locking member.
  • the upstream cylindrical flanges 70 of the ring sectors 20 each comprise at their upstream end an annular flange 72 which extends substantially radially outwards and which is clamped axially on the casing rail 50 by the locking member 80 .
  • the locking member 80 comprises two cylindrical walls 84 and 86 extending downstream, radially outer and radially inner respectively, which are interconnected at their upstream ends by a radial wall 82 which has a greater radial dimension than the radial dimension of the wall 58 of the locking member 52 of the prior art ( figure 1 ).
  • the cylindrical flange 70 of the ring sector is longer than in the prior art, so that the annular flange 72 can be engaged between the radial wall 82 of the locking member and the upstream end of the rail of the housing.
  • the radially outer cylindrical wall 84 of the locking member 80 is engaged outside the rail 50 and its radially inner wall 86 is engaged inside the cylindrical flanges 70 of the ring sectors 20, these flanges 70 being interposed radially between the inner cylindrical wall 86 of the member and the upstream end face of the rail 50.
  • the radius of curvature of the locking member 80 and the rail 50 is smaller than that of the flanges 70 of the ring sectors 20, which allows to mount with some radial prestressing the edges 70 of the sectors ring on the rail 50 and on the locking member.
  • the radial wall 82 of the locking member 80 is interposed axially between the annular flanges 72 of the ring sectors 70 and the outer annular wall 60 of the distributor 12 situated upstream of the ring sectors 20.
  • this distributor 12 In operation of the turbomachine, this distributor 12 is biased downstream by the flow of the gases and exerts an axial force directed downstream on the annular flanges 72 of the ring sectors 70 through the organ 80. This axial force is sufficient to maintain axially tight collars 72 of the ring sectors on the housing rail 50.
  • the flanges 72 of the ring sectors are thus immobilized axially and radially by the locking member 80 on the casing rail 80, and therefore can not wear the housing rail by friction.
  • the ring sectors 20 according to the invention can be hooked onto a used housing rail 50 as shown by the dashed lines 90, which makes it possible to repair the upstream stage of the low turbine at a lower cost. -pressure without touching the turbine housing.
  • the upstream flange 70 of the ring sectors does not bear flange 72 and extends axially to the radial wall 82 of the locking member, along the cylindrical portion of the crankcase rail. which has no radial rim at its upstream end.
  • the downstream end of the flange 70 is applied axially on the casing rail by the locking member 80.

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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 un dispositif de fixation de secteurs d'anneau sur un carter de turbine dans une turbomachine, telle en particulier qu'un turboréacteur ou un turbopropulseur d'avion.The present invention relates to a device for fixing ring sectors on a turbine casing in a turbomachine, such as in particular an airplane turbojet or turboprop engine.

Une turbine de turbomachine comprend plusieurs étages comportant chacun un distributeur formé d'une rangée annulaire d'aubes fixes portées par un carter de la turbine et une roue 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 de la turbine.A turbomachine turbine comprises a plurality of stages, each comprising a distributor formed of an annular row of stationary vanes carried by a casing of the turbine and a rotatably mounted wheel downstream of the distributor in a cylindrical or frustoconical envelope formed by ring sectors. circumferentially attached end-to-end on the turbine casing.

Les secteurs d'anneau comprennent à leurs extrémités amont des moyens circonférentiels tels que des rebords cylindriques engagés avec un petit jeu axial dans une gorge annulaire radialement interne d'un rail annulaire de carter et maintenus radialement dans cette gorge par un organe annulaire de verrouillage à section en C qui est engagé axialement depuis l'amont sur le rail de carter et sur les rebords cylindriques des secteurs d'anneau. Ces secteurs sont maintenus axialement par leurs rebords cylindriques engagés dans la gorge du rail de carter (voir par exemple le document US 2005/002779 A1 ).The ring sectors comprise at their upstream ends circumferential means such as cylindrical flanges engaged with a small axial clearance in a radially inner annular groove of an annular housing rail and held radially in this groove by an annular locking member to C section which is engaged axially from upstream on the casing rail and on the cylindrical edges of the ring sectors. These sectors are held axially by their cylindrical flanges engaged in the groove of the crankcase rail (see for example the document US 2005/002779 A1 ).

Le document EP-A-1 079 076 décrit des secteurs d'anneau comprenant à leurs extrémités amont et aval des moyens d'accrochage sur un carter d'une turbine.The document EP-A-1 079 076 discloses ring sectors comprising at their upstream and downstream ends means for hooking on a casing of a turbine.

Les rebords précités des secteurs d'anneau sont « décambrés » par rapport au rail de carter et à l'organe de verrouillage, c'est-à-dire que les rebords des secteurs d'anneau ont un rayon de courbure supérieur à celui du rail de carter et de l'organe de verrouillage, ce qui permet de monter les rebords des secteurs d'anneau avec une certaine précontrainte radiale entre le fond de la gorge du rail et l'organe de verrouillage et de limiter ainsi les déplacements axiaux des rebords des secteurs d'anneau dans la gorge.The aforementioned edges of the ring sectors are "décambrés" relative to the crankcase rail and the locking member, that is to say that the edges of the ring sectors have a radius of curvature greater than that of the crankcase rail and the locking member, which makes it possible to mount the rims of the ring sectors with a certain radial prestressing between the bottom of the groove of the rail and the locking member and thus to limit the axial displacements of the edges of the ring areas in the gorge.

En fonctionnement, les dilatations thermiques différentielles des secteurs d'anneau et du carter entraînent une augmentation de cette précontrainte radiale qui est appliquée en des zones de contact ponctuelles entre les rebords des secteurs d'anneau et le rail de carter. Mais cette précontrainte disparaît progressivement dans le temps par usure des rebords des secteurs d'anneau et du carter dans ces zones de contact. Lorsque cette précontrainte radiale est nulle, les rebords des secteurs d'anneau peuvent se déplacer axialement dans la gorge du carter et user par frottement les faces amont et aval de la gorge du carter.In operation, the differential thermal expansions of the ring sectors and of the casing cause an increase in this radial prestress which is applied in point contact zones between the flanges of the ring sectors and the casing rail. But this prestressing gradually disappears in time by wear of the edges of the ring sectors and the housing in these contact zones. When this radial prestressing is zero, the flanges of the ring sectors can move axially in the groove of the housing and wear by friction the upstream and downstream faces of the groove of the housing.

Lorsque cette usure dépasse une certaine valeur, les rebords des secteurs d'anneau peuvent, en se déplaçant vers l'aval dans la gorge, se désengager de l'organe de verrouillage, ce qui se traduit par un basculement des secteurs d'anneau vers l'axe de la turbine et un risque de contact entre les secteurs d'anneau et la roue de turbine, susceptible de provoquer une destruction des secteurs d'anneau et de la roue.When this wear exceeds a certain value, the edges of the ring sectors can, by moving downstream in the groove, disengage from the locking member, which results in a tilting of the ring sectors to the axis of the turbine and a risk of contact between the ring sectors and the turbine wheel, may cause destruction of the ring sectors and the wheel.

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 turbine de turbomachine, comprenant au moins un distributeur formé d'une rangée annulaire d'aubes fixes portées par un carter de la turbine, et une roue montée rotative en aval du distributeur dans une enveloppe sensiblement tronconique formée par des secteurs d'anneau fixés circonférentiellement bout à bout uniquement à leurs extrémités amont sur le carter de la turbine, les secteurs d'anneau comprenant à leurs extrémités amont des moyens circonférentiels d'accrochage qui sont engagés sur un rail de carter et qui sont maintenus par un organe annulaire de verrouillage à section en C engagé axialement sur le rail de carter et sur les moyens d'accrochage des secteurs d'anneau, caractérisée en ce que les moyens d'accrochage des secteurs d'anneau sont interposés axialement entre l'organe de verrouillage et le rail de carter et serrés axialement sur le rail de carter par l'organe de verrouillage.To this end, it proposes a turbomachine turbine, comprising at least one distributor formed of an annular row of stationary vanes carried by a casing of the turbine, and a rotatably mounted wheel downstream of the distributor in a substantially frustoconical casing formed by ring sectors circumferentially fixed end-to-end only at their upstream ends on the turbine casing, the ring sectors comprising at their upstream ends circumferential fastening means which are engaged on a casing rail and which are held by an annular locking member of C section axially engaged on the housing rail and on the hooking means of the ring sectors, characterized in that the attachment means of the ring sectors are interposed axially between the body locking and crankcase rail and axially clamped on the crankcase rail by the locking member.

Grâce à l'invention, les moyens d'accrochage des secteurs d'anneau sont immobilisés axialement sur le rail de carter par l'organe de verrouillage, ce qui empêche les moyens d'accrochage d'user par frottement le rail de carter et leur interdit de sortir de l'organe de verrouillage.Thanks to the invention, the attachment means of the ring sectors are axially immobilized on the casing rail by the locking member, which prevents the attachment means from frictionally rubbing the casing rail and their prohibited from exiting the locking member.

Avantageusement, les moyens d'accrochage des secteurs d'anneau sont également immobilisés radialement sur le rail de carter par l'organe de verrouillage.Advantageously, the attachment means of the ring sectors are also immobilized radially on the casing rail by the locking member.

Le dispositif selon l'invention a par ailleurs l'avantage de permettre une fixation des secteurs d'anneau sur un rail de carter indépendamment de l'usure de celui-ci.The device according to the invention also has the advantage of allowing attachment of the ring sectors on a casing rail regardless of the wear thereof.

Selon un mode préféré de réalisation de l'invention, les moyens d'accrochage comprennent une collerette annulaire s'étendant radialement vers l'extérieur à l'extrémité amont de chaque secteur d'anneau.According to a preferred embodiment of the invention, the attachment means comprise an annular flange extending radially outwardly to the upstream end of each ring sector.

La collerette annulaire de chaque secteur d'anneau est préférentiellement formée à l'extrémité amont d'un rebord cylindrique du secteur d'anneau, et est par exemple serrée axialement entre une paroi radiale de l'organe annulaire de verrouillage et une extrémité amont du rail de carter.The annular flange of each ring sector is preferably formed at the upstream end of a cylindrical rim of the ring sector, and is for example axially clamped between a radial wall of the annular locking member and an upstream end of the ring sector. crankcase rail.

L'organe de verrouillage est à section en C et sa paroi radiale est reliée à ses extrémités à des parois cylindriques s'étendant vers l'aval et engagées respectivement à l'extérieur du rail de carter et à l'intérieur du rebord cylindrique de chaque secteur d'anneau.The locking member is of C-section and its radial wall is connected at its ends to cylindrical walls extending downstream and engaged respectively outside the casing rail and inside the cylindrical rim of each ring sector.

L'organe de verrouillage est interposé axialement entre les collerettes des secteurs d'anneau et une paroi annulaire externe d'un distributeur de la turbine, de façon à exercer sur les collerettes annulaires un effort axial vers l'aval lorsque le distributeur est lui-même sollicité vers l'aval par le flux de gaz passant dans la turbine. Cet effort axial exercé par l'organe de verrouillage est suffisant pour immobiliser axialement les collerettes des rebords amont des secteurs d'anneau sur le rail de carter.The locking member is interposed axially between the flanges of the ring sectors and an outer annular wall of a distributor of the turbine, so as to exert on the annular flanges an axial force downstream when the distributor is itself even urged downstream by the flow of gas passing through the turbine. This axial force exerted by the locking member is sufficient to axially immobilize the flanges of the upstream edges of the ring sectors on the casing rail.

L'invention concerne également une turbomachine, telle qu'un turboréacteur ou un turbopropulseur d'avion, comprenant une turbine telle que décrite ci-dessus.The invention also relates to a turbomachine, such as an airplane turbojet or turboprop, comprising a turbine as described above.

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 vue schématique partielle en coupe axiale d'un dispositif de fixation de secteurs d'anneau selon la technique antérieure ;
  • la figure 2 est une vue schématique partielle en coupe axiale d'un dispositif de fixation de secteurs d'anneau selon l'invention.
The invention will be better understood and other features, details and advantages thereof will become more clearly apparent on reading the description which follows, given by way of non-limiting example and with reference to the appended drawings in which:
  • the figure 1 is a partial schematic view in axial section of a ring sector fixing device according to the prior art;
  • the figure 2 is a partial schematic view in axial section of a ring sector fixing device according to the invention.

Le premier étage ou étage amont de la turbine basse-pression 10 partiellement représentée en figure 1 comprend un distributeur 12, 13 formé d'une rangée annulaire d'aubes fixes 14 portées par un carter 16 de la turbine, et une roue 18 montée en aval du distributeur 12, 13 et tournant dans une enveloppe sensiblement tronconique formée par des secteurs d'anneau 20 portés circonférentiellement bout à bout par le carter 16 de la turbine.The first stage or upstream stage of the low-pressure turbine 10 partially shown in FIG. figure 1 comprises a distributor 12, 13 formed of an annular row of fixed blades 14 carried by a housing 16 of the turbine, and a wheel 18 mounted downstream of the distributor 12, 13 and rotating in a substantially frustoconical casing formed by sectors of ring 20 carried circumferentially end to end by the casing 16 of the turbine.

Le distributeur 12, 13 comprend des parois de révolution externe 22 et interne (non visible), respectivement, qui délimitent entre elles la veine annulaire d'écoulement des gaz dans la turbine et entre lesquelles s'étendent radialement les aubes 14. Les moyens de fixation du distributeur comprennent au moins un rebord cylindrique externe 24 orienté vers l'amont et destiné à être engagé dans une rainure annulaire 26 orientée vers l'aval du carter 16.The distributor 12, 13 comprises walls of external revolution 22 and internal (not visible), respectively, which delimit between them the annular flow vein of the gas in the turbine and between which radially extend the blades 14. The means of attachment of the distributor comprise at least one outer cylindrical rim 24 oriented upstream and intended to be engaged in an annular groove 26 facing downstream of the housing 16.

La roue 18 est portée par un arbre de turbine (non représenté) et comprend des viroles externe 28 et interne (non visible), la virole externe 28 comprenant des nervures annulaires externes 30 entourées extérieurement avec un faible jeu par les secteurs d'anneau 20.The wheel 18 is carried by a turbine shaft (not shown) and comprises external and internal (not visible) ferrules 28, the outer ferrule 28 comprising external annular ribs 30 externally surrounded with a small clearance by the ring sectors 20 .

Chaque secteur d'anneau 20 comprend une paroi tronconique 32 et un bloc 34 de matière abradable fixé par brasage et/ou soudage sur la surface radialement interne de la paroi 32, ce bloc 34 étant du type en nid d'abeilles et étant destiné à s'user par frottement sur les nervures 30 de la roue pour minimiser les jeux radiaux entre la roue et les secteurs d'anneau 20.Each ring sector 20 comprises a frustoconical wall 32 and a block 34 of abradable material fixed by soldering and / or welding on the radially inner surface of the wall 32, this block 34 being of the honeycomb type and intended for wear by friction on the ribs 30 of the wheel to minimize the radial clearances between the wheel and the ring sectors 20.

Les extrémités aval des secteurs d'anneau 20 sont engagées depuis l'amont dans un espace annulaire 36 délimité par un rebord cylindrique 38 orienté vers l'amont de la paroi externe 22 du distributeur 13 situé en aval des secteurs d'anneau, d'une part, et par un rebord cylindrique 40 du carter sur lequel est accroché ce distributeur, d'autre part.The downstream ends of the ring sectors 20 are engaged from upstream in an annular space 36 delimited by a cylindrical rim 38 facing upstream of the outer wall 22 of the distributor 13 located downstream of the ring sectors, a part, and a cylindrical rim 40 of the housing on which is attached this distributor, on the other hand.

Les secteurs d'anneau 20 sont maintenus radialement à leurs extrémités aval par appui radial vers l'extérieur de leurs parois 32 sur une face cylindrique radialement interne du rebord 40 du carter, et par appui radial vers l'intérieur de leurs blocs 34 de matière abradable sur une face cylindrique radialement externe du rebord cylindrique 38 du distributeur.The ring sectors 20 are held radially at their downstream ends by radial support towards the outside of their walls 32 on a radially inner cylindrical face of the flange 40 of the casing, and by radial support towards the inside of their blocks 34 of material abradable on a radially outer cylindrical face of the cylindrical rim 38 of the distributor.

Les parois 32 des secteurs d'anneau comprennent chacune à leurs extrémités aval une patte 42 s'étendant axialement vers l'aval et destinée à être engagée dans une cavité 44 correspondante du distributeur aval 13 pour immobiliser en rotation les secteurs d'anneau 20 autour de l'axe de turbine.The walls 32 of the ring sectors each comprise at their downstream ends a tab 42 extending axially downstream and intended to be engaged in a corresponding cavity 44 of the downstream distributor 13 to immobilize in rotation the ring sectors 20 around of the turbine axis.

Les parois tronconiques 32 des secteurs d'anneau 20 comprennent à leurs extrémités amont des rebords cylindriques 46 orientés vers l'amont qui sont engagés avec un jeu axial faible dans une gorge annulaire radialement interne 48 d'un rail annulaire 50 du carter 16. Les rebords 46 sont maintenus radialement dans cette gorge au moyen d'un organe de verrouillage 52 formé d'un anneau fendu à section en C ou en U engagé axialement depuis l'amont sur le rail annulaire 50 du carter et sur les rebords amont 46 des secteurs d'anneau.The frustoconical walls 32 of the ring sectors 20 comprise at their upstream ends cylindrical rims 46 facing upstream which are engaged with a small axial clearance in a radially inner annular groove 48 of an annular rail 50 of the casing 16. The flanges 46 are held radially in this groove by means of a locking member 52 formed of a split ring C or U section axially engaged from upstream on the annular rail 50 of the housing and on the upstream edges 46 of the ring sectors.

L'organe de verrouillage 52 comprend deux parois cylindriques 54 et 56 s'étendant vers l'aval, radialement externe et radialement interne respectivement, qui sont reliées entre elles à leurs extrémités amont par une paroi radiale 58, et qui sont engagées respectivement à l'extérieur du rail 50 et à l'intérieur des rebords cylindriques 46 des secteurs d'anneau 20.The locking member 52 comprises two cylindrical walls 54 and 56 extending downstream, radially outer and radially inner respectively, which are connected together at their upstream ends by a radial wall 58, and which are engaged respectively to the outside the rail 50 and inside the cylindrical flanges 46 of the ring sectors 20.

La paroi radiale 58 de l'organe de verrouillage 52 est interposée axialement entre l'extrémité amont du rail de carter 50 et une paroi annulaire externe 60 du distributeur 12 situé en amont des secteurs d'anneau 20, pour empêcher l'organe de verrouillage 52 de se déplacer axialement vers l'amont et se désengager du rail de carter 50 et des rebords 46 des secteurs d'anneau.The radial wall 58 of the locking member 52 is interposed axially between the upstream end of the casing rail 50 and an outer annular wall 60 of the distributor 12 located upstream of the sectors. ring 20, to prevent the locking member 52 from moving axially upstream and disengage from the housing rail 50 and flanges 46 of the ring sectors.

Le rayon de courbure de l'organe de verrouillage 52 et du rail 50 est inférieur à celui des rebords 46 des secteurs d'anneau 20, ce qui permet de monter avec une certaine précontrainte radiale les rebords 46 des secteurs d'anneau dans la gorge 48 du rail, ces secteurs d'anneau étant localement en appui radial sur le fond de la gorge 48 et sur la paroi radialement interne 56 de l'organe de verrouillage, respectivement.The radius of curvature of the locking member 52 and the rail 50 is smaller than that of the flanges 46 of the ring sectors 20, which makes it possible to mount with a certain radial prestress the flanges 46 of the ring sectors in the groove. 48 of the rail, these ring sectors being locally in radial support on the bottom of the groove 48 and on the radially inner wall 56 of the locking member, respectively.

En fonctionnement, les rebords 46 des secteurs d'anneau 20 vibrent axialement et usent par frottement les faces amont et aval de la gorge 46 du rail.In operation, the flanges 46 of the ring sectors 20 vibrate axially and frictionally use the upstream and downstream faces of the groove 46 of the rail.

Lorsque la face aval de la gorge 48 est très usée (comme cela est représenté en traits pointillés 62), les rebords 46 peuvent en se déplaçant vers l'aval glisser sur la paroi radialement interne 56 de l'organe de verrouillage et se désengager de l'organe de verrouillage, ce qui peut entraîner au moins la destruction des blocs 34 de matière abradable des secteurs d'anneau qui viennent en contact avec les nervures annulaires 30 de la roue 18.When the downstream face of the groove 48 is very worn (as shown in dashed lines 62), the flanges 46 can move downstream to slide on the radially inner wall 56 of the locking member and disengage from the locking member, which can cause at least the destruction of the blocks 34 of abradable material ring sectors which come into contact with the annular ribs 30 of the wheel 18.

L'invention permet d'apporter une solution simple à ce problème grâce à l'immobilisation axiale des rebords des secteurs d'anneau sur le rail de carter par l'organe de verrouillage.The invention makes it possible to provide a simple solution to this problem by axially immobilizing the flanges of the ring sectors on the casing rail by the locking member.

Dans un mode de réalisation de l'invention représenté en figure 2, les rebords cylindriques amont 70 des secteurs d'anneau 20 comprennent chacun à leur extrémité amont une collerette annulaire 72 qui s'étend sensiblement radialement vers l'extérieur et qui est serrée axialement sur le rail de carter 50 par l'organe de verrouillage 80.In one embodiment of the invention shown in figure 2 , the upstream cylindrical flanges 70 of the ring sectors 20 each comprise at their upstream end an annular flange 72 which extends substantially radially outwards and which is clamped axially on the casing rail 50 by the locking member 80 .

L'organe de verrouillage 80 comprend deux parois cylindriques 84 et 86 s'étendant vers l'aval, radialement externe et radialement interne respectivement, qui sont reliées entre elles à leurs extrémités amont par une paroi radiale 82 qui a une dimension radiale plus importante que la dimension radiale de la paroi 58 de l'organe de verrouillage 52 de la technique antérieure (figure 1).The locking member 80 comprises two cylindrical walls 84 and 86 extending downstream, radially outer and radially inner respectively, which are interconnected at their upstream ends by a radial wall 82 which has a greater radial dimension than the radial dimension of the wall 58 of the locking member 52 of the prior art ( figure 1 ).

Le rebord cylindrique 70 du secteur d'anneau est plus long que dans la technique antérieure, pour que la collerette annulaire 72 puisse être engagée entre la paroi radiale 82 de l'organe de verrouillage et l'extrémité amont du rail du carter.The cylindrical flange 70 of the ring sector is longer than in the prior art, so that the annular flange 72 can be engaged between the radial wall 82 of the locking member and the upstream end of the rail of the housing.

La paroi cylindrique radialement externe 84 de l'organe de verrouillage 80 est engagée à l'extérieur du rail 50 et sa paroi radialement interne 86 est engagée à l'intérieur des rebords cylindriques 70 des secteurs d'anneau 20, ces rebords 70 étant interposés radialement entre la paroi cylindrique interne 86 de l'organe et la face d'extrémité amont du rail 50.The radially outer cylindrical wall 84 of the locking member 80 is engaged outside the rail 50 and its radially inner wall 86 is engaged inside the cylindrical flanges 70 of the ring sectors 20, these flanges 70 being interposed radially between the inner cylindrical wall 86 of the member and the upstream end face of the rail 50.

Comme dans la technique antérieure, le rayon de courbure de l'organe de verrouillage 80 et du rail 50 est inférieur à celui des rebords 70 des secteurs d'anneau 20, ce qui permet de monter avec une certaine précontrainte radiale les rebords 70 des secteurs d'anneau sur le rail 50 et sur l'organe de verrouillage.As in the prior art, the radius of curvature of the locking member 80 and the rail 50 is smaller than that of the flanges 70 of the ring sectors 20, which allows to mount with some radial prestressing the edges 70 of the sectors ring on the rail 50 and on the locking member.

La paroi radiale 82 de l'organe de verrouillage 80 est interposée axialement entre les collerettes annulaires 72 des secteurs d'anneau 70 et la paroi annulaire externe 60 du distributeur 12 situé en amont des secteurs d'anneau 20.The radial wall 82 of the locking member 80 is interposed axially between the annular flanges 72 of the ring sectors 70 and the outer annular wall 60 of the distributor 12 situated upstream of the ring sectors 20.

En fonctionnement de la turbomachine, ce distributeur 12 est sollicité vers l'aval par l'écoulement des gaz et exerce un effort axial dirigé vers l'aval sur les collerettes annulaires 72 des secteurs d'anneau 70 par l'intermédiaire de l'organe de verrouillage 80. Cet effort axial est suffisant pour maintenir axialement serrées les collerettes 72 des secteurs d'anneau sur le rail de carter 50.In operation of the turbomachine, this distributor 12 is biased downstream by the flow of the gases and exerts an axial force directed downstream on the annular flanges 72 of the ring sectors 70 through the organ 80. This axial force is sufficient to maintain axially tight collars 72 of the ring sectors on the housing rail 50.

Les collerettes 72 des secteurs d'anneau sont ainsi immobilisées axialement et radialement par l'organe de verrouillage 80 sur le rail de carter 80, et ne peuvent donc pas user par frottement le rail de carter.The flanges 72 of the ring sectors are thus immobilized axially and radially by the locking member 80 on the casing rail 80, and therefore can not wear the housing rail by friction.

Par ailleurs, les secteurs d'anneau 20 selon l'invention peuvent être accrochés sur un rail de carter 50 déjà usé comme cela est représenté par les traits pointillés 90, ce qui permet de réparer à moindres frais l'étage amont de la turbine basse-pression sans toucher au carter de la turbine.Moreover, the ring sectors 20 according to the invention can be hooked onto a used housing rail 50 as shown by the dashed lines 90, which makes it possible to repair the upstream stage of the low turbine at a lower cost. -pressure without touching the turbine housing.

Dans une variante de réalisation, le rebord amont 70 des secteurs d'anneau ne porte pas de collerette 72 et s'étend axialement jusqu'à la paroi radiale 82 de l'organe de verrouillage, le long de la partie cylindrique du rail du carter, qui est dépourvue de rebord radial à son extrémité amont. L'extrémité aval du rebord 70 est appliquée axialement sur le rail de carter par l'organe de verrouillage 80.In an alternative embodiment, the upstream flange 70 of the ring sectors does not bear flange 72 and extends axially to the radial wall 82 of the locking member, along the cylindrical portion of the crankcase rail. which has no radial rim at its upstream end. The downstream end of the flange 70 is applied axially on the casing rail by the locking member 80.

Claims (9)

  1. A turbomachine turbine comprising at least one guide vane element (12) formed of an annular array of fixed blades supported by a casing (16) of the turbine, and a rotor (18) mounted so as to rotate downstream of the guide vane element in a substantially frustoconical envelope formed by ring sectors (20) attached circumferentially end-to-end only at their upstream ends to the turbine casing, the ring sectors (20) comprising at their upstream ends circumferential coupling means (70) that are engaged on a casing rail (50) and that are held by a C-section annular locking member (80) engaged axially on the casing rail (50) and on the circumferential coupling means (70) of the ring sectors, wherein the circumferential coupling means (70) of the ring sectors are interposed axially between the annular locking member (80) and the casing rail (50) and clamped axially on the casing rail (50) by the annular locking member (80).
  2. The turbine as claimed in claim 1, wherein the circumferential coupling means (70) comprise an annular collar (72) extending radially outward at the upstream end of each ring sector (20).
  3. The turbine as claimed in claim 2, wherein the annular collar (72) of each ring sector (20) extends between a radial wall (82) of the annular locking member (80) and an upstream end of the casing rail (50).
  4. The turbine as claimed in claim 2 or 3, wherein the annular locking member (80) is interposed axially between the annular collars (72) of the ring sectors (20) and an outer annular wall (60) of a turbine guide vane element (12).
  5. The turbine as claimed in one of claims 2 to 4, wherein, when the turbomachine operates, the annular locking member (80) exerts an axial force directed in the downstream direction on the annular collars (72) of the ring sectors (20).
  6. The turbine as claimed in one of claims 2 to 5, wherein the annular collar (72) of each ring sector (20) is formed at the upstream end of a cylindrical rim (70) of the ring sector.
  7. The turbine as claimed in claim 6, wherein the annular locking member (80) comprises an inner cylindrical wall (86) extending in the downstream direction and engaged inside the cylindrical rim (70) of each ring sector (20).
  8. The turbine as claimed in one of claims 2 to 7, wherein the annular locking member (80) provides axial and radial immobilization of the annular collars (72) of the ring sectors (20) on the casing rail (50).
  9. A turbomachine, such as an aircraft turbojet or turboprop, which comprises a turbine as claimed in one of the preceding claims.
EP07290301A 2006-03-30 2007-03-08 Device for fixing ring sectors on the casing of a jet engine Active EP1847686B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0602748A FR2899275A1 (en) 2006-03-30 2006-03-30 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

Publications (2)

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EP1847686A1 EP1847686A1 (en) 2007-10-24
EP1847686B1 true EP1847686B1 (en) 2009-06-17

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EP07290301A Active EP1847686B1 (en) 2006-03-30 2007-03-08 Device for fixing ring sectors on the casing of a jet engine

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US (1) US7866943B2 (en)
EP (1) EP1847686B1 (en)
JP (1) JP4809798B2 (en)
CN (1) CN101046162B (en)
CA (1) CA2582398C (en)
DE (1) DE602007001300D1 (en)
FR (1) FR2899275A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4143422B1 (en) * 2020-04-30 2024-03-20 Safran Aircraft Engines Mounting of a sealing ring on an aeronautical turbine engine

Families Citing this family (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2921410B1 (en) * 2007-09-24 2010-03-12 Snecma RING SECTOR INTERLOCKING DEVICE ON A TURBOMACHINE HOUSING, COMPRISING MEANS FOR ITS PRETENSION
FR2923525B1 (en) * 2007-11-13 2009-12-18 Snecma SEALING A ROTOR RING IN A TURBINE FLOOR
FR2931197B1 (en) * 2008-05-16 2010-06-18 Snecma LOCKING SECTOR OF RING SECTIONS ON A TURBOMACHINE CASING, COMPRISING AXIAL PASSAGES FOR ITS PRETENSION
FR2931195B1 (en) 2008-05-16 2014-05-30 Snecma DISSYMMETRICAL MEMBER FOR LOCKING RING SECTIONS ON A TURBOMACHINE HOUSING
DE102009037620A1 (en) * 2009-08-14 2011-02-17 Mtu Aero Engines Gmbh flow machine
FR2952965B1 (en) * 2009-11-25 2012-03-09 Snecma INSULATING A CIRCONFERENTIAL SIDE OF AN EXTERNAL TURBOMACHINE CASTER WITH RESPECT TO A CORRESPONDING RING SECTOR
FR2954400B1 (en) * 2009-12-18 2012-03-09 Snecma TURBINE STAGE IN A TURBOMACHINE
US8939715B2 (en) * 2010-03-22 2015-01-27 General Electric Company Active tip clearance control for shrouded gas turbine blades and related method
FR2960591B1 (en) * 2010-06-01 2012-08-24 Snecma DEVICE FOR ROTATING A DISPENSING SEGMENT IN A TURBOMACHINE HOUSING; PION ANTIROTATION
US8998573B2 (en) * 2010-10-29 2015-04-07 General Electric Company Resilient mounting apparatus for low-ductility turbine shroud
FR2983518B1 (en) * 2011-12-06 2014-02-07 Snecma UNLOCKING DEVICE FOR AXIAL STOP OF A SEALED CROWN CONTACTED BY A MOBILE WHEEL OF AIRCRAFT TURBOMACHINE MODULE
US9080459B2 (en) * 2012-01-03 2015-07-14 General Electric Company Forward step honeycomb seal for turbine shroud
CN102748079B (en) * 2012-07-17 2014-12-10 湖南航翔燃气轮机有限公司 Turbine outer ring device
EP2696036A1 (en) 2012-08-09 2014-02-12 MTU Aero Engines GmbH Clamping ring for a turbomachine
US9410441B2 (en) 2012-09-13 2016-08-09 Pratt & Whitney Canada Corp. Turboprop engine with compressor turbine shroud
US9896971B2 (en) * 2012-09-28 2018-02-20 United Technologies Corporation Lug for preventing rotation of a stator vane arrangement relative to a turbine engine case
US9238977B2 (en) * 2012-11-21 2016-01-19 General Electric Company Turbine shroud mounting and sealing arrangement
US20140271142A1 (en) 2013-03-14 2014-09-18 General Electric Company Turbine Shroud with Spline Seal
WO2014150353A1 (en) * 2013-03-15 2014-09-25 United Technologies Corporation Low leakage duct segment using expansion joint assembly
EP2801702B1 (en) * 2013-05-10 2020-05-06 Safran Aero Boosters SA Inner shroud of turbomachine with abradable seal
ES2935815T3 (en) 2013-09-06 2023-03-10 MTU Aero Engines AG (Dis)assembly of a gas turbine rotor, in particular front
US20150167488A1 (en) * 2013-12-18 2015-06-18 John A. Orosa Adjustable clearance control system for airfoil tip in gas turbine engine
FR3064023B1 (en) * 2017-03-16 2019-09-13 Safran Aircraft Engines TURBINE RING ASSEMBLY
FR3064022B1 (en) * 2017-03-16 2019-09-13 Safran Aircraft Engines TURBINE RING ASSEMBLY
US20180347399A1 (en) * 2017-06-01 2018-12-06 Pratt & Whitney Canada Corp. Turbine shroud with integrated heat shield
DE102018210600A1 (en) * 2018-06-28 2020-01-02 MTU Aero Engines AG COAT RING ARRANGEMENT FOR A FLOWING MACHINE
US10822964B2 (en) * 2018-11-13 2020-11-03 Raytheon Technologies Corporation Blade outer air seal with non-linear response
US10920618B2 (en) 2018-11-19 2021-02-16 Raytheon Technologies Corporation Air seal interface with forward engagement features and active clearance control for a gas turbine engine
US10934941B2 (en) 2018-11-19 2021-03-02 Raytheon Technologies Corporation Air seal interface with AFT engagement features and active clearance control for a gas turbine engine
FR3111382B1 (en) * 2020-06-11 2022-12-23 Safran Aircraft Engines Annular assembly for turbomachine turbine
FR3112806B1 (en) * 2020-07-23 2022-10-21 Safran Aircraft Engines Crown for maintaining sealing sectors of a low pressure turbine
CN115163564B (en) * 2022-07-29 2023-03-24 中国航发沈阳发动机研究所 Aeroengine blade tip position machine casket fluting structure

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5188507A (en) * 1991-11-27 1993-02-23 General Electric Company Low-pressure turbine shroud
US5593277A (en) * 1995-06-06 1997-01-14 General Electric Company Smart turbine shroud
FR2780443B1 (en) * 1998-06-25 2000-08-04 Snecma HIGH PRESSURE TURBINE STATOR RING OF A TURBOMACHINE
US6435820B1 (en) * 1999-08-25 2002-08-20 General Electric Company Shroud assembly having C-clip retainer
JP3825279B2 (en) * 2001-06-04 2006-09-27 三菱重工業株式会社 gas turbine
FR2829525B1 (en) * 2001-09-13 2004-03-12 Snecma Moteurs ASSEMBLY OF SECTORS OF A TURBINE DISTRIBUTOR TO A CRANKCASE
US6893217B2 (en) * 2002-12-20 2005-05-17 General Electric Company Methods and apparatus for assembling gas turbine nozzles
JP4269828B2 (en) * 2003-07-04 2009-05-27 株式会社Ｉｈｉ Shroud segment
US7186078B2 (en) * 2003-07-04 2007-03-06 Ishikawajima-Harima Heavy Industries Co., Ltd. Turbine shroud segment
US7334984B1 (en) * 2003-12-24 2008-02-26 Heico Corporation Turbine shroud assembly with enhanced blade containment capabilities

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4143422B1 (en) * 2020-04-30 2024-03-20 Safran Aircraft Engines Mounting of a sealing ring on an aeronautical turbine engine

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JP4809798B2 (en) 2011-11-09
CN101046162B (en) 2010-10-06
CN101046162A (en) 2007-10-03
FR2899275A1 (en) 2007-10-05
CA2582398A1 (en) 2007-09-30
JP2007270835A (en) 2007-10-18
CA2582398C (en) 2014-04-29
DE602007001300D1 (en) 2009-07-30
US7866943B2 (en) 2011-01-11
US20070231132A1 (en) 2007-10-04
EP1847686A1 (en) 2007-10-24

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