EP1840339A1 - Device for attaching ring sectors around a turbine wheel of a turbomachine - Google Patents

Device for attaching ring sectors around a turbine wheel of a turbomachine Download PDF

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Publication number
EP1840339A1
EP1840339A1 EP07290322A EP07290322A EP1840339A1 EP 1840339 A1 EP1840339 A1 EP 1840339A1 EP 07290322 A EP07290322 A EP 07290322A EP 07290322 A EP07290322 A EP 07290322A EP 1840339 A1 EP1840339 A1 EP 1840339A1
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EP
European Patent Office
Prior art keywords
wall
fixed
ring
turbine
upstream
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.)
Granted
Application number
EP07290322A
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German (de)
French (fr)
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EP1840339B1 (en
Inventor
Didier Durand
Dominique Gehan
Valérie Anne Gros
Didier Sotto-Lamy
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 of EP1840339A1 publication Critical patent/EP1840339A1/en
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Publication of EP1840339B1 publication Critical patent/EP1840339B1/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
    • 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
    • F01D11/122—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 with erodable or abradable material
    • 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
    • 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
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments

Definitions

  • the present invention relates to a device for fixing ring sectors around a turbine wheel 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 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 with a C-section which is engaged axially from upstream on the casing rail and on the circumferential edges of the ring sectors. These sectors are held axially by abutment of their circumferential edges on upstream and downstream faces respectively of the groove of the rail.
  • the flanges 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 rail of the casing and of the locking member, which makes it possible to mount the flanges 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 flanges 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.
  • each ring sector comprising a frustoconical wall which carries a block of abradable material fixed on its inner surface and which comprises its upstream end a circumferential rim engaged in a radially inner annular groove of an annular housing rail and held radially in this groove by an annular locking member C section which is engaged axially from upstream on the housing rail and on the circumferential edges of the ring sectors, characterized in that each ring sector comprises at its downstream end an insert and fixed on the frustoconical wall and on the block of abradable material of the ring sector, this piece being able to come in axial support against a fixed element of the turbine to prevent the disengagement of the upstream edge of the wall of the locking member, the axi al between the support piece and the fixed element being less than the axial length of the support of the upstream flange of the wall on the locking member.
  • the support piece provided at the downstream end of each ring sector limits the possible retreat of the upstream edge of the ring. ring sector in the groove of the crankcase rail and avoids the disengagement of this rim of the locking member.
  • the ring sectors are maintained axially upstream by pressing their upstream flanges on a corresponding face of the crankcase rail and downstream by bearing the part on the fixed element.
  • the support piece advantageously comprises means that can come into radial abutment on the fixed element.
  • Each ring sector is thus retained in the axial direction and in the radial direction on the fixed element.
  • the support piece is fixed on the downstream end of the wall and on the block of abradable material by brazing or welding.
  • the support piece is on the ring sector, as this avoids modifying the manufacturing molds of these sectors.
  • the device according to the invention makes it possible to hang ring sectors on a casing rail independently of the wear thereof.
  • the axial clearance between the support piece and the fixed element is less than the axial length of the support of the upstream flange of the ring sector on the locking member. This ensures that the maximum recoil position of the ring sector is defined by the axial support of the workpiece on the fixed element.
  • This axial clearance between the support piece and the fixed element is for example between 0.3 and 1.2mm approximately.
  • the support piece has a section F and comprises two flanges in cylinder portion which extend downstream, one of these flanges being fixed on a radially inner surface of the wall of the ring sector and the other of these flanges can bear radially on a radially outer face of a cylindrical rim of the fixed element.
  • the fixed element of the turbomachine is advantageously constituted by a turbine distributor located downstream of the ring sector.
  • the invention also relates to a turbomachine turbine and a turbomachine, such as an airplane turbojet or turboprop, comprising at least one device as described above.
  • the invention finally relates to a ring sector for a turbomachine turbine, comprising a frustoconical wall which carries a block of abradable material fixed on its inner surface and which has at its upstream end a hooking flange on a housing, characterized in that it comprises at its downstream end an axial bearing piece and radial attached and fixed on the wall and on the block of abradable material of the ring sector.
  • the support piece is preferably fixed by welding or brazing on the block of abradable material and on the downstream end of the wall of the ring sector.
  • the turbine 10 partially shown in FIG. 1 comprises several stages each comprising a distributor 12, 13 formed of an annular row of stationary vanes 14 carried by a casing 16 of the turbine, and a wheel 18 mounted downstream of the distributor 12, 13 and rotating in a substantially frustoconical envelope formed by ring sectors 20 carried circumferentially end to end by the casing 16 of the turbine.
  • the distributors 12, 13 comprise walls of external revolution 22 and internal (not visible), respectively, which delimit between them the annular stream of gas flow in the turbine and between which the vanes extend radially 14.
  • the distributor fixing means comprise at least one outer cylindrical rim 24 oriented upstream and intended to be engaged in an annular groove 26 facing downstream of the casing 16.
  • the wheels 18 are carried by a turbine shaft (not shown). They comprise external and internal (not visible) ferrules 28, respectively, the outer ferrule 28 of each wheel 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, on the one hand, and by a cylindrical rim 39 of the casing on which this distributor is hooked, 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 39 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 40 extending axially downstream and intended to be engaged in a corresponding cavity 42 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 also comprise at their upstream ends cylindrical rims 44 facing upstream which are engaged with a small axial clearance in a radially inner annular groove 46 of an annular rail 48 of the casing 16. These flanges 44 are held radially in this groove by means of a locking member 50 formed of a split ring C section engaged from upstream on the annular rail 48 of the housing and on the upstream edges 44 of the sectors of ring.
  • the locking member 50 comprises two cylindrical branches 52 and 54 extending downstream, radially outer and radially inner respectively, which are interconnected at their upstream ends by a radial wall 56, and which are respectively applied to a radially outer cylindrical face of the rail 48 and on the circumferential edges 44 of the ring sectors 20.
  • the locking member 50 is prevented from moving axially upstream by axial support of its radial wall 56 on a radial annular flange 58 of the outer wall 22 of the distributor 12 located upstream of the sectors. ring 20.
  • the radius of curvature of the locking member 50 and of the rail 48 is less than that of the flanges 44 of the ring sectors 20, which makes it possible to mount with a certain radial prestress the flanges 44 of the ring sectors in the groove. 46 of the rail, these ring sectors being locally in radial support on the bottom of the groove and on the radially inner arm 54 of the locking member, respectively.
  • the flanges 44 of the ring sectors 20 vibrate axially and frictionally wear the upstream and downstream faces of the groove 46 of the rail.
  • the flanges 44 can move downstream by sliding on the radially inner arm 54 of the locking member, and disengage of the locking member, which can in particular, to cause the blocks 34 of abradable material to be destroyed from the 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 means of a support piece attached and fixed on the downstream end of each ring sector.
  • the support piece 70 has a section F and comprises two downstream radially outer and radially inner rims 72 and 74, respectively, which are connected to each other at their upstream ends by a radial wall 76.
  • the radially outer face of the outer flange 72 is applied and fixed by welding or brazing on a downstream end portion of the radially inner surface of the wall 32 of the ring sector, and the radial wall 76 is applied and fixed by brazing or welding on a radial face of the block 34 of abradable material of the ring sector 20.
  • Each ring sector is held radially at its downstream end by radial support of the internal flange 74 of the part 70 on the cylindrical flange 38 of the downstream distributor, and by radial support of its wall 32 on the radially inner face of the cylindrical flange 39 of the casing 16.
  • the ring sectors are held axially at their upstream ends as previously described with reference to FIG. 1, and at their downstream ends by axial support downstream of the radial wall 76 of the part on the upstream end of the cylindrical flange. 38 of the downstream distributor 13.
  • the radial walls 76 of the parts 70 are separated from the cylindrical flange 38 of the distributor 13 by an axial clearance 78 which is smaller than the axial length 80 on which the flanges 44 of the ring sectors bear on the locking member 50, so that, in the event of significant wear of the downstream face of the groove 46 of the rail, the radial walls 76 of the part 70 come to bear axially on the cylindrical flange 38 of the distributor and limit the possible retraction of the flanges 44 ring areas in the groove preventing them from disengaging from the locking member 50.
  • the axial play is for example between 0.3 and 1.2mm approximately.
  • the ring sectors 20 are held axially on the casing 16, as previously described with reference to FIG. 1, that is to say by axial support of the flanges 44 of the ring sectors on the upstream and downstream faces respectively of the groove 46 of the rail.
  • the ring sectors 20 are held axially downstream by axial support of the radial walls 76 of the parts. 70 on the cylindrical rim 38 of the downstream distributor.
  • Part 70 may be attached and secured to the downstream end of an existing ring sector of the prior art. To do this, it suffices to remove a downstream end portion of the block 34 of abradable material from the ring sector and to fix there instead by brazing or welding a piece 70 of axial and radial support.
  • the support piece may comprise only axial bearing means on the upstream flange 38 of the distributor, the ring sectors being held radially inwards at their downstream ends by radial support of the blocks 34 on this flange. upstream, as is the case in the prior art.

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

Abstract

The device has a ring sector including a support part (70) at its downstream end and fixed on a frusto-conical wall (32) and on a block of abradable matter of the ring sector. The part is supported against a fixed element of a turbine for preventing disengagement of an upstream flange (44) of the wall of a locking unit (50). An end play (78) between the support part and the fixed element is lower to a longitudinal axis (80) of a flange support of the wall on the locking unit. An independent claim is also included for a ring sector for a turbine of a turbo machine.

Description

La présente invention concerne un dispositif de fixation de secteurs d'anneau autour d'une roue 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 around a turbine wheel 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 rebords circonférentiels 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 circonférentiels des secteurs d'anneau. Ces secteurs sont maintenus axialement par butée de leurs rebords circonférentiels sur des faces amont et aval respectivement de la gorge du rail.The ring sectors comprise at their upstream ends circumferential 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 with a C-section which is engaged axially from upstream on the casing rail and on the circumferential edges of the ring sectors. These sectors are held axially by abutment of their circumferential edges on upstream and downstream faces respectively of the groove of the rail.

Les rebords 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 flanges 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 rail of the casing and of the locking member, which makes it possible to mount the flanges 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 flanges 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 un dispositif de fixation de secteurs d'anneau autour d'une roue de turbine dans une turbomachine, chaque secteur d'anneau comprenant une paroi tronconique qui porte un bloc de matière abradable fixé sur sa surface interne et qui comporte à son extrémité amont un rebord circonférentiel engagé dans une gorge annulaire radialement interne d'un rail annulaire de carter et maintenu 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 circonférentiels des secteurs d'anneau, caractérisé en ce que chaque secteur d'anneau comprend à son extrémité aval une pièce rapportée et fixée sur la paroi tronconique et sur le bloc de matière abradable du secteur d'anneau, cette pièce pouvant venir en appui axial contre un élément fixe de la turbine pour empêcher le désengagement du rebord amont de la paroi de l'organe de verrouillage, le jeu axial entre la pièce d'appui et l'élément fixe étant inférieur à la longueur axiale de l'appui du rebord amont de la paroi sur l'organe de verrouillage.To this end, it proposes a device for fastening ring sectors around a turbine wheel in a turbomachine, each ring sector comprising a frustoconical wall which carries a block of abradable material fixed on its inner surface and which comprises its upstream end a circumferential rim engaged in a radially inner annular groove of an annular housing rail and held radially in this groove by an annular locking member C section which is engaged axially from upstream on the housing rail and on the circumferential edges of the ring sectors, characterized in that each ring sector comprises at its downstream end an insert and fixed on the frustoconical wall and on the block of abradable material of the ring sector, this piece being able to come in axial support against a fixed element of the turbine to prevent the disengagement of the upstream edge of the wall of the locking member, the axi al between the support piece and the fixed element being less than the axial length of the support of the upstream flange of the wall on the locking member.

Grâce à l'invention, la pièce d'appui prévue à l'extrémité aval de chaque secteur d'anneau limite le recul possible du rebord amont du secteur d'anneau dans la gorge du rail de carter et évite le désengagement de ce rebord de l'organe de verrouillage.Thanks to the invention, the support piece provided at the downstream end of each ring sector limits the possible retreat of the upstream edge of the ring. ring sector in the groove of the crankcase rail and avoids the disengagement of this rim of the locking member.

Même en cas d'usure importante du rail de carter, les secteurs d'anneau sont maintenus axialement en amont par appui de leurs rebords amont sur une face correspondante du rail de carter et en aval par appui de la pièce sur l'élément fixe.Even in case of significant wear of the crankcase rail, the ring sectors are maintained axially upstream by pressing their upstream flanges on a corresponding face of the crankcase rail and downstream by bearing the part on the fixed element.

La pièce d'appui comprend avantageusement des moyens pouvant venir en appui radial sur l'élément fixe.The support piece advantageously comprises means that can come into radial abutment on the fixed element.

Chaque secteur d'anneau est ainsi retenu en direction axiale et en direction radiale sur l'élément fixe.Each ring sector is thus retained in the axial direction and in the radial direction on the fixed element.

Selon une autre caractéristique de l'invention, la pièce d'appui est fixée sur l'extrémité aval de la paroi et sur le bloc de matière abradable par brasage ou soudage.According to another characteristic of the invention, the support piece is fixed on the downstream end of the wall and on the block of abradable material by brazing or welding.

Il est avantageux, du point de vue économique, que la pièce d'appui soit sur le secteur d'anneau, car cela évite de modifier les moules de fabrication de ces secteurs. De plus, le dispositif selon l'invention permet d'accrocher des secteurs d'anneau sur un rail de carter indépendamment de l'usure de celui-ci.It is advantageous from an economic point of view that the support piece is on the ring sector, as this avoids modifying the manufacturing molds of these sectors. In addition, the device according to the invention makes it possible to hang ring sectors on a casing rail independently of the wear thereof.

Le jeu axial entre la pièce d'appui et l'élément fixe est inférieur à la longueur axiale de l'appui du rebord amont du secteur d'anneau sur l'organe de verrouillage. Cela permet de s'assurer que la position de recul maximal du secteur d'anneau est définie par l'appui axial de la pièce sur l'élément fixe. Ce jeu axial entre la pièce d'appui et l'élément fixe est par exemple compris entre 0,3 et 1,2mm environ.The axial clearance between the support piece and the fixed element is less than the axial length of the support of the upstream flange of the ring sector on the locking member. This ensures that the maximum recoil position of the ring sector is defined by the axial support of the workpiece on the fixed element. This axial clearance between the support piece and the fixed element is for example between 0.3 and 1.2mm approximately.

Dans un mode préféré de réalisation de l'invention, la pièce d'appui a une section en F et comprend deux rebords en portion de cylindre qui s'étendent vers l'aval, un de ces rebords étant fixé sur une surface radialement interne de la paroi du secteur d'anneau et l'autre de ces rebords pouvant venir en appui radial sur une face radialement externe d'un rebord cylindrique de l'élément fixe.In a preferred embodiment of the invention, the support piece has a section F and comprises two flanges in cylinder portion which extend downstream, one of these flanges being fixed on a radially inner surface of the wall of the ring sector and the other of these flanges can bear radially on a radially outer face of a cylindrical rim of the fixed element.

L'élément fixe de la turbomachine est avantageusement constitué par un distributeur de turbine situé en aval du secteur d'anneau.The fixed element of the turbomachine is advantageously constituted by a turbine distributor located downstream of the ring sector.

L'invention concerne également une turbine de turbomachine et une turbomachine, telle qu'un turboréacteur ou un turbopropulseur d'avion, comprenant au moins un dispositif tel que décrit ci-dessus.The invention also relates to a turbomachine turbine and a turbomachine, such as an airplane turbojet or turboprop, comprising at least one device as described above.

L'invention concerne enfin un secteur d'anneau pour une turbine de turbomachine, comprenant une paroi tronconique qui porte un bloc de matière abradable fixé sur sa surface interne et qui comporte à son extrémité amont un rebord d'accrochage sur un carter, caractérisé en ce qu'il comprend à son extrémité aval une pièce d'appui axial et radial rapportée et fixée sur la paroi et sur le bloc de matière abradable du secteur d'anneau.The invention finally relates to a ring sector for a turbomachine turbine, comprising a frustoconical wall which carries a block of abradable material fixed on its inner surface and which has at its upstream end a hooking flange on a housing, characterized in that it comprises at its downstream end an axial bearing piece and radial attached and fixed on the wall and on the block of abradable material of the ring sector.

La pièce d'appui est préférentiellement fixée par soudure ou brasure sur le bloc de matière abradable et sur l'extrémité aval de la paroi du secteur d'anneau.The support piece is preferably fixed by welding or brazing on the block of abradable material and on the downstream end of the wall of the ring sector.

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 characteristics, details and advantages thereof will appear more clearly on reading the description which follows, given by way of nonlimiting example and with reference to the accompanying drawings in which:
  • Figure 1 is a partial schematic view in axial section of a ring sector fixing device according to the prior art;
  • Figure 2 is a partial schematic view in axial section of a ring sector fixing device according to the invention.

La turbine 10 partiellement représentée en figure 1 comprend plusieurs étages comportant chacun 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 turbine 10 partially shown in FIG. 1 comprises several stages each comprising a distributor 12, 13 formed of an annular row of stationary vanes 14 carried by a casing 16 of the turbine, and a wheel 18 mounted downstream of the distributor 12, 13 and rotating in a substantially frustoconical envelope formed by ring sectors 20 carried circumferentially end to end by the casing 16 of the turbine.

Les distributeurs 12, 13 comprennent 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 des distributeurs 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 distributors 12, 13 comprise walls of external revolution 22 and internal (not visible), respectively, which delimit between them the annular stream of gas flow in the turbine and between which the vanes extend radially 14. The distributor fixing means comprise at least one outer cylindrical rim 24 oriented upstream and intended to be engaged in an annular groove 26 facing downstream of the casing 16.

Les roues 18 sont portées par un arbre de turbine (non représenté). Elles comprennent des viroles externes 28 et internes (non visible), respectivement, la virole externe 28 de chaque roue comprenant des nervures annulaires externes 30 entourées extérieurement avec un faible jeu par les secteurs d'anneau 20.The wheels 18 are carried by a turbine shaft (not shown). They comprise external and internal (not visible) ferrules 28, respectively, the outer ferrule 28 of each wheel 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 39 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, on the one hand, and by a cylindrical rim 39 of the casing on which this distributor is hooked, 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 39 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 39 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 40 s'étendant axialement vers l'aval et destinée à être engagée dans une cavité 42 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 40 extending axially downstream and intended to be engaged in a corresponding cavity 42 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 également à leurs extrémités amont des rebords cylindriques 44 orientés vers l'amont qui sont engagés avec un jeu axial faible dans une gorge annulaire radialement interne 46 d'un rail annulaire 48 du carter 16. Ces rebords 44 sont maintenus radialement dans cette gorge au moyen d'un organe de verrouillage 50 formé d'un anneau fendu à section en C engagé depuis l'amont sur le rail annulaire 48 du carter et sur les rebords amont 44 des secteurs d'anneau.The frustoconical walls 32 of the ring sectors 20 also comprise at their upstream ends cylindrical rims 44 facing upstream which are engaged with a small axial clearance in a radially inner annular groove 46 of an annular rail 48 of the casing 16. These flanges 44 are held radially in this groove by means of a locking member 50 formed of a split ring C section engaged from upstream on the annular rail 48 of the housing and on the upstream edges 44 of the sectors of ring.

L'organe de verrouillage 50 comprend deux branches cylindriques 52 et 54 s'étendant vers l'aval, radialement externe et radialement interne respectivement, qui sont reliées entre elles à leurs extrémités amont par une paroi radiale 56, et qui sont appliquées respectivement sur une face cylindrique radialement externe du rail 48 et sur les rebords circonférentiels 44 des secteurs d'anneau 20.The locking member 50 comprises two cylindrical branches 52 and 54 extending downstream, radially outer and radially inner respectively, which are interconnected at their upstream ends by a radial wall 56, and which are respectively applied to a radially outer cylindrical face of the rail 48 and on the circumferential edges 44 of the ring sectors 20.

Dans l'exemple représenté, l'organe de verrouillage 50 est empêché de se déplacer axialement vers l'amont par appui axial de sa paroi radiale 56 sur un rebord annulaire radial 58 de la paroi externe 22 du distributeur 12 situé en amont des secteurs d'anneau 20.In the example shown, the locking member 50 is prevented from moving axially upstream by axial support of its radial wall 56 on a radial annular flange 58 of the outer wall 22 of the distributor 12 located upstream of the sectors. ring 20.

Le rayon de courbure de l'organe de verrouillage 50 et du rail 48 est inférieur à celui des rebords 44 des secteurs d'anneau 20, ce qui permet de monter avec une certaine précontrainte radiale les rebords 44 des secteurs d'anneau dans la gorge 46 du rail, ces secteurs d'anneau étant localement en appui radial sur le fond de la gorge et sur la branche radialement interne 54 de l'organe de verrouillage, respectivement.The radius of curvature of the locking member 50 and of the rail 48 is less than that of the flanges 44 of the ring sectors 20, which makes it possible to mount with a certain radial prestress the flanges 44 of the ring sectors in the groove. 46 of the rail, these ring sectors being locally in radial support on the bottom of the groove and on the radially inner arm 54 of the locking member, respectively.

En fonctionnement, les rebords 44 des secteurs d'anneau 20 vibrent axialement et viennent user par frottement les faces amont et aval de la gorge 46 du rail.In operation, the flanges 44 of the ring sectors 20 vibrate axially and frictionally wear the upstream and downstream faces of the groove 46 of the rail.

Lorsque la face aval de la gorge 46 est très usée (comme cela est représenté en traits pointillés 60), les rebords 44 peuvent se déplacer vers l'aval en glissant sur la branche radialement interne 54 de l'organe de verrouillage, et se désengager de l'organe de verrouillage, ce qui peut entraîner notamment 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 46 is very worn (as shown in dotted lines 60), the flanges 44 can move downstream by sliding on the radially inner arm 54 of the locking member, and disengage of the locking member, which can in particular, to cause the blocks 34 of abradable material to be destroyed from the 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 une pièce d'appui rapportée et fixée sur l'extrémité aval de chaque secteur d'anneau.The invention makes it possible to provide a simple solution to this problem by means of a support piece attached and fixed on the downstream end of each ring sector.

Dans un mode de réalisation de l'invention représenté en figure 2, la pièce d'appui 70 a une section en F et comprend deux rebords 72 et 74 en portion de cylindre orientés vers l'aval, radialement externe et radialement interne respectivement, qui sont reliés entre eux à leurs extrémités amont par une paroi radiale 76.In one embodiment of the invention shown in FIG. 2, the support piece 70 has a section F and comprises two downstream radially outer and radially inner rims 72 and 74, respectively, which are connected to each other at their upstream ends by a radial wall 76.

La face radialement externe du rebord externe 72 est appliquée et fixée par soudage ou brasage sur une partie d'extrémité aval de la surface radialement interne de la paroi 32 du secteur d'anneau, et la paroi radiale 76 est appliquée et fixée par brasage ou soudage sur une face radiale du bloc 34 de matière abradable du secteur d'anneau 20.The radially outer face of the outer flange 72 is applied and fixed by welding or brazing on a downstream end portion of the radially inner surface of the wall 32 of the ring sector, and the radial wall 76 is applied and fixed by brazing or welding on a radial face of the block 34 of abradable material of the ring sector 20.

Chaque secteur d'anneau est maintenu radialement à son extrémité aval par appui radial du rebord interne 74 de la pièce 70 sur le rebord cylindrique 38 du distributeur aval, et par appui radial de sa paroi 32 sur la face radialement interne du rebord cylindrique 39 du carter 16.Each ring sector is held radially at its downstream end by radial support of the internal flange 74 of the part 70 on the cylindrical flange 38 of the downstream distributor, and by radial support of its wall 32 on the radially inner face of the cylindrical flange 39 of the casing 16.

Les secteurs d'anneau sont maintenus axialement à leurs extrémités amont comme précédemment décrit en référence à la figure 1, et à leurs extrémités aval par appui axial vers l'aval de la paroi radiale 76 de la pièce sur l'extrémité amont du rebord cylindrique 38 du distributeur aval 13.The ring sectors are held axially at their upstream ends as previously described with reference to FIG. 1, and at their downstream ends by axial support downstream of the radial wall 76 of the part on the upstream end of the cylindrical flange. 38 of the downstream distributor 13.

Les parois radiales 76 des pièces 70 sont séparées du rebord cylindrique 38 du distributeur 13 par un jeu axial 78 qui est inférieur à la longueur axiale 80 sur laquelle les rebords 44 des secteurs d'anneau sont en appui sur l'organe de verrouillage 50, de manière à ce que, en cas d'usure importante de la face aval de la gorge 46 du rail, les parois radiales 76 de la pièce 70 viennent en appui axial sur le rebord cylindrique 38 du distributeur et limite le recul possible des rebords 44 des secteurs d'anneau dans la gorge en les empêchant de se désengager de l'organe de verrouillage 50. Le jeu axial est par exemple compris entre 0,3 et 1,2mm environ.The radial walls 76 of the parts 70 are separated from the cylindrical flange 38 of the distributor 13 by an axial clearance 78 which is smaller than the axial length 80 on which the flanges 44 of the ring sectors bear on the locking member 50, so that, in the event of significant wear of the downstream face of the groove 46 of the rail, the radial walls 76 of the part 70 come to bear axially on the cylindrical flange 38 of the distributor and limit the possible retraction of the flanges 44 ring areas in the groove preventing them from disengaging from the locking member 50. The axial play is for example between 0.3 and 1.2mm approximately.

Aussi longtemps que le rail de carter 48 n'est pas usé ou est faiblement usé, les secteurs d'anneau 20 sont maintenus axialement sur le carter 16, comme précédemment décrit en référence à la figure 1, c'est-à-dire par appui axial des rebords 44 des secteurs d'anneau sur les faces amont et aval respectivement de la gorge 46 du rail.As long as the guard rail 48 is not worn or is weakly worn, the ring sectors 20 are held axially on the casing 16, as previously described with reference to FIG. 1, that is to say by axial support of the flanges 44 of the ring sectors on the upstream and downstream faces respectively of the groove 46 of the rail.

Lorsque la face orientée vers l'amont de la gorge est fortement usée ou a même complètement disparu (comme représenté en traits pointillés 82), les secteurs d'anneau 20 sont maintenus axialement vers l'aval par appui axial des parois radiales 76 des pièces 70 sur le rebord cylindrique 38 du distributeur aval.When the face facing upstream of the groove is heavily worn or has completely disappeared (as shown in dashed lines 82), the ring sectors 20 are held axially downstream by axial support of the radial walls 76 of the parts. 70 on the cylindrical rim 38 of the downstream distributor.

La pièce 70 peut être rapportée et fixée sur l'extrémité aval d'un secteur d'anneau existant de la technique antérieure. Il suffit pour cela de supprimer une partie d'extrémité aval du bloc 34 de matière abradable du secteur d'anneau et d'y fixer à la place par brasage ou soudage une pièce 70 d'appui axial et radial.Part 70 may be attached and secured to the downstream end of an existing ring sector of the prior art. To do this, it suffices to remove a downstream end portion of the block 34 of abradable material from the ring sector and to fix there instead by brazing or welding a piece 70 of axial and radial support.

En variante, la pièce d'appui peut comprendre uniquement des moyens d'appui axial sur le rebord amont 38 du distributeur, les secteurs d'anneau étant maintenus radialement vers l'intérieur à leurs extrémités aval par appui radial des blocs 34 sur ce rebord amont, comme c'est le cas dans la technique antérieure.Alternatively, the support piece may comprise only axial bearing means on the upstream flange 38 of the distributor, the ring sectors being held radially inwards at their downstream ends by radial support of the blocks 34 on this flange. upstream, as is the case in the prior art.

Claims (11)

Dispositif de fixation de secteurs d'anneau (20) autour d'une roue (18) de turbine dans une turbomachine, chaque secteur d'anneau (20) comprenant une paroi tronconique (32) qui porte un bloc de matière abradable (34) fixé sur sa surface interne et qui comporte à son extrémité amont un rebord circonférentiel (44) engagé dans une gorge annulaire radialement interne d'un rail annulaire (48) de carter et maintenu radialement dans cette gorge par un organe annulaire (50) de verrouillage à section en C qui est engagé axialement depuis l'amont sur le rail de carter et sur les rebords circonférentiels des secteurs d'anneau, caractérisé en ce que chaque secteur d'anneau (20) comprend à son extrémité aval une pièce (70) rapportée et fixée sur la paroi tronconique (32) et sur le bloc de matière abradable du secteur d'anneau, cette pièce pouvant venir en appui axial contre un élément fixe de la turbine pour empêcher le désengagement du rebord amont (44) de la paroi (32) de l'organe de verrouillage (50), le jeu axial (78) entre la pièce d'appui (70) et l'élément fixe étant inférieur à la longueur axiale (80) de l'appui du rebord amont (44) de la paroi (32) sur l'organe de verrouillage (50).Device for fixing ring sectors (20) around a turbine wheel (18) in a turbomachine, each ring sector (20) comprising a frustoconical wall (32) carrying a block of abradable material (34) fixed on its inner surface and which comprises at its upstream end a circumferential flange (44) engaged in a radially inner annular groove of an annular rail (48) housing and held radially in this groove by an annular member (50) locking with a C-section which is engaged axially from upstream on the casing rail and on the circumferential edges of the ring sectors, characterized in that each ring sector (20) comprises at its downstream end a piece (70) reported and fixed on the frustoconical wall (32) and on the block of abradable material of the ring sector, this part being able to bear axially against a fixed element of the turbine to prevent disengagement of the upstream edge (44) of the wall (32) of the locking member (50), the axial clearance (78) between the support piece (70) and the fixed element being less than the axial length (80) of the support of the upstream edge (44) of the wall (32) on the locking member (50). Dispositif selon la revendication 1, caractérisé en ce que la pièce d'appui (70) comprend des moyens pouvant venir en appui radial sur l'élément fixe.Device according to claim 1, characterized in that the support piece (70) comprises means that can bear radially on the fixed element. Dispositif selon la revendication 1 ou 2, caractérisé en ce que la pièce (70) est fixée sur l'extrémité aval de la paroi (32) et sur le bloc de matière abradable par brasage ou soudage.Device according to claim 1 or 2, characterized in that the piece (70) is fixed on the downstream end of the wall (32) and on the block of abradable material by brazing or welding. Dispositif selon l'une des revendications précédentes, caractérisé en ce que le jeu axial (78) entre la pièce d'appui (70) et l'élément fixe est compris entre 0,3 et 1,2mm environ.Device according to one of the preceding claims, characterized in that the axial play (78) between the support piece (70) and the fixed element is between 0.3 and 1.2mm approximately. Dispositif selon l'une des revendications précédentes, caractérisé en ce que la pièce d'appui (70) a une section en F.Device according to one of the preceding claims, characterized in that the support piece (70) has a section F. Dispositif selon la revendication 5, caractérisé en ce que la pièce d'appui (70) comprend deux rebords (72, 74) en portion de cylindre qui s'étendent vers l'aval, un de ces rebords (72) étant fixé sur une surface radialement interne de la paroi (32) du secteur d'anneau (20) et l'autre de ces rebords (74) pouvant venir en appui radial sur une face radialement externe d'un rebord cylindrique (38) de l'élément fixe.Device according to claim 5, characterized in that the support piece (70) comprises two flanges (72, 74) in cylinder portions which extend downstream, one of these flanges (72) being fixed on a radially inner surface of the wall (32) of the ring sector (20) and the other of these flanges (74) which can bear radially on a radially outer face of a cylindrical flange (38) of the fixed element . Dispositif selon l'une des revendications précédentes, caractérisé en ce que l'élément fixe fait partie d'un distributeur (13) de turbine.Device according to one of the preceding claims, characterized in that the fixed element is part of a turbine distributor (13). Turbomachine, telle qu'un turboréacteur ou un turbopropulseur d'avion, caractérisée en ce qu'elle comprend au moins un dispositif selon l'une des revendications précédentes.Turbomachine, such as a jet engine or an airplane turbo-prop engine, characterized in that it comprises at least one device according to one of the preceding claims. Secteur d'anneau (20) pour une turbine de turbomachine, comprenant une paroi tronconique (32) qui porte un bloc de matière abradable (34) fixé sur sa surface interne et qui comporte à son extrémité amont un rebord (44) d'accrochage sur un carter (16), caractérisé en ce qu'il comprend à son extrémité aval une pièce (70) d'appui axial et radial rapportée et fixée sur la paroi (32) et sur le bloc de matière abradable du secteur d'anneau.Ring sector (20) for a turbomachine turbine, comprising a frustoconical wall (32) carrying a block of abradable material (34) fixed on its inner surface and which has at its upstream end a flange (44) hooking on a casing (16), characterized in that it comprises at its downstream end a piece (70) of axial and radial bearing attached and fixed on the wall (32) and on the abradable material block of the ring sector. . Secteur d'anneau (20) selon la revendication 9, caractérisé en ce que la pièce d'appui (70) est fixée par soudure ou brasure sur le bloc de matière abradable et sur l'extrémité aval de la paroi (32) du secteur d'anneau.Ring sector (20) according to claim 9, characterized in that the support piece (70) is fixed by welding or brazing on the block of abradable material and on the downstream end of the wall (32) of the sector. ring. Turbine de turbomachine, caractérisée en ce qu'elle comprend au moins un dispositif selon l'une des revendications 1 à 7.Turbomachine turbine, characterized in that it comprises at least one device according to one of claims 1 to 7.
EP07290322.2A 2006-03-30 2007-03-14 Device for attaching ring sectors around a turbine wheel of a turbomachine Active EP1840339B1 (en)

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FR2923526A1 (en) * 2007-11-13 2009-05-15 Snecma Sa TURBINE OR TURBOMACHINE COMPRESSOR STAGE
FR2923527A1 (en) * 2007-11-13 2009-05-15 Snecma Sa STAGE OF TURBINE OR COMPRESSOR, IN PARTICULAR TURBOMACHINE
EP2060750A1 (en) * 2007-11-13 2009-05-20 Snecma Stage of a turbine or compressor, in particular of a turbomachine
EP2060744A1 (en) * 2007-11-13 2009-05-20 Snecma Stage of a turbine or turbomachine compressor
US8133013B2 (en) 2007-11-13 2012-03-13 Snecma Stage of a turbine or compressor, particularly for a turbomachine
US8277179B2 (en) 2007-11-13 2012-10-02 Snecma Turbine or compressor stage for a turbomachine
EP2112329A1 (en) * 2008-04-23 2009-10-28 Snecma Thermomechanical element rotating around a longitudinal axis, comprising at least one abradable crown intended for a labyrinth seal
FR2930593A1 (en) * 2008-04-23 2009-10-30 Snecma Sa THERMOMECHANICAL ROOM FOR REVOLUTION AROUND A LONGITUDINAL AXIS, COMPRISING AT LEAST ONE ABRADABLE CROWN FOR A SEALING LABYRINTH
US8128352B2 (en) 2008-04-23 2012-03-06 Snecma Thermomechanical part constituting a body of revolution about a longitudinal axis and including at least one abradable ring for a sealing labyrinth
FR2961556A1 (en) * 2010-06-16 2011-12-23 Snecma Turbine i.e. low pressure turbine, for e.g. turbojet engine of airplane, has axial and radial support units that are not in contact with casing to avoid heating, by conduction, of casing by sectorized ring during operation
FR2983518A1 (en) * 2011-12-06 2013-06-07 Snecma UNLOCKING DEVICE FOR AXIAL STOP OF A SEALED CROWN CONTACTED BY A MOBILE WHEEL OF AIRCRAFT TURBOMACHINE MODULE
WO2013083905A1 (en) * 2011-12-06 2013-06-13 Snecma Unlockable device for axially arresting a sealing ring with which an aircraft turbomachine module rotor wheel makes contact
JP2015500424A (en) * 2011-12-06 2015-01-05 スネクマ Releasable device for axially constraining a sealing ring in contact with an aircraft turbomachine module rotor wheel
US9957896B2 (en) 2011-12-06 2018-05-01 Snecma Unlockable device for axially arresting a sealing ring with which an aircraft turbomachine module rotor wheel makes contact
EP3078814B1 (en) * 2013-12-05 2019-10-23 IHI Corporation Turbine
EP2896796A1 (en) * 2014-01-20 2015-07-22 Techspace Aero S.A. Stator of an axial turbomachine and corresponding turbomachine
EP3196411A3 (en) * 2016-01-21 2017-08-23 General Electric Company Flow alignment devices to improve diffuser performance
FR3072713A1 (en) * 2017-10-23 2019-04-26 Safran Aircraft Engines TURBINE RING SECTOR FOR AIRCRAFT TURBOMACHINE
EP3591178A1 (en) * 2018-07-03 2020-01-08 Safran Aircraft Engines Aircraft turbine engine sealing module
FR3083563A1 (en) * 2018-07-03 2020-01-10 Safran Aircraft Engines AIRCRAFT TURBOMACHINE SEALING MODULE
US11035244B2 (en) 2018-07-03 2021-06-15 Safran Aircraft Engines Aircraft turbine engine sealing module
EP4028644B1 (en) * 2019-09-13 2023-06-07 Safran Aircraft Engines Turbomachine seal ring

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RU2403405C2 (en) 2010-11-10
FR2899274B1 (en) 2012-08-17
RU2007111675A (en) 2008-10-10
KR20070098660A (en) 2007-10-05
CN101046161B (en) 2011-06-15
FR2899274A1 (en) 2007-10-05
CN101046161A (en) 2007-10-03
HK1107387A1 (en) 2008-04-03
CA2582401A1 (en) 2007-09-30
EP1840339B1 (en) 2018-01-03
JP4820321B2 (en) 2011-11-24
US20070231127A1 (en) 2007-10-04
KR101369067B1 (en) 2014-02-28
JP2007270836A (en) 2007-10-18
CA2582401C (en) 2014-01-28
US7789619B2 (en) 2010-09-07

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