EP2839117B1 - Turbine stage for a turbomachine - Google Patents
Turbine stage for a turbomachine Download PDFInfo
- Publication number
- EP2839117B1 EP2839117B1 EP13722492.9A EP13722492A EP2839117B1 EP 2839117 B1 EP2839117 B1 EP 2839117B1 EP 13722492 A EP13722492 A EP 13722492A EP 2839117 B1 EP2839117 B1 EP 2839117B1
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- EP
- European Patent Office
- Prior art keywords
- nozzle
- ring
- wall
- downstream
- radially
- Prior art date
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- 238000011144 upstream manufacturing Methods 0.000 claims description 32
- 230000000295 complement effect Effects 0.000 claims description 5
- 238000007789 sealing Methods 0.000 claims description 3
- 230000000717 retained effect Effects 0.000 claims description 2
- 238000004519 manufacturing process Methods 0.000 description 3
- 230000014759 maintenance of location Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 241000920340 Pion Species 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 238000005476 soldering Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/246—Fastening of diaphragms or stator-rings
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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
- F01D11/005—Sealing means between non relatively rotating elements
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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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
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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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
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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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
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- 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
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
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- 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
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- 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
- F05D2240/12—Fluid guiding means, e.g. vanes
- F05D2240/128—Nozzles
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- 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
- F05D2240/90—Mounting on supporting structures or systems
- F05D2240/91—Mounting on supporting structures or systems on a stationary structure
Definitions
- the invention relates to a turbine stage for a turbomachine, such as an airplane turbojet or turboprop.
- a turbine stage of this type comprises a stationary distributor and a turbine wheel mounted downstream of the distributor and inside an annular housing.
- the distributor comprises two coaxial platforms extending one inside the other and interconnected by substantially radial vanes.
- the outer platform comprises two annular tabs, respectively upstream and downstream, which extend radially outwardly and which comprise at their outer peripheries means for attachment to the housing.
- the distributor is held radially by crankcase hooks.
- the downstream annular tab of the distributor is supported radially outwardly on a cylindrical rail of the casing and in axial support downstream on a split annular ring housed in an annular groove of the rail opening radially inwards.
- the wheel is formed of a rotor disc carrying blades at its periphery. It is mounted rotating inside a sectorized ring carried by the housing. Each ring sector comprises at its upstream end a C-section circumferential member which is engaged on the housing rail and which radially holds the rod in the aforementioned groove of the rail.
- the member C is engaged on the casing rail by axial translation from downstream followed by a tilting movement of the ring sector.
- the ring sector is first arranged so that its upstream end is located radially outwardly with respect to its downstream end.
- the ring sector is moved upstream, the C member is engaged on the casing rail over a given axial distance, then the downstream end of the ring sector is tilted radially outward to complete the commitment of the body to the rail.
- the upstream circumferential edge of the radially inner wall of the C-member of each ring sector is separated by an axial clearance of the downstream annular tab of the distributor, this clearance being necessary to allow the aforementioned mounting by tilting of the ring sector. Due to this axial clearance, the radially inner wall of the C-shaped member extends radially inside a small portion of the axial dimension of the rod, which is in principle sufficient to maintain the rod in the throat radially. .
- the above game is of the order of 1.9 mm +/- 0.25.
- EP 1 462 616 A2 , US 5 18 507 A , US 5,848,854 A , US 2005/004810 A1 and FR 2 941 488 A1 disclose turbine stages of the prior art.
- the upstream end portion of the radially inner wall of the C-member which retains the rod may have an axial dimension that is insufficient or even zero under the conditions the most unfavorable. The risk of disengagement of the throat ring is then possible, which would result in the loss of axial blockage downstream of the distributor and would not be acceptable.
- the invention aims to provide a simple, effective and economical solution to this problem of the prior art.
- a turbine stage for a turbomachine comprising a fixed distributor and a wheel mounted downstream of the distributor and inside an annular housing, the distributor being hooked to the housing and being retained axially downstream.
- ring member comprising at least one cooperating notch with complementary means of the distributor to prevent rotation of the ring sector vis-à-vis the distributor.
- the C-shaped member is configured so that its radially inner wall extends axially over the entire axial dimension of the ring and thus ensures the radial retention of the ring whatever the manufacturing tolerances and the differential expansions of the parts.
- the distributor comprises a recess in which the upstream end portion of the radially inner wall of the member is intended to be engaged.
- the upstream end portion of the radially inner wall of the C-member of each ring sector can be separated by an axial clearance of the bottom or a radial wall of the aforementioned recess of the distributor, to allow this mounting .
- This axial clearance can be of the same order of magnitude as that described above, that is to say of the order of about 2 mm.
- each C-member may also be separated by a small or no radial clearance of an outer cylindrical wall of the recess, this wall extending around this end portion which forms radial retaining means of the dispenser.
- the crankcase hook of the prior art which was dedicated to this radial restraint, can therefore be eliminated, which makes it possible to simplify the distributor and to reduce the crankcase mass by approximately 3 kg in a particular embodiment of the invention. .
- Blocking rotation of the ring by the distributor avoids the installation of a specific pin anti-rotation of the ring on the housing which would require increasing the thickness and diameter of the housing to ensure good performance mechanical pion and increase the mass of the housing.
- the anti-rotation according to the invention thus makes it possible to reduce the radial size of the turbine stage.
- the complementary means of the dispenser include local thicknesses of the dispenser.
- the radially inner wall of the C-shaped member of each ring sector has an axial dimension greater than that of the radially outer wall of this member.
- the distributor may comprise at its downstream end a radially outer annular lug having an outer cylindrical surface radially bearing on the casing rail and a downstream radial bearing surface on the rod, the aforementioned recess (s) opening towards the downstream end at less in part on this downstream radial surface.
- the dispenser can be sectored and formed of several sectors arranged circumferentially end to end.
- the aforementioned recesses may have a circumferential orientation, their circumferential ends opening on the circumferential ends of the distributor sectors or being closed by lateral webs of the distributor sectors.
- the lateral edges facing annular tab sectors of the distributor sectors preferably comprise straight grooves housing sealing strips which extend radially outwardly close to the crankcase rail and / or the rod, the grooves extending in a plane located upstream of the aforementioned recesses, or extending at least partly in the aforementioned lateral webs of the distributor sectors. These slats help to limit intersector gas leaks.
- the invention relates to a turbomachine, such as a turbojet engine or a turboprop engine, characterized in that it comprises at least one turbine stage as described above.
- FIG. 1 represents a low-pressure turbine 10 of a turbomachine such as a turbojet or an airplane turboprop, this turbine comprising several stages each comprising a distributor 12 hooked to a casing 14 of the turbine, and a impeller 16 mounted downstream of the distributor 12 and rotating in a ring 18 hooked to the casing 14.
- the distributor 12 comprises two coaxial platforms, respectively internal and external 20, interconnected by substantially radial vanes.
- the outer platform 20 comprises two annular tabs, respectively upstream 22 and downstream 24, which extend radially outwardly and which comprise means for attachment to the housing.
- the tabs 22, 24 of the distributor 12 comprise at their outer peripheries upstream cylindrical rims hooking on cylindrical rails 26 of the housing.
- the cylindrical rim of the downstream leg 24 comprises at least one radial notch in which is engaged a radial pin 28 carried by the casing 14 and intended to lock in rotation the distributor relative to the housing.
- the downstream leg 24 of the distributor 12 comprises a radially outer cylindrical surface 30 of radial support on another rail 32 of the housing and a downstream radial surface 34 of axial support on a split annular ring 36 housed in an annular groove 38 of this rail , this groove 38 opening radially inwards ( figure 2 ).
- This ring 36 ensures the axial retention downstream of the distributor 12.
- the ring 18 is sectored and formed of several sectors which are worn circumferentially end to end by the casing 14 of the turbine.
- Each ring sector 18 comprises a cylindrical or frustoconical wall 40 and a block 42 of abradable material fixed by soldering and / or welding on the radially inner surface of the wall 40, this block 42 being of the honeycomb type and being intended to wear by friction on external annular wipers of the blades of the wheel 16 to minimize the radial clearances between the wheel and the ring sectors 18.
- Each ring sector 18 comprises at its upstream end a circumferential member 44 with a C-section whose opening opens upstream and which is engaged axially downstream on the casing rail 32 and the ring 36 (FIG. figure 2 ).
- each ring sector 18 comprises two cylindrical walls 46 and 48 extending upstream, radially outer and radially inner respectively, which are interconnected at their downstream ends by a radial wall 50.
- the wall 46 of the member is applied radially on a radially outer cylindrical face of the rail 32 and its inner wall 48 extends radially inside a portion of the rod 36, as shown in FIG. figure 2 .
- the inner wall 48 of each member 44 has an axial dimension smaller than that of its outer wall 46 and the upstream circumferential edge of this inner wall is separated from the bearing surface 34 of the distributor 12 by axial clearance. J large enough to allow mounting ring sectors 18 by tilting, as described in the above.
- the upstream end portion of the inner wall 48 of each member 44 extends over a small axial dimension L only of the ring 36, which may not be sufficient to retain it in the groove 38, particularly in the most unfavorable conditions where this distance L is decreased because of the manufacturing tolerances of the parts and the differential thermal expansions of the parts in operation.
- the invention overcomes this problem by extending the internal wall of the C-member of each ring sector, the upstream end portion of this inner wall being housed in a corresponding recess of the distributor for allow mounting of the ring sectors.
- the distributor 112 represented in Figures 3 to 7 differs from that described in the above in particular in that its downstream annular tab 124 comprises recesses of the aforementioned type which, in the example shown, are formed by circumferential grooves 160, 162 of the outer periphery of the tab 124, which open axially downstream ( Figures 3, 4 and 5 ).
- the radially outer portions of these grooves 160, 162 open out on the radial surface 134 of the downstream tab 124 intended to bear on the rod 136 carried by the rail 132 of the housing 114.
- the dispenser 112 is sectored and comprises a plurality of dispenser sectors arranged circumferentially end to end.
- the figure 5 represents only a portion of a dispenser sector (only the outer platform 120 and its annular legs 122, 124 are shown).
- Each manifold sector 112 includes an annular groove 160 extending over more than half the circumferential dimension of the sector, and an annular groove 162 of smaller size. These grooves 160, 162 are located on the same circumference and are separated from each other by an axial extra thickness 164 of the downstream tab 124.
- Each groove 160, 162 has a circumferential end closed by the excess thickness 164 above, and the other circumferential end of each groove is closed by a web of material 166 of the downstream tab 124, the web extending axially downstream.
- the lateral edges facing the distributor sectors 112 comprise straight grooves housing sealing slats (not shown).
- Each side edge comprises a rectilinear groove 170 extending along the longitudinal edge of the outer platform 124, a straight groove 172 extending radially along the side edge of an upstream leg sector 122, and a straight groove 174 extending radially along the lateral edge of a downstream leg sector 124.
- Each groove 174 is formed in part in the aforementioned web 166 and extends to the immediate vicinity of the outer cylindrical surface 130 of the downstream leg .
- the ring sectors 118 represented in Figures 3 to 7 differ from those described above in particular in that the radially inner walls 148 of their C-members 144 have an axial dimension greater than that of their radially outer walls 146. As can be seen in FIG. figure 1 , the radially inner wall 148 of the body 144 of each ring sector 118 extends over the entire axial dimension of the rod 136 and beyond this ring in the upstream direction into the above-mentioned grooves 160, 162 of the distributor.
- the figure 6 is a ring sector 118.
- the inner wall 148 of the member 144 comprises two radial notches 180, 182 in the example shown, these notches being intended to cooperate with complementary means of the distributor to immobilize the sector vis-à- dispenser screw, as will be described in more detail in the following.
- the notches 180, 182 have a substantially U-shaped shape and are defined by two parallel lateral edges connected at their downstream ends by a circumferential edge.
- each side edge of a notch is connected to the circumferential edge of this slot by a circular section orifice 184 for reducing the stress concentrations in operation in this area.
- the notch 180 of the inner wall 148 of the member 144 of each ring sector 118 is situated substantially in the middle of this wall and is intended to receive the local extra thickness 164 of the downstream tab 124 of the distributor.
- the ring sectors 118 are circumferentially offset from the manifold sectors 112, so that the longitudinal edges of the platforms 120 of the manifold sectors are not axially aligned with those of the ring sectors 118. guarantees in particular a better seal of the assembly.
- the notch 182 of the inner wall 148 of the member 144 of each ring sector 118 is intended to receive the material webs 166 facing two adjacent distributor sectors 112, as can be seen in FIG. figure 7 .
- the notches 180, 182 define between them three downstream end portions 184, 186, 188 distinct from the internal wall 148 of the member, one 184 being engaged in a part of the groove 160 of a distributor sector 112, the other 186 being engaged in the groove 162 of this sector and the last 188 being engaged in a part of the groove 160 of an adjacent distributor sector ( figure 7 ).
- the figure 4 represents a step of mounting a ring sector 118 on the housing 114.
- the ring sector 118 is disposed obliquely so that its upstream end is located radially outwardly with respect to its downstream end.
- the ring sector is moved from the downstream to the housing rail 132 until this rail engages between the walls 146, 148 of the C-member 144 of the sector.
- the internal wall 148 of the member then engages in the aforementioned grooves 160, 162 of the downstream tab 124 of the distributor 112, as shown in FIG. figure 4 .
- the downstream end of the ring sector 118 is then tilted radially outwardly to apply this downstream end against a rail of the housing (arrow 190).
- the tilting is performed by rotating the ring sector 118 around a point located substantially in C.
- FIGS 8 to 12 represent an alternative embodiment of the invention in which the distributor sectors 212 are distinguished from those 112 previously described essentially in that the grooves 260, 262 for receiving the walls
- the internal members 246 of the C 244 members of the ring sectors 218 have one of their circumferential ends which is not closed and which therefore opens in the circumferential direction at one of the lateral edges of a distributor sector.
- the groove 260 of greater circumferential dimension of a distributor sector 212 has a circumferential end closed by the local excess thickness 264 above and a circumferential end which opens on one of the lateral edges of the sector.
- the groove 262 of smaller circumferential dimension of a dispenser sector 212 has a circumferential end closed by the aforementioned local excess thickness 264 and a circumferential end which opens on the other side edges of the sector.
- the rectilinear grooves 270 formed in the lateral edges of the downstream leg sectors 224 of the distributor sectors 212 extend here substantially radially in a plane situated upstream of the grooves 260, 262.
- the radially external ends of these grooves 270 are situated in the vicinity immediately of the outer cylindrical surface 230 of the tab 224.
- the ring sectors 218 are distinguished from those 118 previously described essentially in that the radially inner walls 248 of their members C each comprise a single notch 280 which is similar to the notch 180 described above, this notch 280 being intended for receiving the above-mentioned allowance 264 from a distributor sector.
- the notch 280 defines two downstream end portions 284, 286 separate from the inner wall 248 of the member, one 284 being engaged in a portion of the groove 260 of a distributor sector 212 and the other 286 being engaged in the groove 262 of this sector as well as in a portion of the groove 260 of an adjacent distributor sector ( figure 12 ).
- the ring sectors 218 are mounted in the same manner as that described above with reference to the figure 4 .
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Description
L'invention concerne un étage de turbine pour une turbomachine, telle qu'un turboréacteur ou un turbopropulseur d'avion.The invention relates to a turbine stage for a turbomachine, such as an airplane turbojet or turboprop.
Typiquement, un étage de turbine de ce type comprend un distributeur fixe et une roue de turbine montée en aval du distributeur et à l'intérieur d'un carter annulaire. Le distributeur comprend deux plates-formes coaxiales s'étendant l'une à l'intérieur de l'autre et reliées entre elles par des aubes sensiblement radiales. La plate-forme externe comprend deux pattes annulaires, respectivement amont et aval, qui s'étendent radialement vers l'extérieur et qui comportent à leurs périphéries externes des moyens d'accrochage sur le carter. Le distributeur est maintenu radialement par des crochets du carter. La patte annulaire aval du distributeur est en appui radial vers l'extérieur sur un rail cylindrique du carter et en appui axial vers l'aval sur un jonc annulaire fendu logé dans une gorge annulaire du rail débouchant radialement vers l'intérieur.Typically, a turbine stage of this type comprises a stationary distributor and a turbine wheel mounted downstream of the distributor and inside an annular housing. The distributor comprises two coaxial platforms extending one inside the other and interconnected by substantially radial vanes. The outer platform comprises two annular tabs, respectively upstream and downstream, which extend radially outwardly and which comprise at their outer peripheries means for attachment to the housing. The distributor is held radially by crankcase hooks. The downstream annular tab of the distributor is supported radially outwardly on a cylindrical rail of the casing and in axial support downstream on a split annular ring housed in an annular groove of the rail opening radially inwards.
La roue est formée d'un disque de rotor portant à sa périphérie des aubes. Elle est montée tournante à l'intérieur d'un anneau sectorisé porté par le carter. Chaque secteur d'anneau comprend à son extrémité amont un organe circonférentiel à section en C qui est engagé sur le rail de carter et qui maintient radialement le jonc dans la gorge précitée du rail.The wheel is formed of a rotor disc carrying blades at its periphery. It is mounted rotating inside a sectorized ring carried by the housing. Each ring sector comprises at its upstream end a C-section circumferential member which is engaged on the housing rail and which radially holds the rod in the aforementioned groove of the rail.
L'organe en C est engagé sur le rail de carter par une translation axiale depuis l'aval suivie d'un mouvement de basculement du secteur d'anneau. Pour cela, le secteur d'anneau est d'abord disposé de sorte que son extrémité amont soit située radialement à l'extérieur par rapport à son extrémité aval. Le secteur d'anneau est déplacé vers l'amont, l'organe en C est engagé sur le rail de carter sur une distance axiale donnée, puis l'extrémité aval du secteur d'anneau est basculée radialement vers l'extérieur pour terminer l'engagement de l'organe sur le rail.The member C is engaged on the casing rail by axial translation from downstream followed by a tilting movement of the ring sector. For this, the ring sector is first arranged so that its upstream end is located radially outwardly with respect to its downstream end. The ring sector is moved upstream, the C member is engaged on the casing rail over a given axial distance, then the downstream end of the ring sector is tilted radially outward to complete the commitment of the body to the rail.
Dans la technique actuelle, le bord circonférentiel amont de la paroi radialement interne de l'organe en C de chaque secteur d'anneau est séparé par un jeu axial de la patte annulaire aval du distributeur, ce jeu étant nécessaire pour autoriser le montage précité par basculement du secteur d'anneau. Du fait de ce jeu axial, la paroi radialement interne de l'organe en C s'étend radialement à l'intérieur d'une petite partie de la dimension axiale du jonc, qui est en principe suffisante pour maintenir radialement le jonc dans la gorge. Dans un cas particulier de réalisation, le jeu précité est de l'ordre de 1,9mm +/-0,25.
L'invention a pour but d'apporter une solution simple, efficace et économique à ce problème de la technique antérieure.The invention aims to provide a simple, effective and economical solution to this problem of the prior art.
Elle propose à cet effet un étage de turbine pour une turbomachine, comprenant un distributeur fixe et une roue montée en aval du distributeur et à l'intérieur d'un carter annulaire, le distributeur étant accroché au carter et étant retenu axialement vers l'aval par appui sur un jonc annulaire fendu monté dans une gorge annulaire d'un rail du carter, la roue étant montée à l'intérieur d'un anneau sectorisé porté par le carter, les secteurs d'anneau comprenant chacun à leurs extrémités amont un organe à section en C qui est engagé sur le rail de carter et qui maintient radialement le jonc dans la gorge précitée, caractérisé en ce que la paroi radialement interne de l'organe en C de chaque secteur d'anneau s'étend à l'intérieur du jonc sur toute la dimension axiale de ce dernier et sa partie d'extrémité amont est engagée dans au moins un évidement du distributeur, le bord circonférentiel amont de la paroi radialement interne de l'organe en C de chaque secteur d'anneau comprenant au moins une encoche coopérant avec des moyens complémentaires du distributeur pour empêcher la rotation du secteur d'anneau vis-à-vis du distributeur.It proposes for this purpose a turbine stage for a turbomachine, comprising a fixed distributor and a wheel mounted downstream of the distributor and inside an annular housing, the distributor being hooked to the housing and being retained axially downstream. by pressing on a split annular ring mounted in an annular groove of a rail of the housing, the wheel being mounted inside a sectorized ring carried by the casing, the ring sectors each comprising at their upstream ends an element C-section which is engaged on the housing rail and which holds the rod radially in the aforementioned groove, characterized in that the radially inner wall of the C-member of each ring sector extends inside. of the rod over the entire axial dimension of the latter and its upstream end portion is engaged in at least one recess of the distributor, the upstream circumferential edge of the radially inner wall of the C-shaped member of each section. ring member comprising at least one cooperating notch with complementary means of the distributor to prevent rotation of the ring sector vis-à-vis the distributor.
Selon l'invention, l'organe en C est configuré pour que sa paroi radialement interne s'étende axialement sur toute la dimension axiale du jonc et assure ainsi la retenue radiale du jonc quelles que soient les tolérances de fabrication et les dilatations différentielles des pièces. Pour autoriser le montage de cet organe en C, en particulier par basculement, comme décrit dans ce qui précède, le distributeur comprend un évidement dans lequel la partie d'extrémité amont de la paroi radialement interne de l'organe est destinée à être engagée.According to the invention, the C-shaped member is configured so that its radially inner wall extends axially over the entire axial dimension of the ring and thus ensures the radial retention of the ring whatever the manufacturing tolerances and the differential expansions of the parts. . To allow the mounting of this member C, in particular by tilting, as described in the foregoing, the distributor comprises a recess in which the upstream end portion of the radially inner wall of the member is intended to be engaged.
La partie d'extrémité amont de la paroi radialement interne de l'organe en C de chaque secteur d'anneau peut être séparée par un jeu axial du fond ou d'une paroi radiale de l'évidement précité du distributeur, pour autoriser ce montage. Ce jeu axial peut être du même ordre de grandeur que celui décrit précédemment, c'est-à-dire de l'ordre de 2mm environ.The upstream end portion of the radially inner wall of the C-member of each ring sector can be separated by an axial clearance of the bottom or a radial wall of the aforementioned recess of the distributor, to allow this mounting . This axial clearance can be of the same order of magnitude as that described above, that is to say of the order of about 2 mm.
La partie d'extrémité amont de la paroi radialement interne de chaque organe en C peut également être séparée par un jeu radial faible ou nul d'une paroi cylindrique externe de l'évidement, cette paroi s'étendant autour de cette partie d'extrémité qui forme des moyens de retenue radiale du distributeur. Le crochet de carter de la technique antérieure, qui était dédié à cette retenue radiale, peut donc être supprimé, ce qui permet de simplifier le distributeur et de réduire la masse du carter d'environ 3kg dans un cas particulier de réalisation de l'invention.The upstream end portion of the radially inner wall of each C-member may also be separated by a small or no radial clearance of an outer cylindrical wall of the recess, this wall extending around this end portion which forms radial retaining means of the dispenser. The crankcase hook of the prior art, which was dedicated to this radial restraint, can therefore be eliminated, which makes it possible to simplify the distributor and to reduce the crankcase mass by approximately 3 kg in a particular embodiment of the invention. .
Le blocage en rotation de l'anneau par le distributeur évite l'installation d'un pion spécifique d'anti-rotation de l'anneau sur le carter qui nécessiterait d'augmenter l'épaisseur et le diamètre du carter pour assurer une bonne tenue mécanique du pion et augmenterait la masse du carter.Blocking rotation of the ring by the distributor avoids the installation of a specific pin anti-rotation of the ring on the housing which would require increasing the thickness and diameter of the housing to ensure good performance mechanical pion and increase the mass of the housing.
L'anti-rotation selon l'invention permet ainsi de réduire l'encombrement radial de l'étage de turbine.The anti-rotation according to the invention thus makes it possible to reduce the radial size of the turbine stage.
Selon un autre aspect de l'invention, les moyens complémentaires du distributeur comprennent des surépaisseurs locales du distributeur.According to another aspect of the invention, the complementary means of the dispenser include local thicknesses of the dispenser.
Selon une autre caractéristique de l'invention, la paroi radialement interne de l'organe en C de chaque secteur d'anneau a une dimension axiale supérieure à celle de la paroi radialement externe de cet organe.According to another characteristic of the invention, the radially inner wall of the C-shaped member of each ring sector has an axial dimension greater than that of the radially outer wall of this member.
Le distributeur peut comprendre à son extrémité aval une patte annulaire radialement externe comportant une surface cylindrique externe d'appui radial sur le rail de carter et une surface radiale aval d'appui sur le jonc, le ou les évidements précités débouchant vers l'aval au moins en partie sur cette surface radiale aval.The distributor may comprise at its downstream end a radially outer annular lug having an outer cylindrical surface radially bearing on the casing rail and a downstream radial bearing surface on the rod, the aforementioned recess (s) opening towards the downstream end at less in part on this downstream radial surface.
Le distributeur peut être sectorisé et formé de plusieurs secteurs disposés circonférentiellement bout à bout. Les évidements précités peuvent avoir une orientation circonférentielle, leurs extrémités circonférentielles débouchant sur les extrémités circonférentielles des secteurs de distributeur ou étant fermées par des voiles latéraux des secteurs de distributeur.The dispenser can be sectored and formed of several sectors arranged circumferentially end to end. The aforementioned recesses may have a circumferential orientation, their circumferential ends opening on the circumferential ends of the distributor sectors or being closed by lateral webs of the distributor sectors.
Les bords latéraux en regard des secteurs de patte annulaire des secteurs de distributeur comportent de préférence des rainures rectilignes de logement de lamelles d'étanchéité qui s'étendent radialement vers l'extérieur jusqu'à proximité du rail de carter et/ou du jonc, les rainures s'étendant dans un plan situé en amont des évidements précités, ou s'étendant au moins en partie dans les voiles latéraux précités des secteurs de distributeur. Ces lamelles permettent de limiter les fuites de gaz intersecteurs.The lateral edges facing annular tab sectors of the distributor sectors preferably comprise straight grooves housing sealing strips which extend radially outwardly close to the crankcase rail and / or the rod, the grooves extending in a plane located upstream of the aforementioned recesses, or extending at least partly in the aforementioned lateral webs of the distributor sectors. These slats help to limit intersector gas leaks.
L'invention concerne enfin une turbomachine, telle qu'un turboréacteur ou un turbopropulseur d'avion, caractérisée en ce qu'elle comprend au moins un étage de turbine tel que décrit ci-dessus.Finally, the invention relates to a turbomachine, such as a turbojet engine or a turboprop engine, characterized in that it comprises at least one turbine stage as described above.
L'invention sera mieux comprise et d'autres détails, avantages et caractéristiques de l'invention apparaîtront plus clairement à la lecture de la description suivante faite à titre d'exemple non limitatif et en référence aux dessins annexés, dans lesquels :
- la
figure 1 est une demi-vue schématique partielle en coupe axiale d'un étage de turbine d'une turbomachine, selon la technique antérieure ; - la
figure 2 est une vue à plus grande échelle d'une partie de lafigure 1 ; - la
figure 3 est une demi-vue schématique partielle en coupe axiale d'un étage de turbine d'une turbomachine, selon l'invention ; - la
figure 4 est une vue à plus grande échelle d'une partie de lafigure 3 et représente une étape de montage par basculement d'un secteur d'anneau ; - la
figure 5 est une vue schématique en perspective d'une plate-forme externe d'un secteur de distributeur selon l'invention ; - la
figure 6 est une vue schématique en perspective d'un secteur d'anneau selon l'invention ; - la
figure 7 est une vue schématique en perspective de plates-formes externes et de secteurs d'anneau du type de ceux desfigures 5 et 6 , en position de montage ; - la
figure 8 est une vue correspondant à lafigure 3 et représentant une variante de réalisation de l'étage de turbine selon l'invention ; - la
figure 9 est une vue schématique partielle en perspective de l'étage de lafigure 8 ; - la
figure 10 est une vue schématique en perspective d'une plate-forme externe d'un secteur de distributeur selon l'invention ; - la
figure 11 est une vue schématique en perspective d'un secteur d'anneau selon l'invention ; - la
figure 12 est une vue schématique en perspective de plates-formes externes et de secteurs d'anneau du type de ceux desfigures 10 et 11 , en position de montage.
- the
figure 1 is a partial schematic half-view in axial section of a turbine stage of a turbomachine, according to the prior art; - the
figure 2 is a larger-scale view of some of thefigure 1 ; - the
figure 3 is a partial schematic half-view in axial section of a turbine stage of a turbomachine, according to the invention; - the
figure 4 is a larger-scale view of some of thefigure 3 and represents a tilting mounting step of a ring sector; - the
figure 5 is a schematic perspective view of an external platform of a dispenser sector according to the invention; - the
figure 6 is a schematic perspective view of a ring sector according to the invention; - the
figure 7 is a schematic perspective view of external platforms and ring sectors of the type of those ofFigures 5 and 6 , in mounting position; - the
figure 8 is a view corresponding to thefigure 3 and showing an alternative embodiment of the turbine stage according to the invention; - the
figure 9 is a partial schematic perspective view of the floor of thefigure 8 ; - the
figure 10 is a schematic perspective view of an external platform of a dispenser sector according to the invention; - the
figure 11 is a schematic perspective view of a ring sector according to the invention; - the
figure 12 is a schematic perspective view of external platforms and ring sectors of the type of those ofFigures 10 and 11 , in mounting position.
On se réfère d'abord à la
Le distributeur 12 comprend deux plates-formes coaxiales, respectivement interne et externe 20, reliées entre elles par des aubes sensiblement radiales. La plate-forme externe 20 comprend deux pattes annulaires, respectivement amont 22 et aval 24, qui s'étendent radialement vers l'extérieur et qui comportent des moyens d'accrochage sur le carter.The
Les pattes 22, 24 du distributeur 12 comprennent à leurs périphéries externes des rebords cylindriques amont d'accrochage sur des rails cylindriques 26 du carter. Le rebord cylindrique de la patte aval 24 comprend au moins une encoche radiale dans laquelle est engagé un pion radial 28 porté par le carter 14 et destiné à bloquer en rotation le distributeur par rapport au carter.The
La patte aval 24 du distributeur 12 comprend une surface cylindrique radialement externe 30 d'appui radial sur un autre rail 32 du carter et une surface radiale aval 34 d'appui axial sur un jonc annulaire 36 fendu logé dans une gorge annulaire 38 de ce rail, cette gorge 38 débouchant radialement vers l'intérieur (
L'anneau 18 est sectorisé et formé de plusieurs secteurs qui sont portés circonférentiellement bout à bout par le carter 14 de la turbine.The
Chaque secteur d'anneau 18 comprend une paroi cylindrique ou tronconique 40 et un bloc 42 de matière abradable fixé par brasage et/ou soudage sur la surface radialement interne de la paroi 40, ce bloc 42 étant du type en nid d'abeille et étant destiné à s'user par frottement sur des léchettes annulaires externes des aubes de la roue 16 pour minimiser les jeux radiaux entre la roue et les secteurs d'anneau 18.Each
Chaque secteur d'anneau 18 comprend à son extrémité amont un organe circonférentiel 44 à section en C dont l'ouverture débouche vers l'amont et qui est engagé axialement depuis l'aval sur le rail de carter 32 et le jonc 36 (
L'organe 44 de chaque secteur d'anneau 18 comprend deux parois cylindriques 46 et 48 s'étendant vers l'amont, radialement externe et radialement interne respectivement, qui sont reliées entre elles à leurs extrémités aval par une paroi radiale 50. La paroi 46 de l'organe est appliquée radialement sur une face cylindrique radialement externe du rail 32 et sa paroi interne 48 s'étend radialement à l'intérieur d'une partie du jonc 36, comme cela est représenté en
Dans la technique actuelle, la paroi interne 48 de chaque organe 44 a une dimension axiale inférieure à celle de sa paroi externe 46 et le bord circonférentiel amont de cette paroi interne est séparé de la surface d'appui 34 du distributeur 12 par un jeu axial J suffisamment grand pour autoriser le montage des secteurs d'anneau 18 par basculement, comme décrit dans ce qui précède. De ce fait, la partie d'extrémité amont de la paroi interne 48 de chaque organe 44 s'étend sur une petite dimension axiale L seulement du jonc 36, qui peut ne pas être suffisante pour le retenir dans la gorge 38, en particulier dans les conditions les plus défavorables où cette distance L est diminuée du fait des tolérances de fabrication des pièces et des dilations thermiques différentielles des pièces en fonctionnement.In the present technique, the
L'invention permet de remédier à ce problème grâce à l'allongement de la paroi interne de l'organe en C de chaque secteur d'anneau, la partie d'extrémité amont de cette paroi interne étant logée dans un évidement correspondant du distributeur pour autoriser le montage des secteurs d'anneau.The invention overcomes this problem by extending the internal wall of the C-member of each ring sector, the upstream end portion of this inner wall being housed in a corresponding recess of the distributor for allow mounting of the ring sectors.
On se réfère d'abord aux
Le distributeur 112 représenté aux
Le distributeur 112 est sectorisé et comprend plusieurs secteurs de distributeur disposés circonférentiellement bout à bout. La
Chaque secteur de distributeur 112 comprend une gorge annulaire 160 s'étendant sur plus de la moitié de la dimension circonférentielle du secteur, et une gorge annulaire 162 de plus petite dimension. Ces gorges 160, 162 sont situées sur une même circonférence et sont séparées l'une de l'autre par une surépaisseur axiale 164 de la patte aval 124.Each
Chaque gorge 160, 162 a une extrémité circonférentielle fermée par la surépaisseur 164 précitée, et l'autre extrémité circonférentielle de chaque gorge est fermée par un voile de matière 166 de la patte aval 124, ce voile s'étendant axialement vers l'aval.Each
Comme cela est visible aux
Les secteurs d'anneau 118 représentés aux
La
Les encoches 180, 182 ont une forme sensiblement en U et sont définies par deux bords latéraux parallèles reliés à leurs extrémités aval par un bord circonférentiel. Dans l'exemple représenté, chaque bord latéral d'une encoche est relié au bord circonférentiel de cette encoche par un orifice 184 à section circulaire destiné à réduire les concentrations de contraintes en fonctionnement dans cette zone.The
L'encoche 180 de la paroi interne 148 de l'organe 144 de chaque secteur d'anneau 118 est située sensiblement au milieu de cette paroi et est destinée à recevoir la surépaisseur locale 164 de la patte aval 124 du distributeur.The
Comme cela est visible en
L'encoche 182 de la paroi interne 148 de l'organe 144 de chaque secteur d'anneau 118 est destinée à recevoir les voiles de matière 166 en regard de deux secteurs de distributeur 112 adjacents, comme cela est visible en
Comme cela est bien visible en
La
En position de montage représentée en
On se réfère désormais aux
La gorge 260 de plus grande dimension circonférentielle d'un secteur de distributeur 212 a une extrémité circonférentielle fermée par la surépaisseur locale 264 précitée et une extrémité circonférentielle qui débouche sur l'un des bords latéraux du secteur. La gorge 262 de plus petite dimension circonférentielle d'un secteur de distributeur 212 a une extrémité circonférentielle fermée par la surépaisseur locale 264 précitée et une extrémité circonférentielle qui débouche sur l'autre des bords latéraux du secteur.The
Les rainures rectilignes 270 formées dans les bords latéraux des secteurs de patte aval 224 des secteurs de distributeur 212 s'étendent ici sensiblement radialement dans un plan situé en amont des gorges 260, 262. Les extrémités radialement externes de ces rainures 270 sont situées au voisinage immédiat de la surface cylindrique externe 230 de la patte 224.The rectilinear grooves 270 formed in the lateral edges of the
Les secteurs d'anneau 218 se distinguent de ceux 118 précédemment décrits essentiellement en ce que les parois radialement internes 248 de leurs organes en C comprennent chacune une seule encoche 280 qui est similaire à l'encoche 180 décrite précédemment, cette encoche 280 étant destinée à recevoir la surépaisseur 264 précitée d'un secteur de distributeur.The
Comme cela est visible en
Les secteurs d'anneau 218 sont montés de la même façon que celle décrite précédemment en référence à la
Claims (8)
- A turbine stage for a turbine engine, the stage comprising a stationary nozzle (112) and a wheel mounted downstream from the nozzle and inside an annular casing (114), the nozzle being attached to the casing and being retained axially downstream by bearing against an annular split ring (136) mounted in an annular groove of a rail (132) of the casing, the wheel being mounted inside a sectorized ring (118) carried by the casing, each ring sector including at its upstream end a member (144) of C-shaped section that is engaged on the casing rail and that holds the split ring radially in the above-mentioned groove, the stage being characterized in that the radially inner wall (148) of the C-shaped member of each ring sector extends inside the split ring over the entire axial dimension thereof and its upstream end portion is engaged in at least one recess (160, 162) of the nozzle, the upstream circumferential edge of the radially inner wall (148) of the C-shaped member (144) of each ring sector (118) including at least one notch (180, 182) cooperating with complementary means (164, 166) of the nozzle (112) in order to prevent a ring sector from moving in rotation relative to the nozzle.
- A stage according to claim 1, characterized in that the complementary means (164, 166) of the nozzle (112) include local extra thickness of the nozzle (112).
- A stage according to claim 1 or claim 2, characterized in that the radially inner wall (148) of the C-shaped member (144) of each ring sector (118) has an axial dimension that is greater than that of the radially outer wall (146) of that member.
- A stage according to any preceding claim, characterized in that the nozzle (112) includes a radially outer annular tab (124) at its downstream end, the tab having an outer cylindrical surface (130) for bearing radially against the casing rail (132) and a downstream radial surface (134) for bearing against the split ring (136), the above-mentioned recess(es) (160, 162) opening out downstream at least in part in this downstream radial surface.
- A stage according to claim 4, characterized in that the nozzle (112, 212) is sectorized and the recesses (160, 162, 260, 262) are circumferentially oriented, their circumferential ends opening out in the circumferential ends of nozzle sectors, or being closed by side webs (166) of the nozzle sectors.
- A stage according to claim 5, characterized in that the facing lateral edges of the annular tab sectors (124, 224) of the nozzle sectors (112, 212) include rectilinear slots (174, 274) for receiving sealing strips that extend radially outwards to the proximity of the casing rail (132, 232) and/or of the split ring (136, 236), the grooves extending in a plane situated upstream from the above-mentioned recesses (260, 262), or extending at least in part in the above-mentioned side webs (166) of the nozzle sectors.
- A stage according to any preceding claim, characterized in that the upstream end portion of the radially inner wall (148) of the C-shaped member (144) of each ring sector (118) is spaced apart from a radial wall (159) of the above-mentioned recess of the nozzle by axial clearance (J'), and from an outer cylindrical wall (161) of the recess by radial clearance (H) that is small or zero.
- A turbine engine, such as an airplane turboprop or turbojet, characterized in that it includes at least one turbine stage according to any one of claims 1 to 7.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1253644A FR2989724B1 (en) | 2012-04-20 | 2012-04-20 | TURBINE STAGE FOR A TURBOMACHINE |
PCT/FR2013/050843 WO2013156734A1 (en) | 2012-04-20 | 2013-04-17 | Turbine stage for a turbomachine |
Publications (2)
Publication Number | Publication Date |
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EP2839117A1 EP2839117A1 (en) | 2015-02-25 |
EP2839117B1 true EP2839117B1 (en) | 2018-06-06 |
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Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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EP13722492.9A Active EP2839117B1 (en) | 2012-04-20 | 2013-04-17 | Turbine stage for a turbomachine |
Country Status (9)
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US (1) | US9957841B2 (en) |
EP (1) | EP2839117B1 (en) |
JP (1) | JP6336437B2 (en) |
CN (1) | CN104246141B (en) |
BR (1) | BR112014025776B1 (en) |
CA (1) | CA2870102C (en) |
FR (1) | FR2989724B1 (en) |
RU (1) | RU2633316C2 (en) |
WO (1) | WO2013156734A1 (en) |
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FR3015554B1 (en) * | 2013-12-19 | 2016-01-29 | Snecma | TURBINE RING SECTOR FOR AIRCRAFT TURBOMACHINE HAVING IMPROVED GRIPPING PORTS |
DE102014209057A1 (en) | 2014-05-14 | 2015-11-19 | MTU Aero Engines AG | Gas turbine casing assembly |
FR3022578B1 (en) * | 2014-06-23 | 2016-06-03 | Snecma | PROCESS FOR MAKING AND REPAIRING A TURBINE DISPENSER OF A TURBOMACHINE |
US9677427B2 (en) * | 2014-07-04 | 2017-06-13 | Pratt & Whitney Canada Corp. | Axial retaining ring for turbine vanes |
FR3024884B1 (en) * | 2014-08-14 | 2019-07-05 | Safran Aircraft Engines | METHOD FOR PRODUCING A SECTORIZED SEAL RING AND A TURBOMACHINE TURBINE |
FR3024883B1 (en) * | 2014-08-14 | 2016-08-05 | Snecma | TURBOMACHINE MODULE |
FR3041993B1 (en) * | 2015-10-05 | 2019-06-21 | Safran Aircraft Engines | TURBINE RING ASSEMBLY WITH AXIAL RETENTION |
FR3048997B1 (en) * | 2016-03-21 | 2020-03-27 | Safran Aircraft Engines | BLADE PLATFORM AND AERONAUTICAL TURBOMACHINE BLOWER DISC |
EP3290642A1 (en) * | 2016-08-31 | 2018-03-07 | Siemens Aktiengesellschaft | Ring segment for a turbine and assembly for external limiting of a flow path of a turbine |
FR3058756B1 (en) * | 2016-11-15 | 2020-10-16 | Safran Aircraft Engines | TURBINE FOR TURBOMACHINE |
FR3058755B1 (en) * | 2016-11-15 | 2020-09-25 | Safran Aircraft Engines | TURBINE FOR TURBOMACHINE |
US20180347399A1 (en) * | 2017-06-01 | 2018-12-06 | Pratt & Whitney Canada Corp. | Turbine shroud with integrated heat shield |
RU2674813C1 (en) * | 2017-10-05 | 2018-12-13 | Акционерное общество "Объединенная двигателестроительная корпорация" (АО "ОДК") | Stator of gas turbine |
FR3083563B1 (en) * | 2018-07-03 | 2020-07-24 | Safran Aircraft Engines | AIRCRAFT TURBOMACHINE SEALING MODULE |
FR3084103B1 (en) * | 2018-07-18 | 2020-07-10 | Safran Aircraft Engines | SEALING ASSEMBLY FOR A TURBOMACHINE TURBINE ROTOR AND TURBOMACHINE TURBINE COMPRISING SUCH AN ASSEMBLY |
FR3086324B1 (en) * | 2018-09-20 | 2020-11-06 | Safran Helicopter Engines | TIGHTNESS OF A TURBINE |
US11085332B2 (en) * | 2019-01-16 | 2021-08-10 | Raytheon Technologies Corporation | BOAS retention assembly with interlocking ring structures |
FR3100838B1 (en) * | 2019-09-13 | 2021-10-01 | Safran Aircraft Engines | TURBOMACHINE SEALING RING |
FR3127524B1 (en) * | 2021-09-30 | 2023-08-25 | Safran Aircraft Engines | Stator part of turbomachine with tangentially retained retaining ring |
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2012
- 2012-04-20 FR FR1253644A patent/FR2989724B1/en active Active
-
2013
- 2013-04-17 WO PCT/FR2013/050843 patent/WO2013156734A1/en active Application Filing
- 2013-04-17 CN CN201380020828.7A patent/CN104246141B/en active Active
- 2013-04-17 RU RU2014146619A patent/RU2633316C2/en active
- 2013-04-17 CA CA2870102A patent/CA2870102C/en active Active
- 2013-04-17 EP EP13722492.9A patent/EP2839117B1/en active Active
- 2013-04-17 BR BR112014025776-0A patent/BR112014025776B1/en active IP Right Grant
- 2013-04-17 JP JP2015506290A patent/JP6336437B2/en active Active
- 2013-04-17 US US14/394,355 patent/US9957841B2/en active Active
Patent Citations (1)
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FR2941488A1 (en) * | 2009-01-28 | 2010-07-30 | Snecma | Shroud sector for turbine module of turbomachine, has notch cut under form of rectangle comprising round corners at level of base of notch, where base of notch has progressive curvature between bending radius and radius |
Also Published As
Publication number | Publication date |
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CN104246141A (en) | 2014-12-24 |
JP6336437B2 (en) | 2018-06-06 |
EP2839117A1 (en) | 2015-02-25 |
US20150118035A1 (en) | 2015-04-30 |
BR112014025776B1 (en) | 2022-01-04 |
BR112014025776A2 (en) | 2017-06-20 |
FR2989724A1 (en) | 2013-10-25 |
FR2989724B1 (en) | 2015-12-25 |
JP2015514907A (en) | 2015-05-21 |
WO2013156734A1 (en) | 2013-10-24 |
CN104246141B (en) | 2016-08-24 |
US9957841B2 (en) | 2018-05-01 |
CA2870102A1 (en) | 2013-10-24 |
RU2014146619A (en) | 2016-06-10 |
CA2870102C (en) | 2020-03-10 |
RU2633316C2 (en) | 2017-10-11 |
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