EP2839117B1 - Étage de turbine pour une turbomachine - Google Patents

Étage de turbine pour une turbomachine Download PDF

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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
Authority
EP
European Patent Office
Prior art keywords
nozzle
ring
wall
downstream
radially
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.)
Active
Application number
EP13722492.9A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP2839117A1 (fr
Inventor
Alain Dominique Gendraud
Alberto MARTIN-MATOS
Vincent MILLIER
Sébastien Jean Laurent Prestel
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA Services SA
SNECMA SAS
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by SNECMA Services SA, SNECMA SAS filed Critical SNECMA Services SA
Publication of EP2839117A1 publication Critical patent/EP2839117A1/fr
Application granted granted Critical
Publication of EP2839117B1 publication Critical patent/EP2839117B1/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • 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
    • 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
    • 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
    • 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
    • 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
    • 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
    • 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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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP13722492.9A 2012-04-20 2013-04-17 Étage de turbine pour une turbomachine Active EP2839117B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1253644A FR2989724B1 (fr) 2012-04-20 2012-04-20 Etage de turbine pour une turbomachine
PCT/FR2013/050843 WO2013156734A1 (fr) 2012-04-20 2013-04-17 Etage de turbine pour une turbomachine

Publications (2)

Publication Number Publication Date
EP2839117A1 EP2839117A1 (fr) 2015-02-25
EP2839117B1 true EP2839117B1 (fr) 2018-06-06

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ID=48430836

Family Applications (1)

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EP13722492.9A Active EP2839117B1 (fr) 2012-04-20 2013-04-17 Étage de turbine pour une turbomachine

Country Status (9)

Country Link
US (1) US9957841B2 (pt)
EP (1) EP2839117B1 (pt)
JP (1) JP6336437B2 (pt)
CN (1) CN104246141B (pt)
BR (1) BR112014025776B1 (pt)
CA (1) CA2870102C (pt)
FR (1) FR2989724B1 (pt)
RU (1) RU2633316C2 (pt)
WO (1) WO2013156734A1 (pt)

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FR3015554B1 (fr) * 2013-12-19 2016-01-29 Snecma Secteur d'anneau de turbine pour turbomachine d'aeronef, presentant des orifices de prehension ameliores
DE102014209057A1 (de) 2014-05-14 2015-11-19 MTU Aero Engines AG Gasturbinengehäuseanordnung
FR3022578B1 (fr) * 2014-06-23 2016-06-03 Snecma Procede de realisation et de reparation d’un distributeur de turbine d’une turbomachine
US9677427B2 (en) * 2014-07-04 2017-06-13 Pratt & Whitney Canada Corp. Axial retaining ring for turbine vanes
FR3024883B1 (fr) * 2014-08-14 2016-08-05 Snecma Module de turbomachine
FR3024884B1 (fr) * 2014-08-14 2019-07-05 Safran Aircraft Engines Procede de realisation d'un anneau sectorise d'etancheite et d'une turbine de turbomachine
FR3041993B1 (fr) * 2015-10-05 2019-06-21 Safran Aircraft Engines Ensemble d'anneau de turbine avec maintien axial
FR3048997B1 (fr) * 2016-03-21 2020-03-27 Safran Aircraft Engines Plateforme d'aube et disque de soufflante de turbomachine aeronautique
EP3290642A1 (de) 2016-08-31 2018-03-07 Siemens Aktiengesellschaft Ringsegment für eine turbine und anordnung zur äusseren be-grenzung eines strömungspfades einer turbine
FR3058755B1 (fr) * 2016-11-15 2020-09-25 Safran Aircraft Engines Turbine pour turbomachine
FR3058756B1 (fr) * 2016-11-15 2020-10-16 Safran Aircraft Engines Turbine pour turbomachine
US20180347399A1 (en) * 2017-06-01 2018-12-06 Pratt & Whitney Canada Corp. Turbine shroud with integrated heat shield
RU2674813C1 (ru) * 2017-10-05 2018-12-13 Акционерное общество "Объединенная двигателестроительная корпорация" (АО "ОДК") Статор газовой турбины
FR3083563B1 (fr) * 2018-07-03 2020-07-24 Safran Aircraft Engines Module d'etancheite de turbomachine d'aeronef
FR3084103B1 (fr) * 2018-07-18 2020-07-10 Safran Aircraft Engines Ensemble d'etancheite pour un rotor de turbine de turbomachine et turbine de turbomachine comprenant un tel ensemble
FR3086324B1 (fr) * 2018-09-20 2020-11-06 Safran Helicopter Engines Etancheite d'une turbine
US11085332B2 (en) * 2019-01-16 2021-08-10 Raytheon Technologies Corporation BOAS retention assembly with interlocking ring structures
FR3100838B1 (fr) * 2019-09-13 2021-10-01 Safran Aircraft Engines Anneau d’etancheite de turbomachine
FR3127524B1 (fr) * 2021-09-30 2023-08-25 Safran Aircraft Engines Partie statorique de turbomachine à anneau de maintien retenu tangentiellement

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Also Published As

Publication number Publication date
WO2013156734A1 (fr) 2013-10-24
EP2839117A1 (fr) 2015-02-25
FR2989724A1 (fr) 2013-10-25
US9957841B2 (en) 2018-05-01
US20150118035A1 (en) 2015-04-30
CN104246141A (zh) 2014-12-24
BR112014025776A2 (pt) 2017-06-20
CA2870102C (fr) 2020-03-10
RU2014146619A (ru) 2016-06-10
JP2015514907A (ja) 2015-05-21
CN104246141B (zh) 2016-08-24
JP6336437B2 (ja) 2018-06-06
BR112014025776B1 (pt) 2022-01-04
RU2633316C2 (ru) 2017-10-11
FR2989724B1 (fr) 2015-12-25
CA2870102A1 (fr) 2013-10-24

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