EP3591178A1 - Abdichtungsmodul für turbotriebwerk eines luftfahrzeugs - Google Patents

Abdichtungsmodul für turbotriebwerk eines luftfahrzeugs Download PDF

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Publication number
EP3591178A1
EP3591178A1 EP19183350.8A EP19183350A EP3591178A1 EP 3591178 A1 EP3591178 A1 EP 3591178A1 EP 19183350 A EP19183350 A EP 19183350A EP 3591178 A1 EP3591178 A1 EP 3591178A1
Authority
EP
European Patent Office
Prior art keywords
ring
hook
casing
upstream
deflector
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
EP19183350.8A
Other languages
English (en)
French (fr)
Other versions
EP3591178B1 (de
Inventor
Simon Nicolas Morliere
Nicolas Jean-Marc Marcel Beauquin
Renaud James MARTET
Vincent François Georges MILLIER
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
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Safran Aircraft Engines 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 Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP3591178A1 publication Critical patent/EP3591178A1/de
Application granted granted Critical
Publication of EP3591178B1 publication Critical patent/EP3591178B1/de
Active legal-status Critical Current
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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
    • 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
    • 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
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • 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
    • 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
    • F05D2240/55—Seals

Definitions

  • the present invention relates to a turbomachine module, which can be a turbine or be part of a turbine for example.
  • a turbomachine turbine comprises one or more stages, each comprising a distributor formed of an annular row of fixed blades carried by a casing of the turbine, and an impeller mounted rotatably in general downstream of the distributor.
  • the wheel is surrounded by a sealing ring which is sectorized and formed by sectors which are arranged circumferentially end to end and which are hung on the casing of the turbine.
  • Each ring sector generally includes a circumferentially oriented body which carries an abradable coating attached to the internal surface of the body.
  • This coating is for example of the honeycomb type and is intended to wear by friction on external wipers of the impeller vanes, to form a labyrinth seal and minimize the radial clearances between the impeller and the ring areas.
  • Each ring sector comprises at its upstream and downstream ends means for hooking onto the casing.
  • Each ring sector may include at its upstream end a circumferential hook which defines an annular groove in which is engaged, on the one hand, an annular rail of the casing, and on the other hand, a catching spout downstream of the distributor located upstream.
  • the hook of the ring has in cross-section a general U or C shape and comprises two coaxial circumferential walls, respectively internal and external, connected together by a central bottom wall.
  • the downstream attachment spoiler of the distributor has a circumferential orientation and is held tightly radially against the casing rail by means of the circumferential hook upstream of the ring, the circumferential walls of which extend respectively inside the spoiler of the distributor and outside the housing rail. This makes it possible to participate in the radial retention of the distributor with respect to the casing.
  • annular foil for protecting the casing rail, in particular against wear and high temperatures.
  • This foil can be sectorized and then comprises an annular row of foil sectors circumferentially arranged end to end. It has a general U-shaped or C-shaped section and comprises two coaxial circumferential walls, respectively internal and external, connected together by a central bottom wall.
  • the foil sectors are made of sheet metal and make it possible to avoid direct contact between the hooks of the ring sectors and the casing rail, which on the one hand makes it possible to protect the latter against wear by friction and on the other hand apart from thermally protecting it from the ring which can be very hot in operation due to its proximity to the combustion gases flowing in the turbine stream.
  • the longitudinal edges of the circumferential ends of two adjacent sectors of the foil are opposite one another and are separated from each other by a circumferential clearance.
  • the circumferential clearances between the foil sectors can be offset circumferentially relative to the circumferential clearances between the ring sectors, and in particular with respect to the circumferential clearances between the hooks of the ring sectors at which there 'is not possible to mount tabs of the aforementioned type for reasons of space in particular. Hot gases can thus pass through the circumferential clearances between the hooks of the ring sectors and impact the foil sectors, which will heat the casing rail by conduction, and therefore risk reducing its service life.
  • the document WO-A1-2016 / 024060 proposes to circumferentially shift each foil relative to the associated hook so as to better protect the casing rail because the gases which would be likely to pass between the edges of the circumferential ends of the ring sectors are blocked by the foil sectors (due to their circumferential offset with respect to the ring sectors) and do not reach the housing rail.
  • this solution does not make it possible to protect the casing from inter-sector leaks which take place at the level of the bottom middle walls of the ring hooks.
  • the document FR-A1-3 914 350 proposes to circumferentially offset the body of the ring sector, with respect to its hook and its abradable coating.
  • this solution is only applicable in the case where the body of the ring sector covers its hook, which is not always the case when an optimization of the integration is desired.
  • This solution also leads to inter-sector leaks at the hooks of the ring sectors.
  • the gases from the stream which are liable to heat and damage the casing escape from the stream by passing through an axial clearance between the external periphery of the wheel and the external periphery of the distributor located upstream of the wheel. These gases pass through this clearance by passing radially from the inside to the outside and penetrate into an annular space delimited, upstream, by the hooking spout downstream of the distributor, and downstream, by a wiper. sealing upstream of the wheel.
  • This annular space is therefore the place of circulation of leakage gas, which is liable to pass through the inter-sector games and reach the casing.
  • the object of the present invention is in particular to provide a simple, effective and economical solution to this need, in particular by improving the thermal protection of the casing rail in the above-mentioned case.
  • the present invention thus proposes a sealing module for a turbomachine, in particular an aircraft, this sealing module extending around an axis and comprising a distributor fixed to a casing and comprising at least one blade connected to a platform external, the external platform comprising a spoiler fixing to the casing, the turbine module further comprising an impeller rotatably mounted inside the casing and surrounded by a sealing ring attached to this casing, this ring being sectorized and comprising an annular row of ring sectors arranged so that the circumferential end edges of two adjacent sectors are opposite one another, each ring sector comprising a body carrying an abradable coating configured to cooperate with at least one wiper carried by the wheel and a hook which extends circumferentially by being located upstream of said abradable coating and which is configured to cooperate with a rail for attaching the casing, this hook having in section a general C shape whose opening is oriented axially towards upstream and intended to receive said rail.
  • each ring sector further comprises a deflector which is arranged upstream of said coating and which extends radially inwards and upstream relative to the axis so that that its radially internal end extends around a downstream end of the external platform of the distributor.
  • each hook has a circumferential extent identical to that of said deflector, and the circumferential ends of said hook are offset in the circumferential direction from the circumferential ends of said deflector.
  • the deflector is thus intended to be located in the abovementioned annular space, between the external periphery of the wheel and that of the distributor situated upstream, and makes it possible to limit the gas flows in this space.
  • it makes it possible to limit the flow of leakage gases at the level of the upstream hook of each ring sector and therefore to reduce the risk of these gases passing through the inter-sector games at their hooks.
  • the casing is thus better protected and has an optimized service life.
  • the offset of the ends is advantageous because the gases which are liable to pass radially from the inside towards the outside through the circumferential clearances between the circumferential ends of the deflectors, are blocked by the hooks which extend opposite these clearances, and the gases which are liable to pass radially from the inside towards the outside through the circumferential clearances between the circumferential ends of the hooks, are blocked by the deflector sectors which extend opposite these clearances,
  • the present invention also relates to a turbomachine, comprising at least one sealing module as described above.
  • FIG. 1 represents a turbine 10, here low pressure, of a turbomachine such as a turbojet or an airplane turboprop, this turbine comprising several stages (of which only one is here shown) each comprising a distributor 12 formed of a row annular of fixed blades carried by a casing 14 of the turbine, and an impeller 16 mounted downstream of the distributor 12 and rotating around an axis (not visible) in a ring 18 attached to the casing 14.
  • a turbine 10 here low pressure
  • this turbine comprising several stages (of which only one is here shown) each comprising a distributor 12 formed of a row annular of fixed blades carried by a casing 14 of the turbine, and an impeller 16 mounted downstream of the distributor 12 and rotating around an axis (not visible) in a ring 18 attached to the casing 14.
  • the ring 18 is sectorized and formed of several sectors which are carried circumferentially end to end by the casing 14 of the turbine.
  • Each ring sector 18 comprises a body 20 which extends circumferentially and a coating 22 of abradable material fixed by brazing and / or welding on the radially internal surface of the body 20, this coating 22 being of the honeycomb type and being intended to wear by friction on external wipers 24 of the blades of the wheel 16 to minimize the radial clearances between the wheel and the ring sectors 18.
  • the wipers 24 are formed projecting on an external platform 16a of the wheel 16, the external platform 16a being connected to a blade of the impeller.
  • Each ring sector 18 comprises at its upstream end a hook 32 with a C or U section which extends circumferentially and the opening of which opens upstream, this hook 32 being engaged axially from downstream on a spoiler d 'hooking 34 oriented downstream of the distributor 12 which extends circumferentially upstream of the ring sectors 18, on the one hand, and on a cylindrical rail 36 of the casing 14 on which this distributor is hung, on the other hand .
  • the spoiler 34 has a general L shape and is projecting from a platform 12a of the distributor 12, to which at least one blade of the distributor is connected.
  • each ring sector 18 comprises two walls 38 and 40 extending circumferentially and upstream, each wall, respectively radially external and radially internal, are interconnected at their downstream ends by a central bottom wall 42 substantially radial, and which extend respectively radially outside and inside the rail 36, the internal wall 40 radially holding the spoiler 34 of the distributor against the rail 36.
  • the circumferential retention of the distributor 12 is ensured by means of an anti-rotation pin 44 which is carried by the casing 14 and is engaged in a notch of the distributor 12. Its axial retention downstream is ensured by a ring annular 46 split which is mounted in an annular groove 48 of the rail 36, which opens radially inward.
  • the spoiler 34 of the distributor 12 is in axial support downstream on the rod 46 which is held radially in the groove of the casing rail by the internal wall 40, which extends radially inside the rod 46.
  • the axial stop function of the rod 46 can be provided directly by the casing rail 36.
  • the downstream ends of the ring sectors 18 are clamped radially on a cylindrical rail 30 of the casing by the distributor located downstream of the ring sectors.
  • the ring sectors 18 bear radially outwardly on a radially inner cylindrical face of the rail 30 of the casing, and inwardly on a radially outer cylindrical face of a cylindrical rim 28 of the downstream distributor.
  • the downstream ends of the ring sectors 18 are also tightened axially via lugs on the cylindrical rail 30.
  • annular foil 50 which is sectorized and comprises an annular row of foil sectors arranged circumferentially end to end. He has in cross-section in a general C or U shape and comprises two coaxial annular walls, respectively internal 52 and external 54, connected together by a central bottom wall 56.
  • the foil 50 is mounted on the casing rail 36 and on the spoiler 34 of the distributor 12 so that the internal walls 52 of the foil sectors 50 are interposed between the internal walls 40 of the hooks 32 of the ring sectors 18, of on the one hand, and the spoiler 34 of the distributor 12 and the annular ring 46, on the other hand, that the external walls 54 of the foil sectors are interposed between the external walls 38 of the hooks 32 of the ring sectors and the casing rail 36, and that the bottom walls 56 of the foil sectors are interposed between the bottom walls 42 of the hooks of the ring sectors and the casing rail 36.
  • the foil sectors 50 are made of sheet metal and make it possible to avoid direct contact between the hooks 32 of the ring sectors 18 and the casing rail 36, which on the one hand makes it possible to protect the latter against wear by friction and secondly to protect it thermally from the ring which can be very hot in operation due to its proximity to the combustion gases flowing in the turbine stream.
  • the longitudinal edges of the circumferential ends of the ring sectors comprise slots for mounting the tongues 58.
  • the tongues 58 each have a generally elongated and planar shape and each comprise a longitudinal edge engaged in a slot in the edge of a ring sector and an opposite longitudinal edge engaged in a slot in the edge opposite an adjacent ring sector.
  • the figure 1 shows a first sealing ring technology 18 in which the body 20 and the hook 32 are formed in one piece.
  • the figure 2 shows a second sealing ring technology 18 in which the body 20 and the hook 32 are formed from assembled parts.
  • the references used in the figure 2 are the same as those of the figure 1 insofar as they designate the same elements.
  • the second technology covers the case where the hook 32 is fixed under the body, just upstream of the covering 22 (as is the case in the application FR-A1-3 914,350 ), as well as the case where the hook 32 is fixed upstream of the body, as is the case in the example shown.
  • each distributor 12 is separated by an axial clearance J from the outer periphery of the adjacent wheel 16, which can be crossed by leakage gases.
  • the cooperation of the wipers 24 with the abradable coating 22 limits the passage of these leakage gases from upstream to downstream between the wheel 16 and the ring 18.
  • the leakage gases then circulate in the annular space E extending radially between the external platforms 12a, 16a of the distributor 12 and of the wheel 16, and axially between the downstream spoiler 34 of the distributor 12 and the upstream wiper 24a of the wheel 16.
  • the tongues 58 limit the passage of gases from the space E radially outwards, at the level of the circumferential clearances between the bodies 20 of the ring sectors. However, as is better visible at the figure 3 , circumferential clearances are always present between the hooks 32 and gases can pass from the space E radially outwards, in particular between the bottom middle walls 42 of the hooks 32 (arrow F).
  • each ring sector further comprises a deflector 60 which is disposed upstream of the coating 22 and which extends radially inwards relative to the aforementioned axis so that its radially internal end extends around the downstream end of the external platform 12a of the distributor 12.
  • the deflector 60 is formed by a piece independent of the hook 32 and of the body 20, and which is interposed axially between the hook 32 located upstream, and the body 20 and the coating 22 located downstream.
  • the deflector 60 can be formed by an annular sheet sector.
  • the deflector 60 here has a generally curved orientation and a general V shape. It thus comprises a radially external portion 60a extending in a plane substantially perpendicular to the aforementioned axis, and a radially internal portion 60b which is frustoconical.
  • the portion 60a is interposed between the middle bottom wall 42 of the hook 32 and the upstream ends of the body 20 and of the covering 22.
  • the portion 60b extends from downstream to upstream, radially inward. Its internal periphery defines a diameter D which is less than the smallest internal diameters D1, D2 of the hook 32 and of the covering 22. This internal periphery surrounds here with a slight radial clearance the end of the external platform 12a of the distributor 12 ( figure 4 ).
  • the deflector 60 has a circumferential extent around the axis which is identical to that of the body 20 and the coating 22.
  • the circumferential ends of the deflector 60 are substantially axially aligned with those of the body 20 and the coating 22, as can be seen in the figure 5 .
  • the deflector 60 comprises at its circumferential ends notches 62 aligned axially with the slots 64 for accommodating the inter-sector sealing tongues 58. These notches 62 are designed to be able to be crossed by the tongues 58. Each notch 62 has a height (or radial dimension) at least equal to the height (or radial dimension of the slots 64 for housing the tongues), and a width (or dimension circumferential) at least equal to the circumferential dimension between the bottoms of the two slots 64 opposite housing of the tongues.
  • each circumferential end of a ring sector may comprise two slots 64 for housing two tongues 58, which have different lengths and extend one above the another in radial direction.
  • the upstream ends of the slots 64 meet at the upstream end of each edge and both communicate with the notch 62, so that the two tabs 58 of each edge are capable of passing through the notch 62 ( figures 4 and 5 ).
  • the edge of each circumferential end of a ring sector could carry only one tongue 58.
  • Each hook 32 has a circumferential extent identical to that of the deflector 60, and the circumferential ends of the hook 32 are offset in the circumferential direction from the circumferential ends of the deflector ( figure 5 ).
  • Each hook 32 thus comprises a circumferential end portion 32a which makes projecting from the circumferential ends of the other parts of the ring sector, and another circumferential end part 32b which is set back from the circumferential ends of the other parts of the ring sector ( figure 5 ).
  • each ring sector comprising the projecting end portion 32a
  • the tongues 58 bear axially on this end portion (the support zone Z is visible to the Figures 6 and 7 ).
  • the tongues 58 bear axially not on this end portion 32b but on the end portion 32a of the sector adjacent ring.
  • the deflector 60 extends in the space E located between the hook 32 and the end 12 of the external platform 12a of the distributor and divides it into two parts respectively upstream and downstream. Its shape requires the leakage gases passing through the clearance J to flow downstream towards the labyrinth seal defined by the wipers 24. There is therefore less risk of leakage gas circulation at the level of hooks 32 of the ring sectors.
  • the inter-sector clearances at the level of these hooks are also made watertight due to the circumferential offset between the hooks 32 and the deflectors 60. The invention thus makes it possible to effectively protect the casing 14 and to improve its service life and 'Also avoid leakage from the stream to the housing which improves the performance of the turbomachine.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP19183350.8A 2018-07-03 2019-06-28 Abdichtungsmodul für turbomaschine Active EP3591178B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1856139A FR3083563B1 (fr) 2018-07-03 2018-07-03 Module d'etancheite de turbomachine d'aeronef

Publications (2)

Publication Number Publication Date
EP3591178A1 true EP3591178A1 (de) 2020-01-08
EP3591178B1 EP3591178B1 (de) 2022-08-10

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP19183350.8A Active EP3591178B1 (de) 2018-07-03 2019-06-28 Abdichtungsmodul für turbomaschine

Country Status (4)

Country Link
US (1) US11035244B2 (de)
EP (1) EP3591178B1 (de)
CN (1) CN110685753B (de)
FR (1) FR3083563B1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3114841A1 (fr) * 2020-10-05 2022-04-08 Safran Aircraft Engines Ensemble annulaire pour turbine de turbomachine
FR3114840A1 (fr) * 2020-10-05 2022-04-08 Safran Aircraft Engines Ensemble annulaire pour turbine de turbomachine
FR3122692A1 (fr) * 2021-05-07 2022-11-11 Safran Aircraft Engines Pièce annulaire d’étanchéité pour aubes mobiles de turbine de turbomachine

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3100838B1 (fr) * 2019-09-13 2021-10-01 Safran Aircraft Engines Anneau d’etancheite de turbomachine
FR3107079B1 (fr) * 2020-02-07 2022-01-21 Safran Aircraft Engines Aube de turbomachine d’aeronef
FR3108935B1 (fr) * 2020-04-02 2022-03-04 Safran Aircraft Engines Dispositif de distribution d’huile d’un palier a roulement de turbomachine d’aeronef
FR3111382B1 (fr) * 2020-06-11 2022-12-23 Safran Aircraft Engines Ensemble annulaire pour turbine de turbomachine
FR3140112A1 (fr) * 2022-09-22 2024-03-29 Safran Aircraft Engines Amélioration de l’étanchéité dans une turbine de turbomachine

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EP1840339A1 (de) * 2006-03-30 2007-10-03 Snecma Vorrichtung zur Befestigung von Ringsektoren um ein Turbinenlaufrad einer Strömungsmaschine
FR2914350A1 (fr) 2007-03-30 2008-10-03 Snecma Sa Enveloppe externe etanche pour une roue de turbine de turbomachine
WO2013156734A1 (fr) * 2012-04-20 2013-10-24 Snecma Etage de turbine pour une turbomachine
US20140186163A1 (en) * 2012-12-31 2014-07-03 United Technologies Corporation Blade outer air seal having shiplap structure
WO2016024060A1 (fr) 2014-08-14 2016-02-18 Snecma Module de turbomachine
FR3058756A1 (fr) * 2016-11-15 2018-05-18 Safran Aircraft Engines Turbine pour turbomachine

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Patent Citations (6)

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Publication number Priority date Publication date Assignee Title
EP1840339A1 (de) * 2006-03-30 2007-10-03 Snecma Vorrichtung zur Befestigung von Ringsektoren um ein Turbinenlaufrad einer Strömungsmaschine
FR2914350A1 (fr) 2007-03-30 2008-10-03 Snecma Sa Enveloppe externe etanche pour une roue de turbine de turbomachine
WO2013156734A1 (fr) * 2012-04-20 2013-10-24 Snecma Etage de turbine pour une turbomachine
US20140186163A1 (en) * 2012-12-31 2014-07-03 United Technologies Corporation Blade outer air seal having shiplap structure
WO2016024060A1 (fr) 2014-08-14 2016-02-18 Snecma Module de turbomachine
FR3058756A1 (fr) * 2016-11-15 2018-05-18 Safran Aircraft Engines Turbine pour turbomachine

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3114841A1 (fr) * 2020-10-05 2022-04-08 Safran Aircraft Engines Ensemble annulaire pour turbine de turbomachine
FR3114840A1 (fr) * 2020-10-05 2022-04-08 Safran Aircraft Engines Ensemble annulaire pour turbine de turbomachine
FR3122692A1 (fr) * 2021-05-07 2022-11-11 Safran Aircraft Engines Pièce annulaire d’étanchéité pour aubes mobiles de turbine de turbomachine

Also Published As

Publication number Publication date
US11035244B2 (en) 2021-06-15
EP3591178B1 (de) 2022-08-10
US20200011194A1 (en) 2020-01-09
FR3083563A1 (fr) 2020-01-10
FR3083563B1 (fr) 2020-07-24
CN110685753B (zh) 2023-04-28
CN110685753A (zh) 2020-01-14

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