EP4416379B1 - Turbinenleitschaufel mit einem ringförmigen dichtelement - Google Patents

Turbinenleitschaufel mit einem ringförmigen dichtelement

Info

Publication number
EP4416379B1
EP4416379B1 EP22801845.3A EP22801845A EP4416379B1 EP 4416379 B1 EP4416379 B1 EP 4416379B1 EP 22801845 A EP22801845 A EP 22801845A EP 4416379 B1 EP4416379 B1 EP 4416379B1
Authority
EP
European Patent Office
Prior art keywords
deflector
nozzle
flange
turbine
ring seal
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
EP22801845.3A
Other languages
English (en)
French (fr)
Other versions
EP4416379A1 (de
Inventor
Kenny BEAUBOIT
Matthieu Simon
Patrick Jean Laurent SULTANA
Julian Nicolas GIRARDEAU
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
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 EP4416379A1 publication Critical patent/EP4416379A1/de
Application granted granted Critical
Publication of EP4416379B1 publication Critical patent/EP4416379B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • 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
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
    • 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
    • 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
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
    • 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
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms

Definitions

  • the invention relates to a turbojet and more generally to a turbomachine comprising a distributor having a radially internal face carrying an annular sealing element of a labyrinth-type seal, this annular sealing element being made of an abradable material intended to cooperate with wipers carried by a rotor opposite this annular sealing element.
  • a turbomachine generally comprises, from upstream to downstream in the direction of gas flow through the turbomachine, a fan, one or more compressor stages, for example a low pressure compressor and a high pressure compressor, a combustion chamber, one or more turbine stages, for example a high pressure turbine and a low pressure turbine, and a gas exhaust nozzle 8.
  • the turbines are produced in the form of a succession of stages each comprising a wheel of moving blades (rotor) rotating in front of a wheel of fixed blades (stator, or distributor) configured to convert combustion energy into motive energy, in particular to drive the compressor stages and the fan.
  • the rotor disks of the turbine are centered on a longitudinal axis X of the turbomachine and are generally assembled together by means of shrouds on the upstream disk and the downstream disk.
  • Each distributor comprises a plurality of fixed blades distributed circumferentially around the axis.
  • the distributor includes fixed vanes configured to accelerate and deflect a flow of combustion gas toward the moving vanes immediately downstream.
  • Such a seal generally comprises a sealing ring carrying an abradable element integral with the distributor and one or more wipers integral with the rotor.
  • the distributor is exposed to higher temperatures than the rotor disc and the thermal inertia of the distributor is generally lower than that of the disc, which causes a variation in the clearance between the sealing ring and the wipers. This results in an increase in the leakage flow rate when the aforementioned clearance increases and an acceleration of the wear of the abradable element when this clearance decreases.
  • the document FR 3 027 343 discloses a mounting solution allowing radial movement between the sealing ring and the distributor.
  • the sealing of such an assembly is sensitive to temperature variations because the expansion of the sealing ring causes the clearances between the abradable element and the facing wipers to open, which deteriorates the performance of the engine.
  • the cooling flow injected between the abradable element and the wipers does not mix with the hot air from the flow stream that leaks between the distributor and the immediately adjacent rotating disc, which makes the temperature variations of the freely expanding sealing ring dependent on the leakage flow rate of the hot air from the flow stream. In transient phases, this results in a sealing ring that expands under the effect of the increase in temperature, which results in the opening of the seal clearances, an increase in their permeability and therefore a reduction in the performance of the seal.
  • the temperature difference of the upstream and downstream ventilation cavities is substantial, which causes a temperature difference between the ring mounting flanges and creates differential thermal expansion which can block the radial movement of the sealing ring relative to the distributor.
  • the document FR 3 107 298 describes a dispenser according to the preamble of claim 1.
  • An aim of the invention is to remedy the aforementioned drawbacks by proposing a distributor comprising a seal whose performance is less sensitive to temperature variations, in particular when the seal comprises a sealing ring mounted with radial clearance on the distributor, and whose service life is improved.
  • the invention provides a turbine comprising a distributor according to the first aspect.
  • the invention proposes a turbomachine comprising a turbine according to the second aspect and an additional turbine, a rotational speed of the additional turbine being greater than a rotational speed of the turbine.
  • the invention proposes an aircraft comprising a turbomachine according to the third aspect.
  • upstream and downstream are defined relative to the normal flow direction of the gases in the turbomachine 1 (in particular of an aircraft 100), and therefore along the nozzle 3 of the low-pressure turbine 2.
  • the X axis of the nozzle 3 is called the X axis around which the nozzle 3 extends, which corresponds to the X axis of revolution of the rotor 7 of the turbine 2.
  • An axial direction corresponds to the direction of the X axis
  • a radial direction is a direction perpendicular to this X axis and passing through it.
  • a circumferential direction corresponds to a direction perpendicular to the X axis and not passing through it.
  • internal (or interior) and external (or exterior), respectively, are used with reference to a radial direction so that the internal part or face of an element is closer to the X axis than the external part or face of the same element.
  • a distributor 3 in particular of a low-pressure turbine 7, comprises a shroud 4 provided with a plurality of fixed blades 5 distributed circumferentially around the shroud 4.
  • the shroud 4 comprises in particular a flange 6 which extends radially inward relative to the blades 5.
  • the distributor 3 may be sectorized and comprise a plurality of distributor sectors 3 fixed together end to end around the X axis.
  • the distributor 3 may be formed integrally and in one piece, in which case the distributor sectors 3 are monolithic.
  • the turbine 2 further comprises a rotor 7 comprising a plurality of discs 8 each comprising a rim 9 and blades 10.
  • the blades 10 are attached and fixed in cells 11 formed in the rim 9 of the corresponding disc 8 and extend radially from the rim 9.
  • the distributor 3 extends between two adjacent discs 8 of the rotor 7 of the turbine 2.
  • the turbine 2 comprises a succession of stages each comprising a disc 8 of the rotor 7 rotating in front of an associated distributor 3.
  • the flange 6 extends substantially radially from the shell 4 in the direction of the second sealing elements (i.e. opposite the blades) and has an upstream face 6a and a downstream face 6b, substantially radial.
  • the radial portion 16 is mounted on the flange 6 so as to allow radial clearance between the sealing ring 12 and the flange 6.
  • the radial portion 16 may comprise an upstream flange 16a and a downstream flange 16b configured to come into contact with the upstream face 6a and the downstream face 6b, respectively, of the flange 6.
  • the ring 12 and the flange 6 together define an upstream ventilation cavity 17 and a downstream ventilation cavity 18.
  • the upstream cavity 17 is delimited upstream by the rotating disc 8 of the rotor 7 immediately upstream, downstream by the upstream face 6a of the flange 6, radially on the inside by the external face 15b of the axial part of the ring 12 and radially on the outside by the internal face of the shell 4.
  • the downstream cavity 18 is delimited upstream by the downstream face 6b of the flange 6, downstream by the rotating disc 8 of the rotor 7 immediately downstream, radially inside by the external face 15b of the axial part of the ring 12 and radially outside by the internal face of the ferrule 4.
  • a flow of cooling gas F1 (coming in particular from an upstream part of the turbomachine 1, for example from a compressor section) passes through the bottom of the cells 11 and is injected between the abradable element 13 and the lips 14 of the seal in order to cool the seal and ensure its sealing.
  • the distributor 3 further comprises a deflector 19 configured to guide an air flow towards the upstream cavity 17.
  • the deflector 19 can in particular be mounted on one of the flange 6 and the ring 12 so as to extend substantially radially in the upstream cavity 17.
  • at least one through-orifice 20 is formed in the sealing ring 12 in order to put the part of the upstream cavity 17 located between the deflector 19 and the external face 15b of the ring 12 into fluid communication with the internal face 15a of the sealing ring 12.
  • the deflector 19 and the through-orifice(s) 20 thus make it possible to force the cooling fluid F1 (gas) coming from the cells 11 of the disk 8 of the rotor 7 immediately upstream of the distributor 3 to mix with the hot gases F3, F2 coming from the flow stream and the rim 9 of the disk 8, in order to reduce the temperature gradients between the upstream cavity 17 and the downstream cavity 18.
  • the rotation of the rotor 7 of the turbine 2 drives the cooling fluid F1 radially outwards, so that the fluid F1 rises along the deflector 19 into the upstream cavity 17, where it meets the hot gases F2, F3.
  • the mixing of the cooling fluid F1 with the hot gases F2, F3 then makes it possible to cool the upstream cavity 17 (and the upstream flange 16a).
  • a portion F1a of the mixture thus obtained can then pass between the plates 16a, 16b and the flange 6 through the passage 16a provided for this purpose, thus cooling the downstream cavity 18, while another portion F1b descends towards the wipers 14 via the through orifice(s) 20 and ensures the sealing of the seal.
  • through orifices 20 are formed in the ring 12 in order to ensure sufficient passage for the gas flow coming from the upstream cavity 17.
  • an oblong orifice 20 may be formed in the deflector 19 and/or the ring 12. Since the seal is calibrating, it is not necessary for the passage section of the orifice(s) 20 to participate in the calibration of the gas flow in the seal.
  • the deflector 19 is fixed to the ring 12, for example by brazing or by mechanical fixing (bolting, etc.).
  • the deflector 19 then comprises an internal radial end arranged near the sealing ring 20 and an external radial end extending into the upstream cavity 17.
  • the deflector 19 comprises a substantially planar metal sheet comprising a radially inner edge 19a and a radially outer edge 19b.
  • the radially inner edge 19a and the radially outer edge 19b are preferably annular.
  • the deflector 19 may be monolithic or comprise a plurality of sectors fixed end to end, where appropriate with overlap.
  • the through-orifice(s) 20 are formed in the axial portion 15a of the ring 12, close to the bend.
  • the orifice(s) 20 are offset relative to the abradable element 13: they are therefore formed in the portion of the ring 12 which is devoid of abradable element 13, i.e. close to the bend of the upstream edge 15c.
  • the orifices 20 may be formed in the bent portion of the upstream edge 15c and extend radially in the bent portion, so as to open along of the deflector 19 (see figure 2 ).
  • the cooling fluid F1b thus flows through the orifices 20 along the deflector 19 before reaching the seal.
  • the deflector 19 When the deflector 19 is bent, it further comprises a monolithic annular sheet with the radially inner edge of the metal sheet.
  • the deflector 19 can then be attached and fixed to the outer face 15b of the ring 12, close to its upstream edge 15c.
  • the orifice(s) 20 are then formed in correspondence in the deflector 19 and in the axial portion 15a of the ring 12, at the level of their overlap zone.
  • the deflector 19 is fixed on the radial part 16 of the ring 12 or on the flange 6.
  • the deflector 19 then comprises perforations to allow the circulation of the fluid F1 towards the orifices 20 of the ring 12 and, where appropriate (depending on the position relative to the flanges 16a, 16b) towards the gas passage 16c at the level of the flanges 16a, 16b.
  • the deflector 19 comprises an internal radial end extending into the upstream cavity 17 and an external radial end arranged close to the radial part 16 of the sealing ring 20.
  • the deflector 19 may comprise a gutter-shaped metal sheet comprising a first flat sheet configured to be fixed to the flange 6 or the radial portion 16 of the ring 12, a second flat sheet extending substantially radially in the upstream cavity 17 and a central sheet connecting the first and second sheets.
  • the flange 6 or the radial portion 16 of the ring 12 may comprise a bent sheet metal, which may be brazed onto the radial portion or the flange 6.
  • the deflector 19 may then comprise a bent sheet metal, fixed (for example by brazing) onto the bent sheet metal of the flange 6 or of the radial portion.
  • the deflector 19 may comprise a radially inwardly bent sheet metal which is monolithic with the flange 6 or the radial portion 16 of the ring 12.
  • FIG 4 illustrates the circulation of different air flows F1, F2, F3 in a conventional distributor.
  • the hot gases F3 coming from the flow stream leak into the area located between the shell 4 of the distributor 3 and the disc 8 of the rotor 7 immediately upstream.
  • a cooling air flow F1 coming from the cell 11 of this disc 8 is injected between the abradable element 13 and the wipers 14 to cool the seal.
  • a leakage flow F2, hot, near the rim 9 of the discs 8 can be injected into the upstream cavity 17.
  • the cooling fluid F1 does not rise towards the upstream cavity 17, which is therefore very hot, and only cools the seal. This also results in a substantial temperature difference between the upstream cavity 17 and the downstream cavity 18, as well as between the upstream flange 16a and the downstream flange 16b of the ring 12.
  • the circulation of air flows F1, F2 and F3 is illustrated in the figure 1 , which represents a distributor 3 according to an embodiment of the invention.
  • the hot gases F3 coming from the flow stream are mixed in the upstream cavity 17 with the cooling fluid F1 rising along the deflector 19 and with the hot leakage flow F2 from the rims 9 of the discs 8.
  • the total temperature of the upstream cavity 17 is therefore significantly lower than on the figure 4
  • the temperature differences between the upstream cavity 17 and the downstream cavity 18 as well as between the upstream flange 16a and the downstream flange 16b of the ring 12 are furthermore lower, the gases F1a circulating between the flanges 16a, 16b and the flange 6 also having a lower temperature thanks to its mixture with the fluid F1 coming from the cells 11.
  • a part F1b of the cold fluid is returned to the seal via the orifices 20 in order to ensure the cooling of the seal.
  • the ring 12 Since the upstream cavity 17 is constantly supplied with a high cooling flow, the ring 12 undergoes less significant temperature variations during the lifetime of the turbomachine 1 thanks to the mixing of the gases F1, F2, F3 in the upstream cavity 17. The ring 12 is therefore less subject to thermal expansion.
  • the deflector 19 is preferably made of metal and may be made of the same material as the flange 6 or the ring 12.
  • the deflector 19 may comprise an aluminum alloy, steel, etc.
  • the invention can be applied to any axial turbine 2 composed of a succession of moving stages (rotor 7) and static stages (distributors 3), and in particular in the context of turbomachines 1 (and derivatives) and gas turbines.
  • the ring 12 of the turbine 2 can be free, that is to say have radial clearance with the flange 6, or alternatively be fixed relative to the flange 6.
  • the invention finds particular application in the case of turbines 2 having a significant leakage flow rate from the flow stream.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)

Claims (11)

  1. Leitschaufel (3) für eine Turbine (2), die eine Drehachse (X) aufweist und umfasst:
    - einen Flansch (6), der sich radial zur Achse (X) erstreckt;
    - einen Dichtring (12), der auf dem Flansch (6) angebracht ist und eine Innenfläche (15a) aufweist, die zum Tragen eines abriebfähigen Elements (13) ausgebildet ist;
    - einen Belüftungshohlraum (17), der radial innen durch eine Außenfläche (15b) des Dichtrings (12) und stromabwärts durch eine stromaufwärtige Fläche (6a) des Flansches (6) begrenzt ist;
    wobei der Leitschaufel (3) dadurch gekennzeichnet ist, dass sie ferner umfasst:
    - einen Abweiser, der ausgelegt ist, um einen Luftstrom zum Belüftungshohlraum (17) zu leiten, wobei der Abweiser (19) an einer gekrümmten stromaufwärtigen Kante (15c) des Dichtrings (12) befestigt ist, die sich radial nach innen erstreckt; und
    - mindestens eine Durchgangsöffnung (20), die in dem Dichtring (12) ausgebildet und ausgelegt ist, um den Belüftungshohlraum (17) mit der Innenfläche (15a) des Dichtrings (12) in Fluidkommunikation zu versetzen.
  2. Leitschaufel (3) nach Anspruch 1, wobei der Abweiser (19) an einem von dem Flansch (6) und dem Dichtring (12) derart angebracht ist, dass er sich im Wesentlichen radial in den Belüftungshohlraum (17) erstreckt.
  3. Leitschaufel (3) nach einem der Ansprüche 1 oder 2, wobei sich die stromaufwärtige Kante (15c) bis zu einem Auslass einer Zelle (11) erstreckt, die in der Felge (9) einer Scheibe (8) eines Rotors der Turbine (2) neben dem Leitschaufel ausgebildet ist.
  4. Leitschaufel (3) nach einem der Ansprüche 1 bis 3, wobei die mindestens eine Öffnung (20) ausgelegt ist, um den Durchgang des Luftstroms aus dem Belüftungshohlraum (17) zur Innenfläche (15a) des Dichtrings (12) zu gestatten.
  5. Leitschaufel (3) nach einem der Ansprüche 1 bis 4, wobei die Leitschaufel (3) ein an einer stromaufwärtigen Kante (15c) des Dichtrings (12) befestigtes gekrümmtes Blech umfasst, wobei die mindestens eine Öffnung (20) den Abweiser (19) durchquert.
  6. Leitschaufel (3) nach einem der Ansprüche 1 bis 5, wobei der Abweiser (19) ein im Wesentlichen ebenes oder kegelstumpfförmiges Blech umfasst.
  7. Leitschaufel (3) nach einem der Ansprüche 1 bis 6, wobei sich der Abweiser (19) radial zur Achse (X) erstreckt.
  8. Leitschaufel (3) nach einem der Ansprüche 1 bis 7, wobei der Abweiser (19) an einem von dem Flansch (6) und dem Dichtring (12) angelötet oder einstückig mit dem Dichtring (12) ausgebildet ist.
  9. Leitschaufel (3) nach einem der Ansprüche 1 bis 8, wobei der Dichtring (12) angebracht ist, um radial zum Flansch (6) beweglich zu sein.
  10. Turbine (2), die eine Leitschaufel (3) nach einem der Ansprüche 1 bis 9 umfasst.
  11. Turbomaschine (1), die eine Turbine (2) nach Anspruch 10 und eine zusätzliche Turbine umfasst, wobei eine Drehgeschwindigkeit der zusätzlichen Turbine höher ist als eine Drehgeschwindigkeit der Turbine (2).
EP22801845.3A 2021-10-14 2022-10-14 Turbinenleitschaufel mit einem ringförmigen dichtelement Active EP4416379B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2110870A FR3128243B1 (fr) 2021-10-14 2021-10-14 Distributeur de turbine comportant un élément annulaire d’étanchéité
PCT/FR2022/051938 WO2023062327A1 (fr) 2021-10-14 2022-10-14 Distributeur de turbine comportant un élément annulaire d'étanchéité

Publications (2)

Publication Number Publication Date
EP4416379A1 EP4416379A1 (de) 2024-08-21
EP4416379B1 true EP4416379B1 (de) 2025-08-27

Family

ID=79171135

Family Applications (1)

Application Number Title Priority Date Filing Date
EP22801845.3A Active EP4416379B1 (de) 2021-10-14 2022-10-14 Turbinenleitschaufel mit einem ringförmigen dichtelement

Country Status (5)

Country Link
US (1) US12467374B2 (de)
EP (1) EP4416379B1 (de)
CN (1) CN118234923A (de)
FR (1) FR3128243B1 (de)
WO (1) WO2023062327A1 (de)

Family Cites Families (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2928963B1 (fr) * 2008-03-19 2017-12-08 Snecma Distributeur de turbine pour une turbomachine.
FR2928961B1 (fr) * 2008-03-19 2015-11-13 Snecma Distributeur sectorise pour une turbomachine.
GB2478918B8 (en) * 2010-03-23 2013-06-19 Rolls Royce Plc Interstage seal
FR2974841B1 (fr) * 2011-05-04 2013-06-07 Snecma Dispositif d'etancheite pour distributeur de turbine de turbomachine
FR2977274B1 (fr) * 2011-06-30 2013-07-12 Snecma Joint d'etancheite a labyrinthe pour turbine d'un moteur a turbine a gaz
US9080449B2 (en) * 2011-08-16 2015-07-14 United Technologies Corporation Gas turbine engine seal assembly having flow-through tube
FR3002586B1 (fr) * 2013-02-28 2016-06-10 Snecma Reduction des echanges convectifs entre l'air et le rotor dans une turbine
DE102013209746B4 (de) * 2013-05-27 2014-12-18 MTU Aero Engines AG Turbinenstufe mit einer Ausblasanordnung und Verfahren zum Ausblasen einer Sperrgasströmung
DE102013011350A1 (de) * 2013-07-08 2015-01-22 Rolls-Royce Deutschland Ltd & Co Kg Gasturbine mit Hochdruckturbinenkühlsystem
FR3027343B1 (fr) 2014-10-15 2019-08-09 Safran Aircraft Engines Ensemble rotatif pour turbomachine comprenant un anneau de stator auto-porte
FR3057300B1 (fr) * 2016-10-07 2018-10-05 Safran Aircraft Engines Assemblage d'anneau mobile de turbine de turbomachine
DE102016222608A1 (de) * 2016-11-17 2018-05-17 MTU Aero Engines AG Dichtungsanordnung für eine Leitschaufelanordnung einer Gasturbine
PL3409897T3 (pl) * 2017-05-29 2020-04-30 MTU Aero Engines AG Uszczelka maszyny przepływowej, sposób wytwarzania uszczelki oraz maszyna przepływowa
ES2828719T3 (es) * 2017-11-09 2021-05-27 MTU Aero Engines AG Disposición de sellado para una turbomáquina, método para la fabricación de una disposición de sellado y turbomáquina
EP3540180A1 (de) * 2018-03-14 2019-09-18 General Electric Company Zwischenstufen-hohlraumspülkanäle
FR3101374B1 (fr) * 2019-09-30 2021-09-17 Safran Aircraft Engines Structure de refroidissement d’une turbine avec coopération radiale entre anneau d’étanchéité et disque de roue mobile
FR3107298B1 (fr) * 2020-02-18 2022-02-04 Safran Aircraft Engines Turbine comportant un espace secondaire interne équipé d’ailettes de correction de giration d’un flux d’air
FR3108938B1 (fr) * 2020-04-02 2022-03-04 Safran Aircraft Engines Anneau d’étanchéité pour un rotor de turbine de turbomachine
FR3117147B1 (fr) * 2020-12-09 2022-10-28 Safran Aircraft Engines Ensemble statorique de turbine avec degré de liberté radial entre un distributeur et un anneau d’étanchéité
FR3121470B1 (fr) * 2021-03-31 2023-09-22 Safran Aircraft Engines Dispositif d’étanchéité et de réinjection d’un flux de contournement pour distributeur de turbine
GB2606552B (en) * 2021-05-13 2023-11-22 Itp Next Generation Turbines S L Sealing system for gas turbine engine

Also Published As

Publication number Publication date
US20250003348A1 (en) 2025-01-02
US12467374B2 (en) 2025-11-11
FR3128243B1 (fr) 2025-01-31
WO2023062327A1 (fr) 2023-04-20
FR3128243A1 (fr) 2023-04-21
EP4416379A1 (de) 2024-08-21
CN118234923A (zh) 2024-06-21

Similar Documents

Publication Publication Date Title
EP3874131B1 (de) Turbinenmantelabschnitt mit gekühlten dichtungsstreifen
EP2252773B1 (de) Stator einer turbomaschine
FR2948726A1 (fr) Roue a aubes comprenant des moyens de refroidissement ameliores
EP3420198A1 (de) Gleichrichter für turbomaschinenverdichter eines flugzeugs mit luftabsaugungsöffnungen mit gestreckter form im umfangsrichtung
EP4010565B1 (de) Deckband einer turbine einer turbomaschine oder eines turbotriebwerkes
EP3911842B1 (de) Anordnung für eine turbomaschine
CA2827591A1 (fr) Carter de turbine comportant des moyens de fixation de secteurs d'anneau
WO2022189735A1 (fr) Ensemble statorique de turbine
FR3068070B1 (fr) Turbine pour turbomachine
WO2020099762A1 (fr) Etancheite entre une roue mobile et un distributeur d'une turbomachine
FR2999249A1 (fr) Compresseur pour turbomachine dote de moyens de refroidissement d'un joint tournant assurant l'etancheite entre un redresseur et un rotor
EP4416379B1 (de) Turbinenleitschaufel mit einem ringförmigen dichtelement
WO2021209707A1 (fr) Turbine pour une turbomachine
FR3113923A1 (fr) Turbine pour turbomachine comprenant des clinquants de protection thermique
FR3066533B1 (fr) Ensemble d'etancheite pour une turbomachine
WO2022123157A1 (fr) Ensemble statorique de turbine avec degré de liberté radial entre un distributeur et un anneau d'étanchéité
FR2961556A1 (fr) Isolation du carter externe d'une turbine de turbomachine vis-a-vis d'un anneau sectorise
FR3146934A1 (fr) Ensemble d’étanchéité pour turbomachine
FR3160725A1 (fr) Ensemble statorique de turbine de turbomachine d’aeronef, presentant un flux d’air de purge statorique a efficacite renforcee
FR3146932A1 (fr) Architecture pour joint d’étanchéité de turbomachine
WO2021205099A1 (fr) Ensemble d'etancheite pour une turbomachine
FR3085405A1 (fr) Pressurisation de la cavite inter-lechettes par derivation du flux de bypass

Legal Events

Date Code Title Description
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: UNKNOWN

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE INTERNATIONAL PUBLICATION HAS BEEN MADE

PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20240502

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC ME MK MT NL NO PL PT RO RS SE SI SK SM TR

DAV Request for validation of the european patent (deleted)
DAX Request for extension of the european patent (deleted)
REG Reference to a national code

Ref country code: DE

Ref legal event code: R079

Free format text: PREVIOUS MAIN CLASS: F01D0011000000

Ipc: F01D0011160000

Ref country code: DE

Ref legal event code: R079

Ref document number: 602022020362

Country of ref document: DE

Free format text: PREVIOUS MAIN CLASS: F01D0011000000

Ipc: F01D0011160000

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

RIC1 Information provided on ipc code assigned before grant

Ipc: F01D 11/00 20060101ALI20250313BHEP

Ipc: F01D 11/16 20060101AFI20250313BHEP

INTG Intention to grant announced

Effective date: 20250331

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC ME MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602022020362

Country of ref document: DE

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: FRENCH

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20250827

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20251227

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20251020

Year of fee payment: 4

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20251127

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG9D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20251229

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20250827

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20250827

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20250827

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20251024

Year of fee payment: 4

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20251128

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20250827

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20250827

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20250827

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20250827

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20251127

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20250827

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1830157

Country of ref document: AT

Kind code of ref document: T

Effective date: 20250827

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20250827

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20250827

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20250827

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20250827

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20250827

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20250827

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20250827

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20250827