EP4298323B1 - Leitschaufelanordnung für ein turbostrahltriebwerk eines flugzeugs - Google Patents

Leitschaufelanordnung für ein turbostrahltriebwerk eines flugzeugs

Info

Publication number
EP4298323B1
EP4298323B1 EP22710661.4A EP22710661A EP4298323B1 EP 4298323 B1 EP4298323 B1 EP 4298323B1 EP 22710661 A EP22710661 A EP 22710661A EP 4298323 B1 EP4298323 B1 EP 4298323B1
Authority
EP
European Patent Office
Prior art keywords
clamp
root
pads
pad
foot
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
EP22710661.4A
Other languages
English (en)
French (fr)
Other versions
EP4298323A1 (de
Inventor
Alice Marie CLEMENT
Paul Grandin
Clément MARCHAND
Vijeay Patel
Mireya SANCHEZ GOMEZ
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 EP4298323A1 publication Critical patent/EP4298323A1/de
Application granted granted Critical
Publication of EP4298323B1 publication Critical patent/EP4298323B1/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
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/005—Selecting particular materials
    • 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
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • 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
    • 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
    • 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
    • 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
    • F05D2220/321—Application in turbines in gas turbines for a special turbine stage
    • F05D2220/3212—Application in turbines in gas turbines for a special turbine stage the first stage of a turbine
    • 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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/70—Disassembly 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
    • F05D2230/00—Manufacture
    • F05D2230/72—Maintenance
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/175—Superalloys
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/22—Non-oxide ceramics
    • F05D2300/224—Carbon, e.g. graphite

Definitions

  • the invention relates to turbomachines such as aircraft turbojets.
  • turbojet engines with a double-flow system comprising a fan, a low-pressure compressor, a high-pressure compressor, a combustion chamber, a high-pressure turbine and a low-pressure turbine.
  • the low-pressure turbine recovers part of the energy from the combustion of the gases to operate the fan, the compressor and the accessories.
  • the components of the low-pressure turbine include the moving blades and the low-pressure nozzles.
  • the gases expand in the low-pressure nozzle. This accelerates the flow and deflects it. This flow turns the turbine rotor, which forms a moving wheel.
  • This invention is part of the solution to a recurring problem observed on the distributor located on the first stage of the low-pressure turbine.
  • the distributor is formed by elements arranged in succession following the circumferential direction around the axis. Indeed, the particularity of each element is that it is held from above and below.
  • the problem concerns its lower part (i.e. the underside of the lower platform), and more precisely, the foot or leg of the distributor element. This foot is used to hold the part by being pinched.
  • this contact generates wear by friction (or fretting in English), on the other hand, the area is exposed during operation to a risk of type 2 corrosion by sulfur. Thus, the two combine to generate contact corrosion which can seriously degrade the part.
  • One aim of the invention is therefore to facilitate the maintenance of turbomachines and to reduce costs, in the face of this phenomenon of contact corrosion.
  • the pad prevents the foot from friction and contact corrosion. If the pad becomes damaged or worn, it simply needs to be replaced with a new pad, which is less expensive than replacing the distributor element itself.
  • the invention therefore avoids the combined effect of wear and corrosion. If the foot is covered with an anti-corrosion coating, it protects the latter in the contact zone.
  • the invention does not prevent wear, but rather ensures that it is quickly controlled while avoiding the aggravating combination with corrosion, and quickly replaces the worn part. It reduces maintenance costs since there are fewer parts to change and fewer turbine removals. It also improves the machine's performance because, during an inspection, the installation of a new pad ensures less leakage. It therefore makes it possible to control a phenomenon that was previously experienced on the blades.
  • each skate is assembled by complementarity of shape with the foot or with the clamp.
  • each skate is formed of a material different from a material of the foot, for example a stellite, or even of a material, such as carbon or graphite, less hard than a material of the foot.
  • each skate is formed from a material identical to a material of the foot.
  • the invention also provides a turbomachine such as an aircraft turbojet, comprising a subassembly according to the invention.
  • FIG. 1 illustrates an aircraft turbojet engine 1 according to the invention.
  • This is a turbojet engine forming a double-flow, double-spool turbomachine.
  • the turbomachine has a main axis XX.
  • a blower 2 It includes from upstream to downstream, so from left to right on the figure 1 , a blower 2, a low pressure compressor 4, a high pressure compressor 6, a combustion chamber 8, a high pressure turbine 10 and a low pressure turbine 12. These components have moving parts rotating around the axis XX.
  • the compressors 4, 6, the combustion chamber 8 and the turbines 10, 12 define a main air flow vein.
  • a nacelle 16 surrounds the fan 2 so as to form a fan compartment and to define a secondary air flow vein.
  • an air flow entering the turbomachine at an air inlet is compressed, then mixed with fuel and burned in the combustion chamber 8, the combustion gases enabling one or more turbine rotors to rotate around the axis.
  • the high-pressure turbine 10 drives the high-pressure compressor 6, and the low-pressure turbine 10 drives the high-pressure compressor 6, and the low-pressure turbine 10 drives the high-pressure compressor 6.
  • pressure 12 drives the low pressure compressor 4 and the blower 2.
  • upstream and downstream refer to the general direction of air circulation in the turbomachine from its inlet to its outlet.
  • the fixed part of the turbomachine notably comprises a casing, for example an inter-turbine casing 22, which is an intermediate casing interposed between the high pressure and low pressure turbines housed in their respective casings.
  • Each of the high and low pressure turbines comprises a plurality of stages each with a distributor fixed relative to the casing, receiving a gas flow and straightening it to apply it to a moving wheel rotating in a given direction.
  • the low-pressure distributor 24 arranged at the inlet of the low-pressure turbine 12, i.e. the upstream distributor of this turbine. It is arranged downstream of a fluid rectifier of the high-pressure turbine 10 (or TCF casing for Turbine Center Frame ) , for example directly downstream of the rectifier, or downstream of a wheel itself arranged downstream of the rectifier.
  • the distributor 24 therefore corresponds to the first stage of fixed blades of the low-pressure turbine.
  • the distributor 24 may be arranged downstream of the low-pressure turbine, or at the level of another turbine.
  • the distributor 24 has an annular shape centered on the axis XX. It is formed of distributor sectors or elements 25. With reference to the figure 3 , each element 25 comprises a body having an inner (or lower) platform 32 or inner shell, an upper (or outer) platform 34 or outer shell and several blades 36 extending in the radial direction between the platforms 32, 34 and connected thereto. The upper platform 34 is further from the axis than the lower platform 32.
  • the distributor element 25 is connected to the casing by conventional means which will not be detailed.
  • the distributor element 25 is extended by a foot 38 extending in projection from the platform in the radial direction.
  • the foot has a flat shape located in a plane perpendicular to the axis, as shown in particular by figure 4
  • the foot is of a single piece with the body of the distributor element 25.
  • the foot has a known anti-corrosion coating.
  • the machine also includes for each distributor element 25 a clamp 40 configured to fix the foot 38 to the casing 22.
  • this clamp comprises two branches 42 having two main faces 44 facing each other. It is adapted to clamp the foot between the two branches in the direction of the axis XX.
  • the clamp 40 is connected to the inter-turbine casing by means of an annular flange 46.
  • the flange is therefore configured to be securely connected to the fixed part of the turbomachine and to the foot 38 of the distributor element.
  • secure connection between two members it is meant here that the connection is such that a movement of one of the members according to a degree of freedom implies the same movement of the other according to the same degree of freedom.
  • the secure connection is for example a fixing. This connection ensures the maintenance of the foot 38 of the distributor element 25. This connection can also make it possible to separate the upstream and downstream of an area under the foot 38.
  • the flange 46 is thus configured to separate the upstream and downstream of an area under the foot 38 so as to prevent any fluid circulation under the foot. It extends so as to separate an upstream chamber and a downstream chamber arranged respectively upstream and downstream of the foot 38.
  • the upstream chamber is arranged between the inter-turbine casing and the flange.
  • the sealed flange makes it possible, for example, to prevent the circulation of hot air over certain members arranged downstream, typically turbine disks.
  • the flange is adapted to limit heat transfer by convection, conduction and/or radiation from the upstream chamber, in particular from the flow fluid to the flange.
  • the clamp 40 forms a housing allowing relative radial movement of the clamp and the foot during operation without risking the foot being dislodged from the clamp 8.
  • the clamp limits their relative translational movement along the X-X axis.
  • This embodiment is illustrated in the figures 7 and 8 .
  • the foot here carries four 150 skates. On the figure 7 , two of the skates are hidden by the skates in the foreground. On the figure 8 , two of the skates are hidden by the foot.
  • the runners here each have a strip or rail shape.
  • the strips have their longitudinal directions which are parallel to each other and close to the radial direction.
  • the foot having two opposite faces 52. Each of them is in direct contact with two of the pads 150. On each face, the two pads in direct contact with the face are spaced from each other in the circumferential direction to the axis XX, as shown in the figure 8 .
  • each pad 150 is assembled by form fit with the foot 38.
  • each pad comprises three reliefs extending in projection from a face of the pad in contact with the foot, as illustrated in figure 11 in support of the second mode.
  • the reliefs are configured to penetrate into respective cavities of the foot provided for this purpose. It is also possible to provide conversely that the reliefs are located on the clamp and the cavities in the foot.
  • Each pad 150 is interposed between the foot and the clamp, as illustrated.
  • Each branch of the clamp is therefore supported on the foot by a jaw of the branch while being in contact exclusively with the two feet.
  • the pads therefore form an additional material on either side of the foot to accommodate the clamp. Friction therefore occurs on these bands which can wear out and are subsequently repairable.
  • Each pad 150 may be formed from the same material as the distributor element 25, for example a metal alloy. It may also be formed from a different material than a material of the foot, for example a stellite.
  • a stellite is a metal alloy whose principal component is cobalt and the principal alloying element is chromium. It may also contain a small amount of tungsten or molybdenum and a small but significant amount of carbon. A stellite offers good resistance to contact friction.
  • the pads 150 are assembled by form fit with the clamp. Then the latter is fixed to the foot so that the pads are interposed between the foot and the clamp and the clamp is fixed to the casing 22 by means of the flange. The tight assembly with the force of the clamp on the pads ensures that they are held on the foot.
  • the 150 pads are worn, they are dismantled by separating them from the foot. Then new pads are assembled in their place by form fit with the foot, and the clamp is fixed to the foot so that the new pads are interposed between the foot and the clamp.
  • the replacement can also concern only one of the pads, or several of them without it being all of them.
  • Each pad may be provided with a wear indicator, for example in the form of a 53 marking on the sidewall or field of the pad. When this marking is damaged or disappears, it is a sign that the pad must be replaced. Such a wear indicator quickly and effectively shows whether the wear is acceptable or not. In the event that the pad is too worn, it is sufficient to replace it by unseating it and fitting a new pad, as explained.
  • a wear indicator for example in the form of a 53 marking on the sidewall or field of the pad.
  • the base of the distributor element keeps its anti-corrosion coating intact, and friction is controlled.
  • This embodiment is illustrated in the figures 9 to 11 .
  • FIG. 11 shows the reliefs 60 of one of the pads 250 opposite the cavities 62 intended to receive them in the clamp.
  • each pad 250 is formed of a material that is less hard than a material of the foot, such as carbon or graphite, a stellite. This material can thus wear or crumble during friction occurring in operation, thereby reducing the contact friction force.
  • This method has the advantage of being easier to implement because the amount of material required on the clamp is lower.
  • no modification to the base of the distributor element 25 is required, and there is no risk of problems with the application of the anti-corrosion coating on the distributor.
  • the geometry of the base is simplified since it is not necessary to provide one or more cavities.
  • This variant is illustrated in the figure 12 .
  • the relief 60 is unique and has, independently of this, an elongated rectangular parallelepiped shape.
  • the cavity 62 has a female shape complementary to this male shape.
  • the clamp is without jaws.
  • the main faces 44 of its branches 42 are in direct contact with the pads. It is understood that in such an arrangement the jaws of the clamp become useless.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (15)

  1. Unterbaugruppe einer Turbomaschine wie ein Flugzeug-Turbostrahltriebwerk (1), wobei die Unterbaugruppe umfasst:
    - mindestens einen Leitkranz (24) der Niederdruckturbine (12), wobei der Leitkranz einen Fuß (38) umfasst, der mit einem Körper des Leitkranzes einteilig ist,
    - eine Klemme (40), die ausgelegt ist, um den Fuß an einem Gehäuse (22) der Turbomaschine zu befestigen, und
    - mindestens zwei Puffer (150-450), die zwischen dem Fuß und der Klemme angeordnet sind,
    wobei die Unterbaugruppe dadurch gekennzeichnet ist, dass jeder Puffer entweder mit dem Fuß oder der Klemme formschlüssig verbunden ist.
  2. Unterbaugruppe nach vorhergehendem Anspruch, wobei jeder Puffer (150; 350) mit dem Fuß (38) formschlüssig verbunden ist.
  3. Unterbaugruppe nach vorhergehendem Anspruch, wobei jeder Puffer (150; 350) aus einem anderen Material als das Material des Fußes (38) besteht, beispielsweise aus Stellit.
  4. Unterbaugruppe nach einem der Ansprüche 2 bis 3, wobei die Klemme (40) keine Backen hat und Hauptflächen (44) im Kontakt mit den Puffern (350) aufweist.
  5. Unterbaugruppe nach Anspruch 1, wobei jeder Puffer (250; 450) mit der Klemme (40) formschlüssig verbunden ist.
  6. Unterbaugruppe nach vorhergehendem Anspruch, wobei jeder Puffer (250; 450) aus einem Material wie Kohlenstoff oder Graphit besteht, das weniger hart als ein Material des Fußes (38) ist.
  7. Unterbaugruppe nach einem der Ansprüche 5 oder 6, wobei die Puffer (450) Backen der Klemme (40) bilden.
  8. Unterbaugruppe nach einem der vorhergehenden Ansprüche, die mindestens ein Relief (60), beispielsweise mindestens zwei Reliefs, entweder auf dem Fuß (38) oder der Klemme (40) umfasst, das ausgelegt ist, um in eine Vertiefung (62) entweder des Fußes oder der Klemme einzugreifen.
  9. Unterbaugruppe nach vorhergehendem Anspruch, wobei das oder jedes Relief (60) die Form eines rechteckigen Parallelepipeds hat.
  10. Unterbaugruppe nach einem der vorhergehenden Ansprüche, wobei die Puffer (250-450) zwei an der Zahl sind.
  11. Unterbaugruppe nach einem der Ansprüche 1 bis 9, wobei die Puffer (150) vier an der Zahl sind, wobei der Fuß (38) zwei Flächen (52) aufweist, wobei jede Fläche in direktem Kontakt mit zwei von den Puffern ist, wobei die beiden Puffer in direktem Kontakt mit jeder Fläche beispielsweise voneinander beabstandet sind.
  12. Unterbaugruppe nach einem der vorhergehenden Ansprüche, wobei jeder Puffer (150-450) eine Verschleißanzeige (53) aufweist.
  13. Turbomaschine wie ein Flugzeug-Turbostrahltriebwerk (1), die eine Unterbaugruppe nach einem der vorhergehenden Ansprüche umfasst.
  14. Verfahren zur Herstellung einer Turbomaschine wie ein Flugzeug-Turbostrahltriebwerk (1), wobei:
    - zwei Puffer (150-450) entweder mit einem Fuß (38) eines Leitkranzes (24) einer Niederdruckturbine (12) oder einer Klemme (40) formschlüssig verbunden werden, wobei der Fuß mit einem Körper des Leitkranzes einteilig ist,
    - die Klemme (40) derart am Fuß befestigt wird, dass die Puffer zwischen dem Fuß (38) und der Klemme (40) angeordnet sind, und
    - die Klemme (40) an einem Gehäuse (22) der Turbomaschine befestigt wird.
  15. Verfahren zur Wartung einer Turbomaschine wie ein Flugzeug-Turbostrahltriebwerk (1), wobei:
    - ein erster Puffer (150-450) demontiert wird, der zwischen einem Fuß (38) eines Leitkranzes (24) einer Niederdruckturbine (12) und einer Klemme (40) angeordnet ist, die ausgelegt ist, um den Fuß an einem Gehäuse (22) der Turbomaschine zu befestigen, wobei der Fuß mit einem Körper des Leitkranzes einteilig ist,
    - ein zweiter Puffer (150-450) anstelle des ersten Puffers entweder mit dem Fuß (38) oder der Klemme (40) formschlüssig verbunden wird, und
    - die Klemme derart am Fuß befestigt wird, dass der zweite Puffer zwischen dem Fuß und der Klemme angeordnet ist.
EP22710661.4A 2021-02-26 2022-02-18 Leitschaufelanordnung für ein turbostrahltriebwerk eines flugzeugs Active EP4298323B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2101915A FR3120250B1 (fr) 2021-02-26 2021-02-26 Distributeur de turboréacteur d'aéronef
PCT/FR2022/050299 WO2022180329A1 (fr) 2021-02-26 2022-02-18 Distributeur de turboréacteur d'aéronef

Publications (2)

Publication Number Publication Date
EP4298323A1 EP4298323A1 (de) 2024-01-03
EP4298323B1 true EP4298323B1 (de) 2025-08-20

Family

ID=76034723

Family Applications (1)

Application Number Title Priority Date Filing Date
EP22710661.4A Active EP4298323B1 (de) 2021-02-26 2022-02-18 Leitschaufelanordnung für ein turbostrahltriebwerk eines flugzeugs

Country Status (5)

Country Link
US (1) US12492650B2 (de)
EP (1) EP4298323B1 (de)
CN (1) CN117043449A (de)
FR (1) FR3120250B1 (de)
WO (1) WO2022180329A1 (de)

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7160078B2 (en) * 2004-09-23 2007-01-09 General Electric Company Mechanical solution for rail retention of turbine nozzles
US7510371B2 (en) * 2005-06-06 2009-03-31 General Electric Company Forward tilted turbine nozzle
FR3011271B1 (fr) * 2013-10-01 2018-01-19 Safran Aircraft Engines Dispositif de connexion d'une partie fixe de turbomachine et d'un pied de distributeur d'une turbine de turbomachine
FR3011270B1 (fr) * 2013-10-01 2015-09-11 Snecma Dispositif de connexion d'une partie fixe de turbomachine et d'un pied de distributeur d'une turbine de turbomachine
FR3015550B1 (fr) * 2013-12-19 2018-12-14 Safran Aircraft Engines Dispositif de connexion d'une partie fixe de turbomachine et d'un pied de distributeur d'une turbine de turbomachine
US20180016904A1 (en) * 2016-07-13 2018-01-18 Safran Aircraft Engines Optimized aerodynamic profile for a turbine vane, in particular for a nozzle of the first stage of a turbine

Also Published As

Publication number Publication date
US20240133302A1 (en) 2024-04-25
FR3120250B1 (fr) 2023-12-22
WO2022180329A1 (fr) 2022-09-01
US20240229657A9 (en) 2024-07-11
US12492650B2 (en) 2025-12-09
FR3120250A1 (fr) 2022-09-02
CN117043449A (zh) 2023-11-10
EP4298323A1 (de) 2024-01-03

Similar Documents

Publication Publication Date Title
EP2368016B1 (de) Verschleissschutzvorrichtung für die schaufeln eines leitschaufelträgers in einem turbinentriebwerk in der aeronautik
EP3781792B1 (de) Keramische leitschaufel mit einer gedichteten zange um spannungen abzufedern
EP2603670B1 (de) Vorrichtung zur arretierung eines fusses einer laufschaufel
EP2558729B1 (de) Gleichrichter für eine turbomaschine
FR3078100A1 (fr) Couronne aubagee pour stator de turbomachine dont les aubes sont reliees a la virole externe par appui conique et pion frangible
FR2968031A1 (fr) Ensemble de fixation pour distributeur de turbine a gaz et methode de fixation, de depose et d'installation
EP3201438B1 (de) Laufschaufel einer turbomaschine mit einem flansch, der an einer sperrkerbe in der rotorscheibe anliegt
EP2694781B1 (de) Dichtring für eine turbinenstufe einer flugzeugturbomaschine mit geschlitzten drehschutzzapfen
EP4305280A1 (de) Turbinenstatoranordnung
FR2968363A1 (fr) Rotor de turbomachine avec une cale anti-usure entre un disque et un anneau
EP4298323B1 (de) Leitschaufelanordnung für ein turbostrahltriebwerk eines flugzeugs
FR2972482A1 (fr) Etage de turbine pour turbomachine d'aeronef, presentant une etancheite amelioree entre le flasque aval et les aubes de la turbine, par maintien mecanique
FR3068072A1 (fr) Ensemble pour la liaison souple entre un carter de turbine et un element annulaire de turbomachine
FR3061741A1 (fr) Turbine pour turbomachine
EP4259906B1 (de) Turbinenstatorbaugruppe mit radialem freiheitsgrad zwischen einem verteiler und einem dichtring
FR3093532A1 (fr) Dispositif de ventilation d’une roue de turbine de turbomachine et/ou de retenue axiale d’aubes d’une telle roue
FR3113300A1 (fr) Aubage de rotor de turbomachine
FR3107725A1 (fr) Ensemble pour stator de turbomachine d’aéronef, à étanchéité renforcée entre une virole externe et une couronne aubagée de stator entourée par cette virole
EP4248065B1 (de) Rotorelementanordnung eines turbinenmotors mit einer dichtungsvorrichtung
WO2025037059A1 (fr) Joint d'étanchéité pour turbomachine
FR3145583A1 (fr) Ensemble de rotor à plateformes indépendantes et procédé de montage d’un tel rotor
FR3158532A1 (fr) Ensemble d’étanchéité de turbomachine et procédé de montage associé
FR3145186A1 (fr) Cale pour rotor de turbomachine, ensemble de rotor et turbomachine associes
FR3152172A1 (fr) Joint d’étanchéité pour turbomachine
FR3126447A1 (fr) Roue mobile de turbomachine comprenant une pièce de butée axiale pour amortisseur

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: 20230904

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 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)
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

INTG Intention to grant announced

Effective date: 20250403

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 MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

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: 602022019811

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: 20250820

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: 20251220

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: 20251120

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: 20251222

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: 20250820

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: 20250820

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: 20250820

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: 20251121

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: 20250820

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: 20250820

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

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: 20250820

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: 20250820

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: 20251120

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: 20250820

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1827502

Country of ref document: AT

Kind code of ref document: T

Effective date: 20250820

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: 20250820

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

Ref country code: GB

Payment date: 20260219

Year of fee payment: 5

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: 20250820

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

Ref country code: DE

Payment date: 20260217

Year of fee payment: 5

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: 20250820

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: 20250820

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

Ref country code: FR

Payment date: 20260219

Year of fee payment: 5

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: 20250820

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

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: 20250820

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: 20250820