EP3290656B1 - Inner shroud and orientable vane of an axial turbomachine compressor and manufacturing process - Google Patents

Inner shroud and orientable vane of an axial turbomachine compressor and manufacturing process Download PDF

Info

Publication number
EP3290656B1
EP3290656B1 EP17186472.1A EP17186472A EP3290656B1 EP 3290656 B1 EP3290656 B1 EP 3290656B1 EP 17186472 A EP17186472 A EP 17186472A EP 3290656 B1 EP3290656 B1 EP 3290656B1
Authority
EP
European Patent Office
Prior art keywords
bearing
assembly
shroud
turbomachine
axial
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
EP17186472.1A
Other languages
German (de)
French (fr)
Other versions
EP3290656A1 (en
Inventor
Morgan Vyvey
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 Aero Boosters SA
Original Assignee
Safran Aero Boosters SA
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 Aero Boosters SA filed Critical Safran Aero Boosters SA
Publication of EP3290656A1 publication Critical patent/EP3290656A1/en
Application granted granted Critical
Publication of EP3290656B1 publication Critical patent/EP3290656B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
    • F04D29/056—Bearings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/083—Sealings especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00—Components
    • F05B2240/10—Stators
    • F05B2240/12—Fluid guiding means, e.g. vanes
    • 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
    • F05D2240/50—Bearings
    • 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

Definitions

  • the invention relates to the field of orientable blades of an axial turbomachine. More specifically, the invention relates to the pivot connection between an internal ferrule and a steerable vane of a turbomachine. The invention also relates to an axial turbomachine, in particular an aircraft turbojet or an aircraft turboprop.
  • the invention relates to an assembly for an axial turbomachine stator, a turbomachine and a method of assembling an assembly for a turbomachine stator.
  • orientable vanes can equip a turbojet compressor stator housing.
  • Such vanes can rotate during engine operation. Their arched blades tilt relative to the primary flow that they pass through, which makes it possible to adapt their action according to engine speed and flight conditions. The operating range and efficiency are thus extended.
  • the internal shroud which is suspended from the orientable vanes can be split into two axial parts. These two parts can come together in order to enclose the rotating bearings around the internal journals of the orientable vanes.
  • the document FR 3 009 335 A1 discloses a device for guiding a turbomachine variable pitch angle stator vanes.
  • the device comprises a casing from which a row of adjustable vanes starts radially.
  • An internal ferrule is attached to these adjustable vanes.
  • the internal ferrule is suspended from the adjustable vanes by means of cylindrical bushings fitted around the internal journals of the adjustable vanes.
  • the internal ferrule is assembled by axial approximation of its axial parts, while clamping the cylindrical bushes.
  • this assembly operation is complex as the provisional retention of the bushes in a part of the ferrule is unstable.
  • EP 2622 178 A2 shows the technical characteristics of the preamble of the independent claims.
  • the subject of the invention is an assembly for an axial turbomachine stator, in particular for a turbomachine compressor, the assembly comprising: a ferrule, optionally an internal ferrule, which is divided axially into two parts; a pocket formed in the ferrule; a bearing arranged in the pocket; and a steerable vane pivotally mounted in the bearing about a pivot axis; the ferrule comprising an interface for axially separating the parts which is axially offset from the pivot axis of the orientable vane; remarkable in that the bearing comprises a through orifice which is axially eccentric.
  • the bearing provides a seal between the orientable vane and the internal ferrule, optionally the bearing completely fills the pocket.
  • the separation interface axially delimits the bearing, one of the parts optionally comprising a flat circular surface in contact with the bearing.
  • the bearing is axially longer than it is wide along the circumference, and / or wider than it is radially thick.
  • the pocket comprises a sealed bottom, optionally in contact with the bearing.
  • the bearing comprises two generally parallel lateral faces, said faces possibly extending over the majority of the axial length of said bearing.
  • the pocket is predominantly or totally formed in one of the parts, optionally in the upstream part.
  • the downstream part comprises an annular seal, optionally with an abradable material, which is separated axially and / or radially from the bearing.
  • the bearing comprises an external face with a flat and circular surface.
  • the bearing comprises means for locking in rotation, in particular a flat face, cooperating with a pocket partition.
  • the bearing comprises a portion with radial extra thickness partially forming the outer surface of the shell.
  • the subject of the invention is also a turbomachine comprising an assembly for a stator, remarkable in that the assembly conforms to the invention, preferably the turbomachine comprises an intermediate casing with an internal hub.
  • the intermediate casing comprises a downstream face; the assembly being mounted on said downstream face.
  • one of the parts of the ferrule is in contact with the internal hub, and / or one of the parts of the ferrule is at a distance axially from the internal hub.
  • the subject of the invention is also a method of assembling an assembly for a turbomachine stator, the assembly comprising an outer shell, an inner shell with a pocket occupied by a rotating bearing in connection with an orientable blade, the inner shell. being split axially into a first part and into a second part, the method comprising the following steps: (b) placing a first shell part; (c) radial introduction of the orientable vane in a support; (d) radial engagement of the bearing within the steerable vane; the bearing comprising an axial guide face; remarkable in that the method further comprises a step (e) mounting the second part by sliding against the axial guide face of the bearing; the assembly being in accordance with the invention.
  • step (b) placing a first part, said part cooperates with a sealing device of the rotor of the turbomachine.
  • each subject of the invention is also applicable to the other subjects of the invention.
  • each object of the invention can be combined with other objects.
  • the subjects of the invention can also be combined with the embodiments of the description, which in addition can be combined with one another.
  • the invention optimizes the maintenance of the bearings by virtue of their asymmetry which has repercussions on the parts of the shell. Staggering the interface between the parts also allows more space to use a temporary socket holding tool. In addition, the contour of the bearings allows them to better save their place in the pockets.
  • the stator is more economical to produce.
  • the configuration of the ferrule parts like the filling character of the levels; increases the tightness and therefore the efficiency of the turbomachine.
  • the closed shape of the bottom of the pockets further increases the tightness, while increasing the rigidity of the corresponding part.
  • the terms internal and external refer to a positioning relative to the axis of rotation of an axial turbomachine.
  • the axial direction corresponds to the direction along the axis of rotation of the turbomachine.
  • the radial direction is perpendicular to the axis of rotation. Upstream and downstream refer to the main flow direction of the flow in the turbomachine.
  • the figure 1 shows in a simplified manner an axial turbomachine.
  • the turbojet 2 comprises a first level of compression, called low-pressure compressor 4, a second level of compression, called high-pressure compressor 6, a combustion chamber 8 and one or more levels of turbines 10.
  • the mechanical power of the turbine 10 transmitted via the central shaft to the rotor 12 sets in motion the two compressors 4 and 6.
  • the latter comprise several rows of rotor blades associated with rows of stator blades.
  • the rotation of the rotor around its axis of rotation 14 thus makes it possible to generate an air flow and to gradually compress the latter up to the entrance of the combustion chamber 8.
  • An inlet fan commonly referred to as a fan, or blower, 16 is coupled to the rotor 12 and generates an air flow which is divided into a primary flow 18 passing through the various aforementioned levels of the turbomachine, and a secondary flow 19 passing through a annular duct (partially shown) by generating a thrust useful for propelling an airplane.
  • the figure 2 is a sectional view of a compressor portion of an axial turbomachine such as that of the figure 1 .
  • the compressor can be a low-pressure compressor 4.
  • the compressor comprises a stator 20 with a one-piece outer shell 22 which can form the outer casing of the compressor.
  • the outer shell 22 is in one piece. It describes a closed loop. It has a circular material continuity and / or a circular homogeneity. It can be in one piece over its entire length. It can include a portion coming from the material.
  • the rotor 12 may comprise several rows of rotor blades 24, for example two or three or more rotor rows (only one visible). Despite the rotation of the rotor 12, the inclination in space of the chords of the rotor blades 24 remains invariable with respect to the axis of rotation 14.
  • the rotor blades 24 can form a single-piece disc; that is to say, they are inseparable from their support rim 25. Such an arrangement is also known under the term “blisk”.
  • the compressor 4 comprises several rectifiers, for example at least two, or at least three or at least four rectifiers.
  • Each rectifier comprises an annular row of stator vanes 26. These vanes are statoric in the sense that they are mounted on the stator 20 and therefore remain in contact with the latter.
  • the rectifiers are associated with the fan or with a row of rotor blades 24 to straighten their air flows, so as to convert the speed of the flow into static pressure.
  • the stator vanes 26 comprise stator vanes with piloted orientation 26. These orientable vanes 26 extend radially towards the inside of the outer shell 22 and describe an annular row. These orientable vanes 26 are also called variable-pitch vanes, or according to the acronym “VSV” for “Variable Stator Vane”. Their particularity is that they can pivot on themselves, so that the inclination of their cords can vary with respect to the axis of rotation 14 of the compressor 4, and this during its operation.
  • the orientable vanes 26 can pivot relative to the flow 18, so that they more or less cover the fluid stream by virtue of their blades. They can intercept more the primary flow 18.
  • the circumferential width which they occupy can vary. Their leading edge and their trailing edge can approach or move away from the blades of the same row. By being more or less inclined with respect to the general direction of flow, they more or less deflect the primary flow 18 to modulate the rectification of flow that they provide.
  • the stator vanes can comprise other annular rows of vanes 28; these other blades possibly being fixed orientation or piloted orientation.
  • the stator 20 of the compressor 4 comprises an internal ferrule 30 suspended from the internal ends of the orientable vanes 26, but while retaining the pivoting nature of the orientable vanes 26.
  • the internal ferrule 30 is equipped with rotating bearings 32 which are mounted around internal journals 34 of the orientable vanes 26.
  • Radially opposite, the orientable vanes 26 have external journals 36 engaged in orifices 38, possibly formed through bosses 40.
  • the journals (34; 36) can form cylindrical rods, and can be integral with their blade.
  • the steerable vane control system is well known to those skilled in the art and will not be detailed further.
  • the stator 20 comprises an intermediate casing 42, forming part of the supporting structure of the turbomachine.
  • This intermediate casing 42 can receive a separating spout (not shown).
  • the intermediate casing 42 may comprise an outer portion 44, casing arms 46 forming supports passing through the primary flow 18, and an inner hub 48 which may join the inner ferrule 30.
  • the outer shell 22 may include an annular wall 50 and an upstream flange 52 fixed to the outer portion 44 of the intermediate casing 42.
  • the wall 50 may be integral. It can extend axially along the orientable vanes 26 and possibly the other vanes.
  • the internal surface 56 of the external ferrule 22 has an internal diameter which decreases downstream and which matches the external ends of the rotor blades 24. This configuration therefore requires placing the rotor blades 24 in the outer shell 22 before mounting the orientable vanes 26 and their inner shell 30. The opposite would not be physically possible because of the one-piece nature of the outer shell 22.
  • the inner shell 30 is split. It is divided axially into an upstream part 60 and into a downstream part 62. These parts can each form a closed loop. At least one or each part (60; 62) is in one piece, that is to say that it (s) present (s) a continuity of circular material. Alternatively, one of them is segmented angularly. However, a one-piece configuration improves the rigidity and the retention of the internal ferrule 30 via the internal journals 34, which form pivot connections; that is to say a mechanical connection with only one degree of freedom.
  • the figure 3 sketch a plan view of the inner ferrule 30 of the figure 2 , the levels not being shown for the sake of clarity.
  • the axis of rotation 14 is drawn.
  • the upstream part 60 and the downstream part 62 are shown from the outside.
  • the upstream part 60 has an annular row of pockets 64, four of them being shown.
  • the pockets 64 each have a closed bottom 66 allowing a seal against the downstream part 62. They can end against the axial separation interface 68 of the axial parts (60; 62).
  • the axial separation interface 68 may be a plane perpendicular to the axis of rotation 14, or be substantially conical.
  • the pockets 66 have the shapes of the upturned letter “U”, the bearings being of a shape complementary to that of these pockets 64. These pockets 64 are separated by watertight partitions 69.
  • the figure 4 illustrates the bearing 32 in an isometric view, the bearing possibly corresponding to the bearing shown in relation to the figures 2 and 3 .
  • the bearing 32 is in one piece. It has a semi-cylindrical upstream portion, and a rectangular downstream portion provided with lateral faces 70 for axial guidance. These faces 70 can be parallel.
  • An orifice 72 intended to receive the internal journal of the orientable vane is at the interface of the portions.
  • a flat disk-shaped surface 74 surrounds the orifice 72.
  • the bearing has a radial allowance 76, which is in elevation with respect to the planar surface 74. The allowance 76 may join an axial end of the bearing, for example. its flat downstream facet 78 which allows a locking in rotation against the downstream part of the shell.
  • the figure 5 corresponds to an enlargement of an area delimited by figure 2 .
  • the section of the internal ferrule 30 at the level of an orientable vane 26 and of its bearing 32 coincides with the pivot axis 80 of the internal journal 34.
  • the pivot axis 80 is distant from the axial interface 68 between the parts (60; 62). This makes it possible to better maintain the bearing 32 in one of the parts; in this case in the upstream part 60.
  • the distant aspect can be measured in the material of the ferrule 30.
  • the extra thickness 76 is flush with the outside of the shell 30.
  • the extra thickness 76 may partially form the outer surface 82 of the inner shell 30; outer surface 82 which makes it possible to delimit and guide the primary flow 18 in the turbomachine.
  • This extra thickness 76 makes it possible to fill a space in the shell 30 while accommodating its compactness.
  • the profile of the inner shell may have a length greater than or equal to twice its radial thickness.
  • the extra thickness 76 can form a separation between the downstream part 62 and the platen disc 84 of the orientable vane 26. In particular, it can slide against the cylindrical contour of the disc 84.
  • the rotor 12 cooperates in a sealed manner with the downstream part 62, possibly at the level of an abradable seal 86.
  • the bearing 32 does not overlap the annular seal 86 since the interface 68 separates them.
  • the figure 6 is a diagram of an assembly process for a turbomachine.
  • the entities of the turbomachine may correspond to those described in relation to the figures 1 to 5 .
  • the first part in place is in contact with the rotor, for example around and / or in contact with a seal of the rotor.
  • This joint can be a game of wicks.
  • the seal can center the downstream part with respect to the rotor.
  • the other part can be free of joint.
  • step (d) engagement 106 the bearing slides radially against the first part, in particular against the downstream part, and is fitted around the internal journal of the orientable vane.
  • step (e) assembly 108 the upstream part is translated axially while being guided by the guide faces. Since the bearings can rotate relative to the journals, they rotate so as to be centered in their pocket, which simplifies the approach of the upstream part.

Description

Domaine techniqueTechnical area

L'invention se rapporte au domaine des aubes orientables de turbomachine axiale. Plus précisément, l'invention concerne la liaison pivot entre une virole interne et une aube orientable de turbomachine. L'invention a également trait à une turbomachine axiale, notamment un turboréacteur d'avion ou un turbopropulseur d'aéronef.The invention relates to the field of orientable blades of an axial turbomachine. More specifically, the invention relates to the pivot connection between an internal ferrule and a steerable vane of a turbomachine. The invention also relates to an axial turbomachine, in particular an aircraft turbojet or an aircraft turboprop.

Spécifiquement, l'invention concerne un ensemble pour stator de turbomachine axiale, une turbomachine et un procédé d'assemblage d'un ensemble pour stator de turbomachine.Specifically, the invention relates to an assembly for an axial turbomachine stator, a turbomachine and a method of assembling an assembly for a turbomachine stator.

Technique antérieurePrior art

De manière courante, plusieurs rangées d'aubes orientables peuvent équiper un carter statorique de compresseur de turboréacteur. De telles aubes peuvent pivoter pendant le fonctionnement du moteur. Leurs pales cambrées basculent par rapport au flux primaire qu'elles traversent, ce qui permet d'adapter leur action en fonction du régime moteur et des conditions de vol. La plage de fonctionnement et le rendement sont ainsi étendus.Usually, several rows of orientable vanes can equip a turbojet compressor stator housing. Such vanes can rotate during engine operation. Their arched blades tilt relative to the primary flow that they pass through, which makes it possible to adapt their action according to engine speed and flight conditions. The operating range and efficiency are thus extended.

Dans une optique de simplification de montage, ou tout simplement pour que le montage soit physiquement possible, la virole interne qui est suspendue aux aubes orientables peut être scindée en deux parties axiales. Ces deux parties peuvent se réunir afin de renfermer les paliers tournants autour des tourillons internes des aubes orientables.With a view to simplifying assembly, or quite simply so that assembly is physically possible, the internal shroud which is suspended from the orientable vanes can be split into two axial parts. These two parts can come together in order to enclose the rotating bearings around the internal journals of the orientable vanes.

Le document FR 3 009 335 A1 divulgue un dispositif de guidage d'aubes de redresseur à angle de calage variable de turbomachine. Le dispositif comprend un carter d'où part radialement une rangée d'aubes ajustables. Une virole interne est attachée à ces aubes ajustables. La virole interne est suspendue aux aubes ajustables par l'intermédiaire de douilles cylindriques chaussées autour des tourillons internes des aubes ajustables. L'assemblage de la virole interne s'effectue par rapprochement axial de ses parties axiales, tout en enserrant les douilles cylindriques. Toutefois, cette opération d'assemblage est complexe tant le maintien provisoire des douilles dans une partie de virole est instable. De plus, l'opération de rapprochement d'une partie de la virole contre les douilles est complexe puisque la mise en correspondances des parties de virole est perturbée par la présence des douilles, et que ces parties présentent une souplesse relative. En sus, la stabilité de ces douilles dans leur évidement reste réduite. EP 2622 178 A2 montre les caractéristiques techniques du préambule des revendications indépendantes.The document FR 3 009 335 A1 discloses a device for guiding a turbomachine variable pitch angle stator vanes. The device comprises a casing from which a row of adjustable vanes starts radially. An internal ferrule is attached to these adjustable vanes. The internal ferrule is suspended from the adjustable vanes by means of cylindrical bushings fitted around the internal journals of the adjustable vanes. The internal ferrule is assembled by axial approximation of its axial parts, while clamping the cylindrical bushes. However, this assembly operation is complex as the provisional retention of the bushes in a part of the ferrule is unstable. In addition, the operation of bringing a part of the ferrule closer to the bushes is complex since the matching of the ferrule parts is disturbed by the presence of the bushes, and these parts have relative flexibility. In addition, the stability of these bushes in their recess remains reduced. EP 2622 178 A2 shows the technical characteristics of the preamble of the independent claims.

Résumé de l'inventionSummary of the invention Problème techniqueTechnical problem

L'invention a pour objectif de résoudre au moins un des problèmes posés par l'art antérieur. Plus précisément, l'invention a pour objectif d'améliorer le maintien d'un palier articulant une aube orientable par rapport à une virole. L'invention a également pour objectif de proposer une solution simple, résistante, légère, économique, fiable, facile à produire, commode d'entretien, étanche, et d'inspection aisée.The object of the invention is to solve at least one of the problems posed by the prior art. More precisely, the object of the invention is to improve the retention of a bearing articulating a orientable vane with respect to a ferrule. Another objective of the invention is to provide a solution that is simple, resistant, light, economical, reliable, easy to produce, easy to maintain, waterproof, and easy to inspect.

Solution techniqueTechnical solution

L'invention a pour objet un ensemble pour stator de turbomachine axiale, notamment pour compresseur de turbomachine, l'ensemble comprenant : une virole, éventuellement une virole interne, qui est divisée axialement en deux parties ; une poche formée dans la virole ; un palier disposé dans la poche ; et une aube orientable montée de manière pivotante dans le palier autour d'un axe de pivotement ; la virole comprenant une interface de séparation axiale des parties qui est décalée axialement de l'axe de pivotement de l'aube orientable; remarquable en ce que le palier comprend un orifice traversant et excentré axialement.The subject of the invention is an assembly for an axial turbomachine stator, in particular for a turbomachine compressor, the assembly comprising: a ferrule, optionally an internal ferrule, which is divided axially into two parts; a pocket formed in the ferrule; a bearing arranged in the pocket; and a steerable vane pivotally mounted in the bearing about a pivot axis; the ferrule comprising an interface for axially separating the parts which is axially offset from the pivot axis of the orientable vane; remarkable in that the bearing comprises a through orifice which is axially eccentric.

Selon un mode avantageux de l'invention, le palier assure une étanchéité entre l'aube orientable et la virole interne, éventuellement le palier remplit totalement la poche.According to an advantageous embodiment of the invention, the bearing provides a seal between the orientable vane and the internal ferrule, optionally the bearing completely fills the pocket.

Selon un mode avantageux de l'invention, l'interface de séparation délimite axialement le palier, l'une des parties comprenant éventuellement une surface circulaire plate en contact du palier.According to an advantageous embodiment of the invention, the separation interface axially delimits the bearing, one of the parts optionally comprising a flat circular surface in contact with the bearing.

Selon un mode avantageux de l'invention, le palier est plus long axialement que large selon la circonférence, et/ou plus large qu'épais radialement.According to an advantageous embodiment of the invention, the bearing is axially longer than it is wide along the circumference, and / or wider than it is radially thick.

Selon un mode avantageux de l'invention, la poche comprend un fond étanche, éventuellement en contact du palier.According to an advantageous embodiment of the invention, the pocket comprises a sealed bottom, optionally in contact with the bearing.

Selon un mode avantageux de l'invention, le palier comprend deux faces latérales généralement parallèles, lesdites faces s'étendant éventuellement sur la majorité de la longueur axiale dudit palier.According to an advantageous embodiment of the invention, the bearing comprises two generally parallel lateral faces, said faces possibly extending over the majority of the axial length of said bearing.

Selon un mode avantageux de l'invention, la poche est majoritairement ou totalement formée dans l'une des parties, éventuellement dans la partie amont. Selon un mode avantageux de l'invention, la partie aval comprend un joint annulaire, éventuellement avec un matériau abradable, qui est séparé axialement et/ou radialement du palier.According to an advantageous embodiment of the invention, the pocket is predominantly or totally formed in one of the parts, optionally in the upstream part. According to an advantageous embodiment of the invention, the downstream part comprises an annular seal, optionally with an abradable material, which is separated axially and / or radially from the bearing.

Selon un mode avantageux de l'invention, le palier comprend une face externe avec une surface plane et circulaire.According to an advantageous embodiment of the invention, the bearing comprises an external face with a flat and circular surface.

Selon un mode avantageux de l'invention, le palier comprend des moyens de blocage en rotation, notamment une face plane, coopérant avec une cloison de poche.According to an advantageous embodiment of the invention, the bearing comprises means for locking in rotation, in particular a flat face, cooperating with a pocket partition.

Selon un mode avantageux de l'invention, le palier comprend une portion en surépaisseur radiale formant partiellement la surface externe de la virole.According to an advantageous embodiment of the invention, the bearing comprises a portion with radial extra thickness partially forming the outer surface of the shell.

L'invention a également pour objet une turbomachine comprenant un ensemble pour stator, remarquable en ce que l'ensemble est conforme à l'invention, préférentiellement la turbomachine comprend un carter intermédiaire avec un moyeu interne.The subject of the invention is also a turbomachine comprising an assembly for a stator, remarkable in that the assembly conforms to the invention, preferably the turbomachine comprises an intermediate casing with an internal hub.

Selon un mode avantageux de l'invention, le carter intermédiaire comprend une face aval ; l'ensemble étant monté sur ladite face aval.According to an advantageous embodiment of the invention, the intermediate casing comprises a downstream face; the assembly being mounted on said downstream face.

Selon un mode avantageux de l'invention, l'une des parties de la virole est en contact du moyeu interne, et/ou l'une des parties de la virole est à distance axialement du moyeu interne.According to an advantageous embodiment of the invention, one of the parts of the ferrule is in contact with the internal hub, and / or one of the parts of the ferrule is at a distance axially from the internal hub.

L'invention a également pour objet un procédé d'assemblage d'un ensemble pour stator de turbomachine, l'ensemble comprenant une virole externe, une virole interne avec une poche occupée par un palier tournant en liaison avec une aube orientable, la virole interne étant scindée axialement en une première partie et en une deuxième partie, le procédé comprenant les étapes suivantes : (b) mise en place d'une première partie de virole ; (c) introduction radiale de l'aube orientable dans un support ; (d) engagement radial du palier à l'intérieur de l'aube orientable ; le palier comprenant une face de guidage axial; remarquable en ce que le procédé comprend en outre une étape (e) montage de la deuxième partie en glissant contre la face de guidage axial du palier ; l'ensemble étant conforme à l'invention.The subject of the invention is also a method of assembling an assembly for a turbomachine stator, the assembly comprising an outer shell, an inner shell with a pocket occupied by a rotating bearing in connection with an orientable blade, the inner shell. being split axially into a first part and into a second part, the method comprising the following steps: (b) placing a first shell part; (c) radial introduction of the orientable vane in a support; (d) radial engagement of the bearing within the steerable vane; the bearing comprising an axial guide face; remarkable in that the method further comprises a step (e) mounting the second part by sliding against the axial guide face of the bearing; the assembly being in accordance with the invention.

Selon un mode avantageux de l'invention, lors de l'étape (b) mise en place d'une première partie, ladite partie coopère avec un dispositif d'étanchéité du rotor de la turbomachine.According to an advantageous embodiment of the invention, during step (b) placing a first part, said part cooperates with a sealing device of the rotor of the turbomachine.

De manière générale, les modes avantageux de chaque objet de l'invention sont également applicables aux autres objets de l'invention. Dans la mesure du possible, chaque objet de l'invention est combinable aux autres objets. Les objets de l'invention sont également combinables aux modes de réalisation de la description, qui en plus sont combinables entre eux.In general, the advantageous modes of each subject of the invention are also applicable to the other subjects of the invention. As far as possible, each object of the invention can be combined with other objects. The subjects of the invention can also be combined with the embodiments of the description, which in addition can be combined with one another.

Avantages apportésBenefits provided

L'invention optimise le maintien des paliers grâce à leur asymétrie qui se répercute sur les parties de la virole. Décaler l'interface entre les parties permet également d'offrir plus d'espace d'utilisation d'un outil provisoire de maintien des douilles. En outre, le contour des paliers leur permet de mieux gagner leur place dans les poches. Le stator est plus économique à produire.The invention optimizes the maintenance of the bearings by virtue of their asymmetry which has repercussions on the parts of the shell. Staggering the interface between the parts also allows more space to use a temporary socket holding tool. In addition, the contour of the bearings allows them to better save their place in the pockets. The stator is more economical to produce.

La configuration des parties de virole ; comme le caractère remplissant des paliers ; augmente l'étanchéité et donc le rendement de la turbomachine. La forme close du fond des poches accroit encore l'étanchéité, tout en augmentant la rigidité de la partie correspondante.The configuration of the ferrule parts; like the filling character of the levels; increases the tightness and therefore the efficiency of the turbomachine. The closed shape of the bottom of the pockets further increases the tightness, while increasing the rigidity of the corresponding part.

Brève description des dessinsBrief description of the drawings

  • La figure 1 représente une turbomachine axiale selon l'invention.The figure 1 represents an axial turbomachine according to the invention.
  • La figure 2 montre une portion de compresseur de turbomachine selon l'invention.The figure 2 shows a portion of a turbomachine compressor according to the invention.
  • La figure 3 illustre un développé à plat de la virole selon l'invention.The figure 3 illustrates a flat development of the shell according to the invention.
  • La figure 4 est une vue isométrique d'un palier selon l'invention.The figure 4 is an isometric view of a bearing according to the invention.
  • La figure 5 illustre un agrandissement de la virole interne de la figure 2.The figure 5 illustrates an enlargement of the inner shell of the figure 2 .
  • La figure 6 représente un diagramme du procédé d'assemblage d'un ensemble pour stator de turbomachine selon l'invention.The figure 6 represents a diagram of the assembly process of an assembly for a turbomachine stator according to the invention.
Description des modes de réalisationDescription of the embodiments

Dans la description qui va suivre, les termes interne et externe renvoient à un positionnement par rapport à l'axe de rotation d'une turbomachine axiale. La direction axiale correspond à la direction le long de l'axe de rotation de la turbomachine. La direction radiale est perpendiculaire à l'axe de rotation. L'amont et l'aval sont en référence au sens d'écoulement principal du flux dans la turbomachine.In the description which follows, the terms internal and external refer to a positioning relative to the axis of rotation of an axial turbomachine. The axial direction corresponds to the direction along the axis of rotation of the turbomachine. The radial direction is perpendicular to the axis of rotation. Upstream and downstream refer to the main flow direction of the flow in the turbomachine.

La figure 1 représente de manière simplifiée une turbomachine axiale. Il s'agit dans ce cas précis d'un turboréacteur double-flux. Le turboréacteur 2 comprend un premier niveau de compression, dit compresseur basse-pression 4, un deuxième niveau de compression, dit compresseur haute-pression 6, une chambre de combustion 8 et un ou plusieurs niveaux de turbines 10. En fonctionnement, la puissance mécanique de la turbine 10 transmise via l'arbre central jusqu'au rotor 12 met en mouvement les deux compresseurs 4 et 6. Ces derniers comportent plusieurs rangées d'aubes de rotor associées à des rangées d'aubes de stator. La rotation du rotor autour de son axe de rotation 14 permet ainsi de générer un débit d'air et de comprimer progressivement ce dernier jusqu'à l'entrée de la chambre de combustion 8.The figure 1 shows in a simplified manner an axial turbomachine. In this specific case, it is a double-flow turbojet. The turbojet 2 comprises a first level of compression, called low-pressure compressor 4, a second level of compression, called high-pressure compressor 6, a combustion chamber 8 and one or more levels of turbines 10. In operation, the mechanical power of the turbine 10 transmitted via the central shaft to the rotor 12 sets in motion the two compressors 4 and 6. The latter comprise several rows of rotor blades associated with rows of stator blades. The rotation of the rotor around its axis of rotation 14 thus makes it possible to generate an air flow and to gradually compress the latter up to the entrance of the combustion chamber 8.

Un ventilateur d'entrée communément désigné fan, ou soufflante, 16 est couplé au rotor 12 et génère un flux d'air qui se divise en un flux primaire 18 traversant les différents niveaux sus mentionnés de la turbomachine, et un flux secondaire 19 traversant un conduit annulaire (partiellement représenté) en générant une poussée utile à la propulsion d'un avion.An inlet fan commonly referred to as a fan, or blower, 16 is coupled to the rotor 12 and generates an air flow which is divided into a primary flow 18 passing through the various aforementioned levels of the turbomachine, and a secondary flow 19 passing through a annular duct (partially shown) by generating a thrust useful for propelling an airplane.

La figure 2 est une vue en coupe d'une portion de compresseur d'une turbomachine axiale telle que celle de la figure 1. Le compresseur peut être un compresseur basse-pression 4.The figure 2 is a sectional view of a compressor portion of an axial turbomachine such as that of the figure 1 . The compressor can be a low-pressure compressor 4.

Le compresseur comprend un stator 20 avec une virole externe 22 monobloc qui peut former le carter externe du compresseur. La virole externe 22 est d'un seul tenant. Elle décrit une boucle fermée. Elle présente une continuité de matière circulaire et/ou une homogénéité circulaire. Elle peut être monobloc sur toute sa longueur. Elle peut comprendre une portion venue de matière.The compressor comprises a stator 20 with a one-piece outer shell 22 which can form the outer casing of the compressor. The outer shell 22 is in one piece. It describes a closed loop. It has a circular material continuity and / or a circular homogeneity. It can be in one piece over its entire length. It can include a portion coming from the material.

Le rotor 12 peut comprendre plusieurs rangées d'aubes rotoriques 24, par exemple deux ou trois ou d'avantage de rangées rotoriques (une seule visible). Malgré la rotation du rotor 12, l'inclinaison dans l'espace des cordes des aubes rotoriques 24 reste invariante par rapport à l'axe de rotation 14. Les aubes rotoriques 24 peuvent former un disque monobloc ; c'est-à-dire qu'elles sont indissociables de leur jante support 25. Un tel agencement est également connu sous le terme « blisk ».The rotor 12 may comprise several rows of rotor blades 24, for example two or three or more rotor rows (only one visible). Despite the rotation of the rotor 12, the inclination in space of the chords of the rotor blades 24 remains invariable with respect to the axis of rotation 14. The rotor blades 24 can form a single-piece disc; that is to say, they are inseparable from their support rim 25. Such an arrangement is also known under the term “blisk”.

Le compresseur 4 comprend plusieurs redresseurs, par exemple au moins deux, ou au moins trois ou au moins quatre redresseurs. Chaque redresseur comprend une rangée annulaire d'aubes statoriques 26. Ces aubes sont statoriques en ce sens qu'elles sont montées sur le stator 20 et restent donc en contact de ce dernier. Les redresseurs sont associés au fan ou à une rangée d'aubes rotoriques 24 pour redresser leurs flux d'air, de sorte à convertir la vitesse du flux en pression statique.The compressor 4 comprises several rectifiers, for example at least two, or at least three or at least four rectifiers. Each rectifier comprises an annular row of stator vanes 26. These vanes are statoric in the sense that they are mounted on the stator 20 and therefore remain in contact with the latter. The rectifiers are associated with the fan or with a row of rotor blades 24 to straighten their air flows, so as to convert the speed of the flow into static pressure.

Les aubes statoriques 26 comprennent des aubes statoriques à orientation pilotée 26. Ces aubes orientables 26 s'étendent radialement vers l'intérieur de la virole extérieure 22 et décrivent une rangée annulaire. Ces aubes orientables 26 sont également appelées aubes à calage variable, ou selon l'acronyme anglo-saxon « VSV » pour « Variable Stator Vane ». Leur particularité est qu'elles peuvent pivoter sur elles-mêmes, si bien que l'inclinaison de leurs cordes peut varier par rapport à l'axe de rotation 14 du compresseur 4, et ce pendant son fonctionnement.The stator vanes 26 comprise stator vanes with piloted orientation 26. These orientable vanes 26 extend radially towards the inside of the outer shell 22 and describe an annular row. These orientable vanes 26 are also called variable-pitch vanes, or according to the acronym “VSV” for “Variable Stator Vane”. Their particularity is that they can pivot on themselves, so that the inclination of their cords can vary with respect to the axis of rotation 14 of the compressor 4, and this during its operation.

Leurs aubes peuvent balayer avec leurs cordes un angle d'au moins 30° entre deux positions extrêmes. Leurs faces intrados et extrados peuvent être plus ou moins exposées au flux primaire 18. Les aubes orientables 26 peuvent pivoter par rapport au flux 18, si bien qu'elles couvrent plus ou moins la veine fluide grâce à leurs pales. Elles peuvent intercepter davantage le flux primaire 18. La largeur circonférentielle qu'elles occupent peut varier. Leur bord d'attaque et leur bord de fuite peuvent se rapprocher ou s'éloigner des aubes de la même rangée. En étant plus ou moins inclinées par rapport au sens d'écoulement général, elles dévient plus ou moins le flux primaire 18 pour moduler le redressement de flux qu'elles procurent. Ainsi, la turbomachine et le compresseur peuvent suivre différentes courbes de rendements lors du fonctionnement. Les aubes statoriques peuvent comprendre d'autres rangées annulaires d'aubes 28 ; ces autres aubes étant éventuellement à orientation fixe ou à orientation pilotée.Their blades can sweep with their strings an angle of at least 30 ° between two extreme positions. Their intrados and extrados faces may be more or less exposed to the primary flow 18. The orientable vanes 26 can pivot relative to the flow 18, so that they more or less cover the fluid stream by virtue of their blades. They can intercept more the primary flow 18. The circumferential width which they occupy can vary. Their leading edge and their trailing edge can approach or move away from the blades of the same row. By being more or less inclined with respect to the general direction of flow, they more or less deflect the primary flow 18 to modulate the rectification of flow that they provide. Thus, the turbomachine and the compressor can follow different efficiency curves during operation. The stator vanes can comprise other annular rows of vanes 28; these other blades possibly being fixed orientation or piloted orientation.

Le stator 20 du compresseur 4 comprend une virole interne 30 suspendue aux extrémités internes des aubes orientables 26, mais tout en conservant le caractère pivotant des aubes orientables 26. A cet effet, la virole interne 30 est équipée de paliers tournants 32 qui sont montés autour des tourillons internes 34 des aubes orientables 26. Radialement à l'opposé, les aubes orientables 26 présentent des tourillons externes 36 engagés dans des orifices 38, éventuellement formés au travers de bossages 40. Les tourillons (34 ; 36) peuvent former des tiges cylindriques, et peuvent être venus de matière avec leur pale. Le système de commande des aubes orientables est bien connu de l'homme du métier et ne sera pas détaillé davantage.The stator 20 of the compressor 4 comprises an internal ferrule 30 suspended from the internal ends of the orientable vanes 26, but while retaining the pivoting nature of the orientable vanes 26. For this purpose, the internal ferrule 30 is equipped with rotating bearings 32 which are mounted around internal journals 34 of the orientable vanes 26. Radially opposite, the orientable vanes 26 have external journals 36 engaged in orifices 38, possibly formed through bosses 40. The journals (34; 36) can form cylindrical rods, and can be integral with their blade. The steerable vane control system is well known to those skilled in the art and will not be detailed further.

Le stator 20 comporte un carter intermédiaire 42, faisant partie de la structure portante de la turbomachine. Ce carter intermédiaire 42 peut recevoir un bec de séparation (non représenté). Le carter intermédiaire 42 peut comprendre une portion externe 44, des bras de carter 46 formant des supports traversant le flux primaire 18, et un moyeu interne 48 qui peut rejoindre la virole interne 30.The stator 20 comprises an intermediate casing 42, forming part of the supporting structure of the turbomachine. This intermediate casing 42 can receive a separating spout (not shown). The intermediate casing 42 may comprise an outer portion 44, casing arms 46 forming supports passing through the primary flow 18, and an inner hub 48 which may join the inner ferrule 30.

La virole externe 22 peut comprendre une paroi annulaire 50 et une bride amont 52 fixée à la portion externe 44 du carter intermédiaire 42. La paroi 50 peut être venue de matière. Elle peut s'étendre tout le long axialement des aubes orientables 26 et éventuellement des autres aubes.The outer shell 22 may include an annular wall 50 and an upstream flange 52 fixed to the outer portion 44 of the intermediate casing 42. The wall 50 may be integral. It can extend axially along the orientable vanes 26 and possibly the other vanes.

Selon une option de l'invention, la surface interne 56 de la virole externe 22 présente un diamètre interne qui décroit vers l'aval et qui épouse les extrémités externes des aubes rotoriques 24. Cette configuration impose donc de placer les aubes rotoriques 24 dans la virole externe 22 avant de monter les aubes orientables 26 et leur virole interne 30. Le contraire ne serait pas physiquement possible en raison du caractère monobloc de la virole externe 22.According to one option of the invention, the internal surface 56 of the external ferrule 22 has an internal diameter which decreases downstream and which matches the external ends of the rotor blades 24. This configuration therefore requires placing the rotor blades 24 in the outer shell 22 before mounting the orientable vanes 26 and their inner shell 30. The opposite would not be physically possible because of the one-piece nature of the outer shell 22.

En réponse à cette contrainte technique, la virole interne 30 est scindée. Elle est divisée axialement en une partie amont 60 et en une partie aval 62. Ces parties peuvent chacune former une boucle fermée. Au moins une ou chaque partie (60 ; 62) est monobloc, c'est-à-dire qu'elle(s) présent(ent) une continuité de matière circulaire. Alternativement, l'une d'elle est segmentée angulairement. Toutefois une configuration monobloc améliore la rigidité et le maintien de la virole interne 30 via les tourillons internes 34, qui forment des liaisons pivot ; soit une liaison mécanique à un seul degré de liberté.In response to this technical constraint, the inner shell 30 is split. It is divided axially into an upstream part 60 and into a downstream part 62. These parts can each form a closed loop. At least one or each part (60; 62) is in one piece, that is to say that it (s) present (s) a continuity of circular material. Alternatively, one of them is segmented angularly. However, a one-piece configuration improves the rigidity and the retention of the internal ferrule 30 via the internal journals 34, which form pivot connections; that is to say a mechanical connection with only one degree of freedom.

Bien qu'une seule aube orientable 26 et qu'un seul palier 32 ne soient visibles, le présent enseignement peut s'appliquer à toute leur rangée.Although a single orientable vane 26 and a single bearing 32 are not visible, the present teaching can be applied to their entire row.

La figure 3 esquisse une vue en plan de la virole interne 30 de la figure 2, les paliers n'étant pas représentés par soucis de clarté. L'axe de rotation 14 est tracé.The figure 3 sketch a plan view of the inner ferrule 30 of the figure 2 , the levels not being shown for the sake of clarity. The axis of rotation 14 is drawn.

La partie amont 60 et la partie aval 62 sont représentées depuis l'extérieur. La partie amont 60 présente une rangée annulaire de poches 64, quatre d'entre elles étant représentées. Les poches 64 présentent chacune un fond 66 fermé permettant une étanchéité contre la partie aval 62. Elles peuvent se terminer contre l'interface de séparation axiale 68 des parties axiales (60 ; 62). L'interface de séparation axiale 68 peut être un plan perpendiculaire à l'axe de rotation 14, ou être sensiblement conique. Les poches 66 ont des formes de la lettre « U » retournée, les paliers étant de forme complémentaire à celle de ces poches 64. Ces poches 64 sont séparées par des cloisons étanches 69.The upstream part 60 and the downstream part 62 are shown from the outside. The upstream part 60 has an annular row of pockets 64, four of them being shown. The pockets 64 each have a closed bottom 66 allowing a seal against the downstream part 62. They can end against the axial separation interface 68 of the axial parts (60; 62). The axial separation interface 68 may be a plane perpendicular to the axis of rotation 14, or be substantially conical. The pockets 66 have the shapes of the upturned letter “U”, the bearings being of a shape complementary to that of these pockets 64. These pockets 64 are separated by watertight partitions 69.

La figure 4 illustre le palier 32 dans une vue isométrique, le palier pouvant correspondre au palier représenté en relation avec les figures 2 et 3.The figure 4 illustrates the bearing 32 in an isometric view, the bearing possibly corresponding to the bearing shown in relation to the figures 2 and 3 .

Le palier 32 est monobloc. Il présente une portion amont hémicylindrique, et une portion aval rectangulaire dotée de faces latérales 70 de guidage axial. Ces faces 70 peuvent être parallèles. Un orifice 72 destiné à recevoir le tourillon interne de l'aube orientable est à l'interface des portions. Une surface plane 74 en forme de disque entoure l'orifice 72. En complément, le palier présente une surépaisseur radiale 76, qui est en élévation par rapport à la surface plane 74. La surépaisseur 76 peut joindre une extrémité axiale du palier, par exemple sa facette aval 78 plane qui permet un blocage en rotation contre la partie aval de la virole.The bearing 32 is in one piece. It has a semi-cylindrical upstream portion, and a rectangular downstream portion provided with lateral faces 70 for axial guidance. These faces 70 can be parallel. An orifice 72 intended to receive the internal journal of the orientable vane is at the interface of the portions. A flat disk-shaped surface 74 surrounds the orifice 72. In addition, the bearing has a radial allowance 76, which is in elevation with respect to the planar surface 74. The allowance 76 may join an axial end of the bearing, for example. its flat downstream facet 78 which allows a locking in rotation against the downstream part of the shell.

Bien qu'un seul palier 32 ne soit représenté, cet enseignement peut s'appliquer à toute sa rangée annulaire.Although only one bearing 32 is shown, this teaching can be applied to its entire annular row.

La figure 5 correspond à un agrandissement d'une zone délimitée en figure 2. La coupe de la virole interne 30 au niveau d'une aube orientable 26 et de son palier 32 coïncide avec l'axe de pivotement 80 du tourillon interne 34.The figure 5 corresponds to an enlargement of an area delimited by figure 2 . The section of the internal ferrule 30 at the level of an orientable vane 26 and of its bearing 32 coincides with the pivot axis 80 of the internal journal 34.

L'axe de pivotement 80 est distant de l'interface axiale 68 entre les parties (60 ; 62). Ceci permet de mieux maintenir le palier 32 dans l'une des parties ; en l'occurrence dans la partie amont 60. L'aspect distant peut être mesuré dans la matière de la virole 30.The pivot axis 80 is distant from the axial interface 68 between the parts (60; 62). This makes it possible to better maintain the bearing 32 in one of the parts; in this case in the upstream part 60. The distant aspect can be measured in the material of the ferrule 30.

La surépaisseur 76 affleure l'extérieur de la virole 30. La surépaisseur 76 peut former partiellement la surface extérieure 82 de la virole interne 30 ; surface extérieure 82 qui permet de délimiter et de guider le flux primaire 18 dans la turbomachine. Cette surépaisseur 76 permet de combler un espace de la virole 30 tout en s'accommodant de son caractère compact. Par exemple, le profil de la virole interne peut présenter une longueur supérieure ou égale au double de son épaisseur radiale. La surépaisseur 76 peut former une séparation entre la partie aval 62 et le disque platine 84 de l'aube orientable 26. En particulier, elle peut glisser contre le contour cylindrique du disque 84.The extra thickness 76 is flush with the outside of the shell 30. The extra thickness 76 may partially form the outer surface 82 of the inner shell 30; outer surface 82 which makes it possible to delimit and guide the primary flow 18 in the turbomachine. This extra thickness 76 makes it possible to fill a space in the shell 30 while accommodating its compactness. For example, the profile of the inner shell may have a length greater than or equal to twice its radial thickness. The extra thickness 76 can form a separation between the downstream part 62 and the platen disc 84 of the orientable vane 26. In particular, it can slide against the cylindrical contour of the disc 84.

Le rotor 12 coopère de manière étanche avec la partie aval 62, éventuellement au niveau d'un joint abradable 86. Le palier 32 ne chevauche pas le joint annulaire 86 puisque l'interface 68 les sépare.The rotor 12 cooperates in a sealed manner with the downstream part 62, possibly at the level of an abradable seal 86. The bearing 32 does not overlap the annular seal 86 since the interface 68 separates them.

La figure 6 est un diagramme d'un procédé d'assemblage d'une turbomachine. Les entités de la turbomachine peuvent correspondre à celles décrites en relation avec les figures 1 à 5.The figure 6 is a diagram of an assembly process for a turbomachine. The entities of the turbomachine may correspond to those described in relation to the figures 1 to 5 .

Le procédé peut comporter les étapes suivantes, éventuellement réalisées dans l'ordre qui suit :

  1. (a)- agencement 100 de la virole externe autour du rotor ;
  2. (b)- mise en place 102 de la partie aval de la virole interne ;
  3. (c)- introduction 104 radiale de l'aube orientable dans la virole externe ;
  4. (d)- engagement 106 radial du palier à l'intérieur de l'aube orientable ;
  5. (e)- montage 108 de la partie amont de la virole interne en la glissant axialement contre la face de guidage axial du palier.
The method may include the following steps, optionally carried out in the following order:
  1. (a) - arrangement 100 of the outer shell around the rotor;
  2. (b) - positioning 102 of the downstream part of the inner shell;
  3. (c) - radial introduction 104 of the orientable blade into the outer shell;
  4. (d) - radial engagement 106 of the bearing inside the orientable vane;
  5. (e) - mounting 108 of the upstream part of the internal ring by sliding it axially against the axial guide face of the bearing.

Lors de l'étape (b) mise en place 102, la première partie mise en place est en contact du rotor, par exemple autour et/ou au contact d'un joint du rotor. Ce joint peut être un jeu de léchettes. Le joint peut centrer la partie aval par rapport au rotor. L'autre partie peut être libre de joint.During step (b) placement 102, the first part in place is in contact with the rotor, for example around and / or in contact with a seal of the rotor. This joint can be a game of wicks. The seal can center the downstream part with respect to the rotor. The other part can be free of joint.

Lors de l'étape (d) engagement 106, le palier glisse radialement contre la première partie, notamment contre la partie aval, et est chaussé autour du tourillon interne de l'aube orientable.During step (d) engagement 106, the bearing slides radially against the first part, in particular against the downstream part, and is fitted around the internal journal of the orientable vane.

Pendant l'étape (e) montage 108, la partie amont est translatée axialement tout en étant guidée par les faces de guidage. Puisque les paliers peuvent tourner par rapport aux tourillons, ils tournent de sorte à s'axer dans leur poche, ce qui simplifie le rapprochement de la partie amont.During step (e) assembly 108, the upstream part is translated axially while being guided by the guide faces. Since the bearings can rotate relative to the journals, they rotate so as to be centered in their pocket, which simplifies the approach of the upstream part.

Claims (15)

  1. A stator assembly (20) for an axial turbomachine (2), in particular for a compressor (4; 6) of a turbomachine (2), the assembly comprising:
    - a shroud (30), possibly an inner shroud (30), which is axially divided into two parts (60; 62);
    - a pocket (64) formed in the shroud (30);
    - a bearing (32) located in the pocket (64); and
    - an orientable vane (26) pivotably mounted in the bearing (32) about a pivot axis (80);
    the shroud (30) comprising an axial separating interface (68) of the parts (60; 62), the pivot axis (80) of the orientable vane (26) being axially at a distance of the interface of axial separation (68),
    characterized in that the bearing (32) comprises a through opening (72) and axially offset.
  2. The assembly according to claim 1, characterised in that the bearing (32) provides a seal between the orientable vane (26) and the shroud (30), the bearing (32) possibly wholly filling the pocket (64).
  3. The assembly according to one of claims 1 and 2, characterised in that the separating interface (68) axially delimits the bearing (32), one of the parts (60; 62) possibly comprising a flat circular surface in contact with the bearing (32).
  4. The assembly according to one of claims 1 to 3, characterised in that the bearing (32) is longer axially than wide in circumference, and/or wider than its radial thickness.
  5. The assembly according to one of claims 1 to 4, characterised in that the pocket (64) comprises a sealed base (66), which may possibly be in contact with the bearing (32).
  6. The assembly according to one of claims 1 to 5, characterised in that the bearing (32) comprises two generally parallel lateral faces (70) in circumference, said faces possibly extending over most of the axial length of the said bearing (32).
  7. The assembly according to one of claims 1 to 6, characterised in that the pocket (64) is mostly or wholly formed in one of the parts (60; 62), possibly in the upstream part (60).
  8. The assembly according to one of claims 1 to 7, characterised in that the downstream part (62) comprises an annular seal (86), possibly with an abradable material, which is at axially and/or radially distance from the bearing (32).
  9. The assembly according to one of claims 1 to 8, characterised in that the bearing (32) comprises an outer face with a flat and circular surface (74) for guiding the blade in rotation.
  10. The assembly according to one of claims 1 to 9, characterised in that the bearing (32) comprises means for immobilising rotation, in particular a flat face (70; 78) acting together with a wall (69) of the pocket (64).
  11. The assembly according to one of claims 1 to 10, characterised in that the bearing (32) comprises a portion of radial excess thickness (76) partly forming the outer surface (82) of the shroud (30).
  12. A turbomachine (2) comprising a stator assembly, characterised in that the assembly is according to one of claims 1 to 11, preferably the turbomachine (2) comprises an intermediate casing (42) with an inner hub (48).
  13. The turbomachine (2) according to claim 12, characterised in that the intermediate casing (42) comprises a downstream face, the assembly being mounted on the said downstream face, and one of the parts (60; 62) of the shroud (30) is in contact with the inner hub (48), and/or one of the parts (60; 62) of the shroud (30) is at an axial distance from the inner hub (48).
  14. A process for assembling a stator assembly (20) of a turbomachine (2), the assembly comprising an outer shroud (22), an inner shroud (30) with a pocket (64) occupied by a rotating bearing (32) connected to an orientable vane (26), the inner shroud (30) being axially divided into a first part and a second part, the process comprising the following steps:
    (b) fitting (102) a first part (62) of the inner shroud (30);
    (c) radially inserting (104) the orientable vane (26) into a support;
    (d) radially engaging (106) the bearing (32) inside the orientable vane (26);
    the bearing (32) comprising an axial guide face (70),
    characterized in that the process further comprises a step
    (e) fitting (108) the second part (60) by sliding it against the axial guide face (70) of the bearing (32); the assembly being according to one of claims 1 to 11.
  15. The process according to claim 14, characterised in that during the step (b) of fitting (102) a first part (62), said part acts together with a sealing device of the rotor of the turbomachine (2).
EP17186472.1A 2016-08-30 2017-08-16 Inner shroud and orientable vane of an axial turbomachine compressor and manufacturing process Active EP3290656B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
BE2016/5663A BE1024524B1 (en) 2016-08-30 2016-08-30 INTERNAL VIROL AND DIRECT TANK OF AXIAL TURBOMACHINE COMPRESSOR

Publications (2)

Publication Number Publication Date
EP3290656A1 EP3290656A1 (en) 2018-03-07
EP3290656B1 true EP3290656B1 (en) 2021-09-29

Family

ID=56888861

Family Applications (1)

Application Number Title Priority Date Filing Date
EP17186472.1A Active EP3290656B1 (en) 2016-08-30 2017-08-16 Inner shroud and orientable vane of an axial turbomachine compressor and manufacturing process

Country Status (5)

Country Link
US (1) US11512713B2 (en)
EP (1) EP3290656B1 (en)
CN (1) CN107795525B (en)
BE (1) BE1024524B1 (en)
CA (1) CA2976930A1 (en)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE1024605B1 (en) * 2016-09-27 2018-04-26 Safran Aero Boosters S.A. CARTRIDGE WITH SUCTION ARMS FOR AXIAL TURBOMACHINE
US11028709B2 (en) * 2018-09-18 2021-06-08 General Electric Company Airfoil shroud assembly using tenon with externally threaded stud and nut
GB2596701A (en) * 2019-04-01 2022-01-05 Dasari Dileep Systems and methods for increasing the efficiency of axial ducted fans
CN110617117B (en) * 2019-08-02 2022-04-08 中国航发贵阳发动机设计研究所 Method for adjusting throat area of turbine guider
DE102021129534A1 (en) 2021-11-12 2023-05-17 MTU Aero Engines AG Guide vane arrangement of a turbomachine and method for assembling a guide vane arrangement

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB749577A (en) * 1952-07-10 1956-05-30 Havilland Engine Co Ltd Improvements in or relating to blade ring assemblies for axial flow compressors or turbines
US4792277A (en) * 1987-07-08 1988-12-20 United Technologies Corporation Split shroud compressor
US4834613A (en) * 1988-02-26 1989-05-30 United Technologies Corporation Radially constrained variable vane shroud
US5639212A (en) * 1996-03-29 1997-06-17 General Electric Company Cavity sealed compressor
FR2824593B1 (en) * 2001-05-10 2003-07-18 Snecma Moteurs ARRANGEMENT FOR SUPPORTING STATOR BLADE PIVOTS WITH TWO RING PARTS LINKED BY AN INTERNAL ELEMENT
DE102006024085B4 (en) * 2006-05-23 2020-04-16 MTU Aero Engines AG Turbo compressor in axial design
US7713022B2 (en) * 2007-03-06 2010-05-11 United Technologies Operations Small radial profile shroud for variable vane structure in a gas turbine engine
US8500394B2 (en) * 2008-02-20 2013-08-06 United Technologies Corporation Single channel inner diameter shroud with lightweight inner core
US8858165B2 (en) * 2010-09-30 2014-10-14 Rolls-Royce Corporation Seal arrangement for variable vane
JP5747703B2 (en) * 2011-07-13 2015-07-15 株式会社Ihi Turbo compressor
US10125789B2 (en) * 2013-02-15 2018-11-13 United Technologies Corporation Bushing arranged between a body and a shaft, and connected to the body
FR3009335B1 (en) 2013-07-30 2015-09-04 Snecma TURBOMACHINE VARIABLE ROTATION ANGLE RECTIFIER AUB GUIDING DEVICE
JP5736443B1 (en) * 2013-12-19 2015-06-17 川崎重工業株式会社 Variable vane mechanism

Also Published As

Publication number Publication date
CA2976930A1 (en) 2018-02-28
EP3290656A1 (en) 2018-03-07
CN107795525B (en) 2022-01-04
US11512713B2 (en) 2022-11-29
US20180058471A1 (en) 2018-03-01
BE1024524A1 (en) 2018-03-23
CN107795525A (en) 2018-03-13
BE1024524B1 (en) 2018-03-26

Similar Documents

Publication Publication Date Title
EP3290656B1 (en) Inner shroud and orientable vane of an axial turbomachine compressor and manufacturing process
EP3517731B1 (en) Arrangement comprising an annular passage between a stator and a rotor platform of a turbomachine and corresponding method of compressor stability control
EP2801702A1 (en) Inner shroud of turbomachine with abradable seal
EP3477050B1 (en) Turbomachine compressor with asymmetricly contoured wall ring
EP4185767A1 (en) Turbine engine module equipped with a propeller and stator vanes supported by retaining means and corresponding turbine engine
EP3412876B1 (en) Variable geometry compressor of axial turbine engine
WO2017017392A1 (en) Air-flow straightening assembly having improved aerodynamic performances
EP3290657B1 (en) Stator with adjustable vanes for the compressor of an axial turbine engine
EP3382242B1 (en) Brush seal for a turbine engine rotor
FR3073891B1 (en) MAT OF A PROPULSIVE ASSEMBLY
EP4025789B1 (en) Polyspherical hub of a turbomachine for adjustable blades
WO2021123146A1 (en) Module for turbomachine
EP3382155B1 (en) Sealing system for a turbomachine and corresponding turbomachine
BE1026325B1 (en) RUBBER WITH SCALABLE PROFILING FOR TURBOMACHINE COMPRESSOR
BE1026006B1 (en) VARIABLE TIMING AUB SYSTEM FOR TURBOMACHINE COMPRESSOR
WO2024033065A1 (en) Variable vane of an aircraft turbine engine stator, and aircraft turbine engine
BE1025666B1 (en) NON-AXISYMMETRIC CARTER PROFILE FOR TURBOMACHINE COMPRESSOR

Legal Events

Date Code Title Description
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: THE APPLICATION HAS BEEN PUBLISHED

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

AX Request for extension of the european patent

Extension state: BA ME

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: 20180829

RBV Designated contracting states (corrected)

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

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

Free format text: STATUS: EXAMINATION IS IN PROGRESS

17Q First examination report despatched

Effective date: 20201130

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

Free format text: STATUS: EXAMINATION IS IN PROGRESS

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: 20210322

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

Ref country code: AT

Ref legal event code: REF

Ref document number: 1434364

Country of ref document: AT

Kind code of ref document: T

Effective date: 20211015

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602017046663

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: LT

Ref legal event code: MG9D

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: 20211229

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: 20210929

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: 20210929

Ref country code: LT

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: 20210929

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: 20211229

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: 20210929

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: 20210929

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20210929

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1434364

Country of ref document: AT

Kind code of ref document: T

Effective date: 20210929

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: 20210929

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: 20211230

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: 20210929

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: 20220129

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: 20210929

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: 20210929

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: 20220131

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: 20210929

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: 20210929

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: 20210929

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: 20210929

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: 20210929

Ref country code: AL

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: 20210929

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602017046663

Country of ref document: DE

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: 20210929

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

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

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20220630

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

Ref country code: SI

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: 20210929

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: 20210929

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

Ref country code: MC

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: 20210929

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

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

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20220816

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20220831

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20220831

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

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20220816

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

Ref country code: GB

Payment date: 20230720

Year of fee payment: 7

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

Ref country code: FR

Payment date: 20230720

Year of fee payment: 7

Ref country code: DE

Payment date: 20230720

Year of fee payment: 7

Ref country code: BE

Payment date: 20230720

Year of fee payment: 7

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

Ref country code: HU

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

Effective date: 20170816