EP3443202A1 - Blade and method for resurfacing an abradable coating - Google Patents

Blade and method for resurfacing an abradable coating

Info

Publication number
EP3443202A1
EP3443202A1 EP17721425.1A EP17721425A EP3443202A1 EP 3443202 A1 EP3443202 A1 EP 3443202A1 EP 17721425 A EP17721425 A EP 17721425A EP 3443202 A1 EP3443202 A1 EP 3443202A1
Authority
EP
European Patent Office
Prior art keywords
blade
resin
rotor
housing
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.)
Granted
Application number
EP17721425.1A
Other languages
German (de)
French (fr)
Other versions
EP3443202B1 (en
Inventor
Michael ISEMENE
Alexandre Branco
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 EP3443202A1 publication Critical patent/EP3443202A1/en
Application granted granted Critical
Publication of EP3443202B1 publication Critical patent/EP3443202B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • 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
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan 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
    • F05D2230/80—Repairing, retrofitting or upgrading 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
    • F05D2230/90—Coating; Surface treatment
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • 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
    • F05D2300/40—Organic materials
    • F05D2300/44—Resins

Definitions

  • the present invention relates to a blade and a method of reloading an abradable layer on an inner surface of a turbomachine casing for surrounding the blade.
  • the state of the art notably comprises the documents US-A1 - 2002/090302, EP-A1-2,813,672, DE-A1-16,2262, EP-A1-2,899,371 and US-A1 -2007 / 243070. .
  • a turbomachine comprises rotor blades that rotate inside housings. It is known to provide on the inner surface of such a housing a layer of abradable material with which the ends of the blades are intended to cooperate by friction to limit the flow of non-functional leakage air between these ends and the housing, and thus optimize the performance of the turbomachine.
  • the abradable layer is intended to wear out by friction as mentioned above. When it is too worn or when it is damaged for example by impacts of foreign bodies, it must be repaired to maintain the expected performance of the turbomachine.
  • the present invention provides a simple, effective and economical solution to this problem.
  • the invention proposes a blade, in particular a fan blade, for reloading an abradable layer on an inner surface of a turbomachine casing intended to surround the blade, the blade having a foot and a blade having a apex opposite to said foot, the foot comprising a housing for storing or passing a polymerizable resurfacing resin, and the blade having longitudinal conduits whose first ends are connected to said housing and whose opposite ends open at said apex.
  • the invention is particularly advantageous because it uses a blade for reloading an abradable layer.
  • This blade is in fact configured to be able to deposit or projecting the reloading resin during the rotation of the rotor that supports the blade. Under the effect of centrifugal forces, the resin is intended to move from the housing into the ducts and up to the top of the blade, to be then deposited or projected on the housing.
  • the reloading of the layer can be performed under wing without removing the turbomachine and therefore with a limited time of immobilization of the aircraft.
  • the blade according to the invention may comprise one or more of the following characteristics, taken separately from each other or in combination with each other:
  • the dawn comprises a series of longitudinal channels substantially aligned along a rope of the dawn
  • the blade further comprises a scraping member, or even spreading, fixed on said top,
  • said member is removably attached to said end, for example by interlocking
  • said organ has an elongate shape and extends along a rope of the blade; the member and the ducts may extend along the same rope of the blade, so that they can communicate with each other for example, - said member comprises a cavity in fluid communication with outlets of said ducts for its supply in resin, and at least a resin distribution channel extending from said cavity to an end of the member opposite said foot.
  • the invention also relates to a method of reloading an abradable layer on an inner surface of a fan casing of a turbomachine, comprising the following steps:
  • the method comprises a step of spreading and scraping the deposited resin, by means of said member.
  • blades of the rotor are replaced by blades as described above, which are regularly distributed around the axis of rotation of the rotor.
  • Figure 1 is a schematic half-view in axial section of a turbomachine fan, Figure 1 showing the outer periphery of the fan to a smaller scale than its inner periphery;
  • FIG. 2 is a very schematic perspective view of a blade according to the invention.
  • FIG. 3 is a very schematic front view of a fan rotor equipped with four blades according to the invention.
  • FIG. 4 is a very schematic view of an end of a blade according to the invention.
  • FIG. 1 partially represents a fan 10 of a turbomachine, such as an aircraft turbojet engine.
  • a turbomachine comprises from upstream to downstream, that is to say in the flow direction of the gas flows, a blower, one or more compressors, a combustion chamber, one or more turbines, and a nozzle for ejecting the combustion gases leaving the turbine or turbines.
  • the fan 10 is located at the upstream end of the turbomachine. It comprises a rotor 12 comprising a hub 14 bearing an annular row of blades 16, called fan blades, the rotor 12 rotating inside a retention casing 18.
  • the rotor 12 comprises at its outer periphery an annular row of foot mounting cells 20 of the blades 16.
  • Each cell 22 generally has a dovetail-shaped section and each blade root has a shape complementary to the blade. alveole to allow a mounting of the blade by fitting its foot into the cell.
  • a wedge can be inserted between the foot of a blade and the bottom of the cell 22 for receiving this foot, in order to immobilize it.
  • Each blade 16 comprises a blade 24 which extends from the root radially outwardly relative to the axis A of rotation of the rotor 12.
  • the blade comprises an apex opposite the foot, that is to say its radially outer end.
  • the retention housing 18 here has a generally cylindrical shape and extends around the fan blades 16. It comprises an inner cylindrical surface on which is provided an annular layer 26 of abradable material. This layer 26 surrounds the blades 16 and extends over the entire longitudinal dimension of the blades along the axis A.
  • the fan rotor 12 is located downstream of an inlet cone 28, which can be secured to the rotor 12, and upstream of an annular separator 30 which its function is to divide the annular inlet air stream which passes through the fan blades, into two coaxial annular veins, respectively internal for the generation of a primary flow or hot flow, and external for the generation of a flow secondary or cold flow.
  • the invention relates to a blade for reloading an abradable layer on the inner surface of a housing such as the casing 18 of FIG.
  • the foot 20 of the blade 12, better visible in Figure 2, comprises a housing 32 for storing or passing a polymerizable resurfacing resin.
  • this housing 32 can be connected to a source of resin and ensure the distribution of the resin to the rest of the blade, or form itself the resin source.
  • the housing 32 may directly contain the resin or be designed to receive a resin cartridge.
  • the resin may be of the two-component type and thus comprise two components, such as a resin component and a hardener component, to be mixed and cured by polymerization, for example at room temperature.
  • the epoxy resin marketed by 3M under the name Scotch-Weld TM is suitable for example for this application.
  • the blade 24 of the blade 16 comprises several channels 34 for conveying the resin to the top of the blade.
  • These channels are longitudinal, that is to say they extend along the longitudinal axis of the blade, which is a substantially radial axis with respect to the axis A.
  • the channels 34 are preferably substantially rectilinids to facilitate the aforementioned routing. They have for example a diameter of a few millimeters, this diameter being naturally a function of the viscosity of the resin at its temperature of use.
  • the ducts 34 extend between the housing 32 and the top of the blade 24.
  • the radially inner ends of the ducts 34 open into the housing 32 and their radially outer ends open on a radially outer end surface 36 of the blade, which is intended to face the abradable layer 26.
  • Figures 2 and 4 show in more detail the end surface 36 and the outlets 39 of the ducts 34 on this surface 36.
  • the number of internal ducts in the blade can be relatively high. They can be grouped together in groups, as shown in FIG. 4.
  • the ducts 34 can be distributed on the surface and be aligned along a rope of the blade.
  • the top of the blade 16 is advantageously equipped with a spreading and scraping member 38, which is applied and fixed on the end surface 36.
  • the member 38 has an elongate shape and is intended to extend along the rope of the blade. It is advantageously fixed removably on the blade, for example by interlocking or snap elastic.
  • the member 38 comprises pins 40 or clips intended to cooperate with orifices 42 provided at the top of the blade and opening on the surface 36, these pins being visible in Figure 5.
  • This figure shows a embodiment of the member 38 which comprises a cavity 44 intended to be in fluid communication with the outlets 39 of the ducts 34 for its supply of resin.
  • the member 38 may comprise a radially inner bottom wall pierced with orifices intended to be aligned with the outlets 39 of the ducts, when the member is mounted on the blade.
  • the member 38 further comprises at least one resin distribution channel 46 extending from the cavity 44 to a radially outer end of the member 38. This end is preferably configured to spread the resin and scrape the excess resin . It is shaped to reproduce the theoretical profile of the air inlet duct of the blower.
  • the invention also relates to a method of reloading an abradable layer 26 comprising the steps of: - Remove at least one blade of the rotor and replace it with a blade 16 as described above,
  • the method comprises a step of spreading and scraping the deposited resin, by means of this member.
  • vanes of the rotor are replaced by blades 16.
  • These blades 16 are preferably regularly distributed around the axis of rotation of the rotor, the other vanes, d
  • the origin of the rotor is not shown in the figure for the sake of clarity.
  • a pump is used to force the resin to flow from the housing of each blade along its internal ducts.
  • the pump can be set to a pressure of 150 bar and the blower can be rotated, for example manually or by self-rotation, when the pump is turned on.
  • the resin is forced to flow into the conduits by the sole centrifugal force applied due to the rotation of the blower, for example at a speed of about 500 rpm.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The invention relates to a blade (16), in particular a fan blade, for resurfacing an abradable coating (26) on an internal surface of a turbine engine case (18) intended to surround the blade. The comprises a root (20) and an airfoil (24) having a tip opposite the root, said root comprising a housing (32) for the storage or passage of a polymerisable refill resin. The airfoil comprises longitudinal channels (34), the first ends of said channels being connected to the housing and the opposite ends opening at the aforementioned tip.

Description

Aube et procédé de rechargement d'une couche d'abradable  Dawn and method of reloading an abradable layer
DOMAINE TECHNIQUE TECHNICAL AREA
La présente invention concerne une aube et un procédé de rechargement d'une couche d'abradable sur une surface interne d'un carter de turbomachine destiné à entourer l'aube.  The present invention relates to a blade and a method of reloading an abradable layer on an inner surface of a turbomachine casing for surrounding the blade.
ETAT DE L'ART  STATE OF THE ART
L'état de l'art comprend notamment les documents US-A1 - 2002/090302, EP-A1 -2 813 672, DE-A1 -16 28 262, EP-A1 -2 899 371 et US-A1 -2007/243070.  The state of the art notably comprises the documents US-A1 - 2002/090302, EP-A1-2,813,672, DE-A1-16,2262, EP-A1-2,899,371 and US-A1 -2007 / 243070. .
Une turbomachine comprend des aubes de rotor qui tournent à l'intérieur de carters. Il est connu de prévoir sur la surface interne d'un tel carter une couche de matériau abradable avec laquelle les extrémités des aubes sont destinées à coopérer par frottement pour limiter le débit d'air de fuite non fonctionnel entre ces extrémités et le carter, et ainsi optimiser les performances de la turbomachine.  A turbomachine comprises rotor blades that rotate inside housings. It is known to provide on the inner surface of such a housing a layer of abradable material with which the ends of the blades are intended to cooperate by friction to limit the flow of non-functional leakage air between these ends and the housing, and thus optimize the performance of the turbomachine.
C'est notamment le cas des aubes de soufflante d'une turbomachine qui sont entourées par un carter de rétention sur la surface interne duquel est disposée une couche de matériau abradable ou couche d'abradable.  This is particularly the case of the fan blades of a turbomachine which are surrounded by a retention casing on the inner surface of which is disposed a layer of abradable material or abradable layer.
La couche d'abradable est destinée à s'user par frottement comme évoqué ci-dessus. Lorsqu'elle est trop usée ou lorsqu'elle est abîmée par exemple par des impacts de corps étrangers, elle doit être réparée pour conserver les performances attendues de la turbomachine.  The abradable layer is intended to wear out by friction as mentioned above. When it is too worn or when it is damaged for example by impacts of foreign bodies, it must be repaired to maintain the expected performance of the turbomachine.
Deux solutions sont alors possibles : le retrait et le remplacement de la couche d'abradable ou son rechargement en vue par exemple de boucher les trous ou combler les zones trop usées. Ces deux opérations sont longues et coûteuses et entraînent systématiquement une dépose du moteur de l'aéronef auquel il est fixé.  Two solutions are then possible: the removal and replacement of the layer of abradable or reloading for example to plug the holes or fill the areas too worn. These two operations are long and expensive and systematically remove the engine of the aircraft to which it is attached.
La présente invention propose une solution simple, efficace et économique à ce problème.  The present invention provides a simple, effective and economical solution to this problem.
EXPOSE DE L'INVENTION L'invention propose une aube, en particulier de soufflante, pour le rechargement d'une couche d'abradable sur une surface interne d'un carter de turbomachine destiné à entourer l'aube, l'aube comportant un pied et une pale présentant un sommet opposé audit pied, le pied comportant un logement de stockage ou de passage d'une résine polymérisable de rechargement, et la pale comportant des conduits longitudinaux dont des premières extrémités sont reliées audit logement et dont des extrémités opposées débouchent audit sommet. SUMMARY OF THE INVENTION The invention proposes a blade, in particular a fan blade, for reloading an abradable layer on an inner surface of a turbomachine casing intended to surround the blade, the blade having a foot and a blade having a apex opposite to said foot, the foot comprising a housing for storing or passing a polymerizable resurfacing resin, and the blade having longitudinal conduits whose first ends are connected to said housing and whose opposite ends open at said apex.
L'invention est particulièrement avantageuse car elle utilise une aube pour le rechargement d'une couche d'abradable. Cette aube est en effet configurée pour être en mesure de déposer ou de projeter de la résine de rechargement pendant la rotation du rotor qui supporte cette aube. Sous l'effet des forces centrifuges, la résine est destinée à se déplacer du logement jusque dans les conduits puis jusqu'au sommet de l'aube, pour être ensuite déposée ou projetée sur le carter. Le rechargement de la couche peut être réalisé sous aile sans dépose de la turbomachine et donc avec un temps limité d'immobilisation de l'aéronef.  The invention is particularly advantageous because it uses a blade for reloading an abradable layer. This blade is in fact configured to be able to deposit or projecting the reloading resin during the rotation of the rotor that supports the blade. Under the effect of centrifugal forces, the resin is intended to move from the housing into the ducts and up to the top of the blade, to be then deposited or projected on the housing. The reloading of the layer can be performed under wing without removing the turbomachine and therefore with a limited time of immobilization of the aircraft.
L'aube selon l'invention peut comprendre une ou plusieurs des caractéristiques suivantes, prises isolément les unes des autres ou en combinaison les unes avec les autres :  The blade according to the invention may comprise one or more of the following characteristics, taken separately from each other or in combination with each other:
- l'aube comprend une série de canaux longitudinaux sensiblement alignés le long d'une corde de l'aube,  the dawn comprises a series of longitudinal channels substantially aligned along a rope of the dawn,
- l'aube comprend en outre un organe de raclage, voire d'étalement, fixé sur ledit sommet,  - The blade further comprises a scraping member, or even spreading, fixed on said top,
- ledit organe est fixé de manière amovible sur ladite extrémité, par exemple par emboîtement, said member is removably attached to said end, for example by interlocking,
- ledit organe a une forme allongée et s'étend le long d'une corde de l'aube ; l'organe et les conduits peuvent s'étendre selon la même corde de l'aube, de façon à ce qu'ils puissent communiquer entre eux par exemple, - ledit organe comprend une cavité en communication fluidique avec des débouchés desdits conduits pour son alimentation en résine, et au moins un canal de distribution de résine s'étendant depuis ladite cavité vers une extrémité de l'organe opposée audit pied. said organ has an elongate shape and extends along a rope of the blade; the member and the ducts may extend along the same rope of the blade, so that they can communicate with each other for example, - said member comprises a cavity in fluid communication with outlets of said ducts for its supply in resin, and at least a resin distribution channel extending from said cavity to an end of the member opposite said foot.
L'invention concerne également un procédé de rechargement d'une couche d'abradable sur une surface interne d'un carter de soufflante d'une turbomachine, comportant les étapes suivantes :  The invention also relates to a method of reloading an abradable layer on an inner surface of a fan casing of a turbomachine, comprising the following steps:
- démonter au moins une aube d'un rotor, en particulier de soufflante, de ladite turbomachine et la remplacer par une aube telle que décrite ci- dessus,  - disassemble at least one blade of a rotor, in particular of a blower, of said turbomachine and replace it with a blade as described above,
- mettre en rotation ledit rotor de façon à ce que de la résine contenue dans ledit logement circule par effet centrifuge dans lesdits conduits et soient déposées ou projetées sur ladite surface.  - Rotating said rotor so that resin contained in said housing circulates by centrifugal effect in said conduits and are deposited or projected on said surface.
Avantageusement, le procédé comprend une étape consistant à étaler et racler la résine déposée, au moyen dudit organe.  Advantageously, the method comprises a step of spreading and scraping the deposited resin, by means of said member.
De préférence, plusieurs, par exemple quatre, aubes du rotor sont remplacées par des aubes telles que décrites ci-dessus, qui sont régulièrement réparties autour de l'axe de rotation du rotor.  Preferably, several, for example four, blades of the rotor are replaced by blades as described above, which are regularly distributed around the axis of rotation of the rotor.
DESCRIPTION DES FIGURES  DESCRIPTION OF THE FIGURES
L'invention sera mieux comprise et d'autres détails, caractéristiques et avantages de l'invention apparaîtront plus clairement à la lecture de la description suivante faite à titre d'exemple non limitatif et en référence aux dessins annexés dans lesquels :  The invention will be better understood and other details, characteristics and advantages of the invention will emerge more clearly on reading the following description given by way of nonlimiting example and with reference to the appended drawings in which:
- la figure 1 est une demi-vue schématique en coupe axiale d'une soufflante de turbomachine, la figure 1 montrant la périphérie externe de la soufflante à une plus petite échelle que sa périphérie interne ;  - Figure 1 is a schematic half-view in axial section of a turbomachine fan, Figure 1 showing the outer periphery of the fan to a smaller scale than its inner periphery;
- la figure 2 est une vue très schématique en perspective d'une aube selon l'invention; - Figure 2 is a very schematic perspective view of a blade according to the invention;
- la figure 3 est une vue très schématique de face d'un rotor de soufflante équipée de quatre aubes selon l'invention ;  - Figure 3 is a very schematic front view of a fan rotor equipped with four blades according to the invention;
- la figure 4 est une vue très schématique d'une extrémité d'une aube selon l'invention ; et  - Figure 4 is a very schematic view of an end of a blade according to the invention; and
- la figure 5 est une vue en coupe selon la ligne V-V de la figure 3. DESCRIPTION DETAILLEE - Figure 5 is a sectional view along the line VV of Figure 3. DETAILED DESCRIPTION
La figure 1 représente partiellement une soufflante 10 d'une turbomachine, telle qu'un turboréacteur d'aéronef.  FIG. 1 partially represents a fan 10 of a turbomachine, such as an aircraft turbojet engine.
De façon classique, une turbomachine comprend d'amont en aval, c'est-à-dire dans le sens d'écoulement des flux de gaz, une soufflante, un ou plusieurs compresseurs, une chambre de combustion, une ou plusieurs turbines, et une tuyère d'éjection des gaz de combustion sortant de la ou des turbines.  In a conventional manner, a turbomachine comprises from upstream to downstream, that is to say in the flow direction of the gas flows, a blower, one or more compressors, a combustion chamber, one or more turbines, and a nozzle for ejecting the combustion gases leaving the turbine or turbines.
La soufflante 10 est donc située à l'extrémité amont de la turbomachine. Elle comprend un rotor 12 comportant un moyeu 14 portant une rangée annulaire d'aubes 16, dites de soufflante, le rotor 12 tournant à l'intérieur d'un carter de rétention 18.  The fan 10 is located at the upstream end of the turbomachine. It comprises a rotor 12 comprising a hub 14 bearing an annular row of blades 16, called fan blades, the rotor 12 rotating inside a retention casing 18.
Le rotor 12 comprend à sa périphérie externe une rangée annulaire d'alvéoles de montage de pieds 20 des aubes 16. Chaque alvéole 22 a en général en section une forme en queue d'aronde et chaque pied d'aube a une forme complémentaire de l'alvéole pour permettre un montage de l'aube par emmanchement de son pied dans l'alvéole.  The rotor 12 comprises at its outer periphery an annular row of foot mounting cells 20 of the blades 16. Each cell 22 generally has a dovetail-shaped section and each blade root has a shape complementary to the blade. alveole to allow a mounting of the blade by fitting its foot into the cell.
De façon connue, une cale peut être insérée entre le pied d'une aube et le fond de l'alvéole 22 de réception de ce pied, afin de l'immobiliser.  In known manner, a wedge can be inserted between the foot of a blade and the bottom of the cell 22 for receiving this foot, in order to immobilize it.
Chaque aube 16 comprend une pale 24 qui s'étend depuis le pied radialement vers l'extérieur par rapport à l'axe A de rotation du rotor 12. La pale comprend un sommet opposé au pied, c'est-à-dire à son extrémité radialement externe.  Each blade 16 comprises a blade 24 which extends from the root radially outwardly relative to the axis A of rotation of the rotor 12. The blade comprises an apex opposite the foot, that is to say its radially outer end.
Le carter de rétention 18 a ici une forme générale cylindrique et s'étend autour des aubes de soufflante 16. Il comprend une surface cylindrique interne sur laquelle est prévue une couche annulaire 26 de matière abradable. Cette couche 26 entoure les aubes 16 et s'étend sur toute la dimension longitudinale des aubes suivant l'axe A.  The retention housing 18 here has a generally cylindrical shape and extends around the fan blades 16. It comprises an inner cylindrical surface on which is provided an annular layer 26 of abradable material. This layer 26 surrounds the blades 16 and extends over the entire longitudinal dimension of the blades along the axis A.
Le rotor de soufflante 12 est situé en aval d'un cône d'entrée 28, qui peut être solidaire du rotor 12, et en amont d'un séparateur annulaire 30 qui a pour fonction de diviser la veine annulaire d'entrée d'air qui traverse les aubes de soufflante, en deux veines annulaires coaxiales, respectivement interne pour la génération d'un flux primaire ou flux chaud, et externe pour la génération d'un flux secondaire ou flux froid. The fan rotor 12 is located downstream of an inlet cone 28, which can be secured to the rotor 12, and upstream of an annular separator 30 which its function is to divide the annular inlet air stream which passes through the fan blades, into two coaxial annular veins, respectively internal for the generation of a primary flow or hot flow, and external for the generation of a flow secondary or cold flow.
L'invention concerne une aube pour le rechargement d'une couche d'abradable sur la surface interne d'un carter tel que le carter 18 de la figure 1 .  The invention relates to a blade for reloading an abradable layer on the inner surface of a housing such as the casing 18 of FIG.
Le pied 20 de l'aube 12, mieux visible à la figure 2, comprend un logement 32 de stockage ou de passage d'une résine polymérisable de rechargement. Autrement dit, ce logement 32 peut soit être relié à une source de résine et assurer la distribution de la résine au reste de l'aube, soit former lui-même la source de résine. Dans ce dernier cas, le logement 32 peut contenir directement la résine ou être conçu pour recevoir une cartouche de résine.  The foot 20 of the blade 12, better visible in Figure 2, comprises a housing 32 for storing or passing a polymerizable resurfacing resin. In other words, this housing 32 can be connected to a source of resin and ensure the distribution of the resin to the rest of the blade, or form itself the resin source. In the latter case, the housing 32 may directly contain the resin or be designed to receive a resin cartridge.
La résine peut être du type bi-composant et comprendre ainsi deux composants, tels qu'un composant résine et un composant durcisseur, destinés à être mélangés et à durcir par polymérisation, par exemple à température ambiante. La résine à base époxy commercialisée par la société 3M sous la dénomination Scotch-Weld™ convient par exemple pour cette application.  The resin may be of the two-component type and thus comprise two components, such as a resin component and a hardener component, to be mixed and cured by polymerization, for example at room temperature. The epoxy resin marketed by 3M under the name Scotch-Weld ™ is suitable for example for this application.
La pale 24 de l'aube 16 comprend plusieurs canaux 34 d'acheminement de la résine jusqu'au sommet de l'aube. Ces canaux sont longitudinaux, c'est-à-dire qu'ils s'étendent le long de l'axe longitudinal de la pale, qui est un axe sensiblement radial par rapport à l'axe A. Les canaux 34 sont de préférence sensiblement rectilignes pour faciliter l'acheminent précité. Ils ont par exemple un diamètre de quelques millimètres, ce diamètre étant naturellement fonction de la viscosité de la résine à sa température d'utilisation.  The blade 24 of the blade 16 comprises several channels 34 for conveying the resin to the top of the blade. These channels are longitudinal, that is to say they extend along the longitudinal axis of the blade, which is a substantially radial axis with respect to the axis A. The channels 34 are preferably substantially rectilinids to facilitate the aforementioned routing. They have for example a diameter of a few millimeters, this diameter being naturally a function of the viscosity of the resin at its temperature of use.
Les conduits 34 s'étendent entre le logement 32 et le sommet de la pale 24. Les extrémités radialement internes des conduits 34 débouchent dans le logement 32 et leurs extrémités radialement externes débouchent sur une surface d'extrémité 36 radialement externe de la pale, qui est destinée à être en regard de la couche d'abradable 26. The ducts 34 extend between the housing 32 and the top of the blade 24. The radially inner ends of the ducts 34 open into the housing 32 and their radially outer ends open on a radially outer end surface 36 of the blade, which is intended to face the abradable layer 26.
Les figures 2 et 4 montrent plus en détail la surface d'extrémité 36 ainsi que les débouchés 39 des conduits 34 sur cette surface 36. Le nombre de conduits internes dans la pale peut être relativement élevé. Ils peuvent être regroupés par groupe, comme représenté à la figure 4. Les conduits 34 peuvent être répartis sur la surface et être alignés le long d'une corde de l'aube.  Figures 2 and 4 show in more detail the end surface 36 and the outlets 39 of the ducts 34 on this surface 36. The number of internal ducts in the blade can be relatively high. They can be grouped together in groups, as shown in FIG. 4. The ducts 34 can be distributed on the surface and be aligned along a rope of the blade.
Le sommet de l'aube 16 est avantageusement équipé d'un organe 38 d'étalement et de raclage, qui est appliqué et fixé sur la surface d'extrémité 36.  The top of the blade 16 is advantageously equipped with a spreading and scraping member 38, which is applied and fixed on the end surface 36.
L'organe 38 a une forme allongée et est destiné à s'étendre le long de la corde de l'aube. Il est avantageusement fixé de manière amovible sur l'aube, par exemple par emboîtement ou encliquetage élastique. Dans l'exemple représenté, l'organe 38 comprend des pions 40 ou clips destinés à coopérer avec des orifices 42 prévus au sommet de l'aube et débouchant sur la surface 36, ces pions étant visibles à la figure 5. Cette figure montre un exemple de réalisation de l'organe 38 qui comprend une cavité 44 destinée à être en communication fluidique avec les débouchés 39 des conduits 34 pour son alimentation en résine. Pour cela, l'organe 38 peut comprendre une paroi de fond radialement interne percée d'orifices destinés à être alignés avec les débouchés 39 des conduits, lorsque l'organe est monté sur la pale. L'organe 38 comprend en outre au moins un canal 46 de distribution de résine s'étendant depuis la cavité 44 vers une extrémité radialement externe de l'organe 38. Cette extrémité est de préférence configurée pour étaler la résine et racler le surplus de résine. Elle est conformée pour reproduire le profil théorique de la veine d'entrée d'air de la soufflante.  The member 38 has an elongate shape and is intended to extend along the rope of the blade. It is advantageously fixed removably on the blade, for example by interlocking or snap elastic. In the example shown, the member 38 comprises pins 40 or clips intended to cooperate with orifices 42 provided at the top of the blade and opening on the surface 36, these pins being visible in Figure 5. This figure shows a embodiment of the member 38 which comprises a cavity 44 intended to be in fluid communication with the outlets 39 of the ducts 34 for its supply of resin. For this, the member 38 may comprise a radially inner bottom wall pierced with orifices intended to be aligned with the outlets 39 of the ducts, when the member is mounted on the blade. The member 38 further comprises at least one resin distribution channel 46 extending from the cavity 44 to a radially outer end of the member 38. This end is preferably configured to spread the resin and scrape the excess resin . It is shaped to reproduce the theoretical profile of the air inlet duct of the blower.
L'invention concerne également un procédé de rechargement d'une couche d'abradable 26 comportant les étapes consistant à : - démonter au moins une aube du rotor et la remplacer par une aube 16 telle que décrite ci-dessus, The invention also relates to a method of reloading an abradable layer 26 comprising the steps of: - Remove at least one blade of the rotor and replace it with a blade 16 as described above,
- mettre en rotation le rotor de façon à ce que de la résine contenue dans le logement 32 circule par effet centrifuge dans les conduits 34 et soient déposées ou projetées sur la couche d'abradable 26.  - Rotate the rotor so that the resin contained in the housing 32 circulates by centrifugal effect in the ducts 34 and are deposited or projected on the abradable layer 26.
Dans le cas où l'aube est équipée de l'organe 38, le procédé comprend une étape consistant à étaler et racler la résine déposée, au moyen de cet organe.  In the case where the blade is equipped with the member 38, the method comprises a step of spreading and scraping the deposited resin, by means of this member.
Avantageusement, et comme représenté à la figure 3, plusieurs, et par exemple quatre, aubes du rotor sont remplacées par des aubes 16. Ces aubes 16 sont de préférence régulièrement réparties autour de l'axe de rotation du rotor, les autres aubes, d'origine, du rotor n'étant pas représentées dans la figure pour plus de clarté.  Advantageously, and as shown in FIG. 3, several, and for example four, vanes of the rotor are replaced by blades 16. These blades 16 are preferably regularly distributed around the axis of rotation of the rotor, the other vanes, d The origin of the rotor is not shown in the figure for the sake of clarity.
Dans un exemple particulier de réalisation de l'invention, une pompe est utilisée pour forcer la résine à s'écouler depuis le logement de chaque pale le long de ses conduits internes. En pratique, la pompe peut être réglée à une pression de 150 bars et la soufflante peut être entraînée en rotation par exemple manuellement ou par auto-rotation, lors de la mise en route de la pompe.  In a particular embodiment of the invention, a pump is used to force the resin to flow from the housing of each blade along its internal ducts. In practice, the pump can be set to a pressure of 150 bar and the blower can be rotated, for example manually or by self-rotation, when the pump is turned on.
Dans un autre exemple de réalis ation de l'invention, la résine est forcée de s'écouler dans les conduits par la seule force centrifuge appliquée du fait de la rotation de la soufflante, par exemple à une vitesse de 500 tours/minute environ.  In another embodiment of the invention, the resin is forced to flow into the conduits by the sole centrifugal force applied due to the rotation of the blower, for example at a speed of about 500 rpm.

Claims

REVENDICATIONS
1 . Aube (16), en particulier de soufflante, pour le rechargement d'une couche d'abradable (26) sur une surface interne d'un carter (18) de turbomachine destiné à entourer l'aube, l'aube comportant un pied (20) et une pale (24) présentant un sommet opposé audit pied, le pied comportant un logement (32) de stockage ou de passage d'une résine polymérisable de rechargement, et la pale comportant des conduits longitudinaux (34) dont des premières extrémités sont reliées audit logement et dont des extrémités opposées débouchent audit sommet.1. A blade (16), in particular a fan, for reloading an abradable layer (26) on an inner surface of a turbomachine casing (18) intended to surround the blade, the blade comprising a foot ( 20) and a blade (24) having an apex opposite to said foot, the foot comprising a housing (32) for storing or passing a polymerizable resurfacing resin, and the blade comprising longitudinal ducts (34) whose first ends are connected to said housing and opposite ends of which lead to said vertex.
2. Aube (16) selon la revendication 1 , dans laquelle elle comprend une série de canaux longitudinaux (34) sensiblement alignés le long d'une corde de l'aube. 2. blade (16) according to claim 1, wherein it comprises a series of longitudinal channels (34) substantially aligned along a rope of the blade.
3. Aube (16) selon la revendication 1 ou 2, dans laquelle elle comprend en outre un organe (38) de raclage fixé sur ledit sommet.  3. blade (16) according to claim 1 or 2, wherein it further comprises a member (38) scraping fixed on said top.
4. Aube (16) selon la revendication précédente, dans laquelle ledit organe (38) est fixé de manière amovible sur ladite extrémité, par exemple par emboîtement.  4. blade (16) according to the preceding claim, wherein said member (38) is removably attached to said end, for example by interlocking.
5. Aube (16) selon la revendication 3 ou 4, dans laquelle ledit organe (38) a une forme allongée et s'étend le long d'une corde de l'aube.  The blade (16) of claim 3 or 4, wherein said member (38) is elongate in shape and extends along a rope of the blade.
6. Aube (16) selon l'une des revendications 3 à 5, dans laquelle ledit organe (38) comprend une cavité (44) en communication fluidique avec des débouchés desdits conduits pour son alimentation en résine, et au moins un canal (46) de distribution de résine s'étendant depuis ladite cavité vers une extrémité de l'organe opposée audit pied.  6. blade (16) according to one of claims 3 to 5, wherein said member (38) comprises a cavity (44) in fluid communication with outlets of said conduits for its supply of resin, and at least one channel (46). ) of resin distribution extending from said cavity to an end of the member opposite said foot.
7. Procédé de rechargement d'une couche d'abradable sur une surface interne d'un carter, en particulier de soufflante, d'une turbomachine, comportant les étapes suivantes :  7. A method of reloading an abradable layer on an inner surface of a casing, in particular a fan, of a turbomachine, comprising the following steps:
- démonter au moins une aube d'un rotor de ladite turbomachine et la remplacer par une aube (16) selon l'une des revendications précédentes, - mettre en rotation ledit rotor de façon à ce que de la résine contenue dans ledit logement circule par effet centrifuge dans lesdits conduits et soient déposées ou projetées sur ladite surface. disassembling at least one blade of a rotor of said turbomachine and replacing it with a blade (16) according to one of the preceding claims, - Rotating said rotor so that resin contained in said housing circulates by centrifugal effect in said conduits and are deposited or projected on said surface.
8. Procédé selon la revendication 7, l'aube (16) étant telle que définie à l'une des revendications 3 à 5, dans lequel il comprend une étape consistant à étaler et racler la résine déposée, au moyen dudit organe. 8. The method of claim 7, the blade (16) being as defined in one of claims 3 to 5, wherein it comprises a step of spreading and scraping the deposited resin by means of said member.
9. Procédé selon la revendication 7 ou 8, dans lequel plusieurs, par exemple quatre, aubes du rotor sont remplacées par des aubes (16) selon l'une des revendications 1 à 6, qui sont régulièrement réparties autour de l'axe de rotation du rotor. 9. The method of claim 7 or 8, wherein several, for example four, vanes of the rotor are replaced by vanes (16) according to one of claims 1 to 6, which are regularly distributed around the axis of rotation. of the rotor.
EP17721425.1A 2016-04-12 2017-04-10 Blade and method for resurfacing an abradable coating Active EP3443202B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1653220A FR3049978B1 (en) 2016-04-12 2016-04-12 DAWN AND METHOD OF RECHARGING A LAYER OF ABRADABLE
PCT/FR2017/050862 WO2017178747A1 (en) 2016-04-12 2017-04-10 Blade and method for resurfacing an abradable coating

Publications (2)

Publication Number Publication Date
EP3443202A1 true EP3443202A1 (en) 2019-02-20
EP3443202B1 EP3443202B1 (en) 2020-04-01

Family

ID=56101699

Family Applications (1)

Application Number Title Priority Date Filing Date
EP17721425.1A Active EP3443202B1 (en) 2016-04-12 2017-04-10 Blade and method for resurfacing an abradable coating

Country Status (5)

Country Link
US (1) US10982560B2 (en)
EP (1) EP3443202B1 (en)
CN (1) CN109072707B (en)
FR (1) FR3049978B1 (en)
WO (1) WO2017178747A1 (en)

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3346175A (en) * 1966-04-01 1967-10-10 Gen Motors Corp Plastic coating for compressors
GB0100695D0 (en) * 2001-01-11 2001-02-21 Rolls Royce Plc a turbomachine blade
US7252478B2 (en) * 2004-07-21 2007-08-07 Delta T Corporation Fan blade modifications
CN101027486A (en) * 2004-09-28 2007-08-29 大金工业株式会社 Sliding member and fluid machine
CN2742187Y (en) * 2004-10-12 2005-11-23 大庆石油管理局 Anti-wear multistage centrafugal pump
US7410342B2 (en) * 2005-05-05 2008-08-12 Florida Turbine Technologies, Inc. Airfoil support
US9133726B2 (en) * 2007-09-17 2015-09-15 United Technologies Corporation Seal for gas turbine engine component
GB0911330D0 (en) * 2009-07-01 2009-08-12 Rolls Royce Plc Actuatable seal for aerofoil blade tip
CN101825111A (en) * 2010-02-09 2010-09-08 于风福 Wear resistant fan
US20150192029A1 (en) * 2012-09-20 2015-07-09 General Electric Company Turbomachine blade tip insert
FR3007063B1 (en) * 2013-06-13 2015-07-03 Composite Ind ABRADABLE MATERIAL PART FOR MANUFACTURING ABRADABLE ANNULAR JOINT SECTOR FOR TURBOMACHINE AND METHOD OF MANUFACTURING SUCH PART
US10408224B2 (en) * 2014-01-23 2019-09-10 United Technologies Corporation Fan blades with abrasive tips

Also Published As

Publication number Publication date
CN109072707A (en) 2018-12-21
FR3049978B1 (en) 2018-04-27
US10982560B2 (en) 2021-04-20
FR3049978A1 (en) 2017-10-13
EP3443202B1 (en) 2020-04-01
US20190120074A1 (en) 2019-04-25
WO2017178747A1 (en) 2017-10-19
CN109072707B (en) 2021-05-25

Similar Documents

Publication Publication Date Title
FR2744761A1 (en) LABYRINTH DISK WITH INCORPORATED STIFFENER FOR TURBOMACHINE ROTOR
EP3495692A1 (en) Turbine engine speed reduction ring gear with planetary gear
CA2740660A1 (en) Oil separator rotor for turbomachine
WO2015110751A1 (en) Rotor disk having a centripetal air collection device, compressor comprising said disc and turbomachine with such a compressor
FR3029960A1 (en) AUBES WHEEL WITH RADIAL SEAL FOR A TURBOMACHINE TURBINE
FR2978793A1 (en) Turbine rotor for e.g. turbojet engine of aircraft, has annular ring deformed or moved in order to compensate deformation/displacement of plate so as to ensure sealing of annular space irrespective of position of plate
FR3099520A1 (en) Turbomachine wheel
FR2993599A1 (en) TURBOMACHINE LABYRINTH DISK
FR2955152A1 (en) Turbomachine i.e. open rotor type jet engine, for aircraft, has evacuation unit including envelope connected to structural annular walls and extended around enclosure to determine outer and inner annular cavities in space
EP3430238B1 (en) Turbine rotor comprising a ventilation spacer
EP3443202B1 (en) Blade and method for resurfacing an abradable coating
FR3016406A1 (en) TURBOMACHINE ASSEMBLY COMPRISING TWO BODIES AND MEANS FOR GUIDING A FLOWABLE FLUID FROM ONE BODY TO THE OTHER
EP3880939A1 (en) Sealing between a rotor disc and a stator of a turbomachine
FR3070183B1 (en) TURBINE FOR TURBOMACHINE
FR2967453A1 (en) AUBES RETENTION DISC
EP3262283B1 (en) Hydrodynamic bearing
FR3075867A1 (en) DEVICE FOR DEHUILING A TURBOMACHINE LUBRICATION ENCLOSURE
FR2994453A1 (en) Radial inner assembly for bladed ring sector of compressor stator or turbine of e.g. turbojet engine of aircraft, has anti-rotation edge whose length is greater than maximum spacing distance between projections of casing head
FR2999249A1 (en) High pressure axial compressor for e.g. turbojet for aircraft, has air draining unit for injecting cooling air between rotating element and static element such that cooling air immerses side of annular sealing ribs
FR3108659A1 (en) Turbine rotor comprising a device for regulating the flow of cooling fluid and turbomachine comprising such a rotor
FR3069571B1 (en) FLUID FILM COMPRESSION SYSTEM AND ROTATING MACHINE COMPRISING SUCH A SYSTEM
FR3108938A1 (en) Sealing ring for a turbine engine turbine rotor
FR3084697A1 (en) Improved balancing system for aircraft turbomachines
FR3028883B1 (en) TURBOMACHINE ROTOR SHAFT HAVING AN IMPROVED THERMAL EXCHANGE SURFACE
CA2801083C (en) Turbine engine shaft

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: 20181108

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

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: 20191023

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: 1251584

Country of ref document: AT

Kind code of ref document: T

Effective date: 20200415

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602017014024

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: SE

Ref legal event code: TRGR

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: 20200701

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20200401

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

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

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: 20200401

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: 20200817

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: 20200401

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: 20200401

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: 20200701

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: 20200702

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: 20200401

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: 20200801

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1251584

Country of ref document: AT

Kind code of ref document: T

Effective date: 20200401

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: 20200401

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: 20200401

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: 20200401

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: 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: 20200401

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602017014024

Country of ref document: DE

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

Ref country code: CH

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

Effective date: 20200430

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: 20200401

Ref country code: LI

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

Effective date: 20200430

Ref country code: LU

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

Effective date: 20200410

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: 20200401

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: 20200401

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: 20200401

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: 20200401

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: 20200401

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: 20200401

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20200430

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

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

Ref country code: BE

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

Effective date: 20200430

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: 20200401

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: 20200401

26N No opposition filed

Effective date: 20210112

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: 20200410

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: 20200401

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

Ref country code: TR

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: 20200401

Ref country code: MT

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: 20200401

Ref country code: CY

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: 20200401

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

Ref country code: MK

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: 20200401

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

Ref country code: GB

Payment date: 20240320

Year of fee payment: 8

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

Ref country code: SE

Payment date: 20240320

Year of fee payment: 8

Ref country code: IT

Payment date: 20240320

Year of fee payment: 8

Ref country code: FR

Payment date: 20240320

Year of fee payment: 8

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

Ref country code: DE

Payment date: 20240320

Year of fee payment: 8