EP3023595B1 - Stator-innenring eines kompressors eines axialen turbotriebwerks - Google Patents

Stator-innenring eines kompressors eines axialen turbotriebwerks Download PDF

Info

Publication number
EP3023595B1
EP3023595B1 EP15190957.9A EP15190957A EP3023595B1 EP 3023595 B1 EP3023595 B1 EP 3023595B1 EP 15190957 A EP15190957 A EP 15190957A EP 3023595 B1 EP3023595 B1 EP 3023595B1
Authority
EP
European Patent Office
Prior art keywords
shroud
segment
radial flange
radial
internal
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
EP15190957.9A
Other languages
English (en)
French (fr)
Other versions
EP3023595A1 (de
Inventor
Jean-François Cortequisse
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
Priority to EP18159641.2A priority Critical patent/EP3351736B1/de
Publication of EP3023595A1 publication Critical patent/EP3023595A1/de
Application granted granted Critical
Publication of EP3023595B1 publication Critical patent/EP3023595B1/de
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
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • 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
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/40—Organic materials
    • 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
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced

Definitions

  • the field of the present invention is that of axial turbomachines. More particularly, the invention addresses the inner ferrules connected to a row of stator vanes.
  • An inner ferrule is known for delimiting the primary flow of an axial turbomachine, it forms an annular wall which delimits the interior of the fluid vein. Thanks to its external surface, it helps to guide the flow during its expansion in a turbine, or its compression in a compressor.
  • an inner ring may be mounted on inner ends of blades arranged in an annular row, themselves linked to an outer casing.
  • the ferrule has recesses for the introduction of ferrule attachment ends.
  • the inner ferrule is also intended to provide a seal with the rotor around which it is placed.
  • it has a layer of abradable material cooperating by abrasion with wipers formed outside the rotor. In operation, the wipers come close to the abradable, possibly creating circular cuts, so that a dynamic seal is ensured.
  • the document EP 2 075 414 A1 discloses an axial turbomachine compressor comprising rectifiers provided with segmented internal ferrules.
  • Each inner ferrule comprises a tubular wall in which rows of openings are provided. These allow the introduction of the blade roots used for fixing between the ferrule and the blades.
  • Each opening has a lip which radially extends the contour, ribs join the lips of the adjacent openings, the assembly for stiffening the ferrule.
  • the flexural stiffness of the ferrule; especially of its segments remains limited. In case of solicitation, most of the effort is taken up by the branches of the U-shape of the ferrule. In case of vibrations, the openings can open more around the joints surrounding the blades, which degrades the seal.
  • Another example is disclosed in the document EP-1227218 .
  • the document EP1419849A1 discloses a method of repairing a turbine segment.
  • the segment comprises a pair of blades whose ends are connected to an inner shell.
  • the latter has two openings connected to the blades, the opposite edges of the openings being joined by a flange.
  • the object of the invention is to solve at least one of the problems posed by the prior art. More specifically, the object of the invention is to stiffen an inner ferrule or an inner ferrule segment bonded to stator vanes.
  • the invention also aims to improve the rigidity of an assembly comprising a ferrule and blades connected in openings formed in the ferrule.
  • the invention also aims to improve the sealing of a ferrule or a ferrule segment.
  • the subject of the invention is a ferrule or an axial turbomachine shell segment, in particular a compressor, the ferrule or the ferrule segment comprises a circular or semi-circular wall whose profile extends mainly axially, and a circular radial flange. or semi-circular extend radially from the wall towards the inside, the flange having a circular or semicircular surface whose profile extends mainly radially, said surface having asperities.
  • the subject of the invention is also an internal ferrule or inner ring segment of an axial turbomachine, in particular a compressor, the ferrule or the ferrule segment comprising: a circular or semi-circular wall whose profile extends mainly axially; and a row of openings formed in the axial wall, each opening having opposing edges to be laterally arranged on the side and another of a stator blade positioned in said opening for attachment; remarkable in that the wall comprises at least one radial flange which passes through the apertures in the circumferential direction of the shell or ferrule segment, so as to form a mechanical link within each opening to bond the opposite edges.
  • each opening extends mainly axially and each radial flange extends radially inwards from the wall, and travels all around the ferrule or the entire width of the ferrule segment according to the direction of alignment of the row of openings.
  • the ferrule or the ferrule segment comprises at least one band of abradable material, each radial flange extending more radially inwards than each abradable layer.
  • the ferrule or the ferrule segment comprises a plurality of radial flanges which each pass through the openings, possibly each abradable strip is disposed axially between two radial flanges.
  • the axial wall and each radial flange are integral, optionally the axial wall and each radial flange are made of polymer, such as an organic matrix composite material.
  • the radial flange is a through radial flange which passes through the openings, the ferrule or ferrule segment comprising an upstream radial flange disposed upstream of the openings, and a downstream radial flange disposed downstream of the openings.
  • the upstream flange and the downstream flange axially delimit the axial wall.
  • At least one or each radial flange comprises at least one surface with asperities, said surface being generally perpendicular to the axis of revolution of the ferrule or ferrule segment.
  • the asperities form a repeated pattern on substantially an entire face of the corresponding radial flange.
  • the asperities have tooth shapes, possibly triangular, each tooth extends over the majority or over the entire radial height of the associated radial flange.
  • the radial flange comprises portions which each bar an opening, possibly in the direction of alignment of the row of openings.
  • the radial height of at least one or each radial flange is greater than the radial height of each annular rib.
  • At least one or each opening extends over the majority of the axial length of the axial wall.
  • the wall comprises a radial flange disposed at the axial center of the openings, or the wall comprises a plurality of radial flanges distributed axially on the openings.
  • the invention also relates to a method of assembling a stator blade to an inner ferrule or to an inner ring segment of an axial turbomachine, the method comprising the following steps: (a) supplying one or more blades statoric, each stator blade having an inner radial end; (b) providing an inner ferrule or inner ferrule segment with a row of openings; (c) positioning each stator blade end in an opening; (d) attaching each blade tip to the associated opening; remarkable in that the ferrule or the ferrule segment comprises at least one circular or semicircular radial flange passing through the openings, and in that during step (c) positioning each end of blade is in abutment against the flange radial, optionally the inner ferrule or the inner ring segment is in accordance with the invention.
  • each blade end passes through the associated opening.
  • each blade end comes into axial abutment and / or radial abutment against the radial flange, optionally each blade end comprises fastening means .
  • the step (b) supply comprises the realization by additive manufacture of the ferrule or the ferrule segment.
  • the method further comprises a step (e) implementation or realization of seals in the openings around the stator vanes.
  • the invention also relates to a turbomachine comprising a rotor and an inner ring around the rotor or an inner ferrule segment conforming to the rotor, remarkable in that the ferrule or the ferrule segment is in accordance with the invention; and / or the turbomachine comprises a stator blade and an inner ferrule or an inner ferrule segment assembled according to an assembly method, remarkable in that the method is in accordance with the invention.
  • the rotor comprises annular ribs sealingly cooperating with the ferrule or the ferrule segment, the annular ribs of the rotor are each axially spaced apart from each radial flange of the ferrule or ferrule segment.
  • At least one radial flange covers radially and circularly one of the annular ribs.
  • At least one or each radial flange comprises asperities which are formed over the majority of the radial height of the revolution profile of one of the annular ribs of the rotor disposed opposite the associated radial flange.
  • the radial clearance between each radial flange and the rotor is greater than the radial clearance between the annular ribs and the ferrule or the ferrule segment.
  • the rotor comprises N annular ribs, the ferrule or the ferrule segment comprising at least N + 1 radial flanges, preferably at least 2 * N radial flanges forming N pairs of radial flanges adjoining the upstream and downstream surfaces of each annular rib.
  • each opening comprises a seal intended to surround a stator vane disposed in said opening, the seal being in contact with the radial flange which passes through said opening, preferably the seal is made in an elastomeric material such as silicone.
  • At least one or each stator blade comprises a radial step form in axial abutment and / or in radial abutment against one or one of the radial flanges.
  • At least one or each stator blade comprises a notch in which is engaged one or one of the radial flanges of the ferrule, and / or one or one of the radial flanges comprises notches in which are engaged the stator blades.
  • At least one or each stator blade comprises fixing means such as radial retention means.
  • the annular ribs of the rotor and the radial flanges of the inner ring form an alternation.
  • each radial flange has a profile of revolution which extends essentially radially, and the annular ribs each comprise a profile of revolution which extends essentially radially, each flange profile extends over the most of the radial height of each neighboring annular rib profile.
  • the radial flange forms a bridge that spans each opening.
  • the flange thus makes it possible to bind the opposite edges of the openings so as to connect the edges.
  • This mechanical seal makes it possible to bind the opposite edges through each opening, so as to prevent them from moving apart or approaching despite the void of material openings.
  • the invention makes it possible to improve the seal between a ferrule or a ferrule segment with openings in which stator vanes are fixed.
  • the invention thus provides a ferrule or a ferrule segment that is light, rigid and economical to produce.
  • inner or inner and outer or outer 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 lateral direction is according to the circumference.
  • the figure 1 represents in simplified manner an axial turbomachine. It is in this case a double-flow turbojet engine.
  • the turbojet engine 2 comprises a first compression level, called a low-pressure compressor 5, a second compression level, called a high-pressure compressor 6, a combustion chamber 8 and one or more levels of turbines 10.
  • the mechanical power the turbine 10 transmitted via the central shaft to the rotor 12 sets in motion the two compressors 5 and 6.
  • the latter comprise several rows of rotor blades associated with rows of stator vanes. Rotation of the rotor about its axis of rotation 14 thus makes it possible to generate an air flow rate and to compress it gradually to the inlet of the combustion chamber 8. Reducing means can increase the rotational speed transmitted to the compressors.
  • An inlet fan commonly referred to as fan or blower 16 is coupled to the rotor 12 and generates an air flow which splits into a primary flow 18 passing through the various aforementioned levels of the turbomachine, and a secondary flow 20 passing through an annular duct (partially shown) along the machine to then join the primary flow at the turbine outlet.
  • the secondary flow can be accelerated to generate a thrust reaction.
  • the primary 18 and secondary 20 streams are annular flows, they are channeled by the casing of the turbomachine.
  • the casing has cylindrical walls or ferrules which can be internal and external.
  • the figure 2 is a sectional view of a compressor of an axial turbomachine such as that of the figure 1 .
  • the compressor may be a low-pressure compressor 5.
  • the rotor 12 comprises a drum with an outer annular wall which supports several rows of rotor blades 24, in this case three rows.
  • the low pressure compressor 5 comprises several rectifiers, in this case four, each containing a row of stator vanes 26.
  • the rectifiers are associated with the fan or with a row of rotor vanes for straightening the flow of air, so as to convert the speed of the flow into static pressure.
  • the stator vanes 26 extend substantially radially from an outer casing 22, and can be attached thereto by means of an axis.
  • the housing 22 then forms an external support for the different rows.
  • the compressor 5 also comprises internal ferrules 28 which are fixed to the radially inner ends of the stator vanes 26.
  • the inner ferrules 28 make it possible to guide and delimit the primary flux 18. They also seal with the rotor 12 in order to avoid recirculation. air decreasing the compression ratio of the compressor 5, and limiting the efficiency of the turbomachine.
  • Each ferrule 28 may form a ring of one turn, or be segmented angularly.
  • the figure 3 represents a portion of the compressor such as that of the figure 2 .
  • Y is visible a rotor portion 12, an inner radial end of stator vane 26, and an inner ferrule 28 attached thereto.
  • the inner ferrule 28 could be segmented.
  • the shell 28 has a profile of revolution with a portion extending mainly axially and which generates an axial wall 32.
  • the axial wall 32 may be generally tubular, and be substantially inclined relative to the axis of rotation 14 of the turbomachine; the latter may coincide with the general axis of symmetry 14 of the ferrule 28.
  • the ferrule 28 has a series of openings 34 arranged in an annular row. These openings 34 are traversed by the ends 30 of the blades 26 to suspend the ferrule 28. Each opening 34 has opposite edges 36 in the direction of the row of openings 34, these edges 36 being placed opposite the faces of the dawn 26 associated. One is facing the intrados surface of the dawn, the other facing the extrados face. Edges 36 may be generally conjugates; one is concave, the other convex.
  • the ferrule 28 further comprises at least one radial flange 38 which extends radially inwardly from the axial wall 32.
  • the ferrule 28 may comprise a plurality of radial flanges 38 which each cut the openings 34. These radial flanges may be parallel, and distributed axially through the openings.
  • the ferrule 28 may comprise at least three radial flanges including an upstream radial flange 40, a downstream radial flange 42, and a through radial flange 38 which passes through the openings 34, or central radial flange 38.
  • the radial flange 38 is axially disposed between the upstream 40 and downstream 42 flanges.
  • the ferrule may have an "E" or comb profile.
  • the rotor 12 in particular its wall has annular ribs 44, also called “wipers". They extend radially and cooperate with the ferrule 28 in a sealed manner. They can cooperate by abrasion with layers of abradable material 46 where they dig grooves in case of contact.
  • abradable material is meant a friable material in case of contact.
  • the abradable layers 46 may be applied to the blade tips 30, and / or to the axial wall 32.
  • the abradable layers 46 and the radial flanges (38; 40; 42) form an alternation.
  • the radial flanges (38; 40; 42) can be associated in pairs to frame each annular rib 44 of rotor 12, possibly individually.
  • Each radial flange (38; 40; 42) comprises a profile of revolution that extends substantially radially, each flange profile extends over most of the radial height of each profile of the neighboring radial flange.
  • Each rib profile (38; 40; 42) extends over most of the radial height of the profiles of neighboring annular ribs 44.
  • the faces of radial flanges (38; 40; 42) facing annular ribs 44 are covered with asperities 48 which amplify the turbulences 50 or vortices 50 opposing the recirculations 52.
  • the figure 4 represents a section of ferrule 28 and stator vanes 26 along the axis 4-4 plotted on the figure 3 .
  • the cutting plane passes through the radial flange 38 which passes through the openings 34.
  • the ferrule could be formed by ferrule segments which would be placed end to end so as to form a circle.
  • the blades 26 extend radially from the shell 28 and pass through the openings 34. Their radial ends 30 are in radial abutment against the radial flange 38. Each blade end 30 has a radial abutment surface which cooperates with an abutment surface corresponding slot. Seals 54 extend radially into openings 34 and pass through them, they come into contact with radial flange 38. Notch bottoms, or abutment surfaces of notches, are spaced apart from joints 54 and / or the axial wall.
  • the radial flange 38 not only joins all the openings 34, but it also connects all the opposite edges 36 to each other through the openings 34. It forms a reinforcement bar which, in each opening 34, blocks the opposite edges 36
  • the radial flange 38 has an arcuate shape and a crenellated profile. It has a step series forming notches 56 in which are placed the ends of the blades 26. These notches 56 may be a place for fixing the blades 26, for example by gluing or with the aid of fixing plates (not shown). For this purpose, the ends 30 may comprise fixing holes (not shown). Within each opening 34 the radial flange 38 binds the opposite edges 36. This configuration stiffens the ferrule 28, and prevents its bending at the openings, 38 so that the risk of separation at the joints 54 decreases.
  • the figure 5 represents a section along the axis 5-5 drawn on the figure 3 .
  • the section shows a compressor slice between the rotor 12 and an inner shell, seen from the outside. The location of the blade tips 30 is shown.
  • the asperities 48 comprise grooves and ridges forming an alternation with the grooves, which extend radially and are optionally perpendicular to the axis of rotation of the turbomachine.
  • the assembly can form a ridged annular surface.
  • Asperities 48 may have triangular tooth shapes, and have a general sawtooth profile.
  • Asperities 48 are formed in front of wipers 44, preferably on each side.
  • the pattern may be formed circumferentially along radial flanges (38; 40; 42); or all the way round. Thanks to the asperities 48, the radial flanges (38; 40; 42) cause vortices 50 in the air driven by the rotor 12
  • the figure 6 is a diagram of a method of assembling a stator vane on a ferrule, the ferrule being segmentable.
  • Step (b) supply 102 may include the additive manufacture of the ferrule or ferrule segment.
  • the ferrule or each segment can be rimmed and made of polymer, for example a composite hammer with fibers, possibly less than 10 mm in length.
  • Step (c) positioning 104 can be performed by fixing the vanes to an outer compressor casing. Then the shell is moved radially so that the inner ends of the blades are found in the openings. At first, the blade tips enter the openings and then pass through them. Finally, these ends abut against a radial flange. The abutment is then axial and / or radial, which makes it possible to improve the relative position between the blade and the ferrule.
  • the seal made or implemented during step (e) implementation or embodiment 108 is better positioned and / or better achieved.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (15)

  1. Innerer Mantel (28) oder Segment eines inneren Mantels einer axialen Turbomaschine (2), insbesondere eines Kompressors (5 ; 6), wobei der Mantel (28) oder das Mantelsegment Folgendes beinhaltet:
    - eine runde oder halbrunde Wandung (32), deren Profil sich hauptsächlich axial erstreckt, und
    - eine Reihe von Öffnungen (34) in der axialen Wandung (32), wobei jede Öffnung (34) gegenüberliegende Ränder (36) aufweist, die dazu bestimmt sind, um seitlich beiderseits einer Leitschaufel (26) angeordnet zu werden, die zum Zwecke ihrer Befestigung in der genannten Öffnung (34) positioniert wird,
    - wobei die Wandung (32) mindestens einen radialen Flansch (38) beinhaltet, der die Öffnungen (34) in der kreisförmigen Richtung des Mantels (28) oder des Mantelsegments passiert, um eine mechanische Verbindung innerhalb jeder Öffnung (34) zu bilden, um deren gegenüberliegende Ränder (36) zu verbinden;
    dadurch gekennzeichnet, dass
    der Mantel (28) oder das Mangelsegment mindestens ein Band aus Verschleißmaterial (46) beinhaltet und sich jeder radiale Flansch (38 ; 40 ; 42) stärker radial nach innen erstreckt, als jede Verschleißschicht (46).
  2. Mantel (28) oder Mantelsegment nach Anspruch 1, dadurch gekennzeichnet, dass sich jede Öffnung (34) hauptsächlich axial erstreckt und sich jeder radiale Flansch (38) radial von der Wandung (32) aus nach innen und über die gesamte Rundung des Mantels (28) oder die gesamte Breite des Mantelsegments in der Fluchtlinie der Reihe von Öffnungen (34) erstreckt.
  3. Mantel (28) oder Mantelsegment nach einem der Ansprüche 1 bis 2, dadurch gekennzeichnet, dass der Mantel oder das Mangelsegment (28) mehrere radiale Flansche (38) beinhaltet, die jede der Öffnungen passieren, wobei ggf. jedes Band aus Verschleißmaterial (46) axial zwischen zwei radialen Flanschen (38 ; 40 ; 42) angeordnet ist.
  4. Mantel (28) oder Mantelsegment nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass der radiale Flansch (38) ein durchgehender radialer Flansch (38) ist, der die Öffnungen (34), den Mantel (28) oder das Mantelsegment passiert, mit einem oberhalb liegenden radialen Flansch (40), der stromaufwärts der Öffnungen (34) angeordnet ist, und einem unterhalb liegenden radialen Flansch (42), der unterhalb der Öffnungen (34) angeordnet ist, wobei der oberhalb liegende Flansch (40) und der stromabwärts liegende Flansch (42) vorzugsweise die axiale Wandung (32) axial begrenzen
  5. Mantel (28) oder Mantelsegment nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass mindestens einer oder jeder der axialen Flansche (38; 40; 42) mindestens eine Oberfläche mit Unebenheiten (48) beinhaltet, wobei sich die genannte Oberfläche im rechten Winkel zur Rotationsachse (14) des Mantels oder Mantelsegments (28) verhält.
  6. Mantel (28) oder Mantelsegment nach Anspruch 5, dadurch gekennzeichnet, dass die Unebenheiten (48) ein wiederkehrendes Muster auf nahezu der gesamten Fläche des entsprechenden radialen Flansches (38 ; 40 ; 42) bilden und/oder die Unebenheiten (48) die Form von Zähnen besitzen, die eventuell dreieckig sind, wobei sich jeder Zahn über den größten Teil oder die gesamte radiale Höhe des dazugehörigen radialen Flansches (38 ; 40 ; 42) erstreckt.
  7. Verfahren für die Montage einer Leitschaufel (26) an einem inneren Mantel (28) oder einem Segment eines inneren Mantels einer axialen Turbomaschine (2), wobei das Verfahren die folgenden Schritte beinhaltet:
    (a) Bereitstellung (100) von einer oder mehreren Leitschaufeln (26), wobei jede Leitschaufel (26) ein inneres radiales Ende (30) besitzt;
    (b) Bereitstellung (102) eines inneren Mantels (28) oder eines Segments eines inneren Mantels mit einer Reihe von Öffnungen (34), wobei der Mantel (28) oder das Mantelsegment mindestens einen runden oder halbrunden radialen Flansch (38) beinhaltet, der die Öffnungen (34) passiert;
    (c) Positionierung (104) jedes Endes (30) einer Leitschaufel in einer Öffnung (34), so dass jedes Leitschaufelende (30) am radialen Flansch (38) anliegt;
    (d) Befestigung (106) jedes Leitschaufelendes (30) in der dazugehörigen Öffnung (34);
    dadurch gekennzeichnet, dass
    der Mantel (28) oder das Mantelsegment mindestens ein Band aus Verschleißmaterial (46) beinhaltet, wobei sich jeder radiale Flansch (38 ; 40 ; 42) stärker radial nach innen erstreckt, als jede Schicht Abriebmaterial (46) und eventuell der innere Mantel (28) oder das innere Mantelsegment einem der Ansprüche 1 bis 6 entspricht.
  8. Verfahren nach Anspruch 7, dadurch gekennzeichnet, dass anlässlich von Schritt (c) Positionierung (104) jedes Leitschaufelende (30) axial und/oder radial am radialen Flansch (38) anliegt und jedes Leitschaufelende (30) eventuell Befestigungsmittel besitzt.
  9. Verfahren nach einem der Ansprüche 7 bis 8, dadurch gekennzeichnet, dass Schritt (b) Bereitstellung, die Ausführung des Mantels (28) oder Mantelsegments mittels additiver Herstellung beinhaltet; und/oder die axiale Wandung (32) und jeder radiale Flansch (38 ; 40 ; 42) aus einem Material bestehen und eventuell die axiale Wandung (32) und jeder radiale Flansch (38 ; 40 ; 42) aus Polymer bestehen, wie z.B. einem Verbundmaterial mit organischer Matrix.
  10. Turbomaschine (2), bestehend aus einem Rotor (12) und einem inneren Mantel (28) um den Rotor (12) herum, oder einem inneren Mantelsegment, das sich an den Rotor (12) anschmiegt, dadurch gekennzeichnet, dass der Mantel (28) oder das Mantelsegment einem der Ansprüche 1 bis 6 entspricht; und/oder die Turbomaschine (2) eine Leitschaufel (26) und einen inneren Mantel (28) oder ein inneres Mantelsegment mit einer Reihe von Öffnungen (34) beinhaltet, wobei der Mantel (28) oder das Mantelsegment mindestens einen runden oder halbrunden radialen Flansch (38) beinhaltet, der die Öffnungen (34) passiert, wobei die Leitschaufel (26) und der innere Mantel (28) oder das innere Mantelsegment anhand eines Montageverfahrens miteinander verbunden worden sind, dadurch gekennzeichnet, dass der Mantel (28) oder das Mantelsegment mindestens ein Band aus Verschleißmaterial (46) beinhaltet, wobei sich jeder radiale Flansch (38 ; 40 ; 42) radial stärker nach innen erstreckt, als jede Schicht Verschleißmaterial (46) und das Verfahren einem der Ansprüche 7 bis 9 entspricht.
  11. Turbomaschine (2) nach Anspruch 10, dadurch gekennzeichnet, dass der Rotor (12) ringförmige Rippen (44) besitzt, die dicht mit dem Mantel (28) oder Mantelsegment zusammenwirken, wobei sich die ringförmigen Rippen (44) des Rotors jeweils in axialem Abstand von jedem radialen Flansch (38 ; 40 ; 42) des Mantels (28) oder des Mantelsegments befinden.
  12. Turbomaschine (2) nach einem der Ansprüche 10 bis 11, dadurch gekennzeichnet, dass mindestens einer oder jeder radiale Flansch (38 ; 40 ; 42) Unebenheiten (48) besitzt, die auf dem größten Teil der radialen Höhe des Rotationsprofils einer der ringförmigen Rippen (44) des Rotors (12) ausgebildet sind, die gegenüber dem dazugehörigen radialen Flansch (38 ; 40; 42) angeordnet ist.
  13. Turbomaschine (2) nach einem der Ansprüche 10 bis 12, dadurch gekennzeichnet, dass jede Öffnung (34) einen Dichtungsring (54) besitzt, der dazu bestimmt ist, um eine Leitschaufel (26) zu umgeben, die in der genannten Öffnung (34) angeordnet ist, wobei der Dichtungsring (54) mit dem radialen Flansch (38) in Kontakt steht, der die genannte Öffnung (34) passiert, wobei der Flansch vorzugsweise aus einem Silikonelastomer besteht.
  14. Turbomaschine (2) nach einem der Ansprüche 10 bis 13, dadurch gekennzeichnet, dass mindestens eine oder jede Leitschaufel (26) eine Form von radialer Stufe besitzt, die axial und/oder radial an dem oder einem der radialen Flansche (38) anliegt.
  15. Turbomaschine (2) nach einem der Ansprüche 10 bis 14, dadurch gekennzeichnet, dass mindestens eine oder jede Leitschaufel (26) eine Einkerbung besitzt, in welche der oder einer der radialen Flansche (38) des Mantels eingeführt wird und/oder der oder einer der radialen Flansche (38) Einkerbungen besitzt, in welche die Leitschaufeln (26) eingeführt werden.
EP15190957.9A 2014-11-18 2015-10-22 Stator-innenring eines kompressors eines axialen turbotriebwerks Active EP3023595B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP18159641.2A EP3351736B1 (de) 2014-11-18 2015-10-22 Stator-innenring eines kompressors eines axialen turbotriebwerks

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
BE2014/0820A BE1022513B1 (fr) 2014-11-18 2014-11-18 Virole interne de compresseur de turbomachine axiale

Related Child Applications (2)

Application Number Title Priority Date Filing Date
EP18159641.2A Division-Into EP3351736B1 (de) 2014-11-18 2015-10-22 Stator-innenring eines kompressors eines axialen turbotriebwerks
EP18159641.2A Division EP3351736B1 (de) 2014-11-18 2015-10-22 Stator-innenring eines kompressors eines axialen turbotriebwerks

Publications (2)

Publication Number Publication Date
EP3023595A1 EP3023595A1 (de) 2016-05-25
EP3023595B1 true EP3023595B1 (de) 2018-04-18

Family

ID=52449883

Family Applications (2)

Application Number Title Priority Date Filing Date
EP18159641.2A Active EP3351736B1 (de) 2014-11-18 2015-10-22 Stator-innenring eines kompressors eines axialen turbotriebwerks
EP15190957.9A Active EP3023595B1 (de) 2014-11-18 2015-10-22 Stator-innenring eines kompressors eines axialen turbotriebwerks

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP18159641.2A Active EP3351736B1 (de) 2014-11-18 2015-10-22 Stator-innenring eines kompressors eines axialen turbotriebwerks

Country Status (6)

Country Link
US (1) US10113439B2 (de)
EP (2) EP3351736B1 (de)
CN (1) CN105604612B (de)
BE (1) BE1022513B1 (de)
CA (1) CA2909256A1 (de)
RU (1) RU2719521C2 (de)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3056684B1 (de) * 2015-02-16 2018-05-16 MTU Aero Engines GmbH Axial geteilter Innenring für eine Strömungsmaschine, Leitschaufelkranz und Flugtriebwerk
US11028855B2 (en) * 2015-02-27 2021-06-08 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Method of manufacturing supercharger
FR3045716B1 (fr) * 2015-12-18 2018-01-26 Safran Aircraft Engines Ensemble d'anneau de turbine avec maintien elastique a froid
BE1025283B1 (fr) 2017-06-02 2019-01-11 Safran Aero Boosters S.A. Systeme d'etancheite pour compresseur de turbomachine
DE102017211316A1 (de) 2017-07-04 2019-01-10 MTU Aero Engines AG Turbomaschinen-Dichtring
FR3085993B1 (fr) * 2018-09-17 2020-12-25 Safran Aircraft Engines Aube mobile pour une roue d'une turbomachine
FR3087825B1 (fr) * 2018-10-29 2020-10-30 Safran Aircraft Engines Secteur d'anneau de turbine a languettes d'etancheite refroidies
FR3088671B1 (fr) 2018-11-16 2021-01-29 Safran Aircraft Engines Etancheite entre une roue mobile et un distributeur d'une turbomachine
FR3091725B1 (fr) 2019-01-14 2022-07-15 Safran Aircraft Engines Ensemble pour une turbomachine
US10822987B1 (en) 2019-04-16 2020-11-03 Pratt & Whitney Canada Corp. Turbine stator outer shroud cooling fins
JP7370226B2 (ja) * 2019-11-19 2023-10-27 三菱重工業株式会社 蒸気タービン
FR3103851B1 (fr) * 2019-12-03 2021-11-05 Safran Aircraft Engines Barre rigide pour le raccordement electrique d’une machine dans une turbomachine d’aeronef

Family Cites Families (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2410588A (en) * 1942-06-23 1946-11-05 Northrop Aircraft Inc Turbine blade and assembly thereof
US2771622A (en) * 1952-05-09 1956-11-27 Westinghouse Electric Corp Diaphragm apparatus
US2962809A (en) * 1953-02-26 1960-12-06 Gen Motors Corp Method of making a compressor seal
US3836282A (en) * 1973-03-28 1974-09-17 United Aircraft Corp Stator vane support and construction thereof
FR2452590A1 (fr) * 1979-03-27 1980-10-24 Snecma Garniture d'etancheite amovible pour segment de distributeur de turbomachine
US4710097A (en) * 1986-05-27 1987-12-01 Avco Corporation Stator assembly for gas turbine engine
US5201847A (en) * 1991-11-21 1993-04-13 Westinghouse Electric Corp. Shroud design
US5722813A (en) * 1996-10-28 1998-03-03 Alliedsignal Inc. Segmented composite compressor deswirl
US6543995B1 (en) * 1999-08-09 2003-04-08 United Technologies Corporation Stator vane and stator assembly for a rotary machine
US6409472B1 (en) * 1999-08-09 2002-06-25 United Technologies Corporation Stator assembly for a rotary machine and clip member for a stator assembly
US6494677B1 (en) * 2001-01-29 2002-12-17 General Electric Company Turbine nozzle segment and method of repairing same
FR2833035B1 (fr) * 2001-12-05 2004-08-06 Snecma Moteurs Plate-forme d'aube de distributeur pour moteur a turbine a gaz
US6793457B2 (en) * 2002-11-15 2004-09-21 General Electric Company Fabricated repair of cast nozzle
FR2856749B1 (fr) * 2003-06-30 2005-09-23 Snecma Moteurs Redresseur de compresseur de moteur aeronautique a aubes collees
US7229245B2 (en) * 2004-07-14 2007-06-12 Power Systems Mfg., Llc Vane platform rail configuration for reduced airfoil stress
GB2427900B (en) * 2005-07-02 2007-10-10 Rolls Royce Plc Vane support in a gas turbine engine
US7530782B2 (en) * 2005-09-12 2009-05-12 Pratt & Whitney Canada Corp. Foreign object damage resistant vane assembly
EP2075414A1 (de) 2007-12-27 2009-07-01 Techspace aero Stator-Innenring für die Begrenzung des Primärflusses des Triebwerks eines Luftfahrzeugs
EP2196629B1 (de) * 2008-12-11 2018-05-16 Safran Aero Boosters SA Segmentierter Verbundmantelring eines axialen Verdichters
US8544173B2 (en) * 2010-08-30 2013-10-01 General Electric Company Turbine nozzle biform repair
US8966756B2 (en) * 2011-01-20 2015-03-03 United Technologies Corporation Gas turbine engine stator vane assembly
EP2746538B1 (de) * 2012-12-24 2016-05-18 Techspace Aero S.A. Befestigungsplatte einer Statorschaufel eines Turbotriebwerks mit internen Ausparungen

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
RU2719521C2 (ru) 2020-04-21
RU2015146074A (ru) 2017-05-16
RU2015146074A3 (de) 2019-05-20
BE1022513B1 (fr) 2016-05-19
CN105604612A (zh) 2016-05-25
EP3023595A1 (de) 2016-05-25
CA2909256A1 (en) 2016-05-18
US10113439B2 (en) 2018-10-30
EP3351736B1 (de) 2020-01-29
EP3351736A1 (de) 2018-07-25
US20160138413A1 (en) 2016-05-19
CN105604612B (zh) 2018-08-28

Similar Documents

Publication Publication Date Title
EP3023595B1 (de) Stator-innenring eines kompressors eines axialen turbotriebwerks
EP2735707B1 (de) Leitrad einer axialen Turbomaschine mit segmentiertem Innendeckband und zugehöriger Verdichter
EP3018295B1 (de) Gemischter kompressorstator eines axialen turbotriebwerks
EP2977549B1 (de) Beschaufelung einer axialen strömungsmaschine und zugehörige turbomachine
EP2966264B1 (de) Laufradschaufelsegment eines Verdichters eines axialen Turbotriebwerks
EP3109406B1 (de) Gehäuse für kompressor eines axialen turbotriebwerks
EP2735706B1 (de) Gleichrichter mit Laufradschaufeln eines Kompressors eines axialen Turbotriebwerks, und Herstellungsverfahren
EP2977559B1 (de) Stator einer axialen strömungsmaschine und zugehörige strömungsmaschine
EP3095963B1 (de) Laufradschaufel und deckband eines kompressors eines axialen turbotriebwerks
EP2937517A1 (de) Stator einer axialen Turbomachine und zugehörige Turbomachine
EP2873810B1 (de) Ringförmiger Deckel zur Begrenzung der Lagerkammer eines Turbotriebwerks
CA2831522C (fr) Flasque d'etancheite pour etage de turbine de turbomachine d'aeronef, comprenant des tenons anti-rotation fendus
EP2843196B1 (de) Verdichter einer turbomaschine und zugehörige turbomaschine
EP2818635B1 (de) Kompressortrommel einer axialen Turbomaschine mit gemischter Befestigung der Laufradschaufeln
EP2977548B1 (de) Schaufel und zugehörige strömungsmaschine
CA2858797A1 (fr) Redresseur de compresseur pour turbomachine
EP2937516B1 (de) Rundgebogenes Monoblock-Gehäuse für Kompressor einer axialen Turbomaschine und entsprechendes Fertigungsverfahren
EP2886804A1 (de) Dichtungsanordnung für ein Kompressor eines Turbotriebwerks
EP2821595A1 (de) Statorschaufelabschnitt mit abwechselnden Befestigungen für eine axiale Turbomaschine
EP2762681A1 (de) Rotortrommel einer axialen Turbomaschine und zugehörige Turbomaschine
EP2458157B1 (de) Abriebdichtung eines Stator-Innenrings
BE1023367B1 (fr) Fixation de virole interne de compresseur de turbomachine axiale
EP2977550B1 (de) Schaufel einer axialen strömungsmaschine und zugehörige strömungsmaschine

Legal Events

Date Code Title Description
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

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

17P Request for examination filed

Effective date: 20161123

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

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SAFRAN AERO BOOSTERS SA

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20171031

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

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

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 990704

Country of ref document: AT

Kind code of ref document: T

Effective date: 20180515

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: DE

Ref legal event code: R096

Ref document number: 602015010063

Country of ref document: DE

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20180418

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 4

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: 20180418

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

Ref country code: SE

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

Effective date: 20180418

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: 20180418

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: 20180418

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: 20180718

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: 20180718

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: 20180418

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: 20180418

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: 20180418

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

Ref country code: HR

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

Effective date: 20180418

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: 20180719

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: 20180418

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: 20180418

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 990704

Country of ref document: AT

Kind code of ref document: T

Effective date: 20180418

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

Ref country code: PT

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

Effective date: 20180820

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602015010063

Country of ref document: DE

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

Ref country code: RO

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

Effective date: 20180418

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: 20180418

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: 20180418

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: 20180418

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: 20180418

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: 20180418

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: 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: 20180418

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: 20180418

26N No opposition filed

Effective date: 20190121

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: 20180418

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: 20181022

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: 20180418

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

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

Ref country code: LI

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

Effective date: 20181031

Ref country code: CH

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

Effective date: 20181031

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: 20181022

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

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: 20180418

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: 20180418

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

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: 20180418

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: 20151022

Ref country code: MK

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

Effective date: 20180418

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: 20180818

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

Ref country code: GB

Payment date: 20230920

Year of fee payment: 9

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

Ref country code: FR

Payment date: 20230920

Year of fee payment: 9

Ref country code: BE

Payment date: 20230920

Year of fee payment: 9

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

Ref country code: DE

Payment date: 20230920

Year of fee payment: 9