EP3318723B1 - Anneau d'étanchéité d'un rotor et rotor - Google Patents

Anneau d'étanchéité d'un rotor et rotor Download PDF

Info

Publication number
EP3318723B1
EP3318723B1 EP16197268.2A EP16197268A EP3318723B1 EP 3318723 B1 EP3318723 B1 EP 3318723B1 EP 16197268 A EP16197268 A EP 16197268A EP 3318723 B1 EP3318723 B1 EP 3318723B1
Authority
EP
European Patent Office
Prior art keywords
rotor
sealing
fastening
profile
blade
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.)
Not-in-force
Application number
EP16197268.2A
Other languages
German (de)
English (en)
Other versions
EP3318723A1 (fr
Inventor
Peter Kury
Karsten Kolk
Peter Schröder
Yulia Bagaeva
Ivan Lbov
Vyacheslav Veitsman
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.)
Siemens Energy Global GmbH and Co KG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Priority to EP16197268.2A priority Critical patent/EP3318723B1/fr
Priority to PCT/EP2017/076348 priority patent/WO2018082908A1/fr
Publication of EP3318723A1 publication Critical patent/EP3318723A1/fr
Application granted granted Critical
Publication of EP3318723B1 publication Critical patent/EP3318723B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/75—Shape given by its similarity to a letter, e.g. T-shaped
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking

Definitions

  • the invention relates to a sealing ring comprising a plurality of sealing segments distributed around the circumference in a rotor, in particular for use in a gas turbine, the sealing segments having a T-shaped configuration with a central section being attached to the rotor
  • the problem with rotors of gas turbines is that the inner area of the rotor must be protected as best as possible from the hot gas flowing through the gas turbine.
  • sealing measures are taken in the area between the rotor disks, which prevent hot gas from penetrating into the inner area of the rotor as far as possible.
  • a seal is made between the rotor disks as close as possible to the hot gas path. If the installation space between the rotor disks is no longer required after the complete assembly of the rotor, stationary sealing rings are usually used between the rotor disks, which have a simpler shape and a simple type of fastening.
  • the sealing ring is not formed as a closed ring body but from a plurality of sealing segments distributed around the circumference. Their attachment can in turn take place in different ways, the sealing segments having a T-shaped configuration in a known embodiment. In this case, they are releasably attached to a centrally located section in the rotor.
  • the arms of the T-shaped sealing segment here extend on both sides from the center to the rotor disks or to the rotor blades attached to the rotor disks. Due to the T-shaped shape of the sealing segments this enables both favorable assembly on the rotor and an arrangement of the seal near the hot gas path.
  • a rotor in which, instead of a sealing ring formed from segments, a circumferential ring body is formed.
  • This has an approximately T-shaped cross-section, the ring body being fastened between two rotor disk flanges via a central disk-shaped connecting section.
  • the closed annular shape considerably reduces the loads occurring in the fastening of the connecting section. In this embodiment, however, there is no possibility of being able to remove the ring body between the rotor disks.
  • the object of the present invention is therefore to create an improvement in the T-shaped sealing segments in such a way that they are both easy to assemble and also ensure reliable fastening and advantageous sealing.
  • the generic sealing segment is used to form a sealing ring of a rotor.
  • a plurality of sealing segments are distributed around the circumference of the rotor. What kind of rotor is involved here is first of all insignificant, the use of the sealing segment being particularly suitable for a rotor of a gas turbine.
  • the sealing segment has a T-shaped shape, with a central anchoring section extending in the circumferential direction and radially. It is not absolutely necessary here for the anchoring section to have a constant thickness in the axial direction. Rather, this depends on the required strength or the type of connection. At least the anchoring section has a fastening profile on the side facing the rotor axis, by means of which the sealing segment can be fastened to the rotor.
  • a segment center is located at the end of the anchoring section facing radially outward and opposite from the fastening profile.
  • a first sealing section or a second sealing section extends axially on both sides.
  • the sealing sections thus extend essentially in the circumferential direction and in the axial direction.
  • the fastening profile is formed according to the invention as a hook profile that is open on one side.
  • the fastening profile can be hooked into a corresponding receiving profile, for example likewise with the shape of a hook.
  • To one side refers to a side of the anchoring section extending in the circumferential direction and approximately radially, i.e. a lateral movement corresponds approximately to a movement parallel to the rotor axis.
  • the hook profile offers greater freedom when assembling the sealing segment in the rotor, since now, in contrast to the known designs, an exactly radial or exactly axial joining movement is not necessary. Rather, it takes place a hooking in, whereby the required position for the load transfer results almost automatically when the fastening profile is joined to the receiving profile due to the hook shape. Even with this shape deviating from a symmetrical shape of the fastening profile, the necessary load transfer can be ensured.
  • the fastening profile extends in the circumferential direction. This opens up greater possibilities for attaching the fastening profile to the rotor. Furthermore, this considerably simplifies the production of the sealing segment as part of a rotating body. Consequently, the fastening profile is joined as a hook profile on the receiving profile of the rotor in the axial direction or at least in the inclined axial-radial direction or pivoted with an axial-radial movement.
  • fastening profile extends continuously without interruption.
  • the fastening profile extends on both sides in the circumferential direction over the entire length of the sealing segment in the circumferential direction. Accordingly, apart from minimal gaps between the individual segments, the fastening profiles together form a completely ring-shaped profile.
  • the sealing sections each correspond to a section of a body of revolution.
  • the anchoring section is particularly preferably formed as a section of a rotational body.
  • the fastening profile and / or a support section at one axial end and / or both support sections at the opposite ends are also advantageously designed as a section of a body of revolution.
  • the advantageous shape of the sealing segments to form a substantially closed ring body not only favors a separation of an area radially outside the sealing sections from an area radially inside the sealing sections, but also a separation of areas in the axial direction by means of the anchoring section is made possible.
  • one end of the sealing sections and the end of the anchoring section lie opposite one another in the circumferential direction in a longitudinal plane of the rotor through the rotor axis.
  • the fastening profile extends on both sides in the circumferential direction up to the respective longitudinal plane with the end of the sealing section and the end of the anchoring portion extends. This advantageously promotes uniform load transfer from the sealing segments to the rotor disk.
  • one support section or both opposing support sections also run in the circumferential direction up to the longitudinal plane at the end of the sealing sections. This also favors the load transfer via the support sections, and similarly a seal to adjacent rotor disks and / or rotor blades is improved.
  • the support section on one side of the sealing segment is divided into at least two parts in the circumferential direction, at least with the support surface.
  • the support section on one side of the sealing segment is divided into at least two parts in the circumferential direction, at least with the support surface.
  • there is a recess between the parts of the support surface of the support section which in this case facilitates assembly on the rotor.
  • both support sections are designed continuously in the circumferential direction, so that better load support and better sealing are made possible.
  • the sealing sections in a particularly advantageous embodiment, at least in sections between the segment center and the support section, they have a shape that is curved relative to the rotor axis.
  • the deviation from a rectilinear shape results in a significantly improved stability of the sealing sections in the areas that occur Centrifugal forces achieved during operation of the rotor.
  • the curvature is considered along the rotor axis, that is, in a longitudinal section through the rotor axis through the sealing sections, these have an arcuate shape deviating from the straight shape with the curvature pointing towards the rotor axis. It can be provided here that the two sealing sections run unsteadily to one another in the segment center, and it is also possible to design both sealing sections continuously with a common arcuate course over the segment center.
  • the specific shape of the sealing sections is initially unimportant, provided the stability of the sealing sections is improved by the curved shape under the centrifugal forces that occur. It is particularly advantageous here if the shape of the sealing sections is selected such that the centrifugal forces within the sealing section essentially lead to compressive stresses in the direction of the respective support section. Depending on the shape, it can also be advantageous if the stresses in the sealing section are divided and on the one hand are conducted to the support sections as compressive stresses and on the other hand lead to compressive stresses pointing towards the segment center.
  • the respective sealing section starting from the segment center, first approaches the rotor axis axially in the direction of the support sections and then approaches it the distance from the rotor axis to the support sections is increased again.
  • a course that is harmonious over both sealing sections is selected. It is advantageous here if the distance between the sealing sections and the rotor axis increases continuously on both sides, starting from the segment center, up to the support sections.
  • sealing ribs are arranged on the outwardly facing side of the sealing sections to form, for example, a labyrinth seal.
  • the support section has a support surface pointing radially outward and, transversely thereto, a centering surface pointing axially from the segment center. The two surfaces thus enable the compressive forces from the sealing section and the centrifugal forces in the support section to be transmitted via the support surface and the centering surface of the support section to the rotor disk and / or rotor blade.
  • the support section has a curved support surface.
  • This support surface which is curved radially outwards and axially away from the segment center, also enables radial and axial support and thus advantageous load transfer from the support section to the rotor disk and / or the rotor blade, ie in particular the compressive stresses acting from the sealing sections.
  • the support section has an inclined support surface.
  • the inclination can be selected here in such a way that when the sealing segment is used as intended during operation of the rotor, the forces occurring here, ie the compressive forces acting from the sealing sections and the centrifugal forces in the support section, are essentially transmitted as pure compressive stresses across the support surface and, in this respect, in the Support surface transverse forces are largely avoided.
  • An advantageous seal between the area located radially outside and the area below the sealing sections is further promoted if a radially extending sealing strip is present in the support section.
  • the sealing strip can rest against, for example, a rotor blade attached to the rotor disk, so that a further seal between the sealing segment and the rotor blade is improved.
  • the support section has a circumferential, radially outwardly opening receiving groove.
  • the receiving groove - in particular for receiving a sealing strip - can be aligned on the upper side of the support section, i.e. on the radially outwardly facing side, axially within the support section perpendicular to the rotor axis.
  • the receiving groove is provided for receiving a piston ring
  • a design inclined to the radial direction can be selected for a first support section.
  • Both the receiving groove and the piston ring viewed in a longitudinal section through the rotor axis, can have a straight course as well as an arcuate shape.
  • the assembly movement by pivoting the sealing segment around the first support section or its axial end is taken into account, so that the inclined receiving groove or the inclined piston ring is oriented approximately in the direction of the segment center or towards the fastening profile.
  • the receiving groove for receiving the piston ring, can be embodied as an open shoulder pointing axially towards the adjacent rotor disks.
  • the piston ring can be pushed in the axial direction into the receiving groove, which is open radially outward and facing the rotor disk, or the sealing segment can be moved towards a preassembled piston ring when pivoting.
  • the flow seal to a - in contrast to the rotor - standing stator ring is improved if a sealing wing is arranged on the support section, which is axially spaced from the support surface in the direction of the segment center and extends in the circumferential direction and radially.
  • the sealing segment is provided with at least one first centering means.
  • the point at which the centering means is positioned is initially irrelevant.
  • the Zen Trier means can be both a centering recess and a centering projection. According to the attachment of the fastening profile by hooking on a receiving profile with a movement predominantly in the axial direction, it is correspondingly advantageous if the centering means extends axially.
  • an axially and radially extending rib or a mounted, axially and radially extending bolt can be used as the first centering means.
  • An axially extending groove which opens radially inward can also be provided on the fastening profile.
  • a rotor according to the invention is possible, which is used in particular in a gas turbine, the rotor having at least two rotor disks.
  • the rotor disks each have a plurality of blade holding grooves distributed around the circumference.
  • a plurality of sealing segments forming a sealing ring are located between the rotor disks, a corresponding receiving profile being provided for attaching the sealing segments to the fastening profile on the rotor.
  • the receiving profile has a hook profile.
  • sealing segments are used as described above.
  • the receiving profile extends circumferentially and, viewed in a longitudinal section in the rotor axis, forms the hook profile.
  • the assembly of the sealing segments on the rotor can be carried out in different ways, with the hook-shaped embodiment of the fastening profile according to the invention allowing lateral hooking. It is thus possible to attach the fastening profile to a circumferential receiving profile by means of an axial, slightly radially outwardly inclined movement.
  • fastening profile and the receiving profile as well as a first support section and the rotor disk on the one facing the first support section Side are shaped such that a pivoting of the sealing segment around the first support section is possible. It is not absolutely necessary here for a pure circular movement to take place around a fixed pivot point. Rather, it is sufficient if pivoting around the support section is possible so that the fastening profile comes to rest on the receiving profile and the sealing segment can assume the required position. This eliminates the need to provide the support section with interruptions in order to be able to pass projections protruding over the end faces of the rotor disks during assembly.
  • sealing segments and the rotor disks or the rotor are shaped in such a way that two separate annular spaces are formed on both sides of the anchoring section.
  • the arrangement of the receiving profile for fastening the sealing segments to the fastening profile can be varied. In this respect, it is possible, for example, to provide a circumferential receiving profile on an intermediate ring between the two rotor disks.
  • An embodiment is preferred in which the two adjacent rotor disks each have a connecting flange facing one another, the receiving profile being arranged on a connecting flange of one of the rotor disks.
  • the rotor advantageously has rotor blades which are fastened to the blade holding grooves with blade roots and which each have a blade platform extending in the circumferential direction and axially.
  • one rotor disk or both rotor disks each have an at least axially extending fastening projection between the blade holding grooves on. It is provided here that the support sections with the support surfaces come to rest against the fastening projection at least during the rotation of the rotor and to this extent are supported directly on the respective rotor disk.
  • the fastening projection is to be formed complementarily in a particularly advantageous manner, so that the support section is supported axially and radially on the fastening projection.
  • this is supported on an end surface of the rotor disk or on the axially free end of the fastening projection.
  • the fastening shoulder is to be formed in a particularly advantageous manner in an analogously complementary manner, so that the support section rests axially and radially on the fastening shoulder.
  • a first retaining projection is arranged on the rotor disk below the support section on the side facing the rotor axis, on which the support section can come to rest.
  • the rotor blade can also advantageously be provided with a first retaining projection on the blade root.
  • the position of the sealing segment on the rotor can be secured in different ways.
  • a shift in the circumferential direction is provided, with an unhooking via a corresponding locking contour on the fastening profile, in particular on the side opposite the receiving profile, cooperating with an abutment on one of the rotor disks is prevented.
  • a second retaining projection is arranged on the side facing the receiving profile of the rotor blade, which can come to rest on the side facing the rotor axis relative to a second support section.
  • the rotor blades have a collar which starts from the blade platform and projects beyond the rotor disk in the area of the blade holding grooves.
  • This collar can connect to the support section with a minimal sealing gap.
  • the sealing strip in the support section is at least on the collar when the rotor rotates so that an optimal seal between the sealing segment and the rotor blade is achieved.
  • the seal between the sealing segment and the moving blade is improved by using a piston ring between the support sections and the collar of the blade platforms over several, preferably all, segments.
  • a corresponding piston ring is arranged on the support sections and rests against the collar at least when the rotor is in operation.
  • a first piston ring is inclined in a first receiving groove on the first support section. It can be provided that the first piston ring and / or the first receiving groove is straight or curved. Viewed in the longitudinal section, the first piston ring or the first receiving groove points approximately in the direction of the segment center or the fastening profile. This inclined arrangement facilitates the pivoting of the sealing segment around the first support section.
  • a radially extending piston ring can be used both simply and advantageously in an arrangement in radially extending receiving grooves on the second support sections, since when the sealing segments are installed, the second support section is moved essentially radially outward when inserted into the piston ring .
  • the piston ring is arranged in the shoulder in the case of a receiving groove open radially outward and towards the rotor disk in the manner of a shoulder and is thus enclosed between the support section and the rotor disk and the collar of the blade platform.
  • This solution can be used both on the first support section and on both support sections.
  • the piston ring is a one-piece slotted ring as well as two or more segments, it being essential in contrast to the use of sealing strips that in the case of segments these each extend over two or more sealing segments. This means that while the sealing strip can be attached pre-assembled on the respective sealing segment, the piston ring can be attached after the sealing segments (if the rotor blades are not yet in position) or must be attached in front of the sealing segments (if the rotor blades with the blade platforms already cover the assembly area).
  • a second centering means is present on the first and / or the second rotor disk, complementary to the first centering means.
  • the first centering means is arranged on the fastening profile
  • the second centering means is to be arranged accordingly on the receiving profile.
  • the first centering means is arranged on the support section
  • the second complementary centering means can be arranged on the rotor blade, with the second holder projection being advantageously used for this purpose.
  • Two adjacent fastening projections and / or two adjacent retaining projections can advantageously be used as a second centering means complementary to the first centering means.
  • this assembly tool is used for a sealing segment which has a support section at each of the axially opposite ends. It is necessary that the respective support section is a having opposite support section opening mounting recess. Correspondingly, the support section with the mounting recess appears as a radially undercut.
  • the assembly tool here has a first lever and an articulated second lever.
  • the first lever extends in the direction of a support section, a first contact element being arranged at the end of the first lever. This engages in the corresponding mounting recess of the associated support section.
  • the second lever connected via a hinge extends in the direction of the other support section and also has a second contact element at its end. Analogously, the second contact element engages in the associated mounting recess of the corresponding support section. This represents the assembly position of the assembly tool.
  • an actuating element is provided which is attached as an extension of the second lever on the opposite side to the joint. By moving the actuating element towards the first lever, the adjustment between the free position and the assembly position can take place in a simple manner. At the same time, when adjusting in the assembly position, the assembly tool can be handled directly with the sealing segment attached.
  • FIG 1 a first embodiment of a rotor according to the invention and a sealing segment according to the invention are shown schematically in a longitudinal section through the rotor.
  • rotor blades 31 are fastened with a corresponding blade root 32 in a known manner.
  • the two rotor disks 01, 02 are connected to one another via connecting flanges 05, 06 at each end. How the connection flange 05, 06 is designed exactly and how the connection is established is initially irrelevant.
  • Known embodiments can be used in this regard.
  • a plurality of sealing segments 11 are attached to the connecting web 06, distributed around the circumference. Furthermore, the sealing segments 11 adjoin the rotor disks 01, 02 and the rotor blades 31 to be attached on both sides. This advantageously creates a first annular space 08 between the first Rotor disk 01, the connecting flange 05 or 06 and the sealing segment 11 and, opposite, a second annular space 09 between the second rotor disk 02, the connecting flange 06 and the sealing segment 11.
  • the closed annular spaces 08, 09 promote advantageous cooling air guidance in the rotor.
  • the connecting flange 06 has a circumferential receiving profile 04.
  • the hook shape provided here for both the fastening profile 14 and the receiving profile 04 enables the sealing segment 11 to hook into the connecting flange 06 at the side.
  • the sealing segment 11 rests on opposite sides of the rotor disk 01 adjoining a fastening projection 25 and 26 of the rotor disks 01 and 02, so that in addition to the central fastening of the sealing segment 11 on the connecting flange 06, a further contact for load transmission on the Fixing projection 25,26 of the rotor disks 01,02 takes place.
  • a support section 17, 18 is located at each of the axial ends of the sealing segment 11, each of which 17, 18 engages with a radially outwardly pointing support surface 21 under the corresponding fastening projection 25, 26.
  • first support section 17 on the first rotor disk 01 facing the rotor axis is prevented by a first holding projection 27 on the first rotor disk 01.
  • This 27 is arranged radially below the first fastening projection 25.
  • the first support section 17 engages in a cutout between the first fastening projection 45 and the first holding projection 27.
  • the second support section 18 is also supported at the end of the sealing section 15 on a second fastening projection 26 of the second rotor disk 02.To enable the density segment 11 to be swiveled in accordingly, the hook-shaped fastening section 14 is joined to the hook-shaped receiving profile 04 is possible, it is necessary that there is sufficient free space below the second fastening projection 26 for assembly.
  • a second holding section 28 is attached to the rotor blade 31 of the second rotor disk 02. This 28 engages in an analogous manner under the second support section 18 and thus prevents a movement of the second support section 18 facing the rotor axis.
  • FIG 2 an exemplary embodiment of a sealing segment 11 from FIG Fig. 1 outlined. Its T-shaped shape can be seen with sealing sections 15 extending from a segment center 12 on both sides.
  • the sealing sections 15 are arcuate so that an advantageous stress distribution is achieved in sealing segment 11 when centrifugal forces occur.
  • the support section 17, 18 has a radially outwardly pointing support surface 21 and a centering surface 23 pointing axially to the respective rotor disk 01, 02.
  • the support surface 21 and the centering surface 23 are arranged in an L-shape.
  • the support sections 17, 18 each have a receiving groove 24 extending in the circumferential direction. Provision is made for a sealing strip to be inserted into the receiving groove 24, which, at least in the case of centrifugal force, comes to rest under a collar of the respective rotor blades and enables an advantageous seal with respect to the rotor blades.
  • the T-shaped sealing segment also has an anchoring section 13 extending radially inward from the segment center 11.
  • the fastening profile 14 is located at its end opposite to the segment center 12.
  • the fastening profile 14 is designed in the form of a hook that is open at the side, so that this 14 can be fastened in a hook-shaped receiving profile 06. It is obvious how the sealing segment 11 is to be pivoted for assembly and how to move it with the fastening profile 14 in the axial direction.
  • the support sections 17 also have a sealing wing spaced apart from the centering surface 23 in the direction of the segment center 12, which 19 favor a further seal with a stationary stator ring that surrounds the sealing ring formed from sealing segments 11.
  • the sealing segment 11 advantageously has a plurality of radially outwardly extending sealing ribs - the illustration of which has also been omitted - which likewise promote an advantageous seal with respect to the stator ring.
  • FIG 3 is the embodiment from FIG 1 outlined in the state of assembly of the sealing segment 11.
  • the sealing segment 11 can be seen in an inclined position between the two rotor disks 01 and 02. In this position, the sealing segment 11 can be positioned between the rotor disks 01 and 02, in particular between the fastening projection 25 of the first rotor disk 01 and the fastening projection 26 of the second rotor disk 02 is introduced and then inserted with the first support section 17 into the space between the first retaining projection 27 and the first fastening projection 25.
  • the fastening section 14 was joined to the receiving profile 04 with the second support section 18 resting on the second fastening projection 26.
  • the first support section 47 has a curved support surface 51 following the sealing section 15.
  • the curved support surface 51 enables the sealing segment 41 to pivot about the first support section 47 in a particularly advantageous manner, the curved support surface 51 enabling both radial support and centering.
  • the second support section 48 shown on the right largely corresponds to the previous embodiment with a radially outwardly pointing support surface 52 and a radially extending centering surface 53.
  • the sealing segment 41 the arrangement of a first piston ring 35 in a first receiving groove 43 and, opposite, the arrangement of a second piston ring 36 in a second receiving groove 44 is sketched.
  • the second piston ring 36 extends in the radial direction, while the first piston ring 35 - viewed in a longitudinal section through the rotor - has an arcuate shape pointing in the direction of the fastening section. It is provided that the piston ring 35, 36 is attached between the rotor disks 01, 02 before the sealing segments 41 are fitted.
  • the first piston ring 35 is joined into the first receiving groove 35 and, at the end of the pivoting movement, the second piston ring 36 is joined into the second receiving groove 44.
  • FIG. 5 Another exemplary embodiment of an arrangement of a piston ring 36 between the sealing segment, the rotor disk and the rotor blade is outlined. It can be seen analogously to the illustration from Figure 4 the first support section 67 at the end of the sealing section 15.
  • the receiving groove 73 be designed as a shoulder which is open 73 facing the rotor disk.
  • the piston ring 36 can thus be positioned between the first support element 67, the rotor disk 01 and the blade platform 33 of the blade 31 are enclosed. This clearly favors the previous assembly of the piston ring 36 and the subsequent assembly of the sealing segment, since the piston ring 36 now only has to fit into the receiving groove 73 as a shoulder instead of being threaded.
  • an inclined support surface 71 is sketched, the inclination of which is selected so that, when used as intended and the centrifugal forces that occur, essentially only compressive stresses are transmitted via the support surface 71.
  • An exemplary assembly tool 101 is now shown schematically in an assembly position on the sealing segment 11.
  • the sealing segment 11 can again be seen from FIGS Figures 1-3 .
  • the support sections 17, 18 at the end of the sealing sections 15 each have a mounting recess facing the opposite support section 17, 18, which is radially undercut.
  • the assembly tool 101 comprises a first lever 103, which 103 extends essentially axially to one of the support sections 17 and at the 17 end of which a first receiving element 104 is located.
  • This 104 engages in the mounting recess on the corresponding support section 17.
  • a joint 107 on which a second lever 105 is pivotably mounted.
  • This 105 extends analogously in the opposite direction to the other support section 17.
  • a second contact element 106 at the end of the second lever 105 engages in its corresponding mounting recess.
  • the assembly position shown here is made possible by the movement of an actuating element 108, which is connected to the second lever 105 opposite to the joint 107. When the actuating element 108 is grasped with the first lever 103, the sealing segment can be moved with the assembly tool.
  • the assembly tool 101 can be relatively moved by pivoting the second lever 105 to the first lever 103 are removed from the sealing segment 11.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (21)

  1. Anneau d'étanchéité d'un rotor, notamment d'une turbine à gaz, comprenant une pluralité de segments (11, 41) d'étanchéité répartis sur le pourtour, ayant chacun une partie (13) centrale et s'étendant dans la direction du pourtour et radialement, qui (13) a, du côté tourné vers l'axe du rotor, un profil (14) de fixation et, à l'extrémité tournée vers l'extérieur, un milieu (12) de segment, et comprenant des premières et deuxièmes parties (15) d'étanchéité, s'étendant latéralement axialement dans la direction du pourtour sensiblement à partir du milieu (12) du segment et comprenant des premières et deuxièmes parties (17, 18, 47, 47, 67) d'appui se raccordant aux parties (15) d'étanchéité respectives,
    caractérisé
    en ce que le profil (14) de fixation est formé à la forme d'un profil de crochet, ouvert d'un côté, continu ou interrompu et s'étendant dans la direction du pourtour et peut être accroché latéralement dans un profil (04) de réception conjugué.
  2. Anneau d'étanchéité suivant la revendication 1,
    caractérisé
    en ce que le profil (14) de fixation s'étend de manière continue dans la direction du pourtour ; ou
    en ce que le profil (14) de fixation s'étend dans la direction du pourtour d'une manière continue sur toute la longueur du segment (11, 41) d'étanchéité.
  3. Anneau d'étanchéité suivant la revendication 1 ou 2,
    caractérisé
    en ce que les parties (15) d'étanchéité, notamment les parties (17, 18, 41, 48, 67) d'appui et notamment la partie (13) d'ancrage et le profil (14) de fixation correspondent à une partie d'une pièce de révolution.
  4. Anneau d'étanchéité suivant l'une des revendications 1 à 3,
    caractérisé
    en ce que les deux extrémités du segment (11, 41) d'étanchéité se trouvent dans la direction périphérique, respectivement, sensiblement dans un plan longitudinal avec l'axe du rotor.
  5. Anneau d'étanchéité suivant l'une des revendications 1 à 4,
    caractérisé
    en ce que les parties (15) d'étanchéité ont, au moins par endroit, entre le milieu (12) du segment et la partie (17, 18, 47, 48, 67) d'appui, une forme incurvée vers l'axe du rotor ; et/ou en ce que la forme donnée aux parties (15) d'étanchéité est choisie de manière à ce que des forces centrifuges provoquent au moins des contraintes de pression en direction des parties (17, 18, 47, 48, 67) d'appui et, le cas échéant, vers le milieu (12) du segment.
  6. Anneau d'étanchéité suivant l'une des revendications 1 à 5, caractérisé
    en ce que la partie (17, 18, 48) d'appui a une surface (21, 52) tournée vers l'extérieur radialement et une surface (23, 53) de centrage, loin axialement du milieu (12) du segment ; ou en ce que la partie (47) d'appui a une surface (51) d'appui incurvée, qui (51) rend possible un appui radial et axial ; ou
    en ce que la partie (67) d'appui a une surface (71) d'appui inclinée, l'inclinaison étant choisie de manière à pouvoir, pour un usage conforme aux prescriptions et aux forces, qui apparaissent dans ce cas, transmettre sensiblement seulement des contraintes de pression.
  7. Anneau d'étanchéité suivant l'une des revendications 1 à 6,
    caractérisé
    en ce que, dans la partie (17, 18, 47, 48, 67) d'appui, est insérée une baguette d'étanchéité s'étendant radialement ; et/ou
    en ce que, dans la partie (17, 18, 47, 48, 67) d'appui, est présente une rainure (24, 43, 44, 73) de réception s'ouvrant vers l'extérieur radialement.
  8. Anneau d'étanchéité suivant l'une des revendications 1 à 7,
    caractérisé
    en ce que, sur le profil (14) de fixation et/ou sur la partie (17, 18, 47, 48, 67) d'appui, est disposé un premier moyen de centrage s'étendant axialement, notamment un évidement de centrage ou une saillie de centrage.
  9. Rotor, notamment d'une turbine à gaz, comprenant au moins deux disques (01, 02) rotoriques, qui (01, 02) ont, réparties sur le pourtour, une pluralité de rainures (03) de retenue d'aube et comprenant une pluralité de segments (11, 41) d'étanchéité formant un anneau d'étanchéité, dans lequel il y a dans le rotor un profil (04) de réception annulaire où (04) les segments (11, 41) d'étanchéité sont fixés par des profils (14) de fixation,
    caractérisé par
    une exécution de l'anneau (11, 41) d'étanchéité, respectivement, suivant l'une des revendications précédentes, le profil (04) de réception ayant un profil en crochet.
  10. Rotor suivant la revendication 9,
    caractérisé
    en ce que le profil (14) de fixation et le profil (04) de réception sont conformés de manière à rendre possible un pivotement du segment (11, 41) d'étanchéité autour d'une première partie (17) d'appui.
  11. Rotor suivant la revendication 9 ou 10,
    caractérisé
    en ce qu'entre un premier disque (01) rotorique et l'anneau d'étanchéité formé des segments (11, 41) d'étanchéité, il y a un premier espace (08) annulaire et entre un deuxième disque (02) rotorique et l'anneau d'étanchéité, il y a un deuxième espace (09) annulaire distinct.
  12. Rotor suivant l'une des revendications 9 à 11,
    caractérisé
    en ce que les disques (01, 02) rotoriques ont chacun une bride (05) de liaison, tournées l'une vers l'autre, le profil (06) de réception étant disposé sur l'une des brides (05) de liaison.
  13. Rotor suivant l'une des revendications 9 à 12,
    caractérisé
    par des aubes (31) mobiles, qui sont fixées dans les rainures (03) de retenue d'aube par des emplantures (32) d'aube, et qui (31) ont une plateforme (33) d'aube, s'étendant dans la direction du pourtour et axialement et se raccordant aux emplantures (32) d'aube.
  14. Rotor suivant l'une des revendications 9 à 13,
    caractérisé
    en ce qu'un disque (01, 02) rotorique ou les deux disques (01, 02) rotoriques ont, notamment chacun, entre les rainures (03) de retenue d'aube, une saillie (25, 26) de fixation s'étendant axialement, la première et/ou la deuxième partie (17, 18, 47, 48, 67) d'appui venant en contact, au moins lorsque le rotor tourne, de la saillie (25, 26) de fixation associée.
  15. Rotor suivant la revendication 13,
    caractérisé
    en ce que l'emplanture (32) de l'aube et/ou la plateforme (33) de l'aube (31) mobile du premier et/ou du deuxième disque (01, 02) rotorique ont un ressaut de fixation s'étendant axialement, la partie (17, 18, 47, 48, 67) d'appui venant, au moins lorsque le rotor tourne, en contact avec le ressaut de fixation.
  16. Rotor suivant l'une des revendications 13 ou 15,
    caractérisé
    en ce que, sur un premier disque (01) rotorique ou sur l'emplanture des aubes mobiles du premier disque (01) rotorique, est disposée une saillie (27) de retenue avec laquelle (27) la partie (17) d'appui vient en contact.
  17. Rotor suivant l'une des revendications 13, 15 ou 16,
    caractérisé
    en ce que, sur l'emplanture (32) des aubes (31) mobiles, d'un deuxième disque (02) rotorique, est montée une deuxième saillie (28) de retenue, avec laquelle (28) la partie (18) d'appui vient en contact.
  18. Rotor suivant l'une des revendications 13 ou 15,
    caractérisé
    en ce que, entre un collet dépassant des disques (01, 02) rotoriques de la plateforme (33) de l'aube et la partie (17, 18, 47, 48, 67) d'appui, est formé un intervalle d'étanchéité ; et/ou
    en ce que la baguette d'étanchéité s'applique, au moins lorsque le rotor tourne, à un collet dépassant des disques (01, 02) rotoriques de la plateforme (33) de l'aube.
  19. Rotor suivant l'une des revendications 13, 15 ou 18,
    caractérisé
    en ce que, entre un collet dépassant des disques (01, 02) rotoriques des plateformes (33) d'aube et les parties (17, 18, 47, 48, 67) d'appui, est monté un segment (35, 36) de piston.
  20. Rotor suivant la revendication 19,
    caractérisé
    en ce qu'un segment (35) de piston est réalisé sur la première partie (47) d'appui, incliné par rapport à la direction radiale ; ou
    en ce que la rainure (67) de réception est réalisée sur la première partie (67) d'appui, dans laquelle (67) un segment (36) de piston est monté entre la première partie (67) d'appui et le disque (01) rotorique et le collet de la plateforme (33) de l'aube.
  21. Rotor suivant l'une des revendications 13 à 20, comprenant un anneau d'étanchéité suivant la revendication 8 ou suivant les revendications 13 et 17 ayant un anneau d'étanchéité suivant la revendication 8 ou suivant les revendications 14 et 16 ayant un anneau d'étanchéité suivant la revendication 8,
    caractérisé
    en ce que sur le profil (04) de réception est disposé un deuxième moyen de centrage, complémentaire du premier moyen de centrage ; et/ou
    en ce que sur l'aube (31) mobile est disposé un deuxième moyen de centrage, complémentaire du premier moyen de centrage, la deuxième saillie de retenue formant, notamment, le deuxième moyen de centrage ; et/ou
    en ce que le premier moyen de centrage pénètre, respectivement, entre deux saillies (25, 26) de fixation du premier et/ou du deuxième disques (01, 02) rotoriques et/ou entre deux saillies (27) de retenue du premier disque (01) rotorique.
EP16197268.2A 2016-11-04 2016-11-04 Anneau d'étanchéité d'un rotor et rotor Not-in-force EP3318723B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP16197268.2A EP3318723B1 (fr) 2016-11-04 2016-11-04 Anneau d'étanchéité d'un rotor et rotor
PCT/EP2017/076348 WO2018082908A1 (fr) 2016-11-04 2017-10-16 Segment d'étanchéité d'un rotor et rotor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP16197268.2A EP3318723B1 (fr) 2016-11-04 2016-11-04 Anneau d'étanchéité d'un rotor et rotor

Publications (2)

Publication Number Publication Date
EP3318723A1 EP3318723A1 (fr) 2018-05-09
EP3318723B1 true EP3318723B1 (fr) 2021-01-13

Family

ID=57226883

Family Applications (1)

Application Number Title Priority Date Filing Date
EP16197268.2A Not-in-force EP3318723B1 (fr) 2016-11-04 2016-11-04 Anneau d'étanchéité d'un rotor et rotor

Country Status (2)

Country Link
EP (1) EP3318723B1 (fr)
WO (1) WO2018082908A1 (fr)

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2018065739A1 (fr) * 2016-10-07 2018-04-12 Safran Aircraft Engines Assemblage d'anneau mobile de turbine de turbomachine

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5320488A (en) * 1993-01-21 1994-06-14 General Electric Company Turbine disk interstage seal anti-rotation system
FR3009336B1 (fr) * 2013-08-05 2015-09-04 Snecma Ensemble rotatif de turbomachine muni d'une virole labyrinthe cmc

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2018065739A1 (fr) * 2016-10-07 2018-04-12 Safran Aircraft Engines Assemblage d'anneau mobile de turbine de turbomachine

Also Published As

Publication number Publication date
WO2018082908A1 (fr) 2018-05-11
EP3318723A1 (fr) 2018-05-09

Similar Documents

Publication Publication Date Title
EP2960438B1 (fr) Système d'aubes de guidage variables pour une turbine à gaz et turbine à gaz dotée d'un tel système
EP2399004B1 (fr) Section de rotor pour un rotor d'une turbomachine, aube rotorique pour une turbomachine et élément de blocage
DE102010060284B4 (de) Sicherungs-Abstandshalteranordnung für ein Schaufelblattbefestigungssystem zur Einführung in Umfangsrichtung und Rotoranordnung mit derartiger Sicherungs-Abstandshalteranordnung
DE19603388C1 (de) Einrichtung zur Fixierung der Laufschaufeln am Laufrad, insbesondere einer Turbine eines Gasturbinentriebwerks, durch Nietung
DE2549649B2 (de) Schaufelbefestigung fur Gasturbinenstrahltriebwerke
DE102015116935A1 (de) Sicherungsvorrichtung zur axialen Sicherung einer Laufschaufel und Rotorvorrichtung mit einer derartigen Sicherungsvorrichtung
EP0165955A1 (fr) Jante pour vehicules a moteur ou autres
EP2394028B1 (fr) Dispositif d'étanchéité sur l'arbre à aubes d'un étage de rotor d'une turbomachine axiale et son utilisation
EP3318723B1 (fr) Anneau d'étanchéité d'un rotor et rotor
EP3109520B1 (fr) Support d'étanchéité, stator et turbomachine
WO2018036818A1 (fr) Rotor muni d'une bague d'étanchéité segmentée
EP3695100B1 (fr) Rotor pourvu d'élément d'étanchéité et de bague d'étanchéité
EP3129599B1 (fr) Assemblage de disque de roue
DE102017121751B4 (de) Mehrteilige Bremsscheibe
WO2018082907A1 (fr) Segment étanche d'un rotor et rotor
EP3885535B1 (fr) Bague d'étanchéité pour un rotor et rotor doté d'une telle bague d'étanchéité
EP3724456B1 (fr) Rotor à surfaces de contact optimisées au niveau de forces centrifuges
EP3348786A1 (fr) Rotor comprenant une couverture de conduite et plaques d'étanchéité
DE102016205921B4 (de) Rotorscheibenanordnung mit zweiteiliger Dichtung
DE102017220336A1 (de) Dichtsegment eines Rotors sowie Rotor
DE102017214065A1 (de) Rotor mit mittels Dichtelementen fixierten Laufschaufeln
DE102017214062A1 (de) Rotor mit mittels Dichtelemente axial fixierten Laufschaufeln
DE102018203173A1 (de) Lastaufnahmeelement mit hakenförmiger Gestalt
EP3561234B1 (fr) Rotor pourvu de dispositif d'étanchéité
EP3415782B1 (fr) Disque de frein et frein à disque

Legal Events

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

Free format text: ORIGINAL CODE: 0009012

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

Free format text: STATUS: THE APPLICATION HAS BEEN PUBLISHED

AK Designated contracting states

Kind code of ref document: A1

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

AX Request for extension of the european patent

Extension state: BA ME

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

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20180518

RBV Designated contracting states (corrected)

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

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

Free format text: STATUS: EXAMINATION IS IN PROGRESS

17Q First examination report despatched

Effective date: 20181203

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: 20200914

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

RAP2 Party data changed (patent owner data changed or rights of a patent transferred)

Owner name: SIEMENS ENERGY GLOBAL GMBH & CO. KG

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502016012179

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: GERMAN

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1354701

Country of ref document: AT

Kind code of ref document: T

Effective date: 20210215

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20210113

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG9D

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

Ref country code: 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: 20210113

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: 20210113

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: 20210414

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: 20210513

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: 20210413

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: 20210113

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: 20210413

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: 20210113

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: 20210113

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: 20210113

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: 20210113

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: 20210513

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502016012179

Country of ref document: DE

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

Ref country code: SM

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

Effective date: 20210113

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: 20210113

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: 20210113

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: 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: 20210113

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: 20210113

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: 20210113

26N No opposition filed

Effective date: 20211014

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: 20210113

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: 20210113

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: 20210113

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: 20210513

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502016012179

Country of ref document: DE

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

Ref country code: MC

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

Effective date: 20210113

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20211104

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: 20211104

Ref country code: BE

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

Effective date: 20211130

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20211130

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: 20211130

Ref country code: CH

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

Effective date: 20211130

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: 20211104

Ref country code: GB

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

Effective date: 20211104

Ref country code: DE

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

Effective date: 20220601

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

Ref country code: FR

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

Effective date: 20211130

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 1354701

Country of ref document: AT

Kind code of ref document: T

Effective date: 20211104

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 NON-PAYMENT OF DUE FEES

Effective date: 20211104

Ref country code: AT

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

Effective date: 20211104

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

Ref country code: HU

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

Effective date: 20161104

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 NON-PAYMENT OF DUE FEES

Effective date: 20210113

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: 20210113

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: 20210113

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: 20210113

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: 20210113