EP2807344B1 - Statorbauteil mit segmentiertem innenring für eine strömungsmaschine - Google Patents

Statorbauteil mit segmentiertem innenring für eine strömungsmaschine Download PDF

Info

Publication number
EP2807344B1
EP2807344B1 EP13702011.1A EP13702011A EP2807344B1 EP 2807344 B1 EP2807344 B1 EP 2807344B1 EP 13702011 A EP13702011 A EP 13702011A EP 2807344 B1 EP2807344 B1 EP 2807344B1
Authority
EP
European Patent Office
Prior art keywords
stator component
segments
component according
sub
inner ring
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
EP13702011.1A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP2807344A1 (de
Inventor
Herbert Brandl
Hans-Peter Bossmann
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.)
Ansaldo Energia IP UK Ltd
Original Assignee
Ansaldo Energia IP UK Ltd
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 Ansaldo Energia IP UK Ltd filed Critical Ansaldo Energia IP UK Ltd
Priority to EP13702011.1A priority Critical patent/EP2807344B1/de
Publication of EP2807344A1 publication Critical patent/EP2807344A1/de
Application granted granted Critical
Publication of EP2807344B1 publication Critical patent/EP2807344B1/de
Active 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
    • F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
    • 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
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • 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
    • F05D2240/55—Seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/21—Oxide ceramics
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/21—Oxide ceramics
    • F05D2300/2112—Aluminium oxides
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/21—Oxide ceramics
    • F05D2300/2118—Zirconium oxides
    • 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
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/502—Thermal properties
    • F05D2300/5021—Expansivity
    • F05D2300/50212—Expansivity dissimilar

Definitions

  • the present invention relates to a stator component of a turbomachine.
  • a turbine housing of an internal combustion engine has become known from the prior art, which is essentially formed from a hot gas duct through which the hot working gases flow. Due to such operation, a liner made of a refractory material is preferably provided on the inner wall surface of this hot gas duct to prevent the remaining metallic surface of the housing from directly contacting the hot working gases.
  • this thermal protection lining consists of several sub-segments, which are arranged on the inner surface of the turbine housing in the circumferential direction, so that they form a ring. In order to avoid thermal expansion problems at high temperature, the respective sub-segments are circumferentially spaced from each other.
  • WO 2009/126191 A2 discloses a stator component for a turbomachine with an outer ring that carries a segmented inner ring.
  • the inner ring consists of two concentric ceramic layers and a radially outer metal layer.
  • EP 1 225 308 B1 discloses a turbine casing consisting of a split ring having a plurality of split split segments arranged on the inner wall of the gas turbine casing at predetermined intervals circumferentially such that the split segments form a ring which is operatively connected to the rotor blades.
  • Each of the sub-segments has two end surfaces in the circumferential direction, which face the ends of the adjacent sub-segments.
  • At least one of the end surfaces of the partial segment has a transition surface on, which is designed as a cylindrical or spherical surface.
  • the invention aims to remedy the situation.
  • the invention is based on the object of proposing a stator component in which a special spacing of the individual sub-segments from one another in the circumferential direction and relative to the rotor blade tips, in particular the design of the rotor-side surface of the sub-segments, is dispensed with can.
  • the object of the invention is also to propose a configuration and constellation of the sub-segments in which the problems of thermal expansion and compressive stresses can be solved in a simple manner.
  • the stator component of a turbomachine is designed in such a way that it consists essentially of an outer ring and an inner ring, with the outer ring serving as a mount for the inner ring formed from individual sub-segments.
  • the sub-segments are arranged next to one another in such a way that, framed by the outer ring, they form a continuous circular peripheral surface on the rotor side.
  • these partial segments of the inner ring have a trapezoidal or quasi-trapezoidal shape in a section perpendicular to the axis of rotation of the turbomachine Cross-section where the parallel or quasi-parallel sides of the trapezium form the radial inside and radial outside of the ring, respectively.
  • the sub-segments form a self-supporting inner ring under an approximately uniform circumferential and radial pressure at the design point during operation of the turbomachine.
  • the sub-segment is of prismatic or quasi-prismatic shape, at least in a cross-section perpendicular to the circumferential direction of the ring.
  • each sub-segment has a substantially planar, concave, convex or spherical surface with respect to the inner peripheral surface of the outer ring, the sub-segment itself being able to consist of a single monolithic material or of several composite materials of different dimensions or composition.
  • the material used for this or the composite materials used to form such a partial segment have a uniform and/or non-uniform microstructure.
  • the sub-segment formed in this way has a predetermined stress and/or expansion behavior depending on the load ranges of the turbomachine.
  • This expansion behavior of the sub-segments can be configured differently in the radial and/or axial direction using a differentiated structure, in correlation to the different temperatures that prevail in the radial and axial direction of the sub-segment.
  • the stator component according to the invention of a turbomachine consists essentially of at least one axial outer ring and one inner ring, with the outer ring serving as a mount for the inner ring consisting of sub-segments, and with the sub-segments being able to be arranged on one another in such a way that, when installed, they unite on the rotor side with respect to the rotary movement of rotor blades form a circular inner ring.
  • the partial segments consist of a material that is built up gradually at least in the radial direction or of a plurality of partial bodies that are built up from different materials at least in the radial direction.
  • the sub-segments formed in this way are heated depending on the load ranges of the turbomachine during operation of the turbomachine, so that there is a temperature gradient from radially inside to radially outside, with the layering of material in the subsegments being selected in such a way that the inner materials have a lower coefficient of expansion than the outer ones, so that the compressive stress resulting from the expansion of the sub-segments in the circumferential direction between the sub-segments of the inner ring assumes a predetermined stress profile.
  • the sub-segments abut one another in the circumferential direction, forming a pointed gap, with the spacing in the gap being maintained in such a way that due to the temperature gradient during operation, a frictional connection is created between the adjacent sub-segments that extends over the entire radial extent or just over the radial Sections of the sub-segments now leads to a predetermined course of the compressive stress between sub-segments.
  • the sub-segments engage in one another in the circumferential direction to form teeth, with the teeth being spaced apart in the radial direction in such a way that, due to the temperature gradient during operation, a frictional connection is created between the adjacent sub-segments that extends over the entire radial extent or just over the radial Sections of the sub-segments lead to a predetermined course of the compressive stress between sub-segments
  • the layering of material in the sub-segments is selected in such a way that the inner materials have a lower coefficient of expansion than the outer ones, so that the expansion of the sub-segments in the circumferential direction in combination with a pointed gap in the circumferential direction between abutting sub-segments, or in Combination with a toothing of interlocking sub-segments that is spaced apart in the radial direction, leads to a predetermined course of the compressive stress between sub-segments.
  • a predetermined course of the compressive stress can be a uniform radial pressure or a practically constant pressure course. This is, for example, a pressure curve that deviates by no more than 20% from the mean value of the stress over at least 80% of the area where the sub-segments abut one another.
  • the sub-segment designed as an element essentially consists of a ceramic material which, depending on its operational use, in particular during the transient load ranges of the turbomachine up to full operation, has a qualitatively and quantitatively different behavior fulfilled with regard to the stress and strain values.
  • the ceramic sub-segment is created in such a way that it has a gradual material structure, which enables different expansion and stress behavior depending on the operation.
  • the materials of the respective material structure resp.
  • the sub-segment can also consist of different sub-bodies incorporated into one another, which are each constructed from ceramic materials with different chemical and physical properties.
  • the incorporated sub-bodies to form a sub-segment can also have different material structures from one another, which result in a specific physical effect in specific operational states.
  • a particularly important behavior of such a sub-segment relates to the expansion behavior in different operating states of the turbomachine, which are in operative connection with the moving blades of the turbomachine operating there with regard to the gap size that is established.
  • the ceramic sub-segment an operation-dependent expansion behavior and a strength variability, respectively. has a safety behavior against the thermal loads, so that the operational safety of the entire turbomachine is maximized.
  • an operation-dependent expansion behavior of the ceramic element also has a positive effect on the efficiency of the turbomachine, in that, for example, blade tip leakage in the area of the stator/rotor blades can be minimized.
  • an element (partial segment) formed from ceramic materials is particularly suitable for functioning as a heat shield, in particular when the turbomachine is a gas turbine, since ceramic materials are generally very heat-resistant materials.
  • the ceramic element can also consist of just a proportion of ceramic, while the remaining proportions can consist of less heat-resistant materials. Depending on which stretch resp. If such a sub-segment has to comply with the voltage behavior, one behavior can be interpreted in favor of or to the detriment of the other behavior within permissible limits.
  • the body provided as an element ie as a sub-segment, can be produced from pressed ceramic powder by sintering, which enables a high degree of variability in the choice of material.
  • the composition of the element can be varied to affect various chemical and physical properties of the final material, including porosity, hardness, thermal conductivity, or other mechanical, electrical, thermal, and/or magnetic properties.
  • the ceramic element can also have a solid structure when viewed macroscopically, or consist of different sub-bodies which are also structured macroscopically and which, when joined together, result in a firm connection.
  • the element can also contain specific structured cavities, which can fulfill different tasks.
  • these cavities can be used for internal cooling of the ceramic or quasi-ceramic element, and this cooling can also be operated in such a way that at least its expansion behavior is dynamically influenced.
  • these cavities are also designed in such a way that they themselves provide a measure of an adapting expansion behavior. A combination of these two structures to a new final purpose is also possible.
  • the ceramic or quasi-ceramic element preferably carries an abrasion-compatible layer, which is generally designed as a sealing and wear layer opposite the rotor blades.
  • an abrasion-compatible layer which is generally designed as a sealing and wear layer opposite the rotor blades.
  • a good seal is achieved when this wear layer has properties consistent with an abradable layer. This is the case when the wear layer has indentations or Allows cavities, which cause a maximized seal between blade tip and element at least in normal operation of the turbomachine.
  • the invention intervenes here when it comes to ensuring maximized sealing by the expansion behavior of the element depending on the expansion of the rotor, respectively.
  • of the rotor blades is supported by internal material dispositions, which additionally support the described effect of the abrasion-compatible layer.
  • the inner ring on the rotor side is formed by a number of elements, which are preferably of identical shape and size and have a thickness of 3-8 cm in the radial direction.
  • the elements In the circumferential direction, the elements have, for example, an arc angle of 10-15°, as a result of which the entire ring will then consist of 24 to 36 individual sub-segments.
  • the respective ceramic or quasi-ceramic element then preferably has the shape of a trapezium or a quasi-trapezium in the radial direction (in the installed state in a section perpendicular to the axis of rotation of the turbomachine). on what then have a positive effect on the requirement for a self-supporting structure in connection with the outer ring. Irrespective of how the geometric shape of the sub-segment is taken as a basis, the circumferential surface on the rotor side formed by the sub-segments will form a coherent, circular surface for the rotor blades of the turbomachine rotating past there.
  • the inner ring formed by the elements on the rotor side can, as already explained above, consist entirely of a ceramic material.
  • compositions of up to 70% or more by weight or volume can consist of a ceramic material, and the remanence can consist of 100% depending on the predetermined strain and stress behavior of other materials whose compatibility with regard to the final properties of such an element is matched have to be.
  • the present specification often speaks of quasi-ceramic elements.
  • the described stator component can operatively extend as a ring in the axial direction of the turbomachine over all stages of the rotor blades. It is also possible to provide the inner ring consisting of the sub-segments in the axial direction only in the area of the operating rotor blades.
  • the material composition of the sub-segments is adjusted accordingly at different stages, depending on a specific expansion and strength behavior.
  • the ceramic or quasi-ceramic elements are surrounded in the radial extension by an outer metal ring, which ensures the stability of the individual elements in the composite. This stability is extremely important so that the individual elements mutate into a coherent solid body during operation.
  • these elements can have a concave or convex counter-shape, which contributes to the fact that the Positioning of these elements relative to the metal ring, especially during assembly, also result in a positive fit.
  • the ceramic or quasi-ceramic elements can also have intermediate recesses through which a cooling medium can flow as required.
  • grooves can be provided, for example, in the area of the radially running boundary surface on the side of the individual elements positioned next to one another, which on the one hand reduces the active abutment surface between two adjacent elements, but on the other hand contributes to a defined, fuller, form-fitting abutment surface between the elements leads.
  • These radially running grooves can also be used as cooling tracks, the cooling of which acts at least in the region of the elements that are adjacent to one another. This option can also be used to specifically influence the expansion behavior of the elements in certain operating states of the turbomachine.
  • the individual elements should be joined together to form a ring in which the contact surfaces of the adjacent elements form a gas-tight or almost gas-tight connection, particularly when the turbomachine is in operation.
  • the fit in the stator component between the outer ring and the inner ring formed by the sub-segments during assembly is aimed at at least one form fit, at most designed with an initially minimized frictional connection component, whereby the initial frictional connection will increase during operation, and must be designed in such a way that a maximum permissible compressive stress between the individual elements is not exceeded.
  • the ceramic used for the sub-segments can consist of zirconium oxides, aluminum oxides, magnesium oxides, with the sub-segment or Parts thereof can also be composed of different parts of different ceramics.
  • the surface on the rotor side has a compressive stress of greater than zero MPa to 500 MPa for all operating temperatures due to the thickness ratios, the temperature dependence of the thermal expansion coefficients and the stiffness of all materials, with which the sub-segment covers the entire operative load range of the turbomachine can cover.
  • the compressive stress of the sub-segments is preferably limited to up to 50 MPa when they are first installed, which on the one hand leads to a snug fit and on the other hand there is a sufficiently large stress reserve for full operation.
  • the materials are layered in such a way that the materials on the radial inside of the inner ring have the smallest coefficient of thermal expansion and this increases towards the outside.
  • the ratios of the coefficients of expansion are selected from the inside to the outside in such a way that the product of the coefficient of expansion and the temperature increase from cold installation and warm operation remains constant or practically constant for all radial positions. Deviations from a constant value are to be understood as practically constant, for example, which lead to no more than 20% difference between local compressive stresses in the circumferential direction compared to an average compressive stress in the form fit. Edge areas or local defects in the form fit can naturally lead to greater deviations.
  • especially for rings with a large ratio of ring height to ring diameter e.g.
  • the ratios of the expansion coefficients from the inside to the outside are selected in such a way that the product of the expansion coefficient, circumference and Temperature increase from cold installation and warm operation remains constant or practically constant for all radial positions.
  • the adjacent sub-segments can also have a toothed surface in relation to one another, which in the installed state leads to a labyrinth-like seal in the radial direction.
  • the size of the gap in the radial direction of the sub-segments can therefore decrease, in which case the size of the gap, i.e. the distance between the adjacent sub-segments, is superimposed in terms of extension, particularly when the ceramic or quasi-ceramic element consists of different layers or parts of different material composition, for example in terms of porosity, particle size, chemical composition, etc.
  • FIG. 1 shows a schematic representation of a metal ring 10, which forms part of the stator as a ring in the area of the individual partial elements 20, also called partial segments.
  • this outer ring 10 can be divided once or several times 11 for a better integration of the ring-shaped mounted partial elements 20 .
  • a continuous outer ring 10 is also not excluded. However, this requires that the installation of the sub-segments 20 is ensured by precautions when inserting the last sub-element.
  • the outer ring 10 consists of a metallic material, while the sub-segments 20 consist at least partially of ceramic materials.
  • the outer rings 10 can be arranged in such a way that they are only operatively connected to one row of moving blades.
  • the compressive stress of the sub-segments is preferably limited to a maximum of 50 MPa during initial installation, which on the one hand leads to a snug fit and on the other hand there is a sufficiently large upward stress reserve for full operation.
  • the surface on the rotor side has a compressive stress of greater than zero MPa up to 500 MPa for all operating temperatures due to the thickness ratios, the temperature dependence of the thermal expansion coefficients and the stiffness of all materials, with which the sub-segment covers the entire operative load range of the Flow machine can cover.
  • figure 2 shows a schematic representation of a section of the stator component in the area of the sub-segment 20.
  • the in figure 2 The element shown, made of a ceramic or quasi-ceramic material, forms part of a coherent inner ring, which 1 particularly pronounced.
  • the sub-segment 20 is shown here in terms of a unitary body.
  • This unitary body can consist of a uniform material (not part of the claimed invention) or of different materials, e.g. B. be joined by sintering to form a monolithic body.
  • the body thus sintered can then have desired and predefined gradually changing chemical and physical properties.
  • this is not mandatory in itself, because the sub-segment can also consist of a number of sub-bodies, at least in the radial direction, which can also consist of different materials with different material structures, with the ultimate purpose that the stress and strain behavior of the inner ring during operation meet predetermined values. Accordingly, such variations can also easily affect the sub-segment in the axial direction.
  • the entire partial segment 20 must consist integrally of ceramic materials: Configurations can be provided without further ado, in which the incorporation of metallic parts can be useful precisely for the predetermination of the stress and strain behavior.
  • the geometric configuration of the partial segment 20 has a polygonal shape at least in the radial direction, which deviates from a purely rectangular shape at the corners. This is preferably to be provided insofar as the stress-critical edges 22 of the sub-segment 20 experience a significant relief in the installed state.
  • sealing elements are provided between the outer diameter of the outer ring and the inner diameter of the inner ring, which generally prevent a radial flow of the working medium from the main flow channel into the stator.
  • sealing elements are components of positioning elements 23 acting on the sub-segment 20, which ensure that the expansions between the sub-segments and the outer ring can be absorbed at least axially. Since the sealing element is then part of this dynamic positioning element 23, the active effect of the sealing element during operation is maximized.
  • each sub-segment On both sides thereof and in the circumferential direction.
  • the rotor side surface of the Sub-segment has a layer 21 that can be abraded, which in certain operating configurations of the turbomachine contributes to the active removal of this layer by the tip of the moving blade 30 rotating past there, minimizing the gap between the sub-segment and blade tip and thus minimizing the blade tip leakage.
  • the outer ring 10 is also penetrated by a feed channel 24 via which a coolant is fed to the sub-segments 20 .
  • Figures 3 and 4 show an alternative when merging adjacent sub-segments, in the sense that no direct positive or non-positive connection is created here during installation, but the sub-segments abut each other more or less loosely in the circumferential direction, forming a pointed gap 29 .
  • This gap 25 tapers in the radial direction, the angle ⁇ being between 5° and 30°.
  • the basic idea behind this design is the fact that the expansions decrease in the radial direction as a result of the temperature profile, so the spacing on the inside must be greater than on the outside.
  • the gap formed can be as in figure 3 be formed over the entire radial extension of the sub-segment. However, it is also conceivable that the gap is only present over part of the radial extent.
  • the gap is preferably formed in the rotor-side area of the sub-segment.
  • the gap can be straight or curved.
  • the spacing is maintained in such a way that, during operation, a frictional connection is created between the adjacent sub-segments, which leads to a predetermined course of the compressive stress over the entire radial extent or also only over radial sections of the sub-segments.
  • the compressive stress will be uniform or approximately uniform.
  • figure 4 as a view of the circular surface of the inner ring then shows how a toothing of the two adjacent sub-segments 20 can be carried out by creating a labyrinth course that prevents the flow of hot working gases between the sub-segments.
  • the spacing is kept so that during operation between the adjacent sub-segments creates a frictional connection, which now fails approximately uniformly over the entire radial extent or even over radial sections of the sub-segments by just one initial different gap size is provided, as the arrows at X and Y want to characterize.
  • With a labyrinth design there does not have to be a force fit everywhere, since the form fit of the labyrinth itself provides the seal.
  • the sub-segment 20 is composed of different materials with different expansion coefficients in the radial direction, this must be taken into account when designing the gap size 28 so that the desired frictional connection is achieved during operation along the adjacent sub-segments.
  • this expansion behavior of the sub-segments in the radial direction can also be significantly influenced by means of a differentiated structure, this in correlation to the different temperatures that naturally prevail in the radial direction of the sub-segment. Even with such an installation, the compressive stress during operation should not exceed 500 MPa.
  • Figure 5a and 6 show a possible cooling configuration of the sub-segments starting from the coolant supply channel 24.
  • the sub-segment 20 then has, in the circumferential direction, an inner chamber 25 that is in operative connection with the supply channel 24 and is connected across all sub-segments 20, from which angled flow channels 26 branch off, which provide integral cooling of the sub-segment.
  • the cooling medium is then conducted to the outside via the continuation 27 provided in each flow channel 26 .
  • Figure 5a shows that the chamber 25a is only available for a partial segment 20, so that a corresponding number of supply channels 24 must be provided.
  • grooves can also be provided in the area of the radially running boundary surface on the side of the individual sub-segments 20 positioned next to one another, which on the one hand form the active abutment surface between two adjacent Reduce elements, but on the other hand contribute to the fact that it leads to a defined, richer, form-fitting abutment surface between the elements.
  • These grooves which run radially and are not shown in more detail in the figures, can also be used as cooling paths, the cooling of which acts at least in the region of the sub-segments that adjoin one another. This option can also be used to specifically influence the expansion behavior of the sub-segments relative to one another in certain operating states of the turbomachine.
  • the individual sub-segments should be able to be joined together to form a ring in such a way that the abutting surfaces of the adjacent elements form a gas-tight connection, particularly during operation of the turbomachine, and also lead to a compressive stress that does not exceed 500 MPa.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Iron Core Of Rotating Electric Machines (AREA)
EP13702011.1A 2012-01-26 2013-01-25 Statorbauteil mit segmentiertem innenring für eine strömungsmaschine Active EP2807344B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP13702011.1A EP2807344B1 (de) 2012-01-26 2013-01-25 Statorbauteil mit segmentiertem innenring für eine strömungsmaschine

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP12152718 2012-01-26
EP13702011.1A EP2807344B1 (de) 2012-01-26 2013-01-25 Statorbauteil mit segmentiertem innenring für eine strömungsmaschine
PCT/EP2013/051508 WO2013110792A1 (de) 2012-01-26 2013-01-25 Statorbauteil mit segmentiertem innenring für eine strömungsmaschine

Publications (2)

Publication Number Publication Date
EP2807344A1 EP2807344A1 (de) 2014-12-03
EP2807344B1 true EP2807344B1 (de) 2022-11-30

Family

ID=47630330

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13702011.1A Active EP2807344B1 (de) 2012-01-26 2013-01-25 Statorbauteil mit segmentiertem innenring für eine strömungsmaschine

Country Status (8)

Country Link
US (1) US9702262B2 (ja)
EP (1) EP2807344B1 (ja)
JP (1) JP5920856B2 (ja)
KR (1) KR20150002595A (ja)
CN (1) CN104066934B (ja)
CA (1) CA2860928C (ja)
RU (1) RU2615292C2 (ja)
WO (1) WO2013110792A1 (ja)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102015201782A1 (de) * 2015-02-02 2016-08-18 MTU Aero Engines AG Leitschaufelring für eine Strömungsmaschine
CA2924866A1 (en) * 2015-04-29 2016-10-29 Daniel K. Vetters Composite keystoned blade track
EP3109520B1 (de) * 2015-06-24 2020-05-06 MTU Aero Engines GmbH Dichtungsträger, leitschaufelkranz und strömungsmaschine
US10358932B2 (en) * 2015-06-29 2019-07-23 United Technologies Corporation Segmented non-contact seal assembly for rotational equipment
US10287920B2 (en) * 2015-11-24 2019-05-14 General Electric Company System of supporting turbine diffuser
EP3290642A1 (de) * 2016-08-31 2018-03-07 Siemens Aktiengesellschaft Ringsegment für eine turbine und anordnung zur äusseren be-grenzung eines strömungspfades einer turbine
DE102017209682A1 (de) * 2017-06-08 2018-12-13 MTU Aero Engines AG Axial geteilter Turbomaschinen-Innenring
US10876429B2 (en) 2019-03-21 2020-12-29 Pratt & Whitney Canada Corp. Shroud segment assembly intersegment end gaps control
US11015485B2 (en) * 2019-04-17 2021-05-25 Rolls-Royce Corporation Seal ring for turbine shroud in gas turbine engine with arch-style support
JP2023042786A (ja) * 2021-09-15 2023-03-28 東芝エネルギーシステムズ株式会社 タービン段落シール機構およびタービン段落シール機構の製造方法

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4679981A (en) * 1984-11-22 1987-07-14 S.N.E.C.M.A. Turbine ring for a gas turbine engine
US5374161A (en) * 1993-12-13 1994-12-20 United Technologies Corporation Blade outer air seal cooling enhanced with inter-segment film slot
WO2009126191A2 (en) * 2008-04-11 2009-10-15 Siemens Energy, Inc. Sealing arrangement for turbine engine having ceramic components
EP2236763A2 (en) * 2009-03-12 2010-10-06 General Electric Company Turbine Engine Shroud Ring

Family Cites Families (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE792224A (fr) * 1971-12-01 1973-03-30 Penny Robert N Element composite long ayant un coefficient de dilatation lineaire effectif predetermine
US4289447A (en) * 1979-10-12 1981-09-15 General Electric Company Metal-ceramic turbine shroud and method of making the same
DE3019920C2 (de) * 1980-05-24 1982-12-30 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Einrichtung zur äußeren Ummantelung der Laufschaufeln von Axialturbinen für Gasturbinentriebwerke
FR2540939A1 (fr) * 1983-02-10 1984-08-17 Snecma Anneau d'etancheite pour un rotor de turbine d'une turbomachine et installation de turbomachine munie de tels anneaux
US4650395A (en) * 1984-12-21 1987-03-17 United Technologies Corporation Coolable seal segment for a rotary machine
JPS6355308A (ja) * 1986-08-27 1988-03-09 Hitachi Ltd ガスタ−ビンケ−シング構造
SU1749494A1 (ru) * 1988-07-15 1992-07-23 Московский авиационный институт им.Серго Орджоникидзе Турбина с устройством дл уплотнени радиального зазора
JPH09264104A (ja) * 1996-03-27 1997-10-07 Ishikawajima Harima Heavy Ind Co Ltd セラミック製シュラウドリング
JP2002213207A (ja) 2001-01-15 2002-07-31 Mitsubishi Heavy Ind Ltd ガスタービン分割環
US6702550B2 (en) * 2002-01-16 2004-03-09 General Electric Company Turbine shroud segment and shroud assembly
US7128522B2 (en) * 2003-10-28 2006-10-31 Pratt & Whitney Canada Corp. Leakage control in a gas turbine engine
EP1764479A1 (de) * 2005-09-15 2007-03-21 ALSTOM Technology Ltd Gekoppelte Deckplatten für eine Schaufelreihe einer Strömungsmaschine
US7534086B2 (en) * 2006-05-05 2009-05-19 Siemens Energy, Inc. Multi-layer ring seal
US7665960B2 (en) * 2006-08-10 2010-02-23 United Technologies Corporation Turbine shroud thermal distortion control
US7771160B2 (en) * 2006-08-10 2010-08-10 United Technologies Corporation Ceramic shroud assembly
EP1890010B1 (en) * 2006-08-10 2016-05-04 United Technologies Corporation Ceramic turbine shroud assembly
FR2913718B1 (fr) * 2007-03-15 2009-06-05 Snecma Propulsion Solide Sa Ensemble d'anneau de turbine pour turbine a gaz
JP2008309051A (ja) * 2007-06-14 2008-12-25 Ihi Corp タービンシュラウドの冷却構造
US8206092B2 (en) * 2007-12-05 2012-06-26 United Technologies Corp. Gas turbine engines and related systems involving blade outer air seals
US20100061847A1 (en) * 2008-09-09 2010-03-11 General Electric Company Steam turbine part including ceramic matrix composite (cmc)
JP5495941B2 (ja) * 2010-05-21 2014-05-21 三菱重工業株式会社 タービン分割環、これを備えたガスタービンおよびこれを備えた発電プラント
US20120292856A1 (en) * 2011-05-16 2012-11-22 United Technologies Corporation Blade outer seal for a gas turbine engine having non-parallel segment confronting faces

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4679981A (en) * 1984-11-22 1987-07-14 S.N.E.C.M.A. Turbine ring for a gas turbine engine
US5374161A (en) * 1993-12-13 1994-12-20 United Technologies Corporation Blade outer air seal cooling enhanced with inter-segment film slot
WO2009126191A2 (en) * 2008-04-11 2009-10-15 Siemens Energy, Inc. Sealing arrangement for turbine engine having ceramic components
EP2236763A2 (en) * 2009-03-12 2010-10-06 General Electric Company Turbine Engine Shroud Ring

Also Published As

Publication number Publication date
JP5920856B2 (ja) 2016-05-18
JP2015505588A (ja) 2015-02-23
CN104066934B (zh) 2016-12-28
KR20150002595A (ko) 2015-01-07
CN104066934A (zh) 2014-09-24
EP2807344A1 (de) 2014-12-03
US9702262B2 (en) 2017-07-11
RU2014134721A (ru) 2016-03-20
RU2615292C2 (ru) 2017-04-04
CA2860928C (en) 2016-10-18
CA2860928A1 (en) 2013-08-01
WO2013110792A1 (de) 2013-08-01
US20140328672A1 (en) 2014-11-06

Similar Documents

Publication Publication Date Title
EP2807344B1 (de) Statorbauteil mit segmentiertem innenring für eine strömungsmaschine
DE3305170C2 (de) Turbomaschinengehäuse
EP0355649B1 (de) Dichtungseinrichtung
EP0227991B1 (de) Aerodynamisches Gleitlager
EP2796668B1 (de) Gehäuseabschnitt einer Turbomaschinenverdichter- oder Turbomaschinenturbinenstufe
EP2918913B1 (de) Brennkammer einer Gasturbine mit äusserer und innerer Brennkammerwand
EP0217838B1 (de) Strömungsmaschine mit mitteln zur kontrolle des radialspaltes
EP2647795A1 (de) Dichtungssystem für eine Strömungsmaschine
DE102014219552A1 (de) Leitschaufelverstellvorrichtung einer Gasturbine
DE3018621C2 (de) Außengehäuse für Axialverdichter oder -turbinen von Strömungsmaschinen, insbesondere Gasturbinentriebwerken
EP2884055A1 (de) Verstellbare leitschaufeln mit kegelstumpf in einer lageranordnung
EP2344723B1 (de) Gasturbine mit dichtplatten an der turbinenscheibe
EP1653049B1 (de) Leitschaufelring einer Strömungsmaschine und zugehöriges Modifikationsverfahren
EP2342425B1 (de) Gasturbine mit sicherungsplatte zwischen schaufelfuss und scheibe
EP2411631B1 (de) Dichtplatte und Laufschaufelsystem
WO2009109430A1 (de) Dichtungsanordnung und gasturbine
EP2984295A1 (de) Dichtringsegment für einen stator einer turbine
EP2474744A1 (de) Ringförmiger Strömungskanal für einen Axialverdichter
EP1507106A1 (de) Rotationsdichtung
EP2173974B1 (de) Hitzeschildsegment für einen stator einer gasturbine
EP3312388B1 (de) Rotorteil, zugehörigeverdichter, turbine und herstellungsverfahren
EP1960636A1 (de) Strömungsmaschine
WO2009059580A1 (de) Gasturbinenbauteil und verdichter mit einem solchen bauteil
EP3034944A1 (de) Gasturbinenbrennkammer mit veränderter wandstärke
EP2980481A1 (de) Fluggasturbine mit einer dichtung zur abdichtung einer zündkerze an der brennkammerwand einer gasturbine

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

17P Request for examination filed

Effective date: 20140814

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

DAX Request for extension of the european patent (deleted)
RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH

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

Owner name: ANSALDO ENERGIA IP UK LIMITED

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: 20190715

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

Free format text: STATUS: EXAMINATION IS IN PROGRESS

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

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

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20220623

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: CH

Ref legal event code: EP

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1534840

Country of ref document: AT

Kind code of ref document: T

Effective date: 20221215

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: DE

Ref legal event code: R096

Ref document number: 502013016301

Country of ref document: DE

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG9D

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20221130

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: 20221130

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: 20230331

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: 20230228

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: 20221130

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: 20221130

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: 20221130

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

Ref country code: RS

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

Effective date: 20221130

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: 20221130

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: 20221130

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: 20230330

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: 20221130

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: 20230301

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

Ref country code: IT

Payment date: 20230228

Year of fee payment: 11

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: 20221130

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: 20221130

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: 20221130

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: 20221130

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: 20221130

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: 20221130

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

Ref country code: SK

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

Effective date: 20221130

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: 20221130

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502013016301

Country of ref document: DE

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: 20230125

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20230131

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: LI

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

Effective date: 20230131

Ref country code: CH

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

Effective date: 20230131

26N No opposition filed

Effective date: 20230831

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: 20221130

Ref country code: FR

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

Effective date: 20230130

Ref country code: BE

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

Effective date: 20230131

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: 20230125

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 1534840

Country of ref document: AT

Kind code of ref document: T

Effective date: 20230125

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

Ref country code: AT

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

Effective date: 20230125

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

Ref country code: AT

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

Effective date: 20230125

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

Ref country code: DE

Payment date: 20240216

Year of fee payment: 12

Ref country code: GB

Payment date: 20240222

Year of fee payment: 12