EP2604797B1 - Rotor blade with a rib assembly with an abrasive coating - Google Patents
Rotor blade with a rib assembly with an abrasive coating Download PDFInfo
- Publication number
- EP2604797B1 EP2604797B1 EP11193177.0A EP11193177A EP2604797B1 EP 2604797 B1 EP2604797 B1 EP 2604797B1 EP 11193177 A EP11193177 A EP 11193177A EP 2604797 B1 EP2604797 B1 EP 2604797B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- ribs
- rotor blade
- rib
- coating
- radial
- 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
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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/288—Protective coatings for blades
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C24/00—Coating starting from inorganic powder
- C23C24/02—Coating starting from inorganic powder by application of pressure only
- C23C24/04—Impact or kinetic deposition of particles
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/01—Selective coating, e.g. pattern coating, without pre-treatment of the material to be coated
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/30—Manufacture with deposition of material
- F05D2230/31—Layer deposition
- F05D2230/311—Layer deposition by torch or flame spraying
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/30—Manufacture with deposition of material
- F05D2230/31—Layer deposition
- F05D2230/312—Layer deposition by plasma spraying
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
- F05D2240/126—Baffles or ribs
Definitions
- the present invention relates to a rotor blade for a compressor or turbine stage of a gas turbine, with a radially outer rib arrangement arranged on a shroud of the rotor blade and having at least two ribs directed radially outwards.
- the present invention further relates to a turbomachine, in particular a gas turbine, with at least one such blade.
- the object of the present invention is to provide an improved turbomachine.
- a rotor blade with the features of claim 1 is proposed, which can be used in a compressor and / or turbine stage of a gas turbine.
- Claim 6 provides a turbomachine, in particular a gas turbine, with a rotor blade arrangement with such rotor blades under protection. Preferred developments are the subject of the dependent claims.
- One aspect of the present invention is based on the idea of not providing a surface or not only a harder surface but (also) a larger surface by means of a rib coating.
- a rotor blade has a radially outer rib arrangement arranged on a shroud of the rotor blade.
- the rib arrangement has at least two radially outwardly directed ribs.
- the ribs have at least on the two side surfaces a coating on. These coatings are connected to one another via their radially outer end faces of the respective ribs. The thickness of the coating increases, in relation to a cut transverse to the rib, radially outwards on the two radial side surfaces of the rib.
- the rotor blade has a rib arrangement with a plurality of ribs arranged one behind the other in the axial direction.
- the axial direction refers in particular to a coordinate direction that is aligned with an axis of rotation of the rotor blade or turbomachine, in particular a gas turbine, a direction that extends perpendicularly from the axis of rotation as a radial direction and a direction that is perpendicular to the axis of rotation as the circumferential direction and extends perpendicular to the radial direction, in particular in the direction of rotation of the rotor blade or turbomachine, in particular gas turbine.
- a coating is arranged on at least two or more, in particular adjacent, and preferably on all the ribs of the rib arrangement. This is preferably made of metal, plastic and / or ceramic. In a preferred embodiment, the coating has a greater hardness than the rib itself. A hardness according to Vickers, Rockwell, Brinell or a similar test protocol is referred to in the present case as hardness.
- coatings of the rib arrangement each have an outer contour in a meridian section, which contour extends outward in the radial direction, ie expanded with increasing radial distance from the axis of rotation, axially or in the axial direction.
- a meridian section is understood to mean, in particular, a cross section which contains the axial direction and the radial direction.
- an outer contour can expand monotonically, in particular strictly monotonously, in the radial direction to the outside. In the present case, this is understood in particular to mean that a distance in the axial direction between the two outer flanks of the outer contour always remains at least essentially (monotonically) or even always increases (strictly monotonous) with increasing radial distance from the axis of rotation. Equally, however, outer contours are also included, the outer flanks of which approach each other in limited radial areas.
- General is therefore an outer contour that extends outward in the radial direction, in particular an outer contour with two mutually opposite outer flanks, the distance of which in the axial direction is smaller at a first, smaller distance from the axis of rotation than at a second, larger distance from the axis of rotation,
- a gap between mutually facing flanks of adjacent coatings on adjacent ribs of the rib arrangement corresponds at most to an axial width of a radially outer end face of one of the two adjacent ribs.
- the axial width refers in particular to the distance between a front and rear edge in the axial direction of a radially outer end face of a rib. Due to the preferred limitation of the gap to the front axial width of a rib, the leakage in the space between adjacent ribs can be reduced to a level that is not critical for the efficiency.
- a gap between mutually facing flanks of adjacent coatings of adjacent ribs of the rib arrangement corresponds to at most 75% and preferably at most 50% of such an axial width.
- smaller gaps between coatings are preferred, with a gap advantageously having a certain minimum dimension, which in particular can be at least 20% of an axial width of a radially outer end face of one of the two adjacent ribs, in order to prevent the coating from flaking off.
- the ribs of the rib arrangement are inclined in the circumferential direction by an angle which is not equal to 0 ° and less than 10 ° in amount, in particular less than 5 ° and preferably less than 3 °.
- two or more, in particular all, of the ribs of the rib arrangement have outer end faces in the radial direction which, at least essentially, lie at the same radial height. Starting from these end faces, the ribs extend inward in the radial direction at different depths, i.e. are of different heights in the radial direction. On the one hand, this enables the formation of small gaps between the ribs and, on the other hand, an adaptation to blades with varying radial heights.
- outer end faces of two or more, in particular all, of the ribs of the rib arrangement can have a different radial height, in particular — at least essentially — lie on a virtual conical surface.
- two or more, in particular all, ribs of the rib arrangement can have different heights in the radial direction.
- the rib arrangement is arranged on a cover band of the moving blade.
- a shroud is understood to mean, in particular, a flange which extends in the axial and circumferential directions and, in a preferred development, bears in a form-fitting manner on shrouds in the circumferential direction of adjacent blades.
- the cover band can be inclined in the axial direction in order to support the ribs of different heights explained above.
- the coating can be carried out by means of a method for coating one or, preferably, in particular in time in parallel or in succession, a plurality of ribs of a radially outer rib arrangement of a rotor blade, which is particularly suitable for coating a rotor blade according to the aspect explained above.
- a coating material can be sprayed onto the fin arrangement from at least two opposite spray directions, in particular plasma sprayed, flame sprayed, in particular high speed flame sprayed, detonation sprayed, cold gas sprayed, arc sprayed, and / or laser sprayed.
- plasma spraying is understood in particular to mean that, for example in a plasma torch, an electric arc is generated between the anode (s) and cathode (s) by a voltage, and gas or gas mixture is passed through the electric arc and thereby ionized. The dissociation or subsequent ionization generates a highly heated, electrically conductive gas from positive ions and Electrons.
- Powdery coating material can be injected into this generated plasma jet, which is melted by the high plasma temperature.
- the plasma stream entrains the powder particles and hurls them onto the rotor blade to be coated.
- the plasma coating is preferably carried out in a normal atmosphere, inert atmosphere, in vacuum or under water.
- the spray directions can be inclined in opposite directions, but with the same amount, against the radial direction, preferably by an spray angle which is greater than 20 °, in particular greater than 40 °, and / or less than 70 °, in particular less than 50 °.
- the coating material can be sprayed on in succession or simultaneously from the two spray directions.
- One or more coatings can be reworked, simultaneously or in succession, after the coating material has been sprayed on.
- a radially outer end face of the coatings can, for example, be ground, polished or reworked in some other way.
- Fig. 3 shows a meridian section of a gas turbine stage according to an embodiment of the present invention with a moving blade 5, on the inclined cover band 1 of which a rib arrangement with five ribs 2 arranged one behind the other in the axial direction is arranged.
- a honeycomb-like sealing surface 4 is arranged radially opposite the rib arrangement 2.
- the honeycomb-like sealing surface 4 instead of the honeycomb-like sealing surface 4 'with one or two (dashed) counter rib (s) is provided.
- This coating 3 is applied by sequential plasma spraying first in a first spray direction S 1 , and then in an opposite or mirror-symmetrical second spray direction S 2 , as in FIG Fig. 2 indicated by arrows, applied.
- an essentially flat end face of the coatings 3 can be represented.
- the coating in particular its radially outer end face (top in Fig. 2 ) post-processed, in particular ground, after spraying.
- the ribs 2 are inclined against the circumferential direction U by an angle ⁇ , which is 2 ° in the exemplary embodiment.
- ⁇ which is 2 ° in the exemplary embodiment.
- the circumferential direction U and a radial direction R are indicated in the figures, wherein 2 to 4 one section horizontally to the plane of the drawing Fig. 1 can represent, so an axial direction in all figures runs horizontally from left to right.
- the spray layer is not shown.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Mechanical Engineering (AREA)
- Materials Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Coating By Spraying Or Casting (AREA)
Description
Die vorliegende Erfindung betrifft eine Laufschaufel für eine Verdichter- oder Turbinenstufe einer Gasturbine, mit einer radial äußeren, auf einem Deckband der Laufschaufel angeordneten, wenigstens zwei nach radial außen gerichteten Rippen aufweisenden Rippenanordnung. Die vorliegende Erfindung betrifft weiterhin eine Turbomaschine, insbesondere eine Gasturbine, mit wenigstens einer solchen Laufschaufel.The present invention relates to a rotor blade for a compressor or turbine stage of a gas turbine, with a radially outer rib arrangement arranged on a shroud of the rotor blade and having at least two ribs directed radially outwards. The present invention further relates to a turbomachine, in particular a gas turbine, with at least one such blade.
Aus der
Aus der
Aufgabe der vorliegenden Erfindung ist es, eine verbesserte Turbomaschine zur Verfügung zu stellen.The object of the present invention is to provide an improved turbomachine.
Zur Lösung dieser Aufgabe wird eine Laufschaufel mit den Merkmalen des Anspruchs 1 vorgeschlagen, die in einer Verdichter - und/oder Turbinenstufe einer Gasturbine verwendet werden kann. Anspruch 6 stellt eine Turbomaschine, insbesondere eine Gasturbine, mit einer Laufschaufelanordnung mit solchen Laufschaufeln unter Schutz. Bevorzugte Weiterbildungen sind Gegenstand der Unteransprüche.To solve this problem, a rotor blade with the features of
Ein Aspekt der vorliegenden Erfindung beruht auf der Idee, durch eine Rippenbeschichtung nicht bzw, nicht nur eine härtere, sondern (auch) eine größere Oberfläche zur Verfügung zu stellen.One aspect of the present invention is based on the idea of not providing a surface or not only a harder surface but (also) a larger surface by means of a rib coating.
Hierzu weist eine Laufschaufel eine radial äußere, auf einem Deckband der Laufschaufel angeordnete Rippenanordnung auf. Die Rippenanordnung weist wenigstens zwei nach radial außen gerichtete Rippen auf. Die Rippen weisen wenigstens an den jeweils beiden Seitenflächen eine Beschichtung auf. Diese Beschichtungen sind über ihre radial äußeren Stirnflächen der jeweiligen Rippen miteinander verbunden. Die Dicke der Beschichtung nimmt, bezogen auf einen Schnitt quer zur Rippe, auf den beiden radialen Seitenflächen der Rippe radial nach außen zu.For this purpose, a rotor blade has a radially outer rib arrangement arranged on a shroud of the rotor blade. The rib arrangement has at least two radially outwardly directed ribs. The ribs have at least on the two side surfaces a coating on. These coatings are connected to one another via their radially outer end faces of the respective ribs. The thickness of the coating increases, in relation to a cut transverse to the rib, radially outwards on the two radial side surfaces of the rib.
Die Laufschaufel weist eine Rippenanordnung mit mehreren, in Axialrichtung hintereinander angeordneten Rippen auf. Als Axialrichtung wird vorliegend insbesondere eine Koordinatenrichtung bezeichnet, die mit einer Drehachse der Laufschaufel bzw. Turbomaschine, insbesondere Gasturbine, fluchtet, als Radialrichtung entsprechend eine Richtung, die sich senkrecht von der Drehachse weg erstreckt, als Umfangsrichtung eine Richtung, welche sich senkrecht zu der Drehachse und senkrecht zur Radialrichtung, insbesondere in Drehrichtung der Laufschaufel bzw. Turbomaschine, insbesondere Gasturbine, erstreckt.The rotor blade has a rib arrangement with a plurality of ribs arranged one behind the other in the axial direction. In the present case, the axial direction refers in particular to a coordinate direction that is aligned with an axis of rotation of the rotor blade or turbomachine, in particular a gas turbine, a direction that extends perpendicularly from the axis of rotation as a radial direction and a direction that is perpendicular to the axis of rotation as the circumferential direction and extends perpendicular to the radial direction, in particular in the direction of rotation of the rotor blade or turbomachine, in particular gas turbine.
Auf wenigstens zwei oder mehr, insbesondere benachbarten, und bevorzugt auf allen Rippen der Rippenanordnung ist jeweils eine Beschichtung angeordnet. Diese ist vorzugsweise aus Metall, Kunststoff und/oder Keramik hergestellt. Die Beschichtung weist in einer bevorzugten Ausführung eine größere Härte auf als die Rippe selber. Als Härte wird vorliegend insbesondere eine Härte nach Vickers, Rockwell, Brinell oder einem ähnlichen Testprotokoll bezeichnet.A coating is arranged on at least two or more, in particular adjacent, and preferably on all the ribs of the rib arrangement. This is preferably made of metal, plastic and / or ceramic. In a preferred embodiment, the coating has a greater hardness than the rib itself. A hardness according to Vickers, Rockwell, Brinell or a similar test protocol is referred to in the present case as hardness.
Um durch diese Beschichtung(en) eine größere Oberfläche zur Verfügung zu stellen und so insbesondere die Dichtwirkung und somit den Wirkungsgrad zu erhöhen, weisen mehrere, vorzugsweise alle Beschichtungen der Rippenanordnung in einem Meridianschnitt jeweils eine Außenkontur auf, welche sich in radialer Richtung nach außen, d.h. mit zunehmendem radialen Abstand von der Drehachse, axial bzw. in Axialrichtung erweitert.In order to provide a larger surface area by means of this coating (s) and thus in particular to increase the sealing effect and thus the efficiency, several, preferably all, coatings of the rib arrangement each have an outer contour in a meridian section, which contour extends outward in the radial direction, ie expanded with increasing radial distance from the axis of rotation, axially or in the axial direction.
Unter einem Meridianschnitt wird vorliegend insbesondere ein Querschnitt verstanden, welcher die Axialrichtung und die Radialrichtung enthält. Eine Außenkontur kann sich in radialer Richtung nach außen in einer bevorzugten Ausführung monoton, insbesondere streng monoton, erweitern. Hierunter wird vorliegend insbesondere verstanden, dass ein Abstand in Axialrichtung zwischen den beiden Außenflanken der Außenkontur mit wachsendem radialen Abstand zur Drehachse, wenigstens im Wesentlichen, stets wenigstens gleich bleibt (monoton) oder sogar stets zunimmt (streng monoton). Gleichermaßen sind jedoch auch Außenkonturen umfasst, deren Außenflanken sich in begrenzten radialen Bereichen einander nähern. Allgemein wird daher unter einer Außenkontur, welche sich in radialer Richtung nach außen erweitert, insbesondere eine Außenkontur mit zwei einander gegenüberliegenden Außenflanken verstanden, deren Abstand in axialer Richtung in einem ersten, geringeren Abstand zur Drehachse kleiner ist als in einem zweiten, größeren Abstand zur Drehachse,In the present case, a meridian section is understood to mean, in particular, a cross section which contains the axial direction and the radial direction. In a preferred embodiment, an outer contour can expand monotonically, in particular strictly monotonously, in the radial direction to the outside. In the present case, this is understood in particular to mean that a distance in the axial direction between the two outer flanks of the outer contour always remains at least essentially (monotonically) or even always increases (strictly monotonous) with increasing radial distance from the axis of rotation. Equally, however, outer contours are also included, the outer flanks of which approach each other in limited radial areas. General is therefore an outer contour that extends outward in the radial direction, in particular an outer contour with two mutually opposite outer flanks, the distance of which in the axial direction is smaller at a first, smaller distance from the axis of rotation than at a second, larger distance from the axis of rotation,
Infolge einer solchen radial nach außen zunehmenden Außenkontur nähert sich die Außenflanke der Beschichtung einer benachbarten Rippe oder Beschichtung in Axialrichtung gesehen an, so dass sich ein Axialspalt zwischen Beschichtung und benachbarter Rippe oder Beschichtung verringert. Hierdurch wird radial außen eine größere Oberfläche zur Verfügung gestellt und so eine Leckage in die Zwischenräume zwischen benachbarten Rippen reduziert.As a result of such an outer contour increasing radially outwards, the outer flank of the coating approaches an adjacent rib or coating as seen in the axial direction, so that an axial gap between the coating and the adjacent rib or coating is reduced. As a result, a larger surface is made available radially on the outside and leakage into the spaces between adjacent ribs is reduced.
In einer bevorzugten Ausführung entspricht ein Spalt zwischen einander zugewandten Flanken benachbarter Beschichtungen benachbarter Rippen der Rippenanordnung höchstens einer Axialbreite einer radial äußeren Stirnseite einer der beiden benachbarten Rippen. Als Axialbreite wird vorliegend insbesondere der Abstand zwischen einer in Axialrichtung vorderen und hinteren Kante einer radial äußeren Stirnseite einer Rippe bezeichnet. Durch die bevorzugte Limitierung des Spaltes auf die stirnseitige Axialbreite einer Rippe kann die Leckage in den Zwischenraum zwischen benachbarten Rippen auf ein für den Wirkungsgrad unkritisches Maß gesenkt werden.In a preferred embodiment, a gap between mutually facing flanks of adjacent coatings on adjacent ribs of the rib arrangement corresponds at most to an axial width of a radially outer end face of one of the two adjacent ribs. In the present case, the axial width refers in particular to the distance between a front and rear edge in the axial direction of a radially outer end face of a rib. Due to the preferred limitation of the gap to the front axial width of a rib, the leakage in the space between adjacent ribs can be reduced to a level that is not critical for the efficiency.
In einer bevorzugten Weiterbildung entspricht ein Spalt zwischen einander zugewandten Flanken benachbarter Beschichtungen benachbarter Rippen der Rippenanordnung höchstens 75% und vorzugsweise höchstens 50% einer solchen Axialbreite. Allgemein sind kleinere Spalte zwischen Beschichtungen bevorzugt, wobei ein Spalt vorteilhafterweise ein gewisses Mindestmaß, das insbesondere wenigstens 20% einer Axialbreite einer radial äußeren Stirnseite einer der beiden benachbarten Rippen betragen kann, aufweist, um ein Abplatzen der Beschichtung zu vermeiden.In a preferred development, a gap between mutually facing flanks of adjacent coatings of adjacent ribs of the rib arrangement corresponds to at most 75% and preferably at most 50% of such an axial width. In general, smaller gaps between coatings are preferred, with a gap advantageously having a certain minimum dimension, which in particular can be at least 20% of an axial width of a radially outer end face of one of the two adjacent ribs, in order to prevent the coating from flaking off.
Die Rippen der Rippenanordnung sind in Umfangsrichtung um einen Winkel geneigt, der ungleich 0° und betragsmäßig kleiner als 10°, insbesondere kleiner 5° und bevorzugt kleiner 3° ist.The ribs of the rib arrangement are inclined in the circumferential direction by an angle which is not equal to 0 ° and less than 10 ° in amount, in particular less than 5 ° and preferably less than 3 °.
In einer bevorzugten Ausführung weisen zwei oder mehrere, insbesondere alle Rippen der Rippenanordnung in radialer Richtung äußere Stirnseiten auf, die, wenigstens im Wesentlichen, auf derselben radialen Höhe liegen. Ausgehend von diesen Stirnseiten erstrecken sich die Rippen in radialer Richtung unterschiedlich tief nach innen, d.h. sind in radialer Richtung unterschiedlich hoch. Dies ermöglicht zum Einen die Ausbildung kleiner Spalte zwischen den Rippen und zum Anderen eine Anpassung an Schaufeln mit variierender radialer Höhe.In a preferred embodiment, two or more, in particular all, of the ribs of the rib arrangement have outer end faces in the radial direction which, at least essentially, lie at the same radial height. Starting from these end faces, the ribs extend inward in the radial direction at different depths, i.e. are of different heights in the radial direction. On the one hand, this enables the formation of small gaps between the ribs and, on the other hand, an adaptation to blades with varying radial heights.
Gleichermaßen können in radialer Richtung äußere Stirnseiten von zwei oder mehreren, insbesondere allen Rippen der Rippenanordnung eine unterschiedliche radiale Höhe aufweisen, insbesondere - wenigstens im Wesentlichen - auf einer virtuellen Kegelfläche liegen. Zusätzlich oder alternativ können zwei oder mehr, insbesondere alle Rippen der Rippenanordnung in radialer Richtung unterschiedlich hoch sein.Likewise, in the radial direction, outer end faces of two or more, in particular all, of the ribs of the rib arrangement can have a different radial height, in particular — at least essentially — lie on a virtual conical surface. Additionally or alternatively, two or more, in particular all, ribs of the rib arrangement can have different heights in the radial direction.
Die Rippenanordnung ist auf einem Deckband der Laufschaufel angeordnet. Unter einem Deckband wird vorliegend insbesondere ein Flansch verstanden, der sich in Axial- und Umfangsrichtung erstreckt und in bevorzugter Weiterbildung formschlüssig an Deckbändern in Umfangsrichtung benachbarter Schaufeln anliegt. Das Deckband kann in einer bevorzugten Weiterbildung in Axialrichtung schräg sein, um die vorstehend erläuterten Rippen unterschiedlicher Höhe zu tragen.The rib arrangement is arranged on a cover band of the moving blade. In the present case, a shroud is understood to mean, in particular, a flange which extends in the axial and circumferential directions and, in a preferred development, bears in a form-fitting manner on shrouds in the circumferential direction of adjacent blades. In a preferred development, the cover band can be inclined in the axial direction in order to support the ribs of different heights explained above.
Die Beschichtung kann mittels eines Verfahrens zum Beschichten einer oder vorzugsweise, insbesondere zeitlich parallel oder nacheinander, mehrerer Rippen einer radial äußeren Rippenanordnung einer Laufschaufel, das insbesondere zur Beschichtung einer Laufschaufel nach dem vorstehend erläuterten Aspekt geeignet ist, erfolgen.The coating can be carried out by means of a method for coating one or, preferably, in particular in time in parallel or in succession, a plurality of ribs of a radially outer rib arrangement of a rotor blade, which is particularly suitable for coating a rotor blade according to the aspect explained above.
Ein Beschichtungsmaterial kann aus wenigstens zwei gegensinnigen Spritzrichtungen auf die Rippenanordnung aufgespritzt werden, insbesondere plasmagespritzt, flammgespritzt, insbesondere Hochgeschwindigkeits-flammgespritzt, detonationsgespritzt, kaltgasgespritzt, lichtbogengespritzt, und/oder lasergespritzt. Unter einem Plasmaspritzen wird vorliegend insbesondere verstanden, dass, beispielsweise in einem Plasmabrenner, durch eine Spannung ein Lichtbogen zwischen Anode(n) und Kathode(n) erzeugt und Gas oder Gasgemisch durch den Lichtbogen geleitet und hierbei ionisiert wird. Die Dissoziation beziehungsweise anschließende Ionisation erzeugt ein hochaufgeheiztes, elektrisch leitendes Gas aus positiven Ionen und Elektronen. In diesem erzeugten Plasmajet kann pulverförmiges Beschichtungsmaterial eingedüst werden, das durch die hohe Plasmatemperatur aufgeschmolzen wird. Der Plasmastrom reißt die Pulverteilchen mit und schleudert sie auf die zu beschichtende Laufschaufel. Vorzugsweise erfolgt die Plasmabeschichtung in normaler Atmosphäre, inerter Atmosphäre, in Vakuum oder auch unter Wasser.A coating material can be sprayed onto the fin arrangement from at least two opposite spray directions, in particular plasma sprayed, flame sprayed, in particular high speed flame sprayed, detonation sprayed, cold gas sprayed, arc sprayed, and / or laser sprayed. In the present case, plasma spraying is understood in particular to mean that, for example in a plasma torch, an electric arc is generated between the anode (s) and cathode (s) by a voltage, and gas or gas mixture is passed through the electric arc and thereby ionized. The dissociation or subsequent ionization generates a highly heated, electrically conductive gas from positive ions and Electrons. Powdery coating material can be injected into this generated plasma jet, which is melted by the high plasma temperature. The plasma stream entrains the powder particles and hurls them onto the rotor blade to be coated. The plasma coating is preferably carried out in a normal atmosphere, inert atmosphere, in vacuum or under water.
Durch das Aufspritzen in einer gegen die radiale Richtung geneigten Spritzrichtung kann insbesondere die sich in radialer Richtung nach außen erweiternde Außenkontur dargestellt werden. Dabei wird, vergleichbar den Windverfrachtungen von Schnee in Kammlagen, an den Außenkanten der Laufschaufelstimseite mehr Beschichtungsmaterial aufgebracht, wobei sich durch die Neigung der Spritzrichtung eine entsprechende Projektion des Beschichtungsmaterialstrahls auf die Flanke der Rippe einstellt. Zusätzlich können benachbarte Rippen bzw. Beschichtungen den Beschichtungsmaterialstrahl teilweise abschatten, so dass mit abnehmendem radialen Abstand zur Drehachse weniger Beschichtungsmaterial aufgebracht wird.By spraying in an injection direction inclined against the radial direction, in particular the outer contour that widens outward in the radial direction can be represented. Comparable to the wind loads of snow in comb layers, more coating material is applied to the outer edges of the rotor blade front side, the projection of the coating material jet on the flank of the rib resulting from the inclination of the spray direction. In addition, adjacent ribs or coatings can partially shade the coating material jet, so that with decreasing radial distance from the axis of rotation, less coating material is applied.
Die Spritzrichtungen können gegensinnig, jedoch betragsmäßig gleich, gegen die radiale Richtung geneigt sein, vorzugsweise um einen Spritzwinkel, der betragsmäßig größer als 20°, insbesondere größer als 40°, und/oder kleiner als 70°, insbesondere kleiner als 50° ist. Das Beschichtungsmaterial kann nacheinander oder gleichzeitig aus den beiden Spritzrichtungen aufgespritzt werden.The spray directions can be inclined in opposite directions, but with the same amount, against the radial direction, preferably by an spray angle which is greater than 20 °, in particular greater than 40 °, and / or less than 70 °, in particular less than 50 °. The coating material can be sprayed on in succession or simultaneously from the two spray directions.
Eine oder mehrere Beschichtungen können, gleichzeitig oder nacheinander, nach dem Aufspritzen des Beschichtungsmaterials nachbearbeitet werden. Insbesondere kann eine radial äußere Stimfläche der Beschichtungen beispielsweise geschliffen, poliert oder andersartig nachbearbeitet werden.One or more coatings can be reworked, simultaneously or in succession, after the coating material has been sprayed on. In particular, a radially outer end face of the coatings can, for example, be ground, polished or reworked in some other way.
Weitere Vorteile und Merkmale ergeben sich aus den Unteransprüchen und den Ausführungsbeispielen. Hierzu zeigt, teilweise schematisiert:
- Fig. 1:
- das Deckband einer Laufschaufel nach einer Ausführung der vorliegenden Erfindung in einer Draufsicht entgegen einer radialen Richtung;
- Fig. 2:
- einen vergrößerten Ausschnitt der
Fig. 3 bzw. 4; - Fig. 3:
- einen Meridianschnitt einer Gasturbinenstufe nach einer Ausführung der vorliegenden Erfindung; und
- Fig. 4:
- einen Meridianschnitt einer Gasturbinenstufe nach einer weiteren Ausführung der vorliegenden Erfindung.
- Fig. 1:
- the cover band of a blade according to an embodiment of the present invention in a plan view against a radial direction;
- Fig. 2:
- an enlarged section of the
Fig. 3 or 4; - Fig. 3:
- a meridian section of a gas turbine stage according to an embodiment of the present invention; and
- Fig. 4:
- a meridian section of a gas turbine stage according to a further embodiment of the present invention.
Diese Beschichtung 3 wird durch sequentielles Plasmaspritzen zunächst in einer ersten Spritzrichtung S1, und anschließend in einer gegensinnigen bzw. hierzu spiegelsymmetrischen zweiten Spritzrichtung S2, wie in
Hierdurch ergeben sich auf den Rippen 2 Beschichtungen 3, die in dem Meridianschnitt der
Durch die gegensinnige Überlagerung der beiden Spritzrichtungen S1, S2 kann eine im Wesentlichen ebene Stimfläche der Beschichtungen 3 dargestellt werden. Gleichermaßen kann die Beschichtung, insbesondere ihre radial äußere Stirnfläche (oben in
Man erkennt insbesondere in der
Wie in
- 11
- Deckbandshroud
- 22
- Rippe(nanordnung)Rib (nanordnung)
- 33
- Beschichtungcoating
- 3.13.1
- Außenflanke der Beschichtung/BeschichtungsaußenkonturOuter flank of the coating / coating outer contour
- 4; 4'4; 4 '
- Dichtflächesealing surface
- 55
- Laufschaufelblade
Claims (6)
- Rotor blade (5) for a compressor stage or turbine stage of a gas turbine, comprising a radially outer rib arrangement which is arranged on a shroud (1) of the rotor blade (5) and has at least two radially outwardly directed ribs (2), wherein the ribs (2) are arranged one behind the other in the axial direction and are inclined in the circumferential direction (U) by an angle (α) not equal to 0° which is smaller than 10° in absolute value, wherein the ribs (2) have a coating (3) on the respective two axially opposite side surfaces and on the radially outer end face of the ribs (2), via which the side surfaces are connected, wherein the thickness of the coating (3) in a section transverse with respect to the rib (2) on the two radial side surfaces of the rib (2) increases with increasing radial distance from the axis of rotation of the gas turbine.
- Rotor blade (5) according to claim 1, characterized in that a coating (3) is arranged in each case on at least two adjacent ribs (2), and a gap (s) between mutually facing flanks (3.1) of the adjacent coatings (3) corresponding at most to an axial width (b) of a radially outer end face of one of the two adjacent ribs (2).
- Rotor blade (5) according to either of the preceding claims, characterized in that at least two ribs (2) of the rib arrangement have an end face which is outside in the radial direction (R) and which, at least substantially, is at the same radial height, and, starting from the end face, are inwardly different in height in the radial direction.
- Rotor blade (5) according to any of claims 1 to 3, characterized in that at least two ribs (2) of the rib assembly have end faces which are outside in the radial direction (R) and are at different radial heights, the ribs (2) being different in height in the radial direction.
- Rotor blade (5) according to any of the preceding claims, characterized in that a coating (3) has a greater hardness than the rib (2) on which it is arranged.
- Turbomachine comprising a rotor blade assembly having at least one rotor blade (5) according to any of the preceding claims.
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
ES11193177T ES2773743T3 (en) | 2011-12-13 | 2011-12-13 | Paddle that has a set of ribs with an abrasive coating |
EP11193177.0A EP2604797B1 (en) | 2011-12-13 | 2011-12-13 | Rotor blade with a rib assembly with an abrasive coating |
US13/709,322 US9797264B2 (en) | 2011-12-13 | 2012-12-10 | Rotating blade having a rib arrangement with a coating |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP11193177.0A EP2604797B1 (en) | 2011-12-13 | 2011-12-13 | Rotor blade with a rib assembly with an abrasive coating |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2604797A1 EP2604797A1 (en) | 2013-06-19 |
EP2604797B1 true EP2604797B1 (en) | 2020-01-22 |
Family
ID=45400930
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP11193177.0A Active EP2604797B1 (en) | 2011-12-13 | 2011-12-13 | Rotor blade with a rib assembly with an abrasive coating |
Country Status (3)
Country | Link |
---|---|
US (1) | US9797264B2 (en) |
EP (1) | EP2604797B1 (en) |
ES (1) | ES2773743T3 (en) |
Families Citing this family (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102015213555A1 (en) * | 2015-07-20 | 2017-03-09 | MTU Aero Engines AG | Sealing ridge armor and method of making the same |
DE102016211337A1 (en) * | 2016-06-24 | 2017-12-28 | MTU Aero Engines AG | Thickened radially outer ring area of a sealing fin |
DE102016222720A1 (en) * | 2016-11-18 | 2018-05-24 | MTU Aero Engines AG | Sealing system for an axial flow machine and axial flow machine |
CN110312846B (en) * | 2017-02-23 | 2022-05-10 | 三菱动力株式会社 | Turbine rotor blade and gas turbine |
FR3073595B1 (en) * | 2017-11-15 | 2020-02-07 | Safran Helicopter Engines | LABYRINTH JOINT COMPRISING A STICK WITH A DEFLECTOR |
JP7086595B2 (en) * | 2017-12-28 | 2022-06-20 | 三菱重工航空エンジン株式会社 | Aircraft gas turbine |
PL3865660T3 (en) | 2020-02-11 | 2024-06-24 | Mtu Aero Engines Gmbh | Method for machining a blade and a blade for a turbomachine |
Family Cites Families (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4390320A (en) * | 1980-05-01 | 1983-06-28 | General Electric Company | Tip cap for a rotor blade and method of replacement |
US4884820A (en) * | 1987-05-19 | 1989-12-05 | Union Carbide Corporation | Wear resistant, abrasive laser-engraved ceramic or metallic carbide surfaces for rotary labyrinth seal members |
US5038014A (en) * | 1989-02-08 | 1991-08-06 | General Electric Company | Fabrication of components by layered deposition |
US5453329A (en) * | 1992-06-08 | 1995-09-26 | Quantum Laser Corporation | Method for laser cladding thermally insulated abrasive particles to a substrate, and clad substrate formed thereby |
US6476343B2 (en) * | 1996-07-08 | 2002-11-05 | Sandia Corporation | Energy-beam-driven rapid fabrication system |
US5794338A (en) * | 1997-04-04 | 1998-08-18 | General Electric Company | Method for repairing a turbine engine member damaged tip |
US6190124B1 (en) * | 1997-11-26 | 2001-02-20 | United Technologies Corporation | Columnar zirconium oxide abrasive coating for a gas turbine engine seal system |
DE19933445C2 (en) * | 1999-07-16 | 2001-12-13 | Mtu Aero Engines Gmbh | Sealing ring for non-hermetic fluid seals |
US6254345B1 (en) * | 1999-09-07 | 2001-07-03 | General Electric Company | Internally cooled blade tip shroud |
US6224337B1 (en) * | 1999-09-17 | 2001-05-01 | General Electric Company | Thermal barrier coated squealer tip cavity |
US6558119B2 (en) * | 2001-05-29 | 2003-05-06 | General Electric Company | Turbine airfoil with separately formed tip and method for manufacture and repair thereof |
FR2825411B1 (en) * | 2001-05-31 | 2003-09-19 | Snecma Moteurs | TURBINE DAWN WITH SEALING LECHETTE |
CN1692179B (en) | 2002-10-09 | 2011-07-13 | 石川岛播磨重工业株式会社 | Rotor and coating method therefor |
JP2005127276A (en) * | 2003-10-27 | 2005-05-19 | Hitachi Ltd | Roter blade for turbine and turbine |
WO2005061854A1 (en) * | 2003-12-17 | 2005-07-07 | Watson Cogeneration Company | Gas turbine tip shroud rails |
US7587818B2 (en) * | 2004-12-23 | 2009-09-15 | General Electric Company | Repair of gas turbine blade tip without recoating the repaired blade tip |
US7473072B2 (en) * | 2005-02-01 | 2009-01-06 | Honeywell International Inc. | Turbine blade tip and shroud clearance control coating system |
FR2893268B1 (en) * | 2005-11-15 | 2008-02-08 | Snecma Sa | METHOD OF MAKING A REBORD LOCATED AT THE FREE END OF A DAWN, DAWN OBTAINED BY THIS PROCESS AND TURBOMACHINE EQUIPPED WITH SAID DARK |
EP2316988B1 (en) * | 2009-11-02 | 2015-07-08 | Alstom Technology Ltd | Wear-resistant and oxidation-resistant turbine blade |
CH702980A1 (en) * | 2010-03-31 | 2011-10-14 | Alstom Technology Ltd | A seal structure of a shroud of a turbine blade. |
-
2011
- 2011-12-13 EP EP11193177.0A patent/EP2604797B1/en active Active
- 2011-12-13 ES ES11193177T patent/ES2773743T3/en active Active
-
2012
- 2012-12-10 US US13/709,322 patent/US9797264B2/en not_active Expired - Fee Related
Non-Patent Citations (1)
Title |
---|
None * |
Also Published As
Publication number | Publication date |
---|---|
EP2604797A1 (en) | 2013-06-19 |
US20130149165A1 (en) | 2013-06-13 |
ES2773743T3 (en) | 2020-07-14 |
US9797264B2 (en) | 2017-10-24 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP2604797B1 (en) | Rotor blade with a rib assembly with an abrasive coating | |
EP2604792B1 (en) | Method for repairing a component of a gas turbine engine and associated repaired component | |
DE102010001414B4 (en) | Method for repairing labyrinth seal webs | |
DE102012106175A1 (en) | Structured abrasive coatings for surfaces of stationary steam turbine components | |
EP3191244A1 (en) | Method for producing a rotor blade, and blade obtained by such a method | |
DE69604154T2 (en) | ABRASIBLE GASKET SEAL FOR TURBO MACHINES | |
DE10121019A1 (en) | Gas turbine seal | |
EP3054106B1 (en) | Gas turbine component | |
EP2647795A1 (en) | Seal system for a turbo engine | |
EP3324002B1 (en) | Sealing system for a turbomachine and axial flowmachine | |
WO2008095463A1 (en) | Device for the protection of components having a flammable titanium alloy from titanium fire, and method for the production thereof | |
EP1820872B1 (en) | Process of preparing turbine blades with a masking strip having a connector for a subsequent treatment, and turbine blade therefor | |
EP2617945B1 (en) | Rotor for a turbo machine and manufacturing process | |
EP2984294B1 (en) | Turbine blade with staged and chamfered platform edge | |
DE102009055913A1 (en) | Labyrinth seal e.g. tripping collar labyrinth seal, for aircraft gas turbine, has sealing ring comprising upper flank region coated with wear resistant material, where flank region has slew rate that is reduced against lower flank region | |
EP2647796A1 (en) | Seal system for a turbo engine | |
EP2516688A1 (en) | Method for producing a rotor/stator seal of a gas turbine | |
DE102009055914A1 (en) | Sealing rings for a labyrinth seal | |
WO2011026468A2 (en) | Turbomachine, and method for producing a structured abradable coating | |
EP3312388B1 (en) | Rotor part, corresponding compressor, turbine and manufacturing method | |
WO2018206306A1 (en) | Method for maintaining a turbomachine | |
DE102015219513B4 (en) | Repair procedure for sealing segments | |
EP3260664A1 (en) | Thickened radial outer ring area of a sealing fin | |
DE112020001189T5 (en) | Turbine Blade and Contact Surface Fabrication Process | |
EP3274561B1 (en) | Rotor blade for a gas turbine, manufacturing process and post production process |
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: 20121210 |
|
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 |
|
RAP1 | Party data changed (applicant data changed or rights of an application transferred) |
Owner name: MTU AERO ENGINES AG |
|
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: 20161107 |
|
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: 20190801 |
|
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 |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: REF Ref document number: 1227032 Country of ref document: AT Kind code of ref document: T Effective date: 20200215 |
|
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: 502011016416 Country of ref document: DE |
|
REG | Reference to a national code |
Ref country code: NL Ref legal event code: MP Effective date: 20200122 |
|
REG | Reference to a national code |
Ref country code: ES Ref legal event code: FG2A Ref document number: 2773743 Country of ref document: ES Kind code of ref document: T3 Effective date: 20200714 |
|
REG | Reference to a national code |
Ref country code: LT Ref legal event code: MG4D |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: 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: 20200614 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: 20200122 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: 20200122 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: 20200422 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: 20200122 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: BG Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200422 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: 20200423 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: 20200122 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: 20200122 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: 20200122 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: 20200522 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R097 Ref document number: 502011016416 Country of ref document: DE |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: DK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200122 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: 20200122 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: 20200122 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: 20200122 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: 20200122 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: 20200122 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: 20200122 |
|
PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
26N | No opposition filed |
Effective date: 20201023 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: IT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200122 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
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: 20200122 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: 20200122 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R119 Ref document number: 502011016416 Country of ref document: DE |
|
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: 20201213 |
|
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: 20200122 |
|
REG | Reference to a national code |
Ref country code: BE Ref legal event code: MM Effective date: 20201231 |
|
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: 20201213 Ref country code: FR Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20201231 Ref country code: LU Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20201213 |
|
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: 20201231 Ref country code: DE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20210701 Ref country code: GB Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20201213 Ref country code: CH Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20201231 |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: MM01 Ref document number: 1227032 Country of ref document: AT Kind code of ref document: T Effective date: 20201213 |
|
REG | Reference to a national code |
Ref country code: ES Ref legal event code: FD2A Effective date: 20220222 |
|
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: 20201213 |
|
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: 20200122 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: 20200122 Ref country code: ES Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20201214 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: 20200122 |
|
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: 20200122 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: 20200122 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: BE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20201231 |