EP2294286B1 - Rotor with shrouded blades of a turbomachine - Google Patents

Rotor with shrouded blades of a turbomachine Download PDF

Info

Publication number
EP2294286B1
EP2294286B1 EP09745441.7A EP09745441A EP2294286B1 EP 2294286 B1 EP2294286 B1 EP 2294286B1 EP 09745441 A EP09745441 A EP 09745441A EP 2294286 B1 EP2294286 B1 EP 2294286B1
Authority
EP
European Patent Office
Prior art keywords
rotor
shroud
gaps
turbomachine
damping
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Not-in-force
Application number
EP09745441.7A
Other languages
German (de)
French (fr)
Other versions
EP2294286A2 (en
Inventor
Hans-Peter Borufka
Hernan Victor Arrieta
Klemens Hain
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Publication of EP2294286A2 publication Critical patent/EP2294286A2/en
Application granted granted Critical
Publication of EP2294286B1 publication Critical patent/EP2294286B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/183—Two-dimensional patterned zigzag
    • 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
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise

Definitions

  • the present invention relates to a shroud for rotor blades of a turbomachine, in particular a gas turbine, wherein the shroud is arranged on the circumference of a blade row arranged on a rotor with a plurality of blades and at its periphery has at least one separating gap.
  • the invention further relates to a turbomachine, in particular gas turbine, comprising at least one rotor having at least one blade row with a plurality of blades.
  • the sealing gap between rotating blades and the stationary engine casing is an influencing variable, which is of considerable importance for the efficiency of the engine.
  • a shroud which is arranged on the blade tips of the blades.
  • From the DE 40 15 206 C1 is a shroud for an integral wheel with at least one circumferentially arranged Z-shaped separating gap with angularly arranged to the axial direction damping columns smallest gap width and adjoining open gap sections known.
  • the mutually parallel damping gaps form the two legs of the Z-shaped separating gap and are aligned at an angle of 70 ° to 90 ° to the axial direction of the integral wheel.
  • the damping gaps are close together, while the Z-web is formed as an open gap extending in the direction of the shroud edges.
  • the two damping gaps provide a friction surface which allows a corresponding friction damping of the vibrations during operation of the integral wheel.
  • Shrouds with serrated separating gaps are from the EP0536575A1 , the EP0528138A1 and the FR1519898A known.
  • a shroud for moving blades of a turbomachine, in particular a gas turbine, of a rotor according to the invention is arranged on the circumference of a rotor blade row arranged on a rotor with a plurality of rotor blades and has at least one separating gap on its circumference.
  • the separating gap is serrated and has at least three mutually spaced and angularly extending to an axis of rotation of the rotor damping gaps and adjoining the damping column respectively connecting or extending in the direction of the shroud edges connecting gaps, wherein the gap width of the damping column upon rotation of the rotor up to a juxtaposition the partition walls forming the attenuation gaps are reduced.
  • the total available contact surface for friction damping is significantly increased under operating conditions of the turbomachine. This ensures a predominantly resonance-free operation of bladed turbomachines and also an improvement in the coupling stiffness of adjacent blades to one another. There is a continuous distribution of the power flow along the damping column or the contact points of the corresponding gap walls.
  • the resonance-free main operating range results from the control of the fundamental natural frequencies of the bladed disc (overall system blade / rotor) by the possibility of an individual design of the support and stress kinematics of the formed separating gaps.
  • the damping gaps are aligned at an angle of 60 ° to 90 ° to the axis of rotation of the rotor.
  • this ensures that when the turbomachine is started up, the circumferential expansion of the shroud resulting from the centrifugal forces can take place unhindered.
  • the shroud is divided into individual shroud segments, wherein each shroud segment associated with a blade and arranged thereon and form the individual shroud segments with the respective adjacent shroud segments in the circumferential direction of the separation column.
  • each shroud segment of a group of at least two blades is assigned and arranged thereon and form the individual shroud segments with the respective adjacent shroud segments in the circumferential direction of the separation column.
  • the blades are integrally formed with the shroud segments.
  • the shroud according to the invention may have different advantageous embodiments and arrangements.
  • the subdivision of the shroud into shroud segments increases the range of applications.
  • the blades with the shroud segments integral, that is to form in one piece. This leads to a simplified manufacturing process and thus to reduced manufacturing costs.
  • At least one sealing lip is arranged on the outer circumference of the shroud.
  • two spaced-apart and mutually parallel sealing lips may be integrally formed on the outer circumference.
  • the sealing lips may be interrupted in the region of the separating gaps. The arrangement of the sealing lips is a further advantageous reduction of the sealing gap between the rotating blades or the shroud and the stationary engine housing, the efficiency of the turbomachine, in particular the gas turbine is significantly improved.
  • the rotor according to the invention is used in a low-pressure turbine, in particular a low-pressure turbine of an aircraft engine.
  • a turbomachine according to the invention in particular gas turbine, comprises at least one rotor which has at least one blade row with a plurality of rotor blades, wherein a shroud according to the above-described embodiments is arranged on the circumference of the rotor blade row. Due to the design of the shroud, the turbomachine according to the invention ensures predominantly resonance-free operation and an improvement in the coupling rigidity of adjacent blades to one another. This results in a significant increase in the efficiency of the turbomachine.
  • the turbomachine may be a low-pressure turbine, in particular a low-pressure turbine of an aircraft engine.
  • the blades may include components of an integral rotor construction, i. BLISK or BLING, his.
  • FIG. 1 shows a schematic representation of a portion of a turbomachine consisting of a blade 14 with a blade root 52, wherein the blade root 52 is disposed on a rotor 12.
  • the rotor 12 is rotatable about an axis 18.
  • a shroud 10 is arranged on the rotor blade 14.
  • the shroud 10 is arranged on the circumference of a arranged on the rotor 12 blade row consisting of several blades.
  • FIG. 2 1 shows a schematic representation of a plan view of the shroud 10. It can be seen that the shroud 10 has a plurality of separating gaps 16, 16 ', 16 "on its circumference, wherein the separating gaps 16, 16", 16 "are formed in a serrated shape the separating gaps 16, 16 ', 16 "each consist of five spaced apart and at an angle to the axis of rotation 18 of the rotor 12 extending damping columns 20, 22, 24, 26, 28 and to this subsequent, the damping column 20, 22, 24, 26th , 28 in each case connecting or in the direction of the shroud edges 54, 56 extending connecting gaps 30, 32, 34, 36, 38, 40.
  • the individual shroud segments 46, 48 form with the respective adjacent shroud segments in the circumferential direction the separating gaps 16, 16 ', 16 " Separation gaps 16, 16 ', 16 "formed parallel to each other, that is, the individual damping and connecting gaps each extend parallel to each other.
  • damping gaps 20, 22, 24, 26, 28 are aligned at an angle of 60 ° to 90 ° to the axis of rotation 18 of the rotor 12.
  • a total of four damping gaps 20, 22, 24, 26 are aligned parallel to each other in the illustrated embodiment.
  • a further damping gap 28 extends at an acute angle to the previously described damping gaps 20, 22, 24, 26.
  • connection gaps 30, 32, 34, 36, 38, 40 have different angles in a range between 0 ° and 90 ° ° with respect to the axis of rotation 18 of the rotor can take.
  • two mutually parallel sealing lips 62, 64 are integrally formed on the outer circumference of the shroud 10.
  • the sealing lips are interrupted in the area of the separating gaps 16, 16 ', 16 ".
  • the sealing lips 62, 64 result in a further advantageous reduction of the sealing gap between the shroud 10 and a fixed housing of the turbomachine adjoining it, in particular a fixed engine housing (US Pat. not shown).

Description

Die vorliegende Erfindung betrifft ein Deckband für Laufschaufeln einer Strömungsmaschine, insbesondere einer Gasturbine, wobei das Deckband am Umfang einer an einem Rotor angeordneten Laufschaufelreihe mit mehreren Laufschaufeln angeordnet ist und an seinem Umfang mindestens einen Trennspalt aufweist. Die Erfindung betrifft weiterhin eine Strömungsmaschine, insbesondere Gasturbine, umfassend mindestens einen Rotor, der mindestens eine Laufschaufelreihe mit mehreren Laufschaufeln aufweist.The present invention relates to a shroud for rotor blades of a turbomachine, in particular a gas turbine, wherein the shroud is arranged on the circumference of a blade row arranged on a rotor with a plurality of blades and at its periphery has at least one separating gap. The invention further relates to a turbomachine, in particular gas turbine, comprising at least one rotor having at least one blade row with a plurality of blades.

Bei Strömungsmaschinen, insbesondere bei Gasturbinen von Turbotriebwerken, stellt der Dichtspalt zwischen rotierenden Schaufeln und dem feststehenden Triebwerksgehäuse eine Einflussgröße dar, die von erheblicher Bedeutung für den Wirkungsgrad des Triebwerks ist. Zur Minimierung dieses Dichtspalts ist es bei Gasturbinen bekannt, diese mit einem Deckband zu versehen, welches an den Schaufelspitzen der Schaufeln angeordnet ist. Aus der DE 40 15 206 C1 ist dabei ein Deckband für ein Integralrad mit mindestens einem am Umfang angeordneten Z-förmigen Trennspalt mit winkelig zur Achsrichtung angeordneten Dämpfungsspalten geringster Spaltweite und sich daran anschließende offene Spaltabschnitte bekannt. Dabei bilden die parallel zueinander liegenden Dämpfungsspalte die beiden Schenkel des Z-förmigen Trennspalts und sind in einem Winkel von 70° bis 90° zur Achsrichtung des Integralrads ausgerichtet. Unter Betriebsbedingungen liegen die Dämpfungsspalte eng aneinander, während der Z-Steg als ein in Richtung der Deckbandränder verlaufender offener Spalt ausgebildet ist. Dadurch wird eine ungehinderte Umfangsverschiebung des Deckbands möglich, um einen spannungsarmen Thermodehnungsausgleich zu gewährleisten. Des Weiteren bieten die beiden Dämpfungsspalte eine Reibungsfläche, die eine entsprechende Reibungsdämpfung der Schwingungen im Betrieb des Integralrads ermöglicht.In turbomachines, especially in gas turbines of turbo engines, the sealing gap between rotating blades and the stationary engine casing is an influencing variable, which is of considerable importance for the efficiency of the engine. To minimize this sealing gap, it is known in gas turbines to provide them with a shroud, which is arranged on the blade tips of the blades. From the DE 40 15 206 C1 is a shroud for an integral wheel with at least one circumferentially arranged Z-shaped separating gap with angularly arranged to the axial direction damping columns smallest gap width and adjoining open gap sections known. The mutually parallel damping gaps form the two legs of the Z-shaped separating gap and are aligned at an angle of 70 ° to 90 ° to the axial direction of the integral wheel. Under operating conditions, the damping gaps are close together, while the Z-web is formed as an open gap extending in the direction of the shroud edges. As a result, an unobstructed circumferential displacement of the shroud is possible to ensure a low-stress thermal expansion compensation. Furthermore, the two damping gaps provide a friction surface which allows a corresponding friction damping of the vibrations during operation of the integral wheel.

Deckbänder mit zackenförmig ausgebildeten Trennspalten sind aus der EP0536575A1 , der EP0528138A1 und der FR1519898A bekannt.Shrouds with serrated separating gaps are from the EP0536575A1 , the EP0528138A1 and the FR1519898A known.

Es besteht aber insbesondere aufgrund immer höherer Drehzahlen von Strömungsmaschinen, insbesondere von Gasturbinen eines Flugtriebwerks, weiterhin die Notwendigkeit, die im Hauptbetriebsbereich auftretenden Schwingungen, die insbesondere durch die fundamentalen Eigenfrequenzen der beschaufelten Scheibe, das heißt in dem Gesamtsystem Schaufel/Rotor entstehen, weiter zu vermindern beziehungsweise weiter entgegenzuwirken. Zudem besteht weiterhin ein Bedarf einer Verbesserung der Koppelungssteifigkeit benachbarter Schaufeln zueinander.However, in particular due to ever higher rotational speeds of turbomachines, in particular of gas turbines of an aircraft engine, there is still the need to further reduce the vibrations occurring in the main operating range, which arise in particular from the fundamental natural frequencies of the bladed disc, that is, in the overall blade / rotor system or to counteract further. In addition, there is still a need to improve the coupling stiffness of adjacent blades to each other.

Es ist daher Aufgabe der vorliegenden Erfindung ein gattungsgemäße Deckband für Laufschaufeln einer Strömungsmaschine und eine gattungsgemäße Strömungsmaschine bereitzustellen, die einen überwiegend resonanzfreien Betrieb von beschaufelten Strömungsmaschinen und eine Verbesserung der Koppelungssteifigkeit benachbarter Schaufeln zueinander gewährleistet.It is therefore an object of the present invention to provide a generic shroud for blades of a turbomachine and a generic turbomachine, which ensures a predominantly resonance-free operation of bladed turbomachines and an improvement in the coupling stiffness of adjacent blades to each other.

Gelöst werden diese Aufgaben durch einen Rotorgemäß den Merkmalen des Anspruchs 1 sowie eine Strömungsmaschine gemäß den Merkmalen des Anspruchs 8.These objects are achieved by a rotor according to the features of claim 1 and a turbomachine according to the features of claim 8.

Vorteilhafte Ausgestaltungen der Erfindung sind in den jeweiligen Unteransprüchen beschrieben.Advantageous embodiments of the invention are described in the respective subclaims.

Ein Deckband für Laufschaufeln einer Strömungsmaschine, insbesondere einer Gasturbine, eines erfindungsgemäßen Rotors ist am Umfang einer an einem Rotor angeordneten Laufschaufelreihe mit mehreren Laufschaufeln angeordnet und weist an seinem Umfang mindestens einen Trennspalt auf. Dabei ist der Trennspalt zackenförmig ausgebildet und weist mindestens drei voneinander beabstandete und winkelig zu einer Drehachse des Rotors verlaufende Dämpfungsspalte und sich daran anschließende, die Dämpfungsspalte jeweils verbindende oder in Richtung der Deckbandränder verlängernde Verbindungsspalte auf, wobei die Spaltweite der Dämpfungsspalte bei Drehung des Rotors bis zu einem Aneinanderliegen der die Dämpfungsspalte ausbildenden Spaltwände verringert ist. Durch die Ausbildung von mindestens drei voneinander beabstandeten Dämpfungsspalten wird die insgesamt zur Verfügung stehende Kontaktfläche zur Reibungsdämpfung unter Betriebsbedingungen der Strömungsmaschine deutlich erhöht. Dadurch wird ein überwiegend resonanzfreier Betrieb von beschaufelten Strömungsmaschinen und zudem eine Verbesserung der Koppelungssteifigkeit benachbarter Schaufeln zueinander gewährleistet. Es erfolgt eine kontinuierliche Verteilung des Kraftflusses entlang der Dämpfungsspalte beziehungsweise der Kontaktstellen der entsprechenden Spaltwände. Der resonanzfreie Hauptbetriebsbereich ergibt sich durch die Steuerung der fundamentalen Eigenfrequenzen der beschaufelten Scheibe (Gesamtsystem Schaufel/Rotor) durch die Möglichkeit einer individuellen Gestaltung der Abstützungs- und Verspannungskinematik der ausgebildeten Trennspalte.A shroud for moving blades of a turbomachine, in particular a gas turbine, of a rotor according to the invention is arranged on the circumference of a rotor blade row arranged on a rotor with a plurality of rotor blades and has at least one separating gap on its circumference. In this case, the separating gap is serrated and has at least three mutually spaced and angularly extending to an axis of rotation of the rotor damping gaps and adjoining the damping column respectively connecting or extending in the direction of the shroud edges connecting gaps, wherein the gap width of the damping column upon rotation of the rotor up to a juxtaposition the partition walls forming the attenuation gaps are reduced. By forming at least three mutually spaced damping gaps, the total available contact surface for friction damping is significantly increased under operating conditions of the turbomachine. This ensures a predominantly resonance-free operation of bladed turbomachines and also an improvement in the coupling stiffness of adjacent blades to one another. There is a continuous distribution of the power flow along the damping column or the contact points of the corresponding gap walls. The resonance-free main operating range results from the control of the fundamental natural frequencies of the bladed disc (overall system blade / rotor) by the possibility of an individual design of the support and stress kinematics of the formed separating gaps.

Die Dämpfungsspalte sind in einem Winkel von 60° bis 90° zur Drehachse des Rotors ausgerichtet. Vorteilhafterweise ist dadurch gewährleistet, dass bei einem Hochfahren der Strömungsmaschine, die sich durch die Fliehkräfte ergebende Umfangsdehnung des Deckbands ungehindert erfolgen kann. Zudem ist es möglich, dass zumindest zwei der Dämpfungsspalte parallel zueinander ausgerichtet sind, so dass ein ungefähr zeitgleicher Kontakt der die Dämpfungsspalte ausbildenden Spaltwände erfolgt.The damping gaps are aligned at an angle of 60 ° to 90 ° to the axis of rotation of the rotor. Advantageously, this ensures that when the turbomachine is started up, the circumferential expansion of the shroud resulting from the centrifugal forces can take place unhindered. In addition, it is possible for at least two of the damping gaps to be aligned parallel to one another, so that an approximately simultaneous contact of the gap walls forming the damping gaps takes place.

In einer vorteilhaften Ausgestaltung ist das Deckband in einzelne Deckbandsegmente aufgeteilt, wobei jedes Deckbandsegment einer Laufschaufel zugeordnet und daran angeordnet ist und die einzelnen Deckbandsegmente mit den jeweils benachbarten Deckbandsegmenten in Umfangsrichtung die Trennspalte ausbilden. Es ist aber auch möglich, dass jedes Deckbandsegment einer Gruppe von mindestens zwei Laufschaufeln zugeordnet und daran angeordnet ist und die einzelnen Deckbandsegmente mit den jeweils benachbarten Deckbandsegmenten in Umfangsrichtung die Trennspalte ausbilden. Zudem besteht die Möglichkeit, dass die Laufschaufeln mit den Deckbandsegmenten integral ausgebildet sind. Je nach Anforderungen an die auszubildende Strömungsmaschine kann das erfindungsgemäße Deckband unterschiedliche vorteilhafte Ausgestaltungen und Anordnungen aufweisen. Die Unterteilung des Deckbands in Deckbandsegmente erhöht die Variationsbreite der Anwendungen. Insbesondere ist es auch möglich, die Laufschaufeln mit den Deckbandsegmenten integral, das heißt einstückig auszubilden. Dies führt zu einem vereinfachten Herstellungsprozess und damit zu reduzierten Herstellungskosten.In an advantageous embodiment, the shroud is divided into individual shroud segments, wherein each shroud segment associated with a blade and arranged thereon and form the individual shroud segments with the respective adjacent shroud segments in the circumferential direction of the separation column. But it is also possible that each shroud segment of a group of at least two blades is assigned and arranged thereon and form the individual shroud segments with the respective adjacent shroud segments in the circumferential direction of the separation column. In addition, there is the possibility that the blades are integrally formed with the shroud segments. Depending on the requirements of the trainee turbomachine, the shroud according to the invention may have different advantageous embodiments and arrangements. The subdivision of the shroud into shroud segments increases the range of applications. In particular, it is also possible, the blades with the shroud segments integral, that is to form in one piece. This leads to a simplified manufacturing process and thus to reduced manufacturing costs.

In einer weiteren vorteilhaften Ausgestaltung ist am Außenumfang des Deckbands mindestens eine Dichtlippe angeordnet. Insbesondere können am Außenumfang zwei voneinander beabstandete und parallel zueinander angeordnete Dichtlippen angeformt sein. Dabei können die Dichtlippen im Bereich der Trennspalte unterbrochen sein. Durch die Anordnung der Dichtlippen erfolgt eine weitere vorteilhafte Reduzierung des Dichtspalts zwischen den rotierenden Schaufeln beziehungsweise dem Deckband und dem feststehenden Triebwerksgehäuse, wobei der Wirkungsgrad der Strömungsmaschine, insbesondere der Gasturbine deutlich verbessert wird.In a further advantageous embodiment, at least one sealing lip is arranged on the outer circumference of the shroud. In particular, two spaced-apart and mutually parallel sealing lips may be integrally formed on the outer circumference. The sealing lips may be interrupted in the region of the separating gaps. The arrangement of the sealing lips is a further advantageous reduction of the sealing gap between the rotating blades or the shroud and the stationary engine housing, the efficiency of the turbomachine, in particular the gas turbine is significantly improved.

In einer weiteren vorteilhaften Ausgestaltung kommt der erfindungsgemäße Rotor in einer Niederdruckturbine, insbesondere einer Niederdruckturbine eines Flugtriebwerks zum Einsatz.In a further advantageous embodiment, the rotor according to the invention is used in a low-pressure turbine, in particular a low-pressure turbine of an aircraft engine.

Eine erfindungsgemäße Strömungsmaschine, insbesondere Gasturbine, umfasst mindestens einen Rotor, der mindestens eine Laufschaufelreihe mit mehreren Laufschaufeln aufweist, wobei am Umfang der Laufschaufelreihe ein Deckband gemäß dem im Vorhergehenden beschriebenen Ausführungsbeispielen angeordnet ist. Die erfindungsgemäße Strömungsmaschine gewährleistet aufgrund der Ausgestaltung des Deckbands einen überwiegend resonanzfreien Betrieb und eine Verbesserung der Kopplungssteifigkeit benachbarter Schaufeln zueinander. Dadurch ergibt sich eine deutliche Steigerung des Wirkungsgrads der Strömungsmaschine. Insbesondere kann dabei die Strömungsmaschine eine Niederdruckturbine, insbesondere eine Niederdruckturbine eines Flugtriebwerks sein. Zudem können die Laufschaufeln Bestandteile einer integralen Rotor-Konstruktion, d.h. BLISK oder BLING, sein.A turbomachine according to the invention, in particular gas turbine, comprises at least one rotor which has at least one blade row with a plurality of rotor blades, wherein a shroud according to the above-described embodiments is arranged on the circumference of the rotor blade row. Due to the design of the shroud, the turbomachine according to the invention ensures predominantly resonance-free operation and an improvement in the coupling rigidity of adjacent blades to one another. This results in a significant increase in the efficiency of the turbomachine. In particular, the turbomachine may be a low-pressure turbine, in particular a low-pressure turbine of an aircraft engine. In addition, the blades may include components of an integral rotor construction, i. BLISK or BLING, his.

Weitere Vorteile, Merkmale und Einzelheiten der Erfindung ergeben sich aus der nachfolgenden Beschreibung eines zeichnerisch dargestellten Ausführungsbeispiels. Dabei zeigen

Figur 1
eine schematische Darstellung eines Teils einer Strömungsmaschine mit einem Deckband eines erfindungsgemäßen Rotors; und
Figur 2
eine schematische Darstellung einer Aufsicht auf das Deckband des erfindungsgemäßen Rotors.
Further advantages, features and details of the invention will become apparent from the following description of a drawing illustrated embodiment. Show
FIG. 1
a schematic representation of a portion of a turbomachine with a shroud of a rotor according to the invention; and
FIG. 2
a schematic representation of a plan view of the shroud of the rotor according to the invention.

Figur 1 zeigt eine schematische Darstellung eines Teils einer Strömungsmaschine bestehend aus einer Laufschaufel 14 mit einem Schaufelfuß 52, wobei der Schaufelfuß 52 an einem Rotor 12 angeordnet ist. Der Rotor 12 ist dabei um eine Achse 18 drehbar. An dem dem Schaufelfuß 52 gegenüberliegenden Ende ist an der Laufschaufel 14 ein Deckband 10 angeordnet. Das Deckband 10 ist dabei am Umfang einer an dem Rotor 12 angeordneten Laufschaufelreihe bestehend aus mehreren Laufschaufeln angeordnet. FIG. 1 shows a schematic representation of a portion of a turbomachine consisting of a blade 14 with a blade root 52, wherein the blade root 52 is disposed on a rotor 12. The rotor 12 is rotatable about an axis 18. At the end opposite the blade root 52, a shroud 10 is arranged on the rotor blade 14. The shroud 10 is arranged on the circumference of a arranged on the rotor 12 blade row consisting of several blades.

Figur 2 zeigt eine schematische Darstellung einer Aufsicht auf das Deckband 10. Man erkennt, dass das Deckband 10 an seinem Umfang mehrere Trennspalte 16, 16', 16" aufweist, wobei die Trennspalte 16, 16", 16" zackenförmig ausgebildet sind. In dem dargestellten Ausführungsbeispiel bestehen die Trennspalte 16, 16', 16" jeweils aus fünf voneinander beabstandeten und winkelig zu der Drehachse 18 des Rotors 12 verlaufenden Dämpfungsspalten 20, 22, 24, 26, 28 und sich an diese anschließende, die Dämpfungsspalte 20, 22, 24, 26, 28 jeweils verbindende oder in Richtung der Deckbandränder 54, 56 verlängernde Verbindungsspalte 30, 32, 34, 36, 38, 40. Aus der in der Figur gezeigten Detaildarstellung X wird zudem deutlich, dass die Spaltweite der Dämpfungsspalte 20, 22, 24, 26, 28 bei Drehung des Rotors 12 bis zu einem Aneinanderliegen der die Dämpfungsspalte 20, 22, 24, 26, 28 ausbildenden Spaltwände 42, 44 verringert ist. Dagegen bilden die Spaltwände 58, 60 der Verbindungsspalte 30, 32, 34, 36, 38, 40 auch bei Drehung des Rotors weiterhin einen Spalt aus. In der Detaildarstellung X ist nur ein Teilbereich des Trennspalts 16 dargestellt. Des Weiteren wird deutlich, dass in dem dargestellten Ausführungsbeispiel das Deckband 10 in einzelne Deckbandsegmente 46, 48 aufgeteilt ist, wobei jedes Deckband Segmente 46, 48 einer Laufschaufel 14, 50 zugeordnet und daran angeordnet ist. Die einzelnen Deckbandsegmente 46, 48 bilden mit den jeweils benachbarten Deckbandsegmenten in Umfangsrichtung die Trennspalte 16, 16', 16" aus. Dabei sind die Trennspalte 16, 16', 16" parallel zueinander ausgebildet, das heißt die einzelnen Dämpfungs- und Verbindungsspalte verlaufen jeweils parallel zueinander. FIG. 2 1 shows a schematic representation of a plan view of the shroud 10. It can be seen that the shroud 10 has a plurality of separating gaps 16, 16 ', 16 "on its circumference, wherein the separating gaps 16, 16", 16 "are formed in a serrated shape the separating gaps 16, 16 ', 16 "each consist of five spaced apart and at an angle to the axis of rotation 18 of the rotor 12 extending damping columns 20, 22, 24, 26, 28 and to this subsequent, the damping column 20, 22, 24, 26th , 28 in each case connecting or in the direction of the shroud edges 54, 56 extending connecting gaps 30, 32, 34, 36, 38, 40. From the detail shown in the figure X is also clear that the gap width of the damping column 20, 22, 24, 26 , 28 upon rotation of the rotor 12 to a juxtaposition of the damping column 20, 22, 24, 26, 28 forming gap walls 42, 44 is reduced. By contrast, the gap walls 58, 60 of the connecting gaps 30, 32, 34, 36, 38, 40 continue to form a gap even when the rotor rotates. In the detailed illustration X, only a partial area of the separating gap 16 is shown. Furthermore, it is clear that in the illustrated embodiment, the shroud 10 is divided into individual shroud segments 46, 48, wherein each shroud segments 46, 48 associated with a blade 14, 50 and arranged thereon. The individual shroud segments 46, 48 form with the respective adjacent shroud segments in the circumferential direction the separating gaps 16, 16 ', 16 " Separation gaps 16, 16 ', 16 "formed parallel to each other, that is, the individual damping and connecting gaps each extend parallel to each other.

Des Weiteren wird deutlich, dass die Dämpfungsspalte 20, 22, 24, 26, 28 in einem Winkel von jeweils 60° bis 90° zur Drehachse 18 des Rotors 12 ausgerichtet sind. Dabei sind in dem dargestellten Ausführungsbeispiel insgesamt vier Dämpfungsspalte 20, 22, 24, 26 zueinander parallel ausgerichtet. Ein weiterer Dämpfungsspalt 28 verläuft in einem spitzen Winkel zu den vorher beschriebenen Dämpfungsspalten 20, 22, 24, 26. Man erkennt zudem, dass die Verbindungsspalte 30, 32, 34, 36, 38, 40 unterschiedliche Winkel in einem Bereich zwischen 0° und 90° bezüglich der Drehachse 18 des Rotors einnehmen können.Furthermore, it is clear that the damping gaps 20, 22, 24, 26, 28 are aligned at an angle of 60 ° to 90 ° to the axis of rotation 18 of the rotor 12. In this case, a total of four damping gaps 20, 22, 24, 26 are aligned parallel to each other in the illustrated embodiment. A further damping gap 28 extends at an acute angle to the previously described damping gaps 20, 22, 24, 26. It can also be seen that the connection gaps 30, 32, 34, 36, 38, 40 have different angles in a range between 0 ° and 90 ° ° with respect to the axis of rotation 18 of the rotor can take.

In dem dargestellten Ausführungsbeispiel sind am Außenumfang des Deckbands 10 zwei parallel zueinander verlaufende Dichtlippen 62, 64 angeformt. In dem Bereich der Trennspalte 16, 16', 16" sind die Dichtlippen unterbrochen. Durch die Dichtlippen 62, 64 ergibt sich eine weitere vorteilhafte Verringerung des Dichtspalts zwischen dem Deckband 10 und einem sich daran anschließenden feststehenden Gehäuse der Strömungsmaschine, insbesondere eines feststehenden Triebwerksgehäuses (nicht dargestellt).In the illustrated embodiment, two mutually parallel sealing lips 62, 64 are integrally formed on the outer circumference of the shroud 10. The sealing lips are interrupted in the area of the separating gaps 16, 16 ', 16 ".The sealing lips 62, 64 result in a further advantageous reduction of the sealing gap between the shroud 10 and a fixed housing of the turbomachine adjoining it, in particular a fixed engine housing (US Pat. not shown).

Claims (10)

  1. Rotor (12) for a turbomachine, in particular a gas turbine, comprising a rotor blade row which comprises a plurality of rotor blades (14, 50) and is arranged on the rotor (12), and a shroud, the shroud (10) being arranged on the periphery of the rotor blade row and having, on its periphery, at least one separating gap (16, 16', 16"), the separating gap (16, 16', 16") having a zigzag shape and having at least three mutually spaced damping gaps (20, 22, 24, 26, 28) that extend at an angle to an axis of rotation (18) of the rotor (12) and connecting gaps (30, 32, 34, 36, 38, 40) which adjoin said damping gaps and which connect the respective damping gaps (20, 22, 24, 26, 28) or form extensions thereto in the direction of the shroud edges (54, 56), characterized in that the gap width of the damping gaps (20, 22, 24, 26, 28) is reduced when the rotor (12) is rotated until the gap walls (42, 44) that form the damping gaps (20, 22, 24, 26, 28) abut one another and the damping gaps (20, 22, 24, 26, 28) are oriented at an angle of 60° to 90° to the axis of rotation (18) of the rotor (12).
  2. Rotor (12) according to claim 1, characterized in that at least two of the damping gaps (20, 22, 24, 26, 28) are oriented in parallel with one another.
  3. Rotor (12) according to either of the preceding claims, characterized in that the shroud (10) is split into individual shroud segments (46, 48), each shroud segment (46, 48) being associated with a rotor blade (14, 50) and being arranged thereon, and the individual shroud segments (46, 48) forming the separating gaps (16, 16', 16"), together with the respectively adjacent shroud segments in the peripheral direction.
  4. Rotor (12) according to either claim 1 or claim 2, characterized in that the shroud (10) is split into individual shroud segments, each shroud segment being associated with a group of at least two rotor blades and being arranged thereon, and the individual shroud segments forming the separating gaps, together with the respectively adjacent shroud segments in the peripheral direction.
  5. Rotor (12) according to either claim 3 or claim 4, characterized in that the rotor blades (14, 50) are designed to be integral with the shroud segments (46, 48).
  6. Rotor (12) according to any of the preceding claims, characterized in that at least one sealing lip (62, 64) is arranged on the outer periphery of the shroud (10).
  7. Rotor (12) according to any of the preceding claims, characterized in that the turbomachine is a low-pressure turbine, in particular a low-pressure turbine of an aircraft engine.
  8. Turbomachine, in particular a gas turbine, comprising at least one rotor (12) according to any of claims 1 to 6.
  9. Turbomachine according to claim 8, characterized in that the turbomachine is a low-pressure turbine, in particular a low-pressure turbine of an aircraft engine.
  10. Turbomachine according to either claim 8 or claim 9, characterized in that the rotor blades (14, 50) are components of an integral rotor construction.
EP09745441.7A 2008-05-13 2009-04-30 Rotor with shrouded blades of a turbomachine Not-in-force EP2294286B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102008023326A DE102008023326A1 (en) 2008-05-13 2008-05-13 Shroud for blades of a turbomachine and turbomachine
PCT/DE2009/000630 WO2009138057A2 (en) 2008-05-13 2009-04-30 Shroud for rotating blades of a turbo machine, and turbo machine

Publications (2)

Publication Number Publication Date
EP2294286A2 EP2294286A2 (en) 2011-03-16
EP2294286B1 true EP2294286B1 (en) 2019-02-27

Family

ID=41180361

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09745441.7A Not-in-force EP2294286B1 (en) 2008-05-13 2009-04-30 Rotor with shrouded blades of a turbomachine

Country Status (5)

Country Link
US (1) US8573939B2 (en)
EP (1) EP2294286B1 (en)
DE (1) DE102008023326A1 (en)
ES (1) ES2715798T3 (en)
WO (1) WO2009138057A2 (en)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2551460A1 (en) * 2011-07-29 2013-01-30 Siemens Aktiengesellschaft Blade group
US9840917B2 (en) * 2011-12-13 2017-12-12 United Technologies Corporation Stator vane shroud having an offset
US8894368B2 (en) * 2012-01-04 2014-11-25 General Electric Company Device and method for aligning tip shrouds
US20150354374A1 (en) * 2014-06-09 2015-12-10 General Electric Company Turbine blisk and method of manufacturing thereof
DE102016222720A1 (en) * 2016-11-18 2018-05-24 MTU Aero Engines AG Sealing system for an axial flow machine and axial flow machine
US10519783B2 (en) 2016-12-22 2019-12-31 General Electric Company Method for modifying a shroud and blade
KR101874243B1 (en) * 2017-03-31 2018-07-03 두산중공업 주식회사 Structure for damping vibration of bucket and turbo machine having the same
FR3084399B1 (en) * 2018-07-24 2021-05-14 Safran Aircraft Engines MOBILE DAWN FOR ONE WHEEL OF A TURBOMACHINE
CN110701102A (en) * 2019-09-29 2020-01-17 中国航发沈阳发动机研究所 Engine fan rotor with fan rotor blade structure pole provided with same

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1519898A (en) * 1967-02-24 1968-04-05 Creusot Forges Ateliers Improvements to mobile twist blades of turbo-machines
US4710102A (en) * 1984-11-05 1987-12-01 Ortolano Ralph J Connected turbine shrouding
GB2223276B (en) * 1988-09-30 1992-09-02 Rolls Royce Plc Turbine aerofoil blade
DE4015206C1 (en) * 1990-05-11 1991-10-17 Mtu Muenchen Gmbh
DE59202211D1 (en) * 1991-08-08 1995-06-22 Asea Brown Boveri Cover sheet for turbine with axial flow.
EP0536575B1 (en) * 1991-10-08 1995-04-05 Asea Brown Boveri Ag Shroud band for axial flow turbine
JPH07332003A (en) 1994-06-13 1995-12-19 Hitachi Ltd Turbine moving blade
US6164916A (en) * 1998-11-02 2000-12-26 General Electric Company Method of applying wear-resistant materials to turbine blades, and turbine blades having wear-resistant materials
GB0218060D0 (en) * 2002-08-03 2002-09-11 Alstom Switzerland Ltd Sealing arrangements
US7001152B2 (en) * 2003-10-09 2006-02-21 Pratt & Wiley Canada Corp. Shrouded turbine blades with locally increased contact faces
WO2006038879A1 (en) * 2004-10-07 2006-04-13 Volvo Aero Corporation Gas turbine intermediate structure and a gas turbine engine comprising the intermediate structure
US7762779B2 (en) * 2006-08-03 2010-07-27 General Electric Company Turbine blade tip shroud

Non-Patent Citations (1)

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

Also Published As

Publication number Publication date
WO2009138057A2 (en) 2009-11-19
US20110103956A1 (en) 2011-05-05
US8573939B2 (en) 2013-11-05
DE102008023326A1 (en) 2009-11-19
EP2294286A2 (en) 2011-03-16
WO2009138057A3 (en) 2010-08-26
ES2715798T3 (en) 2019-06-06

Similar Documents

Publication Publication Date Title
EP2294286B1 (en) Rotor with shrouded blades of a turbomachine
EP0846867B1 (en) Turbomachine with a transsonic compression stage
EP1320662B1 (en) Seal system
EP2647795B1 (en) Seal system for a turbo engine
EP2921716B1 (en) stator blade GROUP
DE102004055760A1 (en) Sealing arrangement for a turbine, blade, turbine containing same, method for sealing the gap between the rotating and stationary components of a turbine
EP3467261B1 (en) Method for producing a tandem stator blade segment
DE102014118427A1 (en) Damper arrangement for turbine rotor blades
DE102014114555A1 (en) Locking spacer assembly
CH701537B1 (en) Top cover plate with damping ribs for a rotor blade, which is inserted into a rotor disk of a turbine installation.
DE102015102396A1 (en) Turbine blade and method for balancing a tip shroud of a turbine blade and gas turbine
DE112013006105T5 (en) Turbine blades with mid-span shrouds
EP2514975B1 (en) Flow engine
EP2607625B1 (en) Turbomachine and stage of turbomachine
EP2410131A2 (en) Rotor of a turbomachine
EP1970535A1 (en) Shroud connection of a turbine blade
EP2607626A1 (en) Turbomachine and stage of a turbomachine
EP3327258A1 (en) Inlet guide vane for a turbo engine
EP1711689A1 (en) Sealing arrangement
EP3572624B1 (en) Turbo machine assembly
EP3521562B1 (en) Blade of a turbomachine
EP3219914A1 (en) Flow channel, corresponding blade row and turbomachine
DE10352787A1 (en) Guide vane grille and turbomachine with a vane grille
EP2453108B1 (en) Rotor for a turbomachine
WO2021110191A1 (en) Seal carrier for a turbomachine, having slot-like openings in the seal body

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: 20101111

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): 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 SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA RS

DAX Request for extension of the european patent (deleted)
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: 20170811

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: 20181004

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): 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 SE SI SK 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: 1101631

Country of ref document: AT

Kind code of ref document: T

Effective date: 20190315

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: 502009015638

Country of ref document: DE

REG Reference to a national code

Ref country code: ES

Ref legal event code: FG2A

Ref document number: 2715798

Country of ref document: ES

Kind code of ref document: T3

Effective date: 20190606

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20190227

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: 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: 20190227

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: 20190227

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: 20190227

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: 20190527

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: 20190627

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: 20190227

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

Ref country code: HR

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

Effective date: 20190227

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: 20190227

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: 20190528

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: 20190527

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: 20190627

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: 20190227

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: 20190227

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: 20190227

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: 20190227

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: 20190227

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: 20190227

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502009015638

Country of ref document: DE

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: 20190227

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20190430

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: 20190227

Ref country code: LU

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

Effective date: 20190430

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: 20190430

Ref country code: CH

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

Effective date: 20190430

26N No opposition filed

Effective date: 20191128

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: 20190227

Ref country code: BE

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

Effective date: 20190430

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: 20190227

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: 20190430

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

Ref country code: ES

Payment date: 20200516

Year of fee payment: 12

Ref country code: FR

Payment date: 20200421

Year of fee payment: 12

Ref country code: DE

Payment date: 20200423

Year of fee payment: 12

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 1101631

Country of ref document: AT

Kind code of ref document: T

Effective date: 20190430

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

Ref country code: GB

Payment date: 20200423

Year of fee payment: 12

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: 20190430

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

Ref country code: CY

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

Effective date: 20190227

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

Ref country code: HU

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

Effective date: 20090430

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: 20190227

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502009015638

Country of ref document: DE

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

Effective date: 20210430

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

Ref country code: GB

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

Effective date: 20210430

Ref country code: FR

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

Effective date: 20210430

Ref country code: DE

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

Effective date: 20211103

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: 20190227

REG Reference to a national code

Ref country code: ES

Ref legal event code: FD2A

Effective date: 20220801

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

Ref country code: ES

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

Effective date: 20210501