EP2394026A2 - Gas turbine blade for a turbomachine - Google Patents

Gas turbine blade for a turbomachine

Info

Publication number
EP2394026A2
EP2394026A2 EP10798489A EP10798489A EP2394026A2 EP 2394026 A2 EP2394026 A2 EP 2394026A2 EP 10798489 A EP10798489 A EP 10798489A EP 10798489 A EP10798489 A EP 10798489A EP 2394026 A2 EP2394026 A2 EP 2394026A2
Authority
EP
European Patent Office
Prior art keywords
gas turbine
turbine blade
connecting element
blade
receptacle
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.)
Granted
Application number
EP10798489A
Other languages
German (de)
French (fr)
Other versions
EP2394026B1 (en
Inventor
Frank Stiehler
Hans Peter Borufka
Patrick Prokopczuk
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 GmbH
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 GmbH filed Critical MTU Aero Engines GmbH
Publication of EP2394026A2 publication Critical patent/EP2394026A2/en
Application granted granted Critical
Publication of EP2394026B1 publication Critical patent/EP2394026B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • 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
    • F01D5/34—Rotor-blade aggregates of unitary construction, e.g. formed of sheet laminae
    • 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
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking

Definitions

  • the invention relates to a gas turbine blade, in particular a compressor and / or turbine blade, for a turbomachine.
  • the invention further relates to a shroud segment for arrangement on a gas turbine blade, a connection system referred to in the preamble of claim 10, a method referred to in the preamble of claim 12 for connecting a gas turbine blade with a connecting element and a rotor specified in the preamble of claim 13 Kind for a turbomachine.
  • each gas turbine blades When joining gas turbine blades and rotor disks or rings during assembly, repair or maintenance, each gas turbine blades must be positioned, displaced or rotated relative to adjacent gas turbine blades and thereby provided with a pre-tension (so-called pre-twist).
  • pre-twist a pre-tension
  • various connecting elements or special tools by means of which a corresponding mechanical load in the gas turbine blade in question can be introduced.
  • a disadvantage of the known fasteners is the fact that they are relatively expensive, do not allow optimum load transfer into the gas turbine blade and even damage the gas turbine blade in the load application.
  • the object of the present invention is to enable an improved possibility for load introduction into a gas turbine blade.
  • a gas turbine blade with the features of claim 1 a shroud segment with the features of claim 8 for placement on a gas turbine blade, a connection system with the features of patent claim 10, a method having the features of claim 12 for connecting a Gas turbine blade solved with a connecting element and by a rotor having the features of claim 13 for a turbomachine.
  • Advantageous embodiments of the invention are specified in the respective subclaims.
  • An improved possibility for load introduction into a gas turbine blade is made possible according to the invention in that the gas turbine blade comprises at least one receptacle for the form-fitting arrangement of a connecting element, by means of which a mechanical load can be introduced into the gas turbine blade.
  • a geometry of the gas turbine blade according to the invention is designed such that the gas turbine blade has a receptacle which forms an integral interface for the form-fitting arrangement of a corresponding connecting element. Due to the integrated receptacle, the gas turbine blade and the connecting element can engage in one another in a form-fitting manner, so that mechanical loads can be transmitted normally, that is to say at right angles to the surfaces of the two connection partners.
  • the connecting element which may be formed, for example, as a tool, pin, mandrel or the like, is in this way easily and without affecting the remaining gas turbine blade areas form fit introduced or inserted into the receptacle and can be solved if necessary correspondingly easy again from the gas turbine blade.
  • the gas turbine blade can be formed weight neutral or even reduced weight and allows due to the simple structural design a short tolerance chain with a correspondingly high repeatability.
  • the respective geometry of the receptacle for example its arrangement, form-fitting depth or boundary, may be selected depending on the geometry or the intended use of the respective gas turbine blade.
  • a radially inner end region of the gas turbine blade for connecting the gas turbine blade to a rotor disk or a rotor ring of the turbomachine and / or a radially outer end region of the gas turbine blade is designed as a shroud segment.
  • the gas turbine blade can be designed as a compressor and / or turbine blade.
  • a radially outer end region designed as a shroud segment serves for damping blade vibrations and is particularly suitable when using the gas turbine blades in a rear turbine stage.
  • the shroud segment reduces the flow around the gas turbine blade tip and thereby increases the efficiency of the associated turbomachine.
  • the shroud segment can in principle be formed in one piece or in several parts with the gas turbine blade.
  • the receptacle is formed on the radially outer end region of the gas turbine blade. By the receptacle at the radially outer end portion of the gas turbine blade is formed, the receptacle is particularly accessible. In this way, a corresponding connecting element, for example a tool, can be correspondingly easily introduced into the receptacle in order to apply a mechanical load to the gas turbine blade.
  • a weight optimization of the gas turbine blade is made possible in a further embodiment in that it is designed as a hollow blade and comprises at least one cavity.
  • the receptacle is formed as a core exit region of the cavity. This allows a particularly space-saving arrangement of the recording without affecting the other gas turbine blade areas. Further advantages result from the gas turbine blade being integrally formed with the receptacle and / or as a cast part. As a result, the gas turbine blade mechanically particularly stable, inexpensive and easy to manufacture.
  • the actual geometry of the gas turbine blade can be completely or at least largely matched to a target geometry.
  • Geometry can be approximated.
  • electrochemical drilling PECM drilling
  • Another aspect of the invention relates to a shroud segment for arrangement on a gas turbine blade, in particular a gas turbine blade according to one of the preceding exemplary embodiments, wherein an improved possibility for load introduction into a gas turbine blade according to the invention is made possible by the shroud segment a receptacle for the positive arrangement of a connecting element, by means of which a mechanical one
  • Last in the shroud segment is introduced, comprises.
  • the resulting advantages are to be taken from the preceding descriptions, wherein advantageous embodiments of the gas turbine blade are to be regarded as advantageous embodiments of the shroud segment and vice versa.
  • the shroud segment can in principle be made in one piece with the gas turbine blade. formed or initially manufactured as a single part and then connected to the gas turbine blade.
  • the shroud segment has two oppositely arranged and in a longitudinal section substantially Z-shaped contact surfaces for attaching corresponding contact surfaces of two further shroud segments.
  • connection system with a gas turbine blade, in particular a compressor and / or turbine blade for a turbomachine, and with a connecting element, by means of which a mechanical load in the gas turbine blade can be introduced, with an improved possibility for load introduction into the gas turbine blade according to the invention is thereby made possible that the gas turbine blade comprises a correspondingly formed with the connecting element receptacle for the positive arrangement of the connecting element. Due to the integrated receptacle, the gas turbine blade and the corresponding connecting element can engage in one another in a form-fitting manner, so that mechanical loads can be transmitted normally, that is to say at right angles to the surfaces of the two connection partners.
  • the gas turbine blade can be provided, for example, before connecting to a shaft of the turbomachine particularly simple and damage-free with a so-called pre-twist.
  • the gas turbine blade can be provided in the context of a repair or overhaul with a so-called re-twist, so that the gas turbine blade can be readjusted.
  • the receptacle as mecanical tool, in particular as mecanical wrench, in particular as a hexagon wrench, for applying the gas turbine blade are formed with a torque.
  • a load introduction into the gas turbine blade can be carried out in a particularly simple and cost-effective manner, without the need for expensive special tools.
  • This also increases the ease of maintenance of the gas turbine blade or a turbomachine provided with this.
  • the receptacle and the connecting element may alternatively or in addition to an Allen-like configuration basically also slot, Pozidriv, Torx, Tri-Wing, Torq set or tensioner-like design.
  • Another aspect of the invention relates to a method for connecting a gas turbine blade, in particular a compressor and / or turbine blade for a turbomachine, with a connecting element, by means of which a mechanical load can be introduced into the gas turbine blade, wherein an improved possibility for load introduction into the gas turbine blade according to the invention is thereby made possible that the connecting element is arranged in a form-fitting manner in a receptacle of the gas turbine blade formed corresponding to the connecting element. Due to the integrated Aufhahme the gas turbine blade and the corresponding connecting element can be arranged positively in one another, so that mechanical loads normal, that can be transmitted perpendicular to the surfaces of the two connection partners.
  • a further aspect of the invention relates to a rotor for a turbomachine with a rotor disk joined with a blade ring or with a rotor ring grooved with a blade ring, wherein according to the invention it is provided that the blade ring has at least one gas turbine blade, the at least one receptacle for the positive arrangement of a Includes connecting element, wherein by means of the connecting element, a mechanical load in the gas turbine blade can be introduced.
  • the rotor is designed as a blisk ("bladed disk”) or as a bling ("bladed ring”) for a compressor and / or for a turbine of a turbomachine, in particular a thermal gas turbine. As a result, a particularly high structural freedom is given.
  • Figure 1 is a schematic perspective view of three gas turbine blades according to the invention, which are arranged on a rotor disk.
  • FIG. 2 is an enlarged plan view of the detail in shown in FIG. 1;
  • FIG. 3 is a schematic side view of a gas turbine blade shown in FIG. 1; FIG.
  • FIG. 4 is a schematic bottom view of the gas turbine blade shown in FIG. 3; FIG. and
  • FIG. 5 is a schematic sectional side view of the gas turbine blade along the in
  • Fig. 4 shown section line V-V.
  • FIG. 1 shows a schematic perspective view of three gas turbine blades 10 according to the invention, which are arranged on a rotor disk 12.
  • an integrally bladed rotor (so-called blisk or "bladed disk”) can be used for a compressor and / or for a turbine of a turbomachine, in particular a thermal gas turbine
  • a rotor ring (not shown) may also be used instead of a rotor disk 12, whereby a so-called bling ("bladed ring”) can be produced Fig. 2).
  • the shroud segments 16 and their respective gas turbine blades 10 are included formed in the present embodiment in one piece as castings.
  • each gas turbine blade 10 is finished by appropriate post-processing methods such as PECM drilling.
  • each gas turbine blade 10 also has an integral receptacle 18, in which a connecting element (not shown) can be arranged in a form-fitting manner.
  • the receptacles 18 are each formed at the radially outer end portion 14a of the gas turbine blades 10 in the shroud segments 16 as mecanicsechskantaufhahmen.
  • hexagonal key-shaped connecting element can be easily inserted into the respective receptacle 18 releasably to pressurize the gas turbine blade 10 in question with a torque.
  • each gas turbine blade 10 can be easily, without damage and provided without the need for special tool with a so-called pre-twist.
  • Fig. 2 shows an enlarged plan view of the detail shown in Fig. 1 ⁇ .
  • each shroud segment 16 has two contact surfaces (so-called Z-Shroud) arranged opposite each other and substantially Z-shaped in longitudinal section for attaching corresponding contact surfaces 20 of the adjacent shroud segments 16.
  • each shroud segment 16 comprises two opposing sealing fins 22 which, in particular during a rotation of the rotor 12 in a abradable region, rub against a sealing structure of an associated turbomachine.
  • FIG. 3 shows, for further clarification, a schematic side view of one of the gas turbine blades 10 shown in FIG. 1.
  • FIG. 3 will be explained below in conjunction with FIGS. 4 and 5.
  • FIG. 4 shows a schematic bottom view of the gas turbine blade 10 shown in FIG. 3
  • FIG. 5 shows a schematic sectional side view of the gas turbine blade 10 along the section line VV shown in FIG.
  • the gas turbine blade 10 in the present case is designed as a hollow blade and comprises at least one cavity 24.
  • the receptacle 18 is in turn formed as a core exit region of the cavity 24.
  • a fir tree structure 26 formed on a radially inner end region 14b of the gas turbine blade can be seen for joining the gas turbine blade 10 to the rotor disk 12.
  • the geometry and form-fitting depth of the receptacle 18 can be formed as a function of the shroud segment geometry be, for example, the core exit area of the cavity 24, the arrangement of the contact surfaces 20 and / or a geometry of the sealing fins 22 can be considered.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The invention relates to a gas turbine blade (10), in particular a compressor blade and/or turbine blade, for a turbomachine, wherein the gas turbine blade (10) comprises at least one receptacle (18) for arranging a connecting element in a form-closed manner, by means of which connecting element a mechanical load can be applied to the gas turbine blade (10). The invention further relates to an shrouding band segment (16) for arrangement on a gas turbine blade (10), a connection system having a gas turbine blade (10) and having a connecting element, a method for connecting a gas turbine blade (10) to a connecting element, and a rotor for a turbomachine having a rotor disk (12) joined to a blade ring or having a rotor ring joined to a blade ring.

Description

Gasturbinenschaufel für eine Strömungsmaschine  Gas turbine blade for a turbomachine
Beschreibung Die Erfindung betrifft eine Gasturbinenschaufel, insbesondere eine Verdichter- und/oder Turbinenschaufel, für eine Strömungsmaschine. Die Erfindung betrifft weiterhin ein Deckbandsegment zur Anordnung an einer Gasturbinenschaufel, ein Verbindungssystem der im Oberbegriff des Patentanspruchs 10 genannten Art, ein Verfahren der im Oberbegriff des Patentanspruchs 12 genannten Art zum Verbinden einer Gasturbinenschaufel mit einem Verbindungselement sowie einen Rotor der im Oberbegriff des Patentanspruchs 13 angegebenen Art für eine Strömungsmaschine. The invention relates to a gas turbine blade, in particular a compressor and / or turbine blade, for a turbomachine. The invention further relates to a shroud segment for arrangement on a gas turbine blade, a connection system referred to in the preamble of claim 10, a method referred to in the preamble of claim 12 for connecting a gas turbine blade with a connecting element and a rotor specified in the preamble of claim 13 Kind for a turbomachine.
Beim Fügen von Gasturbinenschaufeln und Rotorscheiben oder -ringen während der Montage, Reparatur oder Instandhaltung muss jede Gasturbinenschaufeln positioniert, verschoben oder ge- genüber benachbarten Gasturbinenschaufeln verdreht und hierdurch mit einer Vorspannung (sog. Pre-Twist) versehen werden können. Zu diesem Zweck existieren verschiedene Verbindungselemente bzw. Spezialwerkzeuge, mittels welchen eine entsprechende mechanische Last in die betreffende Gasturbinenschaufel einleitbar ist. Als nachteilig an den bekannten Verbindungselementen ist dabei der Umstand anzusehen, dass diese vergleichsweise teuer sind, keine optimale Lasteinleitung in die Gasturbinenschaufel ermöglichen und die Gasturbinenschaufel bei der Lasteinleitung sogar beschädigen können. When joining gas turbine blades and rotor disks or rings during assembly, repair or maintenance, each gas turbine blades must be positioned, displaced or rotated relative to adjacent gas turbine blades and thereby provided with a pre-tension (so-called pre-twist). For this purpose, there are various connecting elements or special tools, by means of which a corresponding mechanical load in the gas turbine blade in question can be introduced. A disadvantage of the known fasteners is the fact that they are relatively expensive, do not allow optimum load transfer into the gas turbine blade and even damage the gas turbine blade in the load application.
Aufgabe der vorliegenden Erfindung ist es, eine verbesserte Möglichkeit zur Lasteinleitung in ei- ne Gasturbinenschaufel zu ermöglichen. The object of the present invention is to enable an improved possibility for load introduction into a gas turbine blade.
Die Aufgabe wird erfindungsgemäß durch eine Gasturbinenschaufel mit den Merkmalen des Patentanspruchs 1, ein Deckbandsegment mit den Merkmalen des Patentanspruchs 8 zur Anordnung an einer Gasturbinenschaufel, ein Verbindungssystem mit den Merkmalen des Patentan- spruchs 10, ein Verfahren mit den Merkmalen des Patentanspruchs 12 zum Verbinden einer Gasturbinenschaufel mit einem Verbindungselement sowie durch einen Rotor mit den Merkmalen des Patentanspruchs 13 für eine Strömungsmaschine gelöst. Vorteilhafte Ausgestaltungen der Erfindung sind in den jeweiligen Unteransprüchen angegeben. Eine verbesserte Möglichkeit zur Lasteinleitung in eine Gasturbinenschaufel ist erfindungsgemäß dadurch ermöglicht, dass die Gasturbinenschaufel mindestens eine Aufnahme zum formschlüssigen Anordnen eines Verbindungselements, mittels welchem eine mechanische Last in die Gasturbinenschaufel einleitbar ist, umfasst. Mit anderen Worten ist eine Geometrie der erfindungsgemäßen Gasturbinenschaufel derart ausgebildet, dass die Gasturbinenschaufel eine Aufnahme aufweist, welche eine integrale Schnittstelle zur formschlüssigen Anordnung eines korrespondierenden Verbindungselements bildet. Durch die integrierte Aufnahme können die Gasturbinenschaufel und das Verbindungselement formschlüssig ineinander greifen, so dass mechanische Lasten normal, das heißt rechtwinklig zu den Flächen der beiden Verbindungspartner übertragen werden können. Das Verbindungselement, welches beispielsweise als Werkzeug, Zapfen, Dorn oder dergleichen ausgebildet sein kann, ist auf diese Weise einfach und ohne Beeinträchtigung der übrigen Gasturbinenschaufelbereiche formschlüssig in die Aufnahme einbringbar bzw. einsteckbar und kann bei Bedarf entsprechend einfach wieder von der Gasturbinenschaufel gelöst werden. Mechanische Lasten können hierdurch einfach, flexibel und ohne Beschädigung der Gasturbinenschaufel in diese eingeleitet werden. Zudem kann die Gasturbinenschaufel gewichtsneutral oder sogar gewichtsreduziert ausgebildet sein und ermöglicht aufgrund des einfachen konstruktiven Aufbaus eine kurze Toleranzkette mit entsprechend hoher Wiederholgenauigkeit. Die jeweilige Geometrie der Aufnahme, beispielsweise ihre Anordnung, Formschlusstiefe oder Berandung, kann in Abhängigkeit der Geometrie oder des Einsatzzwecks der jeweiligen Gasturbinenschaufel gewählt sein. The object is achieved by a gas turbine blade with the features of claim 1, a shroud segment with the features of claim 8 for placement on a gas turbine blade, a connection system with the features of patent claim 10, a method having the features of claim 12 for connecting a Gas turbine blade solved with a connecting element and by a rotor having the features of claim 13 for a turbomachine. Advantageous embodiments of the invention are specified in the respective subclaims. An improved possibility for load introduction into a gas turbine blade is made possible according to the invention in that the gas turbine blade comprises at least one receptacle for the form-fitting arrangement of a connecting element, by means of which a mechanical load can be introduced into the gas turbine blade. In other words, a geometry of the gas turbine blade according to the invention is designed such that the gas turbine blade has a receptacle which forms an integral interface for the form-fitting arrangement of a corresponding connecting element. Due to the integrated receptacle, the gas turbine blade and the connecting element can engage in one another in a form-fitting manner, so that mechanical loads can be transmitted normally, that is to say at right angles to the surfaces of the two connection partners. The connecting element, which may be formed, for example, as a tool, pin, mandrel or the like, is in this way easily and without affecting the remaining gas turbine blade areas form fit introduced or inserted into the receptacle and can be solved if necessary correspondingly easy again from the gas turbine blade. Mechanical loads can thereby be introduced easily, flexibly and without damaging the gas turbine blade. In addition, the gas turbine blade can be formed weight neutral or even reduced weight and allows due to the simple structural design a short tolerance chain with a correspondingly high repeatability. The respective geometry of the receptacle, for example its arrangement, form-fitting depth or boundary, may be selected depending on the geometry or the intended use of the respective gas turbine blade.
In einer vorteilhaften Ausgestaltung der Erfindung ist vorgesehen, dass ein radial innerer Endbereich der Gasturbinenschaufel zur Verbindung der Gasturbinenschaufel mit einer Rotorscheibe oder einem Rotorring der Strömungsmaschine und/oder ein radial äußerer Endbereich der Gasturbinenschaufel als Deckbandsegment ausgebildet ist. Mit Hilfe eines derartigen radial inneren Endbereichs wird ein einfaches Fügen von Gasturbinenschaufel und Rotorscheibe bzw. Rotorring ermöglicht. Die Gasturbinenschaufel kann dabei als Verdichter- und/oder Turbinenschaufel ausgebildet sein. Ein als Deckbandsegment ausgebildeter radial äußerer Endbereich dient zur Dämpfung von Schaufelschwingungen und eignet sich insbesondere bei einer Verwendung der Gasturbinenschaufeln in einer hinteren Turbinenstufe. Weiterhin vermindert das Deckbandsegment die Umströmung der Gasturbinenschaufelspitze und erhöht hierdurch den Wirkungsgrad der zugeordneten Strömungsmaschine. Das Deckbandsegment kann dabei grundsätzlich einteilig oder mehrteilig mit der Gasturbinenschaufel ausgebildet sein. In einer weiteren vorteilhaften Ausgestaltung der Erfindung ist vorgesehen, dass die Aufnahme am radial äußeren Endbereich der Gasturbinenschaufel ausgebildet ist. Indem die Aufnahme am radial äußeren Endbereich der Gasturbinenschaufel ausgebildet ist, ist die Aufnahme besonders gut zugänglich. Hierdurch kann ein korrespondierendes Verbindungselement, beispielsweise ein Werkzeug, entsprechend einfach in die Aufnahme eingebracht werden, um die Gasturbinen- schaufel mit einer mechanischen Last zu beaufschlagen. In an advantageous embodiment of the invention, it is provided that a radially inner end region of the gas turbine blade for connecting the gas turbine blade to a rotor disk or a rotor ring of the turbomachine and / or a radially outer end region of the gas turbine blade is designed as a shroud segment. With the aid of such a radially inner end region, a simple joining of gas turbine blade and rotor disk or rotor ring is made possible. The gas turbine blade can be designed as a compressor and / or turbine blade. A radially outer end region designed as a shroud segment serves for damping blade vibrations and is particularly suitable when using the gas turbine blades in a rear turbine stage. Furthermore, the shroud segment reduces the flow around the gas turbine blade tip and thereby increases the efficiency of the associated turbomachine. The shroud segment can in principle be formed in one piece or in several parts with the gas turbine blade. In a further advantageous embodiment of the invention it is provided that the receptacle is formed on the radially outer end region of the gas turbine blade. By the receptacle at the radially outer end portion of the gas turbine blade is formed, the receptacle is particularly accessible. In this way, a corresponding connecting element, for example a tool, can be correspondingly easily introduced into the receptacle in order to apply a mechanical load to the gas turbine blade.
Eine Gewichtsoptimierung der Gasturbinenschaufel ist in weiterer Ausgestaltung dadurch ermöglicht, dass diese als Hohlschaufel ausgebildet ist und zumindest einen Hohlraum umfasst. A weight optimization of the gas turbine blade is made possible in a further embodiment in that it is designed as a hollow blade and comprises at least one cavity.
Dabei hat es sich weiterhin als vorteilhaft gezeigt, dass die Aufnahme als Kernaustrittsbereich des Hohlraums ausgebildet ist. Dies ermöglicht eine besonders bauraumsparende Anordnung der Aufnahme ohne Beeinträchtigung der übrigen Gasturbinenschaufelbereiche. Weitere Vorteile ergeben sich, indem die Gasturbinenschaufel einteilig mit der Aufnahme und/oder als Gussteil ausgebildet ist. Hierdurch kann die Gasturbinenschaufel mechanisch besonders stabil, kostengünstig und einfach hergestellt werden. It has also been shown to be advantageous that the receptacle is formed as a core exit region of the cavity. This allows a particularly space-saving arrangement of the recording without affecting the other gas turbine blade areas. Further advantages result from the gas turbine blade being integrally formed with the receptacle and / or as a cast part. As a result, the gas turbine blade mechanically particularly stable, inexpensive and easy to manufacture.
Indem zumindest ein Oberflächenbereich der Gasturbinenschaufel feinbearbeitet ist, kann die Ist- Geometrie der Gasturbinenschaufel vollständig oder zumindest weitgehend an eine Soll-By at least one surface area of the gas turbine blade being finished, the actual geometry of the gas turbine blade can be completely or at least largely matched to a target geometry.
Geometrie angenähert werden. Zum Feinbearbeiten können beispielsweise elektrochemische Bohrverfahren (PECM-Bohren) verwendet werden. Alternativ oder zusätzlich können jedoch auch weitere mechanische und/oder elektrochemische Abtrag- und/oder Auftragverfahren zur Feinbearbeitung vorgesehen sein. Geometry can be approximated. For fine machining, for example, electrochemical drilling (PECM drilling) can be used. Alternatively or additionally, however, it is also possible to provide further mechanical and / or electrochemical removal and / or application methods for fine machining.
Ein weiterer Aspekt der Erfindung betrifft ein Deckbandsegment zur Anordnung an einer Gasturbinenschaufel, insbesondere einer Gasturbinenschaufel nach einem der vorhergehenden Ausfuhrungsbeispiele, wobei eine verbesserte Möglichkeit zur Lasteinleitung in eine Gasturbinenschaufel erfindungsgemäß dadurch ermöglicht ist, dass das Deckbandsegment eine Aufnahme zum formschlüssigen Anordnen eines Verbindungselements, mittels welchem eine mechanischeAnother aspect of the invention relates to a shroud segment for arrangement on a gas turbine blade, in particular a gas turbine blade according to one of the preceding exemplary embodiments, wherein an improved possibility for load introduction into a gas turbine blade according to the invention is made possible by the shroud segment a receptacle for the positive arrangement of a connecting element, by means of which a mechanical one
Last in das Deckbandsegment einleitbar ist, umfasst. Die sich hieraus ergebenden Vorteile sind den vorhergehenden Beschreibungen zu entnehmen, wobei vorteilhafte Ausgestaltungen der Gasturbinenschaufel als vorteilhafte Ausgestaltungen des Deckbandsegments und umgekehrt anzusehen sind. Das Deckbandsegment kann grundsätzlich einteilig mit der Gasturbinenschaufel aus- gebildet oder zunächst als Einzelteil hergestellt und anschließend mit der Gasturbinenschaufel verbunden sein. Last in the shroud segment is introduced, comprises. The resulting advantages are to be taken from the preceding descriptions, wherein advantageous embodiments of the gas turbine blade are to be regarded as advantageous embodiments of the shroud segment and vice versa. The shroud segment can in principle be made in one piece with the gas turbine blade. formed or initially manufactured as a single part and then connected to the gas turbine blade.
In einer vorteilhaften Ausgestaltung der Erfindung ist vorgesehen, dass das Deckbandsegment zwei einander gegenüberliegend angeordnete und im Längsschnitt im Wesentlichen Z-fÖrmige Kontaktflächen zur Anlagerung korrespondierender Kontaktflächen zweier weiterer Deckbandsegmente aufweist. Hierdurch können sich benachbarte Gasturbinenschaufeln, die jeweils mit einem derartigen Deckbandsegment versehen sind, während des Betriebs einer zugeordneten Strömungsmaschine bzw. eines mit diesen Gasturbinenschaufeln versehenen Rotors paarweise aneinander abstützen, wodurch ein mechanisch besonders stabiles Deckband geschaffen wird. Ein unerwünschtes Verbiegen oder Verdrehen der Gasturbinenschaufel während des Betriebs wird hierdurch ebenfalls minimiert. In an advantageous embodiment of the invention, it is provided that the shroud segment has two oppositely arranged and in a longitudinal section substantially Z-shaped contact surfaces for attaching corresponding contact surfaces of two further shroud segments. As a result, adjacent gas turbine blades, which are each provided with such a shroud segment, during operation of an associated turbomachine or a rotor provided with these gas turbine blades pairs abut each other, creating a mechanically particularly stable shroud is created. Undesirable bending or twisting of the gas turbine blade during operation is also minimized thereby.
Ein weiterer Aspekt der Erfindung betrifft ein Verbindungssystem mit einer Gasturbinenschaufel, insbesondere einer Verdichter- und/oder Turbinenschaufel für eine Strömungsmaschine, und mit einem Verbindungselement, mittels welchem eine mechanische Last in die Gasturbinenschaufel einleitbar ist, wobei eine verbesserte Möglichkeit zur Lasteinleitung in die Gasturbinenschaufel erfindungsgemäß dadurch ermöglicht ist, dass die Gasturbinenschaufel eine korrespondierend mit dem Verbindungselement ausgebildete Aufnahme zum formschlüssigen Anordnen des Verbindungselements umfasst. Durch die integrierte Aufnahme können die Gasturbinenschaufel und das korrespondierende Verbindungselement formschlüssig ineinander greifen, so dass mechanische Lasten normal, das heißt rechtwinklig zu den Flächen der beiden Verbindungspartner übertragen werden können. Somit ist eine einfache, lösbare und beschädigungsfreie Lastein- und/oder -ausleitung in bzw. aus der Gasturbinenschaufel möglich. Auf diese Weise kann die Gasturbinenschaufel beispielsweise vor dem Verbinden mit einer Welle der Strömungsmaschine besonders einfach und beschädigungsfrei mit einem sogenannten Pre-Twist versehen werden. Entsprechend einfach und beschädigungsfrei kann die Gasturbinenschaufel im Rahmen einer Reparatur oder Überholung mit einem sogenannten Re-Twist versehen werden, so dass die Gasturbinenschaufel nachgestellt werden kann. Weitere Vorteile sind den vorhergehenden Beschreibungen zu entnehmen, wobei vorteilhafte Ausgestaltungen der Gasturbinenschaufel bzw. des Deckbandelseg- ments als vorteilhafte Ausgestaltungen des Verbindungssystems und umgekehrt anzusehen sind. Another aspect of the invention relates to a connection system with a gas turbine blade, in particular a compressor and / or turbine blade for a turbomachine, and with a connecting element, by means of which a mechanical load in the gas turbine blade can be introduced, with an improved possibility for load introduction into the gas turbine blade according to the invention is thereby made possible that the gas turbine blade comprises a correspondingly formed with the connecting element receptacle for the positive arrangement of the connecting element. Due to the integrated receptacle, the gas turbine blade and the corresponding connecting element can engage in one another in a form-fitting manner, so that mechanical loads can be transmitted normally, that is to say at right angles to the surfaces of the two connection partners. Thus, a simple, releasable and damage-free load input and / or -ausleitung in or out of the gas turbine blade is possible. In this way, the gas turbine blade can be provided, for example, before connecting to a shaft of the turbomachine particularly simple and damage-free with a so-called pre-twist. Correspondingly simple and free of damage, the gas turbine blade can be provided in the context of a repair or overhaul with a so-called re-twist, so that the gas turbine blade can be readjusted. Further advantages can be found in the preceding descriptions, wherein advantageous embodiments of the gas turbine blade or of the cover band segment are to be regarded as advantageous embodiments of the connection system and vice versa.
In einer vorteilhaften Ausgestaltung der Erfindung ist vorgesehen, dass die Aufnahme als Innen- mehrkantaufhahme, insbesondere als Innensechskantaufhahme, und das Verbindungselement als Mehrkantschlüssel, insbesondere als Sechskantschlüssel, zum Beaufschlagen der Gasturbinen- schaufel mit einem Drehmoment ausgebildet sind. Hierdurch kann auf besonders einfache und kostengünstige Weise eine Lasteinleitung in die Gasturbinenschaufel erfolgen, ohne dass teures Spezialwerkzeug erforderlich ist. Dies erhöht zudem die Wartungsfreundlichkeit der Gasturbi- nenschaufel bzw. einer mit dieser versehenen Strömungsmaschine. Dabei können die Aufnahme und das Verbindungselement alternativ oder zusätzlich zu einer Inbus-artigen Ausgestaltung grundsätzlich auch Schlitz-, Pozidriv-, Torx-, Tri-Wing-, Torq-Set- oder Spanner-artig ausgebildet sein. Ein weiterer Aspekt der Erfindung betrifft ein Verfahren zum Verbinden einer Gasturbinenschaufel, insbesondere einer Verdichter- und/oder Turbinenschaufel für eine Strömungsmaschine, mit einem Verbindungselement, mittels welchem eine mechanische Last in die Gasturbinenschaufel einleitbar ist, wobei eine verbesserte Möglichkeit zur Lasteinleitung in die Gasturbinenschaufel erfindungsgemäß dadurch ermöglicht ist, dass das Verbindungselement formschlüssig in einer korrespondierend mit dem Verbindungselement ausgebildeten Aufhahme der Gasturbinenschaufel angeordnet wird. Durch die integrierte Aufhahme können die Gasturbinenschaufel und das korrespondierende Verbindungselement formschlüssig ineinander angeordnet werden, so dass mechanische Lasten normal, das heißt rechtwinklig zu den Flächen der beiden Verbindungspartner übertragen werden können. Somit ist eine einfache, lösbare und beschädigungsfreie Lastein- und/oder -ausleitung in bzw. aus der Gasturbinenschaufel möglich. Weitere Vorteile sind den vorhergehenden Beschreibungen zu entnehmen, wobei vorteilhafte Ausgestaltungen der Gasturbinenschaufel, des Deckbandelsegments und/oder des Verbindungssystems als vorteilhafte Ausgestaltungen des Verfahrens und umgekehrt anzusehen sind. Ein weiterer Aspekt der Erfindung betrifft einen Rotor für eine Strömungsmaschine mit einer mit einem Schaufelkranz gefügten Rotorscheibe oder mit einem mit einem Schaufelkranz gefugten Rotorring, wobei erfindungsgemäß vorgesehen ist, dass der Schaufelkranz wenigstens eine Gas- turbinenschaufel aufweist, die mindestens eine Aufhahme zum formschlüssigen Anordnen eines Verbindungselements umfasst, wobei mittels des Verbindungselements eine mechanische Last in die Gasturbinenschaufel einleitbar ist. Die sich hieraus ergebenden Vorteile sind den vorhergehenden Beschreibungen zu entnehmen, wobei vorteilhafte Ausgestaltungen der Gasturbinenschaufel, des Deckbandelsegments, des Verbindungssystems und/oder des Verfahrens zum Verbinden einer Gasturbinenschaufel mit einem Verbindungselement als vorteilhafte Ausgestaltungen des Rotors und umgekehrt anzusehen sind. Dabei hat es sich als vorteilhaft gezeigt, wenn der Rotor als Blisk („Bladed Disk") oder als Bling („Bladed Ring") für einen Verdichter und/oder für eine Turbine einer Strömungsmaschine, insbesondere einer thermischen Gasturbine, ausgebildet ist. Hierdurch ist eine besonders hohe konstruktive Freiheit gegeben. In an advantageous embodiment of the invention it is provided that the receptacle as Innenkanzaufhahme, in particular as Innensechskantaufhahme, and the connecting element as Polygonal wrench, in particular as a hexagon wrench, for applying the gas turbine blade are formed with a torque. As a result, a load introduction into the gas turbine blade can be carried out in a particularly simple and cost-effective manner, without the need for expensive special tools. This also increases the ease of maintenance of the gas turbine blade or a turbomachine provided with this. In this case, the receptacle and the connecting element may alternatively or in addition to an Allen-like configuration basically also slot, Pozidriv, Torx, Tri-Wing, Torq set or tensioner-like design. Another aspect of the invention relates to a method for connecting a gas turbine blade, in particular a compressor and / or turbine blade for a turbomachine, with a connecting element, by means of which a mechanical load can be introduced into the gas turbine blade, wherein an improved possibility for load introduction into the gas turbine blade according to the invention is thereby made possible that the connecting element is arranged in a form-fitting manner in a receptacle of the gas turbine blade formed corresponding to the connecting element. Due to the integrated Aufhahme the gas turbine blade and the corresponding connecting element can be arranged positively in one another, so that mechanical loads normal, that can be transmitted perpendicular to the surfaces of the two connection partners. Thus, a simple, releasable and damage-free load input and / or -ausleitung in or out of the gas turbine blade is possible. Further advantages can be found in the preceding descriptions, wherein advantageous embodiments of the gas turbine blade, the Deckbandelsegments and / or the connection system are to be regarded as advantageous embodiments of the method and vice versa. A further aspect of the invention relates to a rotor for a turbomachine with a rotor disk joined with a blade ring or with a rotor ring grooved with a blade ring, wherein according to the invention it is provided that the blade ring has at least one gas turbine blade, the at least one receptacle for the positive arrangement of a Includes connecting element, wherein by means of the connecting element, a mechanical load in the gas turbine blade can be introduced. The resulting advantages are to be taken from the preceding descriptions, wherein advantageous embodiments of the gas turbine blade, the Deckbandelsegments, the connection system and / or the method for connecting a gas turbine blade with a connecting element are to be regarded as advantageous embodiments of the rotor and vice versa. It has proven to be advantageous if the rotor is designed as a blisk ("bladed disk") or as a bling ("bladed ring") for a compressor and / or for a turbine of a turbomachine, in particular a thermal gas turbine. As a result, a particularly high structural freedom is given.
Weitere Merkmale der Erfindung ergeben sich aus den Ansprüchen, den Ausführungsbeispielen sowie anhand der Zeichnungen. Die vorstehend in der Beschreibung genannten Merkmale und Merkmalskombinationen sowie die nachfolgend in den Ausführungsbeispielen genannten Merkmale und Merkmalskombinationen sind nicht nur in der jeweils angegebenen Kombination, sondern auch in anderen Kombinationen oder in Alleinstellung verwendbar, ohne den Rahmen der Erfindung zu verlassen. Dabei zeigen: Further features of the invention will become apparent from the claims, the exemplary embodiments and with reference to the drawings. The features and feature combinations mentioned above in the description as well as the features and feature combinations mentioned below in the exemplary embodiments can be used not only in the particular combination indicated, but also in other combinations or in isolation, without departing from the scope of the invention. Showing:
Fig. 1 eine schematische Perspektivansicht von drei erfindungsgemäßen Gasturbinenschaufeln, die auf einer Rotorscheibe angeordnet sind; Figure 1 is a schematic perspective view of three gas turbine blades according to the invention, which are arranged on a rotor disk.
Fig. 2 eine vergrößerte Aufsicht des in Fig. 1 gezeigten Details Π; FIG. 2 is an enlarged plan view of the detail in shown in FIG. 1; FIG.
Fig. 3 eine schematische Seitenansicht einer in Fig. 1 gezeigten Gasturbinenschaufel; FIG. 3 is a schematic side view of a gas turbine blade shown in FIG. 1; FIG.
Fig. 4 eine schematische Unteransicht der in Fig. 3 gezeigten Gasturbinenschaufel; und FIG. 4 is a schematic bottom view of the gas turbine blade shown in FIG. 3; FIG. and
Fig. 5 eine schematische seitliche Schnittansicht der Gasturbinenschaufel entlang der in 5 is a schematic sectional side view of the gas turbine blade along the in
Fig. 4 gezeigten Schnittlinie V-V.  Fig. 4 shown section line V-V.
Fig. 1 zeigt eine schematische Perspektivansicht von drei erfindungsgemäßen Gasturbinenschaufeln 10, die auf einer Rotorscheibe 12 angeordnet sind. Indem die Rotorscheibe 12 vollumfang- Hch mit Gasturbinenschaufeln 10 bestückt und mit diesen verbunden wird, kann ein integral be- schaufelter Rotor (sogenannte Blisk bzw.„Bladed Disk") für einen Verdichter und/oder für eine Turbine einer Strömungsmaschine, insbesondere einer thermischen Gasturbine, hergestellt werden. Anstelle einer Rotorscheibe 12 kann dabei grundsätzlich auch ein Rotorring (nicht gezeigt) verwendet werden, wodurch ein sogenannter Bling ("Bladed Ring") herstellbar ist. Bei jeder Gasturbinenschaufel 10 ist ein radial äußerer Endbereich 14a als Deckbandsegment 16 ausgebildet (vgl. Fig. 2). Die Deckbandsegmente 16 und ihre jeweiligen Gasturbinenschaufeln 10 sind dabei im vorliegenden Ausfuhrungsbeispiel einteilig als Gussteile ausgebildet. Zur Verbesserung der Oberflächengeometrie kann vorgesehen sein, dass eine oder mehrere Gasturbinenschaufeln 10 durch entsprechende Nachbearbeitungsverfahren wie PECM-Bohren feinbearbeitet werden. Zum Einleiten mechanischer Lasten umfasst jede Gasturbinenschaufel 10 zudem eine integrale Aufnahme 18, in welcher ein Verbindungselement (nicht gezeigt) formschlüssig anordenbar ist. Die Aufnahmen 18 sind jeweils am radial äußeren Endbereich 14a der Gasturbinenschaufeln 10 in den Deckbandsegmenten 16 als Innensechskantaufhahmen ausgebildet. Hierdurch kann ein zumindest im Verbindungsbereich sechskantschlüsselförmiges Verbindungselement einfach in die jeweilige Aufnahme 18 lösbar eingesteckt werden, um die betreffende Gasturbinenschaufel 10 mit einem Drehmoment zu beaufschlagen. Auf diese Weise kann jede Gasturbinenschaufel 10 einfach, beschädigungsfrei und ohne die Notwendigkeit von Spezialwerkzeug mit einem sogenannten Pre-Twist versehen werden. 1 shows a schematic perspective view of three gas turbine blades 10 according to the invention, which are arranged on a rotor disk 12. By fully loading and connecting the rotor disk 12 to gas turbine blades 10, an integrally bladed rotor (so-called blisk or "bladed disk") can be used for a compressor and / or for a turbine of a turbomachine, in particular a thermal gas turbine In principle, a rotor ring (not shown) may also be used instead of a rotor disk 12, whereby a so-called bling ("bladed ring") can be produced Fig. 2). The shroud segments 16 and their respective gas turbine blades 10 are included formed in the present embodiment in one piece as castings. To improve the surface geometry, it may be provided that one or more gas turbine blades 10 are finished by appropriate post-processing methods such as PECM drilling. For introducing mechanical loads, each gas turbine blade 10 also has an integral receptacle 18, in which a connecting element (not shown) can be arranged in a form-fitting manner. The receptacles 18 are each formed at the radially outer end portion 14a of the gas turbine blades 10 in the shroud segments 16 as Innensechskantaufhahmen. In this way, at least in the connection region hexagonal key-shaped connecting element can be easily inserted into the respective receptacle 18 releasably to pressurize the gas turbine blade 10 in question with a torque. In this way, each gas turbine blade 10 can be easily, without damage and provided without the need for special tool with a so-called pre-twist.
Fig. 2 zeigt eine vergrößerte Aufsicht des in Fig. 1 gezeigten Details Π. Neben den Deckbandsegmenten 16 und den integralen Aufnahmen 18 ist insbesondere erkennbar, dass jedes Deckbandsegment 16 zwei einander gegenüberliegend angeordnete und im Längsschnitt im Wesentlichen Z-fÖrmige Kontaktflächen (sog. Z-Shroud) zur Anlagerung korrespondierender Kontaktflächen 20 der benachbarten Deckbandsegmente 16 aufweist. Weiterhin ist erkennbar, dass jedes Deckbandsegment 16 zwei gegenüberliegende Dichtfins 22 umfasst, welche insbesondere bei einer Rotation des Rotors 12 in einem Anstreifbereich an einer Dichtungsstruktur einer zugeordneten Strömungsmaschine anstreifen. Fig. 2 shows an enlarged plan view of the detail shown in Fig. 1 Π. In addition to the shroud segments 16 and the integral receptacles 18, it can be seen, in particular, that each shroud segment 16 has two contact surfaces (so-called Z-Shroud) arranged opposite each other and substantially Z-shaped in longitudinal section for attaching corresponding contact surfaces 20 of the adjacent shroud segments 16. Furthermore, it can be seen that each shroud segment 16 comprises two opposing sealing fins 22 which, in particular during a rotation of the rotor 12 in a abradable region, rub against a sealing structure of an associated turbomachine.
Fig. 3 zeigt zur weiteren Verdeutlichung eine schematische Seitenansicht einer der in Fig. 1 gezeigten Gasturbinenschaufeln 10. Fig. 3 wird im Folgenden in Zusammenschau mit Fig. 4 und Fig. 5 erläutert werden. Fig. 4 zeigt hierbei eine schematische Unteransicht der in Fig. 3 gezeigten Gasturbinenschaufel 10, während in Fig. 5 eine schematische seitliche Schnittansicht der Gasturbinenschaufel 10 entlang der in Fig. 4 gezeigten Schnittlinie V-V gezeigt ist. Dabei ist insbesondere in Fig. 5 erkennbar, dass die Gasturbinenschaufel 10 vorliegend als Hohlschaufel ausgebildet ist und zumindest einen Hohlraum 24 umfasst. Die Aufnahme 18 ist ihrerseits als Kernaustrittsbereich des Hohlraums 24 ausgebildet. Weiterhin ist in Fig. 3 eine an einem radial inneren Endbereich 14b der Gasturbinenschaufel ausgebildete Tannenbaumstruktur 26 zum Fügen der Gasturbinenschaufel 10 mit der Rotorscheibe 12 erkennbar. Die Geometrie und Formschlusstiefe der Aufnahme 18 kann in Abhängigkeit der Deckbandsegmentgeometrie ausgebildet sein, wobei beispielsweise der Kernaustrittsbereich des Hohlraums 24, die Anordnung der Kontaktflächen 20 und/oder eine Geometrie der Dichtfins 22 berücksichtigt werden können. FIG. 3 shows, for further clarification, a schematic side view of one of the gas turbine blades 10 shown in FIG. 1. FIG. 3 will be explained below in conjunction with FIGS. 4 and 5. FIG. 4 shows a schematic bottom view of the gas turbine blade 10 shown in FIG. 3, while FIG. 5 shows a schematic sectional side view of the gas turbine blade 10 along the section line VV shown in FIG. It can be seen in particular in FIG. 5 that the gas turbine blade 10 in the present case is designed as a hollow blade and comprises at least one cavity 24. The receptacle 18 is in turn formed as a core exit region of the cavity 24. Furthermore, in FIG. 3, a fir tree structure 26 formed on a radially inner end region 14b of the gas turbine blade can be seen for joining the gas turbine blade 10 to the rotor disk 12. The geometry and form-fitting depth of the receptacle 18 can be formed as a function of the shroud segment geometry be, for example, the core exit area of the cavity 24, the arrangement of the contact surfaces 20 and / or a geometry of the sealing fins 22 can be considered.

Claims

Patentansprüche claims
1. Gasturbinenschaufel (10), insbesondere Verdichter- und/oder Turbinenschaufel, für eine Strömungsmaschine, dadurch gekennzeichnet, dass die Gasturbinenschaufel (10) mindestens eine Aufnahme (18) zum formschlüssigen Anordnen eines Verbindungselements, mittels welchem eine mechanische Last in die Gasturbinenschaufel (10) einleitbar ist, umfasst. 1. gas turbine blade (10), in particular compressor and / or turbine blade, for a turbomachine, characterized in that the gas turbine blade (10) at least one receptacle (18) for the positive arrangement of a connecting element, by means of which a mechanical load in the gas turbine blade (10 ) is introducible.
2. Gasturbinenschaufel (10) nach Anspruch 1, dadurch gekennzeichnet, dass ein radial innerer Endbereich (14b) der Gasturbinenschaufel (10) zur Verbindung der Gasturbinenschaufel (10) mit einer Rotorscheibe (12) oder einem Rotorring der Strömungsmaschine und/oder ein radial äußerer Endbereich (14a) der Gasturbinenschaufel (10) als Deckbandsegment (16) ausgebildet ist. 2. Gas turbine blade (10) according to claim 1, characterized in that a radially inner end region (14b) of the gas turbine blade (10) for connecting the gas turbine blade (10) with a rotor disk (12) or a rotor ring of the turbomachine and / or a radially outer End portion (14 a) of the gas turbine blade (10) is designed as a shroud segment (16).
3. Gasturbinenschaufel (10) nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass die Aufnahme (18) am radial äußeren Endbereich (14a) der Gasturbinenschaufel (10) ausgebildet ist. 3. gas turbine blade (10) according to claim 1 or 2, characterized in that the receptacle (18) at the radially outer end portion (14 a) of the gas turbine blade (10) is formed.
4. Gasturbinenschaufel (10) nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass diese als Hohlschaufel ausgebildet ist und zumindest einen Hohlraum (24) umfasst. 4. gas turbine blade (10) according to one of claims 1 to 3, characterized in that it is designed as a hollow blade and at least one cavity (24).
5. Gasturbinenschaufel (10) nach Anspruch 4, dadurch gekennzeichnet, dass die Aufnahme (18) als Kernaustrittsbereich des Hohlraums (24) ausgebildet ist. 5. gas turbine blade (10) according to claim 4, characterized in that the receptacle (18) is formed as a core exit region of the cavity (24).
6. Gasturbinenschaufel (10) nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass diese einteilig mit der Aufnahme (18) und/oder als Gussteil ausgebildet ist. 6. gas turbine blade (10) according to one of claims 1 to 5, characterized in that it is formed integrally with the receptacle (18) and / or as a casting.
7. Gasturbinenschaufel (10) nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, dass zumindest ein Oberflächenbereich der Gasturbinenschaufel (10) feinbearbeitet ist. 7. Gas turbine blade (10) according to one of claims 1 to 6, characterized in that at least one surface region of the gas turbine blade (10) is finished.
8. Deckbandsegment (16) zur Anordnung an einer Gasturbinenschaufel, insbesondere einer Gasturbinenschaufel (10) nach einem der Ansprüche 1 bis 7, dadurch gekennzeichnet, dass dieses eine Aufnahme (18) zum formschlüssigen Anordnen eines Verbindungselements, mittels welchem eine mechanische Last in das Deckbandsegment (16) einleitbar ist, um- fasst. 8. shroud segment (16) for arrangement on a gas turbine blade, in particular a gas turbine blade (10) according to one of claims 1 to 7, characterized in that this a receptacle (18) for the positive arrangement of a connecting element, by means of which a mechanical load in the shroud segment (16) can be introduced, summarized.
9. Deckbandsegment (16) nach Anspruch 8, dadurch gekennzeichnet, dass dieses zwei einander gegenüberliegend angeordnete und im Längsschnitt im Wesentlichen Z-formige on- taktflächen (20) zur Anlagerung korrespondierender Kontaktflächen (20) zweier weiterer Deckbandsegmente (16) aufweist. 9. shroud segment (16) according to claim 8, characterized in that this two oppositely arranged and in the longitudinal section substantially Z-shaped on- contact surfaces (20) for attachment of corresponding contact surfaces (20) of two further shroud segments (16).
10. Verbindungssystem mit einer Gasturbinenschaufel ( 10), insbesondere einer Verdichterund/oder Turbinenschaufel für eine Strömungsmaschine, und mit einem Verbindungselement, mittels welchem eine mechanische Last in die Gasturbinenschaufel (10) einleitbar ist, dadurch gekennzeichnet, dass die Gasturbinenschaufel (10) eine korrespondierend mit dem Verbindungselement ausgebildete Aufnahme (18) zum formschlüssigen Anordnen des Verbindungselements umfasst. 10. A connection system comprising a gas turbine blade (10), in particular a compressor and / or turbine blade for a turbomachine, and a connecting element, by means of which a mechanical load in the gas turbine blade (10) can be introduced, characterized in that the gas turbine blade (10) a corresponding formed with the connecting element receptacle (18) for the positive arrangement of the connecting element.
11. Verbindungssystem nach Anspruch 10, dadurch gekennzeichnet, dass die Aufnahme (18) als Innenmehrkantaufhahme, insbesondere als Innensechskantaufhahme, und das Verbindungselement als Mehrkantschlüssel, insbesondere als Sechskantschlüssel, zum Beaufschlagen der Gasturbinenschaufel (10) mit einem Drehmoment ausgebildet sind. 11. A connection system according to claim 10, characterized in that the receptacle (18) as Innenmehrkantaufhahme, in particular as Innensechskantaufhahme, and the connecting element as a polygonal key, in particular as a hexagon wrench, for acting on the gas turbine blade (10) are formed with a torque.
12. Verfahren zum Verbinden einer Gasturbinenschaufel (10), insbesondere einer Verdichterund/oder Turbinenschaufel für eine Strömungsmaschine, mit einem Verbindungselement, mittels welchem eine mechanische Last in die Gasturbinenschaufel (10) einleitbar ist, dadurch gekennzeichnet, dass das Verbindungselement formschlüssig in einer korrespondierend mit dem Verbindungselement ausgebildeten Aufnahme (18) der Gasturbinenschaufel (10) angeordnet wird. 12. A method for connecting a gas turbine blade (10), in particular a compressor and / or turbine blade for a turbomachine, with a connecting element, by means of which a mechanical load in the gas turbine blade (10) can be introduced, characterized in that the connecting element form-fitting in a corresponding with The receptacle (18) of the gas turbine blade (10) formed in the connecting element is arranged.
13. Rotor für eine Strömungsmaschine mit einer mit einem Schaufelkranz gefügten Rotorscheibe (12) oder mit einem mit einem Schaufelkranz gefügten Rotorring, dadurch gekennzeichnet, dass der Schaufelkranz wenigstens eine Gasturbinenschaufel (10) aufweist, die mindestens eine Aufnahme (18) zum formschlüssigen Anordnen eines Verbindungselements umfasst, wobei mittels des Verbindungselements eine mechanische Last in die Gasturbinenschaufel (10) einleitbar ist. 13. A rotor for a turbomachine with a rotor blade (12) joined to a blade ring or with a rotor ring joined with a blade ring, characterized in that the blade ring has at least one gas turbine blade (10), the at least one receptacle (18) for the positive arrangement of a Includes connecting element, wherein by means of the connecting element, a mechanical load in the gas turbine blade (10) can be introduced.
14. Rotor nach Anspruch 13, dadurch gekennzeichnet, dass dieser als Blisk („Bladed Disk") oder als Bling („Bladed Ring") für einen Verdichter und/oder für eine Turbine einer Strömungsmaschine, insbesondere einer thermischen Gasturbine, ausgebildet ist. 14. Rotor according to claim 13, characterized in that it is designed as a blisk ("bladed disk") or as a bling ("bladed ring") for a compressor and / or for a turbine of a turbomachine, in particular a thermal gas turbine.
EP10798489.0A 2009-11-13 2010-11-12 Gas turbine blade for a turbomachine Not-in-force EP2394026B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102009052881A DE102009052881A1 (en) 2009-11-13 2009-11-13 Gas turbine blade for a turbomachine
PCT/DE2010/001334 WO2011057622A2 (en) 2009-11-13 2010-11-12 Gas turbine blade for a turbomachine

Publications (2)

Publication Number Publication Date
EP2394026A2 true EP2394026A2 (en) 2011-12-14
EP2394026B1 EP2394026B1 (en) 2013-07-17

Family

ID=43901923

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10798489.0A Not-in-force EP2394026B1 (en) 2009-11-13 2010-11-12 Gas turbine blade for a turbomachine

Country Status (4)

Country Link
US (1) US8622704B2 (en)
EP (1) EP2394026B1 (en)
DE (1) DE102009052881A1 (en)
WO (1) WO2011057622A2 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10428660B2 (en) * 2017-01-31 2019-10-01 United Technologies Corporation Hybrid airfoil cooling

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL295111A (en) * 1962-07-11
US3572968A (en) * 1969-04-11 1971-03-30 Gen Electric Turbine bucket cover
US3626568A (en) * 1969-04-23 1971-12-14 Avco Corp Method for bonding pins into holes in a hollow turbine blade
US4136516A (en) * 1977-06-03 1979-01-30 General Electric Company Gas turbine with secondary cooling means
US5393200A (en) * 1994-04-04 1995-02-28 General Electric Co. Bucket for the last stage of turbine
US6158104A (en) * 1999-08-11 2000-12-12 General Electric Co. Assembly jig for use with integrally covered bucket blades
JP2004108290A (en) * 2002-09-19 2004-04-08 Toshiba Corp Turbine rotor blade
US6883700B2 (en) * 2002-09-26 2005-04-26 Siemens Westinghouse Power Corporation Turbine blade closure system
DE10250779A1 (en) * 2002-10-30 2004-05-19 Alstom (Switzerland) Ltd. Emergency cooling system for a heat-stressed component
DE102005030516A1 (en) * 2005-06-28 2007-01-04 Man Turbo Ag Rotor for a turbine and method and apparatus for producing the rotor
US20080145227A1 (en) * 2006-12-19 2008-06-19 Mark Stefan Maier Methods and apparatus for load transfer in rotor assemblies
SG155788A1 (en) * 2008-03-18 2009-10-29 Turbine Overhaul Services Pte Methods and apparatuses for correcting twist angle in a gas turbine engine blade

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2011057622A2 *

Also Published As

Publication number Publication date
DE102009052881A1 (en) 2011-05-26
WO2011057622A2 (en) 2011-05-19
US8622704B2 (en) 2014-01-07
WO2011057622A3 (en) 2011-10-13
EP2394026B1 (en) 2013-07-17
US20120230825A1 (en) 2012-09-13

Similar Documents

Publication Publication Date Title
EP2089611B1 (en) Turbocharger and corresponding fabrication process
EP3030792B1 (en) Impeller for axial fans
DE10361882B4 (en) Rotor for the high-pressure turbine of an aircraft engine
EP0290783B1 (en) Fastening of an end plate to the rotor blade of a turbo machine
EP3204187B1 (en) Method for mounting rotor blades onto a rotor disk, and corresponding tensioning device for performing such a method
DE202011052265U1 (en) Built shaft brake disk
EP2002085B1 (en) Guide blade segment of a thermal turbomachine, associated production method and thermal turbomachine
DE102009031737A1 (en) Impeller for a turbomachine
WO2011054342A1 (en) Blisk, gas turbine and method for producing a blisk of said type
DE102008008857A1 (en) Connection of a shaft with a rotary component
DE69911025T2 (en) AXIAL BLADE FIXING FOR A TURBINE ROTOR
WO2010099781A2 (en) Rotor for a turbomachine
WO2007095902A1 (en) Method for producing and repairing an integrally bladed rotor
EP2762684B1 (en) Seal mount made from titanium aluminide for a flow machine
DE102016215807A1 (en) Inner ring for a vane ring of a turbomachine
DE102008048261B4 (en) Axial turbomachinery rotor with a paddle lock and method of making the same
EP2394026B1 (en) Gas turbine blade for a turbomachine
EP2378066A2 (en) Turbomachine rotor
EP2860352A1 (en) Rotor, corresponding manufacturing method and blade
WO2010099782A1 (en) Method for producing an integrally bladed rotor
EP1350924B1 (en) Fastening of nozzle segments in a gas turbine
EP2090751A1 (en) Rotor blade for a turbo engine
DE102012106209A1 (en) Method for forging turbine blades
DE2126850A1 (en) Wear insert for turbo machine blade
DE102014220037A1 (en) Turbine rotor for an exhaust gas turbine, turbocharger with such a turbine rotor and a method for producing the turbine rotor

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: 20110909

AK Designated contracting states

Kind code of ref document: A2

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

17Q First examination report despatched

Effective date: 20120820

RIN1 Information on inventor provided before grant (corrected)

Inventor name: STIEHLER, FRANK

Inventor name: BORUFKA, HANS PETER

Inventor name: PROKOPCZUK, PATRICK

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

DAX Request for extension of the european patent (deleted)
GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

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

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 622369

Country of ref document: AT

Kind code of ref document: T

Effective date: 20130815

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502010004087

Country of ref document: DE

Effective date: 20130912

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

Owner name: MTU AERO ENGINES AG

REG Reference to a national code

Ref country code: GB

Ref legal event code: 732E

Free format text: REGISTERED BETWEEN 20131114 AND 20131120

REG Reference to a national code

Ref country code: NL

Ref legal event code: VDEP

Effective date: 20130717

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: 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: 20130717

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: 20131118

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: 20130731

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: 20130717

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: 20131117

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: 20131017

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: 20130717

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

Ref country code: NL

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

Effective date: 20130717

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: 20130717

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: 20130717

Ref country code: ES

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

Effective date: 20131028

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: 20131018

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: 20130717

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: 20130717

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: 20130717

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

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: 20130717

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: 20130717

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: 20130717

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: 20130717

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: 20130717

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

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

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

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

Ref country code: IT

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

Effective date: 20130717

BERE Be: lapsed

Owner name: MTU AERO ENGINES G.M.B.H.

Effective date: 20131130

26N No opposition filed

Effective date: 20140422

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: 20130717

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502010004087

Country of ref document: DE

Effective date: 20140422

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

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

Ref country code: BE

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

Effective date: 20131130

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: 20131112

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

Ref country code: SM

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

Effective date: 20130717

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: 20130717

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

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

Ref country code: 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: 20101112

Ref country code: LI

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

Effective date: 20141130

Ref country code: CH

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

Effective date: 20141130

Ref country code: LU

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

Effective date: 20131112

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: 20130717

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: 20131017

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: 20130717

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

Ref country code: MT

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

Effective date: 20130717

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 6

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 7

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 622369

Country of ref document: AT

Kind code of ref document: T

Effective date: 20151112

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: 20151112

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 8

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

Ref country code: DE

Payment date: 20171124

Year of fee payment: 8

Ref country code: FR

Payment date: 20171124

Year of fee payment: 8

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

Ref country code: GB

Payment date: 20171124

Year of fee payment: 8

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

Ref country code: AL

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

Effective date: 20130717

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502010004087

Country of ref document: DE

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

Effective date: 20181112

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

Ref country code: FR

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

Effective date: 20181130

Ref country code: DE

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

Effective date: 20190601

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: 20181112