EP2187005B1 - Method of making a turbine blade holder for a device to determine flow quantities - Google Patents

Method of making a turbine blade holder for a device to determine flow quantities Download PDF

Info

Publication number
EP2187005B1
EP2187005B1 EP08019938.3A EP08019938A EP2187005B1 EP 2187005 B1 EP2187005 B1 EP 2187005B1 EP 08019938 A EP08019938 A EP 08019938A EP 2187005 B1 EP2187005 B1 EP 2187005B1
Authority
EP
European Patent Office
Prior art keywords
turbine blade
base body
sealing element
dimensional model
recess
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
EP08019938.3A
Other languages
German (de)
French (fr)
Other versions
EP2187005A1 (en
Inventor
Roman Dr. Beyer
Uwe Dunkel
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP08019938.3A priority Critical patent/EP2187005B1/en
Priority to US12/616,162 priority patent/US20100124503A1/en
Publication of EP2187005A1 publication Critical patent/EP2187005A1/en
Application granted granted Critical
Publication of EP2187005B1 publication Critical patent/EP2187005B1/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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/68—Assembly methods using auxiliary equipment for lifting or holding
    • 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
    • F05D2260/80—Diagnostics
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making

Definitions

  • the invention relates to a method for producing a turbine blade holder for a flow rate determination device and to a turbine blade holder which can be produced by the method.
  • Turbine blades are exposed to high temperatures during operation in a chemically aggressive atmosphere, which can lead to their damage. It is therefore necessary to protect the blades by cooling.
  • cooling air channels are formed in the interior of the turbine blades, which communicate with cooling air holes through the outer wall of the turbine blade. During operation, cooling air is injected through openings in the cooling air channels in the blade root, which flows through the channels to the cooling air holes and out of these. The outflowing cooling air reduces the temperature of the turbine blade.
  • a turbine blade has hitherto been positioned on a metallic base body. Then, a flexible sealing body with the negative geometry of the blade root made of a two-component resin is cast around the base of the blade on the basic body in a positive and non-positive manner. To make this possible, it is necessary to prepare the turbine blade beforehand. Thus, parts of the blade must be milled away or cut away, openings closed, Gieskerne mounted and seals are attached.
  • a measuring apparatus is known with which the flow rate of a cooling medium can be determined by a gas turbine blade with internal cooling channels.
  • the turbine blade is in one of a Fixed metal frame existing turbine blade holding member and sealed with an intermediate wedge-shaped sealing element.
  • the metal frame is attached to a test chamber of a flowmeter.
  • a turbine bucket mounting is described with an inflow channel for the supply of a cooling fluid to internal cooling channels of a turbine blade mounted in the holder.
  • the holder has in the region of the turbine blade base an introduced sealing body made of an elastomeric material with which a lateral escape of the cooling fluid is to be prevented.
  • the object of the invention is therefore to provide a method for producing a turbine blade holder for a flow rate determination device, with the aid of a turbine blade support can be obtained, which meets all sealing, positioning and support requirements.
  • This object is achieved according to the invention by providing a base body of the turbine blade holder with inflow channel formed therein and a three-dimensional model of a turbine blade with a recess having the negative geometry of a seal element to be produced, placing the three-dimensional model on the base body and in one of the contours of the Recess and limited by the body cavity around the inflow around the sealing element applied to the body.
  • the sealing element is poured onto the base body. In this case, the limited by the contour of the recess and the body cavity acts as a mold for the casting material.
  • a basic body of the holder is produced, in which an inflow channel for air or another test fluid is formed.
  • a three-dimensional model of the turbine blade to be tested with the aid of the device is created, which has a recess with the negative geometry of the sealing element to be produced.
  • the model is placed on the base body, wherein the contour of the recess and the base define a cavity around the inflow channel, in which the sealing element is applied to the base body.
  • the basic idea of the invention is to use, instead of the turbine blade itself, a three-dimensional model of this for producing the turbine blade holder. It is particularly advantageous that the negative geometry of the sealing element is already integrated in the model. This makes it possible in a simple manner to apply a sealing element on the base body, which exactly corresponds to the spatial requirements of the turbine blade to be examined. For this reason, the sealing element also meets all sealing, positioning and support requirements. In addition, the costly procurement of turbine blades from mass production is eliminated. Finally, the model can also be easily reproduced as often as desired at low cost.
  • a CAD model in particular an STL model, of the turbine blade to which the recess is added for the creation of the three-dimensional model. Then, based on the modified CAD model, the three-dimensional model is created.
  • the CAD model that is usually already developed during the design of turbine blades can be used to provide, after appropriate modification, i. complement of a recess with which help to create a three-dimensional model.
  • the particular advantage here is that modifications to the three-dimensional model or to the sealing element that can be produced with its aid can be made quickly and easily by adapting the CAD model.
  • the three-dimensional model of the turbine blade can be produced by stereolithography, laser sintering or and / or by Oriol milling. Especially if a modified CAD model of the turbine blade is used, the three-dimensional model can be created so fast, automated and with high precision.
  • a sealing element made of silicone can be applied to the base body.
  • a sealing element made of this material shows a particularly high sealing effect.
  • the recess at least partially form with the negative shape of a sealing lip.
  • a sealing element with a sealing lip can be obtained.
  • the sealing lip protrudes from the sealing element and thus realizes a high specific pressing pressure on the sealing surface when the turbine blade is fixed in the holder.
  • a development of the invention provides for forming the recess in sections with the negative form of support and / or positioning elements. In this way, a turbine bucket mount can be made in which the turbine bucket is secured axially and radially against rotation or tilting.
  • a turbine blade holder of a flow rate determination device is the subject of the invention, which can be produced by the method according to the invention.
  • the single figure of the drawing shows in section a turbine blade holder 1 according to the invention during manufacture.
  • the turbine blade holder 1 comprises a main body 2, in particular made of metal or of a metallic alloy, formed therein inflow 3 and a receiving area 4 for a blade root of a turbine blade to be fixed.
  • a three-dimensional model 5 of the turbine blade to be fixed is placed, that has a recess 6 with the negative geometry of a sealing element to be produced.
  • the recess 6 here has sections of the negative shape of a sealing lip.
  • the contour of the recess 6 and the base body 2 define a cavity 7 around the inflow passage 3 around.
  • a sealing element 8 made of silicone is positively and non-positively poured onto the base body 2.
  • the sealing element 8 fills the cavity 7. This means that the cavity determines the shape of the sealing element 8. Consequently, the sealing element 8 is provided in the transition region to the three-dimensional model 5 with a circumferential sealing lip 9 projecting in the direction of the three-dimensional model 5.
  • the base body 2 is first produced by means of methods known in the art, for example using a CNC machine. Then, the three-dimensional model 5 is created. In particular, a (virtual) CAD model of the turbine blade that already exists from the design process can serve as a starting point. The recess 6 is added to this CAD model. Subsequently, based on the thus modified CAD model, the three-dimensional model 5 is produced in a manner known per se, for example by stereolithography. The three-dimensional model 5 is placed on the base body 2. Subsequently, silicone is introduced into the cavity 7 until it is completely filled. The silicone then forms the sealing element 8 in the cavity 7.
  • a (virtual) CAD model of the turbine blade that already exists from the design process can serve as a starting point.
  • the recess 6 is added to this CAD model.
  • the three-dimensional model 5 is produced in a manner known per se, for example by stereolithography.
  • the three-dimensional model 5 is placed on the base body 2. Subsequent
  • the turbine blade to be fixed with its foot area can be used.
  • the turbine blade rests on the sealing element 8.
  • the region of the sealing lip 9 results in a particularly high pressing pressure, whereby a high sealing effect is ensured. If the turbine blade holder 1 according to the invention is used in a flow rate determination, no air escapes between the turbine blade and the turbine blade holder 1.

Landscapes

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

Description

Die Erfindung betrifft ein Verfahren zur Herstellung einer Turbinenschaufelhalterung für eine Durchflussmengenbestimmungseinrichtung sowie eine nach dem Verfahren herstellbare Turbinenschaufelhalterung.The invention relates to a method for producing a turbine blade holder for a flow rate determination device and to a turbine blade holder which can be produced by the method.

Turbinenschaufeln werden während des Betriebs in chemisch aggressiver Atmosphäre hohen Temperaturen ausgesetzt, was zu ihrer Beschädigung führen kann. Es ist daher notwendig, die Schaufeln durch Kühlung zu schützen. Dazu sind im Inneren der Turbinenschaufeln Kühlluftkanäle ausgebildet, die mit Kühlluftbohrungen durch die Außenwandung der Turbinenschaufel kommunizieren. Während des Betriebs wird Kühlluft durch Öffnungen der Kühlluftkanäle im Schaufelfuß eingeblasen, die durch die Kanäle zu den Kühlluftbohrungen und aus diesen heraus strömt. Die ausströmende Kühlluft reduziert die Temperatur der Turbinenschaufel.Turbine blades are exposed to high temperatures during operation in a chemically aggressive atmosphere, which can lead to their damage. It is therefore necessary to protect the blades by cooling. For this purpose, cooling air channels are formed in the interior of the turbine blades, which communicate with cooling air holes through the outer wall of the turbine blade. During operation, cooling air is injected through openings in the cooling air channels in the blade root, which flows through the channels to the cooling air holes and out of these. The outflowing cooling air reduces the temperature of the turbine blade.

Bei neu hergestellten oder reparierten Turbinenschaufeln ist es notwendig zu überprüfen, ob die Kühlluftkanäle und -bohrungen eine hinreichende Kühlung der Turbinenschaufel während des Betriebs sicher stellen können. Aus diesem Grund wird vor der Verwendung die Durchflussmenge an Kühlluft durch die Turbinenschaufel bestimmt.For newly manufactured or repaired turbine blades, it is necessary to check that the cooling air ducts and bores can ensure adequate cooling of the turbine blade during operation. For this reason, the flow rate of cooling air through the turbine blade is determined prior to use.

Im Stand der Technik sind Durchflussmengenbestimmungseinrichtung bekannt, die zur Durchführung eines derartigen Prüfverfahrens verwendet werden können. Diese Einrichtungen weisen eine Halterung auf, in der die zu untersuchende Turbinenschaufel mit ihrem Schaufelfuß fixiert werden kann. In der Halterung ist ein Einströmkanal ausgebildet, durch den Luft in die Öffnungen der Kühlluftkanäle im Schaufelfuß eingeblasen werden kann. Weiterhin ist eine Einrichtung vorgesehen, welche die aus den Kühlluftbohrungen ausströmende Luft vollständig sammelt und einer Messeinrichtung zuleitet. Mit Hilfe der Messeinrichtung kann dann die Durchflussmenge an Luft durch die Turbinenschaufel ermittelt werden.In the prior art flow rate determining means are known, which can be used to carry out such a test method. These devices have a holder in which the turbine blade to be examined can be fixed with its blade root. In the holder, an inflow channel is formed, can be injected through the air into the openings of the cooling air ducts in the blade root. Furthermore, a device is provided which completely collects the air flowing out of the cooling air bores and supplies it to a measuring device. With help The measuring device can then be determined, the flow rate of air through the turbine blade.

Bei den bekannten Vorrichtungen stellt sich das Problem einer ausreichenden Abdichtung zwischen der Halterung und der darin fixierten Turbinenschaufel. Außerdem muss sichergestellt werden, dass die Turbinenschaufel axial und radial gegen eine Drehen oder Verkippen gesichert ist. Schließlich ist es auch notwendig, strömungstechnischen Besonderheiten der einzelnen Turbinenschaufeln Rechnung zu tragen.In the known devices, the problem arises of a sufficient seal between the holder and the turbine blade fixed therein. In addition, it must be ensured that the turbine blade is axially and radially secured against rotation or tilting. Finally, it is also necessary to take flow characteristics of the individual turbine blades into account.

Um diesen Anforderungen gerecht zu werden, ist bei der bekannten Halterung um den Einströmkanal herum eine Dichtung vorgesehen, auf der die Turbinenschaufel im fixierten Zustand flächig aufliegt. Es ist jedoch schwierig eine solche Dichtung herzustellen, die in ausreichendem Maße an die komplexe Geometrie des Schaufelfußes der jeweils zu prüfenden Turbinenschaufel angepasst ist.To meet these requirements, a seal is provided in the known holder to the inflow around, on which the turbine blade rests flat in the fixed state. However, it is difficult to produce such a gasket that is sufficiently adapted to the complex geometry of the blade root of the particular turbine blade to be tested.

Zur Herstellung der Halterung wird bisher eine Turbinenschaufel auf einen metallischen Grundkörper positioniert. Dann wird um den Schaufelfuß herum auf den Grundkörper form- und kraftschlüssig ein flexibeler Dichtkörper mit der negativen Geometrie des Schaufelfußes aus einem Zweikomponentenharz gegossen. Um dies zu ermöglichen, ist es notwendig, die Turbinenschaufel vorher zu präparieren. So müssen Teile der Schaufel weggefräst bzw. weggeschnitten, Öffnungen verschlossen, Gieskerne montiert und Abdichtungen angebracht werden.To produce the holder, a turbine blade has hitherto been positioned on a metallic base body. Then, a flexible sealing body with the negative geometry of the blade root made of a two-component resin is cast around the base of the blade on the basic body in a positive and non-positive manner. To make this possible, it is necessary to prepare the turbine blade beforehand. Thus, parts of the blade must be milled away or cut away, openings closed, Gieskerne mounted and seals are attached.

Trotz des hiermit einhergehenden großen Aufwands gelingt es jedoch nicht, eine Dichtung herzustellen, die den hohen Anforderungen bezüglich der Abdichtleistung und der Stütz- und Positionierungsfunktion genügt.However, despite the great expense involved, it is not possible to produce a gasket that meets the high requirements in terms of the sealing performance and the support and positioning function.

Aus der US 2004/221659 A1 ist eine Messapparatur bekannt, mit der die Fließrate eines Kühlmediums durch eine Gasturbinenschaufel mit innenliegenden Kühlkanälen bestimmt werden kann. Hierzu wird die Turbinenschaufel in einem aus einem Metallrahmen bestehenden Turbinenschaufelhalteelement fixiert und mit einem dazwischen liegenden keilförmigen Dichtungselement abgedichtet. Der Metallrahmen ist an einer Prüfkammer eines Durchflussmessgeräts angebracht.From the US 2004/221659 A1 a measuring apparatus is known with which the flow rate of a cooling medium can be determined by a gas turbine blade with internal cooling channels. For this purpose, the turbine blade is in one of a Fixed metal frame existing turbine blade holding member and sealed with an intermediate wedge-shaped sealing element. The metal frame is attached to a test chamber of a flowmeter.

In der US 2002/0136637 A1 ist eine Turbinenschaufelhalterung mit einem Einströmkanal für die Zuführung eines Kühlfluids zu innenliegenden Kühlkanälen einer in der Halterung befestigten Turbinenschaufel beschrieben. Die Halterung besitzt im Bereich der Turbinenschaufelbasis einen eingebrachten Dichtkörper aus einem Elastomermaterial, mit dem ein seitliches Entweichen des Kühlfluids verhindert werden soll.In the US 2002/0136637 A1 a turbine bucket mounting is described with an inflow channel for the supply of a cooling fluid to internal cooling channels of a turbine blade mounted in the holder. The holder has in the region of the turbine blade base an introduced sealing body made of an elastomeric material with which a lateral escape of the cooling fluid is to be prevented.

Aufgabe der Erfindung ist es daher, ein Verfahren zur Herstellung einer Turbinenschaufelhalterung für eine Durchflussmengenbestimmungseinrichtung anzugeben, mit dessen Hilfe eine Turbinenschaufelhalterung erhalten werden kann, die allen Dichtungs-, Positionierungs- und Stützanforderungen genügt.The object of the invention is therefore to provide a method for producing a turbine blade holder for a flow rate determination device, with the aid of a turbine blade support can be obtained, which meets all sealing, positioning and support requirements.

Diese Aufgabe wird erfindungsgemäß gelöst, indem ein Grundkörper der Turbinenschaufelhalterung mit darin ausgebildetem Einströmkanal und ein dreidimensionales Modell einer Turbinenschaufel mit einer Aussparung, die die negative Geometrie eines herzustellenden Dichtungselements aufweist, erstellt, das dreidimensionale Modell auf den Grundkörper aufgesetzt und in einem von der Kontur der Aussparung und vom Grundkörper begrenzten Hohlraum um den Einströmkanal herum das Dichtungselement auf den Grundkörper aufgebracht. Das Dichtungselement wird auf den Grundkörper gegossen. Dabei wirkt der von der Kontur der Aussparung und dem Grundkörper begrenzte Hohlraum als Form für das Gussmaterial.This object is achieved according to the invention by providing a base body of the turbine blade holder with inflow channel formed therein and a three-dimensional model of a turbine blade with a recess having the negative geometry of a seal element to be produced, placing the three-dimensional model on the base body and in one of the contours of the Recess and limited by the body cavity around the inflow around the sealing element applied to the body. The sealing element is poured onto the base body. In this case, the limited by the contour of the recess and the body cavity acts as a mold for the casting material.

Erfindungsgemäß wird also ein Grundkörper der Halterung hergestellt, in dem ein Einströmkanal für Luft oder ein anderes Prüffluid ausgebildet ist. Außerdem wird ein dreidimensionales Modell der mit Hilfe der Einrichtung zu überprüfenden Turbinenschaufel erstellt, das eine Aussparung mit der negativen Geometrie des herzustellenden Dichtungselements aufweist. Das Modell wird auf den Grundkörper aufgesetzt, wobei die Kontur der Aussparung und der Grundkörper einen Hohlraum um den Einströmkanal herum begrenzen, in dem das Dichtungselement auf den Grundkörper aufgebracht wird.According to the invention, therefore, a basic body of the holder is produced, in which an inflow channel for air or another test fluid is formed. In addition, a three-dimensional model of the turbine blade to be tested with the aid of the device is created, which has a recess with the negative geometry of the sealing element to be produced. The model is placed on the base body, wherein the contour of the recess and the base define a cavity around the inflow channel, in which the sealing element is applied to the base body.

Grundgedanke der Erfindung ist es, anstelle der Turbinenschaufel selbst ein dreidimensionales Modell von dieser zur Herstellung der Turbinenschaufelhalterung zu verwenden. Dabei ist insbesondere vorteilhaft, dass in dem Modell bereits die negative Geometrie des Dichtungselements integriert ist. Dies ermöglicht es auf einfache Weise ein Dichtungselement auf dem Grundkörper aufzubringen, das exakt jeweils den räumlichen Anforderungen der zu untersuchenden Turbinenschaufel entspricht. Aus diesem Grund erfüllt das Dichtungselement auch alle Dichtungs-, Positionierungs- und Stützanforderungen. Außerdem entfällt die aufwendige Beschaffung von Turbinenschaufeln aus der Serienfertigung. Schließlich kann das Modell auch auf einfache Weise zu geringen Kosten beliebig oft reproduziert werden.The basic idea of the invention is to use, instead of the turbine blade itself, a three-dimensional model of this for producing the turbine blade holder. It is particularly advantageous that the negative geometry of the sealing element is already integrated in the model. This makes it possible in a simple manner to apply a sealing element on the base body, which exactly corresponds to the spatial requirements of the turbine blade to be examined. For this reason, the sealing element also meets all sealing, positioning and support requirements. In addition, the costly procurement of turbine blades from mass production is eliminated. Finally, the model can also be easily reproduced as often as desired at low cost.

In Weiterbildung der Erfindung ist vorgesehen, für die Erstellung des dreidimensionalen Modells ein CAD-Modell, insbesondere ein STL-Modell, der Turbinenschaufel zu verwenden, dem die Aussparung hinzugefügt wird. Dann wird auf Grundlage des so modifizierten CAD-Modells das dreidimensionale Modell erstellt. Hier kann das üblicherweise bereits während des Entwurfs von Turbinenschaufeln entwickelte CAD-Modell verwendet werden, um nach entsprechender Modifikation, d.h. der Ergänzung der Aussparung, mit dessen Hilfe das dreidimensionale Modell zu erstellen. Besonderer Vorteil ist dabei, dass schnell und einfach Modifikationen an dem dreidimensionalen Modell bzw. an dem mit seiner Hilfe herzustellendem Dichtungselement vorgenommen werden können, indem das CAD-Modell angepasst wird.In a development of the invention, it is provided to use a CAD model, in particular an STL model, of the turbine blade to which the recess is added for the creation of the three-dimensional model. Then, based on the modified CAD model, the three-dimensional model is created. Here, the CAD model that is usually already developed during the design of turbine blades can be used to provide, after appropriate modification, i. complement of a recess with which help to create a three-dimensional model. The particular advantage here is that modifications to the three-dimensional model or to the sealing element that can be produced with its aid can be made quickly and easily by adapting the CAD model.

Das dreidimensionale Modell der Turbinenschaufel kann durch Stereolithografie, Lasersintern oder und / oder durch Oriol-Fräsen hergestellt wird. Insbesondere wenn ein modifiziertes CAD-Modell der Turbinenschaufel verwendet wird, kann das dreidimensionale Modell so schnell, automatisiert und mit hoher Präzision erstellt werden.The three-dimensional model of the turbine blade can be produced by stereolithography, laser sintering or and / or by Oriol milling. Especially if a modified CAD model of the turbine blade is used, the three-dimensional model can be created so fast, automated and with high precision.

Vorteilhafter Weise kann ein Dichtungselement aus Silikon auf den Grundkörper aufgebracht werden. Ein Dichtungselement aus diesem Material zeigt eine besonders hohe Dichtwirkung.Advantageously, a sealing element made of silicone can be applied to the base body. A sealing element made of this material shows a particularly high sealing effect.

Es ist ebenfalls möglich, dass die Aussparung zumindest abschnittsweise mit der negativen Form einer Dichtungslippe auszubilden. Mit Hilfe eines dreidimensionalen Modells, das eine solche Aussparung aufweist, kann ein Dichtungselement mit einer Dichtungslippe erhalten werden. Die Dichtungslippe ragt von dem Dichtungselement vor und realisiert so einen hohen spezifischen Pressdruck an der Dichtfläche, wenn die Turbinenschaufel in der Halterung fixiert ist.It is also possible that the recess at least partially form with the negative shape of a sealing lip. By means of a three-dimensional model having such a recess, a sealing element with a sealing lip can be obtained. The sealing lip protrudes from the sealing element and thus realizes a high specific pressing pressure on the sealing surface when the turbine blade is fixed in the holder.

Eine Weiterbildung der Erfindung sieht vor, die Aussparung abschnittsweise mit der negativen Form von Stütz- und / oder Positionierungselementen auszubilden. Auf diese Weise kann eine Turbinenschaufelhalterung hergestellt werden, bei der die Turbinenschaufel axial und radial gegen Drehen oder Verkippen gesichert ist.A development of the invention provides for forming the recess in sections with the negative form of support and / or positioning elements. In this way, a turbine bucket mount can be made in which the turbine bucket is secured axially and radially against rotation or tilting.

Weiterhin ist eine Turbinenschaufelhalterung einer Durchflussmengenbestimmungseinrichtung Gegenstand der Erfindung, die nach dem erfindungsgemäßen Verfahren herstellbar ist.Furthermore, a turbine blade holder of a flow rate determination device is the subject of the invention, which can be produced by the method according to the invention.

Die Erfindung wird im Folgenden an Hand eines Ausführungsbeispiels unter Bezugnahme auf die Zeichnung im Detail erläutert.The invention will be explained below with reference to an embodiment with reference to the drawings in detail.

Die einzige Figur der Zeichnung zeigt im Schnitt eine erfindungsgemäße Turbinenschaufelhalterung 1 während der Herstellung.The single figure of the drawing shows in section a turbine blade holder 1 according to the invention during manufacture.

Die Turbinenschaufelhalterung 1 umfasst einen Grundkörper 2, insbesondere aus Metall oder aus einer metallischen Legierung, mit darin ausgebildetem Einströmkanal 3 und einem Aufnahmebereich 4 für einen Schaufelfuß einer zu fixierenden Turbinenschaufel.The turbine blade holder 1 comprises a main body 2, in particular made of metal or of a metallic alloy, formed therein inflow 3 and a receiving area 4 for a blade root of a turbine blade to be fixed.

Auf den Grundkörper 2 ist ein dreidimensionales Modell 5 der zu fixierenden Turbinenschaufel aufgesetzt, dass eine Aussparung 6 mit der negativen Geometrie eines herzustellenden Dichtungselements aufweist. Die Aussparung 6 hat hier abschnittsweise die negative Form einer Dichtungslippe.On the base body 2, a three-dimensional model 5 of the turbine blade to be fixed is placed, that has a recess 6 with the negative geometry of a sealing element to be produced. The recess 6 here has sections of the negative shape of a sealing lip.

Die Kontur der Aussparung 6 und der Grundkörper 2 begrenzen einen Hohlraum 7 um den Einströmkanal 3 herum. In dem Hohlraum 7 ist ein Dichtungselement 8 aus Silikon form- und kraftschlüssig auf den Grundkörper 2 gegossen. Das Dichtungselement 8 füllt den Hohlraum 7 aus. Dies bedeutet, dass der Hohlraum die Form des Dichtungselements 8 bestimmt. Folglich ist Dichtungselement 8 im Übergangsbereich zu dem dreidimensionalen Modell 5 mit einer in Richtung des dreidimensionalen Modells 5 vorragenden umlaufenden Dichtungslippe 9 versehen.The contour of the recess 6 and the base body 2 define a cavity 7 around the inflow passage 3 around. In the cavity 7, a sealing element 8 made of silicone is positively and non-positively poured onto the base body 2. The sealing element 8 fills the cavity 7. This means that the cavity determines the shape of the sealing element 8. Consequently, the sealing element 8 is provided in the transition region to the three-dimensional model 5 with a circumferential sealing lip 9 projecting in the direction of the three-dimensional model 5.

Um die Turbinenschaufelhalterung 1 herzustellen, wird zunächst der Grundköper 2 mit Hilfe von im Stand der Technik bekannten Verfahren, beispielsweise unter Verwendung einer CNC-Maschine produziert. Dann wird das dreidimensionale Modell 5 erstellt. Dabei kann insbesondere ein schon aus dem Konstruktionsprozess vorhandenes (virtuelles) CAD-Modell der Turbinenschaufel als Ausgangspunkt dienen. Diesem CAD-Modell wird die Aussparung 6 hinzugefügt. Anschließend wird auf Grundlage des so modifizierten CAD-Modells das dreidimensionale Modell 5 in an sich bekannter Weise beispielsweise durch Stereolithografie erstellt.
Das dreidimensionale Modell 5 wird auf den Grundkörper 2 aufgesetzt. Anschließend wird Silikon in den Hohlraum 7 eingebracht, bis dieser vollständig ausgefüllt ist. Das Silikon bildet dann in dem Hohlraum 7 das Dichtungselement 8.To manufacture the turbine blade holder 1, the base body 2 is first produced by means of methods known in the art, for example using a CNC machine. Then, the three-dimensional model 5 is created. In particular, a (virtual) CAD model of the turbine blade that already exists from the design process can serve as a starting point. The recess 6 is added to this CAD model. Subsequently, based on the thus modified CAD model, the three-dimensional model 5 is produced in a manner known per se, for example by stereolithography.
The three-dimensional model 5 is placed on the base body 2. Subsequently, silicone is introduced into the cavity 7 until it is completely filled. The silicone then forms the sealing element 8 in the cavity 7.

Nachdem das Dichtungselement 8 so auf den Grundkörper 2 gegossen worden ist, kann das dreidimensionale Modell 5 vom Grundkörper 2 abgenommen werden. Der Grundkörper 2 mit dem daran angebrachten Dichtungselement 8 bildet die Turbinenschaufelhalterung 1.After the sealing member 8 has been poured onto the base body 2, the three-dimensional model 5 of Base 2 are removed. The main body 2 with the sealing element 8 attached thereto forms the turbine blade holder 1.

In die Turbinenschaufelhalterung 1 kann die zu fixierende Turbinenschaufel mit ihren Fußbereich eingesetzt werden. Dabei liegt die Turbinenschaufel auf dem Dichtungselement 8 auf. Insbesondere im Bereich der Dichtungslippe 9 resultiert ein besonders hoher Pressdruck, wodurch eine hohe Dichtungswirkung sichergestellt wird.
Wird die erfindungsgemäße Turbinenschaufelhalterung 1 bei einer Durchflussmengenbestimmung verwendet, entweicht zwischen der Turbinenschaufel und der Turbinenschaufelhalterung 1 keine Luft.In the turbine blade holder 1, the turbine blade to be fixed with its foot area can be used. In this case, the turbine blade rests on the sealing element 8. In particular, in the region of the sealing lip 9 results in a particularly high pressing pressure, whereby a high sealing effect is ensured.
If the turbine blade holder 1 according to the invention is used in a flow rate determination, no air escapes between the turbine blade and the turbine blade holder 1.

Claims (7)

  1. Method for producing a turbine blade holder (1) for an internal flow rate determination device, the turbine blade holder (1) comprising a base body (2) with an influx channel (3) formed in it and a sealing element (8), the method having at least the following steps:
    - making the base body (2);
    - making a three-dimensional model (5) of a turbine blade, with a recess (6) which has the negative geometry of the sealing element (8);
    - placing the three-dimensional model (5) on the base body (2);
    - casting the sealing element (8) on the base body (2) in a cavity (7) delimited by the contour of the recess (6) and the base body (2) around the influx channel (3); and
    - removing the three-dimensional model (5) from the base body (2).
  2. Method according to Claim 1, characterized in that a CAD model is used for making the three-dimensional model (5), in particular an STL model of the turbine blade, wherein the CAD model is added to the recess (6) and then the three-dimensional model (5) is made on the basis of the CAD model thus modified.
  3. Method according to one of the preceding claims, characterized in that the three-dimensional model (5) of the turbine blade is made by stereolithography, laser sintering and/or by oriol machining.
  4. Method according to one of the preceding claims, characterized in that the sealing element (8) consists of silicone.
  5. Method according to one of the preceding claims, characterized in that the recess (6) is formed at least locally by the negative shape of a sealing lip (9).
  6. Method according to one of the preceding claims, characterized in that the recess (6) is formed locally by the negative shape of supporting and/or positioning elements.
  7. Turbine blade holder (1) of an internal flow rate determination device, the turbine blade holder (1) comprising a base body (2) with an influx channel (3) formed in it and a sealing element (8) produced in accordance with a method according to one of the preceding claims.
EP08019938.3A 2008-11-14 2008-11-14 Method of making a turbine blade holder for a device to determine flow quantities Not-in-force EP2187005B1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP08019938.3A EP2187005B1 (en) 2008-11-14 2008-11-14 Method of making a turbine blade holder for a device to determine flow quantities
US12/616,162 US20100124503A1 (en) 2008-11-14 2009-11-11 Method for producing a turbine blade holder for an internal flow rate determination device

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08019938.3A EP2187005B1 (en) 2008-11-14 2008-11-14 Method of making a turbine blade holder for a device to determine flow quantities

Publications (2)

Publication Number Publication Date
EP2187005A1 EP2187005A1 (en) 2010-05-19
EP2187005B1 true EP2187005B1 (en) 2015-04-01

Family

ID=40551970

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08019938.3A Not-in-force EP2187005B1 (en) 2008-11-14 2008-11-14 Method of making a turbine blade holder for a device to determine flow quantities

Country Status (2)

Country Link
US (1) US20100124503A1 (en)
EP (1) EP2187005B1 (en)

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3566669A (en) * 1968-09-04 1971-03-02 Harry Parker Method and apparatus for thermally examining fluid passages in a body
US6820468B2 (en) 2001-03-26 2004-11-23 General Electric Company Fixture for holding a gas turbine engine blade
US20030128736A1 (en) * 2001-11-01 2003-07-10 Dalio Brian A. Turbine component inspection system
US6857325B2 (en) 2003-05-09 2005-02-22 Mitsubishi Heavy Industries, Ltd. Moving blade support jig, moving blade support apparatus, and flow rate measuring apparatus
US20050006047A1 (en) * 2003-07-10 2005-01-13 General Electric Company Investment casting method and cores and dies used therein
US6935187B1 (en) * 2004-03-03 2005-08-30 General Electric Company Test method for assessing thermal mechanical fatigue performance of a test material
CA2517940A1 (en) * 2004-09-24 2006-03-24 Ems-Chemie Ag Injection molding method for manufacturing plastic parts
US7388204B2 (en) * 2005-12-07 2008-06-17 Meyer Tool, Inc. Apparatus and method for analyzing relative outward flow characterizations of fabricated features
US7671338B2 (en) * 2006-06-14 2010-03-02 Meyer Tool, Inc. Apparatus and method for analyzing relative outward flow characterizations of fabricated features
ATE448908T1 (en) * 2007-04-12 2009-12-15 Siemens Ag SYSTEM AND DEVICE CONCEPT FOR A SHOTPEENING SYSTEM FOR SOLIDIFYING GAS TURBINE BLADE FOOT

Also Published As

Publication number Publication date
EP2187005A1 (en) 2010-05-19
US20100124503A1 (en) 2010-05-20

Similar Documents

Publication Publication Date Title
DE602004006342T2 (en) Method for precision casting
DE102014220787A1 (en) Gas turbine component with internal module and method for its production using Selective Laser Melting
DE60318515T2 (en) Core shape for casting cooling channels and improved product design
EP3349928B1 (en) Method and apparatus for additive manufacturing
DE10207279A1 (en) Casting process and casting
DE102009051479A1 (en) Method and device for producing a component of a turbomachine
EP2101938B1 (en) Method for producing a pattern for the precision-cast representation of a component having at least one cavity
DE102015210744A1 (en) Method for manufacturing a turbine blade
DE102013016868A1 (en) Investment casting of hollow components
WO2006056524A1 (en) Method for production of a disposable pattern and core arranged therein
DE102017210909A1 (en) Method for the additive production of a component by means of auxiliary structure
EP2059356B1 (en) Single-part expendable casting mould with a controlled temperature for cast metal parts and associated production method
EP2682832A1 (en) Clamp fixture for clamping turbine blades and method for producing the clamp
EP2845918A1 (en) Method for at least partially coating a blade, a coating device and a blade
EP2187005B1 (en) Method of making a turbine blade holder for a device to determine flow quantities
DE102012220087A1 (en) An aluminum alloy vibration damping automotive aluminum member for a vehicle driveline and method of making the same
EP3147069A1 (en) Method for producing a hybrid rotor blade of a thermal fluid flow engine using built-up welding
DE102017208783A1 (en) Method for reworking a channel in a workpiece
EP0537417B1 (en) Lost pattern and process for making the same
DE102011011486A1 (en) Combustion chamber cooling chamber construction for a half-mold cylinder head casting
EP3198219B1 (en) Turbine blade, method for its preparation and method for determining the position of a casting core after casting a turbine blade
DE10065594C2 (en) Process for the production of 3-dimensional sintered workpieces
EP3616806B1 (en) Method for producing a model form core blank, a model form core and an investment casting molds and a casting method for producing a cast piece with a hollow structure
DE102013002242A1 (en) Producing component, which flows through and around medium, preferably producing housing component, preferably producing valve component, comprises producing component in three dimensions by selective melting of raw material
EP3248727A1 (en) Turbine blade and method of manufacture the turbine blade

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

AK Designated contracting states

Kind code of ref document: A1

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 MT NL NO PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA MK RS

17P Request for examination filed

Effective date: 20100510

17Q First examination report despatched

Effective date: 20100616

AKX Designation fees paid

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 MT NL NO PL PT RO SE SI SK TR

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

Owner name: SIEMENS AKTIENGESELLSCHAFT

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

RIC1 Information provided on ipc code assigned before grant

Ipc: F01D 25/28 20060101AFI20141013BHEP

INTG Intention to grant announced

Effective date: 20141106

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): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC 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: 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: 502008012824

Country of ref document: DE

Effective date: 20150507

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 719218

Country of ref document: AT

Kind code of ref document: T

Effective date: 20150515

Ref country code: CH

Ref legal event code: NV

Representative=s name: SIEMENS SCHWEIZ AG, CH

REG Reference to a national code

Ref country code: NL

Ref legal event code: T3

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: 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: 20150401

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: 20150701

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: 20150401

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: 20150401

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: 20150401

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: 20150401

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: 20150803

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 8

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

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: 20150401

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: 20150702

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: 20150801

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502008012824

Country of ref document: DE

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

Ref country code: DK

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

Effective date: 20150401

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: 20150401

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: 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: 20150401

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: 20150401

Ref country code: RO

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

Effective date: 20150401

26N No opposition filed

Effective date: 20160105

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: 20150401

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

Ref country code: LU

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

Effective date: 20151114

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: 20150401

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: IE

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

Effective date: 20151114

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 9

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 719218

Country of ref document: AT

Kind code of ref document: T

Effective date: 20151114

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

Ref country code: FR

Payment date: 20161123

Year of fee payment: 9

Ref country code: NL

Payment date: 20161108

Year of fee payment: 9

Ref country code: GB

Payment date: 20161114

Year of fee payment: 9

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: 20151114

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

Ref country code: IT

Payment date: 20161128

Year of fee payment: 9

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

Ref country code: CH

Payment date: 20170202

Year of fee payment: 9

Ref country code: DE

Payment date: 20170120

Year of fee payment: 9

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: 20081114

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: 20150401

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: 20150401

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: 20150401

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: 20151130

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: 20150401

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: 20150401

REG Reference to a national code

Ref country code: CH

Ref legal event code: PCOW

Free format text: NEW ADDRESS: WERNER-VON-SIEMENS-STRASSE 1, 80333 MUENCHEN (DE)

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502008012824

Country of ref document: DE

REG Reference to a national code

Ref country code: NL

Ref legal event code: MM

Effective date: 20171201

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

Effective date: 20171114

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

Ref country code: CH

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

Effective date: 20171130

Ref country code: LI

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

Effective date: 20171130

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20180731

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

Ref country code: NL

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

Effective date: 20171201

Ref country code: IT

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

Effective date: 20171114

Ref country code: FR

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

Effective date: 20171130

Ref country code: DE

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

Effective date: 20180602

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: 20171114