EP1914036A1 - Turbine blade for a turbine with a cooling channel - Google Patents

Turbine blade for a turbine with a cooling channel Download PDF

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Publication number
EP1914036A1
EP1914036A1 EP06021677A EP06021677A EP1914036A1 EP 1914036 A1 EP1914036 A1 EP 1914036A1 EP 06021677 A EP06021677 A EP 06021677A EP 06021677 A EP06021677 A EP 06021677A EP 1914036 A1 EP1914036 A1 EP 1914036A1
Authority
EP
European Patent Office
Prior art keywords
platform
turbine
turbine blade
coolant
channel
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
EP06021677A
Other languages
German (de)
French (fr)
Other versions
EP1914036B1 (en
Inventor
Katharina Bergander
Georg Dr. Bostanjoglo
Tobias Dr. Buchal
Winfried Dr. Esser
Dirk Dr. Goldschmidt
Torsten Koch
Rudolf Küperkoch
Thorsten Mattheis
Jan Münzer
Ralf Müsgen
Matthias Dr. Oechsner
Ursula Pickert
Volker Dr. Vosberg
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 EP06021677A priority Critical patent/EP1914036B1/en
Priority to AT06021677T priority patent/ATE459447T1/en
Priority to DE502006006344T priority patent/DE502006006344D1/en
Priority to JP2007266270A priority patent/JP4510864B2/en
Priority to US11/974,895 priority patent/US8021118B2/en
Publication of EP1914036A1 publication Critical patent/EP1914036A1/en
Application granted granted Critical
Publication of EP1914036B1 publication Critical patent/EP1914036B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • 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
    • F05D2230/10—Manufacture by removing material
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/238—Soldering
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms
    • 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 turbine blade for a turbine of a thermal power plant having a platform for partially limiting a flow channel in the turbine, wherein the platform has at least one coolant channel extending inside the platform for guiding a coolant. Furthermore, the invention relates to a turbine with such a turbine blade.
  • a hot flow medium such as superheated steam in the case of a steam turbine or hot gas in the case of a gas turbine
  • flows through the flow channel In order to protect the flow channel partially limiting platform from overheating, it is therefore important to cool the platform.
  • coolant channels in the form of film cooling holes are introduced into the surface of the platform facing the flow channel. These film cooling holes are very thin in cross section and exit at an acute angle from the platform surface. The film cooling holes create a cooling film over the platform surface.
  • the introduction of the cooling air holes in the platform is very expensive. Also, the achievable cooling effect is limited.
  • the turbine blade mentioned above in which the at least one coolant channel opens out at least two connection openings from the platform and which at least one attachable to the platform or attached additional component with a connecting channel which is designed to fluidly connect the connection openings with each other.
  • the object is achieved according to the invention with a turbine having such a turbine blade.
  • the object is further achieved according to the invention with an additional component for a turbine blade of a turbine of a thermal power plant, which has a platform for partially limiting a flow channel in the turbine, which comprises at least one extending within the platform coolant channel for guiding a coolant, which at least two Connecting openings empties out of the platform, wherein the additional component is designed for attachment to the platform and having a connection channel which is adapted to connect the connection openings in fluid communication with each other.
  • the turbine blade according to the invention may be designed for use in a gas turbine or a steam turbine. Furthermore, the turbine blade may be formed as a vane or as a blade.
  • the cooled platform according to the invention may thus be a blade platform and / or a guide blade platform, in particular an upper or lower guide blade platform.
  • the at least one coolant channel with an enlarged cross section can be formed.
  • the coolant channel would have to be designed as a bore with a very small cross-section, in order to minimize the loss of coolant through the connecting openings, which then function as access holes.
  • the coolant channel can be designed with an enlarged cross-section, this can with a correspondingly higher coolant flow rate operate.
  • the cooling effect of the at least one coolant channel is significantly improved.
  • gaseous media such as cooling air and / or liquid cooling media in question.
  • the coolant channel can already be made during the casting of the platform or the turbine blade.
  • the coolant channel must therefore not be subsequently introduced into the platform by means of machining, such as by drilling.
  • the cooling function of the platform can be provided with reduced effort in the production.
  • the cooling channel can also be manufactured with geometry optimized for the cooling effect. For example, it is possible to bend the coolant channel, in particular to make it meandering.
  • the complexity of the component (s) of the turbine to be manufactured as a whole is further reduced. This allows cost savings in the manufacturing process.
  • the modular construction of the turbine blade facilitates a possible repair of the turbine blade.
  • the additional component can be replaced separately if necessary.
  • an improved discharge rate of the individual components can be achieved in the casting process. This can be achieved, for example, by simplified geometries and by avoiding cross-sectional changes. Such an improvement in the discharge rate can be achieved especially in directional solidification of the cast components or of the cast component, such as when using DS or SX alloys.
  • the individual coolant channels in each case at a first connection opening and a second connection opening out of the platform and when a first additional component and a second additional component for the respective fluid-conducting connection of the first connection openings or the second connection openings are provided.
  • a first additional component and a second additional component for the respective fluid-conducting connection of the first connection openings or the second connection openings are provided.
  • the turbine blade has a longitudinal extent, with respect to which it can be mounted radially to a rotor axis of the turbine in the turbine, the platform extends along a main boundary surface transverse to the longitudinal extent of the turbine blade, and arranged transversely to the main boundary surface faces, and the connection openings connected to one another via the at least one additional component are arranged on one of the end faces, in particular on an end face which extends parallel to the rotor axis in the assembled state. This end face then has the exclusion openings to be connected to one another via the additional component.
  • the additional component is designed in such a way that, when mounted on the platform, it continues the surface of the platform facing the flow channel.
  • the attachment component continues the flow surface of the platform such that the transition does not cause any additional turbulence in the flow medium. It is furthermore advantageous if connection openings are arranged on two end faces of the platform pointing in respectively opposite directions. In this case, two additional components should be provided, one for each of the two end faces. Furthermore, it is advantageous if the at least one coolant channel runs parallel to the main boundary surface within the platform. In this embodiment, the main boundary surface of the platform can be cooled particularly effectively.
  • the turbine blade according to the invention is particularly robust in turbine operation when the at least one additional component is connected in a material-locking and / or form-fitting manner to the platform. This creates a load-bearing connection between the platform and the additional component, with the result that the connection between the components withstands the strong forces occurring in turbine operation. This minimizes maintenance and repair interruptions in the operation of the turbine. Furthermore, it is advantageous if the additional component has sealing grooves and / or sealing tips. Furthermore, it is expedient if the additional component is specifically adapted in its shape to compensate for gaps between platforms of two adjacent turbine blades in the assembled state of the turbine blades.
  • the connecting channel extends completely within the additional component and in particular has a U-shape.
  • the coolant flowing through the connecting channel can, in particular, cool the surface of the additional component adjacent to the flow channel.
  • the connecting channel in the additional component can be advantageously formed by prototyping, such as by casting or forging or by subsequent mechanical processing.
  • the platform and the additional component have different materials.
  • the platform is made of a different material or of a different material composition than the additional component.
  • the respective component is manufactured with a material adapted to mechanical or chemical requirements of the respective component.
  • the additional component can be made for example of "foreign material”. It is approximately advantageous if the additional component has oxidation-resistant material.
  • the above object is achieved with the turbine blade mentioned in the introduction, in which the platform is a casting and the at least one coolant channel comprises a recessed during casting of the platform cavity.
  • the coolant channel must therefore not be subsequently introduced into the platform. Rather, the platform may be cast with simultaneous formation of the coolant channel, if necessary, together with other areas of the turbine blade. The production of the turbine blade is thus considerably facilitated.
  • the additional component is likewise a casting and the connecting channel comprises a recessed during casting of the additional component cavity.
  • each connection opening is assigned a cooling channel and the additional component allows the connection of the at least two coolant channels.
  • the at least two coolant channels each extend in a straight line and in particular parallel to one another.
  • the coolant can be guided particularly directly to possible outlet openings on the platform surface.
  • the at least two coolant channels extend transversely to an axial extent of the rotor.
  • cooling channels which are located further upstream, can be acted upon by a correspondingly more cooling coolant than further downstream cooling channels.
  • the cooling behavior of the cooling channels can be adjusted to the temperature profile of the flow medium in the flow channel, the temperature of which decreases downstream.
  • Coolant channels can be cylindrical, conical or polygonal in cross-section.
  • a particularly effective platform cooling can be achieved if further cooling cavities, in particular opening into the surface of the platform cooling holes are provided and the at least one coolant channel is formed as a coolant supply channel, which supplies the other cooling cavities with coolant.
  • Such cooling holes may be designed as film cooling holes, with which a cooling film can be generated over the platform surface.
  • the coolant channel supplies in this case a plurality of cooling cavities with the coolant.
  • the coolant then enters the flow channel through a gap between the adjacent platforms and cools the platform in the region of the abutting edge. Furthermore, it is advantageous if the further cooling cavities are introduced after the casting of the platform by means of machining, such as by drilling in the platform.
  • the additional component is designed as a casting and the at least one connecting channel comprises a recessed in the casting of the additional component cavity. It is also advantageous if further cooling cavities, in particular in the surface of the additional component opening cooling holes are provided in the additional component, which are mounted after the casting of the additional component by means of machining in the additional component.
  • FIG. 1 shows an exemplary embodiment of a turbine blade 10 according to the invention which extends essentially along a longitudinal axis 12.
  • the turbine blade is designed as a guide vane. It should be noted at this point, however, that the invention is not limited to a vane, but should also include about blades.
  • the turbine blade 10 comprises an airfoil 14 extending along the longitudinal axis 12 and only partially shown in FIG. 1.
  • An end 16 of the airfoil 14 is adjoined by a platform 16 oriented transversely to the longitudinal axis 12.
  • the platform 16 serves, with turbine blade mounted in an associated turbine, to use a flow channel in the turbine a main boundary surface 30 of the platform 16 together with platforms of other turbine blades to limit.
  • Downstream of the platform 16 is a mounting structure 18 for attaching the turbine blade to a housing or vane ring.
  • the attachment structure 18 is configured as a blade root for attaching the blade to a rotor of the turbine.
  • the coolant channels 20 are formed in the present case rectilinear and run in the turbine-mounted turbine blade 10 transversely to the axial extent of the rotor of the turbine.
  • the coolant channels lead out of the platform 16 at a first end face 32 and a second end face 34.
  • the two end faces 32 and 34 extend substantially perpendicular to the main boundary surface 30 and transverse to an axial extent of the rotor in the turbine-mounted state of the turbine blade 10.
  • a first additional component 24 is attached to the first end face 32 and a second additional component 26 is fastened to the second end face 34.
  • the individual additional components 24 and 26 each have a connection channel 28 for connecting in each case two connection openings 22 of the associated coolant channels 20.
  • the additional components 24 and 26 may be positively connected to the platform 16, as shown in Fig. 4a. This can be done by means of a groove / web connection, in which the groove is designed dovetailed in cross section.
  • the additional components 24 and 26 may also be materially connected to the platform 16, as illustrated in FIG. 4b. In this case, the corresponding components are preferably fastened to one another by means of a soldered or welded connection 36.

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

Abstract

The blade has a platform (16) for defining a flow channel in a turbine, where the platform has a coolant channel (20), which extends in the platform and guides the coolant. The coolant channel leads to two connection openings of the platform. An auxiliary component (24,26) is fastened at the platform, and has a connecting channel (28), which connects the openings with each other in a fluid-conductive manner. The platform extends transverse to a longitudinal extension of the blade along a main defining surface (30), and has front surfaces, which are arranged transverse to the extension.

Description

Die Erfindung betrifft eine Turbinenschaufel für eine Turbine eines thermischen Kraftwerks mit einer Plattform zum teilweisen Begrenzen eines Strömungskanals in der Turbine, wobei die Plattform mindestens einen sich innerhalb der Plattform erstreckenden Kühlmittelkanal zum Führen eines Kühlmittels aufweist. Weiterhin betrifft die Erfindung eine Turbine mit einer derartigen Turbinenschaufel.The invention relates to a turbine blade for a turbine of a thermal power plant having a platform for partially limiting a flow channel in the turbine, wherein the platform has at least one coolant channel extending inside the platform for guiding a coolant. Furthermore, the invention relates to a turbine with such a turbine blade.

Im Betrieb einer derartigen Turbine strömt ein heißes Strömungsmedium, wie etwa Heißdampf im Fall einer Dampfturbine oder Heißgas im Fall einer Gasturbine, durch den Strömungskanal. Um die den Strömungskanal teilweise begrenzende Plattform vor Überhitzung zu schützen, ist es daher wichtig, die Plattform zu kühlen. Bei Plattformen aus dem Stand der Technik sind dazu Kühlmittelkanäle in Form von Filmkühlbohrungen in die dem Strömungskanal zugewandte Oberfläche der Plattform eingebracht. Diese Filmkühlbohrungen sind sehr dünn im Querschnitt und treten in spitzem Winkel aus der Plattformoberfläche aus. Mittels der Filmkühlbohrungen wird ein Kühlfilm über der Plattformoberfläche erzeugt. Das Einbringen der Kühlluftbohrungen in die Plattform ist allerdings sehr aufwendig. Auch ist die damit erzielbare Kühlwirkung begrenzt.In operation of such a turbine, a hot flow medium, such as superheated steam in the case of a steam turbine or hot gas in the case of a gas turbine, flows through the flow channel. In order to protect the flow channel partially limiting platform from overheating, it is therefore important to cool the platform. In the case of prior art platforms, coolant channels in the form of film cooling holes are introduced into the surface of the platform facing the flow channel. These film cooling holes are very thin in cross section and exit at an acute angle from the platform surface. The film cooling holes create a cooling film over the platform surface. However, the introduction of the cooling air holes in the platform is very expensive. Also, the achievable cooling effect is limited.

Es ist eine Aufgabe der Erfindung, eine gattungsgemäße Turbine bereit zu stellen, bei der die Plattform der Turbinenschaufel wirksamer gekühlt werden kann und/oder die Kühlfunktion der Plattform mit verringertem Aufwand in der Herstellung erreicht werden kann.It is an object of the invention to provide a generic turbine in which the platform of the turbine blade can be cooled more effectively and / or the cooling function of the platform can be achieved with reduced effort in the production.

Diese Aufgabe ist erfindungsgemäß mit der eingangs genannten Turbinenschaufel gelöst, bei der der mindestens eine Kühlmittelkanal an mindestens zwei Anschlussöffnungen aus der Plattform ausmündet und welche mindestens ein an der Plattform befestigbares bzw. befestigtes Zusatzbauteil mit einem Verbindungskanal aufweist, welcher darauf ausgelegt ist, die Anschlussöffnungen fluidleitend miteinander zu verbinden. Darüber hinaus ist die Aufgabe erfindungsgemäß mit einer Turbine gelöst, die eine derartige Turbinenschaufel aufweist. Die Aufgabe ist erfindungsgemäß ferner mit einem Zusatzbauteil für eine Turbinenschaufel einer Turbine eines thermischen Kraftwerks gelöst, welche eine Plattform zum teilweisen Begrenzen eines Strömungskanals in der Turbine aufweist, die mindestens einen sich innerhalb der Plattform erstreckenden Kühlmittelkanal zum Führen eines Kühlmittels umfasst, welcher an mindestens zwei Anschlussöffnungen aus der Plattform ausmündet, wobei das Zusatzbauteil zum Befestigen an der Plattform gestaltet ist und einen Verbindungskanal aufweist, welcher darauf ausgelegt ist, die Anschlussöffnungen fluidleitend miteinander zu verbinden. Die Turbinenschaufel gemäß der Erfindung kann zur Verwendung in einer Gasturbine oder einer Dampfturbine gestaltet sein. Weiterhin kann die Turbinenschaufel als Leitschaufel oder als Laufschaufel ausgebildet sein. Bei der erfindungsgemäß gekühlten Plattform kann es sich damit um eine Laufschaufelplattform und/oder eine Leitschaufelplattform, insbesondere um eine obere oder untere Leitschaufelplattform handeln.This object is achieved according to the invention with the turbine blade mentioned above, in which the at least one coolant channel opens out at least two connection openings from the platform and which at least one attachable to the platform or attached additional component with a connecting channel which is designed to fluidly connect the connection openings with each other. Moreover, the object is achieved according to the invention with a turbine having such a turbine blade. The object is further achieved according to the invention with an additional component for a turbine blade of a turbine of a thermal power plant, which has a platform for partially limiting a flow channel in the turbine, which comprises at least one extending within the platform coolant channel for guiding a coolant, which at least two Connecting openings empties out of the platform, wherein the additional component is designed for attachment to the platform and having a connection channel which is adapted to connect the connection openings in fluid communication with each other. The turbine blade according to the invention may be designed for use in a gas turbine or a steam turbine. Furthermore, the turbine blade may be formed as a vane or as a blade. The cooled platform according to the invention may thus be a blade platform and / or a guide blade platform, in particular an upper or lower guide blade platform.

Durch das erfindungsgemäße Vorsehen eines Zusatzbauteils mit einem Verbindungskanal kann der mindestens eine Kühlmittelkanal mit vergrößertem Querschnitt ausgebildet werden. Durch das Verbinden der mindestens zwei Anschlussöffnungen über den Verbindungskanal des Zusatzbauteils wird verhindert, dass das Kühlmittel an den Anschlussöffnungen austritt und damit für die Plattformkühlung verloren geht. Ohne ein derartiges Zusatzbauteil müsste der Kühlmittelkanal als Bohrung mit sehr kleinem Querschnitt ausgeführt werden, um den Kühlmittelverlust durch die dann als Zugangsbohrungen fungierenden Anschlussöffnungen möglichst gering zu halten.By providing an additional component according to the invention with a connecting channel, the at least one coolant channel with an enlarged cross section can be formed. By connecting the at least two connection openings via the connection channel of the additional component, it is prevented that the coolant exits at the connection openings and is thus lost for the platform cooling. Without such an additional component, the coolant channel would have to be designed as a bore with a very small cross-section, in order to minimize the loss of coolant through the connecting openings, which then function as access holes.

Da bei der erfindungsgemäßen Turbinenschaufel der Kühlmittelkanal mit vergrößertem Querschnitt ausgeführt werden kann, kann dieser mit einem entsprechend höheren Kühlmitteldurchsatz betrieben werden. Damit wird die Kühlwirkung des mindestens einen Kühlmittelkanals erheblich verbessert. Als Kühlmittel zum Durchströmen des Kühlmittelkanals kommen insbesondere gasförmige Medien, wie etwa Kühlluft und/oder flüssige Kühlmedien in Frage.Since in the turbine blade according to the invention, the coolant channel can be designed with an enlarged cross-section, this can with a correspondingly higher coolant flow rate operate. Thus, the cooling effect of the at least one coolant channel is significantly improved. As a coolant for flowing through the coolant channel are in particular gaseous media, such as cooling air and / or liquid cooling media in question.

Durch die mittels der Erfindung geschaffene Möglichkeit, den Kühlmittelkanal mit größerem Querschnitt herzustellen, kann der Kühlmittelkanal bereits während dem Gießen der Plattform bzw. der Turbinenschaufel hergestellt werden. Der Kühlmittelkanal muss damit nicht nachträglich in die Plattform mittels spanender Bearbeitung, wie etwa durch Bohren eingebracht werden. Erfindungsgemäß kann daher die Kühlfunktion der Plattform mit verringertem Aufwand in der Herstellung bereitgestellt werden. Durch die Möglichkeit, den Kühlmittelkanal bereits während dem Gussprozess herzustellen, kann der Kühlkanal auch mit für die Kühlwirkung optimierter Geometrie gefertigt werden. So ist es etwa möglich, den Kühlmittelkanal gebogen, insbesondere mäanderförmig zu gestalten.By created by the invention way to produce the coolant channel with a larger cross section, the coolant channel can already be made during the casting of the platform or the turbine blade. The coolant channel must therefore not be subsequently introduced into the platform by means of machining, such as by drilling. According to the invention, therefore, the cooling function of the platform can be provided with reduced effort in the production. Due to the possibility of producing the coolant channel already during the casting process, the cooling channel can also be manufactured with geometry optimized for the cooling effect. For example, it is possible to bend the coolant channel, in particular to make it meandering.

Durch das Vorsehen eines von der Turbinenschaufel separaten Zusatzbauteils verringert sich weiterhin die Komplexität der bzw. des im Ganzen zu fertigenden Bauteile/Bauteils der Turbine. Dies ermöglicht eine Kostenersparnis im Herstellungsverfahren. Darüber hinaus wird durch den modularen Aufbau der Turbinenschaufel eine mögliche Reparatur der Turbinenschaufel erleichtert. So kann etwa das Zusatzbauteil bei Bedarf separat ausgewechselt werden. Weiterhin kann eine verbesserte Ausbringrate der einzelnen Bauteile im Gussverfahren erreicht werden. Dies kann etwa durch vereinfachte Geometrien und durch Vermeidung von Querschnittsänderungen erreicht werden. Eine derartige Verbesserung der Ausbringrate kann besonders bei gerichteter Erstarrung der Gussbauteile bzw. des Gussbauteils, wie bei Verwendung von DS- oder SX-Legierungen erreicht werden.By providing an additional component separate from the turbine blade, the complexity of the component (s) of the turbine to be manufactured as a whole is further reduced. This allows cost savings in the manufacturing process. In addition, the modular construction of the turbine blade facilitates a possible repair of the turbine blade. For example, the additional component can be replaced separately if necessary. Furthermore, an improved discharge rate of the individual components can be achieved in the casting process. This can be achieved, for example, by simplified geometries and by avoiding cross-sectional changes. Such an improvement in the discharge rate can be achieved especially in directional solidification of the cast components or of the cast component, such as when using DS or SX alloys.

Es ist darüber hinaus zweckmäßig, wenn die einzelnen Kühlmittelkanäle jeweils an einer ersten Anschlussöffnung und einer zweiten Anschlussöffnung aus der Plattform ausmünden und wenn ein erstes Zusatzbauteil und ein zweites Zusatzbauteil zum jeweiligen fluidleitenden Verbinden der ersten Anschlussöffnungen bzw. der zweiten Anschlussöffnungen vorgesehen sind. Damit können etwa zwei Kühlmittelkanäle an beiden Enden mittels Zusatzmodulen verbunden sein, wodurch sich ein geschlossenes Leitungssystem ergibt. Durch dieses kann ein Kühlmittelkreislauf etabliert werden.It is also expedient if the individual coolant channels in each case at a first connection opening and a second connection opening out of the platform and when a first additional component and a second additional component for the respective fluid-conducting connection of the first connection openings or the second connection openings are provided. Thus, about two coolant channels can be connected at both ends by means of additional modules, resulting in a closed line system. Through this, a coolant circuit can be established.

Darüber hinaus ist es vorteilhaft, wenn die Turbinenschaufel eine Längserstreckung aufweist, bezüglich der sie radial zu einer Rotorachse der Turbine in der Turbine montierbar ist, die Plattform sich entlang einer Hauptbegrenzungsfläche quer zur Längserstreckung der Turbinenschaufel erstreckt, sowie quer zur Hauptbegrenzungsfläche angeordnete Stirnflächen aufweist, und die über das mindestens eine Zusatzbauteil miteinander verbundenen Anschlussöffnungen an einer der Stirnflächen, insbesondere an einer Stirnfläche, die sich im montierten Zustand parallel zu der Rotorachse erstreckt, angeordnet sind. Diese Stirnfläche weist dann die über das Zusatzbauteil miteinander zu verbindenden Ausschlussöffnungen auf. Insbesondere ist es vorteilhaft, wenn das Zusatzbauteil derart gestaltet ist, dass es im an die Plattform angebauten Zustand die dem Strömungskanal zugewandte Oberfläche der Plattform fortführt. Vorteilhafterweise führt das Anbaubauteil die Strömungsoberfläche der Plattform derart weiter, dass der Übergang keine zusätzlichen Turbulenzen im Strömungsmedium verursacht. Es ist weiterhin vorteilhaft, wenn Anschlussöffnungen an zwei in jeweils entgegengesetzte Richtungen weisenden Stirnflächen der Plattform angeordnet sind. In diesem Fall sollten zwei Zusatzbauteile vorgesehen sein, eines für jede der beiden Stirnflächen. Ferner ist es vorteilhaft, wenn der mindestens eine Kühlmittelkanal parallel zur Hauptbegrenzungsfläche innerhalb der Plattform verläuft. In dieser Ausgestaltung lässt sich die Hauptbegrenzungsfläche der Plattform besonders wirkungsvoll kühlen.Moreover, it is advantageous if the turbine blade has a longitudinal extent, with respect to which it can be mounted radially to a rotor axis of the turbine in the turbine, the platform extends along a main boundary surface transverse to the longitudinal extent of the turbine blade, and arranged transversely to the main boundary surface faces, and the connection openings connected to one another via the at least one additional component are arranged on one of the end faces, in particular on an end face which extends parallel to the rotor axis in the assembled state. This end face then has the exclusion openings to be connected to one another via the additional component. In particular, it is advantageous if the additional component is designed in such a way that, when mounted on the platform, it continues the surface of the platform facing the flow channel. Advantageously, the attachment component continues the flow surface of the platform such that the transition does not cause any additional turbulence in the flow medium. It is furthermore advantageous if connection openings are arranged on two end faces of the platform pointing in respectively opposite directions. In this case, two additional components should be provided, one for each of the two end faces. Furthermore, it is advantageous if the at least one coolant channel runs parallel to the main boundary surface within the platform. In this embodiment, the main boundary surface of the platform can be cooled particularly effectively.

Die erfindungsgemäße Turbinenschaufel ist im Turbinenbetrieb besonders robust, wenn das mindestens eine Zusatzbauteil stoffschlüssig und/oder formschlüssig mit der Plattform verbunden ist. Damit wird eine belastbare Verbindung zwischen der Plattform und dem Zusatzbauteil geschaffen, was dazu führt, dass die Verbindung zwischen den Bauteilen den im Turbinenbetrieb auftretenden starken Kräften standhält. Damit werden Wartungs- und Reparaturunterbrechungen im Betrieb der Turbine minimiert. Weiterhin ist es vorteilhaft, wenn das Zusatzbauteil Dichtnuten und/oder Dichtspitzen aufweist. Ferner ist es zweckmäßig, wenn das Zusatzbauteil in seiner Form gezielt darauf angepasst ist, Zwischenräume zwischen Plattformen zweier benachbarter Turbinenschaufeln im montierten Zustand der Turbinenschaufeln auszugleichen.The turbine blade according to the invention is particularly robust in turbine operation when the at least one additional component is connected in a material-locking and / or form-fitting manner to the platform. This creates a load-bearing connection between the platform and the additional component, with the result that the connection between the components withstands the strong forces occurring in turbine operation. This minimizes maintenance and repair interruptions in the operation of the turbine. Furthermore, it is advantageous if the additional component has sealing grooves and / or sealing tips. Furthermore, it is expedient if the additional component is specifically adapted in its shape to compensate for gaps between platforms of two adjacent turbine blades in the assembled state of the turbine blades.

In einer weiteren vorteilhaften Ausführungsform erstreckt sich der Verbindungskanal vollständig innerhalb des Zusatzbauteils und weist insbesondere eine U-Form auf. Das durch den Verbindungskanal strömende Kühlmittel kann insbesondere die an den Strömungskanal angrenzende Oberfläche des Zusatzbauteils kühlen. Der Verbindungskanal im Zusatzbauteil kann vorteilhafterweise durch Urformen, wie etwa durch Gießen oder Schmieden oder auch durch nachträgliche mechanische Bearbeitung gebildet werden.In a further advantageous embodiment, the connecting channel extends completely within the additional component and in particular has a U-shape. The coolant flowing through the connecting channel can, in particular, cool the surface of the additional component adjacent to the flow channel. The connecting channel in the additional component can be advantageously formed by prototyping, such as by casting or forging or by subsequent mechanical processing.

In einer weiteren zweckmäßigen Ausführungsform der Turbinenschaufel weisen die Plattform und das Zusatzbauteil unterschiedliche Materialien auf. Damit ist die Plattform aus einem anderen Material bzw. aus einer anderen Materialzusammensetzung als das Zusatzbauteil gefertigt. Vorteilhafterweise wird das jeweilige Bauteil mit einem an mechanische bzw. chemische Anforderungen des jeweiligen Bauteils angepassten Material gefertigt. So kann das Zusatzbauteil etwa aus "artfremdem Material" gefertigt sein. Es etwa vorteilhaft, wenn das Zusatzbauteil oxidationsresistentes Material aufweist.In a further expedient embodiment of the turbine blade, the platform and the additional component have different materials. Thus, the platform is made of a different material or of a different material composition than the additional component. Advantageously, the respective component is manufactured with a material adapted to mechanical or chemical requirements of the respective component. Thus, the additional component can be made for example of "foreign material". It is approximately advantageous if the additional component has oxidation-resistant material.

Weiterhin ist die vorgenannte Aufgabe mit der eingangs genannten Turbinenschaufel gelöst, bei der die Plattform ein Gussteil ist und der mindestens eine Kühlmittelkanal einen beim Gießen der Plattform ausgesparten Hohlraum umfasst. Der Kühlmittelkanal muss damit nicht nachträglich in die Plattform eingebracht werden. Vielmehr kann die Plattform unter gleichzeitiger Ausbildung des Kühlmittelkanals ggf. zusammen mit anderen Bereichen der Turbinenschaufel gegossen werden. Die Herstellung der Turbinenschaufel wird damit erheblich erleichtert. Darüber hinaus ist es vorteilhaft, wenn das Zusatzbauteil ebenfalls ein Gussteil ist und der Verbindungskanal einen beim Gießen des Zusatzbauteils ausgesparten Hohlraum umfasst.Furthermore, the above object is achieved with the turbine blade mentioned in the introduction, in which the platform is a casting and the at least one coolant channel comprises a recessed during casting of the platform cavity. The coolant channel must therefore not be subsequently introduced into the platform. Rather, the platform may be cast with simultaneous formation of the coolant channel, if necessary, together with other areas of the turbine blade. The production of the turbine blade is thus considerably facilitated. Moreover, it is advantageous if the additional component is likewise a casting and the connecting channel comprises a recessed during casting of the additional component cavity.

In einer vorteilhaften Ausführungsform sind zwei Kühlmittelkanäle vorgesehen, die an jeweils einer der mindestens zwei Anschlussöffnungen aus der Plattform aus. Damit ist jeder Anschlussöffnung ein Kühlkanal zugeordnet und das Zusatzbauteil ermöglicht die Verbindung der mindestens zwei Kühlmittelkanäle. In einer darüber hinaus zweckmäßigen Ausführungsform erstrecken sich die mindestens zwei Kühlmittelkanäle jeweils geradlinig und insbesondere parallel zueinander. Damit kann das Kühlmittel besonders direkt zu möglichen Austrittsöffnungen an der Plattformoberfläche geführt werden. Insbesondere erstrecken sich die mindestens zwei Kühlmittelkanäle quer zu einer Axialerstreckung des Rotors. Bei Vorsehen mehrerer quer zur Axialerstreckung des Rotors angeordneter Kühlkanäle kann damit die Plattformkühlung hervorragend auf einen im Strömungskanal entlang der Axialerstreckung des Rotors vorliegenden Temperaturgradienten des Strömungsmediums eingestellt werden. So können Kühlkanäle, die weiter strömungsaufwärts liegen mit einem entsprechend stärker kühlenden Kühlmittel beaufschlagt werden als weiter strömungsabwärts liegende Kühlkanäle. Damit lässt sich das Kühlverhalten der Kühlkanäle auf den Temperaturverlauf des Strömungsmediums im Strömungskanal, deren Temperatur sich strömungsabwärts verringert, einstellen. Kühlmittelkanäle können im Querschnitt zylindrisch, konisch oder polygon gestaltet sein.In an advantageous embodiment, two coolant channels are provided, which at each one of the at least two connection openings from the platform. Thus, each connection opening is assigned a cooling channel and the additional component allows the connection of the at least two coolant channels. In a further expedient embodiment, the at least two coolant channels each extend in a straight line and in particular parallel to one another. Thus, the coolant can be guided particularly directly to possible outlet openings on the platform surface. In particular, the at least two coolant channels extend transversely to an axial extent of the rotor. With the provision of a plurality of cooling channels arranged transversely to the axial extent of the rotor, the platform cooling can thus be adjusted excellently to a temperature gradient of the flow medium present in the flow channel along the axial extension of the rotor. Thus, cooling channels, which are located further upstream, can be acted upon by a correspondingly more cooling coolant than further downstream cooling channels. Thus, the cooling behavior of the cooling channels can be adjusted to the temperature profile of the flow medium in the flow channel, the temperature of which decreases downstream. Coolant channels can be cylindrical, conical or polygonal in cross-section.

Eine besonders wirksame Plattformkühlung kann erreicht werden, wenn weitere Kühlkavitäten, insbesondere in die Oberfläche der Plattform mündende Kühlbohrungen vorgesehen sind und der mindestens eine Kühlmittelkanal als Kühlmittelversorgungskanal ausgebildet ist, der die weiteren Kühlkavitäten mit Kühlmittel versorgt. Derartige Kühlbohrungen können als Filmkühlbohrungen ausgeführt sein, mit denen ein Kühlfilm über der Plattformoberfläche erzeugt werden kann. Der Kühlmittelkanal versorgt in diesen Fall mehrere Kühlkavitäten mit dem Kühlmittel. Durch das Vorsehen eines Kühlmittelversorgungskanals gemäß dieser vorteilhaften Ausführungsform der Erfindung kann das zur Kühlung der Plattform benötigte Kühlmittel den weiteren Kühlkavitäten besonders effizient zugeführt werden. Der Kühlmittelversorgungskanal kann auch Kühlkavitäten speisen, die keinen Auslass an der Oberfläche der Plattform haben. Auch können die Kühlkavitäten etwa an einer Stoßkante zu einer benachbarten Plattform einen Auslass aufweisen. Das Kühlmittel tritt dann durch einen Spalt zwischen den benachbarten Plattformen in den Strömungskanal ein und kühlt die Plattform im Bereich der Stoßkante. Weiterhin ist es vorteilhaft, wenn die weiteren Kühlkavitäten nach dem Gießen der Plattform mittels spanender Bearbeitung, wie etwa durch Bohren in die Plattform eingebracht sind.A particularly effective platform cooling can be achieved if further cooling cavities, in particular opening into the surface of the platform cooling holes are provided and the at least one coolant channel is formed as a coolant supply channel, which supplies the other cooling cavities with coolant. Such cooling holes may be designed as film cooling holes, with which a cooling film can be generated over the platform surface. The coolant channel supplies in this case a plurality of cooling cavities with the coolant. By providing a coolant supply channel according to this advantageous embodiment of the invention, the coolant required for cooling the platform can be supplied to the further cooling cavities particularly efficiently. The coolant supply channel can also feed cooling cavities that have no outlet at the surface of the platform. Also, the cooling cavities may have an outlet at about a butt edge to an adjacent platform. The coolant then enters the flow channel through a gap between the adjacent platforms and cools the platform in the region of the abutting edge. Furthermore, it is advantageous if the further cooling cavities are introduced after the casting of the platform by means of machining, such as by drilling in the platform.

In einer vorteilhaften Ausführungsform des erfindungsgemäßen Zusatzbauteils ist dieses als Gussteil ausgeführt und der mindestens eine Verbindungskanal umfasst einen beim Gießen des Zusatzbauteils ausgesparten Hohlraum. Es ist weiterhin vorteilhaft, wenn in dem Zusatzbauteil weitere Kühlkavitäten, insbesondere in der Oberfläche des Zusatzbauteils mündende Kühlbohrungen vorgesehen sind, die nach dem Gießen des Zusatzbauteils mittels spanender Bearbeitung in das Zusatzbauteil angebracht sind.In an advantageous embodiment of the additional component according to the invention this is designed as a casting and the at least one connecting channel comprises a recessed in the casting of the additional component cavity. It is also advantageous if further cooling cavities, in particular in the surface of the additional component opening cooling holes are provided in the additional component, which are mounted after the casting of the additional component by means of machining in the additional component.

Nachfolgend wird ein Ausführungsbeispiel einer erfindungsgemäßen Turbinenschaufel anhand der beigefügten schematischen Zeichnung näher erläutert.Hereinafter, an embodiment of a turbine blade according to the invention will be explained in more detail with reference to the accompanying schematic drawing.

Es zeigt:

Fig. 1
eine perspektivische Teilansicht eines Ausführungsbeispiels der erfindungsgemäßen Turbinenschaufel mit einer Plattform ohne zeichnerische Darstellung eines Zusatzbauteils zum Anordnen an der Plattform,
Fig. 2
eine perspektivische Ansicht der Plattform gemäß Fig. 1 in stark vereinfachter Darstellung aus einer etwa um 90° gedrehten Blickrichtung zusammen mit zwei an jeweiligen Stirnflächen der Plattform angeordneten Zusatzbauteilen,
Fig. 3
eine Teilansicht der Plattform sowie eines Zusatzbauteils gemäß Fig. 2 im Längsschnitt,
Fig. 4a
eine Teilansicht der Plattform mit einem Zusatzbauteil gemäß Fig. 2 in einer ersten Ausführungsform von der Seite, sowie
Fig. 4b
eine Teilansicht der Plattform mit einem Zusatzbauteil gemäß Fig. 2 in einer zweiten Ausführungsform von der Seite.
It shows:
Fig. 1
1 is a partial perspective view of an embodiment of the turbine blade according to the invention with a platform without a graphical representation of an additional component for placing on the platform,
Fig. 2
a perspective view of the platform of Figure 1 in a highly simplified representation of a rotated approximately 90 ° viewing direction together with two arranged on respective end faces of the platform additional components,
Fig. 3
a partial view of the platform and an additional component according to FIG. 2 in longitudinal section,
Fig. 4a
a partial view of the platform with an additional component of FIG. 2 in a first embodiment of the side, as well
Fig. 4b
a partial view of the platform with an additional component of FIG. 2 in a second embodiment from the side.

In Fig. 1 ist ein Ausführungsbeispiel einer erfindungsgemäßen Turbinenschaufel 10 dargestellt, die sich im Wesentlichen entlang einer Längsachse 12 erstreckt. Im vorliegenden Fall ist die Turbinenschaufel als Leitschaufel ausgeführt. Es sei an dieser Stelle jedoch angemerkt, dass die Erfindung nicht lediglich auf eine Leitschaufel beschränkt ist, sondern etwa auch Laufschaufeln umfassen soll. Die Turbinenschaufel 10 umfasst ein sich entlang der Längsachse 12 erstreckendes und in Fig. 1 nur teilweises dargestelltes Schaufelblatt 14. An einem Ende des Schaufelblatts 14 schließt sich eine quer zur Längsachse 12 ausgerichtete Plattform 16 an. Die Plattform 16 dient dazu, bei in einer zugeordneten Turbine montierter Turbinenschaufel einen Strömungskanal in der Turbine mittels einer Hauptbegrenzungsfläche 30 der Plattform 16 zusammen mit Plattformen anderer Turbinenschaufeln zu begrenzen. An die Plattform 16 schließt sich nach unten hin eine Befestigungsstruktur 18 zum Befestigen der Turbinenschaufel an einem Gehäuse bzw. einem Leitschaufelring an. Im Fall einer Laufschaufel ist die Befestigungsstruktur 18 als Schaufelfuß zum Befestigen der Schaufel an einem Rotor der Turbine gestaltet.FIG. 1 shows an exemplary embodiment of a turbine blade 10 according to the invention which extends essentially along a longitudinal axis 12. In the present case, the turbine blade is designed as a guide vane. It should be noted at this point, however, that the invention is not limited to a vane, but should also include about blades. The turbine blade 10 comprises an airfoil 14 extending along the longitudinal axis 12 and only partially shown in FIG. 1. An end 16 of the airfoil 14 is adjoined by a platform 16 oriented transversely to the longitudinal axis 12. The platform 16 serves, with turbine blade mounted in an associated turbine, to use a flow channel in the turbine a main boundary surface 30 of the platform 16 together with platforms of other turbine blades to limit. Downstream of the platform 16 is a mounting structure 18 for attaching the turbine blade to a housing or vane ring. In the case of a blade, the attachment structure 18 is configured as a blade root for attaching the blade to a rotor of the turbine.

Innerhalb der Plattform 16 erstrecken sich mehrere Kühlmittelkanäle 20. Die Kühlmittelkanäle 20 sind im vorliegenden Fall geradlinig ausgebildet und verlaufen bei in der Turbine montierter Turbinenschaufel 10 quer zur Axialerstreckung des Rotors der Turbine. Die Kühlmittelkanäle münden an einer ersten Stirnfläche 32 und einer zweiten Stirnfläche 34 aus der Plattform 16 aus. Die beiden Stirnflächen 32 und 34 erstrecken sich im Wesentlichen senkrecht zur Hauptbegrenzungsfläche 30 und quer zu einer Axialerstreckung des Rotors im in der Turbine montierten Zustand der Turbinenschaufel 10.Within the platform 16 extend a plurality of coolant channels 20. The coolant channels 20 are formed in the present case rectilinear and run in the turbine-mounted turbine blade 10 transversely to the axial extent of the rotor of the turbine. The coolant channels lead out of the platform 16 at a first end face 32 and a second end face 34. The two end faces 32 and 34 extend substantially perpendicular to the main boundary surface 30 and transverse to an axial extent of the rotor in the turbine-mounted state of the turbine blade 10.

Wie aus Fig. 2 ersichtlich, ist an der ersten Stirnfläche 32 ein erstes Zusatzbauteil 24 und an der zweiten Stirnfläche 34 ein zweites Zusatzbauteil 26 befestigt. Die einzelnen Zusatzbauteile 24 und 26 weisen jeweils einen Verbindungskanal 28 zum Verbinden jeweils zweier Anschlussöffnungen 22 der zugehörigen Kühlmittelkanäle 20 auf. Zur Vereinfachung sind in den Fig. 2 und 3 lediglich zwei Kühlmittelkanäle 20 dargestellt, die von beiden Seiten her mittels der Zusatzbauteile 24 und 26 fluidleitend verbunden sind. Die Zusatzbauteile 24 und 26 können formschlüssig mit der Plattform 16 verbunden sein, wie in Fig. 4a dargestellt. Dies kann mittels einer Nut-/Stegverbindung geschehen, bei der die Nut im Querschnitt schwalbenschwanzförmig gestaltet ist. Alternativ können die Zusatzbauteile 24 und 26 auch stoffschlüssig mit der Plattform 16 verbunden sein, wie in Fig. 4b veranschaulicht. Dabei werden die entsprechenden Bauteile vorzugsweise mittels einer Löt- oder Schweißverbindung 36 aneinander befestigt.As can be seen from FIG. 2, a first additional component 24 is attached to the first end face 32 and a second additional component 26 is fastened to the second end face 34. The individual additional components 24 and 26 each have a connection channel 28 for connecting in each case two connection openings 22 of the associated coolant channels 20. For simplicity, only two coolant channels 20 are shown in Figs. 2 and 3, which are fluidly connected from both sides by means of the additional components 24 and 26. The additional components 24 and 26 may be positively connected to the platform 16, as shown in Fig. 4a. This can be done by means of a groove / web connection, in which the groove is designed dovetailed in cross section. Alternatively, the additional components 24 and 26 may also be materially connected to the platform 16, as illustrated in FIG. 4b. In this case, the corresponding components are preferably fastened to one another by means of a soldered or welded connection 36.

Claims (12)

Turbinenschaufel (10) für eine Turbine,
mit einer Plattform (16) zum teilweisen Begrenzen eines Strömungskanals in der Turbine,
wobei die Plattform (16) mindestens einen sich innerhalb der Plattform (16) erstreckenden Kühlmittelkanal (20) zum Führen eines Kühlmittels aufweist,
dadurch gekennzeichnet, dass
der mindestens eine Kühlmittelkanal (20) an mindestens zwei Anschlussöffnungen (22) aus der Plattform (16) ausmündet und die Turbinenschaufel (10) mindestens ein an der Plattform (16) befestigtes Zusatzbauteil (24, 26) mit einem Verbindungskanal (28) aufweist,
welcher darauf ausgelegt ist, die Anschlussöffnungen (22) fluidleitend miteinander zu verbinden.Turbine blade (10) for a turbine,
with a platform (16) for partially limiting a flow channel in the turbine,
wherein the platform (16) has at least one coolant channel (20) extending inside the platform (16) for guiding a coolant,
characterized in that
the at least one coolant channel (20) opens out of the platform (16) at at least two connection openings (22) and the turbine blade (10) has at least one additional component (24, 26) attached to the platform (16) with a connection channel (28),
which is designed to connect the connection openings (22) in a fluid-conducting manner with each other. Turbinenschaufel (10) nach Anspruch 1,
dadurch gekennzeichnet, dass
die einzelnen Kühlmittelkanäle (20) jeweils an einer ersten Anschlussöffnung (22) und einer zweiten Anschlussöffnung aus der Plattform ausmünden und
dass ein erstes Zusatzbauteil (24) und ein zweites Zusatzbauteil (26) zum jeweiligen fluidleitenden Verbinden der ersten Anschlussöffnungen (22) bzw. der zweiten Anschlussöffnungen vorgesehen sind.Turbine blade (10) according to claim 1,
characterized in that
the individual coolant channels (20) each open out of the platform at a first connection opening (22) and a second connection opening and
a first additional component (24) and a second additional component (26) are provided for the respective fluid-conducting connection of the first connection openings (22) or the second connection openings. Turbinenschaufel (10) nach Anspruch 1 oder 2,
dadurch gekennzeichnet, dass
die Turbinenschaufel (10) eine Längserstreckung (12) aufweist, bezüglich der sie radial zu einer Rotorachse der Turbine in der Turbine montierbar ist,
die Plattform (16) sich entlang einer Hauptbegrenzungsfläche (30) quer zur Längserstreckung (12) der Turbinenschaufel (10) erstreckt sowie quer zur Hauptbegrenzungsfläche (30) angeordnete Stirnflächen (32, 34) aufweist, und
die über das mindestens eine Zusatzbauteil (26) miteinander verbundenen Anschlussöffnungen (22) an einer der Stirnflächen (32, 34) angeordnet sind.Turbine blade (10) according to claim 1 or 2,
characterized in that
the turbine blade (10) has a longitudinal extent (12) with respect to which it can be mounted radially to a rotor axis of the turbine in the turbine,
the platform (16) extends transversely to the longitudinal extent (12) of the turbine blade (10) along a main boundary surface (30) and has end faces (32, 34) arranged transversely to the main boundary surface (30), and
the via the at least one additional component (26) interconnected terminal openings (22) on one of the end faces (32, 34) are arranged. Turbinenschaufel (10) nach einem der vorausgehenden Ansprüche,
dadurch gekennzeichnet, dass
das mindestens eine Zusatzbauteil (24, 26) stoffschlüssig und/oder formschlüssig mit der Plattform (16) verbunden ist.Turbine blade (10) according to one of the preceding claims,
characterized in that
the at least one additional component (24, 26) is connected in a material-locking and / or form-fitting manner to the platform (16). Turbinenschaufel (10) nach einem der vorausgehenden Ansprüche,
dadurch gekennzeichnet, dass
der Verbindungskanal (28) sich vollständig innerhalb des Zusatzbauteils (24, 26) erstreckt und insbesondere eine U-Form aufweist.Turbine blade (10) according to one of the preceding claims,
characterized in that
the connecting channel (28) extends completely within the additional component (24, 26) and in particular has a U-shape. Turbinenschaufel (10) nach einem der vorausgehenden Ansprüche,
dadurch gekennzeichnet, dass
die Plattform (16) und das Zusatzbauteil (24, 26) unterschiedliche Materialien aufweisen.Turbine blade (10) according to one of the preceding claims,
characterized in that
the platform (16) and the additional component (24, 26) have different materials. Turbinenschaufel (10) für eine Turbine, insbesondere nach einem der vorausgehenden Ansprüche,
mit einer Plattform (16) zum teilweisen Begrenzen eines Strömungskanals in der Turbine,
wobei die Plattform (16) mindestens einen sich innerhalb der Plattform (16) erstreckenden Kühlmittelkanal (20) zum Führen eines Kühlmittels aufweist,
dadurch gekennzeichnet, dass
die Plattform (16) ein Gussteil ist und der mindestens eine Kühlmittelkanal (20) einen beim Gießen der Plattform (16) ausgesparten Hohlraum umfasst.Turbine blade (10) for a turbine, in particular according to one of the preceding claims,
with a platform (16) for partially limiting a flow channel in the turbine,
wherein the platform (16) has at least one coolant channel (20) extending inside the platform (16) for guiding a coolant,
characterized in that
the platform (16) is a casting and the at least one coolant channel (20) comprises a cavity recessed when the platform (16) is cast. Turbinenschaufel (10) nach einem der vorausgehenden Ansprüche,
dadurch gekennzeichnet, dass
mindestens zwei Kühlmittelkanäle (20) vorgesehen sind, die an jeweils einer der mindestens zwei Anschlussöffnungen (22) aus der Plattform (16) ausmünden.Turbine blade (10) according to one of the preceding claims,
characterized in that
at least two coolant channels (20) are provided, which open out at each one of the at least two connection openings (22) from the platform (16). Turbinenschaufel (10) nach einem der vorausgehenden Ansprüche,
dadurch gekennzeichnet, dass
weitere Kühlkavitäten, insbesondere in der Oberfläche der Plattform (16) mündende Kühlbohrungen vorgesehen sind und der mindestens eine Kühlmittelkanal (20) als Kühlmittelversorgungskanal ausgebildet ist, der die weiteren Kühlkavitäten mit Kühlmittel versorgt.Turbine blade (10) according to one of the preceding claims,
characterized in that
further cooling cavities, in particular in the surface of the platform (16) opening cooling bores are provided and the at least one coolant channel (20) is designed as a coolant supply channel, which supplies the further cooling cavities with coolant. Turbinenschaufel (10) nach Anspruch 9,
dadurch gekennzeichnet, dass
die weiteren Kühlkavitäten nach dem Gießen der Plattform (16) mittels spanender Bearbeitung in die Plattform (16) eingebracht sind.Turbine blade (10) according to claim 9,
characterized in that
the further cooling cavities after the casting of the platform (16) are introduced by machining into the platform (16). Zusatzbauteil (24, 26) für eine Turbinenschaufel (10) einer Turbine,
insbesondere nach einem der vorausgehenden Ansprüche, welche Turbinenschaufel (10) eine Plattform (16) zum teilweisen Begrenzen eines Strömungskanals in der Turbine aufweist, die mindestens einen sich innerhalb der Plattform (16) erstreckenden Kühlmittelkanal (20) zum Führen eines Kühlmittels umfasst,
welcher Kühlmittelkanal (20) der Turbinenschaufel (10) an mindestens zwei Anschlussöffnungen (22) aus der Plattform (16) ausmündet,
dadurch gekennzeichnet, dass
das Zusatzbauteil (24, 26) zum Befestigen an der Plattform (16) gestaltet ist und einen Verbindungskanal (28) aufweist, welcher darauf ausgelegt ist, nach dem Befestigen an der Turbinenschaufel deren Anschlussöffnungen (22) fluidleitend miteinander zu verbinden.Additional component (24, 26) for a turbine blade (10) of a turbine,
more particularly according to one of the preceding claims, wherein the turbine blade (10) has a platform (16) for partially delimiting a flow channel in the turbine, which comprises at least one coolant channel (20) extending inside the platform (16) for guiding a coolant,
which coolant channel (20) of the turbine blade (10) opens out of the platform (16) at at least two connection openings (22),
characterized in that
the auxiliary component (24, 26) is designed to be fastened to the platform (16) and has a connecting channel (28) which is designed to connect the connection openings (22) in a fluid-conducting manner to one another after fastening to the turbine blade. Turbine für ein stationäres thermisches Kraftwerk mit einer Turbinenschaufel (10) nach einem der Ansprüche 1 bis 10.Turbine for a stationary thermal power plant with a turbine blade (10) according to one of claims 1 to 10.
EP06021677A 2006-10-16 2006-10-16 Turbine blade for a turbine with a cooling channel Not-in-force EP1914036B1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP06021677A EP1914036B1 (en) 2006-10-16 2006-10-16 Turbine blade for a turbine with a cooling channel
AT06021677T ATE459447T1 (en) 2006-10-16 2006-10-16 TURBINE BLADE FOR A TURBINE WITH A COOLANT CHANNEL
DE502006006344T DE502006006344D1 (en) 2006-10-16 2006-10-16 Turbine blade for a turbine with a coolant channel
JP2007266270A JP4510864B2 (en) 2006-10-16 2007-10-12 Turbine blade with coolant passage in turbine
US11/974,895 US8021118B2 (en) 2006-10-16 2007-10-16 Turbine blade for a turbine with a cooling medium passage

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP06021677A EP1914036B1 (en) 2006-10-16 2006-10-16 Turbine blade for a turbine with a cooling channel

Publications (2)

Publication Number Publication Date
EP1914036A1 true EP1914036A1 (en) 2008-04-23
EP1914036B1 EP1914036B1 (en) 2010-03-03

Family

ID=37885892

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06021677A Not-in-force EP1914036B1 (en) 2006-10-16 2006-10-16 Turbine blade for a turbine with a cooling channel

Country Status (5)

Country Link
US (1) US8021118B2 (en)
EP (1) EP1914036B1 (en)
JP (1) JP4510864B2 (en)
AT (1) ATE459447T1 (en)
DE (1) DE502006006344D1 (en)

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Also Published As

Publication number Publication date
JP2008095693A (en) 2008-04-24
US8021118B2 (en) 2011-09-20
DE502006006344D1 (en) 2010-04-15
JP4510864B2 (en) 2010-07-28
US20080240927A1 (en) 2008-10-02
EP1914036B1 (en) 2010-03-03
ATE459447T1 (en) 2010-03-15

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