EP1914036B1 - Turbine blade for a turbine with a cooling channel - Google Patents

Turbine blade for a turbine with a cooling channel Download PDF

Info

Publication number
EP1914036B1
EP1914036B1 EP06021677A EP06021677A EP1914036B1 EP 1914036 B1 EP1914036 B1 EP 1914036B1 EP 06021677 A EP06021677 A EP 06021677A EP 06021677 A EP06021677 A EP 06021677A EP 1914036 B1 EP1914036 B1 EP 1914036B1
Authority
EP
European Patent Office
Prior art keywords
platform
turbine blade
turbine
cooling medium
cooling
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
EP06021677A
Other languages
German (de)
French (fr)
Other versions
EP1914036A1 (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 DE502006006344T priority Critical patent/DE502006006344D1/en
Priority to EP06021677A priority patent/EP1914036B1/en
Priority to AT06021677T priority patent/ATE459447T1/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

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
    • F01D25/08—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.
  • a cast turbine blade which has encapsulated cooling channels inside the platform.
  • the cooling channels are partially formed as a closed cooling channels, partially carried out the discharge of the cooling air used for cooling by arranged in the platform outlet openings.
  • the cast cores needed to make the cooling channels are of complex structure, which makes their manufacturability difficult.
  • This object is achieved according to the invention with the turbine blade mentioned above, in which opens the at least one coolant channel at least two connection openings from the platform and which at least one attachable to the platform or attached additional component with a completely within the extending 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 connecting channel which is adapted to connect the connection openings in fluid conduction 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 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 coolant channel does not have to be retrofitted 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.
  • 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.
  • a turbine blade 10 which extends substantially 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 includes an extending along the longitudinal axis 12 and in Fig. 1 only partially illustrated airfoil 14. At one end of the airfoil 14, a transverse to the longitudinal axis 12 aligned platform 16 connects.
  • 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 attached 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 in Fig. 4a shown. 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 in Fig. 4b illustrated. In this case, the corresponding components are preferably fastened to one another by means of a soldered or welded connection 36.

Landscapes

  • 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.

Aus der US 2006/0056970 A1 ist eine gegossene Turbinenschaufel bekannt, die im Innern der Plattform eingegossene Kühlkanäle aufweist. Die Kühlkanäle sind dabei teilweise als geschlossene Kühlkanäle ausgebildet, teilweise erfolgt das Abführen der zur Kühlung eingesetzten Kühlluft durch in der Plattform angeordnete Austrittsöffnungen. Die zur Herstellung der Kühlkanäle benötigten Gusskerne sind dabei von komplexer Struktur, was Ihre Herstellbarkeit erschwert. Zudem ist deren Befestigung an weiteren Gusskernen, mittels denen die im Schaufelblattprofil angeordneten Hohlräume hergestellt werden, besonders aufwendig und fehlerträchtig.From the US 2006/0056970 A1 For example, a cast turbine blade is known which has encapsulated cooling channels inside the platform. The cooling channels are partially formed as a closed cooling channels, partially carried out the discharge of the cooling air used for cooling by arranged in the platform outlet openings. The cast cores needed to make the cooling channels are of complex structure, which makes their manufacturability difficult. In addition, their attachment to other casting cores, by means of which the arranged in the airfoil profile cavities are made, particularly complex and error prone.

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 sich vollständig innerhalb dessen erstreckenden 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 opens the at least one coolant channel at least two connection openings from the platform and which at least one attachable to the platform or attached additional component with a completely within the extending 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 connecting channel which is adapted to connect the connection openings in fluid conduction 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 weist der Verbindungskanal 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 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.

Der Kühlmittelkanal muss 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.The coolant channel does not have to be retrofitted 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 according to Fig. 1 in a highly simplified representation, from a viewing direction rotated by approximately 90 ° together with two additional components arranged on respective end faces of the platform,
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 according to Fig. 2 in a first embodiment of the page, as well
Fig. 4b
a partial view of the platform with an additional component according to 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.In Fig. 1 an embodiment of a turbine blade 10 according to the invention is shown, which extends substantially 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 includes an extending along the longitudinal axis 12 and in Fig. 1 only partially illustrated airfoil 14. At one end of the airfoil 14, a transverse to the longitudinal axis 12 aligned platform 16 connects. 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.How out Fig. 2 it can be seen, a first additional component 24 is attached to the first end face 32 and a second additional component 26 is attached 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, in the Fig. 2 and 3 only two coolant channels 20 are shown, 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 in Fig. 4a shown. 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 in Fig. 4b illustrated. In this case, the corresponding components are preferably fastened to one another by means of a soldered or welded connection 36.

Claims (11)

  1. Turbine blade (10) for a turbine,
    with a platform (16) for partial delimiting of a flow passage in the turbine,
    wherein the platform (16) has at least one cooling medium passage (20), which extends inside the platform (16), for guiding a cooling medium,
    characterized in that
    the at least one cooling medium passage (20) emerges from the platform (16) at at least two connecting openings (22), and the turbine blade (10) has at least one supplementary component (24, 26) which is fastened on the platform (16) and has a communicating passage (28) extending completely inside it,
    which is designed for interconnecting the connecting openings (22) in a fluid-guiding manner.
  2. Turbine blade (10) according to Claim 1,
    characterized in that
    the individual cooling medium passages (20) emerge in each case from the platform at a first connecting opening (22) and a second connecting opening and
    a first supplementary component (24) and a second supplementary component (26) are provided for respective fluid-guiding connecting of the first connecting openings (22) or of the second connecting openings.
  3. Turbine blade (10) according to Claim 1 or 2,
    characterized in that
    the turbine blade (10) has a longitudinal extent (12), with regard to which it can be installed in the turbine radially to a rotor axis of the turbine,
    the platform (16) extends along a main delimiting surface (30) transversely to the longitudinal extent (12) of the turbine blade (10), and also has end faces (32, 34) which are arranged transversely to the main delimiting surface (30), and
    the connecting openings (22), which are interconnected via the at least one supplementary component (26), are arranged on one of the end faces (32, 34).
  4. Turbine blade (10) according to one of the preceding claims,
    characterized in that
    the at least one supplementary component (24, 26) is connected to the platform (16) in a material-bonding and/or positive locking manner.
  5. Turbine blade (10) according to one of the preceding claims,
    characterized in that
    the communicating passage (28) has a U-shape.
  6. Turbine blade (10) according to one of the preceding claims,
    characterized in that
    the platform (16) and the supplementary component (24, 26) have different materials.
  7. Turbine blade (10) according to one of the preceding claims,
    characterized in that
    at least two cooling medium passages (20) are provided, which emerge from the platform (16) at one of the at least two connecting openings (22) in each case.
  8. Turbine blade (10) according to one of the preceding claims,
    characterized in that
    additional cooling cavities are provided, particularly cooling holes which lead to the surface of the platform (16), and the at least one cooling medium passage (20) is formed as a cooling medium supply passage which supplies the additional cooling cavities with cooling medium.
  9. Method for producing a turbine blade (10) according to Claim 8,
    characterized in that
    after casting of the platform (16), the additional cooling cavities are introduced into the platform (16) by means of a metal-cutting process.
  10. Supplementary component (24, 26) for a turbine blade (10) of a turbine,
    particularly according to one of the preceding claims,
    which turbine blade (10) has a platform (16) for partial delimiting of a flow passage in the turbine, which platform comprises at least one cooling medium passage (20), which extends inside the platform (16), for guiding a cooling medium,
    which cooling medium passage (20) of the turbine blade (10) emerges from the platform (16) at at least two connecting openings (22),
    characterized in that
    the supplementary component (24, 26) is designed for fastening on the platform (16) and has a communicating passage (28) extending completely inside it, which is designed for interconnecting its connecting openings (22) in a fluid-guiding manner after fastening on the turbine blade.
  11. 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
DE502006006344T DE502006006344D1 (en) 2006-10-16 2006-10-16 Turbine blade for a turbine with a coolant channel
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
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 EP1914036A1 (en) 2008-04-23
EP1914036B1 true 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)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2020097146A1 (en) * 2018-11-08 2020-05-14 General Electric Company Turbomachine blade tip attachment
US11203938B2 (en) 2018-11-08 2021-12-21 General Electric Company Airfoil coupon attachment

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8292587B2 (en) * 2008-12-18 2012-10-23 Honeywell International Inc. Turbine blade assemblies and methods of manufacturing the same
GB201016335D0 (en) 2010-09-29 2010-11-10 Rolls Royce Plc Endwall component for a turbine stage of a gas turbine engine
US8636470B2 (en) 2010-10-13 2014-01-28 Honeywell International Inc. Turbine blades and turbine rotor assemblies
US8632298B1 (en) * 2011-03-21 2014-01-21 Florida Turbine Technologies, Inc. Turbine vane with endwall cooling
EP2700789A4 (en) * 2011-04-19 2015-03-18 Mitsubishi Heavy Ind Ltd Turbine stator vane and gas turbine
US9719372B2 (en) * 2012-05-01 2017-08-01 General Electric Company Gas turbomachine including a counter-flow cooling system and method
US20150041590A1 (en) * 2013-08-09 2015-02-12 General Electric Company Airfoil with a trailing edge supplement structure
EP2886798B1 (en) 2013-12-20 2018-10-24 Rolls-Royce Corporation mechanically machined film cooling holes
US9982542B2 (en) * 2014-07-21 2018-05-29 United Technologies Corporation Airfoil platform impingement cooling holes
US10323520B2 (en) * 2017-06-13 2019-06-18 General Electric Company Platform cooling arrangement in a turbine rotor blade
US11130170B2 (en) * 2018-02-02 2021-09-28 General Electric Company Integrated casting core-shell structure for making cast component with novel cooling hole architecture
FR3094034B1 (en) * 2019-03-20 2021-03-19 Safran Aircraft Engines VENTILATION TUBULAR SHIRT FOR A TURBOMACHINE DISTRIBUTOR

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB612097A (en) * 1946-10-09 1948-11-08 English Electric Co Ltd Improvements in and relating to the cooling of gas turbine rotors
US5513955A (en) * 1994-12-14 1996-05-07 United Technologies Corporation Turbine engine rotor blade platform seal
FR2758855B1 (en) * 1997-01-30 1999-02-26 Snecma VENTILATION SYSTEM FOR MOBILE VANE PLATFORMS
FR2810365B1 (en) * 2000-06-15 2002-10-11 Snecma Moteurs SYSTEM FOR VENTILATION OF A PAIR OF JUXTAPOSED DAWN PLATFORMS
EP1489264A1 (en) * 2003-06-18 2004-12-22 Siemens Aktiengesellschaft Blade consisting of moduls
EP1557535A1 (en) * 2004-01-20 2005-07-27 Siemens Aktiengesellschaft Turbine blade and gas turbine with such a turbine blade
US7441331B2 (en) * 2004-08-26 2008-10-28 United Technologies Corporation Turbine engine component manufacture methods
US7147439B2 (en) 2004-09-15 2006-12-12 General Electric Company Apparatus and methods for cooling turbine bucket platforms
JP2006188962A (en) * 2004-12-28 2006-07-20 Mitsubishi Heavy Ind Ltd Cooling structure of gas turbine high temperature part

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2020097146A1 (en) * 2018-11-08 2020-05-14 General Electric Company Turbomachine blade tip attachment
US11143033B2 (en) 2018-11-08 2021-10-12 General Electric Company Turbomachine blade tip attachment
US11203938B2 (en) 2018-11-08 2021-12-21 General Electric Company Airfoil coupon attachment

Also Published As

Publication number Publication date
US20080240927A1 (en) 2008-10-02
JP4510864B2 (en) 2010-07-28
US8021118B2 (en) 2011-09-20
DE502006006344D1 (en) 2010-04-15
EP1914036A1 (en) 2008-04-23
JP2008095693A (en) 2008-04-24
ATE459447T1 (en) 2010-03-15

Similar Documents

Publication Publication Date Title
EP1914036B1 (en) Turbine blade for a turbine with a cooling channel
DE60018817T2 (en) Chilled gas turbine blade
DE112015006056B4 (en) TURBINE BLADE, TURBINE AND METHOD FOR MANUFACTURING A TURBINE BLADE
DE102007007090A1 (en) Gas turbine has cooling air transfer system with several tubular nozzles which are independently arranged in a circle inside a chamber, encompass the rotor and can discharge cooling air
WO2005068783A1 (en) Cooled blade for a gas turbine
DE112020000789B4 (en) HIGH TEMPERATURE COMPONENT AND METHOD FOR PRODUCING THE HIGH TEMPERATURE COMPONENT
EP1895096A1 (en) Cooled turbine rotor blade
EP2823152A1 (en) Turbine rotor blade and axial rotor blade section for a gas turbine
EP2788583B1 (en) Turbine vane with a throttling element
EP1905950A1 (en) Turbine blade
WO1996013668A1 (en) Radial compressor or radial turbine with a turbine nozzle ring or diffuser comprising guide vanes
EP3473808A1 (en) Blade for an internally cooled turbine blade and method for producing same
EP2489837A1 (en) Metering insert for turbine blade and corresponding turbine blade
EP3112593A1 (en) Internally cooled turbine blade
EP1219779B1 (en) Turbomachine component with inspection hole, and method for inspecting and cleaning such a component
EP2826956A1 (en) Rotor for a thermal flow engine
EP2163726A1 (en) Turbine blade with a modular, tiered trailing edge
EP3232001A1 (en) Rotor blade for a turbine
EP1138878B1 (en) Gas turbine component
EP2808558B1 (en) Structure assembly for a turbomachine
EP2598724B1 (en) Steam turbine and process for cooling such a steam turbine
EP1717416A1 (en) Turbine blade, use of the blade and manufacturing method thereof
EP3514333B1 (en) Rotor blade tip shroud for a turbo machine, rotor blade, method for producing a rotor blade cover strip and a rotor blade
DE19961565A1 (en) Coolant flow at a turbine paddle is adjusted by an inserted body into an opening in the coolant channel which reduces its cross section to give the required coolant flow vol
EP2476863A1 (en) Turbine blade for a gas turbine

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 HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK RS

17P Request for examination filed

Effective date: 20081007

AKX Designation fees paid

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR

17Q First examination report despatched

Effective date: 20090806

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

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 HU IE IS IT LI LT LU LV MC NL 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: NV

Representative=s name: SIEMENS SCHWEIZ AG

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

REF Corresponds to:

Ref document number: 502006006344

Country of ref document: DE

Date of ref document: 20100415

Kind code of ref document: P

REG Reference to a national code

Ref country code: NL

Ref legal event code: VDEP

Effective date: 20100303

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

Ref country code: LT

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

Effective date: 20100303

LTIE Lt: invalidation of european patent or patent extension

Effective date: 20100303

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: 20100303

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: 20100303

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: 20100303

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: 20100303

REG Reference to a national code

Ref country code: IE

Ref legal event code: FD4D

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

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: 20100303

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: 20100614

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: 20100604

Ref country code: IE

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: 20100303

Ref country code: NL

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

Effective date: 20100303

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: 20100303

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: 20100303

Ref country code: RO

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

Effective date: 20100303

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

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: 20100703

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: 20100603

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: 20100303

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: 20100303

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: 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: 20100705

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: 20100303

26N No opposition filed

Effective date: 20101206

BERE Be: lapsed

Owner name: SIEMENS A.G.

Effective date: 20101031

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

Ref country code: MC

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

Effective date: 20101031

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: 20101031

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 NON-PAYMENT OF DUE FEES

Effective date: 20101016

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

Effective date: 20100904

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: 20100303

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 459447

Country of ref document: AT

Kind code of ref document: T

Effective date: 20111016

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: 20111016

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 10

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

Ref country code: GB

Payment date: 20151005

Year of fee payment: 10

Ref country code: IT

Payment date: 20151027

Year of fee payment: 10

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

Ref country code: FR

Payment date: 20151016

Year of fee payment: 10

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

Ref country code: DE

Payment date: 20151218

Year of fee payment: 10

Ref country code: CH

Payment date: 20160112

Year of fee payment: 10

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502006006344

Country of ref document: DE

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

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

Effective date: 20161016

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20170630

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

Ref country code: FR

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

Effective date: 20161102

Ref country code: LI

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

Effective date: 20161031

Ref country code: DE

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

Effective date: 20170503

Ref country code: GB

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

Effective date: 20161016

Ref country code: CH

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

Effective date: 20161031

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

Ref country code: IT

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

Effective date: 20161016