EP1766192B1 - Vane wheel of a turbine comprising a vane and at least one cooling channel - Google Patents

Vane wheel of a turbine comprising a vane and at least one cooling channel Download PDF

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Publication number
EP1766192B1
EP1766192B1 EP05766734A EP05766734A EP1766192B1 EP 1766192 B1 EP1766192 B1 EP 1766192B1 EP 05766734 A EP05766734 A EP 05766734A EP 05766734 A EP05766734 A EP 05766734A EP 1766192 B1 EP1766192 B1 EP 1766192B1
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EP
European Patent Office
Prior art keywords
vane
turbulators
platform
blade
cooling 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.)
Active
Application number
EP05766734A
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German (de)
French (fr)
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EP1766192A1 (en
Inventor
Hans-Thomas Bolms
Andreas Heselhaus
Roland Häbel
Torsten Koch
Ralf Müsgen
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Siemens AG
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Siemens AG
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Publication date
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Priority to PL05766734T priority Critical patent/PL1766192T3/en
Priority to EP05766734A priority patent/EP1766192B1/en
Publication of EP1766192A1 publication Critical patent/EP1766192A1/en
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Publication of EP1766192B1 publication Critical patent/EP1766192B1/en
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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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the 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
    • F05D2230/12—Manufacture by removing material by spark erosion methods
    • 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
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/127—Vortex generators, turbulators, or the like, for mixing
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/29—Three-dimensional machined; miscellaneous
    • F05D2250/291—Three-dimensional machined; miscellaneous hollowed
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2212—Improvement of heat transfer by creating turbulence
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs

Definitions

  • the invention relates to a blade wheel of a turbine with a blade whose blade root is supported on a wheel disc, and in which there is at least one cooling channel between the wheel disc of the turbine and the blade root. Furthermore, the invention relates to a blade of such a paddle wheel.
  • Paddle wheels of the type mentioned are used, for example, in stationary gas turbines as blade wheels, which are arranged in the flow direction of fuel gas behind a combustion chamber of the gas turbine and exposed there to high temperatures.
  • the cooling of the blades and in particular the blade roots of such high-temperature loaded gas turbine blades is particularly complicated due to the required complex cooling fluid management and difficult seals at the same time high centrifugal force.
  • convective cooling and other measures are currently being used to enhance the heat transfer between a cooling fluid flowing through cooling channels on the blade root and the blade root. Often, only a comparatively small amount of cooling fluid is available, so that only a small heat flow can be dissipated through a platform of the blade root. Thus, the platform surface temperature can only be lowered slightly.
  • the platform extends from an upstream edge to a downstream edge with respect to the hot gas flowing through the gas turbine in the axial direction.
  • the platform has a downstream, in Circumferential direction of the turbine disk extending downstream edge, which projects beyond the axial width of the turbine disk in the manner of a eaves addition.
  • the cooling air flow influencing structural elements are provided at the bottom of the downstream edge of the platform several. Guide vanes that rapidly rotate with the rotor move over the more or less stationary cooling air and cause a flow deflection of the cooling air from the circumferential direction in the axial direction.
  • both a turbulator-like local base panel and axially extending ribs are provided at the bottom of the platform.
  • the base panel and the ribs locally increase the heat transfer from the downstream edge of the platform into the cooling air bypassing on the underside.
  • the invention has for its object to provide a paddle wheel according to claim 1 for a turbine with a blade, achieved at the blade root or blade platform increased cooling and a relatively high heat flow can be dissipated. It is another object of the invention to provide a manufacturing method for such a blade.
  • This first object is inventively achieved in that a plurality of turbulators is formed on at least one of the walls of the cooling channel of a paddle wheel according to the invention, which are designed such that they increase the turbulence of a cooling fluid flowing through the cooling channel.
  • the cooling fluid does not flow along more or less smooth walls in the cooling channel extending between the outer periphery of the wheel disc and the underside of the platform of the blade in the at least one cooling channel extending axially or in the main flow direction of a hot gas but it is specifically provided a plurality of turbulators or turbulence elements, which are formed on at least one of the walls of the cooling channel and increase the turbulence of the cooling fluid within the cooling passage.
  • turbulators With these turbulators, the heat transfer between the swirling cooling fluid and all walls, but especially the turbulators associated wall of the cooling channel is increased and thereby cooled the blade root reinforced.
  • the turbulators or turbulence elements are adapted in accordance with the desired heat transfer, so that targeted a maximum hot gas side material temperature and the cooling fluid flow through the cooling channel can be dimensioned accordingly to the associated blade.
  • turbulators ribs or nipples or dimples can be used.
  • the plurality of turbulators is advantageously formed on the underside of a platform of the blade root.
  • the plurality of turbulators is advantageously designed in the form of pockets, which are formed in the at least one wall of the cooling channel forming material. Such pockets can also be subsequently formed in existing blades and thus the invention desired enlargement of the heat transfer at the blade root can be achieved.
  • the turbulators or pockets are also advantageously aligned in each case substantially transversely or obliquely to the flow direction of the cooling fluid flowing through the cooling channel. Such turbulators lead to a particularly strong turbulence of cooling fluid flowing in the cooling channel.
  • a particularly good and uniform cooling of the platform can be achieved if the turbulators are aligned obliquely to the flow direction of the cooling fluid flowing through the cooling channel, that they deflect the flowing cooling fluid in the direction of a neck of the blade root.
  • the flow through the cross-section usually wedge-shaped or triangular cooling channel can be selectively adjusted.
  • the number of turbulators or pockets provided per unit area should be increased in comparison to areas of lower heat load in such areas of increased heat load.
  • the blade root of at least one blade should also advantageously be designed with a platform on each of which a cooling channel is located along an elongated neck of the blade root and the plurality of turbulators in the form of a cooling channel on the underside of the platform extending series is designed.
  • paddle wheels can be upgraded without much structural change for use at higher temperatures.
  • the turbulators according to the invention can also be formed in an operation forming the blade and in particular its blade, so that almost no additional effort is required for its production.
  • the turbulators can be formed in a separate operation after at least one operation forming the blade and in particular its blade.
  • paddle wheels of existing turbines in According to the invention be retrofitted with turbulators or pockets, which lead to the above-described improved heat transfer at the blade root.
  • a blade for a blade wheel of a turbine in particular a gas turbine, which is provided with a flowable by a hot gas blade and a blade root having a platform, which, based on the main flow direction of the hot gas, extending from an upstream edge to a downstream edge along a platform longitudinal edge and at which a neck and farther away teeth are disposed on a lower side of the airfoil, and at the side remote from the airfoil bottom of the platform laterally of the neck along the Platform longitudinal edge a plurality of turbulators are formed, which are designed such that they increase the turbulence of a flowing along the bottom cooling fluid in the installed state of the blade.
  • the plurality of turbulators on such a bucket should be in the form of pockets formed in the material of the platform.
  • the turbulators are formed in a the blade forming operation with.
  • the turbulators are thus mitgeformt directly in the re-production of the blade.
  • an existing and used blade can be retrofitted during an inspection incident of the gas turbine with the turbulators by this in a separate operation after at least one Shovel sheet forming operation are formed. In this way, the service life of the blade can be further increased while saving of cooling air, which also has a positive effect on the efficiency of the gas turbine.
  • FIG. 1 a blade 10 is illustrated according to the prior art, which has a blade root 12 and an adjoining blade 14.
  • the blade root 12 is designed as a fir tree root with a platform 16 on which a neck 18 and farther away teeth 20 are arranged on the side opposite the blade blade 14.
  • the platform 16, the neck 18 and the teeth 20 are designed as an elongated profile, which is arranged with a built-in blade 10 in a groove (not shown) of a wheel disc 22 of a turbine rotor and there is provided for holding the blade 14 and for receiving in particular its centrifugal forces ,
  • Such an installation position of a blade 10 on a wheel disc 22 is basically in FIG. 3 illustrated.
  • the neck 18 and the teeth 20 facing bottom of the Platform 16 provided with a substantially smooth surface.
  • the bottom 24 is, however, designed with a plurality of turbulators 26, which may each be arranged in a row on both sides of the neck 18.
  • the turbulators 26 face a cooling channel 28 extending in the main flow direction of a hot gas, which is provided between the underside 24 of the platform 16 and the outer periphery of the wheel disc 22.
  • the cooling channel 28 extends along a platform longitudinal edge, which extends from an upstream edge of the platform 16 to a downstream edge, with respect to the main flow direction of the hot gas flowing through the gas turbine during operation.
  • the cooling channel 28 flows through a cooling fluid, not shown, in a flow direction 30.
  • the turbulators 26 are arranged only along the platform longitudinal edge and with respect to this flow of the cooling fluid transversely or obliquely to the flow direction 30 designed as pockets which are formed in the material of the platform 16, and to the underside 24 each having an opening. In these pockets there is an additional turbulence of the cooling fluid flowing through the cooling channel 28 and thus to an improved heat transfer from the platform 16 into the cooling fluid. Thus, the pockets lead to increased heat dissipation and improved cooling of the blade root 12 and the platform 16.
  • the airfoil 14 has a pressure-side wall 27.
  • the embodiment with turbulators 26 arranged on the underside leads to advantages. If one of the two platform longitudinal edges, for example, the pressure side platform side relative to the airfoil 14 in the circumferential direction of the wheel disc 22 further protrudes than the other of the example is the suction side platform side, it is sufficient that only on the pressure side platform longitudinal edge on the Bottom 24 turbulators 26 are provided as in FIG. 3 shown, which swirl the cooling fluid in the cooling channel 28 and thus also allow for the suction-side platform longitudinal edge 29b of the immediately adjacent turbine blade 10 of the impeller a sufficiently high heat transfer in relation to the prior art.
  • the pockets of the turbulators 26 may, for example, be anodized into the material of the platform 16 and advantageously have a length which corresponds approximately to two to seven times, in particular three to five times, particularly advantageously four times the width of a pocket.
  • the turbulators 26 may also be designed in the form of nipples or dimples on the underside 24 of the platform 16. With such turbulators 26 slots or webs are respectively formed on the underside 24, which represent partial flow resistance for the flowing through the cooling channel 28 cooling fluid and thus lead to turbulence within the cooling fluid.
  • the turbulators 26 are preferably oriented obliquely to the flow of cooling fluid so as to divert the cooling fluid from a gap formed by two endwise opposed platforms 16 of adjacent turbine blades 10.
  • the cooling fluid from the turbulators 26 is also guided against the neck 18 of the blade root 12.
  • FIG. 3 is shown below the platform 16 existing cross-section of the cooling channel 28th wedge-shaped, ie from the platform edge, the radial height of the cross-section decreases towards the neck 18 of the blade root 12.
  • the cooling fluid would flow without such inclined turbulators 26 due to the locally lower flow resistance increasingly in the larger cross-sectional area than in the neck close, smaller cross-sectional area.
  • additional material may be deposited on the underside 24 of the platform 16 for the turbulators 26 by build-up welding. This additional material is then at least partially removed in a subsequent step by suitable methods, so as to form the turbulators 26.
  • a prefabricated, separate module with turbulators 26 in a separate operation from the (cast) production of the turbine blade can also be inexpensively fastened by positive and / or positive connection.
  • Prefabricated modules can be retrofitted for inspection work in a time-saving manner.
  • the turbulator module may for example have the same longitudinal extent as the platform longitudinal edge and, equipped with a tongue and groove configuration, frontally into the platform 16 in one along the Bottom 24 extending corresponding recess be inserted to be subsequently fixed by welding or soldering.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Superconductors And Manufacturing Methods Therefor (AREA)
  • Transition And Organic Metals Composition Catalysts For Addition Polymerization (AREA)

Abstract

The blade wheel of a turbine has at least one blade with its root (12) mounted on a disc, and at least one cooling passage is located between the wheel disc and blade root. A number of turbulators (26) is formed on at least one of the walls of the cooling passage and are designed in such a way that they increase the turbulence of a cooling fluid flowing through the cooling passage. The turbulators are formed on the underside (24) of the blade root platform (16). Independent claims are also included for the following: (A) a blade of a blade wheel of a turbine, especially a gas turbine, with turbulators on the underside of the blade root platform; and (B) a method for the manufacturing of a blade in which the turbulators can be formed in a working process forming the blade aerofoil.

Description

Die Erfindung betrifft ein Schaufelrad einer Turbine mit einer Schaufel, deren Schaufelfuß an einer Radscheibe gehaltert ist, und bei der sich zwischen der Radscheibe der Turbine und dem Schaufelfuß mindestens ein Kühlkanal befindet. Ferner betrifft die Erfindung eine Schaufel eines derartigen Schaufelrades.The invention relates to a blade wheel of a turbine with a blade whose blade root is supported on a wheel disc, and in which there is at least one cooling channel between the wheel disc of the turbine and the blade root. Furthermore, the invention relates to a blade of such a paddle wheel.

Schaufelräder der eingangs genannten Art werden beispielsweise bei stationären Gasturbinen als Laufschaufelräder verwendet, welche in Strömungsrichtung von Brenngas hinter einer Brennkammer der Gasturbine angeordnet und dort hohen Temperaturen ausgesetzt sind. Die Kühlung der Schaufelblätter und insbesondere der Schaufelfüße von solchen hochtemperaturbelasteten Gasturbinenschaufeln ist in Folge der dazu erforderlichen komplizierten Kühlfluidführung und schwierigen Abdichtungen bei zugleich hoher Fliehkraftbelastung besonders aufwendig. Bei Turbinenlaufschaufeln wird derzeit mit konvektiver Kühlung und anderen Maßnahmen zur Verstärkung des Wärmeübergangs zwischen einem durch Kühlkanäle am Schaufelfuß strömenden Kühlfluid und dem Schaufelfuß gearbeitet. Oftmals steht nur eine vergleichsweise geringe Menge Kühlfluid zur Verfügung, so dass nur ein geringer Wärmestrom durch eine Plattform des Schaufelfußes abgeführt werden kann. Damit kann die Plattformoberflächentemperatur nur geringfügig abgesenkt werden.Paddle wheels of the type mentioned are used, for example, in stationary gas turbines as blade wheels, which are arranged in the flow direction of fuel gas behind a combustion chamber of the gas turbine and exposed there to high temperatures. The cooling of the blades and in particular the blade roots of such high-temperature loaded gas turbine blades is particularly complicated due to the required complex cooling fluid management and difficult seals at the same time high centrifugal force. In turbine blades, convective cooling and other measures are currently being used to enhance the heat transfer between a cooling fluid flowing through cooling channels on the blade root and the blade root. Often, only a comparatively small amount of cooling fluid is available, so that only a small heat flow can be dissipated through a platform of the blade root. Thus, the platform surface temperature can only be lowered slightly.

Dazu ist aus der US 2004/0081556 A1 eine Gasturbinenschaufel mit einem Schaufelfuß, einer Plattform und einem Schaufelblatt bekannt. Die Plattform erstreckt sich von einer anströmseitigen Kante zu einer abströmseitigen Kante, bezogen auf das Heißgas, welches die Gasturbine in Axialrichtung durchströmt. Die Plattform weist eine abströmseitige, in Umfangsrichtung der Turbinenscheibe verlaufende abströmseitige Kante auf, welche über die axiale Breite der Turbinenscheibe nach Art einer Traufe hinaus ragt. An der Unterseite der abströmseitigen Kante der Plattform sind mehrere, die Kühlluftströmung beeinflussende Strukturelemente vorgesehen. Sich mit dem Rotor schnell mitdrehende Leitrippen bewegen sich über die mehr oder minder stehende Kühlluft hinweg und bewirken eine Strömungsumlenkung der Kühlluft von Umfangsrichtung in Axialrichtung. Außerdem ist an der Unterseite der Plattform sowohl ein turbulatorartiges lokales Sockelfeld sowie sich in Axialrichtung erstreckende Rippen vorgesehen. Das Sockelfeld und die Rippen erhöhen lokal den Wärmeübergang von der abströmseitigen Kante der Plattform in die unterseitig vorbeiströmende Kühlluft.This is from the US 2004/0081556 A1 a gas turbine blade with a blade root, a platform and an airfoil known. The platform extends from an upstream edge to a downstream edge with respect to the hot gas flowing through the gas turbine in the axial direction. The platform has a downstream, in Circumferential direction of the turbine disk extending downstream edge, which projects beyond the axial width of the turbine disk in the manner of a eaves addition. At the bottom of the downstream edge of the platform several, the cooling air flow influencing structural elements are provided. Guide vanes that rapidly rotate with the rotor move over the more or less stationary cooling air and cause a flow deflection of the cooling air from the circumferential direction in the axial direction. In addition, at the bottom of the platform, both a turbulator-like local base panel and axially extending ribs are provided. The base panel and the ribs locally increase the heat transfer from the downstream edge of the platform into the cooling air bypassing on the underside.

Der Erfindung liegt die Aufgabe zugrunde, ein Schaufelrad gemäss Anspruch 1 für eine Turbine mit einer Schaufel bereitzustellen, an deren Schaufelfuß bzw. Schaufelplattform eine verstärke Kühlung erzielt und ein vergleichsweise hoher Wärmestrom abgeführt werden kann. Ferner ist es Aufgabe der Erfindung, ein Herstellungsverfahren für eine solche Schaufel anzugeben. Diese erstgenannte Aufgabe ist erfindungsgemäß dadurch gelöst, dass an mindestens einer der Wände des Kühlkanals eines erfindungsgemäßen Schaufelrades eine Vielzahl Turbulatoren ausgebildet ist, die derart gestaltet sind, dass sie die Turbulenz eines durch den Kühlkanal strömenden Kühlfluids erhöhen.The invention has for its object to provide a paddle wheel according to claim 1 for a turbine with a blade, achieved at the blade root or blade platform increased cooling and a relatively high heat flow can be dissipated. It is another object of the invention to provide a manufacturing method for such a blade. This first object is inventively achieved in that a plurality of turbulators is formed on at least one of the walls of the cooling channel of a paddle wheel according to the invention, which are designed such that they increase the turbulence of a cooling fluid flowing through the cooling channel.

Im Vergleich zu bekannten Kühlkonfigurationen an Schaufelfüßen bzw. Schaufelplattformen von Turbinenlaufschaufeln strömt erfindungsgemäß in dem mindestens einen sich axial bzw. in Hauptströmungsrichtung eines Heißgases erstreckenden Kühlkanal zwischen dem Außenumfang der Radscheibe und der Unterseite der Plattform der Schaufel das Kühlfluid nicht entlang von mehr oder weniger glatten Wänden, sondern es ist gezielt eine Vielzahl Turbulatoren oder Turbulenzelementen vorgesehen, die an mindestens einer der Wände des Kühlkanals ausgebildet sind und die Turbulenz des Kühlfluids innerhalb des Kühlkanals erhöhen. Mit diesen Turbulatoren wird der Wärmeübergang zwischen dem verwirbelten Kühlfluid und allen Wänden, insbesondere aber der den Turbulatoren zugehörigen Wand des Kühlkanals erhöht und der Schaufelfuß dadurch verstärkt gekühlt. Die Turbulatoren bzw. Turbulenzelemente sind entsprechend dem angestrebten Wärmeübergang angepasst, so dass an der zugehörigen Schaufel gezielt eine maximale heißgasseitige Materialtemperatur vorbestimmt und der Kühlfluidstrom durch den Kühlkanal entsprechend dimensioniert werden kann.Compared to known cooling configurations on blade roots or blade platforms of turbine blades, the cooling fluid does not flow along more or less smooth walls in the cooling channel extending between the outer periphery of the wheel disc and the underside of the platform of the blade in the at least one cooling channel extending axially or in the main flow direction of a hot gas but it is specifically provided a plurality of turbulators or turbulence elements, which are formed on at least one of the walls of the cooling channel and increase the turbulence of the cooling fluid within the cooling passage. With these turbulators, the heat transfer between the swirling cooling fluid and all walls, but especially the turbulators associated wall of the cooling channel is increased and thereby cooled the blade root reinforced. The turbulators or turbulence elements are adapted in accordance with the desired heat transfer, so that targeted a maximum hot gas side material temperature and the cooling fluid flow through the cooling channel can be dimensioned accordingly to the associated blade.

Als Turbulatoren können Rippen bzw. Nippel oder Dimpel zur Anwendung kommen.As turbulators ribs or nipples or dimples can be used.

Bei einer vorteilhaften Weiterbildung des erfindungsgemäßen Schaufelrades ist die Vielzahl Turbulatoren vorteilhaft an der Unterseite einer Plattform des Schaufelfußes ausgebildet. Durch den Einsatz von Turbulatoren bzw. Turbulenzelementen an der Plattformunterseite, welche die Turbulenz im Spalt zwischen Schaufelfuß und dem Scheibenkopf der Radscheibe vergrößern, wird der Wärmestrom in der Plattformwand vergrößert und die Plattformoberflächentemperatur abgesenkt.In an advantageous embodiment of the impeller according to the invention, the plurality of turbulators is advantageously formed on the underside of a platform of the blade root. Through the use of turbulators or turbulence elements on the platform underside, which increase the turbulence in the gap between the blade root and the disk head of the wheel disk, the heat flow in the platform wall is increased and the platform surface temperature is lowered.

Die Vielzahl Turbulatoren ist vorteilhaft in Form von Taschen gestaltet, welche in dem die mindestens eine Wand des Kühlkanals bildenden Material ausgeformt sind. Solche Taschen können auch nachträglich in bereits bestehenden Schaufeln ausgebildet und damit die erfindungsgemäß gewünschte Vergrößerung des Wärmeübergangs am Schaufelfuß erzielt werden.The plurality of turbulators is advantageously designed in the form of pockets, which are formed in the at least one wall of the cooling channel forming material. Such pockets can also be subsequently formed in existing blades and thus the invention desired enlargement of the heat transfer at the blade root can be achieved.

Die Turbulatoren bzw. Taschen sind ferner vorteilhaft jeweils im Wesentlichen quer oder schräg zur Strömungsrichtung des durch den Kühlkanal strömenden Kühlfluids ausgerichtet. Derartige Turbulatoren führen zu einer besonders starken Verwirbelung von im Kühlkanal strömendem Kühlfluid.The turbulators or pockets are also advantageously aligned in each case substantially transversely or obliquely to the flow direction of the cooling fluid flowing through the cooling channel. Such turbulators lead to a particularly strong turbulence of cooling fluid flowing in the cooling channel.

Eine besonders gute und gleichmäßige Kühlung der Plattform kann erreicht werden, wenn die Turbulatoren derart schräg zur Strömungsrichtung des durch den Kühlkanal strömenden Kühlfluids ausgerichtet sind, dass sie das strömende Kühlfluid in Richtung eines Halses des Schaufelfußes umlenken. Damit kann die Durchströmung des im Querschnitt meist keilförmige oder dreieckige Kühlkanals gezielt angepasst werden.A particularly good and uniform cooling of the platform can be achieved if the turbulators are aligned obliquely to the flow direction of the cooling fluid flowing through the cooling channel, that they deflect the flowing cooling fluid in the direction of a neck of the blade root. Thus, the flow through the cross-section usually wedge-shaped or triangular cooling channel can be selectively adjusted.

Damit an besonders zu kühlenden Bereichen des Schaufelrades mit erhöhter Wärmebelastung die erfindungsgemäß verstärkte Kühlung benutzt werden kann, sollte in solchen Bereichen erhöhter Wärmebelastung die Anzahl der pro Flächeneinheit vorgesehenen Turbulatoren bzw. Taschen im Vergleich zu Bereichen geringerer Wärmebelastung erhöht sein.In order to be able to use the cooling according to the invention, which is particularly advantageous for cooling of the blade wheel with increased heat load, the number of turbulators or pockets provided per unit area should be increased in comparison to areas of lower heat load in such areas of increased heat load.

Bei dem erfindungsgemäßen Schaufelrad sollte ferner vorteilhaft der Schaufelfuß mindestens einer Schaufel mit einer Plattform gestaltet sein, an der sich entlang eines lang gestreckten Halses des Schaufelfußes beidseitig jeweils ein Kühlkanal befindet und die Vielzahl Turbulatoren in Form einer sich in dem zugehörigen Kühlkanal an der Unterseite der Plattform erstreckenden Reihe gestaltet ist. Mit derartigen Turbulatoren an der Unterseite der Plattform können Schaufeln erfindungsgemäßer Schaufelräder ohne große bauliche Veränderung für einen Einsatz bei höheren Temperaturen ertüchtigt werden.In the paddle wheel according to the invention, the blade root of at least one blade should also advantageously be designed with a platform on each of which a cooling channel is located along an elongated neck of the blade root and the plurality of turbulators in the form of a cooling channel on the underside of the platform extending series is designed. With such turbulators at the bottom of the platform blades of the invention paddle wheels can be upgraded without much structural change for use at higher temperatures.

Die erfindungsgemäßen Turbulatoren können in einem die Schaufel und insbesondere deren Schaufelblatt ausbildenden Arbeitsgang mit ausgeformt werden, so dass für ihre Herstellung nahezu kein Zusatzaufwand entsteht.The turbulators according to the invention can also be formed in an operation forming the blade and in particular its blade, so that almost no additional effort is required for its production.

Alternativ oder zusätzlich können die Turbulatoren in einem separaten Arbeitsgang nach mindestens einem die Schaufel und insbesondere deren Schaufelblatt ausbildenden Arbeitsgang ausgeformt werden. Mit dieser Vorgehensweise können insbesondere Schaufelräder von bestehenden Turbinen in erfindungsgemäßer Weise mit Turbulatoren bzw. Taschen nachgerüstet werden, welche zu dem oben erläuterten verbesserten Wärmeübergang am Schaufelfuß führen.Alternatively or additionally, the turbulators can be formed in a separate operation after at least one operation forming the blade and in particular its blade. With this procedure, in particular paddle wheels of existing turbines in According to the invention be retrofitted with turbulators or pockets, which lead to the above-described improved heat transfer at the blade root.

Die Aufgabe der Erfindung ist ferner mit einer Schaufel für ein Schaufelrad einer Turbine gemäss Anspruch 10, insbesondere einer Gasturbine, gelöst, die mit einem von einem Heißgas umströmbaren Schaufelblatt und einem Schaufelfuß versehen ist, der eine Plattform aufweist, welche sich, bezogen auf die Hauptströmungsrichtung des Heißgases, von einer anströmseitigen Kante zu einer abströmseitigen Kante entlang einer Plattformlängskante erstreckt und an welcher an einer dem Schaufelblatt gegenüberliegenden Unterseite ein Hals und weiter entfernt Zähne angeordnet sind, und bei der an der von dem Schaufelblatt abgewandten Unterseite der Plattform seitlich des Halses entlang der Plattformlängskante eine Vielzahl Turbulatoren ausgebildet sind, die derart gestaltet sind, dass sie im eingebauten Zustand der Schaufel die Turbulenz eines entlang der Unterseite strömenden Kühlfluids erhöhen.The object of the invention is further achieved with a blade for a blade wheel of a turbine according to claim 10, in particular a gas turbine, which is provided with a flowable by a hot gas blade and a blade root having a platform, which, based on the main flow direction of the hot gas, extending from an upstream edge to a downstream edge along a platform longitudinal edge and at which a neck and farther away teeth are disposed on a lower side of the airfoil, and at the side remote from the airfoil bottom of the platform laterally of the neck along the Platform longitudinal edge a plurality of turbulators are formed, which are designed such that they increase the turbulence of a flowing along the bottom cooling fluid in the installed state of the blade.

Wie oben erläutert wird an einer derartigen erfindungsgemäßen Schaufel eine verbesserte Wärmeabfuhr und Kühlung im Bereich des zugehörigen Schaufelfußes erreicht, wodurch sich, nahezu ohne Kostenaufwand, ein gesteigerter Verkaufswert der Maschinen ergibt.As explained above, improved heat dissipation and cooling in the region of the associated blade root is achieved on such a blade according to the invention, resulting in an increased sales value of the machines, at almost no cost.

Wie ebenfalls bereits erwähnt, sollte die Vielzahl Turbulatoren an einer derartigen Schaufel in Form von Taschen gestaltet sein, welche in dem Material der Plattform ausgeformt sind.As also noted above, the plurality of turbulators on such a bucket should be in the form of pockets formed in the material of the platform.

Zur Lösung der auf das Verfahren gerichteten Aufgabe werden die Turbulatoren in einem das Schaufelblatt ausbildenden Arbeitsgang mit ausgeformt. Die Turbulatoren werden somit unmittelbar bei der Neu-Herstellung der Schaufel mitgeformt. Alternativ kann eine bereits bestehende und eingesetzte Schaufel während eines Inspektionsinterfalls der Gasturbine mit den Turbulatoren nachgerüstet werden, indem diese in einem separaten Arbeitsgang nach mindestens einem das Schaufelblatt ausbildenden Arbeitsgang ausgeformt werden. Hierdurch kann die Standzeit der Schaufel weiter erhöht werden bei gleichzeitiger Einsparung von Kühlluft, welches sich darüber hinaus positiv auf den Wirkungsgrad der Gasturbine auswirkt.To solve the task directed to the process, the turbulators are formed in a the blade forming operation with. The turbulators are thus mitgeformt directly in the re-production of the blade. Alternatively, an existing and used blade can be retrofitted during an inspection incident of the gas turbine with the turbulators by this in a separate operation after at least one Shovel sheet forming operation are formed. In this way, the service life of the blade can be further increased while saving of cooling air, which also has a positive effect on the efficiency of the gas turbine.

Nachfolgend wird ein Ausführungsbeispiel eines erfindungsgemäßen Schaufelrades anhand der beigefügten schematischen Zeichnungen näher erläutert.An exemplary embodiment of a paddle wheel according to the invention is explained in more detail below with reference to the attached schematic drawings.

Es zeigt:

FIG 1
eine perspektivische .Ansicht eines Schaufelfußes einer Schaufel einer Turbine gemäß dem Stand der Technik,
FIG 2
eine perspektivische Ansicht eines Schaufelfußes einer erfindungsgemäßen Schaufel einer Turbine und
FIG 3
eine perspektivische Ansicht der Einbausituation eines Schaufelfußes gemäß Fig. 2.
It shows:
FIG. 1
3 is a perspective view of a blade root of a blade of a turbine according to the prior art;
FIG. 2
a perspective view of a blade root of a blade according to the invention a turbine and
FIG. 3
a perspective view of the installation situation of a blade root according to Fig. 2 ,

In FIG 1 ist eine Schaufel 10 gemäß dem Stand der Technik veranschaulicht, welche ein Schaufelfuß 12 und ein sich daran anschließendes Schaufelblatt 14 aufweist. Der Schaufelfuß 12 ist als Tannenbaumfuß mit einer Plattform 16 gestaltet, an welcher an der dem Schaufelblatt 14 gegenüberliegenden Seite ein Hals 18 und weiter entfernt Zähne 20 angeordnet sind. Die Plattform 16, der Hals 18 und die Zähne 20 sind als längliches Profil gestaltet, welches bei eingebauter Schaufel 10 in eine nicht dargestellte Nut einer Radscheibe 22 eines Turbinenläufers angeordnet ist und dort zum Halten des Schaufelblattes 14 und zum Aufnehmen von insbesondere dessen Fliehkräften vorgesehen ist.In FIG. 1 a blade 10 is illustrated according to the prior art, which has a blade root 12 and an adjoining blade 14. The blade root 12 is designed as a fir tree root with a platform 16 on which a neck 18 and farther away teeth 20 are arranged on the side opposite the blade blade 14. The platform 16, the neck 18 and the teeth 20 are designed as an elongated profile, which is arranged with a built-in blade 10 in a groove (not shown) of a wheel disc 22 of a turbine rotor and there is provided for holding the blade 14 and for receiving in particular its centrifugal forces ,

Eine solche Einbaulage einer Schaufel 10 an einer Radscheibe 22 ist grundsätzlich in FIG 3 veranschaulicht.Such an installation position of a blade 10 on a wheel disc 22 is basically in FIG. 3 illustrated.

Wie in FIG 1 zu erkennen ist, ist bei der bekannten Schaufel 10 die zum Hals 18 und den Zähnen 20 gewandte Unterseite der Plattform 16 mit einer im Wesentlichen glatten Oberfläche versehen.As in FIG. 1 can be seen, in the known blade 10, the neck 18 and the teeth 20 facing bottom of the Platform 16 provided with a substantially smooth surface.

Bei einer in FIG 2 veranschaulichten Schaufel 10, welche hinsichtlich des Schaufelfußes 12 grundsätzlich wie das Beispiel gemäß FIG 1 gestaltet ist, ist die Unterseite 24 hingegen mit einer Vielzahl Turbulatoren 26 gestaltet, die jeweils in einer Reihe an beiden Seiten des Halses 18 angeordnet sein können.At an in FIG. 2 illustrated blade 10, which in principle with respect to the blade root 12 as the example according to FIG. 1 is designed, the bottom 24 is, however, designed with a plurality of turbulators 26, which may each be arranged in a row on both sides of the neck 18.

Die Turbulatoren 26 sind zu einem sich in Hauptströmungsrichtung eines Heißgases erstreckenden Kühlkanal 28 gewandt, der zwischen der Unterseite 24 der Plattform 16 und dem Außenumfang der Radscheibe 22 vorgesehen ist.The turbulators 26 face a cooling channel 28 extending in the main flow direction of a hot gas, which is provided between the underside 24 of the platform 16 and the outer periphery of the wheel disc 22.

Der Kühlkanal 28 verläuft entlang einer Plattformlängskante, welche sich von einer anströmseitigen Kante der Plattform 16 zu einer abströmseitigen Kante erstreckt, bezogen auf die Hauptströmungsrichtung des die Gasturbine beim Betrieb durchströmenden Heißgases.The cooling channel 28 extends along a platform longitudinal edge, which extends from an upstream edge of the platform 16 to a downstream edge, with respect to the main flow direction of the hot gas flowing through the gas turbine during operation.

Der Kühlkanal 28 wird im Betrieb der zugehörigen Gasturbine mit einem nicht dargestellten Kühlfluid in einer Strömungsrichtung 30 durchströmt. Die Turbulatoren 26 sind lediglich entlang der Plattformlängskante angeordnet und hinsichtlich dieser Strömung des Kühlfluids quer oder schräg zur Strömungsrichtung 30 als Taschen gestaltet, welche in dem Material der Plattform 16 ausgeformt sind, und zu deren Unterseite 24 jeweils eine Öffnung aufweisen. In diesen Taschen kommt es zu einer zusätzlichen Verwirbelung des durch den Kühlkanal 28 strömenden Kühlfluids und damit zu einem verbesserten Wärmeübergang von der Plattform 16 in das Kühlfluid. Somit führen die Taschen zu einer erhöhten Wärmeabfuhr und einer verbesserten Kühlung des Schaufelfußes 12 und der Plattform 16.During operation of the associated gas turbine, the cooling channel 28 flows through a cooling fluid, not shown, in a flow direction 30. The turbulators 26 are arranged only along the platform longitudinal edge and with respect to this flow of the cooling fluid transversely or obliquely to the flow direction 30 designed as pockets which are formed in the material of the platform 16, and to the underside 24 each having an opening. In these pockets there is an additional turbulence of the cooling fluid flowing through the cooling channel 28 and thus to an improved heat transfer from the platform 16 into the cooling fluid. Thus, the pockets lead to increased heat dissipation and improved cooling of the blade root 12 and the platform 16.

Das Schaufelblatt 14 weist eine druckseitige Wand 27.The airfoil 14 has a pressure-side wall 27.

Insbesondere bei unsymmetrisch großen Plattformen 16 einer Turbinenschaufel 10, führt die Ausgestaltung mit unterseitig angeordneten Turbulatoren 26 zu Vorteilen. Wenn eine der beiden Plattformlängskanten, beispielsweise die druckseitige Plattformseite bezogen auf das Schaufelblatt 14, in Umfangsrichtung der Radscheibe 22 weiter aus ragt als die andere der, ist für das Beispiel also die saugseitige Plattformseite, ist es ausreichend, dass nur auf der druckseitigen Plattformlängskante an der Unterseite 24 Turbulatoren 26 vorgesehen sind wie in FIG 3 gezeigt, welche das Kühlfluid im Kühlkanal 28 verwirbeln und somit auch für die saugseitige Plattformlängskante 29b der unmittelbar benachbarten Turbinenschaufel 10 des Schaufelrades einen, im Bezug auf den Stand der Technik, ausreichend erhöhten Wärmeübergang ermöglichen.Particularly in the case of asymmetrically large platforms 16 of a turbine blade 10, the embodiment with turbulators 26 arranged on the underside leads to advantages. If one of the two platform longitudinal edges, for example, the pressure side platform side relative to the airfoil 14 in the circumferential direction of the wheel disc 22 further protrudes than the other of the example is the suction side platform side, it is sufficient that only on the pressure side platform longitudinal edge on the Bottom 24 turbulators 26 are provided as in FIG. 3 shown, which swirl the cooling fluid in the cooling channel 28 and thus also allow for the suction-side platform longitudinal edge 29b of the immediately adjacent turbine blade 10 of the impeller a sufficiently high heat transfer in relation to the prior art.

Die Taschen der Turbulatoren 26 können beispielsweise in das Material der Plattform 16 einerodiert sein und weisen dabei vorteilhaft eine Länge auf, welche etwa der zwei- bis siebenfachen, insbesondere drei- bis fünffachen, besonders vorteilhaft, der vierfachen Breite einer Tasche entspricht. Alternativ zu Taschen können an der Unterseite 24 der Plattform 16 die Turbulatoren 26 auch in Gestalt von Nippeln oder Dimpeln ausgebildet sein. Mit solchen Turbulatoren 26 sind an der Unterseite 24 jeweils Schlitze bzw. Stege gestaltet, welche partielle Strömungswiderstände für das durch den Kühlkanal 28 strömende Kühlfluid darstellen und damit zu Turbulenzen innerhalb des Kühlfluids führen.The pockets of the turbulators 26 may, for example, be anodized into the material of the platform 16 and advantageously have a length which corresponds approximately to two to seven times, in particular three to five times, particularly advantageously four times the width of a pocket. As an alternative to pockets, the turbulators 26 may also be designed in the form of nipples or dimples on the underside 24 of the platform 16. With such turbulators 26 slots or webs are respectively formed on the underside 24, which represent partial flow resistance for the flowing through the cooling channel 28 cooling fluid and thus lead to turbulence within the cooling fluid.

Zudem sind die Turbulatoren 26 vorzugsweise derart schräg zur Kühlfluidströmung ausgerichtet, dass sie das Kühlfluid von einem Spalt, der von zwei stirnseitig gegenüberliegenden Plattformen 16 benachbarter Turbinenschaufeln 10 gebildet wird, wegleiten. Somit wird das Kühlfluid von den Turbulatoren 26 auch gegen den Hals 18 des Schaufelfußes 12 geführt. Wie in FIG 3 gezeigt, ist der unterhalb der Plattform 16 vorhandene Querschnitt des Kühlkanals 28 keilförmig, d.h. vom Plattformrand aus verkleinert sich die radiale Höhe des Querschnitts zum Hals 18 des Schaufelfußes 12 hin. Das Kühlfluid würde ohne derart schräggestellte Turbulatoren 26 aufgrund des lokal geringeren Strömungswiderstandes vermehrt im größeren Querschnittsbereich strömen als im halsnahen, kleineren Querschnittsbereich. Mit derart schräg gestellten Turbulatoren 26 wird dieser Effekt wirksam unterdrückt und das Kühlfluid wird verstärkt in den kleineren Querschnittsbereich zum Hals 18 des Schaufelfußes 18 geführt, was zu einer Vergleichmäßigung der Kühlung der Plattform 16 führt. Mit den, vorzugsweise in einem Winkel von 45° - bezogen auf die Strömungsrichtung 30 - schräg gestellten Turbulatoren 26 kann ein spiralförmiger Kühlfluidstrom entlang des Kühlkanals 28 erzwungen werden, der sich unmittelbar unterhalb der Unterseite 24 der Plattform 16 zum Hals 18 des Schaufelfußes 12 hin dreht.In addition, the turbulators 26 are preferably oriented obliquely to the flow of cooling fluid so as to divert the cooling fluid from a gap formed by two endwise opposed platforms 16 of adjacent turbine blades 10. Thus, the cooling fluid from the turbulators 26 is also guided against the neck 18 of the blade root 12. As in FIG. 3 is shown below the platform 16 existing cross-section of the cooling channel 28th wedge-shaped, ie from the platform edge, the radial height of the cross-section decreases towards the neck 18 of the blade root 12. The cooling fluid would flow without such inclined turbulators 26 due to the locally lower flow resistance increasingly in the larger cross-sectional area than in the neck close, smaller cross-sectional area. With such inclined turbulators 26, this effect is effectively suppressed and the cooling fluid is increasingly guided in the smaller cross-sectional area to the neck 18 of the blade root 18, which leads to a homogenization of the cooling of the platform 16. With the, preferably at an angle of 45 ° - with respect to the flow direction 30 - slanted turbulators 26, a spiral cooling fluid flow along the cooling channel 28 can be forced, which rotates immediately below the bottom 24 of the platform 16 to the neck 18 of the blade root 12 out ,

Anstelle von einerodierten Taschen auf der Unterseite 24 der Plattform 16 kann durch Auftragsschweißen zusätzliches Material auf der Unterseite 24 der Plattform 16 für die Turbulatoren 26 aufgetragen werden. Dieses zusätzliche Material wird dann in einem nachfolgenden Arbeitsschritt zumindest teilweise durch geeignete Verfahren abgetragen, um somit die Turbulatoren 26 auszubilden.Instead of anodized pockets on the underside 24 of the platform 16, additional material may be deposited on the underside 24 of the platform 16 for the turbulators 26 by build-up welding. This additional material is then at least partially removed in a subsequent step by suitable methods, so as to form the turbulators 26.

Alternativ zu den vorgestellten Herstellungsverfahren kann auch ein vorgefertigtes, separates Modul mit Turbulatoren 26 in einem von der (Guß-)Herstellung der Turbinenschaufel getrennten Arbeitsgang durch Form- und/oder Kraftschluss kostengünstig befestigt werden. Vorgefertigte Module lassen such bei Revisionsarbeiten nachträglich zeitsparend montieren.As an alternative to the production methods presented, a prefabricated, separate module with turbulators 26 in a separate operation from the (cast) production of the turbine blade can also be inexpensively fastened by positive and / or positive connection. Prefabricated modules can be retrofitted for inspection work in a time-saving manner.

Das Turbulator-Modul kann beispielsweise die gleiche Längserstreckung aufweisen wie die Plattformlängskante und, ausgestattet mit einer Nut und Feder Konfiguration, stirnseitig in die Plattform 16 in eine entlang der Unterseite 24 sich erstreckende korrespondierende Ausnehmung einschiebbar sein, um anschließend durch Schweißen oder Löten fixiert zu werden.The turbulator module may for example have the same longitudinal extent as the platform longitudinal edge and, equipped with a tongue and groove configuration, frontally into the platform 16 in one along the Bottom 24 extending corresponding recess be inserted to be subsequently fixed by welding or soldering.

Claims (15)

  1. Vane wheel for a turbine, with at least one vane (10) around which a hot gas can flow and of which a vane foot (12) having a platform (16) is held on a wheel disk (22), and in which at least one cooling channel (28) extending in the main flow direction of the hot gas is located between the outer circumference of the wheel disk (22) and the platform (16) of the vane (10), characterized in that, on at least one of the walls of the cooling channel (28), a multiplicity of turbulators (26) are formed, which are configured in such a way that they increase the turbulence of a cooling fluid flowing through the cooling channel (28).
  2. Vane wheel according to Claim 1, characterized in that the multiplicity of turbulators (26) are formed on the underside (24) of the platform (16) of the vane foot (12).
  3. Vane wheel according to Claim 1 or 2, characterized in that the multiplicity of turbulators (26) are configured in the form of pockets which are shaped in the material forming the at least one wall of the cooling channel (28).
  4. Vane wheel according to one of the preceding claims, characterized in that the turbulators (26) are oriented in each case essentially transversely or obliquely with respect to the flow direction (30) of the cooling fluid flowing through the cooling channel (28).
  5. Vane wheel according to one of the preceding claims, characterized in that the turbulators (26) are oriented obliquely with respect to the flow direction (30) of the cooling fluid flowing through the cooling channel (28), in such a way that they deflect the flowing cooling fluid in the direction of a neck (18) of the vane foot (12).
  6. Vane wheel according to one of the preceding claims, characterized in that, in at least one region with increased heat load of the vane wheel, the number of turbulators (26) provided per unit area is increased, as compared with at least one region of lower heat load.
  7. Vane wheel according to one of the preceding claims, characterized in that the vane foot (12) of at least one vane (10) is configured with a platform (16), on which a cooling channel (28) is located on each of the two sides along an elongated neck (18) and the multiplicity of turbulators (26) are configured in the form of a row extending in the associated cooling channel (28) on the underside (24) of the platform (16).
  8. Vane wheel according to one of the preceding claims, characterized in that the turbulators (26) have been shaped together in one operation forming the vane (10) and, in particular, its vane leaf (14).
  9. Vane wheel according to one of the preceding claims, characterized in that the turbulators (26) have been shaped in a separate operation after at least one operation forming the vane (10) and, in particular, its vane leaf (14).
  10. Vane (10) for a vane wheel of a turbine, in particular a gas turbine, with a vane leaf (14) around which a hot gas can flow and with a vane foot (12) having a platform (16) which, with respect to the main flow direction of the hot gas, extends from an inflow-side edge (31) to an outflow-side edge (33) along a longitudinal platform edge (29), and on which a neck (18) is arranged on a side lying opposite the vane leaf (14) and, further away, teeth (20) are arranged, wherein on the underside (24) of the platform (16) a multiplicity of turbulators (26) are formed, which are configured in such a way that, in the built-in state of the vane (10), they increase the turbulence of a cooling fluid flowing along the underside (24), characterized in that
    the turbulators (26) are arranged on the side of the neck (18) along the longitudinal platform edge (29).
  11. Vane (10) according to Claim 10, characterized in that the multiplicity of turbulators (26) are configured in the form of pockets which are shaped in the material of the platform (16).
  12. Vane (10) according to Claim 10 or 11, characterized in that the turbulators (26) are oriented obliquely with respect to the flow direction of the cooling fluid flowing along the longitudinal platform edge (29), in such a way that they at least partially deflect the flowing cooling fluid in the direction of the neck (18) of the vane foot (16).
  13. Method for producing a vane (10) according to one of Claims 10, 11 or 12, characterized in that the turbulators (26) are shaped together in one operation forming the vane leaf (14).
  14. Method for producing a vane (10) according to one of Claims 10, 11 or 12, characterized in that the turbulators (26) are shaped in a separate operation after at least one operation forming the vane leaf (14).
  15. Method according to Claim 14, characterized in that the turbulators (26) are prefabricated on a separate module, which module is fastened to the underside (24) of the platform (16) by positive and/or nonpositive connection in a separate operation.
EP05766734A 2004-07-09 2005-06-13 Vane wheel of a turbine comprising a vane and at least one cooling channel Active EP1766192B1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
PL05766734T PL1766192T3 (en) 2004-07-09 2005-06-13 Vane wheel of a turbine comprising a vane and at least one cooling channel
EP05766734A EP1766192B1 (en) 2004-07-09 2005-06-13 Vane wheel of a turbine comprising a vane and at least one cooling channel

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP04016237A EP1614861A1 (en) 2004-07-09 2004-07-09 Turbine wheel comprising turbine blades having turbulators on the platform radially inner surface.
EP05766734A EP1766192B1 (en) 2004-07-09 2005-06-13 Vane wheel of a turbine comprising a vane and at least one cooling channel
PCT/EP2005/052714 WO2006005659A1 (en) 2004-07-09 2005-06-13 Vane wheel of a turbine comprising a vane and at least one cooling channel

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EP1766192A1 EP1766192A1 (en) 2007-03-28
EP1766192B1 true EP1766192B1 (en) 2011-01-12

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EP04016237A Withdrawn EP1614861A1 (en) 2004-07-09 2004-07-09 Turbine wheel comprising turbine blades having turbulators on the platform radially inner surface.
EP05766734A Active EP1766192B1 (en) 2004-07-09 2005-06-13 Vane wheel of a turbine comprising a vane and at least one cooling channel

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EP04016237A Withdrawn EP1614861A1 (en) 2004-07-09 2004-07-09 Turbine wheel comprising turbine blades having turbulators on the platform radially inner surface.

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EP (2) EP1614861A1 (en)
JP (1) JP4637906B2 (en)
CN (1) CN101014752B (en)
AT (1) ATE495347T1 (en)
DE (1) DE502005010841D1 (en)
ES (1) ES2358336T3 (en)
PL (1) PL1766192T3 (en)
WO (1) WO2006005659A1 (en)

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ATE495347T1 (en) 2011-01-15
EP1766192A1 (en) 2007-03-28
EP1614861A1 (en) 2006-01-11
JP4637906B2 (en) 2011-02-23
CN101014752A (en) 2007-08-08
US20080267784A1 (en) 2008-10-30
US7758309B2 (en) 2010-07-20
JP2008506061A (en) 2008-02-28
PL1766192T3 (en) 2011-06-30
ES2358336T3 (en) 2011-05-09
DE502005010841D1 (en) 2011-02-24
WO2006005659A1 (en) 2006-01-19
CN101014752B (en) 2011-06-08

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