EP2025868A1 - Turbine blade having a turbulator at the cooling air inlet - Google Patents

Turbine blade having a turbulator at the cooling air inlet Download PDF

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Publication number
EP2025868A1
EP2025868A1 EP07015784A EP07015784A EP2025868A1 EP 2025868 A1 EP2025868 A1 EP 2025868A1 EP 07015784 A EP07015784 A EP 07015784A EP 07015784 A EP07015784 A EP 07015784A EP 2025868 A1 EP2025868 A1 EP 2025868A1
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EP
European Patent Office
Prior art keywords
turbine blade
coolant
cooling
turbulence
blade
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.)
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Application number
EP07015784A
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German (de)
French (fr)
Inventor
Hans Thermann
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Siemens AG
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Siemens AG
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Publication date
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Priority to EP07015784A priority Critical patent/EP2025868A1/en
Publication of EP2025868A1 publication Critical patent/EP2025868A1/en
Withdrawn legal-status Critical Current

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    • 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
    • F01D5/187—Convection cooling
    • 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
    • F05D2250/00—Geometry
    • F05D2250/50—Inlet or outlet
    • F05D2250/51—Inlet
    • 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

Definitions

  • the invention relates to a turbine blade with an airfoil, in which a cavity suitable for cooling the airfoil is provided, wherein the turbine blade has a feed opening for a coolant that can be supplied to the cavity.
  • Numerous turbine blades with a hollow airfoil are known from the prior art, into the cavity of which a coolant can be flowed in through a feed opening.
  • the turbine blades are known to be used for the deflection of a hot gas to convert the energy content of the hot gas into mechanical energy. Due to the high temperatures of the hot gas, the turbine blades are cooled so that they have a particularly long life despite the particularly high temperatures.
  • known cooling methods are used for cooling the turbine blades.
  • the cooling methods can be film cooling, impingement cooling or convection cooling.
  • the hollow turbine blade In the convection cooling, the hollow turbine blade is flowed through by a coolant, wherein the heat energy in the blade material is absorbed by the coolant by convection by the sweeping of the coolant on the inner surfaces of the cooling to the blade wall.
  • the coolant flowing in the turbine blade impinges perpendicularly on the blade wall to be cooled, whereby particularly good heat transfer can be achieved.
  • the film cooling, the coolant flowing inside the turbine blade exits via a plurality of film cooling holes arranged in a row, forming a protective cooling film on the surface of the outer wall to be cooled, which is exposed to the hot gas, whereby the heat input can be reduced from the hot gas into the blade material.
  • it is necessary to reduce the amount of coolant as an unnecessarily high Consumption unnecessarily lowers the efficiency of the gas turbine equipped with these turbine blades.
  • the object of the invention is therefore to provide a turbine blade mentioned above, in which the coolant is to have the highest possible effectiveness for saving the coolant.
  • the invention provides that a turbine blade of the type mentioned in or at its feed opening has a turbulence agent. Consequently, in addition to the known cooling measures in or at the inflow region, in which the coolant enters the turbine blade, for example, a turbulence grid is attached.
  • the turbulence grid is intended to generate as highly turbulent a flow as possible in the following cavity or in the coolant channel leading to the cavity. Due to the inflated turbulence of the flow, an increase in the heat transfer can be achieved in the downstream cavity of the turbine blade, which leads to a higher cooling efficiency overall. The blade can thus be cooled better. Due to the higher cooling efficiency, a coolant saving can be achieved or the turbine blade can be exposed to higher hot gas temperatures while maintaining the coolant used.
  • turbulence means are not provided in the region of the cavity suitable for cooling the airfoil - such as turbulators provided in the meander channel, for example - but they are arranged in or at the region of the feed opening for swirling the coolant.
  • the feed opening is provided in a fastening section.
  • the turbine blade is held in a mounting portion on a support structure, for example on a vane support or on a rotor of the gas turbine.
  • the supply of coolant takes place in each case via the attachment portion.
  • the feed opening is provided in the attachment portion, so that the turbulence in the coolant can be generated directly upon feeding the coolant into the turbine blade, whereby the higher heat transfer can be achieved.
  • the turbulence means at least partially covers the feed opening.
  • the turbulence agent may be formed as a turbulence grid.
  • the grid which may be formed of a wire mesh or a network of wire, can completely cover the feed opening and is, however, largely permeable to the coolant, wherein the laminar flow prior to entry can be disturbed comparatively strongly.
  • the turbulence grid represents a particularly low pressure loss variant of a turbulence means. Pressure losses are thus kept comparatively low, as a result of which overall efficient cooling of the turbine blade can be achieved.
  • due to the low additional pressure loss of the turbulence grid it is possible to retrofit existing turbine blades with such turbulence means.
  • the turbine blade also has a film and / or convection cooling, possibly also an impingement cooling.
  • the turbine blade is only convectively cooled, wherein the cavity in the airfoil may comprise, for example, meander channels.
  • the meander channels On the inside of the meander channels can further turbulence agents, such as ribs or dimple, be present.
  • the turbine blade may be configured as a blade or vane of a stationary gas turbine. In principle, the turbine blade has been produced by casting and, accordingly, in one piece. The turbulence agent can then be subsequently applied after the casting process in an additional manufacturing step. For example, the turbulence grid may be soldered or welded to the turbine blade.
  • FIG. 2 shows a turbine blade 10 according to the invention in a longitudinal section.
  • the turbine blade 10 comprises an airfoil 12, which is curved profiled aerodynamically in cross section (see. FIG. 1 ).
  • the airfoil 12 has a first platform 14 and a second platform 16.
  • the plan view of the second platform 16 is in FIG. 1 shown.
  • illustrated turbine blade 10 has a total of two cavities 18, 20, each of which a coolant can be supplied.
  • the cavities 18, 20 are disposed within the airfoil 12 such that coolant flowing therein may convectively cool the airfoil 12.
  • the Indian FIG. 2 shown on the left first cavity 18 is disposed in the region of a front edge 22 of the airfoil 12.
  • the second cavity 20 is meander-shaped and terminates at a trailing edge 24.
  • the coolant which can be supplied to the second cavity 20, leaves the turbine blade 10 at the trailing edge 24.
  • outlet openings are provided in the trailing edge 24, which connect the cavity 20 with the space surrounding the airfoil 12.
  • the coolant can be fed to the cavities 18, 20 via supply openings 26 arranged in a fastening region 25.
  • the attachment region 25 is provided on the platform side, wherein the supply openings 26 are arranged on the cold side of the platform 16.
  • a turbulence means 28 is provided in the region of the feed opening 26, whereby the inflowing coolant can be swirled immediately upon entry into the turbine blade 10.
  • the turbulence means 28 is formed as a plate 30 with two openings, over each of which a wire mesh 34 is tensioned.
  • the wire mesh 34 provides a turbulence grid for the coolant, thereby swirling the substantially uniform flow of coolant as it enters the turbine blade 10. Due to the turbulence, there already arises a heat-imparting effect, so that the heat energy present in the blade material can be transferred into the coolant in a particularly simple manner.
  • the turbine blade 10 further comprises a film and / or convection cooling in order to be able to further cool regions of the airfoil 12 which are remote from the feed opening 26.
  • the invention thus relates to a turbine blade 10 with a hollow blade 12, in the cavity 18, 20 through a supply port 26, a coolant can be flowed.
  • a turbulence means 28 is provided on or in the feed opening 26, which, for example, as a turbulence grid is trained. In this way, in particular, a turbulent air flow of coolant already generated during the inflow process can be generated.

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

Abstract

The turbine blade (10) has a blade leaf (12), in which a cavity (18) is provided for cooling the leaf. A supply opening (26) is provided for supplying cooling agent to the cavity. A turbulence unit (28) is provided in or at the supply opening, which is provided in the fixing section.

Description

Die Erfindung betrifft eine Turbinenschaufel mit einem Schaufelblatt, in dem ein zur Kühlung des Schaufelblatts geeigneter Hohlraum vorgesehen ist, wobei die Turbinenschaufel eine Zuführöffnung für ein dem Hohlraum zuführbares Kühlmittel aufweist.The invention relates to a turbine blade with an airfoil, in which a cavity suitable for cooling the airfoil is provided, wherein the turbine blade has a feed opening for a coolant that can be supplied to the cavity.

Aus dem Stand der Technik sind zahlreiche Turbinenschaufeln mit einem hohlen Schaufelblatt bekannt, in deren Hohlraum durch eine Zuführöffnung ein Kühlmittel einströmbar ist. Die Turbinenschaufeln werden bekanntermaßen zur Umlenkung eines Heißgases genutzt, um den Energiegehalt des Heißgases in mechanische Energie umzuwandeln. Aufgrund der hohen Temperaturen des Heißgases werden die Turbinenschaufeln gekühlt, damit diese trotz der besonders hohen Temperaturen eine besonders lange Lebensdauer aufweisen. Zur Kühlung der Turbinenschaufeln kommen bekannte Kühlmethoden zum Einsatz. Bei den Kühlmethoden kann es sich um Filmkühlung, Prallkühlung oder Konvektionskühlung handeln.Numerous turbine blades with a hollow airfoil are known from the prior art, into the cavity of which a coolant can be flowed in through a feed opening. The turbine blades are known to be used for the deflection of a hot gas to convert the energy content of the hot gas into mechanical energy. Due to the high temperatures of the hot gas, the turbine blades are cooled so that they have a particularly long life despite the particularly high temperatures. For cooling the turbine blades known cooling methods are used. The cooling methods can be film cooling, impingement cooling or convection cooling.

Bei der Konvektionskühlung wird die hohle Turbinenschaufel von einem Kühlmittel durchströmt, wobei durch das Entlangstreichen des Kühlmittels an den inneren Oberflächen der zur kühlenden Schaufelwand die im Schaufelmaterial befindliche Wärmeenergie vom Kühlmittel durch Konvektion aufgenommen wird. Im Gegensatz dazu trifft bei der Prallkühlung das in der Turbinenschaufel strömende Kühlmittel senkrecht auf die zu kühlende Schaufelwand, wodurch besonders gute Wärmeübergänge erreicht werden können. Bei der dritten Variante der Schaufelkühlung, der Filmkühlung, tritt das im Inneren der Turbinenschaufel strömende Kühlmittel über eine Vielzahl von in einer Reihe angeordneten Filmkühlöffnungen aus und bildet dabei auf der Oberfläche der zu kühlenden, dem Heißgas ausgesetzten Außenwand einen schützenden Kühlfilm aus, wodurch der Wärmeeintrag aus dem Heißgas in das Schaufelmaterial reduziert werden kann. Bei allen Kühlmethoden gilt es jedoch, die Menge an Kühlmittel zu reduzieren, da ein unnötig hoher Verbrauch den Wirkungsgrad der mit diesen Turbinenschaufeln ausgestatteten Gasturbine unnötig senkt.In the convection cooling, the hollow turbine blade is flowed through by a coolant, wherein the heat energy in the blade material is absorbed by the coolant by convection by the sweeping of the coolant on the inner surfaces of the cooling to the blade wall. In contrast, in the case of impingement cooling, the coolant flowing in the turbine blade impinges perpendicularly on the blade wall to be cooled, whereby particularly good heat transfer can be achieved. In the third variant of the blade cooling, the film cooling, the coolant flowing inside the turbine blade exits via a plurality of film cooling holes arranged in a row, forming a protective cooling film on the surface of the outer wall to be cooled, which is exposed to the hot gas, whereby the heat input can be reduced from the hot gas into the blade material. In all cooling methods, however, it is necessary to reduce the amount of coolant, as an unnecessarily high Consumption unnecessarily lowers the efficiency of the gas turbine equipped with these turbine blades.

Aufgabe der Erfindung ist daher die Bereitstellung einer eingangs genannten Turbinenschaufel, bei der zur Kühlmitteleinsparung die Kühlung eine möglichst hohe Effektivität aufweisen soll.The object of the invention is therefore to provide a turbine blade mentioned above, in which the coolant is to have the highest possible effectiveness for saving the coolant.

Die vorgenannte Aufgabe wird durch eine Turbinenschaufel mit den Merkmalen des Anspruchs 1 gelöst.The aforementioned object is achieved by a turbine blade with the features of claim 1.

Die Erfindung sieht vor, dass eine Turbinenschaufel der eingangs genannten Art in oder an ihrer Zuführöffnung ein Turbulenzmittel aufweist. Folglich ist ergänzend zu den bekannten Kühlmaßnahmen im oder am Einströmbereich, in dem das Kühlmittel in die Turbinenschaufel eintritt, beispielsweise ein Turbulenzgitter angebracht. Das Turbulenzgitter soll im nachfolgenden Hohlraum bzw. im zum Hohlraum führenden Kühlmittelkanal eine möglichst hochturbulente Strömung erzeugen. Aufgrund der angefachten Turbulenz der Strömung kann im nachgeordneten Hohlraum der Turbinenschaufel eine Erhöhung des Wärmeübergangs erreicht werden, was insgesamt zu einer höheren Kühleffektivität führt. Das Schaufelblatt kann somit besser gekühlt werden. Durch die höhere Kühleffektivität kann eine Kühlmitteleinsparung erzielt werden oder die Turbinenschaufel kann bei gleichbleibendem Kühlmitteleinsatz höheren Heißgas-Temperaturen ausgesetzt werden. Sofern als Kühlmittel Kühlluft eingesetzt wird, welche von einem Verdichter der Gasturbine bereitgestellt wird, führt die Kühllufteinsparung ebenfalls zu einer Leistungssteigerung der Gasturbine sowie zu einem gesteigerten Wirkungsgrad. Insgesamt wird somit vorgeschlagen, dass nicht erst im Bereich des zur Kühlung des Schaufelblatts geeigneten Hohlraums Turbulenzmittel vorgesehen sind - wie beispielsweise im Mäanderkanal vorgesehene Turbulatoren -, sondern diese im oder am Bereich der Zuführöffnung zur Verwirbelung des Kühlmittels angeordnet sind.The invention provides that a turbine blade of the type mentioned in or at its feed opening has a turbulence agent. Consequently, in addition to the known cooling measures in or at the inflow region, in which the coolant enters the turbine blade, for example, a turbulence grid is attached. The turbulence grid is intended to generate as highly turbulent a flow as possible in the following cavity or in the coolant channel leading to the cavity. Due to the inflated turbulence of the flow, an increase in the heat transfer can be achieved in the downstream cavity of the turbine blade, which leads to a higher cooling efficiency overall. The blade can thus be cooled better. Due to the higher cooling efficiency, a coolant saving can be achieved or the turbine blade can be exposed to higher hot gas temperatures while maintaining the coolant used. If cooling air is used as the coolant, which is provided by a compressor of the gas turbine, the cooling air saving also leads to an increase in performance of the gas turbine and to an increased efficiency. Overall, it is thus proposed that turbulence means are not provided in the region of the cavity suitable for cooling the airfoil - such as turbulators provided in the meander channel, for example - but they are arranged in or at the region of the feed opening for swirling the coolant.

Vorteilhafte Ausgestaltungen sind in den Unteransprüchen angegeben.Advantageous embodiments are specified in the subclaims.

In einer ersten vorteilhaften Weiterbildung ist die Zuführöffnung in einem Befestigungsabschnitt vorgesehen. Üblicherweise ist die Turbinenschaufel in einem Befestigungsabschnitt an einer Tragstruktur, beispielsweise an einem Leitschaufelträger oder an einem Rotor der Gasturbine, gehalten. Die Zuführung von Kühlmittel erfolgt dabei jeweils über den Befestigungsabschnitt. Dementsprechend ist die Zuführöffnung im Befestigungsabschnitt vorgesehen, so dass bereits unmittelbar beim Einspeisen des Kühlmittels in die Turbinenschaufel die Turbulenzen im Kühlmittel erzeugbar sind, wodurch der höhere Wärmeübergang erreicht werden kann.In a first advantageous development, the feed opening is provided in a fastening section. Usually, the turbine blade is held in a mounting portion on a support structure, for example on a vane support or on a rotor of the gas turbine. The supply of coolant takes place in each case via the attachment portion. Accordingly, the feed opening is provided in the attachment portion, so that the turbulence in the coolant can be generated directly upon feeding the coolant into the turbine blade, whereby the higher heat transfer can be achieved.

Zweckmäßigerweise überdeckt das Turbulenzmittel die Zuführöffnung zumindest teilweise. Beispielsweise kann das Turbulenzmittel als Turbulenzgitter ausgebildet sein. Das Gitter, welches aus einem Drahtgeflecht oder aus einem Netz aus Draht gebildet sein kann, kann vollständig die Zuführöffnung überdecken und ist dabei jedoch in großem Maße durchlässig für das Kühlmittel, wobei die vor dem Eintritt noch laminare Strömung vergleichsweise stark gestört werden kann. Dabei stellt das Turbulenzgitter eine besonders druckverlustarme Variante eines Turbulenzmittels dar. Druckverluste werden somit vergleichsweise gering gehalten, wodurch insgesamt eine effiziente Kühlung der Turbinenschaufel erreicht werden kann. Insbesondere aufgrund des geringen zusätzlichen Druckverlusts des Turbulenzgitters ist es möglich, auch bereits existierende Turbinenschaufeln mit einem derartigen Turbulenzmittel nachzurüsten.Conveniently, the turbulence means at least partially covers the feed opening. For example, the turbulence agent may be formed as a turbulence grid. The grid, which may be formed of a wire mesh or a network of wire, can completely cover the feed opening and is, however, largely permeable to the coolant, wherein the laminar flow prior to entry can be disturbed comparatively strongly. In this case, the turbulence grid represents a particularly low pressure loss variant of a turbulence means. Pressure losses are thus kept comparatively low, as a result of which overall efficient cooling of the turbine blade can be achieved. In particular, due to the low additional pressure loss of the turbulence grid, it is possible to retrofit existing turbine blades with such turbulence means.

Insgesamt weist die Turbinenschaufel auch ein Film- und/oder Konvektionskühlung auf, ggf. auch eine Prallkühlung. Vorzugsweise ist die Turbinenschaufel jedoch lediglich konvektiv gekühlt, wobei der Hohlraum im Schaufelblatt beispielsweise Mäanderkanäle umfassen kann. An der Innenseite der Mäanderkanäle können weitere Turbulenzmitteln, wie beispielsweise Rippen oder Dimpel, vorhanden sein. Die Turbinenschaufel kann als Laufschaufel oder Leitschaufel einer stationären Gasturbine ausgestaltet sein. Prinzipiell ist die Turbinenschaufel im Gießverfahren hergestellt worden und dementsprechend einstückig. Das Turbulenzmittel kann dann im Anschluss an den Gießvorgang in einem zusätzlichen Herstellungsschritt nachträglich angebracht werden. Beispielsweise kann das Turbulenzgitter an die Turbinenschaufel gelötet oder geschweißt werden.Overall, the turbine blade also has a film and / or convection cooling, possibly also an impingement cooling. Preferably, however, the turbine blade is only convectively cooled, wherein the cavity in the airfoil may comprise, for example, meander channels. On the inside of the meander channels can further turbulence agents, such as ribs or dimple, be present. The turbine blade may be configured as a blade or vane of a stationary gas turbine. In principle, the turbine blade has been produced by casting and, accordingly, in one piece. The turbulence agent can then be subsequently applied after the casting process in an additional manufacturing step. For example, the turbulence grid may be soldered or welded to the turbine blade.

Weitere Vorteile und Merkmale der Erfindung werden anhand einer schematischen Zeichnung näher erläutert. Im Detail zeigen die Figuren:

  • FIG 1 die Draufsicht auf die Plattform einer erfindungsgemäßen Turbinenschaufel und
  • FIG 2 den Längsschnitt durch eine derartige Turbinenschaufel.
Further advantages and features of the invention will be explained in more detail with reference to a schematic drawing. In detail, the figures show:
  • FIG. 1 the top view of the platform of a turbine blade according to the invention and
  • FIG. 2 the longitudinal section through such a turbine blade.

FIG 2 zeigt in einem Längsschnitt eine erfindungsgemäße Turbinenschaufel 10. Die Turbinenschaufel 10 umfasst ein Schaufelblatt 12, welches im Querschnitt aerodynamisch profiliert gekrümmt ist (vgl. FIG 1). Das Schaufelblatt 12 weist eine erste Plattform 14 und eine zweite Plattform 16 auf. Die Draufsicht auf die zweite Plattform 16 ist in FIG 1 dargestellt. Die in FIG 2 darstellte Turbinenschaufel 10 weist insgesamt zwei Hohlräume 18, 20 auf, denen jeweils ein Kühlmittel zugeführt werden kann. Die Hohlräume 18, 20 sind derart innerhalb des Schaufelblatts 12 angeordnet, dass ein darin strömendes Kühlmittel das Schaufelblatt 12 konvektiv kühlen kann. Der in der FIG 2 links dargestellte erste Hohlraum 18 ist im Bereich einer Vorderkante 22 des Schaufelblattes 12 angeordnet. Der zweite Hohlraum 20 ist mäanderförmig ausgebildet und endet an einer Hinterkante 24. Das dem zweiten Hohlraum 20 zuführbare Kühlmittel verlässt an der Hinterkante 24 die Turbinenschaufel 10. Hierzu sind in der Hinterkante 24 nicht weiter bezeichnete Ausblasöffnungen vorgesehen, die den Hohlraum 20 mit dem das Schaufelblatt 12 umgebenden Raum verbinden. Über in einem Befestigungsbereich 25 angeordnete Zuführöffnungen 26 ist das Kühlmittel den Hohlräumen 18, 20 zuführbar. Der Befestigungsbereich 25 ist plattformseitig vorgesehen, wobei die Zuführöffnungen 26 auf der Kaltseite der Plattform 16 angeordnet sind. FIG. 2 shows a turbine blade 10 according to the invention in a longitudinal section. The turbine blade 10 comprises an airfoil 12, which is curved profiled aerodynamically in cross section (see. FIG. 1 ). The airfoil 12 has a first platform 14 and a second platform 16. The plan view of the second platform 16 is in FIG. 1 shown. In the FIG. 2 illustrated turbine blade 10 has a total of two cavities 18, 20, each of which a coolant can be supplied. The cavities 18, 20 are disposed within the airfoil 12 such that coolant flowing therein may convectively cool the airfoil 12. The Indian FIG. 2 shown on the left first cavity 18 is disposed in the region of a front edge 22 of the airfoil 12. The second cavity 20 is meander-shaped and terminates at a trailing edge 24. The coolant, which can be supplied to the second cavity 20, leaves the turbine blade 10 at the trailing edge 24. For this purpose, outlet openings (not further described) are provided in the trailing edge 24, which connect the cavity 20 with the space surrounding the airfoil 12. The coolant can be fed to the cavities 18, 20 via supply openings 26 arranged in a fastening region 25. The attachment region 25 is provided on the platform side, wherein the supply openings 26 are arranged on the cold side of the platform 16.

Um eine besonders effiziente Kühlung der Turbinenschaufel 10 beim Betrieb der Gasturbine zu erreichen, ist im Bereich der Zuführöffnung 26 ein Turbulenzmittel 28 vorgesehen, wodurch das einströmende Kühlmittel unmittelbar beim Eintritt in die Turbinenschaufel 10 verwirbelt werden kann. Das Turbulenzmittel 28 ist als ein Blech 30 mit zwei Öffnungen ausgebildet, über denen jeweils ein Drahtgeflecht 34 gespannt ist. Das Drahtgeflecht 34 stellt für das Kühlmittel ein Turbulenzgitter dar, wodurch die im Wesentlichen gleichförmige Kühlmittelströmung beim Eintritt in die Turbinenschaufel 10 verwirbelt wird. Aufgrund der Verwirbelung entsteht bereits dort ein den Wärmeübergang anfachender Effekt, so dass die im Schaufelmaterial vorhandene Wärmeenergie besonders einfach in das Kühlmittel übergehen kann. Im Detail kommt es aufgrund der angefachten Turbulenz zu einem erhöhten Impuls- und Wärmeaustausch und dadurch zu einem erhöhten Wärmeübergang. Folglich kann bereits beim Einströmen des Kühlmittels in die Turbinenschaufel 10 eine besonders effiziente Kühlung bereitgestellt werden. Zweckmäßigerweise umfasst die Turbinenschaufel 10 ferner eine Film- und/oder Konvektionskühlung, um von der Zuführöffnung 26 entfernte Bereiche des Schaufelblattes 12 weiter kühlen zu können.In order to achieve a particularly efficient cooling of the turbine blade 10 during operation of the gas turbine, a turbulence means 28 is provided in the region of the feed opening 26, whereby the inflowing coolant can be swirled immediately upon entry into the turbine blade 10. The turbulence means 28 is formed as a plate 30 with two openings, over each of which a wire mesh 34 is tensioned. The wire mesh 34 provides a turbulence grid for the coolant, thereby swirling the substantially uniform flow of coolant as it enters the turbine blade 10. Due to the turbulence, there already arises a heat-imparting effect, so that the heat energy present in the blade material can be transferred into the coolant in a particularly simple manner. In detail, it comes due to the inflamed turbulence to increased momentum and heat exchange and thereby to increased heat transfer. Consequently, a particularly efficient cooling can already be provided when the coolant flows into the turbine blade 10. Expediently, the turbine blade 10 further comprises a film and / or convection cooling in order to be able to further cool regions of the airfoil 12 which are remote from the feed opening 26.

Insgesamt betrifft somit die Erfindung eine Turbinenschaufel 10 mit einem hohlen Schaufelblatt 12, in dessen Hohlraum 18, 20 durch eine Zuführöffnung 26 ein Kühlmittel einströmbar ist. Um eine besonders turbulente Einströmung des Kühlmittels zu erzeugen, wodurch ein verbesserter Wärmeübergang von im Schaufelmaterial vorhandener Wärmeenergie in das Kühlmittel erfolgen kann, ist an oder in der Zuführöffnung 26 ein Turbulenzmittel 28 vorgesehen, welches beispielsweise als Turbulenzgitter ausgebildet ist. Hierdurch lässt sich insbesondere eine bereits beim Einströmvorgang turbulente Luftströmung von Kühlmittel erzeugen.Overall, the invention thus relates to a turbine blade 10 with a hollow blade 12, in the cavity 18, 20 through a supply port 26, a coolant can be flowed. In order to produce a particularly turbulent inflow of the coolant, whereby an improved heat transfer of existing in the blade material thermal energy can be carried into the coolant, a turbulence means 28 is provided on or in the feed opening 26, which, for example, as a turbulence grid is trained. In this way, in particular, a turbulent air flow of coolant already generated during the inflow process can be generated.

Claims (6)

Turbinenschaufel (10),
mit einem Schaufelblatt (12), in dem ein zur Kühlung des Schaufelblatts (12) geeigneter Hohlraum (18) vorgesehen ist,
wobei die Turbinenschaufel (10) eine Zuführöffnung (26) für ein dem Hohlraum (18) zuführbares Kühlmittel aufweist,
dadurch gekennzeichnet, dass
in oder an der Zuführöffnung (26) ein Turbulenzmittel (28) vorgesehen ist.Turbine blade (10),
with an airfoil (12) in which a cavity (18) suitable for cooling the airfoil (12) is provided,
the turbine blade (10) having a feed opening (26) for a coolant that can be supplied to the cavity (18),
characterized in that
in or at the feed opening (26) a turbulence means (28) is provided. Turbinenschaufel (10) nach Anspruch 1,
bei der die Zuführöffnung (26) in einem Befestigungsabschnitt vorgesehen ist.Turbine blade (10) according to claim 1,
in which the supply opening (26) is provided in a fixing section. Turbinenschaufel (10) nach Anspruch 1 oder 2,
bei der das Turbulenzmittel (28) die Zuführöffnung (26) zumindest teilweise überdeckt.Turbine blade (10) according to claim 1 or 2,
in which the turbulence means (28) at least partially covers the feed opening (26). Turbinenschaufel (10) nach Anspruch 1, 2 oder 3,
bei der das Turbulenzmittel (28) als Turbulenzgitter ausgebildet ist.Turbine blade (10) according to claim 1, 2 or 3,
in which the turbulence means (28) is designed as a turbulence grid. Turbinenschaufel (10) nach einem der vorangehenden Ansprüche,
die eine Konvektionskühlung aufweist.Turbine blade (10) according to one of the preceding claims,
which has a convection cooling. Turbinenschaufel (10) nach einem der vorangehenden Ansprüche,
ausgebildet als Laufschaufel oder Leitschaufel einer stationären Gasturbine.Turbine blade (10) according to one of the preceding claims,
formed as a blade or vane of a stationary gas turbine.
EP07015784A 2007-08-10 2007-08-10 Turbine blade having a turbulator at the cooling air inlet Withdrawn EP2025868A1 (en)

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Publication number Priority date Publication date Assignee Title
US8864438B1 (en) * 2013-12-05 2014-10-21 Siemens Energy, Inc. Flow control insert in cooling passage for turbine vane
EP3199760A1 (en) * 2016-01-29 2017-08-02 Siemens Aktiengesellschaft Turbine blade with a throttle element

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US3645243A (en) * 1969-10-27 1972-02-29 Nils C Ohlsson Fuel mixing and vaporizing device for internal combustion engines
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EP0340149A1 (en) * 1988-04-25 1989-11-02 United Technologies Corporation Dirt removal means for air cooled blades
US5779447A (en) * 1997-02-19 1998-07-14 Mitsubishi Heavy Industries, Ltd. Turbine rotor
WO2002057691A1 (en) * 2001-01-16 2002-07-25 Technologies Echangeurs Gaz-Air (T.E.G.A) Inc. Flexible gas-fired heat exchanger system
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US20050084370A1 (en) * 2003-07-29 2005-04-21 Heinz-Jurgen Gross Cooled turbine blade

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE853534C (en) * 1943-02-27 1952-10-27 Maschf Augsburg Nuernberg Ag Air-cooled gas turbine blade
US3645243A (en) * 1969-10-27 1972-02-29 Nils C Ohlsson Fuel mixing and vaporizing device for internal combustion engines
US4550707A (en) * 1983-09-07 1985-11-05 Alain Kervagoret Method for improving the performance of an internal combustion engine, device for implementing the method, and internal combustion engine equipped with said device
EP0160291A1 (en) * 1984-04-30 1985-11-06 Klöckner-Humboldt-Deutz Aktiengesellschaft Cooled turbine blade
EP0340149A1 (en) * 1988-04-25 1989-11-02 United Technologies Corporation Dirt removal means for air cooled blades
US5779447A (en) * 1997-02-19 1998-07-14 Mitsubishi Heavy Industries, Ltd. Turbine rotor
WO2002057691A1 (en) * 2001-01-16 2002-07-25 Technologies Echangeurs Gaz-Air (T.E.G.A) Inc. Flexible gas-fired heat exchanger system
DE10237341A1 (en) * 2002-08-14 2004-02-26 Siemens Ag Finite vortex model for use in fluid flow numerical simulation, especially for modeling unsteady flows, whereby a general roll-off model is used to model the finite edge vortex
US20050084370A1 (en) * 2003-07-29 2005-04-21 Heinz-Jurgen Gross Cooled turbine blade

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8864438B1 (en) * 2013-12-05 2014-10-21 Siemens Energy, Inc. Flow control insert in cooling passage for turbine vane
EP3199760A1 (en) * 2016-01-29 2017-08-02 Siemens Aktiengesellschaft Turbine blade with a throttle element

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