EP2788583B1 - Turbine vane with a throttling element - Google Patents

Turbine vane with a throttling element Download PDF

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Publication number
EP2788583B1
EP2788583B1 EP12808764.0A EP12808764A EP2788583B1 EP 2788583 B1 EP2788583 B1 EP 2788583B1 EP 12808764 A EP12808764 A EP 12808764A EP 2788583 B1 EP2788583 B1 EP 2788583B1
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EP
European Patent Office
Prior art keywords
turbine
throttle element
coolant
vane
guide vane
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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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EP12808764.0A
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German (de)
French (fr)
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EP2788583A1 (en
Inventor
Fathi Ahmad
Nihal Kurt
Mario Nitsche
Marco Schüler
Andreas Varnholt
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Siemens AG
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Siemens AG
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Priority to EP12808764.0A priority Critical patent/EP2788583B1/en
Publication of EP2788583A1 publication Critical patent/EP2788583A1/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
    • F01D5/12—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
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/185—Two-dimensional patterned serpentine-like
    • 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

Definitions

  • the invention relates to a turbine guide vane with an aerodynamically curved airfoil, which has a channel system equipped with a throttle element of channel sections for guiding coolant.
  • Such a turbine blade is for example from the WO 01/36790 A1 known.
  • the throttling of the cooling air consumption of the known turbine blade takes place with the aid of a plug, which is attached from outside into the turbine guide vanes at a reversal point of the cooling duct.
  • the flow-through cross section of the reversal point and thus the flow rate of cooling air can be easily adjusted to predetermined dimensions.
  • casting-related dimensional differences arising from the production of the turbine blade can be compensated by means of the plug, whereby an excessive consumption of cooling air can be avoided.
  • the throttle may also be formed as a cast web extending transversely into the cooling channel. In this case, however, the size of the throttle effect after casting the turbine blade is no longer adjustable.
  • the object of the invention is to provide an alternative turbine vane, in which despite a present at the deflection point opening for the removal of coolant from the turbine blade a subsequent throttling is possible.
  • the invention is based on the finding that, in the case of a turbine guide vane with an aerodynamically curved airfoil, which has a duct system comprising duct sections for guiding coolant, equipped with a throttle element, the throttle element must be designed in such a way that it also permits the removal of coolant. Consequently, it should be equipped with an inflow opening, an outflow opening and a channel connecting the two openings.
  • the throttle element is now not alone for throttling. It is also used as a switch for splitting the coolant into two separate coolant streams. The first of the two coolant sub-streams continues to flow within the turbine vane and is used to cool the airfoil and its trailing edge.
  • the other of the two coolant sub-streams is led out of the turbine vane immediately.
  • the latter is particularly advantageous if at the end at which the coolant is led out of the turbine vane, further gas turbine components are arranged, which must either be cooled or with which the turbine vane (or other components) include gaps in which a hot gas could penetrate the gas turbine.
  • the respective gaps are blocked by outflowing coolant, so that the hot gas intrusion can be safely avoided.
  • the throttle element is inserted into the turbine guide vane and designed cup-shaped with a circumferentially arranged inflow opening for coolant, wherein the pot opening of the throttle element is disposed in the outer surface of the turbine vane.
  • the pot opening represents the outflow opening for the flow into the throttle element coolant partial flow.
  • Another advantage of this design is that with a single component inserted into the cast turbine vane - the throttle element - the distribution of the incoming coolant flow into two partial streams can take place.
  • the distribution of the coolant flow depends on the size of the inflow opening and on the remaining flow cross-section at the throttle point in the duct system.
  • the pot opening may still have a collar whose diameter is larger than the opening into which the throttle element is inserted. This prevents that when inserting the throttle element this fall into the channel sections and thus can be lost.
  • the turbine guide vane is a cast component, which is designed largely or completely monolithically.
  • the turbine vane includes a foot region and a head region for attachment. Both areas are arranged on both sides of the airfoil.
  • the throttle element may be arranged in the foot area and / or in the head area.
  • the root section of the turbine vane is used to attach the turbine vane on an annular vane carrier.
  • the blade area extends radially inward from the foot region, at the inner end of which the head region adjoins.
  • the foot area and head area generally each comprise a so-called platform for the local, radial delimitation of the hot gas channel of the gas turbine.
  • a low-pressure loss of coolant through the throttle element can take place when the inflow opening faces the incoming coolant flow.
  • the cross-sectional area of all through-flow openings is preferably substantially smaller than the cross-sectional area of the inflow opening.
  • the through-flow openings are located opposite the inflow opening and consequently on the side of the throttle element at which the coolant partial stream remaining in the turbine guide vane for the time being flows out. It is even conceivable that such flow openings are located even in throttle element, if this is not for the removal of cooling air - that is not partially tubular, but solid - configured.
  • the throttle element is arranged in that region which is opposite to the feed.
  • a turbine nozzle 10 for a stationary gas turbine is in FIG. 1 shown in perspective.
  • the turbine vane 10 comprises a foot region 12, an aerodynamically curved airfoil 14 and a head region 16, which follow one another along a longitudinal axis 18.
  • the foot region 12 is located radially outward and the head region 16 is located radially inwards.
  • Both foot region 12 and head region 16 each include a platform 20 which forms the local, radial boundary of the annular hot gas path of the gas turbine in the region of the respective turbine guide vane 10.
  • the airfoil 14 extends through the annular hot gas channel 22.
  • Both foot region 12 and head region 16 have on their sides facing away from the hot gas channel 22 a plurality of hooks 24 for attachment.
  • hooks 24 are used to attach the turbine vane 10 to an annular turbine vane carrier, not shown.
  • the hooks located in the head area 16 serve for fastening a so-called U-ring, which is also not shown here.
  • the airfoil 14 comprises a leading edge 17 and a trailing edge 19, between which a pressure-side and a suction-side airfoil wall 40, 42 extend.
  • FIG. 1 shown blade 14 is not completely perspective, but partially shown in longitudinal section.
  • the channel sections 26 of a channel system 28 present in the interior of the blade 14 are shown.
  • the channel system 28 with the channel sections 26 between the two walls 40, 42 (FIG. FIG. 2 ) arranged.
  • the channel system 28 is configured to guide coolant, which can be supplied via an opening 30 of the turbine guide vane 10 arranged on the base side.
  • three parallel juxtaposed channel portions 26 are provided, two of which are fluidically connected to one another at the head-side region via a deflection region 30.
  • the turbine guide vane 10 has an opening 31 into which a throttle element is connected from the outside 32 is inserted.
  • the throttle element 32 may be welded or soldered to the cast turbine vane 10 at points or peripherally.
  • the throttle element 32 is cup-shaped with a cylindrical shell and a bottom of the pot 34, which is a gap forming a the two channel sections 26 separating partition 36 opposite.
  • FIG. 2 shows the turbine vane 10 according to the section II-II in FIG. 1 with the head portion 16 and the hooks 24 arranged thereon in a perspective view.
  • the throttle element 32 inserted from the outside into the turbine guide vane 10 on the outside is shown in perspective and has an inflow opening 37 which faces one (26a) of the channel sections 26. Through the inflow opening 37 through a pot opening 38 can be seen.
  • the pot bottom 34 is the head-side end 39 ( Fig. 1 ) of the partition wall 36 gap forming opposite.
  • the throttle element 32 is formed cylindrically with a constant diameter.
  • the throttle element is also configured cylindrically with sections of different diameters or conical.
  • the inner surfaces of the airfoil walls 40 42 are spaced, so that the incoming from the channel portion 26 a coolant flow, usually cooling air, flows into two flow streams either into the inflow opening 37 or into the gaps between the blade wall inner surfaces or partition wall 36 and throttle element 32 , The latter partial flow then flows through the channel section 26b and remains in the turbine guide vane 10 for the time being.
  • the partial flow flowing into the inflow opening 37 flows out through the pot opening 38 and can be on the hub side be used for cooling the components located there or to block columns against hot gas intake.
  • one or more flow openings 41 can still be provided in the throttle element.
  • the invention relates to a turbine vane 10 with an aerodynamically curved airfoil 14, which has a equipped with a throttle element 32 channel system 28 of channel portions 26 for guiding coolant.
  • the throttle element 32 is designed for removal of coolant.

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

Description

Die Erfindung betrifft eine Turbinenleitschaufel mit einem aerodynamisch gekrümmten Schaufelblatt, welches ein mit einem Drosselelement ausgestattetes Kanalsystem aus Kanalabschnitten zur Führung von Kühlmittel aufweist.The invention relates to a turbine guide vane with an aerodynamically curved airfoil, which has a channel system equipped with a throttle element of channel sections for guiding coolant.

Eine derartige Turbinenschaufel ist beispielsweise aus der WO 01/36790 A1 bekannt. Die Drosselung des Kühlluftverbrauchs der bekannten Turbinenschaufel erfolgt mit Hilfe eines Stopfens, der von außen in die Turbinenleitschaufeln an einer Umkehrstelle des Kühlkanals angebracht wird. In Abhängigkeit der Eindringtiefe des Stopfens lässt sich der durchströmbare Querschnitt der Umkehrstelle und somit die Durchflussmenge an Kühlluft in vorbestimmten Maße einfach einstellen. Hierdurch können gussbedingte Maßdifferenzen, die durch die Herstellung der Turbinenschaufel entstehen, mit Hilfe des Stopfens kompensiert werden, wodurch ein übermäßiger Verbrauch an Kühlluft vermieden werden kann.Such a turbine blade is for example from the WO 01/36790 A1 known. The throttling of the cooling air consumption of the known turbine blade takes place with the aid of a plug, which is attached from outside into the turbine guide vanes at a reversal point of the cooling duct. Depending on the penetration depth of the plug, the flow-through cross section of the reversal point and thus the flow rate of cooling air can be easily adjusted to predetermined dimensions. As a result, casting-related dimensional differences arising from the production of the turbine blade, can be compensated by means of the plug, whereby an excessive consumption of cooling air can be avoided.

Gemäß der WO 2009/118245 A1 kann die Drossel auch als in dem Kühlkanal quer hineinragender gegossener Steg ausgebildet sein. In diesem Fall ist jedoch Größe der Drosselwirkung nach dem Gießen der Turbinenschaufel nicht mehr einstellbar.According to the WO 2009/118245 A1 For example, the throttle may also be formed as a cast web extending transversely into the cooling channel. In this case, however, the size of the throttle effect after casting the turbine blade is no longer adjustable.

Weiter ist bekannt, dass anstelle einer Drossel an der Umlenkstelle auch eine Öffnung zu Entnahme von Kühlluft angesiedelt sein kann. In diesem Falle ist die Verwendung einer Drossel an dieser Position bisher nicht möglich.It is also known that instead of a throttle at the deflection point and an opening for removal of cooling air can be located. In this case, the use of a throttle at this position is not possible.

Aufgabe der Erfindung ist es, eine alternative Turbinenleitschaufel bereitzustellen, bei der trotz einer an der Umlenkstelle vorhandenen Öffnung zum Herausführen von Kühlmittel aus der Turbinenschaufel eine nachträgliche Drosselung möglich ist.The object of the invention is to provide an alternative turbine vane, in which despite a present at the deflection point opening for the removal of coolant from the turbine blade a subsequent throttling is possible.

Die auf die Turbinenleitschaufel gerichtete Aufgabe wird mit einer solchen gemäß den Merkmalen des Anspruchs 1 gelöst. Vorteilhafte Ausgestaltungen sind in den Unteransprüchen angegeben. Deren Merkmale können in beliebiger Weise miteinander kombiniert werden.The object directed to the turbine guide vane is achieved with such according to the features of claim 1. Advantageous embodiments are specified in the subclaims. Their features can be combined in any way.

Der Erfindung liegt die Erkenntnis zu Grunde, dass bei einer Turbinenleitschaufel mit einem aerodynamisch gekrümmten Schaufelblatt, welches ein mit einem Drosselelement ausgestattetes Kanalsystem aus Kanalabschnitten zur Führung von Kühlmitteln aufweist, das Drosselelement so auszugestalten ist, dass dieses auch die Entnahme von Kühlmittel ermöglicht. Folglich sollte es mit einer Einströmöffnung, einer Ausströmöffnung sowie einem die beiden Öffnungen verbindenden Kanal ausgestattet sein. Insofern dient das Drosselelement nunmehr nicht alleine zur Drosselung. Es wird gleichzeitig auch als Weiche zum Aufteilen des Kühlmittels in zwei getrennte Kühlmittelteilströme verwendet. Der erste der beiden Kühlmittelteilströme fließt innerhalb der Turbinenleitschaufel weiter und wird zur Kühlung des Schaufelblattes und deren Hinterkante eingesetzt. Der andere der beiden Kühlmittelteilströme wird aus der Turbinenleitschaufel unmittelbar herausgeführt. Letzteres ist insbesondere dann von Vorteil, wenn an demjenigen Ende, an dem das Kühlmittel aus der Turbinenleitschaufel herausgeführt wird, weitere Gasturbinenkomponenten angeordnet sind, die entweder gekühlt werden müssen oder mit denen die Turbinenleitschaufel (oder auch andere Bauteile) Spalte einschließen, in die ein Heißgas der Gasturbine eindringen könnte. Durch das Bereitstellen des Kühlmittels an diesen Gasturbinenkomponenten werden die betreffenden Spalte durch ausströmendes Kühlmittel gesperrt, so dass das Heißgaseindringen sicher vermieden werden kann. Sowohl die Kühlung der weiteren Gasturbinenkomponenten als auch das Sperren der Spalte gegen Heißgaseinzug verhindert eine vorzeitige Alterung der Bauteile aufgrund unzulässig hoher Materialtemperaturen und verlängert somit deren Lebensdauer.The invention is based on the finding that, in the case of a turbine guide vane with an aerodynamically curved airfoil, which has a duct system comprising duct sections for guiding coolant, equipped with a throttle element, the throttle element must be designed in such a way that it also permits the removal of coolant. Consequently, it should be equipped with an inflow opening, an outflow opening and a channel connecting the two openings. In this respect, the throttle element is now not alone for throttling. It is also used as a switch for splitting the coolant into two separate coolant streams. The first of the two coolant sub-streams continues to flow within the turbine vane and is used to cool the airfoil and its trailing edge. The other of the two coolant sub-streams is led out of the turbine vane immediately. The latter is particularly advantageous if at the end at which the coolant is led out of the turbine vane, further gas turbine components are arranged, which must either be cooled or with which the turbine vane (or other components) include gaps in which a hot gas could penetrate the gas turbine. By providing the coolant to these gas turbine components, the respective gaps are blocked by outflowing coolant, so that the hot gas intrusion can be safely avoided. Both the cooling of the other gas turbine components as well as the locking of the column against hot gas inlet prevents premature aging of the components due to inadmissibly high material temperatures and thus extends their life.

Gemäß der Erfindung ist das Drosselelement in die Turbinenleitschaufel eingesetzt und topfförmig mit einer umfangsseitig angeordneten Einströmöffnung für Kühlmittel ausgestaltet, wobei die Topföffnung des Drosselelements in der Außenfläche der Turbinenleitschaufel angeordnet ist. In diesem Fall stellt die Topföffnung die Ausströmöffnung für den in das Drosselelement einfließenden Kühlmittelteilstrom dar. Mit Hilfe dieser Ausgestaltung ist eine vergleichsweise einfache Konstruktion einer Strömungsweiche bereitgestellt, wobei der andere der beiden Kühlmittelteilströme dadurch erzeugt wird, dass die ankommende Kühlmittelströmung an dem Drosselelement - genauer gesagt an der Einströmöffnung des Drosselelements - vorbeiströmt und weiter in die stromab liegenden Kanalabschnitte des Kanalsystems. Ein weiterer Vorteil dieser Konstruktion liegt darin, dass mit einem einzigen in die gegossene Turbinenleitschaufel eingesetzten Bauteil - dem Drosselelement - die Aufteilung der ankommenden Kühlmittelströmung in zwei Teilströme erfolgen kann. Die Aufteilung der Kühlmittelströmung hängt von der Größe der Einströmöffnung und von dem verbliebenen Durchströmungsquerschnitt an der Drosselstelle im Kanalsystem ab.According to the invention, the throttle element is inserted into the turbine guide vane and designed cup-shaped with a circumferentially arranged inflow opening for coolant, wherein the pot opening of the throttle element is disposed in the outer surface of the turbine vane. In this case, the pot opening represents the outflow opening for the flow into the throttle element coolant partial flow. With the aid of this embodiment, a comparatively simple construction of a flow switch is provided, wherein the other of the two partial coolant streams is generated by the incoming coolant flow to the throttle element - more precisely at the inlet opening of the throttle element - flows past and further into the downstream channel sections of the channel system. Another advantage of this design is that with a single component inserted into the cast turbine vane - the throttle element - the distribution of the incoming coolant flow into two partial streams can take place. The distribution of the coolant flow depends on the size of the inflow opening and on the remaining flow cross-section at the throttle point in the duct system.

Diese Ausgestaltung hat den weiteren Vorteil, dass bereits im Feld existierende betriebsbeanspruchte Turbinenleitschaufeln ggf. nachträglich mit einer derartigen Drosselvorrichtung ausgestattet werden können, ohne die Turbinenleitschaufeln bearbeitet, modifiziert bzw. dafür vorbereitet werden müssen.This refinement has the further advantage that turbine operating vanes which are already operational in the field can optionally be retrofitted with such a throttle device without the turbine vanes having to be machined, modified or prepared for this purpose.

Zudem kann die Topföffnung noch einen Kragen aufweisen, dessen Durchmesser größer ist als die Öffnung, in die das Drosselelement eingesetzt ist. Dies verhindert, dass beim Einsetzten des Drosselelements dieses in die Kanalabschnitte fallen und somit verloren gehen kann.In addition, the pot opening may still have a collar whose diameter is larger than the opening into which the throttle element is inserted. This prevents that when inserting the throttle element this fall into the channel sections and thus can be lost.

Üblicher Weise handelt es sich bei der Turbinenleitschaufel um ein Gussbauteil, welches weitestgehend oder vollständig monolithisch ausgestaltet ist. Zweckmäßiger Weise umfasst die Turbinenleitschaufel einen Fußbereich und einen Kopfbereich zur Befestigung. Beide Bereiche sind am Schaufelblatt beidendseitig angeordnet. Das Drosselelement kann im Fußbereich und/oder im Kopfbereich angeordnet sein. Der Fußbereich der Turbinenleitschaufel dient zur Befestigung der Turbinenleitschaufel an einem ringförmigen Leitschaufelträger. Vom Fußbereich erstreckt sich nach radial innen das Schaufelblatt, an dessen innerem Ende der Kopfbereich anschließt. Fußbereich und Kopfbereich umfassen jeweils in der Regel eine sogenannte Plattform zur lokalen, radialen Begrenzung des Heißgaskanals der Gasturbine. An der dem Heißgaskanal abgewandten Seite der inneren Plattform sind Haken vorgesehen, welche Teil des Kopfbereichs sind und an welchem in der Regel ein sogenannter U-Ring befestigt wird. Mit diesem werden die Turbinenleitschaufeln oder auch Turbinenleitschaufelsegmente eines Leitschaufelkranzes der Gasturbine miteinander gekoppelt. Da diese U-Ringe gegebenenfalls gekühlt werden müssen und die von diesen Komponenten mit dem Rotor gebildeten Spalte gegen ein Eindringen von Heißgas gesperrt werden müssen, ist es von besonderem Vorteil, wenn das üblicher Weise durch Turbinenleitschaufel geführte Kühlmittel am die kopfseitigen Ende der Turbinenleitschaufel durch das Drosselelement wieder entnommen und dort nabenseitig verwendet werden kann.Usually, the turbine guide vane is a cast component, which is designed largely or completely monolithically. Conveniently, the turbine vane includes a foot region and a head region for attachment. Both areas are arranged on both sides of the airfoil. The throttle element may be arranged in the foot area and / or in the head area. The root section of the turbine vane is used to attach the turbine vane on an annular vane carrier. The blade area extends radially inward from the foot region, at the inner end of which the head region adjoins. The foot area and head area generally each comprise a so-called platform for the local, radial delimitation of the hot gas channel of the gas turbine. On the side facing away from the hot gas channel side of the inner platform hooks are provided, which are part of the head area and on which usually a so-called U-ring is attached. With this, the turbine vanes or turbine vane segments of a vane ring of the gas turbine are coupled together. Since these U-rings may need to be cooled and the gaps formed by these components with the rotor must be blocked against ingress of hot gas, it is particularly advantageous if the usual manner guided by turbine vane coolant at the head end of the turbine vane by the Throttle again removed and used there hub side.

Weiter vorteilhaft ist diejenige Weiterbildung, bei der im Schaufelblatt zwei annähernd parallele, zueinander angeordnete Kühlkanalabschnitte über einen fußseitig oder kopfseitig angeordneten Umlenkbereich strömungstechnisch miteinander verbunden sind und das Drosselelement quer in Bezug auf die lokale Durchströmungsrichtung des Kühlmittels im Umlenkbereich in diesen hineinragt. In diesem Falle liegt zwischen den beiden parallel zueinander angeordneten Kanalabschnitten eine Trennwand vor, die am Umlenkbereich endet, so dass das Drosselelement je nach Eindringtiefe näher oder weiter entfernt von dem Ende dieser Trennwand enden kann. Insofern ist die besagte Trennwand Teil der Drosselvorrichtung, so dass bereits in einer Turbinenleitschaufel vorhandene Elemente eine weitere Funktion übernehmen, für die sie ursprünglich nicht vorgesehen waren, wenn das Drosselelement nachträglich eingebaut wird.Further advantageous is that further development in which two approximately parallel, mutually arranged cooling duct sections in the airfoil are fluidly connected to each other via a foot-side or head-side deflection region and the throttle element protrudes transversely with respect to the local flow direction of the coolant in the deflection region in this. In this case, there is a partition between the two mutually parallel channel sections, which ends at the deflection, so that the throttle element depending on the penetration depth can be closer or further away from the end of this partition. In this respect, the said partition is part of the throttle device, so that already existing in a turbine vane elements assume a further function for which they were not initially provided when the throttle element is retrofitted.

Eine druckverlustarme Entnahme von Kühlmittel durch das Drosselelement kann erfolgen, wenn die Einströmöffnung der ankommenden Kühlmittelströmung zugewandt ist.A low-pressure loss of coolant through the throttle element can take place when the inflow opening faces the incoming coolant flow.

Um so genannte Totwassergebiete in der Kühlmittelströmung bzw. im Kanalsystem unmittelbar stromab des Drosselelements und damit schlechter gekühlte Schaufelwände zu vermeiden, ist vorzugsweise vorgesehen, dass zumindest eine weitere umfangsseitig angeordnete Durchströmungsöffnung im Drosselelement vorgesehen ist. Dabei ist die Querschnittsfläche aller Durchströmungsöffnungen vorzugsweise wesentlich kleiner als die Querschnittsfläche der Einströmöffnung. Vorzugsweise liegen die Durchströmungsöffnungen gegenüber der Einströmöffnung und folglich an derjenigen Seite des Drosselelements, an der der in der Turbinenleitschaufel vorerst verbleibende Kühlmittelteilstrom abströmt. Es ist sogar denkbar, dass derartige Durchströmungsöffnungen selbst dann in Drosselelement angesiedelt sind, wenn dieses nicht zur Entnahmen von Kühlluft - also nicht teilweise röhrförmig, sondern massiv - ausgestaltet ist.In order to avoid so-called dead water areas in the coolant flow or in the channel system immediately downstream of the throttle element and thus less cooled blade walls, it is preferably provided that at least one further circumferentially arranged throughflow opening is provided in the throttle element. In this case, the cross-sectional area of all through-flow openings is preferably substantially smaller than the cross-sectional area of the inflow opening. Preferably, the through-flow openings are located opposite the inflow opening and consequently on the side of the throttle element at which the coolant partial stream remaining in the turbine guide vane for the time being flows out. It is even conceivable that such flow openings are located even in throttle element, if this is not for the removal of cooling air - that is not partially tubular, but solid - configured.

Für die Erfindung ist es unwesentlich, ob die Zuführung von Kühlmittel dabei fußseitig oder kopfseitig erfolgt. Vorzugsweise ist jedoch das Drosselelement in demjenigen Bereich angeordnet, welcher der Zuführung gegenüberliegt.For the invention, it is immaterial whether the supply of coolant takes place on the foot side or on the head side. Preferably, however, the throttle element is arranged in that region which is opposite to the feed.

Weitere Vorteile und Merkmale der Erfindung werden anhand der nachfolgenden Zeichnung näher erläutert. Es zeigen:

Figur 1
eine Turbinenleitschaufel in perspektivischer Darstellung mit einem aufgeschnittenen Schaufelblatt und einem fußseitig eingesetzten Drosselelement und
Figur 2
einen nabenseitigen Querschnitt durch das Schaufelblatt der Turbinenleitschaufel mit dem darin sitzenden Drosselelement.
Further advantages and features of the invention will be explained in more detail with reference to the following drawing. Show it:
FIG. 1
a turbine vane in a perspective view with a cut open blade and a throttle element used on the foot side and
FIG. 2
a hub-side cross section through the airfoil of the turbine vane with the seated therein throttle element.

Eine Turbinenleitschaufel 10 für eine stationäre Gasturbine ist in Figur 1 perspektivisch dargestellt. Die Turbinenleitschaufel 10 umfasst einen Fußbereich 12, ein aerodynamisch gekrümmtes Schaufelblatt 14 sowie einen Kopfbereich 16, die entlang einer Längachse 18 aufeinander folgen. In der Einbaulage in einer Gasturbine ist der Fußbereich 12 radial außen angesiedelt und der Kopfbereich 16 radial innen. Sowohl Fußbereich 12 als auch Kopfbereich 16 umfassen jeweils eine Plattform 20, die die lokale, radiale Begrenzung des ringförmigen Heißgaspfads der Gasturbine im Bereich der betreffenden Turbinenleitschaufel 10 bilden. Insofern erstreckt sich das Schaufelblatt 14 durch den ringförmigen Heißgaskanal 22. Sowohl Fußbereich 12 als auch Kopfbereich 16 haben an ihren dem Heißgaskanal 22 abgewandten Seiten mehrere Haken 24 zur Befestigung. Die am Fußbereich 12 vorgesehenen Haken 24 dienen zur Befestigung der Turbinenleitschaufel 10 an einem nicht dargestellten ringförmigen Turbinenleitschaufelträger. Dagegen dienen die im Kopfbereich 16 angesiedelten Haken zur Befestigung eines sogenannten U-Rings, welcher hier auch nicht weiter dargestellt ist.A turbine nozzle 10 for a stationary gas turbine is in FIG. 1 shown in perspective. The turbine vane 10 comprises a foot region 12, an aerodynamically curved airfoil 14 and a head region 16, which follow one another along a longitudinal axis 18. In the installation position in a gas turbine, the foot region 12 is located radially outward and the head region 16 is located radially inwards. Both foot region 12 and head region 16 each include a platform 20 which forms the local, radial boundary of the annular hot gas path of the gas turbine in the region of the respective turbine guide vane 10. In this respect, the airfoil 14 extends through the annular hot gas channel 22. Both foot region 12 and head region 16 have on their sides facing away from the hot gas channel 22 a plurality of hooks 24 for attachment. The provided on the foot portion 12 hooks 24 are used to attach the turbine vane 10 to an annular turbine vane carrier, not shown. In contrast, the hooks located in the head area 16 serve for fastening a so-called U-ring, which is also not shown here.

Das Schaufelblatt 14 umfasst eine Anströmkante 17 und eine Hinterkante 19, zwischen denen sich eine druckseitige und eine saugseitige Schaufelblattwand 40, 42 erstrecken. Das in Figur 1 dargestellte Schaufelblatt 14 ist nicht vollständig perspektivisch, sondern teilweise im Längsschnitt gezeigt. Dadurch sind die im Inneren des Schaufelblatts 14 vorhandenen Kanalabschnitte 26 eines Kanalsystems 28 dargestellt. Somit ist das Kanalsystem 28 mit den Kanalabschnitten 26 zwischen den beiden Wänden 40, 42 (FIG 2) angeordnet. Das Kanalsystem 28 ist zur Führung von Kühlmittel ausgestaltet, welche über eine fußseitig angeordnete Öffnung 30 der Turbinenleitschaufel 10 zuführbar ist. Im gezeigten Ausführungsbeispiel sind drei parallel nebeneinander angeordnete Kanalabschnitte 26 vorgesehen, von denen zwei am kopfseitigen Bereich über einen Umlenkbereich 30 strömungstechnisch miteinander verbunden sind. In diesem Umlenkbereich 30 weist die Turbinenleitschaufel 10 eine Öffnung 31 auf, in die von außen ein Drosselelement 32 eingesteckt ist. Um die Turbinenleitschaufel 10 gegen den Verlust des Drosselelements zu sichern, kann das Drosselelement 32 punktuell oder auch umlaufend mit der gegossenen Turbinenleitschaufel 10 verschweißt oder verlötet sein.The airfoil 14 comprises a leading edge 17 and a trailing edge 19, between which a pressure-side and a suction-side airfoil wall 40, 42 extend. This in FIG. 1 shown blade 14 is not completely perspective, but partially shown in longitudinal section. As a result, the channel sections 26 of a channel system 28 present in the interior of the blade 14 are shown. Thus, the channel system 28 with the channel sections 26 between the two walls 40, 42 (FIG. FIG. 2 ) arranged. The channel system 28 is configured to guide coolant, which can be supplied via an opening 30 of the turbine guide vane 10 arranged on the base side. In the illustrated embodiment, three parallel juxtaposed channel portions 26 are provided, two of which are fluidically connected to one another at the head-side region via a deflection region 30. In this deflection region 30, the turbine guide vane 10 has an opening 31 into which a throttle element is connected from the outside 32 is inserted. In order to secure the turbine vane 10 against the loss of the throttle element, the throttle element 32 may be welded or soldered to the cast turbine vane 10 at points or peripherally.

Das Drosselelement 32 ist topfförmig ausgebildet mit einem zylindrischem Mantel und einem Topfboden 34, welcher spaltbildend einer die beiden Kanalabschnitte 26 trennenden Trennwand 36 gegenüberliegt.The throttle element 32 is cup-shaped with a cylindrical shell and a bottom of the pot 34, which is a gap forming a the two channel sections 26 separating partition 36 opposite.

Identische Merkmale sind in allen Figuren mit den gleichen Bezugszeichen versehen. Somit zeigt Figur 2 die Turbinenleitschaufel 10 gemäß dem Schnitt II-II in Figur 1 mit dem Kopfbereich 16 und den daran angeordneten Haken 24 in perspektivischer Darstellung. Das von außen kopfseitig in die Turbinenleitschaufel 10 eingesetzte Drosselelement 32 ist perspektivisch dargestellt und weist eine Einströmöffnung 37 auf, die einem (26a) der Kanalabschnitte 26 zugewandt ist. Durch die Einströmöffnung 37 hindurch ist eine Topföffnung 38 erkennbar. Der Topfboden 34 liegt dem kopfseitigen Ende 39 (Fig. 1) der Trennwand 36 spaltbildend gegenüber.Identical features are provided with the same reference numerals in all figures. Thus shows FIG. 2 the turbine vane 10 according to the section II-II in FIG. 1 with the head portion 16 and the hooks 24 arranged thereon in a perspective view. The throttle element 32 inserted from the outside into the turbine guide vane 10 on the outside is shown in perspective and has an inflow opening 37 which faces one (26a) of the channel sections 26. Through the inflow opening 37 through a pot opening 38 can be seen. The pot bottom 34 is the head-side end 39 ( Fig. 1 ) of the partition wall 36 gap forming opposite.

Im gezeigten Ausführungsbeispiel ist das Drosselelement 32 zylindrisch mit einem konstanten Durchmesser ausgebildet. Selbstverständlich ist es möglich, dass das Drosselelement auch zylindrisch mit abschnittsweise unterschiedlichen Durchmessern oder auch konisch ausgestaltet ist.In the illustrated embodiment, the throttle element 32 is formed cylindrically with a constant diameter. Of course, it is possible that the throttle element is also configured cylindrically with sections of different diameters or conical.

Seitlich des Drosselelements 32 sind die Innenflächen der Schaufelblattwände 40 42 beabstandet, so dass die aus dem Kanalabschnitt 26a ankommende Kühlmittelströmung, zumeist Kühlluft, zur Aufteilung in zwei Kühlluftströme entweder in die Einströmöffnung 37 oder in die Spalte zwischen Schaufelwandinnenflächen bzw. Trennwand 36 und Drosselelement 32 einströmt. Letzterer Teilstrom strömt anschließend durch den Kanalabschnitt 26b und verbleibt vorerst in der Turbinenleitschaufel 10. Der in die Einströmöffnung 37 einströmende Teilstrom strömt durch die Topföffnung 38 heraus und kann nabenseitig zur Kühlung der dort angesiedelten Bauteile oder zur Sperrung von Spalten gegen Heißgaseinzug eingesetzt werden.Laterally of the throttle element 32, the inner surfaces of the airfoil walls 40 42 are spaced, so that the incoming from the channel portion 26 a coolant flow, usually cooling air, flows into two flow streams either into the inflow opening 37 or into the gaps between the blade wall inner surfaces or partition wall 36 and throttle element 32 , The latter partial flow then flows through the channel section 26b and remains in the turbine guide vane 10 for the time being. The partial flow flowing into the inflow opening 37 flows out through the pot opening 38 and can be on the hub side be used for cooling the components located there or to block columns against hot gas intake.

Zur Vermeidung von Kühlmittel-Strömungsgebieten mit niedriger Strömungsgeschwindigkeit können noch eine oder mehrere Durchströmungsöffnungen 41 im Drosselelement vorgesehen sein.To avoid coolant flow areas with a low flow velocity, one or more flow openings 41 can still be provided in the throttle element.

Von besonderem Vorteil ist, dass mit Hilfe des Drosselelements 32 die gesamte Kühlluftmenge der Turbinenleitschaufel 10 einerseits und auch das Verhältnis der Aufteilung der beiden Kühlmittelteilströme andererseits eingestellt werden kann, selbst nachdem die Turbinenleitschaufel 10 gegossen wurde. Durch die Einsparung von Kühlluft weist eine mit den erfindungsgemäßen Turbinenleitschaufeln 10 ausgestattete Gasturbine einen verbesserten Wirkungsgrad auf. Gleichzeitig ist es möglich, bereits betriebsbeanspruchte Turbinenleitschaufeln 10 nachträglich mit einem Drosselelement 32 auszustatten, ohne das diese grundlegend bearbeitet werden muss, sofern die Turbinenleitschaufel 10 eine Öffnung zur Entnahme von in ihr strömendem Kühlmittel aufweist. Auch ist es möglich, neuwertige, jedoch nicht spezifikationskonforme Turbinenleitschaufeln 10 mit Hilfe des Drosselelements 32 für den Einsatz in einer Gasturbine zu ertüchtigen. Damit kann die Ausschussrate an Bauteilen vermindert werden, was Kosten minimiert.It is of particular advantage that with the aid of the throttle element 32, the total amount of cooling air of the turbine vane 10 on the one hand and the ratio of the division of the two coolant sub-streams on the other hand can be adjusted, even after the turbine vane 10 has been poured. As a result of the saving of cooling air, a gas turbine equipped with the turbine guide vanes 10 according to the invention has an improved efficiency. At the same time, it is possible to subsequently equip turbine blades 10 already in use with a throttle element 32 without having to fundamentally process them, provided that the turbine guide blade 10 has an opening for removing coolant flowing in it. It is also possible to retrofit as new, but not compliant turbine vanes 10 by means of the throttle element 32 for use in a gas turbine. Thus, the rejection rate of components can be reduced, which minimizes costs.

Insgesamt betrifft die Erfindung eine Turbinenleitschaufel 10 mit einem aerodynamisch gekrümmten Schaufelblatt 14, welches ein mit einem Drosselelement 32 ausgestattetes Kanalsystem 28 aus Kanalabschnitten 26 zur Führung von Kühlmittel aufweist. Um eine alternative Turbinenleitschaufel 10 bereitzustellen, bei der sowohl ein im Inneren strömender Kühlmittelteilstrom als auch ein aus der Turbinenleitschaufel 10 wieder herausgeführter Kühlmittelteilstrom einstellbar ist, wird vorgeschlagen, dass das Drosselelement 32 zur Entnahme von Kühlmittel ausgestaltet ist.Overall, the invention relates to a turbine vane 10 with an aerodynamically curved airfoil 14, which has a equipped with a throttle element 32 channel system 28 of channel portions 26 for guiding coolant. In order to provide an alternative turbine vane 10, in which both an internally flowing coolant partial stream and a recirculated from the turbine vane 10 partial flow of coolant is adjustable, it is proposed that the throttle element 32 is designed for removal of coolant.

Claims (5)

  1. Turbine guide vane (10) with an aerodynamically curved vane airfoil (14),
    which has a system of channels (28) comprising channel sections (26) for conducting coolant and equipped with a throttle element (32),
    characterized in that
    the throttle element (32) is fitted in the turbine guide vane (10) and is designed for the removal of coolant and also in the form of a cup with a circumferentially arranged inflow opening (37) for coolant, the cup opening (38) of the throttle element (32) being arranged in the outer surface of the turbine guide vane (10).
  2. Turbine guide vane (10) according to Claim 1,
    which comprises a root region (12) and a head region (16) for fastening, which regions are arranged at the two ends of the vane airfoil (14) and the throttle element (32) is arranged in the root region (12) and/or in the head region (16) .
  3. The turbine guide vane (10) according to Claim 1 or 2,
    in which two channel sections (26) arranged approximately parallel to one another are connected to one another in terms of flow in the vane airfoil (14) by way of a deflecting region (30) arranged on the root side or on the head side and the throttle element (32) protrudes transversely into the deflecting region (30).
  4. Turbine guide vane (10) according to one of Claims 1,2 or 3,
    in which the inflow opening (37) is facing the incoming coolant flow.
  5. Turbine guide vane (10) according to one of claims 1, 2, 3 or 4,
    in which at least one throughflow opening is provided.
EP12808764.0A 2012-02-14 2012-12-12 Turbine vane with a throttling element Active EP2788583B1 (en)

Priority Applications (1)

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EP12155394.5A EP2628900A1 (en) 2012-02-14 2012-02-14 Turbine vane with a throttling element
PCT/EP2012/075256 WO2013120560A1 (en) 2012-02-14 2012-12-12 Turbine guide vane with a throttle element
EP12808764.0A EP2788583B1 (en) 2012-02-14 2012-12-12 Turbine vane with a throttling element

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EP (2) EP2628900A1 (en)
JP (1) JP6005764B2 (en)
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Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104481927A (en) * 2014-12-12 2015-04-01 常州环能涡轮动力股份有限公司 Flow guiding ring with double-faced centrifugal pressure wheel for micro turbine jet engine
EP3147455A1 (en) 2015-09-23 2017-03-29 Siemens Aktiengesellschaft Turbine vane with a throttling arrangement
EP3199760A1 (en) * 2016-01-29 2017-08-02 Siemens Aktiengesellschaft Turbine blade with a throttle element
CN109374275A (en) * 2018-11-13 2019-02-22 霍山嘉远智能制造有限公司 A kind of inner flow passage detecting tool of turborotor
KR102207971B1 (en) * 2019-06-21 2021-01-26 두산중공업 주식회사 Vane for turbine, turbine including the same
CN112539086A (en) * 2020-10-27 2021-03-23 哈尔滨广瀚燃气轮机有限公司 Sectional rotary supercharging device for cooling air of turbine rotor blade

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2468727A1 (en) * 1979-10-26 1981-05-08 Snecma IMPROVEMENT TO COOLED TURBINE AUBES
US4526551A (en) * 1980-05-30 1985-07-02 Champion Spark Plug Company Production of electrodes
JPS57153903A (en) 1981-03-20 1982-09-22 Hitachi Ltd Cooling structure for turbing blade
US4526512A (en) * 1983-03-28 1985-07-02 General Electric Co. Cooling flow control device for turbine blades
DE3603350A1 (en) 1986-02-04 1987-08-06 Walter Prof Dipl Ph Sibbertsen METHOD FOR COOLING THERMALLY LOADED COMPONENTS OF FLOWING MACHINES, DEVICE FOR CARRYING OUT THE METHOD AND TRAINING THERMALLY LOADED BLADES
US4666368A (en) 1986-05-01 1987-05-19 General Electric Company Swirl nozzle for a cooling system in gas turbine engines
JPH09303103A (en) * 1996-05-16 1997-11-25 Toshiba Corp Closed loop cooling type turbine rotor blade
JPH10306701A (en) 1997-05-08 1998-11-17 Toshiba Corp Turbine bucket and its manufacture
RU2159335C1 (en) 1999-04-28 2000-11-20 Открытое акционерное общество "А.Люлька-Сатурн" Method of cooling turbine wheel rotor of multimode turbojet engine
EP1099825A1 (en) * 1999-11-12 2001-05-16 Siemens Aktiengesellschaft Turbine blade and production method therefor
US7185662B2 (en) * 2003-11-14 2007-03-06 United Technologies Corporation Methods of preparing, cleaning and repairing article and article repaired
EP1789654B1 (en) * 2004-09-16 2017-08-23 General Electric Technology GmbH Turbine engine vane with fluid cooled shroud
US8016547B2 (en) * 2008-01-22 2011-09-13 United Technologies Corporation Radial inner diameter metering plate
WO2009118245A1 (en) * 2008-03-28 2009-10-01 Alstom Technology Ltd Guide vane for a gas turbine and gas turbine comprising such a guide vane
RU2387846C1 (en) * 2008-10-29 2010-04-27 Открытое акционерное общество "Научно-производственное объединение "Сатурн" (ОАО "НПО "Сатурн") Method to cool by-pass gas turbine engine vanes and device to this end

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RU2014136803A (en) 2016-04-10
EP2788583A1 (en) 2014-10-15
US9856738B2 (en) 2018-01-02
US20140377058A1 (en) 2014-12-25
CN104126054A (en) 2014-10-29
IN2014DN05979A (en) 2015-06-26
CN104126054B (en) 2016-02-03
EP2628900A1 (en) 2013-08-21
JP6005764B2 (en) 2016-10-12
JP2015507129A (en) 2015-03-05
RU2615091C2 (en) 2017-04-03

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