EP2788583A1 - Turbine guide vane with a throttle element - Google Patents

Turbine guide vane with a throttle element

Info

Publication number
EP2788583A1
EP2788583A1 EP12808764.0A EP12808764A EP2788583A1 EP 2788583 A1 EP2788583 A1 EP 2788583A1 EP 12808764 A EP12808764 A EP 12808764A EP 2788583 A1 EP2788583 A1 EP 2788583A1
Authority
EP
European Patent Office
Prior art keywords
throttle element
turbine
coolant
guide vane
vane
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP12808764.0A
Other languages
German (de)
French (fr)
Other versions
EP2788583B1 (en
Inventor
Fathi Ahmad
Nihal Kurt
Mario Nitsche
Marco Schüler
Andreas Varnholt
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP12808764.0A priority Critical patent/EP2788583B1/en
Publication of EP2788583A1 publication Critical patent/EP2788583A1/en
Application granted granted Critical
Publication of EP2788583B1 publication Critical patent/EP2788583B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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 with an aerodynamically curved blade which has a throttle element equipped with a channel system Kanalabschnit ⁇ th for guiding of coolant.
  • Such a turbine blade is known for example from WO 01/36790 AI.
  • the throttling of the cooling air consumption of the known turbine blade takes place with the aid of a stop ⁇ fens, which is attached from the outside in the Turbinenleitschaufein at a reversal point of the cooling channel.
  • the flow-through cross section of the reversal point and thus the flow rate of cooling air can be easily adjusted to predetermined dimensions. This allows cast-related differences in measurement resulting from the production of the turbine blade, with the help of the plug are com ⁇ compensated, thus, excessive consumption can be avoided in cooling air.
  • the object of the invention is to provide an alternative Turbinenleit- schaufei, in which despite a present at the deflection point opening for the removal of coolant from the turbine blade a subsequent throttling is mög ⁇ Lich.
  • the object directed to the turbine guide vane is achieved with such according to the features of claim 1.
  • Advantageous embodiments are disclosed in the subclaims. given. Their features can be combined in any way.
  • the invention is based on the finding that in a turbine vane with an aerodynamically curved
  • Airfoil which has a channel system equipped with a throttle element ⁇ out of channel sections for guiding coolant
  • the throttle element is to be designed so that this also allows 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 dividing the coolant into two separate partial coolant streams. The first of the two coolant ⁇ substreams continues to flow within the turbine vane and is used to cool the airfoil and the rear edge ⁇ used. The other of the two coolant sub-streams is led out of the turbine vane immediately.
  • the throttle element is inserted into the turbine guide vane and designed in the shape of a pot with a circumferentially arranged inlet opening for coolant, wherein the pot opening of the throttle selelements in the outer surface of the turbine vane is arranged ⁇ .
  • a comparatively simple construction of a flow ⁇ soft wherein the other of the twodemit ⁇ telteilströme is generated by the fact that the incoming coolant ⁇ mean flow to the throttle element - more precisely at the inflow opening of the throttle element - flows past and further into the downstream channel sections of the channel system.
  • a further advantage of this construction is that with a single component placed in the cast turbine guide vane , the throttle element, the distribution of the incoming coolant flow into two partial flows can take place. The distribution of the coolant flow depends on the
  • This embodiment has the further advantage that already existing in the field Radio tapete Turbinenleitschaufein can optionally be retrofitted with such a throttle device without the Turbinenleitschaufein edited, modified or prepared for it.
  • 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 the throttle element is inserted, it can fall into the channel sections and thus 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 guide vane is used to fasten the turbine guide schaufei 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 Dros ⁇ selelement can take place when the inflow opening faces the incoming coolant flow.
  • at least one further circumferentially arranged throughflow opening is provided in the throttle element.
  • the cross-sectional area of all through ⁇ preferably flow openings substantially smaller than the cross-sectional area of the inflow opening.
  • the through flow openings are located opposite the inlet opening and therefore on that side of the throttle element at which the initially remaining in the turbine vane coolant ⁇ partial stream flows. It is even conceivable that such through-flow openings are located even in throttle element, if this is not designed for the removal of cooling air - that is, not partially tubular, but solid.
  • the choke member in that region is preferential ⁇ as ordered arrival, which is opposite to the feeder.
  • FIG. 1 shows a turbine guide vane in perspective
  • Airfoil of the turbine vane with the seated therein throttle element A turbine nozzle 10 for a stationary gas turbine is shown in perspective in FIG.
  • the turbine guide 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 ⁇ area 12 and head portion 16 each include a platform 20 forming the local, radial boundary of the ring-shaped hot gas path of the gas turbine in the region of the respective turbine vane 10th
  • the airfoil 14 extends through the annular hot gas channel 22.
  • So ⁇ well foot area 12 and head portion 16 have on their sides facing away from the hot gas channel 22 a plurality of hooks 24 for fastening.
  • 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.
  • 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.
  • the blade 14 shown in Figure 1 is not fully 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 2) is 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 foot 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 can be inserted from the outside. ment 32 is inserted.
  • the throttle ⁇ element 32 can be welded or soldered pointwise or circumferentially with the cast turbine vane 10.
  • the throttle element 32 is cup-shaped with a cylindrical shell and a pot bottom 34, which gap forming a the two channel sections 26 separating separation ⁇ wall 36 is opposite.
  • Figure 2 shows the turbine guide blade 10 according to the section II-II in Figure 1 with the head ⁇ region 16 and the hooks 24 disposed thereon vischer in perspective-view.
  • the throttle member 32 is inserted from the outside on the head side in the turbine guide vane 10 is shown perspec ⁇ tivisch and has an inflow opening 37 which faces the channel portions 26 a (26a).
  • a pot opening 38 can be recognized through the inflow opening 37.
  • the pot bottom 34 lies opposite the head-side end 39 (FIG. 1) of the partition wall 36 in a gap-forming manner.
  • 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 such that the coolant flow arriving from the channel section 26a, mostly cooling air, is split into two cooling air streams either into the inflow opening 37 or into the gaps between the airfoil inner walls 36 and the throttling element 32 - flows. The latter partial flow then flows through the
  • 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.

Landscapes

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

Abstract

The invention relates to a turbine guide vane (10) having an aerodynamically bent vane airfoil (14) which has a channel system (28) equipped with a throttle element (32), said channel system comprising channel sections (26) for the guidance of coolant. In order to provide an alternative turbine guide vane (10) by means of which both a partial coolant flow flowing in the interior and a partial coolant flow guided out of the turbine guide vane (10) are adjustable, it is proposed that the throttle element (32) is designed for the removal of coolant.

Description

Beschreibung description
Turbinenleitschaufel mit einem Drosselelement Turbine vane with a throttle element
Die Erfindung betrifft eine Turbinenleitschaufel mit einem aerodynamisch gekrümmten Schaufelblatt, welches ein mit einem Drosselelement ausgestattetes Kanalsystem aus Kanalabschnit¬ ten zur Führung von Kühlmittel aufweist. The invention relates to a turbine with an aerodynamically curved blade which has a throttle element equipped with a channel system Kanalabschnit ¬ th for guiding of coolant.
Eine derartige Turbinenschaufel ist beispielsweise aus der WO 01/36790 AI bekannt. Die Drosselung des Kühlluftverbrauchs der bekannten Turbinenschaufel erfolgt mit Hilfe eines Stop¬ fens, der von außen in die Turbinenleitschaufein an einer Um- kehrstelle 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 kom¬ pensiert werden, wodurch ein übermäßiger Verbrauch an Kühlluft vermieden werden kann. Such a turbine blade is known for example from WO 01/36790 AI. The throttling of the cooling air consumption of the known turbine blade takes place with the aid of a stop ¬ fens, which is attached from the outside in the Turbinenleitschaufein at a reversal point of the cooling channel. 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. This allows cast-related differences in measurement resulting from the production of the turbine blade, with the help of the plug are com ¬ compensated, thus, excessive consumption can be avoided in cooling air.
Weiter ist bekannt, dass anstelle einer Drossel an der Um- lenkstelle auch eine Öffnung zu Entnahme von Kühlluft ange¬ siedelt 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 on the steering environmental imagine also an opening to removal of cooling air is ¬ settled can be. In this case, the use of a throttle at this position is not possible.
Aufgabe der Erfindung ist es, eine alternative Turbinenleit- schaufei bereitzustellen, bei der trotz einer an der Umlenkstelle vorhandenen Öffnung zum Herausführen von Kühlmittel aus der Turbinenschaufel eine nachträgliche Drosselung mög¬ lich ist. Die auf die Turbinenleitschaufel gerichtete Aufgabe wird mit einer solchen gemäß den Merkmalen des Anspruchs 1 gelöst. Vorteilhafte Ausgestaltungen sind in den Unteransprüchen an- gegeben. Deren Merkmale können in beliebiger Weise miteinander kombiniert werden. The object of the invention is to provide an alternative Turbinenleit- schaufei, in which despite a present at the deflection point opening for the removal of coolant from the turbine blade a subsequent throttling is mög ¬ Lich. The object directed to the turbine guide vane is achieved with such according to the features of claim 1. Advantageous embodiments are disclosed in the subclaims. given. Their features can be combined in any way.
Der Erfindung liegt die Erkenntnis zu Grunde, dass bei einer Turbinenleitschaufel mit einem aerodynamisch gekrümmten The invention is based on the finding that in a turbine vane with an aerodynamically curved
Schaufelblatt, welches ein mit einem Drosselelement ausge¬ stattetes 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 Kühl- mittelteilströme verwendet. Der erste der beiden Kühlmittel¬ teilströme fließt innerhalb der Turbinenleitschaufel weiter und wird zur Kühlung des Schaufelblattes und deren Hinter¬ kante eingesetzt. Der andere der beiden Kühlmittelteilströme wird aus der Turbinenleitschaufel unmittelbar herausgeführt. Letzteres ist insbesondere dann von Vorteil, wenn an demjeni¬ gen 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 ein- schließen, 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 Heißgasein¬ dringen sicher vermieden werden kann. Sowohl die Kühlung der weiteren Gasturbinenkomponenten als auch das Sperren derAirfoil, which has a channel system equipped with a throttle element ¬ out of channel sections for guiding coolant, the throttle element is to be designed so that this also allows 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 dividing the coolant into two separate partial coolant streams. The first of the two coolant ¬ substreams continues to flow within the turbine vane and is used to cool the airfoil and the rear edge ¬ used. The other of the two coolant sub-streams is led out of the turbine vane immediately. The latter is particularly advantageous when, other gas turbine components to Demjéni ¬ towards the end at which the coolant is led out of the turbine stator blade arranged to be either cooled or with which the turbine vane (or other components) column switch close, into which a hot gas of the gas turbine could penetrate. By providing the coolant to these gas turbine components, the relevant gaps are blocked by coolant flowing out, so that the hot gas injection can be safely avoided. Both the cooling of the other gas turbine components as well as the blocking of
Spalte gegen Heißgaseinzug verhindert eine vorzeitige Alte¬ rung der Bauteile aufgrund unzulässig hoher Materialtempera¬ turen und verlängert somit deren Lebensdauer. Gemäß einer ersten vorteilhaften Weiterbildung ist das Drosselelement in die Turbinenleitschaufel eingesetzt und topf- förmig mit einer umfangsseitig angeordneten Einströmöffnung für Kühlmittel ausgestaltet, wobei die Topföffnung des Dros- selelements in der Außenfläche der Turbinenleitschaufel ange¬ ordnet ist. In diesem Fall stellt die TopfÖffnung die Aus¬ strömöffnung für den in das Drosselelement einfließenden Kühlmittelteilstrom dar. Mit Hilfe dieser Ausgestaltung ist eine vergleichsweise einfache Konstruktion einer Strömungs¬ weiche bereitgestellt, wobei der andere der beiden Kühlmit¬ telteilströme dadurch erzeugt wird, dass die ankommende Kühl¬ mittelströmung 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 ein¬ gesetzten Bauteil - dem Drosselelement - die Aufteilung der ankommenden Kühlmittelströmung in zwei Teilströme erfolgen kann. Die Aufteilung der Kühlmittelströmung hängt von derColumn against hot gas intake prevents premature aging ¬ tion of components due to impermissibly high Temperatures ¬ tempera ¬ and thus extends their life. According to a first advantageous development, the throttle element is inserted into the turbine guide vane and designed in the shape of a pot with a circumferentially arranged inlet opening for coolant, wherein the pot opening of the throttle selelements in the outer surface of the turbine vane is arranged ¬ . In this case, the cup opening the off ¬ flow orifice for the flowing into the throttling element coolant partial flow. With the help of this embodiment, a comparatively simple construction of a flow ¬ soft is provided, wherein the other of the two Kühlmit ¬ telteilströme is generated by the fact that the incoming coolant ¬ mean flow to the throttle element - more precisely at the inflow opening of the throttle element - flows past and further into the downstream channel sections of the channel system. A further advantage of this construction is that with a single component placed in the cast turbine guide vane , the throttle element, the distribution of the incoming coolant flow into two partial flows can take place. The distribution of the coolant flow depends on the
Größe der Einströmöffnung und von dem verbliebenen Durchströmungsquerschnitt an der Drosselstelle im Kanalsystem ab. Size of the inflow opening and from the remaining flow area at the throttle point in the duct system.
Diese Ausgestaltung hat den weiteren Vorteil, dass bereits im Feld existierende betriebsbeanspruchte Turbinenleitschaufein ggf. nachträglich mit einer derartigen Drosselvorrichtung ausgestattet werden können, ohne die Turbinenleitschaufein bearbeitet, modifiziert bzw. dafür vorbereitet werden müssen. 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 Ein¬ setzten des Drosselelements dieses in die Kanalabschnitte fallen und somit verloren gehen kann. This embodiment has the further advantage that already existing in the field Betriebsbeanspruchte Turbinenleitschaufein can optionally be retrofitted with such a throttle device without the Turbinenleitschaufein edited, modified or prepared for it. 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 the throttle element is inserted, it can fall into the channel sections and thus 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 beid- endseitig angeordnet. Das Drosselelement kann im Fußbereich und/oder im Kopfbereich angeordnet sein. Der Fußbereich der Turbinenleitschaufel dient zur Befestigung der Turbinenleit- schaufei 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 Turbinenleit- schaufeln oder auch Turbinenleitschaufelsegmente eines Leit¬ schaufelkranzes 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 Turbinen- leitschaufel geführte Kühlmittel am die kopfseitigen Ende der Turbinenleitschaufel durch das Drosselelement wieder entnom¬ men und dort nabenseitig verwendet werden kann. Weiter vorteilhaft ist diejenige Weiterbildung, bei der im Schaufelblatt zwei annähernd parallele, zueinander angeord¬ nete 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 Umlenkbe¬ reich 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 ent- fernt 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. Eine druckverlustarme Entnahme von Kühlmittel durch das Dros¬ selelement kann erfolgen, wenn die Einströmöffnung der ankommenden Kühlmittelströmung zugewandt ist. 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 umfangs- seitig angeordnete Durchströmungsöffnung im Drosselelement vorgesehen ist. Dabei ist die Querschnittsfläche aller Durch¬ strömungsöffnungen 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 Kühlmittel¬ teilstrom 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 - ausgestal- tet ist. 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 guide vane is used to fasten the turbine guide schaufei 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 guide vanes or turbine guide vane segments of a guide 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 guide vane coolant at the head end of the turbine vane through the throttle element again entnom ¬ men and can be used there hub side. Further advantageous is that further development in which two approximately parallel, mutually angeord ¬ Nete cooling duct sections are fluidly connected to each other in the airfoil on the foot side or head side arranged and the throttle element extends transversely with respect to the local flow direction of the coolant Umlenkbe ¬ rich in this. In this case, there is a partition wall between the two mutually parallel channel sections, which ends at the deflection area, so that the throttle element can end closer or farther away from the end of this partition depending on the penetration depth. 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. A low-pressure loss of coolant through the Dros ¬ selelement can take place when the inflow opening faces the incoming coolant flow. 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. Here, the cross-sectional area of all through ¬ preferably flow openings substantially smaller than the cross-sectional area of the inflow opening. Preferably, the through flow openings are located opposite the inlet opening and therefore on that side of the throttle element at which the initially remaining in the turbine vane coolant ¬ partial stream flows. It is even conceivable that such through-flow openings are located even in throttle element, if this is not designed for the removal of cooling air - that is, not partially tubular, but solid.
Für die Erfindung ist es unwesentlich, ob die Zuführung von Kühlmittel dabei fußseitig oder kopfseitig erfolgt. Vorzugs¬ weise ist jedoch das Drosselelement in demjenigen Bereich an- geordnet, 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. However, the choke member in that region is preferential ¬ as ordered arrival, which is opposite to the feeder.
Weitere Vorteile und Merkmale der Erfindung werden anhand der nachfolgenden Zeichnung näher erläutert. Es zeigen: Figur 1 eine Turbinenleitschaufel in perspektivischer Further advantages and features of the invention will be explained in more detail with reference to the following drawing. 1 shows a turbine guide vane in perspective
Darstellung mit einem aufgeschnittenen Schaufelblatt und einem fußseitig eingesetzten Drossel¬ element und Figur 2 einen nabenseitigen Querschnitt durch das Representation with a cut open blade and a foot throttle inserted ¬ element and Figure 2 is a hub-side cross-section through the
Schaufelblatt der Turbinenleitschaufel mit dem darin sitzenden Drosselelement. Eine Turbinenleitschaufel 10 für eine stationäre Gasturbine ist in Figur 1 perspektivisch dargestellt. Die Turbinenleit- schaufel 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 Fu߬ bereich 12 als auch Kopfbereich 16 umfassen jeweils eine Plattform 20, die die lokale, radiale Begrenzung des ringför- migen Heißgaspfads der Gasturbine im Bereich der betreffenden Turbinenleitschaufel 10 bilden. Insofern erstreckt sich das Schaufelblatt 14 durch den ringförmigen Heißgaskanal 22. So¬ wohl Fußbereich 12 als auch Kopfbereich 16 haben an ihren dem Heißgaskanal 22 abgewandten Seiten mehrere Haken 24 zur Be- festigung. 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. Airfoil of the turbine vane with the seated therein throttle element. A turbine nozzle 10 for a stationary gas turbine is shown in perspective in FIG. The turbine guide 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 ¬ area 12 and head portion 16 each include a platform 20 forming the local, radial boundary of the ring-shaped hot gas path of the gas turbine in the region of the respective turbine vane 10th In this respect, the airfoil 14 extends through the annular hot gas channel 22. So ¬ well foot area 12 and head portion 16 have on their sides facing away from the hot gas channel 22 a plurality of hooks 24 for fastening. 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 Turbinenleitschau- fel 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 Turbinenleitschau- fel 10 eine Öffnung 31 auf, in die von außen ein Drosselele- ment 32 eingesteckt ist. Um die Turbinenleitschaufel 10 gegen den Verlust des Drosselelements zu sichern, kann das Drossel¬ element 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. The blade 14 shown in Figure 1 is not fully 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 2) is 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 foot 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 can be inserted from the outside. ment 32 is inserted. In order to secure the turbine vane 10 against the loss of the throttle element, the throttle ¬ element 32 can be welded or soldered pointwise or circumferentially with the cast turbine vane 10.
Das Drosselelement 32 ist topfförmig ausgebildet mit einem zylindrischem Mantel und einem Topfboden 34, welcher spaltbildend einer die beiden Kanalabschnitte 26 trennenden Trenn¬ wand 36 gegenüberliegt. The throttle element 32 is cup-shaped with a cylindrical shell and a pot bottom 34, which gap forming a the two channel sections 26 separating separation ¬ wall 36 is opposite.
Identische Merkmale sind in allen Figuren mit den gleichen Bezugszeichen versehen. Somit zeigt Figur 2 die Turbinenleit- schaufel 10 gemäß dem Schnitt II-II in Figur 1 mit dem Kopf¬ bereich 16 und den daran angeordneten Haken 24 in perspekti- vischer Darstellung. Das von außen kopfseitig in die Turbinenleitschaufel 10 eingesetzte Drosselelement 32 ist perspek¬ tivisch dargestellt und weist eine Einströmöffnung 37 auf, die einem (26a) der Kanalabschnitte 26 zugewandt ist. Durch die Einströmöffnung 37 hindurch ist eine Topföffnung 38 er- kennbar. 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, Figure 2 shows the turbine guide blade 10 according to the section II-II in Figure 1 with the head ¬ region 16 and the hooks 24 disposed thereon vischer in perspective-view. The throttle member 32 is inserted from the outside on the head side in the turbine guide vane 10 is shown perspec ¬ tivisch and has an inflow opening 37 which faces the channel portions 26 a (26a). A pot opening 38 can be recognized through the inflow opening 37. The pot bottom 34 lies opposite the head-side end 39 (FIG. 1) of the partition wall 36 in a gap-forming manner.
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 ein- strömt. Letzterer Teilstrom strömt anschließend durch denAt the side of the throttle element 32, the inner surfaces of the airfoil walls 40, 42 are spaced such that the coolant flow arriving from the channel section 26a, mostly cooling air, is split into two cooling air streams either into the inflow opening 37 or into the gaps between the airfoil inner walls 36 and the throttling element 32 - flows. The latter partial flow then flows through the
Kanalabschnitt 26b und verbleibt vorerst in der Turbinenleit- schaufel 10. Der in die Einströmöffnung 37 einströmende Teil¬ strom strömt durch die Topföffnung 38 heraus und kann naben- seitig zur Kühlung der dort angesiedelten Bauteile oder zur Sperrung von Spalten gegen Heißgaseinzug eingesetzt werden. Channel section 26b and remains for the time being in the Turbinenleit- scoop 10. The flowing into the inflow opening 37 part ¬ stream flows out through the pot opening 38 and can hub 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 Durch¬ strömungsöffnungen 41 im Drosselelement vorgesehen sein. To avoid coolant flow areas of low flow velocity can still be one or more provided by ¬ flow openings 41 in the throttle element.
Von besonderem Vorteil ist, dass mit Hilfe des Drosselele¬ ments 32 die gesamte Kühlluftmenge der Turbinenleitschaufel 10 einerseits und auch das Verhältnis der Aufteilung der bei¬ den Kühlmittelteilströme andererseits eingestellt werden kann, selbst nachdem die Turbinenleitschaufel 10 gegossen wurde. Durch die Einsparung von Kühlluft weist eine mit den erfindungsgemäßen Turbinenleitschaufein 10 ausgestattete Gas- turbine einen verbesserten Wirkungsgrad auf. Gleichzeitig ist es möglich, bereits betriebsbeanspruchte Turbinenleitschau- feln 10 nachträglich mit einem Drosselelement 32 auszustat¬ ten, ohne das diese grundlegend bearbeitet werden muss, so¬ fern die Turbinenleitschaufel 10 eine Öffnung zur Entnahme von in ihr strömendem Kühlmittel aufweist. Auch ist es mög¬ lich, neuwertige, jedoch nicht spezifikationskonforme Turbi¬ nenleitschaufein 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 particularly advantageous that with the help of Drosselele ¬ ment 32, the total cooling air amount of the turbine vane 10 on the one hand and the ratio of the distribution of ¬ the coolant partial flows can be adjusted on the other hand, 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 vane 10 according to the invention has an improved efficiency. At the same time, it is possible already feln operationally stressed Turbinenleitschau- 10 subsequently auszustat ¬ th without them must be machined elementary, so far ¬ the turbine vane 10 has an opening for removal of flowing in their coolant with a throttle element 32nd It is mög ¬ Lich also to toughen-new, but not-specification Turbi ¬ nenleitschaufein 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 herausge¬ führter Kühlmittelteilstrom einstellbar ist, wird vorgeschla- gen, 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 flow and a recirculated from the turbine vane 10 led ¬ partial flow of coolant is adjustable, it is proposed that the throttle element 32 is designed for removal of coolant.

Claims

Patentansprüche claims
1. Turbinenleitschaufel (10) mit einem aerodynamisch ge- krümmten Schaufelblatt (14), 1. turbine guide vane (10) with an aerodynamically curved airfoil (14),
welches ein mit einem Drosselelement (32) ausgestattetes Kanalsystem (28) aus Kanalabschnitten (26) zur Führung von Kühlmittel aufweist,  which has a duct system (28) equipped with a throttle element (32) and duct sections (26) for guiding coolant,
dadurch gekennzeichnet, dass  characterized in that
das Drosselelement (32) zur Entnahme von Kühlmittel ausge¬ staltet ist. is the throttle element (32) for the removal of coolant out ¬ staltet.
2. Turbinenleitschaufel (10) nach Anspruch 1, 2. turbine vane (10) according to claim 1,
bei der das Drosselelement (32) in die Turbinenleitschaufel (10) eingesetzt und topfförmig mit einer umfangsseitig an¬ geordneten Einströmöffnung (37) für Kühlmittel ausgestaltet ist, in which the throttle element (32) inserted into the turbine guide vane (10) and pot-shaped with a circumferentially on ¬ arranged inlet opening (37) is designed for coolant,
wobei die Topföffnung (38) des Drosselelements (32) in der Außenfläche der Turbinenleitschaufel (10) angeordnet ist.  wherein the pot opening (38) of the throttling element (32) is arranged in the outer surface of the turbine guide vane (10).
3. Turbinenleitschaufel (10) nach Anspruch 1 oder 2, 3. turbine vane (10) according to claim 1 or 2,
welche einen Fußbereich (12) und einen Kopfbereich (16) zur Befestigung umfasst, die beidendseitig am Schaufelblatt (14) angeordnet sind und das Drosselelement (32) im Fußbe- reich (12) und/oder im Kopfbereich (16) angeordnet ist.  which comprises a foot region (12) and a head region (16) for attachment, which are arranged at both ends on the blade (14) and the throttle element (32) is arranged in the foot region (12) and / or in the head region (16).
4. Turbinenleitschaufel (10) nach Anspruch 1, 2 oder 3, bei der im Schaufelblatt (14) zwei annähernd parallel zu¬ einander angeordnete Kanalabschnitte (26) über einen fuß- seitig oder kopfseitig angeordneten Umlenkbereich (30) strömungstechnisch miteinander verbunden sind und das Drosselelement (32) quer in den Umlenkbereich (30) hineinragt. 4. Turbinenleitschaufel (10) according to claim 1, 2 or 3, wherein in the blade (14) two approximately parallel to each ¬ arranged channel sections (26) via a foot side or head side arranged deflection region (30) are fluidly connected to each other and the Throttle element (32) projects transversely into the deflection region (30).
5. Turbinenleitschaufel (10) nach Anspruch 2 und nach einem oder mehreren der Ansprüche 3 oder 4, 5. turbine guide vane (10) according to claim 2 and according to one or more of claims 3 or 4,
bei dem die Einströmöffnung (37) der ankommenden Kühlmittelströmung zugewandt ist in which the inflow opening (37) faces the incoming coolant flow
6. Turbinenleitschaufein (10) nach Anspruch 2 und nach einem oder mehreren der Ansprüche 3, 4 oder 5, 6. Turbinenleitschaufein (10) according to claim 2 and according to one or more of claims 3, 4 or 5,
bei der zumindest eine Durchströmöffnung vorgesehen ist.  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)

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

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EP3199760A1 (en) * 2016-01-29 2017-08-02 Siemens Aktiengesellschaft Turbine blade with a throttle element
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JP6005764B2 (en) 2016-10-12
US9856738B2 (en) 2018-01-02
EP2628900A1 (en) 2013-08-21
JP2015507129A (en) 2015-03-05
RU2014136803A (en) 2016-04-10
IN2014DN05979A (en) 2015-06-26
US20140377058A1 (en) 2014-12-25
CN104126054A (en) 2014-10-29
CN104126054B (en) 2016-02-03
EP2788583B1 (en) 2016-03-02
WO2013120560A1 (en) 2013-08-22

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