EP2282014A1 - Ring-shaped flow channel section for a turbo engine - Google Patents

Ring-shaped flow channel section for a turbo engine Download PDF

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Publication number
EP2282014A1
EP2282014A1 EP09008227A EP09008227A EP2282014A1 EP 2282014 A1 EP2282014 A1 EP 2282014A1 EP 09008227 A EP09008227 A EP 09008227A EP 09008227 A EP09008227 A EP 09008227A EP 2282014 A1 EP2282014 A1 EP 2282014A1
Authority
EP
European Patent Office
Prior art keywords
flow channel
channel section
platforms
shielding
platform
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.)
Withdrawn
Application number
EP09008227A
Other languages
German (de)
French (fr)
Inventor
Fathi Ahmad
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 EP09008227A priority Critical patent/EP2282014A1/en
Priority to US13/379,530 priority patent/US20120100008A1/en
Priority to CN2010800282474A priority patent/CN102803658A/en
Priority to JP2012516636A priority patent/JP5443600B2/en
Priority to PCT/EP2010/058352 priority patent/WO2010149528A1/en
Priority to EP10725431A priority patent/EP2446119A1/en
Publication of EP2282014A1 publication Critical patent/EP2282014A1/en
Withdrawn legal-status Critical Current

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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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid

Definitions

  • the invention relates to an annular flow channel section for a turbomachine, comprising a vane ring having a number of circumferentially juxtaposed vanes each comprising a blade root, a platform and a radiantly projecting into the flow channel airfoil, wherein the flow channel is platform-side limited by shielding, each sit between two immediately adjacent blades.
  • annular flow channel section is for example from the EP 1 219 787 B1 known.
  • the patent discloses a ring of cast guide vanes of an axial flow turbine in which the vanes have an aerodynamically curved airfoil at each of whose radially outer (foot-side) and inner (head-side) ends platforms are provided. Installed in the turbine, the platforms are covered by ceramic heat shields.
  • the heat shields are configured such that they each cover one half of the platform of two directly adjacent vanes in pairs. They thus essentially extend from the suction side wall of the blade profile of a first guide blade to the pressure side wall of the blade profile of a second guide blade.
  • the ceramic heat shield is connected via a spring fixed to the gas turbine blade, so that the former is attached interchangeable.
  • ceramic heat shields require a comparatively large wall thickness in order to be able to permanently and reliably withstand the temperatures of the hot gas occurring in a stationary gas turbine. If such ceramic heat shields on both the head-side and on the foot side Can be used platform of vanes, this leads to relatively large turbine vanes with correspondingly increased space requirements, which also increases the cost of production.
  • the object of the invention is therefore to provide an annular flow channel section for a turbomachine, which requires a comparatively small space requirement and, moreover, for a particularly long period of time the hot gas flowing in the flow channel section leads particularly reliably and safely without premature signs of wear occurring at the flow channel defining components ,
  • the object is achieved with an annular flow channel section for a turbomachine, in which the shielding elements are arranged under gap formation on the platforms and in the platform impingement cooling openings are provided for impingement cooling of the shielding elements.
  • the invention is based on the finding that the platform integrally formed on the guide vanes can be protected from the hot gas and its corrosive and thermal influences even when the shielding element is not made of a ceramic. In this case, the shielding is then sufficient to cool. According to the invention, it is provided that an impingement cooling of the shielding element is used for cooling. By cooling the shielding this can be configured thin-walled than in the prior art. The comparatively thin-walled design of the shielding element is space-saving and also less expensive. The airfoil of respective vanes can thereby be made shorter in its span, without reducing the flow area of the annular flow channel portion, compared with the known from the prior art flow channel section.
  • the shielding elements preferably each have a base plate which delimits the flow channel and is made of a metallic material which is manufactured separately from the guide vanes. By cooling the shielding can be made of metallic materials. In addition, the entire shielding element is manufactured separately from the guide vanes. This has the advantage that in the event of wear and tear on the shielding only this is to be replaced and not the complete vane, as in non-shielded vane platforms.
  • the shielding element is made of a metallic material having good insulating properties.
  • the wall thickness of the base plate is less than the wall thickness of the covered by the shielding platform.
  • the thinner the shielding element the better this can be cooled by the impingement cooling.
  • a flow channel section that is compact in terms of space can be specified, which reduces the manufacturing and material costs for such a flow channel section.
  • transverse wall sections are provided at the edges of the base plate, which are connectable to lateral walls of the platforms. This makes it possible to accomplish a convenient attachment of the shielding to the vane.
  • each shield member extends over a gap bounded by the platforms of two immediately adjacent vanes. This allows a low-loss guidance of the hot gas in the flow channel, even in the event that, due to thermally induced strains, an offset of adjacent platforms occurs.
  • the shielding element has a protective layer on the flow channel side, in particular a heat-insulating protective layer.
  • FIG. 1 shows the cross section through the blades 14 of two vanes 10 of an annular flow channel portion 12 of a hot gas axially flowed through by a turbomachine, such as gas turbine.
  • the flow channel section 12 essentially comprises a vane ring with a plurality of circumferentially juxtaposed vanes 10.
  • FIG. 1 shows only two of the vanes 10 are shown.
  • the vanes 10 are attached in a conventional manner to a guide vane.
  • the representation is in FIG. 1 chosen so that the blades 14 are shown in cross section and thus a plan view of the platforms 16 of the vanes 10 takes place. Between a suction side airfoil wall 18 of in FIG.
  • the vane ring between each pair of immediately adjacent airfoils 14 each have such a shielding element 22, wherein adjacent shielding elements 22 on the one hand upstream of a leading edge 21 of the airfoil 14 and downstream of a trailing edge 23 of the airfoil 14 with the smallest possible gap abut each other.
  • baffle cooling openings 24 are arranged, for example, grid-shaped.
  • the section along the section line II-II through the vane 10 and the shield 22 shows FIG. 2 , In FIG. 2 are closed FIG. 1 identical features provided with identical reference numerals.
  • the shielding element 22 is arranged with gap formation on the platform 16 on the hot gas side, wherein in the platform 16 to the surface of which, for example, oblique impingement cooling openings 24 are provided.
  • a coolant K is supplied during operation of the turbomachine, which emerge through the impingement cooling openings 24 from the rear space 28 and can enter into the gap between shield 22 and platform 16 like a jet. When the impact cooling jets strike, they cool the shielding element 22, so that, despite the hot gas flowing through the flow channel 26, it has a sufficient service life.
  • Shielding element 22 shown in cross-section is metallic and essentially comprises a base plate 30 which extends parallel to the channel-side platform surface. At the two opposite edges of the base plate 30 laterally transversely to the base plate 30 projecting wall portions 32 are provided, which surround respective side walls of the platform 16 like a clamp.
  • the Wall thickness of the base plate 30 is substantially lower than the wall thickness of the platform 16 in the region of the impact cooling openings 24.
  • the shielding element 22 For fastening the shielding element 22 to the guide blade 10 or to the platform 16, this can be screwed, for example, as indicated by the dot-dash line. Other types of attachment such. As well as a jamming, in particular positive clamping of the shielding member 22 to the platform 16 is also conceivable. If necessary, the shielding member 22 may have on its surface, which is exposed to the hot gas, a thermal heat-insulating layer in order to further increase its thermal resistance.
  • the coolant K flowing into the gap between the shielding element 22 and the platform surface flows after the impingement cooling at that gap 36 (FIG. FIG. 1 ), which is provided between the shielding member 22 and the suction-side airfoil wall 18 and pressure-side airfoil wall 20, respectively.
  • platform 16 and the shielding member 22 disposed above it may be both a foot-side platform and a head-side platform of vanes 10, provided that the guide vanes 10 used in the annular flow channel section 12 at both opposite ends of the blade 14 transverse to the blade 14th have extending platforms 16.
  • the invention can also be applied to only one of the two platforms 16 of such a vane 10.
  • the invention provides an annular flow channel section 12 for a turbomachine comprising a vane ring which has a number of circumferentially juxtaposed vanes 10, each comprising a platform 16 and a radiant manner into the flow channel 26 projecting airfoil 14, wherein the flow channel 26 platform side is limited by shielding 22, which are each arranged between two immediately adjacent airfoils 14, wherein the formation of a particularly space-saving flow channel section 12, the shielding 22 arranged under gap formation on the platforms 16 and in the platform 16th Impact cooling holes 24 are provided.

Abstract

The flow channel section (12) has a guide vane ring comprising a number of guide vanes (10) arranged adjacent to each other in circumferential direction. Shielding elements (22) are arranged on platforms (16) for creating the flow channel section while creating a gap, and impingement-cooling openings (24) are provided in the platform. A flow channel is delimited on the platform side by the shielding elements, where each of the shielding elements is provided between two airfoils (14). The airfoils project into the flow channel.

Description

Die Erfindung betrifft einen ringförmigen Strömungskanalabschnitt für eine Turbomaschine, mit einem Leitschaufelkranz, welcher eine Anzahl von in Umfangsrichtung aneinandergereihten Leitschaufeln jeweils umfassend einen Schaufelfuß, eine Plattform und ein in den Strömungskanal strahlenartig hineinragendes Schaufelblatt aufweist, wobei der Strömungskanal plattformseitig von Abschirmelementen begrenzt ist, die jeweils zwischen zwei unmittelbar benachbarten Schaufelblättern sitzen.The invention relates to an annular flow channel section for a turbomachine, comprising a vane ring having a number of circumferentially juxtaposed vanes each comprising a blade root, a platform and a radiantly projecting into the flow channel airfoil, wherein the flow channel is platform-side limited by shielding, each sit between two immediately adjacent blades.

Ein eingangs genannter ringförmiger Strömungskanalabschnitt ist beispielsweise aus der EP 1 219 787 B1 bekannt. Im Detail offenbart die Patentschrift einen Kranz von gegossenen Leitschaufeln einer axial durchströmten Turbine, bei denen die Leitschaufeln ein aerodynamisch gekrümmtes Schaufelblatt aufweisen, an dessen radial äußerem (fußseitigen) und inneren (kopfseitigen) Ende jeweils Plattformen vorgesehen sind. In der Turbine eingebaut sind die Plattformen von keramischen Hitzeschilden überdeckt. Die Hitzeschilde sind derart ausgestaltet, dass sie jeweils eine Plattformhälfte zweier unmittelbar benachbarter Leitschaufeln paarweise überdecken. Sie erstrecken sich somit im Wesentlichen von der Saugseitenwand des Schaufelprofils einer ersten Leitschaufel bis zur Druckseitenwand des Schaufelprofils einer zweiten Leitschaufel. Das keramische Hitzeschild ist dabei über eine Feder fest mit der Gasturbinenschaufel verbunden, so dass erstgenanntes austauschbar befestigt ist.An initially mentioned annular flow channel section is for example from the EP 1 219 787 B1 known. In detail, the patent discloses a ring of cast guide vanes of an axial flow turbine in which the vanes have an aerodynamically curved airfoil at each of whose radially outer (foot-side) and inner (head-side) ends platforms are provided. Installed in the turbine, the platforms are covered by ceramic heat shields. The heat shields are configured such that they each cover one half of the platform of two directly adjacent vanes in pairs. They thus essentially extend from the suction side wall of the blade profile of a first guide blade to the pressure side wall of the blade profile of a second guide blade. The ceramic heat shield is connected via a spring fixed to the gas turbine blade, so that the former is attached interchangeable.

Keramische Hitzeschilde benötigen jedoch eine vergleichsweise große Wandstärke, um den in einer stationären Gasturbine auftretenden Temperaturen des Heißgases dauerhaft und zuverlässig standhalten zu können. Sofern solche keramische Hitzeschilde sowohl an der kopfseitigen als auch an der fußseitigen Plattform von Leitschaufeln verwendet werden, führt dies zu vergleichsweise großen Turbinenleitschaufeln mit entsprechend vergrößertem Raumbedarf, was gleichfalls die Herstellungskosten erhöht.However, ceramic heat shields require a comparatively large wall thickness in order to be able to permanently and reliably withstand the temperatures of the hot gas occurring in a stationary gas turbine. If such ceramic heat shields on both the head-side and on the foot side Can be used platform of vanes, this leads to relatively large turbine vanes with correspondingly increased space requirements, which also increases the cost of production.

Aufgabe der Erfindung ist daher die Bereitstellung eines ringförmigen Strömungskanalabschnitts für eine Turbomaschine, welche einen vergleichsweise geringen Raumbedarf benötigt und darüber hinaus für einen besonders langen Zeitraum das im Strömungskanalabschnitt strömende Heißgas besonders zuverlässig und sicher führt, ohne dass an den den Strömungskanal begrenzenden Bauteilen vorzeitige Verschleißerscheinungen auftreten.The object of the invention is therefore to provide an annular flow channel section for a turbomachine, which requires a comparatively small space requirement and, moreover, for a particularly long period of time the hot gas flowing in the flow channel section leads particularly reliably and safely without premature signs of wear occurring at the flow channel defining components ,

Die Aufgabe wird mit einem ringförmigen Strömungskanalabschnitt für eine Turbomaschine gelöst, bei der die Abschirmelemente unter Spaltbildung an den Plattformen angeordnet und in der Plattform Prallkühlöffnungen zur Prallkühlung der Abschirmelemente vorgesehen sind.The object is achieved with an annular flow channel section for a turbomachine, in which the shielding elements are arranged under gap formation on the platforms and in the platform impingement cooling openings are provided for impingement cooling of the shielding elements.

Der Erfindung liegt die Erkenntnis zugrunde, dass die an den Leitschaufeln angeformte Plattform auch dann vor dem Heißgas und dessen korrosiven sowie thermischen Einflüssen geschützt werden kann, wenn das Abschirmelement nicht aus einer Keramik besteht. In diesem Fall ist das Abschirmelement dann ausreichend zu kühlen. Erfindungsgemäß ist dazu vorgesehen, dass zur Kühlung eine Prallkühlung des Abschirmelements eingesetzt wird. Durch die Kühlung des Abschirmelements kann dieses dünnwandiger ausgestaltet werden als beim Stand der Technik. Die vergleichsweise dünnwandige Ausgestaltung des Abschirmelements ist platzsparend und auch kostengünstiger. Das Schaufelblatt entsprechender Leitschaufeln kann dadurch in seiner Spannweite kürzer ausgestaltet werden, ohne den Strömungsquerschnitt des ringförmigen Strömungskanalabschnitts, verglichen mit dem aus dem Stand der Technik bekannten Strömungskanalabschnitt, zu verringern.The invention is based on the finding that the platform integrally formed on the guide vanes can be protected from the hot gas and its corrosive and thermal influences even when the shielding element is not made of a ceramic. In this case, the shielding is then sufficient to cool. According to the invention, it is provided that an impingement cooling of the shielding element is used for cooling. By cooling the shielding this can be configured thin-walled than in the prior art. The comparatively thin-walled design of the shielding element is space-saving and also less expensive. The airfoil of respective vanes can thereby be made shorter in its span, without reducing the flow area of the annular flow channel portion, compared with the known from the prior art flow channel section.

Üblicherweise sind Leitschaufeln, die im erfindungsgemäßen Strömungskanalabschnitt eingesetzt sind, im Gussverfahren hergestellt und somit hauptsächlich einstückig. Da bisher die Plattformen derartiger Leitschaufeln nicht nur dem Druck des Heißgases widerstehen mussten, sondern auch die von den Strömungskräfte hervorgerufenen mechanische Belastung des Schaufelblatts an eine rückseitige Verhakung weiterleiten musste, hatten diese bisher vergleichsweise massive Wände, d. h. große Wandstärken. Dies führte zu einer schlechten Kühlbarkeit von Plattformen, wodurch die Lebensdauer derartiger Leitschaufeln bisher auch von den Plattformen begrenzt war. Durch die Verwendung eines erfindungsgemäßen Abschirmelementes kann insbesondere die thermische Belastung derartiger Plattformen reduziert werden, was zu einer signifikanten Verlängerung der Lebensdauer von Leitschaufeln führt.Usually guide vanes, which are used in the flow channel section according to the invention, produced by casting and thus mainly in one piece. Until now, the platforms of such vanes not only had to withstand the pressure of the hot gas, but also had to pass on the induced by the flow forces mechanical stress of the airfoil to a rear hooking, these previously had comparatively massive walls, d. H. large wall thicknesses. This has resulted in poor platform cooling, which has limited the life of such vanes from platforms to date. By using a shielding element according to the invention, in particular, the thermal load of such platforms can be reduced, which leads to a significant extension of the service life of guide vanes.

Insbesondere bei Strömungskanalabschnitten, in denen Leitschaufeln ohne Abschirmelemente eingesetzt waren, traten zudem insbesondere im Bereich eine hohlkehlartigen Übergangs von Plattform zum Schaufelblatt durch eine entsprechende Verrundung eine Masseanhäufung auf, die nur unzureichend kühlbar war. Durch die unzureichende Kühlbarkeit des Übergangs traten auch an diesen Stellen Ermüdungserscheinungen wie Risse auf. Nunmehr kann durch die Verwendung von Abschirmelementen der Übergang vor dem unmittelbaren Kontakt und Einfluss des im Strömungskanal strömenden Heißgases besser geschützt werden, da an dieser Stelle nunmehr ein Spalt zwischen Abschirmelement und Schaufelblattwand resp. Übergang vorhanden ist, durch den die zur Prallkühlung des Abschirmelementes verwendete Kühlmittel, beispielsweise Kühlluft nach Abschluss der Prallkühlung in den Strömungskanal austreten kann. Auch dies führt zu einer verlängerten Lebensdauer der Leitschaufel aufgrund der Reduzierung der thermischen Belastung im Bereich des Übergangs von Plattform zu Schaufelblatt.Particularly in the case of flow channel sections in which guide vanes without shielding elements were used, in addition in the region of a hollow-chord-like transition from platform to blade airfoil an accumulation of mass occurred due to a corresponding rounding, which was insufficiently coolable. Due to the insufficient coolability of the transition, fatigue phenomena such as cracks also appeared at these points. Now can be better protected by the use of shielding the transition from the direct contact and influence of the hot gas flowing in the flow channel, since at this point now a gap between the shielding and the airfoil wall, respectively. Transition is present, through which the coolant used for impact cooling of the shielding, for example, cooling air can escape into the flow channel after completion of the impingement cooling. This also leads to a prolonged life of the vane due to the reduction of thermal stress in the region of the transition from platform to blade.

Weitere vorteilhafte Ausgestaltungen sind in den Unteransprüchen angegeben.Further advantageous embodiments are specified in the subclaims.

Vorzugsweise weisen die Abschirmelemente jeweils eine den Strömungskanal begrenzende Grundplatte aus einem metallischen Werkstoff auf, der separat von den Leitschaufeln gefertigt ist. Durch die Kühlung des Abschirmelements kann auf metallische Materialien zurückgegriffen werden. Zudem ist das gesamte Abschirmelement separat von den Leitschaufeln gefertigt. Dies hat den Vorteil, dass für den Fall des Auftretens von Verschleißerscheinungen am Abschirmelement nur dieses zu ersetzen ist und nicht die komplette Leitschaufel, wie bei nicht abgeschirmten Leitschaufelplattformen.The shielding elements preferably each have a base plate which delimits the flow channel and is made of a metallic material which is manufactured separately from the guide vanes. By cooling the shielding can be made of metallic materials. In addition, the entire shielding element is manufactured separately from the guide vanes. This has the advantage that in the event of wear and tear on the shielding only this is to be replaced and not the complete vane, as in non-shielded vane platforms.

Vorzugsweise ist das Abschirmelement aus einem metallischen Material mit guten Isolationseigenschaften gefertigt.Preferably, the shielding element is made of a metallic material having good insulating properties.

Gemäß einer weiteren vorteilhaften Ausgestaltung ist die Wandstärke der Grundplatte geringer als die Wandstärke der vom Abschirmelement überdeckten Plattform. Je dünnwandiger das Abschirmelement ist, umso besser lässt sich dieses durch die Prallkühlung kühlen. Außerdem kann mit einem vergleichsweise dünnwandigen Abschirmelement ein im Raumbedarf kompakter Strömungskanalabschnitt angegeben werden, was die Herstellungs- und Materialkosten für einen derartigen Strömungskanalabschnitt reduziert.According to a further advantageous embodiment, the wall thickness of the base plate is less than the wall thickness of the covered by the shielding platform. The thinner the shielding element, the better this can be cooled by the impingement cooling. Moreover, with a comparatively thin-walled shielding element, a flow channel section that is compact in terms of space can be specified, which reduces the manufacturing and material costs for such a flow channel section.

Gemäß einer bevorzugten Ausgestaltung sind an den Rändern der Grundplatte quer angeordnete Wandabschnitte vorgesehen, welche mit seitlichen Wänden der Plattformen verbindbar sind. Hierdurch lässt sich eine zweckmäßige Befestigung des Abschirmelements an der Leitschaufel bewerkstelligen.According to a preferred embodiment, transverse wall sections are provided at the edges of the base plate, which are connectable to lateral walls of the platforms. This makes it possible to accomplish a convenient attachment of the shielding to the vane.

Üblicherweise erstreckt sich jedes Abschirmelement über einen von den Plattformen zweier unmittelbar benachbarter Leitschaufeln begrenzten Spalt. Dies ermöglicht eine verlustarme Führung des Heißgases im Strömungskanal, selbst für den Fall, dass aufgrund von thermisch bedingten Dehnungen ein Versatz von einander benachbarten Plattformen auftritt.Typically, each shield member extends over a gap bounded by the platforms of two immediately adjacent vanes. This allows a low-loss guidance of the hot gas in the flow channel, even in the event that, due to thermally induced strains, an offset of adjacent platforms occurs.

Um die thermische Widerstandsfähigkeit des Abschirmelements gegenüber dem Heißgas weiter zu erhöhen, kann es von Vorteil sein, wenn das Abschirmelement strömungskanalseitig eine Schutzschicht, insbesondere eine wärmedämmende Schutzschicht aufweist.In order to further increase the thermal resistance of the shielding element with respect to the hot gas, it can be advantageous if the shielding element has a protective layer on the flow channel side, in particular a heat-insulating protective layer.

Die weitere Erläuterung der Erfindung erfolgt anhand des in der Zeichnung dargestellten Ausführungsbeispiels.The further explanation of the invention is based on the embodiment shown in the drawing.

Es zeigen:

FIG 1
einen Schnitt durch zwei der Schaufelblätter eines ringförmigen Strömungskanalabschnitts als Abwick- lung dessen mit einem über die Plattformen der Leitschaufeln angeordnetem Abschirmelement und
FIG 2
den Schnitt gemäß Schnitt II-II durch die Plattform der Leitschaufel und durch das Abschirmelement.
Show it:
FIG. 1
a section through two of the airfoils of an annular flow channel portion as a settlement thereof with a arranged over the platforms of the vanes shielding and
FIG. 2
the section according to section II-II through the platform of the vane and through the shield.

FIG 1 zeigt den Querschnitt durch die Schaufelblätter 14 von zwei Leitschaufeln 10 eines ringförmigen Strömungskanalabschnitts 12 einer von einem Heißgas axial durchströmbaren Turbomaschine, beispielsweise Gasturbine. Der Strömungskanalabschnitt 12 umfasst im Wesentlichen einen Leitschaufelkranz mit einer Vielzahl von in Umfangsrichtung aneinander gereihten Leitschaufeln 10. Von dem im Stand der Technik vielfach bekannten Leitschaufelkranz sind in FIG 1 lediglich zwei der Leitschaufeln 10 dargestellt. Die Leitschaufeln 10 sind dabei in herkömmlicher Art an einem Leitschaufelträger befestigt.
Die Darstellung ist in FIG 1 so gewählt, dass die Schaufelblätter 14 im Querschnitt dargestellt sind und somit eine Draufsicht auf die Plattformen 16 der Leitschaufeln 10 erfolgt. Zwischen einer saugseitigen Schaufelblattwand 18 der in FIG 1 weiter unten dargestellten Leitschaufel 10 und der druckseitigen Schaufelblattwand 20 der in FIG 1 weiter oben dargestellten Leitschaufel 10 ist ein Abschirmelement 22 formschlüssig angeordnet. Das Abschirmelement 22 überdeckt die darunter liegenden Bereiche der Plattformen 16 zwischen den Schaufelblättern 14 der beiden unmittelbar benachbarten Leitschaufeln 10 vollständig. Der Klarheit halber ist nur eines der im Strömungskanalabschnitt 12 angeordneten Abschirmelemente 22 dargestellt. Prinzipiell weist der Leitschaufelkranz zwischen jedem Paar von unmittelbar benachbarten Schaufelblättern 14 jeweils ein derartiges Abschirmelement 22 auf, wobei benachbarte Abschirmelemente 22 zudem einerseits stromauf einer Vorderkante 21 des Schaufelblatts 14 und stromab einer Hinterkante 23 des Schaufelblatts 14 mit möglichst kleinem Spalt aufeinander stoßen. FIG. 1 shows the cross section through the blades 14 of two vanes 10 of an annular flow channel portion 12 of a hot gas axially flowed through by a turbomachine, such as gas turbine. The flow channel section 12 essentially comprises a vane ring with a plurality of circumferentially juxtaposed vanes 10. Of the well-known in the art Leitschaufelkranz are in FIG. 1 only two of the vanes 10 are shown. The vanes 10 are attached in a conventional manner to a guide vane.
The representation is in FIG. 1 chosen so that the blades 14 are shown in cross section and thus a plan view of the platforms 16 of the vanes 10 takes place. Between a suction side airfoil wall 18 of in FIG. 1 shown below vane 10 and the pressure-side airfoil wall 20 of the FIG. 1 shown above vane 10 is a shield 22nd arranged in a form-fitting manner. The shielding element 22 completely covers the underlying areas of the platforms 16 between the airfoils 14 of the two immediately adjacent vanes 10. For the sake of clarity, only one of the shielding elements 22 arranged in the flow channel section 12 is shown. In principle, the vane ring between each pair of immediately adjacent airfoils 14 each have such a shielding element 22, wherein adjacent shielding elements 22 on the one hand upstream of a leading edge 21 of the airfoil 14 and downstream of a trailing edge 23 of the airfoil 14 with the smallest possible gap abut each other.

Ferner sind in den Plattformen 16 Prallkühlöffnungen 24 beispielweise rasterförmig angeordnet. Den Schnitt gemäß der Schnittlinie II-II durch die Leitschaufel 10 und das Abschirmelement 22 zeigt FIG 2. In FIG 2 sind zu FIG 1 identische Merkmale mit identischen Bezugszeichen versehen. Das Abschirmelement 22 ist unter Spaltbildung an der Plattform 16 heißgasseitig angeordnet, wobei in der Plattform 16 zu dessen Oberfläche beispielsweise schräg verlaufende Prallkühlöffnungen 24 vorgesehen sind. Dem vom Strömungskanal 26 abgewandten Rückraum 28 wird während des Betriebs der Strömungsmaschine ein Kühlmittel K zugeführt, welches durch die Prallkühlöffnungen 24 aus dem Rückraum 28 austreten und in den Spalt zwischen Abschirmelement 22 und Plattform 16 strahlartig eintreten kann. Beim Auftreffen der Prallkühlstrahlen kühlen diese das Abschirmelement 22, so dass trotz des durch das im Strömungskanal 26 strömenden Heißgases dieses eine ausreichende Lebensdauer aufweist.Furthermore, in the platforms 16 baffle cooling openings 24 are arranged, for example, grid-shaped. The section along the section line II-II through the vane 10 and the shield 22 shows FIG. 2 , In FIG. 2 are closed FIG. 1 identical features provided with identical reference numerals. The shielding element 22 is arranged with gap formation on the platform 16 on the hot gas side, wherein in the platform 16 to the surface of which, for example, oblique impingement cooling openings 24 are provided. The remote from the flow channel 26 rear chamber 28, a coolant K is supplied during operation of the turbomachine, which emerge through the impingement cooling openings 24 from the rear space 28 and can enter into the gap between shield 22 and platform 16 like a jet. When the impact cooling jets strike, they cool the shielding element 22, so that, despite the hot gas flowing through the flow channel 26, it has a sufficient service life.

Das in FIG 2 im Querschnitt gezeigte Abschirmelement 22 ist metallisch und umfasst im Wesentlichen eine Grundplatte 30, welche sich parallel zur kanalseitigen Plattformoberfläche erstreckt. An den beiden einander gegenüberliegenden Rändern der Grundplatte 30 sind seitlich quer zur Grundplatte 30 abstehende Wandabschnitte 32 vorgesehen, welche entsprechende Seitenwände der Plattform 16 klammerartig umgreifen. Die Wandstärke der Grundplatte 30 ist dabei wesentlich geringer als die Wandstärke der Plattform 16 im Bereich der Prallkühlöffnungen 24.This in FIG. 2 Shielding element 22 shown in cross-section is metallic and essentially comprises a base plate 30 which extends parallel to the channel-side platform surface. At the two opposite edges of the base plate 30 laterally transversely to the base plate 30 projecting wall portions 32 are provided, which surround respective side walls of the platform 16 like a clamp. The Wall thickness of the base plate 30 is substantially lower than the wall thickness of the platform 16 in the region of the impact cooling openings 24.

Zur Befestigung des Abschirmelements 22 an der Leitschaufel 10 bzw. an der Plattform 16 kann dieses beispielsweise, wie durch die strichpunktierte Linie angedeutet, verschraubt sein. Andere Befestigungsarten wie z. B. auch ein Festklemmen, insbesondere formschlüssiges Festklemmen des Abschirmelements 22 an der Plattform 16 ist auch denkbar. Sofern erforderlich, kann das Abschirmelement 22 an seiner Oberfläche, die dem Heißgas ausgesetzt ist, eine thermische Wärmedämmschutzschicht aufweisen, um dessen thermische Beständigkeit weiter zu erhöhen.For fastening the shielding element 22 to the guide blade 10 or to the platform 16, this can be screwed, for example, as indicated by the dot-dash line. Other types of attachment such. As well as a jamming, in particular positive clamping of the shielding member 22 to the platform 16 is also conceivable. If necessary, the shielding member 22 may have on its surface, which is exposed to the hot gas, a thermal heat-insulating layer in order to further increase its thermal resistance.

Das in den Spalt zwischen Abschirmelement 22 und Plattformoberfläche einströmende Kühlmittel K strömt nach erfolgter Prallkühlung an demjenigen Spalt 36 (FIG 1) aus, welcher zwischen dem Abschirmelement 22 und der saugseitigen Schaufelblattwand 18 bzw. druckseitigen Schaufelblattwand 20 vorgesehen ist.The coolant K flowing into the gap between the shielding element 22 and the platform surface flows after the impingement cooling at that gap 36 (FIG. FIG. 1 ), which is provided between the shielding member 22 and the suction-side airfoil wall 18 and pressure-side airfoil wall 20, respectively.

Bei der in FIG 2 dargestellten Plattform 16 und dem darüber angeordneten Abschirmelement 22 kann es sich dabei sowohl um eine fußseitige Plattform als auch um eine kopfseitige Plattform von Leitschaufeln 10 handeln, sofern die im ringförmigen Strömungskanalabschnitt 12 verwendeten Leitschaufeln 10 an beiden gegenüberliegenden Enden des Schaufelblatts 14 sich quer zum Schaufelblatt 14 erstreckende Plattformen 16 aufweisen. Selbstverständlich kann die Erfindung auch an nur einer der beiden Plattformen 16 einer derartigen Leitschaufel 10 angewendet werden.At the in FIG. 2 illustrated platform 16 and the shielding member 22 disposed above it may be both a foot-side platform and a head-side platform of vanes 10, provided that the guide vanes 10 used in the annular flow channel section 12 at both opposite ends of the blade 14 transverse to the blade 14th have extending platforms 16. Of course, the invention can also be applied to only one of the two platforms 16 of such a vane 10.

Insgesamt wird mit der Erfindung ein ringförmiger Strömungskanalabschnitt 12 für eine Turbomaschine angegeben, mit einem Leitschaufelkranz, welcher eine Anzahl von in Umfangsrichtung aneinandergereihten Leitschaufeln 10, jeweils umfassend eine Plattform 16 und ein in den Strömungskanal 26 strahlenartig hineinragendes Schaufelblatt 14 aufweist, wobei der Strömungskanal 26 plattformseitig von Abschirmelementen 22 begrenzt ist, die jeweils zwischen zwei unmittelbar benachbarten Schaufelblättern 14 angeordnet sind, wobei zur Ausbildung eines besonders platzsparenden Strömungskanalabschnitts 12 die Abschirmelemente 22 unter Spaltbildung an den Plattformen 16 angeordnet und in der Plattform 16 Prallkühlöffnungen 24 vorgesehen sind.Overall, the invention provides an annular flow channel section 12 for a turbomachine comprising a vane ring which has a number of circumferentially juxtaposed vanes 10, each comprising a platform 16 and a radiant manner into the flow channel 26 projecting airfoil 14, wherein the flow channel 26 platform side is limited by shielding 22, which are each arranged between two immediately adjacent airfoils 14, wherein the formation of a particularly space-saving flow channel section 12, the shielding 22 arranged under gap formation on the platforms 16 and in the platform 16th Impact cooling holes 24 are provided.

Claims (6)

Ringförmiger Strömungskanalabschnitt (12) für eine Turbomaschine,
mit einem Leitschaufelkranz, welcher eine Anzahl in Umfangsrichtung aneinandergereihter Leitschaufeln (10) jeweils umfassend einen zur Befestigung vorgesehenen Schaufelfuß, zumindest eine fußseitige Plattform (16) und ein in den Strömungskanal (26) strahlenartig hineinragendes Schaufelblatt (14) aufweist,
wobei der Strömungskanal (26) plattformseitig von Abschirmelementen (22) begrenzt ist, die jeweils zwischen zwei unmittelbar benachbarten Schaufelblättern (14) angeordnet sind,
dadurch gekennzeichnet, dass
die Abschirmelemente (22) unter Spaltbildung an den Plattformen (16) angeordnet und in den Plattformen (16) Prallkühlöffnungen (24) zur Prallkühlung der Abschirmelemente (22) vorgesehen sind.Ring-shaped flow channel section (12) for a turbomachine,
with a vane ring, which has a number of guide vanes (10) lined up in the circumferential direction, each comprising a blade root intended for attachment, at least one foot-side platform (16) and an airfoil (14) radiantly projecting into the flow channel (26),
wherein the flow channel (26) is bounded on the platform side by shielding elements (22) which are each arranged between two immediately adjacent blade leaves (14),
characterized in that
the shielding elements (22) are arranged with gap formation on the platforms (16) and in the platforms (16) impingement cooling openings (24) are provided for impingement cooling of the shielding elements (22). Strömungskanalabschnitt (12) nach Anspruch 1,
bei der die Abschirmelemente (22) jeweils eine den Strömungskanal (26) begrenzende Grundplatte (30) aus einem metallischen Werkstoff aufweisen, welche separat von den Leitschaufeln (10) gefertigt ist.Flow channel section (12) according to claim 1,
in which the shielding elements (22) each have a base plate (30) delimiting the flow channel (26) from a metallic material which is manufactured separately from the guide vanes (10). Strömungskanalabschnitt (12) nach Anspruch 2,
bei der die Wandstärke der Grundplatte (30) geringer ist als die Wandstärke der vom Abschirmelement (22) überdeckten Plattformen (16).Flow channel section (12) according to claim 2,
in which the wall thickness of the base plate (30) is less than the wall thickness of the platforms (16) covered by the shielding element (22). Strömungskanalabschnitt (12) nach Anspruch 2 oder 3, bei der an der Grundplatte (30) quer angeordnete Wandabschnitte (32) vorgesehen sind, welche mit seitlichen Wänden der Plattformen (16) verbindbar sind.A flow channel section (12) according to claim 2 or 3, wherein there are provided on the base plate (30) transversely disposed wall sections (32) connectable to side walls of the platforms (16). Strömungskanalabschnitt (12) nach einem der Ansprüche 1 bis 4,
bei der jedes Abschirmelement (22) einen von den Plattformen (16) unmittelbar benachbarter Leitschaufeln (10) begrenzten Spalt überdeckt.A flow channel section (12) according to any one of claims 1 to 4,
wherein each shielding element (22) covers a gap bounded by the platforms (16) of immediately adjacent vanes (10). Strömungskanalabschnitt (12) nach einem der Ansprüche 1 bis 5,
bei der das Abschirmelement (22) strömungskanalseitig eine Schutzschicht aufweist.A flow channel section (12) according to any one of claims 1 to 5,
in which the shielding element (22) has a protective layer on the flow channel side.
EP09008227A 2009-06-23 2009-06-23 Ring-shaped flow channel section for a turbo engine Withdrawn EP2282014A1 (en)

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EP09008227A EP2282014A1 (en) 2009-06-23 2009-06-23 Ring-shaped flow channel section for a turbo engine
US13/379,530 US20120100008A1 (en) 2009-06-23 2010-06-15 Annular flow channel section for a turbomachine
CN2010800282474A CN102803658A (en) 2009-06-23 2010-06-15 Annular flow channel section for a turbomachine
JP2012516636A JP5443600B2 (en) 2009-06-23 2010-06-15 Annular flow path for turbomachinery
PCT/EP2010/058352 WO2010149528A1 (en) 2009-06-23 2010-06-15 Annular flow channel section for a turbomachine
EP10725431A EP2446119A1 (en) 2009-06-23 2010-06-15 Annular flow channel section for a turbomachine

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EP09008227A EP2282014A1 (en) 2009-06-23 2009-06-23 Ring-shaped flow channel section for a turbo engine

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JP5443600B2 (en) 2014-03-19
CN102803658A (en) 2012-11-28
JP2012530870A (en) 2012-12-06
WO2010149528A1 (en) 2010-12-29
US20120100008A1 (en) 2012-04-26

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