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EP1654440B1 - Gas turbine having a sealing element in the area of the vane ring or of the moving blade ring of the turbine part - Google Patents

Gas turbine having a sealing element in the area of the vane ring or of the moving blade ring of the turbine part Download PDF

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Publication number
EP1654440B1
EP1654440B1 EP04740664A EP04740664A EP1654440B1 EP 1654440 B1 EP1654440 B1 EP 1654440B1 EP 04740664 A EP04740664 A EP 04740664A EP 04740664 A EP04740664 A EP 04740664A EP 1654440 B1 EP1654440 B1 EP 1654440B1
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EP
European Patent Office
Prior art keywords
sealing element
guide
ring
turbine
gas turbine
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.)
Expired - Lifetime
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EP04740664A
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German (de)
French (fr)
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EP1654440A1 (en
Inventor
Peter Tiemann
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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Priority to PL04740664T priority Critical patent/PL1654440T3/en
Priority to EP04740664A priority patent/EP1654440B1/en
Publication of EP1654440A1 publication Critical patent/EP1654440A1/en
Application granted granted Critical
Publication of EP1654440B1 publication Critical patent/EP1654440B1/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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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

Definitions

  • the invention relates to an axial gas turbine, arranged in the hot gas duct axially successive vane rings and blade rings. These blade rings are subjected to cooling air from different pressure levels. For sealing between the individual pressure levels, a sealing element is provided.
  • An axial gas turbine comprises a compressor, a combustion chamber and a turbine part.
  • combustion air is highly compressed, which is burned in the combustion chamber with fuel.
  • the resulting hot gas is passed through a hot gas duct in the turbine part.
  • turbine part In the turbine part alternately successive vane rings and blade rings. In each of these blade rings guide vanes are arranged adjacent in the circumferential direction.
  • the temperatures in such a gas turbine can reach values which exceed the melting points of the materials used or intolerably reduce the heat resistance of the materials. For this reason, the components in the hot gas channel are often cooled with a cooling medium. Usually this air is diverted from the compressor as cooling air. The cooling requirement decreases along the flow direction in the hot gas duct. For this reason, a cooling air with a lower pressure level than cooling air for front turbine stages is sufficient for cooling rear turbine stages. In order to keep the cooling air consumption as low as possible, since this reduces the efficiency of the gas turbine, the axially different turbine stages, ie the different blade rings, are acted upon by cooling air from different pressure levels. In the direction of flow further forward blade rings are supplied with compressed air higher pressure than blade rings, which are further downstream in the flow direction.
  • the U.S. Patent 5,833,244 shows a gas turbine seal assembly.
  • the sealing of two adjacent blade rings is achieved here by a labyrinth seal system.
  • Individual sealing elements are arranged in grooves of rotor discs. These sealing segments have transversely to the flow direction and in the axial direction one behind the other arranged tooth-like elevations, which are arranged opposite a vane tip.
  • a circumferential circumferential labyrinth seal system is provided, which is particularly suitable for the seal in large gas turbines.
  • the object of the invention is to provide a sealing system for sealing located between two blade rings of a gas turbine pressure levels, which has a particularly good sealing effect and at the same time is easy to install and inexpensive.
  • this object is achieved by a directed along a turbine axis axial gas turbine comprising a compressor, a combustion chamber and a turbine part, wherein in the turbine part axially successive vane rings and blade rings are arranged in a hot gas duct, wherein in operation a hot gas flows through the hot gas duct and wherein the Leitschaufelkränze and guide rings are cooled with cooling air at different pressure levels, the pressure level decreases in the flow direction of the hot gas between a vane ring and a vane support (79) or between a guide ring and a vane support (79) a sealing element is arranged, which seals the various pressure levels against each other and extends in one piece at least a quarter of a perpendicular to the turbine axis as a center extending circle.
  • the invention pursues the way of extending a sealing element for sealing in the axial direction over a greater circumferential distance.
  • the sealing effect is considerably improved because circumferentially extending sealing boundaries are reduced.
  • the reduction of components facilitates installation.
  • the reduction in components also causes a more cost-effective design.
  • the sealing element extends around half of the circle.
  • the sealing elements are preferably arranged so that in each case a sealing element extends along one of the two housing halves.
  • the sealing element is designed as an annular plate with extending in the radial direction surface having an outer edge and an inner edge.
  • an annular metal sheet is particularly easy to manufacture.
  • the inner edge engages in each corresponding platform grooves, which is provided in the hot gas duct side facing away from a respective platform of vanes of the vane ring or a radially outwardly of the blade ring lying guide ring.
  • the outer edge is disposed in a carrier groove extending in a vane carrier.
  • Vanes have an airfoil that is bordered by a platform. This platform serves to shield the hot gas from the vane carrier. Attached to the platform is a fixture that secures the vane to the vane support. In the axial direction adjacent to a vane ring, a blade ring, the rotor side also leads through platforms on the blades, the hot gas.
  • the surface of the hot gas passage adjacent the vane support is shielded from the hot gas by guide rings facing the rotating blade tips of the blades.
  • the inner edge of the annular sealing plate can be performed.
  • the outer edge is guided in a carrier groove extending in the guide vane carrier.
  • the sealing element with a pressing on its surface screw, the sealing element against the opposite comparativelynuten sidewall and Victoriaernuten sidewall presses, tense.
  • a secure, independent of the operating condition sealing is achieved.
  • Vanes typically have an entanglement with which they are hooked into the vane carrier. Such a hooking then defines an axial fixed point by an axial contact surface between hooking and Leitschaufelani.
  • the sealing element is arranged in the region of the axial fixed points. This position of the sealing element is particularly advantageous in the above-described active approach of the sealing element, since thermal displacements in the region of the axial fixed point are small.
  • the sealing element is preferably arranged away from the region of the axial fixed points. Due to the large temperature differences at standstill and operating state, considerable thermally induced shifts of the blade platforms or guide rings relative to the guide blade carrier result here. By loosely inserting the sealing element in the platform or Leitschaufelaninuten a passive approach is achieved here just by these thermal shifts.
  • the sealing element is pressed during thermal displacement against the groove walls so that no secure seal is achieved.
  • a further projection extending in the circumferential direction is arranged as an axial contact surface for the sealing element.
  • FIG. 1 shows a gas turbine 1.
  • the gas turbine 1 has along a turbine axis 10 directed successively a compressor 3, a combustion chamber 5 and a turbine part 7.
  • the compressor 3 and the turbine part 7 are arranged on a common shaft 9 extending along the turbine axis 10.
  • In the turbine part 7 extends a conically expanding hot gas channel 12.
  • In this hot gas duct 12 protrude guide vanes 11 and blades 13 into it.
  • a plurality of vanes 11 are disposed adjacent to each other in a vane ring 14 in the circumferential direction.
  • a plurality of blades 13 are arranged in a blade ring 16 circumferentially adjacent to each other. Leitschaufelkränze 14 and blade rings 16 alternate in the hot gas duct 12 alternately.
  • ambient air is sucked in by the compressor 3 and compressed to compressor air 15.
  • the compressor air 15 is fed to the combustion chamber 5 and burned there with the addition of fuel to a hot gas 17.
  • the hot gas 17 flows through the hot gas channel 12 and thus past the guide vanes 11 and the rotor blades 13.
  • the shaft 9 is set in rotation, since the blades 13 absorb kinetic energy from the hot gas 17 and transmitted to the shaft 9, with which they are firmly connected.
  • the energy thus obtained from the hot gas 17 may, for. B. are transmitted to a generator for power generation.
  • FIG. 2 shows a cross section through the hot gas channel 12.
  • a portion of the blade ring 16 and a portion of the vane ring 14 are shown.
  • a formed as an annular plate seal member 35 extends between the vane ring 14 and the blade ring 16 in the circumferential direction over half of a circle 41 which is perpendicular to the turbine axis 10.
  • a similar sealing element 35 runs along the second half of the circle 41, so that both sealing elements 35 form a closed circle.
  • the parting line 42 corresponds to a joint not shown in detail for the half-way division of the hot gas duct 12 enclosing the gas turbine housing.
  • the sealing element 35 is flat, with a plan view of the surface F is shown.
  • the surface F is bounded by an outer edge 37 and an inner edge 39 of the sealing element 35.
  • FIG. 3 shows a section of a longitudinal section through the hot gas channel 12. It is a guide blade 11 is shown, which is enclosed in the axial direction on both sides by a respective guide ring 51. A sealing element 35 is appropriate FIG. 2 educated. The exact arrangement is based on FIG. 4 described.
  • the vane 11 is supplied to cooling air 53 from a first pressure level.
  • the guide ring 51 is supplied with cooling air 55 from a second pressure level.
  • the pressure level of the cooling air 53 is higher than that of the cooling air 55, since there is a higher cooling requirement for the guide vane 11 located further forward in the direction of flow of the hot gas 17 than for the guide ring 51 located farther downstream.
  • FIG. 4 shows enlarged a section of FIG. 3 with the sealing element 35.
  • a groove 85 extending in the circumferential direction is introduced on the side facing away from the hot gas.
  • the guide blade 11 on the side facing away from the hot gas channel 12 is opposite a guide vane carrier 79.
  • In Leitschaufelani 79 is in the radial direction of the platform groove 85 opposite a Leitschaufelaninut 83 also extending in the circumferential direction.
  • the sealing element 35 is a corresponding FIG. 2 trained annular metal strip whose inner edge 39 engages in the platform groove 85.
  • the outer edge 37 of the sealing element 35 is located in the Leitschaufelitatinut 83.
  • the axial position of the sealing element 35 is selected in the region of an entanglement 71 of the guide blade 11.
  • This entanglement 71 is used to mount the guide vane 11. Furthermore, with this entanglement 71 by an axial contact surface fixed an axial fixed point 73, as well as a radial fixed point 75 by means of a radial approach surface.
  • thermal expansions of the platform 87 of the guide blade 11 relative to the guide blade carrier 79 are relatively small, so that a good sealing effect is achieved by the active attachment of the sealing element 35, independently of the operating state of the gas turbine.
  • the guide ring 51 is also arranged by a hooking 77 in the guide vane carrier 79. In prior art configurations, i.
  • FIG. 5 shows a further section of a longitudinal section through the hot gas channel 12. It is in turn a guide blade 11 is shown, which is enclosed on both sides of guide rings 51 in the axial direction. Here, however, the sealing element 35 is far away from the axial fixed point 73 arranged. In addition, no device for pressing the sealing element 35 is provided on the groove walls. This will be explained in more detail by FIG. 6 described.
  • FIG. 6 shows a section with the sealing element 35 FIG. 5 ,
  • the sealing element 35 is again arranged with its inner edge 39 in a platform groove 85 and with its outer edge 37 in a Leitschaufelaninut 83.
  • an additional shoulder 91 is formed as an axial contact surface so that it lies approximately in the region of the radial center of the sealing element 35.
  • the platform groove 85 is arranged in the guide ring 51 in the example shown here.
  • the guide ring 51 is movable relative to the vane support 79 to avoid thermal stresses. In operation, temperature differences result in a displacement of the guide ring 51 relative to the guide blade carrier 79. In this way, the sealing element 35 is bent and pressed against the projection 91 in the guide blade carrier 79.
  • This form of passive approach of the sealing element 35 leads to a good sealing effect, at the same time a very low expenditure on equipment is required.
  • the sealing element 35 When mounting the gas turbine 1 or even during a service operation, the sealing element 35 is simply inserted into the Leitschaufelitatinut 83 and the guide vanes 11 or the guide rings 51 mounted, depending on which of the components has the corresponding platform groove 85. Subsequently, either the guide vanes 11 or the guide rings 51 are then mounted in each case, which adjoin the previously installed components.

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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 axiale Gasturbine, bei der im Heißgaskanal angeordnet axial aufeinander Leitschaufelkränze und Laufschaufelkränze folgen. Diese Schaufelkränze werden mit Kühlluft aus unterschiedlichen Druckniveaus beaufschlagt. Zur Abdichtung zwischen den einzelnen Druckniveaus ist ein Dichtungselement vorgesehen.The invention relates to an axial gas turbine, arranged in the hot gas duct axially successive vane rings and blade rings. These blade rings are subjected to cooling air from different pressure levels. For sealing between the individual pressure levels, a sealing element is provided.

Eine axiale Gasturbine umfasst einen Verdichter, eine Brennkammer und ein Turbinenteil. Im Verdichter wird Verbrennungsluft hochverdichtet, die in der Brennkammer mit Brennstoff verbrannt wird. Das dabei entstehende Heißgas wird durch einen Heißgaskanal im Turbinenteil geleitet. Im Turbinenteil folgen abwechselnd aufeinander Leitschaufelkränze und Laufschaufelkränze. In jedem dieser Schaufelkränze sind Leit- bzw. Laufschaufeln in Umfangsrichtung benachbart angeordnet.An axial gas turbine comprises a compressor, a combustion chamber and a turbine part. In the compressor combustion air is highly compressed, which is burned in the combustion chamber with fuel. The resulting hot gas is passed through a hot gas duct in the turbine part. In the turbine part alternately successive vane rings and blade rings. In each of these blade rings guide vanes are arranged adjacent in the circumferential direction.

Die Temperaturen in einer solchen Gasturbine können Werte erreichen, die die Schmelzpunkte der verwendbaren Materialien überschreiten bzw. die Warmfestigkeit der Materialien intolerabel reduzieren. Aus diesem Grunde werden die Komponenten im Heißgaskanal häufig mit einem Kühlmedium gekühlt. Meistens wird hierzu Luft aus dem Verdichter als Kühlluft abgezweigt. Der Kühlbedarf sinkt entlang der Strömungsrichtung im Heißgaskanal. Aus diesem Grunde reicht zur Kühlung hinterer Turbinenstufen eine Kühlluft mit geringerem Druckniveau als Kühlluft für vordere Turbinenstufen. Um den Kühlluftverbrauch möglichst gering zu halten, da dieser die Effizienz der Gasturbine mindert, werden die axial unterschiedlichen Turbinenstufen, d.h. die unterschiedlichen Schaufelkränze, mit Kühlluft aus unterschiedlichen Druckniveaus beaufschlagt. In Strömungsrichtung weiter vorne liegende Schaufelkränze werden mit Druckluft höheren Druckes versorgt als Schaufelkränze, die in Strömungsrichtung weiter hinten liegen.The temperatures in such a gas turbine can reach values which exceed the melting points of the materials used or intolerably reduce the heat resistance of the materials. For this reason, the components in the hot gas channel are often cooled with a cooling medium. Mostly this air is diverted from the compressor as cooling air. The cooling requirement decreases along the flow direction in the hot gas duct. For this reason, a cooling air with a lower pressure level than cooling air for front turbine stages is sufficient for cooling rear turbine stages. In order to keep the cooling air consumption as low as possible, since this reduces the efficiency of the gas turbine, the axially different turbine stages, ie the different blade rings, are acted upon by cooling air from different pressure levels. In the direction of flow further forward blade rings are supplied with compressed air higher pressure than blade rings, which are further downstream in the flow direction.

Aus dieser unterschiedlichen Versorgung auch benachbart liegender Schaufelkränze folgt die Notwendigkeit einer Abdichtung zwischen den verschiedenen Druckniveaus. Eine Abdichtung ist auch notwendig, um die Einmischung von Heißgas in die Kühlluft, und damit eine geringere Kühlwirkung, zu vermeiden.From this different supply of adjacent vane rings follows the need for a seal between the different pressure levels. A seal is also necessary to avoid the interference of hot gas in the cooling air, and thus a lower cooling effect.

Die US-PS 5,833,244 zeigt eine Gasturbinendichtanordnung. Die Abdichtung zweier benachbarter Schaufelkränze wird hier durch ein Labyrinthdichtungssystem erreicht. Einzelne Dichtungselemente werden in Nuten von Läuferscheiben angeordnet. Diese Dichtsegmente weisen quer zur Strömungsrichtung verlaufende und in axialer Richtung hintereinander angeordnete zahnartige Erhebungen auf, die gegenüber einer Leitschaufelspitze angeordnet sind. Durch die Nebeneinanderanordnung in Umfangsrichtung solcher Segmente wird ein in Umfangsrichtung umlaufendes Labyrinthdichtungssystem bereitgestellt, das insbesondere auch für die Dichtung in großen Gasturbinen geeignet ist.The U.S. Patent 5,833,244 shows a gas turbine seal assembly. The sealing of two adjacent blade rings is achieved here by a labyrinth seal system. Individual sealing elements are arranged in grooves of rotor discs. These sealing segments have transversely to the flow direction and in the axial direction one behind the other arranged tooth-like elevations, which are arranged opposite a vane tip. By the juxtaposition in the circumferential direction of such segments, a circumferential circumferential labyrinth seal system is provided, which is particularly suitable for the seal in large gas turbines.

Von dem Dichtungssystem zwischen zwei Schaufelkränzen in axialer Richtung ist zu unterscheiden eine Dichtungsanordnung die in Umfangsrichtung zwischen Schaufeln ein und desselben Schaufelkranzes wirkt. Eine solche Umfangsdichtung dient zur Abschirmung des im Heißgaskanal strömenden Heißgases gegen die Rotorscheiben oder Leitschaufelträger. Solche Anordnungen sind beispielsweise der US-PS 5,785,499 oder US-PS 6,273,683 zu entnehmen.From the sealing system between two blade rings in the axial direction is to distinguish a sealing arrangement which acts in the circumferential direction between blades of one and the same blade ring. Such a peripheral seal serves to shield the hot gas flowing in the hot gas duct against the rotor disks or guide blade carrier. Such arrangements are for example the U.S. Patent 5,785,499 or U.S. Patent 6,273,683 refer to.

Aufgabe der Erfindung ist es, ein Dichtungssystem zur Abdichtung zwischen zwei Schaufelkränzen einer Gasturbine befindlichen Druckniveaus anzugeben, das eine besonders gute Dichtwirkung aufweist und dabei gleichzeitig einfach einbaubar und kostengünstig ist.The object of the invention is to provide a sealing system for sealing located between two blade rings of a gas turbine pressure levels, which has a particularly good sealing effect and at the same time is easy to install and inexpensive.

Erfindungsgemäß wird diese Aufgabe gelöst durch eine entlang einer Turbinenachse gerichtete axiale Gasturbine, umfassend einen Verdichter, eine Brennkammer und ein Turbinenteil, wobei im Turbinenteil axial aufeinanderfolgend Leitschaufelkränze und Laufschaufelkränze in einem Heißgaskanal angeordnet sind, wobei im Betrieb ein Heißgas durch den Heißgaskanal strömt und wobei die Leitschaufelkränze und Führungsringe mit Kühlluft unterschiedlichem Druckniveaus gekühlt werden, deren Druckniveau in Strömungsrichtung des Heißgases abnimmt wobei zwischen einem Leitschaufelkranz und einem Leitschaufelträger (79) oder zwischen einem Führungsring und einem Leitschaufelträger (79) ein Dichtungselement angeordnet ist, welches die verschiedenen Druckniveaus gegeneinander abdichtet und sich um zumindest ein Viertel eines senkrecht auf der Turbinenachse als Mittelpunkt verlaufenden Kreises einstückig erstreckt.According to the invention this object is achieved by a directed along a turbine axis axial gas turbine comprising a compressor, a combustion chamber and a turbine part, wherein in the turbine part axially successive vane rings and blade rings are arranged in a hot gas duct, wherein in operation a hot gas flows through the hot gas duct and wherein the Leitschaufelkränze and guide rings are cooled with cooling air at different pressure levels, the pressure level decreases in the flow direction of the hot gas between a vane ring and a vane support (79) or between a guide ring and a vane support (79) a sealing element is arranged, which seals the various pressure levels against each other and extends in one piece at least a quarter of a perpendicular to the turbine axis as a center extending circle.

Mit der Erfindung wird somit erstmalig der Weg verfolgt, ein Dichtungselement zur Abdichtung in axialer Richtung über eine größere Umfangsdistanz erstrecken zu lassen. Hierdurch wird die Dichtwirkung erheblich verbessert, da in Umfangsrichtung verlaufende Dichtgrenzen reduziert werden. Weiterhin wird durch die Reduzierung von Bauelementen eine Einbaubarkeit erleichtert. Die Reduzierung an Bauelementen bewirkt zudem auch eine kostengünstigere Ausführung.Thus, for the first time, the invention pursues the way of extending a sealing element for sealing in the axial direction over a greater circumferential distance. As a result, the sealing effect is considerably improved because circumferentially extending sealing boundaries are reduced. Furthermore, the reduction of components facilitates installation. The reduction in components also causes a more cost-effective design.

Vorzugsweise erstreckt sich das Dichtungselement um die Hälfte des Kreises. Somit werden pro abzudichtender Stufe nur noch zwei Dichtelemente benötigt. Bei einem Gasturbinengehäuse, welches aus zwei Hälften besteht, die in einer Teilfuge ineinander greifen, werden die Dichtungselemente bevorzugt so angeordnet, dass jeweils ein Dichtungselement sich entlang einer der beiden Gehäusehälften erstreckt. Hierdurch wird insbesondere auch eine Ausbaubarkeit oder Austauschbarkeit bei einem Servicevorgang an der Gasturbine erleichtert.Preferably, the sealing element extends around half of the circle. Thus, only two sealing elements are required per stage to be sealed. In a gas turbine housing, which consists of two halves, which engage in a parting line, the sealing elements are preferably arranged so that in each case a sealing element extends along one of the two housing halves. As a result, in particular a expandability or interchangeability in a service operation on the gas turbine is facilitated.

Bevorzugt ist das Dichtungselement als ein ringförmiges Blech mit sich in radialer Richtung erstreckender Fläche mit einer Außenkante und einer Innenkante ausgebildet. Ein solches ringförmiges Blech ist fertigungstechnisch besonders einfach herstellbar.Preferably, the sealing element is designed as an annular plate with extending in the radial direction surface having an outer edge and an inner edge. Such an annular metal sheet is particularly easy to manufacture.

Weiter bevorzugt greift die Innenkante in jeweils korrespondierenden Plattformnuten ein, die in der dem Heißgaskanal abgewandten Seite von einer jeweiligen Plattform von Leitschaufeln des Leitschaufelkranzes oder eines radial außerhalb des Laufschaufelkranzes liegenden Führungsringes vorgesehen ist. Die Außenkante ist in einer in einem Leitschaufelträger verlaufenden Trägernut angeordnet. Leitschaufeln weisen ein Schaufelblatt auf, an das eine Plattform grenzt. Diese Plattform dient der Abschirmung des Heißgases vom Leitschaufelträger. An die Plattform schließt eine Befestigungsvorrichtung an, mit der die Leitschaufel im Leitschaufelträger befestigt wird. In axialer Richtung grenzt an einen Leitschaufelkranz ein Laufschaufelkranz, der rotorseitig ebenfalls durch Plattformen an den Laufschaufeln das Heißgas führt. Die an den Leitschaufelträger grenzende Oberfläche des Heißgaskanals wird durch Führungsringe vom Heißgas abgeschirmt, die den rotierenden Schaufelspitzen der Laufschaufeln gegenüberliegen. Durch Nuten in den Leitschaufeln eines Leitschaufelkranzes kann die Innenkante des ringförmigen Dichtbleches geführt werden. Die Außenkante wird in einer im Leitschaufelträger verlaufenden Trägernut geführt.More preferably, the inner edge engages in each corresponding platform grooves, which is provided in the hot gas duct side facing away from a respective platform of vanes of the vane ring or a radially outwardly of the blade ring lying guide ring. The outer edge is disposed in a carrier groove extending in a vane carrier. Vanes have an airfoil that is bordered by a platform. This platform serves to shield the hot gas from the vane carrier. Attached to the platform is a fixture that secures the vane to the vane support. In the axial direction adjacent to a vane ring, a blade ring, the rotor side also leads through platforms on the blades, the hot gas. The surface of the hot gas passage adjacent the vane support is shielded from the hot gas by guide rings facing the rotating blade tips of the blades. By grooves in the vanes of a vane ring, the inner edge of the annular sealing plate can be performed. The outer edge is guided in a carrier groove extending in the guide vane carrier.

Zum Einbau des Dichtelementes ist somit lediglich ein Einlegen in die genannten Nuten erforderlich bzw. das Dichtungselement wird in die Leitschaufelträgernut eingelegt und anschließend die Leitschaufeln so montiert, dass das Dichtungselement in den Plattformnuten zu liegen kommt.For installation of the sealing element thus only one insertion into said grooves is required or the sealing element is inserted into the Leitschaufelträgernut and then the vanes mounted so that the sealing element comes to lie in the platform grooves.

Bevorzugt wird das Dichtungselement mit einer auf seine Fläche drückenden Schraube, die das Dichtungselement gegen die gegenüberliegende Plattformnutenseitenwand und Trägernutenseitenwand drückt, verspannt. Mit einem solchen aktiven Ansatz des Dichtungselementes wird eine sichere, vom Betriebszustand unabhängige Abdichtung erreicht. Weiter bevorzugt wird das Dichtungselement mit einer Vielzahl von Schrauben, vorzugsweise pro Schaufel eines Schaufelkranzes eine Schraube, verspannt.Preferably, the sealing element with a pressing on its surface screw, the sealing element against the opposite Plattformnuten sidewall and Trägerernuten sidewall presses, tense. With such an active approach of the sealing element a secure, independent of the operating condition sealing is achieved. More preferably, the sealing element with a plurality of screws, preferably per blade of a blade ring a screw braced.

Leitschaufeln weisen in der Regel eine Verhakung auf, mit der sie in den Leitschaufelträger eingehakt werden. Eine solche Verhakung definiert dann einen axialen Festpunkt durch eine axiale Anlagefläche zwischen Verhakung und Leitschaufelträger. Bevorzugt ist das Dichtungselement im Bereich der axialen Festpunkte angeordnet. Diese Lage des Dichtungselementes ist insbesondere beim oben beschriebenen aktiven Ansatz des Dichtungselementes von Vorteil, da thermische Verschiebungen im Bereich des axialen Festpunktes gering sind.Vanes typically have an entanglement with which they are hooked into the vane carrier. Such a hooking then defines an axial fixed point by an axial contact surface between hooking and Leitschaufelträger. Preferably, the sealing element is arranged in the region of the axial fixed points. This position of the sealing element is particularly advantageous in the above-described active approach of the sealing element, since thermal displacements in the region of the axial fixed point are small.

Wird kein aktiver Ansatz des Dichtungselementes gewählt, so ist das Dichtungselement vorzugsweise entfernt vom Bereich der axialen Festpunkte angeordnet. Hier ergeben sich durch die großen Temperaturunterschiede bei Stillstand und Betriebszustand erhebliche thermisch induzierte Verschiebungen der Schaufelplattformen bzw. Führungsringe gegenüber dem Leitschaufelträger. Durch das lose Einlegen des Dichtungselementes in die Plattform bzw. Leitschaufelträgernuten wird ein passiver Ansatz hier gerade durch diese thermischen Verschiebungen erreicht. Das Dichtungselement wird bei der thermischen Verschiebung so gegen die Nutwände gedrückt, dass keine sichere Abdichtung erreicht wird. Weiter bevorzugt wird zusätzlich zu den Nutwänden im Leitschaufelträger ein weiterer in Umfangsrichtung verlaufender Vorsprung als axiale Anlagefläche für das Dichtungselement angeordnet.If no active approach of the sealing element is selected, then the sealing element is preferably arranged away from the region of the axial fixed points. Due to the large temperature differences at standstill and operating state, considerable thermally induced shifts of the blade platforms or guide rings relative to the guide blade carrier result here. By loosely inserting the sealing element in the platform or Leitschaufelträgernuten a passive approach is achieved here just by these thermal shifts. The sealing element is pressed during thermal displacement against the groove walls so that no secure seal is achieved. Further preferably, in addition to the groove walls in the guide blade carrier, a further projection extending in the circumferential direction is arranged as an axial contact surface for the sealing element.

Beim oben beschriebenen aktiven Ansatz für das Dichtungselement wird bevorzugt erst der Leitschaufelkranz bei einer Montage durch Einbau der Leitschaufeln vervollständigt und anschließend dann die benachbarten Führungsringe eingebaut.In the above-described active approach for the sealing element, it is preferable to first complete the vane ring during installation by installing the guide vanes, and then then to install the adjacent guide rings.

Die Erfindung wird anhand der Zeichnungen beispielhaft näher erläutert. Gleiche Bezugszeichen haben in den verschiedenen Figuren die gleiche Bedeutung.The invention will be explained in more detail by way of example with reference to the drawings. Like reference numerals have the same meaning in the various figures.

Es zeigen teilweise schematisch und nicht maßstäblich:

  • Figur 1 eine Gasturbine,
  • Figur 2 einen Querschnitt durch das Turbinenteil einer Gasturbine,
  • Figur 3 einen Ausschnitt eines Längsschnittes durch den Heißgaskanal der Gasturbine,
  • Figur 4 eine vergrößerte Ansicht mit einem Dichtungselement aus Figur 3,
  • Figur 5 einen weiteren Ausschnitt eines Längsschnittes durch eine Gasturbine und
  • Figur 6 eine Vergrößerung mit einem Dichtungselement aus Figur 5.
They show partly schematically and not to scale:
  • FIG. 1 a gas turbine,
  • FIG. 2 a cross section through the turbine part of a gas turbine,
  • FIG. 3 a section of a longitudinal section through the hot gas duct of the gas turbine,
  • FIG. 4 an enlarged view with a sealing element FIG. 3 .
  • FIG. 5 a further section of a longitudinal section through a gas turbine and
  • FIG. 6 an enlargement with a sealing element FIG. 5 ,

Figur 1 zeigt eine Gasturbine 1. Die Gasturbine 1 weist entlang einer Turbinenachse 10 gerichtet aufeinanderfolgend einen Verdichter 3, eine Brennkammer 5 und ein Turbinenteil 7 auf. Der Verdichter 3 und das Turbinenteil 7 sind auf einer gemeinsamen, entlang der Turbinenachse 10 sich erstreckenden Welle 9 angeordnet. Im Turbinenteil 7 verläuft ein sich konisch erweiternder Heißgaskanal 12. In diesen Heißgaskanal 12 ragen Leitschaufeln 11 und Laufschaufeln 13 hinein. Eine Vielzahl von Leitschaufeln 11 ist in einem Leitschaufelkranz 14 in Umfangsrichtung zueinander benachbart angeordnet. Eine Vielzahl von Laufschaufeln 13 sind in einem Laufschaufelkranz 16 in Umfangsrichtung zueinander benachbart angeordnet. Leitschaufelkränze 14 und Laufschaufelkränze 16 wechseln im Heißgaskanal 12 alternierend ab. FIG. 1 shows a gas turbine 1. The gas turbine 1 has along a turbine axis 10 directed successively a compressor 3, a combustion chamber 5 and a turbine part 7. The compressor 3 and the turbine part 7 are arranged on a common shaft 9 extending along the turbine axis 10. In the turbine part 7 extends a conically expanding hot gas channel 12. In this hot gas duct 12 protrude guide vanes 11 and blades 13 into it. A plurality of vanes 11 are disposed adjacent to each other in a vane ring 14 in the circumferential direction. A plurality of blades 13 are arranged in a blade ring 16 circumferentially adjacent to each other. Leitschaufelkränze 14 and blade rings 16 alternate in the hot gas duct 12 alternately.

Im Betrieb der Gasturbine 1 wird Umgebungsluft vom Verdichter 3 angesaugt und zu Verdichterluft 15 komprimiert. Die Verdichterluft 15 wird der Brennkammer 5 zugeführt und dort unter Zugabe von Brennstoff zu einem Heißgas 17 verbrannt. Das Heißgas 17 strömt durch den Heißgaskanal 12 und damit an den Leitschaufeln 11 und den Laufschaufeln 13 vorbei. Dabei wird die Welle 9 in Rotation versetzt, da die Laufschaufeln 13 kinetische Energie aus dem Heißgas 17 aufnehmen und auf die Welle 9 übertragen, mit der sie fest verbunden sind. Die so aus dem Heißgas 17 gewonnene Energie kann z. B. auf einen Generator zur Stromerzeugung übertragen werden.During operation of the gas turbine 1, ambient air is sucked in by the compressor 3 and compressed to compressor air 15. The compressor air 15 is fed to the combustion chamber 5 and burned there with the addition of fuel to a hot gas 17. The hot gas 17 flows through the hot gas channel 12 and thus past the guide vanes 11 and the rotor blades 13. In this case, the shaft 9 is set in rotation, since the blades 13 absorb kinetic energy from the hot gas 17 and transmitted to the shaft 9, with which they are firmly connected. The energy thus obtained from the hot gas 17 may, for. B. are transmitted to a generator for power generation.

Figur 2 zeigt einen Querschnitt durch den Heißgaskanal 12. Ein Teil des Laufschaufelkranzes 16 und ein Teil des Leitschaufelkranzes 14 sind dargestellt. Ein als ringförmiges Blech ausgebildetes Dichtungselement 35 erstreckt sich zwischen dem Leitschaufelkranz 14 und dem Laufschaufelkranz 16 in Umfangsrichtung über die Hälfte eines Kreises 41, der senkrecht zur Turbinenachse 10 verläuft. Ein gleichartiges Dichtungselement 35 verläuft entlang der zweiten Hälfte des Kreises 41, so dass beide Dichtungselemente 35 einen geschlossenen Kreis bilden. An einer Teilfuge 42 treffen die beiden Dichtungselemente 35 aufeinander. Die Teilfuge 42 entspricht einer nicht näher dargestellten Fuge zur hälftigen Aufteilung des den Heißgaskanal 12 umschließenden Gasturbinengehäuses. Das Dichtungselement 35 ist flächig, wobei eine Aufsicht auf die Fläche F gezeigt ist. Die Fläche F wird von einer Außenkante 37 und einer Innenkante 39 des Dichtungselementes 35 begrenzt. FIG. 2 shows a cross section through the hot gas channel 12. A portion of the blade ring 16 and a portion of the vane ring 14 are shown. A formed as an annular plate seal member 35 extends between the vane ring 14 and the blade ring 16 in the circumferential direction over half of a circle 41 which is perpendicular to the turbine axis 10. A similar sealing element 35 runs along the second half of the circle 41, so that both sealing elements 35 form a closed circle. At a parting line 42, the two sealing elements 35 meet each other. The parting line 42 corresponds to a joint not shown in detail for the half-way division of the hot gas duct 12 enclosing the gas turbine housing. The sealing element 35 is flat, with a plan view of the surface F is shown. The surface F is bounded by an outer edge 37 and an inner edge 39 of the sealing element 35.

Figur 3 zeigt einen Ausschnitt eines Längsschnittes durch den Heißgaskanal 12. Es ist eine Leitschaufel 11 dargestellt, die in axialer Richtung zu beiden Seiten von jeweils einem Führungsring 51 eingeschlossen ist. Ein Dichtungselement 35 ist entsprechend Figur 2 ausgebildet. Die genaue Anordnung wird anhand von Figur 4 beschrieben. Der Leitschaufel 11 wird Kühlluft 53 aus einem ersten Druckniveau zugeführt. Dem Führungsring 51 wird Kühlluft 55 aus einem zweiten Druckniveau zugeführt. Das Druckniveau der Kühlluft 53 ist höher als das der Kühlluft 55, da für die in Strömungsrichtung des Heißgases 17 weiter vorne liegende Leitschaufel 11 ein höherer Kühlbedarf besteht als für den in Strömungsrichtung weiter hinten gelegenen Führungsring 51. Diese axiale Stufung der Druckniveaus von Kühlluft ist ein Grund für die Notwendigkeit einer Abdichtung zwischen Leitschaufel 11 und Führungsring 51. Ein weiterer Grund ist die möglichst weitgehende Reduzierung von Einmischungen von Heißgas in die Kühlluft 53, 55, um eine daraus folgende Aufheizung der Kühlluft und damit eine schlechtere Kühlbarkeit zu vermeiden. Das hier dargestellte Dichtungselement wird mittels eines aktiven Ansatzes gegen axiale Flächen gepresst, wodurch die Dichtwirkung erzeugt wird. Dies wird näher anhand von Figur 4 erläutert. FIG. 3 shows a section of a longitudinal section through the hot gas channel 12. It is a guide blade 11 is shown, which is enclosed in the axial direction on both sides by a respective guide ring 51. A sealing element 35 is appropriate FIG. 2 educated. The exact arrangement is based on FIG. 4 described. The vane 11 is supplied to cooling air 53 from a first pressure level. The guide ring 51 is supplied with cooling air 55 from a second pressure level. The pressure level of the cooling air 53 is higher than that of the cooling air 55, since there is a higher cooling requirement for the guide vane 11 located further forward in the direction of flow of the hot gas 17 than for the guide ring 51 located farther downstream. This axial graduation of the pressure levels of cooling air is a Another reason is the greatest possible reduction of interference of hot gas in the cooling air 53, 55, to avoid consequent heating of the cooling air and thus a lower cooling ability. The sealing element shown here is pressed by means of an active approach against axial surfaces, whereby the sealing effect is generated. This will be explained in more detail by FIG. 4 explained.

Figur 4 zeigt vergrößert einen Ausschnitt aus Figur 3 mit dem Dichtungselement 35. In einer Plattform 87 der Leitschaufel 11 ist an der dem Heißgas abgewandten Seite eine in Umfangsrichtung verlaufende Nut 85 eingebracht. Der Leitschaufel 11 auf der dem Heißgaskanal 12 abgewandten Seite liegt ein Leitschaufelträger 79 gegenüber. Im Leitschaufelträger 79 ist in radialer Richtung der Plattformnut 85 gegenüberliegend eine Leitschaufelträgernut 83 ebenfalls in Umfangsrichtung verlaufend angeordnet. Das Dichtungselement 35 ist ein entsprechend Figur 2 ausgebildeter ringförmiger Blechstreifen, dessen Innenkante 39 in die Plattformnut 85 eingreift. Die Außenkante 37 des Dichtungselementes 35 liegt in der Leitschaufelträgernut 83. Zwischen Leitschaufel 11 und einem benachbarten Führungsring 51 sind weiterhin Umfangsdichtungen 91 eingebracht, die den Spalt zwischen dem Führungsring 51 und der Plattform 87 zwischen jeweils zwei Leitschaufeln 11 eines Leitschaufelkranzes abdichten. Das Dichtungselement 35 wird mittels einer Anpressvorrichtung 61 an die Seitenwände einerseits der Plattformnut 85 und andererseits der Leitschaufelträgernut 83 gepresst. Hierzu wird ein Anpresskeil 65, der in einer Nut 67 der Anpressvorrichtung 61 geführt wird, mittels einer Schraube 63 etwa in der radialen Mitte des Dichtungselementes 35 gegen dieses gepresst. FIG. 4 shows enlarged a section of FIG. 3 with the sealing element 35. In a platform 87 of the guide vane 11, a groove 85 extending in the circumferential direction is introduced on the side facing away from the hot gas. The guide blade 11 on the side facing away from the hot gas channel 12 is opposite a guide vane carrier 79. In Leitschaufelträger 79 is in the radial direction of the platform groove 85 opposite a Leitschaufelträgernut 83 also extending in the circumferential direction. The sealing element 35 is a corresponding FIG. 2 trained annular metal strip whose inner edge 39 engages in the platform groove 85. The outer edge 37 of the sealing element 35 is located in the Leitschaufelträgernut 83. Between the guide blade 11 and an adjacent guide ring 51 are further circumferential seals 91 is introduced, the gap between the guide ring 51 and the platform 87 between two vanes 11 of a Seal the vane ring. The sealing element 35 is pressed by means of a pressing device 61 against the side walls on the one hand of the platform groove 85 and on the other side of the guide blade carrier groove 83. For this purpose, a pressure wedge 65, which is guided in a groove 67 of the pressing device 61, pressed by means of a screw 63 approximately in the radial center of the sealing element 35 against this.

Die axiale Position des Dichtungselementes 35 ist im Bereich einer Verhakung 71 der Leitschaufel 11 gewählt. Diese Verhakung 71 dient der Montage der Leitschaufel 11. Weiterhin wird mit dieser Verhakung 71 durch eine axiale Anpressfläche ein axialer Festpunkt 73 festgelegt, wie auch ein radialer Festpunkt 75 mittels einer radialen Ansatzfläche. Im Bereich des axialen Festpunktes 73 sind thermische Ausdehnungen der Plattform 87 der Leitschaufel 11 gegenüber dem Leitschaufelträger 79 relativ gering, so dass durch den aktiven Ansatz des Dichtungselementes 35 unabhängig vom Betriebszustand der Gasturbine eine gute Dichtwirkung erzielt wird. Der Führungsring 51 ist ebenfalls durch eine Verhakung 77 im Leitschaufelträger 79 angeordnet. In Konfigurationen gemäss dem Stand der Technik, d.h. ohne das Dichtungselement 35, wurde häufig eine axiale Dichtung mittels der Verhakungen 71 und 77 versucht zu erreichen. Hierzu mussten vergleichsweise geringe Toleranzen eingehalten werden, um möglichst geringe Spalte der Verhakungen 71, 77 im Leitschaufelträger 79 zu erreichen. Dies erschwert die Fertigung und Montage. Mittels des Dichtungselementes 35 ist nunmehr eine einfachere und kostengünstigere und dabei aber sicher abdichtende Möglichkeit zur axialen Abdichtung gegeben.The axial position of the sealing element 35 is selected in the region of an entanglement 71 of the guide blade 11. This entanglement 71 is used to mount the guide vane 11. Furthermore, with this entanglement 71 by an axial contact surface fixed an axial fixed point 73, as well as a radial fixed point 75 by means of a radial approach surface. In the region of the axial fixed point 73, thermal expansions of the platform 87 of the guide blade 11 relative to the guide blade carrier 79 are relatively small, so that a good sealing effect is achieved by the active attachment of the sealing element 35, independently of the operating state of the gas turbine. The guide ring 51 is also arranged by a hooking 77 in the guide vane carrier 79. In prior art configurations, i. without the sealing member 35, an axial seal by means of entanglements 71 and 77 has often been attempted to be achieved. For this purpose, comparatively small tolerances had to be maintained in order to achieve the smallest possible gap of the entanglements 71, 77 in the guide vane carrier 79. This complicates the production and assembly. By means of the sealing element 35 is now given a simpler and more cost-effective and yet safe sealing possibility for axial sealing.

Figur 5 zeigt einen weiteren Ausschnitt eines Längsschnittes durch den Heißgaskanal 12. Es ist wiederum eine Leitschaufel 11 dargestellt, die in axialer Richtung beidseitig von Führungsringen 51 eingeschlossen wird. Hier ist das Dichtungselement 35 aber weit entfernt vom axialen Festpunkt 73 angeordnet. Zudem ist keine Vorrichtung zum Anpressen des Dichtungselementes 35 an die Nutwände vorgesehen. Dies wird näher anhand von Figur 6 beschrieben. FIG. 5 shows a further section of a longitudinal section through the hot gas channel 12. It is in turn a guide blade 11 is shown, which is enclosed on both sides of guide rings 51 in the axial direction. Here, however, the sealing element 35 is far away from the axial fixed point 73 arranged. In addition, no device for pressing the sealing element 35 is provided on the groove walls. This will be explained in more detail by FIG. 6 described.

Figur 6 zeigt einen Ausschnitt mit dem Dichtungselement 35 aus Figur 5. Das Dichtungselement 35 ist wie schon oben beschrieben wiederum mit seiner Innenkante 39 in einer Plattformnut 85 und mit seiner Außenkante 37 in einer Leitschaufelträgernut 83 angeordnet. Im Leitschaufelträger 79 ist ein zusätzlicher Absatz 91 als axiale Anlagefläche so ausgebildet, dass er etwa im Bereich der radialen Mitte des Dichtungselementes 35 liegt. Die Plattformnut 85 ist im hier gezeigten Beispiel im Führungsring 51 angeordnet. Der Führungsring 51 ist zur Vermeidung von thermischen Spannungen gegenüber dem Leitschaufelträger 79 beweglich. Im Betrieb kommt es durch Temperaturunterschiede zu einer Verschiebung des Führungsringes 51 gegenüber dem Leitschaufelträger 79. Hierdurch wird das Dichtungselement 35 verbogen und gegen den Vorsprung 91 im Leitschaufelträger 79 gepresst. Diese Form des passiven Ansatzes des Dichtungselementes 35 führt zu einer guten Dichtwirkung, wobei gleichzeitig ein sehr niedriger apparativer Aufwand erforderlich ist. FIG. 6 shows a section with the sealing element 35 FIG. 5 , As already described above, the sealing element 35 is again arranged with its inner edge 39 in a platform groove 85 and with its outer edge 37 in a Leitschaufelträgernut 83. In the vane support 79, an additional shoulder 91 is formed as an axial contact surface so that it lies approximately in the region of the radial center of the sealing element 35. The platform groove 85 is arranged in the guide ring 51 in the example shown here. The guide ring 51 is movable relative to the vane support 79 to avoid thermal stresses. In operation, temperature differences result in a displacement of the guide ring 51 relative to the guide blade carrier 79. In this way, the sealing element 35 is bent and pressed against the projection 91 in the guide blade carrier 79. This form of passive approach of the sealing element 35 leads to a good sealing effect, at the same time a very low expenditure on equipment is required.

Bei einer Montage der Gasturbine 1 oder auch bei einem Servicevorgang wird das Dichtungselement 35 einfach in die Leitschaufelträgernut 83 eingelegt und die Leitschaufeln 11 oder die Führungsringe 51 montiert, je nachdem welches der Bauteile die korrespondierende Plattformnut 85 aufweist. Anschließend werden dann jeweils entweder die Leitschaufeln 11 oder die Führungsringe 51 montiert, die an die vorher eingebauten Bauteile angrenzen.When mounting the gas turbine 1 or even during a service operation, the sealing element 35 is simply inserted into the Leitschaufelträgernut 83 and the guide vanes 11 or the guide rings 51 mounted, depending on which of the components has the corresponding platform groove 85. Subsequently, either the guide vanes 11 or the guide rings 51 are then mounted in each case, which adjoin the previously installed components.

Claims (7)

  1. Axial gas turbine (1) directed along a turbine axis (10) and comprising a compressor (3), a combustion chamber (5) and a turbine part (7), with guide vane rings (11) and rotor blade rings (13) being arranged in axial succession in a hot-gas duct (12) in the turbine part (7), a hot gas (17) flowing through the hot-gas duct (12) in operation, and the guide vane rings (11) and a guide ring (51) opposite a rotor blade ring (13) each being cooled by cooling air (53, 55) of varying pressure levels, the pressure level of which decreases in the direction of flow of the hot gas (17),
    characterized in that
    a sealing element (35), which seals off the different pressure levels with respect to one another and extends as a single piece around at least a quarter of a circle (41) running perpendicularly on the turbine axis as its center point, is arranged between a guide vane ring (11) and a guide vane carrier (79) or between a guide ring (51) and a guide vane carrier (79).
  2. Gas turbine (1) according to Claim 1,
    in which the sealing element (35) extends over half the circle (41).
  3. Gas turbine (1) according to Claim 1 or 2,
    in which the sealing element (35) is formed as an annular metal sheet with a surface F extending in the radial direction and having an outer edge (37) and an inner edge (39).
  4. Gas turbine (1) according to Claim 3,
    in which the inner edge (39) is engaged in respectively corresponding platform grooves (85), which is provided in the side remote from the hot-gas duct (12) of a respective platform (87) of guide vanes (14) of the guide vane ring (11) or of a guide ring (89) located radially outside the rotor blade ring (13), and the outer edge (37) is arranged in a carrier groove (83) running within a guide vane carrier (79).
  5. Gas turbine (1) according to Claim 4,
    in which the sealing element (35) is clamped using a screw (65) which presses on its surface F and presses the sealing element (35) onto the opposite platform groove side wall and carrier groove side wall.
  6. Gas turbine (1) according to Claim 5,
    in which the guide vanes (14) each have an axial fixed point (73), at which they are fixed against axial displacement in the guide vane carrier (79) by means of a suitable hooked formation (71), with the sealing element (35) being arranged in the region of the axial fixed points (73).
  7. Gas turbine (1) according to Claim 3,
    in which the guide vanes (14) each have an axial fixed point (73), at which they are fixed against axial displacement in the guide vane carrier (11) by means of a suitable hooked formation (71), with the sealing element (35) being arranged remote from the region of the axial fixed points (73).
EP04740664A 2003-08-11 2004-07-05 Gas turbine having a sealing element in the area of the vane ring or of the moving blade ring of the turbine part Expired - Lifetime EP1654440B1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
PL04740664T PL1654440T3 (en) 2003-08-11 2004-07-05 Gas turbine having a sealing element in the area of the vane ring or of the moving blade ring of the turbine part
EP04740664A EP1654440B1 (en) 2003-08-11 2004-07-05 Gas turbine having a sealing element in the area of the vane ring or of the moving blade ring of the turbine part

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP03018240 2003-08-11
PCT/EP2004/007333 WO2005019602A1 (en) 2003-08-11 2004-07-05 Gas turbine having a sealing element between the vane ring and the moving blade ring of the turbine part
EP04740664A EP1654440B1 (en) 2003-08-11 2004-07-05 Gas turbine having a sealing element in the area of the vane ring or of the moving blade ring of the turbine part

Publications (2)

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EP1654440A1 EP1654440A1 (en) 2006-05-10
EP1654440B1 true EP1654440B1 (en) 2009-01-07

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EP04740664A Expired - Lifetime EP1654440B1 (en) 2003-08-11 2004-07-05 Gas turbine having a sealing element in the area of the vane ring or of the moving blade ring of the turbine part

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US (1) US7303371B2 (en)
EP (1) EP1654440B1 (en)
CN (1) CN100395431C (en)
DE (1) DE502004008830D1 (en)
ES (1) ES2316994T3 (en)
PL (1) PL1654440T3 (en)
WO (1) WO2005019602A1 (en)

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US9963989B2 (en) * 2013-06-12 2018-05-08 United Technologies Corporation Gas turbine engine vane-to-transition duct seal
EP3039316B1 (en) * 2013-08-30 2020-10-21 United Technologies Corporation Sliding seal
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PL1654440T3 (en) 2009-06-30
WO2005019602A1 (en) 2005-03-03
ES2316994T3 (en) 2009-04-16
DE502004008830D1 (en) 2009-02-26
EP1654440A1 (en) 2006-05-10
US7303371B2 (en) 2007-12-04
CN1833094A (en) 2006-09-13
US20060245915A1 (en) 2006-11-02
CN100395431C (en) 2008-06-18

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