EP1573172B1 - Turbine and working method for dismantling the blades of a turbine - Google Patents

Turbine and working method for dismantling the blades of a turbine Download PDF

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Publication number
EP1573172B1
EP1573172B1 EP03789132A EP03789132A EP1573172B1 EP 1573172 B1 EP1573172 B1 EP 1573172B1 EP 03789132 A EP03789132 A EP 03789132A EP 03789132 A EP03789132 A EP 03789132A EP 1573172 B1 EP1573172 B1 EP 1573172B1
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EP
European Patent Office
Prior art keywords
guide
blade
turbine
clamping device
rotor
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EP03789132A
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German (de)
French (fr)
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EP1573172A1 (en
Inventor
Peter Tiemann
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Siemens AG
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Siemens AG
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings

Definitions

  • the present invention relates to a turbine according to the preamble of claim 1, and a method for removing the guide vanes of a turbine according to the preamble of claim 9.
  • the DE 606 029 discloses the production of a vane ring for steam or gas turbines in which strips or strips are wrapped around two rollers so that they assume an annular shape.
  • the bands or strips are provided with cutouts into which the blade is inserted.
  • weld the vane ring After inserting all blades, weld the vane ring.
  • the blades are first attached to the strips (which form the platforms) by means of spot welding, and the welding is then continued as build-up welding on the outside of the strips until a sufficient thickness of the weld metal has been formed, which is then partially turned off .can.
  • the welded vane ring is clamped in a lathe and processed until a cross-section schwalbenschwaazförmiger coaxial circumferential approach remains. Subsequently, the circumferential approach, ie the one-piece vane ring, mounted in a circular, tensioned by screws or rivets holder.
  • a vane carrier for a gas turbine is known.
  • the guide blade carrier has on its side facing the hot gas channel inside in its axial longitudinal extent a plurality of successively arranged grooves which are annular in the circumferential direction and are each provided with an undercut.
  • the grooves serve to receive vane feet of a vane. For this the foot of a vane is inserted in the circumferential direction in the annular groove.
  • the gas turbine is opened, so that the guide vane carrier is accessible and the guide vanes can be pushed out of the groove.
  • the opening of the gas turbine is time-consuming and requires a corresponding long standstill of the gas turbine.
  • Object of the present invention is to shorten the downtime of the turbine during repair, inspection and / or maintenance.
  • the inventive solution provides that the Leitschaufelfuß and / or Leitschaufelkopf each vane by means of an accessible from the combustion chamber, manually releasable clamping device is or can be fixed.
  • the downtime of a gas turbine can be shortened profitably by the exchangeable vane can be removed through the accessible combustion chamber.
  • at least one clamping device defining the guide blade can be reached from the combustion chamber.
  • One of the Leitschaufelfuß fixing clamping device is provided on the inner housing and / or the other clamping device defines the Leitschaufelkopf and is arranged on the mounting ring.
  • the clamping device can be fixed to the inner housing or to the fastening housing and the Leitschaufelfuß or Leitschaufelkopf clamped in an operating position by means of an axially extending tie rod.
  • the inner housing or the mounting ring serves as an abutment for the clamping device.
  • the tie rod clamps the clamping device once on the inner housing or on the mounting ring and once on the guide vane.
  • At least the part of the clamping device facing the combustion chamber can be removed from the clearance profile of the guide blade after removal of the tie rod for dismantling the guide vane by the combustion chamber.
  • the clearance profile of the vane is described by the contour of the vane, which results from the view of the combustion chamber in the axial direction. The vane is exposed after moving out of the clamping device from the clearance space.
  • the clamping device is fastened in a parking position exposing the vane foot or guide vane head, this can not hinder the removal of the guide vanes. Accidental entanglement of the clamping device with the vane during its removal of the vane is thus bypassed. Furthermore, the clamping device is effectively secured against accidental falling out. Unintentionally dropped components can cause mechanical damage during operation of the gas turbine.
  • the clamping device comprises two radially extending retaining stops, which can be clamped by means of the tie rod.
  • the two holding stops of a clamping device respectively encompass elements of the inner housing as an abutment and at the same time the Leitschaufelfuß or the Leitschaufelkopf.
  • the retaining stops are clamped by means of the tie rod.
  • the guide vane is located in the direction of flow of a working medium first vane row.
  • the guide vane is easier to reach from the combustion chamber.
  • the clamping device is removable after removal of the guide vane from the inner housing.
  • a guide ring arranged downstream in the flow direction of a working medium is manually accessible.
  • the wear-prone guide ring is thus, similar to the guide vane, particularly easily and quickly accessible for maintenance and / or repair work, without the inner casing of the turbine must be opened.
  • the invention provides that a guide blade of the first row of guide blades seen in the flow direction of the working medium is taken out manually through the combustion chamber by the sequence of the following steps:
  • the arranged on the inner housing clamping device is released, moved to a Leitschaufelfuß exposing parking position and fixed there again.
  • the further arranged on the inner mounting ring clamping device is released, so that the Leitschaufelkopf is exposed.
  • the guide vane is axially displaced against the direction of flow of the working medium, possibly moved radially inwards and tilted around the vane head, so that the vane is then free to move radially outward.
  • the Fig. 1 shows a gas turbine 1 in a longitudinal partial section.
  • the gas turbine 1 has inside a rotatably mounted about a rotation axis 2 rotor 3, which is also referred to as a turbine runner.
  • a suction housing 4 Along the rotor 3 follow one another a suction housing 4, a compressor 5, a toroidal annular combustion chamber 6 with a plurality of coaxially arranged burners 7, a turbine 8 and the exhaust housing 9.
  • the annular combustion chamber 6 forms a combustion chamber 17, which communicates with an annular hot gas duct 18.
  • There four successive turbine stages 10 form the turbine 8.
  • Each turbine stage 10 is formed of two blade rings.
  • As seen in the flow direction of a working medium 11 follows in the hot gas channel 18 a Leitschaufelsch 13 a formed of blades 15 row 14.
  • the vanes 12 are attached to the stator 23, whereas the blades 15 of a row 14 are mounted by means of a turbine disk 19 on the rotor 3.
  • air 16 is sucked and compressed by the compressor 4 through the intake housing.
  • the compressed air provided at the turbine-side end of the compressor 5 is led to the burners 7 where it is mixed with a fuel.
  • the mixture is then burned to form the working medium 11 in the combustion chamber 17.
  • the working medium 11 flows along the hot gas channel 18 past the guide vanes 12 and the blades 15.
  • the working fluid 11 relaxes impulsively, so that the blades 15 drive the rotor 3 and this the driven machine coupled to it.
  • the exposed to the hot working fluid 11 components are subject to thermal stresses during operation of the gas turbine 1.
  • the guide vanes 12 and rotor blades 15 of the first turbine stage 10, viewed in the direction of flow of the working medium 11, are subjected to the highest thermal stress in addition to the heat shield bricks which line the annular combustion chamber 6. In order to withstand the temperatures prevailing there, they are cooled by means of a coolant.
  • Fig. 2 shows a section through the partially illustrated annular combustion chamber 6 and through the first turbine stage 10, which is formed from the guide vane 12 and the downstream blade 15.
  • the blades 12, 15 are arranged in a star shape around the rotor 3 of the gas turbine.
  • the blade 15 is seated on a turbine disk 19, which is arranged on the rotor 3, whereas the guide blade 12 on Stator is attached.
  • the vane 12 has a guide blade root 21 facing the inner casing 20 of the turbine 8 and a vane head 22 opposite the vane root 21.
  • the vane head 22 faces the rotor 3 and fixed to a mounting ring 24 of the stator 23.
  • the clamping device 25 Arranged on the guide blade root 21 and on the inner housing 20 is a clamping device 25 in an operating position.
  • the clamping device 25 comprises two retaining stops 26, 27 and a helical tie rod 28, which is only hinted at here.
  • the retaining stop 27 engages around a projection 29 formed on the guide blade root 21, which projection extends parallel to the axial direction of the rotor 3.
  • An extending in the radial direction of the rotor 3 further projection 30 is also formed on the Leitschaufelfuß 21.
  • This projection 30 protrudes between the two holding stops 26, 27 in such a way that they firmly clamp the projection 30 when the tie rod 28 is tensioned.
  • the inner housing 20 serves as an abutment for the clamping device 25, which defines the Leitschaufelfuß 21 and thus also the vane 12 itself.
  • the tie rod 28 extends through the inner housing 20, wherein it extends through an axial bore 32, which is slot-shaped seen in the radial direction. Radially closest to the outside, a projection 31 is arranged on the inner housing 20.
  • a further clamping device 35 is arranged in its operating position on the guide blade head 22 and on the fastening ring 24.
  • This has two holding stops 36, 37 which clamp by means of a tie rod 38 integrally formed on the guide vane head 22, radially projecting third projection 33 on the fastening ring 24.
  • the arranged on the guide blade root 21 clamping device 25 is achieved by the two holding stops 26, 27 are loosened by releasing the tie rod 28 so far that the retaining stop 27, the projection 29 releases. At the same time, the retaining stop 26 is displaced so far in the direction of the annular combustion chamber 6 that the projection 31 can be encompassed by this. Then the clamping device 25, i. the first retaining stop 26, the second retaining stop 27 and the tie rod 28, jointly moved radially outward. For this purpose, the axial bore 32 is formed slot-like in cross-section. In the radially outer position of the tie rod 28 is tensioned again, so that the clamping device 25 is fixed in its parking position. The Leitschaufelfuß 21 is completely released from her. Viewed from the viewpoint of the annular combustion chamber 6, the contour of the first holding stop 26 is located outside the contour of the guide blade root 21, i. the clamping device 25 is located outside the clearance of the guide vane 12th
  • the guide vane head 22 is exposed by, for this purpose, the tie rod 38 of the fastening ring 24 disposed on the clamping device 35 is released, so that the holding stops 36, 37 release a formed on the vane head 22 third projection 33.
  • the movable clamping device 35 is moved so far radially inward that it surrounds a projection 34 of the fastening ring 24. Then the clamping device 35 is braced again, so that it is in its parking position.
  • the clamping device 35 arranged on the guide blade head 22 is located outside the clearance profile of the guide blade 12.
  • the thus-exposed guide blade 12 can now be removed from the guide blade row 13, in which it is displaced counter to the flow direction of the working medium 11 and then slightly radially inward. This displacement is indicated by the arrow 40. Then, the vane 12 is tilted around the vane head 22 in the direction of the combustion chamber 6. Then, the guide vane 12 is moved into the combustion chamber 17 of the annular combustion chamber 6 and the gas turbine 1 removed.

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

Abstract

The invention relates to a turbine (1) and a method for dismantling a blade (12) of a turbine. Said turbine (1 ) comprises a rotor (3) that extends in an axial direction and an accessible combustion chamber (6), which communicates with an annular hot-gas conduit 18, in which a plurality of blades (12) that form a blade row (13) is arranged. Each blade (12) has a blade root (21) that is fixed to the internal housing and a blade head (22) that lies opposite said root (21) and faces the rotor (3), said head being fixed to a fixing ring (24) of the turbine (1) that encircles the rotor (3). The aim of the invention is to reduce the down time of the turbine (1) during repair, inspection and/or maintenance work. To achieve this, the blade root (21) and/or the blade head (22) can be fixed by means of a manually detachable clamping device (25, 35).

Description

Die vorliegende Erfindung betrifft eine Turbine gemäß dem Oberbegriff des Anspruchs 1, und ein Verfahren zum Ausbau der Leitschaufeln einer Turbine gemäß dem Oberbegriff des Anspruchs 9.The present invention relates to a turbine according to the preamble of claim 1, and a method for removing the guide vanes of a turbine according to the preamble of claim 9.

Die DE 606 029 offenbart die Herstellung eines Leitschaufelkranzes für Dampf- oder Gasturbinen, bei denen Bänder oder Streifen um zwei Rollen herumgelegt werden, sodass sie eine ringförmige Gestalt annehmen. Die Bänder oder Streifen sind mit Ausschnitten versehen, in die die Schaufel eingesetzt werden. Nach dem Einsetzen sämtlicher Schaufeln wird die Schweißung des Leitschaufelkranzes vorgenommen. Dabei werden die Schaufeln zunächst mittels Punktschweißungen an den Streifen (welche die Plattformen bilden) befestigt und die schweißung wird dann als Auftragsschweißung auf der Außenseite der Bänder bzw. Streifens solange fortgesetzt, bis eine ausreichend Dicke Schicht des Schweißmetalls gebildet ist, die anschließend teilweise abgedreht werden.kann. Dazu wird der verschweißte Leitschaufelkranz in einer Drehbank eingespannt und bearbeitet, bis ein im Querschnitt schwalbenschwaazförmiger koaxial umlaufender Ansatz verbleibt. Anschließend wird der umlaufende Ansatz, d.h. der einstückige Leitschaufelkranz, in einer kreisförmigen, von Schrauben oder Nieten spannbaren Halterung befestigt.The DE 606 029 discloses the production of a vane ring for steam or gas turbines in which strips or strips are wrapped around two rollers so that they assume an annular shape. The bands or strips are provided with cutouts into which the blade is inserted. After inserting all blades, weld the vane ring. The blades are first attached to the strips (which form the platforms) by means of spot welding, and the welding is then continued as build-up welding on the outside of the strips until a sufficient thickness of the weld metal has been formed, which is then partially turned off .can. For this purpose, the welded vane ring is clamped in a lathe and processed until a cross-section schwalbenschwaazförmiger coaxial circumferential approach remains. Subsequently, the circumferential approach, ie the one-piece vane ring, mounted in a circular, tensioned by screws or rivets holder.

Aus der DE 195 46 722 A1 ist ein Leitschaufelträger für eine Gasturbine bekannt. Der Leitschaufelträger weist an seiner dem Heißgaskanal zugewandten Innenseite in seiner axialen Längsausdehnung mehrere hintereinander angeordnete Nuten auf, die in Umfangsrichtung ringförmig verlaufen und dabei jeweils mit einer Hinterschneidung versehen sind. Die Nuten dienen zur Aufnahme von Leitschaufelfüßen einer Leitschaufel. Hierzu wird der Fuß einer Leitschaufel in Umfangsrichtung in die ringförmig verlaufende Nut eingeschoben.From the DE 195 46 722 A1 For example, a vane carrier for a gas turbine is known. The guide blade carrier has on its side facing the hot gas channel inside in its axial longitudinal extent a plurality of successively arranged grooves which are annular in the circumferential direction and are each provided with an undercut. The grooves serve to receive vane feet of a vane. For this the foot of a vane is inserted in the circumferential direction in the annular groove.

Zu Reparatur-, Revisione- und/oder Wartungsarbeiten an den Leitschaufeln müssen diese aus der Gasturbine ausgebaut werden. Hierzu wird die Gasturbine geöffnet, so dass der Leitschaufelträger zugänglich ist und die Leitschaufeln aus der Nut herauegeschoben werden können. Das Öffnen der Gasturbine ist zeitintensiv und bedingt einen entsprechenden langen Stillstand der Gasturbine.For repair, overhaul and / or maintenance work on the vanes, these must be removed from the gas turbine. For this purpose, the gas turbine is opened, so that the guide vane carrier is accessible and the guide vanes can be pushed out of the groove. The opening of the gas turbine is time-consuming and requires a corresponding long standstill of the gas turbine.

Aufgabe der vorliegenden Erfindung ist es der Ausfallzeiten der Turbine bei Reparatur-, Revisions- und/oder Wartungsarbeiten zu verkürzen.Object of the present invention is to shorten the downtime of the turbine during repair, inspection and / or maintenance.

Die Aufgabe wird durch die Merkmale und Maßnahmen des Anspruchs 1 gelöst. Weitere vorteilhafte Ausgestaltungen der Erfindung sind in den Unteraneprüchen gegeben.The object is solved by the features and measures of claim 1. Further advantageous embodiments of the invention are given in the Unteraneprüchen.

Die erfindungsgemäße Lösung sieht vor, dass der Leitschaufelfuß und/oder Leitschaufelkopf jeder Leitschaufel mittels einer aus der Brennkammer zugänglichen, manuell lösbaren Klemmvorrichtung festlegbar ist bzw. sind. Die Ausfallzeiten einer Gasturbine können gewinnbringend verkürzt werden, indem die auszutauschende Leitschaufel durch die zugängliche Brennkammer entnehmbar ist. Hierzu ist zumindest eine die Leitschaufel festlegende Klemmvorrichtung von der Brennkammer aus erreichbar. Die eine den Leitschaufelfuß festlegende Klemmvorrichtung ist am Innengehäuse vorgesehen und/oder die andere Klemmvorrichtung legt den Leitschaufelkopf fest und ist am Befestigungsring angeordnet. Von der Brennkammer aus ist somit jede Leitschaufel nach dem Lösen der Klemmvorrichtung(en) entnehmbar, ohne dass das Innengehäuse der Turbine geöffnet werden muss.The inventive solution provides that the Leitschaufelfuß and / or Leitschaufelkopf each vane by means of an accessible from the combustion chamber, manually releasable clamping device is or can be fixed. The downtime of a gas turbine can be shortened profitably by the exchangeable vane can be removed through the accessible combustion chamber. For this purpose, at least one clamping device defining the guide blade can be reached from the combustion chamber. One of the Leitschaufelfuß fixing clamping device is provided on the inner housing and / or the other clamping device defines the Leitschaufelkopf and is arranged on the mounting ring. Thus, each vane can be removed from the combustion chamber after loosening the clamping device (s), without having to open the inner casing of the turbine.

In einer vorteilhaften Weiterbildung ist vorgesehen, dass die Klemmvorrichtung am Innengehäuse bzw. am Befestigungsgehäuse festlegbar ist und den Leitschaufelfuß bzw. Leitschaufelkopf in einer Betriebsposition mittels eines in Axialrichtung verlaufenden Zugankers verspannt. Beim Befestigen der Leitschaufel dient das Innengehäuse bzw. der Befestigungsring als Widerlager für die Klemmvorrichtung. Der Zuganker verspannt die Klemmvorrichtung einmal am Innengehäuse bzw. am Befestigungsring und einmal an der Leitschaufel.In an advantageous development, it is provided that the clamping device can be fixed to the inner housing or to the fastening housing and the Leitschaufelfuß or Leitschaufelkopf clamped in an operating position by means of an axially extending tie rod. When mounting the vane, the inner housing or the mounting ring serves as an abutment for the clamping device. The tie rod clamps the clamping device once on the inner housing or on the mounting ring and once on the guide vane.

In einer weiteren Ausgestaltung ist zum Ausbau der Leitschaufel durch die Brennkammer mindestens der der Brennkammer zugewandten Teil der Klemmvorrichtung nach dem Lösen des Zugankers aus dem Lichtraumprofil der Leitschaufel entfernbar. Das Lichtraumprofil der Leitschaufel wird durch die Kontur der Leitschaufel beschrieben, die sich aus Sicht der Brennkammer in Axialrichtung ergibt. Die Leitschaufel ist nach Herausbewegen der Klemmvorrichtung aus dem Lichtraumprofil freigelegt.In a further refinement, at least the part of the clamping device facing the combustion chamber can be removed from the clearance profile of the guide blade after removal of the tie rod for dismantling the guide vane by the combustion chamber. The clearance profile of the vane is described by the contour of the vane, which results from the view of the combustion chamber in the axial direction. The vane is exposed after moving out of the clamping device from the clearance space.

Wenn in einer weiteren Ausgestaltung die Klemmvorrichtung in einer den Leitschaufelfuß bzw. Leitschaufelkopf freilegenden Parkposition befestigt ist, kann diese die Entnahme der Leitschaufeln nicht behindern. Ein versehentliches Verhaken der Klemmvorrichtung mit der Leitschaufel während deren Entnahme der Leitschaufel wird folglich umgangen. Ferner ist die Klemmvorrichtung gegen unbeabsichtigtes Herausfallen wirksam gesichert. Unbeabsichtigt herausgefallene Komponenten können während des Betriebs der Gasturbine zu mechanischen Zerstörungen führen.If, in another embodiment, the clamping device is fastened in a parking position exposing the vane foot or guide vane head, this can not hinder the removal of the guide vanes. Accidental entanglement of the clamping device with the vane during its removal of the vane is thus bypassed. Furthermore, the clamping device is effectively secured against accidental falling out. Unintentionally dropped components can cause mechanical damage during operation of the gas turbine.

In einem vorteilhaften Vorschlag umfasst die Klemmvorrichtung zwei sich radial erstreckende Halteanschläge, die mittels des Zugankers verspannbar sind. Die beiden Halteanschläge einer Klemmvorrichtung umgreifen jeweils Elemente des Innengehäuses als Widerlager und gleichzeitig den Leitschaufelfuß bzw. den Leitschaufelkopf. Zum Festlegen der Leitschaufel am Innengehäuse sind die Halteanschläge mittels des Zugankers verspannbar.In an advantageous proposal, the clamping device comprises two radially extending retaining stops, which can be clamped by means of the tie rod. The two holding stops of a clamping device respectively encompass elements of the inner housing as an abutment and at the same time the Leitschaufelfuß or the Leitschaufelkopf. To fix the guide vane on the inner housing, the retaining stops are clamped by means of the tie rod.

Vorteilhafterweise befindet sich die Leitschaufel in der der in Strömungsrichtung eines Arbeitsmediums gesehen ersten Leitschaufelreihe. Dadurch ist die Leitschaufel von der Brennkammer aus einfacher erreichbar.Advantageously, the guide vane is located in the direction of flow of a working medium first vane row. As a result, the guide vane is easier to reach from the combustion chamber.

Zweckmäßigerweise ist die Klemmvorrichtung nach Entnahme der Leitschaufel vom Innengehäuse entfernbar.Conveniently, the clamping device is removable after removal of the guide vane from the inner housing.

Als besonders vorteilhaft angesehen wird es, wenn nach Entnahme der am Innengehäuse befestigten Klemmvorrichtung ein in Strömungsrichtung eines Arbeitsmediums nachgeordneter Führungsring manuell zugänglich ist. Der verschleißbehaftete Führungsring ist somit, ähnlich der Leitschaufel, besonders leicht und schnell für Wartungs- und/oder Reparaturarbeiten zugänglich, ohne dass das Innengehäuse der Turbine geöffnet werden muss.It is considered particularly advantageous if, after removal of the clamping device attached to the inner housing, a guide ring arranged downstream in the flow direction of a working medium is manually accessible. The wear-prone guide ring is thus, similar to the guide vane, particularly easily and quickly accessible for maintenance and / or repair work, without the inner casing of the turbine must be opened.

Ein Arbeitsverfahren zum Ausbau der Leitschaufeln einer Turbine wird mit den Merkmalen des Anspruchs 9 beschrieben.A working method for the expansion of the guide vanes of a turbine is described with the features of claim 9.

Die Erfindung sieht vor, dass eine Leitschaufel der in Strömungsrichtung des Arbeitsmedium gesehen erste Leitschaufelreihe durch die Abfolge der folgenden Schritte manuell durch die Brennkammer hindurch entnommen wird:The invention provides that a guide blade of the first row of guide blades seen in the flow direction of the working medium is taken out manually through the combustion chamber by the sequence of the following steps:

Die am Innengehäuse angeordnete Klemmvorrichtung wird gelöst, in eine den Leitschaufelfuß freilegende Parkposition verschoben und dort wieder befestigt. Gegebenenfalls wird die weitere am innenliegenden Befestigungsring angeordnete Klemmvorrichtung gelöst, so dass der Leitschaufelkopf freigelegt ist. Daraufhin wird die Leitschaufel entgegen der Strömungsrichtung des Arbeitsmediums axial verschoben, ggf. radial nach innen bewegt und um den Leitschaufelkopf herum gekippt, so dass die Leitschaufel dann nach radialem nach außen Bewegen frei ist. Diese Vorgehensweise vermeidet ein Öffnen der gesamten Turbine und verkürzt die durch Wartungs- und Reparaturzeiten hervorgerufene Ausfallzeiten der Turbine erheblich. Das Parken in einer Parkposition verhindert ein zufälliges Herausfallen der Klemmvorrichtung und ermöglicht so den störungsfreien Ausbau der Leitschaufel.The arranged on the inner housing clamping device is released, moved to a Leitschaufelfuß exposing parking position and fixed there again. Optionally, the further arranged on the inner mounting ring clamping device is released, so that the Leitschaufelkopf is exposed. Then, the guide vane is axially displaced against the direction of flow of the working medium, possibly moved radially inwards and tilted around the vane head, so that the vane is then free to move radially outward. This approach avoids opening the entire turbine and significantly shortens turbine downtime caused by maintenance and repair times. Parking in a parking position prevents accidental falling out of the clamping device and thus allows trouble-free removal of the vane.

Die Erfindung wird anhand einer Zeichnung näher erläutert. Dabei zeigen die Figuren:

Fig. 1
eine Gasturbine in einem Längsteilschnitt und
Fig. 2
die Brennkammer, den Heißgaskanal, die Leit- und Laufschaufel der ersten Turbinenstufe in einem Teilschnitt gemäß Fig. 1.
The invention will be explained in more detail with reference to a drawing. The figures show:
Fig. 1
a gas turbine in a longitudinal section and
Fig. 2
the combustion chamber, the hot gas duct, the guide and blade of the first turbine stage in a partial section according to Fig. 1 ,

Die Fig. 1 zeigt eine Gasturbine 1 in einem Längsteilschnitt. Die Gasturbine 1 weist im Inneren einen um eine Rotationsachse 2 drehgelagerten Rotor 3 auf, der auch als Turbinenläufer bezeichnet wird. Entlang des Rotors 3 folgen aufeinander ein Ansauggehäuse 4, ein Verdichter 5, eine torusartige Ringbrennkammer 6 mit mehreren koaxial angeordneten Brennern 7, eine Turbine 8 und das Abgasgehäuse 9. Die Ringbrennkammer 6 bildet dabei einen Verbrennungsraum 17, der mit einem ringförmigen Heißgaskanal 18 kommuniziert. Dort bilden vier hintereinandergeschaltete Turbinenstufen 10 die Turbine 8. Jede Turbinenstufe 10 ist aus zwei Schaufelringen gebildet. In Strömungsrichtung eines Arbeitsmediums 11 gesehen folgt im Heißgaskanal 18 einer Leitschaufelreihe 13 eine aus Laufschaufeln 15 gebildete Reihe 14. Die Leitschaufeln 12 sind dabei am Stator 23 befestigt, wohingegen die Laufschaufeln 15 einer Reihe 14 mittels einer Turbinenscheibe 19 am Rotor 3 angebracht sind. An dem Rotor 3 angekoppelt ist ein Generator oder eine Arbeitsmaschine (nicht dargestellt).The Fig. 1 shows a gas turbine 1 in a longitudinal partial section. The gas turbine 1 has inside a rotatably mounted about a rotation axis 2 rotor 3, which is also referred to as a turbine runner. Along the rotor 3 follow one another a suction housing 4, a compressor 5, a toroidal annular combustion chamber 6 with a plurality of coaxially arranged burners 7, a turbine 8 and the exhaust housing 9. The annular combustion chamber 6 forms a combustion chamber 17, which communicates with an annular hot gas duct 18. There four successive turbine stages 10 form the turbine 8. Each turbine stage 10 is formed of two blade rings. As seen in the flow direction of a working medium 11 follows in the hot gas channel 18 a Leitschaufelreihe 13 a formed of blades 15 row 14. The vanes 12 are attached to the stator 23, whereas the blades 15 of a row 14 are mounted by means of a turbine disk 19 on the rotor 3. Coupled to the rotor 3 is a generator or work machine (not shown).

Während des Betriebes der Gasturbine 1 wird vom Verdichter 5 durch das Ansauggehäuse 4 Luft 16 angesaugt und verdichtet. Die am turbinenseitigen Ende des Verdichters 5 bereitgestellte verdichtete Luft wird zu den Brennern 7 geführt und dort mit einem Brennmittel vermischt. Das Gemisch wird dann unter Bildung des Arbeitsmediums 11 im Verbrennungsraum 17 verbrannt. Von dort aus strömt das Arbeitsmedium 11 entlang des Heißgaskanals 18 vorbei an den Leitschaufeln 12 und den Laufschaufeln 15. An den Laufschaufeln 15 entspannt sich das Arbeitsmedium 11 impulsübertragend, so dass die Laufschaufeln 15 den Rotor 3 antreiben und dieser die an ihn angekoppelte Arbeitsmaschine.During operation of the gas turbine 1 4 air 16 is sucked and compressed by the compressor 4 through the intake housing. The compressed air provided at the turbine-side end of the compressor 5 is led to the burners 7 where it is mixed with a fuel. The mixture is then burned to form the working medium 11 in the combustion chamber 17. From there, the working medium 11 flows along the hot gas channel 18 past the guide vanes 12 and the blades 15. At the blades 15, the working fluid 11 relaxes impulsively, so that the blades 15 drive the rotor 3 and this the driven machine coupled to it.

Die dem heißen Arbeitsmedium 11 ausgesetzten Bauteile unterliegen während des Betriebes der Gasturbine 1 thermischen Belastungen. Die Leitschaufeln 12 und Laufschaufeln 15 der in Strömungsrichtung des Arbeitsmediums 11 gesehen ersten Turbinenstufe 10 werden neben den die Ringbrennkammer 6 auskleidenden Hitzeschildsteinen am meisten thermisch belastet. Um den dort herrschenden Temperaturen standzuhalten, werden diese mittels eines Kühlmittels gekühlt.The exposed to the hot working fluid 11 components are subject to thermal stresses during operation of the gas turbine 1. The guide vanes 12 and rotor blades 15 of the first turbine stage 10, viewed in the direction of flow of the working medium 11, are subjected to the highest thermal stress in addition to the heat shield bricks which line the annular combustion chamber 6. In order to withstand the temperatures prevailing there, they are cooled by means of a coolant.

Fig. 2 zeigt einen Schnitt durch die teilweise dargestellte Ringbrennkammer 6 und durch die erste Turbinenstufe 10, welche aus der Leitschaufel 12 und der nachgeordneten Laufschaufel 15 gebildet wird. Die Schaufeln 12, 15 sind dabei sternförmig um den Rotor 3 der Gasturbine angeordnet. Die Laufschaufel 15 sitzt auf einer Turbinenscheibe 19, die am Rotor 3 angeordnet ist, wohingegen die Leitschaufel 12 am Stator befestigt ist. Die Leitschaufel 12 weist einen dem Innengehäuse 20 der Turbine 8 zugewandten Leitschaufelfuß 21 und einen dem Leitschaufelfuß 21 gegenüberliegendem Leitschaufelkopf 22 auf. Der Leitschaufelkopf 22 ist dem Rotor 3 zugewandt und an einem Befestigungsring 24 des Stators 23 festgelegt. Fig. 2 shows a section through the partially illustrated annular combustion chamber 6 and through the first turbine stage 10, which is formed from the guide vane 12 and the downstream blade 15. The blades 12, 15 are arranged in a star shape around the rotor 3 of the gas turbine. The blade 15 is seated on a turbine disk 19, which is arranged on the rotor 3, whereas the guide blade 12 on Stator is attached. The vane 12 has a guide blade root 21 facing the inner casing 20 of the turbine 8 and a vane head 22 opposite the vane root 21. The vane head 22 faces the rotor 3 and fixed to a mounting ring 24 of the stator 23.

Am Leitschaufelfuß 21 und am Innengehäuse 20 angeordnet befindet sich eine Klemmvorrichtung 25 in einer Betriebsposition. Die Klemmvorrichtung 25 umfasst zwei Halteanschläge 26, 27 und einen schraubenförmigen Zuganker 28, der hier nur angedeutet ist. Der Halteanschlag 27 umgreift einen am Leitschaufelfuß 21 angeformten Vorsprung 29, der sich parallel zur Axialrichtung des Rotors 3 erstreckt. Ein sich in Radialrichtung des Rotors 3 erstreckender weiterer Vorsprung 30 ist gleichfalls am Leitschaufelfuß 21 angeformt. Dieser Vorsprung 30 ragt zwischen die beiden Halteanschläge 26, 27 derart hinein, dass diese bei verspanntem Zuganker 28 den Vorsprung 30 fest einklemmen. Das Innengehäuse 20 dient als Widerlager für die Klemmvorrichtung 25, die den Leitschaufelfuß 21 und somit auch die Leitschaufel 12 selbst festlegt.Arranged on the guide blade root 21 and on the inner housing 20 is a clamping device 25 in an operating position. The clamping device 25 comprises two retaining stops 26, 27 and a helical tie rod 28, which is only hinted at here. The retaining stop 27 engages around a projection 29 formed on the guide blade root 21, which projection extends parallel to the axial direction of the rotor 3. An extending in the radial direction of the rotor 3 further projection 30 is also formed on the Leitschaufelfuß 21. This projection 30 protrudes between the two holding stops 26, 27 in such a way that they firmly clamp the projection 30 when the tie rod 28 is tensioned. The inner housing 20 serves as an abutment for the clamping device 25, which defines the Leitschaufelfuß 21 and thus also the vane 12 itself.

Der Zuganker 28 verläuft durch das Innengehäuse 20, wobei er sich durch eine Axialbohrung 32 erstreckt, die in Radialrichtung gesehen langlochförmig ist. Davon radial nächst außen ist am Innengehäuse 20 ein Vorsprung 31 angeordnet.The tie rod 28 extends through the inner housing 20, wherein it extends through an axial bore 32, which is slot-shaped seen in the radial direction. Radially closest to the outside, a projection 31 is arranged on the inner housing 20.

Analog zur Anordnung am Leitschaufelfuß 21 ist am Leitschaufelkopf 22 und am Befestigungsring 24 eine weitere Klemmvorrichtung 35 in ihrer Betriebsposition angeordnet. Diese weist zwei Halteanschläge 36, 37 auf, die mittels eines Zugankers 38 einen am Leitschaufelkopf 22 angeformten, radial auskragenden dritten Vorsprung 33 am Befestigungsring 24 einklemmen.Analogous to the arrangement on the guide blade root 21, a further clamping device 35 is arranged in its operating position on the guide blade head 22 and on the fastening ring 24. This has two holding stops 36, 37 which clamp by means of a tie rod 38 integrally formed on the guide vane head 22, radially projecting third projection 33 on the fastening ring 24.

Zum Ausbau der Leitschaufel 12 werden nach dem Freilegen der Klemmvorrichtungen 25, 35 in der von einem Monteur zugänglichen Brennkammer folgende Schritte durchgeführt:To remove the guide vane 12, the following steps are carried out after exposing the clamping devices 25, 35 in the combustion chamber accessible by a fitter:

Die am Leitschaufelfuß 21 angeordnete Klemmvorrichtung 25 wird gelöst, indem durch das Lösen des Zugankers 28 die beiden Halteanschläge 26, 27 soweit gelockert werden, dass der Halteanschlag 27 den Vorsprung 29 freigibt. Gleichzeitig wird der Halteanschlag 26 in Richtung der Ringbrennkammer 6 so weit verschoben, dass der Vorsprung 31 von diesem umgriffen werden kann. Dann wird die Klemmvorrichtung 25, d.h. der erste Halteanschlag 26, der zweite Halteanschlag 27 und der Zuganker 28, gemeinsam radial nach außen bewegt. Dazu ist die Axialbohrung 32 im Querschnitt langlochartig ausgebildet. In der radial äußeren Position wird der Zuganker 28 wieder verspannt, so dass die Klemmvorrichtung 25 sich festgelegt in ihrer Parkposition befindet. Der Leitschaufelfuß 21 ist vollständig von ihr freigegeben. Aus Sicht der Ringbrennkammer 6 betrachtet, befindet sich die Kontur des ersten Halteanschlags 26 außerhalb der Kontur des Leitschaufelfußes 21, d.h. die Klemmvorrichtung 25 befindet sich außerhalb des Lichtraumprofils der Leitschaufel 12.The arranged on the guide blade root 21 clamping device 25 is achieved by the two holding stops 26, 27 are loosened by releasing the tie rod 28 so far that the retaining stop 27, the projection 29 releases. At the same time, the retaining stop 26 is displaced so far in the direction of the annular combustion chamber 6 that the projection 31 can be encompassed by this. Then the clamping device 25, i. the first retaining stop 26, the second retaining stop 27 and the tie rod 28, jointly moved radially outward. For this purpose, the axial bore 32 is formed slot-like in cross-section. In the radially outer position of the tie rod 28 is tensioned again, so that the clamping device 25 is fixed in its parking position. The Leitschaufelfuß 21 is completely released from her. Viewed from the viewpoint of the annular combustion chamber 6, the contour of the first holding stop 26 is located outside the contour of the guide blade root 21, i. the clamping device 25 is located outside the clearance of the guide vane 12th

Analog wird der Leitschaufelkopf 22 freigelegt, indem dazu der Zuganker 38 der am Befestigungsring 24 angeordneten Klemmvorrichtung 35 gelöst wird, so dass die Halteanschläge 36, 37 einen am Leitschaufelkopf 22 angeformten dritten Vorsprung 33 freigeben. Die bewegliche Klemmvorrichtung 35 wird so weit radial nach innen bewegt, dass sie einen Vorsprung 34 des Befestigungsrings 24 umgreift. Dann wird die Klemmvorrichtung 35 wieder verspannt, so dass sie sich in ihrer Parkposition befindet. Analog zu der Klemmvorrichtung 25 am Leitschaufelfuß 21 befindet sich die am Leitschaufelkopf 22 angeordnete Klemmvorrichtung 35 außerhalb des Lichtraumprofils der Leitschaufel 12.Similarly, the guide vane head 22 is exposed by, for this purpose, the tie rod 38 of the fastening ring 24 disposed on the clamping device 35 is released, so that the holding stops 36, 37 release a formed on the vane head 22 third projection 33. The movable clamping device 35 is moved so far radially inward that it surrounds a projection 34 of the fastening ring 24. Then the clamping device 35 is braced again, so that it is in its parking position. Analogous to the clamping device 25 on the guide blade root 21, the clamping device 35 arranged on the guide blade head 22 is located outside the clearance profile of the guide blade 12.

Die so freigelegte Leitschaufel 12 kann nun der Leitschaufelreihe 13 entnommen werden, in dem sie entgegen der Strömungsrichtung des Arbeitsmediums 11 und anschließend geringfügig radial nach innen verschoben wird. Dieser Verschiebeweg ist durch den Pfeil 40 gekennzeichnet. Dann wird die Leitschaufel 12 um den Leitschaufelkopf 22 in Richtung der Brennkammer 6 gekippt. Daraufhin wird die Leitschaufel 12 in den Verbrennungsraum 17 der Ringbrennkammer 6 hineinbewegt und der Gasturbine 1 entnommen.The thus-exposed guide blade 12 can now be removed from the guide blade row 13, in which it is displaced counter to the flow direction of the working medium 11 and then slightly radially inward. This displacement is indicated by the arrow 40. Then, the vane 12 is tilted around the vane head 22 in the direction of the combustion chamber 6. Then, the guide vane 12 is moved into the combustion chamber 17 of the annular combustion chamber 6 and the gas turbine 1 removed.

Claims (9)

  1. Turbine (1) comprising a rotor (3) extending in the axial direction and an accessible combustion chamber (6) which communicates with an annular hot-gas duct (18) in which a multiplicity of guide blades (12) are arranged in such a way as to form a guide-blade row (13), each guide blade (12) having a guide-blade root (21) fixed to the inner casing (20) and a guide-blade tip (22) which is opposite the guide-blade root (21), faces the rotor (3) and is fixed to a fixing ring (24), enclosing the rotor (3), of the turbine (1), characterized in that the guide-blade root (21) and/or the guide-blade tip (22) of each guide blade (12) can be secured by means of a manually releasable clamping device (25, 35) accessible from the combustion chamber.
  2. Turbine (1) according to Claim 1, characterized in that the clamping device (25, 35) can be secured to the inner casing (20) or to the fixing ring (24), respectively, and fastens the guide-blade root (21) or the guide-blade tip (22), respectively, in an operating position by means of a tie rod (28, 38) running in the axial direction.
  3. Turbine (1) according to Claim 1 or 2, characterized in that, to remove the guide blade (12) through the combustion chamber (6), at least that part of the clamping device (25, 35) which faces the combustion chamber (6) can be removed from the clearance profile of the guide blade (12) after the release of the tie rod (28, 38).
  4. Turbine (1) according to one of the preceding claims, characterized in that, to remove the guide blade (12), the clamping device (25, 35) can be fixed in a parking position exposing the guide-blade root (21) or guide-blade tip (22), respectively.
  5. Turbine (1) according to one of the preceding claims, characterized in that the clamping device (25, 35) comprises two radially extending retaining stops (26, 27, 36, 37) which can be fastened by means of the tie rod (28, 38).
  6. Turbine (1) according to one of the preceding claims, characterized in that the guide blade (12) is arranged in the first guide-blade row (13) as viewed in the direction of flow of a working medium (11).
  7. Turbine (1) according to one of the preceding claims, characterized in that the clamping device (25) can be removed from the inner casing (20) after removal of the guide blade (12).
  8. Turbine (1) according to one of the preceding claims, characterized in that a guide ring arranged downstream in the direction of flow of a working medium (11) is manually accessible after removal of the clamping device (25) fixed to the inner casing (20).
  9. Method of removing a guide blade (12) from a turbine (1) comprising a rotor (3) extending in the axial direction and an accessible combustion chamber (6) which communicates with an annular hot-gas duct (18) in which a multiplicity of guide blades (12) are arranged in such a way as to form a guide-blade row (13), each guide blade (12) having a guide-blade root (21) fixed to the inner casing (20) and a guide-blade tip (22) which is opposite the guide-blade root (21), faces the rotor (3) and is fixed to a fixing ring (24), enclosing the rotor (3), of the turbine (1) according to one or more of the preceding claims, characterized in that the guide blade (12) of the first guide-blade row (13) as viewed in the direction of flow of the working medium (11) is removed manually through the combustion chamber (6) by the sequence of the following steps:
    a. the clamping device (25) arranged on the inner casing is released, then displaced into a parking position exposing the guide-blade root (21) and fixed there again,
    b. the other clamping device (35) arranged at the inner fixing ring (24) is released, so that the guide-blade tip (22) is exposed,
    c. the guide blade (12) is displaced axially against the direction of flow of the working medium and is then tilted about the guide-blade tip (22),
    d. so that the guide blade (12) is free by being moved radially outward.
EP03789132A 2002-12-19 2003-12-04 Turbine and working method for dismantling the blades of a turbine Expired - Lifetime EP1573172B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP03789132A EP1573172B1 (en) 2002-12-19 2003-12-04 Turbine and working method for dismantling the blades of a turbine

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
EP02028511 2002-12-19
EP02028511 2002-12-19
PCT/EP2003/013711 WO2004057158A1 (en) 2002-12-19 2003-12-04 Turbine, fixing device for blades and working method for dismantling the blades of a turbine
EP03789132A EP1573172B1 (en) 2002-12-19 2003-12-04 Turbine and working method for dismantling the blades of a turbine

Publications (2)

Publication Number Publication Date
EP1573172A1 EP1573172A1 (en) 2005-09-14
EP1573172B1 true EP1573172B1 (en) 2010-12-01

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EP03789132A Expired - Lifetime EP1573172B1 (en) 2002-12-19 2003-12-04 Turbine and working method for dismantling the blades of a turbine

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US (1) US7290983B2 (en)
EP (1) EP1573172B1 (en)
CN (1) CN100412322C (en)
DE (1) DE50313299D1 (en)
ES (1) ES2356629T3 (en)
WO (1) WO2004057158A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102017204953A1 (en) 2017-03-23 2018-09-27 MTU Aero Engines AG Turbomachine, method and vane system

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1731711A1 (en) * 2005-06-10 2006-12-13 Siemens Aktiengesellschaft Transition from combustion chamber to turbine, heat shield, and turbine vane in a gas turbine
DE102006050907A1 (en) * 2006-10-28 2008-05-15 Man Turbo Ag Guide device of a turbomachine and vane for such a guide device
EP2206885A1 (en) 2009-01-08 2010-07-14 Siemens Aktiengesellschaft Gas turbine
US8863365B2 (en) * 2010-01-22 2014-10-21 Siemens Energy, Inc. Removal of stuck blade in a turbine engine
US9470422B2 (en) * 2013-10-22 2016-10-18 Siemens Energy, Inc. Gas turbine structural mounting arrangement between combustion gas duct annular chamber and turbine vane carrier
EP2868868A1 (en) * 2013-11-05 2015-05-06 Siemens Aktiengesellschaft Mounting device and mounting method of a vane
EP2980359A1 (en) 2014-07-30 2016-02-03 Siemens Aktiengesellschaft Sealing of guide vane heads relative to an internal stator component
US9816387B2 (en) 2014-09-09 2017-11-14 United Technologies Corporation Attachment faces for clamped turbine stator of a gas turbine engine
CN104675450A (en) * 2015-01-30 2015-06-03 北京华清燃气轮机与煤气化联合循环工程技术有限公司 Gas turbine carrier ring fixing structure
CN108005732B (en) * 2017-12-20 2024-04-19 华瑞（江苏）燃机服务有限公司 Dismounting mechanism of turbine stationary blade assembly of gas turbine
US11560806B1 (en) 2021-12-27 2023-01-24 General Electric Company Turbine nozzle assembly

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB368601A (en) * 1931-05-16 1932-03-10 Asea Ab Improvements in method of manufacturing guide blade devices for steam or gas turbines
GB589541A (en) * 1941-09-22 1947-06-24 Hayne Constant Improvements in axial flow turbines, compressors and the like
FR965713A (en) * 1947-05-07 1950-09-20
US2851246A (en) * 1956-10-24 1958-09-09 United Aircraft Corp Turbine or compressor construction and method of assembly
US3067983A (en) * 1958-07-01 1962-12-11 Gen Motors Corp Turbine mounting construction
CS174516B1 (en) * 1974-09-26 1977-04-29
JPS5268610A (en) * 1975-12-04 1977-06-07 Agency Of Ind Science & Technol Supporting device for nozzle-wing in turbo-fan engine
US4511306A (en) * 1982-02-02 1985-04-16 Westinghouse Electric Corp. Combustion turbine single airfoil stator vane structure
US4684320A (en) * 1984-12-13 1987-08-04 United Technologies Corporation Axial flow compressor case
GB8922339D0 (en) * 1989-10-04 1989-11-22 Rolls Royce Plc Improvements in or relating to labyrinth seal structures
DE19546722B4 (en) 1995-12-14 2005-03-31 Alstom Guide vane carrier for a gas turbine
US5848874A (en) * 1997-05-13 1998-12-15 United Technologies Corporation Gas turbine stator vane assembly

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102017204953A1 (en) 2017-03-23 2018-09-27 MTU Aero Engines AG Turbomachine, method and vane system

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US7290983B2 (en) 2007-11-06
EP1573172A1 (en) 2005-09-14
CN1729352A (en) 2006-02-01
DE50313299D1 (en) 2011-01-13
ES2356629T3 (en) 2011-04-11
WO2004057158A1 (en) 2004-07-08
CN100412322C (en) 2008-08-20
US20060251518A1 (en) 2006-11-09

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