EP2696039A1 - Gas turbine stage - Google Patents

Gas turbine stage Download PDF

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Publication number
EP2696039A1
EP2696039A1 EP12179978.7A EP12179978A EP2696039A1 EP 2696039 A1 EP2696039 A1 EP 2696039A1 EP 12179978 A EP12179978 A EP 12179978A EP 2696039 A1 EP2696039 A1 EP 2696039A1
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EP
European Patent Office
Prior art keywords
gas turbine
wall
circumferential groove
sealing ring
turbine stage
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP12179978.7A
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German (de)
French (fr)
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EP2696039B1 (en
Inventor
Hans-Peter Dr. Hackenberg
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MTU Aero Engines AG
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MTU Aero Engines AG
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Publication date
Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Priority to EP12179978.7A priority Critical patent/EP2696039B1/en
Priority to ES12179978.7T priority patent/ES2547340T3/en
Priority to US13/959,021 priority patent/US20140044537A1/en
Publication of EP2696039A1 publication Critical patent/EP2696039A1/en
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Publication of EP2696039B1 publication Critical patent/EP2696039B1/en
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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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/243—Flange connections; Bolting arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/711—Shape curved convex

Definitions

  • the present invention relates to a gas turbine stage, in particular a low-pressure compressor stage, with a vane assembly and a sealing ring element, a gas turbine, in particular an aircraft gas turbine engine with one or more such gas turbine stages, and a vane assembly and a sealing ring member for such a gas turbine.
  • an inner wall of one of a vane assembly and a sealing ring member engages a circumferential groove of the other of the vane assembly and the sealing ring member.
  • the inner wall has, according to in-house practice in a development in the circumferential direction or in a plan view of the spoke centering a rectangular cross section with two opposite, the Nutinnen vom the circumferential groove facing end faces and two against this by 90 ° angled flanks in one edge into each other pass.
  • the object of the present invention is to provide an improved gas turbine.
  • a gas turbine in particular an aircraft gas turbine engine, one or more gas turbine stages, in particular low-pressure compressor stages, which according to another aspect of the present invention each have a vane assembly with one or more vanes with a radially inner Leitschaufelfuß. Two or more vanes may be connected together in a development, in particular integrally.
  • a sealing ring element On the vane a sealing ring element is supported by a spokes centering, which has an inner wall and a circumferential groove receiving this.
  • a circumferential groove is understood as meaning, in particular, a recess or recess circulating in the circumferential direction and bounded on both sides by, in particular, parallel, groove inner surfaces.
  • a sealing ring element may be part of a multi-part closed sealing ring.
  • a one-piece sealing ring is generally referred to as a sealing ring element in the sense of the present invention.
  • the inner wall has one or more, in particular two opposite, preferably parallel end faces, each facing a Nutinnen dye the circumferential groove and in an undeformed state in particular, at least substantially, can be oriented normal to an axial direction of the gas turbine stage.
  • This adjacent, in particular connecting these, the inner wall one or more, in particular two opposing, preferably parallel flanks, which are each angled against the adjacent (s) end faces or form an angle with these, preferably greater than 75 ° and / or may be less than 105 °.
  • a rounding in particular a radius, is formed between at least one of these end faces and at least one of these flanks.
  • a rounding means in particular, a connecting surface which is mono- or multiply, in particular convexly curved, which may in particular have radially extending straight generatrices, wherein in one development the rounding can be formed kink-free or with continuous curvature.
  • the inner wall of the spoke centering can be connected to the guide blade root, in particular integrally, and the circumferential groove can be formed on the sealing ring element.
  • the inner wall with the sealing ring member, in particular integrally connected and the circumferential groove may be formed on the Leitschaufelfuß.
  • a vane assembly for the gas turbine (n-stage) described herein having an inner wall connected thereto for receiving in a circumferential groove to form a spoke centering of the seal member on the vane assembly, the inner wall at least one of a Nutinnen character the circumferential groove facing end face and one of these adjacent, against this angled edge, and wherein between the end face and the flank a rounding, in particular a radius is formed.
  • the present embodiments in particular advantageous developments, therefore relate equally to such a vane arrangement or such a sealing ring element, a gas turbine stage and a gas turbine with such a spoke centering.
  • the inner wall has at least one radial groove for receiving a sliding element, in particular a sliding block connected to the circumferential groove, for forming the spoke centering.
  • this radius has at least 25%, in particular at least 30%, of a width of the flank.
  • a width of a flank is understood in particular to mean its axial width or the wall thickness of the inner wall.
  • the radius may be at least 0.5 mm, in particular at least 10 mm, and preferably at least 15 mm.
  • a rounding can in particular together with the inner wall or its end face (s) and flank (s) urgeformt, in particular cast. Additionally or alternatively, the fillet may preferably be reshaped and / or machined or made.
  • a rounding can be hardened, in particular by a corresponding thermal method and / or a coating. As a result, in particular the wear in the area of the rounding can be further reduced.
  • the present invention is particularly advantageous for the spoke centering of a brush seal element.
  • a vane arrangement may have a torsion preferential direction, which may for example result from a setting and / or a profile of the guide vanes or the like.
  • this is understood in particular to mean a torsional direction about a radial axis into which the guide vane (s) of the vane arrangement are twisted during operation with increasing flow and / or power of the gas turbine (n-stage).
  • a rounding is then provided in particular also or only at one end of the end face (s) in the circumferential direction, which is delivered in torsion in the Torsionsvorzugsraum against the adjacent Nutinnen Diagram.
  • Fig. 1 shows a meridian section of a portion of a gas turbine with a gas turbine stage with a vane assembly according to an embodiment of the present invention.
  • Guide vane assembly shown in a perspective view has a plurality of integrally connected vanes 1 with a common, radially inner Leitschaufelfuß 1.1, from which a common inner wall 1.2 from a side facing away from the vane blade (bottom in Fig. 1 . 2 ) of the guide blade root 1.1 starting radially inward (down in Fig. 1 . 2 ).
  • a radial groove 1.3 is formed in the inner wall 1.2 a radial groove 1.3 is formed.
  • a sliding block is arranged radially movable, which is connected to a circumferential groove with two legs 2.1, 2.2, which is formed in a brush seal ring element 2.
  • the brush seal element 2 is mounted on the guide vane arrangement in a memory-centered manner.
  • the inner wall 1.2 which is disposed between the two legs 2.1, 2.2 of the circumferential groove of the brush seal member 2, two parallel planar axial end faces 1.4, which are oriented in an undeformed position of the vanes 3 normal to an axial direction of the gas turbine (n) stage ie in Fig. 3 run vertically.
  • These two end faces 1.4 are connected by two parallel planar flanks 1.5, which are angled perpendicular to the end faces 1.4.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The stage has a guide vane assembly comprising a guide vane with a radially inner guide vane root. A brush-type sealing ring element is supported on the guide vane root by a spoke-type centering. The centering comprises circumferential grooves (2.1, 2.2) for receiving an inner wall (1.2). The inner wall has a front surface (1.4) facing a groove inner surface of the circumferential grooves. An edge (1.5) is fixed adjacent to the inner surface. A rounded portion i.e. radius (R), is formed between the front surface and the edge. The inner wall is provided with a radial groove.

Description

Die vorliegende Erfindung betrifft eine Gasturbinenstufe, insbesondere eine Niederdruckverdichterstufe, mit einer Leitschaufelanordnung und einem Dichtringelement, eine Gasturbine, insbesondere eine Flugantrieb-Gasturbine mit einer oder mehreren solcher Gasturbinenstufen, sowie eine Leitschaufelanordnung und ein Dichtringelement für eine solche Gasturbine.The present invention relates to a gas turbine stage, in particular a low-pressure compressor stage, with a vane assembly and a sealing ring element, a gas turbine, in particular an aircraft gas turbine engine with one or more such gas turbine stages, and a vane assembly and a sealing ring member for such a gas turbine.

Aus der WO 2002/090720 A1 ist eine Leitschaufelanordnung bekannt, an der ein Bürstendichtring über eine sogenannte Speichenzentrierung gelagert ist. Auf die Offenbarung dieser gattungsbildenden Druckschrift wird daher zur Vermeidung unnötiger Redundanz vollinhaltlich Bezug genommen und diese ausdrücklich in die Offenbarung der vorliegenden Erfindung einbezogen.From the WO 2002/090720 A1 a vane arrangement is known, on which a brush sealing ring is mounted via a so-called spoke centering. The disclosure of this generic document is therefore incorporated by reference for avoiding unnecessary redundancy and expressly incorporated in the disclosure of the present invention.

Bei einer gattungsgemäßen Speichenzentrierung greift eine Innenwand von dem einen von einer Leitschaufelanordnung und einem Dichtringelement in eine Umfangsnut von dem anderen von der Leitschaufelanordnung und dem Dichtringelement ein. Die Innenwand weist dabei nach betriebsinterner Praxis in einer Abwicklung in Umfangsrichtung bzw. in einer Draufsicht auf die Speichenzentrierung einen recheckigen Querschnitt mit zwei einander gegenüberliegenden, den Nutinnenflächen der Umfangsnut zugewandten Stirnflächen und zwei gegen diese um 90° abgewinkelte Flanken auf, die in einer Kante ineinander übergehen.In a generic spoke centering, an inner wall of one of a vane assembly and a sealing ring member engages a circumferential groove of the other of the vane assembly and the sealing ring member. The inner wall has, according to in-house practice in a development in the circumferential direction or in a plan view of the spoke centering a rectangular cross section with two opposite, the Nutinnenflächen the circumferential groove facing end faces and two against this by 90 ° angled flanks in one edge into each other pass.

Kommt es, insbesondere aufgrund von Druck- und/oder Temperaturlast, zu einer Torsionsverformung der Leitschaufelanordnung, insbesondere einer Torsion von Leitschaufeln um die radiale Richtung, kann dies zu einem Anliegen einer oder zweier einander diagonal gegenüberliegenden Kanten an den Nutinnenflächen kommen. Dies kann insbesondere zu lokalen Spannungsspitzen und/oder erhöhtem Verschleiß führen.If, in particular due to pressure and / or temperature load, a torsional deformation of the vane arrangement, in particular a torsion of vanes about the radial direction, this can lead to a concern of one or two diagonally opposite edges on the Nutinnenflächen. This can in particular lead to local stress peaks and / or increased wear.

Aufgabe der vorliegenden Erfindung ist es, eine verbesserte Gasturbine zur Verfügung zu stellen.The object of the present invention is to provide an improved gas turbine.

Diese Aufgabe wird durch eine Gasturbinenstufe mit den Merkmalen des Anspruchs 1, eine Gasturbine nach Anspruch 11 mit einer oder mehreren solchen Gasturbinenstufen, sowie eine Leitschaufelanordnung nach Anspruch 12 bzw. ein Dichtringelement nach Anspruch 13 für eine solche Gasturbine gelöst. Vorteilhafte Weiterbildungen sind Gegenstand der Unteransprüche.This object is achieved by a gas turbine stage having the features of claim 1, a gas turbine according to claim 11 having one or more such gas turbine stages, and a vane assembly according to claim 12 or a sealing ring element according to claim 13 solved for such a gas turbine. Advantageous developments are the subject of the dependent claims.

Nach einem Aspekt der vorliegenden Erfindung weist eine Gasturbine, insbesondere eine Flugantrieb-Gasturbine, eine oder mehrere Gasturbinenstufen, insbesondere Niederdruckverdichterstufen, auf, die nach einem weiteren Aspekt der vorliegenden Erfindung je eine Leitschaufelanordnung mit einer oder mehreren Leitschaufeln mit einem radial inneren Leitschaufelfuß aufweisen. Zwei oder mehrere Leitschaufeln können in einer Weiterbildung, insbesondere integral, miteinander verbunden sein.According to one aspect of the present invention, a gas turbine, in particular an aircraft gas turbine engine, one or more gas turbine stages, in particular low-pressure compressor stages, which according to another aspect of the present invention each have a vane assembly with one or more vanes with a radially inner Leitschaufelfuß. Two or more vanes may be connected together in a development, in particular integrally.

An der Leitschaufel ist ein Dichtringelement durch eine Speichenzentrierung gelagert, die eine Innenwand und eine diese aufnehmende Umfangsnut aufweist. Unter einer Umfangsnut wird vorliegend insbesondere eine in Umfangsrichtung umlaufende, beidseitig durch, insbesondere parallele, Nutinnenflächen begrenzte, Vertiefung bzw. Aussparung verstanden. Ein Dichtringelement kann ein Teil eines mehrteilig ausgebildeten geschlossenen Dichtringes sein. Zur kompakteren Darstellung wird auch ein einteiliger Dichtring verallgemeinernd als Dichtringelement im Sinne der vorliegenden Erfindung bezeichnet.On the vane a sealing ring element is supported by a spokes centering, which has an inner wall and a circumferential groove receiving this. In the present case, a circumferential groove is understood as meaning, in particular, a recess or recess circulating in the circumferential direction and bounded on both sides by, in particular, parallel, groove inner surfaces. A sealing ring element may be part of a multi-part closed sealing ring. For a more compact representation, a one-piece sealing ring is generally referred to as a sealing ring element in the sense of the present invention.

Die Innenwand weist eine oder mehrere, insbesondere zwei einander gegenüberliegende, vorzugsweise parallele Stirnflächen auf, die jeweils einer Nutinnenfläche der Umfangsnut zugewandt sind und in einem unverformten Zustand insbesondere, wenigstens im Wesentlichen, normal zu einer Axialrichtung der Gasturbinenstufe orientiert sein können. Diesen benachbart, insbesondere diese verbindend, weist die Innenwand eine oder mehrere, insbesondere zwei einander gegenüberliegende, vorzugsweise parallele Flanken auf, die jeweils gegen die benachbarte(n) Stirnseiten abgewinkelt sind bzw. mit diesen einen Winkel bilden, der vorzugsweise größer als 75° und/oder kleiner als 105° sein kann.The inner wall has one or more, in particular two opposite, preferably parallel end faces, each facing a Nutinnenfläche the circumferential groove and in an undeformed state in particular, at least substantially, can be oriented normal to an axial direction of the gas turbine stage. This adjacent, in particular connecting these, the inner wall one or more, in particular two opposing, preferably parallel flanks, which are each angled against the adjacent (s) end faces or form an angle with these, preferably greater than 75 ° and / or may be less than 105 °.

Nach einem Aspekt der vorliegenden Erfindung ist zwischen wenigstens einer dieser Stirnflächen und wenigstens einer dieser Flanken jeweils eine Verrundung, insbesondere ein Radius ausgebildet. Unter einer Verrundung wird vorliegend insbesondere eine ein- oder mehrfach, insbesondere konvex gekrümmte Verbindungsfläche verstanden, die insbesondere sich radial erstreckende geraden Erzeugende aufweisen kann, wobei in einer Weiterbildung die Verrundung knickfrei bzw. mit stetigem Krümmungsverlauf ausgebildet sein kann.According to one aspect of the present invention, a rounding, in particular a radius, is formed between at least one of these end faces and at least one of these flanks. In the present case, a rounding means, in particular, a connecting surface which is mono- or multiply, in particular convexly curved, which may in particular have radially extending straight generatrices, wherein in one development the rounding can be formed kink-free or with continuous curvature.

Indem nach diesem Aspekt anstelle der bisher betriebsintern bekannten Kanten, die zu lokalen Spannungsspitzen und/oder erhöhtem Verschleiß führen können, eine Verrundung zwischen der der Nutinnenfläche zugewandten Stirnseite und der dieser benachbarten Flanke ausgebildet wird, kann, insbesondere bei einer leitschaufeltorsionsbedingten schiefen Anlage der Innenwand an eine oder beide Nutinnenflächen vorteilhafterweise die auftretende Belastung und/oder der Verschleiß reduziert werden.According to this aspect, instead of the previously known internal edges, which can lead to local stress peaks and / or increased wear, a rounding between the Nutinnenfläche facing end side and the adjacent edge is formed, can, especially in a Leitschaufeltorsionsbedingten oblique system of the inner wall one or both Nutinnenflächen advantageously the occurring load and / or wear can be reduced.

Wie einleitend ausgeführt, kann die Innenwand der Speichenzentrierung mit dem Leitschaufelfuß, insbesondere integral, verbunden und die Umfangsnut an dem Dichtringelement ausgebildet sein. Gleichermaßen kann umgekehrt die Innenwand mit dem Dichtringelement, insbesondere integral, verbunden und die Umfangsnut an dem Leitschaufelfuß ausgebildet sein. Entsprechend betreffen weitere Aspekte der vorliegenden Erfindung eine Leitschaufelanordnung bzw. ein Dichtringelement für die vorliegend beschriebene Gasturbine(nstufe), mit einer damit verbundenen Innenwand, die zur Aufnahme in einer Umfangsnut zur Ausbildung einer Speichenzentrierung des Dichtringelements an der Leitschaufelanordnung vorgesehen ist, wobei die Innenwand wenigstens eine einer Nutinnenfläche der Umfangsnut zugewandte Stirnfläche und eine dieser benachbarte, gegen diese abgewinkelte Flanke aufweist, und wobei zwischen der Stirnfläche und der Flanke eine Verrundung, insbesondere ein Radius ausgebildet ist. Die vorliegenden Ausführungen, insbesondere vorteilhafte Weiterbildungen, beziehen sich daher gleichermaßen auf eine solche Leitschaufelanordnung bzw. ein solches Dichtringelement, eine Gasturbinenstufe und eine Gasturbine mit einer solchen Speichenzentrierung.As stated in the introduction, the inner wall of the spoke centering can be connected to the guide blade root, in particular integrally, and the circumferential groove can be formed on the sealing ring element. Similarly, vice versa, the inner wall with the sealing ring member, in particular integrally connected and the circumferential groove may be formed on the Leitschaufelfuß. Accordingly, further aspects of the present invention relate to a vane assembly for the gas turbine (n-stage) described herein, having an inner wall connected thereto for receiving in a circumferential groove to form a spoke centering of the seal member on the vane assembly, the inner wall at least one of a Nutinnenfläche the circumferential groove facing end face and one of these adjacent, against this angled edge, and wherein between the end face and the flank a rounding, in particular a radius is formed. The present embodiments, in particular advantageous developments, therefore relate equally to such a vane arrangement or such a sealing ring element, a gas turbine stage and a gas turbine with such a spoke centering.

In einer Ausführung der vorliegenden Erfindung weist die Innenwand wenigstens eine Radialnut zur Aufnahme eines Gleitelements, insbesondere eines mit der Umfangsnut verbundenen Gleitsteins, zur Ausbildung der Speichenzentrierung auf.In one embodiment of the present invention, the inner wall has at least one radial groove for receiving a sliding element, in particular a sliding block connected to the circumferential groove, for forming the spoke centering.

In einer Weiterbildung der Ausführung, nach der die Verrundung ein Radius ist bzw. eine konstante Krümmung aufweist, weist dieser Radius wenigstens 25%, insbesondere wenigstens 30% einer Breite der Flanke auf. Unter einer Breite einer Flanke wird insbesondere ihre axiale Breite bzw. die Wandstärke der Innenwand verstanden. Insbesondere kann der Radius wenigstens 0,5 mm, insbesondere wenigstens 10 mm und vorzugsweise wenigstens 15 mm betragen.In a further development of the embodiment, according to which the rounding is a radius or has a constant curvature, this radius has at least 25%, in particular at least 30%, of a width of the flank. A width of a flank is understood in particular to mean its axial width or the wall thickness of the inner wall. In particular, the radius may be at least 0.5 mm, in particular at least 10 mm, and preferably at least 15 mm.

Eine Verrundung kann insbesondere zusammen mit der Innenwand bzw. deren Stirnfläche(n) und Flanke(n) urgeformt, insbesondere gegossen, werden. Zusätzlich oder alternativ kann die Verrundung vorzugsweise umgeformt und/oder spanend bearbeitet bzw. hergestellt werden.A rounding can in particular together with the inner wall or its end face (s) and flank (s) urgeformt, in particular cast. Additionally or alternatively, the fillet may preferably be reshaped and / or machined or made.

Nach einer Ausführung der vorliegenden Erfindung kann eine Verrundung gehärtet sein, insbesondere durch ein entsprechendes thermisches Verfahren und/oder eine Beschichtung. Hierdurch kann insbesondere der Verschleiß im Bereich der Verrundung weiter reduziert werden.According to one embodiment of the present invention, a rounding can be hardened, in particular by a corresponding thermal method and / or a coating. As a result, in particular the wear in the area of the rounding can be further reduced.

Die vorliegende Erfindung ist insbesondere zur Speichenzentrierung eines Bürstendichtringelements vorteilhaft.The present invention is particularly advantageous for the spoke centering of a brush seal element.

Eine Leitschaufelanordnung kann eine Torsionsvorzugsrichtung aufweisen, die beispielsweise aus einer Anstellung und/oder einem Profil der Leitschaufeln oder dergleichen resultieren kann. Hierunter wird vorliegend insbesondere eine Torsionsrichtung um eine radiale Achse verstanden, in die die Leitschaufel(n) der Leitschaufelanordnung im Betrieb bei zunehmender Durchströmung und/oder Leistung der Gasturbine(nstufe) tordiert werden. In einer bevorzugten Weiterbildung ist eine Verrundung dann insbesondere auch oder nur an einem Ende der Stirnfläche(n) in Umfangsrichtung vorgesehen, das bei Torsion in der Torsionsvorzugsrichtung gegen die benachbarte Nutinnenfläche zugestellt wird.A vane arrangement may have a torsion preferential direction, which may for example result from a setting and / or a profile of the guide vanes or the like. In the present case, this is understood in particular to mean a torsional direction about a radial axis into which the guide vane (s) of the vane arrangement are twisted during operation with increasing flow and / or power of the gas turbine (n-stage). In a preferred embodiment, a rounding is then provided in particular also or only at one end of the end face (s) in the circumferential direction, which is delivered in torsion in the Torsionsvorzugsrichtung against the adjacent Nutinnenfläche.

Weitere Vorteile und Merkmale ergeben sich aus den Unteransprüchen und dem Ausführungsbeispiel. Hierzu zeigt, teilweise schematisiert:

Fig. 1:
einen Meridianschnitt eines Teils einer Gasturbine mit einer Gasturbinenstufe mit einer Leitschaufelanordnung nach einer Ausführung der vorliegenden Erfindung;
Fig. 2:
die Leitschaufelanordnung der Fig. 1 in perspektivischer Darstellung; und
Fig. 3:
einen abgewickelten Schnitt bzw. eine Draufsicht in radialer Richtung auf eine Speichenzentrierung der Leitschaufelanordnung der Fig. 1.
Further advantages and features emerge from the subclaims and the exemplary embodiment. This shows, partially schematized:
Fig. 1:
a meridian section of a portion of a gas turbine with a gas turbine stage with a vane assembly according to an embodiment of the present invention;
Fig. 2:
the vane arrangement of Fig. 1 in perspective view; and
3:
a developed section and a plan view in the radial direction to a spoke centering of the vane assembly of Fig. 1 ,

Fig. 1 zeigt einen Meridianschnitt eines Teils einer Gasturbine mit einer Gasturbinenstufe mit einer Leitschaufelanordnung nach einer Ausführung der vorliegenden Erfindung. Die in Fig. 2 in perspektivischer Ansicht dargestellte Leitschaufelanordnung weist mehrere integral miteinander verbunden Leitschaufeln 1 mit einem gemeinsamen, radial innenliegenden Leitschaufelfuß 1.1 auf, von dem aus sich eine gemeinsame Innenwand 1.2 von einer leitschaufelblattabgewandten Seite (unten in Fig. 1, 2) des Leitschaufelfußes 1.1 ausgehend nach radial innen (nach unten in Fig. 1, 2) erstreckt. In der Innenwand 1.2 ist eine Radialnut 1.3 ausgebildet. Fig. 1 shows a meridian section of a portion of a gas turbine with a gas turbine stage with a vane assembly according to an embodiment of the present invention. In the Fig. 2 in Guide vane assembly shown in a perspective view has a plurality of integrally connected vanes 1 with a common, radially inner Leitschaufelfuß 1.1, from which a common inner wall 1.2 from a side facing away from the vane blade (bottom in Fig. 1 . 2 ) of the guide blade root 1.1 starting radially inward (down in Fig. 1 . 2 ). In the inner wall 1.2 a radial groove 1.3 is formed.

In dieser ist ein Gleitstein radial beweglich angeordnet, der mit einer Umfangsnut mit zwei Schenkel 2.1, 2.2 verbunden ist, die in einem Bürstendichtringelement 2 ausgebildet ist. Hierdurch ist das Bürstendichtringelement 2 speichenzentriert an der Leitschaufelanordnung gelagert.In this a sliding block is arranged radially movable, which is connected to a circumferential groove with two legs 2.1, 2.2, which is formed in a brush seal ring element 2. As a result, the brush seal element 2 is mounted on the guide vane arrangement in a memory-centered manner.

Wie in dem in Umfangsrichtung abgewickelten Schnitt bzw. der Draufsicht in radialer Richtung von radial außen nach radial innen der Fig. 3 erkennbar, weist die Innenwand 1.2, die zwischen den beiden Schenkeln 2.1, 2.2 der Umfangsnut des Bürstendichtringelements 2 angeordnet ist, zwei parallele ebene axiale Stirnflächen 1.4 auf, die bei unverformter Lage der Leitschaufeln 3 normal zu einer Axialrichtung der Gasturbine(n)stufe orientiert sind, d.h. in Fig. 3 vertikal verlaufen. Diese beiden Stirnflächen 1.4 sind durch zwei parallele ebene Flanken 1.5 verbunden, die gegen die Stirnflächen 1.4 rechtwinklig abgewinkelt sind.As in the circumferentially developed section or the plan view in the radial direction from radially outside to radially inside of the Fig. 3 recognizable, the inner wall 1.2, which is disposed between the two legs 2.1, 2.2 of the circumferential groove of the brush seal member 2, two parallel planar axial end faces 1.4, which are oriented in an undeformed position of the vanes 3 normal to an axial direction of the gas turbine (n) stage ie in Fig. 3 run vertically. These two end faces 1.4 are connected by two parallel planar flanks 1.5, which are angled perpendicular to the end faces 1.4.

Zwischen der in Durchströmungsrichtung vorderen Stirnfläche (links in Fig. 3) und der in Fig. 3 oberen Flanke 1.5 sowie zwischen der in Durchströmungsrichtung hinteren Stirnfläche (rechts in Fig. 3) und der in Fig. 3 unteren Flanke 1.5 ist jeweils eine Verrundung in Form eines Radius R ausgebildet.Between the front in the direction of flow front face (left in Fig. 3 ) and the in Fig. 3 upper flank 1.5 and between the rear face in the flow direction (right in Fig. 3 ) and the in Fig. 3 lower edge 1.5 is in each case a rounding in the form of a radius R formed.

Kommt es leitschaufeltorsionsbedingt, wie in Fig. 3 dargestellt, zu einer Anlage der in Durchströmungsrichtung vorderen Stirnfläche 1.4 an der Nutinnenfläche des Schenkels 2.1, reduziert dieser Radius R die Spannungsbelastung und den Verschleiß. Kommt es bei noch stärkerer Torsion der Leitschaufel 3 (nicht dargestellt), zusätzlich zu einer Anlage der in Durchströmungsrichtung hinteren Stirnfläche 1.4 an der Nutinnenfläche des Schenkels 2.2, reduziert der dortige Radius R ebenfalls die Spannungsbelastung und den Verschleiß. Mit anderen Worten sind die Verrundungen R jeweils an dem Ende der Stirnflächen 1.4 in Umfangsrichtung vorgesehen (oben bei der in Fig. 3 linken Stirnfläche, unten bei der in Fig. 3 rechten Stirnfläche), das bei Torsion in einer Torsionsvorzugsrichtung (mathematisch positiv bzw. gegen den Uhrzeigersinn in Fig. 3) der Leitschaufel 3 gegen die benachbarte Nutinnenfläche zugestellt wird.Is it Leitschaufelt torsionsbedingt, as in Fig. 3 shown, to a plant of the front in the flow direction end face 1.4 on the Nutinnenfläche the leg 2.1, this radius R reduces the stress and wear. If there is an even stronger torsion of the vane 3 (not shown), in addition to a system of the rear end face 1.4 in the flow direction on the Nutinnenfläche of the leg 2.2, the local radius R also reduces the stress and wear. In other words, the fillets R are respectively provided at the end of the end faces 1.4 in the circumferential direction (at the top in the in Fig. 3 left end face, down at the in Fig. 3 right front face), which when torsion in a Torsionsvorzugsrichtung (mathematically positive or counterclockwise in Fig. 3 ) of the vane 3 is delivered against the adjacent Nutinnenfläche.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

11
Leitschaufelvane
1.11.1
Leitschaufelfußvane root
1.21.2
Innenwandinner wall
1.31.3
Radialnutradial groove
1.41.4
Stirnflächeface
1.51.5
Flankeflank
2 2.1,2 2.1,
(Bürsten)Dichtringelement(Brush) sealing ring element
2.22.2
Nutschenkelgroove leg
33
Leitschaufelvane
RR
Radius/VerrundungRadius / rounding

Claims (13)

Gasturbinenstufe, insbesondere Niederdruckverdichterstufe, für eine Gasturbine, insbesondere eine Flugantrieb-Gasturbine, mit einer Leitschaufelanordnung mit wenigstens einer Leitschaufel (1) mit einem radial inneren Leitschaufelfuß (1.1), an dem ein Dichtringelement (2) durch eine Speichenzentrierung gelagert ist, die eine Innenwand (1.2) und eine diese aufnehmende Umfangsnut (2.1, 2.2) aufweist, wobei die Innenwand wenigstens eine einer Nutinnenfläche der Umfangsnut zugewandte Stirnfläche (1.4) und eine dieser benachbarte, gegen diese abgewinkelte Flanke (1.5) aufweist,
dadurch gekennzeichnet, dass
zwischen der Stirnfläche und der Flanke eine Verrundung, insbesondere ein Radius (R) ausgebildet ist.Gas turbine stage, in particular low-pressure compressor stage, for a gas turbine, in particular an aircraft gas turbine engine, having a guide vane assembly with at least one vane (1) with a radially inner Leitschaufelfuß (1.1) on which a sealing ring member (2) is supported by a spokes centering, which has an inner wall (1.2) and having a receiving circumferential groove (2.1, 2.2), wherein the inner wall has at least one groove inner surface of the circumferential groove facing end face (1.4) and one of these adjacent, against this angled edge (1.5),
characterized in that
between the end face and the flank a rounding, in particular a radius (R) is formed. Gasturbinenstufe nach Anspruch 1, dadurch gekennzeichnet, dass die Innenwand (1.2) mit dem Leitschaufelfuß (1.1), insbesondere integral, verbunden und die Umfangsnut (2.1, 2.2) an dem Dichtringelement (2) ausgebildet ist.Gas turbine stage according to Claim 1, characterized in that the inner wall (1.2) is connected to the guide blade root (1.1), in particular integrally, and the circumferential groove (2.1, 2.2) is formed on the sealing ring element (2). Gasturbinenstufe nach Anspruch 1, dadurch gekennzeichnet, dass die Innenwand mit dem Dichtringelement, insbesondere integral, verbunden und die Umfangsnut an dem Leitschaufelfuß ausgebildet ist.Gas turbine stage according to claim 1, characterized in that the inner wall with the sealing ring element, in particular integrally connected and the circumferential groove is formed on the Leitschaufelfuß. Gasturbinenstufe nach einem der vorhergehenden Ansprüche, gekennzeichnet durch wenigstens zwei, insbesondere integral, miteinander verbundene Leitschaufeln (1) mit einer gemeinsamen Innenwand (1.2) oder Umfangsnut.Gas turbine stage according to one of the preceding claims, characterized by at least two, in particular integrally, interconnected guide vanes (1) having a common inner wall (1.2) or circumferential groove. Gasturbinenstufe nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Innenwand eine Radialnut (1.3) zur Aufnahme eines Gleitelements zur Ausbildung der Speichenzentrierung aufweist.Gas turbine stage according to one of the preceding claims, characterized in that the inner wall has a radial groove (1.3) for receiving a sliding element for forming the spoke centering. Gasturbinenstufe nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass der Radius (R) wenigstens 25%, insbesondere wenigstens 30% einer Breite der Flanke aufweist.Gas turbine stage according to one of the preceding claims, characterized in that the radius (R) has at least 25%, in particular at least 30% of a width of the flank. Gasturbinenstufe nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass der Radius (R) wenigstens 0,5 mm, insbesondere wenigstens 10 mm, vorzugsweise wenigstens 15 mm beträgt.Gas turbine stage according to one of the preceding claims, characterized in that the radius (R) is at least 0.5 mm, in particular at least 10 mm, preferably at least 15 mm. Gasturbinenstufe nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Verrundung (R) urgeformt, umgeformt, spanend hergestellt und/oder gehärtet ist.Gas turbine stage according to one of the preceding claims, characterized in that the rounding (R) is urgeformt, formed, machined and / or cured. Gasturbinenstufe nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass das Dichtringelement ein Bürstendichtringelement (2) ist.Gas turbine stage according to one of the preceding claims, characterized in that the sealing ring element is a brush sealing ring element (2). Gasturbinenstufe nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Verrundung (R) an einem Ende der Stirnfläche (1.4) in Umfangsrichtung vorgesehen ist, das bei Torsion in einer Torsionsvorzugsrichtung der Leitschaufelanordnung gegen die benachbarte Nutinnenfläche zugestellt wird.Gas turbine stage according to one of the preceding claims, characterized in that the rounding (R) is provided at one end of the end face (1.4) in the circumferential direction, which is delivered against the adjacent Nutinnenfläche in torsion in a Torsionsvorzugsrichtung the vane assembly. Gasturbine, insbesondere Flugantrieb-Gasturbine, mit wenigstens einer Gasturbinenstufe nach einem der vorhergehenden Ansprüche.Gas turbine, in particular propulsion gas turbine, with at least one gas turbine stage according to one of the preceding claims. Leitschaufelanordnung für eine Gasturbine nach dem vorhergehenden Anspruch, mit wenigstens einer Leitschaufel (1) mit einem radial inneren Leitschaufelfuß (1.1) und einer damit verbundenen Innenwand (1.2), die zur Aufnahme in einer Umfangsnut (2.1, 2.2) eines Dichtringelements (2) der Gasturbine vorgesehen ist, wobei die Innenwand wenigstens eine einer Nutinnenfläche der Umfangsnut zugewandte Stirnfläche (1.4) und eine dieser benachbarte, gegen diese abgewinkelte Flanke (1.5) aufweist, und wobei zwischen der Stirnfläche und der Flanke eine Verrundung, insbesondere ein Radius (R) ausgebildet ist.Guide vane assembly for a gas turbine according to the preceding claim, comprising at least one vane (1) with a radially inner Leitschaufelfuß (1.1) and an associated inner wall (1.2) for receiving in a circumferential groove (2.1, 2.2) of a sealing ring element (2) of Gas turbine is provided, wherein the inner wall has at least one of Nutinnenfläche the circumferential groove facing end face (1.4) and one of these adjacent, against this angled edge (1.5), and wherein between the end face and the flank a rounding, in particular a radius (R) is formed is. Dichtringelement für eine Gasturbine nach dem vorvorhergehenden Anspruch, mit einer damit verbundenen Innenwand, die zur Aufnahme in einer Umfangsnut einer Leitschaufelanordnung der Gasturbine vorgesehen ist, wobei die Innenwand wenigstens eine einer Nutinnenfläche der Umfangsnut zugewandte Stirnfläche und eine dieser benachbarte, gegen diese abgewinkelte Flanke aufweist, und wobei zwischen der Stirnfläche und der Flanke eine Verrundung, insbesondere ein Radius ausgebildet ist.Sealing ring element for a gas turbine according to the vorvorhergehenden claim, with an associated inner wall, which is provided for receiving in a circumferential groove of a guide vane assembly of the gas turbine, wherein the inner wall has at least one groove inner surface of the circumferential groove facing end face and one of these adjacent, against this angled edge, and wherein between the end face and the flank a rounding, in particular a radius is formed.
EP12179978.7A 2012-08-10 2012-08-10 Gas turbine stage Not-in-force EP2696039B1 (en)

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US13/959,021 US20140044537A1 (en) 2012-08-10 2013-08-05 Gas turbine

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Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3208426A1 (en) 2016-02-18 2017-08-23 MTU Aero Engines GmbH Guide blade formation for a flow machine
DE102016222608A1 (en) 2016-11-17 2018-05-17 MTU Aero Engines AG Sealing arrangement for a guide vane arrangement of a gas turbine
EP3483399A1 (en) * 2017-11-09 2019-05-15 MTU Aero Engines GmbH Seal assembly for a turbomachine, method for producing a seal assembly and turbomachine
DE102018213983A1 (en) * 2018-08-20 2020-02-20 MTU Aero Engines AG Adjustable guide vane arrangement, guide vane, seal carrier and turbomachine
EP3885536A1 (en) * 2020-03-25 2021-09-29 MTU Aero Engines AG Gas turbine component

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5224822A (en) * 1991-05-13 1993-07-06 General Electric Company Integral turbine nozzle support and discourager seal
US20030082050A1 (en) * 2001-10-29 2003-05-01 Emil Aschenbruck Device for sealing turbomachines
US20060062673A1 (en) * 2004-09-23 2006-03-23 Coign Robert W Mechanical solution for rail retention of turbine nozzles
GB2425155A (en) * 2005-04-13 2006-10-18 Rolls Royce Plc A mounting arrangement
US20070134088A1 (en) * 2005-12-08 2007-06-14 General Electric Company Methods and apparatus for assembling turbine engines
US20110150640A1 (en) * 2003-08-21 2011-06-23 Peter Tiemann Labyrinth Seal in a Stationary Gas Turbine
EP2360352A2 (en) * 2010-02-12 2011-08-24 Rolls-Royce Deutschland Ltd & Co KG Screw-free intermediate stage seal of a gas turbine

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3829233A (en) * 1973-06-27 1974-08-13 Westinghouse Electric Corp Turbine diaphragm seal structure
US5749584A (en) * 1992-11-19 1998-05-12 General Electric Company Combined brush seal and labyrinth seal segment for rotary machines

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5224822A (en) * 1991-05-13 1993-07-06 General Electric Company Integral turbine nozzle support and discourager seal
US20030082050A1 (en) * 2001-10-29 2003-05-01 Emil Aschenbruck Device for sealing turbomachines
US20110150640A1 (en) * 2003-08-21 2011-06-23 Peter Tiemann Labyrinth Seal in a Stationary Gas Turbine
US20060062673A1 (en) * 2004-09-23 2006-03-23 Coign Robert W Mechanical solution for rail retention of turbine nozzles
GB2425155A (en) * 2005-04-13 2006-10-18 Rolls Royce Plc A mounting arrangement
US20070134088A1 (en) * 2005-12-08 2007-06-14 General Electric Company Methods and apparatus for assembling turbine engines
EP2360352A2 (en) * 2010-02-12 2011-08-24 Rolls-Royce Deutschland Ltd & Co KG Screw-free intermediate stage seal of a gas turbine

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3208426A1 (en) 2016-02-18 2017-08-23 MTU Aero Engines GmbH Guide blade formation for a flow machine
DE102016202519A1 (en) 2016-02-18 2017-08-24 MTU Aero Engines AG Guide vane segment for a turbomachine
US10895162B2 (en) 2016-02-18 2021-01-19 MTU Aero Engines AG Guide vane segment for a turbomachine
EP3324001A1 (en) * 2016-11-17 2018-05-23 MTU Aero Engines AG Sealing assembly for a vane arrangement of a gas turbine
US10677080B2 (en) 2016-11-17 2020-06-09 MTU Aero Engines AG Seal system for a guide blade system of a gas turbine
DE102016222608A1 (en) 2016-11-17 2018-05-17 MTU Aero Engines AG Sealing arrangement for a guide vane arrangement of a gas turbine
EP3483399A1 (en) * 2017-11-09 2019-05-15 MTU Aero Engines GmbH Seal assembly for a turbomachine, method for producing a seal assembly and turbomachine
US10865651B2 (en) 2017-11-09 2020-12-15 MTU Aero Engines AG Sealing assembly for a fluid kinetic machine, method for producing a sealing assembly as well as fluid kinetic machine
DE102018213983A1 (en) * 2018-08-20 2020-02-20 MTU Aero Engines AG Adjustable guide vane arrangement, guide vane, seal carrier and turbomachine
EP3613952A1 (en) 2018-08-20 2020-02-26 MTU Aero Engines GmbH Adjustable guide blade assembly, guide blade, seal carrier, and turbomachine
US11300004B2 (en) 2018-08-20 2022-04-12 MTU Aero Engines AG Adjustable guide vane arrangement, guide vane, seal carrier and turbomachine
EP3885536A1 (en) * 2020-03-25 2021-09-29 MTU Aero Engines AG Gas turbine component
DE102020203840A1 (en) 2020-03-25 2021-09-30 MTU Aero Engines AG Gas turbine component
US11585242B2 (en) 2020-03-25 2023-02-21 MTU Aero Engines AG Gas turbine component

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