EP2787177B1 - Turbomachine axiale et procédé de montage - Google Patents

Turbomachine axiale et procédé de montage Download PDF

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Publication number
EP2787177B1
EP2787177B1 EP13161909.0A EP13161909A EP2787177B1 EP 2787177 B1 EP2787177 B1 EP 2787177B1 EP 13161909 A EP13161909 A EP 13161909A EP 2787177 B1 EP2787177 B1 EP 2787177B1
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EP
European Patent Office
Prior art keywords
segment
inner ring
flow engine
expansion
seal carrier
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EP13161909.0A
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German (de)
English (en)
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EP2787177A1 (fr
Inventor
Alexander Böck
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MTU Aero Engines AG
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MTU Aero Engines AG
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Priority to EP13161909.0A priority Critical patent/EP2787177B1/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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

Definitions

  • the invention relates to an axial flow machine, a use of the axial flow machine and a method for mounting the axial flow machine.
  • Axial flow machines are known from the prior art, in which adjustable guide vanes are fastened by means of bushes in openings of a segmented inner ring. Attached to the inner ring is also a segmented seal carrier which seals the vane channels from a rotor, e.g. by means of a honeycomb structure present on the seal carrier.
  • the DE 10 2006 024 085 A1 discloses a turbomachine with a seal carrier whose segments are pushed in the circumferential direction of the turbomachine on corresponding segments of the inner ring.
  • the attachment is effected by means of a groove formed in the circumferential direction.
  • this groove connection requires a clearance for the assembly, in which leaks and position inaccuracies can occur during operation.
  • a turbomachine without inner ring is known in which a plurality of spring segments between the guide blade feet and segments of a seal carrier are mounted.
  • the seal between the guide blade feet and the segments of the seal carrier by means of a longitudinal section of the flow machine C-shaped spring.
  • the disadvantage here is that the C-shaped spring has a relatively large height in the radial direction of the turbomachine.
  • the DE 10 2004 006 706 A1 also describes a turbomachine without an inner ring, are arranged in the leaf springs made of spring steel between vanes and segments of the seal carrier.
  • the attachment of the seal carrier to the vanes is done by means of wire segments.
  • difficulties could arise in mounting a longer leaf spring over the circumference of a larger segment.
  • an axial flow machine which comprises a stator with adjustable guide vanes, wherein inner pins of the guide vanes are accommodated by means of sockets in an inner ring.
  • the invention is therefore based on the object to provide an axial flow machine, are prevented in the leaks between an inner ring and a seal carrier while a simple assembly is possible.
  • an axial flow machine comprising a stator with adjustable guide vanes, wherein inner pins of the guide vanes are accommodated by bushes in an inner ring which is divided in the circumferential direction of the turbomachine into at least two segments and in one piece in the axial direction of the turbomachine , and wherein a seal carrier, which is divided into segments, is mounted on the inner ring.
  • the seal carrier is clamped to the inner ring by means of a spreader, which is divided into segments and has an elongated arc length relative to the respective segments of the inner ring and the segments of the seal carrier, and a segment of the spreader comprises at least one spreader with spreaders aligned along the circumferential direction and are also spaced apart along the circumferential direction and protrude outwardly from the expansion band in the radial direction of the turbomachine.
  • This arrangement has the advantage that the spreading elements projecting from the spreading band can generate a spring tension between the segments of the inner ring and the segments of the seal carrier, the spreading device being stable and easy to assemble due to its structure.
  • each segment of the inner ring and a segment of the seal carrier are sealed over the entire arc length.
  • the arrangement is also easy to interpret and inexpensive.
  • the accuracy of positioning the segments of the inner ring on the segments of the seal carrier is also improved.
  • the expansion band at least in a middle section in the axial direction of the turbomachine, has a continuous shape along the circumferential direction, and the spreading elements are formed integrally with the expansion band.
  • This special structure of the spreader offers a particularly good stability and manufacturability.
  • the spreader comprises at least one spreader on which the spreader elements are arranged in the form of sprung sections which engage in the assembly of the segment of the seal carrier in pockets of the segment of the inner ring and after assembly of the segment of the seal carrier outside the Bags in the radial direction of the turbomachine by spring tension on the segment of the inner ring abut.
  • the spreading device can be clamped in a controlled manner during a defined assembly step.
  • the spreading elements are designed as tabs, which are arranged on both sides of the expansion band in the axial direction of the turbomachine.
  • the tabs are an easily manufactured means by which the expansion stress can be generated safely.
  • the segment of the spreading device comprises two parallel expansion bands, which are guided in the axial direction of the turbomachine.
  • the split into two spreader strips saves weight and allows controlled clamping of the segment of the inner ring with the segment of the seal carrier in one or two steps.
  • the spreading elements are formed as arcuate portions of the expansion bands.
  • the arcuate portions allow a good flow of force within the spreader and produce a secure spring tension.
  • the length of the individual pockets may increase or decrease along the circumferential direction, allowing for sequential tensioning.
  • the sequential tensioning reduces the temporary force required during assembly.
  • downstream in the axial direction pockets and the associated spreading elements are arranged offset from the upstream pockets and the associated expansion elements.
  • the staggered arrangement allows a clamping, in which a smaller distance between the individual stress points is achieved on the expansion elements in the circumferential direction.
  • each extended relative to the segments of the inner ring and the segments of the seal carrier segment of the spreading at least one Anlagenende, at least partially separable after the clamping of the segment of the seal carrier, umbiegbar on the segment of the inner ring and in at least one associated recess is retractable in the segment of the inner ring.
  • the Switzerlandende is an assembly tool that can be shortened after assembly, so that only a part of the Switzerlandendes remains, by means of which the spreader is secured to the inner ring. The separation and bending of the remaining part of the train end is easy to carry out.
  • the segment of the spreading device is formed from sheet metal material.
  • the axial flow machine as a compressor in a gas turbine, in particular in a jet engine.
  • a seal especially important to minimize flow losses due to leaks and thus efficiency losses.
  • each one segment of the seal carrier is mounted in the circumferential direction of the turbomachine on an associated segment of the inner ring.
  • the segment of the seal carrier is clamped by means of an associated segment of the spreader on the segment of the inner ring, wherein the segment of the spreader moves after mounting the segment of the seal carrier on the segment of the inner ring from a substantially stress-free first mounting state in a second mounting state, in which by means of Segments of the spreader a spring tension between the segment of the inner ring and the segment of the seal carrier is generated.
  • This mounting method allows controlled by the first mounting state and the second mounting state of each segment of the spreading a controlled distortion of the segments of the inner ring with the segments of the seal carrier.
  • the pockets and the spreading elements cooperate in such a way that, in the above-mentioned first assembly state, the spreading elements protrude into the pockets and bear against the segment of the inner ring in the abovementioned second assembly state outside the pockets.
  • the mechanism is safe to use and reliable.
  • the use of the Switzerlandendes allows easy installation and a secure operation of the spreader.
  • the spreading elements are stretched sequentially due to the movement of the segment of the spreading device.
  • Fig. 1 shows a segment of the stator of an axial flow machine not otherwise shown.
  • the stator comprises a plurality of adjustable guide vanes 1a, whose in Fig. 1 not visible pins are mounted by means of sockets 2 in a segment 3 of an inner ring not shown in its entirety.
  • the guide vanes 1a are basically also without sockets 2 in the inner ring storable.
  • a segment 4 of a seal carrier not shown in its entirety is in Fig. 1 partially shown pushed onto the segment 3 of the inner ring. Also in the following figures, only the segments 3, 4, and 5 are shown without the associated entirety of the inner ring, the seal carrier and the spreader.
  • the inner ring according to Fig. 1 has a plurality, at its in the radial direction of the axial flow machine inside page in the circumferential direction u arranged, elongated pockets.
  • the pockets 3a, 3b, 3c are shown here.
  • Two pockets 3a, 3b, 3c are arranged in the circumferential direction u on both sides of the inner ring, but the associated pockets 3a, 3b, 3c are each offset from one another.
  • the length of the pockets 3a, 3b, 3c increases in the circumferential direction u of the axial flow machine. That is, the pocket 3a is shorter than the pocket 3b, and the pocket 3b is shorter than the pocket 3c.
  • the mating pockets 3a, 3b, 3c can not be arranged offset to one another and / or have an equal extent in the circumferential direction and thus be the same length.
  • a first exemplary embodiment of a segment 5 of a spreading device which serves to clamp the segment 4 of the seal carrier on the segment 3 of the inner ring.
  • the segment 5 of the spreading device comprises a spreading belt 5b with a plurality of lugs 5c arranged on both sides as spreading elements.
  • three tabs 5c are shown here on each side.
  • the mating tabs 5c are each offset according to the pockets 3a, 3b, 3c. Of course, the mating tabs 5c can not be arranged offset to one another.
  • the tabs 5c are spaced from each other in the circumferential direction u and are all in the same direction, namely towards the inner ring, angularly away from the spreader 5b.
  • the tabs 5c are made in one piece with the expansion band 5c.
  • the spreader 5b has a tension end 5f comprising a first part 5g and a second part 5h.
  • the part 5g is used to apply a tensile force and is separated after positioning on the segment 3 of the inner ring.
  • the part 5h is used after the separation of the first part 5g for securing the segment 5 of the spreader on the inner ring.
  • Fig. 2a is a section around a tab 5c shown in a first mounting state of the segment 5 of the spreading device.
  • the expansion band 5b is located between the segment 3 of the inner ring and the segment 4 of the seal carrier.
  • the tab 5c of the segment 5 of the spreading device protrudes into the pocket 3a of the segment 3 of the inner ring. For clamping the segment 5 of the spreader is pulled along the circumferential direction u.
  • the Fig. 2b shows a section around a tab 5c in a second mounting state of the segment 5 of the spreader. After pulling the segment 5 of the spreading device along the circumferential direction u, the tab 5c is located outside the pocket 3a of the segment 3 of the inner ring. The attached to the expansion band 5b tab 5c is now stretched between the segment 3 of the inner ring and the segment 4 of the seal carrier.
  • the Fig. 3 1 illustrates a segment 3 of the inner ring with an adjustable guide blade 1a and a second exemplary embodiment of a segment 5 of a spreading device of the axial flow machine according to the invention.
  • the segment 5 of the spreading device here comprises two expansion bands 5d, which are arranged parallel to one another in the circumferential direction u.
  • Each expansion band 5d comprises a plurality of arcuate portions 5e as spreading elements, which are each spaced apart in the circumferential direction u and which protrude from the spreader ribbons 5d in the direction of the segment 3 of the inner ring.
  • the expansion bands 5 d each have a tension end 5 f, which projects beyond the end of the segment 3 of the inner ring.
  • the segment 3 of the inner ring has several pockets in the circumferential direction u, of which two pockets 3a, 3b are shown here by way of example.
  • the length of the pockets 3a, 3b decreases in the circumferential direction u, ie the pocket 3a is shorter than the pocket 3b.
  • the arcuate portions 5e are arranged in the pockets 3a, 3b.
  • the Fig. 3a represents in a section of the segment 1 of the stator after assembly of the segment 4 of the seal carrier on the segment 3 of the inner ring by means of the segment 5 of the spreading. Of the segment 5 of the spreading only the Glasenden 5f are visible, in the circumferential direction u on the segment 3 of the inner ring and beyond the segment 4 of the seal carrier protrude.
  • the segment 3 of the inner ring carries by way of example an adjustable guide blade 1a.
  • the segment 3 of the inner ring has at its illustrated end two provided for the Werenden 5 f depressions 3d.
  • Fig. 3b is shown in the radial direction of the axial flow machine side of the segment 3 of the inner ring. Visible here are the depressions 3d and the sockets 2, which guide the adjustable guide vanes, not shown here.
  • the bushings 2 have parallel flattened portions 2a extending in the circumferential direction u, which guide the spreading bands 5d between the segment 3 of the inner ring and the segment 4 of the seal carrier (in FIG Fig. 3b not shown).
  • Fig. 3c shows the segment 3 of the inner ring, which exemplarily carries an adjustable guide blade 1a.
  • the segment 5 of the spreading device is shown in the fully assembled state, ie the second parts 5h of the tension ends 5f of the expansion bands 5d are bent over and accommodated in the depressions 3d of the segment 3 of the inner ring.
  • the arcuate sections 5e of the segment 5 of the spreading device are located outside the pockets 3a, 3b of different length. Actually, this mounting state is reached with bent second parts 5h of the tension ends 5f only after the segment 4 of the seal carrier is mounted. However, this is not shown here, so that the position of the segment 5 of the spreader is better visible.
  • Fig. 3d shows the same end of segment 1 of the stator as in Fig.
  • Fig. 4 is a 180 ° segment 3 of an inner ring shown, are attached to the three adjustable vanes 1a representative of the entirety of the blading.
  • segment 3 of the inner ring are two 90 ° segments 5 of the spreader on.
  • the segments 5 of the spreading device in the direction of the arrows z, which indicate the pulling direction, in the space between the segment 3 of the inner ring and the or the segments of the seal carrier along the Circumferential direction u moves.
  • the segments 5 of the spreading device can according to the Fig. 2 to 2b or the Fig. 3 to 3d be executed.
  • Fig. 5 shows a section through the assembled arrangement of a segment 3 of the inner ring with an adjustable guide blade 1a, the pin 1b is mounted by means of a sleeve 2 in the inner ring, a segment 4 of the seal carrier and two Sp Dahlb Sn according to the Fig. 3 to 3d ,
  • the section lies in a plane of a longitudinal section of an axial flow machine not shown here.
  • the segment 4 of the seal carrier is mounted in the circumferential direction on the segment 3 of the inner ring.
  • the invention relates to an axial flow machine comprising a stator with adjustable vanes, wherein inner pins of the vanes are housed by bushes in an inner ring which is divided in the circumferential direction of the turbomachine into at least two segments and in the axial direction of the turbomachine integral, and wherein a seal carrier, which is divided into segments, mounted on the inner ring.
  • the seal carrier is clamped to the inner ring by means of a spreader, which is divided into segments and with respect to the associated segments of the inner ring and the segments of the seal carrier has an extended arc length and a segment of the spreader comprises at least one spreader with spreaders aligned along the circumferential direction and also spaced apart along the circumferential direction and extending outwardly from the spreader in the radial direction of the turbomachine.

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

Claims (14)

  1. Turbomachine à flux axial qui comprend un stator pourvu d'aubes directrices réglables (la), des tiges intérieure (1b) des aubes directrices étant logées au moyen de douilles (2) dans une bague intérieure qui est divisée dans la direction circonférentielle (u) de la turbomachine en au moins deux segments (3) et qui est d'une seule pièce dans la direction axiale de la turbomachine, et un support de garniture d'étanchéité, qui est divisé en segments (4), étant monté sur la bague intérieure, caractérisée en ce que le support de garniture d'étanchéité est serré avec la bague intérieure au moyen d'un dispositif extensible qui est divisé en segments (5) et qui a une longueur d'arc de forme allongée par rapport aux segments (3) associés de la bague intérieure et aux segments (4) du support de garniture d'étanchéité, et en ce qu'un segment (5) du dispositif extensible comporte au moins une bande extensible (5b, 5d) pourvue d'éléments extensibles (5c, 5e) qui sont orientés le long de la direction circonférentielle (u) et également espacés les uns des autres le long de la direction circonférentielle (u) et qui font saillie de la bande extensible (5b, 5d) vers l'extérieur dans une direction radiale de la turbomachine.
  2. Turbomachine à flux axial selon la revendication 1, caractérisée en ce que la bande extensible (5d) comporte au moins dans une partie médiane par référence à la direction axiale de la turbomachine une forme continue le long de la direction circonférentielle (u) et les éléments extensibles (5c) sont formés d'une seule pièce avec la bande extensible (5d).
  3. Turbomachine à flux axial selon l'une des revendications 1 ou 2, caractérisée en ce que le dispositif extensible comporte au moins une bande extensible (5b, 5d) sur laquelle les éléments extensibles (5c, 5e) sont disposés sous la forme de parties, montées sur ressorts, qui s'engagent dans des poches (3a, 3b, 3c) du segment (3) de la bague intérieure lors du montage du segment (4) du support de garniture d'étanchéité et qui s'appuient sur le segment (3) de la bague intérieure par tension des ressort dans une direction radiale de la turbomachine à l'extérieur des poches (3a, 3b, 3c) après le montage du segment (4) du support de garniture d'étanchéité.
  4. Turbomachine à flux axial selon l'une des revendications 1 à 3, caractérisée en ce que les éléments extensibles (5c) sont conçus sous forme de pattes (5c) qui sont disposées des deux côtés de la bande extensible (5b) par référence à la direction axiale de la turbomachine.
  5. Turbomachine à flux axial selon l'une des revendications 1 à 4, caractérisée en ce que le segment (5) du dispositif extensible comprend deux bandes extensibles parallèles (5d) qui sont guidées dans la direction axiale de la turbomachine.
  6. Turbomachine à flux axial selon l'une des revendications 1 à 3 ou 5, caractérisée en ce que les éléments extensibles (5e) sont conçus sous la forme de parties cintrées (5e) des bandes extensibles (5d).
  7. Turbomachine à flux axial selon l'une des revendications 1 à 6, caractérisée en ce que la longueur des poches individuelles (3a, 3b, 3c) augmente ou diminue le long de la direction circonférentielle (u) de façon à permettre un serrage séquentiel.
  8. Turbomachine à flux axial selon l'une des revendications 1 à 7, caractérisée en ce que les poches (3a, 3b, 3c) situées en aval par référence à la direction axiale et les éléments extensibles (5c, 5e) associés sont disposés de façon décalée par rapport aux poches (3a, 3b, 3c) situées en amont et aux éléments extensibles (5c, 5e) associés.
  9. Turbomachine à flux axial selon l'une des revendications 1 à 8, caractérisée en ce que chaque segment (5) du dispositif extensible, qui a une forme allongée par rapport aux segments (3) de la bague intérieure et aux segments (4) du support de garniture d'étanchéité, forme au moins une extrémité de traction (5f) qui peut être au moins partiellement détachée après le serrage du segment (4) du support de garniture d'étanchéité, qui peut être cintrée au niveau du segment (3) de la bague intérieure et qui peut être enfoncée dans au moins un évidement associé (3d) ménagé dans le segment de la bague intérieure.
  10. Turbomachine à flux axial selon l'une des revendications 1 à 9, caractérisée en ce que le segment (5) du dispositif extensible est formé à partir d'une matière en feuille.
  11. Utilisation de la turbomachine à flux axial selon l'une des revendications 1 à 10 comme un compresseur dans une turbine à gaz, en particulier dans un moteur à réaction.
  12. Procédé de montage de la turbomachine à flux axial selon l'une des revendications 1 à 10, dans lequel chaque segment (4) du support de garniture d'étanchéité est monté sur un segment (3) associé de la bague intérieure dans la direction circonférentielle de la turbomachine, caractérisé en ce que le segment (4) du support de garniture d'étanchéité est serré sur le segment (3) de la bague intérieure au moyen d'un segment (5) associé du dispositif extensible, le segment (5) du dispositif extensible étant déplacé après le montage du segment (4) du support de garniture d'étanchéité sur le segment (3) de la bague intérieure, d'un premier état de montage sensiblement sans contrainte dans un second état de montage dans lequel une tension de ressort est générée entre le segment (3) de la bague intérieure et le segment (4) du support de garniture d'étanchéité au moyen du segment (5) du dispositif extensible.
  13. Procédé de montage de la turbomachine à flux axial selon la revendication 12, le procédé comprenant les étapes suivantes consistant à :
    a) appliquer un segment (5) du dispositif extensible sur le segment (3) associé de la bague intérieure, les éléments extensibles (5c, 5e) du segment du dispositif extensible faisant saillie dans les poches (3a, 3b, 3c),
    b) monter un segment (4) du support de garniture d'étanchéité sur le segment (3) associé de la bague intérieure dans la direction circonférentielle (u) de la turbomachine,
    c) déplacer le segment (5) du dispositif extensible dans la direction circonférentielle (u) de la turbomachine par traction sur l'extrémité de traction (5f), les éléments extensible (5c, 5e) étant sortis des poches (3a, 3b, 3c) et serrant par une force de ressort le segment (4) du support de garniture d'étanchéité par rapport au segment (3) de la bague intérieure,
    d) découper une première partie (5g) de l'extrémité de traction (5f),
    e) cintrer et insérer une seconde partie restante (5h) de l'extrémité de traction (5f) dans l'évidement (3d) associé ménagé au niveau du segment (3) de la bague intérieure,
    f) répéter les étapes a) à e) pour les autres segments (3, 4, 5), allant ensemble, d'une bague intérieure, d'un support de garniture d'étanchéité et d'un dispositif extensible,
  14. Procédé de montage de la turbomachine à flux axial selon l'une des revendications 12 ou 13, caractérisé en ce que, lorsque la longueur des poches (3a, 3b, 3c) augmente ou diminue, les éléments extensibles (5c, 5e) sont serrés de manière séquentielle en raison du déplacement du segment (5) du dispositif extensible.
EP13161909.0A 2013-04-02 2013-04-02 Turbomachine axiale et procédé de montage Active EP2787177B1 (fr)

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Application Number Priority Date Filing Date Title
EP13161909.0A EP2787177B1 (fr) 2013-04-02 2013-04-02 Turbomachine axiale et procédé de montage

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EP13161909.0A EP2787177B1 (fr) 2013-04-02 2013-04-02 Turbomachine axiale et procédé de montage

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EP2787177B1 true EP2787177B1 (fr) 2017-01-18

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3290642A1 (fr) 2016-08-31 2018-03-07 Siemens Aktiengesellschaft Segment annulaire de turbine et systeme destine a la delimitation exterieure d'un trajet d'ecoulement d'une turbine
DE102017211316A1 (de) * 2017-07-04 2019-01-10 MTU Aero Engines AG Turbomaschinen-Dichtring

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Publication number Priority date Publication date Assignee Title
US4897021A (en) 1988-06-02 1990-01-30 United Technologies Corporation Stator vane asssembly for an axial flow rotary machine
FR2723614B1 (fr) * 1994-08-10 1996-09-13 Snecma Dispositif d'assemblage d'un etage circulaire d'aubes pivotantes.
EP1205639A1 (fr) * 2000-11-09 2002-05-15 General Electric Company Système de fixation des aubes statoriques variables dans une virole interieure de turbines
DE102004006706A1 (de) 2004-02-11 2005-08-25 Mtu Aero Engines Gmbh Dämpfungsanordnung für Leifschaufeln
US7125222B2 (en) * 2004-04-14 2006-10-24 General Electric Company Gas turbine engine variable vane assembly
DE102006024085B4 (de) 2006-05-23 2020-04-16 MTU Aero Engines AG Turboverdichter in Axialbauweise

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