EP3287608B1 - Bague intérieure d'une couronne d'aubes directrices d'une turbomachine - Google Patents

Bague intérieure d'une couronne d'aubes directrices d'une turbomachine Download PDF

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Publication number
EP3287608B1
EP3287608B1 EP17179470.4A EP17179470A EP3287608B1 EP 3287608 B1 EP3287608 B1 EP 3287608B1 EP 17179470 A EP17179470 A EP 17179470A EP 3287608 B1 EP3287608 B1 EP 3287608B1
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EP
European Patent Office
Prior art keywords
fixing
ring
vane
elements
inner ring
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EP17179470.4A
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German (de)
English (en)
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EP3287608A1 (fr
Inventor
Joseph Tomsik
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MTU Aero Engines AG
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MTU Aero Engines AG
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Publication of EP3287608A1 publication Critical patent/EP3287608A1/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
    • 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
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162—Bearing supports
    • 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
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking

Definitions

  • Multi-stage turbomachines such as thermal gas turbines often include a vane ring between adjacent rotor stages. These vane rings are at least partially equipped with adjustable guide vanes in order to deflect the respective operating fluid of the turbomachine in a targeted manner, so that the operating fluid impinges on the downstream rotor stage at an optimum angle.
  • the adjustable vanes are rotatably mounted at one end in an outer ring or housing of the turbomachine and the other end in an inner ring.
  • a gas turbine which comprises a stator vane ring with an inner ring as a stator stage in a compressor, wherein the inner ring consists of elastically deformable semicircular ring segments.
  • the inner ring consists of elastically deformable semicircular ring segments.
  • a first aspect of the invention relates to an inner ring for a vane ring of a turbomachine, by means of which adjustable guide vanes are rotatably storable.
  • a higher mechanical and aerodynamic load capacity of the inner ring and thus the vane ring is inventively achieved in that the inner ring comprises a first and a second fixing ring, which are connected to each other via at least one relative to a central axis of the inner ring fixing element, wherein the at least one fixing element with a an associated guide vane corresponding, with respect to the central axis radially projecting blade storage for rotatably supporting the vane includes.
  • the fixing rings Due to the division of the inner ring into two fixing rings, it is also not necessary to form the fixing rings elastically deformable for mounting, since the fixing rings can be arranged without deformation of an upstream and downstream side of the guide vanes and can be combined via the at least one fixing element to the inner ring , Due to the higher mechanical and aerodynamic load capacity of the inner ring an improvement in the efficiency, the surge limit and the power of an associated turbomachine is made possible with the same axial length of the associated stator stage or the associated vane ring. By integrating these two functionalities in the fixing element also space is gained because no additional space is required for through-bolts or other securing means.
  • the pitch that is, the circumferential distance between the vanes
  • the inner ring for such a guide vane comprises such a fixing element.
  • terms such as "axial” and “radial” basically refer to the central axis of the inner ring, which in the installed position runs coaxially to a rotational axis of an associated turbomachine.
  • the fixing rings can basically be produced by means of turning and / or milling methods or generatively, for example by selective laser melting.
  • the fixing element (s) may also generally be produced generatively, for example by selective laser melting. Alternatively, however, other production methods, such as forging and / or milling are conceivable.
  • the fixing element comprises a bushing as a blade bearing, in which a bearing journal of the associated vane can be arranged, or that the fixing element as a blade bearing comprises a bearing pin, which can be arranged in a socket of the associated vane.
  • first fixing ring and / or the second fixing ring is formed segmented or are.
  • first fixing ring and / or the second fixing ring may be divided into two, three, four or more ring segments. This segmentation facilitates in certain applications, the assembly of the respective fixing ring and thus the vane ring.
  • first fixing ring and / or the second fixing ring carries or carry a sealing element, in particular a honeycomb seal.
  • the inner ring can be sealed against other components of the turbomachine, which contributes to a further reduction of flow losses.
  • the sealing element can be materially connected, for example by soldering, with the relevant fixing ring.
  • the relevant Fixing ring be produced generatively together with the sealing element.
  • other manufacturing methods are conceivable.
  • the fixing element against rotation in particular form-fitting, is arranged in a corresponding, preferably polygonal mounting opening of the first fixing ring and / or the second fixing ring.
  • the fixing element along its axial extent has one or more areas which are geometrically designed such that the fixing element is arranged against rotation in an associated mounting opening.
  • the relevant area of the fixing element and the associated mounting opening in cross section may be oval, triangular, square, rectangular or polygonal, whereby a fluid-tight and torsion-proof arrangement is ensured.
  • tilting of a guide blade mounted by means of the fixing element is particularly reliably prevented in this way.
  • the mounting opening (s) can be introduced, for example, by drilling, milling and / or electrochemical removal (ECM / PEM) in the respective fixing ring. If both fixing rings should have mutually aligned mounting holes, it has been shown to minimize tolerance to be advantageous to pair the fixing rings analogous to the installation position and to produce the mounting holes together.
  • the fixing element is coupled in a first end region with a locking element designed as a locking element.
  • the fixing element can be supported axially on one of the fixing rings and is secured at least in one direction against falling out.
  • the first fixing ring and / or the second fixing ring has a receiving profile in which the locking plate is added safe fall.
  • the receiving profile can in principle also be formed by the first and second fixing ring, if they are arranged in their installation position, so that each fixing ring taken by itself has only a portion of the receiving profile.
  • the blocking plate rests on the second fixing ring.
  • the fixing element is fixed in a second end region with a securing element, preferably designed as a nut, on the second fixing ring.
  • a securing element preferably designed as a nut
  • the fixing element can be axially supported on the respective fixing ring and is secured at least in one direction against falling out.
  • the fixing element preferably has a corresponding thread.
  • inner ring for the production of the vane ring this has a certain axial length one comparatively higher mechanical and aerodynamic load capacity than known from the prior art vane rings.
  • the outer ring can in principle be formed in one piece or as part of the housing.
  • the skilled worker is aware that the specified sequence of steps can be varied at least in part, without departing from the scope of the inventive method. Furthermore, it can be provided that the specified steps for disassembly of the vane ring can be carried out in the reverse order. Also in this case, corresponding variations of the step sequence are conceivable.
  • step c) bushes are used as radially inner blade bearings in the inner plate of the vanes and used bearing pins as radially projecting blade bearings of the fixing in the jacks.
  • bearing journals are used as blade bearings of the guide vanes in respective bushes as radially projecting blade bearings of the fixing elements.
  • a mechanically particularly stable connection of the inner ring is made possible in a further advantageous embodiment of the invention in that in step g) nuts are screwed as securing elements on the second end portions of the fixing elements until the first and the second fixing ring are fixed on the fixing elements to each other.
  • a third aspect of the invention relates to a turbomachine, in particular an aircraft engine, comprising at least one inner ring according to the first aspect of the invention and / or at least one vane ring, which is produced by a method according to the second aspect of the invention.
  • Fig. 1 shows a schematic sectional side view of an inner ring 14 according to the invention for a vane ring 10 according to a first embodiment, wherein only the radially inner region is shown.
  • Fig. 1 is described below in synopsis with Fig. 2 and Fig. 3 be explained, wherein Fig. 2 a fragmentary perspective view of the vane ring 10 in the flow direction according to arrow II and Fig. 3 a schematic sectional view of the Guide vane 10 according to section line III-III shows.
  • the vane ring 10 comprises a plurality of adjustable guide vanes 12, which are rotatably mounted in an inner ring 14, wherein the inner ring 14 is an independent invention aspect.
  • the inner ring 14 comprises a first fixing ring 16a which is axially forward when viewed in the flow direction, and an axially rear second fixing ring 16b, between which a fixing element 18 extends axially per guide blade 12 relative to a central axis M of the inner ring 14.
  • the fixing rings 16a, 16b can be formed independently of one another as a 360 ° or ring elements or segmented, for example as half-ring segments.
  • the axially rear fixing ring 16b additionally carries a sealing element 17, which in the present case is designed as a honeycomb seal and is connected by soldering to the fixing ring 16b.
  • the fixing element 18 comprises approximately in its center a radially outwardly projecting blade bearing 20, which is in the present case designed as a bearing journal.
  • the fixing element 18 has a first region 18a and a second region 18b, which are square or square in cross section. In these areas 18a, 18b, the fixing element 18 is positively and non-rotatably arranged in corresponding mounting holes 28a, 28b in the first and second fixing ring 16a, 16b. As a result, the guide vane 12 is additionally secured in its installed position against tilting.
  • a securing element 30a designed as a U-shaped blocking plate is pushed onto a first end region of the fixing element 18. It can be seen that the securing element 30a rests on the second fixing ring 16b and is received in a corresponding receiving profile 32. This reliably prevents unwanted falling out of the securing element 30a.
  • the fixing element 18 is screwed to a securing element 30b designed as a nut, whereby the fixing rings 16a, 16b are connected to one another via the fixing element 18.
  • the radially outer ends of the guide vanes 12 are inserted into a one-piece outer ring (not shown) or in a housing of a turbomachine. Subsequently, in each case a bushing 24 and a fixing element 18 are inserted into the inner plates 26 of the individual guide vanes 12. Thereafter, the first fixing ring 16a is pushed from the front onto the fixing elements 18 and the securing elements 30a are pushed radially from below onto the fixing elements 18. Then the second fixing ring 16b is pushed from the rear side onto the fixing elements 18, whereby at the same time the securing elements 30a are secured against radial falling out. Finally, the nuts 30b are screwed onto the fixing elements 18.
  • Fig. 4 shows a schematic sectional side view of an inner ring 14 according to the invention for a vane ring 10 according to a second embodiment.
  • the basic structure and the assembly or disassembly of the vane ring 10 substantially correspond to those of the first embodiment.
  • the fixing element 18 in the present case as a blade bearing 20 on a socket or bore, in which a bearing pin 34 of the associated vane 12 is arranged.
  • the blade bearing 20 of the fixing element 18 is sealed by means of a sealing element 36 designed as a sealing ring or piston ring relative to the first fixing ring 16a and the second fixing ring 16b.
  • the sealing element 36 is arranged on the outside of the blade bearing 20 before the arrangement of the fixing rings 16a, 16b.
  • Fig. 5 shows for further clarification a schematic perspective view of the in Fig. 4 shown fixing element 18, in the blade bearing 20, the guide vane 12 is arranged. It can be seen that the blocking plate 30a is inserted into a groove 38 in an end region of the fixing element 18. Likewise, the square-shaped areas 18a, 18b can be seen, which serve for the positive and rotationally fixed arrangement of the fixing element 18.

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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 (15)

  1. Bague intérieure (14) d'une couronne d'aubes directrices (10) d'une turbomachine, au moyen de laquelle des aubes directrices réglables (12) peuvent être montées en rotation, caractérisée en ce qu'elle comprend une première et une seconde bague de fixation (16a, 16b) qui sont reliées entre elles par au moins un élément de fixation (18) axial par rapport à un axe central (M) de la bague intérieure (14), l'au moins un élément de fixation (18) comprenant un palier d'aubes (20) correspondant à une aube directrice (12) et fixé radialement par rapport à l'axe central (M), pour le stockage de l'aube directrice (12) d'une façon autorisant le mouvement.
  2. Bague intérieure (14) selon la revendication 1, caractérisée en ce que l'élément de fixation (18) comprend, en tant que palier d'aubes (20), une douille dans laquelle peut être disposé un axe de support (34) de l'aube directrice (12) associée, ou en ce que l'élément de fixation (18) comprend, en tant que palier d'aubes (20), un axe de support qui peut être disposé dans une douille (24) de l'aube directrice associée (12).
  3. Bague intérieure (14) selon la revendication 1 ou 2, caractérisée en ce que la première bague de fixation (16a) et/ou la seconde bague de fixation (16b) est ou sont segmentée(s).
  4. Bague intérieure (14) selon l'une des revendications 1 à 3, caractérisée en ce que la première bague de fixation (16a) et/ou la seconde bague de fixation (16b) porte(nt) un élément d'étanchéité (17), en particulier un joint en nid-d'abeilles.
  5. Bague intérieure (14) selon l'une des revendications 1 à 4, caractérisée en ce que l'élément de fixation (18) est disposé de manière non rotative, en particulier par complémentarité de forme, dans une ouverture de montage (28a, 28b) correspondante, de préférence polygonale, de la première bague de fixation (16a) et/ou de la seconde bague de fixation (16b).
  6. Bague intérieure (14) selon l'une des revendications 1 à 5, caractérisée en ce que l'élément de fixation (18) est couplé, dans une première zone d'extrémité, à un élément de verrouillage (30a) prenant la forme d'une plaque de verrouillage.
  7. Bague intérieure (14) selon la revendication 6, caractérisée en ce que la plaque de verrouillage est conçue en forme de U et/ou disposée dans une rainure (38) de l'élément de fixation (18).
  8. Bague intérieure (14) selon la revendication 6 ou 7, caractérisée en ce que la première bague de fixation (16a) et/ou la seconde bague de fixation (16b) présente un profilé de réception (32) dans lequel la plaque de verrouillage est reçue de manière sécurisée contre les chutes et/ou en ce que la plaque de verrouillage repose sur la seconde bague de fixation (16b).
  9. Bague intérieure (14) selon l'une des revendications 1 à 8, caractérisée en ce que l'élément de fixation (18) est fixé dans une seconde zone d'extrémité au niveau de la seconde bague de fixation (16b) par un élément de fixation (30b) de préférence sous forme d'écrou.
  10. Bague intérieure (14) selon l'une des revendications 1 à 9, caractérisée en ce que le palier d'aubes (20) de l'élément de fixation (18) est rendu étanche par rapport à la première bague de fixation (16a) et/ou à la seconde bague de fixation (16b) au moyen d'un élément d'étanchéité (36), en particulier une bague d'étanchéité.
  11. Procédé de fabrication d'une couronne d'aubes directrices (10) d'une turbomachine, comprenant les étapes :
    a) de mise à disposition d'une bague extérieure et de plusieurs aubes directrices réglables (12) ;
    b) d'insertion de paliers d'aube radialement extérieurs des aubes directrices (12) dans la bague extérieure ;
    c) de raccordement de paliers d'aube radialement intérieurs des aubes directrices (12) à un palier d'aubes (20) faisant saillie radialement d'un élément de fixation (18) associé ;
    d) de disposition d'une première bague de fixation (16a) au niveau des premières zones d'extrémité respectives des éléments de fixation (18) ;
    e) de disposition, à chaque fois, d'un élément de fixation (30a) au niveau des premières zones d'extrémité des éléments de fixation (18), les éléments de fixation (30a) limitant un mouvement axial relatif de la première bague de fixation (16a) par rapport aux éléments de fixation (18) ;
    f) de disposition d'une seconde bague de fixation (16b) au niveau des secondes parties d'extrémité respectives des éléments de fixation (18) de sorte que les éléments de fixation (18) s'étendent axialement entre la première et la seconde bague de fixation (16a, 16b) ;
    g) de disposition, à chaque fois, d'un élément de fixation (30b) à chaque seconde partie d'extrémité des éléments de fixation (18), les éléments de fixation (30b) limitant un mouvement axial relatif de la seconde bague de fixation (16b) par rapport aux éléments de fixation (18).
  12. Procédé selon la revendication 11, caractérisé en ce que, dans l'étape c), des douilles (24) sont insérées en tant que paliers d'aube radialement intérieurs dans les plaques intérieures (26) des aubes directrices (12) et des axes de palier sont insérés en tant que paliers d'aubes (20) des éléments de fixation (18) faisant saillie radialement dans les douilles (24) et/ou en ce que, dans l'étape c), des axes de support (34) sont insérés comme paliers d'aube des aubes directrices (12) dans des douilles respectives, en tant que paliers d'aubes (20) faisant saillie radialement des éléments de fixation (18).
  13. Procédé selon la revendication 11 ou 12, caractérisé en ce que, dans l'étape e), un élément de fixation (30a) respectif sous la forme d'une plaque de verrouillage est inséré radialement de l'intérieur dans une rainure respective (38) dans les premières zones d'extrémité des éléments de fixation (18) et repose sur celle-ci après la disposition de la seconde bague de fixation (16b) à l'étape f).
  14. Procédé selon l'une des revendications 11 à 13, caractérisé en ce que, dans l'étape g), des écrous sont vissés sur les secondes zones d'extrémité des éléments de fixation (18) comme éléments de fixation (30b), jusqu'à ce que les première et seconde bagues de fixation (16a, 16b) soient fixées entre elles par les éléments de fixation (18).
  15. Turbomachine, en particulier un moteur d'avion, comprenant au moins une bague intérieure (14) selon l'une des revendications 1 à 10 et/ou au moins une couronne d'aubes directrices (10), laquelle est fabriquée par un procédé selon l'une des revendications 11 à 14.
EP17179470.4A 2016-08-23 2017-07-04 Bague intérieure d'une couronne d'aubes directrices d'une turbomachine Active EP3287608B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102016215807.4A DE102016215807A1 (de) 2016-08-23 2016-08-23 Innenring für einen Leitschaufelkranz einer Strömungsmaschine

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EP3287608A1 EP3287608A1 (fr) 2018-02-28
EP3287608B1 true EP3287608B1 (fr) 2019-05-01

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US (1) US10494937B2 (fr)
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US10494937B2 (en) 2019-12-03
EP3287608A1 (fr) 2018-02-28
US20180058231A1 (en) 2018-03-01
DE102016215807A1 (de) 2018-03-01

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