EP2075412B1 - Vorrichtung zur Befestigung durch Verschraubung von Leitschaufeln an den Mantelring einer Statorstufe einer Strömungsmaschine und entsprechendes Befestigungsverfahren durch Verschraubung - Google Patents

Vorrichtung zur Befestigung durch Verschraubung von Leitschaufeln an den Mantelring einer Statorstufe einer Strömungsmaschine und entsprechendes Befestigungsverfahren durch Verschraubung Download PDF

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Publication number
EP2075412B1
EP2075412B1 EP20070124067 EP07124067A EP2075412B1 EP 2075412 B1 EP2075412 B1 EP 2075412B1 EP 20070124067 EP20070124067 EP 20070124067 EP 07124067 A EP07124067 A EP 07124067A EP 2075412 B1 EP2075412 B1 EP 2075412B1
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EP
European Patent Office
Prior art keywords
platform
blade
stator stage
bolting
shoulder
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.)
Active
Application number
EP20070124067
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English (en)
French (fr)
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EP2075412A1 (de
Inventor
André Lhoest
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aero Boosters SA
Original Assignee
Techspace Aero SA
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Filing date
Publication date
Application filed by Techspace Aero SA filed Critical Techspace Aero SA
Priority to EP20070124067 priority Critical patent/EP2075412B1/de
Publication of EP2075412A1 publication Critical patent/EP2075412A1/de
Application granted granted Critical
Publication of EP2075412B1 publication Critical patent/EP2075412B1/de
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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
    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/64—Mounting; Assembling; Disassembling of axial pumps
    • F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/40—Organic materials
    • F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/40—Organic materials
    • F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
    • F05D2300/431—Rubber
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/501—Elasticity

Definitions

  • the invention relates to the field of parts forming the stator of turbomachines and more particularly turbojets.
  • turbomachine stator stages and the axial compression stator of turbojet engines.
  • It relates to a device and a method of fastening by bolting blades on the ferrules forming part of the constitution of this type of stages.
  • the object of the invention is to propose another solution for fixing vanes on a ferrule which makes it possible to obtain an angular setting of the blades that are precise and at a lower cost.
  • the invention relates to a stator stage according to claim 1.
  • This comprises at least one ferrule and a plurality of blades fixed by bolting to the ferrule and whose platform portion is housed in a groove of the ferrule.
  • ferrule wherein the platform comprises at least one shoulder, a material element compressible being, in the compressed state at least in part, bearing against this shoulder and against the groove of the ferrule.
  • an additional element of compressible material is implanted whose location is forced by the shoulder and which is compressed during the bolting of the blade to the shell.
  • the systematic setting of the stator vanes is made during the tightening of the bolt / nut system between the blade and the ferrule.
  • the element increases the manufacturing tolerances of the blade and the ferrule.
  • the platforms of the blades and the bearing faces in the groove of the shell can be machined with tolerances large enough not to penalize their manufacturing cost.
  • the element of compressible material according to the invention thus provides a guarantee, only by chain of ribs, the wedging of the blades in the required tolerance range. Correction of the wedging or the incidence of the blades are therefore no longer to be achieved later bolting as in the prior art.
  • shoulder it is understood in the context of the invention, a sudden change in dimensions of the upper face of the platform of the blade opposite the shell with the function of serving as a support surface for the element made of compressible material. It may therefore be for example a groove, that is to say a long cut on the part of the platform facing the ferrule. It can also be a chamfer on one of the edges of the platform opposite the ferrule.
  • the shell to which the blade is fixed by bolting is preferably the outer shell of the floor.
  • the stage may comprise an element of continuous compressible material on the entire periphery of the stage. It may also comprise elements of discontinuous compressible material on the entire periphery of the stage. According to this variant of the discontinuous elements, each element of compressible material is of length at most equal to the circumferential width of the platform.
  • the element of compressible material may comprise a generally toroidal piece and circular section in the uncompressed state.
  • the compressible material may advantageously be chosen from elastomeric materials, silicone. It may be a VITON® type rubber. For example, they may be seal-type elements currently used in turbojet engines in low-pressure compressors at drum grooves.
  • the shoulder according to the invention can be made on part of the height of the platform.
  • the shoulder may comprise a wall inclined at an angle of between 30 and 45 ° with respect to the axis of the blade.
  • a stator stage particularly targeted by the invention is a compressor rectifier stage of a turbojet engine.
  • the invention also relates to a turbomachine comprising at least one stator stage described above.
  • a plurality of blades is fixed according to steps a) to d) and a single element of continuous compressible material is inserted over the entire periphery of the stage.
  • step c) can be carried out before step b).
  • the compressor straightener stage of a turbojet comprises a plurality of blades 1 attached to an outer shell 2 and an inner shell not shown here.
  • Each blade 1 comprises a central blade portion 10 and a platform portion 11 whose inner face 110 provides the definition of the aerodynamic stream.
  • the outer shell 2 is a one-piece piece in the form of an annular ring whose inner face 20 is machined hollow forming a groove so that the platforms 11 of the blades 1 can fit into it.
  • the blades 1 are all fixed by bolting to the outer shell 2 by means of bolts whose threaded rod 12 is an integral part of each blade 1.
  • an additional element 3 of compressible material is added according to the invention before bolting the blade 1.
  • the location of this element 3 is forced by the shoulder 111 made in the platform 11.
  • the shoulder 111 is made by machining and comprises two walls 111a, 111b.
  • One of the walls 111a makes an angle of between 30 and 45 ° with the axis X of the blade 1 and the other of the walls 111b is substantially parallel to the upper face 112 of the platform 11, that is to say that facing the groove 20 of the ferrule 2.
  • a single element of compressible material 3 continuous over the entire periphery of the stage is inserted ( figure 1 ).
  • the compressibility level of the material of the element 3 is variable and depends on the desired tolerances. Thus, for accuracy on the given angular setting, the more the mounting clearance between the platform of the other and the throat of the shell is accurate, the less the material used 3 must be compressible and the less effort to apply to the bolting of dawn must be important.
  • the element 3 is in the partially compressed state against both the walls 111a, 111b of the shoulder 11 and against the groove 20 of the shell 2.
  • the height h of the shoulder 111 corresponds to a portion of the height H of the platform 11 of the blade.
  • the element 3 used is advantageously a VITON® type generally circular O-ring type gasket whose length substantially corresponds to the peripheral length of the groove 20 of the shell 2.
  • the possible materials for the element 3 can also be either elastomeric materials or silicone.
  • the machining tolerances according to the fastening techniques of the prior art are of the order of X / 100 th on the platform widths and the ferrule groove in order to meet the required tolerance on the angular setting of the blades. Thanks to the invention, it is quite possible to double these tolerances, that is to say to perform machining with tolerances of the order of 2X / 100 eme while maintaining the same tolerance required on calibration angular blades.

Claims (16)

  1. Statorstufe mit mindestens einem Ring (2) sowie einer Mehrzahl von Schaufeln (1), die durch Verschraubung des Gewindeschaftes, der fester Bestandteil jeder Schaufel ist, an dem Ring befestigt sind und deren Plattform bildender Teil (11) Aufnahme in einer Nut (20) des Rings (2) findet,
    dadurch gekennzeichnet,
    dass die Plattform (11) mindestens einen Absatz (111, 111a, 111b) aufweist, wobei sich ein Element aus zusammendrückbarem Werkstoff (3) in einem Zustand, in dem es zumindest teilweise zusammengedrückt ist, in Anlage an diesem Absatz (111, 111a, 111b) und an der Nut (20) des Rings (2) befindet, wobei das Element, das beim Verschrauben zusammengedrückt wird, bei der Montage Spiel zwischen der Plattform der Schaufel und dem Ring aufnimmt und damit die Herstellung einer systematischen Anstellung der Schaufeln ermöglicht.
  2. Statorstufe nach Anspruch 1, bei der der Ring, an dem die Schaufel durch Verschraubung befestigt wird, der Mantelring der Statorstufe ist.
  3. Statorstufe nach Anspruch 1 oder 2, die ein Element aus zusammendrückbarem Werkstoff aufweist, das sich ohne Unterbrechung über den gesamten Außenumfang der Stufe erstreckt.
  4. Statorstufe nach Anspruch 1 oder 2, die Elemente aus zusammendrückbarem Werkstoff aufweist, die
    mit Unterbrechungen über den gesamten Außenumfang der Stufe angeordnet sind.
  5. Statorstufe nach Anspruch 4, die ein Element aus zusammendrückbarem Werkstoff in Anlage an jeder Plattform aufweist, wobei das Element aus zusammendrückbarem Werkstoff höchstens die gleiche Umfangslinienbreite hat wie die Plattform.
  6. Statorstufe nach einem der vorherigen Ansprüche, bei der das Element aus einem Werkstück besteht, das in nicht zusammengedrücktem Zustand allgemein wulstförmig mit kreisförmige Querschnitt ist.
  7. Statorstufe nach einem der vorherigen Ansprüche, bei der der zusammendrückbare Werkstoff unter den Elastomeren, Silikon und Viton® gewählt ist.
  8. Statorstufe nach einem der vorherigen Ansprüche, bei der der Absatz (111, 111a, 111b) über einen Teil der Höhe (H) der Plattform (11) ausgeführt ist.
  9. Statorstufe nach einem der vorherigen Ansprüche, bei der der Absatz von einer Abschrägung gebildet wird.
  10. Statorstufe nach einem der Ansprüche 1 bis 8, bei der der Absatz von einer Rille gebildet wird.
  11. Statorstufe nach einem der vorherigen Ansprüche, bei der der Absatz eine in einem Winkel von 30 bis 45° zur Achse X der Schaufel geneigte Wand (111a) aufweist.
  12. Statorstufe nach einem der Ansprüche 1 bis 11, die eine Leitstufe des Verdichters eines Turbotriebwerks bildet.
  13. Turbomaschine mit mindestens einer Statorstufe nach einem der Ansprüche 1 bis 12.
  14. Verfahren zur Befestigung von mindestens einer Schaufel (1) an einem Statorstufenring (2), wobei die folgenden Schritte ausgeführt werden:
    a) Herstellung eines Absatzes (11, 111a, 111b) an einer Plattform (11) einer Schaufel (1),
    b) Einsetzen der Plattform (11) der Schaufel in eine Nut (20) des Rings (2),
    c) Einfügen eines Elements aus zusammendrückbarem Wertstoff (3), dessen Höhe in nicht zusammengedrücktem Zustand größer ist als die Höhe (h) des Absatzes (11), zwischen die Plattform und die Nut,
    d) Verschrauben des Gewindeschafts, der fester Bestandteil jeder Schaufel ist, an dem Ring, wobei das Element, das beim Verschrauben zusammengedrückt wird, bei der Montage Spiel zwischen der Plattform der Schaufel und dem Ring aufnimmt und damit die Herstellung einer systematischen Anstellung der Schaufeln ermöglicht.
  15. Verfahren nach Anspruch 14, bei dem eine Vielzahl von Schaufeln gemäß den Arbeitsschritten a) bis d) befestigt werden und bei dem ein einziges, sich ohne Unterbrechung über den gesamten Außenumfang der Stufe erstreckendes Element aus zusammendrückbarem Werkstoff eingesetzt wird.
  16. Verfahren nach Anspruch 14 oder 15, bei dem der Arbeitsschritt c) vor dem Arbeitsschritt b) ausgeführt wird.
EP20070124067 2007-12-26 2007-12-26 Vorrichtung zur Befestigung durch Verschraubung von Leitschaufeln an den Mantelring einer Statorstufe einer Strömungsmaschine und entsprechendes Befestigungsverfahren durch Verschraubung Active EP2075412B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP20070124067 EP2075412B1 (de) 2007-12-26 2007-12-26 Vorrichtung zur Befestigung durch Verschraubung von Leitschaufeln an den Mantelring einer Statorstufe einer Strömungsmaschine und entsprechendes Befestigungsverfahren durch Verschraubung

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP20070124067 EP2075412B1 (de) 2007-12-26 2007-12-26 Vorrichtung zur Befestigung durch Verschraubung von Leitschaufeln an den Mantelring einer Statorstufe einer Strömungsmaschine und entsprechendes Befestigungsverfahren durch Verschraubung

Publications (2)

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EP2075412A1 EP2075412A1 (de) 2009-07-01
EP2075412B1 true EP2075412B1 (de) 2012-02-29

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Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2821595A1 (de) 2013-07-03 2015-01-07 Techspace Aero S.A. Statorschaufelabschnitt mit abwechselnden Befestigungen für eine axiale Turbomaschine
EP2886802B1 (de) * 2013-12-20 2019-04-10 Safran Aero Boosters SA Innenringdichtung der letzten Kompressorstufe eines axialen Turbotriebwerks
FR3108674B1 (fr) * 2020-03-27 2022-03-11 Safran Aircraft Engines Assemblage a etancheite renforcee pour turbomachine d’aeronef, comprenant une roue aubagee de stator ainsi qu’un carter exterieur agence autour de la roue aubagee

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE449091A (de) * 1940-12-21
BE471415A (de) * 1946-02-25
DE69815815T2 (de) * 1998-05-01 2004-05-13 Techspace Aero, Milmort Leitbeschaufelung für eine Turbomaschine
US6343912B1 (en) * 1999-12-07 2002-02-05 General Electric Company Gas turbine or jet engine stator vane frame
US6371725B1 (en) * 2000-06-30 2002-04-16 General Electric Company Conforming platform guide vane
FR2906296A1 (fr) * 2006-09-26 2008-03-28 Snecma Sa Dispositif de fixation d'une aube fixe dans un carter annulaire de turbomachine, turboreacteur incorporant le dispositif et procede de montage de l'aube.

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