EP2818638B1 - Assemblage aubes-disque, procédé et turbomachine - Google Patents

Assemblage aubes-disque, procédé et turbomachine Download PDF

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Publication number
EP2818638B1
EP2818638B1 EP13174014.4A EP13174014A EP2818638B1 EP 2818638 B1 EP2818638 B1 EP 2818638B1 EP 13174014 A EP13174014 A EP 13174014A EP 2818638 B1 EP2818638 B1 EP 2818638B1
Authority
EP
European Patent Office
Prior art keywords
blade
rotor
disc
cut
blades
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.)
Not-in-force
Application number
EP13174014.4A
Other languages
German (de)
English (en)
Other versions
EP2818638A1 (fr
Inventor
Alexander Dr. Klötzer
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Priority to EP13174014.4A priority Critical patent/EP2818638B1/fr
Publication of EP2818638A1 publication Critical patent/EP2818638A1/fr
Application granted granted Critical
Publication of EP2818638B1 publication Critical patent/EP2818638B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3053—Fixing blades to rotors; Blade roots ; Blade spacers by means of pins

Definitions

  • the invention relates to a blade-disc composite according to the preamble of patent claim 1, a method for producing such a blade-disc composite and a turbomachine.
  • a blade-disc composite in which the blades are arranged on one side on a radial collar of the disc and engage with a foot portion in a circumferential anchoring groove.
  • a blade-disc composite in which the blades are arranged on both sides of a radial collar.
  • the securing of the blades via securing wires which are inserted in receiving grooves extending in the circumferential direction and are each having a cross section in the radial collar and in the blade roots.
  • the blade feet could interfere with foot sections in the peripheral anchoring of the radial collar form fit.
  • a blade-disc composite in which the blades engage in a form-fitting manner in a peripheral anchoring groove of the disc.
  • the blades In the radial direction, the blades are secured via the positive connection with the anchoring groove.
  • adjacent blades In the circumferential direction adjacent blades are secured by longitudinal pins which are inserted into corresponding Nutwandungen.
  • the object of the invention is to provide a blade-disc composite comprising an alternative blade guard and easy to assemble and disassemble. Furthermore, it is an object of the invention to provide a method for assembling such a blade-disc composite and a turbomachine.
  • An inventive blade-disk composite of a turbomachine has a plurality of juxtaposed blades, which are used with their foot sections in a circumferential anchoring a rotor disc and with sections of a front wall and a rear wall of the anchoring groove in the radial direction positively cooperate.
  • at least one of the walls has at least one radial cutout for insertion of the rotor blades, two blades resting against a stop limited in the circumferential direction for forming two mutually opposite circumferential positive engagement and between them a middle blade is arranged by at least one wire element secured against tilting movements in the axial direction that extends in the circumferential direction between the cut-out wall and platform portions of the blades.
  • the blade-disk assembly in particular life-time-minimizing securing elements are dispensed with.
  • the inventive type of constructive the blades are in the radial, axial direction and circumferentially positively and non-positively secured to the disc.
  • the securing of the blades in the radial direction via the positive connection of their foot sections with the wall sections of the anchoring groove.
  • the securing of the blades in the circumferential direction is effected by the lateral stops or lateral boundaries of the cutouts in cooperation with at least two blades.
  • the securing of the blades in the axial direction and thus securing the middle blades takes place by the at least one wire element.
  • the blade-disc composite according to the invention is substantially more temperature-resistant than conventional blade-disc composites with plastically deformed securing elements.
  • the at least one wire element is inserted into a receiving groove which is formed in the rotor blades and / or at the end of the rotor disk.
  • a receiving groove can be easily trained.
  • the at least one middle blade and / or the rotor disc can have a receiving groove-side limiting section for fixing the position of the at least one wire element in the circumferential direction.
  • the limiting section is arranged in the region of the respective cutout, so that its position relative to the limiting section can be checked visually easily without aids.
  • the blades may have laterally of the central blade a platform-side axial downgrading to rest against the stops.
  • a platform-side downgrading is technically easy to perform.
  • individual blade groups are thereby formed in a plurality of cutouts, which are each secured in the circumferential direction.
  • a plurality of cutouts are provided in at least one of the walls, a plurality of receiving grooves and a plurality of wire elements.
  • the wire elements lie in each case with their ends on two nearest middle blades.
  • each blade is secured by two wire elements against tilting movements, so that even in the unlikely event of failure of one of the wire elements, the affected middle blade is secured by the other wire elements against tilting movements in the axial direction.
  • the number of grooves and the Wire elements preferably depend on the number of cutouts and are preferably identical to these.
  • the assembly of the at least one wire element can be simplified if the at least one wire element or the wire elements are in particular bent according to the course of the at least one receiving groove. In this way, the at least one wire element can be easily inserted into the at least one receiving groove.
  • the assembly can be simplified if the at least one wire element is straight and the receiving grooves are inclined to the rotor disk.
  • a rotor disk with a circumferential anchoring groove is first provided, wherein at least one radial cut-out is made in at least one of the two groove walls. Then the blades are inserted individually into the anchoring groove in the region of the at least one cutout. Thereafter, the at least one wire element is inserted in the circumferential direction in a receiving groove between blade platforms and the cut-out wall.
  • An assembly of the at least one wire element takes place without plastic deformation or screwing, whereby undefined material stresses are avoided by deformation and thus possible cracking.
  • the at least one wire element is only slightly elastically deformed for mounting and relaxes after insertion into the receiving groove.
  • the at least one wire element is held by the construction according to the invention stress-free in the blade-disc composite.
  • the blade-disc composite according to the invention is substantially more temperature-resistant than conventional blade-disc composites with plastically deformed securing elements.
  • the lack of plastic deformation allows easy, fast and reproducible assembly and disassembly or securing and unlocking of the blades.
  • the at least one wire element can be reused.
  • a plurality of cutouts are provided in at least one of the walls, wherein in each cutout three blades are assigned to the cutouts.
  • a first blade is inserted into the anchoring groove in the region of a cutout and displaced up to a stop in the circumferential direction.
  • a second blade is inserted into the anchoring groove in the region of the cutout and moved in a direction opposite to the opposite direction to a counter-stop.
  • a third blade is inserted into the anchoring groove in the region of the cutout.
  • a wire element is inserted into the respective receiving groove and this out with its ends in each case on two next middle blades.
  • blade groups are formed, which are each secured in the circumferential direction.
  • a turbomachine according to the invention such as a gas turbine and in particular an aircraft engine, has at least one blade-disk assembly according to the invention.
  • the blade-disc composite can be arranged on the compressor side and / or turbine side, so that a turbomachine with a plurality of such blade-disc composites is characterized by a heavy duty rotor.
  • a blade-disk composite 1 according to the invention of a turbomachine has a blade row 2 and a rotor disk 4.
  • the front view corresponds to a plan view in the axial flow direction of a hot gas flowing through the turbomachine.
  • the rear view thus corresponds to an upstream view or an axial view opposite to the flow direction.
  • the turbomachine is, for example, a gas turbine and in particular an aircraft engine.
  • the blade-disc composite 1 forms part of a rotor which rotates about an axial axis of rotation.
  • the rotor is a turbine rotor in the illustrated embodiment, but may also be a compressor rotor.
  • the blade row 2 consists of a plurality of in the circumferential direction of the blade-disc composite 1 juxtaposed blades 6, 8, 10. For reasons of clarity, only three blades 6, 8, 10 of the blade row 2 are numbered.
  • the blades 6, 8, 10 are as in axial section in FIG. 3 shown on the blade 8, each with its foot 12 and its neck 14 received in a circumferential anchoring groove 16 of the rotor disk 4.
  • the anchoring groove 16 has a front wall 18 viewed in the flow direction and a rear wall 20, which are connected to one another via a groove base 22.
  • the walls 18, 20 have two opposite annular beads 24, 26 against which the blades 6, 8, 10 with their widened compared to their necks 14 feet 12 in operation in the radial direction. From the groove bottom 22, the blades 6, 8, 10 are always spaced with their feet 12.
  • the blades 6, 8, 10 extend upstream with a front platform portion 28 over the front wall 18 and terminate flush with a radially extending end face 30 of the front wall 18.
  • the Blades 6, 8, 10 In the resting state are the Blades 6, 8, 10 with their front platform sections 28 each on a peripheral surface 32 of the front wall 18 and are spaced in operation over a small radial gap therefrom.
  • the front wall 18 is circumferentially formed with a uniform height so that all the blades 6, 8, 10 have the same front platform portion 28.
  • a wire element 40 for securing the respective circumferentially centered in the cutouts 38 blade 10 is inserted against axial tilting movements.
  • the respective wire element 40 which will be explained in more detail below, is inserted in each case a receiving groove 42 which in the embodiment shown here in sections in a bottom 44 of the rear platform sections 36 and the respective cutout 38 laterally bounding radial projections 46, 48 of the rear Wall 20 is introduced.
  • the projections 46, 48 are in FIG. 2 quantified.
  • the wire element 40 and the receiving groove 42 have a corresponding circular cross-section.
  • the blade-disc composite 1 described here by way of example has a large number of cut-outs 38, to each of which three rotor blades 6, 8, 10 are assigned. For clarity, only a section 38 is numbered representative of all sections.
  • the rotor blades 6, 8, 10 are each associated with a cutout 38 such that one of the rotor blades 10, as already mentioned above, is arranged centrally in the circumferential direction of the cutout 38 and the two other rotor blades 6, 8 are arranged laterally of the middle blade 10.
  • the lateral blades 6, 8 form sections a circumferential overlap with the projections 46, 48 and are thereby secured against axial tilting.
  • the lateral blades 6, 8 as in FIG. 4 shown in each case a lateral and axial downgrading 50, 52 in their rear platform section 36.
  • the projections 46, 48 of the rear wall 20 engage in each one of the downgrades 50, 52 and form with these two mutually opposite positive-locking connections, so that the blades 6, 8, 10 as a single 3-groups in Circumferential direction on the rotor disk 4 are secured in position.
  • the projections 46, 48 thus act as a stop and Jacobanaschlag for the two lateral blades 6, 8 of the blade group.
  • Each wire element 40, 40 ' extends between two adjacent cutouts 38, 38' and thus over a projection 48. They each extend over two adjacent lateral rotor blades 6, 8 'away and terminate at the end on two next middle rotor blades 10, 10'.
  • the middle blades 10, 10' shown in each case a receiving groove-side limiting section 58, 58 'on which the wire elements 40, 40' with their opposite end portions 54, 56 'abut the front side or nearly abut.
  • the wire elements 40, 40 ' are preferably bent in the circumferential direction and thus trace the bending of the receiving grooves 42.
  • the receiving grooves 42 thus extend in the embodiment shown here via two adjacent lateral blades 6, 8 'and end on two next middle blades 10, 10'.
  • the rotor disk 4 is first provided with a plurality of radial cutouts 38. Then, the blades 6, 8, 10 are inserted into the anchoring groove 16. For this purpose, the first lateral blade 6 is tilted or rotated in the middle of the cutout 38 in the anchoring groove 16. The lateral blade 6 is then moved in the circumferential direction until it rests with its front platform portion 28 on the projection 48 of the rotor disk 4. Then the circumferentially opposite second lateral blade 8 is tilted or rotated centrally of the cutout 36 in the anchoring groove 16 of the rotor disk 4 and displaced in the opposite direction to the projection 46 until it engages in its decrement 52.
  • the middle blade 10 is centered in the cutout 38 between the side blades 6, 8 tipped into the anchoring groove 16. Thereafter, in the region of an adjacent cutout 38 ', the rotor blades 6', 8 ', 10' are inserted into the anchoring groove 16.
  • a wire element 40 is inserted into the receiving groove 42 extending on the two middle moving blades 10, 10 ', in that they abut the front side on the receiving groove-side limiting sections 58, 58 'of the middle moving blades 10, 10'.
  • the assembly of the wire element 40 takes place in each case from the outside by lateral insertion into the receiving grooves 42 in the circumferential direction until it is present at an end portion 54 on the limiting section 58.
  • the wire element 40 is slightly elastically deformed in each case.
  • the other end portion 56 of the wire member 40 then snaps into the receiving groove 42 over its entire length and sets the front end on the limiting portion 58 'of the next middle blade 10' a. This process is repeated until all blades 6, 8, 10 or 6 ', 8', 10 'are used.
  • the disassembly of the respective wire element 40 is performed in reverse order.
  • the wire members 40 are slightly elastically deformed and then can be pulled outward in the circumferential direction.
  • a corresponding recess is provided in the receiving grooves 42 and / or in the wire elements 40.
  • the two Side of the middle blade 10 arranged lateral blades 6, 8 are each provided with a front platform side downgrading 50, 52 for cooperation with the lateral, the cutout bounding projections 46, 48 for securing the blade row 2 in the circumferential direction.
  • the wire elements 40 and the cutouts 36 are arranged in the region of the rear wall 20. Of course, they can also be arranged in the region of the front wall 18 or on both walls 18, 20.
  • the cutouts 38 may also have such an extent in the circumferential direction that they are assigned more than three blades 6, 8, 10.
  • blade groups with four, five, six or more blades are also possible, so that two, three, four or more middle blades 10 per cutout 38 are provided.
  • a blade-disk assembly of a turbomachine having a plurality of juxtaposed blades which are inserted with their root portions in a circumferentially extending anchoring groove of a rotor disc and cooperate with sections of a front wall and a rear wall of the anchoring groove in the radial direction positively wherein at least one of the walls has a radial cut-out for insertion of the blades, wherein two blades each abut against a stopper bounding the cut-out in the circumferential direction for forming two mutually opposite circumferential interlocking connection and between them a middle blade is arranged by at least one wire element secured against tilting movements in the axial direction, which extends in the circumferential direction between the cut-out wall and platform portions of the blades.

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

Claims (10)

  1. Assemblage aubes-disque (1) d'une turbomachine, avec une pluralité d'aubes mobiles (6, 8, 10) disposées côte à côte, insérées par leurs pieds (12) dans une rainure d'ancrage (16) périphérique d'un disque de rotor (4) et coopérant par correspondance de forme avec des segments (24, 26) d'une paroi avant (18) et d'une paroi arrière (20) de la rainure d'ancrage (16) en direction radiale, caractérisé en ce qu'au moins une des parois (18, 20) présente un évidement radial (38) pour l'insertion des aubes mobiles (6, 8, 10), deux aubes mobiles (6, 8) reposant chacune contre une butée (46, 48) limitant l'évidement (38) en direction périphérique pour former deux liaisons mécaniques périphériques opposées l'une à l'autre, et une aube mobile centrale (10) étant disposée entre celles-ci, dont les mouvements de basculement en direction axiale sont empêchés par au moins un élément filaire métallique (40) s'étendant en direction périphérique entre la paroi (20) évidée et des parties en plate-forme (36) des aubes mobiles (6, 8, 10).
  2. Assemblage aubes-disque selon la revendication 1, où ledit au moins un élément filaire métallique (40) est inséré dans une rainure de réception (42) formée dans les aubes mobiles (6, 8, 10) et/ou dans le disque de rotor (4).
  3. Assemblage aubes-disque selon la revendication 1 ou 2, où ladite au moins une aube mobile centrale (10) et/ou le disque de rotor (4) présentent un segment de délimitation (58) côté rainure de réception pour la fixation en position dudit au moins un élément filaire métallique (40) en direction périphérique.
  4. Assemblage aubes-disque selon la revendication 1, 2 ou 3, où les aubes mobiles (6, 8) latérales présentent une rétrogradation (50, 52) axiale côté plate-forme pour appui contre les butées (46, 48).
  5. Assemblage aubes-disque selon l'une des revendications précédentes, où une pluralité d'évidements (38) est prévue dans au moins une des parois (18, 20), une pluralité de rainures de réception (42) et une pluralité d'éléments filaires métalliques (40), lesquels sont passés par leurs extrémités (54, 56) sur les deux aubes mobiles (10, 10') les plus proches.
  6. Assemblage aubes-disque selon l'une des revendications précédentes, où ledit au moins un élément filaire métallique (40) est pré-plié.
  7. Assemblage aubes-disque selon l'une des revendications 1 à 5, où ledit au moins un élément filaire métallique (40) est droit et ladite au moins une rainure de réception est disposée obliquement par rapport au disque de rotor (4).
  8. Procédé de montage d'un assemblage aubes-disque (1) selon l'une des revendications précédentes, comprenant les étapes suivantes :
    - préparation d'un disque de rotor (4) avec une rainure d'ancrage (16) périphérique, où au moins un évidement (38) radial est ménagé dans au moins une des deux parois (18, 20),
    - insertion des aubes mobiles (6, 8, 10) dans la rainure d'ancrage(16) au niveau dudit au moins un évidement (38), et
    - insertion d'au moins un élément filaire métallique (40) en direction périphérique dans une rainure de réception (42) entre les plates-formes d'aubes (28, 36) et la paroi évidée (20).
  9. Procédé selon la revendication 8, où une pluralité d'évidements (38) est prévue dans au moins une des parois (18, 20) et où trois aubes mobiles (6, 8, 10) sont associées aux évidements (38), une première aube mobile (6) étant insérée dans la rainure d'ancrage (16) au niveau d'un évidement (38) et poussée jusqu'à une butée (48) en direction périphérique, une deuxième aube mobile (8) étant insérée dans la rainure d'ancrage (16) au niveau de l'évidement (38) et déplacée jusqu'à une contre-butée (46) en direction périphérique contraire, une troisième aube mobile (10) étant insérée dans la rainure d'ancrage (16) au niveau de l'évidement (38), et un élément filaire métallique (40) étant inséré dans la rainure de réception (42) correspondante, celui-ci étant passé par ses extrémités (54, 56) sur deux aubes mobiles centrales (10, 10') contiguës.
  10. Turbomachine comprenant un assemblage aubes-disque (2) selon l'une des revendications 1 à 7.
EP13174014.4A 2013-06-27 2013-06-27 Assemblage aubes-disque, procédé et turbomachine Not-in-force EP2818638B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP13174014.4A EP2818638B1 (fr) 2013-06-27 2013-06-27 Assemblage aubes-disque, procédé et turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13174014.4A EP2818638B1 (fr) 2013-06-27 2013-06-27 Assemblage aubes-disque, procédé et turbomachine

Publications (2)

Publication Number Publication Date
EP2818638A1 EP2818638A1 (fr) 2014-12-31
EP2818638B1 true EP2818638B1 (fr) 2016-04-27

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP13174014.4A Not-in-force EP2818638B1 (fr) 2013-06-27 2013-06-27 Assemblage aubes-disque, procédé et turbomachine

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Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB630732A (en) 1946-06-21 1949-10-20 Brush Electrical Eng An improved blade fixing for turbines and the like
US2873088A (en) * 1953-05-21 1959-02-10 Gen Electric Lightweight rotor construction
US3282561A (en) 1964-12-14 1966-11-01 Associated Electric Ind Ltd Turbine rotors
JPH01131801U (fr) * 1988-03-03 1989-09-07
DE10346263A1 (de) 2003-10-06 2005-04-28 Alstom Technology Ltd Baden Schaufelfußbefestigung
DE102004051116A1 (de) 2004-10-20 2006-04-27 Mtu Aero Engines Gmbh Rotor einer Turbomaschine, insbesondere Gasturbinenrotor
DE102005003511A1 (de) 2005-01-26 2006-07-27 Mtu Aero Engines Gmbh Rotor einer Turbomaschine, insbesondere Gasturbinenrotor
EP2022944A1 (fr) * 2007-07-27 2009-02-11 Siemens Aktiengesellschaft Fixation d'aube dans une rainure circonférentielle au moyen d'une masse céramique durcissable

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