EP3561234B1 - Rotor pourvu de dispositif d'étanchéité - Google Patents

Rotor pourvu de dispositif d'étanchéité Download PDF

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Publication number
EP3561234B1
EP3561234B1 EP18169222.9A EP18169222A EP3561234B1 EP 3561234 B1 EP3561234 B1 EP 3561234B1 EP 18169222 A EP18169222 A EP 18169222A EP 3561234 B1 EP3561234 B1 EP 3561234B1
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EP
European Patent Office
Prior art keywords
rotor
closing element
sealing surface
engagement portion
installation
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
EP18169222.9A
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German (de)
English (en)
Other versions
EP3561234A1 (fr
Inventor
Kevin KAMPKA
Peter Schröder
Joana VERHEYEN
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.)
Siemens Energy Global GmbH and Co KG
Original Assignee
Siemens 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
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Priority to EP18169222.9A priority Critical patent/EP3561234B1/fr
Publication of EP3561234A1 publication Critical patent/EP3561234A1/fr
Application granted granted Critical
Publication of EP3561234B1 publication Critical patent/EP3561234B1/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
    • 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
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
    • 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
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor

Definitions

  • the invention relates to a rotor of a gas turbine with a sealing arrangement with regard to the sealing of an assembly space between two cover elements arranged in front of a rotor disk.
  • Rotors of gas turbines generally comprise a plurality of rotor disks, with at least some of the rotor disks being intended to accommodate the rotor blades.
  • the corresponding rotor disk has a plurality of blade holding grooves distributed around the circumference.
  • the end face of the blade retaining grooves is to be separated fluidically from the hot gas flowing through the gas turbine if possible, since cooling air is usually guided through the blade retaining grooves.
  • the rotor disks usually have sealing plates distributed in the circumference in front of the end face, which are fastened to the rotor disk and / or the rotor blades.
  • the inner edge section of the sealing plates facing the rotor disk engages in a circumferential annular groove.
  • the side of the inner edge section pointing away from the rotor disk rests against a flank of the annular groove.
  • an embodiment is often used in which the sealing plates are designed to overlap in the circumferential direction and to each other are movable.
  • the necessary free space can be created in order to be able to use the last rotor blade.
  • the sealing plates are pushed onto a block in the circumferential direction, with a larger gap in the width of the blade retaining groove being created between two sealing plates.
  • the sealing plates are again evenly distributed around the circumference.
  • a rotor according to the preamble of claim 1 which has a rotor disk with a plurality of blade retaining grooves, in each of which rotor blades are fastened.
  • Sealing plates are arranged in front of an end face of the rotor disk or the rotor blades. These are mounted in an annular groove in the rotor disk. In this case, the sealing plates can be partially displaced against one another in the circumferential direction for assembly. This creates an assembly space in the annular groove that is not closed by the sealing plates.
  • a closing element which is arranged below the sealing elements on the side facing the rotor axis and which closes the assembly space at least in sections.
  • the WO 2015/193033 A1 discloses, in an initially analogous manner, a rotor according to the preamble of claim 7 with a rotor disk to which a plurality of rotor blades are attached distributed around the circumference.
  • the overlapping sealing plates are again located in front of the rotor disk, the sealing plates being mounted on the outer circumference in an annular groove formed by the rotor blades.
  • the object of the present invention is therefore to improve the sealing by means of the sealing plates on the annular groove or the annular segment groove.
  • the object set for sealing an inner assembly space is achieved by an embodiment according to the invention according to the teaching of claim 1 and for sealing an outer assembly free space according to the teaching of claim 7.
  • the generic rotor is particularly preferably used in a gas turbine. Independently of this, however, the embodiment can also be used in other types of rotary or turbomachines. At least the rotor comprises at least one rotor disk. This rotor disk has a plurality of blade holding grooves which axially penetrate the rotor disk and are distributed around the circumference. Adjacent to the rotor disk, the rotor further comprises a rotor component, it being irrelevant in this regard whether the rotor component is likewise a bladed rotor disk or some other annular component. Furthermore, the generic rotor comprises a plurality of rotor blades, which are each fastened with a blade root in the blade holding grooves. A blade platform, which extends in the circumferential direction and axially, and here as a rule an end face of the rotor disk, adjoins the blade root towers. An airfoil extends radially outward from the airfoil platform.
  • the rotor has a circumferential annular groove which can be arranged both in the rotor disk and in the rotor component. At least the annular groove here is designed to open radially outward and thus has, viewed in the axial direction, on both sides a flank extending in the circumferential direction and essentially radially. One of these two flanks forms a sealing surface.
  • ring segment grooves are present in the blade platforms of the rotor blades in the protrusion protruding beyond the end face of the rotor disk, which extend in the circumferential direction and are designed to be open facing the rotor axis. At least one of the two flanks of the ring segment groove that extend in the circumferential direction and radially forms a sealing surface.
  • the generic rotor has the first version with the ring groove and the second version with the ring segment grooves at the same time.
  • the rotor comprises at least one first cover element and at least one second cover element.
  • the two cover elements can be designed as identical parts or different from one another.
  • At least the first cover element has at least one first engagement section which engages in the annular groove or in the annular segment groove.
  • the second cover element has at least one second engagement section, which likewise engages in the annular groove or in the annular segment groove. Both cover elements here rest against the sealing surface of the annular groove or the annular segment groove in the area of the engagement section.
  • the generic rotor has an assembly space in the area between the two cover elements, which is generally required for assembly of the cover elements and the rotor blades.
  • the assembly space adjoins the sealing surface and extends in the circumferential direction from an edge adjoining the sealing surface in the circumferential direction of the cover element to the opposite edge of the adjacent cover element adjoining the sealing surface.
  • the corresponding edge does not have to be the end of the cover element in the circumferential direction.
  • the cover elements each have an inner engagement section which is mounted in the annular groove and which extends toward the rotor axis. There is an inner assembly space between the inner engagement sections of the cover elements.
  • the cover elements each have an outer engagement section which is mounted in the ring segment groove and extends in a radially outward direction. There is an external assembly space between the outer engagement sections of the cover elements.
  • the tightness in the area of the annular groove or in the area of the annular segment groove is now improved in that a closing element is used.
  • the closing element is attached to the first engagement section and extends in the circumferential direction in sections to the adjacent engagement section. It is essential here that the closing element covers the assembly space between the two cover elements adjacent to the sealing surface, at least when the rotor is rotating. This is the case when, in a radial direction of view of the closing element or the assembly gap, the groove base of the annular groove or the annular segment groove located behind it is covered.
  • the closing element is fastened according to the invention to the first inner engagement section and in this case rests against the second inner engagement section when the rotor rotates. Accordingly, the inner assembly space is essentially closed.
  • the closing element is advantageously arranged essentially on the side facing the rotor axis below the engagement sections, so that the centrifugal force in the closing element presses it against the engagement sections.
  • the closing element is positioned with sufficient security in terms of sealing the assembly clearance and with regard to the necessary stability of the closing element only partially overlaps the second engagement section.
  • the closing element is adjustable on the first outer engagement section attached, wherein the rotation of the rotor leads to an adjustment of the closing element with a contact in the circumferential direction on the second engagement portion and / or with a contact in the radial direction on the groove base of the ring segment groove.
  • the closing element is advantageously arranged on the edge in the circumferential direction and at the same time on the radially outer edge.
  • a cover element has a spaced apart from the sealing surface, i. on the rear flap element arranged pointing to an end face of the rotor disk and the adjacent cover element, in contrast, has a front flap element.
  • the front tab element covers the rear tab element in sections, the front tab element still resting against the sealing surface.
  • the rear flap element is arranged on the second cover element and the front flap element is arranged on the first cover element.
  • the front strap element is correspondingly arranged on the second cover element.
  • the assembly space is located between the free end of the front tab element viewed in the circumferential direction and opposite in the circumferential direction a shoulder at which the rear tab element begins.
  • the assembly space extends, viewed in the axial direction, from the sealing surface to the rear bracket element.
  • each cover element i.e. the first cover element and the second cover element can be identical parts and consequently each cover element has a front tab element at one end in the circumferential direction and a rear tab element at the other end in the circumferential direction.
  • the closing element in the first embodiment advantageously rests against the tab element at least when the rotor rotates on the side facing the rotor axis, since these limit the assembly space on three sides.
  • a receiving profile extending in the axial direction is arranged on the first engagement section.
  • the receiving profile penetrates the engagement section in the axial direction.
  • the receiving profile is designed to be open to the rotor axis.
  • the receiving profile can be designed in the form of a T-slot or the like.
  • the closing element has a retaining profile which is fastened in the receiving profile.
  • the retaining profile is designed to be complementary to the receiving profile.
  • the length of the closing element in the circumferential direction is limited to 0.5 times the length of the first cover element and to 0.5 times the length of the second cover element. It is particularly advantageous if the length of the closing element corresponds to a maximum of 0.3 times the length of the cover element in the circumferential direction in the area of the annular groove.
  • the length of the closing element in the circumferential direction is considered greater than twice the length of the assembly space in the same direction.
  • the free length is greater than 1.5 times the length of the assembly space. It can thus be ensured that the assembly space is reliably covered and that there is contact with the engagement sections of the two cover elements on the three circumferential sides.
  • the width of the closing element, viewed in the axial direction, in the area of the fastening of the closing element on the first engagement section corresponds to at least 0.95 times the thickness of the first engagement section at the same point.
  • the movement space of the closing element in the axial direction is very limited relative to the engagement section. It is particularly advantageous if the width of the closing element in the area of the fastening corresponds to at least 0.99 times the thickness of the first engagement section. It can thus be assumed that when the first engagement section rests on the sealing surface, the closing element can also largely bear on the sealing surface.
  • the width of the closing element is not chosen to be unnecessarily large, but rather sufficient to cover the assembly space and to ensure that it is safe Abutment of the closing element in particular on the rear flap element. It is therefore advantageous if the width of the closing element apart from its attachment to the first engagement section and in this respect at least in the area of the assembly clearance corresponds to a maximum of 0.95 times the thickness of the annular groove. It is particularly advantageous if the width corresponds to a maximum of 0.8 times the thickness of the annular groove. This is considered to be sufficient to cover the assembly space and to ensure the necessary stability and, in contrast, allows easy assembly and avoids unnecessary weight.
  • the rotor in the area of the cover element 11 is shown in a longitudinal section.
  • the closing element 21, which is essential for the invention, cannot be seen and in this respect this illustration does not differ from the generic in the prior art.
  • the rotor disk 01 can be seen with a blade retaining groove 02 extending axially through the rotor disk 01.
  • a plurality of cover elements 11 are distributed around the circumference in front of an end face of the rotor disk 01 and in front of the blade retaining grooves 02.
  • the arrangement of a rotor component 06 is adjacent to the rotor disk 01 to recognize.
  • the rotor component 06 has a circumferential annular groove 07 which opens axially outward.
  • the annular groove 07 viewed in the axial direction, has a front flank and a rear flank.
  • the cover elements 11 are each received with an inner engaging section 12 in the annular groove 07.
  • the Fig. 2 in a further perspective illustration a view of the gap between 2 cover elements 11a and 11b.
  • the first cover element 11a has on the right edge in the illustration in the circumferential direction a rear tab element 13, which is arranged on the side facing the rotor disk 01.
  • This 13 is overlapped by a front tab element 14, which 14 is arranged on the left edge in the circumferential direction of the adjacent second cover element 11b.
  • An inner assembly space 09 is formed between the edge of the front flap element 14 and the shoulder from which the rear flap element 13 begins.
  • the inner assembly space 09 is required in order to be able to move the cover elements 11 in the circumferential direction so far that there is sufficient space is available for mounting the last rotor blade in the blade retaining groove 02.
  • the area between the cover elements 11 and the rotor disk 01 is supplied with cooling air, which in all Usually flow through the blade retaining grooves 02 into the individual rotor blades.
  • a closing element 21 is now used, which 21 covers the remaining inner assembly space 09 as best as possible.
  • the closing element 21 is fastened to the first cover element 11a at the first inner engagement section 12a and on the side facing the rotor axis rests against the second inner engagement section 12b of the second cover element 12b.
  • the Figures 3 and 4 the arrangement of the closing element 21 on the inner engagement portions 12a and 12b of the cover elements 11a and 11b.
  • the closing element 21 has a complementary retaining profile 22 which is fastened 22 in the receiving profile 16.
  • the actual function is fulfilled by the closing element 21 by its abutment on the side facing the rotor axis on the first inner engagement section and on the second inner engagement section, or in particular on the underside of the rear tab element 13 and the front tab element 14.
  • the length of the closing element 21 in the circumferential direction is selected to be significantly smaller than the length of the individual cover elements 11. This facilitates assembly and reduces the weight of this embodiment, as if a rotating piston ring were used.
  • cover elements 11 with the inner engagement sections 12 and the closing element 21 bear against a flank of the annular groove 07 in a sealing manner.
  • the Fig. 5 a section through the rotor component 06 with the annular groove 03.
  • the flank of the annular groove 07 pointing away from the rotor disk 01 forms a sealing surface 08.
  • the engagement sections 12 rest against this 08.
  • the closing element 21 likewise rests against the sealing surface 08.
  • the cover element 11 is sketched again in a perspective view, which 11 is used in this embodiment as the same part for the first cover element 11a and the second cover element 11b.
  • the arrangement of the rear strap element 13 on one side in the circumferential direction, the side opposite the front strap element 14 and the inner engagement section 12 with the receiving profile 16 can be seen.
  • the rotor in the area of the closing element 25 is now shown in detail.
  • the two adjacent cover elements 11a and 11b can be seen.
  • the blade platform 36 of the rotor blade 35 is located radially outside the cover element 11.
  • In the blade platform 36 there is an annular segment groove 37 on the side facing the rotor axis, the flank of the annular segment groove 37 facing away from the rotor disk forming a sealing surface 38.
  • An outer engagement section 15 of the cover element 11 engages in the ring segment groove.
  • the cover elements 11 are designed to overlap at their joint in the circumferential direction, the first cover element 11a having a rear tab element 13 and the adjacent second cover element 11b having a front tab element 14 protruding beyond the rear tab element 13.
  • the first cover element 11a has, as again in FIG Fig. 9 shown, a guide groove 17 in the first outer engagement section 15a, which 17 is aligned diagonally with an outer assembly space 10.
  • the locking element 25, which can be adjusted along the guide groove 17, is located in the guide groove 17. It is easy to see how the closing element 25 can be pushed completely into the guide groove 17 for the assembly of the sealing plates and blades, so that the cover elements 11 are pushed together completely in the circumferential direction can.
  • an outer assembly space 10 is created between the cover elements 11. This assembly space 10 leads, in particular in the area of the outer engagement sections 15 in the ring segment groove 37, to a gap through which cooling air can escape.
  • the Fig. 10 Again the cover element 11, which 11 can also be used in this embodiment as identical parts for all cover elements 11.
  • the outer engagement section 12 and the rear tab element 13, which is located on the edge in the circumferential direction, can again be seen.
  • the guide groove 17 for receiving the closing element 25 can also be seen.
  • the Fig. 12 shows schematically a second variant of the first embodiment from FIG Figs. 1 to 7 analogous to the illustration in Fig. 4 .
  • the inner engagement section 42 of the cover element 41 with the receiving profile 46 can be seen.
  • the closing element 51 is arranged on the side facing the rotor axis, which engages 51 with a holding profile 52 in the receiving profile 46.
  • the inner engagement section 42 is mounted with the closing element 51 in an annular groove 07 of the rotor disk 01.
  • the closing element 51 is sketched, the length of which extends in the circumferential direction beyond the length of the cover element 41 and thus two assembly spaces can be covered at the same time.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (10)

  1. Rotor, notamment d'une turbine à gaz,
    comprenant un disque (01) de rotor, qui a une pluralité de rainures (02) de retenue d'aube traversant axialement le disque (01) du rotor, en étant réparties sur le pourtour, dans lequel, dans le disque (01) du rotor ou dans une pièce (06) rotorique voisine du disque (01) du rotor, est prévue une rainure (07) annulaire faisant le tour et s'ouvrant vers l'extérieur radialement, dont un flanc, s'étendant dans la direction du pourtour et radialement, forme une surface (08) d'étanchéité, et comprenant au moins un premier élément (11a, 41) de recouvrement, qui (11a, 41) pénètre par une première partie (12a, 42) intérieure de pénétration dans la rainure (07) annulaire et s'applique à la surface (08) d'étanchéité, et comprenant au moins un deuxième élément (11b) de recouvrement, qui (11b) pénètre au voisinage du premier élément (11a) de recouvrement par une deuxième partie (12b) intérieure de pénétration dans la rainure (07) annulaire et s'applique à la surface (08) d'étanchéité, un espace (09) libre intérieur voisin de la surface (08) d'étanchéité étant présent entre les deux parties (12a, 12b, 42) de pénétration,
    dans lequel il est prévu un élément (21, 51) de fermeture, qui (21, 51) est fixé à la première partie (12a, 42) intérieure de pénétration et qui s'applique à la deuxième partie (12b) intérieure de pénétration au moins à la rotation du rotor et ferme l'espace (09) libre intérieur de montage,
    dans lequel l'élément (21, 41) de fermeture est fixé par un profilé (22, 52) de retenue dans un profilé (16, 46) de réception ouvert vers l'axe du rotor,
    caractérisé en ce que le profilé (16, 46) de réception traverse dans la direction axiale la première partie de pénétration.
  2. Rotor suivant la revendication 1,
    caractérisé
    en ce que la longueur de l'élément (21) de fermeture, dans la direction du pourtour, est plus petite que 0,5 fois, notamment plus petite que 0,3 fois, la longueur du premier élément (11a) de recouvrement et plus petite que 0,5 fois, notamment plus petite que 0,3 fois, la longueur du deuxième élément (11b) de recouvrement.
  3. Rotor suivant la revendication 1 u 2,
    caractérisé
    en ce que la longueur de l'élément (21, 51) de fermeture, dans la direction du pourtour, est plus grande que 2 fois la longueur de l'espace (08) libre de montage ; et/ou en ce que la longueur de l'élément (21, 51) de fermeture du profilé de retenue à l'extrémité libre, dans la direction du pourtour, est plus grande que 1,5 fois la longueur de l'espace (08) libre de montage.
  4. Rotor suivant l'une des revendications 1 à 3,
    caractérisé
    en ce que la largeur de l'élément (21, 51) de fermeture, dans la direction axiale dans la région de sa fixation à la première partie (12a, 42) de pénétration, représente au moins 0,95 fois, notamment au moins 0,99 fois, l'épaisseur de la première partie (12a, 42) de pénétration.
  5. Rotor suivant l'une des revendications 1 à 4,
    caractérisé
    en ce que la largeur de l'élément (21, 51) de fermeture, dans la direction axiale dans la région de l'espace (08) libre de montage, représente au moins 0,6 fois, notamment au moins 0,7 fois, la largeur de l'espace (08) libre de montage.
  6. Rotor suivant l'une des revendications 1 à 5,
    caractérisé
    en ce que la largeur de l'élément (21) de fermeture, dans la direction axiale dans la région de l'espace (08) libre de montage, représente au maximum 0,95 fois, notamment au maximum 0,8 fois, l'épaisseur de la rainure (07) annulaire.
  7. Rotor, notamment d'une turbine à gaz,
    comprenant un disque (01) de rotor, qui (01) a une pluralité de rainures (02) de retenue d'aube traversant axialement le disque (01) du rotor, en étant réparties dans le pourtour, et une pluralité d'aubes (35) mobiles, qui (35) sont chacune fixées par une emplanture d'aube dans les rainures (02) de retenue d'aube, à laquelle se raccorde une plateforme (36) d'aube dépassant le disque du rotor, et qui ont un corps d'aube s'étendant vers l'extérieur radialement, dans lequel, dans les plateformes (36) d'aube, est prévue, respectivement, une rainure (37) en forme de segment annulaire, s'étendant dans la direction du pourtour, s'ouvrant vers l'axe du rotor et dont le flanc, s'étendant dans la direction du pourtour et radialement, forme une surface (38) d'étanchéité, et comprenant au moins un premier élément (11a) de recouvrement, qui (11a) pénètre, par une partie (15a) extérieure de pénétration, dans la rainure (37) en forme de segment annulaire et s'applique à la surface (38) d'étanchéité, comprenant au moins un deuxième élément (11b) de recouvrement, qui (11b), en étant voisin du premier élément (11a) de recouvrement, pénètre, par une deuxième partie (15b) extérieure de pénétration, dans la rainure (37) en forme de segment annulaire et s'applique à la surface (38) d'étanchéité, un espace (10) libre extérieur de montage, voisin de la surface (38) d'étanchéité, étant présent entre les deux parties (15a, 15b) de pénétration,
    dans lequel
    un élément (25) de fermeture, qui (25) est fixé à la première partie (15a) extérieure de pénétration et s'applique à la deuxième partie (15b) de pénétration et/ou au fond de la rainure (37) en forme de segment annulaire, au moins à la rotation du rotor, et ferme l'espace (10) libre extérieur de montage,
    caractérisé en ce que
    dans la première partie (15a) extérieure de pénétration, il y a une rainure (17) de guidage s'étendant en diagonale dans la direction du pourtour et, en même temps, dans la direction radiale, rainure (17) dans laquelle l'élément (25) de fermeture est monté coulissant.
  8. Rotor suivant l'une des revendication 1 à 7,
    caractérisé
    en ce que le premier élément (11a) de recouvrement a un élément (13) d'attache postérieur à distance de la surface (08, 38) d'étanchéité et le deuxième élément (11b) de recouvrement a un élément (14) d'attache antérieur s'appliquant à la surface (08, 38) d'étanchéité et recouvrant, par endroits, l'élément (13) d'attache postérieur ; ou
    en ce que le deuxième élément (41) de recouvrement a un élément d'attache postérieur à distance de la surface d'étanchéité et le premier élément (41) de recouvrement a un élément d'attache antérieur s'appliquant à la surface d'étanchéité et recouvrant, par endroits, l'élément d'attache postérieur ;
    dans lequel l'espace (09, 10) libre de montage s'étend de l'élément (13) d'attache postérieur à la surface (08, 38) d'étanchéité.
  9. Rotor suivant la revendication 8,
    caractérisé
    en ce que l'élément (21, 25) de fermeture est fixé à la première partie (12a, 15a) de pénétration, au voisinage de l'élément (13) d'attache postérieur.
  10. Rotor suivant la revendication 8 ou 9,
    caractérisé en ce que l'élément (21, 25, 51) de fermeture s'applique aux éléments (13, 14) d'attache.
EP18169222.9A 2018-04-25 2018-04-25 Rotor pourvu de dispositif d'étanchéité Active EP3561234B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP18169222.9A EP3561234B1 (fr) 2018-04-25 2018-04-25 Rotor pourvu de dispositif d'étanchéité

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EP18169222.9A EP3561234B1 (fr) 2018-04-25 2018-04-25 Rotor pourvu de dispositif d'étanchéité

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EP3561234B1 true EP3561234B1 (fr) 2020-10-07

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Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2957725A1 (fr) * 2014-06-16 2015-12-23 Siemens Aktiengesellschaft Rotor avec toles d'étanchéité
EP2975218A1 (fr) * 2014-07-17 2016-01-20 Siemens Aktiengesellschaft Assemblage de disque de roue

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* Cited by examiner, † Cited by third party
Title
None *

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