EP3287604B1 - Élément de positionnement pourvu des évidements pour un système d'aube de guidage - Google Patents

Élément de positionnement pourvu des évidements pour un système d'aube de guidage Download PDF

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Publication number
EP3287604B1
EP3287604B1 EP17184378.2A EP17184378A EP3287604B1 EP 3287604 B1 EP3287604 B1 EP 3287604B1 EP 17184378 A EP17184378 A EP 17184378A EP 3287604 B1 EP3287604 B1 EP 3287604B1
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EP
European Patent Office
Prior art keywords
positioning element
axially
recess
element according
base portion
Prior art date
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Application number
EP17184378.2A
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German (de)
English (en)
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EP3287604A3 (fr
EP3287604A2 (fr
Inventor
Lothar Albers
Alexander Böck
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MTU Aero Engines AG
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MTU Aero Engines AG
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Publication date
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Publication of EP3287604A2 publication Critical patent/EP3287604A2/fr
Publication of EP3287604A3 publication Critical patent/EP3287604A3/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
    • 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
    • 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
    • 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
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • 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
    • F05D2230/644—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins for adjusting the position or the alignment, e.g. wedges or eccenters
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/14—Casings or housings protecting or supporting assemblies within
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/14—Two-dimensional elliptical
    • F05D2250/141—Two-dimensional elliptical circular
    • 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
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction

Definitions

  • the present invention relates to a positioning element for a guide vane arrangement of a guide vane stage of a gas turbine, with at least one base section curved in the circumferential direction; a plurality of receiving openings arranged adjacent to one another in the circumferential direction on the base section, the opening axis of which extends essentially in the radial direction and which are set up to receive a respective radially inner guide vane section; a coupling section provided on the base section, which can be coupled or coupled to a seal carrier of a sealing arrangement.
  • An example of a positioning element for a guide vane arrangement of a guide vane stage of a gas turbine is in the document US 2007/0128020 given.
  • Directional information such as “axial” or “axial”, “radial” or “radial” and “circumferential” are basically to be understood in relation to the machine axis of the gas turbine, unless something else explicitly or implicitly results from the context.
  • An addressed vane stage can be arranged in the area of a compressor or in the area of the turbine.
  • the feature coupling section is to be understood broadly and includes, for example, a section that enables a positive connection with a counterpart of a seal carrier. However, the coupling section can also simply be an area or a surface of the base section to which a sealing element can be attached directly.
  • Such a positioning element can also be referred to as a position ring or position half ring.
  • the circular arrangement in a gas turbine is achieved by two semicircular position half-rings which abut one another in a common parting plane. It has been shown that, due to the thermal conditions, a radial temperature gradient forms in the position half rings, the position half rings radially on the outside being subject to greater expansion in the circumferential direction than radially on the inside. This greater radially outer circumferential expansion leads in particular in the region of the parting plane to severe deformations of the positioning element and the seal carrier coupled to it. These deformations can also be described as constrictions and are known under the term cording effect.
  • the result of this is that, in particular, the seal carrier or its sealing elements come into contact with sealing fins rotating relative to these, so that the sealing elements are subject to severe wear.
  • the cording effect leads in particular to a narrowing or localization in the area of the parting plane Reduction in diameter when the gas turbine is accelerated and widening or local increase in diameter when the gas turbine is slowed down.
  • the object of the invention is to provide a positioning element in which the cording effect is reduced.
  • At least one recess is provided in the base section, which is arranged between two adjacent receiving openings and extends at least in the radial direction from the inside outwards.
  • the provision of such recesses enables the positioning element in the region of the recess to have a smaller effective radial height, to which the temperature gradient acts and which has an influence on the expansion of the positioning element. If such cutouts are provided along the circumference at a plurality of locations between the respective receiving openings, the cording effect can be influenced, since the deformations that occur are less than in the case of a continuous positioning element without cutouts.
  • the recesses in the positioning element also lead to a reduced bending stiffness of the positioning element.
  • the cording effect is also influenced by the ratio of the bending stiffness of the positioning element and seal carrier. It is advantageous if the positioning element is "softer" or less stiff, because this reduces the cording effect. Furthermore, with a less rigid positioning element, a stiffer seal carrier can counteract the constriction of the positioning element.
  • the positioning element can have an annular design and two semicircular base sections.
  • a reduction in the cording effect and thus in constrictions on the positioning element also leads to a reduction in local inlets at a division level from the semicircular base sections.
  • the coupling portion may include at least one axially front groove and one axially rear groove that run along the circumferential direction at the base portion. These two circumferential grooves are used in particular to couple a seal carrier to the positioning element.
  • the axially front groove and the axially rear groove can have essentially the same distance in the radial direction from a radial inside of the base section.
  • the two grooves are at approximately the same level or are at substantially the same distance (radius) from a machine axis.
  • the recess can also extend in the axial direction between two receiving openings and extend from an axially front surface of the base section to an axially rear surface of the base section.
  • the recess can be designed as a slot in the base section.
  • the recess can have a changing radial height along the axial direction or have a constant height. Furthermore, the recess along the axial direction can have a changing width in the circumferential direction or have a constant width.
  • the cording effect can be influenced in a targeted manner by an appropriate design or dimensioning of the cutouts or of the slot, in particular also taking into account that the radial temperature gradient also changes over the axial length.
  • the cutout can run in the circumferential direction in an axially rear region of the base section, such that outer walls of the receiving openings which are essentially cylindrical are visible from the axially rear.
  • the recess can be limited in the axial direction by an axially front wall section. The result is a continuous recess in an axially rear region, which extends forward in the axial direction between the receiving openings and ends at the axially front wall section.
  • the axially front groove and the axially rear groove can have a different distance from a radial inside of the base section.
  • the positioning element of the second embodiment can be produced by means of an additive manufacturing method, in particular by means of selective laser melting.
  • the invention also relates to a seal carrier for a seal arrangement with a base section which is curved in the circumferential direction and on which a sealing element is provided radially on the inside; a counter-coupling section which can be coupled or coupled to a coupling section of a positioning element, the counter-coupling section having an axially front spring section and an axially rear spring section which can be inserted or introduced with corresponding grooves in the coupling section of the positioning element. It is proposed that the axially front spring section and the axially rear spring section have a different distance from a radial inside of the base section.
  • Such a seal carrier is particularly suitable for coupling to a positioning element of the second embodiment.
  • the spring sections can be attached to an axially front support wall and to an axially rear support wall, such that the two spring sections face each other in the axial direction.
  • the base section can have a cover section which is inclined radially on the outside in relation to the axial direction and the radial direction.
  • Such an inclined cover section serves in particular in a coupled state to cover the recess on the positioning element.
  • a plurality of openings can be provided next to one another in the circumferential direction.
  • the invention also relates to a guide vane carrier arrangement for a gas turbine, in particular an aircraft gas turbine, with at least one positioning element according to the first embodiment and at least one associated seal carrier or with at least one positioning element according to the second embodiment and at least one seal carrier described above.
  • Fig. 1 shows a simplified schematic plan view in the axial direction of a first embodiment of a positioning element 10 and Fig. 2 shows an enlarged section of the positioning element 10.
  • the positioning element 10 has a base section 12 which is curved in a semicircle.
  • a plurality of receiving openings 14 arranged next to one another in the circumferential direction UR are provided in the base section 12.
  • the receiving openings 14 are used in particular for receiving guide vanes, not shown here.
  • Recesses 16 can be seen in the circumferential direction UR between two adjacent receiving openings 14. These recesses 16 extend in the radial direction RR from the inside to the outside.
  • the dashed line TE Fig. 1
  • the so-called parting plane is indicated.
  • the base section 12 further comprises a coupling section 18 located radially on the inside.
  • a sealing carrier (not shown here) can be attached to this coupling section 18.
  • the cutouts 16 extend in particular through the coupling section 18.
  • the feature coupling section can be understood broadly and comprises, for example, a section which enables a form-fitting connection to a counterpart of a seal carrier.
  • the coupling section can also simply be an area or a surface of the base section to which a sealing element can be attached directly.
  • FIG. 3 and 4 show the positioning element 10, which is also referred to in technical jargon as a locating ring or positioning ring, in a perspective view from the radial inside.
  • the Fig. 3 In particular, an abutting surface 20 of the base section 12 can be seen. With this abutting surface 20, the base section 12 lies in the area of the parting plane TE ( Fig. 1 ) on the other semicircular base section.
  • the coupling section 18 has a type of inverted T-profile.
  • an axially front groove 22 and an axially rear groove 24 are formed.
  • Corresponding counterparts or spring-like counter-coupling sections of a seal carrier are to be connected with these two grooves 22, 24.
  • the recesses 16 in particular also extend through the grooves 22, 24.
  • FIG. 5 is a view from the axially rear of the base section 12. From this illustration and also from the previous illustrations it can be seen that the cutouts 16 of FIG extend radially inward to radially outward. However, the cutouts 16 do not cut through the base section 12. Rather, the recesses 16 are slit-like. The width in the circumferential direction of such a recess 16 along the axial direction and / or along the radial direction can be constant or variable.
  • the 6A) and 6B ) are sectional views in the area of a recess 16 or slot, as shown by the section line VI-VI of Fig. 3 is indicated.
  • a radial height RH of the recesses 16 can, as can be seen from the sectional views in FIG 6A) and 6B ) can be seen, also be constant or changeable.
  • a variable height RH of the recess 16 or the slot is shown.
  • a constant height RH is shown over the axial extent.
  • the recesses can be adapted to respective properties, in particular the radial temperature gradients, by changing their dimensions in height and width.
  • Such temperature gradients also depend in particular on further structural boundary conditions of an inner ring and guide vane arrangement of a gas turbine.
  • FIG. 7 two variants of a base section 12 are shown in sub-figures A) and B).
  • the base section 12 in Figure 7A has a few, here in each case five recesses 16, starting from the division level TE.
  • the recesses are therefore not distributed along the circumference of the entire base section 12, but rather only near the parting plane TE.
  • cutouts 16 are provided along the entire circumference, but a cutout 16 is only provided every two receiving openings 14.
  • the Figure 7B corresponds to the Fig. 5 .
  • Fig. 7 shows a second embodiment of a positioning element 110 with a base section 112 in a perspective view obliquely from behind (axial direction).
  • Recesses 116 are provided between receiving openings 114 and extend at least in the radial direction RR.
  • the recesses 116 are not designed as slots, but are designed such that the outer peripheral walls 115 of the receiving openings 114 are visible.
  • the base section also has a coupling section 118, which has an axially front groove 122 and an axially rear groove 124.
  • the axially rear groove 124 is arranged radially on the outside of the base section 112. This changed arrangement of the axially rear groove 124 is due to the larger recesses 116 and material missing radially on the inside, on which an axially rear groove could be formed as in the first embodiment.
  • the axially rear groove 124 is located radially further outward than the axially front groove 122 with respect to a machine axis of the gas turbine.
  • the recesses 116 are delimited axially at the front by an axially front wall section 117.
  • the axially front wall section 117 also forms the back or opposite side of a groove base of the axially front groove 122.
  • the shape of the base section 112 with the recesses 116 and the coupling section 118 with the two grooves 122, 124 presented here is optimized in such a way that the base section 112 can be produced by means of an additive manufacturing method, in particular by means of selective laser melting.
  • the semicircular base section 112 can be built up in layers, for example, from axially front to axially rear.
  • the seal carrier 130 comprises counter-coupling sections 132, 134.
  • the counter-coupling sections 132, 134 project in the axial direction, such that spring-like projections are formed. Accordingly, the counter coupling section 132 can engage in the axially front groove 122 of the base section, and the counter coupling section 134 can engage in the axially rear groove 124 of the base section 112.
  • a sealing element, not shown here, would have to be provided on the radial inside 136 of the seal carrier 130.
  • the negative feedback sections 132, 134 are designed as axially front spring section 132 and as axially rear spring section 134. In particular, they are at a different distance from a radial inside of a base section 138.
  • the seal carrier 130 has the base section 138 which is arranged opposite (radially inside) the receptacle openings 114 in the assembled state.
  • This base section merges into or comprises an inclined covering section 140.
  • the covering section 140 is used in particular to enable producibility by means of selective laser melting.
  • a plurality of openings 142 are provided in the inclined cover section 140. These openings 142 also serve to produce them by means of selective laser melting.
  • the shape of the seal carrier 130 is thus designed such that it can be manufactured by means of an additive manufacturing method, in particular by means of selective laser melting.
  • Both embodiments have in common that recesses 16, 116 are provided in the base section 12, 112, which serve to reduce the cording effect on the positioning element 10, 110.
  • the cutouts act in particular to provide interruptions so that a radial temperature gradient cannot develop its full effect along the entire circumference of the positioning element 10, 110.
  • the cutouts also serve to reduce the bending stiffness of the positioning element, which likewise reduces the cording effect.

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

Claims (15)

  1. Élément de positionnement (10) pour un système d'aube de guidage d'un étage d'aube de guidage d'une turbine à gaz, pourvu d'au moins une section de base (12 ; 112) incurvée dans la direction circonférentielle (UR) ;
    une pluralité d'ouvertures de réception (14 ; 114) disposées les unes à côté des autres dans la direction circonférentielle (UR) au niveau de la section de base (12 ; 112), l'axe d'ouverture des ouvertures de réception s'étendant sensiblement dans la direction radiale et étant conçu pour recevoir une section d'aube de guidage respective radialement intérieure ;
    une section de couplage (18 ; 118) prévue au niveau de la section de base (12 ; 112), laquelle section de couplage peut être couplée ou est couplée à un support d'étanchéité (130) d'un système d'étanchéité ;
    caractérisé en ce qu'au moins un évidement (16 ; 116) est prévu dans la section de base (12 ; 112), lequel évidement est disposé entre deux ouvertures de réception (14 ; 114) adjacentes et s'étend de l'intérieur vers l'extérieur au moins dans la direction radiale (RR).
  2. Élément de positionnement selon la revendication 1, caractérisé en ce qu'il est annulaire et comporte deux sections de base (12 ; 112) semi-circulaires.
  3. Élément de positionnement selon la revendication 1 ou 2, caractérisé en ce que la section de couplage (18 ; 118) comprend au moins une rainure axialement avant (22 ; 122) et une rainure axialement arrière (24 ; 124) s'étendant le long de la direction circonférentielle (UR) au niveau de la section de base (12 ; 112).
  4. Élément de positionnement selon la revendication 3, caractérisé en ce que la rainure axialement avant (22) et la rainure axialement arrière (24) présentent sen siblement la même distance par rapport à un côté radialement intérieur de la section de base (12) dans la direction radiale (RR).
  5. Élément de positionnement selon l'une des revendications 1 à 4, caractérisé en ce que l'évidement (16) s'étend dans la direction axiale (AR) entre deux ouvertures de réception (14) et s'étend d'une surface axialement avant de la section de base (12) à une surface axialement arrière de la section de base (12).
  6. Élément de positionnement selon la revendication 5, caractérisé en ce que l'évidement (16) est réalisé sous la forme d'une fente dans la section de base (14).
  7. Élément de positionnement selon la revendication 6, caractérisé en ce que l'évidement (16) présente une hauteur radiale (RH) variable le long de la direction axiale (AR) ou présente une hauteur (RH) constante.
  8. Élément de positionnement selon la revendication 6 ou 7, caractérisé en ce que l'évidement (16) le long de la direction axiale (AR) présente une largeur variable dans la direction circonférentielle (UR) ou présente une largeur constante.
  9. Élément de positionnement selon l'une des revendications 1 à 3, caractérisé en ce que l'évidement (116) dans une zone axialement arrière de la section de base (112) s'étend dans la direction circonférentielle (UR) de telle manière que les parois extérieures (115) des ouvertures de réception (114), qui présentent une forme sensiblement cylindrique, sont visibles de l'arrière axialement.
  10. Élément de positionnement selon l'une des revendications 1 à 3 ou selon la revendication 9, caractérisé en ce que l'évidement (116) est limité dans la direction axiale (AR) par une section de paroi axialement avant (117).
  11. Élément de positionnement selon la revendication 9 ou 10 ou selon l'une des revendications 1 à 3, caractérisé en ce que la rainure axialement avant (122) et la rainure axialement arrière (124) présentent une distance différente par rapport à un côté radialement intérieur de la section de base (112).
  12. Élément de positionnement selon l'une des revendications 9 à 11, caractérisé en ce qu'il est produit au moyen d'un procédé de fabrication additif, en particulier au moyen d'une fusion sélective par laser.
  13. Système de support d'aube de guidage pour une turbine à gaz, en particulier une turbine à gaz d'avion, comportant au moins un élément de positionnement (10) selon l'une des revendications 1 à 3 et au moins un support d'étanchéité associé.
  14. Système de support d'aube de guidage pour une turbine à gaz, en particulier une turbine à gaz d'avion, comportant au moins un élément de positionnement (110) selon l'une des revendications 9 à 12 et au moins un support d'étanchéité (130), dans lequel le support d'étanchéité comprend :
    une section de base (138) incurvée dans la direction circonférentielle (UR) au niveau de laquelle un élément d'étanchéité est prévu radialement vers l'intérieur ;
    une section de contre-couplage (132, 134) étant ou pouvant être couplée à la section de couplage (122, 124) de l'élément de positionnement (110), dans lequel la section de contre-couplage comprend une section de ressort axialement avant (132) et une section de ressort axialement arrière (134) qui peuvent être insérées ou sont insérées dans des rainures (122, 124) correspondantes de la section de couplage de l'élément de positionnement (110), et dans lequel la section de ressort axialement avant (132) et la section de ressort axialement arrière (134) présente une distance différente par rapport à un côté radialement intérieur de la section de base (130).
  15. Système d'aube de guidage selon la revendication 14, caractérisé en ce que les sections de ressort (132, 134) sontfixées à une paroi de support axialement avant et à une paroi de support axialement arrière de telle manière que les deux sections de ressort (132, 132) soient orientées l'une vers l'autre dans la direction axiale (AR), dans lequel, de préférence, la section de base (138) comporte une section de recouvrement (140) inclinée radialement vers l'extérieur par rapport à la direction axiale (AR) et à la direction radiale (RR), dans lequel, de préférence, dans la section de base (138), en particulier dans sa section de recouvrement (140), une pluralité d'ouvertures (142) sont prévues les unes à côté des autres dans la direction circonférentielle (UR).
EP17184378.2A 2016-08-23 2017-08-02 Élément de positionnement pourvu des évidements pour un système d'aube de guidage Active EP3287604B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102016215784.1A DE102016215784A1 (de) 2016-08-23 2016-08-23 Positionierungselement mit Aussparungen für eine Leitschaufelanordnung

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EP3287604A2 EP3287604A2 (fr) 2018-02-28
EP3287604A3 EP3287604A3 (fr) 2018-05-16
EP3287604B1 true EP3287604B1 (fr) 2020-07-08

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US (1) US11156127B2 (fr)
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US11879480B1 (en) 2023-04-07 2024-01-23 Rolls-Royce North American Technologies Inc. Sectioned compressor inner band for variable pitch vane assemblies in gas turbine engines

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Also Published As

Publication number Publication date
US20180058263A1 (en) 2018-03-01
US11156127B2 (en) 2021-10-26
EP3287604A3 (fr) 2018-05-16
EP3287604A2 (fr) 2018-02-28
DE102016215784A1 (de) 2018-03-01

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