EP3155227B1 - Aube de turbine - Google Patents

Aube de turbine Download PDF

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Publication number
EP3155227B1
EP3155227B1 EP15760398.6A EP15760398A EP3155227B1 EP 3155227 B1 EP3155227 B1 EP 3155227B1 EP 15760398 A EP15760398 A EP 15760398A EP 3155227 B1 EP3155227 B1 EP 3155227B1
Authority
EP
European Patent Office
Prior art keywords
section
turbine blade
passage section
fluid
central
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
EP15760398.6A
Other languages
German (de)
English (en)
Other versions
EP3155227A1 (fr
Inventor
Stefan Dahlke
Tilman Auf Dem Kampe
Marc Fraas
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 AG
Original Assignee
Siemens AG
Siemens Corp
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 Siemens AG, Siemens Corp filed Critical Siemens AG
Publication of EP3155227A1 publication Critical patent/EP3155227A1/fr
Application granted granted Critical
Publication of EP3155227B1 publication Critical patent/EP3155227B1/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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • 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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/186—Film cooling
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting
    • F05D2230/211—Manufacture essentially without removing material by casting by precision casting, e.g. microfusing or investment casting
    • 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
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/32—Arrangement of components according to their shape
    • F05D2250/323—Arrangement of components according to their shape convergent
    • 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
    • F05D2250/30—Arrangement of components
    • F05D2250/32—Arrangement of components according to their shape
    • F05D2250/324—Arrangement of components according to their shape divergent
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling

Definitions

  • the invention relates to a turbine blade for a turbomachine according to the preamble of claim 1.
  • Such turbine blades are known from JP 2006 307 842 A known.
  • Turbomachines in particular gas turbines (in the broad sense), have a gas turbine (in the narrower sense), in which a hot gas, which was previously compressed in a compressor and heated in a combustion chamber, is relaxed to work.
  • gas turbines are designed in Axialbauweise, wherein the gas turbine is formed by a plurality of successively located in the flow direction blade rings.
  • the blade rings have circumferentially disposed blades and vanes, with the blades attached to a rotor of the gas turbine and the vanes secured to the housing of the gas turbine.
  • thermodynamic efficiency of gas turbines is the higher, the higher the inlet temperature of the hot gas is in the gas turbine.
  • the height of the inlet temperature limits are set by the thermal load capacity of the turbine blades. Accordingly, an object is to provide turbine blades that have sufficient mechanical strength for the operation of the gas turbine even at high thermal loads.
  • turbine blades are provided with elaborate coating systems.
  • To further increase the allowable turbine inlet temperature turbine blades are cooled during operation of the gas turbine.
  • the film cooling is a very effective and reliable method for cooling of highly stressed turbine blades. In this case, cooling air is tapped from the compressor and fed into the provided with internal cooling channels turbine blades.
  • the air After a convective cooling of the material from the inside of the turbine blades forth the air is directed through fluid channels to the outer surface of the turbine blade. There it forms a film that flows along the outer surface of the turbine blade and cools it, while protecting it from the hot flow.
  • Ring vortex ⁇ 1 The cooling air jet acts like an inclined cylinder on the main flow and accelerates it. There are pressure differences between the upstream and downstream side and the top of the cooling air jet, which lead to a compensating flow. As a result, ring vortices ⁇ 1 are formed. The rotation of the exiting boundary layer of the cooling air supports this effect.
  • Kidney vertebra ⁇ 2 The kidney vertebrae are the result of a pair of vertebrae in the fluid channel. Frictional forces in the free shear layer between the exiting cooling fluid jet and the main flow additionally amplify the rotation.
  • Horseshoe vortices ⁇ 3 are formed in the dust area of a cylinder standing vertically in a boundary layer flow. Near the wall, the pressure in the boundary layer is minimal. In contrast, a positive pressure gradient forms in the outer layer of the main flow boundary layer. The boundary layer separates and rolls against the main flow in the direction of the pressure minimum on the wall. The resulting vortex lays on both sides of the cylinder.
  • the direction of rotation of the horseshoe vortices ⁇ 3 is opposite to that of the neighboring ealds ⁇ 2, and the horseshoe vortices ⁇ 3 run laterally below the cooling air jet in the case of single-hole blow-out.
  • Instationary vertebrae ⁇ 4 The unsteady vertebrae are similar to Kármán vertebrae in the wake of a cylinder.
  • the cause of vortex formation is the boundary layer separation on the suction side of the cylinder.
  • the unsteady vortices ⁇ 4 arise perpendicular to the cooled surface.
  • Each of the two vortex arms ⁇ 2 is formed by a vortex, wherein the velocity vectors of the hot gas to Coolant fluid jet, and it forms by the action of the hot gas at the jet edge of a chimney vortex with two vortex arms ⁇ 2.
  • Each of the two vortex arms ⁇ 2 is formed by a vortex, wherein the velocity vectors of the hot gas on the two inner sides of the vortex arms point away from the outer wall.
  • the central channel section adjoins the intermediate channel section to form an intermediate, lying perpendicular to the longitudinal axis of the fluid channel shoulder surface.
  • a shoulder surface may be formed which lies in a plane inclined at an angle ⁇ 90 °, for example approximately 45 °, to the longitudinal axis of the fluid channel.
  • the shoulder surface is formed on a wall region of the fluid channel, while on the opposite wall region of the intermediate channel section and the central channel section in a straight line, ie without shouldering, merge into each other.
  • the wall of the fluid channel can extend in a straight line over its entire length.
  • a shoulder with a low shoulder height can also be formed here.
  • an intermediate channel section is provided between the central channel section and the inflow channel section which has a constant, preferably circular or oval cross-section over its length, the longitudinal axis of the intermediate channel section being offset from the longitudinal axis of the central fluid channel section and in particular runs parallel to this.
  • the flow of the cooling fluid in the fluid channel can be influenced by the change in geometry according to the invention in such a way that the local flow velocities in the fluid channel are adapted in such a way that, on the one hand, the in Figure 15 vortex pair ⁇ 2 turns exactly the other way round and on the other hand, the separation in the diffuser can be moved to the upstream side, as in the FIG. 13 is shown. Both effects have a positive influence on the film cooling efficiency and in particular can cause the lateral expansion of the cooling fluid jet.
  • the central channel section has a cross-sectional area which is smaller by at least 30%, in particular by at least 40% and preferably at least 60%, compared with the intermediate channel section.
  • the outflow channel section may be formed in a manner known per se diffuser-like with a widening cross-section.
  • the wall of the fluid channel extends at its side facing the cold gas side wall region in the direction the longitudinal axis of the fluid channel and connects in a straight line to the central channel section.
  • the outflow channel section has a constant, in particular round cross-section over its entire length.
  • the outflow channel section preferably runs concentrically with the central channel section and has the same cross section as the latter.
  • FIG. 1 is a section of a turbine blade wall 1, in which a fluid channel 2 is formed, through which a cooling fluid such as cooling air from a cold gas side of the turbine blade - here the interior of the turbine blade - to a hot gas overflowed outer surface of the turbine blade wall 1, which a Hot gas side of the turbine blade forms, can flow.
  • a cooling fluid such as cooling air from a cold gas side of the turbine blade - here the interior of the turbine blade - to a hot gas overflowed outer surface of the turbine blade wall 1, which a Hot gas side of the turbine blade forms, can flow.
  • the fluid channel 2 has at its to the cold gas side pointing end portion an inflow channel portion 2a with a fluid inlet port 3, at its end facing the hot gas side of the turbine blade wall 1 end a diffuser-like expanding Ausström- channel section 2b with a Fluidauslassö réelle 4 and between the inflow channel section 2a and the outflow channel section 2b a central channel section 2c, which defines a longitudinal axis X of the fluid channel 2 and has a constant circular or oval cross section over its length, on.
  • the longitudinal axis X of the fluid channel 2 encloses an acute angle, which is measured between the longitudinal axis X and the surface on the upstream side and the upstream side of the fluid channel, with the surface of the turbine blade wall 1 overflowed by the hot gas.
  • an intermediate channel portion 2d having a larger cross sectional area than the central channel portion 2c.
  • the inflow channel portion 2a and the intermediate channel portion 2d are formed as a continuous bore, so that the intermediate channel portion 2d to the inflow channel portion 2a rectilinear and has a constant cross section over its length.
  • the transition region between the intermediate channel section 2d and the central channel section 2c is sharp-edged, wherein the wall of the fluid channel 2 is rectilinear on that side of the fluid channel 2 which faces the cold gas side, and a shoulder surface 5 on the opposite wall region facing the hot gas side is formed between the intermediate channel portion 2d and the central channel portion 2c, which is perpendicular to the longitudinal axis X of the fluid channel 2.
  • a shoulder surface 5 on the intermediate channel portion 2d and the central channel section 2c on the cold gas side facing wall region, in which case on the opposite, ie facing the hot gas side wall region the Wall of the fluid channel 2 in a straight line, that runs without shouldering.
  • the transition from the intermediate channel section 2d to the central channel section 2c of the fluid channel 2 is clearly visible.
  • the intermediate channel section 2d and the central channel section 2c each have a circular cross-section, the diameter D of the intermediate channel section 2d being significantly larger than the diameter 2d of the central channel section 2c.
  • the diameter ratio D / d is about 1.5.
  • the cross-sectional area of the central channel portion 2c has a cross sectional area smaller by about 55% than the intermediate channel portion 2d.
  • the intermediate channel portion 2d goes straight into the central channel portion 2c, while in the remaining peripheral portions the shoulder surface 5 is formed between the two channel portions 2d, 2c.
  • the intermediate channel section 2d has an oval cross section and the central channel section 2c has a circular cross section. Due to the oval configuration of the intermediate channel section 2d, the shoulder surface 5 is present only at the upstream wall region of the fluid channel 2.
  • the sharp-edged constriction in the transition region between the intermediate channel section 2d and the central channel section 2c causes the flow of cooling fluid - as in FIG FIG. 13 shown in the diffuser-extended outflow channel section 2b from the wall of the fluid channel at the upstream side with respect to the hot gas flow H side dissolves.
  • the cooling fluid thus optimally contacts the outer surface after leaving the fluid channel 2 the turbine blade wall 1, in order to protect them from the overflowing hot gas.
  • FIG. 5 a similar fluid channel 2 is shown in a turbine blade wall 1.
  • the fluid inlet opening 3 is formed in the end face of a bead 6, which protrudes inwardly from the inner surface of the turbine blade wall 1, so that the cooling fluid enters the front side into the fluid channel 2.
  • FIG. 6 a further embodiment of a fluid channel 2 in a turbine blade wall 1 is shown.
  • this comprises an inflow channel section 2a on the cold side of the turbine blade wall 1, an outflow channel section 2b on the hot side of the turbine blade wall 1, an inlet channel section 2a and the outflow channel section 2a.
  • Channel section 2b lying central channel portion 2c with a constant over its length, circular cross section, and an intermediate channel portion 2d, which is formed between the inflow channel portion 2a and the central channel portion 2c.
  • the inflow channel section 2a and the intermediate channel section 2d are formed in the manner of a cylindrical bore with a constant diameter over the length, which is larger than the diameter of the central channel section 2c.
  • the longitudinal axis defined by the intermediate fluid passage 2d and the inflow fluid passage 2a is offset from the longitudinal axis X of the central passage portion 2c.
  • the arrangement is such that between the intermediate channel section 2d and the central channel section 2c, a shoulder surface 5 is formed on the side facing the cold gas side of the fluid channel 2, while on the opposite, ie the hot gas side facing the Fluidkanalwandung in the transition region between the Between channel section 2d and the central channel section 2c is rectilinear, so here is a steady transition from the intermediate channel section 2d takes place in the central channel section 2c without shouldering.
  • the shoulder surface 5 is not perpendicular to the longitudinal axis of the fluid channel, but in a relative to the longitudinal axis X by about 45 ° inclined plane.
  • the transition region is in the cross section of FIG. 11 recognizable.
  • the shoulder surface may also be formed on the wall region of the fluid channel 2 pointing to the hot gas side, while the fluid channel wall in the transitional region between the intermediate channel section 2d and the central channel section 2c runs rectilinearly on the opposite side, ie facing the cold gas side.
  • FIGS. 7 and 8 Such embodiments are in the FIGS. 7 and 8 shown.
  • FIG. 7 it can be seen that the plane in which the shoulder surface 5 lies encloses an angle ⁇ 90 ° with the wall area situated to the hot gas side, so that a kind of return is formed.
  • the shoulder surface 5 with the cold gas side wall area an angle ⁇ 90 ° include forming a recess, as in FIG. 9 is shown.
  • the outflow channel section 2b is formed diffuser-like.
  • the outflow passage portion 2b may be as shown in FIG. 10 shown also represent a continuation of the central channel section 2c.
  • the inflow channel portion 2a and the intermediate channel portion 2d form a larger diameter bore
  • the central channel portion 2c and the outflow channel portion 2b have a smaller diameter bore, the bores being offset such that a shoulder surface 5 in the transitional region between the Inter-channel portion 2d and the central channel portion 2c formed on the downstream side of the Fluidkanalwandung.
  • the cooling fluid in the fluid channel 2 is initially delayed and then accelerated in the region of the inclined shoulder surface 5 and deflected such that a separation of the cooling fluid flow in the upstream side the Fluidkanalwandung takes place.

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

Claims (12)

  1. Aube de turbine pour une turbomachine, comprenant une paroi (1) d'aube de turbine, dans laquelle est constitué au moins un canal (2) pour du fluide, par lequel un fluide de refroidissement peut passer d'un côté de gaz froid à une surface balayée par du gaz chaud, c'est-à-dire au côté de gaz chaud de la paroi (1) de l'aube de turbine, et dans laquelle le au moins un canal (2) pour du fluide a, sur sa partie d'extrémité tournée vers le côté de gaz froid, un tronçon (2a) de canal d'entrée, sur sa partie d'extrémité tournée vers le côté de gaz chaud de la paroi (1) de l'aube de turbine, un tronçon (2b) de canal de sortie et, entre le tronçon (2a) de canal d'entrée et le tronçon (2b) de canal de sortie, un tronçon (2c) de canal central, de section transversale circulaire ou ovale, constante sur la longueur, qui définit un axe (X) longitudinal du canal (2) pour du fluide, lequel fait, avec la surface balayée par du gaz chaud de la paroi (1) de l'aube de turbine, un angle aigu, le canal (2) pour du fluide ayant, entre le tronçon (2a) de canal d'entrée et le tronçon (2c) de canal central, un tronçon (2d) de canal intermédiaire, qui a une surface de section transversale plus grande que le tronçon (2c) de canal central, dans laquelle
    - le tronçon (2c) de canal central est raccordé au tronçon (2d) de canal intermédiaire avec formation d'une surface (5) en épaulement entre eux, perpendiculaire à l'axe longitudinal du canal (2) pour du fluide ou
    - en ce que dans la partie de transition, entre le tronçon (2d) de canal intermédiaire et le tronçon (2c) de canal central, est constituée une surface (5) en épaulement, qui se trouve dans un plan incliné d'un angle α≠90° par rapport à l'axe longitudinal du canal (2) pour du fluide, la surface (5) en épaulement étant constituée sur une partie de paroi du canal (2) pour du fluide, caractérisée en ce que
    sur la partie de paroi opposée à la surface (5) en épaulement, le tronçon (2d) de canal intermédiaire et le tronçon (2c) de canal central se transforment l'un dans l'autre en ligne droite, c'est-à-dire sans formation d'un épaulement.
  2. Aube de turbine suivant la revendication 1, caractérisée en ce que le tronçon (2d) de canal intermédiaire a une section transversale constante sur sa longueur.
  3. Aube de turbine suivant la revendication 2, caractérisée en ce que le tronçon (2d) de canal intermédiaire a une section transversale circulaire ou ovale et l'axe longitudinal du tronçon (2d) de canal intermédiaire est décalé par rapport à l'axe (X) longitudinal du tronçon (2c) central du canal pour du fluide.
  4. Aube de turbine suivant l'une des revendications précédentes, caractérisée en ce que la surface (5) en épaulement est constituée sur la partie de paroi, tournée vers le côté de gaz chaud, du canal (2) pour du fluide.
  5. Aube de turbine suivant l'une des revendications précédentes, caractérisée en ce que la surface (5) en épaulement est constituée sur la partie de paroi, tournée vers le côté de gaz froid, du canal (2) pour du fluide.
  6. Aube de turbine suivant l'une des revendications précédentes, caractérisée en ce que le tronçon (2c) de canal central a, par rapport au tronçon (2d) de canal intermédiaire, une surface de section transversale plus petite d'au moins 30%, notamment d'au moins 40%, et de préférence d'au moins 60%.
  7. Aube de turbine suivant la revendication 6, caractérisée en ce que le tronçon (2c) de canal central et le tronçon (2d) de canal intermédiaire ont chacun une section transversale circulaire et le diamètre (D) du tronçon (2d) de canal intermédiaire et le diamètre (d) du tronçon (2d) de canal central sont dans le rapport D/d = 1,3 à 1,7, notamment D/d = 1,5.
  8. Aube de turbine suivant l'une des revendications précédentes, caractérisé en ce que le tronçon (2b) de canal de sortie est constitué à la manière d'un diffuseur, en ayant une section transversale, qui s'évase.
  9. Aube de turbine suivant la revendication 8, caractérisée en ce que la paroi du canal (2) pour du fluide s'étend, à sa partie de paroi tournée vers le côté de gaz froid, s'étend dans la direction de l'axe longitudinale du canal (2) pour du fluide et se raccorde en ligne droite au tronçon (2c) de canal central.
  10. Aube de turbine suivant l'une des revendications 1 à 7, caractérisée en ce que le tronçon (2c) de canal de sortie a, sur toute sa longueur, une section transversale, qui reste la même, notamment circulaire.
  11. Aube de turbine suivant la revendication 10, caractérisée en ce que le tronçon (2b) de canal de sortie s'étend concentriquement à l'axe (X) longitudinal du canal (2) pour du fluide et a notamment la même section transversale que le tronçon (2c) de canal central.
  12. Aube de turbine suivant l'une des revendications précédentes, caractérisée en ce que l'aube de turbine est fabriquée par le procédé de coulée de précision.
EP15760398.6A 2014-08-26 2015-08-21 Aube de turbine Not-in-force EP3155227B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP14182277.5A EP2990605A1 (fr) 2014-08-26 2014-08-26 Aube de turbine
PCT/EP2015/069232 WO2016030289A1 (fr) 2014-08-26 2015-08-21 Aube de turbine

Publications (2)

Publication Number Publication Date
EP3155227A1 EP3155227A1 (fr) 2017-04-19
EP3155227B1 true EP3155227B1 (fr) 2019-01-02

Family

ID=51392173

Family Applications (2)

Application Number Title Priority Date Filing Date
EP14182277.5A Withdrawn EP2990605A1 (fr) 2014-08-26 2014-08-26 Aube de turbine
EP15760398.6A Not-in-force EP3155227B1 (fr) 2014-08-26 2015-08-21 Aube de turbine

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Application Number Title Priority Date Filing Date
EP14182277.5A Withdrawn EP2990605A1 (fr) 2014-08-26 2014-08-26 Aube de turbine

Country Status (5)

Country Link
US (1) US9915150B2 (fr)
EP (2) EP2990605A1 (fr)
JP (1) JP6328847B2 (fr)
CN (1) CN106574507B (fr)
WO (1) WO2016030289A1 (fr)

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CN113719323B (zh) * 2021-07-09 2022-05-17 北京航空航天大学 一种燃气轮机涡轮叶片复合冷却结构
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JP2025117176A (ja) * 2024-01-30 2025-08-12 本田技研工業株式会社 壁部材及びその製造方法
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EP3155227A1 (fr) 2017-04-19
WO2016030289A1 (fr) 2016-03-03
US9915150B2 (en) 2018-03-13
CN106574507B (zh) 2018-05-11
JP2017530291A (ja) 2017-10-12
JP6328847B2 (ja) 2018-05-23
US20170268347A1 (en) 2017-09-21
EP2990605A1 (fr) 2016-03-02
CN106574507A (zh) 2017-04-19

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