EP3206814B1 - Die cast system for forming a component usable in a gas turbine engine - Google Patents
Die cast system for forming a component usable in a gas turbine engine Download PDFInfo
- Publication number
- EP3206814B1 EP3206814B1 EP14796598.2A EP14796598A EP3206814B1 EP 3206814 B1 EP3206814 B1 EP 3206814B1 EP 14796598 A EP14796598 A EP 14796598A EP 3206814 B1 EP3206814 B1 EP 3206814B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- inner liner
- sub
- ceramic
- core
- die cast
- 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
Links
- 239000000919 ceramic Substances 0.000 claims description 69
- 238000001816 cooling Methods 0.000 claims description 38
- 239000000463 material Substances 0.000 claims description 24
- 238000000034 method Methods 0.000 claims description 19
- 238000005266 casting Methods 0.000 claims description 17
- 229910010293 ceramic material Inorganic materials 0.000 claims description 17
- 238000005524 ceramic coating Methods 0.000 claims description 12
- 238000011144 upstream manufacturing Methods 0.000 claims description 8
- 238000010304 firing Methods 0.000 claims description 7
- 238000010309 melting process Methods 0.000 claims description 6
- 239000002184 metal Substances 0.000 claims description 6
- 229910052751 metal Inorganic materials 0.000 claims description 6
- 239000011248 coating agent Substances 0.000 claims description 3
- 238000000576 coating method Methods 0.000 claims description 3
- 238000007493 shaping process Methods 0.000 claims 13
- 238000002844 melting Methods 0.000 claims 1
- 230000008018 melting Effects 0.000 claims 1
- 239000011162 core material Substances 0.000 description 56
- 239000002131 composite material Substances 0.000 description 7
- 238000002347 injection Methods 0.000 description 7
- 239000007924 injection Substances 0.000 description 7
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- 230000008859 change Effects 0.000 description 3
- -1 but not limited to Substances 0.000 description 2
- 229910052742 iron Inorganic materials 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/02—Sand moulds or like moulds for shaped castings
- B22C9/04—Use of lost patterns
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C7/00—Patterns; Manufacture thereof so far as not provided for in other classes
- B22C7/02—Lost patterns
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/10—Cores; Manufacture or installation of cores
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
- B22D17/00—Pressure die casting or injection die casting, i.e. casting in which the metal is forced into a mould under high pressure
- B22D17/20—Accessories: Details
Definitions
- This invention is directed generally to die cast systems, and more particularly to manufacturing methods for turbine airfoils usable in turbine engines.
- Turbine blade airfoils typically have internal cooling systems formed from a plurality of cooling channels, as shown in Figure 2 and 3 .
- a casting mold is often used and includes an internal ceramic core and external ceramic shell.
- the ceramic core as shown in Figure 1 , is manufactured to include detail features on the core die surface in order to form efficient cooling devices inside the blade casting.
- the core dies typically used to form cores are most often formed from hard steel, which are expensive to manufacture.
- the core die surfaces are typically in direct contact with the ceramic core material during the high pressure injection process. The core die will wear out after sufficient injections and lead to non-conforming casting. To maintain accurate casting dimensions, the core die needs to be reworked or replaced when a core die becomes worn, which is an expensive endeavor. Even a small improvement on an internal surface requires that a completely new die be made. Thus, a need exists for a more robust, less expensive system.
- a die cast system having an inner liner insert that enables the configuration of a component produced by the system to be easily changed by changing the inner liner insert without having to rework the die housing is disclosed. Because the inner liner insert only need be removed and replaced to change the configuration of an outer surface of a component produced by the system, the cost savings is significant in contrast with conventional systems in which the die would have to be reworked.
- the die cast system may also include an inner liner formed from first and second end sub-inner liners, whereby the first end sub-inner liner may be from a first material that is less compliant than a material forming the second end sub-inner liner enabling more intricate cooling systems to be created by the second end sub-inner liner that is formed from a more compliant material.
- the die cast system may include a die housing having one or more inner chambers forming an insert receiving chamber and one or more inner liners positioned within the insert receiving chamber of the inner chamber of the die housing.
- the inner liner may have an inner surface defining boundaries useful to form an inner surface of a turbine component, whereby the inner liner may be formed via a selective laser melting process.
- the inner liner may be formed from a first side sub-inner liner forming a first side of the turbine component and a second side sub-inner liner forming a second side of the turbine component.
- the first side sub-inner liner may form an outer wall of a suction side of an airfoil usable in a gas turbine engine and may include at least one cavity on an inner side of the outer wall that is configured to form at least a portion of an internal airfoil cooling system.
- the second side sub-inner liner may form an outer wall of a pressure side of an airfoil usable in a gas turbine engine and may include one or more cavities on an inner side of the outer wall that is configured to form at least a portion of an internal airfoil cooling system.
- the inner liner may be formed from a non-ceramic, flexible material.
- the inner liner may be formed from a different material than the die housing.
- the die housing may be formed from a first sub-die housing and a second sub-die housing having a mateable interface positioned therebetween such that the first and second sub-die housings are mateable at the mateable interface.
- the inner liner may be formed from a first end sub-inner liner forming a first end of the turbine component and a second end sub-inner liner forming a second end of the turbine component.
- the first end sub-inner liner may be formed from a first material that is less compliant than a material forming the second end sub-inner liner.
- the second end sub-inner liner being more compliant may be used to form intricate aspects to the internal cooling system.
- the first end sub-inner liner may be configured to form a leading edge of an airfoil usable in a turbine engine and second end sub-inner liner is configured to form a trailing edge of the airfoil usable in the turbine engine.
- the first end sub-inner liner may be formed from a first end, first side sub-inner liner and a first end, second side sub-inner liner.
- the first end, first side sub-inner liner may form a suction side outer wall of an upstream portion of a suction side of an airfoil usable in a gas turbine engine and may include one or more cavities on an inner side of the suction side outer wall that is configured to form at least a portion of an internal airfoil cooling system.
- the first end, second side sub-inner liner may form a pressure side outer wall of a pressure side of the upstream portion of an airfoil usable in a gas turbine engine and may include one or more cavities on an inner side of the pressure side outer wall that is configured to form at least a portion of an internal airfoil cooling system.
- the second end sub-inner liner may be formed from a second end, first side sub-inner liner and a second end, second side sub-inner liner.
- the second end, first side sub-inner liner may form a suction side outer wall of a downstream portion of a suction side of an airfoil usable in a gas turbine engine and may include one or more cavities on an inner side of the suction side outer wall that is configured to form at least a portion of an internal airfoil cooling system.
- the second end, second side sub-inner liner may form a pressure side outer wall of a pressure side of the downstream portion of an airfoil usable in a gas turbine engine and may include one or more cavities on an inner side of the pressure side outer wall that is configured to form at least a portion of an internal airfoil cooling system.
- a method of forming a turbine component may include injecting a ceramic material into at least one inner cavity formed within a composite die cast system, wherein the die cast system may be formed from a die housing having one or more inner chambers forming an insert receiving chamber and one or more inner liners positioned within the insert receiving chamber of the inner chamber of the die housing.
- the inner liner may have an inner surface defining boundaries useful to form an inner surface of a turbine component.
- the inner liner may be formed via a selective laser melting process.
- the method may also include removing the die cast system thereby revealing a ceramic core.
- the method may include firing the ceramic core, placing the ceramic core within an inner cavity formed by an inner surface of a wax die, and injecting wax into one or more openings formed between the ceramic core and the inner surface of the wax die.
- the method may also include removing the wax die to reveal a wax component, coating the wax component with a ceramic coating to form a ceramic shell with a ceramic core positioned therein and removing the wax component within the ceramic coating leaving one or more cavities within the ceramic coating.
- the method may also include filling the cavity within the ceramic coating with a molten metal and removing the ceramic shell and the ceramic core to form a cast component.
- An advantage of the composite die cast system is that because the inner liner insert only need be removed and replaced to change the configuration of an inner surface of a component produced by the system, a significant cost savings is captured in contrast with conventional systems in which the die would have to be reworked.
- hybrid die cast system Another advantage of the hybrid die cast system is that use of the hybrid die cast system will reduce time and effort required to create a core die in a conventional casting process.
- the inner liner may be formed from different portions formed from different materials, thereby enabling portions of the inner liner proximate to aspects of the core where intricate aspects of an internal cooling system are located, to be formed from more compliant material enabling those intricate aspects of the internal cooling system to be formed.
- a die cast system 10 having an inner liner insert 12 that enables the configuration of a component 14 produced by the system 10 to be easily changed by changing the inner liner insert 12 without having to rework the die housing 16 is disclosed. Because the inner liner insert 12 only need be removed and replaced to change the configuration of an inner surface 18 of a component 14 produced by the system 10, the cost savings is significant in contrast with conventional systems in which the die would have to be reworked.
- the die cast system 10 may also include an inner liner 12 formed from first and second end sub-inner liners 20, 22, whereby the first end sub-inner liner 20 may be from a first material that is less compliant than a material forming the second end sub-inner liner 22 enabling more intricate cooling systems to be created by the second end sub-inner liner 22, which is more compliant than the first end inner liner 20.
- the die cast system 10 may include a die housing 16 may have one or more inner chambers 23 forming an insert receiving chamber 24.
- the die cast system 10 may also include one or more inner liners 12 positioned within the insert receiving chamber 24 of the inner chamber 24 of the die housing 16.
- the inner liner 12 may have an inner surface 26 defining boundaries useful to form an inner surface 18 of a turbine component 14.
- the inner surface 26 of the inner liner 12 may be configured to form an airfoil 138 usable in a gas turbine engine.
- the airfoil 138 may be formed from a generally elongated, hollow airfoil 140 having a leading edge 142 on an opposite side from a trailing edge 144 and separated by a concave pressure side 146 and a convex suction side 148.
- the generally elongated, hollow airfoil 60 may have one or more film cooling holes 150 at one or more of the leading edge 142 forming a showerhead, concave pressure side 146, the convex suction side 148 or the trailing edge 144, or any combination thereof.
- the inner liner 12 may be formed via a selective laser melting process, with a material such as, but not limited to, iron.
- the inner liner 12 may be formed from a first side sub-inner liner 30 forming a first side 32 of the turbine component 14 and a second side sub-inner liner 34 forming a second side 36 of the turbine component 14.
- the first side sub-inner liner 30 may be formed from an outer wall 38 of a suction side 40 of an airfoil shaped core 42 and may include one or more cavities 44 on an inner side 46 of the outer wall 38 that is configured to form at least a portion of an internal airfoil cooling system 48.
- the second side sub-inner liner 34 may form an outer wall 50 of a pressure side 52 of the airfoil shaped core 42 and may include one or more cavities 44 on an inner side 56 of the outer wall 50 that is configured to form at least a portion of an internal airfoil cooling system 48.
- the first side sub-inner liner 30 and the second side sub-inner liner 34 may together form a plurality of inner cavities 44 forming the internal airfoil cooling system 48.
- the inner liner 12 may be formed from a non-ceramic material, such as, but not limited to, iron, or another appropriate material.
- the inner liner 12 may be formed from a different material than the die housing 16.
- the die housing 16 may be formed from a first sub-die housing 58 and a second sub-die housing 60 having a mateable interface 62 positioned therebetween such that the first and second sub-die housings 58, 60 are mateable at the mateable interface 62.
- the inner liner 12 may be formed from a first end sub-inner liner 20 forming a first end 64 of the turbine component 14 and a second end sub-inner liner 22 forming a second end 66 of the turbine component 14.
- the first end sub-inner liner 20 may be formed from a first material that is less compliant than a material forming the second end sub-inner liner 22. As such, that less compliant material may be used to form intricate aspects of the internal cooling system 48.
- the second end sub-inner liner 22 form from the less compliant material may be formed by processes employed by Mikro Systems of Charlottesville, VA.
- the first end sub-inner liner 20 may be configured to form a leading edge 70 of an airfoil shaped core 42 usable in a turbine engine
- second end sub-inner liner 22 may be configured to form a trailing edge 72 of the airfoil shaped core 42 usable in the turbine engine.
- the first end sub-inner liner 20 may be formed from a first end, first side sub-inner liner 74 and a first end, second side sub-inner liner 76.
- the first end, first side sub-inner liner 74 may form a suction side outer wall 38 of an upstream portion 78 of a suction side 40 of an airfoil shaped core 42.
- the first end, first side sub-inner liner 74 may include one or more cavities 44 on an inner side 46 of the suction side outer wall 38 that is configured to form at least a portion of an internal airfoil cooling system 48.
- the first end, second side sub-inner liner 76 may form a pressure side outer wall 50 of a pressure side 52 of the upstream portion 78 of an airfoil shaped core 42.
- the first end, second side sub-inner liner 76 may include one or more cavities 44 on an inner side 56 of the pressure side outer wall 50 that is configured to form at least a portion of the internal airfoil cooling system 48.
- the second end sub-inner liner 22 may be formed from a second end, first side sub-inner liner 80 and a second end, second side sub-inner liner 82.
- the second end, first side sub-inner liner 80 may form a suction side outer wall 38 of a downstream portion 84 of a suction side 40 of an airfoil shaped core 42 and may include one or more cavities 44 on an inner side 46 of the suction side outer wall 38 that is configured to form at least a portion of an internal airfoil cooling system 48.
- the second end, second side sub-inner liner 82 may form a pressure side outer wall 50 of a pressure side 52 of the downstream portion 84 of the airfoil shaped core 42 and may include one or more cavities 44 on an inner side 56 of the pressure side outer wall 50 that is configured to form at least a portion of the internal airfoil cooling system 48.
- a method 100 of forming a turbine component 14 may include forming a ceramic core die 90 at 101 and Figures 4 and 16 via a selective laser melting process.
- the die 90 may be positioned within a die housing 16 at 102 and Figures 5 and 17 .
- the method 100 may also include injecting a ceramic material 98 at 103 and Figures 6 and 18 into one or more inner cavities 44 formed within a die cast system 10 in which the die cast system 10 may be formed from a die housing 16 having one or more inner chambers 23 forming an insert receiving chamber 24.
- the die cast system 10 may also include one or more inner liners 12 positioned within the insert receiving chamber 24 of the inner chamber 23 of the die housing 16.
- the inner liner 12 may have an inner surface 26 defining boundaries useful to form an inner surface 18 of a turbine component 14.
- the inner liner 12 may be formed via a selective laser melting process.
- the method may include removing the die cast system 10 at 104 and Figures 7 and 19 thereby revealing a ceramic core 90.
- the method may also include firing the ceramic core 90 at 106 and Figures 8 and 20 and placing the ceramic core 90 at 108 within an inner cavity 92 formed by an inner surface 94 of a wax die 96.
- the method may also include injecting wax 88 at 110 and Figures 9 and 21 into at least opening 92 formed between the ceramic core 90 and the inner surface 94 of the wax die 96.
- the method may include removing the wax die 96 at 112 and Figures 10 and 22 to reveal a wax component 86 and coating the wax component 86 at 114 and Figures 11 and 23 with a ceramic coating 116 to form a ceramic shell 118 with a ceramic core 90 positioned therein.
- the method may include removing the wax component 86 at 120 and Figures 12 and 24 within the ceramic coating 116 leaving one or more cavities 122 within the ceramic coating 116.
- the method may include filling the cavity 122 at 124 and Figures 13 and 25 within the ceramic coating 116 with a molten metal and removing the ceramic shell 118 and the ceramic core 90 at 126 and Figures 14 and 26 to form a cast component 14.
- the step of injection a ceramic material at 102 may include injecting a ceramic material into at least one inner cavity 122 formed within the composite die cast system 10, wherein the inner liner 12 is formed from a first side sub-inner liner 30 forming a first side 32 of the turbine component 14 and a second side sub-inner liner 34 forming a second side 36 of the turbine component 14.
- the step of injection a ceramic material at 102 may include injecting a ceramic material into at least one inner cavity 122 formed within the composite die cast system 10, wherein the first side sub-inner liner 30 may form an outer wall 38 of a suction side 40 of an airfoil shaped core 42 and may include one or more cavities 44 on an inner side 46 of the outer wall 38 that is configured to form at least a portion of an internal airfoil cooling system 48.
- the second side sub-inner liner 34 may form an outer wall 50 of a pressure side 52 of an airfoil shaped core 42 and may include one or more cavities 44 on an inner side 56 of the outer wall 50 that is configured to form at least a portion of an internal airfoil cooling system 48.
- the step of injection a ceramic material at 102 may include injecting a ceramic material into at least one inner cavity 122 formed within the composite die cast system 10, wherein the inner liner 12 may be formed from a first end sub-inner liner 20 forming a first end 64 of the turbine component 14 and a second end sub-inner liner 22 forming a second end 66 of the turbine component 14, wherein the first end sub-inner liner 20 may be formed from a first material having a less compliant than a material forming the second end sub-inner liner 22.
- the step of injection a ceramic material at 102 may include injecting a ceramic material into at least one inner cavity 122 formed within the composite die cast system 10, wherein the first end sub-inner liner 20 may be formed from a first end, first side sub-inner liner 74 and a first end, second side sub-inner liner 76, and wherein the first end, first side sub-inner liner 74 may form a suction side outer wall 38 of an upstream portion 78 of a suction side 40 of an airfoil shaped core 42 and may include one or more cavities 44 on an inner side 46 of the suction side outer wall 38 that is configured to form at least a portion of an internal airfoil cooling system 48.
- the first end, second side sub-inner liner 76 may form a pressure side outer wall 50 of a pressure side 52 of the upstream portion 78 of an airfoil shaped core 42 and may include one or more cavities 44 on an inner side 56 of the pressure side outer wall 50 that is configured to form at least a portion of an internal airfoil cooling system 48.
- the step of injection a ceramic material at 102 may include injecting a ceramic material into at least one inner cavity 122 formed within the composite die cast system 10, wherein the second end sub-inner liner 22 may be formed from a second end, first side sub-inner liner 80 and a second end, second side sub-inner liner 82, and wherein the second end, first side sub-inner liner 80 may form a suction side outer wall 38 of a downstream portion 84 of a suction side 40 of an airfoil shaped core 42 and may include one or more cavities 44 on an inner side 46 of the suction side outer wall 38 that is configured to form at least a portion of an internal airfoil cooling system 48.
- the second end, second side sub-inner liner 82 may form a pressure side outer wall 50 of a pressure side 52 of the downstream portion 84 of an airfoil shaped core 42 and may include one or more cavities 44 on an inner side 56 of the pressure side outer wall 50 that is configured to form at least a portion of an internal airfoil cooling system 48.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Molds, Cores, And Manufacturing Methods Thereof (AREA)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PCT/US2014/060562 WO2016060653A1 (en) | 2014-10-15 | 2014-10-15 | Die cast system for forming a component usable in a gas turbine engine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3206814A1 EP3206814A1 (en) | 2017-08-23 |
EP3206814B1 true EP3206814B1 (en) | 2020-07-01 |
Family
ID=51894203
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP14796598.2A Active EP3206814B1 (en) | 2014-10-15 | 2014-10-15 | Die cast system for forming a component usable in a gas turbine engine |
Country Status (5)
Country | Link |
---|---|
US (1) | US20170297085A1 (ja) |
EP (1) | EP3206814B1 (ja) |
JP (1) | JP2017537250A (ja) |
CN (1) | CN107427905A (ja) |
WO (1) | WO2016060653A1 (ja) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2018080549A1 (en) | 2016-10-31 | 2018-05-03 | Hewlett-Packard Development Company, L.P. | Dynamic threshold based error diffusion |
Family Cites Families (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CA2511154C (en) * | 2004-07-06 | 2012-09-18 | General Electric Company | Synthetic model casting |
EP1772210A3 (en) * | 2005-09-30 | 2008-05-28 | General Electric Company | Methods for making ceramic casting cores and cores |
US7302989B1 (en) * | 2006-06-06 | 2007-12-04 | Siemens Power Generation, Inc. | Modular mold system with ceramic inserts |
US8413709B2 (en) * | 2006-12-06 | 2013-04-09 | General Electric Company | Composite core die, methods of manufacture thereof and articles manufactured therefrom |
EP1930096A1 (de) * | 2006-12-07 | 2008-06-11 | Siemens Aktiengesellschaft | Verfahren zum Herstellen eines Modells für die feingusstechnische Darstellung einer wenigstens einen Hohlraum aufweisenden Komponente |
US7487819B2 (en) * | 2006-12-11 | 2009-02-10 | General Electric Company | Disposable thin wall core die, methods of manufacture thereof and articles manufactured therefrom |
ES2427616T3 (es) * | 2008-06-12 | 2013-10-31 | Alstom Technology Ltd | Procedimiento para la fabricación técnica por fundición de una pala para una turbina de gas así como útil para la fabricación de un núcleo de fundición para la fabricación técnica por fundición de la pala |
JP5422304B2 (ja) * | 2009-08-26 | 2014-02-19 | 三菱重工業株式会社 | タービン翼用鋳型およびタービン翼の製造方法 |
US20110094698A1 (en) * | 2009-10-28 | 2011-04-28 | Howmet Corporation | Fugitive core tooling and method |
KR20130008511A (ko) * | 2010-12-07 | 2013-01-22 | 미크로 시스템즈, 인코포레이티드 | 가요성 왁스 패턴 공구를 이용하는 인베스트먼트 주조 |
US20120285652A1 (en) * | 2011-05-09 | 2012-11-15 | Fathi Ahmad | Liner for a Die Body |
US8899303B2 (en) * | 2011-05-10 | 2014-12-02 | Howmet Corporation | Ceramic core with composite insert for casting airfoils |
US8561668B2 (en) * | 2011-07-28 | 2013-10-22 | United Technologies Corporation | Rapid manufacturing method |
WO2015112885A1 (en) * | 2014-01-23 | 2015-07-30 | United Technologies Corporation | An additive manufactured mold, a method of manufacturing the mold, and a workpiece casted from the mold |
-
2014
- 2014-10-15 JP JP2017520365A patent/JP2017537250A/ja not_active Ceased
- 2014-10-15 CN CN201480082746.XA patent/CN107427905A/zh active Pending
- 2014-10-15 WO PCT/US2014/060562 patent/WO2016060653A1/en active Application Filing
- 2014-10-15 US US15/516,906 patent/US20170297085A1/en not_active Abandoned
- 2014-10-15 EP EP14796598.2A patent/EP3206814B1/en active Active
Non-Patent Citations (1)
Title |
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None * |
Also Published As
Publication number | Publication date |
---|---|
WO2016060653A1 (en) | 2016-04-21 |
JP2017537250A (ja) | 2017-12-14 |
US20170297085A1 (en) | 2017-10-19 |
CN107427905A (zh) | 2017-12-01 |
EP3206814A1 (en) | 2017-08-23 |
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