EP3767074B1 - Component of a turbine - Google Patents
Component of a turbine Download PDFInfo
- Publication number
- EP3767074B1 EP3767074B1 EP20188996.1A EP20188996A EP3767074B1 EP 3767074 B1 EP3767074 B1 EP 3767074B1 EP 20188996 A EP20188996 A EP 20188996A EP 3767074 B1 EP3767074 B1 EP 3767074B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- component
- turbulator
- inner surfaces
- channel
- cooling channel
- 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
- 238000001816 cooling Methods 0.000 claims description 65
- 239000002826 coolant Substances 0.000 claims description 19
- 238000011144 upstream manufacturing Methods 0.000 claims description 11
- 238000000034 method Methods 0.000 description 6
- 239000000919 ceramic Substances 0.000 description 4
- 238000005266 casting Methods 0.000 description 3
- DETVQFQGSVEQBH-UHFFFAOYSA-N 1,1'-Ethylidenebistryptophan Chemical compound C1=C(CC(N)C(O)=O)C2=CC=CC=C2N1C(C)N1C2=CC=CC=C2C(CC(N)C(O)=O)=C1 DETVQFQGSVEQBH-UHFFFAOYSA-N 0.000 description 1
- WYTGDNHDOZPMIW-RCBQFDQVSA-N alstonine Natural products C1=CC2=C3C=CC=CC3=NC2=C2N1C[C@H]1[C@H](C)OC=C(C(=O)OC)[C@H]1C2 WYTGDNHDOZPMIW-RCBQFDQVSA-N 0.000 description 1
- 239000012141 concentrate Substances 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000012407 engineering method Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Images
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
-
- 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
- F05D2250/13—Two-dimensional trapezoidal
- F05D2250/131—Two-dimensional trapezoidal polygonal
-
- 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
- F05D2260/221—Improvement of heat transfer
- F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
-
- 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
- F05D2260/221—Improvement of heat transfer
- F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
- F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs
Definitions
- the present application relates to components of a turbine.
- the inner surface widths W1 and W3 are greater than the waist width W2, so the channel profile 46 has an hourglass shape formed by convexity of the side surfaces 52, 54. This shape increases the coolant flow 25 toward the corners C of the channel.
- the overall coolant flow direction is normal to the page in this view.
- the arrows 25 illustrate a flow-increasing aspect of the profile 46 relative to a channel without an hourglass shape and/or without fins next described.
- Fins 44 are provided on the inner surfaces 48, 50.
- the fins are aligned with the overall flow direction 22 ( FIG 1 ) which is normal to the plane of FIG 3 .
- the fins have heights that follow a convex profile such as 56A or 56B, providing a maximum fin height H at mid-width of the near-wall inner surface 48 and/or 50.
- These fins 44 increase the surface area of the near-wall surfaces 48, 50, and also increase the flow 25 in the corners C.
- the taller middle fins reduce the flow centrally, while the shorter distal fins encourage flow 25 in the corners C.
- the combination of convex sides 52, 54 and a convex fin height profile 56A, 56B provides synergy that focuses cooling toward the channel corners C.
- FIG. 9 shows an embodiment as in FIG 8 combined according to the invention with profiled fins 44 on the near-wall inner surfaces 48, 50 as previously described.
- the present hourglass-shaped channels are useful in any near-wall cooling 20 application, such as in vanes, blades, shrouds, and possibly in combustors and transition ducts of gas turbines. They increase uniformity of cooling, especially in a parallel series of channels with either parallel flows or alternating serpentine flows.
- the present channels may be formed by known fabrication techniques -- for example by casting an airfoil over a positive ceramic core that is chemically removed after casting.
Description
- The present application relates to components of a turbine.
- Components in the hot gas flow path of gas turbines often have cooling channels. Cooling effectiveness is important to minimize thermal stress on these components, and cooling efficiency is important to minimize the volume of air diverted from the compressor for cooling. Film cooling provides a film of cooling air on outer surfaces of a component via holes from internal cooling channels. Film cooling can be inefficient, because a high volume of cooling air is required. Thus, film cooling has been used selectively in combination with other techniques. Impingement cooling is a technique in which perforated baffles are spaced from a surface to create impingement jets of cooling air against the surface. Serpentine cooling channels have been provided in turbine components, including airfoils such as blades and vanes. The present invention increases effectiveness and efficiency in cooling channels.
-
US 2012/177503 A1 discloses a prior art component of a turbine according to the preamble of claim 1, comprising a cooling channel. -
EP 2 258 925 A2 -
EP 1 630 353 A2 discloses a prior art internally cooled gas turbine aerofoil. -
US 6 837 683 B2 discloses a prior art gas turbine engine aerofoil. - According to an aspect of the present invention, there is provided a component of a turbine as set forth in claim 1. Advantageous aspects of the invention are set forth in
dependent claims 2 to 15. - The invention is explained in the following description in view of the drawings that show:
-
FIG. 1 is a sectional side view of a turbine blade with cooling channels. -
FIG. 2 is a sectional view of an airfoil trailing edge taken on line 2-2 ofFIG 1 , with 30 cooling channels. -
FIG. 3 is a transverse profile of a cooling channel. -
FIG. 4 is a sectional view of one-sided near-wall cooling channels. -
FIG. 5 is a sectional view of cooling channels in a tapered component. -
FIG. 6 is a transverse sectional view of a turbine airfoil with hourglass shaped 35 cooling channels. -
FIG. 7 shows a process of molding ceramic cores for a mold for hourglass shaped cooling channels. -
FIG. 8 shows a transverse sectional view of an hourglass shaped cooling channel with converging side surfaces defined by peaked turbulators. -
FIG. 9 shows an embodiment as inFIG 8 combined according to the invention with fins on the near-wall inner surfaces. -
FIG. 10 is a view taken along line 10-10 ofFIG 8 as well as a view according to the invention taken along line 10-10 ofFIG 9 , showing peaked turbulators with convex upstream sides. -
FIG 1 is a sectional view of aturbine blade 20 having a leadingedge 21 and atrailing edge 23. Coolingair 22 from the turbine compressor enters aninlet 24 in theblade root 26, and flows throughchannels film cooling holes 32. A trailing edge portion TE of the blade may haveturbulator pins 34 andexit channels 36. Eacharrow 22 indicates an overall coolant flow direction at the arrow, meaning a predominant or average flow direction at that point. -
FIG 2 is a sectional view of a turbine airfoil trailing edge portion TE taken along line 2-2 ofFIG 1 . The trailing edge portion has first and secondexterior surfaces pressure side walls Cooling channels 36 may havefins 44 oninner surfaces exterior walls inner surfaces side surfaces inner surfaces -
FIG 3 is a transversesectional profile 46 of a cooling channel that is shaped to efficiently cool two opposed exterior surfaces. The channel may be atrailing edge channel 36 or any other cooling channel, such aschannels FIG 1 . It has two opposed near-wallinner surfaces exterior surfaces FIG 2 . Here "parallel" means with respect to the portions of the near-wall inner surface closest to the exterior surface, not considering thefins 44. The channel has widths W1, W3 at the near-wallinner surfaces interior side surfaces inner surfaces channel profile 46 has an hourglass shape formed by convexity of theside surfaces coolant flow 25 toward the corners C of the channel. The overall coolant flow direction is normal to the page in this view. Thearrows 25 illustrate a flow-increasing aspect of theprofile 46 relative to a channel without an hourglass shape and/or without fins next described. - Fins 44 are provided on the
inner surfaces FIG 1 ) which is normal to the plane ofFIG 3 . The fins have heights that follow a convex profile such as 56A or 56B, providing a maximum fin height H at mid-width of the near-wallinner surface 48 and/or 50. Thesefins 44 increase the surface area of the near-wall surfaces flow 25 in the corners C. The taller middle fins reduce the flow centrally, while the shorter distal fins encourageflow 25 in the corners C. The combination ofconvex sides fin height profile - Dimensions of the
channel profile 46 may be selected using known engineering methods. The illustrated proportions are provided as an example only. The following length units are dimensionless and may be sized proportionately in any unit of measurement, since proportion is the relevant aspect exemplified in this drawing. In one embodiment the relative dimensions are B = 1.00, D = 0.05, H = 0.20, W1 = 1.00, W2 = 0.60. The side taper angle A = -30° in this example. Herein, a negative taper angle A ofsides profile 46 means the sides converge toward each other toward an intermediate position between theinner surfaces inner surfaces -
FIG 4 shows acooling channel 36B shaped to cool asingle exterior surface channel 36 previously described. The near-wall inner surface width W1 is greater than the minimum channel width W2 due to tapered interior side surfaces 52, 54.Fins 44 are provided on the near-wallinner surface 48, and they may have a convex height profile centered on the width W1 of the near-wall inner surface.Such cooling channels 36B may be used for example in a relatively thicker part of a trailing edge portion TE of an airfoil rather than the relatively thinner part of the trailing edge portion TE where acooling profile 46 as inFIG 3 might be used. The transverse sectional profile of this embodiment may be trapezoidal, in which the near-wallinner surface 48 defines a longest side thereof. -
FIG 5 shows that the exterior surfaces 40 and 42 may be non-parallel in a transverse section plane of thechannel 36. The near-wallinner surfaces -
FIG 6 shows a transverse section of aturbine airfoil 60 with hourglass-shapedspan-wise cooling channels FIG 1 channels fins 44 as previously described regardingFIG 3 . -
FIG 7 shows a process of formingceramic cores airfoil 60. Flexible dies 84A, 84B, 85A, 85B or dies with flexible liners may be used to form thecores US patents 7,141,812 and7,410,606 and7,411,204 assigned to Mikro Systems Inc. of Charlottesville, Virginia . Even small negative taper angles such as -1 to -3 degrees are significant and useful for cooling efficiency compared to the positive taper angles required for removal of conventional rigid dies. -
FIG 8 shows a transverse sectional view of an hourglass shaped coolingchannel 65 with converging side surfaces 52, 54 defined byturbulators 92. Each turbulator has a peak 97 in a middle portion thereof that defines the waist of the cooling channel. The side surfaces 52, 54 on the turbulators may have the taper range previously described, or especially in the range of -2 to -5 degrees (-5 degrees shown). Theturbulators 92 may alternate withsurfaces - The embodiments as disclosed in the
figures 1-8 , when only considered individually, do not fall under the scope of the claimed invention. -
FIG. 9 shows an embodiment as inFIG 8 combined according to the invention with profiledfins 44 on the near-wallinner surfaces -
FIG. 10 is a view taken along line 10-10 ofFIG 8 as well as a view according to the invention taken along line 10-10 ofFIG 9 , showing peaked turbulators 92 with convexupstream sides 93 and straightdownstream sides 94. The convexupstream sides 93 urge theflow 22 toward the corners C. The straightdownstream sides 94 facilitate pulling the dies 84A, 84B, 85A, 85B ofFIG 7 straight out, normal to thecores downstream sides 94 of the turbulators may be convex (not shown) such as parallel to the upstream sides 93. - The embodiments of
FIGs 8-10 can be fabricated using the cost-effective process ofFIG 7 . Theturbulators 92 concentrate the coolant flow toward the near-wallinner surfaces FIG 9 according to the invention is especially effective and efficient, since theturbulators 92 slow theflow 22 centrally while concentrating it toward theinner surfaces ribs 44 transfer heat from the exterior surfaces 40, 42, and increase theflow 22 toward the corners C. - The present hourglass-shaped channels are useful in any near-
wall cooling 20 application, such as in vanes, blades, shrouds, and possibly in combustors and transition ducts of gas turbines. They increase uniformity of cooling, especially in a parallel series of channels with either parallel flows or alternating serpentine flows. The present channels may be formed by known fabrication techniques -- for example by casting an airfoil over a positive ceramic core that is chemically removed after casting. - A benefit of the invention is that the near-wall distal corners C of the channels remove more heat than prior cooling channels for a given coolant flow volume. This improves efficiency, effectiveness, and uniformity of cooling by overcoming the tendency of coolant to flow more slowly in the corners. Increasing the corner cooling helps compensate for the cooling gaps G between channels. The invention also provides increased heat transfer from the
primary surfaces fins 44. - While various embodiments of the present invention have been shown and described herein, it will be obvious that such embodiments are provided by way of example only.
Claims (15)
- A component of a turbine comprising a cooling channel (65), the cooling channel
(65) further comprising:a first inner surface (48) parallel to a first exterior surface (40) of the component and a tapered transverse sectional profile that is wider at the first inner surface (48) and narrower away from the first inner surface (48);a plurality of parallel fins (44) with a transverse height profile that is convex across a width of the inner surface (48), wherein the fins (44) are oriented with a direction of a coolant flow (22) in the channel (65), wherein the cooling channel (65) is effective to urge a coolant flow (22) therein toward corners (C) of the cooling channel (65),a second inner surface (50) parallel to a second exterior surface (42) of the component;first and second interior side surfaces (52, 54) spanning between the first and second inner surfaces (48, 50); and characterized by the cooling channel (65) further comprisinga turbulator (92) on a corresponding one of the side surfaces (52, 54) to urge the coolant flow (22) toward the inner surfaces (48, 50). - The component of claim 1, wherein the turbulator is provided as a plurality of turbulators (92) on each of the interior side surfaces (52, 54) of the channel (65) that urge the coolant flow (22) toward the inner surfaces (48, 50), wherein a peak (97) in a middle portion of each turbulator (92) defines a waist of the cooling channel (65) that is narrower than a width of either of the first and second inner surfaces (48, 50).
- The component of claim 2, wherein each turbulator (92) comprises a convex upstream side (93).
- The component of claim 2, wherein each turbulator comprises a convex upstream side (93) and a straight downstream side (94).
- The component of claim 1, wherein:the component is a turbine airfoil component;the cooling channel is a coolant exit channel (65) in a trailing edge portion of the turbine airfoil component;the first and second inner surfaces are first and second near-wall inner surfaces (48, 50);the first and second exterior surfaces (40, 42) are first and second exterior surfaces of the trailing edge portion;the first and second interior side surfaces (52, 54) between the near-wall inner surfaces (48, 50) converge to a waist at an intermediate position between the first and second near-wall inner surfaces (48, 50) forming an hourglass-shaped transverse profile of the channel (65); andthe plurality of fins (44) are aligned with an overall flow direction of the coolant exit channel (65), and the plurality of fins (44) has a convex height profile across the width of each near-wall inner surface (48, 50).
- The component of claim 5, wherein the turbulator is provided as a plurality of turbulators (92) on each of the side surfaces (52, 54) that urge the coolant flow (22) toward the near-wall inner surfaces (48, 50), wherein a peak (97) in a middle portion of each turbulator (92) defines the waist of the cooling channel (65).
- The component of claim 6, wherein each turbulator (92) comprises a convex upstream side (93).
- The component of claim 6, wherein each turbulator comprises a convex upstream side (93) and a straight downstream side (94).
- The component of claim 5, further comprising:
a plurality of turbulators (92) on each of the side surfaces (52, 54), each turbulator (92) comprising a convex upstream side (93), and a peak (97) in a middle portion of the turbulator (92) that defines the waist of the cooling channel (65). - The component of claim 1, wherein:the cooling channel is an interior cooling channel (65);the first and second inner surfaces are first and second inner surfaces (48, 50) of respective first and second exterior walls (41, 43) of the component;a transverse section of the channel (65) has an hourglass-shaped profile in which the interior side surfaces (52, 54) taper toward each other to a waist that is narrower than a width of each of the first and second inner surfaces (48, 50); andan overall direction of a coolant flow (22) in the channel (65) is normal to the hourglass-shaped profile.
- The component of claim 10, wherein:the first and second inner surfaces (48, 50) are parallel to respective first and second portions of exterior surfaces (40, 42) of the respective exterior walls (41, 43); and/orwherein the first and second exterior walls (41, 43) are respectively pressure and suction sides of a turbine airfoil.
- The component of claim 10 or 11, wherein:the waist comprises a width of 80% or less than the width of at least one of the inner surfaces (48, 50); and/orwherein the each of the side surfaces (48, 50) has a taper angle in the profile of at least -1 degrees toward the waist relative to a straight line between corresponding ends of the two side surfaces (52, 54).
- The component of any of claims 10 to 12, further comprising a plurality of parallel fins (44) with a transverse height profile that is convex across a width of at least one of the inner surfaces (48, 50), wherein the fins (44) are oriented with the coolant flow direction.
- The component of any of claims 10 to 13, wherein the turbulator is provided as a plurality of turbulators (92) on each of the side surfaces (52, 54) that urge the coolant toward the inner surfaces (48, 50), wherein a peak (97) in a middle portion of each turbulator (92) defines the waist of the cooling channel (65) optionally wherein each turbulator (92) comprises a convex upstream side (93), further optionally wherein each turbulator (92) comprises a straight downstream side (94).
- The component of any of claims 10 to 14, wherein a height profile that transversely connects adjacent peaks of the fins (44) is convex across a width of each of the inner surfaces (48, 50), wherein the turbulator is provided as a plurality of turbulators (92) on each of the side surfaces (52, 54), each turbulator (92) comprising a convex upstream side (93), and a peak (97) in a middle portion of the turbulator (92) that defines the waist of the cooling channel (65).
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/760,107 US9017027B2 (en) | 2011-01-06 | 2013-02-06 | Component having cooling channel with hourglass cross section |
EP14706400.0A EP2954169B1 (en) | 2013-02-06 | 2014-02-05 | Component of a turbine |
PCT/US2014/014858 WO2014123994A1 (en) | 2013-02-06 | 2014-02-05 | Component having cooling channel with hourglass cross section and corresponding turbine airfoil component |
Related Parent Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP14706400.0A Division EP2954169B1 (en) | 2013-02-06 | 2014-02-05 | Component of a turbine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3767074A1 EP3767074A1 (en) | 2021-01-20 |
EP3767074B1 true EP3767074B1 (en) | 2023-03-29 |
Family
ID=50159546
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP14706400.0A Active EP2954169B1 (en) | 2013-02-06 | 2014-02-05 | Component of a turbine |
EP20188996.1A Active EP3767074B1 (en) | 2013-02-06 | 2014-02-05 | Component of a turbine |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP14706400.0A Active EP2954169B1 (en) | 2013-02-06 | 2014-02-05 | Component of a turbine |
Country Status (5)
Country | Link |
---|---|
EP (2) | EP2954169B1 (en) |
JP (1) | JP6120995B2 (en) |
CN (1) | CN105829654B (en) |
RU (1) | RU2629790C2 (en) |
WO (1) | WO2014123994A1 (en) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9803939B2 (en) * | 2013-11-22 | 2017-10-31 | General Electric Company | Methods for the formation and shaping of cooling channels, and related articles of manufacture |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
SU444888A1 (en) * | 1973-01-03 | 1974-09-30 | Предприятие П/Я В-2504 | Coolable turbine blade |
US5695321A (en) * | 1991-12-17 | 1997-12-09 | General Electric Company | Turbine blade having variable configuration turbulators |
US5752801A (en) * | 1997-02-20 | 1998-05-19 | Westinghouse Electric Corporation | Apparatus for cooling a gas turbine airfoil and method of making same |
US7141812B2 (en) | 2002-06-05 | 2006-11-28 | Mikro Systems, Inc. | Devices, methods, and systems involving castings |
WO2002098624A1 (en) | 2001-06-05 | 2002-12-12 | Mikro Systems Inc. | Methods for manufacturing three-dimensional devices and devices created thereby |
GB0127902D0 (en) * | 2001-11-21 | 2002-01-16 | Rolls Royce Plc | Gas turbine engine aerofoil |
JP4191578B2 (en) * | 2003-11-21 | 2008-12-03 | 三菱重工業株式会社 | Turbine cooling blade of gas turbine engine |
US7080683B2 (en) * | 2004-06-14 | 2006-07-25 | Delphi Technologies, Inc. | Flat tube evaporator with enhanced refrigerant flow passages |
GB0418906D0 (en) * | 2004-08-25 | 2004-09-29 | Rolls Royce Plc | Internally cooled aerofoils |
GB0909255D0 (en) * | 2009-06-01 | 2009-07-15 | Rolls Royce Plc | Cooling arrangements |
US8764394B2 (en) * | 2011-01-06 | 2014-07-01 | Siemens Energy, Inc. | Component cooling channel |
-
2014
- 2014-02-05 CN CN201480007603.2A patent/CN105829654B/en active Active
- 2014-02-05 RU RU2015132763A patent/RU2629790C2/en active
- 2014-02-05 EP EP14706400.0A patent/EP2954169B1/en active Active
- 2014-02-05 EP EP20188996.1A patent/EP3767074B1/en active Active
- 2014-02-05 WO PCT/US2014/014858 patent/WO2014123994A1/en active Application Filing
- 2014-02-05 JP JP2015557025A patent/JP6120995B2/en active Active
Also Published As
Publication number | Publication date |
---|---|
CN105829654B (en) | 2018-05-11 |
WO2014123994A1 (en) | 2014-08-14 |
JP6120995B2 (en) | 2017-04-26 |
RU2015132763A (en) | 2017-03-15 |
EP2954169A1 (en) | 2015-12-16 |
JP2016510380A (en) | 2016-04-07 |
RU2629790C2 (en) | 2017-09-04 |
EP2954169B1 (en) | 2020-08-05 |
EP3767074A1 (en) | 2021-01-20 |
CN105829654A (en) | 2016-08-03 |
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