CN102966380A - Airfoil with array of cooling pins - Google Patents
Airfoil with array of cooling pins Download PDFInfo
- Publication number
- CN102966380A CN102966380A CN2012103158304A CN201210315830A CN102966380A CN 102966380 A CN102966380 A CN 102966380A CN 2012103158304 A CN2012103158304 A CN 2012103158304A CN 201210315830 A CN201210315830 A CN 201210315830A CN 102966380 A CN102966380 A CN 102966380A
- Authority
- CN
- China
- Prior art keywords
- airfoil
- pin
- array
- rib
- cooling holes
- 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.)
- Pending
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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
- F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
-
- 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
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade
-
- 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
- F05D2260/2212—Improvement of heat transfer by creating turbulence
-
- 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
Abstract
The present application provides an airfoil (100) with a cooling flow (130) therein. The airfoil (100) may include an internal cooling passage (110), a number of cooling holes (120) in communication with the internal cooling passage (110), and a number of pin-fms (150) positioned within the internal cooling passage (110). The pin-fms (150) are arranged with one or more turning openings (170) and one or more guiding openings (180) so as to direct the cooling flow (130) towards the cooling holes (120).
Description
Technical field
The application and the patent that obtains relate in general to gas turbine engine, and relate more specifically to for the water conservancy diversion needle-rib array (pin-fin array) in uses such as combustion gas turbine airfoils.
Background technique
Combustion gas turbine comprises a plurality of levels, and its bucket leaf stretches out from the supporting rotor dish.Each bucket leaf comprises airfoil, and combustion gas flow through airfoil.Must cool off to air-flow the high temperature that is produced to bear combustion gas.Inadequate cooling may cause the overstress on the airfoil, and may cause or cause fatigue and/or damage.Therefore, airfoil normally has the hollow piece of one or more internal cooling flow channels.Can provide from the cooling-air of compressor or other position to inner cooling flow channel and release.Can be by the heat transfer by convection between the inner metal surfaces that strengthens cool stream and airfoil with needle-rib array, turbulator etc.Produce in needle-rib array or the turbulator boundary layer around and upset, conduct heat in order to increase.
Airfoil has the single cool stream feeding section of leading to pin array and a plurality of outlets usually.Yet this structure causes usually with respect to the angled stream by the pin array of outlet.This angled stream may cause wherein, and heat transfer efficiency reduces.Can use current stabilizer (flow straighteners), but like this so that the space that the pin array region takies and complexity increase.
Therefore, need a kind of airfoil with improved internal cooling stream scheme, this improved internal cooling stream scheme has needle-rib array.This improved cool stream scheme can provide needle-rib array to be used for more effective heat transfer, better current control and lower manufacture cost.
Summary of the invention
The application and the patent that obtains provide a kind of airfoil that wherein has cool stream.This airfoil can comprise internal cooling path, a plurality of Cooling Holes that are communicated with the internal cooling path and be positioned at the interior a plurality of pin ribs of internal cooling path.The pin rib is arranged to have one or more opening and one or more guide opening of turning to, in order to towards Cooling Holes cool stream is guided.
Described a plurality of pin rib comprises non-homogeneous array.Described airfoil also comprises a plurality of internal cooling paths.Described a plurality of pin rib comprises the staggered location that strides across a pair of row; Perhaps comprise the staggered location that strides across a plurality of row.Described one or more opening that turns to is included in the first distance between first pair of pin rib in described a plurality of pin rib, described one or more guide opening is included in the second distance between second pair of pin rib in described a plurality of pin rib, and described the first distance is greater than described second distance.Described one or more opening that turns to makes described cool stream turn to about 90 (90) degree.Described a plurality of Cooling Holes comprises a plurality of trailing edge Cooling Holes.Described airfoil also comprises a plurality of a plurality of openings that turn to that list, and/or a plurality of a plurality of guide opening that list.
The application and the patent that obtains further provide a kind of airfoil that wherein has cool stream.This airfoil can comprise internal cooling path, a plurality of Cooling Holes that are communicated with the internal cooling path and be positioned at a plurality of pin ribs in the internal cooling path with non-homogeneous array.The pin rib is arranged to have one or more opening and the one or more guide opening of turning to that are in staggered location, in order to towards Cooling Holes cool stream is guided.
Described one or more opening that turns to is included in the first distance between first pair of pin rib in described a plurality of pin rib, described one or more guide opening is included in the second distance between second pair of pin rib in described a plurality of pin rib, and described the first distance is greater than described second distance.Described one or more opening that turns to makes described cool stream turn to about 90 (90) degree.Described a plurality of Cooling Holes comprises a plurality of trailing edge Cooling Holes.Described airfoil also comprises a plurality of a plurality of openings that turn to that list, and/or a plurality of a plurality of guide opening that list.
The application and the patent that obtains further provide a kind of internal cooling path that wherein has cool stream.This internal cooling path can comprise a plurality of Cooling Holes and be positioned at the interior a plurality of pin ribs of internal cooling path.The pin rib is arranged to comprise one or more opening and one or more guide opening of turning to, described one or more opening that turns to has the first distance between first pair of pin rib, described one or more guide opening has second distance between second pair of pin rib, and wherein first the distance greater than second distance.
Described a plurality of pin rib comprises non-homogeneous array.Described one or more opening that turns to makes described cool stream turn to about 90 (90) degree.Described internal cooling path also comprises a plurality of a plurality of openings that turn to that list.
By in conjunction with some accompanying drawings and claims reading detailed description hereinafter, the feature of these and other of the application and the patent that obtains and improving will become apparent for those of ordinary skills.
Description of drawings
Fig. 1 is the schematic representation of gas turbine engine.
Fig. 2 is the perspective view of turbo machine bucket leaf.
Fig. 3 is the side cross-sectional view of the turbo machine bucket leaf of Fig. 2.
Fig. 4 is the schematic representation of known needle-rib array.
Fig. 5 is the schematic representation of the example of needle-rib array as described in this specification.
Reference numerals list:
10 gas turbine engines, 36 airfoils
12 compressors, 38 roots
14 air streams, 40 points
16 burners, 42 pressure sidewalls
18 fuel flows, 44 suction sidewall
20 combustion gas flow 46 leading edges
22 turbo machines, 48 trailing edges
24 axles, 50 trailing edge Cooling Holes
26 loads, 52 leading edge Cooling Holes
28 turbo machine bucket leaves, 54 internal cooling paths
30 dovetail joints, 56 pin arrays
32 handles, 58 pin ribs
34 platforms, 60 uniform arrays
62 cool stream, 100 airfoils
170 turn to opening
110 internal cooling paths, 180 guide opening
120 Cooling Holes, 190 staggered location
130 cool stream, 200 first rows
140 pin arrays, 210 secondary series
150 pin ribs 220 the 3rd row
160 non-homogeneous array 230 the 4th row
Embodiment
Referring now to accompanying drawing, in the accompanying drawings, similar reference character refers to similar element in whole some accompanying drawings, and Fig. 1 shows the schematic representation such as the operable gas turbine engine 10 of this specification.Gas turbine engine 10 can comprise compressor 12.12 pairs of air streams that enter 14 of compressor compress.Compressor 12 will be delivered to burner 16 through the air stream 14 of overcompression.Burner 16 will mix with fuel flow 18 through overcompression and the some burning mixt through the air stream 14 of overcompression, to produce combustion gas stream 20.Although only show single burner 16, gas turbine engine 10 can comprise any amount of burner 16.Combustion gas stream 20 then is transported to turbo machine 22.20 pairs of turbo machines 22 of combustion gas stream drive, in order to produce mechanical work.The mechanical work that produces in the turbo machine 22 is by axle 24 drive compression machines 12 and drive external loading 26, such as generator etc.
Fig. 2 shows the example of the turbo machine bucket leaf 28 that can use with turbo machine mentioned above 22.Turbo machine bucket leaf 28 can preferably form the single type high-temperature alloy casting.Turbo machine bucket leaf 28 can comprise traditional dovetail joint 30, and traditional dovetail joint 30 is attached to traditional rotor disk.Blade handle 32 extends upward and ends at the platform 34 from dovetail joint 30, and handle 32 is outwards given prominence to and hold to platform 34 from handle 32.
Fig. 3 shows the side cross-sectional view of airfoil 36.As shown in the figure, airfoil 36 can comprise a plurality of internal coolings path 54.Airfoil 36 can be the cooling of air cooled, steam, open loop or closed-loop path.Leading edge Cooling Holes 52 can be communicated with the one or more internal coolings path 54 in the internal cooling path 54.Similarly, trailing edge Cooling Holes 50 can be communicated with the one or more internal coolings path 54 in the internal cooling path 54.One or more internal coolings path 54 in the internal cooling path 54 can also comprise pin array (pin array) 56.Pin array 56 can be the array of pin rib (pin-fin) 58.Pin rib 58 can have any desired size, shape or structure.In this example, pin array 56 is around trailing edge Cooling Holes 50 location.The present invention can use the heat transfer technology of other type.
Fig. 4 shows the example of pin array 56.In this example, pin rib 58 is arranged in the uniform array 60.As shown in the figure, pin rib 58 is arranged to have between each pin rib 58 substantially uniformly distance.Therefore, cool stream 62 can flow through at a certain angle with respect to trailing edge Cooling Holes 50 zone of dumping of pin array 56 or other type.As mentioned above, this angle overall heat transfer of can trading off.
Fig. 5 shows the as described in this specification part of airfoil 100.Airfoil 100 comprises a plurality of internal coolings path 110 and a plurality of Cooling Holes 120 that run through wherein.Cool stream 130 can flow through internal cooling path 110 and leave by Cooling Holes 120, in order to airfoil 100 is cooled off.Cooling Holes 120 can be along the internal cooling path 110 location so that cool stream 130 need to turn to by wherein.The present invention can use other structure and other parts.
Airfoil 100 also comprises the pin array 140 in the one or more internal coolings path 110 that is arranged in internal cooling path 110.Pin array 140 can comprise a plurality of pin ribs 150.Pin rib 150 can have any desired size, shape or structure.Can use any amount of pin rib 150.The present invention also can use the flow spoiler such as other type of turbulator etc.
In this example, pin rib 150 can be positioned in the non-homogeneous array 160.By using term " non-homogeneous " array 160, we are intended to represent that the distance between the independent pin rib 150 can change.Particularly, can use between the independent pin rib 150 and turn to opening 170 and guide opening 180.Compare guide opening 180, turn to opening 170 only to have larger open area between pin rib 150.Particularly, turn to opening 170 can be than guide opening 180 larger about ten Percent five (15%) to about 60 (60%) percent, yet the present invention can use other scope.Turn to the larger open area of opening 170 to tend to make cool stream 130 along the directional steering of expectation.Pin rib 150 can also have staggered location 190, variable downstream.Staggered location 190, variable downstream also helps as required cool stream 130 to be guided or lead.In illustrated example, pin array 140 can have a plurality of row: first row 200, secondary series 210, the 3rd row 220 and the 4th row 230.The present invention can use any amount of row.Therefore, staggered location 190 extends across described row.
Therefore, cool stream 130 changes turning in the opening 170 in the first row 200 over to, and continues to enter the turning in the opening 170 of secondary series 210, the 3rd row 220 and the 4th row 230.Cool stream 130 is mainly carried out about 90 (90) degree and is turned to and enter Cooling Holes 120 along internal cooling path 110.Pin array 140 shown in this specification only is used for the example purpose.The location of single pin rib 150 can change according to the geometrical shape of airfoil 100, internal cooling path 110, Cooling Holes 120, pin rib 150 etc.This location also may change owing to any amount of different operating and performance parameter.
Therefore, use to turn to opening 170 in order to cool stream 130 is turned to, can make pin array 140 more effectively for improvement of heat transfer and current control.Cool stream 130 will have perpendicular significant momentum component.Therefore, cool stream 130 is imported dumping in the zone of Cooling Holes 120 or other efficiently.Particularly, cool stream 130 alternately or is alternatively stagnated in that differing needles is capable, in order to this direction is provided.In addition, pin rib 150 is positioned in order to optimize local velocity.Improved heat transfer can make stream require to reduce, and strengthens the raising of overall efficiency.Pin array 140 also has larger pin spacing, in order to reduce manufacture cost and complexity, still provides effective heat exchange and current control simultaneously.
Should it is evident that this specification only relates to the application and some embodiment of the patent that obtains.Those of ordinary skills can carry out numerous changes and remodeling to the present invention in situation about not departing from such as the overall spirit of the present invention that limited by following claim and equivalents thereof and scope.
Claims (10)
1. an airfoil (100) has cool stream (130) in described airfoil (100), and described airfoil (100) comprising:
Internal cooling path (110);
A plurality of Cooling Holes (120), described a plurality of Cooling Holes (120) are communicated with described internal cooling path (110); And
A plurality of pin ribs (150), described a plurality of pin ribs (150) are positioned in the described internal cooling path (110);
Described a plurality of pin ribs (150) comprise and one or morely turn to opening (170) and one or more guide opening (180), in order to towards described a plurality of Cooling Holes (120) described cool stream (130) is guided.
2. airfoil according to claim 1 (100) is characterized in that, described a plurality of pin ribs (150) comprise non-homogeneous array (160).
3. airfoil according to claim 1 (100) is characterized in that, described airfoil (100) also comprises a plurality of internal cooling paths (110).
4. airfoil according to claim 1 (100) is characterized in that, described a plurality of pin ribs (150) comprise the staggered location (190) that strides across a pair of row (200,210).
5. airfoil according to claim 4 (100) is characterized in that, described a plurality of pin ribs (150) comprise the staggered location (190) that strides across a plurality of row (200,210,220,230).
6. airfoil according to claim 1 (100), it is characterized in that, described one or more opening (170) that turns to is included in the first distance between first pair of pin rib in described a plurality of pin ribs (150), described one or more guide opening (180) is included in the second distance between second pair of pin rib in described a plurality of pin ribs (150), and described the first distance is greater than described second distance.
7. airfoil according to claim 1 (100) is characterized in that, described one or more openings (180) that turn to make described cool stream (130) turn to about 90 (90) degree.
8. airfoil according to claim 1 (100) is characterized in that, described a plurality of Cooling Holes (120) comprise a plurality of trailing edges (48) Cooling Holes (120).
9. airfoil according to claim 1 (100) is characterized in that, described airfoil (100) also comprises a plurality of openings (170) that turn on a plurality of row (200,210,220,230).
10. airfoil according to claim 1 (100) is characterized in that, described airfoil (100) also comprises a plurality of guide opening (180) on a plurality of row (200,210,220,230).
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US13/221,009 | 2011-08-30 | ||
| US13/221,009 US20130052036A1 (en) | 2011-08-30 | 2011-08-30 | Pin-fin array |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102966380A true CN102966380A (en) | 2013-03-13 |
Family
ID=46679213
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012103158304A Pending CN102966380A (en) | 2011-08-30 | 2012-08-30 | Airfoil with array of cooling pins |
Country Status (3)
| Country | Link |
|---|---|
| US (1) | US20130052036A1 (en) |
| EP (1) | EP2565382A3 (en) |
| CN (1) | CN102966380A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105673089A (en) * | 2016-03-31 | 2016-06-15 | 中国船舶重工集团公司第七�三研究所 | Crown-free air film cooling rotor blade for turbine of gas turbine |
| CN106014488A (en) * | 2016-07-07 | 2016-10-12 | 周丽玲 | Gas turbine blade with longitudinal intersection rib cooling structure |
| CN106996314A (en) * | 2015-12-21 | 2017-08-01 | 通用电气公司 | Cooling circuit for many wall blades |
| CN113250758A (en) * | 2020-02-10 | 2021-08-13 | 通用电气波兰有限责任公司 | Turbine nozzle segment and turbine nozzle comprising such a turbine nozzle segment |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB201217125D0 (en) * | 2012-09-26 | 2012-11-07 | Rolls Royce Plc | Gas turbine engine component |
| US9732617B2 (en) | 2013-11-26 | 2017-08-15 | General Electric Company | Cooled airfoil trailing edge and method of cooling the airfoil trailing edge |
| US9784123B2 (en) * | 2014-01-10 | 2017-10-10 | Genearl Electric Company | Turbine components with bi-material adaptive cooling pathways |
| US10927680B2 (en) | 2017-05-31 | 2021-02-23 | General Electric Company | Adaptive cover for cooling pathway by additive manufacture |
| US10760430B2 (en) | 2017-05-31 | 2020-09-01 | General Electric Company | Adaptively opening backup cooling pathway |
| US10704399B2 (en) | 2017-05-31 | 2020-07-07 | General Electric Company | Adaptively opening cooling pathway |
| US11041389B2 (en) | 2017-05-31 | 2021-06-22 | General Electric Company | Adaptive cover for cooling pathway by additive manufacture |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5601399A (en) * | 1996-05-08 | 1997-02-11 | Alliedsignal Inc. | Internally cooled gas turbine vane |
| US20020021966A1 (en) * | 1999-10-05 | 2002-02-21 | Kvasnak William S. | Method and apparatus for cooling a wall within a gas turbine engine |
| CN1580519A (en) * | 2003-08-08 | 2005-02-16 | 联合工艺公司 | Microcircuit cooling for a turbine blade |
| US20050169752A1 (en) * | 2003-10-24 | 2005-08-04 | Ching-Pang Lee | Converging pin cooled airfoil |
| CN102089498A (en) * | 2008-07-10 | 2011-06-08 | 西门子公司 | Turbine vane for a gas turbine and casting core for the production of such |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3858290A (en) * | 1972-11-21 | 1975-01-07 | Avco Corp | Method of making inserts for cooled turbine blades |
| FR2476207A1 (en) * | 1980-02-19 | 1981-08-21 | Snecma | IMPROVEMENT TO AUBES OF COOLED TURBINES |
| US6254334B1 (en) * | 1999-10-05 | 2001-07-03 | United Technologies Corporation | Method and apparatus for cooling a wall within a gas turbine engine |
| US6257831B1 (en) * | 1999-10-22 | 2001-07-10 | Pratt & Whitney Canada Corp. | Cast airfoil structure with openings which do not require plugging |
| DE19963349A1 (en) * | 1999-12-27 | 2001-06-28 | Abb Alstom Power Ch Ag | Blade for gas turbines with throttle cross section at the rear edge |
| US7014424B2 (en) * | 2003-04-08 | 2006-03-21 | United Technologies Corporation | Turbine element |
| US7125225B2 (en) * | 2004-02-04 | 2006-10-24 | United Technologies Corporation | Cooled rotor blade with vibration damping device |
-
2011
- 2011-08-30 US US13/221,009 patent/US20130052036A1/en not_active Abandoned
-
2012
- 2012-08-16 EP EP20120180753 patent/EP2565382A3/en not_active Withdrawn
- 2012-08-30 CN CN2012103158304A patent/CN102966380A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5601399A (en) * | 1996-05-08 | 1997-02-11 | Alliedsignal Inc. | Internally cooled gas turbine vane |
| US20020021966A1 (en) * | 1999-10-05 | 2002-02-21 | Kvasnak William S. | Method and apparatus for cooling a wall within a gas turbine engine |
| CN1580519A (en) * | 2003-08-08 | 2005-02-16 | 联合工艺公司 | Microcircuit cooling for a turbine blade |
| US20050169752A1 (en) * | 2003-10-24 | 2005-08-04 | Ching-Pang Lee | Converging pin cooled airfoil |
| CN102089498A (en) * | 2008-07-10 | 2011-06-08 | 西门子公司 | Turbine vane for a gas turbine and casting core for the production of such |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106996314A (en) * | 2015-12-21 | 2017-08-01 | 通用电气公司 | Cooling circuit for many wall blades |
| CN106996314B (en) * | 2015-12-21 | 2021-05-11 | 通用电气公司 | Cooling circuit for multiwall vane |
| CN105673089A (en) * | 2016-03-31 | 2016-06-15 | 中国船舶重工集团公司第七�三研究所 | Crown-free air film cooling rotor blade for turbine of gas turbine |
| CN105673089B (en) * | 2016-03-31 | 2018-06-29 | 中国船舶重工集团公司第七�三研究所 | A kind of Gas Turbine is without hat gaseous film control rotor blade |
| CN106014488A (en) * | 2016-07-07 | 2016-10-12 | 周丽玲 | Gas turbine blade with longitudinal intersection rib cooling structure |
| CN113250758A (en) * | 2020-02-10 | 2021-08-13 | 通用电气波兰有限责任公司 | Turbine nozzle segment and turbine nozzle comprising such a turbine nozzle segment |
| CN113250758B (en) * | 2020-02-10 | 2024-03-01 | 通用电气波兰有限责任公司 | Turbine nozzle segment and turbine nozzle comprising such a turbine nozzle segment |
Also Published As
| Publication number | Publication date |
|---|---|
| US20130052036A1 (en) | 2013-02-28 |
| EP2565382A2 (en) | 2013-03-06 |
| EP2565382A3 (en) | 2015-04-22 |
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| PB01 | Publication | ||
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| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20130313 |