CN103195499A - Device and method for sealing a gas path in a turbine - Google Patents
Device and method for sealing a gas path in a turbine Download PDFInfo
- Publication number
- CN103195499A CN103195499A CN2013100017031A CN201310001703A CN103195499A CN 103195499 A CN103195499 A CN 103195499A CN 2013100017031 A CN2013100017031 A CN 2013100017031A CN 201310001703 A CN201310001703 A CN 201310001703A CN 103195499 A CN103195499 A CN 103195499A
- Authority
- CN
- China
- Prior art keywords
- conduit
- sheath section
- block piece
- gas path
- fluid
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A device for sealing a gas path in a turbine includes a first shroud segment and a slot in a surface of the first shroud segment. A barrier extends inside the slot, and a bypass channel in the slot provides fluid communication between the barrier and the slot to the gas path in the turbine. A method for sealing a gas path in a turbine includes placing a barrier between a first slot in a first shroud segment and a second slot in a second shroud segment and flowing a fluid between the barrier and the first slot to the gas path in the turbine, wherein the fluid flows through a first bypass channel in the first slot.
Description
Technical field
The disclosure is broadly directed to the apparatus and method for the gas path of sealing turbine.
Background technique
Turbine is widely used in multiple aviation, industry and the power generation applications with acting.Each turbine roughly comprises the stator stator blade (vane) of installation peripherally and the alternate level of rotation blade (blade).The stator stator blade can be attachable to fixed component, for example surrounds the shell of turbine, and rotation blade can be attachable to rotor, and it is along the longitudinal center line setting of turbine.Compression working fluid, for example steam, combustion gas or air flow through turbine to produce merit along gas path.The stator stator blade accelerates also the guiding compression working fluid to the rotation blade of one-level subsequently, giving rotation blade with motion, thus rotor and acting.
The compression working fluid that leaks or walk around around stator stator blade or rotation blade reduces the efficient of turbine.U. S. Patent the 4th, 902 has been described the equipment that is used for the diaphragm type cooling for No. 198, and it comprises the inside and outside sheath section (shroud segment) that circumferentially arranges along gas path.Strip Sealing in the conduit between the adjacent sheath section reduces from the amount of the compression working fluid of the effusion of the gas path between the adjacent sheath section.In addition, the interruption gap in the hole in the sheath section and the strip Sealing provides the fluid passage, and it is across the strip Sealing and enter in the gas path.So, but supplied with pressurised fluid is passed the hole, across the gap and enter in the gas path to prevent the leakage from gas path, and provides the diaphragm type cooling to the strip Sealing.Yet, gap in strip Sealing reduction strip Sealing, thus premature failure may be caused, maintenance increases and/or foreign matter is released in the gas path.Therefore, be useful for the seal arrangement of the gas path that seals turbine and the lasting improvement in the method.
Summary of the invention
Aspects and advantages of the present invention will be illustrated in aftermentioned is described, maybe can be apparent from description, maybe can learn by practice of the present invention.
One embodiment of the present of invention are a kind of devices for the gas path that seals turbine, and it comprises first sheath section and the conduit in the surface of first sheath section.Block piece extends in that conduit is inner, and the fluid that the bypass path in the conduit is provided between block piece and the conduit gas path in the turbine is communicated with.
An alternative embodiment of the invention is a kind of device of gas path for the sealing turbine, and it comprises first sheath section with first conduit and second sheath section adjacent with first sheath section, and wherein second sheath section has second conduit.Block piece extends to the second conduit inside from the first conduit inside, and block piece has the general planar surface, and it contacts towards gas path and with in first and second conduits each.The first fluid passage of the gas path in the turbine is between block piece and first conduit.
The present invention also can comprise a kind of method for the gas path that seals turbine.This method comprises: block piece is positioned between first conduit and second conduit in second sheath section in first sheath section, and make fluid flow to gas path in the turbine between block piece and first conduit, wherein fluid flows and passes the first bypass path in first conduit.
Those skilled in the art after reading this specification, will understand better this embodiment feature and aspect and other.
Description of drawings
Complete and the disclosure that can implement of the present invention comprises its preferred forms to those skilled in the art, more specifically illustrates in the remainder of this specification, and this specification comprises with reference to accompanying drawing, wherein:
Fig. 1 is the side cross-sectional view of demonstration turbine within the scope of the invention;
Fig. 2 is the axial, cross-sectional view according to an embodiment's the adjacent sheath section shown in Figure 1 that obtains along line A-A;
Fig. 3 is the axial, cross-sectional view of the adjacent sheath section shown in Figure 1 that obtains along line A-A according to an alternative embodiment;
Fig. 4 is the side cross-sectional view according to an embodiment's the sheath section shown in Figure 2 that obtains along line B-B;
Fig. 5 is the side cross-sectional view of the sheath section shown in Figure 2 that obtains along line B-B according to an alternative embodiment; And
Fig. 6 is the side cross-sectional view according to another embodiment's the sheath section shown in Figure 2 that obtains along line B-B.
List of parts
10 turbines
12 shells
14 stators
16 rotation blades
18 rotors
20 working fluids
22 sheath section
24 adjacently situated surfaces
26 conduits
28 block pieces
30 plat surface
32 sizes
34 fluid ports
36 fluid passages or bypass path
38 grooves
40 arcuate shape
42 block piece segmentations.
Embodiment
Will be in detail with reference to current embodiment of the present invention, one of them or more example are shown in the drawings.The feature in numeral and the alphabetical label indication accompanying drawing is used in detailed description.Similar or similar label in using accompanying drawing and describing is indicated similar or similar part of the present invention.As using in this article, term " first ", " second " and " the 3rd " can use to distinguish each other member interchangeably, and are not intended to position or significance into the expression individual components.
Provide each example to explain the present invention rather than to limit mode of the present invention.In fact, will be it is evident that to those skilled in the art, can change in the present invention and be out of shape, and do not depart from the scope of the present invention or spirit.For example, describe as the part among the embodiment or the feature described can be used for another embodiment and obtains further embodiment.Therefore, intention the present invention is encompassed in interior this change and the distortion of scope of claims and their equivalent.
Various embodiment of the present invention comprises the apparatus and method for the gas path of sealing turbine.In a particular embodiment, the block piece between the adjacent sheath section can prevent that compression working fluid from freely flowing and flow to outside the gas path between sheath section.Block piece can extend from the inside conduit of the adjacently situated surfaces that is formed at sheath section.One or more be included in block piece in the sheath section and the fluid port between the conduit and/or fluid passage or bypass path.Pressure fluid can supply by fluid port with between block piece and conduit, flow and the inflow gas path in, to prevent the leakage from gas path, also provide convection current and/or diaphragm type cooling to conduit and block piece simultaneously.Although example embodiment of the present invention will roughly be described under the situation of the gas path in turbine, those skilled in the art will easily understand, and embodiments of the invention can be applicable to comprise the arbitrary gas path of pressure fluid.
Fig. 1 provides the simplification sectional view of the part of turbine 10 according to an embodiment of the invention.As shown in Figure 1, turbine 10 can comprise fixing and rotating member, and it is surrounded by shell 12.Fixed component can comprise fixed nozzle or the stator stator blade 14 that for example attaches to shell 12.Rotating member can comprise the rotation blade 16 that for example attaches to rotor 18.Working fluid 20, for example steam, combustion gas or air as shown in Figure 1, are from left to right crossed turbine 10 along the hot gas path flow.The first order of stator stator blade 14 is accelerated and guiding working fluid 20 arrives the first order of rotation blade 16, thereby makes the first order and rotor 18 rotations of rotation blade 16.Working fluid 20 is followed the second level of flowing across stator stator blade 14, and this stator stator blade 14 accelerates also to reboot working fluid 20 to the next stage (not shown) of rotation blade, and this process is in each level repetition subsequently.
As shown in Figure 1, the inner radial of shell 12 can comprise a series of sheath section 22 that are connected in shell 12, its circumferentially around and limit the working fluid 20 of stator stator blade 14 or rotation blade 16 is walked around in the hot gas path with minimizing amount.As using in this article, term " guard shield " or " sheath section " can in fact comprise and comprise and be exposed to any static or mounting hardware temperature and pressure relevant with working fluid 20, in the hot gas path.For example, in specific embodiment shown in Figure 1, sheath section 22 is positioned at the radial outside of stator stator blade 14 and rotation blade 16, and sheath section 22 also can be positioned at the radially inner side of stator stator blade 14 and/or rotation blade 16 in other specific embodiment.
Fig. 2 and Fig. 3 provide the axial, cross-sectional view of the adjacent sheath section 22 shown in Figure 1 that obtains along line A-A according to various embodiments of the present invention.In each figure, sheath section 22 is positioned at the radial outside of stator stator blade 14, and gas path is below the sheath section 22 and between Fig. 2 and rotation blade shown in Figure 3.As shown in the figure, sheath section 22 has adjacently situated surfaces 24, and each adjacently situated surfaces 24 can have conduit (slot) 26, groove (indent) or groove (groove), and it extends in the surface 24 at least in part.As using in this article, term " conduit ", " groove " and " groove " are intended to interchangeable, and contain or comprise any path, slit (crevice), recess (notch) or the groove that limits in the surface 24 of sheath section 22.Block piece 28, Sealing, pin or other structure can be extended between conduit 26 inside and the conduit 26 in adjacently situated surfaces 24, so that sheath section 22 is kept in position flexibly, minimize also simultaneously or prevent that working fluid 20 from overflowing from the gas path between adjacent guard shield 22.Block piece 28 can be formed by other suitable material that pottery, alloyed steel maybe can continue to be exposed to the temperature and pressure relevant with gas path.
Shown in Fig. 2 and Fig. 3, block piece 28 can have general planar surface 30, and it contacts in the face of gas path and with each conduit 26.So, contact enhance fluid seal between the plat surface 30 of block piece 28 and the conduit 26, this fluid sealing reduces and/or prevents that working fluid 20 from overflowing or leak from gas path.In specific embodiment shown in Figure 3, block piece 28 has size (dimension) 32, and it is inner than big between sheath section 22 at conduit 26, to strengthen the sealing between block piece 28 and conduit 26.
One or more sheath section 22 can comprise the fluid port 34 that passes sheath section 22.Fluid port 34 can provide and pass sheath section 22 to the fluid connection of conduit 26.So, can provide pressure fluid, for example pressurized air, inert gas or steam pass sheath section 22 to conduit 26, cross the block piece 28 in conduit 26 and between sheath section 22 to flow, thereby convection current and/or diaphragm type cooling are provided.Alternatively or additionally, the fluid passage between block piece 28 and one or more conduit 26 or bypass path 36 can provide fluid to be communicated with, and flow through block piece 28 and enter in the gas path to allow pressure fluid.In Fig. 2 and Fig. 3, fluid passage or bypass path 36 generally are depicted as extension below block piece 28, with fluid stream (in Fig. 2 and Fig. 3 being in the paper) approximate vertical in the gas path.
Fig. 4-6 provides the side cross-sectional view of the sheath section shown in Figure 2 22 that obtains along line B-B, with explanation within the scope of the invention the fluid passage or the various embodiments of bypass path 36.In specific embodiment shown in Figure 4, fluid passage or bypass path 36 are included in a plurality of grooves that evenly separate 38 in the conduit 26.Groove 38 allows that pressure fluid flows, and removes heat with convection current ground from block piece 28 and/or sheath section 22 between the general planar of block piece 28 surface 30 and conduit 26.Because pressure fluid leaves the conduit 26 of sheath section 22 and enters gas path, so pressure fluid provides the diaphragm type cooling layer to block piece 28 and/or sheath section 22.In specific embodiment shown in Figure 5, fluid passage or bypass path 36 have arcuate shape 40 in conduit 26, to reduce the point of contact between block piece 28 and the conduit 26, thereby when pressure fluid between block piece 28 and conduit 26, flow and the inflow gas path in the time, strengthen convection current and diaphragm type cooling to block piece 28.Those skilled in the art will easily understand, and fluid passage or bypass path 36 can have different shape and size, and the present invention is not subject to fluid passage or the bypass path 36 of any given shape or size, unless statement especially in the claims.
Fig. 6 illustrates another embodiment, and wherein, block piece 28 comprises a plurality of segmentations 42, and almost parallel ground extends between its conduit 26 in adjacently situated surfaces 24.In addition, the groove 38 in fluid passage or the bypass path 36 has direction width and/or the degree of depth that reduce, in conduit 26 that flows at working fluid 20 in gas path.Darker wideer groove 38 allows extra pressure fluid to flow between block piece 28 and conduit 26, provide extra convection current cooling with the upstream portion to sheath section 22 and block piece 28, and when pressure fluid flows in the gas path, provide the diaphragm type cooling of enhancing across block piece 28 and sheath section 22.The certain width of groove 38 and the degree of depth can be according to the positions of the sheath section 22 in the gas path and are different.
Various embodiments shown in Fig. 1-6 also can be provided for sealing the method for the gas path in the turbine 10.This method can comprise block piece 28 is positioned between the conduit 26 in the adjacently situated surfaces 24 of adjacent sheath section 22, and make pressure fluid between block piece 28 and one or more conduit 26, flow to gas path in the turbine 10, be passed in one or more fluid passage or bypass path 36 in this one or more conduit 26 so that pressure fluid flows.In a particular embodiment, this method can comprise the groove that pressure fluid flowed pass in one or more conduit 26 38 and/or pressure fluid be flowed pass fluid port 34 in one or more sheath section 22.
This written explanation usage example comprises preferred forms, and makes any those skilled in the art can put into practice the present invention with open the present invention, comprises manufacturing and uses any device or system, and carry out the method for any merging.The scope of applying for a patent of the present invention is defined by the claims, and can comprise other example of being expected by those skilled in the art.If these other examples comprise not different with the literal language of claim structural elements, if perhaps these other examples comprise the equivalent structure element that does not have marked difference with the literal language of claim, then these other example intentions within the scope of the claims.
Claims (19)
1. device that is used for the gas path of sealing turbine comprises:
A. first sheath section;
B. the conduit in the surface of described first sheath section;
C. at the inner block piece that extends of described conduit; With
D. the fluid that the bypass path in described conduit, wherein said bypass path are provided between described block piece and the described conduit gas path in the described turbine is communicated with.
2. device as claimed in claim 1 is characterized in that, also comprises second sheath section, and it is adjacent with described first sheath section, and wherein said first and second sheath section have adjacently situated surfaces.
3. device as claimed in claim 1 is characterized in that, described block piece is included in a plurality of segmentations of extending between the described conduit.
4. device as claimed in claim 1 is characterized in that, the fluid stream in the gas path in described bypass path and the described turbine generally perpendicularly extends.
5. device as claimed in claim 1 is characterized in that, described bypass path is included in a plurality of grooves that evenly separate in the described conduit.
6. device as claimed in claim 1 is characterized in that, described bypass path has arcuate shape.
7. device as claimed in claim 1 is characterized in that, also comprises fluid port, and it passes the described conduit of described first sheath section in described first sheath section.
8. device that is used for the gas path of sealing turbine comprises:
A. first sheath section, wherein said first sheath section has first conduit;
B. second sheath section, it is adjacent with described first sheath section, and wherein said second sheath section has second conduit;
C. block piece, it extends to the described second conduit inside from the described first conduit inside, and wherein said block piece has the general planar surface, and it contacts towards described gas path and with in described first and second conduits each; With
D. first fluid passage, it is the gas path in the described turbine between described block piece and described first conduit.
9. device as claimed in claim 8 is characterized in that, described block piece has size, and it is inner than big between described first and second sheath section at described first and second conduits.
10. device as claimed in claim 8 is characterized in that, described block piece comprises a plurality of segmentations, and it extends to the described second conduit inside from the described first conduit inside.
11. device as claimed in claim 8 is characterized in that, described first fluid passage extends in the direction of described second sheath section.
12. device as claimed in claim 8 is characterized in that, described first fluid passage is included in a plurality of grooves that evenly separate in described first conduit.
13. device as claimed in claim 8 is characterized in that, described first fluid passage is included in a plurality of arcuate furrows in described first conduit.
14. device as claimed in claim 8 is characterized in that, also comprises fluid port, it passes described first conduit of described first sheath section in described first sheath section.
15. device as claimed in claim 8 is characterized in that, also comprises second fluid passage, it is the gas path in the described turbine between described block piece and described second conduit.
16. a method that is used for the gas path of sealing turbine comprises:
A. block piece is positioned between first conduit and second conduit in second sheath section in first sheath section; And
B. make fluid flow to gas path in the described turbine between described block piece and described first conduit, wherein said fluid flows and passes the first bypass path in described first conduit.
17. method as claimed in claim 16 is characterized in that, also comprises making the mobile a plurality of grooves that are passed in described first conduit of described fluid.
18. method as claimed in claim 16 is characterized in that, also comprises the fluid port that described fluid flowed pass in described first sheath section described first conduit in described first sheath section.
19. method as claimed in claim 16, it is characterized in that, comprise also making described fluid between described block piece and described second conduit, flow to gas path in the described turbine that wherein said fluid flows and passes the second bypass path in described second conduit.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US13/343,911 US20130177383A1 (en) | 2012-01-05 | 2012-01-05 | Device and method for sealing a gas path in a turbine |
| US13/343,911 | 2012-01-05 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103195499A true CN103195499A (en) | 2013-07-10 |
Family
ID=47678512
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2013100017031A Pending CN103195499A (en) | 2012-01-05 | 2013-01-05 | Device and method for sealing a gas path in a turbine |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US20130177383A1 (en) |
| EP (1) | EP2620597A1 (en) |
| JP (1) | JP2013139806A (en) |
| CN (1) | CN103195499A (en) |
| RU (1) | RU2012158308A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110857629A (en) * | 2018-08-24 | 2020-03-03 | 通用电气公司 | Spline seal with cooling features for turbine engines |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2015119687A2 (en) | 2013-11-11 | 2015-08-13 | United Technologies Corporation | Segmented seal for gas turbine engine |
| US9416675B2 (en) * | 2014-01-27 | 2016-08-16 | General Electric Company | Sealing device for providing a seal in a turbomachine |
| US10634055B2 (en) | 2015-02-05 | 2020-04-28 | United Technologies Corporation | Gas turbine engine having section with thermally isolated area |
| US9920652B2 (en) | 2015-02-09 | 2018-03-20 | United Technologies Corporation | Gas turbine engine having section with thermally isolated area |
| US10458264B2 (en) * | 2015-05-05 | 2019-10-29 | United Technologies Corporation | Seal arrangement for turbine engine component |
| CN111936725B (en) * | 2018-03-30 | 2022-08-16 | 西门子能源全球两合公司 | Sealing arrangement between turbine shroud segments |
| US20220290573A1 (en) * | 2021-03-09 | 2022-09-15 | Raytheon Technologies Corporation | Chevron grooved mateface seal |
| US11781440B2 (en) * | 2021-03-09 | 2023-10-10 | Rtx Corporation | Scalloped mateface seal arrangement for CMC platforms |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5167485A (en) * | 1990-01-08 | 1992-12-01 | General Electric Company | Self-cooling joint connection for abutting segments in a gas turbine engine |
| US5624227A (en) * | 1995-11-07 | 1997-04-29 | General Electric Co. | Seal for gas turbines |
| EP1162346A2 (en) * | 2000-06-08 | 2001-12-12 | General Electric Company | Cooling for turbine shroud segments |
| EP1286021A1 (en) * | 2001-08-21 | 2003-02-26 | ALSTOM (Switzerland) Ltd | Method of making a groove-like recess and relevant groove-like recess |
| JP2005016324A (en) * | 2003-06-23 | 2005-01-20 | Hitachi Ltd | Sealing device and gas turbine |
| CN100396884C (en) * | 2002-07-29 | 2008-06-25 | 通用电气公司 | Sideface gap sealing of filler sealing used for turbine partition board and improving method |
| CN102191954A (en) * | 2010-03-03 | 2011-09-21 | 通用电气公司 | Cooling gas turbine components with seal slot channels |
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| US4902198A (en) | 1988-08-31 | 1990-02-20 | Westinghouse Electric Corp. | Apparatus for film cooling of turbine van shrouds |
| GB2280935A (en) * | 1993-06-12 | 1995-02-15 | Rolls Royce Plc | Cooled sealing strip for nozzle guide vane segments |
| US5531457A (en) * | 1994-12-07 | 1996-07-02 | Pratt & Whitney Canada, Inc. | Gas turbine engine feather seal arrangement |
| FR2758856B1 (en) * | 1997-01-30 | 1999-02-26 | Snecma | SEALING WITH STACKED INSERTS SLIDING IN RECEPTION SLOTS |
| JP2002201913A (en) * | 2001-01-09 | 2002-07-19 | Mitsubishi Heavy Ind Ltd | Split wall of gas turbine and shroud |
| US6843479B2 (en) * | 2002-07-30 | 2005-01-18 | General Electric Company | Sealing of nozzle slashfaces in a steam turbine |
| US7217081B2 (en) * | 2004-10-15 | 2007-05-15 | Siemens Power Generation, Inc. | Cooling system for a seal for turbine vane shrouds |
| US7527472B2 (en) * | 2006-08-24 | 2009-05-05 | Siemens Energy, Inc. | Thermally sprayed conformal seal |
-
2012
- 2012-01-05 US US13/343,911 patent/US20130177383A1/en not_active Abandoned
- 2012-12-21 EP EP12199011.3A patent/EP2620597A1/en not_active Withdrawn
- 2012-12-26 JP JP2012281921A patent/JP2013139806A/en active Pending
- 2012-12-27 RU RU2012158308/06A patent/RU2012158308A/en not_active Application Discontinuation
-
2013
- 2013-01-05 CN CN2013100017031A patent/CN103195499A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5167485A (en) * | 1990-01-08 | 1992-12-01 | General Electric Company | Self-cooling joint connection for abutting segments in a gas turbine engine |
| US5624227A (en) * | 1995-11-07 | 1997-04-29 | General Electric Co. | Seal for gas turbines |
| EP1162346A2 (en) * | 2000-06-08 | 2001-12-12 | General Electric Company | Cooling for turbine shroud segments |
| EP1286021A1 (en) * | 2001-08-21 | 2003-02-26 | ALSTOM (Switzerland) Ltd | Method of making a groove-like recess and relevant groove-like recess |
| CN100396884C (en) * | 2002-07-29 | 2008-06-25 | 通用电气公司 | Sideface gap sealing of filler sealing used for turbine partition board and improving method |
| JP2005016324A (en) * | 2003-06-23 | 2005-01-20 | Hitachi Ltd | Sealing device and gas turbine |
| CN102191954A (en) * | 2010-03-03 | 2011-09-21 | 通用电气公司 | Cooling gas turbine components with seal slot channels |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110857629A (en) * | 2018-08-24 | 2020-03-03 | 通用电气公司 | Spline seal with cooling features for turbine engines |
Also Published As
| Publication number | Publication date |
|---|---|
| JP2013139806A (en) | 2013-07-18 |
| RU2012158308A (en) | 2014-07-10 |
| US20130177383A1 (en) | 2013-07-11 |
| EP2620597A1 (en) | 2013-07-31 |
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| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20130710 |