CN101313178B - A combustion apparatus - Google Patents
A combustion apparatus Download PDFInfo
- Publication number
- CN101313178B CN101313178B CN2006800436353A CN200680043635A CN101313178B CN 101313178 B CN101313178 B CN 101313178B CN 2006800436353 A CN2006800436353 A CN 2006800436353A CN 200680043635 A CN200680043635 A CN 200680043635A CN 101313178 B CN101313178 B CN 101313178B
- Authority
- CN
- China
- Prior art keywords
- cyclone
- gas
- cup
- bottom plate
- annular bottom
- 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.)
- Expired - Fee Related
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
- F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
Abstract
A combustion apparatus comprising: a device for mixing a fuel with an oxidant; a combustion chamber in which combustion of the fuel/oxidant mix takes place; a pre-chamber located between the device and the combustion chamber; and means for supplying a gas to the pre-chamber so as to form a film of gas on the interior surface of the pre-chamber so as to prevent a combustion flame from the combustion chamber attaching itself to this interior surface damaging the pre-chamber, the supply of gas to the pre-chamber being such that where the gas first reaches the interior surface of the pre-chamber it forms a substantially continuous film of gas over this interior surface.
Description
Technical field
The present invention relates to a kind of combustion apparatus.
More specifically, the present invention relates to a kind of combustion apparatus, this equipment comprises: the device that is used for fuel combination and oxidant; The combustion chamber of fuel/oxidant mixture burns takes place within it; Cup (pre-chamber) between device and combustion chamber; With the apparatus that is used for to the cup supply gas, make on the inner surface of cup, to form gas film, thereby the combustion flame oneself that prevents the combustion chamber is attached to this inner surface and damages cup.
Background technology
Known by in the wall of cup, forming the hole, and via these holes to the cup supply gas, thereby on the inner surface of cup, obtain gas film.This shortcoming that has is, the place of the preceding chamber internal surface that at first arrives at gas, and gas is the form of a large amount of discontinuous air-flows, goes out one air-flow from each orifice flow.Thereby, for the zone of the inner surface between the discontinuous air-flow, there is not the protection that prevents the flame attach inner surface.
Summary of the invention
According to the present invention, a kind of combustion apparatus is provided, this equipment comprises: the device that is used for fuel combination and oxidant; The combustion chamber of fuel/oxidant mixture burns takes place within it; Cup between device and combustion chamber; With the apparatus that is used for to the cup supply gas, make and on the inner surface of cup, form gas film, thereby the combustion flame oneself that prevents the combustion chamber is attached to this inner surface and damages cup, make to the gas supply of cup: the place of the preceding chamber internal surface that at first arrives at gas, gas forms the roughly continuous gas film that covers this inner surface.
In the equipment according to aforementioned paragraphs, the apparatus that preferably is used for supply gas comprises the cyclone of the eddy flow (swirling flow) that is used to produce gas, and the inner surface that this gas cyclone flows through cup enters the combustion chamber.
In the equipment according to aforementioned paragraphs, preferably cyclone comprises a plurality of grooves that are used to guide gas, and this groove is arranged to a circle and is extended radially inwardly roughly.
In equipment according to aforementioned paragraphs, preferably cyclone comprises annular bottom plate and a plurality of wedge shape part that circumferentially is provided with at interval around annular bottom plate, between adjacent wedge shape part, to be formed for guiding the groove of gas, the wedge shape part is provided with backward from the radially inward edge of annular bottom plate, thus limit on the annular bottom plate directly from the radially outer annular protrusion of radially inward edge.
Preferably the equipment according to aforementioned paragraphs also comprises the ring seal plate that is fixed to cyclone, make a side of ring seal plate form the wall of groove, the wedge shape part is provided with backward from the radially inward edge of ring seal plate, thus limit on the ring seal plate directly from the radially outer annular protrusion of the radially inward edge of ring seal plate.
In according to aforementioned two paragraphs in the equipment of arbitrary paragraph, preferably cyclone is between device and cup, and cyclone joins by level and smooth shoulder and cup, and this shoulder forms between the inner surface of annular protrusion on the annular bottom plate of cyclone and cup.
In the equipment of the arbitrary paragraph in according to aforementioned three paragraphs except that the 3rd paragraph, the apparatus that preferably is used for supply gas is between device and cup.
In according to aforementioned seven paragraphs in the equipment of arbitrary paragraph, device comprises the cyclone of the vortex mixed thing that is used to produce fuel and oxidant, and this mixture enters the combustion chamber along cup.
In the equipment of arbitrary paragraph, oxidant can be that air and gas can be air in according to aforementioned eight paragraphs.
The present invention also extends to a kind of gas-turbine engine, this gas-turbine engine comprises the equipment according to arbitrary paragraph in aforementioned nine paragraphs, wherein from the Compressed Gas of engine compressor at device be used for distributing between the apparatus of supply gas, majority of gas is fed to device.
Description of drawings
Now will be by example in conjunction with present invention is described with reference to the accompanying drawings, wherein:
Fig. 1 is the decomposition diagram according to combustion apparatus of the present invention;
Fig. 2 is the decomposition diagram of the combustion apparatus among Fig. 1, has taked the perspective view different with Fig. 1, and has omitted most of combustion chamber of equipment;
Fig. 3 is the decomposition side view of the equipment among Fig. 1, has wherein omitted the combustion chamber;
Fig. 4 is the view along the IV-IV line among Fig. 3;
Fig. 5 is the view along the V-V line among Fig. 3;
Fig. 6 is the sectional view along the VI-VI line among Fig. 3;
Fig. 7 is the side view of the equipment among Fig. 1, and this equipment is equipped with the combustion chamber, abridged;
Fig. 8 is the sectional view along the VIII-VIII line among Fig. 7;
Fig. 9 is the sectional view along the IX-IX line among Fig. 7; And
Figure 10 is the schematic sectional view along the length of the equipment among Fig. 1.
The specific embodiment
With reference to the accompanying drawings, equipment comprises first cyclone 1 of the vortex mixed thing that is used to produce fuel and air, the combustion chamber 3 of fuel/air mixture combusts, second cyclone 5 that is used to produce air swirl, the ring seal plate 7 that separates cyclone 1 and 5 and the cup 9 between second cyclone 5 and combustion chamber 3 takes place within it.
First cyclone 1 comprises annular bottom plate 11 and a plurality of wedge shape part 13, and this wedge shape part is provided with around annular bottom plate 11 circumferential compartment of terrains, to form groove 15 between adjacent wedge shape part 13.Plate 11 has inlet 17 in the radial outer end portion of each groove 15, enters the mouth to first cyclone, 1 fuel supplying by this.Each wedge shape part 13 has hole 21 in the radial outer end portion of one side 19, by this hole also to first cyclone, 1 fuel supplying.A plurality of installing holes 23 pass wedge shape part 13 and base plate 11 extends.The radial inner end 25 that wedge shape part 13 approaches is provided with backward from the radially inward edge 27 of annular bottom plate 11, thereby limits the directly 27 radially outer annular protrusions 29 from the edge.
Second cyclone, 5 form classes are similar to first cyclone 1, and comprise annular bottom plate 31 and a plurality of wedge shape part 33, and this wedge shape part is provided with around annular bottom plate 31 circumferential compartment of terrains, to form groove 35 between adjacent wedge shape part 33.Wedge shape part 13 on the base plate 11 in the height of the wedge shape part 33 on the base plate 31 and first cyclone 1 highly compare reduced many.A plurality of installing holes 37 pass wedge shape part 33 and base plate 31 extends.The thin radial inner end 39 of wedge shape part 33 is provided with backward from the radially inward edge 41 of annular bottom plate 31, thereby limits the directly 41 radially outer annular protrusions 43 from the edge.
First cyclone 1, ring seal plate 7 and second cyclone 5 (with integrally formed cup 9) utilize installing hole 23 in the cyclone 1, installing hole 45 in the plate 7 and the installing hole 37 in the cyclone 5 to be fixed together by the nuts and bolt fixture.Thereby a side of plate 7 forms the wall of each groove 15 of first cyclone 1, and the opposite side of plate 7 forms the wall of each groove 35 of second cyclone 5.The wedge shape part 13 of first cyclone 1 can be as seen from Figure 8 with the relation of ring seal plate 7.The thin radial inner end 25 of wedge shape part 13 just in time extends to the radially inward edge 51 of ring seal plate 7.The wedge shape part 33 of second cyclone 5 can be as seen from Figure 9 with the relation of ring seal plate 7.The thin radial inner end 39 of wedge shape part 33 is provided with backward from the radially inward edge 51 of ring seal plate 7, thereby limits the directly 51 radially outer annular protrusions 53 from the edge.
The operation of combustion apparatus will be described now.
Air is supplied to the radial outer end portion of the groove 15 of first cyclone 1, and radially moves inward substantially along groove 15.Fuel is supplied to the inlet 17 and the hole 21 of first cyclone 1, thereby enters groove 15 and mix with the air that moves along groove 15.Thereby first cyclone 1 has produced the vortex mixed thing of fuel and air in annular region, and this annular region is directly radially inside from the radial inner end of groove 15, referring to the arrow among Fig. 8 55.This vortex mixed thing axially moves along equipment, passes ring seal plate 7, second cyclone 5 and cup 9, arrives combustion chamber 3, referring to the arrow among Figure 10 57.
Lighting by the firing device (not shown) of fuel/air mixture realizes that this firing device is positioned at the circular open of the annular bottom plate 11 of first cyclone 1.In the case, combustion apparatus comprises the miscellaneous part (not shown) of the equipment left part that places as shown in Figure 1, and these parts have the face of the circular open that occupies annular bottom plate 11.Firing device places in this face.After being lighted by firing device, burning is (self-sustaining) that controls oneself.
Air also is supplied to the radial outer end portion of the groove 35 of second cyclone 5, and radially moves inward substantially along groove 35.Thereby second cyclone 5 has produced air swirl in annular region, and this annular region is directly radially inside from the radial inner end of groove 35, referring to the arrow among Fig. 4 59.This eddy flow turns round and round between the annular protrusion 43 of the annular protrusion 53 of ring seal plate 7 and second cyclone 5, through 90 ° of shoulders 49 between the inner surface 47 of annular protrusion 43 and cup 9, and axially move to combustion chamber 3 along cup 9, referring to the arrow among Figure 10 61.
Providing the purpose of air stream by second cyclone 5 is to provide air film on the inner surface 47 of cup 9, thereby prevents to be attached to inner surface 47 and to damage cup 9 from the combustion flame oneself of combustion chamber 3.Make by second cyclone 5 supply air, the place of the inner surface 47 that at first arrives at air, just along the position of 90 ° of shoulders 49, air forms the continuous air film that covers inner surface 47.This continuation property is that this annular protrusion 43 is provided with wedge shape part 33 backward by the edge 41 from second cyclone 5 and forms owing to (i) existence of annular protrusion 43; The (ii) existence of annular protrusion 53, this annular protrusion 53 is provided with wedge shape part 33 backward by the edge 51 from ring seal plate 7 and forms; And the (iii) existence of 90 ° of shoulders 49 between second cyclone 5 and the cup 9.
Design idea is to make the speed from the air stream of second cyclone 5, referring to the arrow among Figure 10 61, approaches the speed from the fuel/air mixture of first cyclone 1 as much as possible, referring to the arrow among Figure 10 57.In this way, because the disturbance minimum of the air stream 61 that mixing logistics 57 causes, thereby the corruption of protection air film 61 is minimized.
In the said equipment, the air conservation film is arranged on the inner surface of cup 9.Should recognize that this diaphragm needs not to be air, can also be other gas, for example carbon dioxide.Similarly, diaphragm can be fuel gas and AIR MIXTURES, if do not light in the zone of cup 9 inner surfaces under the condition of used specific mixture (concentration of airborne fuel) in being present in cup 9.Thereby, can use lean mixture (lean mix), wherein the concentration of fuel maybe can be used rich mixture (rich mix) under the concentration value that can light, and wherein the concentration of fuel is on the concentration value that can light.In fact, under the situation of rich mixture, the concentration of fuel can be 100%, does not just have air to exist.
In the said equipment, cyclone is used to provide and is used for burnt fuel and AIR MIXTURES.Should recognize that fuel/air mixture can be provided by the device that substitutes, this device can provide enough fuel and air mixture uniformly.
In the said equipment, cyclone is used to supply the diaphragm on the inner surface that air forms cup 9.Should recognize that replacement appliances can be used for this purpose, if the air supply makes the place of the inner surface that at first arrives at air, air forms the roughly continuous air film that covers this surface.
In the said equipment, second cyclone 5 is located immediately at before the cup 9.Should recognize that cyclone 5 can be positioned to partly the length along cup 9, making only provides the air conservation film about cup 9 remainders between cyclone 5 and the combustion chamber 3.In addition, this equipment can comprise that 5, one of two second cyclones are located immediately at before the cup 9, and another is positioned to partly the length along cup 9.Partly the cyclone 5 of locating along the length of cup 9 protects air so that the protection air that is provided by the cyclone 5 before being located immediately at cup 9 to be provided in providing.Should replenish the cup 9 of air with auxiliary protection cyclone 5 downstreams, this cyclone 5 is positioned to partly the length along cup.
The present invention can obtain application-specific in gas-turbine engine.Under the situation of the said equipment, to distribute between first cyclone 1 and second cyclone 5 from the Compressed Gas of the compressor of engine, majority of gas is fed to first cyclone 1.
The present invention is particularly useful in the fuel combustion of high-speed flame.When using such fuel, for combustion flame, tend to back flash (flashback) to a greater degree and return cup, and oneself be attached to the inner surface of cup from the combustion chamber.
Claims (5)
1. combustion apparatus, it comprises:
The device that is used for fuel combination and oxidant;
The combustion chamber of described fuel and oxidant mixture burning takes place within it;
Cup between described device and described combustion chamber; With
Be used for apparatus, make on the inner surface of described cup, to form gas film, thereby the combustion flame oneself that prevents described combustion chamber is attached to this inner surface and damages described cup to described cup supply gas,
Make to the gas supply of described cup: described gas at first arrive described before the place of chamber internal surface, this gas forms the roughly continuous gas film of this inner surface of covering,
Described device comprises first cyclone of the vortex mixed thing that is used to produce fuel and oxidant, and described mixture enters into described combustion chamber along described cup;
Described first cyclone comprises first annular bottom plate and a plurality of first wedge shape part that circumferentially is provided with at interval around described first annular bottom plate;
The described apparatus that is used for supply gas comprises second cyclone of the eddy flow that is used to produce described gas, and the inner surface that this gas cyclone flows through described cup enters described combustion chamber,
Described second cyclone comprises a plurality of grooves that are used to guide described gas,
Described groove is arranged to a circle and is extended radially inwardly roughly,
Described second cyclone comprises second annular bottom plate and a plurality of second wedge shape part that circumferentially at interval is provided with around described second annular bottom plate, between the adjacent second wedge shape part, being formed for guiding the described groove of described gas,
The described second wedge shape part is provided with backward from the radially inward edge of described second annular bottom plate, thus limit on described second annular bottom plate directly from the radially outer annular protrusion of described radially inward edge;
Described equipment also comprises the ring seal plate that is fixed to described second cyclone, make a side of described ring seal plate form the wall of described groove, the described second wedge shape part is provided with backward from the radially inward edge of described ring seal plate, thus limit on described ring seal plate directly from the radially outer annular protrusion of the radially inward edge of described ring seal plate;
First wedge height on first annular bottom plate in the height of the second wedge shape part on second annular bottom plate of described second cyclone and described first cyclone compare reduced many.
2. equipment as claimed in claim 1, wherein said second cyclone is between described device and described cup, and described second cyclone joins by level and smooth shoulder and described cup, and described shoulder forms between the inner surface of annular protrusion on second annular bottom plate of described second cyclone and described cup.
3. equipment as claimed in claim 1, wherein said second cyclone is between described device and described cup.
4. as each described equipment among the claim 1-3, wherein said oxidant is that air and described gas are air.
5. gas-turbine engine, described gas-turbine engine comprises as described above each described equipment in the claim, wherein the Compressed Gas from engine compressor distributes between described device and described second cyclone, and most of described gases are fed to described device.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB0524097.3 | 2005-11-26 | ||
| GB0524097A GB2432655A (en) | 2005-11-26 | 2005-11-26 | Combustion apparatus |
| PCT/EP2006/068870 WO2007060216A1 (en) | 2005-11-26 | 2006-11-24 | A combustion apparatus |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101313178A CN101313178A (en) | 2008-11-26 |
| CN101313178B true CN101313178B (en) | 2011-08-31 |
Family
ID=35601270
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2006800436353A Expired - Fee Related CN101313178B (en) | 2005-11-26 | 2006-11-24 | A combustion apparatus |
Country Status (7)
| Country | Link |
|---|---|
| US (1) | US20090142716A1 (en) |
| EP (1) | EP1952066B1 (en) |
| JP (1) | JP4785932B2 (en) |
| CN (1) | CN101313178B (en) |
| GB (1) | GB2432655A (en) |
| RU (1) | RU2419031C2 (en) |
| WO (1) | WO2007060216A1 (en) |
Families Citing this family (24)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1867925A1 (en) * | 2006-06-12 | 2007-12-19 | Siemens Aktiengesellschaft | Burner |
| JP5172468B2 (en) * | 2008-05-23 | 2013-03-27 | 川崎重工業株式会社 | Combustion device and control method of combustion device |
| EP2169312A1 (en) | 2008-09-25 | 2010-03-31 | Siemens Aktiengesellschaft | Stepped swirler for dynamic control |
| EP2192347B1 (en) | 2008-11-26 | 2014-01-01 | Siemens Aktiengesellschaft | Tubular swirling chamber |
| FR2945854B1 (en) | 2009-05-19 | 2015-08-07 | Snecma | MIXTURE SPINDLE FOR A FUEL INJECTOR IN A COMBUSTION CHAMBER OF A GAS TURBINE AND CORRESPONDING COMBUSTION DEVICE |
| EP2327933A1 (en) * | 2009-11-30 | 2011-06-01 | Siemens Aktiengesellschaft | Burner assembly |
| JP5156066B2 (en) * | 2010-08-27 | 2013-03-06 | 株式会社日立製作所 | Gas turbine combustor |
| CN102310199B (en) * | 2011-10-10 | 2013-08-07 | 西南大学 | Method for preparing WC-Co nano composite powder by in situ reduction and carbonization |
| US9322549B2 (en) * | 2011-12-20 | 2016-04-26 | Exxonmobil Chemical Patents Inc. | Mixer/flow distributors |
| JP5584260B2 (en) * | 2012-08-08 | 2014-09-03 | 日野自動車株式会社 | Exhaust purification device burner |
| US9447974B2 (en) | 2012-09-13 | 2016-09-20 | United Technologies Corporation | Light weight swirler for gas turbine engine combustor and a method for lightening a swirler for a gas turbine engine |
| US9534790B2 (en) * | 2013-01-07 | 2017-01-03 | General Electric Company | Fuel injector for supplying fuel to a combustor |
| CN103486618B (en) * | 2013-09-29 | 2015-07-01 | 北京动力机械研究所 | Cyclone for aviation gas turbine engine |
| CN104329689B (en) * | 2014-03-26 | 2016-08-17 | 中国科学院工程热物理研究所 | A kind of combustor using swirl vane trailing edge pre-film atomizing type |
| CN104534514B (en) * | 2014-11-27 | 2017-09-15 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of gas-turbine combustion chamber blade bleed swirl nozzle |
| WO2017023530A1 (en) * | 2015-07-31 | 2017-02-09 | Nuvera Fuel Cells, LLC | Burner assembly with low nox emissions |
| EP3159609A1 (en) * | 2015-10-21 | 2017-04-26 | Siemens Aktiengesellschaft | Combustor for a gas turbine |
| CA3010044C (en) | 2016-01-15 | 2021-06-15 | Siemens Aktiengesellschaft | Combustor for a gas turbine |
| CN107014618B (en) * | 2017-03-29 | 2019-03-29 | 浙江大学 | A kind of combustion chamber and turbine coupling mechanism experiment research device |
| GB2561190A (en) * | 2017-04-04 | 2018-10-10 | Edwards Ltd | Purge gas feeding means, abatement systems and methods of modifying abatement systems |
| US11280495B2 (en) * | 2020-03-04 | 2022-03-22 | General Electric Company | Gas turbine combustor fuel injector flow device including vanes |
| CN112684099B (en) * | 2020-12-18 | 2022-09-09 | 郑州大学 | Assembled turbulent flame extinguishing device |
| US11761632B2 (en) * | 2021-08-05 | 2023-09-19 | General Electric Company | Combustor swirler with vanes incorporating open area |
| CN114294676B (en) * | 2021-12-16 | 2023-05-12 | 北京动力机械研究所 | Pre-combustion chamber structure with wide ignition boundary |
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| US3618317A (en) * | 1969-04-17 | 1971-11-09 | Gen Electric | Fuel delivery apparatus |
| DE4228816C2 (en) * | 1992-08-29 | 1998-08-06 | Mtu Muenchen Gmbh | Burners for gas turbine engines |
| JP2666117B2 (en) * | 1994-06-10 | 1997-10-22 | 財団法人石油産業活性化センター | Pre-evaporation premix combustor |
| CA2194911C (en) * | 1994-07-13 | 2004-11-16 | Anders Sjunnesson | Low-emission combustion chamber for gas turbine engines |
| DE69617290T2 (en) * | 1995-01-13 | 2002-06-13 | Europ Gas Turbines Ltd | Combustion device for gas turbine engine |
| GB2299399A (en) * | 1995-03-25 | 1996-10-02 | Rolls Royce Plc | Variable geometry air-fuel injector |
| FR2752917B1 (en) * | 1996-09-05 | 1998-10-02 | Snecma | ADVANCED HOMOGENIZATION INJECTION SYSTEM |
| FR2753779B1 (en) * | 1996-09-26 | 1998-10-16 | AERODYNAMIC INJECTION SYSTEM FOR A FUEL AIR MIXTURE | |
| EP0849530A3 (en) * | 1996-12-20 | 1999-06-09 | United Technologies Corporation | Fuel nozzles and centerbodies therefor |
| US6550251B1 (en) * | 1997-12-18 | 2003-04-22 | General Electric Company | Venturiless swirl cup |
| GB2333832A (en) * | 1998-01-31 | 1999-08-04 | Europ Gas Turbines Ltd | Multi-fuel gas turbine engine combustor |
| GB2337102A (en) * | 1998-05-09 | 1999-11-10 | Europ Gas Turbines Ltd | Gas-turbine engine combustor |
| GB9818160D0 (en) * | 1998-08-21 | 1998-10-14 | Rolls Royce Plc | A combustion chamber |
| US6865889B2 (en) * | 2002-02-01 | 2005-03-15 | General Electric Company | Method and apparatus to decrease combustor emissions |
| FR2836986B1 (en) * | 2002-03-07 | 2004-11-19 | Snecma Moteurs | MULTI-MODEL INJECTION SYSTEM FOR AN AIR / FUEL MIXTURE IN A COMBUSTION CHAMBER |
| US7104066B2 (en) * | 2003-08-19 | 2006-09-12 | General Electric Company | Combuster swirler assembly |
| US7065972B2 (en) * | 2004-05-21 | 2006-06-27 | Honeywell International, Inc. | Fuel-air mixing apparatus for reducing gas turbine combustor exhaust emissions |
-
2005
- 2005-11-26 GB GB0524097A patent/GB2432655A/en not_active Withdrawn
-
2006
- 2006-11-24 RU RU2008125896/06A patent/RU2419031C2/en not_active IP Right Cessation
- 2006-11-24 EP EP06819738.3A patent/EP1952066B1/en not_active Expired - Fee Related
- 2006-11-24 JP JP2008541752A patent/JP4785932B2/en not_active Expired - Fee Related
- 2006-11-24 US US12/084,601 patent/US20090142716A1/en not_active Abandoned
- 2006-11-24 WO PCT/EP2006/068870 patent/WO2007060216A1/en active Application Filing
- 2006-11-24 CN CN2006800436353A patent/CN101313178B/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| EP1952066B1 (en) | 2016-08-31 |
| GB0524097D0 (en) | 2006-01-04 |
| JP2009517621A (en) | 2009-04-30 |
| GB2432655A (en) | 2007-05-30 |
| US20090142716A1 (en) | 2009-06-04 |
| WO2007060216A1 (en) | 2007-05-31 |
| CN101313178A (en) | 2008-11-26 |
| RU2008125896A (en) | 2010-01-10 |
| EP1952066A1 (en) | 2008-08-06 |
| JP4785932B2 (en) | 2011-10-05 |
| RU2419031C2 (en) | 2011-05-20 |
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| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20110831 Termination date: 20181124 |