EP1985924A1 - Swirler - Google Patents
Swirler Download PDFInfo
- Publication number
- EP1985924A1 EP1985924A1 EP07008236A EP07008236A EP1985924A1 EP 1985924 A1 EP1985924 A1 EP 1985924A1 EP 07008236 A EP07008236 A EP 07008236A EP 07008236 A EP07008236 A EP 07008236A EP 1985924 A1 EP1985924 A1 EP 1985924A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- swirler
- twisted
- central axis
- vane
- vanes
- 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.)
- Withdrawn
Links
Images
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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN A CARRIER GAS OR AIR
- F23C7/00—Combustion apparatus characterised by arrangements for air supply
- F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
- F23C7/004—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion using vanes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
- F23D2900/14—Special features of gas burners
- F23D2900/14021—Premixing burners with swirling or vortices creating means for fuel or air
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
- F23D2900/14—Special features of gas burners
- F23D2900/14701—Swirling means inside the mixing tube or chamber to improve premixing
Definitions
- the invention relates to a fuel injection system and improvements for the further diminishment of air pollutants such as nitrogen oxides (NO x ).
- air pollutants such as nitrogen oxides (NO x ).
- the first is to use a fine distribution of fuel in the air, generating a fuel/air mixture with a low fuel fraction.
- the thermal mass of the excess air present in the reaction zone of a lean premixed combustor absorbs heat and limits the temperature rise of the products of combustion to a level where thermal NO x is not excessively formed.
- the second measure is to provide a thorough mixing of fuel and air prior to combustion. The better the mixing, the fewer regions exist where the fuel concentration is significantly higher than average, the fewer the regions reaching higher temperatures than average, the lower the fraction of thermal NO x will be.
- premixing of fuel and air in a gas turbine engine takes place by injecting fuel into an air stream in a swirling zone of a combustor which is located upstream from the combustion zone.
- the swirling produces a mixing of fuel and air before the mixture enters the combustion zone.
- An object of the invention is to provide a swirler, allowing for a better pre-mixing of gaseous fuel and compressor air to provide a homogeneous fuel/air mixture and thereby reduce formation of NO x .
- Another objective is to provide a burner with an improved swirler.
- Still another objective is to provide a gas turbine with an improved swirler.
- An inventive swirler incorporates a modified radial swirler assembly.
- the modification is best described by a partly twisted radial swirler.
- None of the prior art is targeting the generation of turbulent secondary flows along the swirl vanes with the specific aim of assisting fuel air mixing.
- the twisted vanes comprise straight parts at the base portions of the twisted vanes.
- This feature provides a well defined shear layer region for any reverse flow into the swirler assembly. This is advantageous because it increases the stability of any flame in that region.
- the height of the straight parts should not exceed 50% of the twisted vanes' height in order to benefit from the turbulent secondary flows generated in the twisted parts. Therefore it is also advantageous to twist the vanes by an angle of up to 120°. However, twisted vanes with angles differing considerably from 120° will also provide desirable turbulent secondary flows.
- FIG. 1 a typical prior art radial swirler 1 is shown.
- the turning vanes 9 of a radial swirler 1 are arranged on a first plate 2 that is normal to the central axis 3 of the swirler 1 body.
- the vanes 9 are of pie slice type with substantially triangular footprints 4 (see Figure 3 ) and rectangular side faces 13 and a slightly curved outer surface 10.
- the turning vanes 9 are fixed to a second plate 8 with their sides showing away from the first plate 2.
- Swirler passages 14 are formed by opposing side faces 13 of swirler vanes 9, by the surface of the first plate 2 and by a surface of the second plate 8.
- the second plate 8 is connected to a combustion pre-chamber 11.
- This configuration of the swirler 1 forces the airflow (as shown by the arrows) to move within the passages 14 radially inwardly towards the central axis 3 of the swirler 1 body.
- a radial swirler 1 is capable of creating strong swirl and thorough mixing with little concern of the problem of aerodynamic wake flows.
- FIG 2 shows the view of an embodiment of the inventive swirler 1.
- Respective base portions 6 of the turning vanes 9 are arranged on a first plate 2 that is normal to the central axis 3 of the swirler 1 body and the footprints 4 (see Figure 3 ) of the vanes 9 are of substantially triangular shape.
- the vanes 9 are twisted and will be referred to as twisted vanes 5.
- the embodiment of Figure 2 comprises twisted vanes 5 with straight base portions 6 and twisted parts 7.
- the straight base portions 6 have a shape described by a translation of the vane footprints 4 (see Figure 3 ) parallel to the central axis 3 of the swirler 1, whereas the twisted parts 7 have a shape described by a further translation of the vane footprints 4 along the central axis 3 superimposed by a rotation of the vane footprints 4 about the central axis 3.
- an inventive swirler 1 is shown without second plate 8 and combustor pre-chamber 11 (see Figures 1 and 2 ) where the twisted vanes 5 are arranged on a first plate 2.
- the substantially triangular vane footprints 4 can be seen very clearly in this view.
- Figure 3 shows the turbulent secondary flows 12 generated along the twisted vanes 5, improving fuel/air mixing.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gas Burners (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Disclosed is a swirler (1), comprising a plate (2) normal to a central axis (3) of the swirler (1), a plurality of vane footprints (4) arranged on the plate (2) and radially positioned about the central axis (3) and a plurality of twisted vanes (5).
Description
- The invention relates to a fuel injection system and improvements for the further diminishment of air pollutants such as nitrogen oxides (NOx).
- Air pollution is a worldwide concern and many countries have enacted stricter laws further limiting the emission of pollutants from gas turbine engines or offer fiscal or other benefits for environmentally sound installations. Although the prior techniques for reducing the emissions of NOx from gas turbine engines are steps in the right direction, the need for additional improvements remains.
- There are two main measures by which reduction of the temperature of the combustion flame can be achieved. The first is to use a fine distribution of fuel in the air, generating a fuel/air mixture with a low fuel fraction. The thermal mass of the excess air present in the reaction zone of a lean premixed combustor absorbs heat and limits the temperature rise of the products of combustion to a level where thermal NOx is not excessively formed. The second measure is to provide a thorough mixing of fuel and air prior to combustion. The better the mixing, the fewer regions exist where the fuel concentration is significantly higher than average, the fewer the regions reaching higher temperatures than average, the lower the fraction of thermal NOx will be.
- Usually the premixing of fuel and air in a gas turbine engine takes place by injecting fuel into an air stream in a swirling zone of a combustor which is located upstream from the combustion zone. The swirling produces a mixing of fuel and air before the mixture enters the combustion zone.
- An object of the invention is to provide a swirler, allowing for a better pre-mixing of gaseous fuel and compressor air to provide a homogeneous fuel/air mixture and thereby reduce formation of NOx. Another objective is to provide a burner with an improved swirler. Still another objective is to provide a gas turbine with an improved swirler.
- These objectives are achieved by the claims. The dependent claims describe advantageous developments and modifications of the invention.
- An inventive swirler incorporates a modified radial swirler assembly. The modification is best described by a partly twisted radial swirler.
- Unlike axial swirlers where the air inflow is predominantly entering the swirler and being deflected by the action of an aerofoil, air is admitted to the swirler over the entire length of the swirl slot or vane section, where it is deflected into a swirling motion.
- The added advantage of such a configuration is that the twisted vane ensures that the air entry flow is 'tumbled' and hence provides a means for enhanced fuel air mixing.
- None of the prior art is targeting the generation of turbulent secondary flows along the swirl vanes with the specific aim of assisting fuel air mixing.
- In an advantageous arrangement the twisted vanes comprise straight parts at the base portions of the twisted vanes. This feature provides a well defined shear layer region for any reverse flow into the swirler assembly. This is advantageous because it increases the stability of any flame in that region. The height of the straight parts should not exceed 50% of the twisted vanes' height in order to benefit from the turbulent secondary flows generated in the twisted parts. Therefore it is also advantageous to twist the vanes by an angle of up to 120°. However, twisted vanes with angles differing considerably from 120° will also provide desirable turbulent secondary flows.
- By such a design a better pre-mixing of gaseous fuel with compressor air and a homogeneous fuel/air mixture is achieved to reduce formation of NOx.
- The invention will now be further described with reference to the accompanying drawings in which:
-
Figure 1 shows a perspective view of a prior art radial swirler, -
Figure 2 shows a perspective view of a swirler in accordance with the present invention, and -
Figure 3 shows another perspective view of a swirler with twisted vanes in accordance with the present invention. - In the drawings like references identify like or equivalent parts.
- Referring to
Figure 1 , a typical prior art radial swirler 1 is shown. The turning vanes 9 of a radial swirler 1 are arranged on afirst plate 2 that is normal to the central axis 3 of the swirler 1 body. The vanes 9 are of pie slice type with substantially triangular footprints 4 (seeFigure 3 ) andrectangular side faces 13 and a slightly curvedouter surface 10. The turning vanes 9 are fixed to asecond plate 8 with their sides showing away from thefirst plate 2. Swirlerpassages 14 are formed by opposing side faces 13 of swirler vanes 9, by the surface of thefirst plate 2 and by a surface of thesecond plate 8. Thesecond plate 8 is connected to a combustion pre-chamber 11. - This configuration of the swirler 1 forces the airflow (as shown by the arrows) to move within the
passages 14 radially inwardly towards the central axis 3 of the swirler 1 body. Already with this simple prior art straight vane geometry, a radial swirler 1 is capable of creating strong swirl and thorough mixing with little concern of the problem of aerodynamic wake flows. -
Figure 2 shows the view of an embodiment of the inventive swirler 1.Respective base portions 6 of the turning vanes 9 are arranged on afirst plate 2 that is normal to the central axis 3 of the swirler 1 body and the footprints 4 (seeFigure 3 ) of the vanes 9 are of substantially triangular shape. Unlike prior art, the vanes 9 are twisted and will be referred to astwisted vanes 5. The embodiment ofFigure 2 comprisestwisted vanes 5 withstraight base portions 6 andtwisted parts 7. Thestraight base portions 6 have a shape described by a translation of the vane footprints 4 (seeFigure 3 ) parallel to the central axis 3 of the swirler 1, whereas thetwisted parts 7 have a shape described by a further translation of thevane footprints 4 along the central axis 3 superimposed by a rotation of thevane footprints 4 about the central axis 3. - With reference to
Figure 3 , an inventive swirler 1 is shown withoutsecond plate 8 and combustor pre-chamber 11 (seeFigures 1 and 2 ) where thetwisted vanes 5 are arranged on afirst plate 2. The substantiallytriangular vane footprints 4 can be seen very clearly in this view.Figure 3 shows the turbulentsecondary flows 12 generated along thetwisted vanes 5, improving fuel/air mixing.
Claims (8)
- A swirler (1), comprising:a plate (2) normal to a central axis (3) of the swirler (1); a plurality of vane footprints (4) arranged on the plate (2) and radially positioned about the central axis (3); anda plurality of twisted vanes (5) arranged on the vane footprints (4).
- The swirler (1) as claimed in claim 1, further comprising straight base portions (6) arranged on the footprints (4) and included in the twisted vanes (5).
- The swirler (1) as claimed in claim 2, wherein straight base portions (6) have a shape described by a translation of the vane footprints (4) parallel to the central axis (3).
- The swirler (1) as claimed in claim 1, wherein twisted parts (7) of the twisted vanes (5) have a shape described by a translation of the vane footprints (4) along the central axis (3) superimposed by a rotation about the central axis (3).
- The swirler (1) as claimed in claim 1 or claim 4, wherein an angle of rotation is up to 120°.
- The swirler (1) as claimed in claim 2 or claim 3, wherein the straight base portions (6) have a height less than 50% of a twisted vane height.
- A burner comprising a swirler (1) as claimed in any of the preceding claims.
- A turbine engine with a burner as claimed in claim 7.
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP07008236A EP1985924A1 (en) | 2007-04-23 | 2007-04-23 | Swirler |
CN2008800133415A CN101668989B (en) | 2007-04-23 | 2008-04-17 | Swirler |
PCT/EP2008/054658 WO2008128955A1 (en) | 2007-04-23 | 2008-04-17 | Swirler |
EP08736322A EP2137460A1 (en) | 2007-04-23 | 2008-04-17 | Swirler |
US12/597,261 US20100175381A1 (en) | 2007-04-23 | 2008-04-17 | Swirler |
RU2009143010/06A RU2467253C2 (en) | 2007-04-23 | 2008-04-17 | Swirler |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP07008236A EP1985924A1 (en) | 2007-04-23 | 2007-04-23 | Swirler |
Publications (1)
Publication Number | Publication Date |
---|---|
EP1985924A1 true EP1985924A1 (en) | 2008-10-29 |
Family
ID=38521629
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP07008236A Withdrawn EP1985924A1 (en) | 2007-04-23 | 2007-04-23 | Swirler |
EP08736322A Withdrawn EP2137460A1 (en) | 2007-04-23 | 2008-04-17 | Swirler |
Family Applications After (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP08736322A Withdrawn EP2137460A1 (en) | 2007-04-23 | 2008-04-17 | Swirler |
Country Status (5)
Country | Link |
---|---|
US (1) | US20100175381A1 (en) |
EP (2) | EP1985924A1 (en) |
CN (1) | CN101668989B (en) |
RU (1) | RU2467253C2 (en) |
WO (1) | WO2008128955A1 (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2010107401A3 (en) * | 2009-03-19 | 2011-04-07 | Brinox, D.O.O. | Device for coating particles via an airflow vortex generation |
WO2012156631A1 (en) * | 2011-05-17 | 2012-11-22 | Snecma | Annular combustion chamber for a turbomachine |
Families Citing this family (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8517719B2 (en) * | 2009-02-27 | 2013-08-27 | Alstom Technology Ltd | Swirl block register design for wall fired burners |
EP2718644B1 (en) * | 2011-06-10 | 2020-09-09 | Carrier Corporation | Ejector with motive flow swirl |
EP2685160B1 (en) * | 2012-07-10 | 2018-02-21 | Ansaldo Energia Switzerland AG | Premix burner of the multi-cone type for a gas turbine |
CN103851623B (en) * | 2014-03-28 | 2017-03-15 | 李延新 | A kind of combustor of pressure Hui Yan |
EP3236157A1 (en) | 2016-04-22 | 2017-10-25 | Siemens Aktiengesellschaft | Swirler for mixing fuel with air in a combustion engine |
JP2023007855A (en) * | 2021-07-02 | 2023-01-19 | 本田技研工業株式会社 | fuel nozzle device |
US20230212984A1 (en) * | 2021-12-30 | 2023-07-06 | General Electric Company | Engine fuel nozzle and swirler |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE4203598C1 (en) * | 1992-02-07 | 1993-06-24 | Industrial Technology Research Institute, Chutung, Hsing-Chu, Tw | Burner swirl-inducing component with axial vanes - has deflection points on curved vanes determined dependent on inner and outer radii edge curvature and passage diameter |
US5394688A (en) * | 1993-10-27 | 1995-03-07 | Westinghouse Electric Corporation | Gas turbine combustor swirl vane arrangement |
EP0902237A2 (en) * | 1997-09-10 | 1999-03-17 | Mitsubishi Heavy Industries, Ltd. | Combustor swirler with twisted vanes |
US6141967A (en) * | 1998-01-09 | 2000-11-07 | General Electric Company | Air fuel mixer for gas turbine combustor |
US20030172655A1 (en) * | 2002-03-12 | 2003-09-18 | Verdouw Albert J. | Dry low combustion system with means for eliminating combustion noise |
Family Cites Families (24)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2657741A (en) * | 1948-07-06 | 1953-11-03 | Ralph C Brierly | Air control ring |
JPS6097351U (en) * | 1983-12-09 | 1985-07-03 | アイシン精機株式会社 | Swirler for Stirling engine |
US4681532A (en) * | 1985-05-02 | 1987-07-21 | Landy Chung | Boiler furnace air register |
US5144804A (en) * | 1989-07-07 | 1992-09-08 | Fuel Systems Textron Inc. | Small airblast fuel nozzle with high efficiency inner air swirler |
DE4110507C2 (en) * | 1991-03-30 | 1994-04-07 | Mtu Muenchen Gmbh | Burner for gas turbine engines with at least one swirl device which can be regulated in a load-dependent manner for the supply of combustion air |
JPH06272862A (en) * | 1993-03-18 | 1994-09-27 | Hitachi Ltd | Method and apparatus for mixing fuel into air |
US5450724A (en) * | 1993-08-27 | 1995-09-19 | Northern Research & Engineering Corporation | Gas turbine apparatus including fuel and air mixer |
CN1162089A (en) * | 1995-12-21 | 1997-10-15 | Abb研究有限公司 | Combustion device of heat generator |
FR2752917B1 (en) * | 1996-09-05 | 1998-10-02 | Snecma | ADVANCED HOMOGENIZATION INJECTION SYSTEM |
US5899075A (en) * | 1997-03-17 | 1999-05-04 | General Electric Company | Turbine engine combustor with fuel-air mixer |
ATE244380T1 (en) * | 1997-11-21 | 2003-07-15 | Alstom | BURNER FOR OPERATION OF A HEAT GENERATOR |
US6082113A (en) * | 1998-05-22 | 2000-07-04 | Pratt & Whitney Canada Corp. | Gas turbine fuel injector |
DE19859829A1 (en) * | 1998-12-23 | 2000-06-29 | Abb Alstom Power Ch Ag | Burner for operating a heat generator |
US7104066B2 (en) * | 2003-08-19 | 2006-09-12 | General Electric Company | Combuster swirler assembly |
US7131273B2 (en) * | 2004-12-17 | 2006-11-07 | General Electric Company | Gas turbine engine carburetor with flat retainer connecting primary and secondary swirlers |
CN101137869A (en) * | 2005-03-09 | 2008-03-05 | 阿尔斯托姆科技有限公司 | Premix burner for operating a combustion chamber |
US7237730B2 (en) * | 2005-03-17 | 2007-07-03 | Pratt & Whitney Canada Corp. | Modular fuel nozzle and method of making |
US8104285B2 (en) * | 2005-09-30 | 2012-01-31 | Ansaldo Energia S.P.A. | Gas turbine equipped with a gas burner and axial swirler for the burner |
FR2896031B1 (en) * | 2006-01-09 | 2008-04-18 | Snecma Sa | MULTIMODE INJECTION DEVICE FOR COMBUSTION CHAMBER, IN PARTICULAR A TURBOREACTOR |
JP4719059B2 (en) * | 2006-04-14 | 2011-07-06 | 三菱重工業株式会社 | Gas turbine premixed combustion burner |
US7762058B2 (en) * | 2007-04-17 | 2010-07-27 | Pratt & Whitney Rocketdyne, Inc. | Ultra-compact, high performance aerovortical rocket thruster |
US8037689B2 (en) * | 2007-08-21 | 2011-10-18 | General Electric Company | Turbine fuel delivery apparatus and system |
US8015821B2 (en) * | 2008-01-11 | 2011-09-13 | Spytek Aerospace Corporation | Apparatus and method for a gas turbine entrainment system |
US20090249789A1 (en) * | 2008-04-08 | 2009-10-08 | Baifang Zuo | Burner tube premixer and method for mixing air and gas in a gas turbine engine |
-
2007
- 2007-04-23 EP EP07008236A patent/EP1985924A1/en not_active Withdrawn
-
2008
- 2008-04-17 US US12/597,261 patent/US20100175381A1/en not_active Abandoned
- 2008-04-17 WO PCT/EP2008/054658 patent/WO2008128955A1/en active Application Filing
- 2008-04-17 EP EP08736322A patent/EP2137460A1/en not_active Withdrawn
- 2008-04-17 RU RU2009143010/06A patent/RU2467253C2/en not_active IP Right Cessation
- 2008-04-17 CN CN2008800133415A patent/CN101668989B/en not_active Expired - Fee Related
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE4203598C1 (en) * | 1992-02-07 | 1993-06-24 | Industrial Technology Research Institute, Chutung, Hsing-Chu, Tw | Burner swirl-inducing component with axial vanes - has deflection points on curved vanes determined dependent on inner and outer radii edge curvature and passage diameter |
US5394688A (en) * | 1993-10-27 | 1995-03-07 | Westinghouse Electric Corporation | Gas turbine combustor swirl vane arrangement |
EP0902237A2 (en) * | 1997-09-10 | 1999-03-17 | Mitsubishi Heavy Industries, Ltd. | Combustor swirler with twisted vanes |
US6141967A (en) * | 1998-01-09 | 2000-11-07 | General Electric Company | Air fuel mixer for gas turbine combustor |
US20030172655A1 (en) * | 2002-03-12 | 2003-09-18 | Verdouw Albert J. | Dry low combustion system with means for eliminating combustion noise |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2010107401A3 (en) * | 2009-03-19 | 2011-04-07 | Brinox, D.O.O. | Device for coating particles via an airflow vortex generation |
RU2542276C2 (en) * | 2009-03-19 | 2015-02-20 | Бринокс, Д.О.О. | Perfected device for application of coating on particles by new process with help of airflow vortex generator |
WO2012156631A1 (en) * | 2011-05-17 | 2012-11-22 | Snecma | Annular combustion chamber for a turbomachine |
US9951955B2 (en) | 2011-05-17 | 2018-04-24 | Snecma | Annular combustion chamber for a turbine engine |
Also Published As
Publication number | Publication date |
---|---|
US20100175381A1 (en) | 2010-07-15 |
CN101668989B (en) | 2012-01-04 |
EP2137460A1 (en) | 2009-12-30 |
RU2009143010A (en) | 2011-05-27 |
CN101668989A (en) | 2010-03-10 |
WO2008128955A1 (en) | 2008-10-30 |
RU2467253C2 (en) | 2012-11-20 |
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