WO2009142026A1 - 燃焼装置および燃焼装置の制御方法 - Google Patents
燃焼装置および燃焼装置の制御方法 Download PDFInfo
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- WO2009142026A1 WO2009142026A1 PCT/JP2009/002274 JP2009002274W WO2009142026A1 WO 2009142026 A1 WO2009142026 A1 WO 2009142026A1 JP 2009002274 W JP2009002274 W JP 2009002274W WO 2009142026 A1 WO2009142026 A1 WO 2009142026A1
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- 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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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- 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
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- 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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/34—Feeding into different combustion zones
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- 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
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03343—Pilot burners operating in premixed mode
Definitions
- the present invention relates to a combustion apparatus used for a device that requires a high-temperature gas supply, such as a gas turbine engine or a boiler, and a method for controlling the fuel concentration of the combustion apparatus, particularly in the radial direction of a premixed gas.
- Gas turbine engines have strict environmental standards regarding the composition of exhaust gas emitted by combustion, considering environmental conservation, and it is required to reduce harmful substances such as nitrogen oxides (hereinafter referred to as NOx). It has been.
- NOx nitrogen oxides
- large-scale gas turbine engines for ground facilities and aircraft gas turbine engines tend to have a high pressure ratio due to demands for low fuel consumption and high output.
- the combustion temperature tends to increase as the inlet temperature of the combustion apparatus increases, and there is a concern that it may be a factor that rather increases NOx.
- the diffusion combustion method burns fuel and air while diffusing and mixing them, so it is difficult to blow out even at low loads and has the advantage of excellent flame holding performance, while reducing the amount of NOx generated.
- the combined combustion method it is possible to reduce the amount of NOx generated by premixed combustion at high load while ensuring combustion stability by diffusion combustion at start-up and low load.
- a fixed swirl vane is provided so as to surround the outside of a diffusion combustion burner (pilot burner) 82 disposed at the top 81 a of the combustion cylinder 81 of the combustion apparatus 80.
- a swirl type burner unit 85 is provided, in which a premixed combustion burner (main burner) 84 having a radial swirler 83 is disposed, and the premixed gas P is injected into the combustion chamber as a swirling flow.
- an air passage 86 from the gas turbine compressor is formed between the combustion cylinder 81 and the housing H covering the outside thereof, and the air A is generated. Some of them are introduced from the downstream end of the combustion cylinder 81 toward the top 81a which is the upstream end in the direction opposite to the combustion gas. In that case, the air A that has passed through the air passage 86 is introduced into the premixing passage from the inlet of the radial swirler 83 that opens radially outward, mixed with fuel, and in the direction opposite to the flow of compressed air as premixed air Is injected into the combustion cylinder.
- the flow direction of the air A introduced into the radial swirler 83 from the air passage 86 is changed by approximately 90 °, so that the axial flow rate of the air in the upstream portion of the premixing passage is caused by the centrifugal force accompanying the direction change.
- the distribution is biased.
- the vane angle of the swirl vanes of the radial swirler is increased to stabilize the flame holding as described above, the axial dimension of the inlet portion is increased, so that the uneven flow distribution is further increased.
- the fuel concentration distribution in the radial direction of the premixed gas injected into the combustion chamber from the premixing passage is also biased, so that the fuel concentration distribution in the radial direction is made uniform or intentionally adjusted to the fuel concentration. There was a problem that it was difficult to control the distribution.
- the present invention maintains a large vane angle of the swirl vanes of the radial swirler and generates a strong back flow in the combustion chamber, thereby stabilizing the flame holding, and the radial direction of the premixed gas injected from the burner to the combustion chamber It is an object of the present invention to provide a combustion apparatus capable of easily controlling the concentration distribution and a control method of the combustion apparatus for easily controlling the radial fuel concentration distribution of the premixed gas in the combustion apparatus.
- a combustion apparatus includes a combustion cylinder that forms a combustion chamber on the inside, a top portion of the combustion cylinder, and a fuel and air preliminarily disposed in the combustion chamber.
- a main burner having a premixing passage for injecting air-fuel mixture, a radial swirler for introducing fuel and air into the premixing passage radially inward, and a fuel injection pipe for injecting fuel into the radial swirler from its inlet side;
- the radial swirler includes a plurality of swirler stages divided in the axial direction by a dividing plate.
- the radial swirler is divided into a plurality of swirler stages in the axial direction by the dividing plate, the flow rate of air introduced into the radial swirler can be prevented from being biased in the axial direction.
- the fuel injection pipe includes a plurality of fuel injection ports corresponding to the respective swirler stages. According to this configuration, since the fuel injection pipe for injecting fuel to the radial swirler has the injection ports corresponding to the respective swirler stages, the radial direction of the premixed gas injected from the premixing passage into the combustion chamber is provided. It is possible to greatly suppress the deviation of the fuel concentration distribution.
- the fuel flow rate supplied from the fuel injection pipe may be set for each swirler stage. According to this configuration, the control of making the fuel concentration distribution in the radial direction of the premixed gas injected from the premixing passage into the combustion chamber more uniform or forming the intended fuel concentration distribution becomes easy.
- each of the plurality of fuel injection ports of the fuel injection pipe are configured to have different diameters. Also good.
- each of the plurality of fuel injection ports may be configured to have an individually set diameter.
- the radial length of the dividing plate may be shorter than the straight portion along the radial direction forming the upstream portion of the premixing passage.
- the air that has passed through the air passage changes direction toward the radial swirler, it receives the largest centrifugal force at the inlet of the radial swirler, so that it only suppresses the deviation of the air flow rate in the axial direction at this portion.
- a radial length is sufficient.
- the premixing passage after exiting the radial swirler is lengthened by the short radial length of the radial swirler, so that premixing is promoted.
- the diameter of the premixed gas injected from the main burner into the combustion chamber is controlled by controlling the flow rate of the fuel supplied for each swirler stage. Control the fuel concentration distribution in the direction.
- the radial swirler is divided in the axial direction so that the flow distribution in the axial direction of the air is made uniform, so the flow rate of fuel supplied to each swirler stage is controlled. Only by this, the radial fuel concentration distribution of the premixed gas injected into the combustion chamber can be easily controlled.
- FIG. 1 is a schematic view showing a gas turbine engine to which a combustion apparatus according to an embodiment of the present invention is applied. It is sectional drawing which shows the combustion apparatus of FIG. It is sectional drawing which expands and shows the principal part of the combustion apparatus of FIG.
- FIG. 4 is a sectional view taken along line IV-IV in FIG. 3. It is a schematic diagram for demonstrating the air flow of the combustion apparatus of FIG. It is a schematic diagram for demonstrating the air flow of the conventional combustion apparatus. It is sectional drawing which shows the conventional combustion apparatus.
- FIG. 1 is a simplified configuration diagram showing a gas turbine engine to which a combustion apparatus according to an embodiment of the present invention is applied.
- the gas turbine engine GT includes a compressor 1, a combustion device 2, and a turbine 3 as main components.
- the compressed air supplied from the compressor 1 is combusted by the combustion device 2, and high-pressure combustion gas generated thereby. Is supplied to the turbine 3.
- the compressor 1 is connected to the turbine 3 via the rotating shaft 5 and is driven by the turbine 3.
- the load 4 such as an aircraft rotor or generator is driven by the output of the gas turbine engine GT.
- the fuel F fed from the fuel supply device 9 is supplied to the combustion device 2 via the fuel control device 8.
- FIG. 2 is a cross-sectional view showing the combustion apparatus 2.
- This combustion apparatus 2 is a can type that is arranged in a ring shape around the engine rotation axis, and is attached to a combustion cylinder 12 that forms a combustion chamber 10 inside, and a top portion 12 a of the combustion cylinder 12.
- a burner unit 14 for injecting a premixed fuel and air mixture.
- the combustion cylinder 12 and the burner unit 14 are accommodated concentrically in a substantially cylindrical housing H that is an outer cylinder of the combustion apparatus 2.
- An end cover 18 is fixed to the front end of the housing H with bolts 20.
- This combustion device 2 is of a reverse flow type, and the compressed air A from the compressor 1 is directed between the housing H and the side wall 12b of the combustion cylinder 12 in the direction toward the burner unit 14 as indicated by the arrow, that is, the combustion chamber.
- An air passage 30 that leads in the direction opposite to the flow direction of the combustion gas G in 10 is formed.
- One or a plurality of spark plugs 36 are fixed to the housing H through the housing H and the combustion cylinder 12 on the upstream peripheral wall of the combustion cylinder 12, and are injected from a pilot burner 44 described later of the burner unit 14.
- the premixed gas is ignited to form a combustion region S in the upstream portion of the combustion cylinder 12.
- a plurality of dilution air holes (not shown) formed by penetrating short pipes are disposed on the downstream side of the combustion region S in the combustion cylinder 12.
- FIG. 3 is a cross-sectional view showing a main part of the combustion apparatus 2 of FIG.
- the burner unit 14 includes a main burner 42 that injects an annular premixed gas P ⁇ b> 1 that includes a swirling component, and a pilot burner 44 that is disposed inside the main burner 42.
- the burner unit 14 includes an outer peripheral cylindrical portion 46a concentric with the axis O of the combustion cylinder 12, and an outer peripheral disc extending in a disc shape in a direction perpendicular to the axis O from the upstream end of the outer peripheral cylindrical portion 46a.
- the inner peripheral cylindrical portion 48a located on the radially inner side of the outer peripheral cylindrical portion 46a, and the outer peripheral disc portion 46b from the vicinity of the upstream end of the inner peripheral cylindrical portion 48a. It has a burner inner cylinder 48 composed of an inner peripheral disc portion 48b extending parallel to the outer peripheral disc portion 46b on the upstream side.
- the space between the burner outer cylinder 46 and the burner inner cylinder 48 forms an annular first premixing passage 42 a of the main burner 42, and the inner space of the burner inner cylinder 48 is the second premixed gas of the pilot burner 44.
- a passage 44a is formed.
- the first premixing passage 42a of the main burner 42 is L-shaped in a longitudinal section passing through the axis O (that is, a section including the axis O), and is upstream in the radial direction, that is, two disks.
- a radial swirler 50 is attached between the outermost peripheral portions of the portions 46b and 48b. The downstream part of the first premixing passage 42a faces in the axial direction.
- the radial outer end of the radial swirler 50 is formed as an inlet portion 50a for introducing the air A and the fuel F1 radially inward into the first premixing passage 42a, and further on the radially outer side of the inlet portion 50a.
- a first fuel injection pipe 52 that forms a fuel passage for supplying the fuel F1 is disposed through the end cover 18.
- a plurality of first fuel injection pipes 52 are provided side by side at equal intervals in the circumferential direction.
- the radial swirler 50 is fixed to the main burner 42 by being fitted into a fitting portion 42b formed between the outermost peripheral portions of the two disc portions 46b and 48b.
- FIG. 4 which is a cross-sectional view taken along the line IV-IV of FIG. 3, the radial swirler 50 includes fixed swirl vanes 54 that swirl the air A and the fuel F1 introduced into the first premixing passage 42a. Have. Further, the radial swirler 50 is provided with an annular dividing plate 56.
- the radial swirler 50 is formed with a plurality of swirler stages 50b divided in the axis O direction by the dividing plate 56 as swirler portions.
- the radial swirler 50 is divided into five swirler stages 50 b by four dividing plates 56. Therefore, the inlet portion of the first premixing passage 42 a is also divided into five in the axial direction by the dividing plate 56.
- the fuel is injected into the combustion chamber 10 from an injection port 42c formed by an opening on the downstream side of the premix passage 42a.
- the number of the dividing plates is 2 or more and 6 or less, preferably 3 or more and 5 or less, and the swirler 50 is divided into 3 to 7, preferably 4 to 6.
- the dividing plate 56 has a radial length sufficient to deflect the compressed air A that has passed through the air passage 30 radially inward and introduce it into the first premixing passage 42a.
- the preferred range of the radial length L1 of the dividing plate 56 that is, the radial length of the radial swirler 50, is 1/2 of the length L2 of the straight portion along the radial direction on the upstream side of the first premixing passage 42a. It is 6 to 2/3, and more preferably 1/4 to 1/2.
- the radial length L1 of the dividing plate 56 is set to 1/3 of the radial straight portion length L2 of the first premixing passage 42a.
- the ratio L1 / D between the radial length L1 of the dividing plate 56 and the interval in the axis O direction of each dividing plate 56 (that is, the dimension width in the axial direction of each swirler stage 50b) D is 2.0. However, 1.0 to 3.0 is preferable, and 1.5 to 2.5 is more preferable.
- the ratio L1 / D is less than 1.0, the length L1 of the fixed swirl blade 54 with respect to the large-mouth passage area (circumferential length of the swirler inlet ⁇ D) is relatively shortened. The effect of suppressing the deviation of the air flow rate in the direction becomes small.
- the same number of fuel injection ports 52a as the plurality of swirler stages 50b are arranged in the axial direction.
- Each fuel injection port 52a is arranged to face each swirler stage 50b from the inlet side, and the fuel F1 is injected to each swirler stage 50b through each of the plurality of fuel injection ports 52a.
- the diameters of the fuel injection ports 52a are the same, and the flow rate of the fuel F1 injected into each swirler stage 50b is set to be uniform.
- the upstream portion of the second premixing passage 44a has an annular first passage plate 63 supported by the pilot burner 44 and a bolt 65 so as to face the first passage plate 63 in the axial direction through a spacer 64. It is formed between the disc-shaped second passage plate 66 attached in the above.
- a second fuel injection pipe 67 for supplying fuel F2 is disposed through the end cover 18 on the radially outer side of the upstream end of the second premixed gas passage 44a.
- the first fuel injection pipe 52 that supplies the fuel F1 to the main burner 42 and the second fuel supply passage 67 that supplies the fuel F2 to the pilot burner 44 are provided as fuel supply systems independent of each other. By individually controlling each, the fuel concentration (air-fuel ratio) of the air-fuel mixture can be adjusted independently.
- the compressed air A from the compressor 1 passes through an air passage 30, which is a backflow passage formed between the side wall 12 b of the combustion cylinder 12 and the housing H, and passes through the air passage 30 of the main burner 42. 1 It guide
- the flow rate of the air A has a large axial front end side (left side in FIG. 5B) due to the influence of centrifugal force.
- a bias arises.
- the air A is divided and introduced into a plurality of swirler stages 50 b divided in the axial direction by the dividing plate 56. Therefore, in each swirler stage 50b, a slight deviation in the axial flow rate occurs, but the deviation in the axial flow rate of the air A in the radial swirler 50 as a whole is greatly suppressed.
- the flow rates of both the air A and the fuel F1 introduced into each swirler stage 50b divided in the axial direction by the dividing plate 56 are controlled almost uniformly. Therefore, the fuel concentration distribution in the axial direction of the premixed gas P1 formed in the upstream portion of the first premixing passage 42a is made uniform. As a result, the fuel concentration distribution in the radial direction of the premixed gas P1 injected from the first premixing passage 42a into the combustion chamber 10 can be made uniform.
- the diameters of the plurality of fuel injection ports 52a of the first fuel injection pipe 52 may not be the same, but may be set individually. That is, the plurality of fuel injection ports 52a of the first fuel injection pipe 52 may have different diameters.
- the optimal fuel concentration distribution of the premixed gas P1 injected into the combustion chamber 10 for realizing low NOx combustion is the shape of the combustion chamber 10, the structure of the pilot burner 44 used in combination with the main burner 42, etc. May vary due to various factors. That is, there is a case where the fuel concentration of the premixed gas P1 injected into the combustion chamber 10 is not necessarily uniform and should be controlled to have an intentionally distributed distribution.
- the radial swirler 50 is divided in the axial direction, so that the flow distribution in the axial direction of the air A is made uniform. Only by controlling the flow rate of the supplied fuel F1, the radial fuel concentration distribution of the premixed gas P1 injected into the combustion chamber 10 can be easily controlled.
- Control of the flow rate of the fuel supplied to each swirler stage 50b can be easily performed, for example, by individually setting the diameter of the fuel injection port 52a corresponding to each swirler stage 50b as described above.
- the swirler 50 multi-staged in the axial direction can obtain a particularly great effect in the case of this embodiment.
- the air A introduced into the radial swirler 50 receives a large centrifugal force when the flow direction is changed by 90 ° through the radial swirler 50, but the dividing plate 56 is provided on the radial swirler 50.
- the deviation of the flow distribution in the axial direction of the air A introduced into the radial swirler 50 can be minimized. Therefore, while the combustion apparatus 2 has a compact configuration, low NOx combustion can be realized by optimizing the radial fuel concentration distribution of the premixed gas P1 in the combustion chamber 10.
- the radial swirler 50 is divided into five swirler stages 50b by four dividing plates 56, but the number of swirler stages 50b provided separately is not limited to five. May be set as appropriate.
- the fixed swirl vane 54 and the split plate 56 of the radial swirler 50 are configured to have substantially the same radial length, but the fixed swirl vane 54 and the split plate 56 have different radial lengths. You may have. Further, the radial length and the axial length of each swirler stage 50b may be different for each swirler stage.
- the shape of the corner 42d on the inner diameter side connecting the upstream portion along the radial direction and the downstream portion along the axial direction of the first premixed gas passage 42a is an elliptical arc as shown by a two-dot chain line in FIG. It is good also as a shape.
- the pilot burner 44 has been described as a burner that injects the premixed gas P2 into the combustion chamber 10. However, the pilot burner 44 separates the fuel F2 and the air A into the combustion chamber 10, respectively. It may be a diffusion combustion burner for injection.
- the combustion apparatus which concerns on this invention requires supply of high temperature gas, such as a boiler, not only a gas turbine engine. It can be applied to other devices.
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Abstract
Description
Claims (8)
- 内側に燃焼室を形成する燃焼筒と、
前記燃焼筒の頂部に配置されて、前記燃焼室に環状に燃料と空気との予混合気を噴射する予混合通路、および該予混合通路に燃料と空気を径方向内方に導入するラジアルスワーラを有するメインバーナと、
前記ラジアルスワーラにその入口側から燃料を噴射する燃料噴射管と、を備え、
前記ラジアルスワーラが、分割板によって軸線方向に分割された複数のスワーラ段を有する燃焼装置。 - 請求項1において、前記燃料筒を収容するハウジングをさらに備え、前記ハウジングと前記燃焼筒の周壁との間に、空気を前記燃焼室内の燃焼ガスの流動方向と逆方向に導く空気通路が形成されている燃焼装置。
- 請求項2において、前記予混合通路は、前記径方向に向く上流部と軸線方向に向く下流部とを有し、縦断面がL字形である燃焼装置。
- 請求項1において、前記燃料噴射管が、前記各スワーラ段に対応する複数の燃料噴射口を備えている燃焼装置。
- 請求項4において、前記燃料噴射管から供給される燃料流量を前記各スワーラ段ごとに設定可能な燃焼装置。
- 請求項5において、前記燃料噴射管の前記複数の燃料噴射口のうち少なくとも一部のものは、互いに異なる口径を有する燃焼装置。
- 請求項1において、前記分割板の径方向長さが予混合通路の上流部を形成する径方向に沿った直線部よりも短い燃焼装置。
- 内側に燃焼室を形成する燃焼筒と、前記燃焼筒の頂部に配置されて、前記燃焼室に環状に燃料と空気との予混合気を噴射する予混合通路、および該予混合通路に燃料と空気を径方向内方に導入するラジアルスワーラを有するメインバーナと、前記ラジアルスワーラにその入口側から燃料を噴射する燃料噴射管と、を備え、前記ラジアルスワーラが、分割板によって軸線方向に分割された複数のスワーラ段を有する燃焼装置の制御方法であって、
前記各スワーラ段ごとに供給する燃料の流量を制御することにより、前記メインバーナから前記燃焼室内に噴射される予混合気の径方向の燃料濃度分布を制御する燃焼装置の制御方法。
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EP09750388.2A EP2309188B1 (en) | 2008-05-23 | 2009-05-22 | Combustion device and control method thereof |
US12/993,233 US8555650B2 (en) | 2008-05-23 | 2009-05-22 | Combustion device for annular injection of a premixed gas and method for controlling the combustion device |
RU2010152687/06A RU2468295C2 (ru) | 2008-05-23 | 2009-05-22 | Устройство сгорания и способ управления устройством сгорания |
CA2724460A CA2724460C (en) | 2008-05-23 | 2009-05-22 | Combustion device and method for controlling combustion device |
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JP2008136068A JP5172468B2 (ja) | 2008-05-23 | 2008-05-23 | 燃焼装置および燃焼装置の制御方法 |
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WO2009038625A2 (en) * | 2007-09-14 | 2009-03-26 | Siemens Energy, Inc. | A multi-stage axial combustion system |
WO2009038625A3 (en) * | 2007-09-14 | 2010-05-06 | Siemens Energy, Inc. | A multi-stage axial combustion system |
US7886539B2 (en) | 2007-09-14 | 2011-02-15 | Siemens Energy, Inc. | Multi-stage axial combustion system |
JP2013178003A (ja) * | 2012-02-28 | 2013-09-09 | Ihi Corp | バーナ及びこのバーナを備えたガスタービン燃焼器 |
CN107076422A (zh) * | 2014-11-05 | 2017-08-18 | 川崎重工业株式会社 | 烧嘴、燃烧器以及燃气轮机 |
CN112325333A (zh) * | 2021-01-04 | 2021-02-05 | 成都裕鸢航空零部件制造有限公司 | 航空发动机油气混合方法及混合腔结构 |
CN113739153A (zh) * | 2021-09-03 | 2021-12-03 | 盛能工业科技(廊坊)有限公司 | 一种燃烧室喷嘴 |
Also Published As
Publication number | Publication date |
---|---|
US8555650B2 (en) | 2013-10-15 |
JP5172468B2 (ja) | 2013-03-27 |
EP2309188A4 (en) | 2016-03-23 |
US20110094233A1 (en) | 2011-04-28 |
RU2010152687A (ru) | 2012-06-27 |
CA2724460A1 (en) | 2009-11-26 |
JP2009281689A (ja) | 2009-12-03 |
EP2309188B1 (en) | 2019-07-03 |
EP2309188A1 (en) | 2011-04-13 |
CA2724460C (en) | 2013-03-19 |
RU2468295C2 (ru) | 2012-11-27 |
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