JP2008163942A - 後縁スロット流量を減少させた翼形及び翼形の製造方法 - Google Patents
後縁スロット流量を減少させた翼形及び翼形の製造方法 Download PDFInfo
- Publication number
- JP2008163942A JP2008163942A JP2007333394A JP2007333394A JP2008163942A JP 2008163942 A JP2008163942 A JP 2008163942A JP 2007333394 A JP2007333394 A JP 2007333394A JP 2007333394 A JP2007333394 A JP 2007333394A JP 2008163942 A JP2008163942 A JP 2008163942A
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- Prior art keywords
- component
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- insert
- trailing edge
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- 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.)
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/10—Cores; Manufacture or installation of cores
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/21—Manufacture essentially without removing material by casting
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
- F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge of a stator vane
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/202—Heat transfer, e.g. cooling by film cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/221—Improvement of heat transfer
- F05D2260/2212—Improvement of heat transfer by creating turbulence
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/221—Improvement of heat transfer
- F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/221—Improvement of heat transfer
- F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
- F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/49336—Blade making
- Y10T29/49339—Hollow blade
- Y10T29/49341—Hollow blade with cooling passage
- Y10T29/49343—Passage contains tubular insert
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Molds, Cores, And Manufacturing Methods Thereof (AREA)
Abstract
【解決手段】前縁105及び後縁107を有する胴部を備える翼形構成部品は、内部冷却通路201と、内部冷却通路201と連通状態にある細長開口211とを含む。開口211は、鋳造中に構造安定性を与える形状で構成されて、効率的な構成部品動作を実現するために開口211を通る空気流を十分に絞る断面を有する。鋳造インサートは、外縁部突起と、インサートの周囲に鋳造された時の開口の形状に対応するウェブ部分とを有し、鋳造インサートの周囲に翼形構成部品を鋳造した後、開口211を有する構成部品を完成するためにインサートは除去される。
【選択図】図2
Description
100 動翼(翼形構成部品)
101 ガス
103 翼形(エーロフォイル)
104 翼根(ルート)
105 前縁
106 翼端
107 後縁
図2
201 通路
203 回路
204 冷却流体
205 入口開口
207 前縁開口
209 翼端開口
211 後縁開口
図3〜図4
図5
501 セラミックコア
503 インサート突起
505 部分
図6
601 外縁部突起
603 ウェブ部分
図7
701 幅
703 長さ
図8
801 第1寸法
803 第2寸法
805 第1端部
807 第2端部
809 弦
Claims (10)
- 翼形構成部品(100)であって、
前縁(105)及び後縁(107)を有する胴部と、
内部冷却通路(201)と、
内部冷却通路(201)と連通状態にある細長開口(211)と
を備え、前記開口(211)は、鋳造中に構造安定性を与える形状で構成され且つ該開口(211)を通る冷却流体流を十分に絞る断面を有し、効率的な構成部品動作を実現する、翼形構成部品。 - 構成部品(100)であって、開口(211)は、第1寸法(801)及び第2寸法(803、804)を有する細長形状を有し、第1寸法(801)は、開口(211)の対向端部に配置された第1端部(805)及び第2端部(807)を有し、
第2寸法(803、804)は第1寸法(801)に対して垂直に配置され、さらに、第1端部(805)及び第2端部(807)間に位置する少なくとも1つの最小値(803)及び少なくとも1つの最大値(804)をさらに含む、請求項1に記載の構成部品。 - 構成部品(100)であって、少なくとも1つの最小値(803)は最大値(804)の90%未満である、請求項2に記載の構成部品。
- 構成部品(100)であって、少なくとも1つの最小値(803)は最大値(804)の80%未満である、請求項3に記載の構成部品。
- 構成部品(100)であって、開口は後縁(107)に隣接して配置される、請求項1に記載の構成部品。
- 構成部品(100)であって、タービン動翼又は静翼である、請求項1に記載の構成部品。
- 構成部品(100)であって、構成部品(100)はタービンシュラウドである、請求項1に記載の構成部品。
- 構成部品(100)であって、開口は構成部品(100)を鋳造インサートの周囲に鋳造することによって形成され、鋳造インサートは、
セラミックインサート胴部(501)と、
胴部から延出して、ウェブ部分(603)によって接続された外縁部突起(601)を有するコアインサート突起503であって、外縁部突起(601)は、ウェブ部分(603)に沿った厚さがウェブ部分(603)の厚さより大きい、コアインサート突起(503)と
を有しており、
コアインサート突起(503)及びウェブ部分(603)は、構成部品(100)をインサートの周囲に鋳造できるようにするのに十分な構造安定性を有する、請求項1に記載の構成部品。 - ウェブ部分(603)は、ウェブ部分(603)に沿った厚さが外縁部突起(601)の厚さの90%未満である、請求項8に記載の鋳造インサート。
- ウェブ部分(603)は、ウェブ部分(603)に沿った厚さが外縁部突起(601)の厚さの80%未満である、請求項9に記載の鋳造インサート。
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/616,176 US20100034662A1 (en) | 2006-12-26 | 2006-12-26 | Cooled airfoil and method for making an airfoil having reduced trail edge slot flow |
Publications (1)
Publication Number | Publication Date |
---|---|
JP2008163942A true JP2008163942A (ja) | 2008-07-17 |
Family
ID=38984139
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2007333394A Pending JP2008163942A (ja) | 2006-12-26 | 2007-12-26 | 後縁スロット流量を減少させた翼形及び翼形の製造方法 |
Country Status (5)
Country | Link |
---|---|
US (1) | US20100034662A1 (ja) |
EP (1) | EP1942251B1 (ja) |
JP (1) | JP2008163942A (ja) |
CA (1) | CA2614031A1 (ja) |
RU (1) | RU2007148893A (ja) |
Cited By (1)
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---|---|---|---|---|
JP2013181538A (ja) * | 2012-03-01 | 2013-09-12 | General Electric Co <Ge> | 輪郭形成した屈曲部を有するコアキャビティを備えたタービンバケット |
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Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
IT1394713B1 (it) * | 2009-06-04 | 2012-07-13 | Ansaldo Energia Spa | Pala di turbina |
US8371814B2 (en) | 2009-06-24 | 2013-02-12 | Honeywell International Inc. | Turbine engine components |
US8529193B2 (en) | 2009-11-25 | 2013-09-10 | Honeywell International Inc. | Gas turbine engine components with improved film cooling |
US8628293B2 (en) | 2010-06-17 | 2014-01-14 | Honeywell International Inc. | Gas turbine engine components with cooling hole trenches |
US9650900B2 (en) | 2012-05-07 | 2017-05-16 | Honeywell International Inc. | Gas turbine engine components with film cooling holes having cylindrical to multi-lobe configurations |
US10107107B2 (en) * | 2012-06-28 | 2018-10-23 | United Technologies Corporation | Gas turbine engine component with discharge slot having oval geometry |
US10113433B2 (en) | 2012-10-04 | 2018-10-30 | Honeywell International Inc. | Gas turbine engine components with lateral and forward sweep film cooling holes |
WO2014130244A1 (en) * | 2013-02-19 | 2014-08-28 | United Technologies Corporation | Gas turbine engine airfoil platform cooling passage and core |
FR3025444B1 (fr) * | 2014-09-04 | 2016-09-23 | Snecma | Procede de production d'un noyau ceramique |
FR3034128B1 (fr) * | 2015-03-23 | 2017-04-14 | Snecma | Noyau ceramique pour aube de turbine multi-cavites |
US11021965B2 (en) | 2016-05-19 | 2021-06-01 | Honeywell International Inc. | Engine components with cooling holes having tailored metering and diffuser portions |
EP3415250A1 (en) * | 2017-06-15 | 2018-12-19 | Siemens Aktiengesellschaft | Casting core with crossover bridge |
DE102019125779B4 (de) * | 2019-09-25 | 2024-03-21 | Man Energy Solutions Se | Schaufel einer Strömungsmaschine |
DE102020207646A1 (de) * | 2020-06-22 | 2021-12-23 | Siemens Aktiengesellschaft | Turbinenschaufel und Verfahren zum Bearbeiten einer solchen |
CN113623014B (zh) * | 2021-07-22 | 2023-04-14 | 西安交通大学 | 一种燃气轮机透平叶片-轮盘联合冷却结构 |
Citations (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS60216022A (ja) * | 1984-02-15 | 1985-10-29 | ナシヨナル・エアロノ−テイツクス・アンド・スペ−ス・アドミニストレイシヨン | 冷気膜流による表面の冷却装置 |
JPS61155601A (ja) * | 1984-12-21 | 1986-07-15 | ユナイテツド・テクノロジ−ズ・コ−ポレイシヨン | ガスタ−ビンエンジン |
EP0375175A1 (en) * | 1988-12-23 | 1990-06-27 | ROLLS-ROYCE plc | Cooled turbomachinery components |
US5651662A (en) * | 1992-10-29 | 1997-07-29 | General Electric Company | Film cooled wall |
JPH1089005A (ja) * | 1996-09-18 | 1998-04-07 | Toshiba Corp | 高温部材冷却装置 |
JPH1162507A (ja) * | 1997-08-11 | 1999-03-05 | Ishikawajima Harima Heavy Ind Co Ltd | フィルム冷却孔 |
JP2000246392A (ja) * | 1999-03-02 | 2000-09-12 | Hitachi Metals Ltd | セラミック中子を有するワックス模型の成型方法 |
JP2001012204A (ja) * | 1999-06-30 | 2001-01-16 | Toshiba Corp | ガスタービン翼 |
JP2001227302A (ja) * | 2000-02-18 | 2001-08-24 | General Electric Co <Ge> | 後縁ブロックが冷却されるセラミックタービン翼形部 |
JP2002515338A (ja) * | 1998-05-14 | 2002-05-28 | シーメンス アクチエンゲゼルシヤフト | 金属中空体の製造方法及び装置 |
JP2003120204A (ja) * | 2001-08-30 | 2003-04-23 | General Electric Co <Ge> | ガスタービンエンジン用のタービン翼形部 |
JP2003201805A (ja) * | 2001-12-12 | 2003-07-18 | General Electric Co <Ge> | ガスタービンエンジンのタービンノズル用の翼形部及びその製作方法 |
Family Cites Families (19)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3706508A (en) * | 1971-04-16 | 1972-12-19 | Sean Lingwood | Transpiration cooled turbine blade with metered coolant flow |
US4236870A (en) * | 1977-12-27 | 1980-12-02 | United Technologies Corporation | Turbine blade |
US4626169A (en) * | 1983-12-13 | 1986-12-02 | United Technologies Corporation | Seal means for a blade attachment slot of a rotor assembly |
US4582467A (en) * | 1983-12-22 | 1986-04-15 | United Technologies Corporation | Two stage rotor assembly with improved coolant flow |
US4820123A (en) * | 1988-04-25 | 1989-04-11 | United Technologies Corporation | Dirt removal means for air cooled blades |
GB2227965B (en) * | 1988-10-12 | 1993-02-10 | Rolls Royce Plc | Apparatus for drilling a shaped hole in a workpiece |
US6092982A (en) * | 1996-05-28 | 2000-07-25 | Kabushiki Kaisha Toshiba | Cooling system for a main body used in a gas stream |
US5820774A (en) * | 1996-10-28 | 1998-10-13 | United Technologies Corporation | Ceramic core for casting a turbine blade |
US6059529A (en) * | 1998-03-16 | 2000-05-09 | Siemens Westinghouse Power Corporation | Turbine blade assembly with cooling air handling device |
US6126396A (en) * | 1998-12-09 | 2000-10-03 | General Electric Company | AFT flowing serpentine airfoil cooling circuit with side wall impingement cooling chambers |
US6176677B1 (en) * | 1999-05-19 | 2001-01-23 | Pratt & Whitney Canada Corp. | Device for controlling air flow in a turbine blade |
US6186741B1 (en) * | 1999-07-22 | 2001-02-13 | General Electric Company | Airfoil component having internal cooling and method of cooling |
US6390774B1 (en) * | 2000-02-02 | 2002-05-21 | General Electric Company | Gas turbine bucket cooling circuit and related process |
US6491496B2 (en) * | 2001-02-23 | 2002-12-10 | General Electric Company | Turbine airfoil with metering plates for refresher holes |
US6416275B1 (en) * | 2001-05-30 | 2002-07-09 | Gary Michael Itzel | Recessed impingement insert metering plate for gas turbine nozzles |
US6933459B2 (en) * | 2003-02-03 | 2005-08-23 | General Electric Company | Methods and apparatus for fabricating a turbine engine blade |
US6974306B2 (en) * | 2003-07-28 | 2005-12-13 | Pratt & Whitney Canada Corp. | Blade inlet cooling flow deflector apparatus and method |
US7328580B2 (en) * | 2004-06-23 | 2008-02-12 | General Electric Company | Chevron film cooled wall |
US7510376B2 (en) * | 2005-08-25 | 2009-03-31 | General Electric Company | Skewed tip hole turbine blade |
-
2006
- 2006-12-26 US US11/616,176 patent/US20100034662A1/en not_active Abandoned
-
2007
- 2007-12-13 CA CA002614031A patent/CA2614031A1/en not_active Abandoned
- 2007-12-18 EP EP07123432A patent/EP1942251B1/en not_active Expired - Fee Related
- 2007-12-25 RU RU2007148893/06A patent/RU2007148893A/ru unknown
- 2007-12-26 JP JP2007333394A patent/JP2008163942A/ja active Pending
Patent Citations (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS60216022A (ja) * | 1984-02-15 | 1985-10-29 | ナシヨナル・エアロノ−テイツクス・アンド・スペ−ス・アドミニストレイシヨン | 冷気膜流による表面の冷却装置 |
JPS61155601A (ja) * | 1984-12-21 | 1986-07-15 | ユナイテツド・テクノロジ−ズ・コ−ポレイシヨン | ガスタ−ビンエンジン |
EP0375175A1 (en) * | 1988-12-23 | 1990-06-27 | ROLLS-ROYCE plc | Cooled turbomachinery components |
US5651662A (en) * | 1992-10-29 | 1997-07-29 | General Electric Company | Film cooled wall |
JPH1089005A (ja) * | 1996-09-18 | 1998-04-07 | Toshiba Corp | 高温部材冷却装置 |
JPH1162507A (ja) * | 1997-08-11 | 1999-03-05 | Ishikawajima Harima Heavy Ind Co Ltd | フィルム冷却孔 |
JP2002515338A (ja) * | 1998-05-14 | 2002-05-28 | シーメンス アクチエンゲゼルシヤフト | 金属中空体の製造方法及び装置 |
JP2000246392A (ja) * | 1999-03-02 | 2000-09-12 | Hitachi Metals Ltd | セラミック中子を有するワックス模型の成型方法 |
JP2001012204A (ja) * | 1999-06-30 | 2001-01-16 | Toshiba Corp | ガスタービン翼 |
JP2001227302A (ja) * | 2000-02-18 | 2001-08-24 | General Electric Co <Ge> | 後縁ブロックが冷却されるセラミックタービン翼形部 |
JP2003120204A (ja) * | 2001-08-30 | 2003-04-23 | General Electric Co <Ge> | ガスタービンエンジン用のタービン翼形部 |
JP2003201805A (ja) * | 2001-12-12 | 2003-07-18 | General Electric Co <Ge> | ガスタービンエンジンのタービンノズル用の翼形部及びその製作方法 |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2013181538A (ja) * | 2012-03-01 | 2013-09-12 | General Electric Co <Ge> | 輪郭形成した屈曲部を有するコアキャビティを備えたタービンバケット |
Also Published As
Publication number | Publication date |
---|---|
US20100034662A1 (en) | 2010-02-11 |
RU2007148893A (ru) | 2009-06-27 |
EP1942251A2 (en) | 2008-07-09 |
CA2614031A1 (en) | 2008-06-26 |
EP1942251B1 (en) | 2012-04-11 |
EP1942251A3 (en) | 2010-09-08 |
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