JP5410011B2 - 二重送り蛇行冷却ブレード - Google Patents
二重送り蛇行冷却ブレード Download PDFInfo
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- JP5410011B2 JP5410011B2 JP2007241452A JP2007241452A JP5410011B2 JP 5410011 B2 JP5410011 B2 JP 5410011B2 JP 2007241452 A JP2007241452 A JP 2007241452A JP 2007241452 A JP2007241452 A JP 2007241452A JP 5410011 B2 JP5410011 B2 JP 5410011B2
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- 238000001816 cooling Methods 0.000 title claims description 204
- 238000005192 partition Methods 0.000 claims description 22
- 239000000567 combustion gas Substances 0.000 claims description 15
- 239000007789 gas Substances 0.000 claims description 9
- 238000004891 communication Methods 0.000 claims description 6
- 239000012530 fluid Substances 0.000 claims description 6
- 238000000034 method Methods 0.000 claims description 3
- 230000007423 decrease Effects 0.000 claims description 2
- 230000001105 regulatory effect Effects 0.000 claims description 2
- 230000001174 ascending effect Effects 0.000 description 5
- 238000012423 maintenance Methods 0.000 description 4
- 230000000630 rising effect Effects 0.000 description 4
- 238000007796 conventional method Methods 0.000 description 3
- 238000007599 discharging Methods 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 229910000601 superalloy Inorganic materials 0.000 description 2
- 230000008646 thermal stress Effects 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000005219 brazing Methods 0.000 description 1
- 230000000295 complement effect Effects 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000284 extract Substances 0.000 description 1
- 238000000605 extraction Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 239000010409 thin film Substances 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
Images
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
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- 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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
Claims (8)
- タービンブレード(10)であって、
対応する前方衝突回路(1)で終端する前方蛇行冷却回路(2〜4)及び対応する後方衝突流路(8)で終端する後方蛇行冷却回路(5〜7)を具備し、各冷却回路は、その最終流路(2、7)に配分される入口流れより多くの入口流れを第1の流路(4、5)に配分するための2つの流量調整入口(54〜60)を有し、
前記タービンブレード(10)は、
前記蛇行冷却回路(2〜4)、(5〜7)及びそれらと協働する前記衝突流路(1、8)を規定するために、加圧側(22)とその反対側の吸引側(24)とを接合し且つ前縁部(26)とその反対側の後縁部(28)との間で翼弦方向に互いに離間して配置される複数の仕切り(40)を有する中空のエーロフォイル(14)と;
プラットフォーム(16)において前記エーロフォイル(14)に一体に接合され、前記蛇行冷却回路に別個に接合された4つの入口流路(44〜50)を含むダブテール(18)と;
前記4つの入口流路(44〜50)を被覆し且つ前記最終流路(2、7)に配分される流れより多くの流れを前記第1の流路(4、5)に配分するように前記ダブテール(18)に接合された流量調整板(52)と
を更に具備し、
前記エーロフォイルの先端部(32)は、前記前方蛇行冷却回路及び前記後方蛇行冷却回路(2〜7)を直接被覆するように前記先端部に凹部として形成された先端部フロア(42)を具備し;
前記4つの入口流路(44〜50)は、前記蛇行冷却回路より広い流れ面積を有し;
前記流量調整板(52)は、前記4つの入口流路(44〜50)より狭い流れ面積を有する第1の開口入口(54)、第2の開口入口(56)、第3の開口入口(58)及び第4の開口入口(60)を含み、通過する冷却流れ(34)を相応して流量調整する
ことを特徴とする、タービンブレード(10)。 - 前記入口流路は、
前記ダブテール(18)を貫通し、前記最終流路(2)において前記前方蛇行冷却回路に接合するように拡張する第1の入口流路(44)と;
前記ダブテール(18)を貫通し、前記第1の流路(4)において前記前方蛇行冷却回路に接合するように縮小する第2の入口流路(46)と;
前記ダブテール(18)を貫通し、前記第1の流路(5)において前記後方蛇行冷却回路に接合するように縮小する第3の入口流路(48)と;
前記ダブテール(18)を貫通し、前記最終流路(7)において前記後方蛇行冷却回路に接合するように拡張する第4の入口流路(50)とを具備する請求項1記載のブレード。 - 前記前方蛇行冷却回路(2〜4)は、前記プラットフォーム(16)において前記第2の入口流路(46)と流体連通する状態で始まり且つ前記先端部フロア(42)において第2の流路(3)に接合する第1の前方流れ屈曲部(62)で終端する第1の前方流路(4)を含み、前記第2の流路(3)が、前記プラットフォーム(16)において前記第1の入口流路(44)及び前記前方最終流路(2)に接合された第2の前方流れ屈曲部(64)で終端し;
前記後方蛇行冷却回路(5〜7)は、前記プラットフォーム(16)において前記第3の入口流路(48)と流体連通する状態で始まり且つ前記先端部フロア(42)において第2の後方流路(6)に接合する第1の後方流れ屈曲部(66)で終端する第1の後方流路(5)を含み、前記第2の後方流路(6)が、前記プラットフォーム(16)において前記第4の入口流路(50)及び前記後方最終流路(7)に接合された第2の後方流れ屈曲部(68)で終端する請求項2記載のブレード。 - 前記第1の入口流路(44)は前記第2の前方流れ屈曲部(64)で拡張し、前記第4の入口流路(50)は前記第2の後方流れ屈曲部(68)で拡張する請求項3記載のブレード。
- 前記第2の前方流路(3)及び前記前方最終流路(2)における前記第1の入口流路(44)は、いずれの流路よりも広い流れ面積を有し;
前記第2の後方流路(6)及び前記後方最終流路(7)における前記第4の入口流路(50)は、いずれの流路よりも広い流れ面積を有する請求項3記載のブレード。 - 前記前縁部(26)の衝突冷却のために、前記前方衝突流路(1)と前記前方最終流路(2)との間の前記仕切り(40)は前記前縁部の後に穴を有し;
前記後縁部(28)の衝突冷却のために、前記後方衝突流路(8)と前記後方最終流路(7)との間の前記仕切り(40)は前記後縁部の前に穴を有し;
前記第2の前方流路(3)と前記前方最終流路(2)との間の前記仕切り(40)には、前記先端部フロア(42)の付近にあるそれらの流路の間の前方抽気穴(72)を除いて穴が形成されず;
前記第2の後方流路(6)と前記後方最終流路(7)との間の前記仕切り(40)には、前記先端部フロア(42)の付近にあるそれらの流路の間の後方抽気穴(72)を除いて穴が形成されない請求項3記載のブレード。 - 前記先端部(32)の付近で前記エーロフォイル前縁部(26)を追加冷却するために、前記前方抽気穴(72)は前記第1の前方流れ屈曲部(62)の下方に配置され、前記先端部(32)の付近で前記エーロフォイル後縁部(28)を追加冷却するために、前記後方抽気穴(72)は前記第1の後方流れ屈曲部(66)に配置される請求項3記載のブレード。
- ガスタービンエンジン(12)において請求項3記載の前記ブレード(10)を冷却する方法において、
前記冷却流れ(34)の全流量を前記ブレード(10)へ搬送することと;
前記エーロフォイル(14)に沿って燃焼ガスが流れる間、前記前縁部(26)及び前記後縁部(28)に沿って前記エーロフォイルの温度を低下する一方で、前記エーロフォイル(14)の翼弦中央領域に沿って前記エーロフォイルの動作温度を上昇するために、前記冷却流れ(34)の一部を前記第2の入口流路(46)及び前記第3の入口流路(48)から前記第1の入口流路(44)及び前記第4の入口流路(50)へ方向転換するように前記全流量を流量調整することとから成る方法。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/602,137 US8591189B2 (en) | 2006-11-20 | 2006-11-20 | Bifeed serpentine cooled blade |
US11/602,137 | 2006-11-20 |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2008128234A JP2008128234A (ja) | 2008-06-05 |
JP5410011B2 true JP5410011B2 (ja) | 2014-02-05 |
Family
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Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2007241452A Active JP5410011B2 (ja) | 2006-11-20 | 2007-09-18 | 二重送り蛇行冷却ブレード |
Country Status (3)
Country | Link |
---|---|
US (1) | US8591189B2 (ja) |
EP (1) | EP1923537B1 (ja) |
JP (1) | JP5410011B2 (ja) |
Families Citing this family (59)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7726944B2 (en) * | 2006-09-20 | 2010-06-01 | United Technologies Corporation | Turbine blade with improved durability tip cap |
US20090060714A1 (en) * | 2007-08-30 | 2009-03-05 | General Electric Company | Multi-part cast turbine engine component having an internal cooling channel and method of forming a multi-part cast turbine engine component |
US8210814B2 (en) * | 2008-06-18 | 2012-07-03 | General Electric Company | Crossflow turbine airfoil |
FR2937372B1 (fr) * | 2008-10-22 | 2010-12-10 | Snecma | Aube de turbine equipee de moyens de reglage de son debit de fluide de refroidissement |
GB2468669C (en) * | 2009-03-17 | 2013-11-13 | Rolls Royce Plc | A flow discharge device |
US8025482B1 (en) * | 2009-04-04 | 2011-09-27 | Florida Turbine Technologies, Inc. | Turbine blade with dual serpentine cooling |
GB0915680D0 (en) | 2009-09-09 | 2009-10-07 | Rolls Royce Plc | Cooled aerofoil blade or vane |
US8535006B2 (en) | 2010-07-14 | 2013-09-17 | Siemens Energy, Inc. | Near-wall serpentine cooled turbine airfoil |
US9022736B2 (en) | 2011-02-15 | 2015-05-05 | Siemens Energy, Inc. | Integrated axial and tangential serpentine cooling circuit in a turbine airfoil |
US9017025B2 (en) | 2011-04-22 | 2015-04-28 | Siemens Energy, Inc. | Serpentine cooling circuit with T-shaped partitions in a turbine airfoil |
JP6002505B2 (ja) * | 2012-08-27 | 2016-10-05 | 三菱日立パワーシステムズ株式会社 | ガスタービン及びガスタービン翼、及びガスタービン翼の製造方法 |
FR2995342B1 (fr) * | 2012-09-13 | 2018-03-16 | Safran Aircraft Engines | Aube refroidie de turbine haute pression |
WO2014120565A1 (en) * | 2013-02-04 | 2014-08-07 | United Technologies Corporation | Bell mouth inlet for turbine blade |
WO2014164888A1 (en) * | 2013-03-11 | 2014-10-09 | United Technologies Corporation | Low pressure loss cooled blade |
US9551226B2 (en) | 2013-10-23 | 2017-01-24 | General Electric Company | Turbine bucket with endwall contour and airfoil profile |
US9528379B2 (en) * | 2013-10-23 | 2016-12-27 | General Electric Company | Turbine bucket having serpentine core |
US9347320B2 (en) | 2013-10-23 | 2016-05-24 | General Electric Company | Turbine bucket profile yielding improved throat |
US9376927B2 (en) | 2013-10-23 | 2016-06-28 | General Electric Company | Turbine nozzle having non-axisymmetric endwall contour (EWC) |
US9670784B2 (en) | 2013-10-23 | 2017-06-06 | General Electric Company | Turbine bucket base having serpentine cooling passage with leading edge cooling |
US9797258B2 (en) | 2013-10-23 | 2017-10-24 | General Electric Company | Turbine bucket including cooling passage with turn |
US9638041B2 (en) | 2013-10-23 | 2017-05-02 | General Electric Company | Turbine bucket having non-axisymmetric base contour |
US9726023B2 (en) * | 2015-01-26 | 2017-08-08 | United Technologies Corporation | Airfoil support and cooling scheme |
US10156157B2 (en) * | 2015-02-13 | 2018-12-18 | United Technologies Corporation | S-shaped trip strips in internally cooled components |
EP3059394B1 (en) * | 2015-02-18 | 2019-10-30 | Ansaldo Energia Switzerland AG | Turbine blade and set of turbine blades |
US10107108B2 (en) | 2015-04-29 | 2018-10-23 | General Electric Company | Rotor blade having a flared tip |
FR3037829B1 (fr) * | 2015-06-29 | 2017-07-21 | Snecma | Noyau pour le moulage d'une aube ayant des cavites superposees et comprenant un trou de depoussierage traversant une cavite de part en part |
JP6025941B1 (ja) * | 2015-08-25 | 2016-11-16 | 三菱日立パワーシステムズ株式会社 | タービン動翼、及び、ガスタービン |
US10060269B2 (en) | 2015-12-21 | 2018-08-28 | General Electric Company | Cooling circuits for a multi-wall blade |
US9932838B2 (en) | 2015-12-21 | 2018-04-03 | General Electric Company | Cooling circuit for a multi-wall blade |
US9976425B2 (en) | 2015-12-21 | 2018-05-22 | General Electric Company | Cooling circuit for a multi-wall blade |
US9926788B2 (en) | 2015-12-21 | 2018-03-27 | General Electric Company | Cooling circuit for a multi-wall blade |
US10119405B2 (en) | 2015-12-21 | 2018-11-06 | General Electric Company | Cooling circuit for a multi-wall blade |
US10030526B2 (en) * | 2015-12-21 | 2018-07-24 | General Electric Company | Platform core feed for a multi-wall blade |
US10053989B2 (en) | 2015-12-21 | 2018-08-21 | General Electric Company | Cooling circuit for a multi-wall blade |
US10808547B2 (en) * | 2016-02-08 | 2020-10-20 | General Electric Company | Turbine engine airfoil with cooling |
US20170234447A1 (en) * | 2016-02-12 | 2017-08-17 | United Technologies Corporation | Methods and systems for modulating airflow |
FR3052183B1 (fr) * | 2016-06-02 | 2020-03-06 | Safran Aircraft Engines | Aube de turbine comprenant une portion d'admission d'air de refroidissement incluant un element helicoidal pour faire tourbillonner l'air de refroidissement |
US10494930B2 (en) * | 2016-06-16 | 2019-12-03 | General Electric Company | Ceramic matrix composite component cooling |
US10208608B2 (en) | 2016-08-18 | 2019-02-19 | General Electric Company | Cooling circuit for a multi-wall blade |
US10227877B2 (en) | 2016-08-18 | 2019-03-12 | General Electric Company | Cooling circuit for a multi-wall blade |
US10267162B2 (en) | 2016-08-18 | 2019-04-23 | General Electric Company | Platform core feed for a multi-wall blade |
US10208607B2 (en) | 2016-08-18 | 2019-02-19 | General Electric Company | Cooling circuit for a multi-wall blade |
US10221696B2 (en) | 2016-08-18 | 2019-03-05 | General Electric Company | Cooling circuit for a multi-wall blade |
US10443404B2 (en) * | 2017-03-24 | 2019-10-15 | DOOSAN Heavy Industries Construction Co., LTD | Film and impingement platform cooling for serpentine cooled turbine blades |
US11021967B2 (en) * | 2017-04-03 | 2021-06-01 | General Electric Company | Turbine engine component with a core tie hole |
US10513947B2 (en) | 2017-06-05 | 2019-12-24 | United Technologies Corporation | Adjustable flow split platform cooling for gas turbine engine |
US10815791B2 (en) * | 2017-12-13 | 2020-10-27 | Solar Turbines Incorporated | Turbine blade cooling system with upper turning vane bank |
KR102113682B1 (ko) * | 2018-10-01 | 2020-05-21 | 두산중공업 주식회사 | 터빈 블레이드 |
KR102152415B1 (ko) * | 2018-10-16 | 2020-09-04 | 두산중공업 주식회사 | 터빈 베인 및 터빈 블레이드 및 이를 포함하는 가스 터빈 |
US11512597B2 (en) * | 2018-11-09 | 2022-11-29 | Raytheon Technologies Corporation | Airfoil with cavity lobe adjacent cooling passage network |
US10731478B2 (en) * | 2018-12-12 | 2020-08-04 | Solar Turbines Incorporated | Turbine blade with a coupled serpentine channel |
KR102161765B1 (ko) * | 2019-02-22 | 2020-10-05 | 두산중공업 주식회사 | 터빈용 에어포일, 이를 포함하는 터빈 |
US10895168B2 (en) | 2019-05-30 | 2021-01-19 | Solar Turbines Incorporated | Turbine blade with serpentine channels |
KR102307577B1 (ko) | 2020-03-10 | 2021-10-01 | 두산중공업 주식회사 | 터빈기관용 터빈 날개의 내부 냉각구조 |
KR102294770B1 (ko) | 2020-03-13 | 2021-08-27 | 두산중공업 주식회사 | 터빈기관용 터빈 날개의 내부냉각용 미터링 플레이트 |
KR102456633B1 (ko) | 2020-10-23 | 2022-10-18 | 두산에너빌리티 주식회사 | 터빈 블레이드의 트레일링 에지 냉각 구조 |
EP4112881A1 (en) * | 2021-07-01 | 2023-01-04 | Doosan Enerbility Co., Ltd. | Blade for a turo machine, blade assembly, gas turbine, and method for manufacturing a blade for a turbo machine |
US11840941B2 (en) | 2022-02-16 | 2023-12-12 | General Electric Company | Engine component with cooling architecture |
WO2023223741A1 (ja) * | 2022-05-20 | 2023-11-23 | 三菱重工業株式会社 | タービン翼及びガスタービン |
Family Cites Families (29)
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 |
US4073599A (en) | 1976-08-26 | 1978-02-14 | Westinghouse Electric Corporation | Hollow turbine blade tip closure |
US4775296A (en) | 1981-12-28 | 1988-10-04 | United Technologies Corporation | Coolable airfoil for a rotary machine |
JPS58170801A (ja) | 1982-03-31 | 1983-10-07 | Toshiba Corp | タ−ビンの翼 |
JPS62228603A (ja) | 1986-03-31 | 1987-10-07 | Toshiba Corp | ガスタ−ビンの翼 |
JP3006174B2 (ja) | 1991-07-04 | 2000-02-07 | 株式会社日立製作所 | 内部に冷却通路を有する部材 |
DE69328439T2 (de) | 1992-11-24 | 2000-12-14 | United Technologies Corp | Kühlbare schaufelsstruktur |
US5403159A (en) | 1992-11-30 | 1995-04-04 | United Technoligies Corporation | Coolable airfoil structure |
JP2645209B2 (ja) * | 1993-08-16 | 1997-08-25 | 株式会社東芝 | タービンの翼 |
JP3137527B2 (ja) | 1994-04-21 | 2001-02-26 | 三菱重工業株式会社 | ガスタービン動翼チップ冷却装置 |
JP3642537B2 (ja) * | 1995-03-23 | 2005-04-27 | 株式会社東芝 | ガスタービン冷却翼 |
US5902093A (en) | 1997-08-22 | 1999-05-11 | General Electric Company | Crack arresting rotor blade |
US5967752A (en) | 1997-12-31 | 1999-10-19 | General Electric Company | Slant-tier turbine airfoil |
US6126396A (en) * | 1998-12-09 | 2000-10-03 | General Electric Company | AFT flowing serpentine airfoil cooling circuit with side wall impingement cooling chambers |
US6340047B1 (en) | 1999-03-22 | 2002-01-22 | General Electric Company | Core tied cast airfoil |
JP2001012205A (ja) | 1999-06-29 | 2001-01-16 | Mitsubishi Heavy Ind Ltd | ガスタービン動翼冷却流量調整構造 |
JP2001234703A (ja) * | 2000-02-23 | 2001-08-31 | Mitsubishi Heavy Ind Ltd | ガスタービン動翼 |
CA2334071C (en) | 2000-02-23 | 2005-05-24 | Mitsubishi Heavy Industries, Ltd. | Gas turbine moving blade |
US6491496B2 (en) * | 2001-02-23 | 2002-12-10 | General Electric Company | Turbine airfoil with metering plates for refresher holes |
US6607356B2 (en) * | 2002-01-11 | 2003-08-19 | General Electric Company | Crossover cooled airfoil trailing edge |
JP4137508B2 (ja) | 2002-05-02 | 2008-08-20 | ゼネラル・エレクトリック・カンパニイ | リフレッシュ用孔のメータリング板を備えるタービン翼形部 |
DE60217071T2 (de) | 2002-05-09 | 2007-07-12 | General Electric Co. | Kühlkonfiguration für ein Turbomaschinenschaufelblatt |
US6832889B1 (en) | 2003-07-09 | 2004-12-21 | General Electric Company | Integrated bridge turbine blade |
JP4205553B2 (ja) * | 2003-11-06 | 2009-01-07 | エルピーダメモリ株式会社 | メモリモジュール及びメモリシステム |
DE102004037444A1 (de) | 2004-03-30 | 2005-10-20 | Alstom Technology Ltd Baden | Vorrichtung zur Kühlluftbeaufschlagung einer rotierenden Komponente, insbesondere für eine Laufschaufel in einer Rotationsmaschine |
US7137780B2 (en) | 2004-06-17 | 2006-11-21 | Siemens Power Generation, Inc. | Internal cooling system for a turbine blade |
US7097419B2 (en) * | 2004-07-26 | 2006-08-29 | General Electric Company | Common tip chamber blade |
JP4435676B2 (ja) | 2004-12-28 | 2010-03-24 | 高圧ガス保安協会 | 圧力調整器 |
JP4782065B2 (ja) | 2007-04-13 | 2011-09-28 | 三笠産業株式会社 | スチレン−(メタ)アクリル樹脂の分解方法 |
-
2006
- 2006-11-20 US US11/602,137 patent/US8591189B2/en active Active
-
2007
- 2007-09-13 EP EP07116280.4A patent/EP1923537B1/en not_active Revoked
- 2007-09-18 JP JP2007241452A patent/JP5410011B2/ja active Active
Also Published As
Publication number | Publication date |
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US8591189B2 (en) | 2013-11-26 |
EP1923537A3 (en) | 2012-11-28 |
EP1923537B1 (en) | 2016-07-13 |
US20080118366A1 (en) | 2008-05-22 |
JP2008128234A (ja) | 2008-06-05 |
EP1923537A2 (en) | 2008-05-21 |
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