EP1400698A1 - Maítrise de la position axiale d'une aube de soufflante - Google Patents
Maítrise de la position axiale d'une aube de soufflante Download PDFInfo
- Publication number
- EP1400698A1 EP1400698A1 EP03292280A EP03292280A EP1400698A1 EP 1400698 A1 EP1400698 A1 EP 1400698A1 EP 03292280 A EP03292280 A EP 03292280A EP 03292280 A EP03292280 A EP 03292280A EP 1400698 A1 EP1400698 A1 EP 1400698A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blade
- upstream
- disk
- blades
- flange
- 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.)
- Granted
Links
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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/32—Locking, e.g. by final locking blades or keys
- F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor
-
- 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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
- F04D29/322—Blade mountings
-
- 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
- F05D2230/60—Assembly methods
- F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
-
- 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
- F05D2260/30—Retaining components in desired mutual position
-
- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/40—Organic materials
- F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
Definitions
- the invention relates to a control system of the position axial of the removable vanes of a blower of the turbojet engine.
- a fan rotor having a disk whose rim has a plurality of grooves substantially axial and regularly distributed angularly, a pluralities of removable vanes that extend radially outward to the periphery of said disk, each blade having a dawn foot housing in a groove, a flange downstream secured to said disk and against which the downstream faces of the blade roots are in abutment, and an upstream flange removable integral with said disk and for retaining the blade roots in the grooves.
- the upstream face refers to the directed face towards the front of the engine and the downstream face designates that directed towards the rear.
- the upstream flange of a fan rotor is generally removable to allow the replacement of a blade in case of damage. This can happen if foreign bodies are swallowed, such as particularly during the take-off and approach phases of the aircraft equipped with turbojets.
- US 4,033,705 discloses an axial retention system of vanes which has at each end of a blade root a tenon which cooperates with two oblique mortises formed in the rim of the disc of part and else of the groove receiving this foot of dawn.
- the studs provided on each disc face are retained radially by a ring secured to the disc.
- This document provides between each end face of the foot dawn and adjacent tenon a sheet forming spring whose role is to immobilize the tenon radially when assembling the blades, before the setting up and fixing the retaining ring. These springs create a mounting game at each end of dawn as this is shown on Figure 7 of this document, which is not controlled.
- US 5,282,720 provides for interposing between the retaining flanges and the ends of the blade roots, honeycomb elements intended for to absorb some of the energy if you eat birds. During ingestion, the honeycomb is gradually deformed and thus dissipates a part of the energy. Honeycomb elements must retain their integrity when mounting the flanges, so there is inevitably a axial clearance after assembly, and random axial displacement is possible in operation of the blower.
- the object of the invention is to propose a fan rotor such described in the introduction in which the axial position of the blades is controlled by a simple and inexpensive device, without creating a problem for the assembly and disassembly of the blades in case of repair possible.
- the flange upstream is equipped on its downstream face with elastic means intended to on the upstream faces of the blade roots, after assembly, sufficient efforts to prevent axial displacement of the blades during operation normal engine.
- the fan rotor further comprises a shim interposed between each blade root and the bottom of the groove corresponding, this wedge comprising a radial heel bearing against the upstream face of said blade root, the elastic means are advantageously bearing against said heels.
- Figure 1 shows an X-axis fan rotor 1 which has a disc 2 and a plurality of blades 3 regularly spaced angularly around the X axis which extend radially outwards at the periphery of the disc 2.
- Each of the blades 3 has a foot blade 4 which is retained in a groove or cell 5 substantially axial formed in the rim of the disk 2.
- the blade roots 4 have a shape in dovetail, and the grooves 5 have a complementary shape. Under the action of the centrifugal forces, when the fan is in operation, the blade roots 4 are retained in the grooves 5 by the radially outer walls of these grooves 5.
- a shim 6 is disposed between the base of each blade root 4 and the bottom of the groove 5.
- This shim 6 comprises, on the side of the upstream face 7 of the disc 2, a heel 8 which bears against the upstream face 9 of the foot 4 of the dawn 3.
- the role of the hold 6 is to prevent the dawn 3 from falling into the groove 5, when stopping the blower and cash a portion of the energy during a shock on the blade of the dawn as a result of the ingestion of a foreign body for example or the rupture of a neighboring dawn.
- downstream face 10 of the disk 2 On the downstream face 10 of the disk 2 is fixed a downstream flange, no shown in the drawings, against which the feet 4 of the blades 3 are in stop.
- An upstream flange 12 is also provided on the upstream face 7 of the disk 2, whose role is to prevent the feet 4 of the blades 3 of to escape from the grooves 5 by sliding after mounting the rotor 1.
- This upstream flange 12 is fixed on flanges of the disc 2 by screws, so that to allow its dismantling, in case of need of replacement of a dawn 3.
- the upstream flange 12 has in front of each dawn foot 4 an orifice 15 which holds the drum 16 of a pin 17 in elastomer, this pin 17 having a head 18 of larger diameter than that of the orifice 15, and having a thickness at least equal to the set J.
- the head 18 of the pin 17 is disposed on the downstream face 13 of the upstream flange 12, and this head 18 is compressed between the downstream face 13 of the upstream flange 12 and the upstream face of the heel 8 of the hold 6.
- the pin 17 thus exerts elastic forces on the heel 8 in an axial direction.
- the heel 8 is in support against the dawn foot 4 adjacent, it is permanently urged to the downstream flange, against which he is in abutment.
- This simple arrangement allows you to control the axial play of the blades 3 and to prevent random axial displacement of the blades 3.
- FIG. 4a and 4b show in perspective views of the pawn 17 and FIG. 5 shows in perspective the downstream face 13 of the upstream flange 12.
- the pins 17 are obviously mounted on the upstream flange 12 before mounting it on disk 2.
- Reference 20 designates an orifice formed in the upstream flange 12 and serving for fixing this last on flanges of disc 2 by means of screws. The tightening of these screws exerts on the heads 18 of the pins 17, a sufficient compressive force to prevent further axial displacement of the blades 3, depending the difference between the thicknesses of the heads 18 at rest and the mounting clearance J of origin. This compression effort may vary from one blade to another according to the manufacturing tolerances of blades 3 and pins 17.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
- la figure 1 est une coupe schématique d'un rotor de soufflante ;
- la figure 2 est une vue détaillée de la disposition du flasque amont et d'une aube, qui montre le jeu de montage ;
- les figures 4a et 4b sont des vues en perspective d'un pion ; et
- la figure 5 montre en perspective la face aval du flasque amont équipé de ses pions.
Claims (4)
- Rotor de soufflante comportant un disque (2) dont la jante comporte une pluralité de rainures (5) sensiblement axiales et régulièrement réparties angulairement, une pluralité d'aubes (3) amovibles qui s'étendent radialement vers l'extérieur à la périphérie dudit disque (2), chaque aube (3) comportant un pied d'aube (4) logeant dans une rainure (5), un flasque aval solidaire dudit disque (2) et contre lequel les faces aval des pieds d'aube sont en butée, et un flasque amont (12) amovible solidaire dudit disque (2) et destiné à retenir les pieds d'aube (4) dans les rainures (5),
caractérisé par le fait que le flasque amont (12) est équipé sur sa face aval (13) de moyens élastiques (17) destinés à exercer sur les faces amont des pieds d'aube, après montage, des efforts suffisants pour empêcher tout déplacement axial des aubes (3) lors du fonctionnement normal du moteur. - Rotor de soufflante selon la revendication 1, caractérisé par le fait qu'il est prévu des moyens élastiques (17) propres à chaque pied d'aube (4).
- Rotor de soufflante selon la revendication 2, caractérisé par le fait que les moyens élastiques propres à chaque pied d'aube (4) sont constitués par un pion (17) en élastomère retenu dans un orifice (15) ménagé dans le flasque amont (12).
- Rotor de soufflante selon l'une quelconque des revendications 1 à 3, caractérisé par le fait qu'il comporte en outre une cale (6) interposée entre chaque pied d'aube (4) et le fond de la rainure (5) correspondante, cette cale (6) comportant un talon (8) radial en appui contre la face amont (9) dudit pied d'aube (4), et par le fait que les moyens élastiques sont en appui contre lesdits talons (8).
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0211539A FR2844562B1 (fr) | 2002-09-18 | 2002-09-18 | Maitrise de la position axiale d'une aube de rotor de soufflante |
FR0211539 | 2002-09-18 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1400698A1 true EP1400698A1 (fr) | 2004-03-24 |
EP1400698B1 EP1400698B1 (fr) | 2008-09-03 |
Family
ID=31897464
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP03292280A Expired - Lifetime EP1400698B1 (fr) | 2002-09-18 | 2003-09-16 | Maîtrise de la position axiale d'une aube de soufflante |
Country Status (9)
Country | Link |
---|---|
US (1) | US6910866B2 (fr) |
EP (1) | EP1400698B1 (fr) |
JP (1) | JP4059827B2 (fr) |
CA (1) | CA2440995C (fr) |
DE (1) | DE60323309D1 (fr) |
ES (1) | ES2314167T3 (fr) |
FR (1) | FR2844562B1 (fr) |
RU (1) | RU2315206C2 (fr) |
UA (1) | UA79088C2 (fr) |
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2903154A1 (fr) * | 2006-06-29 | 2008-01-04 | Snecma Sa | Rotor de turbomachine et turbomachine comportant un tel rotor |
FR2929660A1 (fr) * | 2008-04-07 | 2009-10-09 | Snecma Sa | Dispositif anti-usure pour rotor de turbomachine, bouchon formant dispositif anti-usure et rotor de compresseur de moteur a turbine a gaz comportant un bouchon anti-usure |
WO2009144401A1 (fr) * | 2008-05-29 | 2009-12-03 | Snecma | Rotor de soufflante pour une turbomachine |
FR2948725A1 (fr) * | 2009-07-28 | 2011-02-04 | Snecma | Dispositif anti-usure d'un rotor de turbomachine |
FR2964584A1 (fr) * | 2010-09-10 | 2012-03-16 | Snecma | Dispositif et procede de frettage d'une piece anti-usure dans un trou localise dans un element de turboreacteur |
FR3048448A1 (fr) * | 2016-03-02 | 2017-09-08 | Snecma | Bouchon d'etancheite pour tambour de compresseur basse pression, tambour de compresseur basse pression et turbomachine associes |
FR3119646A1 (fr) * | 2021-02-11 | 2022-08-12 | Safran Aircraft Engines | Rotor de turbomachine |
WO2022195207A1 (fr) | 2021-03-16 | 2022-09-22 | Safran Aircraft Engines | Procédé de fabrication d'un disque de soufflante avec partie en fabrication additive |
Families Citing this family (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2927997A1 (fr) * | 2008-02-25 | 2009-08-28 | Snecma Sa | Procede pour tester un revetement de pied d'aube. |
FR2927998A1 (fr) * | 2008-02-25 | 2009-08-28 | Snecma Sa | Machine de test d'un revetement pour pied d'aube. |
FR2933887B1 (fr) * | 2008-07-18 | 2010-09-17 | Snecma | Procede de reparation ou de reprise d'un disque de turbomachine et disque de turbomachine repare ou repris |
US8568102B2 (en) * | 2009-02-18 | 2013-10-29 | Pratt & Whitney Canada Corp. | Fan blade anti-fretting insert |
US8616849B2 (en) * | 2009-02-18 | 2013-12-31 | Pratt & Whitney Canada Corp. | Fan blade platform |
RU2461717C1 (ru) * | 2011-03-17 | 2012-09-20 | Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" | Устройство демпфирования колебаний широкохордных рабочих лопаток вентиляторов с большой конусностью втулки и вентилятор газотурбинного двигателя |
GB201104994D0 (en) * | 2011-03-25 | 2011-05-11 | Rolls Royce Plc | a rotor having an annulus filler |
FR2974864B1 (fr) * | 2011-05-04 | 2016-05-27 | Snecma | Rotor de turbomachine avec moyen de retenue axiale des aubes |
FR2974863B1 (fr) * | 2011-05-06 | 2015-10-23 | Snecma | Disque de soufflante de turbomachine |
FR2986284B1 (fr) * | 2012-01-31 | 2014-03-28 | Snecma | Procede de reparation de marques d’usure. |
RU2494365C1 (ru) * | 2012-03-27 | 2013-09-27 | Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" | Нагрузочное устройство для исследования торцевого демпфирования колебаний лопаток вентилятора газотурбинного двигателя на вибростенде |
US9410439B2 (en) * | 2012-09-14 | 2016-08-09 | United Technologies Corporation | CMC blade attachment shim relief |
US11220920B2 (en) * | 2014-04-07 | 2022-01-11 | Safran Aircraft Engines | Turbine engine rotor lock |
FR3033359B1 (fr) * | 2015-03-02 | 2017-04-07 | Snecma | Disque aubage monobloc comportant un moyeu ayant une face evidee a laquelle est rapporte un organe de comblement |
CN109488390B (zh) * | 2018-12-18 | 2021-10-01 | 中国航发沈阳发动机研究所 | 一种转子叶片连接组件及涡轮性能试验组件 |
FR3106615B1 (fr) * | 2020-01-23 | 2021-12-31 | Safran Aircraft Engines | Ensemble pour turbomachine |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4033705A (en) * | 1976-04-26 | 1977-07-05 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Blade retainer assembly |
GB2262139A (en) * | 1991-12-04 | 1993-06-09 | Rolls Royce Plc | Fan blade retainer |
US5259728A (en) * | 1992-05-08 | 1993-11-09 | General Electric Company | Bladed disk assembly |
US5282720A (en) * | 1992-09-15 | 1994-02-01 | General Electric Company | Fan blade retainer |
EP0690203A2 (fr) * | 1994-06-28 | 1996-01-03 | ROLLS-ROYCE plc | Système de fixation pour les aubes de soufflante d'un réacteur à turbine à gaz |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2502690B1 (fr) * | 1981-03-27 | 1985-09-13 | Snecma | Dispositif de verrouillage d'aubes de soufflante et de fixation de capot avant d'un turboreacteur |
US4523890A (en) * | 1983-10-19 | 1985-06-18 | General Motors Corporation | End seal for turbine blade base |
FR2561307B1 (fr) * | 1984-03-14 | 1986-09-12 | Snecma | Dispositif de verrouillage d'aubes de soufflantes |
FR2715975B1 (fr) * | 1994-02-10 | 1996-03-29 | Snecma | Rotor de turbomachine à rainures d'aube débouchantes axiales ou inclinées. |
FR2803623B1 (fr) * | 2000-01-06 | 2002-03-01 | Snecma Moteurs | Agencement de retenue axiale d'aubes dans un disque |
-
2002
- 2002-09-18 FR FR0211539A patent/FR2844562B1/fr not_active Expired - Fee Related
-
2003
- 2003-09-11 US US10/659,290 patent/US6910866B2/en not_active Expired - Lifetime
- 2003-09-12 JP JP2003321226A patent/JP4059827B2/ja not_active Expired - Lifetime
- 2003-09-15 CA CA2440995A patent/CA2440995C/fr not_active Expired - Lifetime
- 2003-09-16 ES ES03292280T patent/ES2314167T3/es not_active Expired - Lifetime
- 2003-09-16 EP EP03292280A patent/EP1400698B1/fr not_active Expired - Lifetime
- 2003-09-16 DE DE60323309T patent/DE60323309D1/de not_active Expired - Lifetime
- 2003-09-17 RU RU2003128928/06A patent/RU2315206C2/ru active
- 2003-09-17 UA UA2003098538A patent/UA79088C2/uk unknown
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4033705A (en) * | 1976-04-26 | 1977-07-05 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Blade retainer assembly |
GB2262139A (en) * | 1991-12-04 | 1993-06-09 | Rolls Royce Plc | Fan blade retainer |
US5259728A (en) * | 1992-05-08 | 1993-11-09 | General Electric Company | Bladed disk assembly |
US5282720A (en) * | 1992-09-15 | 1994-02-01 | General Electric Company | Fan blade retainer |
EP0690203A2 (fr) * | 1994-06-28 | 1996-01-03 | ROLLS-ROYCE plc | Système de fixation pour les aubes de soufflante d'un réacteur à turbine à gaz |
Cited By (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1873401A3 (fr) * | 2006-06-29 | 2017-04-12 | Safran Aircraft Engines | Rotor de turbomachine et turbomachine comportant un tel rotor |
RU2446287C2 (ru) * | 2006-06-29 | 2012-03-27 | Снекма | Ротор турбинной установки и турбинная установка, содержащая такой ротор |
FR2903154A1 (fr) * | 2006-06-29 | 2008-01-04 | Snecma Sa | Rotor de turbomachine et turbomachine comportant un tel rotor |
US8113785B2 (en) | 2006-06-29 | 2012-02-14 | Snecma | Turbomachine rotor and turbomachine comprising such a rotor |
US8985961B2 (en) | 2008-04-07 | 2015-03-24 | Snecma | Turbomachine rotor comprising an anti-wear plug, and anti-wear plug |
FR2929660A1 (fr) * | 2008-04-07 | 2009-10-09 | Snecma Sa | Dispositif anti-usure pour rotor de turbomachine, bouchon formant dispositif anti-usure et rotor de compresseur de moteur a turbine a gaz comportant un bouchon anti-usure |
WO2009124949A1 (fr) * | 2008-04-07 | 2009-10-15 | Carbone Lorraine Composants | Rotor de turbomachine comportant un bouchon anti-usure, bouchon anti-usure |
WO2009144401A1 (fr) * | 2008-05-29 | 2009-12-03 | Snecma | Rotor de soufflante pour une turbomachine |
US8740568B2 (en) | 2008-05-29 | 2014-06-03 | Snecma | Turbomachine fan rotor |
FR2931871A1 (fr) * | 2008-05-29 | 2009-12-04 | Snecma | Rotor de soufflante pour une turbomachine. |
FR2948725A1 (fr) * | 2009-07-28 | 2011-02-04 | Snecma | Dispositif anti-usure d'un rotor de turbomachine |
US8573944B2 (en) | 2009-07-28 | 2013-11-05 | Snecma | Anti-wear device of a turbomachine rotor |
FR2964584A1 (fr) * | 2010-09-10 | 2012-03-16 | Snecma | Dispositif et procede de frettage d'une piece anti-usure dans un trou localise dans un element de turboreacteur |
FR3048448A1 (fr) * | 2016-03-02 | 2017-09-08 | Snecma | Bouchon d'etancheite pour tambour de compresseur basse pression, tambour de compresseur basse pression et turbomachine associes |
FR3119646A1 (fr) * | 2021-02-11 | 2022-08-12 | Safran Aircraft Engines | Rotor de turbomachine |
WO2022195207A1 (fr) | 2021-03-16 | 2022-09-22 | Safran Aircraft Engines | Procédé de fabrication d'un disque de soufflante avec partie en fabrication additive |
FR3120813A1 (fr) | 2021-03-16 | 2022-09-23 | Safran Aircraft Engines | Procédé de fabrication d’un disque de soufflante avec partie en fabrication additive |
Also Published As
Publication number | Publication date |
---|---|
EP1400698B1 (fr) | 2008-09-03 |
CA2440995C (fr) | 2011-02-08 |
RU2003128928A (ru) | 2005-03-20 |
ES2314167T3 (es) | 2009-03-16 |
FR2844562A1 (fr) | 2004-03-19 |
JP4059827B2 (ja) | 2008-03-12 |
US6910866B2 (en) | 2005-06-28 |
UA79088C2 (uk) | 2007-05-25 |
RU2315206C2 (ru) | 2008-01-20 |
CA2440995A1 (fr) | 2004-03-18 |
US20040126240A1 (en) | 2004-07-01 |
FR2844562B1 (fr) | 2004-10-29 |
JP2004263688A (ja) | 2004-09-24 |
DE60323309D1 (de) | 2008-10-16 |
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