EP1580402A1 - Turbomachine with two sub - parts being under axial pressure - Google Patents
Turbomachine with two sub - parts being under axial pressure Download PDFInfo
- Publication number
- EP1580402A1 EP1580402A1 EP05290663A EP05290663A EP1580402A1 EP 1580402 A1 EP1580402 A1 EP 1580402A1 EP 05290663 A EP05290663 A EP 05290663A EP 05290663 A EP05290663 A EP 05290663A EP 1580402 A1 EP1580402 A1 EP 1580402A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- annular
- turbomachine
- subassemblies
- turbomachine according
- parts
- 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
- 125000006850 spacer group Chemical group 0.000 claims abstract description 5
- 238000000429 assembly Methods 0.000 abstract 2
- 230000000712 assembly Effects 0.000 abstract 1
- 238000002485 combustion reaction Methods 0.000 description 2
- 230000006378 damage Effects 0.000 description 2
- 230000003014 reinforcing effect Effects 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 230000015556 catabolic process Effects 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000012634 fragment Substances 0.000 description 1
- 239000011229 interlayer Substances 0.000 description 1
- 238000004513 sizing Methods 0.000 description 1
- 238000004381 surface treatment 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
Definitions
- the invention generally relates to a turbomachine, including a turbocharger charged with supplying combustion air, under pressure, to the combustion chamber of a jet engine. She more particularly a reinforcing enhancement sealing the junction between two subassemblies of such a machine, for example the junction under stress between a housing and a support fixed vanes of the stator.
- the stator is assembled to an outer casing.
- two subassemblies, of the housing and the stator are shaped to define between them an annular chamber in which is inserted a seal. This one takes support between two annular walls vis-a-vis belonging respectively to both subsets.
- the two annular parts in contact of the two subsets are applied against each other with axial stress.
- the constraint can be expressed in millimeters, this value designating the axial interference that would exist between the two subsets, if they were not in abeyance under duress. So far, relatively low constraints have been implemented, typically of the order of 0.3 mm. More recently, this constraint mounting was increased to 0.75 mm.
- the chamber enclosing the seal may open under the effect of original deformations thermal. Moreover, in operation the seal undergoes deformations and wear and tear that can go as far as the loss of fragments that driven by the pressure difference, are caught between the facing the annular chamber. These faces are damaged and air leaks increase.
- the object of the invention is to prevent the opening of the chamber avoid release of seal pieces and surface degradation against which he rests.
- the invention relates to a turbomachine comprising at least two subassemblies assembled to one another and defining between them an annular chamber housing a joint sealing, characterized in that two annular parts in contact respectively belonging to the two subassemblies and defining room are urged towards each other, in a manner known per se, with axial constraint and in that an annular spacer is inserted between their abutting surfaces.
- the constraint axial can be significantly increased. In particular, it can be between 1.5 and 3 mm.
- a constraint value currently preferred is close to 2.25 mm.
- This strong constraint to assembly allows to absorb variations of thermal origin and avoids the opening of the chamber and the destruction of the joint. This piece is little expensive and easy to change if it is damaged. Therefore, two subassemblies are protected and are not likely to be damaged.
- the arrangement is such that the contact area between the two abutment subassemblies are increased. This results in a decrease in the pressure of matting and better behavior vis-à-vis relative displacements between the subsets.
- the invention applies particularly to the connection between an outer casing and an element of stator carrying the blades of a turbocharger.
- FIG. 1 and 2 there is shown a portion of a turbocharger 11 entering the constitution of an aircraft engine reactor.
- Two subassemblies 14,16 are assembled under axial stress by defining between them an annular chamber 18 inside which is inserted a 20.
- the subassembly 14 constitutes an outer casing while the subassembly 16 constitutes the support of a plurality of vanes 22 of the turbocharger.
- the unrepresented blades are between the vanes fixed.
- the support of fixed blades consists of several segments 26 assembled end to end, each segment carrying a series of fixed vanes. The entire support is fixed to an inner casing 27.
- This inner casing this extends radially outward by three rings, a first ring 30 is fixed by a bolt assembly 31 to a first inner frame 32 of the housing outside, a second ring 34 comes to bear without constraint against a second frame 36 of the outer housing extending inwardly.
- the third ring 37 is fixed by a set of bolts 38 to a inner chord 39 of the outer casing 14.
- the second ring 34 has a flat annular surface 40 extending radially inward, extended by an axial cylindrical portion 42 supported by its circular field 43 against said second frame 36. More particularly, it comprises another surface annular flat 45 facing the crown, surmounted by a approximately tubular protuberance 46 covering with play an outer cylindrical portion of the second ring.
- This arrangement therefore defines the annular chamber 18 inside which is installed the seal 20 which bears between the two flat surfaces 40, 45.
- the sizing of the subassemblies 14, 16 is such that the assembly is carried out with a constraint caused by the This constraint is thus exerted between the field circular 43 of the second ring and the inner end of the surface plate 45 of the second chord.
- the arrangement described so far is classic. However, the mounting stress was relatively low, of the order of 0.3 mm. In some cases, the constraint has been 0.75 mm without being able to completely solve the problem of leaks and the destruction of the joint, as explained above.
- the invention appears in FIG. 3 and proposes to dispose of a annular spacer piece 50 between the abutting surfaces of the two subsets, that is to say here between the circular field 43 of the crown 34 and the circular end of the flat surface 45 of the chord 36.
- This piece 50 makes it possible to increase the stress of mounting which can now be between 1.5 mm and 3 mm, typically around 2.25 mm.
- the room tab 50 is shaped to increase the contact area to the end of at least one of the annular parts, here more particularly the flat surface 45 of said second chord 36.
- the axial cylindrical portion 42 of the crown makes it possible to guide the positioning of the insert 50 because it comprises a cylindrical surface 52 fitting on said cylindrical portion 42.
- the radial portion 54 of the intermediate piece bears against the surface plate 45 of said second chord.
- the radial section of the intermediate piece 50 has therefore the shape of an L.
- the insert can undergo a treatment of surface, before mounting, reinforcing its resistance. Treatment can particularly concerning the radial portion 54. It is therefore not necessary apply such treatment to the crown or chord.
- insert 50a is extended by a deflector portion 56, to inside.
- this part has a substantially conical shape.
Abstract
Description
L'invention se rapporte en général à une turbomachine, notamment un turbocompresseur chargé de fournir l'air comburant, sous pression, à la chambre de combustion d'un moteur d'avion à réaction. Elle concerne plus particulièrement un perfectionnement renforçant l'étanchéité de la jonction entre deux sous-ensembles d'une telle machine, par exemple la jonction sous contrainte entre un carter et un support d'aubes fixes du stator.The invention generally relates to a turbomachine, including a turbocharger charged with supplying combustion air, under pressure, to the combustion chamber of a jet engine. She more particularly a reinforcing enhancement sealing the junction between two subassemblies of such a machine, for example the junction under stress between a housing and a support fixed vanes of the stator.
Dans un turbocompresseur du genre indiqué ci-dessus, le stator est assemblé à un carter extérieur. Pour éviter les fuites d'air, deux sous-ensembles, du carter et du stator, sont conformés pour définir entre eux une chambre annulaire dans laquelle est inséré un joint. Celui-ci prend appui entre deux parois annulaires en vis-à-vis appartenant respectivement aux deux sous-ensembles. Les deux parties annulaires en contact des deux sous-ensembles sont appliquées l'une contre l'autre avec contrainte axiale. La contrainte peut s'exprimer en millimètres, cette valeur désignant l'interférence axiale qui existerait entre les deux sous-ensembles, si ceux-ci n'étaient pas en aboutement sous contrainte. Jusqu'à présent, on a mis en oeuvre des contraintes relativement faibles, classiquement de l'ordre de 0,3 mm. Plus récemment, cette contrainte au montage a été portée à 0,75 mm.In a turbocharger of the type indicated above, the stator is assembled to an outer casing. To prevent air leakage, two subassemblies, of the housing and the stator, are shaped to define between them an annular chamber in which is inserted a seal. This one takes support between two annular walls vis-a-vis belonging respectively to both subsets. The two annular parts in contact of the two subsets are applied against each other with axial stress. The constraint can be expressed in millimeters, this value designating the axial interference that would exist between the two subsets, if they were not in abeyance under duress. So far, relatively low constraints have been implemented, typically of the order of 0.3 mm. More recently, this constraint mounting was increased to 0.75 mm.
Pendant certaines phases de fonctionnement, la chambre abritant le joint peut s'ouvrir sous l'effet de déformations d'origine thermique. Par ailleurs, en fonctionnement le joint subit des déformations et des usures qui peuvent aller jusqu'à la perte de fragments qui, entraínées par la différence de pression, viennent se coincer entre les faces en regard de la chambre annulaire. Ces faces sont endommagées et les fuites d'air augmentent.During certain phases of operation, the chamber enclosing the seal may open under the effect of original deformations thermal. Moreover, in operation the seal undergoes deformations and wear and tear that can go as far as the loss of fragments that driven by the pressure difference, are caught between the facing the annular chamber. These faces are damaged and air leaks increase.
L'invention a pour but d'éviter l'ouverture de la chambre pour éviter la libération de morceaux du joint et la dégradation des surfaces contre lesquelles il repose.The object of the invention is to prevent the opening of the chamber avoid release of seal pieces and surface degradation against which he rests.
Plus particulièrement, l'invention concerne une turbomachine comprenant au moins deux sous-ensembles assemblés l'un à l'autre et définissant entre eux une chambre annulaire abritant un joint d'étanchéité, caractérisée en ce que deux parties annulaires en contact appartenant respectivement aux deux sous-ensembles et définissant ladite chambre sont sollicitées l'une vers l'autre, de façon connue en soi, avec contrainte axiale et en ce qu'une pièce intercalaire annulaire est insérée entre leurs surfaces en aboutement.More particularly, the invention relates to a turbomachine comprising at least two subassemblies assembled to one another and defining between them an annular chamber housing a joint sealing, characterized in that two annular parts in contact respectively belonging to the two subassemblies and defining room are urged towards each other, in a manner known per se, with axial constraint and in that an annular spacer is inserted between their abutting surfaces.
Lorsqu'une telle pièce intercalaire annulaire (dite pièce "martyre") est installée entre les deux sous-ensembles, la contrainte axiale peut être notablement augmentée. Elle peut notamment être comprise entre 1,5 et 3 mm. Une valeur de contrainte actuellement préférée est voisine de 2,25 mm. Cette forte contrainte au montage permet d'absorber les variations d'origine thermique et évite ainsi l'ouverture de la chambre et la destruction du joint. Cette pièce est peu coûteuse et facile à changer si elle est endommagée. Par conséquent, les deux sous-ensembles sont protégés et ne risquent plus d'être endommagés. L'agencement est tel que la surface de contact entre les deux sous-ensembles en aboutement est augmentée. Il en résulte une diminution de la pression de matage et un meilleur comportement vis-à-vis des déplacements relatifs entre les sous-ensembles. De plus, il est relativement facile de réaliser un traitement de surface de cette pièce intercalaire, améliorant sa résistance. L'invention s'applique tout particulièrement à la liaison entre un carter extérieur et un élément de stator portant les aubes fixes d'un turbocompresseur.When such an annular spacer "martyrdom") is installed between the two subsets, the constraint axial can be significantly increased. In particular, it can be between 1.5 and 3 mm. A constraint value currently preferred is close to 2.25 mm. This strong constraint to assembly allows to absorb variations of thermal origin and avoids the opening of the chamber and the destruction of the joint. This piece is little expensive and easy to change if it is damaged. Therefore, two subassemblies are protected and are not likely to be damaged. The arrangement is such that the contact area between the two abutment subassemblies are increased. This results in a decrease in the pressure of matting and better behavior vis-à-vis relative displacements between the subsets. In addition, it is relatively easy to perform a surface treatment of this piece interlayer, improving its resistance. The invention applies particularly to the connection between an outer casing and an element of stator carrying the blades of a turbocharger.
L'invention sera mieux comprise et d'autres avantages de celle-ci apparaítront plus clairement à la lumière de la description qui va suivre, donnée uniquement à titre d'exemple et faite en référence aux dessins annexés dans lesquels :
- la figure 1 est une vue schématique illustrant deux sous-ensembles assemblés et constituant une partie d'un turbocompresseur, l'assemblage étant classique, avec contrainte axiale au voisinage d'une chambre de joint ;
- la figure 2 est une vue schématique à plus grande échelle de l'encadré 2 de la figure 1 ;
- la figure 3 est une vue analogue à la figure 2 illustrant le perfectionnement conforme à l'invention ; et
- la figure 4 est une vue analogue à la figure 3 illustrant une variante.
- Figure 1 is a schematic view illustrating two subsets assembled and forming part of a turbocharger, the assembly being conventional, with axial stress in the vicinity of a joint chamber;
- Figure 2 is a schematic view on a larger scale of the box 2 of Figure 1;
- Figure 3 is a view similar to Figure 2 illustrating the improvement according to the invention; and
- Figure 4 is a view similar to Figure 3 illustrating a variant.
En considérant plus particulièrement les figures 1 et 2 relatives
à l'art antérieur, on a représenté une partie d'un turbocompresseur 11
entrant dans la constitution d'un réacteur de moteur d'avion. Deux sous-ensembles
14,16 sont assemblés sous contrainte axiale en définissant
entre eux une chambre annulaire 18 à l'intérieur de laquelle est inséré un
joint 20. Le sous-ensemble 14 constitue un carter extérieur tandis que le
sous-ensemble 16 constitue le support d'une pluralité d'aubes fixes 22 du
turbocompresseur. Les aubes mobiles non représentées se situent entre
les aubes fixes. Le support d'aubes fixes est constitué de plusieurs
segments 26 assemblés bout à bout, chaque segment portant une série
d'aubes fixes. L'ensemble du support est fixé à un carter intérieur 27. Ce
carter intérieur ce prolonge radialement vers l'extérieur par trois
couronnes annulaires, une première couronne 30 est fixée par un
ensemble de boulon 31 à une première membrure interne 32 du carter
extérieur, une seconde couronne 34 vient en appui sans contrainte contre
une seconde membrure 36 du carter extérieur, s'étendant vers l'intérieur.
La troisième couronne 37 est fixée par un ensemble de boulons 38 à une
membrure interne 39 du carter extérieur 14.Considering more particularly Figures 1 and 2 relating to
in the prior art, there is shown a portion of a
Comme on le voit plus particulièrement sur la figure 2, la
seconde couronne 34 comporte une surface annulaire plate 40 s'étendant
radialement vers l'intérieur, prolongée par une portion cylindrique axiale
42 prenant appui par son champ circulaire 43 contre ladite seconde
membrure 36. Plus particulièrement, celle-ci comporte une autre surface
annulaire plate 45 faisant face à celle de la couronne, surmontée d'une
excroissance 46 approximativement tubulaire venant recouvrir avec jeu
une partie cylindrique extérieure de la seconde couronne. Cet agencement
définit donc la chambre annulaire 18 à l'intérieur de laquelle est installé le
joint 20 qui prend appui entre les deux surfaces plates 40, 45. Comme
mentionné ci-dessus, le dimensionnement des sous-ensembles 14, 16 est
tel que le montage s'effectue avec une contrainte provoquée par le
serrage des boulons 31. Cette contrainte s'exerce donc entre le champ
circulaire 43 de la seconde couronne et l'extrémité intérieure de la surface
plate 45 de la seconde membrure. L'agencement décrit jusqu'à présent est
classique. Cependant, la contrainte de montage était relativement faible,
de l'ordre de 0,3 mm. Dans certains cas, la contrainte a été portée jusqu'à
0,75 mm sans pouvoir complètement résoudre le problème des fuites et
de la destruction du joint, comme expliqué ci-dessus.As can be seen more particularly in Figure 2, the
L'invention apparaít sur la figure 3 et propose de disposer une
pièce intercalaire annulaire 50 entre les surfaces en aboutement des deux
sous-ensembles, c'est-à-dire ici entre le champ circulaire 43 de la
couronne 34 et l'extrémité circulaire de la surface plate 45 de la membrure
36. La présence de cette pièce 50 permet d'augmenter la contrainte de
montage qui peut dorénavant se situer entre 1,5 mm et 3 mm,
typiquement aux environs de 2,25 mm. En effet, on voit que la pièce
intercalaire 50 est conformée pour augmenter la surface de contact à
l'extrémité d'au moins l'une des parties annulaires, en l'occurrence ici plus
particulièrement la surface plate 45 de ladite seconde membrure 36. En
outre, la portion cylindrique axiale 42 de la couronne permet de guider le
positionnement de la pièce intercalaire 50 du fait que celle-ci comporte
une surface cylindrique 52 s'ajustant sur ladite portion cylindrique 42. Une
portion radiale 54 de la pièce intercalaire prend appui contre la surface
plate 45 de ladite seconde membrure. Globalement, comme cela apparaít
clairement sur la figure 3, la section radiale de la pièce intercalaire 50 a
donc la forme d'un L. La pièce intercalaire peut subir un traitement de
surface, avant montage, renforçant sa résistance. Le traitement peut
notamment concerner la portion radiale 54. Il n'est donc pas nécessaire
d'appliquer un traitement de ce genre à la couronne ou à la membrure.The invention appears in FIG. 3 and proposes to dispose of a
En variante, comme le montre la figure 4, la pièce
intercalaire 50a se prolonge par une partie formant déflecteur 56, vers
l'intérieur. Dans l'exemple, cette partie a une forme sensiblement conique.
Ainsi, en cas de fuite résiduelle, l'air chaud ne vient plus frapper
localement le carter intérieur mais se diffuse dans la chambre 58 définie
entre le carter et le support d'aubes.Alternatively, as shown in FIG.
Claims (7)
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR0403128A FR2868125B1 (en) | 2004-03-26 | 2004-03-26 | TURBOMACHINE COMPRISING TWO SUBASSEMBLIES ASSEMBLED WITH AXIAL CONSTRAINTS |
| FR0403128 | 2004-03-26 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP1580402A1 true EP1580402A1 (en) | 2005-09-28 |
| EP1580402B1 EP1580402B1 (en) | 2007-07-18 |
Family
ID=34855166
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP05290663A Active EP1580402B1 (en) | 2004-03-26 | 2005-03-25 | Turbomachine with two sub-assemblies being under axial pressure |
Country Status (9)
| Country | Link |
|---|---|
| US (1) | US7571614B2 (en) |
| EP (1) | EP1580402B1 (en) |
| JP (1) | JP4643326B2 (en) |
| CA (1) | CA2500947C (en) |
| DE (1) | DE602005001641T2 (en) |
| ES (1) | ES2290863T3 (en) |
| FR (1) | FR2868125B1 (en) |
| RU (1) | RU2380546C2 (en) |
| UA (1) | UA86354C2 (en) |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2898641B1 (en) * | 2006-03-17 | 2008-05-02 | Snecma Sa | CARTERING IN A TURBOJET ENGINE |
| US8197186B2 (en) * | 2007-06-29 | 2012-06-12 | General Electric Company | Flange with axially extending holes for gas turbine engine clearance control |
| US8393855B2 (en) * | 2007-06-29 | 2013-03-12 | General Electric Company | Flange with axially curved impingement surface for gas turbine engine clearance control |
| US8998573B2 (en) * | 2010-10-29 | 2015-04-07 | General Electric Company | Resilient mounting apparatus for low-ductility turbine shroud |
| EP2886802B1 (en) * | 2013-12-20 | 2019-04-10 | Safran Aero Boosters SA | Gasket of the inner ferrule of the last stage of an axial turbomachine compressor |
| US10202863B2 (en) | 2016-05-23 | 2019-02-12 | United Technologies Corporation | Seal ring for gas turbine engines |
| US10392967B2 (en) | 2017-11-13 | 2019-08-27 | General Electric Company | Compliant seal component and associated method |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0236567A1 (en) * | 1985-12-12 | 1987-09-16 | Communaute Europeenne De L'energie Atomique (Euratom) | Sealing system between two metallic flanges |
| FR2646221A1 (en) * | 1989-04-19 | 1990-10-26 | Snecma | Sealing gasket, device including it and application to a turbo machine |
| US5320484A (en) * | 1992-08-26 | 1994-06-14 | General Electric Company | Turbomachine stator having a double skin casing including means for preventing gas flow longitudinally therethrough |
| JPH11343809A (en) * | 1998-06-02 | 1999-12-14 | Ishikawajima Harima Heavy Ind Co Ltd | Sealing structure of turbine shroud part for gas turbine |
| WO2003054358A1 (en) * | 2001-12-11 | 2003-07-03 | Alstom Technology Ltd | Gas turbine assembly |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH076407B2 (en) * | 1992-08-26 | 1995-01-30 | ゼネラル・エレクトリック・カンパニイ | Turbo shaft engine |
| FR2766517B1 (en) * | 1997-07-24 | 1999-09-03 | Snecma | DEVICE FOR VENTILATION OF A TURBOMACHINE RING |
| US6402466B1 (en) * | 2000-05-16 | 2002-06-11 | General Electric Company | Leaf seal for gas turbine stator shrouds and a nozzle band |
| US6450762B1 (en) * | 2001-01-31 | 2002-09-17 | General Electric Company | Integral aft seal for turbine applications |
| US6612809B2 (en) * | 2001-11-28 | 2003-09-02 | General Electric Company | Thermally compliant discourager seal |
| US6568903B1 (en) * | 2001-12-28 | 2003-05-27 | General Electric Company | Supplemental seal for the chordal hinge seals in a gas turbine |
-
2004
- 2004-03-26 FR FR0403128A patent/FR2868125B1/en not_active Expired - Fee Related
-
2005
- 2005-03-23 CA CA2500947A patent/CA2500947C/en active Active
- 2005-03-23 US US11/086,359 patent/US7571614B2/en active Active
- 2005-03-24 JP JP2005085761A patent/JP4643326B2/en active Active
- 2005-03-25 RU RU2005108494/06A patent/RU2380546C2/en active
- 2005-03-25 EP EP05290663A patent/EP1580402B1/en active Active
- 2005-03-25 UA UAA200502763A patent/UA86354C2/en unknown
- 2005-03-25 DE DE602005001641T patent/DE602005001641T2/en active Active
- 2005-03-25 ES ES05290663T patent/ES2290863T3/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0236567A1 (en) * | 1985-12-12 | 1987-09-16 | Communaute Europeenne De L'energie Atomique (Euratom) | Sealing system between two metallic flanges |
| FR2646221A1 (en) * | 1989-04-19 | 1990-10-26 | Snecma | Sealing gasket, device including it and application to a turbo machine |
| US5320484A (en) * | 1992-08-26 | 1994-06-14 | General Electric Company | Turbomachine stator having a double skin casing including means for preventing gas flow longitudinally therethrough |
| JPH11343809A (en) * | 1998-06-02 | 1999-12-14 | Ishikawajima Harima Heavy Ind Co Ltd | Sealing structure of turbine shroud part for gas turbine |
| WO2003054358A1 (en) * | 2001-12-11 | 2003-07-03 | Alstom Technology Ltd | Gas turbine assembly |
Non-Patent Citations (1)
| Title |
|---|
| PATENT ABSTRACTS OF JAPAN vol. 2000, no. 03 30 March 2000 (2000-03-30) * |
Also Published As
| Publication number | Publication date |
|---|---|
| CA2500947C (en) | 2012-11-20 |
| US7571614B2 (en) | 2009-08-11 |
| RU2005108494A (en) | 2006-09-27 |
| JP2005291203A (en) | 2005-10-20 |
| JP4643326B2 (en) | 2011-03-02 |
| ES2290863T3 (en) | 2008-02-16 |
| DE602005001641T2 (en) | 2008-06-05 |
| CA2500947A1 (en) | 2005-09-26 |
| FR2868125B1 (en) | 2006-07-21 |
| RU2380546C2 (en) | 2010-01-27 |
| EP1580402B1 (en) | 2007-07-18 |
| FR2868125A1 (en) | 2005-09-30 |
| US20050260066A1 (en) | 2005-11-24 |
| DE602005001641D1 (en) | 2007-08-30 |
| UA86354C2 (en) | 2009-04-27 |
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