EP1580402B1 - Turbomachine with two sub-assemblies being under axial pressure - Google Patents
Turbomachine with two sub-assemblies being under axial pressure Download PDFInfo
- Publication number
- EP1580402B1 EP1580402B1 EP05290663A EP05290663A EP1580402B1 EP 1580402 B1 EP1580402 B1 EP 1580402B1 EP 05290663 A EP05290663 A EP 05290663A EP 05290663 A EP05290663 A EP 05290663A EP 1580402 B1 EP1580402 B1 EP 1580402B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- turboshaft engine
- annular
- engine according
- subassemblies
- chamber
- 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.)
- Active
Links
- 238000000429 assembly Methods 0.000 title description 3
- 125000006850 spacer group Chemical group 0.000 description 4
- 238000002485 combustion reaction Methods 0.000 description 2
- 230000006378 damage Effects 0.000 description 2
- 230000003014 reinforcing effect Effects 0.000 description 2
- 238000004381 surface treatment 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
- 238000004513 sizing 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, in particular a turbocharger charged with supplying combustion air, under pressure, to the combustion chamber of a jet engine. It relates more particularly to an improvement reinforcing the tightness of the junction between two subassemblies of such a machine, for example the junction under stress between a housing and a fixed blade support of the stator.
- the stator is assembled to an outer casing.
- two subassemblies, the housing and the stator are shaped to define between them an annular chamber in which is inserted a seal. It is supported between two annular walls vis-à-vis belonging respectively to the two subassemblies.
- the two annular parts in contact with the two subassemblies are applied against each other with axial stress.
- a turbomachine according to the prior art is known in the document FR 2646221 .
- the constraint can be expressed in millimeters, this value designating the axial interference that would exist between the two subsets, if they were not abutting under stress. Hitherto, relatively low stresses have been implemented, conventionally of the order of 0.3 mm. More recently, this mounting stress has been raised to 0.75 mm.
- the chamber housing the seal can open under the effect of deformation of thermal origin. Moreover, in operation the seal undergoes deformations and wear that can go as far as the loss of fragments which, driven by the pressure difference, are jammed between the facing faces of the annular chamber. These faces are damaged and air leaks increase.
- the invention aims to prevent the opening of the chamber to prevent the release of pieces of the seal and the degradation of the surfaces against which it rests.
- the invention relates to a turbomachine comprising at least two subsets assembled to one another and defining between them an annular chamber housing a seal, wherein two annular contacting parts respectively belonging to the two sub-assemblies. sets and defining said chamber are urged towards each other, in a manner known per se, with axial constraint and characterized in that an annular spacer is inserted between their abutting surfaces.
- the axial stress can be significantly increased. It may especially be between 1.5 and 3 mm. A presently preferred stress value is close to 2.25 mm.
- This strong mounting constraint makes it possible to absorb variations of thermal origin and thus prevents the opening of the chamber and the destruction of the seal.
- This piece is inexpensive and easy to change if it is damaged. Therefore, both sub-assemblies are protected and no longer risk being damaged.
- the arrangement is such that the contact area between the two abutting subsets is increased. This results in a decrease in the matting pressure and a better behavior vis-à-vis the relative displacements between the subsets.
- the invention is particularly applicable to the connection between an outer casing and a stator element carrying the blades of a turbocharger.
- FIG. 1 a portion of a turbocharger 11 forming part 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 seal 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 located between the blades.
- the fixed blade support consists of several segments 26 assembled end to end, each segment carrying a series of blades. The entire support is fixed to an inner casing 27.
- This inner casing extends radially outwards by three annular rings, a first ring 30 is fixed by a bolt assembly 31 to a first inner frame 32 of the outer casing, a second ring 34 bears unrestrained against a second frame 36 of the outer casing, extending inwardly.
- the third ring 37 is fixed by a set of bolts 38 to an inner frame 39 of the outer casing 14.
- the second ring 34 comprises a flat annular surface 40 extending radially inwards, extended by an axial cylindrical portion 42 bearing by its circular field 43 against said second frame 36. More particularly, it comprises another flat annular surface 45 facing that of the crown, surmounted by an approximately tubular protrusion 46 coming to cover play with an outer cylindrical portion of the second ring.
- This arrangement therefore defines the annular chamber 18 within which the gasket 20 which is supported between the two flat surfaces 40, 45 is installed.
- the sizing of the subassemblies 14, 16 is such that the mounting is performed with a constraint caused by the tightening of the bolts 31.
- the invention appears in FIG. 3 and proposes to arrange an annular spacer 50 between the abutting surfaces of the two subassemblies, that is to say here between the circular field 43 of the ring 34 and the circular end of the flat surface 45 of the frame 36.
- This piece 50 increases the mounting stress which can now be between 1.5 mm and 3 mm, typically around 2.25 mm.
- the intermediate part 50 is shaped to increase the contact surface at the end of at least one of the annular parts, in this case more particularly the flat surface 45 of said second frame 36.
- the axial cylindrical portion 42 of the ring gear makes it possible to guide the positioning of the intermediate piece 50 because the latter comprises a cylindrical surface 52 fitting on said cylindrical portion 42.
- a radial portion 54 of the intermediate piece takes bearing against the flat surface 45 of said second chord.
- the radial section of the insert 50 is in the shape of an L.
- the insert can undergo a surface treatment, before mounting, reinforcing its strength.
- the treatment may especially relate to the radial portion 54. It is therefore not necessary to apply a treatment of this kind to the crown or chord.
- the spacer 50a is extended by a deflector portion 56, inwardly.
- this part has a substantially conical shape.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gasket Seals (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Supercharger (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
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, in particular a turbocharger charged with supplying combustion air, under pressure, to the combustion chamber of a jet engine. It relates more particularly to an improvement reinforcing the tightness of the junction between two subassemblies of such a machine, for example the junction under stress between a housing and a fixed blade support 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. Une turbomachine selon l'art antérieur est connue dans le document
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, entraînées 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 operating phases, the chamber housing the seal can open under the effect of deformation of thermal origin. Moreover, in operation the seal undergoes deformations and wear that can go as far as the loss of fragments which, driven by the pressure difference, are jammed between the facing faces of 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 invention aims to prevent the opening of the chamber to prevent the release of pieces of the seal and the degradation of the surfaces against which it 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, où 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 caractérisée 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 subsets assembled to one another and defining between them an annular chamber housing a seal, wherein two annular contacting parts respectively belonging to the two sub-assemblies. sets and defining said chamber are urged towards each other, in a manner known per se, with axial constraint and characterized 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 (called "martyr" piece) is installed between the two subassemblies, the axial stress can be significantly increased. It may especially be between 1.5 and 3 mm. A presently preferred stress value is close to 2.25 mm. This strong mounting constraint makes it possible to absorb variations of thermal origin and thus prevents the opening of the chamber and the destruction of the seal. This piece is inexpensive and easy to change if it is damaged. Therefore, both sub-assemblies are protected and no longer risk being damaged. The arrangement is such that the contact area between the two abutting subsets is increased. This results in a decrease in the matting pressure and a better behavior vis-à-vis the relative displacements between the subsets. In addition, it is relatively easy to perform a surface treatment of the insert, improving its strength. The invention is particularly applicable to the connection between an outer casing and a stator element carrying the blades of a turbocharger.
L'invention sera mieux comprise et d'autres avantages de celle-ci apparaîtront 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.Referring more particularly to Figures 1 and 2 relating to 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 FIG. 2, the
L'invention apparaît 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 apparaît 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 arrange an
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 Figure 4, the
Claims (7)
- A turboshaft engine comprising at least two subassemblies assembled with each other and defining between them an annular chamber (18) housing a seal, wherein two annular parts in contact respectively being part of the two subassemblies and defining the said chamber are stressed against each other, in a way that is known per se, with axial stress and the turboshaft engine being characterised in that an annular interposed part (50) is inserted between their butting surfaces.
- The turboshaft engine according to claim 1, characterised in that the said axial stress between the said two annular parts is between 1.5 and 3 mm, preferably close to 2.25 mm.
- The turboshaft engine according to claim 1 or 2, characterised in that the said interposed part (50) is shaped to increase the contact area at the end of at least one of the annular parts.
- The turboshaft engine according to one of the preceding claims, characterised in that one of the annular parts comprises a cylindrical portion (42) and in that the said interposed part comprises a cylindrical surface (52) fitting itself onto the said cylindrical portion and a radial portion (54) bearing against a flat surface (45) of the other annular part.
- The turboshaft engine according to claim 4, characterised in that the radial section of the said interposed part (50) is L-shaped.
- The turboshaft engine according to one of the preceding claims, characterised in that the said interposed part is extended by a section forming a deflector (56).
- The turboshaft engine according to one of the preceding claims, characterised in that the two subassemblies constitute a casing and a stator component respectively.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR0403128 | 2004-03-26 | ||
| FR0403128A FR2868125B1 (en) | 2004-03-26 | 2004-03-26 | TURBOMACHINE COMPRISING TWO SUBASSEMBLIES ASSEMBLED WITH AXIAL CONSTRAINTS |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP1580402A1 EP1580402A1 (en) | 2005-09-28 |
| EP1580402B1 true 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 |
| US8393855B2 (en) * | 2007-06-29 | 2013-03-12 | General Electric Company | Flange with axially curved impingement surface for gas turbine engine clearance control |
| US8197186B2 (en) * | 2007-06-29 | 2012-06-12 | General Electric Company | Flange with axially extending holes 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 |
Family Cites Families (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| LU86209A1 (en) * | 1985-12-12 | 1987-01-13 | Euratom | SEALING SYSTEM BETWEEN TWO METAL FLANGES |
| FR2646221B1 (en) * | 1989-04-19 | 1991-06-14 | Snecma | SEAL, DEVICE COMPRISING SAME AND APPLICATION TO A TURBOMACHINE |
| FR2695164B1 (en) * | 1992-08-26 | 1994-11-04 | Snecma | Turbomachine provided with a device preventing a longitudinal circulation of gas around the stages of straightening vanes. |
| 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 |
| JPH11343809A (en) * | 1998-06-02 | 1999-12-14 | Ishikawajima Harima Heavy Ind Co Ltd | Sealing structure of turbine shroud part for gas turbine |
| 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 |
| RU2302534C2 (en) * | 2001-12-11 | 2007-07-10 | Альстом (Свитзерлэнд) Лтд. | Gas-turbine device |
| 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 US US11/086,359 patent/US7571614B2/en active Active
- 2005-03-23 CA CA2500947A patent/CA2500947C/en active Active
- 2005-03-24 JP JP2005085761A patent/JP4643326B2/en active Active
- 2005-03-25 EP EP05290663A patent/EP1580402B1/en active Active
- 2005-03-25 ES ES05290663T patent/ES2290863T3/en active Active
- 2005-03-25 DE DE602005001641T patent/DE602005001641T2/en active Active
- 2005-03-25 RU RU2005108494/06A patent/RU2380546C2/en active
- 2005-03-25 UA UAA200502763A patent/UA86354C2/en unknown
Non-Patent Citations (1)
| Title |
|---|
| None * |
Also Published As
| Publication number | Publication date |
|---|---|
| US7571614B2 (en) | 2009-08-11 |
| RU2005108494A (en) | 2006-09-27 |
| FR2868125B1 (en) | 2006-07-21 |
| EP1580402A1 (en) | 2005-09-28 |
| CA2500947C (en) | 2012-11-20 |
| JP4643326B2 (en) | 2011-03-02 |
| ES2290863T3 (en) | 2008-02-16 |
| DE602005001641D1 (en) | 2007-08-30 |
| US20050260066A1 (en) | 2005-11-24 |
| DE602005001641T2 (en) | 2008-06-05 |
| RU2380546C2 (en) | 2010-01-27 |
| JP2005291203A (en) | 2005-10-20 |
| CA2500947A1 (en) | 2005-09-26 |
| UA86354C2 (en) | 2009-04-27 |
| FR2868125A1 (en) | 2005-09-30 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP1580402B1 (en) | Turbomachine with two sub-assemblies being under axial pressure | |
| EP1811131B1 (en) | Set of fixed sectorised diffuser inserts for a turbomachine compressor | |
| CA2622116C (en) | High-pressure turbine of a turbomachine | |
| EP1873385B1 (en) | Exhaust cone for channeling a gas stream downstream of a turbine | |
| EP1517005A1 (en) | Gas turbine sealing joint having lamellar structure | |
| EP1598524A1 (en) | Assembly method for unitary vaned rotors and device for the damping of vane vibrations | |
| CA2647057C (en) | Sectorized distributor for a turbine | |
| FR2952965A1 (en) | INSULATING A CIRCONFERENTIAL SIDE OF AN EXTERNAL TURBOMACHINE CASTER WITH RESPECT TO A CORRESPONDING RING SECTOR | |
| EP2060751B1 (en) | Turbine or compressor stage of a jet engine | |
| WO2011069940A1 (en) | Retaining ring assembly and supporting flange for said ring | |
| EP4025780A1 (en) | Ejection cone having a flexible aerodynamic attachment | |
| WO2019048766A1 (en) | Turbine assembly with ring segments | |
| EP4240955A1 (en) | Fastening of an exhaust cone in a turbomachine nozzle | |
| EP4240957A1 (en) | Assembly for a turbomachine | |
| FR3094031A1 (en) | SET FOR A TURBOMACHINE | |
| FR2961556A1 (en) | Turbine i.e. low pressure turbine, for e.g. turbojet engine of airplane, has axial and radial support units that are not in contact with casing to avoid heating, by conduction, of casing by sectorized ring during operation | |
| FR3116305A1 (en) | CONNECTING SHAFT OF A HIGH PRESSURE BODY OF A TURBOMACHINE | |
| FR3137721A1 (en) | Turbomachine turbine assembly | |
| WO2023247903A1 (en) | Bladed assembly for a turbomachine, turbine for a turbomachine, and turbomachine | |
| FR3121168A1 (en) | Reduction of leaks in a turbomachine | |
| FR3137722A1 (en) | Turbomachine turbine assembly | |
| WO2023242496A1 (en) | Assembly for a turbine engine | |
| FR3115568A1 (en) | TURBOMACHINE TURBINE ASSEMBLY | |
| WO2022074323A1 (en) | Sealing assembly for a turbine ejection cone | |
| WO2023209290A1 (en) | Assembly for a turbine engine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
| 17P | Request for examination filed |
Effective date: 20050402 |
|
| AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU MC NL PL PT RO SE SI SK TR |
|
| AX | Request for extension of the european patent |
Extension state: AL BA HR LV MK YU |
|
| RIN1 | Information on inventor provided before grant (corrected) |
Inventor name: SUET, PATRICE Inventor name: PONTOIZEAU, BRUCE Inventor name: MESIC, MARICA Inventor name: LEJARS, CLAUDE Inventor name: ROY, ALEXANDRE |
|
| AKX | Designation fees paid |
Designated state(s): DE ES FR GB IT SE |
|
| RTI1 | Title (correction) |
Free format text: TURBOMACHINE WITH TWO SUB-ASSEMBLIES BEING UNDER AXIAL PRESSURE |
|
| GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
| GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
| GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
| AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): DE ES FR GB IT SE |
|
| REG | Reference to a national code |
Ref country code: GB Ref legal event code: FG4D Free format text: NOT ENGLISH |
|
| REF | Corresponds to: |
Ref document number: 602005001641 Country of ref document: DE Date of ref document: 20070830 Kind code of ref document: P |
|
| REG | Reference to a national code |
Ref country code: SE Ref legal event code: TRGR |
|
| GBT | Gb: translation of ep patent filed (gb section 77(6)(a)/1977) |
Effective date: 20071010 |
|
| REG | Reference to a national code |
Ref country code: ES Ref legal event code: FG2A Ref document number: 2290863 Country of ref document: ES Kind code of ref document: T3 |
|
| PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
| STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
| 26N | No opposition filed |
Effective date: 20080421 |
|
| PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: ES Payment date: 20120309 Year of fee payment: 8 |
|
| REG | Reference to a national code |
Ref country code: ES Ref legal event code: FD2A Effective date: 20140609 |
|
| PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: ES Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20130326 |
|
| REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 12 |
|
| REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 13 |
|
| REG | Reference to a national code |
Ref country code: FR Ref legal event code: CD Owner name: SAFRAN AIRCRAFT ENGINES Effective date: 20170719 |
|
| REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 14 |
|
| REG | Reference to a national code |
Ref country code: DE Ref legal event code: R082 Ref document number: 602005001641 Country of ref document: DE Representative=s name: CBDL PATENTANWAELTE GBR, DE |
|
| PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: DE Payment date: 20240220 Year of fee payment: 20 Ref country code: GB Payment date: 20240220 Year of fee payment: 20 |
|
| PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: SE Payment date: 20240220 Year of fee payment: 20 Ref country code: IT Payment date: 20240220 Year of fee payment: 20 Ref country code: FR Payment date: 20240220 Year of fee payment: 20 |