EP1748158B1 - Bushing for pivoting the variable vanes of a turbomachine - Google Patents

Bushing for pivoting the variable vanes of a turbomachine Download PDF

Info

Publication number
EP1748158B1
EP1748158B1 EP06117010.6A EP06117010A EP1748158B1 EP 1748158 B1 EP1748158 B1 EP 1748158B1 EP 06117010 A EP06117010 A EP 06117010A EP 1748158 B1 EP1748158 B1 EP 1748158B1
Authority
EP
European Patent Office
Prior art keywords
branches
bushing
branch
ring
ring according
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
Application number
EP06117010.6A
Other languages
German (de)
French (fr)
Other versions
EP1748158A1 (en
Inventor
Michel Bouru
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP1748158A1 publication Critical patent/EP1748158A1/en
Application granted granted Critical
Publication of EP1748158B1 publication Critical patent/EP1748158B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/12—Control of the pumps
    • F02B37/24—Control of the pumps by using pumps or turbines with adjustable guide vanes

Definitions

  • the present invention relates to the general field of blades with variable pitch angle for turbomachine, and more particularly to the bushings for the guide pivots of these blades.
  • the high-pressure compressor of a gas turbine engine typically consists of several circular blade stages whose orientation can be adjusted to change the gas flow characteristics according to the operating conditions of the turbomachine. These blades are called blades variable pitch angle.
  • variable pitch angle vanes of the same stage each comprise a control pivot head and a foot guide pin.
  • the control pivot passes through a stator casing of the turbomachine and cooperates with a control member. From an action on this controller, it is possible to change the orientation of the blades of the stage concerned.
  • the vane guide pivot it is movable in a bushing mounted in a corresponding recess of an inner ring of the turbomachine centered on the longitudinal axis of the latter (see the publication FR 2,698,405 ).
  • the main purpose of the present invention is therefore to overcome such drawbacks by proposing a socket capable of ensuring a permanent centering quality of the guide pivots of the blades, whatever the operating phase of the turbomachine and regardless of the materials used to produce the turbine. socket and the inner ring in which it is mounted.
  • turbomachine ring as defined by claim 1.
  • each socket distributed equidistantly around the circumference of the tubular body of the socket makes it possible to center the socket whatever the operating temperature and whatever the materials used to make the socket and the socket. inner ring.
  • each branch of the sleeves has a substantially rectangular cross section.
  • each branch of the sleeves also has walls substantially parallel to a longitudinal plane of symmetry of the branch.
  • each branch of the bushings is in the form of a tubular branch of substantially oval cross-section.
  • the walls of these branches can be deformable, each wall of the branches then being intended to be pressed against walls of the recess of the ring in which the sleeve is intended to be mounted.
  • each branch of the sleeves is provided with two deformable tongues extending along the longitudinal axis of the tubular body, each tongue being intended to be folded against the walls of the recess of the ring in which the socket is mounted.
  • the sleeve advantageously comprises at least four branches distributed substantially equidistantly on the circumference of the tubular body.
  • the socket may be made of a material having a coefficient of thermal expansion different from that of the ring.
  • the invention also relates to a compressor and a turbomachine comprising at least one ring as defined above.
  • the blades 2 variable pitch angle of the high-pressure compressor of the turbomachine are distributed in circular stages centered on the longitudinal axis XX of the turbomachine and arranged between stages of moving blades (not shown) which are fixed on a rotor of the turbomachine.
  • Each blade 2 with variable pitch angle of a circular stage extends along a main axis Y-Y which has a radial direction relative to the longitudinal axis X-X of the turbomachine.
  • the blade 2 is in the form of a blade 4 ending at an outer radial end (or blade head) by a control pivot 6 (or upper pivot) and at an inner radial end (or foot of dawn) by a guide pin 8 (or lower pivot).
  • the control pivot 6 of the blade 2 variable pitch angle, centered on its main axis Y-Y, through an annular envelope 10 of the stator of the turbomachine and cooperates with a control member of the orientation of the blades. More specifically, the control pivot 6 of the blades 2 protrudes radially outwardly of the stator casing 10 and ends with a head 12 on which is engaged a control rod end 14 whose other end cooperates with a control ring 16 centered on the longitudinal axis XX of the turbomachine.
  • the rods 14 and the control ring 16 form the control member of the orientation of the blades.
  • the rotation of the control ring 16 around the longitudinal axis XX of the turbomachine makes it possible to rotate the control rods 14 and thus simultaneously change the orientation of all the blades 2 variable pitch of the same stage of the high-pressure compressor.
  • the guide pin 8 of the blade 2 with variable pitch angle, centered on its main axis Y-Y, is intended to pivot inside a hollow sleeve 100.
  • Each bushing 100 is mounted in a recess 104 formed in an inner ring 24 of the high-pressure compressor of the turbomachine which is centered on the longitudinal axis XX of the turbomachine, the bushing and the recess being of substantially complementary shapes.
  • an additional sleeve 26 forming a collar can be mounted tightly around each guide pin 8 of the blades 2.
  • Such additional sleeve 26 of substantially cylindrical shape is interposed between the guide pin 8 of the blades and the sleeve 100. It allows thus to avoid premature wear of the socket.
  • the sleeve 100 has a substantially tubular body 102 of longitudinal axis ZZ which is intended to receive the guide pin 8 of the blade.
  • the bushing 100 comprises at least three branches 106 (or teeth or tabs) extending radially outwardly relative to the longitudinal axis ZZ of the tubular body 102 and axially along the entire length of the tubular body ( figure 2 ).
  • the three branches 106 are also distributed substantially equidistantly over the entire circumference of the tubular body 102 of the sleeve 100 (that is to say that the angle between two adjacent branches is 120 °).
  • the recess in which the sleeve is mounted is of substantially complementary shape to the latter, that is to say that it has a central bore for the passage of the tubular body of the sleeve and three grooves each receiving a branch.
  • the concentricity of the bushing 100 in the recess 104 of the inner ring 24 is thus ensured by at least three radial guides (with respect to the direction defined by the longitudinal axis XX of the turbomachine) which are materialized by the three branches. 106 of the socket distributed equidistantly.
  • the socket according to the invention and the inner ring in which the socket is intended to be mounted can be made of materials having different thermal expansion coefficients.
  • the socket can be made of steel and the inner ring of aluminum.
  • the sleeve has three branches while in the other embodiments, the sleeve is provided with four branches.
  • the sleeve may comprise a different number of branches, provided that this number is at least three and that the branches meet the previously formulated characteristics.
  • each branch of the bushing has a substantially rectangular cross section and has walls substantially parallel to a longitudinal plane of symmetry of the branch.
  • the sleeve 100 is provided with three branches 106, each having a rectangular cross section and walls 112 which are parallel to each other with respect to a longitudinal plane of symmetry 114 of the branch.
  • the bushing 200 has four branches 206 equidistantly distributed over the entire circumference of the tubular body 202 (i.e. the angle between two adjacent branches is 90 °).
  • each of the four branches 206 of the sleeve 200 has a rectangular cross section and walls 212 which are parallel to each other with respect to a longitudinal plane of symmetry (not shown in the figures for reasons of clarity). ).
  • the particular shape of the sleeve 200 according to this first embodiment makes it possible to obtain a quality of adjustment between its branches 206 and the equivalent grooves 210 of the recess 204 of the inner ring 24 which is equivalent to that which would be required for a classic accurate centering.
  • this centering can be of the H7g6 type according to the standard defined by AFNOR (French Association of Standardization) for the adjustment between two pieces.
  • this quality of adjustment is not degraded in operation, that is to say when the temperature of these two elements rises, even when these elements are made of materials having different thermal expansion coefficients.
  • branches 106, 206 rectangular cross section of the sleeves 100, 200 according to this first embodiment of the invention also provide anti-rotation of the sleeve in its recess 104, 204.
  • each branch is in the form of a tubular branch of substantially oval cross-section.
  • the bushing 300 has four tubular branches 306 distributed equidistantly around the circumference of the tubular body 302 of the bushing, each branch having a substantially oval cross-section.
  • the particular shape of the bushing 300 also ensures anti-rotation thereof in its recess 304.
  • the sleeve 400 comprises a tubular body 402 and four tubular branches 406 (only one of them is shown in these figures). Furthermore, each tubular branch 406 of the sleeve has a substantially oval cross section and is deformable.
  • each tubular branch 406 of the sleeve 400 has a recess 416 turned towards the inside of the branch which is intended to facilitate the mounting of the sleeve in its recess 404.
  • a suitable mechanical system for example by injecting a liquid or a gas inside the tubular branches, it is then possible to cause a deformation of the recess 416 of the wall of the branches 406 to the outside ( Figure 7B ).
  • the wall defined by each branch of the bushing perfectly fits the contours of the recess 404 in which the bushing is mounted, thus ensuring perfect concentricity between the bushing and the recess of the inner ring.
  • the bushing 500 comprises a tubular body 502 and four branches 506.
  • Each branch 506 of the bushing is furthermore provided with two deformable tongues 518 extending along the longitudinal axis (ZZ) of the tubular body 502, each tongue being intended for to fall back against the groove walls 510 of the recess 504 of the inner ring 24 in which the sleeve is intended to be mounted.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Description

Arrière-plan de l'inventionBackground of the invention

La présente invention se rapporte au domaine général des aubes à angle de calage variable pour turbomachine, et plus particulièrement aux douilles pour les pivots de guidage de ces aubes.The present invention relates to the general field of blades with variable pitch angle for turbomachine, and more particularly to the bushings for the guide pivots of these blades.

Le compresseur à haute pression d'une turbomachine à turbine à gaz se compose typiquement de plusieurs étages circulaires d'aubes dont l'orientation peut être réglée afin de modifier les caractéristiques d'écoulement des gaz selon les régimes de fonctionnement de la turbomachine. Ces aubes sont appelées aubes à angle de calage variable.The high-pressure compressor of a gas turbine engine typically consists of several circular blade stages whose orientation can be adjusted to change the gas flow characteristics according to the operating conditions of the turbomachine. These blades are called blades variable pitch angle.

Les aubes à angle de calage variable d'un même étage comportent chacune un pivot de commande en tête et un pivot de guidage en pied. Le pivot de commande traverse une enveloppe de stator de la turbomachine et coopère avec un organe de commande. A partir d'une action sur cet organe de commande, il est possible de modifier l'orientation des aubes de l'étage concerné. Quant au pivot de guidage des aubes, il est mobile dans une douille montée dans un évidement correspondant d'un anneau intérieur de la turbomachine centré sur l'axe longitudinal de cette dernière (voir la publication FR 2,698,405 ).The variable pitch angle vanes of the same stage each comprise a control pivot head and a foot guide pin. The control pivot passes through a stator casing of the turbomachine and cooperates with a control member. From an action on this controller, it is possible to change the orientation of the blades of the stage concerned. As for the vane guide pivot, it is movable in a bushing mounted in a corresponding recess of an inner ring of the turbomachine centered on the longitudinal axis of the latter (see the publication FR 2,698,405 ).

Lors du montage des aubes sur l'anneau intérieur, il est important d'assurer un centrage optimum des pivots de guidage des aubes. Ce centrage est obtenu en faisant en sorte que les douilles et les évidements de l'anneau intérieur dans lesquels sont montées les douilles soient parfaitement concentriques. La qualité de ce centrage des aubes doit par ailleurs être maintenue quelle que soit la phase de fonctionnement de la turbomachine. Or, les montages connus de douilles sur l'anneau intérieur ne comportent aucun aménagement particulier pour assurer le maintien de la qualité de centrage. Le centrage des pivots de guidage des aubes a donc tendance à perdre de son efficacité en fonctionnement, notamment lorsque les douilles de support pivotant et l'anneau intérieur sont réalisés dans des matériaux ayant des coefficients de dilatation thermique différents.When assembling the blades on the inner ring, it is important to ensure optimum centering of the blade guide pivots. This centering is obtained by ensuring that the bushings and the recesses of the inner ring in which the bushes are mounted are perfectly concentric. The quality of this centering of the blades must also be maintained regardless of the operating phase of the turbomachine. However, the known mounting bushings on the inner ring do not include any particular arrangement to ensure the maintenance of centering quality. The centering of the blade guide pivots therefore tends to lose its efficiency in operation, especially when the pivoting support bushes and the inner ring are made of materials having different thermal expansion coefficients.

Objet et résumé de l'inventionObject and summary of the invention

La présente invention a donc pour but principal de pallier de tels inconvénients en proposant une douille apte à assurer une qualité permanente de centrage des pivots de guidage des aubes, quelle que soit la phase de fonctionnement de la turbomachine et indépendamment des matériaux utilisés pour réaliser la douille et l'anneau intérieur dans laquelle celle-ci est montée.The main purpose of the present invention is therefore to overcome such drawbacks by proposing a socket capable of ensuring a permanent centering quality of the guide pivots of the blades, whatever the operating phase of the turbomachine and regardless of the materials used to produce the turbine. socket and the inner ring in which it is mounted.

A cet effet, il est prévu un anneau de turbomachine tel que défini par la revendication 1.For this purpose, there is provided a turbomachine ring as defined by claim 1.

L'utilisation des branches de chaque douille réparties de façon équidistante sur la circonférence du corps tubulaire de la douille permet d'assurer un centrage de la douille quelle que soit la température de fonctionnement et quels que soient les matériaux utilisés pour réaliser la douille et l'anneau intérieur.The use of the branches of each socket distributed equidistantly around the circumference of the tubular body of the socket makes it possible to center the socket whatever the operating temperature and whatever the materials used to make the socket and the socket. inner ring.

Selon un mode de réalisation de l'invention, chaque branche des douilles présente une section transversale sensiblement rectangulaire. De préférence, chaque branche des douilles présente en outre des parois sensiblement parallèles par rapport à un plan de symétrie longitudinale de la branche.According to one embodiment of the invention, each branch of the sleeves has a substantially rectangular cross section. Preferably, each branch of the sleeves also has walls substantially parallel to a longitudinal plane of symmetry of the branch.

Selon un autre mode de réalisation de l'invention, chaque branche des douilles se présente sous la forme d'une branche tubulaire de section transversale sensiblement ovale. Les parois de ces branches peuvent être déformables, chaque paroi des branches étant alors destinée à venir s'appliquer contre des parois de l'évidement de l'anneau dans lequel la douille est destinée à être montée.According to another embodiment of the invention, each branch of the bushings is in the form of a tubular branch of substantially oval cross-section. The walls of these branches can be deformable, each wall of the branches then being intended to be pressed against walls of the recess of the ring in which the sleeve is intended to be mounted.

Selon encore un autre mode de réalisation de l'invention, chaque branche des douilles est munie de deux languettes déformables s'étendant selon l'axe longitudinal du corps tubulaire, chaque languette étant destinée à venir se rabattre contre des parois de l'évidement de l'anneau dans lequel la douille est montée.According to yet another embodiment of the invention, each branch of the sleeves is provided with two deformable tongues extending along the longitudinal axis of the tubular body, each tongue being intended to be folded against the walls of the recess of the ring in which the socket is mounted.

Quel que soit le mode de réalisation, la douille comporte avantageusement au moins quatre branches réparties de façon sensiblement équidistante sur la circonférence du corps tubulaire.Whatever the embodiment, the sleeve advantageously comprises at least four branches distributed substantially equidistantly on the circumference of the tubular body.

Selon une autre caractéristique particulière de l'invention, la douille peut être réalisée dans un matériau ayant un coefficient de dilatation thermique différent de celui de l'anneau.According to another particular characteristic of the invention, the socket may be made of a material having a coefficient of thermal expansion different from that of the ring.

L'invention a également pour objet un compresseur et une turbomachine comportant au moins un anneau tel que défini précédemment.The invention also relates to a compressor and a turbomachine comprising at least one ring as defined above.

Brève description des dessinsBrief description of the drawings

D'autres caractéristiques et avantages de la présente invention ressortiront de la description faite ci-dessous, en référence aux dessins annexés qui en illustrent un exemple de réalisation dépourvu de tout caractère limitatif. Sur les figures :

  • la figure 1 est une vue en coupe d'une douille selon l'invention dans son environnement ;
  • la figure 2 est une vue en perspective de la douille de la figure 1;
  • la figure 3 est une vue en perspective de douilles montées sur un anneau selon une variante de réalisation de la douille de la figure 2 ;
  • la figure 4 est une vue de face de la douille de la figure 3 ;
  • la figure 5 est une vue en perspective de douilles montées sur un anneau selon une autre mode de réalisation de l'invention ;
  • la figure 6 est une vue de face de la douille de la figure 5 ;
  • les figures 7A et 7B sont des vues partielles d'une douille montée sur un anneau selon une variante de réalisation de la douille de la figure 6 ; et
  • la figure 8 est une vue de face d'une douille montée dans un anneau selon encore un autre mode de réalisation de l'invention.
Other features and advantages of the present invention will emerge from the description given below, with reference to the accompanying drawings which illustrate an embodiment having no limiting character. In the figures:
  • the figure 1 is a sectional view of a socket according to the invention in its environment;
  • the figure 2 is a perspective view of the socket of the figure 1 ;
  • the figure 3 is a perspective view of bushings mounted on a ring according to an embodiment variant of the bushing of the figure 2 ;
  • the figure 4 is a front view of the socket of the figure 3 ;
  • the figure 5 is a perspective view of bushings mounted on a ring according to another embodiment of the invention;
  • the figure 6 is a front view of the socket of the figure 5 ;
  • the Figures 7A and 7B are partial views of a socket mounted on a ring according to an embodiment variant of the socket of the figure 6 ; and
  • the figure 8 is a front view of a bushing mounted in a ring according to yet another embodiment of the invention.

Description détaillée d'un mode de réalisationDetailed description of an embodiment

En liaison avec la figure 1, les aubes 2 à angle de calage variable du compresseur haute-pression de la turbomachine sont réparties en étages circulaires centrés sur l'axe longitudinal X-X de la turbomachine et disposés entre des étages d'aubes mobiles (non représentées) qui sont fixées sur un rotor de la turbomachine.In connection with the figure 1 , the blades 2 variable pitch angle of the high-pressure compressor of the turbomachine are distributed in circular stages centered on the longitudinal axis XX of the turbomachine and arranged between stages of moving blades (not shown) which are fixed on a rotor of the turbomachine.

Chaque aube 2 à angle de calage variable d'un étage circulaire s'étend selon un axe principal Y-Y qui possède une direction radiale par rapport à l'axe longitudinal X-X de la turbomachine. L'aube 2 se présente sous la forme d'une pale 4 se terminant à une extrémité radiale externe (ou tête d'aube) par un pivot de commande 6 (ou pivot supérieur) et à une extrémité radiale interne (ou pied d'aube) par un pivot de guidage 8 (ou pivot inférieur).Each blade 2 with variable pitch angle of a circular stage extends along a main axis Y-Y which has a radial direction relative to the longitudinal axis X-X of the turbomachine. The blade 2 is in the form of a blade 4 ending at an outer radial end (or blade head) by a control pivot 6 (or upper pivot) and at an inner radial end (or foot of dawn) by a guide pin 8 (or lower pivot).

Le pivot de commande 6 de l'aube 2 à angle de calage variable, centré sur son axe principal Y-Y, traverse une enveloppe annulaire 10 de stator de la turbomachine et coopère avec un organe de commande de l'orientation des aubes. Plus précisément, le pivot de commande 6 des aubes 2 fait saillie radialement vers l'extérieur de l'enveloppe 10 de stator et se termine par une tête 12 sur laquelle est engagée une extrémité de bielle de commande 14 dont l'autre extrémité coopère avec un anneau de commande 16 centré sur l'axe longitudinal X-X de la turbomachine.The control pivot 6 of the blade 2 variable pitch angle, centered on its main axis Y-Y, through an annular envelope 10 of the stator of the turbomachine and cooperates with a control member of the orientation of the blades. More specifically, the control pivot 6 of the blades 2 protrudes radially outwardly of the stator casing 10 and ends with a head 12 on which is engaged a control rod end 14 whose other end cooperates with a control ring 16 centered on the longitudinal axis XX of the turbomachine.

Les bielles 14 et l'anneau 16 de commande forment l'organe de commande de l'orientation des aubes. La rotation de l'anneau de commande 16 autour de l'axe longitudinal X-X de la turbomachine permet en effet de faire tourner les bielles de commande 14 et ainsi de modifier simultanément l'orientation de toutes les aubes 2 à calage variable d'un même étage du compresseur haute-pression.The rods 14 and the control ring 16 form the control member of the orientation of the blades. The rotation of the control ring 16 around the longitudinal axis XX of the turbomachine makes it possible to rotate the control rods 14 and thus simultaneously change the orientation of all the blades 2 variable pitch of the same stage of the high-pressure compressor.

Le pivot de guidage 8 de l'aube 2 à angle de calage variable, centré sur son axe principal Y-Y, est destiné à pivoter à l'intérieur d'une douille creuse 100.The guide pin 8 of the blade 2 with variable pitch angle, centered on its main axis Y-Y, is intended to pivot inside a hollow sleeve 100.

Chaque douille 100 est montée dans un évidement 104 formé dans un anneau intérieur 24 du compresseur haute-pression de la turbomachine qui est centré sur l'axe longitudinal X-X de la turbomachine, la douille et l'évidement étant de formes sensiblement complémentaires.Each bushing 100 is mounted in a recess 104 formed in an inner ring 24 of the high-pressure compressor of the turbomachine which is centered on the longitudinal axis XX of the turbomachine, the bushing and the recess being of substantially complementary shapes.

Par ailleurs, comme illustré sur la figure 1, une douille supplémentaire 26 formant frette peut être montée serrée autour de chaque pivot de guidage 8 des aubes 2. Une telle douille supplémentaire 26 de forme sensiblement cylindrique vient s'interposer entre le pivot de guidage 8 des aubes et la douille 100. Elle permet ainsi d'éviter toute usure prématurée de la douille.Moreover, as illustrated on the figure 1 , an additional sleeve 26 forming a collar can be mounted tightly around each guide pin 8 of the blades 2. Such additional sleeve 26 of substantially cylindrical shape is interposed between the guide pin 8 of the blades and the sleeve 100. It allows thus to avoid premature wear of the socket.

Comme illustré sur la figure 2, la douille 100 présente un corps sensiblement tubulaire 102 d'axe longitudinal Z-Z qui est destiné à recevoir le pivot de guidage 8 de l'aube.As illustrated on the figure 2 , the sleeve 100 has a substantially tubular body 102 of longitudinal axis ZZ which is intended to receive the guide pin 8 of the blade.

Selon l'invention, afin d'assurer une parfaite concentricité entre la douille 100 et l'évidement 104 quels que soit la température de fonctionnement et les matériaux de fabrication de ces pièces, la douille 100 comporte au moins trois branches 106 (ou dents ou pattes) qui s'étendent, d'une part radialement vers l'extérieur par rapport à l'axe longitudinal Z-Z du corps tubulaire 102, et d'autre part axialement sur toute la hauteur longitudinale du corps tubulaire (figure 2). Les trois branches 106 sont par ailleurs réparties de façon sensiblement équidistante sur toute la circonférence du corps tubulaire 102 de la douille 100 (c'est-à-dire que l'angle entre deux branches adjacentes est de 120°).According to the invention, in order to ensure perfect concentricity between the bushing 100 and the recess 104 whatever the operating temperature and the materials of manufacture of these parts, the bushing 100 comprises at least three branches 106 (or teeth or tabs) extending radially outwardly relative to the longitudinal axis ZZ of the tubular body 102 and axially along the entire length of the tubular body ( figure 2 ). The three branches 106 are also distributed substantially equidistantly over the entire circumference of the tubular body 102 of the sleeve 100 (that is to say that the angle between two adjacent branches is 120 °).

Bien entendu, comme expliqué précédemment, l'évidement dans lequel est montée la douille est de forme sensiblement complémentaire à cette dernière, c'est-à-dire qu'il présente un alésage central pour le passage du corps tubulaire de la douille et trois rainures recevant chacune une branche.Of course, as explained above, the recess in which the sleeve is mounted is of substantially complementary shape to the latter, that is to say that it has a central bore for the passage of the tubular body of the sleeve and three grooves each receiving a branch.

La concentricité de la douille 100 dans l'évidement 104 de l'anneau intérieur 24 est ainsi assurée par au minimum trois guidages radiaux (par rapport à la direction définie par l'axe longitudinal X-X de la turbomachine) qui sont matérialisés par les trois branches 106 de la douille réparties de façon équidistante.The concentricity of the bushing 100 in the recess 104 of the inner ring 24 is thus ensured by at least three radial guides (with respect to the direction defined by the longitudinal axis XX of the turbomachine) which are materialized by the three branches. 106 of the socket distributed equidistantly.

La douille selon l'invention et l'anneau intérieur dans lequel la douille est destinée à être montée peuvent être réalisés dans des matériaux ayant des coefficients de dilatation thermique différents. A titre d'exemple, la douille peut être réalisée en acier et l'anneau intérieur en aluminium.The socket according to the invention and the inner ring in which the socket is intended to be mounted can be made of materials having different thermal expansion coefficients. For example, the socket can be made of steel and the inner ring of aluminum.

On décrira maintenant différents modes de réalisation de la douille selon l'invention. Dans le mode de réalisation illustré par les figures 1 et 2, la douille comporte trois branches tandis que dans les autres modes de réalisation, la douille est munie de quatre branches. Bien entendu, dans tous ces modes de réalisation, la douille peut comporter un nombre différent de branches, à condition que ce nombre soit au moins égal à trois et que les branches répondent aux caractéristiques formulées précédemment.Various embodiments of the sleeve according to the invention will now be described. In the embodiment illustrated by the figures 1 and 2 , the sleeve has three branches while in the other embodiments, the sleeve is provided with four branches. Of course, in all these embodiments, the sleeve may comprise a different number of branches, provided that this number is at least three and that the branches meet the previously formulated characteristics.

Selon un premier mode de réalisation de la douille selon l'invention représenté par les figures 1 à 4, chaque branche de la douille présente une section transversale sensiblement rectangulaire et comporte des parois sensiblement parallèles par rapport à un plan de symétrie longitudinale de la branche.According to a first embodiment of the socket according to the invention represented by the Figures 1 to 4 each branch of the bushing has a substantially rectangular cross section and has walls substantially parallel to a longitudinal plane of symmetry of the branch.

Ainsi, sur l'exemple de réalisation de la figure 2, la douille 100 est munie de trois branches 106, chacune ayant une section transversale rectangulaire et des parois 112 qui sont parallèles entre elles par rapport à un plan de symétrie longitudinale 114 de la branche.So, on the embodiment of the figure 2 , the sleeve 100 is provided with three branches 106, each having a rectangular cross section and walls 112 which are parallel to each other with respect to a longitudinal plane of symmetry 114 of the branch.

Selon une variante de ce premier mode de réalisation illustrée par les figures 3 et 4, la douille 200 comporte quatre branches 206 réparties de façon équidistante sur toute la circonférence du corps tubulaire 202 (c'est-à-dire que l'angle entre deux branches adjacentes est de 90°).According to a variant of this first embodiment illustrated by the figures 3 and 4 the bushing 200 has four branches 206 equidistantly distributed over the entire circumference of the tubular body 202 (i.e. the angle between two adjacent branches is 90 °).

Par ailleurs, chacune des quatre branches 206 de la douille 200 selon cette variante de réalisation présente une section transversale rectangulaire et des parois 212 qui sont parallèles entre elles par rapport à un plan de symétrie longitudinale (non représenté sur les figures pour des raisons de clarté).Moreover, each of the four branches 206 of the sleeve 200 according to this embodiment has a rectangular cross section and walls 212 which are parallel to each other with respect to a longitudinal plane of symmetry (not shown in the figures for reasons of clarity). ).

Comme illustré sur la figure 4, la forme particulière de la douille 200 selon ce premier mode de réalisation permet d'obtenir au montage une qualité d'ajustement entre ses branches 206 et les rainures équivalentes 210 de l'évidement 204 de l'anneau intérieur 24 qui est équivalente à celle qui serait exigée pour un centrage précis classique. A titre d'exemple, ce centrage peut être de type H7g6 selon la norme définie par l'AFNOR (Association Française de Normalisation) pour l'ajustement entre deux pièces.As illustrated on the figure 4 , the particular shape of the sleeve 200 according to this first embodiment makes it possible to obtain a quality of adjustment between its branches 206 and the equivalent grooves 210 of the recess 204 of the inner ring 24 which is equivalent to that which would be required for a classic accurate centering. By way of example, this centering can be of the H7g6 type according to the standard defined by AFNOR (French Association of Standardization) for the adjustment between two pieces.

Par ailleurs, cette qualité d'ajustement n'est pas dégradée en fonctionnement, c'est-à-dire lorsque la température de ces deux éléments s'élève, même lorsque ces éléments sont réalisés dans des matériaux ayant des coefficients de dilatation thermique différents. Il existe également un faible jeu entre l'alésage central 208 de l'évidement 204 pour le passage du corps tubulaire 202 de la douille. A froid, ce jeu peut être de l'ordre de 0,2mm environ pour une douille ayant un corps tubulaire de 9mm de diamètre externe.Moreover, this quality of adjustment is not degraded in operation, that is to say when the temperature of these two elements rises, even when these elements are made of materials having different thermal expansion coefficients. There is also a small clearance between the central bore 208 of the recess 204 for the passage of the tubular body 202 of the sleeve. In cold, this game can be of the order of about 0.2mm for a socket having a tubular body of 9mm external diameter.

On notera les branches 106, 206 à section transversale rectangulaire des douilles 100, 200 selon ce premier mode de réalisation de l'invention assurent également une anti-rotation de la douille dans son évidement 104, 204.Note the branches 106, 206 rectangular cross section of the sleeves 100, 200 according to this first embodiment of the invention also provide anti-rotation of the sleeve in its recess 104, 204.

Selon un second mode de réalisation de la douille selon l'invention représenté par les figures 5, 6, 7A et 7B, chaque branche se présente sous la forme d'un branche tubulaire de section transversale sensiblement ovale.According to a second embodiment of the socket according to the invention represented by the figures 5 , 6 , 7A and 7B each branch is in the form of a tubular branch of substantially oval cross-section.

Ainsi, sur l'exemple de réalisation des figures 5 et 6, la douille 300 comporte quatre branches tubulaires 306 réparties de façon équidistante sur la circonférence du corps tubulaire 302 de la douille, chaque branche ayant une section transversale sensiblement ovale.Thus, on the exemplary embodiment of figures 5 and 6 , the bushing 300 has four tubular branches 306 distributed equidistantly around the circumference of the tubular body 302 of the bushing, each branch having a substantially oval cross-section.

Comme illustré sur la figure 6, lors du montage de la douille 300 dans l'évidement 304 de l'anneau intérieur 24, il existe un faible jeu entre les rainures 310 de l'évidement et les branches tubulaires 306 de la douille. Par application d'un effort mécanique, par exemple par injection d'un fluide sous pression dans les branches tubulaires 306, les parois de ces branches viennent s'appliquer contre les parois de l'évidement de l'anneau intérieur pour combler ce jeu comme cela est représenté par les flèches sur la figure 6. Ainsi, il est possible d'assurer une parfaite concentricité entre la douille et l'évidement de l'anneau intérieur dès la montée en température de ces deux éléments.As illustrated on the figure 6 when the bushing 300 is mounted in the recess 304 of the inner ring 24, there is little clearance between the grooves 310 of the recess and the tubular branches 306 of the bushing. By application of a mechanical force, for example by injection of a pressurized fluid into the tubular branches 306, the walls of these branches are pressed against the walls of the recess of the inner ring to fill this game as this is represented by the arrows on the figure 6 . Thus, it is possible to ensure perfect concentricity between the bushing and the recess of the inner ring as soon as the temperature rise of these two elements.

Comme pour le premier mode de réalisation précédemment décrit, la forme particulière de la douille 300 assure également une anti-rotation de celle-ci dans son évidement 304.As for the first embodiment previously described, the particular shape of the bushing 300 also ensures anti-rotation thereof in its recess 304.

Selon une variante de ce second mode de réalisation illustrée par les figures 7A et 7B, la douille 400 comporte un corps tubulaire 402 et quatre branches tubulaires 406 (une seule d'entre elles est représentée sur ces figures). Par ailleurs, chaque branche tubulaire 406 de la douille présente une section transversale sensiblement ovale et est déformable.According to a variant of this second embodiment illustrated by the Figures 7A and 7B , the sleeve 400 comprises a tubular body 402 and four tubular branches 406 (only one of them is shown in these figures). Furthermore, each tubular branch 406 of the sleeve has a substantially oval cross section and is deformable.

Plus précisément, comme représenté sur la figure 7A, la paroi définie par chaque branche tubulaire 406 de la douille 400 présente un renfoncement 416 tourné vers l'intérieur de la branche qui est destiné à faciliter le montage de la douille dans son évidement 404. Par l'intermédiaire d'un système mécanique adapté, par exemple en injectant un liquide ou un gaz à l'intérieur des branches tubulaires, il est ensuite possible de provoquer une déformation du renfoncement 416 de la paroi des branches 406 vers l'extérieur (figure 7B). De la sorte, la paroi définie par chaque branche de la douille vient épouser parfaitement les contours de l'évidement 404 dans lequel est montée la douille, assurant ainsi une parfaite concentricité entre la douille et l'évidement de l'anneau intérieur.More precisely, as represented on the Figure 7A , the wall defined by each tubular branch 406 of the sleeve 400 has a recess 416 turned towards the inside of the branch which is intended to facilitate the mounting of the sleeve in its recess 404. Via a suitable mechanical system for example by injecting a liquid or a gas inside the tubular branches, it is then possible to cause a deformation of the recess 416 of the wall of the branches 406 to the outside ( Figure 7B ). In this way, the wall defined by each branch of the bushing perfectly fits the contours of the recess 404 in which the bushing is mounted, thus ensuring perfect concentricity between the bushing and the recess of the inner ring.

Selon encore un autre mode de réalisation de l'invention représenté par la figure 8, la douille 500 comporte un corps tubulaire 502 et quatre branches 506. Chaque branche 506 de la douille est par ailleurs munie de deux languettes déformables 518 s'étendant selon l'axe longitudinal (Z-Z) du corps tubulaire 502, chaque languette étant destinée à venir se rabattre contre les parois de rainures 510 de l'évidement 504 de l'anneau intérieur 24 dans lequel la douille est destinée à être montée.According to yet another embodiment of the invention represented by the figure 8 the bushing 500 comprises a tubular body 502 and four branches 506. Each branch 506 of the bushing is furthermore provided with two deformable tongues 518 extending along the longitudinal axis (ZZ) of the tubular body 502, each tongue being intended for to fall back against the groove walls 510 of the recess 504 of the inner ring 24 in which the sleeve is intended to be mounted.

Claims (10)

  1. A turbomachine ring (24) including a plurality of recesses (104, 204, 304, 404, 504) each for receiving a guide pivot (8) of a variable-pitch vane (2), and a plurality of bushings (100, 200, 300, 400, 500) each mounted in one of said recesses, characterised in that each bushing comprises a body (102, 202, 302, 402, 502) that is substantially tubular having a longitudinal axis (Z-Z) and at least three branches (106, 206, 306, 406, 506) extending radially outwards relative to the longitudinal axis (Z-Z) of the tubular body and being distributed in substantially equidistant manner around the circumference of the tubular body, said branches extending axially over the full height of said tubular body.
  2. A ring according to claim 1, in which each branch (106, 206, 306, 406, 506) of the bushings presents a cross-section that is substantially rectangular.
  3. A ring according to claim 2, in which each branch (106, 206) of the bushings presents walls that are substantially parallel on either side of a longitudinal plane of symmetry (114) of the branch.
  4. A ring according to claim 1, in which each branch of the bushings (300, 400) is in the form of a tubular branch (306, 406) of cross-section that is substantially oval.
  5. A ring according to claim 4, in which the walls of the branches (406) of the bushings (400) are deformable, each wall of the branches being for pressing against walls of the recess (404) in the ring in which the bushing (400) is mounted.
  6. A ring according to claim 1, in which each branch (506) of the bushings (500) is provided with two deformable tongues (518) extending along the longitudinal axis (Z-Z) of the tubular body (502), each tongue (518, 520) being for folding down against walls of the recess (504) in the ring in which the bushing (500) is mounted.
  7. A ring according to any one of claims 1 to 6, in which each bushing comprises at least four branches (106, 206, 306, 406, 506) distributed in substantially equidistant manner around the circumference of the tubular body.
  8. A ring according to any one of claims 1 to 7, in which each bushing is made of a material having a coefficient of thermal expansion that is different from that of the ring.
  9. A turbomachine compressor comprising at least one ring according to any one of claims 1 to 8.
  10. A turbomachine comprising at least one ring according to any one of claims 1 to 8.
EP06117010.6A 2005-07-27 2006-07-12 Bushing for pivoting the variable vanes of a turbomachine Active EP1748158B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0508000A FR2889242B1 (en) 2005-07-27 2005-07-27 SOCKET FOR VANE PIVOT WITH VARIABLE SETTING ANGLE FOR TURBOMACHINE

Publications (2)

Publication Number Publication Date
EP1748158A1 EP1748158A1 (en) 2007-01-31
EP1748158B1 true EP1748158B1 (en) 2017-03-01

Family

ID=36182397

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06117010.6A Active EP1748158B1 (en) 2005-07-27 2006-07-12 Bushing for pivoting the variable vanes of a turbomachine

Country Status (4)

Country Link
US (1) US7670106B2 (en)
EP (1) EP1748158B1 (en)
FR (1) FR2889242B1 (en)
RU (1) RU2405941C2 (en)

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7451093B2 (en) * 2004-04-29 2008-11-11 Srs Labs, Inc. Systems and methods of remotely enabling sound enhancement techniques
US7360990B2 (en) * 2004-10-13 2008-04-22 General Electric Company Methods and apparatus for assembling gas turbine engines
US8050434B1 (en) 2006-12-21 2011-11-01 Srs Labs, Inc. Multi-channel audio enhancement system
FR2913048B1 (en) * 2007-02-28 2009-04-10 Snecma Sa TURBOMACHINE BLOWER
WO2013032822A2 (en) 2011-08-26 2013-03-07 Dts Llc Audio adjustment system
US9932988B2 (en) 2013-02-15 2018-04-03 United Technologies Corporation Bushing arranged between a body and a shaft, and connected to the shaft
EP3039252B1 (en) * 2013-08-28 2024-09-25 RTX Corporation Variable vane bushing
FR3055374B1 (en) * 2016-08-23 2018-08-03 Safran Aircraft Engines INTERFACE PIECE FOR RECONDITIONING A CONTROL RING OF A MOTOR COMPRESSOR, AND ASSOCIATED RECONDITIONING METHOD
DE102016215807A1 (en) * 2016-08-23 2018-03-01 MTU Aero Engines AG Inner ring for a vane ring of a turbomachine
DE102017109952A1 (en) * 2017-05-09 2018-11-15 Rolls-Royce Deutschland Ltd & Co Kg Rotor device of a turbomachine
FR3079553B1 (en) * 2018-03-30 2020-03-13 Safran Aircraft Engines TURBOMACHINE ASSEMBLY
DE102018210601A1 (en) * 2018-06-28 2020-01-02 MTU Aero Engines AG SEGMENT RING FOR ASSEMBLY IN A FLOWING MACHINE
US11428243B2 (en) * 2019-09-09 2022-08-30 Raytheon Technologies Corporation Variable vane arrangement with vane receptacle insert(s)

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2698405B1 (en) * 1992-11-25 1994-12-23 Snecma Multi-stage turbomachine of stator blades with variable orientation.
US5893446A (en) * 1995-08-11 1999-04-13 Exedy Corporation Clutch disc assembly
FR2742799B1 (en) * 1995-12-20 1998-01-16 Snecma INTERNAL END END OF PIVOTING VANE
US6086327A (en) * 1999-01-20 2000-07-11 Mack Plastics Corporation Bushing for a jet engine vane
US6481960B2 (en) * 2001-03-30 2002-11-19 General Electric Co. Variable gas turbine compressor vane structure with sintered-and-infiltrated bushing and washer bearings
ITTO20020428A1 (en) * 2002-05-20 2003-11-20 Tecnost Sistemi S P A INK JET PRINTER WITH HIGH CAPACITY TANK AND RELATED INK SUPPLY SYSTEM.
US7360990B2 (en) * 2004-10-13 2008-04-22 General Electric Company Methods and apparatus for assembling gas turbine engines

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
RU2405941C2 (en) 2010-12-10
FR2889242B1 (en) 2007-11-02
RU2006127188A (en) 2008-02-10
FR2889242A1 (en) 2007-02-02
US20070025842A1 (en) 2007-02-01
US7670106B2 (en) 2010-03-02
EP1748158A1 (en) 2007-01-31

Similar Documents

Publication Publication Date Title
EP1748158B1 (en) Bushing for pivoting the variable vanes of a turbomachine
EP1764483B1 (en) Bushing for the pivot of a variable pitch vane of a turbomachine, and corresponding stator blading, compressor and turbomachine
FR2941018A1 (en) A VARIABLE CALIPER FOR A RECTIFIER STAGE, COMPRISING A NON-CIRCULAR INTERNAL PLATFORM
EP1481756B1 (en) Method of fabricating a hollow turbine blade
CA2763415A1 (en) Stationary actuator device for controlling the orientation of the blades of a turboprop fan
EP1887188B1 (en) Control device of a variable pitch angle blade of a turbomachine with cylindrical connecting rod
CA2885650C (en) Turbomachine casing and impeller
EP0947668A1 (en) Circular row of turbomachine guide vanes with inner ends assembled by a linking ring
FR2814206A1 (en) VARIABLE SETTING BLADE CONTROL DEVICE
EP2053203A1 (en) Improvement of a ring for controlling the pitch of stator vanes of a turbomachine.
EP1577495B1 (en) Turbomachine rolling bearing assembly having a reduced space requirement
CA2518355A1 (en) Retention of centring keys of the rings under the variable setting stator blades of a gas turbine engine
FR3085712A1 (en) MOBILE WHEEL BLADE FOR AN AIRCRAFT TURBOMACHINE HAVING A DECOUPLED BLADE HEEL
FR3029562A1 (en) CONTROL RING OF A VARIABLE SHIFT AUBRA STAGE FOR A TURBOMACHINE
FR3080146A1 (en) CMC DISPENSER WITH EFFORT REPEAT
EP3759319B1 (en) Assembly for a turbomachine
FR2874977A1 (en) Pivoting carrier bushing for variable vane`s pivot, has polygonal transversal section and shoulder, and is composed of single piece, where shoulder cooperates with complementary notch formed in inner ring sector of inner ring
FR2882577A1 (en) Actuating ring`s centering adjusting device for rotary blade of turbomachine, has brake shoe comprising rod with longitudinal groove, and washer comprising radial pin engaged in groove and radial slots engaged in slots of cavity of ring
EP0780545A1 (en) Arrangement of the root ends of a variable angle row of blades
FR2966426A1 (en) HYDRAULIC DEVICE FOR CHANGING PROPELLER PITCH
WO2023041868A1 (en) Moving blade for a turbine of a turbine engine, comprising a stilt equipped with projections for radially retaining the blade
EP4305281A1 (en) Bearing for turbomachine variable pitch stator vane pivot, stator vane comprising such a bearing and turbomachine comprising such stator vanes
FR2994453A1 (en) Radial inner assembly for bladed ring sector of compressor stator or turbine of e.g. turbojet engine of aircraft, has anti-rotation edge whose length is greater than maximum spacing distance between projections of casing head
FR3011585A1 (en) AIRCRAFT TURBOMACHINE ASSEMBLY COMPRISING A FREESTRATED AXIAL HOLDING RING OF A BRUSH JOINT
FR3079553A1 (en) ASSEMBLY FOR TURBOMACHINE

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: 20060712

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 LV MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK YU

AKX Designation fees paid

Designated state(s): DE FR GB

17Q First examination report despatched

Effective date: 20160525

REG Reference to a national code

Ref country code: DE

Ref legal event code: R079

Ref document number: 602006051807

Country of ref document: DE

Free format text: PREVIOUS MAIN CLASS: F01D0017160000

Ipc: F04D0029560000

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

RIC1 Information provided on ipc code assigned before grant

Ipc: F01D 9/04 20060101ALI20160913BHEP

Ipc: F04D 29/56 20060101AFI20160913BHEP

Ipc: F02B 37/24 20060101ALI20160913BHEP

Ipc: F01D 17/16 20060101ALI20160913BHEP

INTG Intention to grant announced

Effective date: 20160930

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 FR GB

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602006051807

Country of ref document: DE

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: DE

Ref legal event code: R097

Ref document number: 602006051807

Country of ref document: DE

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: 20171204

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 13

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20240620

Year of fee payment: 19

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20240619

Year of fee payment: 19

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20240619

Year of fee payment: 19