EP1936121B1 - Angular setting of turbomachine stator vanes. - Google Patents

Angular setting of turbomachine stator vanes. Download PDF

Info

Publication number
EP1936121B1
EP1936121B1 EP06292026A EP06292026A EP1936121B1 EP 1936121 B1 EP1936121 B1 EP 1936121B1 EP 06292026 A EP06292026 A EP 06292026A EP 06292026 A EP06292026 A EP 06292026A EP 1936121 B1 EP1936121 B1 EP 1936121B1
Authority
EP
European Patent Office
Prior art keywords
platform
groove
blade
blade according
housing
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.)
Not-in-force
Application number
EP06292026A
Other languages
German (de)
French (fr)
Other versions
EP1936121A1 (en
Inventor
David Robert Gilbert Depaepe
Philippe Ernst
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 Aero Boosters SA
Original Assignee
Techspace Aero SA
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 Techspace Aero SA filed Critical Techspace Aero SA
Priority to EP06292026A priority Critical patent/EP1936121B1/en
Priority to AT06292026T priority patent/ATE556197T1/en
Priority to US11/962,852 priority patent/US8075264B2/en
Publication of EP1936121A1 publication Critical patent/EP1936121A1/en
Application granted granted Critical
Publication of EP1936121B1 publication Critical patent/EP1936121B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • 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
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/64—Mounting; Assembling; Disassembling of axial pumps
    • F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/128—Nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/182—Two-dimensional patterned crenellated, notched
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position

Definitions

  • the present invention relates to turbomachine stator vanes, such as in particular an aircraft turbojet engine.
  • a stator blade comprises a blade, connected at its radially outer end to a platform, with a threaded rod which extends radially outwardly from the platform.
  • the upstream and downstream edges of the platform are engaged in an annular groove formed in the inner surface of a substantially cylindrical housing, the rod being inserted into a hole in the bottom of the groove.
  • the dawn thus positioned is wedged angularly by abutment of the platform on the flanks of the groove.
  • a nut is screwed onto the threaded rod to secure the blade to the crankcase. The tightening of the nut on the casing makes it possible to maintain the stator vane in a fixed position so that it optimally assures its function of rectifying the flow of air circulating in the turbomachine.
  • the nominal width of the platform i.e. its nominal dimension in the longitudinal plane of the turbomachine
  • Nominal width of the groove which induces a minimum clearance of the platform mounted in the groove.
  • Clamping the fixing nut causes an angular offset of the platform of the blade which is more or less important because of the manufacturing tolerances of the groove of the housing and the platform.
  • the blade of the blade is thus angularly offset with respect to its theoretical position and therefore no longer provides optimum recovery of the air flow through the turbomachine.
  • the angular offset of several stator vanes can thus lead to a loss of efficiency and efficiency of the turbomachine.
  • stator vanes which comprise non-circular contoured platforms, housed in orifices having a shape conjugate with that of the platforms, which are formed in a ring fixedly mounted in a groove of a casing, this arrangement permitting to give a predetermined orientation to the stator vanes but not taking into account the variations due to the manufacturing tolerances of the vanes, rings and grooves of the casing.
  • the invention proposes to improve the angular setting of the blade in the groove simply, efficiently and economically.
  • a turbomachine rectifier blade comprising a platform arranged at a radially outer end of the blade and intended to be engaged in an annular groove of an inner surface of a housing, and a threaded rod. extending radially outwardly from the platform and intended to pass through an orifice of the housing to receive an attachment nut external to the housing, characterized in that the upstream and downstream edges of the platform each comprise a protrusion extending in the plane of the platform to limit the rotation of the platform in the groove when tightening the nut screwed on the threaded rod.
  • the platform is substantially rectangular and a projection is located at one end of the upstream edge of the platform and the other projection is substantially symmetrical with the first relative to the center of the platform.
  • the positioning of the projections at opposite ends of the platform makes it possible to have an optimum tightening torque when the nut is screwed onto the threaded rod while avoiding any marking phenomenon by matting the parts.
  • the projections are formed at the ends of the edges of the platform which are intended to bear against the flanks of the groove when tightening the fixing nut.
  • the projections are of substantially rectangular shape and have a dimension, in the direction of the flanks of the groove, defined as a function of the clearance necessary for mounting the platform in the groove taking into account tolerances on the width of the groove and the platform.
  • the threaded rod is connected to a central portion of the platform forming an extra thickness with respect to the upstream and downstream edges of the platform, the thickened portion being able to form a circular zone centered on the axis of the stem.
  • the projections and the extra thickness of the platform can be made for example by machining.
  • the invention also relates to a turbomachine, such as an aircraft turbojet, characterized in that it comprises stator vanes of the type described above.
  • FIG. 1 represents an alternation of blades 10 and vanes 12 such that one can, for example, find it in a compressor of a turbomachine.
  • the blades 10 are connected in their radially inner portion to a rotor, the vanes being fixed to a housing in their radially inner and radially outer portion.
  • a fixed blade comprises a substantially rectangular platform 14 connecting the radially outer end of a blade 16 to a threaded rod 18 extending radially outwardly from the platform.
  • the platform 14 is engaged in an annular groove 20 of the inner surface of a housing with a geometry of revolution 22 and held fixed in the groove by the rod 18 which is inserted into a radial orifice 24 of the housing 22.
  • Nuts 26 fastening are screwed on the rods 18 to ensure the tightening of the blade on the housing 22.
  • the blades and the vanes cooperate to pass air through the different parts of the engine.
  • the blades also called stator vanes
  • the blades have the function of straightening the flow of air flowing in the turbomachine.
  • the orientation of the blades 16 of the stator vanes 12 with respect to the air flow is essential to ensure optimum operation of the turbomachine.
  • a minimum clearance must be provided between the groove 20 and the platform 14 to ensure the insertion of the platform 14 of the blade in the groove 20.
  • the nominal width of the platform that is to say, its nominal dimension along the axis of the turbomachine must necessarily be less than the nominal width of the groove 20.
  • the blade 12 thus mounted, after tightening the nut 26 on the housing, has a angular offset in the groove 20. This shift is more or less important depending on the actual width of the platform and the actual width of the groove are at the upper or lower limit of manufacturing tolerances.
  • important means in terms of tooling and control of the orientation of the blade platforms are necessary, thus making expensive and long the mounting operation of the straightening vanes.
  • the invention proposes, to reduce the angular offset of the rectifier blades assembly, to form projections 28 at the ends of the upstream and downstream edges of the platform, these projections extending in the plane of the platform.
  • These projections 28 are of substantially rectangular shape in the embodiment of the Figures 3 to 5 and are placed at two vertices of the platform 14, symmetrically with respect to the center of the platform 14. These two vertices are those which come to rest on the flanks of the groove when the tightening of the nut fastening rotates the platform of the blade in the groove, and the projections are at the ends of the upstream and downstream edges of the platform which depart from these two peaks.
  • Such placement of the projections allows to have a maximum torque at the nut fixing the blade when the projections bear against the flanks of the groove.
  • projections 28 at the ends of the upstream and downstream edges of the platform makes it possible to size the platform 14 of the blade 12 so that its nominal width is equal to the nominal width of the groove 20.
  • Two cases can be distinguished according to the fact that, due to the manufacturing tolerances of the parts, the actual width of the platform is less than or greater than the actual width of the groove.
  • figure 4 is represented the case where the actual width of the platform 14 is greater than the actual width of the groove 20.
  • the rotation of the blade 12 in the opposite direction to the clamping reduces the axial size of the plate -form 14 so that it is less than the actual width of the groove 20.
  • the insertion of the platform 14 in the groove 20 can thus be performed.
  • figure 5 is shown the case where the actual width of the platform is less than the actual width of the groove 20.
  • the insertion of the platform 14 into the groove 20 presents no difficulty and we are then in a configuration mounting similar to that of the prior art.
  • the dimensions of the projections 28 must be chosen according to the manufacturing tolerances of the parts so that the insertion of the platform 14 into the groove 20 is always possible. In particular, to avoid creating additional stress zones, it is important that the length of the projections 28 is sufficient for the contacts between the platform 14 and the groove 20 to be made at the projections 28 and not at the level of the projections 28. vertices of the platform 14 which do not include projection.
  • the two projections of the platform may have the same width or dimension in the longitudinal plane of the turbomachine, defined as a function of the clearance needed to mount the platform in the groove taking into account the tolerances on the width of the groove and the platform.
  • each projection is of the order of 0.2 to 0.3 mm and its length is of the order of 5 mm. These dimensions are given as an indication for a platform and a groove of nominal width of about 50 mm, the lateral dimension of the platform being about 30 mm.
  • the platform comprises a thickened part 30, forming a circular zone, centered on the axis of the threaded rod 18.
  • the contact between the platform 14 and the housing 22 is thus limited to the portion 30 of extra thickness and does not extend to the upstream and downstream edges of the platform, which makes it possible to reduce the stresses on the leading edge 32 and the trailing edge 34 of the blade 16 which are due to the clamping of the threaded rod 18 on the housing 22.
  • the projections and the extra thickness of the platform can be made by machining.
  • the invention is therefore particularly interesting in that it makes it possible to improve the initial positioning of a blade in a groove of a casing, while maintaining the same manufacturing tolerances.

Landscapes

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

Abstract

The vane (12) has a platform body (14) arranged at an end radially external of the vane and a threaded rod (18) extended radially towards exterior of the body, where the rod is passed through an opening of a casing for receiving a fixation screw outside the casing. The upstream and downstream edges of the body have a ridge (28) extended in a plane of the body for limiting the rotation of the body in an annular groove during tightening the screw on the rod. The threaded rod is connected to a central part of the body.

Description

La présente invention concerne des aubes de redresseur pour turbomachine, telle en particulier qu'un turboréacteur d'avion.The present invention relates to turbomachine stator vanes, such as in particular an aircraft turbojet engine.

De façon connue, une aube de redresseur comprend une pale, raccordée à son extrémité radialement externe à une plate-forme, avec une tige filetée qui s'étend radialement vers l'extérieur depuis la plate-forme. Les bords amont et aval de la plate-forme sont engagés dans une rainure annulaire formée dans la surface interne d'un carter sensiblement cylindrique, la tige étant insérée dans un orifice du fond de la rainure. L'aube ainsi positionnée est calée angulairement par butée de la plate-forme sur les flancs de la rainure. Un écrou est vissé sur la tige filetée pour fixer l'aube sur le carter. Le serrage de l'écrou sur le carter permet de maintenir l'aube de redresseur dans une position fixe afin que celle-ci assure au mieux sa fonction de redressement du flux d'air circulant dans la turbomachine.In known manner, a stator blade comprises a blade, connected at its radially outer end to a platform, with a threaded rod which extends radially outwardly from the platform. The upstream and downstream edges of the platform are engaged in an annular groove formed in the inner surface of a substantially cylindrical housing, the rod being inserted into a hole in the bottom of the groove. The dawn thus positioned is wedged angularly by abutment of the platform on the flanks of the groove. A nut is screwed onto the threaded rod to secure the blade to the crankcase. The tightening of the nut on the casing makes it possible to maintain the stator vane in a fixed position so that it optimally assures its function of rectifying the flow of air circulating in the turbomachine.

Dans la technique actuelle, pour positionner la plate-forme de l'aube dans la rainure, la largeur nominale de la plate-forme, c'est-à-dire sa dimension nominale dans le plan longitudinal de la turbomachine, est inférieure à la largeur nominale de la rainure, ce qui induit un jeu minimal de la plate-forme montée dans la rainure. Le serrage de l'écrou de fixation engendre un décalage angulaire de la plateforme de l'aube lequel est plus ou moins important du fait des tolérances de fabrication de la rainure du carter et de la plate-forme. La pale de l'aube se retrouve ainsi décalée angulairement par rapport à sa position théorique et n'assure donc plus de façon optimale le redressement du flux d'air traversant la turbomachine. Le décalage angulaire de plusieurs aubes de redresseur peut ainsi conduire à une perte de rendement et d'efficacité de la turbomachine.In the present art, to position the blade platform in the groove, the nominal width of the platform, i.e. its nominal dimension in the longitudinal plane of the turbomachine, is less than Nominal width of the groove, which induces a minimum clearance of the platform mounted in the groove. Clamping the fixing nut causes an angular offset of the platform of the blade which is more or less important because of the manufacturing tolerances of the groove of the housing and the platform. The blade of the blade is thus angularly offset with respect to its theoretical position and therefore no longer provides optimum recovery of the air flow through the turbomachine. The angular offset of several stator vanes can thus lead to a loss of efficiency and efficiency of the turbomachine.

Actuellement, le calage angulaire des aubes de redresseur sur la carter nécessite des moyens importants en terme d'outillage et de contrôle ce qui rend d'autant plus coûteuse et longue cette phase de montage. La diminution des tolérances de fabrication des plates-formes des aubes et des rainures du carter n'est pas une solution envisageable dans la mesure où cela augmenterait considérablement les coûts de fabrication.Currently, the angular setting of the stator vanes on the housing requires significant resources in terms of tools and control which makes it all the more expensive and long this phase of assembly. The Decreasing the manufacturing tolerances of the platforms of the blades and crankcase grooves is not a feasible solution since it would considerably increase manufacturing costs.

Il est donc important d'améliorer le positionnement angulaire de l'aube dans la rainure afin d'assurer un positionnement optimal de la pale de l'aube par rapport à l'écoulement d'air, tout en conservant les mêmes tolérances de fabrication.It is therefore important to improve the angular position of the blade in the groove to ensure optimal positioning of the vane blade relative to the air flow, while maintaining the same manufacturing tolerances.

Le document US-A2-2,755,064 décrit des aubes de redresseur qui comprennent des plates-formes à contour non circulaire, logées dans des orifices ayant une forme conjuguée de celle des plates-formes, qui sont pratiqués dans un anneau monté fixe dans une gorge d'un carter, ce montage permettant de donner une orientation prédéterminée aux aubes de redresseur mais ne prenant en compte les variations dues aux tolérances de fabrication des aubes, des anneaux et des gorges du carter.The document US-A2-2,755,064 describes stator vanes which comprise non-circular contoured platforms, housed in orifices having a shape conjugate with that of the platforms, which are formed in a ring fixedly mounted in a groove of a casing, this arrangement permitting to give a predetermined orientation to the stator vanes but not taking into account the variations due to the manufacturing tolerances of the vanes, rings and grooves of the casing.

L'invention se propose d'améliorer le calage angulaire de l'aube dans la rainure de façon simple, efficace et économique.The invention proposes to improve the angular setting of the blade in the groove simply, efficiently and economically.

Elle propose à cet effet une aube de redresseur pour turbomachine, comprenant une plate-forme agencée à une extrémité radialement externe de l'aube et destinée à être engagée dans une rainure annulaire d'une surface interne d'un carter, et une tige filetée s'étendant radialement vers l'extérieur depuis la plate-forme et destinée à passer à travers un orifice du carter pour recevoir un écrou de fixation extérieur au carter, caractérisée en ce que les bords amont et aval de la plate-forme comprennent chacun une saillie s'étendant dans le plan de la plate-forme pour limiter la rotation de la plate-forme dans la rainure lors du serrage de l'écrou vissé sur la tige filetée.It proposes for this purpose a turbomachine rectifier blade, comprising a platform arranged at a radially outer end of the blade and intended to be engaged in an annular groove of an inner surface of a housing, and a threaded rod. extending radially outwardly from the platform and intended to pass through an orifice of the housing to receive an attachment nut external to the housing, characterized in that the upstream and downstream edges of the platform each comprise a protrusion extending in the plane of the platform to limit the rotation of the platform in the groove when tightening the nut screwed on the threaded rod.

La réalisation de saillies sur les bords amont et aval de la plate-forme permet d'engager dans la rainure du carter, une plateforme dont la largeur nominale est égale à la largeur nominale de la rainure.The production of projections on the upstream and downstream edges of the platform allows to engage in the groove of the housing, a platform whose nominal width is equal to the nominal width of the groove.

Par conséquent, il n'y a plus de jeu minimal entre la plate-forme et la rainure. Le décalage angulaire entre ces deux pièces après vissage de l'écrou est réduit et est uniquement fonction des tolérances de fabrication. L'invention permet donc d'améliorer le positionnement de l'aube tout en conservant les mêmes tolérances de fabrication.As a result, there is no longer any minimum clearance between the platform and the groove. The angular offset between these two parts after screwing the nut is reduced and depends solely on manufacturing tolerances. The invention therefore improves the positioning of the blade while maintaining the same manufacturing tolerances.

Avantageusement, la plate-forme est sensiblement rectangulaire et une saillie est située à une extrémité du bord amont de la plate-forme et l'autre saillie est sensiblement symétrique de la première par rapport au centre de la plate-forme.Advantageously, the platform is substantially rectangular and a projection is located at one end of the upstream edge of the platform and the other projection is substantially symmetrical with the first relative to the center of the platform.

Le positionnement des saillies à des extrémités opposées de la plate-forme permet d'avoir un couple de serrage optimal lors du vissage de l'écrou sur la tige filetée tout en évitant tout phénomène de marquage par matage des pièces.The positioning of the projections at opposite ends of the platform makes it possible to have an optimum tightening torque when the nut is screwed onto the threaded rod while avoiding any marking phenomenon by matting the parts.

Selon une autre caractéristique de l'invention, les saillies sont formées aux extrémités des bords de la plate-forme qui sont destinées à venir en appui sur les flancs de la rainure lors du serrage de l'écrou de fixation.According to another characteristic of the invention, the projections are formed at the ends of the edges of the platform which are intended to bear against the flanks of the groove when tightening the fixing nut.

Dans un mode de réalisation préféré de l'invention, les saillies sont de forme sensiblement rectangulaire et ont une dimension, en direction des flancs de la rainure, définie en fonction du jeu nécessaire au montage de la plate-forme dans la rainure en tenant compte des tolérances sur la largeur de la rainure et de la plate forme.In a preferred embodiment of the invention, the projections are of substantially rectangular shape and have a dimension, in the direction of the flanks of the groove, defined as a function of the clearance necessary for mounting the platform in the groove taking into account tolerances on the width of the groove and the platform.

Dans une variante de l'invention, la tige filetée est reliée à une partie centrale de la plate-forme formant une surépaisseur par rapport aux bords amont et aval de la plate forme, la partie en surépaisseur pouvant former une zone circulaire centrée sur l'axe de la tige.In a variant of the invention, the threaded rod is connected to a central portion of the platform forming an extra thickness with respect to the upstream and downstream edges of the platform, the thickened portion being able to form a circular zone centered on the axis of the stem.

Les saillies et la surépaisseur de la plate-forme peuvent être réalisées par exemple par usinage.The projections and the extra thickness of the platform can be made for example by machining.

L'invention concerne également une turbomachine, telle qu'un turboréacteur d'avion, caractérisée en ce qu'elle comprend des aubes de redresseur du type décrit ci-dessus.The invention also relates to a turbomachine, such as an aircraft turbojet, characterized in that it comprises stator vanes of the type described above.

D'autres avantages et caractéristiques de l'invention apparaîtront à la lecture de la description suivante faite à titre d'exemple non limitatif et en référence aux dessins annexés dans lesquels :

  • la figure 1 est une vue schématique partielle en coupe illustrant le montage d'une aube de redresseur dans une rainure d'un carter ;
  • la figure 2 est une vue schématique de dessus d'une aube de redresseur fixée dans une rainure du carter et illustrant le décalage angulaire de l'aube lors du serrage dans la technique antérieure ;
  • la figure 3 est une vue schématique en perspective d'une aube de redresseur selon l'invention ;
  • les figures 4 et 5 sont des vues schématiques de dessus d'une plate-forme d'une aube selon l'invention dans deux cas de figure.
Other advantages and characteristics of the invention will appear on reading the following description given by way of nonlimiting example and with reference to the appended drawings in which:
  • the figure 1 is a partial schematic sectional view illustrating the mounting of a stator vane in a groove of a housing;
  • the figure 2 is a schematic top view of a stator blade fixed in a groove of the housing and illustrating the angular offset of the blade during clamping in the prior art;
  • the figure 3 is a schematic perspective view of a stator blade according to the invention;
  • the Figures 4 and 5 are schematic views from above of a platform of a blade according to the invention in two cases.

On se réfère tout d'abord à la figure 1 qui représente une alternance d'aubes mobiles 10 et d'aubes fixes 12 telle qu'on peut, par exemple, la trouver dans un compresseur d'une turbomachine. Les aubes mobiles 10 sont reliées dans leur partie radialement interne à un rotor, les aubes fixes étant fixées à un carter dans leur partie radialement interne et radialement externe.We first refer to the figure 1 which represents an alternation of blades 10 and vanes 12 such that one can, for example, find it in a compressor of a turbomachine. The blades 10 are connected in their radially inner portion to a rotor, the vanes being fixed to a housing in their radially inner and radially outer portion.

Une aube fixe comprend une plate-forme 14 sensiblement rectangulaire raccordant l'extrémité radialement externe d'une pale 16 à une tige filetée 18 s'étendant radialement vers l'extérieur depuis la plate-forme. La plate-forme 14 est engagée dans une rainure annulaire 20 de la surface interne d'un carter à géométrie de révolution 22 et maintenue fixe dans la rainure grâce à la tige 18 laquelle est insérée dans un orifice radial 24 du carter 22. Des écrous 26 de fixation sont vissés sur les tiges 18 pour assurer le serrage de l'aube sur le carter 22.A fixed blade comprises a substantially rectangular platform 14 connecting the radially outer end of a blade 16 to a threaded rod 18 extending radially outwardly from the platform. The platform 14 is engaged in an annular groove 20 of the inner surface of a housing with a geometry of revolution 22 and held fixed in the groove by the rod 18 which is inserted into a radial orifice 24 of the housing 22. Nuts 26 fastening are screwed on the rods 18 to ensure the tightening of the blade on the housing 22.

Lors du fonctionnement de la turbomachine, les aubes mobiles et les aubes fixes coopèrent pour faire passer l'air à travers les différentes parties du moteur. Les aubes fixes (encore appelées aubes de redresseur) ont pour fonction de redresser le flux d'air circulant dans la turbomachine. Ainsi, l'orientation des pales 16 des aubes 12 de redresseur par rapport à l'écoulement d'air est essentielle pour assurer un fonctionnement optimal de la turbomachine.During the operation of the turbomachine, the blades and the vanes cooperate to pass air through the different parts of the engine. The blades (also called stator vanes) have the function of straightening the flow of air flowing in the turbomachine. Thus, the orientation of the blades 16 of the stator vanes 12 with respect to the air flow is essential to ensure optimum operation of the turbomachine.

Dans la technique connue, représentée en figure 2, un jeu minimal doit être prévu entre la rainure 20 et la plate-forme 14 afin de garantir l'insertion de la plate-forme 14 de l'aube dans la rainure 20. Pour cela, la largeur nominale de la plate-forme, c'est-à-dire sa dimension nominale selon l'axe de la turbomachine doit être obligatoirement inférieure à la largeur nominale de la rainure 20. L'aube 12 ainsi montée, après serrage de l'écrou 26 sur le carter, présente un décalage angulaire dans la rainure 20. Ce décalage est plus ou moins important selon que la largeur réelle de la plate-forme et la largeur réelle de la rainure sont en limite supérieure ou inférieure de tolérances de fabrication. Afin d'assurer un calage angulaire correct des redresseurs, des moyens importants en terme d'outillage et de contrôle de l'orientation des plates-formes des aubes sont nécessaires, rendant ainsi coûteuse et longue l'opération de montage des aubes redresseur.In the known art, represented in figure 2 , a minimum clearance must be provided between the groove 20 and the platform 14 to ensure the insertion of the platform 14 of the blade in the groove 20. For this, the nominal width of the platform, that is to say, its nominal dimension along the axis of the turbomachine must necessarily be less than the nominal width of the groove 20. The blade 12 thus mounted, after tightening the nut 26 on the housing, has a angular offset in the groove 20. This shift is more or less important depending on the actual width of the platform and the actual width of the groove are at the upper or lower limit of manufacturing tolerances. In order to ensure correct angular setting of the straighteners, important means in terms of tooling and control of the orientation of the blade platforms are necessary, thus making expensive and long the mounting operation of the straightening vanes.

Comme représenté aux figures 3 à 5, l'invention propose, pour réduire le décalage angulaire des aubes de redresseur au montage, de former des saillies 28 aux extrémités des bords amont et aval de la plate-forme, ces saillies s'étendant dans le plan de la plate-forme.As represented in Figures 3 to 5 , the invention proposes, to reduce the angular offset of the rectifier blades assembly, to form projections 28 at the ends of the upstream and downstream edges of the platform, these projections extending in the plane of the platform.

Ces saillies 28 sont de forme sensiblement rectangulaire dans le mode de réalisation des figures 3 à 5 et sont placées à deux sommets de la plate-forme 14, de façon symétrique par rapport au centre de la plate-forme 14. Ces deux sommets sont ceux qui viennent s'appuyer sur les flancs de la rainure lorsque le serrage de l'écrou de fixation fait tourner la plate-forme de l'aube dans la rainure, et les saillies sont aux extrémités des bords amont et aval de la plate-forme qui partent de ces deux sommets. Un tel placement des saillies permet d'avoir un couple de serrage maximum au niveau de l'écrou de fixation de l'aube lorsque les saillies viennent en appui sur les flancs de la rainure.These projections 28 are of substantially rectangular shape in the embodiment of the Figures 3 to 5 and are placed at two vertices of the platform 14, symmetrically with respect to the center of the platform 14. These two vertices are those which come to rest on the flanks of the groove when the tightening of the nut fastening rotates the platform of the blade in the groove, and the projections are at the ends of the upstream and downstream edges of the platform which depart from these two peaks. Such placement of the projections allows to have a maximum torque at the nut fixing the blade when the projections bear against the flanks of the groove.

La réalisation de saillies 28 aux extrémités des bords amont et aval de la plate-forme permet de dimensionner la plate-forme 14 de l'aube 12 de manière à ce que sa largeur nominale soit égale à la largeur nominale de la rainure 20. Deux cas peuvent être distingués selon que, en raison des tolérances de fabrication des pièces, la largeur réelle de la plate-forme est inférieure ou supérieure à la largeur réelle de la rainure.The production of projections 28 at the ends of the upstream and downstream edges of the platform makes it possible to size the platform 14 of the blade 12 so that its nominal width is equal to the nominal width of the groove 20. Two cases can be distinguished according to the fact that, due to the manufacturing tolerances of the parts, the actual width of the platform is less than or greater than the actual width of the groove.

En figure 4 est représenté le cas où la largeur réelle de la plate-forme 14 est supérieure à la largeur réelle de la rainure 20. La rotation de l'aube 12 dans le sens inverse à celui du serrage permet de réduire l'encombrement axial de la plate-forme 14 de manière à ce qu'il soit inférieur à la largeur réelle de la rainure 20. L'insertion de la plateforme 14 dans la rainure 20 peut ainsi être effectuée.In figure 4 is represented the case where the actual width of the platform 14 is greater than the actual width of the groove 20. The rotation of the blade 12 in the opposite direction to the clamping reduces the axial size of the plate -form 14 so that it is less than the actual width of the groove 20. The insertion of the platform 14 in the groove 20 can thus be performed.

En figure 5, est représenté le cas où la largeur réelle de la plate-forme est inférieure à la largeur réelle de la rainure 20. L'insertion de la plate-forme 14 dans la rainure 20 ne présente aucune difficulté et on se retrouve alors dans une configuration de montage similaire à celle de l'art antérieur.In figure 5 , is shown the case where the actual width of the platform is less than the actual width of the groove 20. The insertion of the platform 14 into the groove 20 presents no difficulty and we are then in a configuration mounting similar to that of the prior art.

Dans les deux cas, présentés ci-dessus, on obtient une réduction du décalage angulaire maximum de l'aube par rapport à la position théorique. Cette réduction est supérieure à 50 % par rapport à une plate-forme sans saillies, tout en conservant les mêmes tolérances de fabrication que dans l'art antérieur. L'invention permet également qu'une aube dont la largeur réelle de la plate-forme est égale à la largeur nominale de la rainure, ne présente aucun décalage angulaire au serrage de l'écrou de fixation, ce qui est impossible avec une aube de l'art antérieur.In both cases, presented above, we obtain a reduction of the maximum angular offset of the blade relative to the theoretical position. This reduction is greater than 50% compared to a platform without projections, while maintaining the same manufacturing tolerances as in the prior art. The invention also allows a blade whose actual width of the platform is equal to the nominal width of the groove, has no angular offset to the tightening of the fixing nut, which is impossible with a blade of the prior art.

Les dimensions des saillies 28 doivent être choisies en fonction des tolérances de fabrication des pièces de telle façon que l'insertion de la plate-forme 14 dans la rainure 20 soit toujours possible. En particulier, pour éviter de créer des zones de contraintes supplémentaires, il est important que la longueur des saillies 28 soit suffisante pour que les contacts entre la plate-forme 14 et la rainure 20 soient réalisés au niveau des saillies 28 et non pas au niveau des sommets de la plate-forme 14 qui ne comprennent pas de saillie.The dimensions of the projections 28 must be chosen according to the manufacturing tolerances of the parts so that the insertion of the platform 14 into the groove 20 is always possible. In particular, to avoid creating additional stress zones, it is important that the length of the projections 28 is sufficient for the contacts between the platform 14 and the groove 20 to be made at the projections 28 and not at the level of the projections 28. vertices of the platform 14 which do not include projection.

Les deux saillies de la plate-forme peuvent avoir la même largeur ou dimension dans le plan longitudinal de la turbomachine, définie en fonction du jeu nécessaire au montage de la plate-forme dans la rainure en tenant compte des tolérances sur la largeur de la rainure et de la plate forme.The two projections of the platform may have the same width or dimension in the longitudinal plane of the turbomachine, defined as a function of the clearance needed to mount the platform in the groove taking into account the tolerances on the width of the groove and the platform.

Dans le mode de réalisation de l'invention représenté aux dessins, la largeur de chaque saillie est de l'ordre de 0,2 à 0,3 mm et sa longueur est de l'ordre de 5 mm. Ces dimensions sont données à titre indicatif pour une plate-forme et une rainure de largeur nominale d'environ 50 mm, la dimension latérale de la plate-forme étant d'environ 30 mm.In the embodiment of the invention shown in the drawings, the width of each projection is of the order of 0.2 to 0.3 mm and its length is of the order of 5 mm. These dimensions are given as an indication for a platform and a groove of nominal width of about 50 mm, the lateral dimension of the platform being about 30 mm.

Avantageusement, la plate-forme comprend une partie 30 en surépaisseur, formant une zone circulaire, centrée sur l'axe de la tige filetée 18. Le contact entre la plate-forme 14 et le carter 22 est ainsi limité à la partie 30 en surépaisseur et ne s'étend pas jusqu'aux bords amont et aval de la plate-forme, ce qui permet de diminuer les contraintes sur le bord d'attaque 32 et le bord de fuite 34 de la pale 16 qui sont dues au serrage de la tige filetée 18 sur le carter 22.Advantageously, the platform comprises a thickened part 30, forming a circular zone, centered on the axis of the threaded rod 18. The contact between the platform 14 and the housing 22 is thus limited to the portion 30 of extra thickness and does not extend to the upstream and downstream edges of the platform, which makes it possible to reduce the stresses on the leading edge 32 and the trailing edge 34 of the blade 16 which are due to the clamping of the threaded rod 18 on the housing 22.

Les saillies ainsi que la surépaisseur de la plate-forme peuvent être réalisés par usinage.The projections and the extra thickness of the platform can be made by machining.

L'invention est donc particulièrement intéressante en ce qu'elle permet d'améliorer le positionnement initial d'une aube dans une rainure d'un carter, tout en conservant les mêmes tolérances de fabrication.The invention is therefore particularly interesting in that it makes it possible to improve the initial positioning of a blade in a groove of a casing, while maintaining the same manufacturing tolerances.

L'invention précédemment décrite peut être utilisée dans tous les compartiments de la turbomachine nécessitant une fixation angulaire précise des aubes de redresseur. L'invention n'est pas limitée à la seule forme de saillie décrite et représentée et d'autres formes peuvent être également envisagées dans le cadre des caractéristiques techniques de l'invention telle que revendiquée.The invention described above can be used in all compartments of the turbomachine requiring precise angular attachment of the stator vanes. The invention is not limited to the single projection form described and shown and other forms may also be contemplated within the scope of the technical features of the invention as claimed.

Claims (9)

  1. A straightener blade (12) for a turbomachine, comprising a platform (14) arranged at a radially external end of the blade (12) and adapted to be engaged in a annular groove (20) of an inner surface of a housing, and a lead screw (18) radially extending outwardly from the platform (14) and adapted to pass through a port (24) of the housing in order to receive a fixing nut (26) external to the housing, characterised in that the upstream and downstream edges of the platform (14) each comprise a protrusion (28) extending in the plan of the platform (14) to limit the rotation of the platform (14) in the groove (20) when nut (26) screwed on the lead screw (18) is tightened.
  2. A blade according to claim 1, characterised in that the platform (14) is substantially rectangular and one protrusion (28) is located at an end of the upstream edge of the platform (14), and the other one (28) is substantially symmetrical to the first one relative to the centre of the platform (14).
  3. A blade according to claim 1 or claim 2, characterised in that the protrusions (28) are formed on the edge-ends of the platform which are adapted to rest on the flanks of the groove (20) when the fixing nut (26) is tightened.
  4. A blade according to any preceding claim, characterised in that the protrusions (28) are substantially rectangular shaped.
  5. A blade according to one of claims 1 to 4, characterised in that the protrusions (28) have a dimension toward the flanks of the groove defined according to the backlash required for fitting the platform in the groove taking tolerances of the width of the groove (20) and platform (14) into account.
  6. A blade according to any preceding claim, characterised in that the lead screw (18) is connected to a centre part of the platform (14) forming an oversized portion (30) relative to upstream and downstream edges of the platform (14).
  7. A blade according to claim 6, characterised in that the oversized portion (30) forms a circular area centred on the axe of the screw (18).
  8. A blade according to claim 6 or claim 7, characterised in that the protrusions (28) and the oversized portion (30) of the platform (14) are provided by machining.
  9. A turbomachine, such as a plane turbo-jet, characterised in that it comprises straightener blades (12) according to any preceding claim.
EP06292026A 2006-12-22 2006-12-22 Angular setting of turbomachine stator vanes. Not-in-force EP1936121B1 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP06292026A EP1936121B1 (en) 2006-12-22 2006-12-22 Angular setting of turbomachine stator vanes.
AT06292026T ATE556197T1 (en) 2006-12-22 2006-12-22 ANGLE FIXATION FOR TURBO MACHINES GUIDE VANES
US11/962,852 US8075264B2 (en) 2006-12-22 2007-12-21 Blade angle setting for a turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP06292026A EP1936121B1 (en) 2006-12-22 2006-12-22 Angular setting of turbomachine stator vanes.

Publications (2)

Publication Number Publication Date
EP1936121A1 EP1936121A1 (en) 2008-06-25
EP1936121B1 true EP1936121B1 (en) 2012-05-02

Family

ID=38068425

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06292026A Not-in-force EP1936121B1 (en) 2006-12-22 2006-12-22 Angular setting of turbomachine stator vanes.

Country Status (3)

Country Link
US (1) US8075264B2 (en)
EP (1) EP1936121B1 (en)
AT (1) ATE556197T1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2738356A1 (en) 2012-11-29 2014-06-04 Techspace Aero S.A. Vane of a turbomachine, vane assembly of a turbomachine, and corresponding assembly method

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2199544B1 (en) 2008-12-22 2016-03-30 Techspace Aero S.A. Assembly of guide vanes
EP2264284B1 (en) 2009-06-18 2015-01-28 Techspace Aero S.A. Method for manufacturing vanes built into a shroud ring and stator ring obtained according to the method
EP2371521B1 (en) 2010-04-02 2014-07-02 Techspace Aero S.A. Method of manufacturing a rectifier
GB201206603D0 (en) * 2012-04-16 2012-05-30 Rolls Royce Plc Variable stator vane arrangement
US9546559B2 (en) * 2013-10-08 2017-01-17 General Electric Company Lock link mechanism for turbine vanes
EP2977559B1 (en) * 2014-07-25 2017-06-07 Safran Aero Boosters SA Axial turbomachine stator and corresponding turbomachine
US20200072070A1 (en) * 2018-09-05 2020-03-05 United Technologies Corporation Unified boas support and vane platform

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR965713A (en) * 1947-05-07 1950-09-20
US2755064A (en) * 1950-08-30 1956-07-17 Curtiss Wright Corp Stator blade positioning means
US2834537A (en) * 1954-01-18 1958-05-13 Ryan Aeronautical Co Compressor stator structure
US4643636A (en) * 1985-07-22 1987-02-17 Avco Corporation Ceramic nozzle assembly for gas turbine engine
EP0953729B1 (en) * 1998-05-01 2003-06-25 Techspace aero Guide vanes for a turbomachine

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2738356A1 (en) 2012-11-29 2014-06-04 Techspace Aero S.A. Vane of a turbomachine, vane assembly of a turbomachine, and corresponding assembly method
US10202859B2 (en) 2012-11-29 2019-02-12 Safran Aero Boosters Sa Axial turbomachine blade with platforms having an angular profile

Also Published As

Publication number Publication date
EP1936121A1 (en) 2008-06-25
US20080206049A1 (en) 2008-08-28
ATE556197T1 (en) 2012-05-15
US8075264B2 (en) 2011-12-13

Similar Documents

Publication Publication Date Title
EP1936121B1 (en) Angular setting of turbomachine stator vanes.
EP1862644B1 (en) Air-flow guiding device for a turbomachine, and corresponding turbomachine and diffuser
EP3074609B1 (en) Device for guiding synchronizing ring vanes with variable pitch angle of a turbine engine and method for assembling such a device
EP1970537B1 (en) Turbomachine fan
EP1584784B1 (en) Assembly device for annular flanges, in particular in turbomachines
EP3775501B1 (en) Cooling device for a turbine of a turbomachine
EP2678531B1 (en) Fan rotor and corresponding turbojet engine
EP1801357A1 (en) Bladed nozzle of a turbomachine, turbomachine comprising this nozzle and turbomachine vane
FR2882570A1 (en) AUB CONTROL DEVICE WITH VARIABLE SHIFT IN A TURBOMACHINE
WO2010097438A2 (en) Fan blades with cyclic setting
EP2901021A1 (en) Turbomachine casing and impeller
WO2013150224A1 (en) Variable pitch rectifier for a turbomachine compressor comprising two inner rings
EP0953729B1 (en) Guide vanes for a turbomachine
FR2971022A1 (en) COMPRESSOR RECTIFIER STAGE FOR A TURBOMACHINE
FR2942638A1 (en) Angular sector for rectifier in compressor of e.g. turbojet engine, of airplane, has angular locking flange arranged coaxially around outer shell and including shoulder that is radially supported against outer shell
FR2914944A1 (en) High pressure compressor for e.g. jet prop engine of aircraft, has blades each including pivot connected to actuating ring by toothed wheel, where wheel is rotatably connected to pivot and engaged with corresponding gear teeth of ring
FR2922588A1 (en) Rotor disk or drum i.e. booster drum, for e.g. turbojet engine of airplane, has flange including orifice for mounting bolt, where rim of bolt cooperates with edges of reinforcement of flange for immobilizing bolt in orifice
EP1936125B1 (en) Turbomachine compressor
EP3444439A1 (en) Turbine for turbine engine comprising blades with a root having an exapnding form in axial direction
FR2896019A1 (en) Diffuser insert for high pressure compressor of e.g. jet engine, has inner blade support shell with multiple orifices whose side wall has four blade positioning bosses defining blade support points contacting surfaces of outer wall of blade
FR2942645A1 (en) Fan part for turbofan engine of aircraft, has strip whose geometry permits application of displacement parallel to axis, during its rotary movement with respect to stator part, to assure variation of blade incidence based on setting law
FR2966530A1 (en) Variable-pitch vane stage for high-pressure compressor of turbomachine e.g. turbojet, of aircraft, has inner ring including bearing with smooth outer cylindrical surface, and another bearing with external threading
WO2011015767A1 (en) Rectifier stage for a turbine engine
WO2016034822A1 (en) Blade comprising a platform with a hollow bumper
FR3105996A1 (en) Locking member for assembling a first part and a second part of a 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

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 RS

17P Request for examination filed

Effective date: 20081204

AKX Designation fees paid

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

REG Reference to a national code

Ref country code: DE

Ref legal event code: R079

Ref document number: 602006029211

Country of ref document: DE

Free format text: PREVIOUS MAIN CLASS: F01D0009040000

Ipc: F01D0017160000

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: F04D 29/64 20060101ALI20111012BHEP

Ipc: F04D 29/56 20060101ALI20111012BHEP

Ipc: F01D 25/24 20060101ALI20111012BHEP

Ipc: F04D 29/54 20060101ALI20111012BHEP

Ipc: F01D 17/16 20060101AFI20111012BHEP

Ipc: F01D 9/04 20060101ALI20111012BHEP

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): 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

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: CH

Ref legal event code: EP

Ref country code: AT

Ref legal event code: REF

Ref document number: 556197

Country of ref document: AT

Kind code of ref document: T

Effective date: 20120515

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: FRENCH

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602006029211

Country of ref document: DE

Effective date: 20120621

REG Reference to a national code

Ref country code: NL

Ref legal event code: VDEP

Effective date: 20120502

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

Effective date: 20120502

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120502

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120502

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120902

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120502

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120502

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120502

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 556197

Country of ref document: AT

Kind code of ref document: T

Effective date: 20120502

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120502

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120502

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120903

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120803

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120502

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120502

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120502

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120502

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120502

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120502

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120502

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120502

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: 20130205

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 FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120813

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602006029211

Country of ref document: DE

Effective date: 20130205

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120802

Ref country code: MC

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20121231

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20121231

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20121231

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20121222

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120502

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20121222

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20061222

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

Ref country code: GB

Payment date: 20141126

Year of fee payment: 9

Ref country code: DE

Payment date: 20141121

Year of fee payment: 9

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 10

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 602006029211

Country of ref document: DE

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20151222

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20151222

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160701

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 11

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 12

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

Ref country code: BE

Payment date: 20181127

Year of fee payment: 13

Ref country code: FR

Payment date: 20181127

Year of fee payment: 13

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20191231

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20191231

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20191231