EP3724454B1 - Multi-blade vane for a turbomachine rotor and rotor comprising same - Google Patents
Multi-blade vane for a turbomachine rotor and rotor comprising same Download PDFInfo
- Publication number
- EP3724454B1 EP3724454B1 EP18829759.2A EP18829759A EP3724454B1 EP 3724454 B1 EP3724454 B1 EP 3724454B1 EP 18829759 A EP18829759 A EP 18829759A EP 3724454 B1 EP3724454 B1 EP 3724454B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- platform
- blade
- blades
- vane
- radial
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000005304 joining Methods 0.000 claims description 3
- 241000272165 Charadriidae Species 0.000 description 56
- 238000011144 upstream manufacturing Methods 0.000 description 11
- 210000003462 vein Anatomy 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 3
- 230000007547 defect Effects 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000001627 detrimental effect Effects 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000014759 maintenance of location Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000009827 uniform distribution Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
- F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/146—Shape, i.e. outer, aerodynamic form of blades with tandem configuration, split blades or slotted blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
- F04D29/322—Blade mountings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
-
- 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
- F05D2240/80—Platforms for stationary or moving blades
-
- 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
- F05D2240/90—Mounting on supporting structures or systems
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
- F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction
Definitions
- the present invention relates to the field of bladed rotors in turbomachines, more particularly the case where the blades are made individually and fixed on a disc to form the bladed rotor.
- a low pressure turbine rotor is generally made up of several tens or even hundreds of blades mounted on a disc.
- Each blade is made up of at least one blade, an attachment for fitting into the rotor disc and a platform, placed between the two, so as to form the internal face of the stream in which the flow of gas crossed by the blades.
- Such a rotor can be heavily loaded by a very high rotational speed. Maintaining the blades on the rotors and sealing vis-Ã -vis the flow of gas at the platforms are part of the problems to be solved during the design of these rotors and their blades.
- a two-bladed vane 100 comprises two blades 101,102, extending in span along a radial direction R between an internal platform 103 and an external platform 104 delimiting the flow path of the gas flow.
- the internal platform 103 also makes the connection between the blades 101, 102, and a one-piece attachment foot 105 which is inserted between the teeth 106 of the disc of a rotor 107 (shown only near dawn).
- the dovetail-shaped attachment comprises a bulb 107 placed at the end of a stilt 108 in two parts, each of the two parts joining the base of a blade.
- the manufacture of the blade being made by foundry, so as not to have a solid zone between the two parts of the stilt 108, a cavity 109 is made between the two parts of the stilt 108 using a core used in the foundry process.
- the attachment foot 105 is substantially centered in the circumferential direction T between the two blades 101, 102, so as to balance the stresses to retain the blades under the centrifugal forces.
- this requires the two parts of the stilt 108 to have a non-radial part to join the base of the blades.
- the arrows on the figure 1 schematically show the path of the stresses due to centrifugal forces, along the stilt 108 and the blades 101, 102. In the part where the arrows are not aligned with the radial direction R this creates a moment in the stilt and therefore additional constraints.
- the attachment foot 105 must hold two blades instead of one, resisting additional stresses due to the offset of the foot 105 relative to the blades.
- the foot 105 being crossed by the core 109, it must be even wider than twice a single foot to hold a single blade.
- the object of the invention is to propose a solution for minimizing the mass of the attachment of a two-bladed blade, in particular by reducing the level of the stresses to which the attachment of the blades must withstand during operation of the rotor.
- Another object of the invention is to avoid too much hyperstatism between the disc and the blade, which would require expensive precision adjustments between the attachments of the blades and the fixing teeth on the disc.
- Another object of the invention is to minimize the mass of the rotor assembly at the level of the connection with the blades.
- the invention relates to a turbomachine rotor blade comprising a first blade and a second blade arranged to form two successive blades of a bladed rotor, a platform substantially forming an angular wall sector in an axial direction, said two blades being connected to the platform by one of their ends, extending substantially in a so-called radial direction substantially perpendicular to said axial direction, and fastening means connected to the platform which are intended to cooperate with fastening means on a disk of the rotor .
- Said blade is characterized in that said attachment means comprise two separate stilts, each stilt extending from the platform, in the radial direction, in the extension of one of said two blades, and carrying an attachment element at a opposite end to the platform, said attachment element extending substantially parallel to said axial direction and comprising at least one surface facing the platform with a constant sectional profile perpendicular to said axial direction, so as to form a surface bearing intended to hold the blade in said radial direction oriented from the platform towards the blades.
- each stilt extends parallel to the axial direction with a constant profile of the bearing surface makes it possible to mount the blade according to the invention by sliding the attachment element against teeth of the rotor disk in the axial direction.
- each stilt in the extension of each blade makes it possible to better align the passage of the stresses to hold the blade between the blades and the stilts during the rotation of the rotor. There is therefore no extra thickness to be provided in the dimensioning of the stilts to resist significant twisting moments and this allows a weight saving on the blade compared to the state of the art of a two-bladed blade. with a central foot.
- the disc when the disc is thus equipped with a succession of vanes such that the blades can be associated two by two with stilts which are in their extension, it may suffice to provide holding teeth only in one out of two circumferential intervals between the stilts. Indeed, if the attachment means are symmetrical, one interval out of two corresponds to the presence of the bearing surfaces and the other is empty of holding means.
- the invention makes it possible to limit the hyperstatic nature of the radial support against centrifugal forces.
- the blade according to the invention has only two contact planes instead of four. With four contact planes, it would be necessary to impose much tighter manufacturing tolerances than what is done in the state of the art to ensure that one or two of the bearing surfaces are not inoperative.
- the greater spacing of the bearing surfaces is also advantageous for the positioning of the blades of the dawn relative to the disc and therefore their positioning in the engine.
- these support surfaces define with the teeth of the disc contact surfaces which position the blades. The greater the distance between the two contact surfaces, the smaller the defects on these surfaces will have on the angular positioning defect of the blades.
- the support surface of the attachment element carried by each stilt is located on one side of the outer attachment element relative to the two stilts in a circumferential direction perpendicular to said axial and radial directions.
- the stilts with their attachment element can be slid during assembly between two successive teeth of the disc, leaving a gap between the two stilts.
- the bearing surface is itself generally inclined with respect to the radial direction.
- the placement of the bearing surfaces circumferentially outside the stilts contributes to the stability of the connection to the disc with respect to the forces exerted on the blade during operation. of the rotor.
- each stilt comprises a veil substantially plane and parallel to the axial direction forming said end bearing the attachment element, said veil and the attachment element being arranged to have a side face facing in the direction opposite to the another stilt that is parallel to the axial direction with a constant profile.
- part of the veil can also be engaged between the teeth of the disc and thus cooperate with the teeth to participate in the lateral retention of the blade.
- the attachment element comprises a lug forming a lug with respect to said sail at the end of the stilt.
- This embodiment minimizes the mass used to make the attachment of the blade.
- the blades being offset by a given distance at their junction with the platform in a circumferential direction, perpendicular to said axial and radial directions, said ends of the two stilts carrying the attachment element are offset by a distance substantially equal to said given distance.
- the attachments of several successive blades to the rotor create a repeating pattern which can cooperate with a uniform distribution of similar teeth on the periphery of the rotor disk.
- each stilt is positioned in a circumferential direction, perpendicular to said axial and radial directions, on an average position of the end linked to the platform of the corresponding blade.
- each stilt is shaped so that the junction of the stilt with the platform follows the junction with the platform of the corresponding blade in its evolution along the axial direction.
- the blade can advantageously comprise at least one wall connecting the two stilts transversely to said axial direction.
- Such a wall has a stiffening function. It will prevent deformation of the stilts under centrifugal forces and can make it possible to reduce the thickness of the stilts, and therefore their mass.
- Said wall may extend radially between the stilts from the platform to a line joining radial ends of the attachment elements opposite the platform.
- the invention also relates to a turbomachine rotor comprising blades as described above.
- the disk of said rotor carries at its periphery a succession of similar teeth shaped to cooperate with the attachment means of the blades, two successive teeth being separated in the circumferential direction by a distance at least equal to the width of one tooth. following this direction.
- a turbine blade 1 according to the invention comprises two blades 2, 3 extending spanwise in a radial direction R between an internal platform 4 and an external platform 5.
- the blade 1 is fixed on a rotor disc 6 movable around an axis of direction X (shown in the figure 4 ), of which only a peripheral part is shown with the teeth 7 for holding the blade.
- the axial and radial directions refer to the axis of the rotor, the terms internal and external refer to the radial direction.
- the terms upstream and downstream in the axial direction refer to the direction of flow for which the blades were designed.
- the internal 4 and external 5 platforms delimit an angular sector of the passage passage of the gas flow around said axis X.
- the external platform 5 is not concerned by the invention and may possibly not exist, it is elsewhere generally the case for compressor blades. It is therefore not described further.
- the internal platform 4 is delimited along the circumferential direction T between two axial planes, so as to fit with the platforms adjacent blades in order to ensure continuity of the wall of the vein.
- the body 8 of the internal platform 4 delimiting the vein has a radial profile determined by the design of the turbine which can be inclined with respect to the radial direction R. In the example, this profile deviates from the axis X of the rotor from upstream to downstream.
- the internal platform 4 here comprises an upstream radial web 9 and a downstream radial web 10 which extend radially so as to come into contact with the teeth 7 holding on the disc 6, at the same distance of the X axis.
- the upstream veil 9 and the downstream veil 10 have a function of maintaining the blade 1, on the one hand to block its movement in the radial direction towards the X axis, on the other hand to block the rotation around a direction parallel to the axis X.
- the internal platform 4 generally comprises devices fixed to the upstream 9 and downstream 10 sails, for example annular spoilers 11, to effect sealing with the stator elements of the turbine that surround the rotor in the axial direction.
- the two blades 2, 3 have a curved and inclined profile with respect to the axial direction X which can evolve along their span in the radial direction R.
- figure 4 shows the shape of this profile at the base of the blades 2, 3, at the level of their junction with the platform 4.
- the geometries of the two blades 2, 3, are similar with an angular offset corresponding to the design of the rotor and the number of blades which must be installed there.
- the bases of the blades 2, 3 are therefore offset by a distance D determined at the level of the internal platform 4.
- the attachment of the blade 1 to the disc 6 here comprises two separate stilts 12, 13 which are connected to the body 8 of the platform 4 and extend from the latter in the radial extension of one of the blades 2, 3, having substantially the same extension as said blades 2, 3 in the axial direction X.
- Each stilt 12, 13 ends here, on the side opposite the platform, with an axial web 14, 15, parallel to the radial direction R , which is connected to a leg 16, 17, parallel to the axial direction X and inclined with respect to the radial direction, which leg forms the free end of the stilt.
- Said lug 16, 17 deviates laterally outwards starting from the axial web 14,15, forming, in cross section, an end lug, so that its outer lateral surface S1, S2 faces the platform 4.
- the support surface S1, S2 is generally inclined with respect to the radial direction.
- the angle of inclination depends on the design made by the person skilled in the art according to the geometry of the turbine and the operating constraints. Classically it takes values between 40 and 50°, but can be outside this range.
- Each lug 16, 17 thus forms an attachment element for the blade 1 and the surfaces S1, S2 form support surfaces allowing the blade to be retained in the radial direction R oriented from the platform towards the blades.
- the axial webs 14, 15 of the stilts 12, 13 and the end legs 16, 17 cooperate with the teeth 7 of the disc 6 to hold the blade 1 according to an operation which will be described later.
- the axial sails 14, 15 of the ends of each stilt 12, 13 are centered on an average position of the bases of the blades 2, 3 on the platform 4 in the circumferential direction T and are therefore offset along this direction by a distance D′ substantially equal to the offset D between the bases of said blades 2, 3.
- the assemblies formed of the axial sails 14, 15 and the end legs 16, 17, are substantially symmetrical with respect to an axial plane passing through the middle of the stilts 12, 13.
- Each stilt 12, 13 has a three-dimensional shape between the axial web 14, 15, and the platform 4, to follow the profile of the base of the blade 2, 3 corresponding to the level of its junction with the body 8 of the platform 4.
- the disc 6 of the rotor comprises at its periphery a crown of similar teeth 7 which are offset along the circumferential direction T by a distance substantially equal to twice the offset distance D between the bases of the blades 2, 3, of so that there are twice as many teeth 7 as blades 2, 3 on the rotor.
- Each tooth 7 here extends parallel to the axis X over a distance substantially corresponding to the gap between the upstream 9 and downstream 10 webs of the platform, with a constant transverse profile.
- the blade 1 described above can be installed between two successive teeth 7 by sliding, in the axial direction X, the axial webs 14, 15 of the stilts 12, 13 and the end legs 16, 17, between two teeth 7 successive.
- Known devices, not described here, then make it possible to maintain the blade 1 in its axial position with respect to the rotor. These devices are not concerned by the invention.
- each tooth 7 here has the shape of a bulb.
- the tooth therefore comprises a part of constant given thickness followed by a widening.
- the shape of this widening is defined so as to form, on one side of the tooth 7, a surface facing the disc 6 which is in contact with the support surface S1 connected to one of the stilts 12 of the blade 1 and to form on the other side of the tooth, another surface facing the disc 6 which is in contact with the support surface S2 linked to the other of the stilts 13 of an adjacent blade, similar to the blade 1.
- the profile of the teeth 7 is symmetrical with respect to a median radial plane of the tooth.
- tooth 7 has a substantially flat radially outer surface or forming a circular cylinder portion centered on axis X of the rotor.
- each stilt 12, 13 The bearing surface S1, S2 of the end tab 16, 17, carried by each stilt 12, 13 is designed to absorb approximately half of the centrifugal forces applied to the blade 1, that is to say substantially those corresponding to one of said blades 2, 3.
- a stilt 12, 13 with its end leg 16, 17 must therefore be sized substantially to withstand the stresses imposed by a blade.
- the three-dimensional part of the stilt 12, 13 takes up these forces towards the base of the corresponding blade 2, 3 with a slight radial inclination since it is essentially a question here of compensating for the curved shape of the profile of the blade 2, 3 but not a circumferential offset of half an interval with said blade.
- the blade 1 is held by the contacts of only two bearing surfaces S1 and S2, each extending in an inclined manner with respect to the radial direction, at the exterior of a stilt 12, 13 in the circumferential direction T.
- said bearing surfaces S1, S2 are themselves spaced apart and located near the edges of the blade 1 in the circumferential direction T. This improves the stability of the assembly under the stress of the forces centrifugal, with respect to a single attachment gathered in the center of the blade.
- the invention also allows a gain in mass on the disk 6. It can be seen on the figures 3 and 4 that the space between the two stilts 12, 13 of a two-bladed blade 1 is empty of teeth. On the other hand, by repeating from one blade 1 to another, each tooth 7 of the disc 6 occupies a space extending between two blades in the circumferential direction T, one belonging to a blade, the other belonging to adjacent dawn. Therefore, compared to the known solution of a two-bladed blade with a central root, the teeth 7 of a disk adapted to blades according to the invention are much narrower than for a disk adapted to two-bladed blades with a single root. , as can be seen by comparing the picture 3 and the figure 1 .
- the figure 5 illustrates the mass saving obtained compared to the use of single-bladed blades or two-bladed blades with 2 attachments in accordance with the state of the art and which would therefore have 4 contact surfaces between the disc and the blade.
- the teeth with the single-blade blades would have a lesser thickness along the circumferential direction T but would be twice as numerous since it would be necessary to add the tooth 7' indicated in dotted lines to retain each blade, which results in the fact that, overall, the invention makes it possible to gain on the mass of the teeth of the disc.
- the blade 21 also comprises one or more transverse stiffening webs 18 which connect the two stilts 13, 14.
- a stiffening web 18 extends radially from the body 8 of the platform 4. In the example presented in figure 6 , it only closes the space between the stilts 12, 13 at the level of the three-dimensional part, leaving the space between the axial sails 14,15 free.
- such a realization leaves free an air passage zone under the platform 4 and the upstream 9 and downstream 10 sails, between the teeth 7 of the disc 6 of the rotor.
- the blade 31 comprises at least one stiffening web 19 which extends as far as the radial end of the attachment lugs 16, 17 carried by the stilts 12, 13, following the periphery of the disc 6, so as to close the axial air passage between the teeth 7 under the platform 4 and the upstream 9 and downstream 10 sails.
- the description of the embodiments of the invention given in this document is not limiting.
- the blade described here is two-bladed but one can envisage blades comprising a succession of pairs of blades with their stilts in the extension. In this case, however, the mounting of the bearing surfaces on the teeth becomes hyperstatic for the blade, and therefore more difficult to adjust.
- Other embodiments of the means of connection with the disk, not shown, can also be envisaged.
- the radial blocking of the blade towards the axis can be ensured by an element carried by the stilts which presses on the disc 6 or on the radial apex of the teeth 7.
- the internal platform 4 can then have no veil upstream or downstream having a holding function.
- an attachment element at the end of the stilts 12, 13 other than a tab forming an elbow with respect to the axial web 14, 15, can be used to produce the bearing surfaces S1, S2. It can be achieved, for example, by spoilers deviating from the surface of the veil.
- the shape of the teeth on the disk will then be adapted to the shape of the attachment elements used on the blade.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
La présente invention concerne le domaine des rotors à aubes dans les turbomachines, plus particulièrement le cas où les aubes sont réalisées individuellement et fixées sur un disque pour former le rotor à aubes.The present invention relates to the field of bladed rotors in turbomachines, more particularly the case where the blades are made individually and fixed on a disc to form the bladed rotor.
Notamment, un rotor de turbine basse pression est généralement composé de plusieurs dizaines voir centaines d'aubes montées sur un disque. Chaque aube est composée au minimum d'une pale, d'une attache pour se mettre en place dans le disque du rotor et d'une plateforme, placée entre les deux, de manière à former la face interne de la veine dans laquelle passe le flux de gaz traversé par les pales.In particular, a low pressure turbine rotor is generally made up of several tens or even hundreds of blades mounted on a disc. Each blade is made up of at least one blade, an attachment for fitting into the rotor disc and a platform, placed between the two, so as to form the internal face of the stream in which the flow of gas crossed by the blades.
Un tel rotor peut être fortement chargé par un régime de rotation très élevé. Le maintien des aubes sur les rotors et l'étanchéité vis-à -vis du flux de gaz au niveau des plateformes font partie des problèmes à résoudre lors de la conception de ces rotors et de leurs aubes.Such a rotor can be heavily loaded by a very high rotational speed. Maintaining the blades on the rotors and sealing vis-à -vis the flow of gas at the platforms are part of the problems to be solved during the design of these rotors and their blades.
Il existe plusieurs avantages à prévoir plusieurs pales sur une même aube. En premier lieu, produire plusieurs pales sur une même pièce permet de réduire les coûts de production du rotor complet. De plus, entre chaque aube, des jeux sont nécessaires pour le montage et pour éviter les contacts lors des dilatations thermiques. Ces jeux provoquent des fuites entre la veine et le hors veine, néfastes pour la performance de la turbomachine.There are several advantages to providing several blades on the same blade. First of all, producing several blades on the same part makes it possible to reduce the production costs of the complete rotor. In addition, between each blade, clearances are necessary for assembly and to avoid contact during thermal expansion. These clearances cause leaks between the vein and the outside of the vein, which are detrimental to the performance of the turbomachine.
Il est ainsi connu d'utiliser des aubes bipales, comme cela est présenté dans le document
En référence à la
Le pied d'attache 105 est sensiblement centré suivant la direction circonférentielle T entre les deux pales 101, 102, de manière à équilibrer les contraintes pour retenir les pales sous les efforts centrifuges. On voit sur la
D'un point de vue du dimensionnement, le pied d'attache 105 doit tenir deux pales au lieu d'une, en résistant à des contraintes supplémentaires du fait du décalage du pied 105 par rapport aux pales. De plus le pied 105 étant traversé par le noyau 109, il doit être encore plus large que le double d'un pied simple pour tenir une seule pale.From a dimensioning point of view, the
Une autre solution connue serait d'avoir deux pieds d'attache distincts sous chaque pale, mais le montage serait fortement hyperstatique. En effet, dans l'état de l'art, l'aube et le disque sont déjà hyperstatiques en fonctionnement, car il y a deux plans de contact. Si l'on met deux attaches normales, il y aura quatre plans de contacts donc beaucoup plus de problèmes d'hyperstatisme.Another known solution would be to have two separate attachment feet under each blade, but the assembly would be highly hyperstatic. Indeed, in the state of the art, the blade and the disc are already hyperstatic in operation, because there are two contact planes. If two normal attachments are used, there will be four contact planes, therefore many more problems of hyperstatism.
Par ailleurs, il existe un besoin de minimiser la masse des aubes, pour diminuer les contraintes sur les liaisons avec le disque ainsi que pour le bilan de masse global.Furthermore, there is a need to minimize the mass of the blades, to reduce the stresses on the connections with the disc as well as for the overall mass balance.
L'invention a pour but de proposer une solution pour minimiser la masse de l'attache d'une aube bipale, notamment en diminuant le niveau des contraintes auxquelles l'attache des aubes doit résister lors du fonctionnement du rotor.The object of the invention is to propose a solution for minimizing the mass of the attachment of a two-bladed blade, in particular by reducing the level of the stresses to which the attachment of the blades must withstand during operation of the rotor.
L'invention a aussi pour but d'éviter trop d'hyperstatisme entre le disque et l'aube, ce qui nécessiterait des ajustages coûteux en précision entre les attaches des aubes et les dents de fixation sur le disque.Another object of the invention is to avoid too much hyperstatism between the disc and the blade, which would require expensive precision adjustments between the attachments of the blades and the fixing teeth on the disc.
L'invention a également pour but de minimiser la masse de l'ensemble du rotor au niveau de la liaison avec les aubes.Another object of the invention is to minimize the mass of the rotor assembly at the level of the connection with the blades.
L'invention concerne une aube de rotor de turbomachine comprenant une première pale et une deuxième pale agencées pour former deux pales successives d'un rotor à aubes, une plateforme formant sensiblement un secteur angulaire de paroi suivant une direction axiale, lesdites deux pales étant reliées à la plateforme par une de leurs extrémités en s'étendant sensiblement suivant une direction dite radiale sensiblement perpendiculaire à ladite direction axiale, et des moyens d'attache reliés à la plateforme qui sont destinés à coopérer avec des moyens de fixation sur un disque du rotor.The invention relates to a turbomachine rotor blade comprising a first blade and a second blade arranged to form two successive blades of a bladed rotor, a platform substantially forming an angular wall sector in an axial direction, said two blades being connected to the platform by one of their ends, extending substantially in a so-called radial direction substantially perpendicular to said axial direction, and fastening means connected to the platform which are intended to cooperate with fastening means on a disk of the rotor .
Ladite aube est caractérisée en ce que lesdits moyens d'attache comprennent deux échasses séparées, chaque échasse s'étendant de la plateforme, suivant la direction radiale, dans le prolongement d'une desdites deux pales, et portant un élément d'attache à une extrémité opposée à la plateforme, ledit élément d'attache s'étendant de manière sensiblement parallèle à ladite direction axiale et comportant au moins une surface tournée vers la plateforme avec un profil constant en coupe perpendiculaire à ladite direction axiale, de manière à former une surface d'appui destinée à retenir l'aube suivant ladite direction radiale orientée de la plateforme vers les pales.Said blade is characterized in that said attachment means comprise two separate stilts, each stilt extending from the platform, in the radial direction, in the extension of one of said two blades, and carrying an attachment element at a opposite end to the platform, said attachment element extending substantially parallel to said axial direction and comprising at least one surface facing the platform with a constant sectional profile perpendicular to said axial direction, so as to form a surface bearing intended to hold the blade in said radial direction oriented from the platform towards the blades.
Le fait que l'élément d'attache de chaque échasse s'étende de manière parallèle à la direction axiale avec un profil constant de la surface d'appui permet de monter l'aube selon l'invention en glissant l'élément d'attache contre des dents du disque du rotor suivant la direction axiale.The fact that the attachment element of each stilt extends parallel to the axial direction with a constant profile of the bearing surface makes it possible to mount the blade according to the invention by sliding the attachment element against teeth of the rotor disk in the axial direction.
Le fait de mettre chaque échasse dans le prolongement de chaque aube permet de mieux aligner le passage des contraintes pour tenir l'aube entre les pales et les échasses lors de la rotation du rotor. Il n'y a donc pas de surépaisseur à prévoir dans le dimensionnement des échasses pour résister à des moments de torsion importants et cela permet un gain de masse sur l'aube par rapport à l'état de l'art d'une aube bipale avec un pied central.The fact of placing each stilt in the extension of each blade makes it possible to better align the passage of the stresses to hold the blade between the blades and the stilts during the rotation of the rotor. There is therefore no extra thickness to be provided in the dimensioning of the stilts to resist significant twisting moments and this allows a weight saving on the blade compared to the state of the art of a two-bladed blade. with a central foot.
De plus, lorsque le disque est ainsi équipé d'une succession d'aubes telles que les pales peuvent être associées deux par deux à des échasses qui sont dans leur prolongement, il peut suffire de ne prévoir des dents de maintien que dans un intervalle circonférentiel sur deux entre les échasses. En effet, si les moyens d'attaches sont symétriques, un intervalle sur deux correspond à la présence des surfaces d'appui et l'autre est vide de moyens de maintien.Moreover, when the disc is thus equipped with a succession of vanes such that the blades can be associated two by two with stilts which are in their extension, it may suffice to provide holding teeth only in one out of two circumferential intervals between the stilts. Indeed, if the attachment means are symmetrical, one interval out of two corresponds to the presence of the bearing surfaces and the other is empty of holding means.
Cela permet donc de diminuer la masse des dents de maintien en périphérie du disque. En effet, par rapport à des aubes monopales, on diminue le nombre de dents équivalentes par deux, et par rapport à des aubes bipales selon l'état de l'art avec un pied central, on diminue la masse des dents en les écartant et en diminuant leur largeur circonférentielle.This therefore makes it possible to reduce the mass of the retaining teeth on the periphery of the disc. Indeed, compared to single-bladed blades, the number of equivalent teeth is reduced by two, and compared to two-bladed blades according to the state of the art with a central root, the mass of the teeth is reduced by moving them apart and by decreasing their circumferential width.
Enfin, du point de vue du maintien de l'aube sur le disque en rotation, dans le cas d'une aube bipale, ne comprenant donc que la première et la deuxième pale, l'invention permet de limiter le caractère hyperstatique du maintien radial face aux efforts centrifuges. En effet, par rapport à une solution de l'état de l'art pour une aube bipale avec une attache complète sous chaque pale, l'aube selon l'invention ne présente que deux plans de contact au lieu de quatre. Avec quatre plans de contact, il faudrait imposer des tolérances de fabrication beaucoup plus serrées que ce qui se fait dans l'état de l'art pour s'assurer qu'une ou deux des surfaces d'appui ne soient pas inopérantes.Finally, from the point of view of maintaining the blade on the rotating disc, in the case of a two-bladed blade, therefore comprising only the first and the second blade, the invention makes it possible to limit the hyperstatic nature of the radial support against centrifugal forces. Indeed, compared to a state-of-the-art solution for a two-bladed blade with a complete attachment under each blade, the blade according to the invention has only two contact planes instead of four. With four contact planes, it would be necessary to impose much tighter manufacturing tolerances than what is done in the state of the art to ensure that one or two of the bearing surfaces are not inoperative.
De plus l'écartement plus important des surfaces d'appui est aussi avantageux pour le positionnement des pales de l'aube par rapport au disque et donc leur positionnement dans le moteur. En effet, ces surfaces d'appui définissent avec les dents du disque des surfaces de contact qui positionnent les aubes. Plus la distance entre les deux surfaces de contact est grande, plus les défauts sur ces surfaces auront un impact faible sur le défaut de positionnement angulaire des pales.In addition, the greater spacing of the bearing surfaces is also advantageous for the positioning of the blades of the dawn relative to the disc and therefore their positioning in the engine. Indeed, these support surfaces define with the teeth of the disc contact surfaces which position the blades. The greater the distance between the two contact surfaces, the smaller the defects on these surfaces will have on the angular positioning defect of the blades.
Préférentiellement, la surface d'appui de l'élément d'attache porté par chaque échasse se trouve sur un côté de l'élément d'attache extérieur par rapport aux deux échasses suivant une direction circonférentielle perpendiculaire auxdites directions axiale et radiale.Preferably, the support surface of the attachment element carried by each stilt is located on one side of the outer attachment element relative to the two stilts in a circumferential direction perpendicular to said axial and radial directions.
Dans ce cas, les échasses avec leur élément d'attache peuvent être glissées au montage entre deux dents successives du disque en laissant un vide entre les deux échasses.In this case, the stilts with their attachment element can be slid during assembly between two successive teeth of the disc, leaving a gap between the two stilts.
La surface d'appui est elle-même généralement inclinée par rapport à la direction radiale.The bearing surface is itself generally inclined with respect to the radial direction.
De plus, dans le cas d'une aube bipale, le placement des surfaces d'appui circonférentiellement à l'extérieur des échasses concourre à la stabilité de la liaison au disque vis-à -vis des efforts exercés sur l'aube lors du fonctionnement du rotor.In addition, in the case of a two-bladed blade, the placement of the bearing surfaces circumferentially outside the stilts contributes to the stability of the connection to the disc with respect to the forces exerted on the blade during operation. of the rotor.
Avantageusement, chaque échasse comporte un voile sensiblement plan et parallèle à la direction axiale formant ladite extrémité portant l'élément d'attache, ledit voile et l'élément d'attache étant agencés pour avoir une face latérale tournée dans la direction opposée à l'autre échasse qui est parallèle à la direction axiale avec un profil constant.Advantageously, each stilt comprises a veil substantially plane and parallel to the axial direction forming said end bearing the attachment element, said veil and the attachment element being arranged to have a side face facing in the direction opposite to the another stilt that is parallel to the axial direction with a constant profile.
Dans cette configuration, une partie du voile peut aussi être engagée entre les dents du disque et coopérer ainsi avec les dents pour participer au maintien latéral de l'aube.In this configuration, part of the veil can also be engaged between the teeth of the disc and thus cooperate with the teeth to participate in the lateral retention of the blade.
Dans un mode de réalisation préféré, l'élément d'attache comporte une patte formant un ergot par rapport audit voile en bout de l'échasse.In a preferred embodiment, the attachment element comprises a lug forming a lug with respect to said sail at the end of the stilt.
Cette réalisation minimise la masse utilisée pour réaliser l'attache de l'aube.This embodiment minimizes the mass used to make the attachment of the blade.
De préférence, les pales étant décalées d'une distance donnée au niveau de leur jonction avec la plateforme suivant une direction circonférentielle, perpendiculaire auxdites directions axiale et radiale, lesdites extrémités des deux échasses portant l'élément d'attache sont décalées d'une distance sensiblement égale à ladite distance donnée.Preferably, the blades being offset by a given distance at their junction with the platform in a circumferential direction, perpendicular to said axial and radial directions, said ends of the two stilts carrying the attachment element are offset by a distance substantially equal to said given distance.
Ainsi, les attaches de plusieurs aubes successives sur le rotor créent un motif répétitif qui peut coopérer avec une distribution uniforme de dents semblables en périphérie du disque du rotor.Thus, the attachments of several successive blades to the rotor create a repeating pattern which can cooperate with a uniform distribution of similar teeth on the periphery of the rotor disk.
De préférence, l'élément d'attache de chaque échasse est positionné suivant une direction circonférentielle, perpendiculaire auxdites directions axiale et radiale, sur une position moyenne de l'extrémité liée à la plateforme de la pale correspondante.Preferably, the attachment element of each stilt is positioned in a circumferential direction, perpendicular to said axial and radial directions, on an average position of the end linked to the platform of the corresponding blade.
De la sorte, on minimise les décalages que l'échasse doit rattraper entre les aubes au profil courbe et les surfaces d'appui ayant une extension axiale rectiligne. On minimise ainsi le dimensionnement des échasses par rapport aux contraintes induites par les efforts centrifuges.In this way, the offsets that the stilt must make up between the blades with a curved profile and the bearing surfaces having a rectilinear axial extension are minimized. This minimizes the dimensioning of the stilts with respect to the stresses induced by the centrifugal forces.
Avantageusement, chaque échasse est conformée de manière à ce que la jonction de l'échasse avec la plateforme suive la jonction avec la plateforme de la pale correspondante dans son évolution suivant la direction axiale.Advantageously, each stilt is shaped so that the junction of the stilt with the platform follows the junction with the platform of the corresponding blade in its evolution along the axial direction.
L'aube peut avantageusement comprendre au moins une paroi reliant les deux échasses de manière transversale à ladite direction axiale.The blade can advantageously comprise at least one wall connecting the two stilts transversely to said axial direction.
Une telle paroi a une fonction de raidisseur. Elle évitera les déformations des échasses sous les efforts centrifuges et peut permettre de réduire l'épaisseur des échasses, donc leur masse.Such a wall has a stiffening function. It will prevent deformation of the stilts under centrifugal forces and can make it possible to reduce the thickness of the stilts, and therefore their mass.
Ladite paroi peut s'étendre radialement entre les échasses depuis la plateforme jusqu'à une ligne joignant des extrémités radiales des éléments d'attache opposées à la plateforme.Said wall may extend radially between the stilts from the platform to a line joining radial ends of the attachment elements opposite the platform.
Cela permet de fermer le passage d'air sous la plateforme de l'aube, entre les dents du disque.This closes the air passage under the blade platform, between the teeth of the disc.
L'invention concerne également un rotor de turbomachine comportant des aubes telles que décrites précédemment.The invention also relates to a turbomachine rotor comprising blades as described above.
Avantageusement, le disque dudit rotor porte à sa périphérie une succession de dents semblables conformées pour coopérer avec les moyens d'attache des aubes, deux dents successives étant séparées suivant la direction circonférentielle d'une distance au moins égale à la largeur d'une dent suivant cette direction.Advantageously, the disk of said rotor carries at its periphery a succession of similar teeth shaped to cooperate with the attachment means of the blades, two successive teeth being separated in the circumferential direction by a distance at least equal to the width of one tooth. following this direction.
La présente invention sera mieux comprise et d'autres détails, caractéristiques et avantages de la présente invention apparaîtront plus clairement à la lecture de la description qui suit, en référence aux dessins annexés sur lesquels :
- La
figure 1 représente une vue de l'arrière suivant l'axe de rotation d'une aube bipale selon l'état de l'art coupée selon un plan radial. - La
figure 2 représente une vue de l'arrière suivant l'axe de rotation d'une aube bipale selon l'invention. - La
figure 3 représente une vue de l'arrière suivant l'axe de rotation d'une aube bipale selon l'invention coupée selon un plan radial. - La
figure 4 représente une vue en projection radiale sur la plateforme interne des éléments d'une aube selon l'invention. - La
figure 5 représente un détail de lafigure 3 avec la représentation d'une dent fictive supprimée grâce à l'invention par rapport à certaines réalisations selon l'état de l'art. - La
figure 6 représente une vue en perspective de l'arrière d'un perfectionnement de l'aube bipale selon l'invention coupée selon un plan radial. - La
figure 7 représente une partie de la vue de l'arrière suivant l'axe de rotation d'une variante par rapport à l'aube de lafigure 6 . - La
figure 8 représente une partie de vue de l'arrière d'une variante par rapport à l'aube de lafigure 6 .
- The
figure 1 shows a rear view along the axis of rotation of a two-bladed blade according to the state of the art cut along a radial plane. - The
figure 2 shows a rear view along the axis of rotation of a two-bladed blade according to the invention. - The
picture 3 - The
figure 4 represents a view in radial projection on the internal platform of the elements of a blade according to the invention. - The
figure 5 represents a detail of thepicture 3 - The
figure 6 shows a perspective view of the rear of an improvement of the two-bladed blade according to the invention cut along a radial plane. - The
figure 7 represents part of the rear view along the axis of rotation of a variant with respect to the blade of thefigure 6 . - The
figure 8 represents a part of view of the rear of a variant compared to the dawn of thefigure 6 .
Les éléments ayant les mêmes fonctions dans différentes variantes d'aubes selon l'invention sont repérés avec les mêmes références sur les figures.The elements having the same functions in different variants of blades according to the invention are marked with the same references in the figures.
En référence aux
Les directions axiale et radiale font référence à l'axe du rotor, les termes interne et externe s'entendent par rapport à la direction radiale. Les termes amont et aval dans la direction axiale font référence au sens de l'écoulement pour lequel les aubes ont été conçues.The axial and radial directions refer to the axis of the rotor, the terms internal and external refer to the radial direction. The terms upstream and downstream in the axial direction refer to the direction of flow for which the blades were designed.
Les plateformes interne 4 et externe 5 délimitent un secteur angulaire de la veine de passage du flux de gaz autour dudit axe X. La plateforme externe 5 n'est pas concernée par l'invention et peut éventuellement ne pas exister, c'est d'ailleurs généralement le cas pour les aubes de compresseur. Elle n'est donc pas décrite plus avant. Plus particulièrement, la plateforme interne 4 est délimitée suivant la direction circonférentielle T entre deux plans axiaux, de manière à s'ajuster avec les plateformes des aubes adjacentes en vue d'assurer une continuité de paroi de la veine. Le corps 8 de la plateforme interne 4 délimitant la veine a un profil radial déterminé par la conception de la turbine qui peut être incliné par rapport à la direction radiale R. Sur l'exemple, ce profil s'écarte de l'axe X du rotor en allant de l'amont vers l'aval. Aux extrémités axiales dudit corps 8, la plateforme interne 4 comprend ici un voile radial amont 9 et un voile radial aval 10 qui s'étendent radialement de manière à entrer en contact avec les dents 7 de maintien sur le disque 6, à une même distance de l'axe X. Ici, le voile amont 9 et le voile aval 10 ont une fonction de maintien de l'aube 1, d'une part pour bloquer son mouvement dans le sens radial vers l'axe X, d'autre part pour bloquer la rotation autour d'une direction parallèle à l'axe X. La plateforme interne 4 comprend en général des dispositifs fixés aux voiles amont 9 et aval 10, par exemple des becquets annulaires 11, pour effectuer une étanchéité avec les éléments stator de la turbine qui entourent le rotor dans la direction axiale.The internal 4 and external 5 platforms delimit an angular sector of the passage passage of the gas flow around said axis X. The
Les deux pales 2, 3, ont un profil courbe et incliné par rapport à la direction axiale X qui peut évoluer le long de leur envergure suivant la direction radiale R. La
L'attache de l'aube 1 au disque 6 comporte ici deux échasses 12, 13 séparées qui sont reliées au corps 8 de la plateforme 4 et s'étendent à partir de celui-ci dans le prolongement radial d'une des pales 2, 3, en ayant sensiblement la même extension que lesdites pales 2, 3 suivant la direction axiale X. Chaque échasse 12, 13 se termine ici, du côté opposé à la plateforme, par un voile axial 14, 15, parallèle à la direction radiale R, qui est relié à une patte 16, 17, parallèle à la direction axiale X et inclinée par rapport à la direction radiale, laquelle patte forme l'extrémité libre de l'échasse. La dite patte 16, 17 s'écarte latéralement vers l'extérieur en partant du voile axial 14,15, formant, en coupe transverse, un ergot d'extrémité, de sorte que sa surface latérale extérieure S1, S2, est tournée vers la plateforme 4. La surface d'appui S1, S2 est généralement inclinée par rapport à la direction radiale. L'angle d'inclinaison dépend de la conception faite par l'homme du métier en fonction de la géométrie de la turbine et des contraintes de fonctionnement. Classiquement il prend des valeurs entre 40 et 50°, mais peut se trouver en dehors de cette plage. Chaque patte 16, 17 forme ainsi un élément d'attache de l'aube 1 et les surfaces S1, S2 forment des surface d'appui permettant de retenir l'aube dans la direction radiale R orientée de la plateforme vers les pales. Les voiles axiaux 14, 15 des échasses 12, 13 et les pattes d'extrémité 16, 17 coopèrent avec les dents 7 du disque 6 pour maintenir l'aube 1 suivant un fonctionnement qui sera décrit par la suite.The attachment of the
Les voiles axiaux 14, 15 des extrémités de chaque échasse 12, 13 sont centrés sur une position moyenne des bases des pales 2, 3 sur la plateforme 4 dans la direction circonférentielle T et sont donc décalés suivant cette direction d'une distance D' sensiblement égale au décalage D entre les bases desdites pales 2, 3. Ici, les ensembles formés des voiles axiaux 14, 15 et des pattes d'extrémité 16, 17, sont sensiblement symétriques par rapport à un plan axial passant au milieu des échasses 12, 13.The axial sails 14, 15 of the ends of each
Chaque échasse 12, 13 a une forme tridimensionnelle entre le voile axial 14, 15, et la plateforme 4, pour suivre le profil de la base de la pale 2, 3 correspondante au niveau de sa jonction avec le corps 8 de la plateforme 4.Each
En correspondance, le disque 6 du rotor comporte à sa périphérie une couronne de dents 7 semblables qui sont décalées suivant la direction circonférentielle T d'une distance sensiblement égale à deux fois la distance de décalage D entre les bases des pales 2, 3, de sorte qu'il y a deux fois moins de dents 7 que de pales 2, 3, sur le rotor.In correspondence, the
Chaque dent 7 s'étend ici parallèlement à l'axe X sur une distance correspondant sensiblement à l'écart entre les voiles amont 9 et aval 10 de la plateforme, avec un profil transverse constant. De cette manière, l'aube 1 décrite précédemment peut être installée entre deux dents 7 successives en glissant, suivant la direction axiale X, les voiles axiaux 14, 15 des échasses 12, 13 et les pattes d'extrémité 16, 17, entre deux dents 7 successives. Des dispositifs connus, non décrits ici, permettent alors de maintenir l'aube 1 dans sa position axiale par rapport au rotor. Ces dispositifs ne sont pas concernés par l'invention.Each
Le profil de chaque dent 7 a ici la forme d'un bulbe. En partant de la surface extérieure du disque 6, la dent comporte donc une partie d'épaisseur donnée constante suivie d'un élargissement. La forme de cet élargissement est définie de manière à former, d'un côté de la dent 7, une surface tournée vers le disque 6 qui est en contact avec la surface d'appui S1 liée à l'une des échasses 12 de l'aube 1 et à former de l'autre côté de la dent, une autre surface tournée vers le disque 6 qui est en contact avec la surface d'appui S2 liée à l'autre des échasses 13 d'une aube adjacente, semblable à l'aube 1. Lorsque les éléments d'attache 16, 17, des deux échasses 12, 13 des aubes sont symétriques, comme décrit précédemment, le profil des dents 7 est symétrique par rapport à un plan radial médian de la dent.The profile of each
Enfin la dent 7 comporte une surface radialement extérieure sensiblement plate ou formant une portion de cylindre circulaire centré sur l'axe X du rotor. Ainsi, les bords libres des voiles amont 9 et aval 10 de la plateforme 4 peuvent prendre appui dessus lorsque le moteur est à l'arrêt. Comme indiqué précédemment, l'appui des voiles amont 9 et aval 10 bloque les déplacements radiaux de l'aube 1 vers le disque 6, de manière à maintenir le positionnement correct de l'aube 1 sur le rotor.Finally,
La surface d'appui S1, S2 de la patte d'extrémité 16, 17, portée par chaque échasse 12, 13 est conçue pour reprendre environ la moitié des efforts centrifuges appliqués à l'aube 1, soit sensiblement ceux correspondant à une desdites pales 2, 3. Une échasse 12, 13 avec sa patte d'extrémité 16, 17 doivent donc être dimensionnées sensiblement pour supporter les contraintes imposées par une pale. Par ailleurs, comme cela est représenté par les flèches sur la
On notera que, pour ce qui est de résister aux efforts centrifuges, l'aube 1 est maintenue par les contacts de seulement deux surfaces d'appui S1 et S2, chacune s'étendant de manière inclinée par rapport à la direction radiale, à l'extérieur d'une échasse 12, 13 suivant la direction circonférentielle T. Cela permet de limiter l'hyperstatisme entre l'aube et le disque. De plus les deux échasses 12, 13 étant écartées, lesdites surfaces d'appui S1, S2 sont elles mêmes écartées et situées près des bords de l'aube 1 dans la direction circonférentielle T. Cela améliore la stabilité du montage sous la contrainte des efforts centrifuges, par rapport à une attache unique rassemblée au centre de l'aube.It will be noted that, as regards resisting centrifugal forces, the
L'invention permet aussi un gain en masse sur le disque 6. On peut voir sur les
Selon un perfectionnement de l'invention, en référence à la
Dans une variante, représentée sur la
La description des modes de réalisation de l'invention faite dans ce document n'est pas limitative. L'aube décrite ici est bipale mais on peut envisager des aubes comportant une succession de couples de pales avec leurs échasses dans le prolongement. Dans ce cas, cependant, le montage des surfaces d'appui sur les dents devient hyperstatique pour l'aube, donc plus délicat à ajuster. D'autres réalisations des moyens de liaison avec le disque, non représentées, peuvent aussi être envisagées. Par exemple, le blocage radial de l'aube vers l'axe peut être assuré par un élément porté par les échasses qui appuie sur le disque 6 ou sur le sommet radial des dents 7. La plateforme interne 4 peut alors ne pas comporter de voile amont ou aval ayant une fonction de maintien. L'invention a été décrite dans le cas d'une aube de turbine mais elle peut également concerner des aubes adaptées à d'autres types de rotors, tels des rotors de compresseur pas exemple. Par ailleurs, un élément d'attache en extrémité des échasses 12, 13 autre qu'une patte formant un coude par rapport au voile axial 14, 15, peut être utilisé pour réaliser les surfaces d'appui S1, S2. Il peut être réalisé, par exemple, par des becquets s'écartant de la surface du voile. La forme des dents sur le disque sera alors adaptée à la forme des éléments d'attache utilisés sur l'aube.The description of the embodiments of the invention given in this document is not limiting. The blade described here is two-bladed but one can envisage blades comprising a succession of pairs of blades with their stilts in the extension. In this case, however, the mounting of the bearing surfaces on the teeth becomes hyperstatic for the blade, and therefore more difficult to adjust. Other embodiments of the means of connection with the disk, not shown, can also be envisaged. For example, the radial blocking of the blade towards the axis can be ensured by an element carried by the stilts which presses on the
Claims (10)
- A vane (1) for a turbomachine rotor comprising a first blade (2) and a second blade (3) arranged to form two successive blades of a bladed rotor, a platform (4) substantially forming an angular wall sector in an axial direction (X), said two blades (2, 3) being connected to the platform (4) by one of the ends thereof by extending substantially in a direction referred to as radial (R) which is substantially perpendicular to said axial direction (X), and attachment means connected to the platform (4) which are designed to cooperate with fastening means (7) on a disk (6) of the rotor, characterised in that the attachment means comprise two individual supports (12, 13), each support extending from the platform (4), in the radial direction (R), in the extension of one of said two blades (2, 3), and carrying an attachment member (16, 17) at an end opposite said platform (4), said attachment member extending substantially parallel to said axial direction (X) and comprising at least one surface (S1, S2) facing the platform (4) with a constant cross-sectional profile perpendicular to said axial direction (X), so as to form a bearing surface for holding the vane (1) in said radial direction (R) oriented from the platform (4) to the blades (2, 3).
- The vane (1) according to the preceding claim, characterised in that the bearing surface (S1, S2) of the attachment member (16, 17) carried by each support is on a side of the attachment member which is external with respect to the two supports (12, 13) in a circumferential direction (T) perpendicular to said axial (X) and radial (R) directions.
- The vane (1) according to any one of the preceding claims, characterised in that each support (12, 13) comprises a substantially planar web (14, 15) parallel to the axial direction (X) forming said end carrying the attachment member (16, 17), said web (14, 15) and the attachment member (16, 17) being arranged so as to have a lateral face facing the opposite direction to the other support which is parallel to the axial direction (X) with a constant profile.
- The vane (1) according to the preceding claim, characterized in that the attachment member (16, 17) comprises a tab forming a lug with respect to the web (14, 15) at the end of the support.
- The vane (1) according to any one of the preceding claims, characterized in that, the blades (2, 3) being offset by a given distance (D) at their junction with the platform (4) in a circumferential direction (T), perpendicular to said axial (X) and radial (R) directions, said ends of the two supports (12, 13) carrying the attachment member (16, 17) are offset by a distance (D') substantially equal to said given distance (D).
- The vane (1) according to any one of the preceding claims, characterised in that the attachment member (16, 17) of each support (12, 13) is positioned in a circumferential direction (T), perpendicular to said axial (X) and radial (R) directions, on a mean position of the end connected to the platform (4) of the corresponding blade (2, 3).
- The vane (1) according to any one of the preceding claims, characterized in that each support (12, 13) is shaped in such a way that the junction of the support with the platform (4) follows the junction with the platform (4) of the corresponding blade (2, 3) in its evolution along the axial direction (X).
- The vane (21, 31) according to any one of the preceding claims, characterised in that it comprises at least one wall (18, 19) connecting the two supports (12, 13) transversely to said axial direction (X).
- The vane (31) according to the preceding claim, characterised in that, said wall (18, 19) extends radially between the supports (12, 13) from the platform (4) to a line joining radial ends of the attachment members (16, 17) opposite to the platform.
- A turbomachine rotor comprising vanes according to any one of the preceding claims.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1762028A FR3074839B1 (en) | 2017-12-13 | 2017-12-13 | TURBOMACHINE ROTOR MULTIPAL ROTOR AUB AND ROTOR COMPRISING SAME |
PCT/EP2018/084462 WO2019115578A1 (en) | 2017-12-13 | 2018-12-12 | Multi-blade vane for a turbomachine rotor and rotor comprising same |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3724454A1 EP3724454A1 (en) | 2020-10-21 |
EP3724454B1 true EP3724454B1 (en) | 2022-02-16 |
Family
ID=61224105
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP18829759.2A Active EP3724454B1 (en) | 2017-12-13 | 2018-12-12 | Multi-blade vane for a turbomachine rotor and rotor comprising same |
Country Status (5)
Country | Link |
---|---|
US (1) | US11156108B2 (en) |
EP (1) | EP3724454B1 (en) |
CN (1) | CN111448366B (en) |
FR (1) | FR3074839B1 (en) |
WO (1) | WO2019115578A1 (en) |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5735673A (en) * | 1996-12-04 | 1998-04-07 | United Technologies Corporation | Turbine engine rotor blade pair |
FR2851285B1 (en) | 2003-02-13 | 2007-03-16 | Snecma Moteurs | REALIZATION OF TURBINES FOR TURBOMACHINES HAVING DIFFERENT ADJUSTED RESONANCE FREQUENCIES AND METHOD FOR ADJUSTING THE RESONANCE FREQUENCY OF A TURBINE BLADE |
ES2316035T3 (en) * | 2006-07-18 | 2009-04-01 | Industria De Turbo Propulsores S.A. | HIGH SPEAKER ROTOR. |
RU2645510C2 (en) | 2012-11-13 | 2018-02-21 | Снекма | Blank and single-piece blade unit for intermediate casing of gas turbine engine |
US9677405B2 (en) * | 2013-03-05 | 2017-06-13 | Rolls-Royce Corporation | Composite gas turbine engine blade having multiple airfoils |
-
2017
- 2017-12-13 FR FR1762028A patent/FR3074839B1/en active Active
-
2018
- 2018-12-12 WO PCT/EP2018/084462 patent/WO2019115578A1/en unknown
- 2018-12-12 EP EP18829759.2A patent/EP3724454B1/en active Active
- 2018-12-12 US US16/770,856 patent/US11156108B2/en active Active
- 2018-12-12 CN CN201880079927.5A patent/CN111448366B/en active Active
Also Published As
Publication number | Publication date |
---|---|
WO2019115578A1 (en) | 2019-06-20 |
US20200392855A1 (en) | 2020-12-17 |
EP3724454A1 (en) | 2020-10-21 |
FR3074839A1 (en) | 2019-06-14 |
FR3074839B1 (en) | 2019-11-08 |
US11156108B2 (en) | 2021-10-26 |
CN111448366A (en) | 2020-07-24 |
CN111448366B (en) | 2022-09-16 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP2705223B1 (en) | Sealing apparatus of a guide conduit of a turbine of a turbomachine | |
EP2459884B1 (en) | Outer shell sector for a bladed stator ring of an aircraft turbine engine, comprising vibration-damping blocks | |
EP2603670B1 (en) | Device for locking a root of a rotor blade | |
EP2694781B1 (en) | Sealing ring for a turbine stage of an aircraft turbomachine, comprising slotted anti-rotation pegs | |
WO2013150224A1 (en) | Variable pitch rectifier for a turbomachine compressor comprising two inner rings | |
FR3029960A1 (en) | AUBES WHEEL WITH RADIAL SEAL FOR A TURBOMACHINE TURBINE | |
FR3082233A1 (en) | TURBINE SET | |
FR3099520A1 (en) | Turbomachine wheel | |
FR3001760A1 (en) | Fixed blading for air flow distribution in low pressure turbine of turboshaft engine, has annular sealing plate brought back on annular inner platform at upstream side of radial partition of inner platform with respect to air flow | |
FR3029961A1 (en) | AUBES WHEEL WITH BECQUETS FOR A TURBOMACHINE TURBINE | |
EP3265654B1 (en) | Bladed integrated disk comprising a shortened hub and a supporting element | |
EP3724454B1 (en) | Multi-blade vane for a turbomachine rotor and rotor comprising same | |
EP3149286B1 (en) | Sealing plate with fuse function | |
FR2960589A1 (en) | Paddle wheel i.e. low pressure turbine wheel, for turboshaft engine e.g. turbopropeller, of airplane, has sealing units arranged between piece and upstream ends of platforms of paddles | |
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 | |
EP4088008A1 (en) | Blade for a rotating bladed disk for an aircrft turbine engine comprising a sealing lip having an optimized non-constant cross section | |
FR3108938A1 (en) | Sealing ring for a turbine engine turbine rotor | |
FR3084399A1 (en) | MOBILE VANE FOR A WHEEL OF A TURBOMACHINE | |
FR3078740A1 (en) | DYNAMIC LICENSE SEAL COMPRISING AN ACTIVE PART IN A CIRCONFERENTIALLY LIMITED SIZE | |
FR2948737A1 (en) | Outer shell sector forming assembly for bladed ring sector of turbine or compressor stator in turbojet engine of aircraft, has vibration-damping block supported against two friction surfaces respectively provided on two elementary sectors | |
FR3137121A1 (en) | Bladed assembly with inter-platform connection by interposed rolling element | |
FR3001761A1 (en) | Flow distribution vane for use in turboshaft engine of aircraft, has sealing plate comprising quibblings uniformly distributed along circumference of plate for holding plate in axial position in groove with respect to axis of inner platform | |
FR2962481A1 (en) | Vibration dampener for blade of rotor of gas turbine engine, has connection zone providing support against external support surface under effect of centrifugal rotation force of rotor in way to ensure axial sealing against gases |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: UNKNOWN |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE INTERNATIONAL PUBLICATION HAS BEEN MADE |
|
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 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE |
|
17P | Request for examination filed |
Effective date: 20200623 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
AX | Request for extension of the european patent |
Extension state: BA ME |
|
DAV | Request for validation of the european patent (deleted) | ||
DAX | Request for extension of the european patent (deleted) | ||
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: GRANT OF PATENT IS INTENDED |
|
INTG | Intention to grant announced |
Effective date: 20210419 |
|
RIN1 | Information on inventor provided before grant (corrected) |
Inventor name: NEGRI, ARNAUD, NICOLAS |
|
GRAJ | Information related to disapproval of communication of intention to grant by the applicant or resumption of examination proceedings by the epo deleted |
Free format text: ORIGINAL CODE: EPIDOSDIGR1 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE |
|
INTC | Intention to grant announced (deleted) | ||
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: GRANT OF PATENT IS INTENDED |
|
INTG | Intention to grant announced |
Effective date: 20210923 |
|
GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE PATENT HAS BEEN GRANTED |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM 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 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R096 Ref document number: 602018031008 Country of ref document: DE |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: REF Ref document number: 1468998 Country of ref document: AT Kind code of ref document: T Effective date: 20220315 |
|
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: SE Ref legal event code: TRGR |
|
REG | Reference to a national code |
Ref country code: LT Ref legal event code: MG9D |
|
REG | Reference to a national code |
Ref country code: NL Ref legal event code: MP Effective date: 20220216 |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: MK05 Ref document number: 1468998 Country of ref document: AT Kind code of ref document: T Effective date: 20220216 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: RS 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: 20220216 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: 20220616 Ref country code: NO 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: 20220516 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: 20220216 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: 20220216 Ref country code: HR 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: 20220216 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: 20220216 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: 20220516 |
|
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: 20220216 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: 20220216 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: 20220517 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: 20220216 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: 20220216 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
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: 20220617 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: SM 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: 20220216 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: 20220216 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: 20220216 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: 20220216 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: 20220216 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: 20220216 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R097 Ref document number: 602018031008 Country of ref document: DE |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: AL 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: 20220216 |
|
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: 20221117 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: IT Payment date: 20221122 Year of fee payment: 5 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
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: 20220216 |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: PL |
|
REG | Reference to a national code |
Ref country code: BE Ref legal event code: MM Effective date: 20221231 |
|
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: 20221212 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: LI Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20221231 Ref country code: IE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20221212 Ref country code: CH Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20221231 |
|
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: 20221231 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20231121 Year of fee payment: 6 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: SE Payment date: 20231121 Year of fee payment: 6 Ref country code: FR Payment date: 20231122 Year of fee payment: 6 Ref country code: DE Payment date: 20231121 Year of fee payment: 6 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
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: 20220216 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: MK 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: 20220216 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; INVALID AB INITIO Effective date: 20181212 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: MC 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: 20220216 |