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EP3433469B1 - Platform, fan assembly and fan - Google Patents

Platform, fan assembly and fan Download PDF

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Publication number
EP3433469B1
EP3433469B1 EP17716956.2A EP17716956A EP3433469B1 EP 3433469 B1 EP3433469 B1 EP 3433469B1 EP 17716956 A EP17716956 A EP 17716956A EP 3433469 B1 EP3433469 B1 EP 3433469B1
Authority
EP
European Patent Office
Prior art keywords
platform
disk
fan
upstream
bottom wall
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP17716956.2A
Other languages
German (de)
French (fr)
Other versions
EP3433469A1 (en
Inventor
Thomas Alain DE GAILLARD
Alexandre Bernard Marie BOISSON
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Safran Aircraft Engines SAS
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Publication date
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP3433469A1 publication Critical patent/EP3433469A1/en
Application granted granted Critical
Publication of EP3433469B1 publication Critical patent/EP3433469B1/en
Active legal-status Critical Current
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
    • 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
    • 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

Definitions

  • the present invention relates to the general field of aeronautical turbomachines, and more specifically to the field of blade and disk platforms of the fan of an aeronautical turbomachine, an assembly comprising the platforms and the disk, and a fan comprising this assembly.
  • the fan blade platforms In a turbomachine, the fan blade platforms must fulfill several functions. From an aerodynamic point of view, these platforms have the primary function of defining the air flow path. In addition, they must also be capable of withstanding high forces while deforming as little as possible and remaining integral with the disk which carries them.
  • the platforms have a first part making it possible to define the air flow path and to ensure the retention of the platform when the motor is rotating, and a second part making it possible to limit the deformations of the first part under the effects of centrifugal forces and to maintain the platform in position when the engine is stopped.
  • the platform can take the form of a box with a two-dimensional vein wall retained downstream by a drum and upstream by a shroud, the upstream retention by the shroud being carried out above the fan disc tooth (a flange of the shroud blocking the platform axially and radially upstream).
  • the document US 2016/0069355 A1 discloses an example of a turbomachine comprising blade platforms and a fan disk.
  • Such upstream retention carried out above the tooth of the disc with a ferrule has the disadvantage of imposing a high hub ratio, the hub ratio being the ratio of the radius taken between the axis of rotation and the point of the edge leading edge of the blade flush with the surface of the platform, on the radius taken between the axis of rotation and the outermost point of the leading edge.
  • this upstream retention is liable to generate over-stresses on the tooth and in the socket of the disc, at the level of the connection between the ferrule and the disc.
  • Axial means the direction of the greatest length of the platform, and “radial” means the direction perpendicular to the axial direction and to the main surface of the bottom wall.
  • Upstream means upstream with respect to the direction of air flow, when the platform rests on a fan disc.
  • the platform can take the form of a box formed by assembling the vein wall and the bottom wall.
  • the duct wall makes it possible to delimit the flow duct of the air entering the fan.
  • the bottom wall makes it possible to hold the vein wall in position, and also to limit its deformations under the effect of centrifugal forces.
  • the bottom wall also comprises a main surface which can be supported on a fan disk.
  • the axial and radial retention surfaces arranged on two axial ends of the platform, make it possible to retain and maintain the platform in position relative to the disc on which it rests, when the disc is in motion.
  • the radial retention surface arranged on the upstream axial end of the platform is offset radially with respect to a main surface of the bottom wall.
  • “Radially offset” means offset in the direction in which the bottom wall bears on the disc.
  • the radial retention surface and the main surface of the bottom wall can be substantially parallel with respect to each other.
  • This offset of the radial retention surface makes it possible to modify the shape of the upstream axial end of the stream wall, and therefore of the platform, with respect to known platforms.
  • the platform can take the form of a plunging box, that is to say the upstream axial end of which is offset radially with respect to the main surface of the bottom wall.
  • This modification of the shape of the platform thus makes it possible to modify the air flow path when the platform is placed in a fan, is therefore to reduce the hub ratio in order to improve the performance of the fan, and therefore to the turbomachine in which the fan is mounted.
  • the bottom wall has a surface inclined with respect to the main surface of the bottom wall, continuously connecting the main surface of the bottom wall and the radial retention surface disposed on the upstream axial end of the platform.
  • the radial retention surface arranged on the upstream axial end of the platform being offset radially with respect to the main surface of the bottom wall, the inclined surface corresponds to the zone of the bottom wall making it possible to compensate for the offset between the surface radial retention and the main surface of the bottom wall. It is therefore understood that the inclined surface rests on the disc.
  • the radial retention surface disposed on the upstream axial end of the platform, the inclined surface and the main surface of the bottom wall can be in one piece constituting the bottom wall.
  • the inclined surface is a straight wall portion.
  • the rectilinear wall portion linearly connects the radial retention surface with the main surface of the bottom wall, thus modifying the shape of the upstream axial end of the platform in order to reduce the hub ratio.
  • This rectilinear wall portion has the advantage of having a simple shape that is easy to produce, for example by machining.
  • the inclined surface is a curvilinear wall portion.
  • curvilinear wall portion progressively connects the radial retention surface with the main surface of the bottom wall, thus modifying the shape of the upstream axial end of the platform in order to reduce the hub ratio.
  • This portion of curvilinear wall has the advantage of softening the change in slope from the main surface of the bottom wall, avoiding the presence of a break at the junction between the inclined surface and the main surface, unlike the straight wall portion, and thus reduce the stresses at this junction.
  • the inclined surface and the vein wall are substantially parallel.
  • the upstream axial end of the platform has a plunging shape, the inclined surface and the section of the stream being inclined radially in the same way in the direction in which the platform bears on the disc.
  • This shape of the upstream axial end of the platform makes it possible to reduce the hub ratio.
  • upstream face is understood to mean upstream with respect to the direction in which the air flows, when the disc is placed in a fan.
  • Axial projections are understood to mean axial in the direction of air flow, when the disk is placed in a fan.
  • Randomly offset means offset towards the inside of the disc, that is to say towards the axis of rotation of the disc.
  • the disk can comprise as many axial projections as there are teeth.
  • the axial projections may each include a hole allowing the axial projections to be fixed to a fan platform retention flange, using a screw or a bolt, for example.
  • this fixing zone being offset radially with respect to the teeth of the disc, this has the advantage of freeing up space at the level of the upstream axial end of the tooth of the disc, making it possible, for example, to machine the tooth of the disc.
  • the axial projections are studs machined on the upstream face of the disc.
  • the fixing holes can make it possible to fix an element external to the disc, for example a retaining flange or a ferrule, using a screw or a bolt, for example.
  • Axial projections can also have an insertion hole machined radially on an outer face of the projections. The insertion holes may permit the insertion of fasteners, through which an outer member may be attached to the disc.
  • An upstream axial end of the disk teeth has a beveled surface.
  • the beveled surface may be in the form of an inclined surface, with respect to a main surface of the tooth of the disc, towards the inside of the disc.
  • the beveled surface can be produced by machining the upstream axial end of the tooth of the disc, for example. This machining is possible thanks to the space freed up by the radial offset of the axial projections on the upstream face of the disc.
  • the presence of this beveled surface has the advantage of being able to adapt the shape of the tooth of the disc to the shape of a platform bearing on the tooth, and thus of reducing the hub ratio to improve the performance of the fan.
  • the interface between the flange and the disc is offset radially towards the inside of the disc, with respect to the tooth of the disc, compared to known systems in which this interface is located at the level of the tooth of the disc.
  • This offset makes it possible to limit the stresses at the level of the upstream axial end of the teeth and of the grooves of the disc.
  • the offset of this interface makes it possible to free up space at the level of the upstream axial end of the tooth of the disc, offering more possibility of machining the tooth and therefore of modifying the shape of the platform and thus, reduction of the hub ratio.
  • the inclined surface of the bottom wall is in contact with the beveled surface of the tooth of the disc.
  • the inclined surface and the beveled surface can be parallel.
  • the disc tooth can be machined more freely.
  • the upstream axial end of the tooth may have a bevel to adapt to the shape of the platform, the beveled surface being parallel to the inclined surface of the platform.
  • the upstream retention flange is a ferrule.
  • This presentation also relates to a turbomachine fan comprising an assembly according to any one of the embodiments described in this presentation, and a plurality of vanes mounted in the grooves of the disk.
  • the term “longitudinal” and its derivatives are defined with respect to the main direction of the platform considered; the terms “radial”, “inner”, “outer” and their derivatives are defined with respect to the main axis of the turbomachine; finally, the terms “upstream” and “downstream” are defined with respect to the direction of flow of the fluid passing through the turbomachine. Also, unless otherwise indicated, the same reference signs in different figures designate the same characteristics.
  • FIG. 1 shows a schematic view in longitudinal section of a turbofan engine 1 centered on the axis A according to the invention. It comprises, from upstream to downstream: a fan 2, a low compressor pressure 3, a high pressure compressor 4, a combustion chamber 5, a high pressure turbine 6, and a low pressure turbine 7.
  • FIG 2 shows a schematic view of the fan 2 of the figure 1 according to direction II.
  • the fan 2 comprises a fan disc 40 in which a plurality of grooves 42 are made at its outer periphery. These grooves 42 are rectilinear and extend axially from upstream to downstream all along the disc 40. They are also regularly distributed all around the axis A of the disc 40. In this way, each groove 42 defines with its neighbor a tooth 44 which also extends axially from upstream to downstream all along the disc 40. Equivalently, a groove 42 is delimited between two neighboring teeth 44.
  • the fan 2 further comprises a plurality of blades 20 of curvilinear profile (only four blades 20 have been shown on the figure 2 ).
  • Each blade 20 has a root 20a which is mounted in a respective groove 42 of the fan disk 40.
  • the root 20a of a blade 20 can have a fir tree or dovetail shape adapted to the geometry of the grooves 42.
  • the fan 2 comprises a plurality of added platforms 30, each platform 30 being mounted in the interval between two neighboring fan blades 20, in the vicinity of the feet 20a thereof, in order to delimit, on the interior side, a vein annular air inlet into the fan 2, the vein being delimited on the outside by a fan casing.
  • THE figures 1 and 2 also show an internal radius RI and an external radius RE.
  • the internal radius RI corresponds to the radius taken between the axis of rotation A and the point of the leading edge of a blade 20 flush with the surface of a platform 30.
  • the external radius RE corresponds to the radius taken between the axis of rotation A and the outermost point of the leading edge of a blade 20.
  • These two radii RI, RE are those used in the calculation of the hub ratio RI/RE that the assembly according to the invention proposes to reduce (in particular by reducing the internal radius RI). In other words, the reduction in the hub ratio, by acting in particular on the internal radius RI, amounts to bringing the aerodynamic air inlet vein closer to the fan disc.
  • the figures 3A and 3B show views in longitudinal section of the platform 30.
  • the platform 30, object of the present invention comprises a vein wall 34, a bottom wall 36, and radial and axial retention surfaces 38 and 39 arranged at the two axial ends of the platform 30.
  • the assembly formed by the vein wall 34 and the wall 36 forms a box 32, constituting the platform 30.
  • the bottom wall consists of a main surface 36a and an inclined surface 36b.
  • the inclined surface 36b continuously connects the main surface 36a and the retention surface 38, such that the retention surface 38, located at the upstream axial end of the platform, is offset radially with respect to the main surface 36a.
  • the inclined surface 36b is a straight wall portion.
  • the inclined surface 36b is a curvilinear wall portion.
  • FIG 4 shows a perspective view of a fan disk having an outer surface 40a and an upstream face 40b.
  • the outer surface 40a has a succession of grooves 42 in which a foot 20a of the fan blade 20 can be housed, and of teeth 44 interposed between the grooves 42, which can support the platforms 30 of the fan.
  • Each tooth 44 may have a major tooth surface 44a, and has a beveled surface 44b.
  • the beveled surface 44b is produced, for example by machining the upstream axial end of the tooth 44, so that the shape of the beveled surface 44b is identical to the shape of the inclined surface 36b of the platform 30.
  • the disc 40 comprises, on its upstream face 40b, a plurality of axial projections 46, which may have a cubic shape and be arranged circumferentially, at regular intervals, around the axis A.
  • the number of axial projections 46 may be equal to the number of teeth 44, each projection 46 being aligned radially with the corresponding tooth 44.
  • each axial projection 46 is offset radially towards the inside of the disc, that is to say towards the axis A, with respect to the corresponding tooth 44. For example, a distance between the A axis and a face external 46a of a projection 46 perhaps smaller than the distance between the axis A and a groove 42.
  • Each axial projection 46 may include a fixing hole 460b on its upstream face 46b, allowing the insertion of a fixing means 49, for example a screw or a bolt.
  • Each axial projection 46 may also include an insertion orifice 460a on its external face 46a, allowing the insertion of a fixing element 47, for example an insert, comprising a threaded hole.
  • an upstream retention flange 50 for example a ferrule
  • the fixing of an upstream retention flange 50 can thus be carried out at the level of an axial projection 46, by inserting for example the fixing means 49 through a flange orifice 52 and the orifice fixing element 460b of the projection, the fixing element 49 then being fixed, for example screwed, to the fixing element 47 inserted through the insertion hole 460a of the projection.
  • the retention flange 50 being fixed to the disc 40, an upper surface 54 of the flange 50 then makes it possible to ensure the radial retention of the platform 30.

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

Description

DOMAINE DE L'INVENTIONFIELD OF THE INVENTION

La présente invention concerne le domaine général des turbomachines aéronautiques, et plus précisément le domaine des plateformes d'aubes et de disque de la soufflante d'une turbomachine aéronautique, un ensemble comprenant les plateformes et le disque, et une soufflante comprenant cet ensemble.The present invention relates to the general field of aeronautical turbomachines, and more specifically to the field of blade and disk platforms of the fan of an aeronautical turbomachine, an assembly comprising the platforms and the disk, and a fan comprising this assembly.

ETAT DE LA TECHNIQUE ANTERIEURESTATE OF THE PRIOR ART

Dans une turbomachine, les plateformes d'aubes de la soufflante doivent assurer plusieurs fonctions. D'un point de vue aérodynamique, ces plateformes ont pour fonction première de définir la veine d'écoulement de l'air. En outre, elles doivent aussi être capables de résister à des efforts importants en se déformant le moins possible et en restant solidaires du disque qui les porte.In a turbomachine, the fan blade platforms must fulfill several functions. From an aerodynamic point of view, these platforms have the primary function of defining the air flow path. In addition, they must also be capable of withstanding high forces while deforming as little as possible and remaining integral with the disk which carries them.

Afin de satisfaire ces différentes exigences, certaines configurations ont été proposées dans lesquelles les plateformes possèdent une première partie permettant de définir la veine d'écoulement de l'air et d'assurer la rétention de la plateforme lorsque le moteur est en rotation, et une deuxième partie permettant de limiter les déformations de la première partie sous les effets des efforts centrifuges et de maintenir la plateforme en position lorsque le moteur est à l'arrêt.In order to satisfy these different requirements, certain configurations have been proposed in which the platforms have a first part making it possible to define the air flow path and to ensure the retention of the platform when the motor is rotating, and a second part making it possible to limit the deformations of the first part under the effects of centrifugal forces and to maintain the platform in position when the engine is stopped.

Dans les solutions existantes, la plateforme peut prendre la forme d'un caisson avec une paroi de veine bidimensionnelle retenue à l'aval par un tambour et à l'amont par une virole, la rétention amont par la virole étant réalisée au-dessus de la dent du disque de soufflante (une bride de la virole venant bloquer axialement et radialement la plateforme à l'amont). Le document US 2016/0069355 A1 divulgue un exemple de turbomachine comportant des plateformes d'aubes et un disque de soufflante.In the existing solutions, the platform can take the form of a box with a two-dimensional vein wall retained downstream by a drum and upstream by a shroud, the upstream retention by the shroud being carried out above the fan disc tooth (a flange of the shroud blocking the platform axially and radially upstream). The document US 2016/0069355 A1 discloses an example of a turbomachine comprising blade platforms and a fan disk.

Une telle rétention amont effectuée au-dessus de la dent du disque avec une virole présente l'inconvénient d'imposer un rapport de moyeu élevé, le rapport de moyeu étant le rapport du rayon pris entre l'axe de rotation et le point du bord d'attaque de l'aube affleurant en surface de la plateforme, sur le rayon pris entre l'axe de rotation et le point du bord d'attaque le plus externe. Par ailleurs, cette rétention amont est susceptible d'engendrer des sur-contraintes sur la dent et dans l'alvéole du disque, au niveau de la liaison entre la virole et le disque.Such upstream retention carried out above the tooth of the disc with a ferrule has the disadvantage of imposing a high hub ratio, the hub ratio being the ratio of the radius taken between the axis of rotation and the point of the edge leading edge of the blade flush with the surface of the platform, on the radius taken between the axis of rotation and the outermost point of the leading edge. Moreover, this upstream retention is liable to generate over-stresses on the tooth and in the socket of the disc, at the level of the connection between the ferrule and the disc.

Afin d'optimiser les performances de la soufflante, et plus généralement de la turbomachine, il est souhaitable de disposer d'un assemblage d'une plateforme rapportée d'aube de soufflante sur un disque de soufflante qui présente un rapport de moyeu le plus faible possible, tout en limitant les contraintes au niveau de la dent et de l'alvéole du disque.In order to optimize the performance of the fan, and more generally of the turbomachine, it is desirable to have an assembly of an attached fan blade platform on a fan disc which has the lowest hub ratio possible, while limiting the stresses at the level of the tooth and the alveolus of the disc.

PRESENTATION DE L'INVENTIONPRESENTATION OF THE INVENTION

Un mode de réalisation concerne une plateforme telle que définie dans la revendication 1, apte à être intercalée entre deux aubes adjacentes d'une soufflante, et comportant :

  • Une paroi de veine pour définir une veine d'écoulement d'air de soufflante,
  • Une paroi de fond avec une surface principale pour prendre appui sur un disque de soufflante ; et
  • Des surfaces de rétention axiale et radiale disposées sur deux extrémités axiales de la plateforme, caractérisée en ce que la surface de rétention radiale disposée sur l'extrémité axiale amont de la plateforme est décalée radialement, dans la direction d'appui de la paroi de fond sur le disque, par rapport à une surface principale de la paroi de fond.
One embodiment relates to a platform as defined in claim 1, capable of being inserted between two adjacent blades of a fan, and comprising:
  • A duct wall for defining a fan airflow duct,
  • A bottom wall with a main surface for bearing on a fan disk; And
  • Axial and radial retention surfaces arranged on two axial ends of the platform, characterized in that the radial retention surface arranged on the upstream axial end of the platform is offset radially, in the direction of support of the bottom wall on the disc, with respect to a main surface of the bottom wall.

Par « axiale », on comprend suivant la direction de la plus grande longueur de la plateforme, et par « radiale », on comprend la direction perpendiculaire à la direction axiale et à la surface principale de la paroi de fond.“Axial” means the direction of the greatest length of the platform, and “radial” means the direction perpendicular to the axial direction and to the main surface of the bottom wall.

Par « amont », on comprend amont par rapport au sens d'écoulement de l'air, lorsque la plateforme prend appui sur un disque de soufflante.“Upstream” means upstream with respect to the direction of air flow, when the platform rests on a fan disc.

La plateforme peut prendre la forme d'un caisson formé par l'assemblage de la paroi de veine et de la paroi de fond. La paroi de veine permet de délimiter la veine d'écoulement de l'air entrant dans la soufflante. La paroi de fond permet de maintenir en position la paroi de veine, et également de limiter ses déformations sous l'effet des forces centrifuges. La paroi de fond comporte également une surface principale pouvant prendre appui sur un disque de soufflante.The platform can take the form of a box formed by assembling the vein wall and the bottom wall. The duct wall makes it possible to delimit the flow duct of the air entering the fan. The bottom wall makes it possible to hold the vein wall in position, and also to limit its deformations under the effect of centrifugal forces. The bottom wall also comprises a main surface which can be supported on a fan disk.

Les surfaces de rétention axiale et radiale, disposées sur deux extrémités axiales de la plateforme, permettent de retenir et de maintenir en position la plateforme par rapport au disque sur lequel elle prend appui, lorsque le disque est en mouvement.The axial and radial retention surfaces, arranged on two axial ends of the platform, make it possible to retain and maintain the platform in position relative to the disc on which it rests, when the disc is in motion.

La surface de rétention radiale disposée sur l'extrémité axiale amont de la plateforme est décalée radialement par rapport à une surface principale de la paroi de fond. Par « décalée radialement », on comprend décalée dans la direction d'appui de la paroi de fond sur le disque. La surface de rétention radiale et la surface principale de la paroi de fond peuvent être sensiblement parallèles l'une par rapport à l'autre. Ce décalage de la surface de rétention radiale permet de modifier la forme de l'extrémité axiale amont de la paroi de veine, et donc de la plateforme, par rapport aux plateformes connues. Par exemple, la plateforme peut prendre la forme d'un caisson plongeant, c'est-à-dire dont l'extrémité axiale amont est décalée radialement par rapport à la surface principale de la paroi de fond. Cette modification de la forme de la plateforme permet ainsi de modifier la veine d'écoulement d'air lorsque la plateforme est disposée dans une soufflante, est donc de diminuer le rapport de moyeu afin d'améliorer les performances de la soufflante, et donc de la turbomachine dans laquelle est montée la soufflante.The radial retention surface arranged on the upstream axial end of the platform is offset radially with respect to a main surface of the bottom wall. “Radially offset” means offset in the direction in which the bottom wall bears on the disc. The radial retention surface and the main surface of the bottom wall can be substantially parallel with respect to each other. This offset of the radial retention surface makes it possible to modify the shape of the upstream axial end of the stream wall, and therefore of the platform, with respect to known platforms. For example, the platform can take the form of a plunging box, that is to say the upstream axial end of which is offset radially with respect to the main surface of the bottom wall. This modification of the shape of the platform thus makes it possible to modify the air flow path when the platform is placed in a fan, is therefore to reduce the hub ratio in order to improve the performance of the fan, and therefore to the turbomachine in which the fan is mounted.

La paroi de fond comporte une surface inclinée par rapport à la surface principale de la paroi de fond, reliant de manière continue la surface principale de la paroi de fond et la surface de rétention radiale disposée sur l'extrémité axiale amont de la plateforme.The bottom wall has a surface inclined with respect to the main surface of the bottom wall, continuously connecting the main surface of the bottom wall and the radial retention surface disposed on the upstream axial end of the platform.

La surface de rétention radiale disposée sur l'extrémité axiale amont de la plateforme étant décalée radialement par rapport à la surface principale de la paroi de fond, la surface inclinée correspond à la zone de la paroi de fond permettant de compenser le décalage entre la surface de rétention radiale et la surface principale de la paroi de fond. On comprend par conséquent que la surface inclinée prend appui sur le disque. La surface de rétention radiale disposée sur l'extrémité axiale amont de la plateforme, la surface inclinée et la surface principale de la paroi de fond, peuvent être d'un seul tenant constituant la paroi de fond.The radial retention surface arranged on the upstream axial end of the platform being offset radially with respect to the main surface of the bottom wall, the inclined surface corresponds to the zone of the bottom wall making it possible to compensate for the offset between the surface radial retention and the main surface of the bottom wall. It is therefore understood that the inclined surface rests on the disc. The radial retention surface disposed on the upstream axial end of the platform, the inclined surface and the main surface of the bottom wall, can be in one piece constituting the bottom wall.

La présence de cette surface inclinée permet de modifier la forme de la plateforme et de l'optimiser afin de diminuer le rapport de moyeu, en améliorant ainsi les performances de la soufflante et de la turbomachine.The presence of this inclined surface makes it possible to modify the shape of the platform and to optimize it in order to reduce the hub ratio, thereby improving the performance of the fan and of the turbomachine.

Dans certains modes de réalisation, la surface inclinée est une portion de paroi rectiligne.In some embodiments, the inclined surface is a straight wall portion.

Par conséquent, la portion de paroi rectiligne relie de manière linéaire la surface de rétention radiale avec la surface principale de la paroi de fond, modifiant ainsi la forme de l'extrémité axiale amont de la plateforme afin de diminuer le rapport de moyeu. Cette portion de paroi rectiligne présente l'avantage d'avoir une forme simple et facile à réaliser, par usinage par exemple.Consequently, the rectilinear wall portion linearly connects the radial retention surface with the main surface of the bottom wall, thus modifying the shape of the upstream axial end of the platform in order to reduce the hub ratio. This rectilinear wall portion has the advantage of having a simple shape that is easy to produce, for example by machining.

Dans certains modes de réalisation, la surface inclinée est une portion de paroi curviligne.In some embodiments, the inclined surface is a curvilinear wall portion.

Par conséquent, la portion de paroi curviligne relie de manière progressive la surface de rétention radiale avec la surface principale de la paroi de fond, modifiant ainsi la forme de l'extrémité axiale amont de la plateforme afin de diminuer le rapport de moyeu. Cette portion de paroi curviligne présente l'avantage d'adoucir le changement de pente depuis la surface principale de la paroi de fond, en évitant la présence d'une cassure au niveau de la jonction entre la surface inclinée et la surface principale, contrairement à la portion de paroi rectiligne, et ainsi de réduire les contraintes au niveau de cette jonction.Consequently, the curvilinear wall portion progressively connects the radial retention surface with the main surface of the bottom wall, thus modifying the shape of the upstream axial end of the platform in order to reduce the hub ratio. This portion of curvilinear wall has the advantage of softening the change in slope from the main surface of the bottom wall, avoiding the presence of a break at the junction between the inclined surface and the main surface, unlike the straight wall portion, and thus reduce the stresses at this junction.

Dans certains modes de réalisation, la surface inclinée et la paroi de veine sont sensiblement parallèles.In some embodiments, the inclined surface and the vein wall are substantially parallel.

Par conséquent, l'extrémité axiale amont de la plateforme présente une forme plongeante, la surface inclinée et la partie de veine étant inclinées radialement de la même façon dans la direction d'appui de la plateforme sur le disque. Cette forme de l'extrémité axiale amont de la plateforme permet de diminuer le rapport de moyeu.Consequently, the upstream axial end of the platform has a plunging shape, the inclined surface and the section of the stream being inclined radially in the same way in the direction in which the platform bears on the disc. This shape of the upstream axial end of the platform makes it possible to reduce the hub ratio.

Le présent exposé concerne également un ensemble tel que défini dans la revendication 5, comprenant un disque et au moins une plateforme selon l'un quelconque des modes de réalisation précédents, et comprenant en outre au moins une bride de rétention amont pour assurer la rétention axiale et radiale de l'extrémité axiale amont de la plateforme, dans lequel la bride de rétention amont est fixée sur une saillie de la face amont du disque. Le disque est apte à supporter des plateformes et des aubes d'une soufflante, et comporte :

  • une surface externe présentant une succession de rainures pour recevoir les aubes de soufflante et de dents intercalées entre les rainures pour supporter les plateformes de soufflante,
  • une face amont du disque, et
  • une pluralité de saillies axiales disposées radialement autour de l'axe du disque sur la face amont du disque, et aptes à être fixées à une bride de rétention de plateforme de soufflante, les saillies étant décalées radialement vers l'intérieur du disque par rapport aux dents du disque.
This presentation also relates to an assembly as defined in claim 5, comprising a disc and at least one platform according to any one of the preceding embodiments, and further comprising at least one upstream retention flange to ensure axial retention and radial from the upstream axial end of the platform, in which the upstream retention flange is fixed on a projection of the upstream face of the disc. The disc is capable of supporting platforms and fan blades, and comprises:
  • an outer surface having a succession of grooves to receive the fan blades and teeth intercalated between the grooves to support the fan platforms,
  • an upstream face of the disc, and
  • a plurality of axial projections arranged radially around the axis of the disk on the upstream face of the disk, and adapted to be fixed to a retention flange of a fan platform, the projections being offset radially towards the inside of the disk with respect to the disc teeth.

Par « face amont », on comprend amont par rapport au sens d'écoulement de l'air, lorsque le disque est disposé dans une soufflante.The term “upstream face” is understood to mean upstream with respect to the direction in which the air flows, when the disc is placed in a fan.

Par « saillies axiales », on comprend axiales suivant le sens d'écoulement de l'air, lorsque le disque est disposé dans une soufflante.“Axial projections” are understood to mean axial in the direction of air flow, when the disk is placed in a fan.

Par « décalées radialement », on comprend décalées vers l'intérieur du disque, c'est-à-dire vers l'axe de rotation du disque.“Radially offset” means offset towards the inside of the disc, that is to say towards the axis of rotation of the disc.

Le disque peut comporter autant de saillies axiales que de dents.The disk can comprise as many axial projections as there are teeth.

Les saillies axiales peuvent comporter chacune un orifice permettant aux saillies axiales d'être fixées à une bride de rétention de plateforme de soufflante, à l'aide d'une vis ou d'un boulon, par exemple.The axial projections may each include a hole allowing the axial projections to be fixed to a fan platform retention flange, using a screw or a bolt, for example.

Les saillies axiales étant décalées radialement vers l'intérieur du disque par rapport aux dents du disque, lorsque les saillies sont fixées sur une bride de rétention de plateforme, la zone de fixation se trouvant sur les saillies est ainsi décalée radialement par rapport aux dents du disque. Cela présente l'avantage de limiter les contraintes au niveau de la dent du disque, lorsqu'un élément externe, par exemple une bride de rétention de plateforme, est fixé sur le disque.Since the axial projections are offset radially towards the inside of the disk relative to the teeth of the disk, when the projections are fixed to a platform retention flange, the attachment zone located on the projections is thus offset radially relative to the teeth of the disk. This has the advantage of limiting the stresses at the level of the tooth of the disc, when an external element, for example a platform retention flange, is fixed to the disc.

Par ailleurs, cette zone de fixation étant décalée radialement par rapport aux dents du disque, cela présente l'avantage de libérer de l'espace au niveau de l'extrémité axiale amont de la dent du disque, permettant par exemple d'usiner la dent du disque.Furthermore, this fixing zone being offset radially with respect to the teeth of the disc, this has the advantage of freeing up space at the level of the upstream axial end of the tooth of the disc, making it possible, for example, to machine the tooth of the disc.

Dans certains modes de réalisation, les saillies axiales sont des plots usinés sur la face amont du disque.In certain embodiments, the axial projections are studs machined on the upstream face of the disc.

Elles peuvent avoir une forme cubique, et comporter chacune un orifice de fixation usiné axialement sur une face amont des saillies. Les orifices de fixation peuvent permettre de fixer un élément extérieur au disque, par exemple une bride de rétention ou une virole, à l'aide d'une vis ou d'un boulon, par exemple. Les saillies axiales peuvent également comporter un orifice d'insertion usiné radialement sur une face externe des saillies. Les orifices d'insertion peuvent permettre d'insérer des éléments de fixation, par lesquelles un élément extérieur peut être fixé au disque.They may have a cubic shape, and each comprise a fixing orifice machined axially on an upstream face of the projections. The fixing holes can make it possible to fix an element external to the disc, for example a retaining flange or a ferrule, using a screw or a bolt, for example. Axial projections can also have an insertion hole machined radially on an outer face of the projections. The insertion holes may permit the insertion of fasteners, through which an outer member may be attached to the disc.

Une extrémité axiale amont des dents du disque présente une surface biseautée.An upstream axial end of the disk teeth has a beveled surface.

La surface biseautée peut se présenter sous la forme d'une surface inclinée, par rapport à une surface principale de la dent du disque, vers l'intérieur du disque. La surface biseautée peut être réalisée par usinage de l'extrémité axiale amont de la dent du disque, par exemple. Cet usinage est possible grâce à l'espace libéré par le décalage radial des saillies axiales sur la face amont du disque. La présence de cette surface biseautée présente l'avantage de pouvoir adapter la forme de la dent du disque à la forme d'une plateforme venant prendre appui sur la dent, et ainsi de diminuer le rapport de moyeu pour améliorer les performances de la soufflante.The beveled surface may be in the form of an inclined surface, with respect to a main surface of the tooth of the disc, towards the inside of the disc. The beveled surface can be produced by machining the upstream axial end of the tooth of the disc, for example. This machining is possible thanks to the space freed up by the radial offset of the axial projections on the upstream face of the disc. The presence of this beveled surface has the advantage of being able to adapt the shape of the tooth of the disc to the shape of a platform bearing on the tooth, and thus of reducing the hub ratio to improve the performance of the fan.

Lorsque la bride de rétention est fixée sur le disque, l'interface entre la bride et le disque, correspondant à la zone de fixation de la bride sur une saillie axiale du disque, est décalée radialement vers l'intérieur du disque, par rapport à la dent du disque, par rapport aux systèmes connus dans lesquels cette interface se situe au niveau de la dent du disque. Ce décalage permet de limiter les contraintes au niveau de l'extrémité axiale amont des dents et des rainures du disque. De plus, le décalage de cette interface permet de libérer de l'espace au niveau de l'extrémité axiale amont de la dent du disque, offrant plus de possibilité d'usinage de la dent et donc de modification de la forme de la plateforme et ainsi, de diminution du rapport de moyeu.When the retention flange is fixed on the disc, the interface between the flange and the disc, corresponding to the zone of attachment of the flange to an axial projection of the disc, is offset radially towards the inside of the disc, with respect to the tooth of the disc, compared to known systems in which this interface is located at the level of the tooth of the disc. This offset makes it possible to limit the stresses at the level of the upstream axial end of the teeth and of the grooves of the disc. In addition, the offset of this interface makes it possible to free up space at the level of the upstream axial end of the tooth of the disc, offering more possibility of machining the tooth and therefore of modifying the shape of the platform and thus, reduction of the hub ratio.

Lorsque la plateforme prend appui sur une dent du disque, la surface inclinée de la paroi de fond est en contact avec la surface biseautée de la dent du disque. La surface inclinée et la surface biseautée peuvent être parallèles.When the platform is supported on a tooth of the disc, the inclined surface of the bottom wall is in contact with the beveled surface of the tooth of the disc. The inclined surface and the beveled surface can be parallel.

L'interface entre la bride de rétention et le disque étant décalée vers l'intérieur du disque, la dent du disque peut être plus librement usinée. Ainsi, l'extrémité axiale amont de la dent peut présenter un biseautage permettant de s'adapter à la forme de la plateforme, la surface biseautée étant parallèle à la surface inclinée de la plateforme. Cela présente l'avantage de créer un ensemble compact, dans lequel la plateforme est retenue contre la dent du disque par la bride de rétention fixée au niveau d'une saillie du disque.Since the interface between the retention flange and the disc is offset towards the inside of the disc, the disc tooth can be machined more freely. Thus, the upstream axial end of the tooth may have a bevel to adapt to the shape of the platform, the beveled surface being parallel to the inclined surface of the platform. This has the advantage of creating a compact assembly, in which the platform is retained against the tooth of the disc by the retention flange fixed at a projection of the disc.

Dans certains modes de réalisation, la bride de rétention amont est une virole.In some embodiments, the upstream retention flange is a ferrule.

Le présent exposé concerne également une soufflante de turbomachine comprenant un ensemble selon l'un quelconque des modes de réalisation décrits dans le présent exposé, et une pluralité d'aubes montées dans les rainures du disque.This presentation also relates to a turbomachine fan comprising an assembly according to any one of the embodiments described in this presentation, and a plurality of vanes mounted in the grooves of the disk.

BREVE DESCRIPTION DES DESSINSBRIEF DESCRIPTION OF THE DRAWINGS

L'invention et ses avantages seront mieux compris à la lecture de la description détaillée faite ci-après de différents modes de réalisation de l'invention donnés à titre d'exemples non limitatifs. Cette description fait référence aux pages de figures annexées, sur lesquelles :

  • la figure 1 est une vue schématique en coupe d'une turbomachine selon l'invention,
  • la figure 2 est une vue schématique selon la direction II de la soufflante de la figure 1,
  • les figures 3A et 3B sont des vues en coupe longitudinale d'une plateforme selon l'invention,
  • La figure 4 est une vue en perspective d'un disque selon l'invention,
  • La figure 5 est une vue en coupe longitudinale d'un ensemble comprenant une bride de rétention, une plateforme et un disque selon l'invention.
The invention and its advantages will be better understood on reading the detailed description given below of various embodiments of the invention given by way of non-limiting examples. This description refers to the pages of appended figures, on which:
  • there figure 1 is a schematic sectional view of a turbomachine according to the invention,
  • there figure 2 is a schematic view along direction II of the fan of the figure 1 ,
  • THE figures 3A and 3B are views in longitudinal section of a platform according to the invention,
  • There figure 4 is a perspective view of a disc according to the invention,
  • There figure 5 is a view in longitudinal section of an assembly comprising a retention flange, a platform and a disc according to the invention.

DESCRIPTION DETAILLEE D'EXEMPLES DE REALISATIONDETAILED DESCRIPTION OF EXAMPLES OF REALIZATION

Dans le présent exposé, le terme « longitudinal » et ses dérivés sont définis par rapport à la direction principale de la plateforme considérée ; les termes « radial », « intérieur », « extérieur » et leurs dérivés sont quant à eux définis par rapport à l'axe principal de la turbomachine ; enfin, les termes « amont » et « aval » sont définis par rapport au sens d'écoulement du fluide traversant la turbomachine. Aussi, sauf indication contraire, les mêmes signes de référence sur différentes figures désignent les mêmes caractéristiques.In this presentation, the term “longitudinal” and its derivatives are defined with respect to the main direction of the platform considered; the terms “radial”, “inner”, “outer” and their derivatives are defined with respect to the main axis of the turbomachine; finally, the terms “upstream” and “downstream” are defined with respect to the direction of flow of the fluid passing through the turbomachine. Also, unless otherwise indicated, the same reference signs in different figures designate the same characteristics.

La figure 1 montre une vue schématique en coupe longitudinale d'un turboréacteur à double flux 1 centré sur l'axe A selon l'invention. Il comporte, d'amont en aval : une soufflante 2, un compresseur basse pression 3, un compresseur haute pression 4, une chambre de combustion 5, une turbine haute pression 6, et une turbine basse pression 7.There figure 1 shows a schematic view in longitudinal section of a turbofan engine 1 centered on the axis A according to the invention. It comprises, from upstream to downstream: a fan 2, a low compressor pressure 3, a high pressure compressor 4, a combustion chamber 5, a high pressure turbine 6, and a low pressure turbine 7.

La figure 2 montre une vue schématique de la soufflante 2 de la figure 1 selon la direction II. La soufflante 2, comprend un disque de soufflante 40 dans lequel une pluralité de rainures 42 sont pratiquées au niveau de sa périphérie extérieure. Ces rainures 42 sont rectilignes et s'étendent axialement d'amont en aval tout le long du disque 40. Elles sont en outre régulièrement réparties tout autour de l'axe A du disque 40. De cette manière, chaque rainure 42 définit avec sa voisine une dent 44 qui s'étend également axialement d'amont en aval tout le long du disque 40. De façon équivalente, une rainure 42 est délimitée entre deux dents 44 voisines.There figure 2 shows a schematic view of the fan 2 of the figure 1 according to direction II. The fan 2 comprises a fan disc 40 in which a plurality of grooves 42 are made at its outer periphery. These grooves 42 are rectilinear and extend axially from upstream to downstream all along the disc 40. They are also regularly distributed all around the axis A of the disc 40. In this way, each groove 42 defines with its neighbor a tooth 44 which also extends axially from upstream to downstream all along the disc 40. Equivalently, a groove 42 is delimited between two neighboring teeth 44.

La soufflante 2 comprend en outre une pluralité d'aubes 20 de profil curviligne (seules quatre aubes 20 ont été représentées sur la figure 2). Chaque aube 20 possède un pied 20a qui est monté dans une rainure 42 respective du disque de soufflante 40. A cette fin, le pied 20a d'une aube 20 peut posséder une forme en sapin ou en queue d'aronde adaptée à la géométrie des rainures 42.The fan 2 further comprises a plurality of blades 20 of curvilinear profile (only four blades 20 have been shown on the figure 2 ). Each blade 20 has a root 20a which is mounted in a respective groove 42 of the fan disk 40. To this end, the root 20a of a blade 20 can have a fir tree or dovetail shape adapted to the geometry of the grooves 42.

Enfin, la soufflante 2 comprend une pluralité de plateformes 30 rapportées, chaque plateforme 30 étant montée dans l'intervalle entre deux aubes de soufflante 20 voisines, au voisinage des pieds 20a de celles-ci, afin de délimiter, du côté intérieur, une veine annulaire d'entrée d'air dans la soufflante 2, la veine étant délimitée du côté extérieur par un carter de soufflante.Finally, the fan 2 comprises a plurality of added platforms 30, each platform 30 being mounted in the interval between two neighboring fan blades 20, in the vicinity of the feet 20a thereof, in order to delimit, on the interior side, a vein annular air inlet into the fan 2, the vein being delimited on the outside by a fan casing.

Les figures 1 et 2 montrent également un rayon interne RI et un rayon externe RE. Le rayon interne RI correspond au rayon pris entre l'axe de rotation A et le point du bord d'attaque d'une aube 20 affleurant en surface d'une plateforme 30. Le rayon externe RE correspond quant à lui au rayon pris entre l'axe de rotation A et le point du bord d'attaque d'une aube 20 le plus externe. Ces deux rayons RI, RE sont ceux utilisés dans le calcul du rapport de moyeu RI/RE que l'assemblage selon l'invention se propose de diminuer (en réduisant notamment le rayon interne RI). En d'autres termes, la diminution du rapport de moyeu, en agissant notamment sur le rayon interne RI, revient à rapprocher la veine aérodynamique d'entrée d'air au plus près du disque de soufflante.THE figures 1 and 2 also show an internal radius RI and an external radius RE. The internal radius RI corresponds to the radius taken between the axis of rotation A and the point of the leading edge of a blade 20 flush with the surface of a platform 30. The external radius RE corresponds to the radius taken between the axis of rotation A and the outermost point of the leading edge of a blade 20. These two radii RI, RE are those used in the calculation of the hub ratio RI/RE that the assembly according to the invention proposes to reduce (in particular by reducing the internal radius RI). In other words, the reduction in the hub ratio, by acting in particular on the internal radius RI, amounts to bringing the aerodynamic air inlet vein closer to the fan disc.

Les figures 3A et 3B montrent des vues en coupe longitudinale de la plateforme 30. La plateforme 30, objet de la présente invention, comprend une paroi de veine 34, une paroi de fond 36, et des surfaces de rétention radiale et axiale 38 et 39 disposées aux deux extrémités axiales de la plateforme 30. L'ensemble formé par la paroi de veine 34 et la paroi de 36, forme un caisson 32, constituant la plateforme 30. La paroi de fond est constituée d'une surface principale 36a et une surface inclinée 36b. La surface inclinée 36b relie de manière continue la surface principale 36a et la surface de rétention 38, de sorte que la surface de rétention 38, située à l'extrémité axiale amont de la plateforme, est décalée radialement par rapport à la surface principale 36a. Dans l'exemple de la figure 3A, la surface inclinée 36b est une portion de paroi rectiligne. Dans l'exemple de la figure 38, la surface inclinée 36b est une portion de paroi curviligne.THE figures 3A and 3B show views in longitudinal section of the platform 30. The platform 30, object of the present invention, comprises a vein wall 34, a bottom wall 36, and radial and axial retention surfaces 38 and 39 arranged at the two axial ends of the platform 30. The assembly formed by the vein wall 34 and the wall 36, forms a box 32, constituting the platform 30. The bottom wall consists of a main surface 36a and an inclined surface 36b. The inclined surface 36b continuously connects the main surface 36a and the retention surface 38, such that the retention surface 38, located at the upstream axial end of the platform, is offset radially with respect to the main surface 36a. In the example of the Figure 3A , the inclined surface 36b is a straight wall portion. In the example of Figure 38, the inclined surface 36b is a curvilinear wall portion.

La figure 4 montre une vue en perspective d'un disque de soufflante comportant une surface externe 40a et une face amont 40b. La surface externe 40a présente une succession de rainures 42 dans lesquelles peuvent se loger un pied 20a d'aube 20 de soufflante, et de dents 44 intercalées entre les rainures 42, pouvant supporter les plateformes 30 de soufflante. Chaque dent 44 peut comporter une surface principale de dent 44a, et présente une surface biseautée 44b. La surface biseautée 44b est réalisée, par exemple par usinage de l'extrémité axiale amont de la dent 44, de telle sorte que la forme de la surface biseautée 44b soit identique à la forme de la surface inclinée 36b de la plateforme 30. Par conséquent, lorsqu'une plateforme 30 prend appui sur une dent 44, la surface principale 36a de la plateforme est en contact avec la surface principale de la dent 44a, et la surface inclinée 36b de la plateforme est en contact avec la surface biseautée 44b de la dent, comme illustré sur la figure 5.There figure 4 shows a perspective view of a fan disk having an outer surface 40a and an upstream face 40b. The outer surface 40a has a succession of grooves 42 in which a foot 20a of the fan blade 20 can be housed, and of teeth 44 interposed between the grooves 42, which can support the platforms 30 of the fan. Each tooth 44 may have a major tooth surface 44a, and has a beveled surface 44b. The beveled surface 44b is produced, for example by machining the upstream axial end of the tooth 44, so that the shape of the beveled surface 44b is identical to the shape of the inclined surface 36b of the platform 30. Consequently , when a platform 30 bears on a tooth 44, the main surface 36a of the platform is in contact with the main surface of the tooth 44a, and the inclined surface 36b of the platform is in contact with the beveled surface 44b of the tooth, as shown in the figure 5 .

Par ailleurs, le disque 40 comporte, sur sa face amont 40b, une pluralité de saillies axiales 46, pouvant avoir une forme cubique et être disposées de manière circonférentielle, à intervalles réguliers, autour de l'axe A. Le nombre de saillies axiales 46 peut être égal au nombre de dents 44, chaque saillie 46 étant alignée radialement avec la dent 44 correspondante. De plus, chaque saillie axiale 46 est décalée radialement vers l'intérieur du disque, c'est-à-dire vers l'axe A, par rapport à la dent 44 correspondante. Par exemple, une distance entre l'axe A et une face externe 46a d'une saillie 46 peut-être plus petite que la distance entre l'axe A et une rainure 42.Furthermore, the disc 40 comprises, on its upstream face 40b, a plurality of axial projections 46, which may have a cubic shape and be arranged circumferentially, at regular intervals, around the axis A. The number of axial projections 46 may be equal to the number of teeth 44, each projection 46 being aligned radially with the corresponding tooth 44. In addition, each axial projection 46 is offset radially towards the inside of the disc, that is to say towards the axis A, with respect to the corresponding tooth 44. For example, a distance between the A axis and a face external 46a of a projection 46 perhaps smaller than the distance between the axis A and a groove 42.

Chaque saillie axiale 46 peut comporter un orifice de fixation 460b sur sa face amont 46b, permettant d'insérer un moyen de fixation 49, par exemple une vis ou un boulon. Chaque saillie axiale 46 peut également comporter un orifice d'insertion 460a sur sa face externe 46a, permettant d'insérer un élément de fixation 47, par exemple un insert, comportant un trou taraudé. La fixation d'une bride de rétention amont 50, par exemple une virole, peut ainsi s'effectuer au niveau d'une saillie axiale 46, en insérant par exemple le moyen de fixation 49 à travers un orifice de bride 52 et l'orifice de fixation 460b de la saillie, l'élément de fixation 49 étant alors fixé, par exemple vissé, à l'élément de fixation 47 inséré par l'orifice d'insertion 460a de la saillie. La bride de rétention 50 étant fixée au disque 40, une surface supérieure 54 de la bride 50 permet alors d'assurer la rétention radiale de la plateforme 30.Each axial projection 46 may include a fixing hole 460b on its upstream face 46b, allowing the insertion of a fixing means 49, for example a screw or a bolt. Each axial projection 46 may also include an insertion orifice 460a on its external face 46a, allowing the insertion of a fixing element 47, for example an insert, comprising a threaded hole. The fixing of an upstream retention flange 50, for example a ferrule, can thus be carried out at the level of an axial projection 46, by inserting for example the fixing means 49 through a flange orifice 52 and the orifice fixing element 460b of the projection, the fixing element 49 then being fixed, for example screwed, to the fixing element 47 inserted through the insertion hole 460a of the projection. The retention flange 50 being fixed to the disc 40, an upper surface 54 of the flange 50 then makes it possible to ensure the radial retention of the platform 30.

La zone de fixation entre le disque 40 et la bride de rétention 50 étant située au niveau des saillies axiales 46, cela permet de limiter les contraintes exercées lors du fonctionnement de la soufflante au niveau de surfaces sensibles telles que l'extrémité axiale amont des dents 44 et des rainures 42 du disque. Par ailleurs, cette interface entre le disque 40 et la bride de rétention 50 étant décalée radialement par rapport aux dents du disque, en comparaison des structures connues, cela permet de libérer de l'espace au niveau de l'extrémité axiale amont des dents du disque. Il est par conséquent possible de modifier plus librement l'extrémité axiale amont des dents 44, et donc l'extrémité axiale amont de la plateforme 30, et ainsi, de diminuer le rapport de moyeu afin d'optimiser les performances de la soufflante, et donc de la turbomachine dans laquelle est montée la soufflante. La figure 5 illustre par exemple une plateforme 30 dont le caisson 32 possède une forme plongeante vers l'intérieur du disque 40, grâce à la surface biseautée 44b du disque 40 et à la surface inclinée 36b de la plateforme 30.The attachment zone between the disc 40 and the retention flange 50 being located at the level of the axial projections 46, this makes it possible to limit the stresses exerted during operation of the fan at the level of sensitive surfaces such as the upstream axial end of the teeth 44 and grooves 42 of the disc. Furthermore, this interface between the disc 40 and the retention flange 50 being offset radially with respect to the teeth of the disc, in comparison with known structures, this makes it possible to free up space at the level of the upstream axial end of the teeth of the disk. It is therefore possible to more freely modify the upstream axial end of the teeth 44, and therefore the upstream axial end of the platform 30, and thus, to reduce the hub ratio in order to optimize the performance of the fan, and therefore of the turbomachine in which the fan is mounted. There figure 5 illustrates for example a platform 30 whose box 32 has a plunging shape towards the inside of the disc 40, thanks to the beveled surface 44b of the disc 40 and the inclined surface 36b of the platform 30.

Bien que la présente invention ait été décrite en se référant à des exemples de réalisation spécifiques, il est évident que des modifications et des changements peuvent être effectués sur ces exemples sans sortir de la portée générale de l'invention telle que définie par les revendications. En particulier, des caractéristiques individuelles des différents modes de réalisation illustrés/mentionnés peuvent être combinées dans des modes de réalisation additionnels. Par conséquent, la description et les dessins doivent être considérés dans un sens illustratif plutôt que restrictif.Although the present invention has been described with reference to specific embodiments, it is obvious that modifications and changes can be made to these examples without departing from the general scope of the invention as defined by the claims. In particular, individual characteristics of different illustrated/mentioned embodiments can be combined in additional embodiments. Accordingly, the description and the drawings should be considered in an illustrative rather than restrictive sense.

Claims (9)

  1. A platform (30) suitable for being interposed between two adjacent blades (20) of a fan (2), the platform comprising:
    - a passage wall (34) for defining a fan air flow passage;
    - a bottom wall (36) having a main surface (36a) for bearing against a fan disk (40);
    the platform (30) having axial and radial retention surfaces arranged at the two axial ends of the platform (30), a radial retention surface (38) being arranged at the upstream axial end of the platform (30) and radially offset from the main surface (36a) of the bottom wall (36) in the direction in which the bottom wall (36) bears against the disk (40), the bottom wall (36) having an inclined surface (36b) inclined relative to the main surface (36a) of the bottom wall (36) and connecting the main surface (36a) of the bottom wall (36) in continuous manner with the radial retention surface (38) arranged at the upstream axial end of the platform (30), characterized in that the inclined surface (36b) is configured to bear against a chamfered surface (44b) of the tooth (44) of the fan disk (40).
  2. A platform (30) according to claim 1, wherein the inclined surface (36b) is a rectilinear wall portion.
  3. A platform (30) according to claim 1, wherein the inclined surface (36b) is a curvilinear wall portion.
  4. A platform (30) according to any one of claims 1 to 3, wherein the inclined surface (36b) and the passage wall (34) are substantially parallel.
  5. An assembly comprising at least one platform (30) according to any one of claims 1 to 4 and a disk (40) suitable for supporting platforms (30) and blades (20) of a fan (2), the disk (40) comprising an outer surface (40a) presenting a succession of slots (42) for receiving fan blades (20) and of teeth (44) interposed between the slots (42) in order to support the fan platforms (30); an upstream face (40b) of the disk; and a plurality of axial projections (46) arranged radially around the axis A of the disk on the upstream face (40b) of the disk (40), and suitable for being fastened to a fan platform retention flange (50), the projections (46) being radially offset towards the inside of the disk (40) relative to the teeth (44) of the disk (40), an upstream axial ends of the teeth (44) of the disk present surfaces (44b) that are chamfered, wherein, when the platform (30) bears against a tooth (44) of the disk (40), the inclined surface (36b) of the bottom wall (36) is in contact with the chamfered surface (44b) of the tooth (44) of the disk, the assembly further comprising at least one upstream retention flange (50) for axially and radially retaining the upstream end of the platform (30), wherein the upstream retention flange (50) is fastened on at least one axial projection (46) of the plurality of axial projections (46) of the upstream face (40b) of the disk (40).
  6. An assembly according to claim 5, wherein the axial projections (46) are studs machined on the upstream face (40b) of the disk.
  7. An assembly according to claim 5 or 6, wherein the inclined surface (36b) and the chamfered surface (44b) are parallel.
  8. An assembly according to any one of claim 5 to 7, wherein the upstream retention flange (50) is a shroud.
  9. A turbine engine fan (2) comprising an assembly according to any one of claims 5 to 8 together with a plurality of blades (20) mounted in the slots (42) of the disk (40).
EP17716956.2A 2016-03-21 2017-03-20 Platform, fan assembly and fan Active EP3433469B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1652401A FR3048997B1 (en) 2016-03-21 2016-03-21 BLADE PLATFORM AND AERONAUTICAL TURBOMACHINE BLOWER DISC
PCT/FR2017/050649 WO2017162975A1 (en) 2016-03-21 2017-03-20 Fan assembly, disk and platform

Publications (2)

Publication Number Publication Date
EP3433469A1 EP3433469A1 (en) 2019-01-30
EP3433469B1 true EP3433469B1 (en) 2023-04-26

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EP17716956.2A Active EP3433469B1 (en) 2016-03-21 2017-03-20 Platform, fan assembly and fan

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US (1) US11021973B2 (en)
EP (1) EP3433469B1 (en)
JP (1) JP7164435B2 (en)
CN (1) CN108884720B (en)
CA (1) CA3018448A1 (en)
FR (1) FR3048997B1 (en)
RU (1) RU2728547C2 (en)
WO (1) WO2017162975A1 (en)

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FR3089548B1 (en) * 2018-12-07 2021-03-19 Safran Aircraft Engines BLOWER INCLUDING AN INTER-BLADE PLATFORM FIXED UPSTREAM BY A VIROLE
FR3120813B1 (en) 2021-03-16 2024-02-09 Safran Aircraft Engines Process for manufacturing a blower disc with additive manufacturing part

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Also Published As

Publication number Publication date
EP3433469A1 (en) 2019-01-30
CN108884720A (en) 2018-11-23
FR3048997B1 (en) 2020-03-27
RU2018136891A3 (en) 2020-06-03
RU2728547C2 (en) 2020-07-30
JP7164435B2 (en) 2022-11-01
BR112018069179A2 (en) 2019-01-29
CA3018448A1 (en) 2017-09-28
RU2018136891A (en) 2020-04-22
FR3048997A1 (en) 2017-09-22
US11021973B2 (en) 2021-06-01
WO2017162975A1 (en) 2017-09-28
JP2019512639A (en) 2019-05-16
US20190055847A1 (en) 2019-02-21
CN108884720B (en) 2021-11-02

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