EP3899207B1 - Turbomachine assembly comprising fan blades with an extended trailing edge - Google Patents

Turbomachine assembly comprising fan blades with an extended trailing edge Download PDF

Info

Publication number
EP3899207B1
EP3899207B1 EP19848803.3A EP19848803A EP3899207B1 EP 3899207 B1 EP3899207 B1 EP 3899207B1 EP 19848803 A EP19848803 A EP 19848803A EP 3899207 B1 EP3899207 B1 EP 3899207B1
Authority
EP
European Patent Office
Prior art keywords
fan
extension
blade
radial
assembly
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
EP19848803.3A
Other languages
German (de)
French (fr)
Other versions
EP3899207A1 (en
Inventor
Paul Antoine FORESTO
Vivien Mickaël COURTIER
Stéphane Roger MAHIAS
William Henri Joseph RIERA
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
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP3899207A1 publication Critical patent/EP3899207A1/en
Application granted granted Critical
Publication of EP3899207B1 publication Critical patent/EP3899207B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • 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
    • 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
    • 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
    • F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade
    • 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
    • F05D2240/55—Seals
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced

Definitions

  • the invention generally relates to the field of dual-flow turbomachines, and more particularly that of the fans of these turbomachines and their interaction with the inlet of the primary stream.
  • a turbomachine generally comprises, from upstream to downstream in the direction of gas flow, a fan, an annular primary flow path and an annular secondary flow path.
  • the mass of air sucked in by the fan is thus divided into a primary flow, which circulates in the primary flow path, and a secondary flow, which is concentric with the primary flow and circulates in the secondary flow path.
  • the primary flow path passes through a primary body comprising one or more compressor stages, for example a low pressure compressor and a high pressure compressor, a combustion chamber, one or more turbine stages, for example a high pressure turbine and a low pressure turbine, and a gas exhaust nozzle.
  • a primary body comprising one or more compressor stages, for example a low pressure compressor and a high pressure compressor, a combustion chamber, one or more turbine stages, for example a high pressure turbine and a low pressure turbine, and a gas exhaust nozzle.
  • the fan comprises a rotor disc carrying a plurality of blades whose roots are engaged and retained in substantially axial grooves formed at the periphery of the disc.
  • the grooves are separated two by two by teeth.
  • These blades are associated at their radially inner end with inter-blade platforms which are arranged in the extension of an inlet cone of the fan and are configured to delimit, on the inner side, the annular air inlet vein in the blower.
  • the turbomachine comprises, immediately downstream of the fan, at the inlet of the primary stream, a part which may correspond, depending on the embodiment of the fan, to a drum of the booster (for low pressure compressor in English ), which corresponds to the inner ring of the booster on which the rotating vanes of the booster are fixed, an inner ring of an IGV (English acronym for Inlet Guide Vane, that is to say the first stage stator of the booster in the primary body of a turbomachine) or even a rotating spacer which is formed of an annular flange extending between the fan and the drum of the booster and which rotates at the same speed as the blower.
  • IGV International acronym for Inlet Guide Vane
  • a functional clearance is provided between the downstream face of the fan disc and an upstream edge of the part. This clearance, however, forms a cavity disturbing the flow by generating recirculations of the gas flow downstream of the root of the fan blades and a leakage rate.
  • the platforms are sized so as to extend beyond the downstream face of the fan disk to at least partially cover this cavity.
  • this solution does not make it possible to eliminate the cavity over the entire circumference of the fan, insofar as it is necessary to leave an opening downstream of the grooves in order to allow the insertion and fixing of the fan blades on the disk. of blower. Consequently, the part of the cavity which opens downstream of the fan blades remains partly open.
  • the internal shroud of the IGV must be sized so as to adopt an aerodynamically robust design.
  • robust we mean that the shell must be capable of withstanding poor quality flows without creating excessive losses or separations.
  • the counterpart of this dimensioning is that the efficiency of the blades of such an IGV is lower than that of conventional IGVs. The presence of these cavities therefore degrades the operation of the booster.
  • the document JP 2011-069286 describes a fan blade comprising a blade, a platform and a leading edge shield.
  • WO 2017/006054 discloses a fan blade insert mounted on a fan disc that has a low hub ratio.
  • One objective of the invention is therefore to provide a turbomachine in which the operation of the booster is not degraded, by limiting or even eliminating gas recirculation and leakage flow rates downstream of the root of the fan blades.
  • the upstream and the downstream are defined with respect to the direction of normal flow of the gas in the turbomachine 1.
  • turbomachinery corresponds to the direction of the axis X of the turbomachine, and a radial direction is a direction perpendicular to this axis and passing through it.
  • an axial plane is a plane containing the axis X of the turbomachine and a radial plane is a plane perpendicular to this axis X and passing through it.
  • the tangential (or circumferential) direction is a direction perpendicular to the X axis and not passing through it.
  • internal (or interior) and external (or exterior), respectively, are used with reference to a radial direction so that the part or face internal (ie radially internal) of an element is closer to the X axis than the external (ie radially external) part or face of the same element.
  • Part 3 can comprise a drum of the booster, an internal shroud of an IGV or else a rotating spacer.
  • the fan 2 comprises a fan disc 10 having an upstream face, a downstream face 14 and a radial face 12. It carries a plurality of fan blades 20 2 associated with inter-blade platforms 16 20. Axial grooves, separated two by two by teeth, are formed in the radial face 12 of the disc 10.
  • the blades 20 are associated at their radially inner end with inter-blade platforms 16.
  • Each platform 16 has an upstream end, configured to extend at the level of the upstream face of the fan disk 10, and a downstream end configured to come opposite the part 3 extending immediately downstream of the fan 2.
  • the platform 16 defines radially inside the flow path in the fan 2, so that each blade 20 has an aerodynamic surface corresponding to the part of the blade 20 extending in the gas flow.
  • the radially inner limit of the aerodynamic surface is defined by the platform 16.
  • the aerodynamic surface of the blade 20 has a main direction of extension, defining the axis of extension Y of the blade 20 which is substantially radial to the axis of revolution X of the turbomachine.
  • the aerodynamic surface also has a height H corresponding to a distance between a lower limit of the aerodynamic surface and a tip 22 of the blade 20, at the level of an intersection between the trailing edge 25 and the lower limit.
  • the lower limit corresponds to the interface between the blade 23 and the adjacent platform 16.
  • Each blade 20 comprises a foot 21 configured to be inserted into a groove of the fan disc 10, a head 22 (or apex) and a blade 23 having a leading edge 24, a trailing edge 25, an intrados wall 26 and an extrados wall 27.
  • the leading edge 24 is configured to extend facing the flow of gases entering the turbomachine. It corresponds to the anterior part of an aerodynamic profile which faces the airflow and which divides the airflow into an underside flow and an underside flow.
  • the trailing edge 25 for its part corresponds to the rear part of the aerodynamic profile, where the intrados and extrados flows meet.
  • part 3 it comprises an upstream edge 4 configured to extend in the extension of platform 16.
  • the downstream face 14 of the fan disc 10 and the upstream edge 4 of the part 3 are separated by a functional clearance creating an annular cavity 6 opening into the flow path.
  • each platform 16 extends beyond the downstream face 14 of the fan disk 10, in the direction of the upstream edge 4 of the part 3.
  • the downstream end of the platform 16 can be fixed on the upstream edge 4 of the part 3.
  • part 3 comprises a stator, typically an inner shroud of an IGV
  • the downstream end of the platform 16 extends facing the upstream edge 4 of part 3 without coming into contact with that -this.
  • each blade 20 of fan 2 comprises an extension 30, attached and fixed to the trailing edge 25 of its blade 23 and which extends beyond the downstream face 14 of the fan disc 10 in the direction of the upstream edge 4 of the part 3.
  • the extension 30 therefore has the function of extending the trailing edge of the blade 23 beyond the downstream face 14 of the disc 10 to cover the less partially the cavity 6.
  • the extension 30 does not penalize for as much as the mounting of the blades 20 on the disk 10 of the fan, since it does not block access to the grooves.
  • the extension 30 therefore forms, in the zones of the blades 20 on which it is fixed, the trailing edge of the blade 20 since it is at its level that the intrados and extrados flows which bypass the blade 20 meet. , and no longer at the level of the trailing edge 25 of the blade 23.
  • the trailing edge 25 of the blade 23 also forms the trailing edge of dawn 20.
  • the extension 30 can be attached and fixed to the trailing edge 25 of the blade 23 by any means, for example by gluing.
  • the type of glue 40 chosen will depend on the material of which the blade 23 and the extension 30 are made.
  • an epoxy glue 40 can be used in the case where the blade 23 and/or the extension 30 comprise a metal of the aluminum or titanium , Inconel, or a composite material comprising a fibrous reinforcement densified by a polymer matrix.
  • the extension 30 is fixed on the trailing edge 25 of the blade 23 so as to come into contact with the platform 16, and more particularly its outer radial face. However, the extension 30 does not cover the entire trailing edge 25 of the blade 23. In other words, a height h of the extension 30 is less than the height H of the aerodynamic surface of the blade 20, knowing that the height h of extension 30 corresponds to the dimension of extension 30 between its inner and outer radial faces 34, 35 along axis Y. In this way, extensions 30 do not unnecessarily penalize the mass of fan 2 and extend only on the height necessary to ensure their maintenance on the blades 23 and cover the cavity 6.
  • the extension 30 comprises a nose 31, configured to axially extend the trailing edge 25 of the blade 23 downstream, an intrados wing 32 configured to partially cover the intrados wall 26 of the blade 23 and an extrados wing 33 configured to cover partially the extrados wall 27 of the blade 23.
  • the intrados and extrados wings 32, 33 therefore extend upstream, when the extension 30 is fixed on the blade 23, without reaching the leading edge 24 of the blade 23.
  • the internal radial face 34 of the extension 30 is moreover configured to bear against the platform 16.
  • each wing 32, 33 is chosen so as to ensure sufficient retention of the extension 30 on the blade 20.
  • each wing of the extension 30 covers the blade 23 over a length of between 5% and 20% of a chord of the blade 23 at this point, where the chord corresponds to the distance between the leading edge 24 and the trailing edge 25 of the blade 23 at this point.
  • the blade 20 therefore has a surplus of chord at the level of the platform 16, this surplus of chord being due to the presence of the extension 30.
  • the extension 30 therefore creates a bumpy shape at the level of the trailing edge of the blade 20 by relative to the trace of the trailing edge 25 of the blade 23 devoid of extension 30 (see diagram picture 3 ).
  • the extension 30 extends to the upstream edge 4 of the part 3, without covering it.
  • the extension 30 therefore covers the cavity 6, but not the part 3.
  • This embodiment is suitable for part 3 to include a rotor (booster drum or rotating spacer) or a stator (internal shroud of an IGV), since the extension 30 does not come into contact with part 3.
  • a rotor booster drum or rotating spacer
  • a stator internal shroud of an IGV
  • this embodiment makes it possible to eliminate the rotating spacer.
  • the initial function of a rotating spacer is to reduce the size of the cavity 6 between the inner shroud of an IGV and the fan 2 in a turbomachine.
  • extensions 30 on the blades 23 in combination with the platforms 16 which are dimensioned so as to cover the cavity 6 it is no longer necessary to reduce the size of the cavity 6 by adding such a spacer turning. Consequently, the fixing of extensions 30 on the trailing edges of the blades 23 makes it possible to reduce the mass of the turbomachine assembly 1 by eliminating the rotating spacer as well as the associated fixing means (generally, an annular flange and a connection bolted).
  • the extension 30 covers the upstream edge 4 of the part 3.
  • the extension 30 intersects and crosses a plane radial to the axis of revolution and passing through the upstream edge 4 of the part 3.
  • This embodiment is more particularly suitable when the part 3 comprises a rotor (booster drum or rotating spacer), the relative movements between the extension 30 and the rotor being reduced.
  • a rotor booster drum or rotating spacer
  • the fan 2 can further comprise a seal 7, attached and fixed to the extension 30 and configured to fill the cavity 6.
  • the seal 7 is configured to come into contact with the upstream edge 4 of part 3.
  • seal 7 is fixed to extension 30 so as to extend between extension 30 and upstream edge 4 of part 3, being housed in cavity 6.
  • the seal 7 is fixed on the internal radial face 34 of the extension 30, in the zone of the extension 30 which covers the cavity 6.
  • the seal 7 is fixed on the part of the extension 30 which protrudes from the downstream face 14 of the disk 10 of the fan.
  • the seal 7 is preferably made of an elastomeric material, for example rubber.
  • the gasket 7 can only be fixed against the internal radial face 34 of the extension 30, without covering the intrados and extrados walls 26, 27 of the blade 23 nor the intrados and extrados wings 32, 33.
  • the gasket 7 can on the contrary partially cover the intrados and extrados walls 26, 27 in order to provide sealing to said walls 26, 27.
  • the seal 7 then extends under the platform 16, that is to say outside the vein flow.
  • the part of the joint 7 which is fixed on the extension 30 and the part of the joint 7 which partially covers the intrados and extrados walls 26, 27 can be in one piece, or alternatively comprise two separate joints 7.
  • the seal 7 comes into contact with the downstream end of the nose 31 of the extension 30, in order to guarantee sufficient sealing between the fan disc 10 and the part 3.
  • the seal 7 can extend as far as the downstream end of the nose 31 of the extension 30, without however going beyond it, as illustrated in the figure 5 . If necessary, the seal 7 may have an extra thickness at the level of the cavity 6, in order to fill said cavity 6, and a thinned zone in the part configured to come opposite, or even bear, against the upstream edge 4 of the part 3.
  • the attachment of an extension 30 attached and fixed on the trailing edge 25 of the blade 23 has the advantage of making it possible to produce this extension 30 in a material distinct from that of the rest of the blade 23.
  • the extension 30 does not play effect not a structural role, so that the stresses that it is likely to undergo are different from those undergone by the blade 23. It can therefore have a lower modulus of elasticity than the material constituting the blade 23 and/or lower density.
  • the blade 23 is made of a composite material comprising a fibrous reinforcement densified by a matrix, in particular a polymer matrix.
  • the fibrous reinforcement is generally formed from a fibrous preform obtained by three-dimensional weaving with progressive thickness, the matrix then being injected under vacuum using processes of the RTM type (for "Resin Transfer Moulding), or even VARRTM (for Vacuum Resin Transfer Moulding).
  • RTM Resin Transfer Moulding
  • VARRTM Vacuum Resin Transfer Moulding
  • this technology does not make it possible to obtain directly, on leaving the mould, a trailing edge 25 whose thickness is thin and rounded.
  • the trailing edge 25 is generally truncated and has a substantially angular section which favors cracks and harms the general acoustics of the fan 2.
  • the fixing of the extension 30 on the trailing edge 25 allows therefore to cover this angular trailing edge 25 with an envelope made of a different material, so that its shape can be more easily controlled.
  • extension 30 can be made of metal.
  • the extension 30 can be made of aluminum, insofar as this metal is of low density.
  • its Young's modulus is not too high, which makes it possible to limit the shearing stresses in the adhesive 40 at the interface between the blade 23 and the extension 30.
  • the extension 30 can be made of a composite material comprising a two-dimensional fabric reinforced with a polymer matrix in order to limit the shear stresses in the glue 40 between the blade 23 and the extension 30.
  • the extension 30 is simply obtained by successive draping of ribbons or filamentary deposit and/or comprises short fibers making it possible to achieve lower thicknesses.
  • the blade 23 is made of a composite material comprising a fibrous reinforcement made from a fibrous preform obtained by three-dimensional weaving with varying thickness, it also becomes possible to obtain a blade 20 whose trailing edge 25 is thin and rounded. , as opposed to the angular, thick trailing edges likely to be achieved with current three-dimensional weaving technologies.
  • the extension 30 therefore also makes it possible to reduce the thickness of the wakes of the blade 20 of the fan 2 and therefore the performance of the fan 2, but also to improve the flow at the inlet of the booster and its first stage of rectifiers by making the flow more homogeneous, in addition to improving the seal between the fan 2 and the part 3.
  • the extension 30 therefore preferably extends between the separation line of the primary and secondary flows and the platform 16, so that only the flow entering the primary body (the booster) benefits from the thinning of the trailing edge. 25 of the blade 20 through the extension 30.
  • the outer radius R2 of the extension 30, corresponding to the distance between the outer radial face 35 of the extension 30 and the axis X of revolution, in a radial plane, is therefore substantially equal ( to within 10%) to the outer radius R1 of part 3, corresponding to the distance between the radially outer end 5 of part 3 furthest upstream from part 3 (i.e. at the level of the line flow separation) and the axis X of revolution.
  • the extension 30 can be attached and fixed to the trailing edge 25 of the blade 23 using conventional techniques for fixing a structural shield to a blade 23 made of composite material. Thus, a dimpling of the intrados and extrados walls 26, 27 of the blade 23 can be carried out in order to facilitate the assembly of the extension 30 (see picture 2 ). The extension 30 is then attached and fixed to the machined parts of the blade 23 using an adhesive 40.
  • the transition between the extension 30, whose nose 31 is rounded and has a small thickness in comparison with the trailing edge 25 of the blade 23, and the angular trailing edge 25 of the blade 23 can be achieved using a transition piece, fixed between the outer radial face 35 of the extension 30 and the blade 23.
  • This transition piece therefore has a changing shape between its inner radial end, where the transition piece has a shape and a thickness substantially identical to those of the outer radial face 35 extension 30, and an outer radial end, where the transition piece has a shape and a thickness substantially identical to those of the blade 23.
  • the transition piece can be integrated directly into the extension 30 or alternatively be reported and attached to it.

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)

Description

DOMAINE DE L'INVENTIONFIELD OF THE INVENTION

L'invention concerne de manière générale le domaine des turbomachines à double flux, et plus particulièrement celui des soufflantes de ces turbomachines et de leur interaction avec l'entrée de la veine primaire.The invention generally relates to the field of dual-flow turbomachines, and more particularly that of the fans of these turbomachines and their interaction with the inlet of the primary stream.

ARRIERE-PLAN TECHNOLOGIQUETECHNOLOGICAL BACKGROUND

Une turbomachine à double flux comprend généralement, d'amont en aval dans le sens de l'écoulement des gaz, une soufflante, une veine annulaire d'écoulement primaire et une veine annulaire d'écoulement secondaire. La masse d'air aspirée par la soufflante est ainsi divisée en un flux primaire, qui circule dans la veine d'écoulement primaire, et en un flux secondaire, qui est concentrique avec le flux primaire et circule dans la veine d'écoulement secondaire.A turbomachine generally comprises, from upstream to downstream in the direction of gas flow, a fan, an annular primary flow path and an annular secondary flow path. The mass of air sucked in by the fan is thus divided into a primary flow, which circulates in the primary flow path, and a secondary flow, which is concentric with the primary flow and circulates in the secondary flow path.

La veine d'écoulement primaire traverse un corps primaire comprenant un ou plusieurs étages de compresseurs, par exemple un compresseur basse pression et un compresseur haute pression, une chambre de combustion, un ou plusieurs étages de turbines, par exemple une turbine haute pression et une turbine basse pression, et une tuyère d'échappement des gaz.The primary flow path passes through a primary body comprising one or more compressor stages, for example a low pressure compressor and a high pressure compressor, a combustion chamber, one or more turbine stages, for example a high pressure turbine and a low pressure turbine, and a gas exhaust nozzle.

La soufflante comprend un disque de rotor portant une pluralité d'aubes dont les pieds sont engagés et retenus dans des rainures sensiblement axiales formées à la périphérie du disque. Les rainures sont séparées deux à deux par des dents. Ces aubes sont associées à leur extrémité radialement interne à des plateformes inter-aubes qui sont disposées dans le prolongement d'un cône d'entrée de la soufflante et sont configurées pour délimiter, du côté intérieur, la veine annulaire d'entrée d'air dans la soufflante.The fan comprises a rotor disc carrying a plurality of blades whose roots are engaged and retained in substantially axial grooves formed at the periphery of the disc. The grooves are separated two by two by teeth. These blades are associated at their radially inner end with inter-blade platforms which are arranged in the extension of an inlet cone of the fan and are configured to delimit, on the inner side, the annular air inlet vein in the blower.

De façon connue en soi, la turbomachine comprend, immédiatement en aval de la soufflante, en entrée de la veine primaire, une pièce pouvant correspondre, selon la forme de réalisation de la soufflante, à un tambour du booster (pour compresseur basse pression en anglais), qui correspond à la virole interne du booster sur laquelle sont fixées les aubes tournantes du booster, une virole interne d'un IGV (acronyme anglais pour Inlet Guide Vane, c'est-à-dire le premier étage stator du booster dans le corps primaire d'une turbomachine) ou encore un espaceur tournant qui est formé d'une bride annulaire s'étendant entre la soufflante et le tambour du booster et qui tourne à la même vitesse que la soufflante.In a manner known per se, the turbomachine comprises, immediately downstream of the fan, at the inlet of the primary stream, a part which may correspond, depending on the embodiment of the fan, to a drum of the booster (for low pressure compressor in English ), which corresponds to the inner ring of the booster on which the rotating vanes of the booster are fixed, an inner ring of an IGV (English acronym for Inlet Guide Vane, that is to say the first stage stator of the booster in the primary body of a turbomachine) or even a rotating spacer which is formed of an annular flange extending between the fan and the drum of the booster and which rotates at the same speed as the blower.

Afin d'éviter toute interaction mécanique entre le disque de soufflante et cette pièce immédiatement en aval, un jeu fonctionnel est ménagé entre la face aval du disque de soufflante et un bord amont de la pièce. Ce jeu forme cependant une cavité perturbant l'écoulement en générant des recirculations du flux gazeux en aval du pied des aubes de soufflante et un débit de fuite.In order to avoid any mechanical interaction between the fan disc and this part immediately downstream, a functional clearance is provided between the downstream face of the fan disc and an upstream edge of the part. This clearance, however, forms a cavity disturbing the flow by generating recirculations of the gas flow downstream of the root of the fan blades and a leakage rate.

Pour réduire cette cavité, les plateformes sont dimensionnées de sorte à s'étendre au-delà de la face aval du disque de soufflante pour recouvrir au moins partiellement cette cavité. Toutefois, cette solution ne permet pas de supprimer la cavité sur toute la circonférence de la soufflante, dans la mesure où il est nécessaire de laisser une ouverture en aval des rainures afin de permettre l'insertion et la fixation des aubes de soufflante sur le disque de soufflante. Par conséquent, la partie de la cavité qui débouche en aval des aubes de soufflante reste en partiel ouverte.To reduce this cavity, the platforms are sized so as to extend beyond the downstream face of the fan disk to at least partially cover this cavity. However, this solution does not make it possible to eliminate the cavity over the entire circumference of the fan, insofar as it is necessary to leave an opening downstream of the grooves in order to allow the insertion and fixing of the fan blades on the disk. of blower. Consequently, the part of the cavity which opens downstream of the fan blades remains partly open.

Afin de protéger le fonctionnement du booster de cet écoulement dégradé, la virole interne de l'IGV doit être dimensionnée de sorte à adopter une conception aérodynamiquement robuste. Par robuste on entend que la virole doit être capable de supporter des écoulements de mauvaise qualité sans créer des pertes ou des décollements trop importants. La contrepartie de ce dimensionnement est que le rendement des aubages d'un tel IGV est inférieur à celui des IGV classiques. La présence de ces cavités dégrade donc le fonctionnement du booster.In order to protect the operation of the booster from this degraded flow, the internal shroud of the IGV must be sized so as to adopt an aerodynamically robust design. By robust, we mean that the shell must be capable of withstanding poor quality flows without creating excessive losses or separations. The counterpart of this dimensioning is that the efficiency of the blades of such an IGV is lower than that of conventional IGVs. The presence of these cavities therefore degrades the operation of the booster.

Le document JP 2011-069286 décrit une aube de soufflante comprenant une pale, une plateforme et un bouclier de bord d'attaque.The document JP 2011-069286 describes a fan blade comprising a blade, a platform and a leading edge shield.

Le document WO 2017/006054 décrit une plateforme rapportée d'aube de soufflante montée sur un disque de soufflante qui présente un faible rapport de moyeu.The document WO 2017/006054 discloses a fan blade insert mounted on a fan disc that has a low hub ratio.

RESUME DE L'INVENTIONSUMMARY OF THE INVENTION

Un objectif de l'invention est donc de proposer une turbomachine dont le fonctionnement du booster n'est pas dégradé, en limitant voire en éliminant les recirculations de gaz et les débits de fuite en aval du pied des aubes de soufflante.One objective of the invention is therefore to provide a turbomachine in which the operation of the booster is not degraded, by limiting or even eliminating gas recirculation and leakage flow rates downstream of the root of the fan blades.

Pour cela, l'invention propose un ensemble d'une turbomachine présentant un axe de révolution et comprenant, d'amont en aval dans le sens d'écoulement des gaz dans la turbomachine, une soufflante et une pièce, la pièce s'étendant immédiatement en aval de la soufflante et comprenant un bord amont séparé de la soufflante par une cavité,
la soufflante comprenant :

  • une série d'aubes comportant une pale comprenant un bord de fuite et un bouclier rapporté et fixé sur le bord de fuite de la pale,
  • un disque de soufflante présentant une face radiale configurée pour recevoir les aubes, et une face aval s'étendant en regard du bord amont de la pièce et
  • une série de plateformes inter-aubes, chaque plateforme étant rapportée et fixée sur la face radiale, chaque plateforme étant configurée pour recouvrir la face radiale et s'étendre au-delà de la face aval du disque de soufflante en direction du bord amont de la pièce de sorte à recouvrir au moins partiellement la cavité,
l'ensemble étant caractérisé en ce que le bouclier rapporté et fixé sur le bord de fuite de la pale est un prolongateur de chaque aube de soufflante et ce prolongateur s'étend au-delà de la face aval du disque de soufflante en direction du bord amont de la pièce et recouvre au moins partiellement la cavité.For this, the invention proposes an assembly of a turbomachine having an axis of revolution and comprising, from upstream to downstream in the direction of gas flow in the turbomachine, a fan and a part, the part extending immediately downstream of the fan and comprising an upstream edge separated from the fan by a cavity,
the blower comprising:
  • a series of vanes comprising a blade comprising a trailing edge and an attached shield fixed to the trailing edge of the blade,
  • a fan disc having a radial face configured to receive the blades, and a downstream face extending facing the upstream edge of the part and
  • a series of inter-blade platforms, each platform being attached and fixed on the radial face, each platform being configured to cover the radial face and extend beyond the downstream face of the fan disc in the direction of the upstream edge of the piece so as to at least partially cover the cavity,
the assembly being characterized in that the attached shield fixed to the trailing edge of the blade is an extension of each fan blade and this extension extends beyond the downstream face of the fan disc in the direction of the edge upstream of the part and at least partially covers the cavity.

Certaines caractéristiques préférées mais non limitatives de l'ensemble décrit ci-dessus sont les suivantes, prises individuellement ou en combinaison :

  • dans lequel la pièce comprend un rotor, notamment un espaceur tournant ou un tambour d'un compresseur basse pression.
  • tout ou partie des prolongateurs recouvrent le bord amont de la pièce.
  • la pièce comprend un stator, notamment une virole interne d'un IGV.
  • tout ou partie des prolongateurs s'étendent jusqu'au bord amont de la pièce sans recouvrir ledit bord amont.
  • l'ensemble comprend en outre un joint d'étanchéité rapporté et fixé sur le prolongateur et configuré pour combler la cavité entre le prolongateur et le bord amont de la pièce.
  • la pale présente une surface aérodynamique et tout ou partie des prolongateurs s'étendent depuis la plateforme adjacente de l'aube, sur une hauteur inférieure à une hauteur de ladite surface aérodynamique, où la hauteur de la surface aérodynamique correspond à une dimension, suivant un axe radial à l'axe de révolution passant par le bord de fuite, entre ladite plateforme et une tête de l'aube et où la hauteur du prolongateur correspond à une dimension, suivant cet axe radial, entre la plateforme et une face radiale externe d'extrémité du prolongateur.
  • la pièce présente en outre une extrémité radialement externe amont, configurée pour séparer un flux primaire entrant dans la pièce d'un flux secondaire contournant la pièce, et un premier rayon externe correspondant à une distance radiale entre l'extrémité radialement externe amont et l'axe de révolution, le prolongateur présente un deuxième rayon externe, correspondant à une distance radiale entre la face radiale externe d'extrémité du prolongateur et l'axe de révolution et le rayon externe du prolongateur étant sensiblement égal au rayon externe de la pièce.
  • le prolongateur présente un nez, configuré pour prolonger axialement le bord de fuite de la pale vers l'aval, ledit nez étant plus arrondi que le bord de fuite de la pale.
  • l'ensemble comprend en outre, pour chaque aube de soufflante, une pièce de transition, fixée sur une face radiale externe du prolongateur, ladite pièce de transition présentant une forme évolutive entre une extrémité radiale intérieure, où la pièce de transition présente une forme et une épaisseur sensiblement identiques à celles de la face radiale externe du prolongateur, et une extrémité radiale extérieure, où la pièce de transition présente une forme et une épaisseur sensiblement identiques à celles du bord de fuite de la pale.
Some preferred but non-limiting features of the assembly described above are as follows, taken individually or in combination:
  • wherein the part comprises a rotor, in particular a rotating spacer or a drum of a low pressure compressor.
  • all or part of the extensions cover the upstream edge of the part.
  • the part comprises a stator, in particular an internal shroud of an IGV.
  • all or part of the extensions extend to the upstream edge of the part without covering said upstream edge.
  • the assembly further comprises an attached seal fixed to the extension and configured to fill the cavity between the extension and the upstream edge of the part.
  • the blade has an aerodynamic surface and all or part of the extensions extend from the adjacent platform of the blade, over a height less than a height of said aerodynamic surface, where the height of the aerodynamic surface corresponds to a dimension, along a axis radial to the axis of revolution passing through the trailing edge, between said platform and a tip of the blade and where the height of the extension corresponds to a dimension, along this radial axis, between the platform and an outer radial face d end of the extension.
  • the part also has an upstream radially outer end, configured to separate a primary flow entering the part from a secondary flow bypassing the part, and a first outer radius corresponding to a radial distance between the upstream radially outer end and the axis of revolution, the extension has a second external radius, corresponding to a radial distance between the external radial end face of the extension and the axis of revolution and the external radius of the extension being substantially equal to the external radius of the part.
  • the extension has a nose, configured to axially extend the trailing edge of the blade downstream, said nose being more rounded than the trailing edge of the blade.
  • the assembly further comprises, for each fan blade, a transition piece, fixed to an outer radial face of the extension, said transition piece having a changing shape between an inner radial end, where the transition piece has a shape and a thickness substantially identical to those of the outer radial face of the extension, and an outer radial end, where the transition piece has a shape and a thickness substantially identical to those of the trailing edge of the blade.

BREVE DESCRIPTION DES DESSINSBRIEF DESCRIPTION OF THE DRAWINGS

D'autres caractéristiques, buts et avantages de la présente invention apparaîtront mieux à la lecture de la description détaillée qui va suivre, et au regard des dessins annexés donnés à titre d'exemples non limitatifs et sur lesquels :

  • La figure 1 illustre un exemple de réalisation d'un exemple d'ensemble d'une turbomachine conforme à l'invention.
  • La figure 2 est une vue en coupe transversale d'un exemple de réalisation d'un bord de fuite d'une aube de soufflante pouvant être utilisée dans un ensemble d'une turbomachine conforme à l'invention.
  • La figure 3 est une vue de côté d'un exemple de réalisation d'une aube de soufflante pouvant être utilisée dans un ensemble d'une turbomachine conforme à l'invention.
  • La figure 4 est une vue de côté partielle et schématisée d'un premier mode de réalisation d'une aube de soufflante et du bord amont d'une pièce pouvant être utilisées dans un ensemble d'une turbomachine conforme à l'invention.
  • La figure 5 est une vue de côté partielle et schématisée d'un deuxième mode de réalisation d'une aube de soufflante et du bord amont d'une pièce pouvant être utilisées dans un ensemble d'une turbomachine conforme à l'invention.
Other characteristics, objects and advantages of the present invention will appear better on reading the detailed description which follows, and with regard to the appended drawings given by way of non-limiting examples and in which:
  • The figure 1 illustrates an exemplary embodiment of an exemplary assembly of a turbomachine according to the invention.
  • The figure 2 is a cross-sectional view of an embodiment of a trailing edge of a fan blade that can be used in an assembly of a turbomachine according to the invention.
  • The picture 3 is a side view of an embodiment of a fan blade that can be used in an assembly of a turbomachine according to the invention.
  • The figure 4 is a partial and diagrammatic side view of a first embodiment of a fan blade and of the upstream edge of a part that can be used in an assembly of a turbomachine according to the invention.
  • The figure 5 is a partial and diagrammatic side view of a second embodiment of a fan blade and of the upstream edge of a part that can be used in an assembly of a turbomachine according to the invention.

DESCRIPTION DETAILLEE D'UN MODE DE REALISATIONDETAILED DESCRIPTION OF AN EMBODIMENT

Dans la présente demande, l'amont et l'aval sont définis par rapport au sens d'écoulement normal du gaz dans la turbomachine 1. Par ailleurs, on appelle axe de révolution de la turbomachine, l'axe X de symétrie radiale de la turbomachine. La direction axiale correspond à la direction de l'axe X de la turbomachine, et une direction radiale est une direction perpendiculaire à cet axe et passant par lui. De même, un plan axial est un plan contenant l'axe X de la turbomachine et un plan radial est un plan perpendiculaire à cet axe X et passant par lui. La direction tangentielle (ou circonférentielle) est une direction perpendiculaire à l'axe X et ne passant pas par lui. Sauf précision contraire, interne (ou intérieur) et externe (ou extérieur), respectivement, sont utilisés en référence à une direction radiale de sorte que la partie ou la face interne (i.e. radialement interne) d'un élément est plus proche de l'axe X que la partie ou la face externe (i.e. radialement externe) du même élément.In the present application, the upstream and the downstream are defined with respect to the direction of normal flow of the gas in the turbomachine 1. turbomachinery. The axial direction corresponds to the direction of the axis X of the turbomachine, and a radial direction is a direction perpendicular to this axis and passing through it. Similarly, an axial plane is a plane containing the axis X of the turbomachine and a radial plane is a plane perpendicular to this axis X and passing through it. The tangential (or circumferential) direction is a direction perpendicular to the X axis and not passing through it. Unless otherwise specified, internal (or interior) and external (or exterior), respectively, are used with reference to a radial direction so that the part or face internal (ie radially internal) of an element is closer to the X axis than the external (ie radially external) part or face of the same element.

Un ensemble 1 d'une turbomachine notamment, d'amont en aval, une soufflante 2 et une pièce 3. La pièce 3 peut comprendre un tambour du booster, une virole interne d'un IGV ou encore un espaceur tournant.An assembly 1 of a turbomachine in particular, from upstream to downstream, a fan 2 and a part 3. Part 3 can comprise a drum of the booster, an internal shroud of an IGV or else a rotating spacer.

La soufflante 2 comprend un disque 10 de soufflante présentant une face amont, une face aval 14 et une face radiale 12. Il porte une pluralité d'aubes 20 de soufflante 2 associées à des plateformes 16 inter-aubes 20. Des rainures axiales, séparées deux à deux par des dents, sont formées dans la face radiale 12 du disque 10.The fan 2 comprises a fan disc 10 having an upstream face, a downstream face 14 and a radial face 12. It carries a plurality of fan blades 20 2 associated with inter-blade platforms 16 20. Axial grooves, separated two by two by teeth, are formed in the radial face 12 of the disc 10.

Les aubes 20 sont associées à leur extrémité radialement interne à des plateformes 16 inter-aubes. Chaque plateforme 16 présente une extrémité amont, configurée pour s'étendre au niveau de la face amont du disque 10 de soufflante, et une extrémité aval configurée pour venir en regard de la pièce 3 s'étendant immédiatement en aval de la soufflante 2. La plateforme 16 délimite radialement à l'intérieur la veine d'écoulement dans la soufflante 2, de sorte que chaque aube 20 présente une surface aérodynamique correspondant à la partie de l'aube 20 s'étendant dans l'écoulement gazeux. La limite radialement intérieure de la surface aérodynamique est définie par la plateforme 16.The blades 20 are associated at their radially inner end with inter-blade platforms 16. Each platform 16 has an upstream end, configured to extend at the level of the upstream face of the fan disk 10, and a downstream end configured to come opposite the part 3 extending immediately downstream of the fan 2. The platform 16 defines radially inside the flow path in the fan 2, so that each blade 20 has an aerodynamic surface corresponding to the part of the blade 20 extending in the gas flow. The radially inner limit of the aerodynamic surface is defined by the platform 16.

La surface aérodynamique de l'aube 20 présente une direction principale d'extension, définissant l'axe d'extension Y de l'aube 20 qui est sensiblement radial à l'axe de révolution X de la turbomachine. La surface aérodynamique présente en outre une hauteur H correspondant à une distance entre une limite inférieure de la surface aérodynamique et une tête 22 de l'aube 20, au niveau d'une intersection entre le bord de fuite 25 et la limite inférieure. La limite inférieure correspond à l'interface entre la pale 23 et la plateforme 16 adjacente.The aerodynamic surface of the blade 20 has a main direction of extension, defining the axis of extension Y of the blade 20 which is substantially radial to the axis of revolution X of the turbomachine. The aerodynamic surface also has a height H corresponding to a distance between a lower limit of the aerodynamic surface and a tip 22 of the blade 20, at the level of an intersection between the trailing edge 25 and the lower limit. The lower limit corresponds to the interface between the blade 23 and the adjacent platform 16.

Chaque aube 20 comporte un pied 21 configuré pour être inséré dans une rainure du disque 10 de soufflante, une tête 22 (ou sommet) et une pale 23 présentant un bord d'attaque 24, un bord de fuite 25, une paroi intrados 26 et une paroi extrados 27. Le bord d'attaque 24 est configuré pour s'étendre en regard de l'écoulement des gaz entrant dans la turbomachine. Il correspond à la partie antérieure d'un profil aérodynamique qui fait face au flux d'air et qui divise l'écoulement d'air en un écoulement d'intrados et en un écoulement extrados. Le bord de fuite 25 quant à lui correspond à la partie postérieure du profil aérodynamique, où se rejoignent les écoulements intrados et extrados.Each blade 20 comprises a foot 21 configured to be inserted into a groove of the fan disc 10, a head 22 (or apex) and a blade 23 having a leading edge 24, a trailing edge 25, an intrados wall 26 and an extrados wall 27. The leading edge 24 is configured to extend facing the flow of gases entering the turbomachine. It corresponds to the anterior part of an aerodynamic profile which faces the airflow and which divides the airflow into an underside flow and an underside flow. The trailing edge 25 for its part corresponds to the rear part of the aerodynamic profile, where the intrados and extrados flows meet.

Quelle que soit la forme de réalisation de la pièce 3, celle-ci comporte un bord amont 4 configuré pour s'étendre dans le prolongement de la plateforme 16.Whatever the embodiment of part 3, it comprises an upstream edge 4 configured to extend in the extension of platform 16.

La face aval 14 du disque 10 de soufflante et le bord amont 4 de la pièce 3 sont séparés par un jeu fonctionnel créant une cavité annulaire 6 débouchant dans la veine d'écoulement.The downstream face 14 of the fan disc 10 and the upstream edge 4 of the part 3 are separated by a functional clearance creating an annular cavity 6 opening into the flow path.

Cette cavité 6 est recouverte au moins partiellement par les plateformes 16. Pour cela, chaque plateforme 16 s'étend au-delà de la face aval 14 du disque 10 de soufflante, en direction du bord amont 4 de la pièce 3. Lorsque la pièce 3 est un rotor et tourne à la même vitesse que le disque 10 de soufflante, typiquement lorsque la pièce 3 comprend un tambour du booster ou un espaceur tournant, l'extrémité aval de la plateforme 16 peut être fixée sur le bord amont 4 de la pièce 3. En variante, lorsque la pièce 3 comprend un stator, typiquement une virole interne d'un IGV, l'extrémité aval de la plateforme 16 s'étend en regard du bord amont 4 de la pièce 3 sans entrer en contact avec celle-ci.This cavity 6 is at least partially covered by the platforms 16. For this, each platform 16 extends beyond the downstream face 14 of the fan disk 10, in the direction of the upstream edge 4 of the part 3. When the part 3 is a rotor and rotates at the same speed as the fan disk 10, typically when part 3 comprises a booster drum or a rotating spacer, the downstream end of the platform 16 can be fixed on the upstream edge 4 of the part 3. As a variant, when part 3 comprises a stator, typically an inner shroud of an IGV, the downstream end of the platform 16 extends facing the upstream edge 4 of part 3 without coming into contact with that -this.

Afin de limiter les risques de recirculation du flux gazeux et de débit de fuite, chaque aube 20 de soufflante 2 comporte un prolongateur 30, rapporté et fixé sur le bord de fuite 25 de sa pale 23 et qui s'étend au-delà de la face aval 14 du disque 10 de soufflante en direction du bord amont 4 de la pièce 3. Le prolongateur 30 a donc pour fonction de prolonger le bord de fuite de la pale 23 au-delà de la face aval 14 du disque 10 pour recouvrir au moins partiellement la cavité 6. Toutefois, le prolongateur 30 ne pénalise pas pour autant le montage des aubes 20 sur le disque 10 de soufflante, puisqu'il ne bloque pas l'accès aux rainures.In order to limit the risks of recirculation of the gas flow and leakage rate, each blade 20 of fan 2 comprises an extension 30, attached and fixed to the trailing edge 25 of its blade 23 and which extends beyond the downstream face 14 of the fan disc 10 in the direction of the upstream edge 4 of the part 3. The extension 30 therefore has the function of extending the trailing edge of the blade 23 beyond the downstream face 14 of the disc 10 to cover the less partially the cavity 6. However, the extension 30 does not penalize for as much as the mounting of the blades 20 on the disk 10 of the fan, since it does not block access to the grooves.

Le prolongateur 30 forme donc, dans les zones de l'aubes 20 sur lesquelles il est fixé, le bord de fuite de l'aube 20 puisque c'est à son niveau que se rejoignent les écoulements intrados et extrados qui contournent l'aube 20, et non plus au niveau du bord de fuite 25 de la pale 23. En revanche, dans les autres zones de la pale 23 qui ne sont éventuellement pas recouvertes par le prolongateur 30, le bord de fuite 25 de la pale 23 forme également le bord de fuite de l'aube 20.The extension 30 therefore forms, in the zones of the blades 20 on which it is fixed, the trailing edge of the blade 20 since it is at its level that the intrados and extrados flows which bypass the blade 20 meet. , and no longer at the level of the trailing edge 25 of the blade 23. On the other hand, in the other zones of the blade 23 which are possibly not covered by the extension 30, the trailing edge 25 of the blade 23 also forms the trailing edge of dawn 20.

Le prolongateur 30 peut être rapporté et fixé sur le bord de fuite 25 de la pale 23 par tous moyens, par exemple par collage. Le type de colle 40 choisi dépendra du matériau constitutif de la pale 23 et du prolongateur 30. Par exemple, une colle 40 epoxy peut être utilisée dans le cas où la pale 23 et/ou le prolongateur 30 comprennent un métal du type aluminium, titane, Inconel, ou un matériau composite comprenant un renfort fibreux densifié par une matrice polymère.The extension 30 can be attached and fixed to the trailing edge 25 of the blade 23 by any means, for example by gluing. The type of glue 40 chosen will depend on the material of which the blade 23 and the extension 30 are made. For example, an epoxy glue 40 can be used in the case where the blade 23 and/or the extension 30 comprise a metal of the aluminum or titanium , Inconel, or a composite material comprising a fibrous reinforcement densified by a polymer matrix.

Le prolongateur 30 est fixé sur le bord de fuite 25 de la pale 23 de sorte à venir en contact avec la plateforme 16, et plus particulièrement sa face radiale externe. Toutefois, le prolongateur 30 ne recouvre pas tout le bord de fuite 25 de la pale 23. En d'autres termes, une hauteur h du prolongateur 30 est inférieure à la hauteur H de la surface aérodynamique de l'aube 20, sachant que la hauteur h du prolongateur 30 correspond à la dimension du prolongateur 30 entre ses faces radiales interne et externe 34, 35 suivant l'axe Y. De la sorte, les prolongateurs 30 ne pénalisent pas inutilement la masse de la soufflante 2 et s'étendent uniquement sur la hauteur nécessaire pour assurer leur maintien sur les pales 23 et recouvrir la cavité 6.The extension 30 is fixed on the trailing edge 25 of the blade 23 so as to come into contact with the platform 16, and more particularly its outer radial face. However, the extension 30 does not cover the entire trailing edge 25 of the blade 23. In other words, a height h of the extension 30 is less than the height H of the aerodynamic surface of the blade 20, knowing that the height h of extension 30 corresponds to the dimension of extension 30 between its inner and outer radial faces 34, 35 along axis Y. In this way, extensions 30 do not unnecessarily penalize the mass of fan 2 and extend only on the height necessary to ensure their maintenance on the blades 23 and cover the cavity 6.

Le prolongateur 30 comprend un nez 31, configuré pour prolonger axialement le bord de fuite 25 de la pale 23 vers l'aval, une aile intrados 32 configurée pour recouvrir partiellement la paroi intrados 26 de la pale 23 et une aile extrados 33 configurée pour recouvrir partiellement la paroi extrados 27 de la pale 23. Les ailes intrados et extrados 32, 33 s'étendent donc vers l'amont, lorsque le prolongateur 30 est fixé sur la pale 23, sans atteindre le bord d'attaque 24 de la pale 23. La face radiale interne 34 du prolongateur 30 est par ailleurs configurée pour venir en appui contre la plateforme 16.The extension 30 comprises a nose 31, configured to axially extend the trailing edge 25 of the blade 23 downstream, an intrados wing 32 configured to partially cover the intrados wall 26 of the blade 23 and an extrados wing 33 configured to cover partially the extrados wall 27 of the blade 23. The intrados and extrados wings 32, 33 therefore extend upstream, when the extension 30 is fixed on the blade 23, without reaching the leading edge 24 of the blade 23. The internal radial face 34 of the extension 30 is moreover configured to bear against the platform 16.

La longueur axiale de chaque aile 32, 33 est choisie de manière à assurer un maintien suffisant du prolongateur 30 sur l'aube 20. Par exemple, en tout point de la hauteur h du prolongateur 30, chaque aile du prolongateur 30 recouvre la pale 23 sur une longueur comprise entre 5% et 20% d'une corde de la pale 23 en ce point, où la corde correspond à la distance entre le bord d'attaque 24 et le bord de fuite 25 de la pale 23 en ce point.The axial length of each wing 32, 33 is chosen so as to ensure sufficient retention of the extension 30 on the blade 20. For example, at any point of the height h of the extension 30, each wing of the extension 30 covers the blade 23 over a length of between 5% and 20% of a chord of the blade 23 at this point, where the chord corresponds to the distance between the leading edge 24 and the trailing edge 25 of the blade 23 at this point.

L'aube 20 présente donc un surplus de corde au niveau de la plateforme 16, ce surplus de corde étant dû à la présence du prolongateur 30. Le prolongateur 30 crée donc une forme bossue au niveau du bord de fuite de l'aube 20 par rapport à la trace du bord de fuite 25 de la pale 23 dépourvue de prolongateur 30 (voir le schéma figure 3).The blade 20 therefore has a surplus of chord at the level of the platform 16, this surplus of chord being due to the presence of the extension 30. The extension 30 therefore creates a bumpy shape at the level of the trailing edge of the blade 20 by relative to the trace of the trailing edge 25 of the blade 23 devoid of extension 30 (see diagram picture 3 ).

Dans une première forme de réalisation (figure 4), le prolongateur 30 s'étend jusqu'au bord amont 4 de la pièce 3, sans le recouvrir. Le prolongateur 30 recouvre donc bien la cavité 6, mais pas la pièce 3.In a first embodiment ( figure 4 ), the extension 30 extends to the upstream edge 4 of the part 3, without covering it. The extension 30 therefore covers the cavity 6, but not the part 3.

Cette forme de réalisation est adaptée que la pièce 3 comprenne un rotor (tambour de booster ou espaceur tournant) ou un stator (virole interne d'un IGV), puisque le prolongateur 30 n'entre pas en contact avec la pièce 3.This embodiment is suitable for part 3 to include a rotor (booster drum or rotating spacer) or a stator (internal shroud of an IGV), since the extension 30 does not come into contact with part 3.

Le cas échéant, cette forme de réalisation rend possible la suppression de l'espaceur tournant. En effet, la fonction initiale d'un espaceur tournant est de réduire la taille de la cavité 6 entre la virole interne d'un IGV et la soufflante 2 dans une turbomachine. Or, grâce à l'ajout de prolongateurs 30 sur les pales 23 en combinaison avec les plateformes 16 qui sont dimensionnées de sorte à recouvrir la cavité 6, il n'est plus nécessaire de réduire la taille de la cavité 6 en ajoutant un tel espaceur tournant. Par conséquent, la fixation de prolongateurs 30 sur les bords de fuite des pales 23 permet de réduire la masse de l'ensemble 1 de turbomachine en supprimant l'espaceur tournant ainsi que les moyens de fixation associés (généralement, une bride annulaire et une liaison boulonnée).If necessary, this embodiment makes it possible to eliminate the rotating spacer. Indeed, the initial function of a rotating spacer is to reduce the size of the cavity 6 between the inner shroud of an IGV and the fan 2 in a turbomachine. However, thanks to the addition of extensions 30 on the blades 23 in combination with the platforms 16 which are dimensioned so as to cover the cavity 6, it is no longer necessary to reduce the size of the cavity 6 by adding such a spacer turning. Consequently, the fixing of extensions 30 on the trailing edges of the blades 23 makes it possible to reduce the mass of the turbomachine assembly 1 by eliminating the rotating spacer as well as the associated fixing means (generally, an annular flange and a connection bolted).

Dans une deuxième forme de réalisation (figure 5), le prolongateur 30 recouvre le bord amont 4 de la pièce 3. En d'autres termes, le prolongateur 30 coupe et traverse un plan radial à l'axe de révolution et passant par le bord amont 4 de la pièce 3.In a second embodiment ( figure 5 ), the extension 30 covers the upstream edge 4 of the part 3. In other words, the extension 30 intersects and crosses a plane radial to the axis of revolution and passing through the upstream edge 4 of the part 3.

Cette forme de réalisation est plus particulièrement adaptée lorsque la pièce 3 comprend un rotor (tambour de booster ou espaceur tournant), les mouvements relatifs entre le prolongateur 30 et le rotor étant réduits.This embodiment is more particularly suitable when the part 3 comprises a rotor (booster drum or rotating spacer), the relative movements between the extension 30 and the rotor being reduced.

La soufflante 2 peut en outre comprendre un joint d'étanchéité 7, rapporté et fixé sur le prolongateur 30 et configuré pour combler la cavité 6. Dans la première forme de réalisation, le joint 7 est configuré pour venir à champ avec le bord amont 4 de la pièce 3. Dans la deuxième forme de réalisation, le joint 7 est fixé sur le prolongateur 30 de sorte à s'étendre entre le prolongateur 30 et le bord amont 4 de la pièce 3, en étant logé dans la cavité 6.The fan 2 can further comprise a seal 7, attached and fixed to the extension 30 and configured to fill the cavity 6. In the first embodiment, the seal 7 is configured to come into contact with the upstream edge 4 of part 3. In the second embodiment, seal 7 is fixed to extension 30 so as to extend between extension 30 and upstream edge 4 of part 3, being housed in cavity 6.

Quelle que soit la forme de réalisation, le joint 7 est fixé sur la face radiale interne 34 du prolongateur 30, dans la zone du prolongateur 30 qui recouvre la cavité 6. En d'autres termes, le joint 7 est fixé sur la partie du prolongateur 30 qui dépasse de la face aval 14 du disque 10 de soufflante.Whatever the embodiment, the seal 7 is fixed on the internal radial face 34 of the extension 30, in the zone of the extension 30 which covers the cavity 6. In other words, the seal 7 is fixed on the part of the extension 30 which protrudes from the downstream face 14 of the disk 10 of the fan.

Le joint 7 est de préférence réalisé dans un matériau élastomère, par exemple en caoutchouc.The seal 7 is preferably made of an elastomeric material, for example rubber.

Le joint 7 peut être uniquement fixé contre la face radiale interne 34 du prolongateur 30, sans recouvrir les parois intrados et extrados 26, 27 de la pale 23 ni les ailes intrados et extrados 32, 33. En variante, le joint 7 peut au contraire recouvrir partiellement les parois intrados et extrados 26, 27 afin de fournir une étanchéité aux auxdites parois 26, 27. Dans ce cas, le joint 7 s'étend alors sous la plateforme 16, c'est-à-dire en dehors de la veine d'écoulement. La partie du joint 7 qui est fixée sur le prolongateur 30 et la partie du joint 7 qui recouvre partiellement les parois intrados et extrados 26, 27 peuvent être monoblocs, ou en variante comprendre deux joints 7 distincts.The gasket 7 can only be fixed against the internal radial face 34 of the extension 30, without covering the intrados and extrados walls 26, 27 of the blade 23 nor the intrados and extrados wings 32, 33. Alternatively, the gasket 7 can on the contrary partially cover the intrados and extrados walls 26, 27 in order to provide sealing to said walls 26, 27. In this case, the seal 7 then extends under the platform 16, that is to say outside the vein flow. The part of the joint 7 which is fixed on the extension 30 and the part of the joint 7 which partially covers the intrados and extrados walls 26, 27 can be in one piece, or alternatively comprise two separate joints 7.

Dans la première forme de réalisation, le joint 7 arrive à champ avec l'extrémité aval du nez 31 du prolongateur 30, afin de garantir une étanchéité suffisante entre le disque 10 de soufflante et la pièce 3.In the first embodiment, the seal 7 comes into contact with the downstream end of the nose 31 of the extension 30, in order to guarantee sufficient sealing between the fan disc 10 and the part 3.

Dans la deuxième forme de réalisation, seule une partie de la face radiale interne 34 du prolongateur 30 qui chevauche le bord amont 4 de la pièce 3 peut être recouverte par le joint 7, l'extrémité aval du nez 31 pouvant être dépourvue de joint 7. Alternativement, le joint 7 peut s'étendre jusqu'à l'extrémité aval du nez 31 du prolongateur 30, sans toutefois la dépasser, comme illustré sur la figure 5. Le cas échéant, le joint 7 peut présenter une surépaisseur au niveau de la cavité 6, afin de combler ladite cavité 6, et une zone amincie dans la partie configurée pour venir en regard, voire en appui, contre le bord amont 4 de la pièce 3.In the second embodiment, only part of the internal radial face 34 of the extension 30 which overlaps the upstream edge 4 of the part 3 can be covered by the gasket 7, the downstream end of the nose 31 possibly having no gasket 7 Alternatively, the seal 7 can extend as far as the downstream end of the nose 31 of the extension 30, without however going beyond it, as illustrated in the figure 5 . If necessary, the seal 7 may have an extra thickness at the level of the cavity 6, in order to fill said cavity 6, and a thinned zone in the part configured to come opposite, or even bear, against the upstream edge 4 of the part 3.

La fixation d'un prolongateur 30 rapporté et fixé sur le bord de fuite 25 de la pale 23 présente l'avantage de permettre de réaliser ce prolongateur 30 dans un matériau distinct de celui du reste de la pale 23. Le prolongateur 30 ne joue en effet pas un rôle structurel, de sorte que les contraintes qu'il est susceptible de subir sont différentes de celles subies par la pale 23. Il peut donc présenter un module d'élasticité plus faible que le matériau constitutif de la pale 23 et/ou une densité plus faible.The attachment of an extension 30 attached and fixed on the trailing edge 25 of the blade 23 has the advantage of making it possible to produce this extension 30 in a material distinct from that of the rest of the blade 23. The extension 30 does not play effect not a structural role, so that the stresses that it is likely to undergo are different from those undergone by the blade 23. It can therefore have a lower modulus of elasticity than the material constituting the blade 23 and/or lower density.

Cela est particulièrement avantageux lorsque la pale 23 est réalisée dans un matériau composite comprenant un renfort fibreux densifié par une matrice, en particulier une matrice polymère. En effet, le renfort fibreux est généralement formé à partir d'une préforme fibreuse obtenue par tissage tridimensionnel avec épaisseur évolutive, la matrice étant ensuite injectée sous vide à l'aide de procédés du type RTM (pour « Resin Transfer Moulding), ou encore VARRTM (pour Vacuum Resin Transfer Molding). Or, cette technologie ne permet pas d'obtenir directement, en sortie du moule, un bord de fuite 25 dont l'épaisseur est fine et arrondie. Au contraire, le bord de fuite 25 est généralement tronqué et présente section sensiblement anguleuse qui favorise les fissures et nuit à l'acoustique générale de la soufflante 2. La fixation du prolongateur 30 sur le bord de fuite 25 permet donc de recouvrir ce bord de fuite 25 anguleux avec une enveloppe réalisée dans un matériau différent, de sorte que sa forme peut être plus facilement maîtrisée.This is particularly advantageous when the blade 23 is made of a composite material comprising a fibrous reinforcement densified by a matrix, in particular a polymer matrix. Indeed, the fibrous reinforcement is generally formed from a fibrous preform obtained by three-dimensional weaving with progressive thickness, the matrix then being injected under vacuum using processes of the RTM type (for "Resin Transfer Moulding), or even VARRTM (for Vacuum Resin Transfer Moulding). However, this technology does not make it possible to obtain directly, on leaving the mould, a trailing edge 25 whose thickness is thin and rounded. On the contrary, the trailing edge 25 is generally truncated and has a substantially angular section which favors cracks and harms the general acoustics of the fan 2. The fixing of the extension 30 on the trailing edge 25 allows therefore to cover this angular trailing edge 25 with an envelope made of a different material, so that its shape can be more easily controlled.

Typiquement, le prolongateur 30 peut être réalisé en métal. Par exemple, le prolongateur 30 peut être réalisé en aluminium, dans la mesure où ce métal est de faible masse volumique. De plus, son module d'Young n'est pas trop élevé, ce qui permet de limiter les contraintes de cisaillement dans la colle 40 à l'interface entre la pale 23 et le prolongateur 30.Typically, extension 30 can be made of metal. For example, the extension 30 can be made of aluminum, insofar as this metal is of low density. In addition, its Young's modulus is not too high, which makes it possible to limit the shearing stresses in the adhesive 40 at the interface between the blade 23 and the extension 30.

En variante, le prolongateur 30 peut être réalisé dans un matériau composite comprenant un tissu bidimensionnel renforcé par une matrice polymère afin de limiter les contraintes de cisaillement dans la colle 40 entre la pale 23 et le prolongateur 30. Dans ce cas, le prolongateur 30 est simplement obtenu par drapage successif de rubans ou dépose filamentaire et/ou comprend des fibres courtes permettant d'atteindre des épaisseurs plus faibles.As a variant, the extension 30 can be made of a composite material comprising a two-dimensional fabric reinforced with a polymer matrix in order to limit the shear stresses in the glue 40 between the blade 23 and the extension 30. In this case, the extension 30 is simply obtained by successive draping of ribbons or filamentary deposit and/or comprises short fibers making it possible to achieve lower thicknesses.

Lorsque la pale 23 est réalisée en matériau composite comprenant un renfort fibreux réalisé à partir d'une préforme fibreuse obtenue par tissage tridimensionnel avec épaisseur évolutive, il devient en outre possible d'obtenir une aube 20 dont le bord de fuite 25 est fin et arrondi, par opposition aux bords de fuite anguleux et épais susceptibles d'être obtenus avec les technologies de tissage tridimensionnel actuelles. Le prolongateur 30 permet donc également de réduire l'épaisseur des sillages de l'aube 20 de soufflante 2 et donc les performances de la soufflante 2, mais également d'améliorer l'écoulement en entrée du booster et de son premier étage de redresseurs en rendant l'écoulement plus homogène, en plus d'améliorer l'étanchéité entre la soufflante 2 et la pièce 3.When the blade 23 is made of a composite material comprising a fibrous reinforcement made from a fibrous preform obtained by three-dimensional weaving with varying thickness, it also becomes possible to obtain a blade 20 whose trailing edge 25 is thin and rounded. , as opposed to the angular, thick trailing edges likely to be achieved with current three-dimensional weaving technologies. The extension 30 therefore also makes it possible to reduce the thickness of the wakes of the blade 20 of the fan 2 and therefore the performance of the fan 2, but also to improve the flow at the inlet of the booster and its first stage of rectifiers by making the flow more homogeneous, in addition to improving the seal between the fan 2 and the part 3.

Les coupes aérodynamiques des aubes 20 de soufflante 2 étant plus fines vers la tête 22 de l'aube 20, il n'est pas nécessaire d'appliquer le prolongateur 30 sur toute la hauteur H de la surface aérodynamique. Le prolongateur 30 s'étend donc de préférence entre la ligne de séparation des flux primaire et secondaire et la plateforme 16, de sorte que seul l'écoulement entrant dans le corps primaire (le booster) bénéficie de l'amincissement du bord de fuite 25 de l'aube 20 grâce au prolongateur 30. Le rayon externe R2 du prolongateur 30, correspondant à la distance entre la face radiale externe 35 du prolongateur 30 et l'axe X de révolution, dans un plan radial, est donc sensiblement égal (à 10% près) au rayon externe R1 de la pièce 3, correspondant à la distance entre l'extrémité radialement externe 5 de la pièce 3 la plus en amont de la pièce 3 (c'est-à-dire au niveau de la ligne de séparation des flux) et l'axe X de révolution.Since the aerodynamic sections of the blades 20 of the fan 2 are thinner towards the head 22 of the blade 20, it is not necessary to apply the extension 30 over the entire height H of the aerodynamic surface. The extension 30 therefore preferably extends between the separation line of the primary and secondary flows and the platform 16, so that only the flow entering the primary body (the booster) benefits from the thinning of the trailing edge. 25 of the blade 20 through the extension 30. The outer radius R2 of the extension 30, corresponding to the distance between the outer radial face 35 of the extension 30 and the axis X of revolution, in a radial plane, is therefore substantially equal ( to within 10%) to the outer radius R1 of part 3, corresponding to the distance between the radially outer end 5 of part 3 furthest upstream from part 3 (i.e. at the level of the line flow separation) and the axis X of revolution.

Le prolongateur 30 peut être rapporté et fixé sur le bord de fuite 25 de la pale 23 à l'aide des techniques conventionnelles de fixation d'un bouclier structurel sur une pale 23 en matériau composite. Ainsi, un soyage des parois intrados et extrados 26, 27 de la pale 23 peut être effectué afin de faciliter l'assemblage du prolongateur 30 (voir figure 2). Le prolongateur 30 est ensuite rapporté et fixé sur les parties usinées de la pale 23 à l'aide d'une colle 40.The extension 30 can be attached and fixed to the trailing edge 25 of the blade 23 using conventional techniques for fixing a structural shield to a blade 23 made of composite material. Thus, a dimpling of the intrados and extrados walls 26, 27 of the blade 23 can be carried out in order to facilitate the assembly of the extension 30 (see picture 2 ). The extension 30 is then attached and fixed to the machined parts of the blade 23 using an adhesive 40.

La transition entre le prolongateur 30, dont le nez 31 est arrondie et présente une faible épaisseur en comparaison avec le bord de fuite 25 de la pale 23, et le bord de fuite 25 anguleux de la pale 23 peut être réalisée à l'aide d'une pièce de transition, fixée entre la face radiale externe 35 du prolongateur 30 et la pale 23. Cette pièce de transition présente donc une forme évolutive entre son extrémité radiale intérieure, où la pièce de transition présente une forme et une épaisseur sensiblement identiques à celles de la face radiale externe 35 prolongateur 30, et une extrémité radiale extérieure, où la pièce de transition présente une forme et une épaisseur sensiblement identiques à celles de la pale 23. La pièce de transition peut être intégrée directement au prolongateur 30 ou en variante être rapportée et fixée sur celui-ci.The transition between the extension 30, whose nose 31 is rounded and has a small thickness in comparison with the trailing edge 25 of the blade 23, and the angular trailing edge 25 of the blade 23 can be achieved using a transition piece, fixed between the outer radial face 35 of the extension 30 and the blade 23. This transition piece therefore has a changing shape between its inner radial end, where the transition piece has a shape and a thickness substantially identical to those of the outer radial face 35 extension 30, and an outer radial end, where the transition piece has a shape and a thickness substantially identical to those of the blade 23. The transition piece can be integrated directly into the extension 30 or alternatively be reported and attached to it.

Claims (10)

  1. Assembly (1) of a turbomachine having an axis (X) of revolution and comprising, from upstream to downstream in the direction of flow of the gases in the turbomachine, a fan (2) and a part (3),
    - the part (3) extending immediately downstream of the fan (2) and comprising an upstream edge (4) separated from the fan (2) by a cavity (6)
    the fan (2) comprising :
    - a series of blades (20) comprising an airfoil (23) comprising a trailing edge (25) and a shield attached and fixed to the trailing edge (25) of the airfoil (23),
    - a fan (2) disc (10) having a radial face (12) configured to receive the blades (20) a downstream face (14) extending opposite the upstream edge (4) of the part (3) and
    - a series of inter-blade platforms (16), each platform (16) being attached and fixed to the radial face (12), each platform (16) being configured to overlie the radial face (12) and extend beyond the downstream face of the fan disc (10) towards the upstream edge (4) of the part (3) so as to at least partially overlie the cavity (6),
    the assembly (1) being characterised in that the shield attached and fixed to the trailing edge (25) of the airfoil (23) is an extension piece (30) of each fan blade (20) of the fan (2) and this extension piece (30) extends beyond the downstream face (14) of the disc (10) of the fan (2) in the direction of the upstream edge (4) of the part (3) and at least partially covers the cavity (6).
  2. The assembly (1) according to claim 1, wherein the part (3) comprises a rotor, in particular a rotating spacer or a drum of a low pressure compressor.
  3. An assembly (1) according to any of claims 1 or 2, wherein all or part of the extension pieces (30) cover the upstream edge (4) of the part (3).
  4. The assembly (1) according to claim 1, wherein the part (3) comprises a stator, in particular an inner shell of an IGV.
  5. An assembly (1) according to any of claims 1, 2 or 4, wherein some or all of the extension pieces (30) extend up to the upstream edge (4) of the part (3) without covering the upstream edge (4).
  6. An assembly (1) according to one of claims 1 to 5, further comprising a seal (7) attached and fixed to the extension piece (30) and configured to fill the cavity (6) between the extension piece (30) and the upstream edge (4) of the part (3).
  7. An assembly (1) according to any one of claims 1 to 6, wherein the airfoil (23) has an aerodynamic surface and some or all of the extensions (30) extend from the platform (16) adjacent to the blade (20) over a height (h) less than a height (H) of said aerodynamic surface, wherein the height (H) of the aerodynamic surface corresponds to a dimension along an axis (Y) radial to the axis (X) of revolution passing through the trailing edge (25), between said platform (16) and a tip of the blade (20) and where the height (h) of the extension piece (30) corresponds to a dimension, along this radial axis (Y), between the platform (16) and a radial outer end face (35) of the extension piece (30).
  8. An assembly (1) according to claim 7, wherein:
    - the part (3) further comprises a radially outer upstream end (5), configured to divide a primary flow entering the part (3) and a secondary flow bypassing the part (3), and a first outer radius (R1) corresponding to a radial distance between the radially outer upstream end (5) and the axis (X) of revolution
    - the extension piece (30) has a second external radius (R2), corresponding to a radial distance between the radially external end face (35) of the extension piece (30) and the axis (X) of revolution,
    the outer radius (R2) of the extension piece (30) being substantially equal to the outer radius (R1) of the part (3).
  9. An assembly (1) according to any of claims 1 to 8, wherein the extension piece (30) has a nose (31), configured to axially extend the trailing edge (25) of the airfoil (23) in a downstream direction, said nose (31) being more rounded than the trailing edge (25) of the airfoil (23).
  10. Assembly (1) according to claim 9, further comprising, for each fan blade (20), a transition piece, fixed to a radial outer face of the extension piece (30), said transition piece having a shape evolving between a radial inner end where the transition piece has a shape and thickness substantially identical to those of the radial outer face (35) of the extension piece (30), and a radial outer end, where the transition piece has a shape and thickness substantially identical to those of the trailing edge (25) of the airfoil (23).
EP19848803.3A 2018-12-21 2019-12-20 Turbomachine assembly comprising fan blades with an extended trailing edge Active EP3899207B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1873734A FR3090733B1 (en) 2018-12-21 2018-12-21 Turbomachine assembly including fan blades with extended trailing edge
PCT/FR2019/053234 WO2020128384A1 (en) 2018-12-21 2019-12-20 Turbomachine assembly comprising fan blades with an extended trailing edge

Publications (2)

Publication Number Publication Date
EP3899207A1 EP3899207A1 (en) 2021-10-27
EP3899207B1 true EP3899207B1 (en) 2022-07-27

Family

ID=68281472

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19848803.3A Active EP3899207B1 (en) 2018-12-21 2019-12-20 Turbomachine assembly comprising fan blades with an extended trailing edge

Country Status (5)

Country Link
US (1) US11473430B2 (en)
EP (1) EP3899207B1 (en)
CN (1) CN113423921B (en)
FR (1) FR3090733B1 (en)
WO (1) WO2020128384A1 (en)

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7144221B2 (en) * 2004-07-30 2006-12-05 General Electric Company Method and apparatus for assembling gas turbine engines
US8016561B2 (en) * 2006-07-11 2011-09-13 General Electric Company Gas turbine engine fan assembly and method for assembling to same
JP5370046B2 (en) * 2009-09-25 2013-12-18 株式会社Ｉｈｉ Aircraft engine fan
US9121294B2 (en) * 2011-12-20 2015-09-01 General Electric Company Fan blade with composite core and wavy wall trailing edge cladding
US9399922B2 (en) * 2012-12-31 2016-07-26 General Electric Company Non-integral fan blade platform
WO2014137446A1 (en) * 2013-03-07 2014-09-12 United Technologies Corporation Hybrid fan blades for jet engines
GB201408824D0 (en) * 2014-05-19 2014-07-02 Rolls Royce Plc Fan disc
US10099434B2 (en) * 2014-09-16 2018-10-16 General Electric Company Composite airfoil structures
US9745851B2 (en) * 2015-01-15 2017-08-29 General Electric Company Metal leading edge on composite blade airfoil and shank
FR3038653B1 (en) * 2015-07-08 2017-08-04 Snecma ASSEMBLY OF A REPORTED PLATFORM OF BLOWER BLADE ON A BLOWER DISK
US10730112B2 (en) * 2016-08-02 2020-08-04 Raytheon Technologies Corporation Micro lattice hybrid composite fan blade
EP3409892B1 (en) * 2017-05-31 2020-07-15 Ansaldo Energia Switzerland AG Gas turbine blade comprising winglets to compensate centrifugal forces

Also Published As

Publication number Publication date
CN113423921A (en) 2021-09-21
WO2020128384A1 (en) 2020-06-25
FR3090733B1 (en) 2020-12-04
US11473430B2 (en) 2022-10-18
EP3899207A1 (en) 2021-10-27
CN113423921B (en) 2023-03-24
FR3090733A1 (en) 2020-06-26
US20220056803A1 (en) 2022-02-24

Similar Documents

Publication Publication Date Title
EP2673473B1 (en) Blade-platform assembly for supersonic flow
FR2971539A1 (en) PLATFORM BLADE ASSEMBLY FOR SUBSONIC FLOW
FR3082876A1 (en) BLOWER COMPRISING A PLATFORM AND A LOCKING LATCH
EP3409902B1 (en) Sealing system for a turbine engine compressor
FR2960603A1 (en) Radial diffuser for turboshaft engine e.g. turbojet of airplane, has slots whose shape and positioning are complementary to that of projecting portions such that projecting portions are embedded into slots
CA3059196A1 (en) Reinforced axial diffuser
EP3899207B1 (en) Turbomachine assembly comprising fan blades with an extended trailing edge
EP3781791B1 (en) Gas turbine vane having a passive system for reinjecting leakage gas into the gas path
EP3663530B1 (en) Fan comprising an inter-blade platform
FR3087831A1 (en) BLADE COMPRISING A COMPOSITE MATERIAL STRUCTURE AND A METAL STRAINING PART
FR3085415A1 (en) BLADE COMPRISING A COMPOSITE MATERIAL STRUCTURE AND A METAL HULL
WO2022106772A1 (en) Blade comprising a shield having a defrosting air passage duct
WO2017144805A1 (en) Rectifier for aircraft turbomachine compressor, comprising air extraction openings having a stretched form in the peripheral direction
FR3089258A1 (en) Blower comprising an inter-blade platform fixed radially by a sacrificial protective sheet
EP3683450A1 (en) Turbine engine rotor assembly
FR3116089A1 (en) Turbomachine rotary fan blade, fan and turbomachine provided with the same
WO2021044107A1 (en) Turbomachine polyspherical hub for variable pitch blades
FR3108665A1 (en) Fan rotor with upstream center of gravity vanes
FR3107301A1 (en) blade for a movable bladed wheel of an aircraft turbomachine comprising a sealing spoiler with an optimized scalable section
FR3108662A1 (en) Turbomachine rotary fan blade, fan and turbomachine fitted therewith
EP4010562B1 (en) Rotor blade for a rotor of an aircraft turbomachine, rotor for an aircraft turbomachine and aircraft turbomachine
EP3382155A1 (en) Sealing system for a turbomachine and corresponding turbomachine
EP3987155B1 (en) Method for coating a turbomachine guide vane and associated guide vane
EP3768950B1 (en) Bladed disk flexible in the lower part of the blades
FR3082871A1 (en) BLOWER COMPRISING A PLATFORM AND A LOCKING LATCH

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: 20210719

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

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

INTG Intention to grant announced

Effective date: 20220511

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

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: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602019017616

Country of ref document: DE

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1507189

Country of ref document: AT

Kind code of ref document: T

Effective date: 20220815

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: FRENCH

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

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: 20220727

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

Ref country code: SE

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

Effective date: 20220727

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: 20220727

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: 20221128

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: 20221027

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: 20220727

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: 20220727

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: 20220727

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: 20220727

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: 20220727

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1507189

Country of ref document: AT

Kind code of ref document: T

Effective date: 20220727

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: 20220727

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: 20221127

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: 20220727

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: 20221028

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: 20220727

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: 20220727

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: 20220727

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: 20220727

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: 20220727

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602019017616

Country of ref document: DE

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

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: 20220727

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: 20220727

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

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: 20220727

26N No opposition filed

Effective date: 20230502

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: 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: 20220831

Ref country code: LU

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

Effective date: 20221220

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: 20221220

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: 20231124

Year of fee payment: 5

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

Ref country code: FR

Payment date: 20231122

Year of fee payment: 5

Ref country code: DE

Payment date: 20231121

Year of fee payment: 5

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: 20220727

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: 20220727

Ref country code: IT

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

Effective date: 20220727

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: 20191220

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: 20220727

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: 20220727