EP2896796B1 - Stator of an axial turbomachine and corresponding turbomachine - Google Patents

Stator of an axial turbomachine and corresponding turbomachine Download PDF

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Publication number
EP2896796B1
EP2896796B1 EP14151761.5A EP14151761A EP2896796B1 EP 2896796 B1 EP2896796 B1 EP 2896796B1 EP 14151761 A EP14151761 A EP 14151761A EP 2896796 B1 EP2896796 B1 EP 2896796B1
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EP
European Patent Office
Prior art keywords
band
platform
stator
wall
ribbon
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
EP14151761.5A
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German (de)
French (fr)
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EP2896796A1 (en
Inventor
Jean-François Cortequisse
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aero Boosters SA
Original Assignee
Safran Aero Boosters SA
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Priority to EP14151761.5A priority Critical patent/EP2896796B1/en
Priority to CN201510011528.3A priority patent/CN104791303A/en
Publication of EP2896796A1 publication Critical patent/EP2896796A1/en
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Publication of EP2896796B1 publication Critical patent/EP2896796B1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position

Definitions

  • the invention relates to an axial turbomachine stator. More specifically, the invention relates to a compressor housing provided with an abradable axial turbomachine seal. The invention also relates to an axial turbomachine.
  • the English language expression "abradable” is commonly used to designate a friable material capable of ensuring a certain seal with a moving surface relative to this material.
  • This material can have various compositions, structures and shapes.
  • a wall, possibly external, of an axial turbomachine compressor provided with a layer of this material makes it possible to ensure rotary sealing with the ends of the rotor vanes of said compressor. This makes it possible to preserve the integrity of the assembly, despite the slight deformations inherent in the turbomachine, in particular deformations in elongation of the blades due to the centrifugal forces.
  • the efficiency and efficiency of the turbojet engine are increased.
  • compressors, blowers and turbines are equipped with gaskets.
  • Gaskets of abradable material are disposed on the stator surfaces and cooperate with the rotor.
  • abradable seals are disposed on the inner surface of the low-pressure compressor casing and seal with the rotor blades of the compressor.
  • crankcase of the compressor In order to lighten the crankcase of the compressor, it is known to produce it in a composite material with organic matrix and carbon fibers. Gold, adhesion between the abradable material and the crankcase composite material is low due to the differential expansion. To counter this effect, a metal strip is interposed between the housing and the abradable. The strip being glued to the composite housing, its surface is perforated to improve the anchoring of the glue to the strip.
  • the document EP 2418387 A1 discloses a composite casing of axial turbomachine compressor.
  • the housing comprises a plurality of annular rows of blades, a metal strip disposed between the rows of blades and a layer of abradable material applied to the inner surface of the strip.
  • the strip is glued to the inner surface of the housing wall.
  • the adhesion of the glue is limited. This attachment requires an additional mounting operation.
  • the glue must degas during its implementation, which requires some adaptations of the strip.
  • the document EP 0 713 977 A2 discloses a device for controlling the radial clearance around a blade in an axial compressor.
  • the latter comprises stator vanes whose platforms cover segments of joints.
  • the invention aims to solve at least one of the technical problems presented by the prior art, and possibly to retain at least one of the advantages mentioned.
  • the invention also aims to improve the maintenance of a circular ribbon receiving an abradable layer of an axial turbomachine stator.
  • the invention relates to an axial turbomachine stator according to claim 1, comprising in particular a generally circular wall with an inner surface; at least one annular row of stator vanes extending radially inwardly from the wall; a circular ribbon disposed against the inner surface of the wall, and having an inner surface and a surface external ; a layer of abradable material on the inner surface of the ribbon, adapted to cooperate by abrasion with rotor blades of the turbomachine; remarkable in that at least one of the stator vanes comprises a platform covering an edge of the ribbon so as to maintain it.
  • each blade platform comprises a portion of lesser thickness covering the inner surface of the edge of the ribbon so as to maintain it radially, preferably said portions are contiguous and form a tubular bearing fitted inside circular ribbon.
  • At least one or each portion of lesser platform thickness is in axial contact with the abradable layer, and preferably has a thickness substantially equal to the thickness of the abradable layer.
  • the ribbon comprises a circular upstream edge and a circular downstream edge
  • the or each blade platform comprises a radial shoulder which cooperates with one of the circular edges of the ribbon so as to maintain it axially, possibly the radial height of each shoulder is substantially less than the thickness of the ribbon.
  • the abradable layer and the blade platform or platforms cover the entire internal surface of the ribbon.
  • the majority, preferably all of the outer surface of the ribbon wife the inner surface of the wall.
  • the ribbon is axially longer than the abradable layer, and preferably the ribbon projects axially upstream and downstream of the abradable layer.
  • the ribbon is thinner than each platform, preferably at least five times thinner, more preferably at least ten times thinner.
  • At least one or each platform cooperates by contact with the internal surface of the ribbon over an axial length greater than the thickness of the ribbon, preferentially the axial length of the contact is between five and fifty times the thickness of the ribbon.
  • each platform comprises clamping means for fixing on the wall, the area of the inner surface of the ribbon which is covered by each platform is deformed, possibly by work hardening.
  • the wall and each platform form a hook with a cavity whose interior volume is predominantly, preferably totally occupied by the ribbon.
  • the stator vanes each comprise a leading edge and a trailing edge, the ribbon extending axially from the leading edges or vanes trailing edges towards the outside of the vehicle.
  • the platform that covers it; and / or each platform comprises an upstream edge and a downstream edge, the ribbon extending axially towards the outside of the platform which covers it from the upstream edge or the downstream edge of said platform.
  • the row of stator vanes is a first row, the wall further comprising a second annular row of stator vanes, said rows being successive stator rows between which is arranged the ribbon, preferably the stator comprises a plurality of annular rows of stator vanes and a plurality of circular ribbons, the rows of stator vanes and the ribbons being arranged alternately.
  • the ribbon comprises at least one series of perforations arranged in several annular rows of perforations, each platform covers the inner surface of the ribbon on at least five rows of perforations, preferably on at least ten rows of perforations. .
  • each platform (36) comprises titanium; the ribbon is a metal strip of steel or titanium, or an alloy of iron and nickel; the wall is made of a composite material, preferably with a fiber preform and a matrix organic ; the abradable layer comprises an abradable material of the AI-Si Polyester type.
  • the wall and / or the ribbon is / are generally tubular (s).
  • the inner surface and the outer surface of the ribbon are oriented radially in opposite directions.
  • the Al-Si Polyester type abradable material is projected by plasma.
  • the wall comprises fixing means, such as orifices, which cooperate with the clamping means of each platform.
  • the hook is an annular hook.
  • the platform covers the inner surface of the strip over an axial length of between 1% and 20% of the axial length of the strip, preferably between 3% and 8%.
  • the blades are only fixed to the wall.
  • the ribbon extends axially over between 2% and 50% of the axial length of the wall, preferably between 4% and 30%, more preferably between 6% and 15%.
  • the wall has a generally constant thickness.
  • the ribbon revolution profile is inclined relative to the turbomachine rotation axis by an angle greater than 2 °, preferably greater than 5 °, more preferably greater than 10 °.
  • the circular ribbon has a constant thickness of between 0.05 mm and 2.00 mm; preferably between 0.10 mm and 0.60 mm; more preferably between 0.15 mm and 0.25 mm.
  • the wall is made of material, possibly the wall and at least one stator flange are made of material.
  • the perforations form at least one perforated annular zone
  • the platform extends axially over the majority of the axial length of one of the at least one perforated zone.
  • the invention also relates to an axial turbomachine compressor provided with an axial turbomachine stator, remarkable in that the stator is in accordance with the invention, preferably the wall extends axially over most of the length of the compressor.
  • the invention also relates to an axial turbomachine comprising a stator, remarkable in that the stator is in accordance with the invention, preferably the turbomachine comprises at least one turbine and / or at least one compressor, the wall being a wall of a turbine and extends over most of the axial length of the turbine, where the wall is a wall of the compressor and extends over most of the axial length of the compressor, more preferably the compressor is a low pressure compressor.
  • the turbomachine is a turbojet engine.
  • the invention proposes a simple and effective fastening of the ribbon. It can form two annular hooks that can pinch each ribbon. The latter is maintained at its upstream and downstream circular edges. This maintenance solution eliminates glue, and thus chemical problems.
  • the invention employs clamping means which may be reversible securing means simplifying the replacement of the abradable layer and / or ribbon.
  • the assembly is fast and economical since it reduces the number of assembly operations.
  • the method of attachment is compact because it does not increase the axial thickness of the wall and platforms.
  • the ribbon forms a support and a mark for the angular orientation of the stator vanes. It provides support circles ideally oriented relative to the axis of rotation, which is particularly effective for blades each substantially fixed to the wall using an axis.
  • the contact between the shoulders and a ribbon also makes it possible to position them axially. By this means, it is possible to precisely position two rows of successive stator vanes with respect to one another, for example when the vanes are fixed to the wall via orifices with mechanical clearances.
  • inner or inner and outer or outer refer to a positioning relative to the axis of rotation of an axial turbomachine.
  • the axial direction is along the axis of rotation of the turbomachine, the radial direction is perpendicular to the axis of rotation.
  • the figure 1 represents in simplified manner an axial turbomachine. It is in this case a double-flow turbojet engine.
  • the turbojet engine 2 comprises a first compression level, called a low-pressure compressor 4, a second compression level, called a high-pressure compressor 6, a combustion chamber 8 and one or more levels of turbines 10.
  • a first compression level called a low-pressure compressor 4
  • a second compression level called a high-pressure compressor 6
  • a combustion chamber 8 and one or more levels of turbines 10.
  • the mechanical power of the turbine 10 transmitted via the central shaft to the rotor 12 sets in motion the two compressors 4 and 6.
  • the latter comprise several rows of rotor blades associated with rows of stator vanes.
  • the rotation of the rotor about its axis of rotation 14 thus makes it possible to generate an air flow and to compress it progressively until it reaches the combustion chamber 8.
  • An inlet fan commonly referred to as a blower 16 or a fan, is coupled to the rotor 12 and generates a stream of air that splits into a primary stream 18 passing through the above-mentioned levels of the turbomachine, and a secondary stream 20 passing through an annular duct. (partially shown) along the machine to then join the primary flow at the turbine outlet.
  • the figure 2 is a sectional view of a compressor of an axial turbomachine 2 such as that of the figure 1 .
  • the compressor may be a low-pressure compressor 4.
  • the rotor 12 comprises several rows of rotor blades 24, occurrence three.
  • the compressor includes a stator.
  • the stator comprises at least one annular row of stator vanes 26, in this case four.
  • Each row of blades is optionally provided with an inner ferrule with an inner layer of abradable.
  • Each row of stator vanes 26 may form a rectifier associated with the blower 16, or a row of compressor rotor blades so as to rectify the airflow to convert the speed of the flow into pressure.
  • the stator may comprise a housing 28.
  • the housing may comprise a wall 30 and / or at least one, preferably at least two radially extending annular flanges 32 which are arranged upstream and downstream of the wall 30.
  • a flange 32 can be used for fixing the separation spout 22 and / or the attachment of the compressor 4 on an intermediate casing 34 of the turbomachine.
  • the wall 30 includes an inner surface and an outer surface. It can be formed of two half-shells separated by an axially extending plane.
  • the stator vanes 26 extend substantially radially from the inner surface of the wall 30. They are regularly spaced from each other, and have for each row the same angular orientation in the flow.
  • the blades of the same row can be identical.
  • At least one stator blade 26, preferably each stator blade 26 comprises an outer platform 36 and a blade extending in the primary flow from the associated platform 36, for example perpendicularly.
  • Each platform 36 may be made of metal, such as titanium.
  • Each platform 36 may be disposed against the inner surface of the wall 30.
  • the blade platforms 36 form at least one, preferably several annular rows of platforms.
  • Each platform 36 may comprise clamping means 38 for fixing the vanes 26 to the wall 30.
  • the associated clamping means 38 at each blade may comprise an axis, such as a threaded shaft or a lockbolt.
  • two axes of clamping means are associated with the same blade.
  • the stator vanes can share the same platform, and / or the same clamping means.
  • the wall 30 may have a profile of revolution with respect to the axis 14, it may generally have a circular shape, or a tubular shape, or an ogival shape with a variation of its radius along the axis 14. This evolution of the radius can be reversed.
  • the outer surface of the wall 30 may define a free annular outer space, which is preferably predominantly empty, which may extend over most of its length.
  • the wall 30 may be made of a composite material, and may be manufactured by injection according to a method of the RTM (acronym for Resin Transfer Molding) type.
  • a composite material may comprise a matrix and a fibrous reinforcement.
  • the matrix may comprise an organic material, such as a thermosetting material, possibly epoxy.
  • the fibers may be in the form of a fibrous preform.
  • a preform may comprise a three-dimensionally woven fiber mat, and / or a stack of fiber plies or fiber sheets comprising fibers arranged in fiber bundles woven in at least two directions.
  • the fibers may be carbon fibers and / or glass fibers.
  • the wall may be made using a resin filled with fibers, for example based on a thermoplastic material, optionally with polyetherimide (PEI) and / or polyetheretherketone (PEEK).
  • the fibers may be dissociated fibers, with a length of less than 3.00 mm, preferably less than 0.50 mm.
  • the stator comprises a circular ribbon 40 with an inner surface and an outer surface, which are generally radially oriented.
  • the ribbon 40 may be disposed inside the wall 30, possibly on the inner surface of the wall 30.
  • the stator may comprise a plurality of annular ribbons on the wall 30, possibly spaced apart and / or distributed axially along the wall 30 Ribbons and annular rows of platforms are arranged alternately.
  • the stator comprises at least one layer, optionally circular, of abradable material 42, preferably several layers, possibly circular, of abradable material 42.
  • Each abradable layer 42 is intended to cooperate by abrasion with rotor blades 24 so as to allow seal.
  • Each abradable layer 42 may be disposed on each internal ribbon surface 40 of the housing. The strips may make it possible to improve the cohesion of the abradable layers 42 on the wall 30, possibly by forming an interlayer whose coefficient of expansion represents between 10% and 500%, preferably between 50% and 200% of the expansion coefficient of the abradable.
  • Each abradable layer 40 may be deposited by plasma spraying on a ribbon.
  • the figure 3 represents a stator portion of the turbomachine.
  • a ribbon is disposed within the wall and receives an abradable layer.
  • a rotor blade 24 and two stator blades 26 with their platforms are visible.
  • the ribbon may comprise perforations 52, possibly aligned, for example according to a regular mesh.
  • the ribbon 40 can comprise a circular upstream edge 46 and a circular downstream edge 48, which may each describe a circle.
  • the ribbon can be a strap. It can be a band that forms a loop.
  • the ribbon 40 may comprise a metallic material, such as steel, titanium, a nickel alloy, or an alloy of these materials. It may be made of a material different from the wall 30. It has a constant thickness. Its thickness may be between 0.05 mm and 3 mm, preferably between 0.15 mm and 0.25 mm.
  • At least one platform 36 of stator blade 26 cooperates with the ribbon 40 in order to maintain it, for example axially and / or radially since the platform 36 is fixed to the wall 40.
  • each stator blade of a row of blades comprises a platform which cooperates with the ribbon in order to maintain it, possibly each stator blade of each row of vanes mounted on the wall comprises a blade platform which cooperates with the ribbon in order to maintain it.
  • At least one or each platform 36 can cooperate with the tape by contact with its inner surface 50 and / or by covering it.
  • the or each ribbon cover may be at one of the upstream or downstream edges of each ribbon.
  • At least one or each platform 36 may have at least one zone of lesser thickness 54 cooperating with the ribbon 40, for example by contacting its inner surface 50. At least one or each zone of lesser thickness 54 may be mainly disposed on the surface internal 50 of the ribbon 40.
  • each platform 36 of one or each row of stator blades 26 bonded to the wall 30 has a thinner portion 54, thus forming at least one or more tubular bearings, for example fitted into an internal surface 50 of ribbon 40.
  • Each blade platform 36 may be in contact with the abradable 42 and / or plug perforations 52, possibly via its zone of smaller thickness 54.
  • the inner surface 50 of the ribbon 40 may completely covered by the abradable 42 and the platform or platforms 36 cooperating with the ribbon, thus creating a tight barrier.
  • At least one or each platform 36 may have at least one radial shoulder 56 which cooperates, possibly by contact with one of the upstream edges 46 or downstream 48 of the ribbon 40, for example to form an axial abutment.
  • each platform 36 of one or each row of blades connected to the wall 30 has at least one radial shoulder 56, preferably at least two shoulders.
  • Each platform 36, in combination with the wall 30, may form an open hook towards the ribbon 40.
  • Each hook has a cavity which may be predominantly, preferably totally occupied by the ribbon 40.
  • Each blade of the same row may comprise a platform, so as to form an annular cavity in combination with the wall; possibly using the smaller thickness portions 54 and / or the shoulders 56.
  • At least one or each platform 36 covers, for example with contact, with the ribbon 40 over an axial length greater than the thickness of the ribbon 40, preferably the axial contact between the platform 36 and the ribbon 40 is between five and fifty times, more preferably between fifteen and thirty times the thickness of the ribbon 40.
  • this embodiment essentially forms a heterogeneous material with a metal phase deposited by thermal spraying, more particularly by plasma spraying.
  • This material may be of the Al-Si-Polyester type.
  • Plasma spraying is a technique used to manufacture powder metallurgy and is used to produce a large number of highly abradable materials.
  • the plasma is generated by concentric electrodes subjected to a high electrical potential difference and a strong direct current, which ionize an inert gas (nitrogen, argon, helium) and make it reach a high pressure and an extremely high temperature (over 16 000 [deg.] C for a current of 1000 A).
  • a flow of powder is then injected into the conduit and driven by the plasma. This technique makes it possible to melt any metal, even the most refractory given the temperatures reached.
  • FIG 4 sketch a portion of stator according to the invention.
  • a platform 36 of stator vane 26 can cooperate with two ribbons 40 in order to maintain them, said ribbons 40 each receiving an abradable layer 42.
  • the wall 30 may have fixing means 58, such fixing holes 58, which cooperate with the clamping means 38 of the platforms 36 of the blade 26.
  • the fastening means 58 may comprise inserts (not shown). When tightening the clamping means 38, each platform 36 can press against the inner surface 50 of the ribbon 40 and exert a stress. The ribbon can then be deformed, for example elastically, possibly by work hardening.
  • the ribbon 40 may have been sandblasted beforehand.
  • At least one or each blade platform 26, and / or each minor zone 54 of platform 36 is thicker than the ribbon 40.
  • the ribbon 40 may be at least twenty times thinner than the platforms 36.
  • a platform blade can be a fixing platform and / or a plate and / or present a body with a general shape of polyhedron, such as a polyhedron or parallelepiped, optionally rectangle base or parallelogram.
  • the body may be generally a hexahedron whose outer edges upstream and downstream are cut in the form of a step.
  • the thickness is measured radially, possibly perpendicular to the inner surface of the wall, it may be the average thickness.
  • the difference in thickness between a platform and the ribbon promotes rigidity of the platform and deformability of the ribbon; thus a platform allows a firmer maintenance of the ribbon.
  • the shoulder 56 may be of radial height less than the thickness of the ribbon 40.
  • the organic matrix composite wall 30 and the metal ribbon 40 may have a radial depression 60 in the wall 30, thus improving its thickness. axial anchoring, possibly further improved by the perforations 52 in which the material of the wall is encrusted.
  • Each stator vane 26 has a leading edge 62 and a trailing edge 64, which may be curved and / or inclined relative to the radial direction. At least one of the ribbons 40 or each ribbon 40 may extend axially in a direction opposite to the platform 36 which covers it from one of the leading edges 62 or trailing edge 64. One of the upstream or downstream edges 46 of one of the ribbons 40 may be disposed axially of the leading edge 62 or the trailing edge 64 of the stator blade 26. By thus disposing the ribbon 40, the blade of the blade 26 stiffens the platform 36 and limits its flexion. The ribbon is held more firmly, which may be advantageous because of the vibrations of the turbomachine. The compactness of the assembly is also improved.
  • At least one or each platform 36 of stator blade 26 has an upstream edge 66 and an axially opposite downstream edge 68. These edges are delimited respectively by the leading edge 62 of the blade and the upstream platform end 70; and by the trailing edge 64 of the blade and the downstream end 72 of the platform.
  • the upstream and downstream ends 70 and 72 may be parallel, and may be abradable layers in contact with the layers 42.
  • At least one of the tapes 40 or each tape 40 may extend axially in a direction opposite to the platform 36 which covers since the upstream edge 66 or the downstream edge 68 of the platform 36. This configuration limits the form of walking that the platform presents and preserves its intrinsic rigidity.
  • the figure 5 illustrates and a circular ribbon 40 disposed between two annular rows of platforms 36 of stator vanes 26 seen radially from the outside, the wall not being shown.
  • the configuration of the platforms 36 and / or blades 26 with respect to the upstream edges 46 and downstream 48 of the ribbon may be mixed.
  • the upstream edge 46 of the ribbon 40 may be further upstream than the trailing edge 64 of the stator vane 26 whose platform 36 covers its inner surface, and the downstream edge 48 may be further upstream than the leading edge 62 of the dawn whose platform covers its internal surface.
  • the ribbon 40 may have several circular zones, for example at least one or two perforated zones, namely a first upstream perforated zone 74 and a second downstream perforated zone 76, and at least one smooth zone 78 disposed axially between the perforated zones (74). 76). Each smooth zone 78 may be united, and / or homogeneous, at any point. Each perforated zone (74; 76) has a series of perforations 52 distributed over its surface.
  • the perforations 52 can pass through the ribbon and can be made by laser, by punching, by machining.
  • At least one or each perforated zone (74; 76) may comprise at least one perforation 52 per cm 2, preferably at least twenty perforations per cm 2, more preferably at least one hundred perforations per cm 2.
  • At least one or each perforated zone (74; 76) may comprise perforations 52 having a diameter less than or equal to 3.00 mm, preferably less than or equal to 0.60 mm, more preferably less than or equal to 0.05 mm.
  • Each perforated zone (74; 76) may represent between 1% and 30%, preferably between 5% and 15% of the internal surface of the strip 40. At least one or each blade platform 36 extends axially over at least 10 %, preferably on the majority, possibly on the axial totality of an associated perforated zone; for example because of its smaller area. Perforations 52 of at least one or each perforated area (74; 76) are arranged in annular rows. The perforations may form at least two, or at least seven, or at least twenty, or at least fifty annular rows of perforations. At least one or each blade platform extends axially along at least 10%, preferably the majority, possibly all the rows of perforations; for example because of its smaller area.
  • the characteristics described are applicable to a compressor as well as to a turbomachine turbine.

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  • General Engineering & Computer Science (AREA)
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Description

Domaine techniqueTechnical area

L'invention a trait à un stator de turbomachine axiale. Plus précisément, l'invention a trait à un carter de compresseur muni d'un joint abradable de turbomachine axiale. L'invention a également trait à une turbomachine axiale.The invention relates to an axial turbomachine stator. More specifically, the invention relates to a compressor housing provided with an abradable axial turbomachine seal. The invention also relates to an axial turbomachine.

Il est à noter que l'expression de langue anglaise " abradable " est communément utilisée pour désigner un matériau friable apte à assurer une certaine étanchéité avec une surface mobile par rapport à ce matériau. Ce matériau peut présenter diverses compositions, structures et formes. A titre d'exemple, une paroi, éventuellement externe, de compresseur de turbomachine axiale, pourvue d'une couche de ce matériau permet d'assurer une étanchéité tournante avec les extrémités des aubes rotoriques dudit compresseur. Cela permet de conserver l'intégrité de l'ensemble et ce malgré les déformations, mêmes légères, inhérentes à la turbomachine, notamment des déformations en élongation des aubes en raison des forces centrifuges. En réduisant au minimum le jeu entre les aubes mobiles et le carter de la veine fluide, on augmente l'efficacité et le rendement du turboréacteur.It should be noted that the English language expression "abradable" is commonly used to designate a friable material capable of ensuring a certain seal with a moving surface relative to this material. This material can have various compositions, structures and shapes. By way of example, a wall, possibly external, of an axial turbomachine compressor provided with a layer of this material makes it possible to ensure rotary sealing with the ends of the rotor vanes of said compressor. This makes it possible to preserve the integrity of the assembly, despite the slight deformations inherent in the turbomachine, in particular deformations in elongation of the blades due to the centrifugal forces. By reducing to a minimum the clearance between the blades and the casing of the fluid stream, the efficiency and efficiency of the turbojet engine are increased.

Technique antérieurePrior art

Afin d'augmenter le rendement d'une turbomachine, les compresseurs, les soufflantes, les turbines sont équipés de joints. Des joints en matériau abradable sont disposés sur les surfaces de stator et coopèrent avec le rotor. En particulier, des joints en abradable sont disposés sur la surface interne du carter du compresseur basse pression et assurent l'étanchéité avec les aubes rotoriques du compresseur.In order to increase the efficiency of a turbomachine, compressors, blowers and turbines are equipped with gaskets. Gaskets of abradable material are disposed on the stator surfaces and cooperate with the rotor. In particular, abradable seals are disposed on the inner surface of the low-pressure compressor casing and seal with the rotor blades of the compressor.

Afin d'alléger le carter du compresseur, il est connu de le réaliser en un matériau composite à matrice organique et en fibres de carbone. Or, l'adhésion entre le matériau abradable et le matériau composite du carter est faible à cause de la dilatation différentielle. Pour contrer cet effet, un feuillard métallique est intercalé entre le carter et l'abradable. Le feuillard étant collé au carter composite, sa surface est perforée afin d'améliorer l'ancrage de la colle au feuillard.In order to lighten the crankcase of the compressor, it is known to produce it in a composite material with organic matrix and carbon fibers. Gold, adhesion between the abradable material and the crankcase composite material is low due to the differential expansion. To counter this effect, a metal strip is interposed between the housing and the abradable. The strip being glued to the composite housing, its surface is perforated to improve the anchoring of the glue to the strip.

Le document EP 2418 387 A1 divulgue un carter composite de compresseur de turbomachine axiale. Le carter comprend plusieurs rangées annulaires d'aubes, un feuillard métallique disposé entre les rangées d'aubes et une couche de matériau abradable appliquée sur la surface interne du feuillard. Afin de le fixer, le feuillard est collé à la surface interne de la paroi du carter. Or, l'adhésion de la colle est limitée. Cette fixation nécessite une opération de montage supplémentaire. De plus, la colle doit dégazer lors de sa mise en oeuvre, ce qui demande certaines adaptations du feuillard.The document EP 2418387 A1 discloses a composite casing of axial turbomachine compressor. The housing comprises a plurality of annular rows of blades, a metal strip disposed between the rows of blades and a layer of abradable material applied to the inner surface of the strip. In order to fix it, the strip is glued to the inner surface of the housing wall. However, the adhesion of the glue is limited. This attachment requires an additional mounting operation. In addition, the glue must degas during its implementation, which requires some adaptations of the strip.

Le document EP 0 713 977 A2 divulgue un dispositif de contrôle du jeu radial autour d'un aubage dans un compresseur axial. Ce dernier comporte des aubes statoriques dont les plateformes recouvrent des segments de joints.The document EP 0 713 977 A2 discloses a device for controlling the radial clearance around a blade in an axial compressor. The latter comprises stator vanes whose platforms cover segments of joints.

Résumé de l'inventionSummary of the invention Problème techniqueTechnical problem

L'invention a pour objectif de résoudre au moins un des problèmes techniques présenté par l'art antérieur, et éventuellement de conserver au moins un des avantages cités. L'invention a également pour objectif d'améliorer le maintien d'un ruban circulaire recevant une couche d'abradable d'un stator de turbomachine axiale.The invention aims to solve at least one of the technical problems presented by the prior art, and possibly to retain at least one of the advantages mentioned. The invention also aims to improve the maintenance of a circular ribbon receiving an abradable layer of an axial turbomachine stator.

Solution techniqueTechnical solution

L'invention a trait à un stator de turbomachine axiale selon la revendication 1, comprenant notamment une paroi généralement circulaire avec une surface intérieure ; au moins une rangée annulaire d'aubes statoriques s'étendant radialement vers l'intérieur depuis la paroi ; un ruban circulaire disposé contre la surface intérieure de la paroi, et comportant une surface interne et une surface externe ; une couche de matériau abradable sur la surface interne du ruban, apte à coopérer par abrasion avec des aubes rotoriques de la turbomachine; remarquable en ce qu'au moins une des aubes statoriques comprend une plateforme recouvrant un bord du ruban de sorte à le maintenir.The invention relates to an axial turbomachine stator according to claim 1, comprising in particular a generally circular wall with an inner surface; at least one annular row of stator vanes extending radially inwardly from the wall; a circular ribbon disposed against the inner surface of the wall, and having an inner surface and a surface external ; a layer of abradable material on the inner surface of the ribbon, adapted to cooperate by abrasion with rotor blades of the turbomachine; remarkable in that at least one of the stator vanes comprises a platform covering an edge of the ribbon so as to maintain it.

Selon un mode avantageux de l'invention, chaque plateforme d'aube comporte une portion de moindre épaisseur recouvrant la surface interne du bord du ruban de sorte à le maintenir radialement, préférentiellement lesdites portions sont jointives et forment une portée tubulaire emmanchée à l'intérieur du ruban circulaire.According to an advantageous embodiment of the invention, each blade platform comprises a portion of lesser thickness covering the inner surface of the edge of the ribbon so as to maintain it radially, preferably said portions are contiguous and form a tubular bearing fitted inside circular ribbon.

Selon un mode avantageux de l'invention, au moins une ou chaque portion de moindre épaisseur de plateforme est en contact axialement de la couche d'abradable, et présente préférentiellement une épaisseur essentiellement égale à l'épaisseur de la couche d'abradable.According to an advantageous embodiment of the invention, at least one or each portion of lesser platform thickness is in axial contact with the abradable layer, and preferably has a thickness substantially equal to the thickness of the abradable layer.

Selon un mode avantageux de l'invention, le ruban comprend un bord amont circulaire et un bord aval circulaire, la ou chaque plateforme d'aube comporte un épaulement radial qui coopère avec un des bords circulaires du ruban de sorte à le maintenir axialement, éventuellement la hauteur radiale de chaque épaulement est sensiblement inférieure à l'épaisseur du ruban.According to an advantageous embodiment of the invention, the ribbon comprises a circular upstream edge and a circular downstream edge, the or each blade platform comprises a radial shoulder which cooperates with one of the circular edges of the ribbon so as to maintain it axially, possibly the radial height of each shoulder is substantially less than the thickness of the ribbon.

Selon un mode avantageux de l'invention, la couche d'abradable et la ou les plateformes d'aubes recouvrent toute la surface interne du ruban. Selon l'invention la majorité, préférentiellement la totalité de la surface externe du ruban épouse la surface intérieure de la paroi.According to an advantageous embodiment of the invention, the abradable layer and the blade platform or platforms cover the entire internal surface of the ribbon. According to the invention the majority, preferably all of the outer surface of the ribbon wife the inner surface of the wall.

Selon un mode avantageux de l'invention, le ruban est plus long axialement que la couche d'abradable, préférentiellement le ruban dépasse axialement en amont et en aval de la couche d'abradable.According to an advantageous embodiment of the invention, the ribbon is axially longer than the abradable layer, and preferably the ribbon projects axially upstream and downstream of the abradable layer.

Selon un mode avantageux de l'invention, le ruban est moins épais que chaque plateforme, préférentiellement au moins cinq fois moins épais, plus préférentiellement au moins dix fois moins épais.According to an advantageous embodiment of the invention, the ribbon is thinner than each platform, preferably at least five times thinner, more preferably at least ten times thinner.

Selon un mode avantageux de l'invention, au moins une ou chaque plateforme coopère par contact avec la surface interne du ruban sur une longueur axiale supérieure à l'épaisseur du ruban, préférentiellement la longueur axiale du contact représente entre cinq et cinquante fois l'épaisseur du ruban.According to an advantageous embodiment of the invention, at least one or each platform cooperates by contact with the internal surface of the ribbon over an axial length greater than the thickness of the ribbon, preferentially the axial length of the contact is between five and fifty times the thickness of the ribbon.

Selon l'invention, chaque plateforme comprend des moyens de serrage permettant une fixation sur la paroi, la zone de la surface interne du ruban qui est recouverte par chaque plateforme est déformée, éventuellement par écrouissage.According to the invention, each platform comprises clamping means for fixing on the wall, the area of the inner surface of the ribbon which is covered by each platform is deformed, possibly by work hardening.

Selon un mode avantageux de l'invention, la paroi et chaque plateforme forment un crochet avec une cavité dont le volume intérieur est majoritairement, préférentiellement totalement occupé par le ruban.According to an advantageous embodiment of the invention, the wall and each platform form a hook with a cavity whose interior volume is predominantly, preferably totally occupied by the ribbon.

Selon un mode avantageux de l'invention, les aubes statoriques comprennent chacune un bord d'attaque et un bord de fuite, le ruban s'étendant axialement depuis les bords d'attaque ou les bords de fuite d'aubes vers l'extérieur de la plateforme qui le recouvre ; et/ou chaque plateforme comprend un bord amont et un bord aval, le ruban s'étendant axialement vers l'extérieur de la plateforme qui le recouvre depuis le bord amont ou le bord aval de ladite plateforme.According to an advantageous embodiment of the invention, the stator vanes each comprise a leading edge and a trailing edge, the ribbon extending axially from the leading edges or vanes trailing edges towards the outside of the vehicle. the platform that covers it; and / or each platform comprises an upstream edge and a downstream edge, the ribbon extending axially towards the outside of the platform which covers it from the upstream edge or the downstream edge of said platform.

Selon un mode avantageux de l'invention, la rangée d'aube statoriques est une première rangée, la paroi comprenant en outre une deuxième rangée annulaire d'aubes statoriques, lesdites rangées étant des rangées statoriques successives entres lesquelles est disposé le ruban, préférentiellement le stator comprend une pluralité de rangées annulaires d'aubes statoriques et une pluralité de rubans circulaires, les rangées d'aubes statoriques et les rubans étant disposés par alternance.According to an advantageous embodiment of the invention, the row of stator vanes is a first row, the wall further comprising a second annular row of stator vanes, said rows being successive stator rows between which is arranged the ribbon, preferably the stator comprises a plurality of annular rows of stator vanes and a plurality of circular ribbons, the rows of stator vanes and the ribbons being arranged alternately.

Selon un mode avantageux de l'invention, le ruban comprend au moins une série de perforations disposées en plusieurs rangées annulaires de perforations, chaque plateforme recouvre la surface interne du ruban sur au moins cinq rangées de perforations, préférentiellement sur au moins dix rangées de perforations.According to an advantageous embodiment of the invention, the ribbon comprises at least one series of perforations arranged in several annular rows of perforations, each platform covers the inner surface of the ribbon on at least five rows of perforations, preferably on at least ten rows of perforations. .

Selon un mode avantageux de l'invention, chaque plateforme (36) comprend du titane ; le ruban est un feuillard métallique en acier ou en titane, ou en alliage de fer et nickel ; la paroi est réalisée en un matériau composite, de préférence avec une préforme fibreuse et une matrice organique ; la couche d'abradable comprend un matériau abradable du type AI-Si Polyester.According to an advantageous embodiment of the invention, each platform (36) comprises titanium; the ribbon is a metal strip of steel or titanium, or an alloy of iron and nickel; the wall is made of a composite material, preferably with a fiber preform and a matrix organic ; the abradable layer comprises an abradable material of the AI-Si Polyester type.

Selon un mode avantageux de l'invention, la paroi et/ou le ruban est/sont généralement tubulaire(s).According to an advantageous embodiment of the invention, the wall and / or the ribbon is / are generally tubular (s).

Selon un mode avantageux de l'invention, la surface interne et la surface externe du ruban sont orientées radialement dans des sens opposés.According to an advantageous embodiment of the invention, the inner surface and the outer surface of the ribbon are oriented radially in opposite directions.

Selon un mode avantageux de l'invention, l'abradable du type Al-Si Polyester est projeté par plasma.According to an advantageous embodiment of the invention, the Al-Si Polyester type abradable material is projected by plasma.

Selon un mode avantageux de l'invention, la paroi comprend des moyens de fixation, tels des orifices, qui coopèrent avec les moyens de serrage de chaque plateforme.According to an advantageous embodiment of the invention, the wall comprises fixing means, such as orifices, which cooperate with the clamping means of each platform.

Selon un mode avantageux de l'invention, le crochet est un crochet annulaire.According to an advantageous embodiment of the invention, the hook is an annular hook.

Selon un mode avantageux de l'invention, la plateforme recouvre la surface interne du ruban sur une longueur axiale comprise entre 1% et 20% de la longueur axiale du ruban, préférentiellement comprise entre 3% et 8%.According to an advantageous embodiment of the invention, the platform covers the inner surface of the strip over an axial length of between 1% and 20% of the axial length of the strip, preferably between 3% and 8%.

Suivant un mode avantageux de l'invention, les aubes sont uniquement fixées à la paroi.According to an advantageous embodiment of the invention, the blades are only fixed to the wall.

Suivant un mode avantageux de l'invention, le ruban s'étend axialement sur entre 2% et 50% de la longueur axiale de la paroi, préférentiellement entre 4% et 30%, plus préférentiellement entre 6% et 15%.According to an advantageous embodiment of the invention, the ribbon extends axially over between 2% and 50% of the axial length of the wall, preferably between 4% and 30%, more preferably between 6% and 15%.

Suivant un mode avantageux de l'invention, la paroi présente une épaisseur généralement constante.According to an advantageous embodiment of the invention, the wall has a generally constant thickness.

Suivant un mode avantageux de l'invention, le profil de révolution du ruban est incliné par rapport à l'axe de rotation de turbomachine d'un angle supérieur à 2°, préférentiellement supérieur à 5°, plus préférentiellement supérieur à 10°.According to an advantageous embodiment of the invention, the ribbon revolution profile is inclined relative to the turbomachine rotation axis by an angle greater than 2 °, preferably greater than 5 °, more preferably greater than 10 °.

Suivant un mode avantageux de l'invention, le ruban circulaire présente une épaisseur constante comprise entre 0,05 mm et 2,00 mm ; préférentiellement comprise entre 0,10 mm et 0,60mm; plus préférentiellement comprise entre 0,15 mm et 0,25 mm.According to an advantageous embodiment of the invention, the circular ribbon has a constant thickness of between 0.05 mm and 2.00 mm; preferably between 0.10 mm and 0.60 mm; more preferably between 0.15 mm and 0.25 mm.

Selon un mode avantageux de l'invention, la paroi est venue de matière, éventuellement la paroi et au moins une bride de stator sont venues de matière.According to an advantageous embodiment of the invention, the wall is made of material, possibly the wall and at least one stator flange are made of material.

Selon un mode avantageux de l'invention, les perforations forment au moins une zone annulaire perforée, la plateforme s'étend axialement sur la majorité de la longueur axiale d'une des au moins une zone perforée.According to an advantageous embodiment of the invention, the perforations form at least one perforated annular zone, the platform extends axially over the majority of the axial length of one of the at least one perforated zone.

L'invention a également trait à un compresseur de turbomachine axiale muni d'un stator de turbomachine axiale, remarquable en ce que le stator est conforme à l'invention, préférentiellement la paroi s'étend axialement sur la majorité de la longueur du compresseur.The invention also relates to an axial turbomachine compressor provided with an axial turbomachine stator, remarkable in that the stator is in accordance with the invention, preferably the wall extends axially over most of the length of the compressor.

L'invention a également trait à une turbomachine axiale comprenant un stator, remarquable en ce que le stator est conforme à l'invention, préférentiellement la turbomachine comprend au moins une turbine et/ou au moins un compresseur, la paroi étant une paroi d'une turbine et s'étend sur la majorité de la longueur axiale de la turbine, ou la paroi étant une paroi du compresseur et s'étend sur la majorité de la longueur axiale du compresseur, plus préférentiellement le compresseur est un compresseur basse pression.The invention also relates to an axial turbomachine comprising a stator, remarkable in that the stator is in accordance with the invention, preferably the turbomachine comprises at least one turbine and / or at least one compressor, the wall being a wall of a turbine and extends over most of the axial length of the turbine, where the wall is a wall of the compressor and extends over most of the axial length of the compressor, more preferably the compressor is a low pressure compressor.

Selon un mode avantageux de l'invention, la turbomachine est un turboréacteur.According to an advantageous embodiment of the invention, the turbomachine is a turbojet engine.

Avantages apportésBenefits brought

L'invention propose une fixation simple et efficace du ruban. Elle peut former deux crochets annulaires qui peuvent pincer chaque ruban. Ce dernier est maintenu au niveau de ses bords circulaires amont et aval. Cette solution de maintien permet de s'affranchir de colle, et donc des problèmes chimiques liés.The invention proposes a simple and effective fastening of the ribbon. It can form two annular hooks that can pinch each ribbon. The latter is maintained at its upstream and downstream circular edges. This maintenance solution eliminates glue, and thus chemical problems.

L'invention emploie des moyens de serrage qui peuvent être des moyens de fixation réversibles simplifiant le remplacement de la couche d'abradable et/ou du ruban. Le montage est rapide et économique puisqu'il réduit le nombre d'opérations de montage. Le mode de fixation est compact car il n'augmente pas l'épaisseur axiale de la paroi et des plateformes.The invention employs clamping means which may be reversible securing means simplifying the replacement of the abradable layer and / or ribbon. The assembly is fast and economical since it reduces the number of assembly operations. The method of attachment is compact because it does not increase the axial thickness of the wall and platforms.

Le ruban forme un support et un repère pour l'orientation angulaire des aubes statoriques. Il fournit des cercles d'appui idéalement orientés par rapport à l'axe de rotation, ce qui est particulièrement efficace pour des aubes chacune essentiellement fixée à la paroi à l'aide d'un axe. Le contact entre les épaulements et un ruban permet également de les positionner axialement. Par ce biais, il est possible de positionner précisément deux rangées d'aubes statoriques successives l'une par rapport à l'autre, par exemple lorsque les aubes sont fixées à la paroi via des orifices avec des jeux mécaniques.The ribbon forms a support and a mark for the angular orientation of the stator vanes. It provides support circles ideally oriented relative to the axis of rotation, which is particularly effective for blades each substantially fixed to the wall using an axis. The contact between the shoulders and a ribbon also makes it possible to position them axially. By this means, it is possible to precisely position two rows of successive stator vanes with respect to one another, for example when the vanes are fixed to the wall via orifices with mechanical clearances.

Brève description des dessinsBrief description of the drawings

  • La figure 1 représente une turbomachine axiale selon l'invention.The figure 1 represents an axial turbomachine according to the invention.
  • La figure 2 est un schéma d'un compresseur de turbomachine selon l'invention.The figure 2 is a diagram of a turbomachine compressor according to the invention.
  • La figure 3 illustre une portion de stator de turbomachine avec un ruban entre deux plateformes selon l'invention.The figure 3 illustrates a turbomachine stator portion with a ribbon between two platforms according to the invention.
  • La figure 4 illustre une portion de stator avec une plateforme d'aube entre deux rubans selon l'invention.The figure 4 illustrates a stator portion with a blade platform between two ribbons according to the invention.
  • La figure 5 illustre et un ruban disposé entre deux rangées annulaires de plateformes d'aubes vus depuis l'extérieur.The figure 5 illustrates and a ribbon disposed between two annular rows of paddles seen from the outside.
Description des modes de réalisationDescription of the embodiments

Dans la description qui va suivre, les termes intérieur ou interne et extérieur ou externe renvoient à un positionnement par rapport à l'axe de rotation d'une turbomachine axiale. La direction axiale est selon l'axe de rotation de la turbomachine, la direction radiale est perpendiculaire à l'axe de rotation.In the following description, the terms inner or inner and outer or outer refer to a positioning relative to the axis of rotation of an axial turbomachine. The axial direction is along the axis of rotation of the turbomachine, the radial direction is perpendicular to the axis of rotation.

La figure 1 représente de manière simplifiée une turbomachine axiale. Il s'agit dans ce cas précis d'un turboréacteur double-flux. Le turboréacteur 2 comprend un premier niveau de compression, dit compresseur basse-pression 4, un deuxième niveau de compression, dit compresseur haute-pression 6, une chambre de combustion 8 et un ou plusieurs niveaux de turbines 10. En fonctionnement, la puissance mécanique de la turbine 10 transmise via l'arbre central jusqu'au rotor 12 met en mouvement les deux compresseurs 4 et 6. Ces derniers comportent plusieurs rangées d'aubes de rotor associées à des rangées d'aubes de stators. La rotation du rotor autour de son axe de rotation 14 permet ainsi de générer un débit d'air et de comprimer progressivement ce dernier jusqu'à l'entrée de la chambre de combustion 8.The figure 1 represents in simplified manner an axial turbomachine. It is in this case a double-flow turbojet engine. The turbojet engine 2 comprises a first compression level, called a low-pressure compressor 4, a second compression level, called a high-pressure compressor 6, a combustion chamber 8 and one or more levels of turbines 10. In operation, the mechanical power of the turbine 10 transmitted via the central shaft to the rotor 12 sets in motion the two compressors 4 and 6. The latter comprise several rows of rotor blades associated with rows of stator vanes. The rotation of the rotor about its axis of rotation 14 thus makes it possible to generate an air flow and to compress it progressively until it reaches the combustion chamber 8.

Un ventilateur d'entrée communément désigné soufflante 16 ou fan est couplé au rotor 12 et génère un flux d'air qui se divise en un flux primaire 18 traversant les différents niveaux sus mentionnés de la turbomachine, et un flux secondaire 20 traversant un conduit annulaire (partiellement représenté) le long de la machine pour ensuite rejoindre le flux primaire en sortie de turbine.An inlet fan, commonly referred to as a blower 16 or a fan, is coupled to the rotor 12 and generates a stream of air that splits into a primary stream 18 passing through the above-mentioned levels of the turbomachine, and a secondary stream 20 passing through an annular duct. (partially shown) along the machine to then join the primary flow at the turbine outlet.

La figure 2 est une vue en coupe d'un compresseur d'une turbomachine axiale 2 telle que celle de la figure 1. Le compresseur peut être un compresseur basse-pression 4. On peut y observer une partie de la soufflante 16 et le bec de séparation 22 du flux primaire 18 et du flux secondaire 20. Le rotor 12 comprend plusieurs rangées d'aubes rotoriques 24, en l'occurrence trois.The figure 2 is a sectional view of a compressor of an axial turbomachine 2 such as that of the figure 1 . The compressor may be a low-pressure compressor 4. There may be seen a portion of the blower 16 and the separation nozzle 22 of the primary flow 18 and the secondary flow 20. The rotor 12 comprises several rows of rotor blades 24, occurrence three.

Le compresseur comprend un stator. Le stator comprend au moins une rangée annulaire d'aubes statoriques 26, en l'occurrence quatre. Chaque rangée d'aubes est éventuellement dotée d'une virole interne avec une couche interne d'abradable. Chaque rangée d'aubes statoriques 26 peut former un redresseur associé à la soufflante 16, ou à une rangée d'aubes rotoriques de compresseur de sorte à redresser le flux d'air pour convertir la vitesse du flux en pression.The compressor includes a stator. The stator comprises at least one annular row of stator vanes 26, in this case four. Each row of blades is optionally provided with an inner ferrule with an inner layer of abradable. Each row of stator vanes 26 may form a rectifier associated with the blower 16, or a row of compressor rotor blades so as to rectify the airflow to convert the speed of the flow into pressure.

Le stator peut comprendre un carter 28. Le carter peut comprendre une paroi 30 et/ou au moins une, préférentiellement au moins deux brides annulaires 32 s'étendant radialement et qui sont disposée en amont et en aval de la paroi 30. Une bride 32 peut servir à la fixation du bec de séparation 22 et/ou à la fixation du compresseur 4 sur un carter intermédiaire 34 de la turbomachine. La paroi 30 comprend une surface intérieure et une surface extérieure. Elle peut être formée de deux demi-coquilles séparées par un plan s'étendant axialement.The stator may comprise a housing 28. The housing may comprise a wall 30 and / or at least one, preferably at least two radially extending annular flanges 32 which are arranged upstream and downstream of the wall 30. A flange 32 can be used for fixing the separation spout 22 and / or the attachment of the compressor 4 on an intermediate casing 34 of the turbomachine. The wall 30 includes an inner surface and an outer surface. It can be formed of two half-shells separated by an axially extending plane.

Les aubes statoriques 26 s'étendent essentiellement radialement depuis la surface intérieure de la paroi 30. Elles sont régulièrement espacées les unes des autres, et présentent pour chaque rangée une même orientation angulaire dans le flux. Les aubes d'une même rangée peuvent être identiques. Au moins une aube statorique 26, préférentiellement chaque aube statorique 26 comprend une plateforme 36 externe et une pale s'étendant dans le flux primaire depuis la plateforme 36 associée, par exemple perpendiculairement. Chaque plateforme 36 peut être réalisée en métal, tel du titane. Chaque plateforme 36 peut être disposée contre la surface intérieure de la paroi 30. Les plateformes 36 d'aubes forment au moins une, préférentiellement plusieurs rangées annulaires de plateformes.The stator vanes 26 extend substantially radially from the inner surface of the wall 30. They are regularly spaced from each other, and have for each row the same angular orientation in the flow. The blades of the same row can be identical. At least one stator blade 26, preferably each stator blade 26 comprises an outer platform 36 and a blade extending in the primary flow from the associated platform 36, for example perpendicularly. Each platform 36 may be made of metal, such as titanium. Each platform 36 may be disposed against the inner surface of the wall 30. The blade platforms 36 form at least one, preferably several annular rows of platforms.

Chaque plateforme 36 peut comprendre des moyens de serrage 38 pour la fixation des aubes 26 sur la paroi 30. Les moyens de serrage associés 38 à chaque aube peuvent comprendre un axe, tel un axe fileté ou un lockbolt. Eventuellement deux axes de moyens de serrage sont associés à une même aube. Les aubes statoriques peuvent partager une même plateforme, et/ou des mêmes moyens de serrage.Each platform 36 may comprise clamping means 38 for fixing the vanes 26 to the wall 30. The associated clamping means 38 at each blade may comprise an axis, such as a threaded shaft or a lockbolt. Optionally two axes of clamping means are associated with the same blade. The stator vanes can share the same platform, and / or the same clamping means.

La paroi 30 peut présenter un profil de révolution par rapport à l'axe 14, elle peut généralement présenter une forme circulaire, ou une forme tubulaire, ou une forme d'ogive avec une variation de son rayon le long de l'axe 14. Cette évolution du rayon peut s'inverser. La surface extérieure de la paroi 30 peut délimiter un espace extérieur annulaire libre, qui est préférentiellement majoritairement vide, qui peut s'étendre sur la majorité de sa longueur.The wall 30 may have a profile of revolution with respect to the axis 14, it may generally have a circular shape, or a tubular shape, or an ogival shape with a variation of its radius along the axis 14. This evolution of the radius can be reversed. The outer surface of the wall 30 may define a free annular outer space, which is preferably predominantly empty, which may extend over most of its length.

La paroi 30 peut être réalisée en un matériau composite, et peut être fabriquée par injection selon un procédé du type RTM (acronyme anglais pour Resin Transfer Molding). Un matériau composite peut comprendre une matrice et un renfort fibreux. La matrice peut comprende un matériau organique, tel un matériau thermodurcissable, éventuellement de l'époxy. Les fibres peuvent être sous forme d'une préforme fibreuse. Une préforme peut comprendre un matelas de fibres tissées tridimensionnellement, et/ou un empilement de plis fibreux ou feuilles de fibres comprenant des fibres agencées en faisceaux de fibres tissés selon au moins deux directions. Les fibres peuvent être des fibres de carbone et/ou des fibres de verre. La paroi peut être réalisée à l'aide d'une résine chargée de fibres, par exemple à base d'un matériau thermoplastique, éventuellement avec du polyétherimide (PEI) et/ou du polyétheréthercétone (PEEK). Les fibres peuvent être des fibres dissociées, de longueur inférieure à 3,00 mm, préférentiellement inférieure à 0,50 mm.The wall 30 may be made of a composite material, and may be manufactured by injection according to a method of the RTM (acronym for Resin Transfer Molding) type. A composite material may comprise a matrix and a fibrous reinforcement. The matrix may comprise an organic material, such as a thermosetting material, possibly epoxy. The fibers may be in the form of a fibrous preform. A preform may comprise a three-dimensionally woven fiber mat, and / or a stack of fiber plies or fiber sheets comprising fibers arranged in fiber bundles woven in at least two directions. The fibers may be carbon fibers and / or glass fibers. The wall may be made using a resin filled with fibers, for example based on a thermoplastic material, optionally with polyetherimide (PEI) and / or polyetheretherketone (PEEK). The fibers may be dissociated fibers, with a length of less than 3.00 mm, preferably less than 0.50 mm.

Le stator comprend un ruban 40 circulaire avec une surface interne et une surface externe, qui sont généralement orientées radialement. Le ruban 40 peut être disposé à l'intérieur de la paroi 30, éventuellement sur la surface intérieure de la paroi 30. Le stator peut comprendre plusieurs rubans annulaires sur la paroi 30, éventuellement espacés et/ou répartis axialement le long de la paroi 30. Les rubans et les rangées annulaires de plateformes sont disposés par alternance.The stator comprises a circular ribbon 40 with an inner surface and an outer surface, which are generally radially oriented. The ribbon 40 may be disposed inside the wall 30, possibly on the inner surface of the wall 30. The stator may comprise a plurality of annular ribbons on the wall 30, possibly spaced apart and / or distributed axially along the wall 30 Ribbons and annular rows of platforms are arranged alternately.

Le stator comprend au moins une couche, éventuellement circulaire, de matériau abradable 42, préférentiellement plusieurs couches, éventuellement circulaires, de matériau abradable 42. Chaque couche d'abradable 42 est destinée à coopérer par abrasion avec des aubes rotoriques 24 de sorte à permettre une étanchéité. Chaque couche d'abradable 42 peut être disposée sur chaque surface interne de ruban 40 du carter. Les rubans peuvent permettre d'améliorer la cohésion des couches d'abradable 42 sur la paroi 30, éventuellement en formant un intercalaire dont le coefficient de dilation représente entre 10% et 500%, préférentiellement entre 50% et 200% du coefficient de dilatation de l'abradable. Chaque couche d'abradable 40 peut être déposée par projection plasma sur un ruban.The stator comprises at least one layer, optionally circular, of abradable material 42, preferably several layers, possibly circular, of abradable material 42. Each abradable layer 42 is intended to cooperate by abrasion with rotor blades 24 so as to allow seal. Each abradable layer 42 may be disposed on each internal ribbon surface 40 of the housing. The strips may make it possible to improve the cohesion of the abradable layers 42 on the wall 30, possibly by forming an interlayer whose coefficient of expansion represents between 10% and 500%, preferably between 50% and 200% of the expansion coefficient of the abradable. Each abradable layer 40 may be deposited by plasma spraying on a ribbon.

La figure 3 représente une portion de stator de la turbomachine. Un ruban est disposé à l'intérieur de la paroi et reçoit une couche d'abradable. Une aube rotorique 24 et deux aubes statoriques 26 avec leurs plateformes sont visibles. Le ruban peut comporter des perforations 52, éventuellement alignées, par exemple selon un maillage régulier.The figure 3 represents a stator portion of the turbomachine. A ribbon is disposed within the wall and receives an abradable layer. A rotor blade 24 and two stator blades 26 with their platforms are visible. The ribbon may comprise perforations 52, possibly aligned, for example according to a regular mesh.

La majorité, préférentiellement la totalité de la surface externe 44 du ruban 40 épouse la surface intérieure de la paroi 30. Le ruban 40 peut comprendre un bord amont 46 circulaire et un bord aval 48 circulaire, qui peuvent chacun décrire un cercle. Le ruban peut être un feuillard. Il peut être une bande qui forme une boucle. Le ruban 40 peut comprendre un matériau métallique, tel de l'acier, du titane, un alliage de nickel, ou un alliage de ces matériaux. Il peut être réalisé en un matériau différent de la paroi 30. Il présente une épaisseur constante. Son épaisseur peut être comprise entre 0,05 mm et 3 mm, préférentiellement comprise entre 0,15 mm et 0,25 mm.Most, preferably all of the outer surface 44 of the ribbon 40 matches the inner surface of the wall 30. The ribbon 40 can comprise a circular upstream edge 46 and a circular downstream edge 48, which may each describe a circle. The ribbon can be a strap. It can be a band that forms a loop. The ribbon 40 may comprise a metallic material, such as steel, titanium, a nickel alloy, or an alloy of these materials. It may be made of a material different from the wall 30. It has a constant thickness. Its thickness may be between 0.05 mm and 3 mm, preferably between 0.15 mm and 0.25 mm.

Au moins une plateforme 36 d'aube statorique 26 coopère avec le ruban 40 afin de le maintenir, par exemple axialement et/ou radialement puisque la plateforme 36 est fixée à la paroi 40. Préférentiellement, chaque aube statorique d'une rangé d'aube comprend une plateforme qui coopère avec le ruban afin de le maintenir, éventuellement chaque aube statorique de chaque rangée d'aubes montée sur la paroi comprend une plateforme d'aube qui coopère avec le ruban afin de le maintenir. Au moins une ou chaque plateforme 36 peut coopérer avec le ruban par contact de sa surface interne 50 et/ou en le recouvrant. Au moins une plateforme 36 d'aube statorique 26, préférentiellement chaque plateforme d'une rangée, plus préférentiellement chaque plateforme peut recouvrir au moins un des bords du ruban 40, préférentiellement chaque bord de ruban afin de le maintenir. Le ou chaque recouvrement de ruban peut être au niveau d'un des bords amont ou aval de chaque ruban.At least one platform 36 of stator blade 26 cooperates with the ribbon 40 in order to maintain it, for example axially and / or radially since the platform 36 is fixed to the wall 40. Preferably, each stator blade of a row of blades comprises a platform which cooperates with the ribbon in order to maintain it, possibly each stator blade of each row of vanes mounted on the wall comprises a blade platform which cooperates with the ribbon in order to maintain it. At least one or each platform 36 can cooperate with the tape by contact with its inner surface 50 and / or by covering it. At least one platform 36 of stator blade 26, preferably each platform of a row, more preferably each platform can cover at least one edge of the ribbon 40, preferably each ribbon edge to maintain it. The or each ribbon cover may be at one of the upstream or downstream edges of each ribbon.

Au moins une ou chaque plateforme 36 peut présenter au moins une zone de moindre épaisseur 54 coopérant avec le ruban 40, par exemple par contact de sa surface interne 50. Au moins une ou chaque zone de moindre épaisseur 54 peut être principalement disposée sur la surface interne 50 du ruban 40. Eventuellement, chaque plateforme 36 d'une ou de chaque rangée d'aubes statoriques 26 liées à la paroi 30 présente une portion de moindre épaisseur 54, formant ainsi au moins une ou plusieurs portées tubulaires, par exemple emmanchées dans une surface interne 50 de ruban 40. Chaque plateforme d'aube 36 peut être en contact de l'abradable 42 et/ou boucher des perforations 52, éventuellement via sa zone de moindre épaisseur 54. La surface interne 50 du ruban 40 peut être totalement recouverte par l'abradable 42 et la ou les plateformes 36 coopérant avec le ruban, créant ainsi une barrière étanche.At least one or each platform 36 may have at least one zone of lesser thickness 54 cooperating with the ribbon 40, for example by contacting its inner surface 50. At least one or each zone of lesser thickness 54 may be mainly disposed on the surface internal 50 of the ribbon 40. Optionally, each platform 36 of one or each row of stator blades 26 bonded to the wall 30 has a thinner portion 54, thus forming at least one or more tubular bearings, for example fitted into an internal surface 50 of ribbon 40. Each blade platform 36 may be in contact with the abradable 42 and / or plug perforations 52, possibly via its zone of smaller thickness 54. The inner surface 50 of the ribbon 40 may completely covered by the abradable 42 and the platform or platforms 36 cooperating with the ribbon, thus creating a tight barrier.

Au moins une ou chaque plateforme 36 peut présenter au moins un épaulement radial 56 qui coopère, éventuellement par contact avec un des bords amont 46 ou aval 48 du ruban 40, par exemple pour former une butée axiale. Eventuellement, chaque plateforme 36 d'une ou de chaque rangée d'aubes liées à la paroi 30 présente au moins un épaulement radial 56, préférentiellement au moins deux épaulements.At least one or each platform 36 may have at least one radial shoulder 56 which cooperates, possibly by contact with one of the upstream edges 46 or downstream 48 of the ribbon 40, for example to form an axial abutment. Optionally, each platform 36 of one or each row of blades connected to the wall 30 has at least one radial shoulder 56, preferably at least two shoulders.

Chaque plateforme 36, en combinaison de la paroi 30 peut former un crochet ouvert vers le ruban 40. Chaque crochet présente une cavité qui peut être majoritairement, préférentiellement totalement occupée par le ruban 40. Chaque aube d'une même rangée peut comprendre une plateforme, de sorte à former une cavité annulaire en combinaison avec la paroi ; éventuellement à l'aide des portions de moindre épaisseur 54 et/ou des épaulements 56.Each platform 36, in combination with the wall 30, may form an open hook towards the ribbon 40. Each hook has a cavity which may be predominantly, preferably totally occupied by the ribbon 40. Each blade of the same row may comprise a platform, so as to form an annular cavity in combination with the wall; possibly using the smaller thickness portions 54 and / or the shoulders 56.

Au moins une ou chaque plateforme 36 recouvre, par exemple avec contact, avec le ruban 40 sur une longueur axiale supérieure à l'épaisseur du ruban 40, préférentiellement le contact axial entre la plateforme 36 et le ruban 40 représente entre cinq et cinquante fois, plus préférentiellement entre quinze et trente fois l'épaisseur du ruban 40.At least one or each platform 36 covers, for example with contact, with the ribbon 40 over an axial length greater than the thickness of the ribbon 40, preferably the axial contact between the platform 36 and the ribbon 40 is between five and fifty times, more preferably between fifteen and thirty times the thickness of the ribbon 40.

L'abradable 42 est appliqué sur la surface interne 50 du ruban 40. Le ruban 40 est plus long axialement que la couche d'abradable 42, il peut dépasser axialement en amont et/ou en aval de l'abradable 42. L'abradable 42 peut recouvrir la majorité de la surface interne du ruban 50, éventuellement au moins 70% de cette surface 50. Un abradable est un matériau présentant des caractéristiques d'abradabilité garantissant l'intégrité des aubes rotoriques lors de contact avec le matériau. Plus particulièrement un abradable peut comprendre les éléments suivants:

  • une phase structurelle qui permet de garantir la rigidité du revêtement et la résistance à la corrosion,
  • une phase non structurelle ayant pour rôle de lubrifier le contact au passage de l'extrémité de la pale (phase appelée parfois lubrifiant solide),
  • des porosités qui permettent le détachement aisé des particules de revêtement lors du contact.
The abradable 42 is applied to the inner surface 50 of the ribbon 40. The ribbon 40 is axially longer than the abradable layer 42, it can protrude axially upstream and / or downstream of the abradable 42. The abradable 42 can cover the majority of the internal surface of the tape 50, possibly at least 70% of this surface 50. An abradable material is a material with abradability characteristics ensuring the integrity of the rotor blades during contact with the material. More particularly, an abradable may include the following elements:
  • a structural phase which makes it possible to guarantee the rigidity of the coating and the resistance to corrosion,
  • a non-structural phase whose function is to lubricate the contact at the passage of the end of the blade (phase sometimes called solid lubricant),
  • porosities which allow the easy detachment of the coating particles during contact.

Dans ce mode de réalisation, il forme essentiellement un matériau hétérogène avec une phase métallique, déposé par projection thermique, plus particulièrement par projection plasma. Ce matériau peut être du type Al-Si-Polyester.In this embodiment, it essentially forms a heterogeneous material with a metal phase deposited by thermal spraying, more particularly by plasma spraying. This material may be of the Al-Si-Polyester type.

La technique par projection plasma est une technique de fabrication de la métallurgie des poudres, elle est utilisée pour donner un grand nombre de matériaux à forte abradabilité. Le plasma est généré par des électrodes concentriques soumises à une forte différence de potentiel électrique et un fort courant continu, qui ionisent un gaz inerte (azote, argon, hélium) et lui font atteindre une forte pression et une température extrêmement élevée (plus de 16 000[deg.]C pour un courant de 1000 A). Un flux de poudre est ensuite injecté dans le conduit et entraîné par le plasma. Cette technique permet de faire entrer en fusion n'importe quel métal, même le plus réfractaire étant donné les températures atteintes.Plasma spraying is a technique used to manufacture powder metallurgy and is used to produce a large number of highly abradable materials. The plasma is generated by concentric electrodes subjected to a high electrical potential difference and a strong direct current, which ionize an inert gas (nitrogen, argon, helium) and make it reach a high pressure and an extremely high temperature (over 16 000 [deg.] C for a current of 1000 A). A flow of powder is then injected into the conduit and driven by the plasma. This technique makes it possible to melt any metal, even the most refractory given the temperatures reached.

La figure 4 esquisse une portion de stator selon l'invention. Une plateforme 36 d'aube statorique 26 peut coopérer avec deux rubans 40 afin de les maintenir, lesdits rubans 40 recevant chacun une couche d'abradable 42.The figure 4 sketch a portion of stator according to the invention. A platform 36 of stator vane 26 can cooperate with two ribbons 40 in order to maintain them, said ribbons 40 each receiving an abradable layer 42.

La paroi 30 peut présenter des moyens de fixation 58, tels orifices de fixation 58, qui coopèrent avec les moyens de serrage 38 des plateformes 36 de l'aube 26. Les moyens de fixation 58 peuvent comprendre des inserts (non représentés). Lors du serrage des moyens de serrage 38, chaque plateforme 36 peut appuyer contre la surface interne 50 du ruban 40 et exercer une contrainte. Le ruban peut alors se déformer, par exemple élastiquement, éventuellement par écrouissage. Le ruban 40 peut avoir été préalablement sablé.The wall 30 may have fixing means 58, such fixing holes 58, which cooperate with the clamping means 38 of the platforms 36 of the blade 26. The fastening means 58 may comprise inserts (not shown). When tightening the clamping means 38, each platform 36 can press against the inner surface 50 of the ribbon 40 and exert a stress. The ribbon can then be deformed, for example elastically, possibly by work hardening. The ribbon 40 may have been sandblasted beforehand.

Au moins une ou chaque plateforme 36 d'aube 26, et/ou chaque zone de moindre épaisseur 54 de plateforme 36 est plus épaisse que le ruban 40. Le ruban 40 peut être au moins vingt fois moins épais que les plateformes 36. Une plateforme d'aube peut être une plateforme de fixation et/ou une plaque et/ou présenter un corps avec une forme générale de polyhèdre, tel un polyèdre ou parallélipipède, éventuellement à base rectangle ou de parallélogramme. Le corps peut être généralement un hexaèdre dont les arrêtes externes amont et aval sont entaillées en forme de marche. L'épaisseur est mesurée radialement, éventuellement perpendiculairement à la surface intérieure de la paroi, elle peut être l'épaisseur moyenne. La différence d'épaisseur entre une plateforme et le ruban favorise une rigidité de la plateforme et une déformabilité du ruban ; ainsi une plateforme permet un maintien plus ferme du ruban.At least one or each blade platform 26, and / or each minor zone 54 of platform 36 is thicker than the ribbon 40. The ribbon 40 may be at least twenty times thinner than the platforms 36. A platform blade can be a fixing platform and / or a plate and / or present a body with a general shape of polyhedron, such as a polyhedron or parallelepiped, optionally rectangle base or parallelogram. The body may be generally a hexahedron whose outer edges upstream and downstream are cut in the form of a step. The thickness is measured radially, possibly perpendicular to the inner surface of the wall, it may be the average thickness. The difference in thickness between a platform and the ribbon promotes rigidity of the platform and deformability of the ribbon; thus a platform allows a firmer maintenance of the ribbon.

L'épaulement 56 peut être de hauteur radiale inférieure à l'épaisseur du ruban 40. La paroi 30 pouvant être composite à matrice organique et le ruban 40 en métal, ce dernier peut présenter un enfoncement radial 60 dans la paroi 30, améliorant ainsi son ancrage axial, éventuellement encore amélioré par les perforations 52 dans lesquelles s'incruste le matériau de la paroi.The shoulder 56 may be of radial height less than the thickness of the ribbon 40. The organic matrix composite wall 30 and the metal ribbon 40 may have a radial depression 60 in the wall 30, thus improving its thickness. axial anchoring, possibly further improved by the perforations 52 in which the material of the wall is encrusted.

Chaque aube statorique 26 présente un bord d'attaque 62 et un bord de fuite 64, qui peuvent être courbes et/ou inclinés par rapport à la direction radiale. Au moins un des rubans 40 ou chaque ruban 40 peut s'étendre axialement dans un sens opposé à la plateforme 36 qui la recouvre depuis l'un des bords d'attaque 62 ou de fuite 64 d'aube. Un des bords amont 46 ou aval 48 d'un des rubans 40 peut être disposé au niveau axialement du bord d'attaque 62 ou du bord de fuite 64 de l'aube statorique 26. En disposant ainsi le ruban 40, la pale de l'aube 26 rigidifie la plateforme 36 et limite sa flexion. Le ruban est maintenu plus fermement, ce qui peut être avantageux en raison des vibrations de la turbomachine. La compacité du montage est également améliorée.Each stator vane 26 has a leading edge 62 and a trailing edge 64, which may be curved and / or inclined relative to the radial direction. At least one of the ribbons 40 or each ribbon 40 may extend axially in a direction opposite to the platform 36 which covers it from one of the leading edges 62 or trailing edge 64. One of the upstream or downstream edges 46 of one of the ribbons 40 may be disposed axially of the leading edge 62 or the trailing edge 64 of the stator blade 26. By thus disposing the ribbon 40, the blade of the blade 26 stiffens the platform 36 and limits its flexion. The ribbon is held more firmly, which may be advantageous because of the vibrations of the turbomachine. The compactness of the assembly is also improved.

Au moins une ou chaque plateforme 36 d'aube statorique 26 présente un bord amont 66 et un bord aval 68 axialement opposés. Ces bords sont respectivement délimités par le bord d'attaque 62 de l'aube et l'extrémité amont 70 de plateforme ; et par le bord de fuite 64 de l'aube et l'extrémité aval 72 de plateforme. Les extrémités amont 70 et aval 72 peuvent être parallèles, et peuvent être des plans en contact de couches d'abradable 42. Au moins un des rubans 40 ou chaque ruban 40 peut s'étendre axialement dans un sens opposé à la plateforme 36 qui la recouvre depuis le bord amont 66 ou le bord aval 68 de la plateforme 36. Cette configuration limite la forme de marche que présente la plateforme et préserve sa rigidité intrinsèque.At least one or each platform 36 of stator blade 26 has an upstream edge 66 and an axially opposite downstream edge 68. These edges are delimited respectively by the leading edge 62 of the blade and the upstream platform end 70; and by the trailing edge 64 of the blade and the downstream end 72 of the platform. The upstream and downstream ends 70 and 72 may be parallel, and may be abradable layers in contact with the layers 42. At least one of the tapes 40 or each tape 40 may extend axially in a direction opposite to the platform 36 which covers since the upstream edge 66 or the downstream edge 68 of the platform 36. This configuration limits the form of walking that the platform presents and preserves its intrinsic rigidity.

La figure 5 illustre et un ruban circulaire 40 disposé entre deux rangées annulaires de plateformes 36 d'aubes statoriques 26 vues radialement depuis l'extérieur, la paroi n'étant pas représentée.The figure 5 illustrates and a circular ribbon 40 disposed between two annular rows of platforms 36 of stator vanes 26 seen radially from the outside, the wall not being shown.

La configuration des plateformes 36 et/ou des aubes 26 par rapport aux bords amont 46 et aval 48 du ruban peut être mixte. Le bord amont 46 du ruban 40 peut être plus en amont que le bord de fuite 64 de l'aube statorique 26 dont la plateforme 36 recouvre sa surface interne, et le bord aval 48 peut être plus en amont que le bord d'attaque 62 de l'aube dont la plateforme recouvre sa surface interne.The configuration of the platforms 36 and / or blades 26 with respect to the upstream edges 46 and downstream 48 of the ribbon may be mixed. The upstream edge 46 of the ribbon 40 may be further upstream than the trailing edge 64 of the stator vane 26 whose platform 36 covers its inner surface, and the downstream edge 48 may be further upstream than the leading edge 62 of the dawn whose platform covers its internal surface.

Le ruban 40 peut présenter plusieurs zones circulaires, par exemple au moins une ou deux zones perforées, à savoir une première zone perforée amont 74 et une deuxième zone perforée aval 76, et au moins une zone lisse 78 disposée axialement entre les zones perforées (74 ; 76). Chaque zone lisse 78 peut être unie, et/ou homogène, en tout point. Chaque zone perforée (74 ; 76) présente une série de perforations 52 réparties sur sa surface.The ribbon 40 may have several circular zones, for example at least one or two perforated zones, namely a first upstream perforated zone 74 and a second downstream perforated zone 76, and at least one smooth zone 78 disposed axially between the perforated zones (74). 76). Each smooth zone 78 may be united, and / or homogeneous, at any point. Each perforated zone (74; 76) has a series of perforations 52 distributed over its surface.

Les perforations 52 peuvent traverser le ruban et peuvent être faites par laser, par poinçonnage, par usinage. Au moins une ou chaque zone perforée (74 ; 76) peut comprendre au moins une perforation 52 par cm2, préférentiellement au moins vingt perforations par cm2, plus préférentiellement au moins cent perforations par cm2. Au moins une ou chaque zone perforée (74 ; 76) peut comprendre des perforations 52 ayant un diamètre inférieur ou égal à 3,00 mm, préférentiellement inférieur ou égal à 0,60 mm, plus préférentiellement inférieur ou égal à 0,05 mm.The perforations 52 can pass through the ribbon and can be made by laser, by punching, by machining. At least one or each perforated zone (74; 76) may comprise at least one perforation 52 per cm 2, preferably at least twenty perforations per cm 2, more preferably at least one hundred perforations per cm 2. At least one or each perforated zone (74; 76) may comprise perforations 52 having a diameter less than or equal to 3.00 mm, preferably less than or equal to 0.60 mm, more preferably less than or equal to 0.05 mm.

Chaque zone perforée (74; 76) peut représenter entre 1% et 30%, préférentiellement entre 5% et 15% de la surface interne du ruban 40. Au moins une ou chaque plateforme 36 d'aube s'étend axialement sur au moins 10%, préférentiellement sur la majorité, éventuellement sur la totalité axiale d'une zone perforée associée ; par exemple grâce à sa zone de moindre épaisseur. Les perforations 52 d'au moins une ou de chaque zone perforée (74 ; 76) sont disposées en rangées annulaires. Les perforations peuvent former au moins deux, ou au moins sept, ou au moins vingt, ou au moins cinquante rangées annulaires de perforations. Au moins une ou chaque plateforme d'aube s'étend axialement le long d'au moins 10%, préférentiellement la majorité, éventuellement la totalité des rangées de perforations ; par exemple grâce à sa zone de moindre épaisseur.Each perforated zone (74; 76) may represent between 1% and 30%, preferably between 5% and 15% of the internal surface of the strip 40. At least one or each blade platform 36 extends axially over at least 10 %, preferably on the majority, possibly on the axial totality of an associated perforated zone; for example because of its smaller area. Perforations 52 of at least one or each perforated area (74; 76) are arranged in annular rows. The perforations may form at least two, or at least seven, or at least twenty, or at least fifty annular rows of perforations. At least one or each blade platform extends axially along at least 10%, preferably the majority, possibly all the rows of perforations; for example because of its smaller area.

Les caractéristiques décrites sont applicables à un compresseur tout comme à une turbine de turbomachine.The characteristics described are applicable to a compressor as well as to a turbomachine turbine.

Claims (15)

  1. Stator for an axial flow turbomachine (2), comprising:
    - a generally circular wall (30) with an inner surface;
    - at least one annular row of stator blades (26) extending radially inwardly from the wall (30);
    - a circular band (40) disposed against the inner surface of the wall (30) and comprising an inner surface (50) and an outer surface (44), most of the outer surface (44) of the circular band (40) fitting the inner surface of the wall (30);
    - a layer of abradable material (42) on the inner surface (50) of the band (40), able to cooperate by abrasion with the rotor blades (24) of the turbomachine (2);
    such that at least one of the stator blades (26) comprises a platform (36) covering an edge of the band (40) so as to hold said band,
    characterised in that each platform (36) comprises clamping means (38) enabling a fixation to the wall (30), and the zone of the inner surface (50) of the band that is covered by each platform (36) is deformed.
  2. Stator according to Claim 1, characterized in that each blade platform (36) comprises a portion of reduced thickness (54) covering the inner surface (50) of the edge of the band (40) so as to hold said band radially, said portions (50) preferably being joined and forming a tubular bearing surface fitted inwardly of the circular band (40).
  3. Stator according to Claim 2, characterized in that at least one, or each, portion of reduced thickness (54) of the platform (36) is in contact axially with the layer of abradable matter (42) and preferably has a thickness substantially equal to the layer of abradable matter (42).
  4. Stator according to one of Claims 1 to 3, characterized in that the band (40) comprises a circular upstream edge (46) and a circular downstream edge (48), the, or each, blade platform (36) comprises a radial shoulder (56) that cooperates with one of the circular edges (46; 48) of the band (40) so as to hold said band axially, and the radial height of each shoulder (56) is possibly substantially less than the thickness of the band (40).
  5. Stator according to one of Claims 1 to 4, characterized in that the layer of abradable matter (42) and the blade platform or the blade platforms (36) cover the entire inner surface (50) of the band (40), and preferably the entire outer surface (44) of the band (40) fits the inner surface of the wall (30).
  6. Stator according to one of Claims 1 to 5, characterized in that the band (40) is axially longer than the layer of abradable matter (42), and the band (40) preferably extends beyond the layer of abradable matter (42) axially, upstream and downstream thereof.
  7. Stator according to one of Claims 1 to 6, characterized in that the band (40) is thinner than each platform (36), preferably at least five times thinner, more preferably at least ten times thinner.
  8. Stator according to one of Claims 1 to 7, characterized in that at least one, or each, platform (36) cooperates by contact with the inner surface (50) of the band (40) over an axial length greater than the thickness of the band (40), and the axial length of the contact preferably represents between five and fifty times the thickness of the band (40).
  9. Stator according to one of Claims 1 to 8, characterized in that the zone of the inner surface (50) of the band that is covered by each platform (36) is deformed by work hardening.
  10. Stator according to one of Claims 1 to 9, characterized in that the wall (30) and each platform (36) form a hook with a cavity of which the inner volume is occupied for the majority, preferably completely, by the band (40).
  11. Stator according to one of Claims 1 to 10, characterized in that the stator blades (26) each comprise a leading edge (62) and a trailing edge (64), the band (40) extending axially outwardly from the platform covering said band, from the leading edges (62) or the trailing edges (64) of blades; and/or each platform (36) comprises an upstream edge (66) and a downstream edge (68), the band extending axially outwardly from the platform (36) covering said band, from the upstream edge (66) or the downstream edge (68) of said platform.
  12. Stator according to one of Claims 1 to 11, characterized in that the row of stator blades (26) is a first row, the wall further comprising a second annular row of stator blades (26), said rows being successive stator rows, between which the band (40) is disposed, the stator preferably comprising a plurality of annular rows of stator blades (26) and a plurality of circular bands (40), the rows of stator blades (26) and the bands (40) being disposed alternately.
  13. Stator according to one of Claims 1 to 12, characterized in that the band (40) comprises at least one series of perforations (52) disposed in a number of annular rows of perforations (52), and each platform (36) covers the inner surface (50) of the band (40) over at least five rows of perforations (52), preferably over at least ten rows of perforations (52).
  14. Stator according to any one of Claims 1 to 13, characterized in that each platform (36) comprises titanium; the band (50) is a metal strip made of steel or of titanium or of an alloy of iron and nickel; the wall (30) is made of a composite material, preferably with a fibrous preform and an organic matrix; the layer of abradable matter (42) comprises an abradable material of the Al-Si polyester type.
  15. Turbomachine (2) comprising a stator, characterized in that the stator is formed in accordance with one of Claims 1 to 14 and the turbomachine (2) preferably comprises at least one turbine (10) and/or at least one compressor (4; 6), the wall (30) being a wall of a turbine (10) and extending over the majority of the axial length of the turbine (10), or the wall (30) being a wall (30) of the compressor (4; 6) and extending over the majority of the axial length of the compressor (4; 6), more preferably the compressor being a low-pressure compressor (4).
EP14151761.5A 2014-01-20 2014-01-20 Stator of an axial turbomachine and corresponding turbomachine Active EP2896796B1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP14151761.5A EP2896796B1 (en) 2014-01-20 2014-01-20 Stator of an axial turbomachine and corresponding turbomachine
CN201510011528.3A CN104791303A (en) 2014-01-20 2015-01-09 Housing with wear-resistant seal member for axial flow turbine compressor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP14151761.5A EP2896796B1 (en) 2014-01-20 2014-01-20 Stator of an axial turbomachine and corresponding turbomachine

Publications (2)

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EP2896796A1 EP2896796A1 (en) 2015-07-22
EP2896796B1 true EP2896796B1 (en) 2019-09-18

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CN (1) CN104791303A (en)

Cited By (1)

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US11028855B2 (en) * 2015-02-27 2021-06-08 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Method of manufacturing supercharger

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BE1025753B1 (en) * 2017-11-30 2019-07-04 Safran Aero Boosters S.A. DRAIN PLATFORM SEALING - CASING IN AXIAL TURBOMACHINE COMPRESSOR
FR3091725B1 (en) * 2019-01-14 2022-07-15 Safran Aircraft Engines TOGETHER FOR A TURBOMACHINE
BE1027280B1 (en) * 2019-05-16 2020-12-15 Safran Aero Boosters Sa TURBOMACHINE COMPRESSOR HOUSING
FR3096723B1 (en) * 2019-05-29 2022-03-25 Safran Helicopter Engines SEAL RING FOR A TURBOMACHINE TURBINE WHEEL
BE1029166B1 (en) * 2021-03-03 2022-10-03 Safran Aero Boosters CRANKCASE FOR TURBOMACHINE COMPRESSOR
CN113757157A (en) * 2021-08-19 2021-12-07 鑫磊压缩机股份有限公司 Impeller combined structure of magnetic suspension axial flow fan
CN113847269A (en) * 2021-08-19 2021-12-28 鑫磊压缩机股份有限公司 Stator impeller of magnetic suspension axial flow fan

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DE4442157A1 (en) * 1994-11-26 1996-05-30 Abb Management Ag Method and device for influencing the radial clearance of the blades in compressors with axial flow
EP0844369B1 (en) * 1996-11-23 2002-01-30 ROLLS-ROYCE plc A bladed rotor and surround assembly
FR2829176B1 (en) * 2001-08-30 2005-06-24 Snecma Moteurs STATOR CASING OF TURBOMACHINE
FR2835563B1 (en) * 2002-02-07 2004-04-02 Snecma Moteurs ARRANGEMENT FOR HANGING SECTORS IN A CIRCLE OF A CIRCLE OF A BLADE-BEARING DISTRIBUTOR
US20070099027A1 (en) * 2005-10-28 2007-05-03 Anand Krishnamurthy Wear resistant coatings
FR2899274B1 (en) * 2006-03-30 2012-08-17 Snecma DEVICE FOR FASTENING RING SECTIONS AROUND A TURBINE WHEEL OF A TURBOMACHINE
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