EP2896796B1 - Stator einer axialen Strömungsmaschine und zugehörige Strömungsmaschine - Google Patents

Stator einer axialen Strömungsmaschine und zugehörige Strömungsmaschine 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
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Application number
EP14151761.5A
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English (en)
French (fr)
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EP2896796A1 (de
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/de
Priority to CN201510011528.3A priority patent/CN104791303A/zh
Publication of EP2896796A1 publication Critical patent/EP2896796A1/de
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Publication of EP2896796B1 publication Critical patent/EP2896796B1/de
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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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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (15)

  1. Stator einer axialen Turbomaschine (2), umfassend:
    - eine allgemein kreisförmige Wand (30) mit einer inneren Oberfläche;
    - zumindest eine ringförmige Reihe von Statorblättern (26), sie sich von der Wand (30) aus radial nach innen erstrecken;
    - ein kreisförmiges Band (40), das gegen die innere Oberfläche der Wand (30) angeordnet ist und eine innere Oberfläche (50) und eine äußere Oberfläche (44) umfasst, wobei der Großteil der äußeren Oberfläche (44) des Bandes (40) sich an die innere Oberfläche der Wand (30) anschmiegt;
    - eine Schicht aus einem abreibbaren Material (42) auf der inneren Oberfläche (50) des Bandes (40), die dazu angepasst ist, durch Abrasion mit den Rotorblättern (24) der Turbomaschine (2) zusammenzuwirken;
    derart, dass zumindest eines der Statorblätter (26) eine Plattform (36) umfasst, die einen Rand des Bandes (40) bedeckt, um es so zu halten,
    gekennzeichnet dadurch, dass jede Plattform (36) Klemmmittel (38) umfasst, die eine Befestigung auf der Wand (30) erlauben, wobei die Zone der inneren Oberfläche (50) des Bandes, die von jeder Plattform (36) bedeckt ist, verformt ist.
  2. Stator gemäß Anspruch 1, gekennzeichnet dadurch, dass jede Blätterplattform (36) einen Teil mit geringerer Dicke (54) aufweist, der die innere Oberfläche (50) des Randes des Bandes (40) bedeckt, um es radial zu halten, wobei die besagten Teile (50) vorzugsweise miteinander verbunden sind und eine röhrenförmige Auflage bilden, die im Inneren des kreisförmigen Bandes (40) eingesetzt ist.
  3. Stator gemäß Anspruch 2, gekennzeichnet dadurch, dass zumindest ein oder jedes Teil mit geringerer Dicke (54) der Plattform (36) axial in Kontakt ist mit der abreibbaren Schicht (42) und vorzugsweise eine Dicke hat, die im Wesentlichen gleich der Dicke der abreibbaren Schicht (42) ist.
  4. Stator gemäß einem der Ansprüche 1 bis 3, gekennzeichnet dadurch, dass das Band (40) einen stromaufwärtigen kreisförmigen Rand (46) und einen stromabwärtigen kreisförmigen Rand (48) umfasst, wobei die oder jede Blätterplattform (36) einen radialen Vorsprung (56) aufweist, der mit einem der kreisförmigen Ränder (46; 48) des Bandes (40) zusammenwirkt, um es so axial zu halten, und wobei die radiale Höhe von jedem Vorsprung (56) möglicherweise geringer ist als die Dicke des Bandes (40).
  5. Stator gemäß einem der Ansprüche 1 bis 4, gekennzeichnet dadurch, dass die abreibbare Schicht (42) und die Blätterplattform oder die Blätterplattformen (36) die gesamte innere Oberfläche (50) des Bandes (40) bedecken, wobei vorzugsweise sich die gesamte äußere Oberfläche (44) des Bandes (40) an die innere Oberfläche der Wand (30) anschmiegt.
  6. Stator gemäß einem der Ansprüche 1 bis 5, gekennzeichnet dadurch, dass das Band (40) axial länger ist als die Schicht des Abreibbaren (42), wobei vorzugsweise das Band (40) axial stromaufwärts und stromabwärts über die Schicht des Abreibbaren (42) hinausgeht.
  7. Stator gemäß einem der Ansprüche 1 bis 6, gekennzeichnet dadurch, dass das Band (40) dünner ist als jede Plattform (36), vorzugsweise zumindest fünfmal dünner, noch bevorzugter zumindest zehnmal dünner.
  8. Stator gemäß einem der Ansprüche 1 bis 7, gekennzeichnet dadurch, dass zumindest eine oder jede Plattform (36) durch Kontakt mit der inneren Oberfläche (50) des Bandes (40) über eine axiale Länge zusammenwirkt, die größer ist als die Dicke des Bandes (40), und wobei die axiale Länge des Kontaktes vorzugsweise zwischen fünfmal und fünfzigmal die Dicke des Bandes (40) ist.
  9. Stator gemäß einem der Ansprüche 1 bis 8, gekennzeichnet dadurch, dass die Zone der inneren Oberfläche (50) des Bandes, die von jeder Plattform (36) bedeckt ist, durch Kaltverformung verformt ist.
  10. Stator gemäß einem der Ansprüche 1 bis 9, gekennzeichnet dadurch, dass die Wand (30) und jede Plattform (36) einen Haken mit einem Hohlraum ausbilden, dessen inneres Volumen überwiegend, vorzugsweise vollständig, von dem Band (40) eingenommen ist.
  11. Stator gemäß einem der Ansprüche 1 bis 10, gekennzeichnet dadurch, dass die Statorblätter (26) jeweils einen vorderen Rand (62) und einen hinteren Rand (64) aufweisen, wobei sich das Band (40) axial von den vorderen Rändern (62) oder den hinteren Rändern (64) der Blätter zum Äußeren der Plattform hin erstrecken, die es bedeckt; und/oder wobei jede Plattform (36) einen stromaufwärtigen Rand (66) und einen stromabwärtigen Rand (68) aufweist, wobei das Band sich axial zum Äußeren der Plattform (36) hin erstreckt, die es von dem stromaufwärtigen Rand (66) oder dem stromabwärtigen Rand (68) der besagten Plattform bedeckt.
  12. Stator gemäß einem der Ansprüche 1 bis 11, gekennzeichnet dadurch, dass die Reihe von Statorblättern (26) eine erste Reihe ist, die Wand weiterhin eine zweite ringförmige Reihe von Statorblättern (26) umfasst, wobei die besagten Reihen aufeinander folgende Statorreihen sind, zwischen denen das Band (40) angeordnet ist, und wobei der Stator vorzugsweise eine Mehrzahl von ringförmigen Reihen von Statorblättern (26) und eine Mehrzahl von kreisförmigen Bändern (40) umfasst, wobei die Reihen Statorblätter (26) und die Bänder (40) abwechselnd angeordnet sind.
  13. Stator gemäß einem der Ansprüche 1 bis 12, gekennzeichnet dadurch, dass das Band (40) zumindest eine Abfolge von Perforationen (52) umfasst, die in mehreren ringförmigen Reihen von Perforationen (52) angeordnet sind, wobei jede Plattform (36) die innere Oberfläche (50) des Bandes (40) über zumindest fünf Reihen von Perforationen (52) bedeckt, vorzugsweise über zumindest zehn Reihen von Perforationen (52).
  14. Stator gemäß einem der Ansprüche 1 bis 13, gekennzeichnet dadurch, dass jede Plattform (36) Titan umfasst; das Band (50) ein Metallband aus Stahl oder aus Titan oder aus einer Legierung von Eisen und Nickel ist; die Wand (30) aus einem Kompositmaterial ausgebildet ist, vorzugsweise mit einer faserigen Vorform und einer organischen Matrix; und die abreibbare Schicht (42) ein abreibbares Material des Types Al-Si Polyester umfasst.
  15. Turbomaschine (2) umfassend einen Stator, gekennzeichnet dadurch, dass der Stator gemäß einem der Ansprüche 1 bis 14 ist, wobei die Turbomaschine (2) vorzugsweise zumindest eine Turbine (10) und/oder zumindest einen Kompressor (4; 6) umfasst, wobei die Wand (30) eine Wand einer Turbine (10) ist und sich über den Großteil der axialen Länge der Turbine (10) erstreckt, oder wobei die Wand (30) eine Wand (30) des Kompressors (4; 6) ist und sich über den Großteil der axialen Länge des Kompressors (4; 6) erstreckt, wobei der Kompressor noch bevorzugter ein Niederdruckkompressor (4) ist.
EP14151761.5A 2014-01-20 2014-01-20 Stator einer axialen Strömungsmaschine und zugehörige Strömungsmaschine Active EP2896796B1 (de)

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CN201510011528.3A CN104791303A (zh) 2014-01-20 2015-01-09 用于轴流涡轮机压缩机的带有耐磨密封件的壳体

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BE1025753B1 (fr) * 2017-11-30 2019-07-04 Safran Aero Boosters S.A. Etancheite plateforme d’aube - carter dans un compresseur de turbomachine axiale
FR3091725B1 (fr) * 2019-01-14 2022-07-15 Safran Aircraft Engines Ensemble pour une turbomachine
BE1027280B1 (fr) * 2019-05-16 2020-12-15 Safran Aero Boosters Sa Carter de compresseur pour turbomachine
FR3096723B1 (fr) * 2019-05-29 2022-03-25 Safran Helicopter Engines Anneau d’etancheite pour une roue de turbine de turbomachine
BE1029166B1 (fr) * 2021-03-03 2022-10-03 Safran Aero Boosters Carter pour compresseur de turbomachine
CN113757157A (zh) * 2021-08-19 2021-12-07 鑫磊压缩机股份有限公司 一种磁悬浮轴流风机的叶轮组合结构
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