EP2937517B1 - Stator of an axial turbomachine and corresponding turbomachine - Google Patents
Stator of an axial turbomachine and corresponding turbomachine Download PDFInfo
- Publication number
- EP2937517B1 EP2937517B1 EP14165800.5A EP14165800A EP2937517B1 EP 2937517 B1 EP2937517 B1 EP 2937517B1 EP 14165800 A EP14165800 A EP 14165800A EP 2937517 B1 EP2937517 B1 EP 2937517B1
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- European Patent Office
- Prior art keywords
- ring
- stator
- shroud
- stator according
- layer
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Images
Classifications
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- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
-
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
-
- 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
- F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D19/00—Axial-flow pumps
- F04D19/007—Axial-flow pumps multistage fans
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/08—Sealings
- F04D29/16—Sealings between pressure and suction sides
- F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
- F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
-
- 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
- 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
- F01D25/005—Selecting particular materials
-
- 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
- F05D2250/00—Geometry
- F05D2250/70—Shape
- F05D2250/71—Shape curved
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
- F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/17—Alloys
- F05D2300/171—Steel alloys
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/40—Organic materials
- F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/40—Organic materials
- F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
- F05D2300/437—Silicon polymers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/50—Intrinsic material properties or characteristics
- F05D2300/501—Elasticity
Definitions
- the invention relates to an axial turbomachine compressor stator. More particularly, the invention relates to a stator with an axial turbomachine blade retaining rod. The invention also relates to an axial turbomachine.
- the stator of an axial turbomachine is generally provided with coaxial shells delimiting the inside and the outside of the flow.
- the stator also includes an annular array of vanes extending radially between the ferrules. The blades may be inserted into openings in a ferrule, and held individually on the ferrule in question.
- Maintaining can be achieved by means of a retention rod which cooperates with notches formed in blade tips located beyond the ferrule, outside the flow.
- the document GB 748.912 A discloses a blade assembly on an axial turbomachine compressor shell.
- the ferrule comprises two annular walls with openings for the insertion of blade tips.
- Each blade has a free end, extending radially outside the shell, which has a retention notch.
- the notches of the blades have a squeezing outwards.
- the notches are arranged in rows and receive blade retention rods whose transverse profile is arched. Thus arranged, the rods form corners that block the blades.
- a blade may be subjected to significant tensile forces that can separate a blade from its wand. Indeed in case of traction, the inclined edges of a notch can crush the rod in the arching more, so that the stick can come out of the notch. The dawn concerned is then no longer maintained by his wand.
- the object of the invention is to solve at least one of the problems posed by the prior art. More particularly, the object of the invention is to improve the retention between a blade and an arcuate transverse profile rod of an axial turbomachine. The invention also aims to increase the life of a rotor with vanes retained to a ferrule with a rod.
- the subject of the invention is an axial turbomachine stator, in particular a compressor, the stator comprising: a ferrule with an annular row of openings, an annular row of stator vanes which extend essentially radially through the openings (36) each blade comprises a retention notch (38) and a blade intended to extend in a flow of the turbomachine, each retention notch has an inlet with a narrowing and is situated opposite the blade relative to the aperture traversed by the corresponding blade, at least one blade retention strip inserted into the notches, the strip-shaped strip with an arcuate transverse profile which contacts the constrictions so as to hold the strip in the notches , remarkable in that the ferrule comprises a layer of abradable material enveloping the transverse profile of the rod so as to block the curvature of the transverse profile. arched to prevent the rod from coming out of the narrowing of the notches by deforming.
- the rod is bent circumferentially so as to be parallel to the ferrule, the rod being spaced radially from the openings of the ferrule.
- the rod in the absence of the abradable layer, is configured to be introduced and / or extracted. notches flattening or arching further its arcuate profile; the deformation possibly being a plastic deformation of the rod.
- the rod is a spring configured to be deformable elastically over at least 5%, preferably at least 10% of its axial length and / or its radial height, the rod being made of steel at spring, preferably steel 45S7, 55S7, 45SCD6, 60SC7, 45SW8, 45C4, 50CV4 according to the AFNOR standard.
- the radial majority of the abradable layer is disposed between the ferrule and the rod.
- the thickness of the strip of the strip is less than 1 mm, preferably less than 0.25 mm, more preferably less than 0.1 mm.
- the arcuate transverse profile of the rod described between a tenth of a circle and a semicircle, preferably between a sixth and a third of a circle, more preferably between a fifth and a quarter circle.
- the arcuate transverse profile of the rod has a main elongation generally parallel to the axis of rotation of the axial turbomachine.
- the abradable layer is an annular layer which covers both sides of the strip of the rod, and the rod is surrounded by the abradable layer all along the intervals between the blades, the abradable layer also closes the openings of the shell around the blades.
- the notches are open radially, the radial depths of the notches being greater than the radial height of the rod.
- each notch comprises two axially opposed hooks which close the passage of the notch, so as to allow radial retention of the rod.
- the ferrule is an inner ferrule, the ferrule and the rod being segmented, each ferrule segment comprising at least three openings for the insertion of blades.
- the rod comprises a curved surface facing the ferrule, preferably the rod comprises two radially projecting circular edges which are arranged radially on the side of the ferrule.
- the abradable layer comprises optionally filled elastomer or silicone, and is intended to cooperate by abrasion with the rotor of the axial turbomachine.
- the shell is able to define an axial annular flow of the turbomachine, the blades being intended to extend radially in the annular flow, possibly by deviating.
- the layer of abradable material prevents the rod from coming out of the narrowing of the notches by modifying the curvature of the arcuate transverse profile.
- 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 a low-pressure compressor provided with a stator according to the invention.
- the proposed stator architecture makes it possible to operate a synergy between the abradable layer and the rod.
- the abradable layer improves the stability of the rod by locking its curvature which guarantees its retention.
- the rod is better locked in position in the notches, against narrowing.
- the rod improves the mechanical connection between the blades and the abradable layer.
- the presence of the abradable layer between the ferrule and the rod promotes the distribution of forces, forming a cushion cushioning stress peaks in case of shocks. Thus, the radial retention of the blades to the shell is safer.
- the blocking function of the abradable layer may be performed by any polymeric material, possibly a composite, the abradable function being optional.
- inner or inner and outer or outer refer to a positioning relative to the axis of rotation of an axial turbomachine.
- 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.
- the mechanical power the turbine 10 transmitted via the central shaft to the rotor 12 sets in motion the two compressors 4 and 6.
- Reducing means can increase the speed of rotation transmitted to the compressors.
- the different turbine stages can each be connected to the compressor stages via concentric shafts.
- 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 10.
- An inlet fan commonly referred to as fan or blower 16 is coupled to the rotor 12 and generates an air flow which splits into a primary flow 18 passing through the various aforementioned levels of the turbomachine, and a secondary flow 20 passing through an annular duct (partially shown) along the machine to then join the primary flow at the turbine outlet.
- the secondary stream can be accelerated to generate a push reaction.
- the primary 18 and secondary 20 streams are annular flows, they are channeled by the casing of the turbomachine, and can flow axially.
- the casing has cylindrical walls or ferrules which can be internal and external.
- 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, in the occurrence three.
- the low-pressure compressor 4 comprises a stator with several rectifiers, in this case four, which each contain an annular row of stator vanes 26.
- the rectifiers are associated with the fan 16 or with a row of rotor vanes to straighten the flow. air, so as to convert the speed of the flow into pressure.
- the stator vanes 26 extend substantially radially from an outer stator casing, and can be attached thereto by means of an axis, such as a stud, a lockbolt.
- the stator housing may be an outer shell.
- the stator comprises at least one ferrule 28, for example an inner ferrule 28, for guiding the primary flow 18.
- the stator may comprise several ferrules, for example several inner ferrules.
- Each ferrule 28 has an annular row of openings. These are distributed homogeneously around the inner rings and are crossed by the ends of the blades for anchoring.
- Each ferrule may comprise an annular wall, generally tubular or substantially conical, and optionally one or two annular flanges disposed at the axial ends of the annular wall. Each annular flange extends radially inwards or outwards.
- the rings 28 may be made of metal, for example titanium alloy, or composite material to reduce their mass. The ferrules form mechanical links between the blades.
- the stator comprises at least one or more blade retention rods 26. Each rod 30 is inserted into notches formed at the ends of the blades, for example the inner ends located radially under the inner ferrules.
- the stator may include a plurality of rods 30, each associated with an annular row of blades, for radially retaining the blades of the row at the associated ferrule.
- the stator comprises at least one or more layers of material 32 associated with at least one ferrule. At least one or each layer of material may be a layer of abradable material 32, or layer of friable material, housed in the hollow of the inner ferrules 28. At least one or each layer may be annular.
- the abradable layers 32 may be of substantially constant thickness so as to form a band. These abradable layers 32 are intended to cooperate by abrasion with rotor wipers, or circumferential fins, so as to ensure a seal, for example a dynamic seal.
- the abradable layers 32 provide a waterproof filling and can be structuring. Each layer of abradable can provide cushioning.
- Each abradable layer may adhere to a rod, and / or a shell, and / or a blade.
- the rotor moves and deforms so that the radial ends of the wipers touch the associated abradable layers. They can dig annular furrows.
- the or each ferrule 28 may be formed of a plurality of annular segments, which form angular sectors of circles.
- the rod 30 may also be segmented, as is the abradable layer 32.
- the annular segments have an arcuate shape. They each have a plurality of openings in which are introduced inner ends of the stator vanes 26.
- each annular segment may be connected to at least three vanes, possibly four vanes.
- the figure 3 represents an axial turbomachine stator with a series of stator vanes 26 connected to a ferrule 28 via a retention rod 30 and an abradable layer 32.
- the stator is shown in a section along the axis 3-3 plotted on the figure 2 .
- the present teaching can be applied to an inner shell as to an outer shell.
- the ends 34 for example internal, blades 26 pass through the openings 36 of the shell 28.
- Each opening 36 can marry the associated blade, or arrange a game around the blade 26.
- the game can be filled by the layer of abradable 32, or by an additional silicone seal (not shown) to ensure a seal in the seal.
- Each blade 26 may have continuity of profile on both sides of the ferrule 28. Beyond the profile continuities, the blade ends 34 comprise the retention notches 38. These notches 38 are engaged, for example by positive contact, to their associated wand 30.
- the blades comprise blades disposed in the flow, and radially opposite ends of the blades relative to the ferrules. The ferrule separates the ends of the blades disposed in the flow.
- the wand 30 may have a band shape with two faces. Each face may be covered with the abradable layer 32.
- the wand 30 may be wrapped by the abradable layer 32 between each end 34 of blade 26, or all along the ferrule.
- the rod 30 may be bent so as to follow the inner annular surface or the outer annular surface of the ferrule 28 associated. The rod 30 may remain radially away from the annular surface of the ferrule 28. In this way, part of the abradable layer 32 may be disposed between the shell 28 and the rod 30.
- the majority of the radial thickness of the abradable layer is located between the ferrule and the rod.
- the space between the rod 30 and the ferrule 28 is advantageously occupied by the abradable layer 32.
- the abradable layer may be in contact with the ferrule and the rod.
- the rod 30 can form a reinforcing core of the ferrule 28.
- the ferrule 28 can form a support for the abradable layer 32, and / or a protective skin covering the abradable layer 32.
- the abradable layer 32 may comprise elastomer, the viscoelastic nature of which, coupled with the presence of the rod 30, improves cushioning against vibrations in the stator.
- the abradable layer 32 may stick to the blades 26, and / or to the ferrule 28, and / or to the rod 30. Glue may be applied to the rod 30 so that it sticks to its environment.
- the abradable layer 32 may be silicone; possibly with spheres to improve friability.
- the material of at least one or each rod may be a metal.
- the metal may be manganese siliceous steel, for example with 1.5% to 2% silicon, for example with 0.6% to 0.7% manganese, 0.4% to 0.6% carbon.
- the metal or steel may comprise chromium, and / or tungsten, and / or molybdenum and / or vanadium.
- the steel can be of the type 45S7, 55S7, 45SCD6, 60SC7, 45SW8, or 45C4, 50CV4 according to the AFNOR standard.
- the metal may also be copper with 1% to 2% beryllium. Percentages are mass percentages.
- the figure 4 represents a stator enlargement with a radial end 34 of blade joined to a ferrule 28 with a rod 30 embedded in an abradable layer 32 applied in the shell.
- the end 34 of the blade 26 passes through the ferrule 28 and extends beyond the ferrule on the opposite side to the fluid vein.
- the end 34 comprises a retention notch 38 or anchoring.
- the notch 38 can be oriented axially or stiffly. By oriented one can hear open.
- a notch may extend predominantly axially and be open radially.
- the notch 38 may form a cutout in the end 34 of the blade 26.
- the retention notch 38 delimits a space in which the rod 30 is integrated in order to ensure retention.
- the notch 38 has an inlet through which can be introduced or output the rod, and a bottom 40 opposite the input.
- the notch may have a narrowing or tightening.
- the narrowing may be formed between the inlet and the bottom 40 and may be progressive. It forms a decrease in passage width with respect to the entrance.
- the notch 38 may comprise two slices 42 joining the inlet and the bottom 40. The slices 42 may come together to form the constriction.
- the end 34 of the blade may comprise two hooks 44 so as to form the narrowing. They can get closer to one another locally.
- the narrowing is axial because the notch 38 is open radially. It may be radial in the case of an axially open slot.
- the rod 30 has a band or ribbon shape, the main elongation of which follows the circumference of the shell 28.
- the transverse profile of the band is arcuate, it has a curved shape.
- the curved aspect makes it possible to reduce the transverse width of the rod 30 and / or to increase the thickness thereof; the thickness being perpendicular to the elongation and the transverse direction.
- the profile of the rod 30 has a main elongation. This main elongation may be oriented radially or axially, for example depending on the orientation of the narrowing and its retention function.
- the stick, or at least its band is essentially fine. Its thickness is less than 1.00 mm, possibly less than 0.25 mm.
- the arcuate shape of the transverse profile describes a fraction of a circle, possibly more than one turn.
- the profile may describe a portion of curve or circle between 180 ° and 30 °, preferably between 120 ° and 60 °, more preferably between 90 ° and 72 °.
- the arcuate shape comes into contact with the narrowing so as to maintain the rod in the notch, and may also be in contact with the bottom of the notch.
- the rod 30 may comprise a concave surface facing the ferrule, for confining a portion of the abradable layer with the ferrule.
- the arched shape increases the size of the profile of the rod 30. Thus it can offer more support surface for a blade retention. Apart from its arched appearance, the band can have a constant thickness.
- the arcuate transverse profile of the rod 30 offers a relative flexibility, which allows to introduce it into the notch 38 by crushing it. It can be crushed transversely or axially to enter the notch, for example by deforming plastically.
- the wand may also be a spring that deforms elastically when it is in the notch. It deforms elastically radially or axially more than 5%, preferably more than 10% of the dimension concerned.
- the rod 30 is held by the abradable layer 32.
- the abradable layer 32 surrounds the profile, for example all around the transverse profile.
- This abradable layer 32 may have a thickness greater than half the radial thickness of the shell 28. It can block the curvature of the profile to lock the rod 30 in the notch 38, to avoid what sort in case of pulling the rod out of the notch following its deformation. This deformation can then increase the curvature of the arc, or flatten it according to the orientation of the bend with respect to the narrowing.
- each characteristic can be applied to all the ferrules and / or to all the rods, and / or to all the abradable layers, and / or to all the notches of the stator of the turbomachine; or a majority of them.
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Description
L'invention a trait à un stator de compresseur de turbomachine axiale. Plus particulièrement, l'invention a trait à un stator avec une baguette de retenue d'aubes de turbomachine axiale. L'invention a également trait à une turbomachine axiale.The invention relates to an axial turbomachine compressor stator. More particularly, the invention relates to a stator with an axial turbomachine blade retaining rod. The invention also relates to an axial turbomachine.
Afin de délimiter un flux annulaire, le stator d'une turbomachine axiale est généralement muni de viroles coaxiales délimitant l'intérieur et l'extérieur du flux. Le stator comprend également une rangée annulaire d'aubes s'étendant radialement entre les viroles. Les aubes peuvent être insérées dans des ouvertures ménagées dans une virole, et maintenues de manière individuelle sur la virole en question.In order to define an annular flow, the stator of an axial turbomachine is generally provided with coaxial shells delimiting the inside and the outside of the flow. The stator also includes an annular array of vanes extending radially between the ferrules. The blades may be inserted into openings in a ferrule, and held individually on the ferrule in question.
Le maintien peut être réalisé à l'aide d'une baguette de rétention qui coopère avec des encoches formées dans des extrémités d'aubes situées au-delà de la virole, en dehors du flux.Maintaining can be achieved by means of a retention rod which cooperates with notches formed in blade tips located beyond the ferrule, outside the flow.
Le document
Cependant, une aube peut être soumise à d'importants efforts de traction pouvant désolidariser une aube de sa baguette. En effet en cas de traction, les bords inclinés d'une encoche peuvent écraser la baguette en l'arquant d'avantage, si bien que la baguette peut sortir de l'encoche. L'aube concernée n'est alors plus maintenue par sa baguette.However, a blade may be subjected to significant tensile forces that can separate a blade from its wand. Indeed in case of traction, the inclined edges of a notch can crush the rod in the arching more, so that the stick can come out of the notch. The dawn concerned is then no longer maintained by his wand.
L'invention a pour objectif de résoudre au moins un des problèmes posés par l'art antérieur. Plus particulièrement, l'invention a pour objectif d'améliorer la rétention entre une aube et une baguette à profil transversal arqué d'une turbomachine axiale. L'invention a également pour objectif d'augmenter la durée de vie d'un rotor avec des aubes retenues à une virole à l'aide d'une baguette.The object of the invention is to solve at least one of the problems posed by the prior art. More particularly, the object of the invention is to improve the retention between a blade and an arcuate transverse profile rod of an axial turbomachine. The invention also aims to increase the life of a rotor with vanes retained to a ferrule with a rod.
L'invention a pour objet un stator de turbomachine axiale, notamment de compresseur, le stator comprenant :une virole avec une rangée annulaire d'ouvertures, une rangée annulaire d'aubes statoriques qui s'étendent essentiellement radialement en traversant les ouvertures (36), chaque aube comporte une encoche de rétention (38) et une pale destinée à s'étendre dans un flux de la turbomachine, chaque encoche de rétention comporte une entrée avec un rétrécissement et est située à l'opposé de la pale par rapport à l'ouverture traversée par l'aube correspondante, au moins une baguette de rétention d'aubes insérée dans les encoches, la baguette présentant une forme de bande avec un profil transversal arqué qui est en contact des rétrécissements de sorte à maintenir la baguette dans les encoches, remarquable en ce que la virole comprend une couche de matériau abradable enveloppant le profil transversal de la baguette de sorte à bloquer la courbure du profil transversal arqué afin d'empêcher la baguette de sortir des rétrécissements des encoches en se déformant.The subject of the invention is an axial turbomachine stator, in particular a compressor, the stator comprising: a ferrule with an annular row of openings, an annular row of stator vanes which extend essentially radially through the openings (36) each blade comprises a retention notch (38) and a blade intended to extend in a flow of the turbomachine, each retention notch has an inlet with a narrowing and is situated opposite the blade relative to the aperture traversed by the corresponding blade, at least one blade retention strip inserted into the notches, the strip-shaped strip with an arcuate transverse profile which contacts the constrictions so as to hold the strip in the notches , remarkable in that the ferrule comprises a layer of abradable material enveloping the transverse profile of the rod so as to block the curvature of the transverse profile. arched to prevent the rod from coming out of the narrowing of the notches by deforming.
Selon un mode avantageux de l'invention, la baguette est cintrée circonférentiellement de sorte à être parallèle à la virole, la baguette étant à distance radialement des ouvertures de la virole.According to an advantageous embodiment of the invention, the rod is bent circumferentially so as to be parallel to the ferrule, the rod being spaced radially from the openings of the ferrule.
Selon un mode avantageux de l'invention, en l'absence de la couche d'abradable, la baguette est configurée pour être introduite et/ou extraite des encoches en aplatissant ou en arquant d'avantage son profil arqué ; la déformation étant éventuellement une déformation plastique de la baguette.According to an advantageous embodiment of the invention, in the absence of the abradable layer, the rod is configured to be introduced and / or extracted. notches flattening or arching further its arcuate profile; the deformation possibly being a plastic deformation of the rod.
Selon un mode avantageux de l'invention, la baguette est un ressort configuré pour pouvoir se déformer élastiquement sur au moins 5%, préférentiellement au moins 10% de sa longueur axiale et/ou de sa hauteur radiale, la baguette étant réalisée en acier à ressort, préférentiellement de l'acier 45S7, 55S7, 45SCD6, 60SC7, 45SW8, 45C4, 50CV4 selon la norme AFNOR.According to an advantageous embodiment of the invention, the rod is a spring configured to be deformable elastically over at least 5%, preferably at least 10% of its axial length and / or its radial height, the rod being made of steel at spring, preferably steel 45S7, 55S7, 45SCD6, 60SC7, 45SW8, 45C4, 50CV4 according to the AFNOR standard.
Selon un mode avantageux de l'invention, axialement au niveau de la baguette, la majorité radiale de la couche d'abradable est disposée entre la virole et la baguette.According to an advantageous embodiment of the invention, axially at the rod, the radial majority of the abradable layer is disposed between the ferrule and the rod.
Selon un mode avantageux de l'invention, l'épaisseur de la bande de la baguette est inférieure à 1 mm, préférentiellement inférieure à 0,25 mm, plus préférentiellement inférieure à 0,1 mm.According to an advantageous embodiment of the invention, the thickness of the strip of the strip is less than 1 mm, preferably less than 0.25 mm, more preferably less than 0.1 mm.
Selon un mode avantageux de l'invention, le profil transversal arqué de la baguette décrit entre un dixième de cercle et un demi-cercle, préférentiellement entre un sixième et un tiers de cercle, plus préférentiellement entre un cinquième et un quart de cercle.According to an advantageous embodiment of the invention, the arcuate transverse profile of the rod described between a tenth of a circle and a semicircle, preferably between a sixth and a third of a circle, more preferably between a fifth and a quarter circle.
Selon un mode avantageux de l'invention, le profil transversal arqué de la baguette présente un allongement principal généralement parallèle à l'axe de rotation de la turbomachine axiale.According to an advantageous embodiment of the invention, the arcuate transverse profile of the rod has a main elongation generally parallel to the axis of rotation of the axial turbomachine.
Selon un mode avantageux de l'invention, la couche d'abradable est une couche annulaire qui recouvre les deux faces de la bande de la baguette, et la baguette est entourée de la couche d'abradable tout le long des intervalles entre les aubes, la couche d'abradable bouchant également les ouvertures de la virole autour des aubes.According to an advantageous embodiment of the invention, the abradable layer is an annular layer which covers both sides of the strip of the rod, and the rod is surrounded by the abradable layer all along the intervals between the blades, the abradable layer also closes the openings of the shell around the blades.
Selon un mode avantageux de l'invention, les encoches sont ouvertes radialement, les profondeurs radiales des encoches étant supérieures à la hauteur radiale de la baguette.According to an advantageous embodiment of the invention, the notches are open radially, the radial depths of the notches being greater than the radial height of the rod.
Selon un mode avantageux de l'invention, chaque encoche comprend deux crochets opposés axialement qui referment le passage de l'encoche, de sorte à permettre une rétention radiale de la baguette.According to an advantageous embodiment of the invention, each notch comprises two axially opposed hooks which close the passage of the notch, so as to allow radial retention of the rod.
Selon un mode avantageux de l'invention, la virole est une virole interne, la virole et la baguette étant segmentées, chaque segment de virole comprenant au moins trois ouvertures pour l'insertion d'aubes.According to an advantageous embodiment of the invention, the ferrule is an inner ferrule, the ferrule and the rod being segmented, each ferrule segment comprising at least three openings for the insertion of blades.
Selon un mode avantageux de l'invention, la baguette comprend une surface incurvée en regard de la virole, préférentiellement la baguette comprend deux arrêtes circulaires faisant saillie radialement et qui sont disposées radialement du côté de la virole.According to an advantageous embodiment of the invention, the rod comprises a curved surface facing the ferrule, preferably the rod comprises two radially projecting circular edges which are arranged radially on the side of the ferrule.
Selon un mode avantageux de l'invention, la couche d'abradable, comprend de l'élastomère ou du silicone éventuellement chargé, et est destinée à coopérer par abrasion avec le rotor de la turbomachine axiale.According to an advantageous embodiment of the invention, the abradable layer comprises optionally filled elastomer or silicone, and is intended to cooperate by abrasion with the rotor of the axial turbomachine.
Selon un mode avantageux de l'invention, la virole est apte à délimiter un flux annulaire axial de la turbomachine, les pales étant destinées à s'étendre radialement dans le flux annulaire, éventuellement en le déviant.According to an advantageous embodiment of the invention, the shell is able to define an axial annular flow of the turbomachine, the blades being intended to extend radially in the annular flow, possibly by deviating.
Selon un mode avantageux de l'invention, la couche de matériau abradable empêche la baguette de sortir des rétrécissements des encoches en modifiant la courbure du profil transversal arqué.According to an advantageous embodiment of the invention, the layer of abradable material prevents the rod from coming out of the narrowing of the notches by modifying the curvature of the arcuate transverse profile.
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 un compresseur basse pression muni d'un stator conforme à l'invention.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 a low-pressure compressor provided with a stator according to the invention.
L'architecture de stator proposée permet d'opérer une synergie entre la couche d'abradable, et la baguette. La couche d'abradable améliore la stabilité de la baguette en verrouillant sa courbure qui est garante de sa rétention. La baguette est mieux bloquée en position dans les encoches, contre les rétrécissements. La baguette permet d'améliorer le lien mécanique entre les aubes et la couche d'abradable. La présence de la couche d'abradable entre la virole et la baguette y favorise la répartition des efforts, en formant un coussin amortissant les pics de contraintes en cas de chocs. Ainsi, la rétention radiale des aubes à la virole est plus sûre. La fonction de blocage de la couche d'abradable peut être réalisée par tout matériau polymère, éventuellement un composite, la fonction abradable étant optionnelle.The proposed stator architecture makes it possible to operate a synergy between the abradable layer and the rod. The abradable layer improves the stability of the rod by locking its curvature which guarantees its retention. The rod is better locked in position in the notches, against narrowing. The rod improves the mechanical connection between the blades and the abradable layer. The presence of the abradable layer between the ferrule and the rod promotes the distribution of forces, forming a cushion cushioning stress peaks in case of shocks. Thus, the radial retention of the blades to the shell is safer. The blocking function of the abradable layer may be performed by any polymeric material, possibly a composite, the abradable function being optional.
La durée de vie d'un tel stator est améliorée car l'ancrage ainsi réalisé n'est plus dépendant de la seule cohésion entre l'aube et l'abradable. En cas de choc, d'ingestion, d'un détachement d'une aube de fan, les aubes parviendront d'avantage à rester solidaire de leur virole.The life of such a stator is improved because the anchoring thus produced is no longer dependent on the only cohesion between the blade and the abradable. In case of shock, ingestion, a detachment of a fan blade, the blades will achieve more to remain attached to their shell.
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La
figure 1 représente une turbomachine axiale selon l'invention.Thefigure 1 represents an axial turbomachine according to the invention. -
La
figure 2 est un schéma d'un compresseur de turbomachine selon l'invention.Thefigure 2 is a diagram of a turbomachine compressor according to the invention. -
La
figure 3 illustre une coupe suivant l'axe 3-3 tracé sur lafigure 2 d'un stator de turbomachine selon l'invention.Thefigure 3 illustrates a section along the 3-3 axis drawn on thefigure 2 a turbomachine stator according to the invention. -
La
figure 4 esquisse une extrémité d'aube montée dans une virole selon l'invention.Thefigure 4 sketch a blade end mounted in a ferrule according to the invention.
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.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.
La
Un ventilateur d'entrée communément désigné fan ou soufflante 16 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. Le flux secondaire peut être accéléré de sorte à générer une réaction de poussée. Les flux primaire 18 et secondaire 20 sont des flux annulaires, ils sont canalisés par le carter de la turbomachine, et peuvent circuler axialement. A cet effet, le carter présente des parois cylindriques ou viroles qui peuvent être internes et externes.An inlet fan commonly referred to as fan or
La
Le compresseur basse pression 4 comprend un stator avec plusieurs redresseurs, en l'occurrence quatre, qui contiennent chacun une rangée annulaire d'aubes statoriques 26. Les redresseurs sont associés au fan 16 ou à une rangée d'aubes rotoriques pour redresser le flux d'air, de sorte à convertir la vitesse du flux en pression. Les aubes statoriques 26 s'étendent essentiellement radialement depuis un carter statorique extérieur, et peuvent y être fixées à l'aide d'un axe, tel un goujon, un lockbolt. Le carter statorique peut être une virole externe.The low-
Le stator comprend au moins une virole 28, par exemple une virole interne 28, permettant de guider le flux primaire 18. Le stator peut comprendre plusieurs viroles, par exemple plusieurs viroles internes. Chaque virole 28 présente une rangée annulaire d'ouvertures. Ces dernières sont réparties de manière homogène sur le pourtour des viroles internes et sont traversées par les extrémités des aubes en vue de leur ancrage. Chaque virole peut comprendre une paroi annulaire, généralement tubulaire ou sensiblement conique, et éventuellement une ou deux brides annulaires disposées aux extrémités axiales de la paroi annulaire. Chaque bride annulaire s'étend radialement vers l'intérieur ou l'extérieur. Les viroles 28 peuvent être réalisées en métal, par exemple en alliage de titane, ou en matériau composite pour réduire leur masse. Les viroles forment de liens mécaniques entre les aubes.The stator comprises at least one
Le stator comprend au moins une ou plusieurs baguettes 30 de rétention d'aubes 26. Chaque baguette 30 est introduite dans des encoches formées aux extrémités des aubes, par exemple les extrémités internes situées radialement sous les viroles internes. Le stator peut comprendre plusieurs baguettes 30, chacune associée à une rangée annulaire d'aubes, pour retenir radialement les aubes de la rangée à la virole associée.The stator comprises at least one or more
Le stator comprend au moins une ou plusieurs couches de matériau 32 associées à au moins une virole. Au moins une ou chaque couche de matériau peut être une couche de matériau abradable 32, ou couche de matériau friable, logée dans le creux des viroles internes 28. Au moins une ou chaque couche peut être annulaire. Les couches d'abradable 32 peuvent être d'épaisseurs sensiblement constantes, de manière à former une bande. Ces couches d'abradable 32 sont destinées à coopérer par abrasion avec des léchettes de rotor, ou ailettes circonférentielles, de sorte à assurer une étanchéité, par exemple une étanchéité dynamique. Les couches d'abradable 32 assurent un remplissage étanche et peuvent être structurants. Chaque couche d'abradable peut assurer un amorti. Chaque couche d'abradable peut adhérer à une baguette, et/ou à une virole, et/ou à une aube. Lors du fonctionnement de la turbomachine, le rotor se déplace et se déforme de sorte que les extrémités radiales des léchettes effleurent les couches d'abradable associées. Elles peuvent y creuser des sillons annulaires.The stator comprises at least one or more layers of
La ou chaque virole 28 peut être formée d'une pluralité de segments annulaires, qui forment des secteurs angulaires de cercles. La baguette 30 peut également être segmentée, tout comme la couche d'abradable 32. Les segments annulaires présentent une forme arquée. Ils présentent chacun une pluralité d'ouvertures dans lesquelles sont introduites des extrémités intérieures des aubes statoriques 26. Par exemple, chaque segment annulaire peut être relié à au moins trois aubes, éventuellement quatre aubes.The or each
La
Les extrémités 34, par exemple internes, des aubes 26 traversent les ouvertures 36 de la virole 28. Chaque ouverture 36 peut épouser l'aube associée, ou ménager un jeu autour de l'aube 26. Le jeu peut être comblé par la couche d'abradable 32, ou par un joint silicone additionnel (non représenté) pour assurer une étanchéité dans le joint. Chaque aube 26 peut présenter une continuité de profil des deux côtés de la virole 28. Au-delà des continuités de profil, les extrémités 34 d'aubes comprennent les encoches de rétention 38. Ces encoches 38 sont engagées, par exemple par contact positif, à leur baguette 30 associée. Les aubes comprennent des pales disposées dans le flux, et des extrémités à l'opposé radialement des pales par rapport aux viroles. La virole sépare les extrémités des pales disposées dans le flux.The ends 34, for example internal,
La baguette 30 peut avoir une forme de bande avec deux faces. Chaque face peut être recouverte de la couche d'abradable 32. La baguette 30 peut être enveloppée par la couche d'abradable 32 entre chaque extrémité 34 d'aube 26, ou tout le long de la virole. La baguette 30 peut être cintrée de sorte à longer la surface annulaire interne ou la surface annulaire externe de la virole 28 associée. La baguette 30 peut rester à distance radialement de la surface annulaire de la virole 28. De la sorte, une partie de la couche d'abradable 32 peut être disposée entre la virole 28 et la baguette 30. Eventuellement, axialement au niveau de la baguette 30, la majorité de l'épaisseur radiale de la couche d'abradable est située entre la virole et la baguette.The
L'espace entre la baguette 30 et la virole 28 est avantageusement occupé par la couche d'abradable 32. La couche d'abradable peut être en contact de la virole et de la baguette. Ainsi, il y a une meilleure répartition des efforts entre la baguette 30 et la virole 28, et donc entre les aubes 26 et la virole 28. Les concentrations de contraintes sont réduites, ce qui améliore la durée de vie de la virole 28, et/ou permet de l'amincir afin de l'alléger. La baguette 30 peut former une âme de renfort de la virole 28. La virole 28 peut former un support pour la couche d'abradable 32, et/ou une peau de protection recouvrant la couche d'abradable 32.The space between the
La couche d'abradable 32 peut comprendre de l'élastomère dont le caractère viscoélastique, couplé à la présence de la baguette 30 améliore l'amorti face à des vibrations dans le stator. La couche d'abradable 32 peut coller aux aubes 26, et/ou à la virole 28, et/ou à la baguette 30. De la colle peut être appliquée sur la baguette 30 pour qu'elle colle à son environnement. La couche d'abradable 32 peut être du silicone ; éventuellement avec des sphères pour améliorer la friabilité.The
Le matériau d'au moins une ou de chaque baguette 30 peut être un métal. Le métal peut être de l'acier mangano-siliceux, par exemple avec 1,5 % à 2 % de silicium, par exemple avec 0,6 % à 0,7 % de manganèse, 0,4 % à 0,6 % de carbone. Le métal ou l'acier peut comprendre du chrome, et/ou du tungstène, et/ou du molybdène et/ou du vanadium. L'acier peut être du type 45S7, 55S7, 45SCD6, 60SC7, 45SW8, ou 45C4, 50CV4 selon la norme AFNOR. Le métal peut également être du cuivre avec 1% à 2% de béryllium. Les pourcentages sont des pourcentages massiques.The material of at least one or each rod may be a metal. The metal may be manganese siliceous steel, for example with 1.5% to 2% silicon, for example with 0.6% to 0.7% manganese, 0.4% to 0.6% carbon. The metal or steel may comprise chromium, and / or tungsten, and / or molybdenum and / or vanadium. The steel can be of the type 45S7, 55S7, 45SCD6, 60SC7, 45SW8, or 45C4, 50CV4 according to the AFNOR standard. The metal may also be copper with 1% to 2% beryllium. Percentages are mass percentages.
La
L'extrémité 34 de l'aube 26 traverse la virole 28 et sétend au-delà de la virole, du côté opposé à la veine fluide. L'extrémité 34 comprend une encoche de rétention 38 ou d'ancrage. L'encoche 38 peut être orientée axialement ou raidialement. Par orientée on peut entendre ouverte. Une encoche peut s'étendre majoritairement axialement et être ouverte radialement. L'encoche 38 peut former une découpe dans l'extrémité 34 de l'aube 26. L'encoche 38 de rétention délimite un espace dans lequel est intégré la baguette 30 afin d'assurer une rétention.The
L'encoche 38 comporte une entrée par laquelle peut être introduite ou sortie la baguette, et un fond 40 opposé à l'entrée. L'encoche peut présenter un rétrécissement ou resserement. Le rétrécissement peut être formé entre l'entrée et le fond 40 et peut être progressif. Il forme une diminution de largeur de passage par rapport à l'entrée. L'encoche 38 peut comprendre deux tranches 42 joignant l'entrée et le fond 40. Les tranches 42 peuvent se rapprocher de sorte à former le rétrécissement. L'extrémité 34 de l'aube peut comprendre deux crochets 44 de sorte à former le rétrécissement. Ils peuvent se rapprocher localement l'un de l'autre. Le rétrécissement est axial, car l'encoche 38 est ouverte radialement. Il peut être radial dans le cas d'une encoche ouverte axialement.The
La baguette 30 a une forme de bande ou de ruban, dont l'allongement principal suit la circonférence de la virole 28. Le profil transversal de la bande est arqué, il présente une forme courbe. L'aspect courbe permet de réduire la largeur transversale de la baguette 30 et/ou d'en augmenter l'épaisseur ; l'épaisseur étant perpendiculaide à l'allongement et à la direction transversale. Le profil de la baguette 30 présente un allongement principal. Cet allongement principal peut être orienté radialement ou axialement, par exemple en fonction de l'orientation du rétrécissement et de sa fonction de rétention. La baguette, ou du moins sa bande, est essentiellement fine. Son épaisseur est inférieure à 1,00 mm, éventuellement inférieure à 0,25 mm.The
La forme arquée du profil transversal décrit une fraction de cercle, éventuellement plus d'un tour. Le profil peut décrire une portion de courbe ou de cercle entre 180° et 30°, préférentiellement entre 120° et 60°, plus préférentiellement entre 90° et 72°. La forme arquée vient en contact du rétrécissement de sorte à assurer un maintien de la baguette dans l'encoche, et peut également être en contact du fond de l'encoche. La baguette 30 peut comporter une surface concave en regard de la virole, permettant de confiner une partie de la couche d'abradable avec la virole.The arcuate shape of the transverse profile describes a fraction of a circle, possibly more than one turn. The profile may describe a portion of curve or circle between 180 ° and 30 °, preferably between 120 ° and 60 °, more preferably between 90 ° and 72 °. The arcuate shape comes into contact with the narrowing so as to maintain the rod in the notch, and may also be in contact with the bottom of the notch. The
La forme arqué permet d'augmenter l'encombrement du profil de la baguette 30. Ainsi elle peut offrir d'avantage de surface d'appui pour une rétention d'aube. Hormis son aspect arqué, la bande peut avoir une épaisseur constante. Le profil transversal arqué de la baguette 30 offre une relative souplesse, qui permet de l'introduire dans l'encoche 38 en l'écrasant. Elle peut être écrasée transversalement ou axialement pour rentrer dans l'encoche, par exemple en se déformant plastiquement. La baguette peut également être un ressort qui se déforme élastiquement lorsqu'il est rentré dans l'encoche. Il se déforme élastiquement radialement ou axialement de plus de 5%, préférentiellement plus de 10% de la dimension concernée.The arched shape increases the size of the profile of the
Afin d'éviter la déformation inverse, la baguette 30 est maintenue par la couche d'abradable 32. La couche d'abradable 32 enveloppe le profil, par exemple sur tout le tour du profil transversal. Cette couche d'abradable 32 peut présenter une épaisseur supérieure à la moitié de l'épaisseur radiale de la virole 28. Elle peut bloquer la courbure du profil pour verrouiller la baguette 30 dans l'encoche 38, pour éviter quelle ne sorte en cas de traction de la baguette hors de l'encoche suite à sa déformation. Cette déformation peut alors augmenter la courbure de l'arc, ou l'applatir suivant l'orientation de la coubure par rapport au rétrécissement.In order to avoid the reverse deformation, the
Les caractéristiques présentées ci-dessus sont détaillées pour une virole et/ou pour une baguette, et/ou pour une couche d'abradable, et/ou pour une encoche. Cependant chaque caractéristique peut s'appliquer à toutes les viroles et/ou à toutes les baguettes, et/ou à toutes les couches d'abradable, et/ou à toutes les encoches du stator de la turbomachine ; ou encore à la majorité d'entre elles.The characteristics presented above are detailed for a ferrule and / or for a rod, and / or for an abradable layer, and / or for a notch. However, each characteristic can be applied to all the ferrules and / or to all the rods, and / or to all the abradable layers, and / or to all the notches of the stator of the turbomachine; or a majority of them.
Claims (15)
- Stator of an axial-flow turbomachine (2), in particular of a compressor (4; 6), the stator comprising:- a shroud (28) having an annular row of openings (36),- an annular row of stator blades (26) which extend essentially radially by passing through the openings (36), each blade including a retaining slot (38) and a blade leaf intended to extend in a flow of the turbomachine, each retaining slot (38) including an inlet having a taper and being situated on the other side of the blade leaf in relation to the opening (36) passed through by the corresponding blade (26),- at least one retaining ring (30) for blades (26) inserted into the slots, the ring (30) exhibiting the form of a strip having an arched transversal profile which is in contact with the tapers in such a way as to maintain the ring (30) in the slots (38),characterized in that
the shroud (28) comprises a layer of abradable material (32) enclosing the transversal profile of the ring (30) in such a way as to block the curvature of the arched transversal profile in order to prevent the ring from exiting from the tapers of the slots (38) by being deformed. - Stator according to Claim 1, characterized in that the ring (30) is curved circumferentially in such a way as to be parallel to the shroud (28), the ring (30) being situated at a distance radially from the openings (36) of the shroud.
- Stator according to one of Claims 1 to 2, characterized in that, in the absence of the layer of abradable material (32), the ring (30) is configured so as to be introduced into and/or removed from the slots (38) by flattening or by further arching its arched profile; the deformation possibly being a plastic deformation of the ring.
- Stator according to one of Claims 1 to 3, characterized in that the ring (30) is a spring configured so as to be capable of deforming elastically over at least 5%, and preferably at least 10%, of its axial length and/or its radial height, the ring (30) being made from spring steel, preferably from 45S7, 55S7, 45SCD6, 60SC7, 45SW8, 45C4, 50CV4 grade steel according to the AFNOR standard.
- Stator according to one of Claims 1 to 4, characterized in that, axially in the area of the ring (30), the radial majority of the layer of abradable material (32) is positioned between the shroud (28) and the ring (30).
- Stator according to one of Claims 1 to 5, characterized in that the thickness of the strip of the ring (30) is less than 1 mm, preferably less than 0.25 mm, and more preferably less than 0.1 mm.
- Stator according to one of Claims 1 to 6, characterized in that the arched transversal profile of the ring (30) describes between one tenth of a circle and a semi-circle, preferably between one sixth and one third of a circle, and more preferably between one fifth and one quarter of a circle.
- Stator according to one of Claims 1 to 7, characterized in that the arched transversal profile of the ring (30) exhibits a principal elongation that is generally parallel to the axis of rotation (14) of the axial-flow turbomachine (2).
- Stator according to one of Claims 1 to 8, characterized in that the layer of abradable material (32) is an annular layer which covers the two faces of the strip of the ring (30), and the ring is surrounded by the layer of abradable material for the entire length of the intervals between the blades (26), the layer of abradable material (32) also filling the openings (36) of the shroud around the blades (26).
- Stator according to one of Claims 1 to 9, characterized in that the slots (38) are radially open, the radial depths of the slots being greater than the radial height of the ring (30).
- Stator according to one of Claims 1 to 10, characterized in that each slot comprises two axially opposing hooks (44), which close the passage in the slot (38) in such a way as to permit the radial retention of the ring (30).
- Stator according to one of Claims 1 to 11, characterized in that the shroud (28) is an internal shroud, the shroud and the ring being segmented, each segment of the shroud comprising at least three openings for the insertion of blades (26).
- Stator according to one of Claims 1 to 12, characterized in that the ring (30) comprises a curved surface with respect to the shroud (28), the ring (30) preferably comprising two circular edges projecting radially and being positioned radially on the side of the shroud.
- Stator according to one of Claims 1 to 13, characterized in that the layer of abradable material (32) comprises elastomer or silicone with which it has possibly been charged, and is intended to interact by abrasion with the rotor (12) of the axial-flow turbomachine (2).
- Axial-flow turbomachine (2) comprising a stator, characterized in that the stator is consistent with one of Claims 1 to 14, the turbomachine (2) preferably comprising a low-pressure compressor (4) equipped with a stator in accordance with one of Claims 1 to 14.
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP14165800.5A EP2937517B1 (en) | 2014-04-24 | 2014-04-24 | Stator of an axial turbomachine and corresponding turbomachine |
CA2888531A CA2888531A1 (en) | 2014-04-24 | 2015-04-21 | Blade retaining ring for an internal shroud of an axial-flow turbomachine compressor |
RU2015115261A RU2614302C2 (en) | 2014-04-24 | 2015-04-23 | Axial turbine machine stator blades retaining ring and axial turbomachine |
CN201510201427.2A CN105003467B (en) | 2014-04-24 | 2015-04-24 | Blade retaining ring for axial flow turbo-machine compressor interior shield |
US14/695,292 US9995159B2 (en) | 2014-04-24 | 2015-04-24 | Blade retaining ring for an internal shroud of an axial-flow turbomachine compressor |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP14165800.5A EP2937517B1 (en) | 2014-04-24 | 2014-04-24 | Stator of an axial turbomachine and corresponding turbomachine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2937517A1 EP2937517A1 (en) | 2015-10-28 |
EP2937517B1 true EP2937517B1 (en) | 2019-03-06 |
Family
ID=50630578
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP14165800.5A Active EP2937517B1 (en) | 2014-04-24 | 2014-04-24 | Stator of an axial turbomachine and corresponding turbomachine |
Country Status (5)
Country | Link |
---|---|
US (1) | US9995159B2 (en) |
EP (1) | EP2937517B1 (en) |
CN (1) | CN105003467B (en) |
CA (1) | CA2888531A1 (en) |
RU (1) | RU2614302C2 (en) |
Families Citing this family (14)
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FR3057908B1 (en) * | 2016-10-21 | 2019-11-22 | Safran Aircraft Engines | ROTARY ASSEMBLY OF A TURBOMACHINE PROVIDED WITH AN AXIAL MAINTAINING SYSTEM OF A DAWN |
US10253643B2 (en) | 2017-02-07 | 2019-04-09 | General Electric Company | Airfoil fluid curtain to mitigate or prevent flow path leakage |
US10370990B2 (en) | 2017-02-23 | 2019-08-06 | General Electric Company | Flow path assembly with pin supported nozzle airfoils |
US10378373B2 (en) | 2017-02-23 | 2019-08-13 | General Electric Company | Flow path assembly with airfoils inserted through flow path boundary |
US10247019B2 (en) | 2017-02-23 | 2019-04-02 | General Electric Company | Methods and features for positioning a flow path inner boundary within a flow path assembly |
US10253641B2 (en) | 2017-02-23 | 2019-04-09 | General Electric Company | Methods and assemblies for attaching airfoils within a flow path |
US10385776B2 (en) | 2017-02-23 | 2019-08-20 | General Electric Company | Methods for assembling a unitary flow path structure |
US10385709B2 (en) | 2017-02-23 | 2019-08-20 | General Electric Company | Methods and features for positioning a flow path assembly within a gas turbine engine |
US10385731B2 (en) | 2017-06-12 | 2019-08-20 | General Electric Company | CTE matching hanger support for CMC structures |
US10746035B2 (en) | 2017-08-30 | 2020-08-18 | General Electric Company | Flow path assemblies for gas turbine engines and assembly methods therefore |
US10669894B2 (en) * | 2018-01-26 | 2020-06-02 | Raytheon Technologies Corporation | Annular retention strap |
PL431184A1 (en) * | 2019-09-17 | 2021-03-22 | General Electric Company Polska Spółka Z Ograniczoną Odpowiedzialnością | Turboshaft engine set |
US11268394B2 (en) | 2020-03-13 | 2022-03-08 | General Electric Company | Nozzle assembly with alternating inserted vanes for a turbine engine |
CN113565799A (en) * | 2021-08-24 | 2021-10-29 | 中国航发湖南动力机械研究所 | Detachable axial flow compressor |
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FR2404102A1 (en) * | 1977-09-27 | 1979-04-20 | Snecma | Labyrinth seal for fixed blades of jet engine compressor - has abradable resin surface in contact with ridges of rotor seal |
FR2671140B1 (en) * | 1990-12-27 | 1995-01-13 | Snecma | RECTIFIER BLADE FOR TURBOMACHINE COMPRESSOR. |
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US6409472B1 (en) * | 1999-08-09 | 2002-06-25 | United Technologies Corporation | Stator assembly for a rotary machine and clip member for a stator assembly |
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GB2422641B (en) * | 2005-01-28 | 2007-11-14 | Rolls Royce Plc | Vane for a gas turbine engine |
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2014
- 2014-04-24 EP EP14165800.5A patent/EP2937517B1/en active Active
-
2015
- 2015-04-21 CA CA2888531A patent/CA2888531A1/en not_active Abandoned
- 2015-04-23 RU RU2015115261A patent/RU2614302C2/en active
- 2015-04-24 US US14/695,292 patent/US9995159B2/en not_active Expired - Fee Related
- 2015-04-24 CN CN201510201427.2A patent/CN105003467B/en not_active Expired - Fee Related
Non-Patent Citations (1)
Title |
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None * |
Also Published As
Publication number | Publication date |
---|---|
RU2015115261A (en) | 2016-11-10 |
CN105003467B (en) | 2019-07-09 |
RU2614302C2 (en) | 2017-03-24 |
US9995159B2 (en) | 2018-06-12 |
CA2888531A1 (en) | 2015-10-24 |
EP2937517A1 (en) | 2015-10-28 |
US20150308277A1 (en) | 2015-10-29 |
CN105003467A (en) | 2015-10-28 |
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