EP2977559A1 - Vane with wire mesh sealed in a compressor shroud of an axial turbomachine, and corresponding turbomachine - Google Patents
Vane with wire mesh sealed in a compressor shroud of an axial turbomachine, and corresponding turbomachine Download PDFInfo
- Publication number
- EP2977559A1 EP2977559A1 EP14178502.2A EP14178502A EP2977559A1 EP 2977559 A1 EP2977559 A1 EP 2977559A1 EP 14178502 A EP14178502 A EP 14178502A EP 2977559 A1 EP2977559 A1 EP 2977559A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- stator
- blade
- wall
- lattice
- mesh
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000004873 anchoring Methods 0.000 claims abstract description 37
- 239000000463 material Substances 0.000 claims abstract description 21
- 239000000654 additive Substances 0.000 claims abstract description 4
- 230000000996 additive effect Effects 0.000 claims abstract description 4
- 238000004519 manufacturing process Methods 0.000 claims abstract description 4
- 239000011159 matrix material Substances 0.000 claims description 8
- 238000011144 upstream manufacturing Methods 0.000 claims description 8
- 230000004323 axial length Effects 0.000 claims description 4
- 239000002131 composite material Substances 0.000 claims description 4
- 229920001296 polysiloxane Polymers 0.000 claims description 4
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims description 3
- 238000005299 abrasion Methods 0.000 claims description 2
- 239000007787 solid Substances 0.000 claims description 2
- 230000014759 maintenance of location Effects 0.000 abstract description 10
- 238000005192 partition Methods 0.000 description 3
- 239000011324 bead Substances 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 230000002457 bidirectional effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000013536 elastomeric material Substances 0.000 description 1
- 230000037406 food intake Effects 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 229920000642 polymer Polymers 0.000 description 1
- 239000011347 resin Substances 0.000 description 1
- 229920005989 resin Polymers 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
Images
Classifications
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- 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
- F04D29/60—Mounting; Assembling; Disassembling
- F04D29/64—Mounting; Assembling; Disassembling of axial pumps
- F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
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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
- 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
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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
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- 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
- F04D19/02—Multi-stage pumps
- F04D19/022—Multi-stage pumps with concentric rows of vanes
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- 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
- F04D29/083—Sealings especially adapted for elastic fluid pumps
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- 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
- F04D29/10—Shaft sealings
- F04D29/102—Shaft sealings especially adapted for elastic fluid pumps
-
- 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
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
Definitions
- the invention relates to a stator stage of axial turbomachine. More specifically, the invention relates to the attachment between a shell and a stator blade of axial turbomachine. The invention also relates to an axial turbomachine provided with a stator blade.
- a turbomachine offers mechanical work thanks to the gas flows that pass through it. These flows are guided by casings and series of internal ferrules.
- the inner shells are generally connected to the casing of the turbomachine via the stator vanes.
- the latter have internal ends with attachment portions to which the ferrules are connected. For example, it is known to anchor a ferrule to an annular row of vanes with the aid of a retention rod.
- the document EP 2 735 707 A1 discloses an axial turbomachine compressor stator.
- the rectifier comprises an outer casing, an annular array of vanes extending radially from the casing, and an inner ferrule connected to the inner ends of the vanes. These blade tips each have a retention hook in which is engaged a retention rod.
- the rod and the hooks are embedded in an abradable layer applied inside the blade, which allows the retention of the ferrule.
- the retention provided by this architecture is strong; it is particularly resistant to ingestions. However, it requires the addition of a retention rod that increases assembly costs and weighs down the rectifier. In the context of a segmented ferrule, the ferrule can tilt around the rod. The abradable wrapping wand at the rod is then strongly stressed and can degrade.
- the object of the invention is to solve at least one of the problems posed by the prior art. More specifically, the invention aims to improve the anchoring between a blade and a wall. The invention also aims to reduce the costs of assembling a stator with a wall connected to blades while improving anchoring and optimizing the distribution of forces between a blade and a wall.
- the subject of the invention is an axial turbomachine stator, in particular a compressor, the stator comprising: a circular or arcuate wall, the wall comprising a guide surface intended to guide a flow of the turbomachine; a circular or semicircular array of stator vanes, at least one of the stator vanes comprising a blade for extending radially in the flow from the guide surface and an anchor portion extending from the guide surface to the radially opposite of the blade; remarkable in that the anchoring portion of the blade comprises a lattice anchored to the wall so as to fix said blade to the wall via the lattice.
- the lattice is a three-dimensional lattice with intersecting rods and joined to each other so as to form meshes, the lattice comprising several meshes according to the thickness and / or the length of the blade and or in the radial direction.
- the at least one blade comprises a leading edge, a trailing edge, an intrados surface and an extrados surface, the intrados surface and the extrados surface extending from the leading edge to the upper surface. trailing edge; and the mesh extending from the leading edge to the trailing edge of the blade, and from the intrados surface to the extrados surface.
- the wall is an inner ferrule or an inner ferrule segment, preferably the inner ferrule and / or the wall is made of an organic matrix composite material.
- the wall comprises at least one opening in which the anchoring portion is arranged, preferably the mesh projects radially beyond the opening, more preferably the mesh is at a distance radially from the opening.
- the wall is made of material and is formed of a material that fills the lattice.
- the stator comprises a seal placed against the wall opposite the radially of the guide surface, the mesh being at least partially anchored in the radial thickness of the seal, possibly the seal comprises a matrix and balls in contact with the mesh.
- the seal comprises a layer of abradable material intended to cooperate by abrasion with the rotor of the turbomachine, the lattice being at least partially disposed in the radial thickness of the abradable layer, optionally the Abradable layer comprises a silicone material.
- the lattice extends over the majority of the axial length of the wall and / or the radial height of the wall.
- the blade comprises a solid body which extends over most of its radial height, preferably at least over its entire radial height.
- the mesh comprises a compactness of less than 60%, preferably less than 30%, more preferably less than 10%.
- the anchoring portion is a first anchoring portion
- the lattice is a first lattice
- the wall is a first wall
- the at least one blade further comprising a second portion of anchoring with a second lattice radially opposite the first lattice with respect to the blade and anchored in a second wall which is concentric with the first wall.
- the blade comprises a fixing platform, possibly with a fixing pin, arranged radially opposite the mesh relative to the blade; preferably the stator comprises an outer casing, the platform being fixed to said outer casing.
- the blade, the lattice, and possibly the attachment platform are made of material and are produced by additive manufacturing, preferably based on titanium powder.
- the guide surface being at a height radially between the blade and the anchoring portion.
- At least one or each anchoring portion is joined to a blade.
- the wall comprises an upstream axial half and a downstream axial half, preferably the lattice is axially spaced from one of the axial halves, possibly spaced from the upstream half.
- the wall may be annular or generally tubular, or form an angular portion of a ring or tube.
- the anchoring portion comprises an array of channels passing through the anchoring portion and the mesh, optionally axially and / or laterally.
- the mesh comprises a regular mesh; or the mesh is variable, possibly the mesh densifies in the radial direction of the blade, or densifies in the vicinity of the leading edge or the trailing edge.
- the lattice and the wall are made of different materials.
- the mesh is filled with a polymeric material, such as an elastomeric resin.
- the lattice comprises at least one rod extending over the majority, preferably the entire length or width of the blade.
- the lattice comprises at least two sets, preferably at least three sets of parallel rods, each set comprising rods perpendicular to the rods of the other games.
- the mesh comprises at least four sets of parallel rods, each set comprising rods oriented at 60 ° with respect to the rods of the other games.
- the lattice extends over the majority, preferably over the whole, of the axial length and / or the thickness of the blade.
- the lattice in the state not anchored to the shell, is predominantly empty, preferably 75% empty, more preferably 90% empty.
- the compactness of the lattice is understood as the ratio between the volume that is occupied by the material forming the lattice and the total volume in which the lattice is disposed.
- the mesh is shorter axially than the opening or each opening.
- the blade and each anchoring portion form a radial stack.
- the subject of the invention is also a turbomachine, comprising a stator, which is remarkable in that the stator is in accordance with the invention.
- the wall comprises an upstream axial half and a downstream axial half, preferably the trellis is axially distant from the trunk. one of the axial halves, possibly at a distance from the upstream half.
- the invention makes it possible to improve the stability of the anchoring between a blade and a wall.
- the invention increases and distributes the contact surface between the anchoring portion and the wall; possibly via the joint, so that the Inclined and asymmetrical ferrules as on the first rectifier and on the last rectifier are more stable.
- the trellis distributes the forces between the dawn and the wall. Its lower compactness than that of the blade reduces the stator mass.
- the mesh forms a zone of less stiffness in the dawn, it is more flexible and can absorb, damping a shock by limiting the energy transmitted to the wall.
- the rods may be inclined relative to the radial direction to promote the radial elongation of the mesh and further reduce the energy transmitted in case of radial tearing force. In this way, retention and fixation become safer.
- 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.
- 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.
- 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 8.
- An inlet fan commonly referred to as a fan or fan 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 reaction.
- the primary 18 and secondary 20 streams are annular flows, they are channeled by the casing of the turbomachine.
- 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 compressor 4 comprises several rectifiers, in this case four, each containing a row of stator vanes 26.
- the rectifiers are associated with the fan 16 or a row of rotor blades 24 to straighten the air flow, so to convert the speed of the flow into pressure.
- the compressor comprises a stator 28, possibly with an outer casing 30 which forms a partition supporting the separation spout 22.
- the partition supports the straighteners and annular layers of abradable materials disposed between the straighteners.
- the outer casing 30 can have a circular or annular shape and / or be formed of half-shells. It can be made of organic matrix composite material.
- the stator vanes 26 extend essentially radially from the partition of the outer casing 30, and can be fixed thereto by means of a through axis 32.
- the stator 28 comprises at least one wall 34, preferably several walls, such as inner rings 34, connected to the inner ends of the stator vanes 26 via anchoring portions.
- the wall 34 and the outer casing 30 are concentric.
- the anchoring portion of at least one stator vane 26 comprises a trellis 36, preferably each vane of a row of stator vanes 26 comprises an anchoring portion with a trellis 36, more preferably each stator vane 26 of at least one compressor 4 of the turbomachine comprises an anchoring portion with a mesh 36.
- the or each mesh 36 may be anchored or sealed to the wall 34 and / or to the inner shell 34.
- the stator 28 may comprise at least one seal 38 associated with the wall 34 or with each wall 34.
- the or at least one or each mesh 36 may be engaged in the seal 38 so as to anchor thereon and form a fastener between a stator blade 26 and the seal 38, and therefore between a stator vane 26 and the associated wall 34.
- the stator 28 shown is that of the compressor, but the invention could equally well be applied to a turbine stator or a turbomachine fan stator.
- the figure 3 represents the stator 28. There is an inner ferrule connected to the outer casing 30 via a stator blade 26, the mesh 36 of the blade is housed in the seal 38.
- the blade or each blade 26 comprises several radial portions, including a blade 40 extending radially in the flow and at least one anchoring portion 42.
- the blade 26 may optionally comprise a fastening platform 44 which forms a support for mounting.
- the platform 44 can be fixed to the outer casing 30 by means of its attachment pin 32 and a lockbolt 46, or have orifices coinciding with orifices of the outer casing. It may be a rectangular or parallelogram plate, and may be axially bordered by annular layers 48 of material abradable upstream and downstream.
- the platform 44 can be pressed against the outer casing 30, and / or can marry the outer casing 30, possibly over most of the length.
- the blade comprises a leading edge 50 connected to the trailing edge 52 by the intrados surface and the extrados surface. Dawn 26 may be curved, arched.
- the wall 34 may be the inner shell 34.
- the wall may comprise a guide surface 54 for guiding and delimiting a flow, such as the primary flow 18 of the turbomachine.
- This surface is generally annular, possibly substantially cylindrical, and can be segmented angularly. It extends all along the blade 40, and can extend beyond upstream and downstream.
- the wall 34 may comprise at least one opening 56 or a row of openings 56, each opening 56 receiving an anchoring portion 42 of blade 26 for attachment, in particular by anchoring.
- This attachment can be made in different ways, for example with a rod.
- the space between the opening 56 that the blade 26 passes through and the blade 40 can be closed with a silicone bead 58 to prevent leakage.
- the anchoring portion 42 may comprise a smooth portion to cooperate with the cord 58, the mesh being recessed radially with respect to the cord 58 and / or the opening 56.
- the blade 40 may extend radially outwards from the wall 34, from an opening 56.
- the wall may comprise pockets in which are anchored the trellises.
- the wall may have a web with a profile of revolution about the axis of rotation 14 in the shape of an inverted "U", with an axial portion, such as a sleeve, extended radially and delimited axially by radial portions.
- the veil can delimit an internal annular space.
- the wall 34 may be metallic or of organic matrix composite material to reduce the mass while optimizing rigidity.
- the wall 34 may be circular or form a circular arc. It can be a ferrule segment, that is to say have a shape of angular sector of a circle. In this case, a stator forms a circle through several segments put end-to-end.
- the stator 28 may comprise an annular or semi-annular seal 38, disposed against the wall 34, opposite the blade 40 relative to the guide surface 54.
- This seal 38 may be placed in the space annular wall of the wall 34, and can fill this space. It can wrap the ends of blades 26 or blades 40, and penetrate the or each anchoring portion 42.
- the seal 38 may be an elastomeric material that forms a matrix, such as silicone. It may be an annular layer of abradable material capable of crumbling in the event of contact with the rotor. It may comprise a matrix and particles, such as beads to promote the friable character of the seal. These balls can cooperate with the mesh and be configured to improve the anchoring.
- the or each mesh 36 may form the inner end, the tip of the blade 26.
- the or each mesh 36 may comprise rods 60 connected to each other. They can be straight or curved. They can be related to each other at their crossings.
- the rods 60 may form nodes at their intersections, possibly integrated into their sections.
- the mesh can be monobloc.
- the or each lattice 36 may be plane, and / or be formed along a left surface, for example parallel to the radial extension of the intrados surface or the extrados surface. It can be essentially bidirectional, for example by presenting flat meshes formed by its rods 60.
- the or each trellis can be three-dimensional, and present polyhedral meshes whose edges are formed by the rods 60.
- the meshes can be tetrahedra and / or cubes.
- Its rods 60 may be arranged in at least three directions, for example perpendicular to each other.
- the rods 60 may form sets of rods 60 having the same directions, and / or the same hangers.
- the or each mesh 36 may extend in the radial extension of the blade 40. It may extend between the leading edge 50 and the trailing edge 52, possibly it exceeds these edges. It may extend over the majority, preferably over the entire rope of the blade 40 at the guide surface 54.
- the or each mesh 36 may form several meshes along the blade 40, preferably at least ten meshes, more preferably at least fifty meshes.
- the or each mesh 36 may extend over the majority of the axial length of the wall 34.
- the axial elongation of the mesh 36 limits the tilting of the wall 34 relative to the blade 26, which may occur when the wall is short depending on the circumference.
- At least one rod 60 or a set of rods 60 may extend over the majority, possibly over the entire axial axis of the blade 40 and / or the anchoring portion 42.
- the or each trellis 36 may have a variable, heterogeneous mesh.
- the meshes can be tightened towards the blade 40, and possibly at the leading edge 50 and the trailing edge 52, for example to increase the efforts that can be transmitted to the rods 60 of the mesh 36 if ingested.
- the rods 60 can multiply and / or become thinner inwards.
- the compactness of each mesh 36 is less than 90%, preferably less than 50%, more preferably less than 5%. Compactness can double from one extreme to another. It can vary from 10%, preferably 30%. Alternatively, the mesh can be constant, homogeneous, possibly locally.
- the or each mesh 36 may be anchored in the gasket 38 and / or in the material itself forming the wall 34 and the guide surface 54.
- the mesh 36 is embedded in the material of the gasket 38, the rods 60 mingle with the gasket 38
- the seal 38 penetrates and occupies the meshes of the lattice so as to fill them. In this way, the seal 38 completely fills the space that the lattice, via its rods, does not occupy. All these properties of the seal are transposable to the material of the wall.
- the seal 38 may be molded on the wall, or projected.
- the mesh 36 may extend over most of the thickness of the revolution profile of the seal 36. This anchoring depth in the seal improves the retention, and the sealing effect.
- stator 28 of the turbomachine roughing a portion of the stator 28 of the turbomachine.
- stator vanes 26 fix a wall 34 to another wall 30 via mesh 36 integral with the seal 38.
- the row of blades may be an annular or semi-annular row; that is to say which describes an angular sector of a circle.
- Platforms 44 may be in contact with each other through their lateral edges to position the blades 26, and therefore the wall 34.
- At least one or each mesh 36 may extend radially in the extension of the thickness of the blade 40, the thickness that can be heard according to the circumference.
- At least one or each mesh 36 may extend the aerodynamic profile of the blade 40 at the guiding surface 54, possibly by reproducing the arched appearance of said profile.
- At least one or each mesh 36 may form several meshes according to the thickness of the blade 40, for example at least two, preferably at least five, more preferably at least ten meshes. At least one or each trellis 36 may have, radially at its maximum thickness, several rods which extend mainly axially. The mesh 36 may be wider than the blade 40 and less wide than the associated opening 56.
- the height of at least one or each mesh 36 may be greater than the maximum thickness of the blade 40, preferably at least three times greater. At least one or each mesh 36 may be spaced radially from the associated opening 56, and / or from the inner surface of the seal 38. At least one or each mesh 36 may have a general envelope whose surfaces are inclined with respect to the intrados surface 62 and the extrados surface 64 of the associated blade at the level of the guiding surface 54.
- each blade may comprise two lattices to be anchored to two walls.
- At least one or each blade 26 of the row may comprise a first internal anchoring portion anchored by its first lattice to the inner shell 34, and a second external anchoring portion anchored by a second lattice to the outer casing 30.
- the trellises are separated by the blade, each of them can be anchored in the thickness of the web of the outer casing, especially when the latter is molded.
- At least one or each blade 26, in particular its blade 40, its mesh 36 and possibly its platform 44; or its blade and lattices are made of material and can be made by additive manufacturing. They can be made of titanium powder or polymer so as to form a set of matter. The blade can form a monoblock element with a mixed structure, having a full blade and a partially empty lattice.
- the blade may be produced in the form of a row of vanes, with at least one or more anchor lattice vanes, and possibly other attachment means on the same radial side as the lattice on other vanes.
- the row of blades may have a common platform with several blades.
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- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
L'invention a trait à un stator (28) de compresseur de turbomachine axiale. Le stator (28) comprend une paroi circulaire (34), telle une virole interne (34), avec une surface de guidage (54) pour guider le flux primaire (18) de la turbomachine. Le stator inclut par ailleurs une rangée circulaire d'aubes statoriques (26), chacune d'elle comprend une pale (40) s'étendant radialement dans le flux primaire (18) de la turbomachine, et une portion d'ancrage (42). La portion d'ancrage (42) de l'aube comprend un treillis (36) avec des tiges, ancré et/ou scellé dans la virole (34) de sorte à fixer les aubes (26) à la virole via les treillis (36). Le stator (28) comprend un joint (38) en matériau abradable disposé à l'intérieur de la virole interne (34), et dans lequel est ancré le treillis (36) de sorte à assurer une rétention, une fixation entre l'aube (26) et la virole interne (34). L'aube est réalisée par fabrication additive.The invention relates to an axial turbomachine compressor stator (28). The stator (28) comprises a circular wall (34), such as an inner shell (34), with a guide surface (54) for guiding the primary flow (18) of the turbomachine. The stator further includes a circular array of stator vanes (26), each of which comprises a blade (40) extending radially in the primary flow (18) of the turbomachine, and an anchoring portion (42). . The anchoring portion (42) of the blade comprises a mesh (36) with rods, anchored and / or sealed in the shell (34) so as to secure the blades (26) to the shell via the lattices (36). ). The stator (28) comprises a seal (38) of abradable material disposed inside the inner ferrule (34), and in which the mesh (36) is anchored so as to ensure a retention, a fixation between the dawn (26) and the inner ferrule (34). Dawn is achieved by additive manufacturing.
Description
L'invention a trait à un étage statorique de turbomachine axiale. Plus précisément, l'invention a trait à la fixation entre une virole et une aube statorique de turbomachine axiale. L'invention a également trait à une turbomachine axiale munie d'une aube statorique.The invention relates to a stator stage of axial turbomachine. More specifically, the invention relates to the attachment between a shell and a stator blade of axial turbomachine. The invention also relates to an axial turbomachine provided with a stator blade.
Une turbomachine offre un travail mécanique grâce aux flux gazeux qui la traversent. Ces flux sont guidés par des carters et des séries de viroles internes. Les viroles internes sont généralement reliées au carter de la turbomachine via les aubes statoriques. Ces dernières présentent des extrémités internes avec des portions de fixation auxquelles sont liées les viroles. Il est par exemple connu d'ancrer une virole à une rangée annulaire d'aubes à l'aide d'une baguette de rétention.A turbomachine offers mechanical work thanks to the gas flows that pass through it. These flows are guided by casings and series of internal ferrules. The inner shells are generally connected to the casing of the turbomachine via the stator vanes. The latter have internal ends with attachment portions to which the ferrules are connected. For example, it is known to anchor a ferrule to an annular row of vanes with the aid of a retention rod.
Le document
L'invention a pour objectif de résoudre au moins un des problèmes posés par l'art antérieur. Plus précisément, l'invention a pour objectif d'améliorer l'ancrage entre une aube et une paroi. L'invention a également pour objectif de réduire les coûts d'assemblage d'un stator avec une paroi liée à des aubes tout en améliorant l'ancrage et en optimisant la répartition des efforts entre une aube et une paroi.The object of the invention is to solve at least one of the problems posed by the prior art. More specifically, the invention aims to improve the anchoring between a blade and a wall. The invention also aims to reduce the costs of assembling a stator with a wall connected to blades while improving anchoring and optimizing the distribution of forces between a blade and a wall.
L'invention a pour objet un stator de turbomachine axiale, notamment de compresseur, le stator comprenant : une paroi circulaire ou en arc de cercle, la paroi comportant une surface de guidage destinée à guider un flux de la turbomachine ; une rangée circulaire ou semi-circulaire d'aubes statoriques, au moins une des aubes statoriques comprenant une pale destinée à s'étendre radialement dans le flux depuis la surface de guidage et une portion d'ancrage s'étendant depuis la surface de guidage à l'opposé radialement de la pale ; remarquable en ce que la portion d'ancrage de l'aube comprend un treillis ancré à la paroi de sorte à fixer ladite aube à la paroi via le treillis.The subject of the invention is an axial turbomachine stator, in particular a compressor, the stator comprising: a circular or arcuate wall, the wall comprising a guide surface intended to guide a flow of the turbomachine; a circular or semicircular array of stator vanes, at least one of the stator vanes comprising a blade for extending radially in the flow from the guide surface and an anchor portion extending from the guide surface to the radially opposite of the blade; remarkable in that the anchoring portion of the blade comprises a lattice anchored to the wall so as to fix said blade to the wall via the lattice.
Selon un mode avantageux de l'invention, le treillis est un treillis tridimensionnel avec des tiges entrecroisées et jointes les unes aux autres de sorte à former des mailles, le treillis comprenant plusieurs mailles suivant l'épaisseur et/ou la longueur de la pale et/ou suivant la direction radiale.According to an advantageous embodiment of the invention, the lattice is a three-dimensional lattice with intersecting rods and joined to each other so as to form meshes, the lattice comprising several meshes according to the thickness and / or the length of the blade and or in the radial direction.
Selon un mode avantageux de l'invention, la au moins une aube comprend un bord d'attaque, un bord de fuite, une surface intrados et une surface extrados, la surface intrados et la surface extrados s'étendant du bord d'attaque au bord de fuite ; et le treillis s'étendant du bord d'attaque au bord de fuite de la pale, et de la surface intrados à la surface extrados.According to an advantageous embodiment of the invention, the at least one blade comprises a leading edge, a trailing edge, an intrados surface and an extrados surface, the intrados surface and the extrados surface extending from the leading edge to the upper surface. trailing edge; and the mesh extending from the leading edge to the trailing edge of the blade, and from the intrados surface to the extrados surface.
Selon un mode avantageux de l'invention, la paroi est une virole interne ou un segment de virole interne, préférentiellement la virole interne et/ou la paroi est réalisée en un matériau composite à matrice organique.According to an advantageous embodiment of the invention, the wall is an inner ferrule or an inner ferrule segment, preferably the inner ferrule and / or the wall is made of an organic matrix composite material.
Selon un mode avantageux de l'invention, la paroi comprend au moins une ouverture dans laquelle est disposée la portion d'ancrage, préférentiellement le treillis dépasse radialement de l'ouverture, plus préférentiellement le treillis est à distance radialement de l'ouverture.According to an advantageous embodiment of the invention, the wall comprises at least one opening in which the anchoring portion is arranged, preferably the mesh projects radially beyond the opening, more preferably the mesh is at a distance radially from the opening.
Selon un mode avantageux de l'invention, la paroi est venue de matière et est formée d'un matériau qui comble le treillis.According to an advantageous embodiment of the invention, the wall is made of material and is formed of a material that fills the lattice.
Selon un mode avantageux de l'invention, le stator comprend un joint d'étanchéité placé contre la paroi à l'opposé radialement de la surface de guidage, le treillis étant au moins partiellement ancré dans l'épaisseur radiale du joint, éventuellement le joint comprend une matrice et des billes en contact du treillis.According to an advantageous embodiment of the invention, the stator comprises a seal placed against the wall opposite the radially of the guide surface, the mesh being at least partially anchored in the radial thickness of the seal, possibly the seal comprises a matrix and balls in contact with the mesh.
Selon un mode avantageux de l'invention, le joint comprend une couche de matériau abradable destiné à coopérer par abrasion avec le rotor de la turbomachine, le treillis étant au moins partiellement disposé dans l'épaisseur radiale de la couche d'abradable, éventuellement la couche d'abradable comprend un matériau silicone.According to an advantageous embodiment of the invention, the seal comprises a layer of abradable material intended to cooperate by abrasion with the rotor of the turbomachine, the lattice being at least partially disposed in the radial thickness of the abradable layer, optionally the Abradable layer comprises a silicone material.
Selon un mode avantageux de l'invention, le treillis s'étend sur la majorité de la longueur axiale de la paroi et/ou de la hauteur radiale de la paroi.According to an advantageous embodiment of the invention, the lattice extends over the majority of the axial length of the wall and / or the radial height of the wall.
Selon un mode avantageux de l'invention, la pale comprend un corps plein qui s'étend sur la majorité de sa hauteur radiale, préférentiellement au moins sur la totalité de sa hauteur radiale.According to an advantageous embodiment of the invention, the blade comprises a solid body which extends over most of its radial height, preferably at least over its entire radial height.
Selon un mode avantageux de l'invention, le treillis comprend une compacité inférieure à 60%, préférentiellement inférieure à 30%, plus préférentiellement inférieure à 10%.According to an advantageous embodiment of the invention, the mesh comprises a compactness of less than 60%, preferably less than 30%, more preferably less than 10%.
Selon un mode avantageux de l'invention, la portion d'ancrage est une première portion d'ancrage, et le treillis est un premier treillis, la paroi est une première paroi, la au moins une aube comprenant en outre une deuxième portion d'ancrage avec un deuxième treillis radialement opposé au premier treillis par rapport à la pale et ancré dans une deuxième paroi qui est concentrique à la première paroi.According to an advantageous embodiment of the invention, the anchoring portion is a first anchoring portion, and the lattice is a first lattice, the wall is a first wall, the at least one blade further comprising a second portion of anchoring with a second lattice radially opposite the first lattice with respect to the blade and anchored in a second wall which is concentric with the first wall.
Selon un mode avantageux de l'invention, l'aube comprend une plateforme de fixation, éventuellement avec un axe de fixation, disposée radialement à l'opposé du treillis par rapport à la pale ; préférentiellement le stator comprend un carter externe, la plateforme étant fixée audit carter externe.According to an advantageous embodiment of the invention, the blade comprises a fixing platform, possibly with a fixing pin, arranged radially opposite the mesh relative to the blade; preferably the stator comprises an outer casing, the platform being fixed to said outer casing.
Selon un mode avantageux de l'invention, la pale, le treillis, et éventuellement la plateforme de fixation, sont venus de matière et sont réalisés par fabrication additive, préférentiellement à base de poudre de titane.According to an advantageous embodiment of the invention, the blade, the lattice, and possibly the attachment platform, are made of material and are produced by additive manufacturing, preferably based on titanium powder.
Selon un mode avantageux de l'invention, la surface de guidage étant à hauteur radialement entre la pale et la portion d'ancrage.According to an advantageous embodiment of the invention, the guide surface being at a height radially between the blade and the anchoring portion.
Selon un mode avantageux de l'invention, au moins une ou chaque portion d'ancrage est jointe à une pale.According to an advantageous embodiment of the invention, at least one or each anchoring portion is joined to a blade.
Selon un mode avantageux de l'invention, la paroi comprend une moitié axiale amont et une moitié axiale aval, préférentiellement le treillis est à distance axialement de l'une des moitiés axiales, éventuellement à distance de la moitié amont.According to an advantageous embodiment of the invention, the wall comprises an upstream axial half and a downstream axial half, preferably the lattice is axially spaced from one of the axial halves, possibly spaced from the upstream half.
Selon un mode avantageux de l'invention, la paroi peut être annulaire ou généralement tubulaire, ou former une portion angulaire d'anneau ou de tube.According to an advantageous embodiment of the invention, the wall may be annular or generally tubular, or form an angular portion of a ring or tube.
Selon un mode avantageux de l'invention, la portion d'ancrage comprend un réseau de canaux traversant la portion d'ancrage et le treillis, éventuellement axialement et/ou latéralement.According to an advantageous embodiment of the invention, the anchoring portion comprises an array of channels passing through the anchoring portion and the mesh, optionally axially and / or laterally.
Selon un mode avantageux de l'invention, le treillis comprend un maillage régulier ; ou le maillage est variable, éventuellement le maillage se densifie en direction radialement de la pale, ou se densifie au voisinage du bord d'attaque ou du bord de fuite.According to an advantageous embodiment of the invention, the mesh comprises a regular mesh; or the mesh is variable, possibly the mesh densifies in the radial direction of the blade, or densifies in the vicinity of the leading edge or the trailing edge.
Selon un mode avantageux de l'invention, le treillis et la paroi sont réalisés en des matériaux différents.According to an advantageous embodiment of the invention, the lattice and the wall are made of different materials.
Selon un mode avantageux de l'invention, le treillis est comblé par un matériau polymère, telle une résine élastomère.According to an advantageous embodiment of the invention, the mesh is filled with a polymeric material, such as an elastomeric resin.
Selon un mode avantageux de l'invention, le treillis comprend au moins une tige s'étendant sur la majorité, préférentiellement la totalité de la longueur ou de la largeur de l'aube.According to an advantageous embodiment of the invention, the lattice comprises at least one rod extending over the majority, preferably the entire length or width of the blade.
Selon un mode avantageux de l'invention, le treillis comprend au moins deux jeux, préférentiellement au moins trois jeux de tiges parallèles, chaque jeu comprenant des tiges perpendiculaires aux tiges des autres jeux.According to an advantageous embodiment of the invention, the lattice comprises at least two sets, preferably at least three sets of parallel rods, each set comprising rods perpendicular to the rods of the other games.
Selon un mode avantageux de l'invention, le treillis comprend au moins quatre jeux de tiges parallèles, chaque jeu comprenant des tiges orientées à 60° par rapport aux tiges des autres jeux.According to an advantageous embodiment of the invention, the mesh comprises at least four sets of parallel rods, each set comprising rods oriented at 60 ° with respect to the rods of the other games.
Selon un mode avantageux de l'invention, le treillis s'étend sur la majorité, préférentiellement sur la totalité, de la longueur axiale et/ou de l'épaisseur de la pale.According to an advantageous embodiment of the invention, the lattice extends over the majority, preferably over the whole, of the axial length and / or the thickness of the blade.
Selon un mode avantageux de l'invention, dans l'état non ancré à la virole, le treillis est majoritairement vide, préférentiellement vide à 75%, plus préférentiellement vide à 90%.According to an advantageous embodiment of the invention, in the state not anchored to the shell, the lattice is predominantly empty, preferably 75% empty, more preferably 90% empty.
La compacité du treillis est entendue comme le rapport entre le volume qui est occupé par le matériau formant le treillis et le volume total dans lequel le treillis est disposé.The compactness of the lattice is understood as the ratio between the volume that is occupied by the material forming the lattice and the total volume in which the lattice is disposed.
Selon un mode avantageux de l'invention, le treillis est moins long axialement que l'ouverture ou que chaque ouverture.According to an advantageous embodiment of the invention, the mesh is shorter axially than the opening or each opening.
Selon un mode avantageux de l'invention, la pale et chaque portion d'ancrage forment un empilement radial.According to an advantageous embodiment of the invention, the blade and each anchoring portion form a radial stack.
L'invention a également pour objet une turbomachine, comprenant un stator, remarquable en ce que le stator est conforme à l'invention éventuellement la paroi comprend une moitié axiale amont et une moitié axiale aval, préférentiellement le treillis est à distance axialement de l'une des moitiés axiales, éventuellement à distance de la moitié amont.The subject of the invention is also a turbomachine, comprising a stator, which is remarkable in that the stator is in accordance with the invention. If appropriate, the wall comprises an upstream axial half and a downstream axial half, preferably the trellis is axially distant from the trunk. one of the axial halves, possibly at a distance from the upstream half.
L'invention permet d'améliorer la stabilité de l'ancrage entre une aube et une paroi. L'invention augmente et réparti la surface de contact entre la portion d'ancrage et la paroi ; éventuellement via le joint, si bien que les viroles inclinées et asymétriques comme sur le premier redresseur et sur le dernier redresseur sont davantage stables. Le treillis réparti les efforts entre l'aube et la paroi. Sa compacité inférieure à celle de la pale réduit la masse du stator.The invention makes it possible to improve the stability of the anchoring between a blade and a wall. The invention increases and distributes the contact surface between the anchoring portion and the wall; possibly via the joint, so that the Inclined and asymmetrical ferrules as on the first rectifier and on the last rectifier are more stable. The trellis distributes the forces between the dawn and the wall. Its lower compactness than that of the blade reduces the stator mass.
Le treillis forme une zone de moindre raideur dans l'aube, il est plus souple et peut absorber, amortir un choc en limitant l'énergie transmise à la paroi. Les tiges peuvent être inclinées par rapport à la direction radiale pour favoriser l'allongement radial du treillis et encore réduire l'énergie transmise en cas d'effort d'arrachement radial. Par ce biais, la rétention et la fixation deviennent plus sûrs.The mesh forms a zone of less stiffness in the dawn, it is more flexible and can absorb, damping a shock by limiting the energy transmitted to the wall. The rods may be inclined relative to the radial direction to promote the radial elongation of the mesh and further reduce the energy transmitted in case of radial tearing force. In this way, retention and fixation become safer.
L'emploi d'un treillis est compatible à un moulage d'une paroi ou d'un joint sur les portions d'ancrage. Cette solution réduit les coûts d'assemblage pour une résistance de rétention donnée.The use of a mesh is compatible with a molding of a wall or a seal on the anchoring portions. This solution reduces assembly costs for a given retention strength.
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La
figure 1 représente une turbomachine axiale selon l'invention.Thefigure 1 represents an axial turbomachine according to the invention. -
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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. -
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figure 3 illustre une section d'un stator de turbomachine selon l'invention vu de profil.Thefigure 3 illustrates a section of a turbomachine stator according to the invention seen in profile. -
La
figure 4 ébauche une coupe d'une portion de stator de turbomachine selon l'invention observé axialement.Thefigure 4 roughing a section of a turbomachine stator portion according to the invention observed axially.
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. Les flux primaire 18 et secondaire 20 sont des flux annulaires, ils sont canalisés par le carter de la turbomachine. A cet effet, le carter présente des parois cylindriques ou viroles qui peuvent être internes et externes.An inlet fan commonly referred to as a fan or
La
Le compresseur 4 comprend plusieurs redresseurs, en l'occurrence quatre, qui contiennent chacun une rangée d'aubes statoriques 26. Les redresseurs sont associés au fan 16 ou à une rangée d'aubes rotoriques 24 pour redresser le flux d'air, de sorte à convertir la vitesse du flux en pression.The
Le compresseur comprend un stator 28, éventuellement avec un carter externe 30 qui forme une cloison supportant le bec de séparation 22. La cloison supporte les redresseurs et des couches annulaires de matériaux abradables disposées entre les redresseurs. Le carter externe 30 peut présenter une forme circulaire ou annulaire et/ou être formé de demi-coquilles. Il peut être réalisé en matériau composite à matrice organique. Les aubes statoriques 26 s'étendent essentiellement radialement depuis la cloison du carter extérieur 30, et peuvent y être fixées à l'aide d'un axe 32 traversant.The compressor comprises a
Le stator 28 comprend au moins une paroi 34, préférentiellement plusieurs parois, telles des viroles internes 34, reliées aux extrémités internes des aubes statoriques 26 via des portions d'ancrage. La paroi 34 et le carter externe 30 sont concentriques. La portion d'ancrage d'au moins une aube statorique 26 comprend un treillis 36, préférentiellement chaque aube d'une rangée d'aubes statoriques 26 comprend une portion d'ancrage avec un treillis 36, plus préférentiellement chaque aube statorique 26 d'au moins un compresseur 4 de la turbomachine comprend une portion d'ancrage avec un treillis 36. Le ou chaque treillis 36 peut être ancré ou scellé à la paroi 34 et/ou à la virole interne 34.The
Le stator 28 peut comprendre au moins un joint 38 associé à la paroi 34 ou à chaque paroi 34. Le ou au moins ou chaque treillis 36 peut être engagé dans le joint 38 afin de s'y ancrer et former une fixation entre une aube statorique 26 et le joint 38, et donc entre une aube statorique 26 et la paroi 34 associée. Le stator 28 représenté est celui du compresseur, mais l'invention pourrait tout aussi bien s'appliquer à un stator de turbine ou à un stator de soufflante de turbomachine.The
La
L'aube ou chaque aube 26 comprend plusieurs portions radiales, dont une pale 40 s'étendant radialement dans le flux et au moins une portion d'ancrage 42. L'aube 26 peut éventuellement comprendre une plateforme de fixation 44 qui forme un support de montage. La plateforme 44 peut être fixée au carter externe 30 à l'aide de son axe de fixation 32 et d'un lockbolt 46, ou présenter des orifices coïncidant avec des orifices du carter externe. Elle peut être une plaque rectangulaire ou en parallélogramme, et peut être bordée axialement par des couches annulaires 48 de matériau abradable en amont et en aval. La plateforme 44 peut être plaquée contre le carter externe 30, et/ou peut épouser le carter externe 30, éventuellement sur la majorité de la longueur. L'aube comprend un bord d'attaque 50 reliée au bord de fuite 52 par la surface intrados et la surface extrados. L'aube 26 peut être incurvée, cambrée.The blade or each
La paroi 34 peut être la virole interne 34. La paroi peut comprendre une surface de guidage 54 pour guider et délimiter un flux, tel le flux primaire 18 de la turbomachine. Cette surface est généralement annulaire, éventuellement sensiblement cylindrique, et peut être segmentée angulairement. Elle s'étend tout le long de la pale 40, et peut s'étendre au-delà en amont et en aval.The
La paroi 34 peut comprendre au moins une ouverture 56 ou une rangée d'ouvertures 56, chaque ouverture 56 recevant une portion d'ancrage 42 d'aube 26 en vue de sa fixation, notamment par ancrage. Cette fixation peut s'effectuer de différentes manières, par exemple avec une baguette. L'espace entre l'ouverture 56 que l'aube 26 traverse et la pale 40 peut être fermé à l'aide d'un cordon de silicone 58 pour éviter les fuites. La portion d'ancrage 42 peut comprendre une partie lisse pour coopérer avec le cordon 58, le treillis étant en retrait radialement par rapport au cordon 58 et/ou à l'ouverture 56. La pale 40 peut s'étendre radialement vers l'extérieur depuis la paroi 34, à partir d'une ouverture 56. Alternativement, la paroi peut comprendre des poches dans lesquelles sont ancrés les treillis.The
La paroi peut présenter un voile avec un profil de révolution autour de l'axe de rotation 14 en forme de « U » inversé, avec une portion axiale, telle une manche, prolongée radialement et délimitée axialement par des portions radiales. Le voile peut délimiter un espace annulaire interne. La paroi 34 peut être métallique ou en matériau composite à matrice organique pour réduire la masse tout en optimisant la rigidité. La paroi 34 peut être circulaire ou former un arc de cercle. Elle peut être un segment de virole, c'est-à-dire avoir une forme de secteur angulaire de cercle. Dans ce cas, un stator forme un cercle grâce à plusieurs segments mis bout-à-bout.The wall may have a web with a profile of revolution about the axis of
Le stator 28 peut comprendre un joint d'étanchéité 38 annulaire ou semi-annulaire, disposé contre la paroi 34, à l'opposé de la pale 40 par rapport à la surface de guidage 54. Ce joint 38 peut être placé dans l'espace annulaire du voile de la paroi 34, et peut combler cet espace. Il peut envelopper les extrémités d'aubes 26 ou de pales 40, et pénétrer la ou chaque portion d'ancrage 42. Le joint 38 peut être un matériau élastomère qui forme une matrice, tel du silicone. Il peut être une couche annulaire de matériau abradable apte à s'effriter en cas de contact avec le rotor. Il peut comprendre une matrice et des particules, telles des billes pour favoriser le caractère friable du joint. Ces billes peuvent coopérer avec le treillis et être configurées pour améliorer l'ancrage.The
Le ou chaque treillis 36 peut former l'extrémité interne, la pointe de l'aube 26. Le ou chaque treillis 36 peut comprendre des tiges 60 reliées les unes aux autres. Elles peuvent être droites ou cintrées. Elles peuvent être liées les unes aux autres à leurs croisements. Les tiges 60 peuvent former des noeuds à leurs intersections, éventuellement intégrés dans leurs sections. Le treillis peut être monobloc.The or each
Le ou chaque treillis 36 peut être plan, et/ou être formé selon une surface gauche, par exemple parallèlement au prolongement radial de la surface intrados ou de la surface extrados. Il peut être essentiellement bidirectionnel, par exemple en présentant des mailles plates formées par ses tiges 60. Le ou chaque treillis peut être tridimensionnel, et présenter des mailles polyédriques dont les arrêtes sont formées par les tiges 60. Les mailles peuvent être des tétraèdres et/ou des cubes. Ses tiges 60 peuvent être agencées selon au moins trois directions, par exemple perpendiculaires les unes aux autres. Les tiges 60 peuvent former des jeux de tiges 60 présentant des mêmes directions, et/ou des mêmes cintres.The or each
Le ou chaque treillis 36 peut s'étendre dans le prolongement radial de la pale 40. Il peut s'étendre entre le bord d'attaque 50 et le bord de fuite 52, éventuellement il dépasse de ces bords. Il peut s'étendre sur la majorité, préférentiellement sur la totalité de la corde de la pale 40 au niveau de la surface de guidage 54. Le ou chaque treillis 36 peut former plusieurs mailles le long de la pale 40, préférentiellement au moins dix mailles, plus préférentiellement au moins cinquante mailles. Le ou chaque treillis 36 peut s'étendre sur la majorité de la longueur axiale de la paroi 34. L'allongement axial du treillis 36 permet de limiter le basculement de la paroi 34 par rapport à l'aube 26, ce qui peut se produire lorsque la paroi est courte selon la circonférence. Au moins une tige 60 ou un jeu de tiges 60 peut s'étendre sur la majorité, éventuellement sur la totalité axiale de la pale 40 et/ou de la portion d'ancrage 42.The or each
Le ou chaque treillis 36 peut présenter un maillage variable, hétérogène. Les mailles peuvent se resserrer vers la pale 40, et éventuellement au niveau du bord d'attaque 50 et du bord de fuite 52, par exemple pour augmenter les efforts que peuvent se transmettre les tiges 60 du treillis 36 en cas d'ingestion. Les tiges 60 peuvent se multiplier et/ou devenir plus fines vers l'intérieur. La compacité de chaque treillis 36 est inférieure à 90%, préférentiellement inférieure à 50%, plus préférentiellement inférieure à 5%. La compacité peut doubler d'un extrême à l'autre. Elle peut varier de 10%, préférentiellement de 30%. Alternativement, le maillage peut être constant, homogène, éventuellement localement.The or each
Le ou chaque treillis 36 peut être ancré dans le joint 38 et/ou dans le matériau même formant la paroi 34 et la surface de guidage 54. Le treillis 36 est noyé dans le matériau du joint 38, les tiges 60 se mêlent au joint 38. Le joint 38 pénètre et occupe les mailles du treillis de sorte à les combler. De la sorte, le joint 38 rempli totalement l'espace que le treillis, via ses tiges, n'occupe pas. Toutes ces propriétés du joint sont transposables au matériau de la paroi. Le joint 38 peut être moulé sur la paroi, ou encore projeté. Le treillis 36 peut s'étendre sur la majorité de l'épaisseur du profil de révolution du joint 36. Cette profondeur d'ancrage dans le joint améliore la rétention, et l'effet de scellement.The or each
La
La rangée d'aubes peut être une rangée annulaire, ou semi-annulaire ; c'est-à-dire qui décrit un secteur angulaire d'un cercle. Les plateformes 44 peuvent être en contact les unes avec les autres grâce à leurs bords latéraux pour positionner les aubes 26, et donc la paroi 34. Au moins un ou chaque treillis 36 peut s'étendre radialement dans le prolongement de l'épaisseur de la pale 40, l'épaisseur pouvant être entendue selon la circonférence. Au moins un ou chaque treillis 36 peut prolonger le profil aérodynamique de la pale 40 au niveau de la surface de guidage 54, éventuellement en reproduisant l'aspect cambré dudit profil.The row of blades may be an annular or semi-annular row; that is to say which describes an angular sector of a circle.
Au moins un ou chaque treillis 36 peut former plusieurs mailles selon l'épaisseur de la pale 40, par exemple au moins deux, préférentiellement au moins cinq, plus préférentiellement au moins dix mailles. Au moins un ou chaque treillis 36 peut présenter, au niveau radialement de son épaisseur maximale, plusieurs tiges qui s'étendent principalement axialement. Le treillis 36 peut être plus large que la pale 40 et moins large que l'ouverture 56 associée.At least one or each
La hauteur d'au moins un ou de chaque treillis 36 peut être supérieure à l'épaisseur maximale de la pale 40, préférentiellement au moins trois fois supérieure. Au moins un ou chaque treillis 36 peut être à distance radialement de l'ouverture 56 associée, et/ou de la surface interne du joint 38. Au moins un ou chaque treillis 36 peut présenter une enveloppe générale dont les surfaces sont inclinée par rapport à la surface intrados 62 et à la surface extrados 64 de l'aube associée au niveau de la surface de guidage 54.The height of at least one or each
La présence de plateformes de fixation 44 est entièrement optionnelle, car chaque aube peut comprendre deux treillis pour être ancrée à deux parois. Au moins une ou chaque aube 26 de la rangée peut comprendre une première portion d'ancrage interne ancrée grâce à son premier treillis à la virole interne 34, et une deuxième portion d'ancrage externe ancrée grâce à un deuxième treillis au carter externe 30. Les treillis sont séparés par la pale, chacun d'eux peut être ancré dans l'épaisseur du voile du carter externe, notamment lorsque ce dernier est moulé.The presence of
Au moins une ou chaque aube 26, en particulier sa pale 40, son treillis 36 et éventuellement sa plateforme 44 ; ou sa pale et ses treillis sont venus de matière et peuvent être réalisés par fabrication additive. Ils peuvent être réalisés à base de poudre titane ou polymère de sorte à former un ensemble venu de matière. L'aube peut former un élément monobloc avec une structure mixte, en présentant une pale pleine et un treillis partiellement vide.At least one or each
L'aube peut être produite sous la forme de rangée d'aubes, avec au moins une ou plusieurs aubes à treillis d'ancrage, et éventuellement d'autres moyens de fixation du même côté radial que les treillis sur d'autres aubes. Dans cette alternative de réalisation, la rangée d'aubes peut présenter une plateforme commune à plusieurs pales.The blade may be produced in the form of a row of vanes, with at least one or more anchor lattice vanes, and possibly other attachment means on the same radial side as the lattice on other vanes. In this alternative embodiment, the row of blades may have a common platform with several blades.
Claims (15)
la portion d'ancrage (42) de l'aube comprend un treillis (36) ancré à la paroi (34) de sorte à fixer ladite aube (26) à la paroi (34) via le treillis (36).Stator (28) for axial turbomachine (2), in particular compressor (4; 6), the stator (28) comprising:
the anchoring portion (42) of the blade comprises a lattice (36) anchored to the wall (34) so as to fix said blade (26) to the wall (34) via the lattice (36).
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP14178502.2A EP2977559B1 (en) | 2014-07-25 | 2014-07-25 | Axial turbomachine stator and corresponding turbomachine |
CA2897889A CA2897889A1 (en) | 2014-07-25 | 2015-07-20 | Blade with sealed lattice in a shroud of an axial turbomachine compressor |
RU2015130479A RU2696177C2 (en) | 2014-07-25 | 2015-07-23 | Axial turbomachine |
US14/808,256 US9957980B2 (en) | 2014-07-25 | 2015-07-24 | Vane with sealed lattice in a shroud of an axial turbomachine compressor |
CN201510445706.3A CN105275869B (en) | 2014-07-25 | 2015-07-27 | There is the blade of sealing screen work in the cover of axial-flow turbine unit compressor |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP14178502.2A EP2977559B1 (en) | 2014-07-25 | 2014-07-25 | Axial turbomachine stator and corresponding turbomachine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2977559A1 true EP2977559A1 (en) | 2016-01-27 |
EP2977559B1 EP2977559B1 (en) | 2017-06-07 |
Family
ID=51228321
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP14178502.2A Active EP2977559B1 (en) | 2014-07-25 | 2014-07-25 | Axial turbomachine stator and corresponding turbomachine |
Country Status (5)
Country | Link |
---|---|
US (1) | US9957980B2 (en) |
EP (1) | EP2977559B1 (en) |
CN (1) | CN105275869B (en) |
CA (1) | CA2897889A1 (en) |
RU (1) | RU2696177C2 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3351320A3 (en) * | 2017-01-23 | 2018-08-01 | General Electric Company | System and method for the hybrid construction of multi-piece parts |
Families Citing this family (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
USD871468S1 (en) * | 2017-03-28 | 2019-12-31 | General Electric Company | Flow ingestion discourager with ridged pattern for a turbomachine shroud |
BE1025753B1 (en) * | 2017-11-30 | 2019-07-04 | Safran Aero Boosters S.A. | DRAIN PLATFORM SEALING - CASING IN AXIAL TURBOMACHINE COMPRESSOR |
GB201816989D0 (en) * | 2018-10-18 | 2018-12-05 | Rolls Royce Plc | Debris retention |
FR3091893B1 (en) * | 2019-01-18 | 2021-09-03 | Safran Helicopter Engines | HOLLOW DAWN CONTAINING AN INTERIOR LATTICE |
FR3092137B1 (en) * | 2019-01-30 | 2021-02-12 | Safran Aircraft Engines | Turbomachine stator sector with high stress areas |
US11352895B2 (en) | 2019-10-29 | 2022-06-07 | Raytheon Technologies Corporation | System for an improved stator assembly |
US12006842B1 (en) | 2023-06-02 | 2024-06-11 | Rtx Corporation | Airfoil with sandwich composite |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2418387A1 (en) * | 2010-08-11 | 2012-02-15 | Techspace Aero S.A. | Shroud ring of an axial turbomachine compressor |
EP2735707A1 (en) | 2012-11-27 | 2014-05-28 | Techspace Aero S.A. | Axial turbomachine guide nozzle with segmented inner shroud and corresponding compressor |
Family Cites Families (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2772069A (en) * | 1951-10-31 | 1956-11-27 | Gen Motors Corp | Segmented stator ring assembly |
FR2073239A1 (en) * | 1969-12-01 | 1971-10-01 | Snecma | |
US3932056A (en) * | 1973-09-27 | 1976-01-13 | Barry Wright Corporation | Vane damping |
GB2043798B (en) * | 1979-03-14 | 1983-01-12 | Rolls Royce | Gas turbine stator vane assembly |
GB2254378B (en) * | 1981-12-30 | 1993-03-31 | Rolls Royce | Gas turbine engine ring shroud ring mounting |
US4861229A (en) * | 1987-11-16 | 1989-08-29 | Williams International Corporation | Ceramic-matrix composite nozzle assembly for a turbine engine |
RU2006591C1 (en) * | 1992-01-27 | 1994-01-30 | Уральский научно-исследовательский институт композиционных материалов | Compressor composite blade |
US6264369B1 (en) * | 1999-01-29 | 2001-07-24 | General Electric Company | Variable vane seal and washer materials |
EP1213484B1 (en) * | 2000-12-06 | 2006-03-15 | Techspace Aero S.A. | Compressor stator stage |
DE10346239A1 (en) * | 2003-10-06 | 2005-04-21 | Alstom Technology Ltd Baden | Method for fixing the blading of a turbomachine and fixing device |
EP1936121B1 (en) * | 2006-12-22 | 2012-05-02 | Techspace Aero | Angular setting of turbomachine stator vanes. |
FR2928963B1 (en) * | 2008-03-19 | 2017-12-08 | Snecma | TURBINE DISPENSER FOR A TURBOMACHINE. |
EP2196629B1 (en) * | 2008-12-11 | 2018-05-16 | Safran Aero Boosters SA | Segmented composite shroud ring of an axial compressor |
EP2218918A1 (en) * | 2009-02-13 | 2010-08-18 | Siemens Aktiengesellschaft | Axial turbo compressor for a gas turbine with low blade-tip leakage losses and diffuser losses |
FR2952052B1 (en) * | 2009-10-30 | 2012-06-01 | Snecma Propulsion Solide | THERMOSTRUCTURAL COMPOSITE MATERIAL PIECE OF LOW THICKNESS AND MANUFACTURING METHOD THEREFOR. |
FR2976968B1 (en) * | 2011-06-21 | 2015-06-05 | Snecma | TURBOMACHINE COMPRESSOR COMPRESSOR OR TURBINE DISPENSER PART AND METHOD FOR MANUFACTURING THE SAME |
EP2586989B1 (en) * | 2011-10-27 | 2015-04-29 | Techspace Aero S.A. | Co-injected composite shroud of an axial turbomachine compressor |
-
2014
- 2014-07-25 EP EP14178502.2A patent/EP2977559B1/en active Active
-
2015
- 2015-07-20 CA CA2897889A patent/CA2897889A1/en not_active Abandoned
- 2015-07-23 RU RU2015130479A patent/RU2696177C2/en active
- 2015-07-24 US US14/808,256 patent/US9957980B2/en active Active
- 2015-07-27 CN CN201510445706.3A patent/CN105275869B/en active Active
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2418387A1 (en) * | 2010-08-11 | 2012-02-15 | Techspace Aero S.A. | Shroud ring of an axial turbomachine compressor |
EP2735707A1 (en) | 2012-11-27 | 2014-05-28 | Techspace Aero S.A. | Axial turbomachine guide nozzle with segmented inner shroud and corresponding compressor |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3351320A3 (en) * | 2017-01-23 | 2018-08-01 | General Electric Company | System and method for the hybrid construction of multi-piece parts |
US10830071B2 (en) | 2017-01-23 | 2020-11-10 | General Electric Company | System and method for the hybrid construction of multi-piece parts |
US11766722B2 (en) | 2017-01-23 | 2023-09-26 | General Electric Company | Method for the hybrid construction of multi-piece parts |
Also Published As
Publication number | Publication date |
---|---|
US20160025108A1 (en) | 2016-01-28 |
RU2696177C2 (en) | 2019-07-31 |
US9957980B2 (en) | 2018-05-01 |
CA2897889A1 (en) | 2016-01-25 |
RU2015130479A3 (en) | 2019-01-17 |
EP2977559B1 (en) | 2017-06-07 |
CN105275869A (en) | 2016-01-27 |
RU2015130479A (en) | 2017-01-26 |
CN105275869B (en) | 2018-08-28 |
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