EP3290656A1 - Inner shroud and orientable vane of an axial turbomachine compressor and manufacturing process - Google Patents
Inner shroud and orientable vane of an axial turbomachine compressor and manufacturing process Download PDFInfo
- Publication number
- EP3290656A1 EP3290656A1 EP17186472.1A EP17186472A EP3290656A1 EP 3290656 A1 EP3290656 A1 EP 3290656A1 EP 17186472 A EP17186472 A EP 17186472A EP 3290656 A1 EP3290656 A1 EP 3290656A1
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- EP
- European Patent Office
- Prior art keywords
- bearing
- assembly
- ferrule
- turbomachine
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- 238000004519 manufacturing process Methods 0.000 title 1
- 238000000926 separation method Methods 0.000 claims abstract description 14
- 238000000034 method Methods 0.000 claims abstract description 11
- 238000011144 upstream manufacturing Methods 0.000 claims description 13
- 239000000463 material Substances 0.000 claims description 5
- 230000004323 axial length Effects 0.000 claims description 3
- 238000005192 partition Methods 0.000 claims description 3
- 238000007789 sealing Methods 0.000 claims description 3
- 238000012423 maintenance Methods 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000014759 maintenance of location Effects 0.000 description 2
- BASFCYQUMIYNBI-UHFFFAOYSA-N platinum Chemical compound [Pt] BASFCYQUMIYNBI-UHFFFAOYSA-N 0.000 description 2
- 230000000903 blocking effect Effects 0.000 description 1
- 230000000295 complement effect Effects 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 229910052697 platinum Inorganic materials 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 210000003462 vein Anatomy 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
- F04D29/40—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
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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
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially 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
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
- F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
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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
- F04D29/00—Details, component parts, or accessories
- F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
- F04D29/056—Bearings
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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
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2240/00—Components
- F05B2240/10—Stators
- F05B2240/12—Fluid guiding means, e.g. vanes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/50—Bearings
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/80—Platforms for stationary or moving blades
Definitions
- the invention relates to the field of steerable blades axial turbomachine. More specifically, the invention relates to the pivot connection between an inner shell and a steerable rotor blade. The invention also relates to an axial turbomachine, in particular an aircraft turbojet engine or an aircraft turboprop engine.
- vanes can equip a stator housing turbojet compressor.
- Such vanes may pivot during engine operation. Their arched blades tilt relative to the primary flow through which they adapt their action according to engine speed and flight conditions. The operating range and efficiency are thus extended.
- the inner shell which is suspended from the steerable vanes can be split into two axial parts. These two parts can be assembled to enclose the rotating bearings around the inner journals of the steerable vanes.
- the document FR 3,009,335 A1 discloses a rectifier blade guide device with a variable turbine engine timing angle.
- the device comprises a casing from which radially a row of adjustable vanes.
- An inner ferrule is attached to these adjustable vanes.
- the inner ferrule is suspended from the adjustable vanes by means of cylindrical bushings shod around the internal trunnions of the adjustable vanes.
- the assembly of the inner ferrule is carried out by axial approximation of its axial portions, while enclosing the cylindrical bushings.
- this assembly operation is complex as the temporary retention of the sleeves in a ferrule portion is unstable.
- 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 maintenance of a bearing articulating a steerable blade relative to a ferrule. The invention also aims to provide a simple solution, resistant, lightweight, economical, reliable, easy to produce, convenient maintenance, waterproof, and easy inspection.
- the subject of the invention is an assembly for an axial turbomachine stator, in particular for a turbomachine compressor, the assembly comprising: a shell, optionally an inner shell, which is divided axially into two parts; a pocket formed in the shell; a bearing disposed in the pocket; and a steerable blade pivotally mounted in the bearing about a pivot axis; remarkable in that the shell comprises an axial separation interface parts which is axially offset from the pivot axis of the steerable blade.
- the bearing ensures a seal between the steerable blade and the inner shell, optionally the bearing completely fills the pocket.
- the separation interface defines axially the bearing, one of the parts possibly comprising a flat circular surface in contact with the bearing.
- the assembly comprises an outer monoblock shell to which the steerable blade is mounted.
- the bearing is longer axially than broad depending on the circumference, and / or wider than radially thick.
- the bag comprises a sealed bottom, possibly in contact with the bearing.
- the bearing comprises two generally parallel lateral faces, said faces possibly extending over most of the axial length of said bearing.
- the bag is predominantly or totally formed in one of the parts, possibly in the upstream part.
- the downstream part comprises an annular seal, possibly with an abradable material, which is separated axially and / or radially from the bearing.
- the bearing comprises an outer face with a flat and circular surface.
- the bearing comprises a through hole and axially eccentric.
- the bearing comprises rotational locking means, in particular a planar face cooperating with a pocket partition.
- the bearing comprises a portion in radial excess partially forming the outer surface of the ferrule.
- the steerable blade comprises a disk with a contour, the extra-thick portion axially separating said disk from one of the parts.
- the bearing comprises a semicircular axial portion.
- the blade comprises an external pin and / or an internal pin cooperating with the bearing.
- the journal in particular the journal, is remote from the axial separation interface.
- the axial separation interface is a plane, and / or circularly and axially cut the ferrule.
- the bearing surrounds the inner pin and / or is in one piece.
- the bearing completely fills the pocket between the blade and the ferrule.
- At least one or each part of the ferrule is in one piece.
- the inner ring or one of the parts has a general profile of revolution which is longer, or at least twice as long, or at least three times longer axially than radially thick.
- the pivot axis of the steerable blade is inside one of the parts, and / or at a distance axially from the other of the two parts.
- the pivot axis of the steerable blade is inside the annular envelope of one of the parts, and / or at an axial distance from the annular envelope of the other of the two parts.
- the sealed bottom marries the bearing over its entire axial length.
- the depth of the pocket increases upstream, particularly at the level of the extra thickness of the bearing.
- At least one of the parts comprises axial partition walls of the pockets.
- the invention also relates to an assembly for axial turbomachine stator, the assembly comprising: a ferrule which is divided axially into two parts via an axial separation interface; a pocket formed in the shell; a bearing disposed in the pocket; and a steerable blade pivotally mounted in the bearing about a pivot axis; remarkable in that the pocket comprises a sealed bottom, possibly in contact with the bearing.
- the invention also relates to an assembly for axial turbomachine stator, the assembly comprising: a ferrule which is divided axially into two parts via an axial separation interface and which comprises an annular surface for guiding an annular flow of the turbomachine; a formed pocket in the ferrule; a bearing disposed in the pocket; and a steerable blade pivotally mounted in the bearing about a pivot axis; remarkable in that the bearing comprises a portion in radial excess partially forming the guide surface of the ferrule.
- the invention also relates to a turbomachine comprising a stator assembly, characterized in that the assembly is in accordance with the invention, preferably the turbomachine comprises an intermediate casing with an internal hub.
- the intermediate casing comprises a downstream face; the assembly being mounted on said downstream face.
- one of the parts of the ferrule is in contact with the inner hub, and / or one of the parts of the ferrule is axially spaced from the inner hub.
- the subject of the invention is also a method of assembling an assembly for a turbomachine stator, the assembly comprising an outer ferrule, an inner ferrule with a pocket occupied by a rotating bearing in connection with an orientable blade, the inner ferrule being axially split into a first portion and a second portion, the method comprising the steps of: (b) placing a first ferrule portion; (c) radial introduction of the steerable blade into a support; (d) radial engagement of the bearing within the steerable blade; remarkable in that the bearing comprises an axial guide face, and in that the method further comprises a step (e) mounting the second portion by sliding against the axial guide face of the bearing; the assembly being optionally in accordance with the invention.
- the bearing slides radially against the first part, in particular against the downstream part.
- step (b) during step (b) implementation of a first part, said part cooperates with a sealing device of the rotor of the turbomachine.
- each object of the invention is also applicable to the other objects of the invention.
- each object of the invention is combinable with other objects.
- the Objects of the invention are also combinable with the embodiments of the description, which in addition are combinable with each other.
- the invention optimizes the maintenance of the bearings due to their asymmetry which has repercussions on the parts of the shell. Staggering the interface between the parts also makes it possible to offer more space for use of a temporary socket holding tool. In addition, the outline of the bearings allows them to better gain their place in the pockets. The stator is more economical to produce.
- the configuration of the ferrule parts like the filling character of the bearings; increases the sealing and therefore the efficiency of the turbomachine.
- the closed form of the bottom of the pockets further increases the seal, while increasing the rigidity of the corresponding part.
- inner and outer refer to a positioning relative to the axis of rotation of an axial turbomachine.
- the axial direction corresponds to the direction along the axis of rotation of the turbomachine.
- the radial direction is perpendicular to the axis of rotation. Upstream and downstream are in reference to the main flow direction of the flow in the 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.
- 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 blower, 16 is coupled to the rotor 12 and generates a flow of air which splits into a primary flow 18 passing through the various levels mentioned above of the turbomachine, and a secondary flow 19 passing through a annular duct (partially shown) by generating a thrust useful to the propulsion of an aircraft.
- the figure 2 is a sectional view of a compressor portion of an axial turbomachine such as that of the figure 1 .
- the compressor may be a low-pressure compressor 4.
- the compressor comprises a stator 20 with an integral outer shell 22 which can form the outer casing of the compressor.
- the outer shell 22 is in one piece. It describes a closed loop. It has a continuity of circular material and / or a circular homogeneity. It can be monobloc along its entire length. It can include a portion of matter.
- the rotor 12 may comprise several rows of rotor blades 24, for example two or three or more rows of rotor (only one visible). Despite the rotation of the rotor 12, the inclination in the space of the ropes of the rotor blades 24 remains invariant with respect to the axis of rotation 14.
- the rotor blades 24 can form a one-piece disc; that is to say that they are indissociable from their support rim 25. Such an arrangement is also known by the term "blisk”.
- the compressor 4 comprises several rectifiers, for example at least two, or at least three or at least four rectifiers.
- Each rectifier comprises an annular row of stator vanes 26. These vanes are stator in the sense that they are mounted on the stator 20 and therefore remain in contact with the latter.
- the rectifiers are associated with the fan or with a row of rotor vanes 24 to straighten their air flows, so as to convert the speed of the flow into static pressure.
- the stator vanes 26 comprise pilot-driven stator vanes 26. These orientable vanes 26 extend radially inwardly of the outer ferrule 22 and describe an annular array. These steerable vanes 26 are also called variable-pitch vanes, or according to the acronym "VSV” for "Variable Stator Vane”. Their particularity is that they can pivot on themselves, so that the inclination of their ropes can vary with respect to the axis of rotation 14 of the compressor 4, and during its operation.
- the steerable vanes 26 can pivot relative to the flow 18, so that they cover more or less fluid vein with their blades. They may further intercept the primary stream 18. The circumferential width they occupy may vary. Their leading edge and their trailing edge can move toward or away from the blades of the same row. Being more or less inclined relative to the general direction of flow, they deviate more or less the primary flow 18 to modulate the flow recovery they provide. Thus, the turbomachine and the compressor can follow different yield curves during operation.
- the stator vanes may comprise other annular rows of blades 28; these other blades being optionally fixed orientation or controlled orientation.
- the stator 20 of the compressor 4 comprises an inner ferrule 30 suspended at the inner ends of the steerable vanes 26, but retaining the pivoting nature of the steerable vanes 26.
- the inner ferrule 30 is equipped with rotating bearings 32 which are mounted around internal journals 34 of the steerable vanes 26. Radially opposite, the steerable vanes 26 have external journals 36 engaged in orifices 38, possibly formed through bosses 40.
- the pins (34; 36) can form cylindrical rods, and can be integral with their blade.
- the steerable blade control system is well known to those skilled in the art and will not be detailed further.
- the stator 20 comprises an intermediate casing 42, forming part of the bearing structure of the turbomachine.
- This intermediate casing 42 may receive a separation spout (not shown).
- the intermediate casing 42 may comprise an outer portion 44, casing arms 46 forming supports passing through the primary stream 18, and an inner hub 48 which can join the inner shell 30.
- the outer shell 22 may comprise an annular wall 50 and an upstream flange 52 fixed to the outer portion 44 of the intermediate casing 42.
- the wall 50 may be integral. It may extend axially along the blades 26 and optionally other vanes.
- the inner surface 56 of the outer shell 22 has an internal diameter which decreases downstream and which matches the outer ends of the rotor blades 24. This configuration therefore requires placing the rotor blades 24 in the external ferrule 22 before mounting the steerable vanes 26 and their inner ferrule 30. The opposite would not be physically possible because of the one-piece nature of the outer ferrule 22.
- the inner ferrule 30 is split. It is divided axially into an upstream portion 60 and a downstream portion 62. These portions may each form a closed loop. At least one or each portion (60; 62) is integral, i.e. present (s) a continuity of circular material. Alternatively, one of them is angularly segmented. However, a one-piece configuration improves the rigidity and retention of the inner shell 30 via the internal pins 34, which form pivot links; a mechanical connection with a single degree of freedom.
- the figure 3 sketch a plan view of the inner ferrule 30 of the figure 2 the bearings are not shown for the sake of clarity.
- the axis of rotation 14 is drawn.
- the upstream portion 60 and the downstream portion 62 are shown from the outside.
- the upstream portion 60 has an annular row of pockets 64, four of which are shown.
- the pockets 64 each have a bottom 66 closed to seal against the downstream portion 62. They can end against the axial separation interface 68 of the axial portions (60; 62).
- the axial separation interface 68 may be a plane perpendicular to the axis of rotation 14, or be substantially conical.
- the pockets 66 have forms of the letter "U" returned, the bearings being of complementary shape to that of these pockets 64. These pockets 64 are separated by bulkheads 69.
- the figure 4 illustrates the bearing 32 in an isometric view, the bearing may correspond to the bearing shown in relation to the figures 2 and 3 .
- the bearing 32 is monobloc. It has a hemicylindrical upstream portion, and a rectangular downstream portion having lateral faces 70 of axial guidance. These faces 70 may be parallel.
- An orifice 72 for receiving the inner pin of the steerable blade is at the interface of the portions.
- a disk-shaped flat surface 74 surrounds the orifice 72.
- the bearing has a radial excess thickness 76, which is in elevation relative to the plane surface 74. The extra thickness 76 can join an axial end of the bearing, for example its downstream facet 78 plane which allows blocking in rotation against the downstream part of the ferrule.
- the figure 5 corresponds to an enlargement of a zone delimited in figure 2 .
- the section of the inner ring 30 at the level of an orientable blade 26 and its bearing 32 coincides with the pivot axis 80 of the internal pin 34.
- the pivot axis 80 is remote from the axial interface 68 between the portions (60; 62). This makes it possible to better maintain the bearing 32 in one of the parts; in this case in the upstream part 60.
- the remote aspect can be measured in the material of the ferrule 30.
- the extra thickness 76 is flush with the outside of the ferrule 30.
- the excess thickness 76 may partially form the outer surface 82 of the inner ferrule 30; outer surface 82 which delimits and guide the primary flow 18 in the turbomachine.
- This extra thickness 76 makes it possible to fill a space of the ferrule 30 while accommodating its compactness.
- the profile of the inner shell may have a length greater than or equal to twice its radial thickness.
- the excess thickness 76 can form a separation between the downstream portion 62 and the platinum disk 84 of the steerable blade 26. In particular, it can slide against the cylindrical contour of the disk 84.
- the rotor 12 cooperates sealingly with the downstream part 62, possibly at an abradable seal 86.
- the bearing 32 does not overlap the annular seal 86 since the interface 68 separates them.
- the figure 6 is a diagram of a method of assembling a turbomachine.
- the entities of the turbomachine can correspond to those described in connection with the Figures 1 to 5 .
- the first portion in place is in contact with the rotor, for example around and / or in contact with a rotor seal.
- This seal can be a game of wipers.
- the seal may center the downstream portion relative to the rotor.
- the other part can be free of joint.
- step (d) engagement 106 the bearing slides radially against the first part, in particular against the downstream part, and is shod around the inner pin of the steerable blade.
- step (e) mounting 108 the upstream portion is translated axially while being guided by the guide faces. Since the bearings can rotate relative to the journals, they rotate so as to be in their pocket, which simplifies the approach of the upstream part.
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Abstract
L'invention propose un ensemble pour stator de compresseur de turbomachine. L'ensemble comprend : une virole (30), éventuellement une virole interne (30), qui est divisée axialement en deux parties ; une poche formée dans la virole (30); un palier (32) disposé dans la poche ; et une aube orientable (26) montée de manière pivotante dans le palier (32) autour d'un axe de pivotement (80). La virole (30) comprend une interface de séparation axiale (68) des parties (60 ; 62) qui est décalée axialement de l'axe de pivotement (80) de l'aube orientable (26). L'invention propose également un procédé d'assemblage de l'ensemble.The invention proposes an assembly for turbomachine compressor stator. The assembly comprises: a shell (30), optionally an inner shell (30), which is divided axially into two parts; a pocket formed in the ferrule (30); a bearing (32) disposed in the pocket; and a steerable blade (26) pivotally mounted in the bearing (32) about a pivot axis (80). The ferrule (30) includes an axial separation interface (68) of the portions (60; 62) which is axially offset from the swivel axis (80) of the steerable blade (26). The invention also proposes a method of assembling the assembly.
Description
L'invention se rapporte au domaine des aubes orientables de turbomachine axiale. Plus précisément, l'invention concerne la liaison pivot entre une virole interne et une aube orientable de turbomachine. L'invention a également trait à une turbomachine axiale, notamment un turboréacteur d'avion ou un turbopropulseur d'aéronef.The invention relates to the field of steerable blades axial turbomachine. More specifically, the invention relates to the pivot connection between an inner shell and a steerable rotor blade. The invention also relates to an axial turbomachine, in particular an aircraft turbojet engine or an aircraft turboprop engine.
De manière courante, plusieurs rangées d'aubes orientables peuvent équiper un carter statorique de compresseur de turboréacteur. De telles aubes peuvent pivoter pendant le fonctionnement du moteur. Leurs pales cambrées basculent par rapport au flux primaire qu'elles traversent, ce qui permet d'adapter leur action en fonction du régime moteur et des conditions de vol. La plage de fonctionnement et le rendement sont ainsi étendus.Commonly, several rows of steerable vanes can equip a stator housing turbojet compressor. Such vanes may pivot during engine operation. Their arched blades tilt relative to the primary flow through which they adapt their action according to engine speed and flight conditions. The operating range and efficiency are thus extended.
Dans une optique de simplification de montage, ou tout simplement pour que le montage soit physiquement possible, la virole interne qui est suspendue aux aubes orientables peut être scindée en deux parties axiales. Ces deux parties peuvent se réunir afin de renfermer les paliers tournants autour des tourillons internes des aubes orientables.In order to simplify assembly, or simply so that mounting is physically possible, the inner shell which is suspended from the steerable vanes can be split into two axial parts. These two parts can be assembled to enclose the rotating bearings around the inner journals of the steerable vanes.
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 le maintien d'un palier articulant une aube orientable par rapport à une virole. L'invention a également pour objectif de proposer une solution simple, résistante, légère, économique, fiable, facile à produire, commode d'entretien, étanche, et d'inspection aisée.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 maintenance of a bearing articulating a steerable blade relative to a ferrule. The invention also aims to provide a simple solution, resistant, lightweight, economical, reliable, easy to produce, convenient maintenance, waterproof, and easy inspection.
L'invention a pour objet un ensemble pour stator de turbomachine axiale, notamment pour compresseur de turbomachine, l'ensemble comprenant : une virole, éventuellement une virole interne, qui est divisée axialement en deux parties ; une poche formée dans la virole ; un palier disposé dans la poche ; et une aube orientable montée de manière pivotante dans le palier autour d'un axe de pivotement ; remarquable en ce que la virole comprend une interface de séparation axiale des parties qui est décalée axialement de l'axe de pivotement de l'aube orientable.The subject of the invention is an assembly for an axial turbomachine stator, in particular for a turbomachine compressor, the assembly comprising: a shell, optionally an inner shell, which is divided axially into two parts; a pocket formed in the shell; a bearing disposed in the pocket; and a steerable blade pivotally mounted in the bearing about a pivot axis; remarkable in that the shell comprises an axial separation interface parts which is axially offset from the pivot axis of the steerable blade.
Selon un mode avantageux de l'invention, le palier assure une étanchéité entre l'aube orientable et la virole interne, éventuellement le palier remplit totalement la poche.According to an advantageous embodiment of the invention, the bearing ensures a seal between the steerable blade and the inner shell, optionally the bearing completely fills the pocket.
Selon un mode avantageux de l'invention, l'interface de séparation délimite axialement le palier, l'une des parties comprenant éventuellement une surface circulaire plate en contact du palier.According to an advantageous embodiment of the invention, the separation interface defines axially the bearing, one of the parts possibly comprising a flat circular surface in contact with the bearing.
Selon un mode avantageux de l'invention, l'ensemble comprend une virole externe monobloc à laquelle l'aube orientable est montée.According to an advantageous embodiment of the invention, the assembly comprises an outer monoblock shell to which the steerable blade is mounted.
Selon un mode avantageux de l'invention, le palier est plus long axialement que large selon la circonférence, et/ou plus large qu'épais radialement.According to an advantageous embodiment of the invention, the bearing is longer axially than broad depending on the circumference, and / or wider than radially thick.
Selon un mode avantageux de l'invention, la poche comprend un fond étanche, éventuellement en contact du palier.According to an advantageous embodiment of the invention, the bag comprises a sealed bottom, possibly in contact with the bearing.
Selon un mode avantageux de l'invention, le palier comprend deux faces latérales généralement parallèles, lesdites faces s'étendant éventuellement sur la majorité de la longueur axiale dudit palier.According to an advantageous embodiment of the invention, the bearing comprises two generally parallel lateral faces, said faces possibly extending over most of the axial length of said bearing.
Selon un mode avantageux de l'invention, la poche est majoritairement ou totalement formée dans l'une des parties, éventuellement dans la partie amont. Selon un mode avantageux de l'invention, la partie aval comprend un joint annulaire, éventuellement avec un matériau abradable, qui est séparé axialement et/ou radialement du palier.According to an advantageous embodiment of the invention, the bag is predominantly or totally formed in one of the parts, possibly in the upstream part. According to an advantageous embodiment of the invention, the downstream part comprises an annular seal, possibly with an abradable material, which is separated axially and / or radially from the bearing.
Selon un mode avantageux de l'invention, le palier comprend une face externe avec une surface plane et circulaire.According to an advantageous embodiment of the invention, the bearing comprises an outer face with a flat and circular surface.
Selon un mode avantageux de l'invention, le palier comprend un orifice traversant et excentré axialement.According to an advantageous embodiment of the invention, the bearing comprises a through hole and axially eccentric.
Selon un mode avantageux de l'invention, le palier comprend des moyens de blocage en rotation, notamment une face plane, coopérant avec une cloison de poche.According to an advantageous embodiment of the invention, the bearing comprises rotational locking means, in particular a planar face cooperating with a pocket partition.
Selon un mode avantageux de l'invention, le palier comprend une portion en surépaisseur radiale formant partiellement la surface externe de la virole. Selon un mode avantageux de l'invention, l'aube orientable comprend un disque avec un contour, la portion en surépaisseur séparant axialement ledit disque de l'une des parties.According to an advantageous embodiment of the invention, the bearing comprises a portion in radial excess partially forming the outer surface of the ferrule. According to an advantageous embodiment of the invention, the steerable blade comprises a disk with a contour, the extra-thick portion axially separating said disk from one of the parts.
Selon un mode avantageux de l'invention, le palier comprend une portion axiale semi-circulaire.According to an advantageous embodiment of the invention, the bearing comprises a semicircular axial portion.
Selon un mode avantageux de l'invention, l'aube comprend un tourillon externe et/ou un tourillon interne coopérant avec le palier.According to an advantageous embodiment of the invention, the blade comprises an external pin and / or an internal pin cooperating with the bearing.
Selon un mode avantageux de l'invention, le tourillon, notamment interne, est à distance de l'interface de séparation axiale.According to an advantageous embodiment of the invention, the journal, in particular the journal, is remote from the axial separation interface.
Selon un mode avantageux de l'invention, l'interface de séparation axiale est un plan, et/ou coupe circulairement et axialement la virole.According to an advantageous embodiment of the invention, the axial separation interface is a plane, and / or circularly and axially cut the ferrule.
Selon un mode avantageux de l'invention, le palier entoure le tourillon interne et/ou est monobloc.According to an advantageous embodiment of the invention, the bearing surrounds the inner pin and / or is in one piece.
Selon un mode avantageux de l'invention, le palier rempli totalement la poche entre l'aube et la virole.According to an advantageous embodiment of the invention, the bearing completely fills the pocket between the blade and the ferrule.
Selon un mode avantageux de l'invention, au moins une ou chaque partie de la virole est monobloc.According to an advantageous embodiment of the invention, at least one or each part of the ferrule is in one piece.
Selon un mode avantageux de l'invention, la virole interne ou l'une des parties présente un profil de révolution général qui est plus long, ou au moins deux fois plus long, ou au moins trois fois plus long axialement qu'épais radialement. Selon un mode avantageux de l'invention, l'axe de pivotement de l'aube orientable est à l'intérieur d'une des parties, et/ou à distance axialement de l'autre des deux parties.According to an advantageous embodiment of the invention, the inner ring or one of the parts has a general profile of revolution which is longer, or at least twice as long, or at least three times longer axially than radially thick. According to an advantageous embodiment of the invention, the pivot axis of the steerable blade is inside one of the parts, and / or at a distance axially from the other of the two parts.
Selon un mode avantageux de l'invention, l'axe de pivotement de l'aube orientable est à l'intérieur de l'enveloppe annulaire de l'une des parties, et/ou à distance axialement de l'enveloppe annulaire de l'autre des deux parties.According to an advantageous embodiment of the invention, the pivot axis of the steerable blade is inside the annular envelope of one of the parts, and / or at an axial distance from the annular envelope of the other of the two parts.
Selon un mode avantageux de l'invention, le fond étanche épouse le palier sur toute sa longueur axiale.According to an advantageous embodiment of the invention, the sealed bottom marries the bearing over its entire axial length.
Selon un mode avantageux de l'invention, la profondeur de la poche augmente vers l'amont, notamment au niveau de la surépaisseur du palier.According to an advantageous embodiment of the invention, the depth of the pocket increases upstream, particularly at the level of the extra thickness of the bearing.
Selon un mode avantageux de l'invention, au moins une des parties comprend des cloisons axiales de séparation des poches.According to an advantageous embodiment of the invention, at least one of the parts comprises axial partition walls of the pockets.
L'invention a également pour objet un ensemble pour stator de turbomachine axiale, l'ensemble comprenant : une virole qui est divisée axialement en deux parties via une interface de séparation axiale ; une poche formée dans la virole; un palier disposé dans la poche ; et une aube orientable montée de manière pivotante dans le palier autour d'un axe de pivotement ; remarquable en ce que la poche comprend un fond étanche, éventuellement en contact du palier. L'invention a également pour objet un ensemble pour stator de turbomachine axiale, l'ensemble comprenant : une virole qui est divisée axialement en deux parties via une interface de séparation axiale et qui comprend une surface annulaire de guidage d'un flux annulaire de la turbomachine ; une poche formée dans la virole; un palier disposé dans la poche ; et une aube orientable montée de manière pivotante dans le palier autour d'un axe de pivotement ; remarquable en ce que le palier comprend une portion en surépaisseur radiale formant partiellement la surface de guidage de la virole.The invention also relates to an assembly for axial turbomachine stator, the assembly comprising: a ferrule which is divided axially into two parts via an axial separation interface; a pocket formed in the shell; a bearing disposed in the pocket; and a steerable blade pivotally mounted in the bearing about a pivot axis; remarkable in that the pocket comprises a sealed bottom, possibly in contact with the bearing. The invention also relates to an assembly for axial turbomachine stator, the assembly comprising: a ferrule which is divided axially into two parts via an axial separation interface and which comprises an annular surface for guiding an annular flow of the turbomachine; a formed pocket in the ferrule; a bearing disposed in the pocket; and a steerable blade pivotally mounted in the bearing about a pivot axis; remarkable in that the bearing comprises a portion in radial excess partially forming the guide surface of the ferrule.
L'invention a également pour objet une turbomachine comprenant un ensemble pour stator, caractérisée en ce que l'ensemble est conforme à l'invention, préférentiellement la turbomachine comprend un carter intermédiaire avec un moyeu interne.The invention also relates to a turbomachine comprising a stator assembly, characterized in that the assembly is in accordance with the invention, preferably the turbomachine comprises an intermediate casing with an internal hub.
Selon un mode avantageux de l'invention, le carter intermédiaire comprend une face aval ; l'ensemble étant monté sur ladite face aval.According to an advantageous embodiment of the invention, the intermediate casing comprises a downstream face; the assembly being mounted on said downstream face.
Selon un mode avantageux de l'invention, l'une des parties de la virole est en contact du moyeu interne, et/ou l'une des parties de la virole est à distance axialement du moyeu interne.According to an advantageous embodiment of the invention, one of the parts of the ferrule is in contact with the inner hub, and / or one of the parts of the ferrule is axially spaced from the inner hub.
L'invention a également pour objet un procédé d'assemblage d'un ensemble pour stator de turbomachine, l'ensemble comprenant une virole externe, une virole interne avec une poche occupée par un palier tournant en liaison avec une aube orientable, la virole interne étant scindée axialement en une première partie et en une deuxième partie, le procédé comprenant les étapes suivantes : (b) mise en place d'une première partie de virole ; (c) introduction radiale de l'aube orientable dans un support ; (d) engagement radial du palier à l'intérieur de l'aube orientable ; remarquable en ce que le palier comprend une face de guidage axial, et en ce que le procédé comprend en outre une étape (e) montage de la deuxième partie en glissant contre la face de guidage axial du palier ; l'ensemble étant éventuellement conforme à l'invention.The subject of the invention is also a method of assembling an assembly for a turbomachine stator, the assembly comprising an outer ferrule, an inner ferrule with a pocket occupied by a rotating bearing in connection with an orientable blade, the inner ferrule being axially split into a first portion and a second portion, the method comprising the steps of: (b) placing a first ferrule portion; (c) radial introduction of the steerable blade into a support; (d) radial engagement of the bearing within the steerable blade; remarkable in that the bearing comprises an axial guide face, and in that the method further comprises a step (e) mounting the second portion by sliding against the axial guide face of the bearing; the assembly being optionally in accordance with the invention.
Selon un mode avantageux de l'invention, lors de l'étape (d) engagement, le palier glisse radialement contre la première partie, notamment contre la partie aval.According to an advantageous embodiment of the invention, during step (d) engagement, the bearing slides radially against the first part, in particular against the downstream part.
Selon un mode avantageux de l'invention, lors de l'étape (b) mise en place d'une première partie, ladite partie coopère avec un dispositif d'étanchéité du rotor de la turbomachine.According to an advantageous embodiment of the invention, during step (b) implementation of a first part, said part cooperates with a sealing device of the rotor of the turbomachine.
De manière générale, les modes avantageux de chaque objet de l'invention sont également applicables aux autres objets de l'invention. Dans la mesure du possible, chaque objet de l'invention est combinable aux autres objets. Les objets de l'invention sont également combinables aux modes de réalisation de la description, qui en plus sont combinables entre eux.In general, the advantageous modes of each object of the invention are also applicable to the other objects of the invention. As far as possible, each object of the invention is combinable with other objects. The Objects of the invention are also combinable with the embodiments of the description, which in addition are combinable with each other.
L'invention optimise le maintien des paliers grâce à leur asymétrie qui se répercute sur les parties de la virole. Décaler l'interface entre les parties permet également d'offrir plus d'espace d'utilisation d'un outil provisoire de maintien des douilles. En outre, le contour des paliers leur permet de mieux gagner leur place dans les poches. Le stator est plus économique à produire.The invention optimizes the maintenance of the bearings due to their asymmetry which has repercussions on the parts of the shell. Staggering the interface between the parts also makes it possible to offer more space for use of a temporary socket holding tool. In addition, the outline of the bearings allows them to better gain their place in the pockets. The stator is more economical to produce.
La configuration des parties de virole ; comme le caractère remplissant des paliers ; augmente l'étanchéité et donc le rendement de la turbomachine. La forme close du fond des poches accroit encore l'étanchéité, tout en augmentant la rigidité de la partie correspondante.The configuration of the ferrule parts; like the filling character of the bearings; increases the sealing and therefore the efficiency of the turbomachine. The closed form of the bottom of the pockets further increases the seal, while increasing the rigidity of the corresponding part.
-
La
figure 1 représente une turbomachine axiale selon l'invention.Thefigure 1 represents an axial turbomachine according to the invention. -
La
figure 2 montre une portion de compresseur de turbomachine selon l'invention.Thefigure 2 shows a portion of turbomachine compressor according to the invention. -
La
figure 3 illustre un développé à plat de la virole selon l'invention.Thefigure 3 illustrates a developed flat of the ferrule according to the invention. -
La
figure 4 est une vue isométrique d'un palier selon l'invention.Thefigure 4 is an isometric view of a bearing according to the invention. -
La
figure 5 illustre un agrandissement de la virole interne de lafigure 2 .Thefigure 5 illustrates an enlargement of the inner shell of thefigure 2 . -
La
figure 6 représente un diagramme du procédé d'assemblage d'un ensemble pour stator de turbomachine selon l'invention.Thefigure 6 represents a diagram of the assembly method of a turbomachine stator assembly according to the invention.
Dans la description qui va suivre, les termes interne et externe renvoient à un positionnement par rapport à l'axe de rotation d'une turbomachine axiale. La direction axiale correspond à la direction le long de l'axe de rotation de la turbomachine. La direction radiale est perpendiculaire à l'axe de rotation. L'amont et l'aval sont en référence au sens d'écoulement principal du flux dans la turbomachine.In the following description, the terms inner and outer refer to a positioning relative to the axis of rotation of an axial turbomachine. The axial direction corresponds to the direction along the axis of rotation of the turbomachine. The radial direction is perpendicular to the axis of rotation. Upstream and downstream are in reference to the main flow direction of the flow in the 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 19 traversant un conduit annulaire (partiellement représenté) en générant une poussée utile à la propulsion d'un avion.An inlet fan commonly referred to as a fan, or blower, 16 is coupled to the
La
Le compresseur comprend un stator 20 avec une virole externe 22 monobloc qui peut former le carter externe du compresseur. La virole externe 22 est d'un seul tenant. Elle décrit une boucle fermée. Elle présente une continuité de matière circulaire et/ou une homogénéité circulaire. Elle peut être monobloc sur toute sa longueur. Elle peut comprendre une portion venue de matière.The compressor comprises a
Le rotor 12 peut comprendre plusieurs rangées d'aubes rotoriques 24, par exemple deux ou trois ou d'avantage de rangées rotoriques (une seule visible). Malgré la rotation du rotor 12, l'inclinaison dans l'espace des cordes des aubes rotoriques 24 reste invariante par rapport à l'axe de rotation 14. Les aubes rotoriques 24 peuvent former un disque monobloc ; c'est-à-dire qu'elles sont indissociables de leur jante support 25. Un tel agencement est également connu sous le terme « blisk ».The
Le compresseur 4 comprend plusieurs redresseurs, par exemple au moins deux, ou au moins trois ou au moins quatre redresseurs. Chaque redresseur comprend une rangée annulaire d'aubes statoriques 26. Ces aubes sont statoriques en ce sens qu'elles sont montées sur le stator 20 et restent donc en contact de ce dernier. Les redresseurs sont associés au fan ou à une rangée d'aubes rotoriques 24 pour redresser leurs flux d'air, de sorte à convertir la vitesse du flux en pression statique.The
Les aubes statoriques 26 comprennent des aubes statoriques à orientation pilotée 26. Ces aubes orientables 26 s'étendent radialement vers l'intérieur de la virole extérieure 22 et décrivent une rangée annulaire. Ces aubes orientables 26 sont également appelées aubes à calage variable, ou selon l'acronyme anglo-saxon « VSV » pour « Variable Stator Vane ». Leur particularité est qu'elles peuvent pivoter sur elles-mêmes, si bien que l'inclinaison de leurs cordes peut varier par rapport à l'axe de rotation 14 du compresseur 4, et ce pendant son fonctionnement.The stator vanes 26 comprise pilot-driven stator vanes 26. These
Leurs aubes peuvent balayer avec leurs cordes un angle d'au moins 30° entre deux positions extrêmes. Leurs faces intrados et extrados peuvent être plus ou moins exposées au flux primaire 18. Les aubes orientables 26 peuvent pivoter par rapport au flux 18, si bien qu'elles couvrent plus ou moins la veine fluide grâce à leurs pales. Elles peuvent intercepter davantage le flux primaire 18. La largeur circonférentielle qu'elles occupent peut varier. Leur bord d'attaque et leur bord de fuite peuvent se rapprocher ou s'éloigner des aubes de la même rangée. En étant plus ou moins inclinées par rapport au sens d'écoulement général, elles dévient plus ou moins le flux primaire 18 pour moduler le redressement de flux qu'elles procurent. Ainsi, la turbomachine et le compresseur peuvent suivre différentes courbes de rendements lors du fonctionnement. Les aubes statoriques peuvent comprendre d'autres rangées annulaires d'aubes 28 ; ces autres aubes étant éventuellement à orientation fixe ou à orientation pilotée.Their blades can sweep with their ropes an angle of at least 30 ° between two extreme positions. Their faces intrados and extrados can be more or less exposed to the
Le stator 20 du compresseur 4 comprend une virole interne 30 suspendue aux extrémités internes des aubes orientables 26, mais tout en conservant le caractère pivotant des aubes orientables 26. A cet effet, la virole interne 30 est équipée de paliers tournants 32 qui sont montés autour des tourillons internes 34 des aubes orientables 26. Radialement à l'opposé, les aubes orientables 26 présentent des tourillons externes 36 engagés dans des orifices 38, éventuellement formés au travers de bossages 40. Les tourillons (34 ; 36) peuvent former des tiges cylindriques, et peuvent être venus de matière avec leur pale. Le système de commande des aubes orientables est bien connu de l'homme du métier et ne sera pas détaillé davantage.The
Le stator 20 comporte un carter intermédiaire 42, faisant partie de la structure portante de la turbomachine. Ce carter intermédiaire 42 peut recevoir un bec de séparation (non représenté). Le carter intermédiaire 42 peut comprendre une portion externe 44, des bras de carter 46 formant des supports traversant le flux primaire 18, et un moyeu interne 48 qui peut rejoindre la virole interne 30.The
La virole externe 22 peut comprendre une paroi annulaire 50 et une bride amont 52 fixée à la portion externe 44 du carter intermédiaire 42. La paroi 50 peut être venue de matière. Elle peut s'étendre tout le long axialement des aubes orientables 26 et éventuellement des autres aubes.The
Selon une option de l'invention, la surface interne 56 de la virole externe 22 présente un diamètre interne qui décroit vers l'aval et qui épouse les extrémités externes des aubes rotoriques 24. Cette configuration impose donc de placer les aubes rotoriques 24 dans la virole externe 22 avant de monter les aubes orientables 26 et leur virole interne 30. Le contraire ne serait pas physiquement possible en raison du caractère monobloc de la virole externe 22.According to an option of the invention, the
En réponse à cette contrainte technique, la virole interne 30 est scindée. Elle est divisée axialement en une partie amont 60 et en une partie aval 62. Ces parties peuvent chacune former une boucle fermée. Au moins une ou chaque partie (60 ; 62) est monobloc, c'est-à-dire qu'elle(s) présent(ent) une continuité de matière circulaire. Alternativement, l'une d'elle est segmentée angulairement. Toutefois une configuration monobloc améliore la rigidité et le maintien de la virole interne 30 via les tourillons internes 34, qui forment des liaisons pivot ; soit une liaison mécanique à un seul degré de liberté.In response to this technical constraint, the
Bien qu'une seule aube orientable 26 et qu'un seul palier 32 ne soient visibles, le présent enseignement peut s'appliquer à toute leur rangée.Although only one
La
La partie amont 60 et la partie aval 62 sont représentées depuis l'extérieur. La partie amont 60 présente une rangée annulaire de poches 64, quatre d'entre elles étant représentées. Les poches 64 présentent chacune un fond 66 fermé permettant une étanchéité contre la partie aval 62. Elles peuvent se terminer contre l'interface de séparation axiale 68 des parties axiales (60 ; 62). L'interface de séparation axiale 68 peut être un plan perpendiculaire à l'axe de rotation 14, ou être sensiblement conique. Les poches 66 ont des formes de la lettre « U » retournée, les paliers étant de forme complémentaire à celle de ces poches 64. Ces poches 64 sont séparées par des cloisons étanches 69.The
La
Le palier 32 est monobloc. Il présente une portion amont hémicylindrique, et une portion aval rectangulaire dotée de faces latérales 70 de guidage axial. Ces faces 70 peuvent être parallèles. Un orifice 72 destiné à recevoir le tourillon interne de l'aube orientable est à l'interface des portions. Une surface plane 74 en forme de disque entoure l'orifice 72. En complément, le palier présente une surépaisseur radiale 76, qui est en élévation par rapport à la surface plane 74. La surépaisseur 76 peut joindre une extrémité axiale du palier, par exemple sa facette aval 78 plane qui permet un blocage en rotation contre la partie aval de la virole.The
Bien qu'un seul palier 32 ne soit représenté, cet enseignement peut s'appliquer à toute sa rangée annulaire.Although only one
La
L'axe de pivotement 80 est distant de l'interface axiale 68 entre les parties (60 ; 62). Ceci permet de mieux maintenir le palier 32 dans l'une des parties ; en l'occurrence dans la partie amont 60. L'aspect distant peut être mesuré dans la matière de la virole 30.The
La surépaisseur 76 affleure l'extérieur de la virole 30. La surépaisseur 76 peut former partiellement la surface extérieure 82 de la virole interne 30 ; surface extérieure 82 qui permet de délimiter et de guider le flux primaire 18 dans la turbomachine. Cette surépaisseur 76 permet de combler un espace de la virole 30 tout en s'accommodant de son caractère compact. Par exemple, le profil de la virole interne peut présenter une longueur supérieure ou égale au double de son épaisseur radiale. La surépaisseur 76 peut former une séparation entre la partie aval 62 et le disque platine 84 de l'aube orientable 26. En particulier, elle peut glisser contre le contour cylindrique du disque 84.The
Le rotor 12 coopère de manière étanche avec la partie aval 62, éventuellement au niveau d'un joint abradable 86. Le palier 32 ne chevauche pas le joint annulaire 86 puisque l'interface 68 les sépare.The
La
Le procédé peut comporter les étapes suivantes, éventuellement réalisées dans l'ordre qui suit :
- (a)-
agencement 100 de la virole externe autour du rotor ; - (b)- mise en
place 102 de la partie aval de la virole interne ; - (c)-
introduction 104 radiale de l'aube orientable dans la virole externe ; - (d)-
engagement 106 radial du palier à l'intérieur de l'aube orientable ; - (e)-
montage 108 de la partie amont de la virole interne en la glissant axialement contre la face de guidage axial du palier.
- (a) -
arrangement 100 of the outer shell around the rotor; - (b) -
establishment 102 of the downstream part of the inner shell; - (c) -
introduction 104 radial blade steerable in the outer shell; - (d) -
radial engagement 106 of the bearing inside the steerable blade; - (e) - mounting 108 of the upstream portion of the inner ring by sliding axially against the axial guide face of the bearing.
Lors de l'étape (b) mise en place 102, la première partie mise en place est en contact du rotor, par exemple autour et/ou au contact d'un joint du rotor. Ce joint peut être un jeu de léchettes. Le joint peut centrer la partie aval par rapport au rotor. L'autre partie peut être libre de joint.During step (b)
Lors de l'étape (d) engagement 106, le palier glisse radialement contre la première partie, notamment contre la partie aval, et est chaussé autour du tourillon interne de l'aube orientable.During step (d)
Pendant l'étape (e) montage 108, la partie amont est translatée axialement tout en étant guidée par les faces de guidage. Puisque les paliers peuvent tourner par rapport aux tourillons, ils tournent de sorte à s'axer dans leur poche, ce qui simplifie le rapprochement de la partie amont.During step (e) mounting 108, the upstream portion is translated axially while being guided by the guide faces. Since the bearings can rotate relative to the journals, they rotate so as to be in their pocket, which simplifies the approach of the upstream part.
Claims (15)
la virole (30) comprend une interface de séparation axiale (68) des parties (60 ; 62), l'axe de pivotement (80) de l'aube orientable (26) étant axialement à distance de ladite interface de séparation axiale (68).Axial turbomachine stator assembly (20), in particular for turbomachine compressor (4; 6), the assembly comprising:
the ferrule (30) comprises an axial separation interface (68) of the portions (60; 62), the pivot axis (80) of the steerable blade (26) being axially spaced from said axial separation interface (68); ).
caractérisé en ce que le palier (32) comprend une face de guidage axial (70),
et en ce que le procédé comprend en outre une étape
characterized in that the bearing (32) comprises an axial guide face (70),
and in that the method further comprises a step
Applications Claiming Priority (1)
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BE2016/5663A BE1024524B1 (en) | 2016-08-30 | 2016-08-30 | INTERNAL VIROL AND DIRECT TANK OF AXIAL TURBOMACHINE COMPRESSOR |
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US (1) | US11512713B2 (en) |
EP (1) | EP3290656B1 (en) |
CN (1) | CN107795525B (en) |
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BE1024605B1 (en) * | 2016-09-27 | 2018-04-26 | Safran Aero Boosters S.A. | CARTRIDGE WITH SUCTION ARMS FOR AXIAL TURBOMACHINE |
US11028709B2 (en) * | 2018-09-18 | 2021-06-08 | General Electric Company | Airfoil shroud assembly using tenon with externally threaded stud and nut |
US20220145905A1 (en) * | 2019-04-01 | 2022-05-12 | Dileep Dasari | Systems And Methods For Increasing The Efficiency Of Axial Ducted Fans |
CN110617117B (en) * | 2019-08-02 | 2022-04-08 | 中国航发贵阳发动机设计研究所 | Method for adjusting throat area of turbine guider |
DE102021129534A1 (en) | 2021-11-12 | 2023-05-17 | MTU Aero Engines AG | Guide vane arrangement of a turbomachine and method for assembling a guide vane arrangement |
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US20120082545A1 (en) * | 2010-09-30 | 2012-04-05 | Brian Peck | Seal arrangement for variable vane |
FR3009335A1 (en) | 2013-07-30 | 2015-02-06 | Snecma | TURBOMACHINE VARIABLE ROTATION ANGLE RECTIFIER AUB GUIDING DEVICE |
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US5639212A (en) * | 1996-03-29 | 1997-06-17 | General Electric Company | Cavity sealed compressor |
DE102006024085B4 (en) * | 2006-05-23 | 2020-04-16 | MTU Aero Engines AG | Turbo compressor in axial design |
US7713022B2 (en) * | 2007-03-06 | 2010-05-11 | United Technologies Operations | Small radial profile shroud for variable vane structure in a gas turbine engine |
US8500394B2 (en) * | 2008-02-20 | 2013-08-06 | United Technologies Corporation | Single channel inner diameter shroud with lightweight inner core |
JP5747703B2 (en) * | 2011-07-13 | 2015-07-15 | 株式会社Ihi | Turbo compressor |
US9932988B2 (en) * | 2013-02-15 | 2018-04-03 | United Technologies Corporation | Bushing arranged between a body and a shaft, and connected to the shaft |
JP5736443B1 (en) * | 2013-12-19 | 2015-06-17 | 川崎重工業株式会社 | Variable vane mechanism |
-
2016
- 2016-08-30 BE BE2016/5663A patent/BE1024524B1/en not_active IP Right Cessation
-
2017
- 2017-08-16 EP EP17186472.1A patent/EP3290656B1/en active Active
- 2017-08-18 US US15/681,162 patent/US11512713B2/en active Active
- 2017-08-22 CA CA2976930A patent/CA2976930A1/en not_active Abandoned
- 2017-08-29 CN CN201710755808.4A patent/CN107795525B/en active Active
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GB749577A (en) * | 1952-07-10 | 1956-05-30 | Havilland Engine Co Ltd | Improvements in or relating to blade ring assemblies for axial flow compressors or turbines |
EP0298894A1 (en) * | 1987-07-08 | 1989-01-11 | United Technologies Corporation | Split shroud compressor |
US4834613A (en) * | 1988-02-26 | 1989-05-30 | United Technologies Corporation | Radially constrained variable vane shroud |
FR2824593A1 (en) * | 2001-05-10 | 2002-11-15 | Snecma Moteurs | Stator blades pivot support installation comprises bringing together two rings comprising half of internal pivot bores and sliding snap ring into groove in junction between rings |
US20120082545A1 (en) * | 2010-09-30 | 2012-04-05 | Brian Peck | Seal arrangement for variable vane |
FR3009335A1 (en) | 2013-07-30 | 2015-02-06 | Snecma | TURBOMACHINE VARIABLE ROTATION ANGLE RECTIFIER AUB GUIDING DEVICE |
Also Published As
Publication number | Publication date |
---|---|
BE1024524A1 (en) | 2018-03-23 |
CN107795525A (en) | 2018-03-13 |
EP3290656B1 (en) | 2021-09-29 |
CA2976930A1 (en) | 2018-02-28 |
US20180058471A1 (en) | 2018-03-01 |
BE1024524B1 (en) | 2018-03-26 |
US11512713B2 (en) | 2022-11-29 |
CN107795525B (en) | 2022-01-04 |
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