EP3290657B1 - Stator with adjustable vanes for the compressor of an axial turbine engine - Google Patents

Stator with adjustable vanes for the compressor of an axial turbine engine Download PDF

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Publication number
EP3290657B1
EP3290657B1 EP17186486.1A EP17186486A EP3290657B1 EP 3290657 B1 EP3290657 B1 EP 3290657B1 EP 17186486 A EP17186486 A EP 17186486A EP 3290657 B1 EP3290657 B1 EP 3290657B1
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EP
European Patent Office
Prior art keywords
blades
row
annular
vanes
turbomachine
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP17186486.1A
Other languages
German (de)
French (fr)
Other versions
EP3290657A1 (en
Inventor
Morgan Vyvey
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aero Boosters SA
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Safran Aero Boosters SA
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Publication of EP3290657A1 publication Critical patent/EP3290657A1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • 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
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/047—Nozzle boxes
    • 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
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/321—Application in turbines in gas turbines for a special turbine stage
    • F05D2220/3216—Application in turbines in gas turbines for a special turbine stage for a special compressor stage
    • F05D2220/3217—Application in turbines in gas turbines for a special turbine stage for a special compressor stage for the first stage of a compressor or a low pressure compressor
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/50—Building or constructing in particular ways
    • F05D2230/53—Building or constructing in particular ways by integrally manufacturing a component, e.g. by milling from a billet or one piece construction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/14—Casings or housings protecting or supporting assemblies within
    • 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
    • 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
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/20—Purpose of the control system to optimize the performance of a machine
    • 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
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/306—Mass flow
    • F05D2270/3061—Mass flow of the working fluid

Definitions

  • the invention relates to the field of stators with blades with controlled orientation for an axial turbomachine.
  • the invention also relates to the assembly of a stator with adjustable vanes.
  • the invention also relates to an axial turbomachine, in particular an aircraft turbojet or an aircraft turboprop.
  • orientable vanes can be fitted to a turbojet compressor stator housing.
  • Such vanes can rotate during engine operation. Their arched blades tilt relative to the primary flow that they pass through, which makes it possible to adapt their action according to engine speed and flight conditions. The operating range is thus extended, and the efficiency is optimized.
  • the performance of the compressor is based on the angular positioning accuracy of the blades relative to the housing, as well as the positioning of the blades relative to each other.
  • the relative positioning accuracy of the blades is understood both within their row but also with respect to the other rows.
  • the efficiency requires that the blades form a blade that best respects a predefined geometry.
  • the document US 2014/0182292 A1 discloses a double-flow turbofan.
  • the turbofan has a low pressure compressor fitted with several rows of blades, including a row of stator vanes with variable geometry.
  • the different rows of stator vanes are supported by dedicated outer shrouds; these various outer shells being fixed one after the other by means of radial annular flanges.
  • This configuration allows mounting in the presence of one-piece bladed disc.
  • the compressor is assembled by alternately fixing the rows of rotor blades and the rows of stator vanes. Each of these rows forms a ring which is brought axially against its support and which radially covers the row. blades present downstream.
  • this architecture is particularly bulky.
  • the efficiency of such a turbomachine is limited.
  • the document WO2010 / 026180 A1 discloses an assembly for an axial turbomachine stator.
  • the stator comprises an outer shell supporting two rows of blades, one of which has a variable orientation.
  • the turbomachine has a rotor whose blades are integral with their circular supports. The design of the outer shell can only support two rows of blades.
  • the object of the invention is to solve at least one of the problems posed by the prior art. More precisely, the object of the invention is to improve the efficiency of a turbomachine with a stator with controllable geometry.
  • the invention also aims to provide a compact, resistant, light, economical, reliable solution.
  • the subject of the invention is an assembly for an axial flow turbomachine, corresponding to the characteristics of claim 1, in particular for an axial flow turbomachine compressor, the assembly comprising: a first annular row of radially extending first stator vanes in the axial flow; a second annular row of second stator vanes with piloted orientation which extend radially in the axial flow; a one-piece outer shell on which the first vanes and the second vanes are mounted and; a rotor with a third annular row of third vanes arranged between the first vanes and the second vanes, remarkable in that it further comprises a fourth annular row of fourth vanes, said fourth vanes being mounted on the one-piece outer shell.
  • the second row of blades is disposed upstream of the first row of blades.
  • the outer shell has a fixing flange at its upstream end, optionally at the level of the second row of blades, and optionally a fixing flange at its downstream end.
  • the outer shell comprises a first annular row of orifices to which the first blades are mounted, and a second annular row of orifices to which the second vanes are mounted.
  • the outer shell comprises an annular wall which is integral, and which optionally extends from the first blades to the second blades.
  • the outer shell comprises a free axial portion of annular flange, said portion optionally comprising a generally tubular or substantially frustoconical outer surface.
  • the outer shell comprises an annular section of constant thickness, or of which the thickness varies by at most 30%, or at most 15%; said annular section being arranged between the first vanes and the second vanes.
  • the annular section extends axially over the majority of the space between the first blades and the second blades.
  • the assembly comprises a second internal ferrule mounted at the internal ends of the second vanes, said second internal ferrule having a continuity of circular material.
  • the second internal ring is split axially into elements each having a continuity of circular material.
  • the assembly comprises a synchronization ring arranged around the outer shell.
  • the ring is arranged axially between the first vanes and the second vanes.
  • the outer shell comprises an inner surface of annular shape, the diameter of which decreases downstream, in particular along at least one or each row of blades.
  • the diameter of the internal surface decreases monotonically or continuously.
  • the outer shell has a continuity of circumferential material, and optionally over its entire axial length.
  • the outer shell has a continuity of material along the axially of the first blades and of the second blades.
  • the outer shell is at least one piece from the first row of orifices to the second row of orifices. According to an advantageous embodiment of the invention, the outer shell forms a continuous closed loop and / or in one piece and / or integral.
  • the second vanes are mounted so as to be able to rotate in the orifices of the second row of orifices.
  • the orifices of the second row are configured to allow guiding in rotation of the second blades, and / or are higher radially than the orifices of the first row of orifices.
  • the orientation of the second vanes can vary with respect to the first vanes and / or with respect to the outer shell.
  • the orientation of the second blades can vary by at least 10 ° or 20 ° or 30 °.
  • the first vanes and / or the fourth vanes have a fixed orientation, and / or each comprise an internal ferrule.
  • the fourth blades are arranged downstream of the first blades.
  • the second ferrule comprises means for guiding in rotation, in particular orifices, cooperating with the second vanes.
  • Another subject of the invention is a turbomachine comprising a stator with an assembly, remarkable in that the assembly conforms to the invention.
  • the turbomachine comprises a compressor, the second row of blades forming the row of blades upstream of said compressor.
  • the turbomachine comprises a casing comprising an annular stream through which the axial flow of the turbomachine passes, and an axial face, the outer shell being mounted on said axial face, optionally around said annular stream.
  • the turbomachine comprises a rotor with at least two rows of rotor blades, for example separated axially by the first annular row of first vanes or by the second annular row of second vanes, each row of Rotor blades forming at least two one-piece assemblies and / or two integral assemblies, optionally the at least two rows of rotor blades forming the same single-piece and / or integral assembly.
  • the rows of stator vanes and the rows of rotor vanes can be placed alternately.
  • each subject of the invention is also applicable to the other subjects of the invention.
  • each object of the invention can be combined with other objects.
  • the objects of the invention can also be combined with the embodiments of the description, which in addition can be combined with one another.
  • the invention makes it possible to improve the efficiency of the turbomachine. To this end, it allows greater precision in positioning the blades of at least two annular rows of blades.
  • the operation of the turbomachine is improved over a wider operating range.
  • the solution proposed by the invention also respects the assembly constraints, and preserves the simplicity of certain operations.
  • the terms internal and external 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 refer to the main flow direction of the flow in the turbomachine.
  • Each blade, rotor as well as stator has a leading edge, a trailing edge, an intrados surface and an extrados surface; said surfaces connecting the leading edge to the trailing edge; just like the ropes of dawn.
  • the figure 1 shows in a simplified manner an axial turbomachine.
  • the turbojet 2 comprises a first level of compression, called low-pressure compressor 4, a second level of compression, called high-pressure compressor 6, a combustion chamber 8 and one or more levels of turbines 10.
  • the mechanical power of the turbine 10 transmitted via the central shaft to the rotor 12 sets in motion the two compressors 4 and 6.
  • the latter comprise several rows of rotor blades associated with rows of stator blades.
  • the rotation of the rotor around its axis of rotation 14 thus makes it possible to generate an air flow and to gradually compress the latter up to the entrance of the combustion chamber 8.
  • a transmission 15 with an epicyclic reduction gearbox can be mounted in the rotor 12.
  • An inlet fan commonly referred to as a fan, or blower, 16 is coupled to the rotor 12 and generates an air flow which divides into a primary flow 18 passing through the various aforementioned levels of the turbomachine, and a secondary flow 20 passing through a annular duct (partially shown) by generating a thrust useful for propelling an airplane.
  • the figure 2 is a sectional view of a compressor portion of an axial turbomachine such as that of the figure 1 .
  • the compressor can be a low-pressure compressor 4.
  • the compressor comprises a stator 22 with an outer shell 23 in one piece. It is all in one piece. It describes a closed loop. It has a circular material continuity and / or a circular homogeneity. It can be one-piece over its entire length. It can include a portion coming from the material.
  • the outer shell 23 is fitted around the axis of rotation 14 and surrounds the rotor 12.
  • the rotor 12 can comprise several rows of rotor blades 24, for example two or three or more rotor rows. A single row of rotor blades 24 being visible here. These rotor vanes 24, also called third vanes 24 describe an annular row, called the third row. Despite the rotation of the rotor 12, the inclination in space of the chords of the rotor blades 24 remains invariable with respect to the axis of rotation 14.
  • the third blades 24 can form a one-piece disc; that is to say, they are inseparable from their support rim 25. Such an arrangement is also known under 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 includes an annular row of stator vanes (26; 28). These vanes are statoric in the sense that they are mounted on the stator 22 and therefore remain in contact with the latter.
  • the rectifiers are associated with the fan 16 or with a row of rotor blades 24 to straighten their air flows, so as to convert the speed of the flow into static pressure.
  • the stator vanes (26; 28) extend essentially radially from the outer shell 23 inwards.
  • the stator vanes (26; 28) include fixed orientation first stator vanes 26 which form a first annular row, and second stator vanes 28 with piloted orientation which form a second annular row. They stator vanes can also include a fourth row of fourth vanes (not shown), and optionally a fifth row of fifth vanes (not shown). These other rows of vanes can be placed downstream from the first vanes 26, which are themselves downstream from the second vanes 28. Each of these rows are axially spaced from one another.
  • the first vanes 26 can be axially separated from the second vanes 28 by the annular row of the third vanes 24.
  • the second vanes 28 are also called variable-pitch vanes, or according to the acronym “VSV” for “Variable Stator Vane”. Their particularity is that the inclination of their cords can vary with respect to the axis of rotation 14 of the compressor 4, and this during the operation of the turbomachine. Their intrados and extrados faces can be more or less exposed to the primary flow 18. Their orientation can be controlled during the operation of the turbomachine, for example so as to sweep an angle of at least 30 °.
  • the stator of the compressor is mixed. It includes both piloted orientation vanes; and therefore modifiable; and fixed orientation vanes. Admittedly, only one row of piloted orientation vanes is presented, however this stator could also receive more rows of piloted orientation vanes.
  • the second vanes 28 can pivot relative to the flow 18, so that they more or less cover the fluid stream by virtue of their blades. They can intercept more the primary flow 18.
  • the circumferential width which they occupy can vary. Their leading edges and their trailing edges can approach or move away from the blades of the same row. By being more or less inclined with respect to the general direction of flow, they more or less deflect the primary flow 18 to modulate the rectification of flow that they provide.
  • the turbomachine and the compressor can follow different efficiency curves during operation, and this thanks to a variable geometry of their blades.
  • the compressor 4 may include internal ferrules (30; 32) suspended from the internal ends of the stator vanes (26; 28), including a first internal ferrule 30 fixed to the first vanes 26, and a second internal ferrule 32 with respect to which the second vanes 28 are articulated. In order to allow the rotation of the latter, these have internal journals 34 engaged in the second internal ferrule 32. Likewise, they have external journals 36 passing through the outer ferrule 23 at the level of bosses 38. The bosses 38 may include second orifices 40 making it possible to form a pivot connection with the external journals 36.
  • the journals (34; 36) can form cylindrical rods, and can be integral with their blade.
  • Bearings may be provided around the internal journals 34, as well as between the second orifices 40 and the external journals 36. These are extended by control rods to which are mounted control levers 42 controlled by a synchronization ring 44 which controls each of the second blades 28 via their control levers 42.
  • a control system actuator (not shown) makes it possible to control the synchronization ring 44, and therefore the orientation of the second blades 28 in the primary flow 18.
  • the first blades 26 are fixed and rigidly linked to the outer shell 23 via their rods 46 which are introduced through orifices 48 describing a row, called the first row of orifices 48.
  • a clamping means helps to freeze the orientation of the first blades 26.
  • the orifices (40; 48) can be produced during the same phase on the same machine, so that their respective positions are better controlled, and the implantation of their blades (26; 28) respects better the predefined geometry.
  • the stator 22 comprises an annular wall 50.
  • it comprises an upstream fixing flange 52, a downstream fixing flange (not shown), and an annular seal 54 which is applied inside the annular wall 50 and which cooperates. in a sealed manner with the third blades 24 of the rotor 12.
  • the upstream flange 52 forms the upstream end of the wall 50, and allows attachment to a casing of the turbomachine, for example the upstream casing, or the intermediate casing.
  • the wall 50 may have come integrally. It can extend axially along the second vanes 28 and the first vanes 26, and possibly all along the fourth vanes.
  • the wall 50 forms a mounting support for the stator vanes (26; 28).
  • the internal surface 56 of the external ferrule 23 has an internal diameter which decreases downstream and which matches the ends external third vanes 24 mounted on rotor 12. This configuration therefore requires placing the third vanes 24 in the outer shell 23 before mounting the second vanes 28 and their inner shell 32. The opposite would not be technically possible because these second vanes 28 would obstruct the entry of the rotor 12 inside the outer shell 23.
  • the second vanes 28 are adjustable. They can pivot on themselves by virtue of their external journals 36 which are adjusted to the orifices 40. Consequently, their assembly is carried out by radial introduction, or by following their pivot axes 58 which become their introduction axes.
  • the second internal ferrule 32 is split. It is divided axially into an upstream element 60 and into a downstream element 62 which each form closed loops. At least one or each of these elements (60; 62) is each in one piece, that is to say that it has a continuity of circular material. One of them can be angularly segmented. At least one of them cooperates in a sealed manner with the rotor 12 with wipers.
  • the downstream element 62 is placed opposite the third vanes 24. Then the second vanes 28 are introduced by placing their internal journals 34 facing axially and at the radial level of the downstream member 62.
  • the 'upstream element 60 is fitted axially against the downstream element 62 while maintaining the internal journals 34.
  • the latter are then enclosed between the elements (60; 62) while forming a pivot connection; that is to say a mechanical connection with only one degree of freedom.
  • the outer shell 23 comprises a homogeneous axial portion 64.
  • This axial portion 64 may be free of an annular flange, and may have an exterior surface 66 which is generally tubular or substantially frustoconical. This outer surface 66 can be axially continuous.
  • the axial portion 64 may extend over the majority of the space between the first 26 and second vanes 28, and may show a reduction in diameter from the second vanes 28 towards the first vanes 26.
  • the axial portion 64 can define on the wall 50 an annular section of constant thickness.
  • the thickness of the annular section can vary axially by at most 20%, or at most 10%.
  • This annular section is disposed between the first blades 26 and the second blades 28, and can extend axially over the majority of the space between the first vanes 26 and the second vanes 28.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Description

Domaine techniqueTechnical area

L'invention rapporte au domaine des stators avec des aubes à orientation commandée pour turbomachine axiale. L'invention concerne également l'assemblage d'un stator à aubes ajustables. 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 stators with blades with controlled orientation for an axial turbomachine. The invention also relates to the assembly of a stator with adjustable vanes. The invention also relates to an axial turbomachine, in particular an aircraft turbojet or an aircraft turboprop.

Technique antérieurePrior art

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 est ainsi étendue, et le rendement est optimisé.Usually, several rows of orientable vanes can be fitted to a turbojet compressor stator housing. Such vanes can rotate during engine operation. Their arched blades tilt relative to the primary flow that they pass through, which makes it possible to adapt their action according to engine speed and flight conditions. The operating range is thus extended, and the efficiency is optimized.

La performance du compresseur repose sur la précision de positionnement angulaire des aubes par rapport au carter, ainsi que sur le positionnement des aubes les unes par rapport aux autres. La précision de positionnement relative des aubes s'entend à la fois au sein de leur rangée mais également par rapport aux autres rangées. En particulier, le rendement nécessite que les aubes forment un aubage respectant au mieux une géométrie prédéfinie.The performance of the compressor is based on the angular positioning accuracy of the blades relative to the housing, as well as the positioning of the blades relative to each other. The relative positioning accuracy of the blades is understood both within their row but also with respect to the other rows. In particular, the efficiency requires that the blades form a blade that best respects a predefined geometry.

Le document US 2014/0182292 A1 divulgue une turbosoufflante double flux. La turbosoufflante comporte un compresseur basse pression muni de plusieurs rangées d'aubes, dont une rangée d'aubes de stator à géométrie variable. Les différentes rangées d'aubes de stator sont supportées par des viroles externes dédiées ; ces différentes viroles externes étant fixées les unes à la suite des autres au moyen de brides annulaires radiales. Cette configuration autorise un montage en présence de disque aubagés monobloc. En effet, le compresseur est assemblé en fixant par alternance les rangées d'aubes rotoriques et les rangées d'aubes statoriques. Chacune de ces rangées forme une bague qui est amenée axialement contre son support et qui recouvre radialement la rangée d'aubes présente en aval. Or, cette architecture est particulièrement encombrante. En outre, le rendement d'une telle turbomachine est limité.The document US 2014/0182292 A1 discloses a double-flow turbofan. The turbofan has a low pressure compressor fitted with several rows of blades, including a row of stator vanes with variable geometry. The different rows of stator vanes are supported by dedicated outer shrouds; these various outer shells being fixed one after the other by means of radial annular flanges. This configuration allows mounting in the presence of one-piece bladed disc. Indeed, the compressor is assembled by alternately fixing the rows of rotor blades and the rows of stator vanes. Each of these rows forms a ring which is brought axially against its support and which radially covers the row. blades present downstream. However, this architecture is particularly bulky. In addition, the efficiency of such a turbomachine is limited.

Le document WO2010/026180 A1 divulgue un ensemble pour stator de turbomachine axiale. Le stator comporte une virole externe supportant deux rangées d'aubes, dont une à orientation variable. La turbomachine présente un rotor dont les aubes sont solidaires de leurs supports circulaires. La conception de la virole externe ne permet de supporter que deux rangées d'aubes.The document WO2010 / 026180 A1 discloses an assembly for an axial turbomachine stator. The stator comprises an outer shell supporting two rows of blades, one of which has a variable orientation. The turbomachine has a rotor whose blades are integral with their circular supports. The design of the outer shell can only support two rows of blades.

Résumé de l'inventionSummary of the invention Problème techniqueTechnical problem

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 rendement d'une turbomachine avec un stator à géométrie pilotable. L'invention a également pour objectif de proposer une solution compacte, résistante, légère, économique, fiable.The object of the invention is to solve at least one of the problems posed by the prior art. More precisely, the object of the invention is to improve the efficiency of a turbomachine with a stator with controllable geometry. The invention also aims to provide a compact, resistant, light, economical, reliable solution.

Solution techniqueTechnical solution

L'invention a pour objet un ensemble pour turbomachine à flux axial, , correspondant aux caractéristiques de la revendication 1, notamment pour compresseur de turbomachine à flux axial, l'ensemble comprenant : une première rangée annulaire de premières aubes de stator s'étendant radialement dans le flux axial ; une deuxième rangée annulaire de deuxièmes aubes de stator à orientation pilotée qui s'étendent radialement dans le flux axial ; une virole externe monobloc sur laquelle les premières aubes et les deuxièmes aubes sont montées et ; un rotor avec une troisième rangée annulaire de troisièmes aubes disposées entre les premières aubes et les deuxièmes aubes remarquable en ce qu'il comprend en outre une quatrième rangée annulaire de quatrièmes aubes, lesdites quatrièmes aubes étant montées sur la virole externe monobloc.The subject of the invention is an assembly for an axial flow turbomachine, corresponding to the characteristics of claim 1, in particular for an axial flow turbomachine compressor, the assembly comprising: a first annular row of radially extending first stator vanes in the axial flow; a second annular row of second stator vanes with piloted orientation which extend radially in the axial flow; a one-piece outer shell on which the first vanes and the second vanes are mounted and; a rotor with a third annular row of third vanes arranged between the first vanes and the second vanes, remarkable in that it further comprises a fourth annular row of fourth vanes, said fourth vanes being mounted on the one-piece outer shell.

Selon un mode avantageux de l'invention, la deuxième rangée d'aubes est disposée en amont de la première rangée d'aubes.According to an advantageous embodiment of the invention, the second row of blades is disposed upstream of the first row of blades.

Selon un mode avantageux de l'invention, la virole externe présente une bride de fixation à son extrémité amont, éventuellement au niveau de la deuxième rangée d'aubes, et optionnellement une bride de fixation à son extrémité aval. Selon un mode avantageux de l'invention, la virole externe comprend une première rangée annulaire d'orifices auxquels les premières aubes sont montées, et une deuxième rangée annulaire d'orifices auxquels les deuxièmes aubes sont montées.According to an advantageous embodiment of the invention, the outer shell has a fixing flange at its upstream end, optionally at the level of the second row of blades, and optionally a fixing flange at its downstream end. According to an advantageous embodiment of the invention, the outer shell comprises a first annular row of orifices to which the first blades are mounted, and a second annular row of orifices to which the second vanes are mounted.

Selon un mode avantageux de l'invention, la virole externe comprend une paroi annulaire qui est venue de matière, et qui s'étend éventuellement des premières aubes aux deuxièmes aubes.According to an advantageous embodiment of the invention, the outer shell comprises an annular wall which is integral, and which optionally extends from the first blades to the second blades.

Selon un mode avantageux de l'invention, au niveau et/ou entre les premières aubes et les deuxièmes aubes, la virole externe comprend une portion axiale libre de bride annulaire, ladite portion comprenant éventuellement une surface extérieure généralement tubulaire ou sensiblement tronconique.According to an advantageous embodiment of the invention, at and / or between the first blades and the second blades, the outer shell comprises a free axial portion of annular flange, said portion optionally comprising a generally tubular or substantially frustoconical outer surface.

Selon un mode avantageux de l'invention, la virole externe comprend un tronçon annulaire d'épaisseur constante, ou dont l'épaisseur varie d'au plus 30%, ou au plus 15% ; ledit tronçon annulaire étant disposé entre les premières aubes et les deuxièmes aubes.According to an advantageous embodiment of the invention, the outer shell comprises an annular section of constant thickness, or of which the thickness varies by at most 30%, or at most 15%; said annular section being arranged between the first vanes and the second vanes.

Selon un mode avantageux de l'invention, le tronçon annulaire s'étend axialement sur la majorité de l'espace entre les premières aubes et les deuxièmes aubes.According to an advantageous embodiment of the invention, the annular section extends axially over the majority of the space between the first blades and the second blades.

Selon un mode avantageux de l'invention, l'ensemble comprend une deuxième virole interne montée aux extrémités internes des deuxièmes aubes, ladite deuxième virole interne présentant une continuité de matière circulaire.According to an advantageous embodiment of the invention, the assembly comprises a second internal ferrule mounted at the internal ends of the second vanes, said second internal ferrule having a continuity of circular material.

Selon un mode avantageux de l'invention, la deuxième virole interne est scindée axialement en éléments présentant chacun une continuité de matière circulaire.According to an advantageous embodiment of the invention, the second internal ring is split axially into elements each having a continuity of circular material.

Selon un mode avantageux de l'invention, l'ensemble comporte une bague de synchronisation disposée autour de la virole externe.According to an advantageous embodiment of the invention, the assembly comprises a synchronization ring arranged around the outer shell.

Selon un mode avantageux de l'invention, la bague est disposée axialement entre les premières aubes et les deuxièmes aubes.According to an advantageous embodiment of the invention, the ring is arranged axially between the first vanes and the second vanes.

Selon un mode avantageux de l'invention, la virole externe comprend une surface intérieure de forme annulaire dont le diamètre décroit vers l'aval, notamment le long d'au moins une ou de chaque rangée d'aubes.According to an advantageous embodiment of the invention, the outer shell comprises an inner surface of annular shape, the diameter of which decreases downstream, in particular along at least one or each row of blades.

Selon un mode avantageux de l'invention, le diamètre de la surface interne décroit de manière monotone ou continue.According to an advantageous embodiment of the invention, the diameter of the internal surface decreases monotonically or continuously.

Selon un mode avantageux de l'invention, la virole externe présente une continuité de matière circonférentielle, et éventuellement sur toute sa longueur axiale.According to an advantageous embodiment of the invention, the outer shell has a continuity of circumferential material, and optionally over its entire axial length.

Selon un mode avantageux de l'invention, la virole externe présente une continuité de matière le long axialement des premières aubes et des deuxièmes aubes.According to an advantageous embodiment of the invention, the outer shell has a continuity of material along the axially of the first blades and of the second blades.

Selon un mode avantageux de l'invention, la virole externe est au moins monobloc de la première rangée d'orifices à la deuxième rangée d'orifices. Selon un mode avantageux de l'invention, la virole externe forme une boucle fermée continue et/ou monobloc et/ou venue de matière.According to an advantageous embodiment of the invention, the outer shell is at least one piece from the first row of orifices to the second row of orifices. According to an advantageous embodiment of the invention, the outer shell forms a continuous closed loop and / or in one piece and / or integral.

Selon un mode avantageux de l'invention, les deuxièmes aubes sont montées mobiles en rotation dans les orifices de la deuxième rangée d'orifices.According to an advantageous embodiment of the invention, the second vanes are mounted so as to be able to rotate in the orifices of the second row of orifices.

Selon un mode avantageux de l'invention, les orifices de la deuxième rangée sont configurés pour permettre un guidage en rotation des deuxièmes aubes, et/ou sont plus hauts radialement que les orifices de la première rangée d'orifices.According to an advantageous embodiment of the invention, the orifices of the second row are configured to allow guiding in rotation of the second blades, and / or are higher radially than the orifices of the first row of orifices.

Selon un mode avantageux de l'invention, l'orientation des deuxièmes aubes peut varier par rapport aux premières aubes et/ou par rapport à la virole externe.According to an advantageous embodiment of the invention, the orientation of the second vanes can vary with respect to the first vanes and / or with respect to the outer shell.

Selon un mode avantageux de l'invention, l'orientation des deuxièmes aubes peuvent varier d'au moins 10° ou 20° ou 30°.According to an advantageous embodiment of the invention, the orientation of the second blades can vary by at least 10 ° or 20 ° or 30 °.

Selon un mode avantageux de l'invention, les premières aubes et/ou les quatrièmes aubes sont à orientation fixe, et/ou comprennent chacun une virole interne.According to an advantageous embodiment of the invention, the first vanes and / or the fourth vanes have a fixed orientation, and / or each comprise an internal ferrule.

Selon un mode avantageux de l'invention, les quatrièmes aubes sont disposées en aval des premières aubes.According to an advantageous embodiment of the invention, the fourth blades are arranged downstream of the first blades.

Selon un mode avantageux de l'invention, la deuxième virole comprend des moyens de guidage en rotation, notamment des orifices, coopérant avec les deuxièmes aubes.According to an advantageous embodiment of the invention, the second ferrule comprises means for guiding in rotation, in particular orifices, cooperating with the second vanes.

L'invention a également pour objet une turbomachine comprenant un stator avec un ensemble, remarquable en ce que l'ensemble est conforme à l'invention.Another subject of the invention is a turbomachine comprising a stator with an assembly, remarkable in that the assembly conforms to the invention.

Selon un mode avantageux de l'invention, la turbomachine comprend un compresseur, la deuxième rangée d'aubes formant la rangée d'aubes en amont dudit compresseur.According to an advantageous embodiment of the invention, the turbomachine comprises a compressor, the second row of blades forming the row of blades upstream of said compressor.

Selon un mode avantageux de l'invention, la turbomachine comprend un carter comportant une veine annulaire traversée par le flux axial de la turbomachine, et une face axiale, la virole externe étant montée sur ladite face axiale, éventuellement autour de ladite veine annulaire.According to an advantageous embodiment of the invention, the turbomachine comprises a casing comprising an annular stream through which the axial flow of the turbomachine passes, and an axial face, the outer shell being mounted on said axial face, optionally around said annular stream.

Selon un mode avantageux de l'invention, la turbomachine comporte un rotor avec au moins deux rangées d'aubes rotoriques, par exemple séparés axialement par la première rangée annulaire de première aubes ou par la deuxième rangée annulaire de deuxième aubes, chaque rangées d'aubes rotoriques formant au moins deux ensembles monoblocs et/ou deux ensembles venus de matière, éventuellement les au moins deux rangées d'aubes rotoriques formant un même ensemble monobloc et/ou venu de matière. Les rangées d'aubes statoriques et les rangées d'aubes rotoriques peuvent être placées par alternance.According to an advantageous embodiment of the invention, the turbomachine comprises a rotor with at least two rows of rotor blades, for example separated axially by the first annular row of first vanes or by the second annular row of second vanes, each row of Rotor blades forming at least two one-piece assemblies and / or two integral assemblies, optionally the at least two rows of rotor blades forming the same single-piece and / or integral assembly. The rows of stator vanes and the rows of rotor vanes can be placed alternately.

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 subject of the invention are also applicable to the other subjects of the invention. As far as possible, each object of the invention can be combined with other objects. The objects of the invention can also be combined with the embodiments of the description, which in addition can be combined with one another.

Avantages apportésBenefits provided

L'invention permet d'améliorer le rendement de la turbomachine. A cet effet, elle permet une plus grande précision de positionnement des aubes d'au moins deux rangées annulaires d'aubes. Le fonctionnement de la turbomachine est amélioré sur une plage de fonctionnement plus étendue. La solution proposée par l'invention respecte également les contraintes d'assemblage, et préserve la simplicité de certaines opérations.The invention makes it possible to improve the efficiency of the turbomachine. To this end, it allows greater precision in positioning the blades of at least two annular rows of blades. The operation of the turbomachine is improved over a wider operating range. The solution proposed by the invention also respects the assembly constraints, and preserves the simplicity of certain operations.

Brève description des dessinsBrief description of the drawings

  • La figure 1 représente une turbomachine axiale selon l'invention.The figure 1 represents an axial turbomachine according to the invention.
  • La figure 2 est un schéma d'une portion de compresseur de turbomachine selon l'invention.The figure 2 is a diagram of a portion of a turbomachine compressor according to the invention.
Description des modes de réalisationDescription of embodiments

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 description which will follow, the terms internal and external 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 refer to the main flow direction of the flow in the turbomachine.

Chaque aube, rotorique comme statorique, présente un bord d'attaque, un bord de fuite, une surface intrados et une surface extrados ; lesdites surfaces reliant le bord d'attaque au bord de fuite ; tout comme les cordes de l'aube. Dans la description qui suit, on peut se référer à une corde médiane.Each blade, rotor as well as stator, has a leading edge, a trailing edge, an intrados surface and an extrados surface; said surfaces connecting the leading edge to the trailing edge; just like the ropes of dawn. In the following description, reference may be made to a median chord.

La figure 1 représente de manière simplifiée une turbomachine axiale. Il s'agit dans ce cas précis d'un turboréacteur double-flux. Le turboréacteur 2 comprend un premier niveau de compression, dit compresseur basse-pression 4, un deuxième niveau de compression, dit compresseur haute-pression 6, une chambre de combustion 8 et un ou plusieurs niveaux de turbines 10. En fonctionnement, la puissance mécanique de la turbine 10 transmise via l'arbre central jusqu'au rotor 12 met en mouvement les deux compresseurs 4 et 6. Ces derniers comportent plusieurs rangées d'aubes de rotor associées à des rangées d'aubes de stator. La rotation du rotor autour de son axe de rotation 14 permet ainsi de générer un débit d'air et de comprimer progressivement ce dernier jusqu'à l'entrée de la chambre de combustion 8. Une transmission 15 avec un réducteur épicycloïdal peut être monté dans le rotor 12.The figure 1 shows in a simplified manner an axial turbomachine. In this specific case, it is a double-flow turbojet. The turbojet 2 comprises a first level of compression, called low-pressure compressor 4, a second level of compression, called high-pressure compressor 6, a combustion chamber 8 and one or more levels of turbines 10. In operation, the mechanical power of the turbine 10 transmitted via the central shaft to the rotor 12 sets in motion the two compressors 4 and 6. The latter comprise several rows of rotor blades associated with rows of stator blades. The rotation of the rotor around its axis of rotation 14 thus makes it possible to generate an air flow and to gradually compress the latter up to the entrance of the combustion chamber 8. A transmission 15 with an epicyclic reduction gearbox can be mounted in the rotor 12.

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) 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 rotor 12 and generates an air flow which divides into a primary flow 18 passing through the various aforementioned levels of the turbomachine, and a secondary flow 20 passing through a annular duct (partially shown) by generating a thrust useful for propelling an airplane.

La figure 2 est une vue en coupe d'une portion de compresseur d'une turbomachine axiale telle que celle de la figure 1. Le compresseur peut être un compresseur basse-pression 4.The figure 2 is a sectional view of a compressor portion of an axial turbomachine such as that of the figure 1 . The compressor can be a low-pressure compressor 4.

Le compresseur comprend un stator 22 avec une virole externe 23 monobloc. Elle 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. La virole externe 23 est emmanchée autour de l'axe de rotation 14 et entoure le rotor 12.The compressor comprises a stator 22 with an outer shell 23 in one piece. It is all in one piece. It describes a closed loop. It has a circular material continuity and / or a circular homogeneity. It can be one-piece over its entire length. It can include a portion coming from the material. The outer shell 23 is fitted around the axis of rotation 14 and surrounds the rotor 12.

Le rotor 12 peut comprendre plusieurs rangées d'aubes rotoriques 24, par exemple deux ou trois ou d'avantage de rangées rotoriques. Une seule rangée d'aubes rotoriques 24 étant ici visible. Ces aubes rotoriques 24, également appelées troisièmes aubes 24 décrivent une rangée annulaire, dite troisième rangée. 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 troisièmes aubes 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 rotor 12 can comprise several rows of rotor blades 24, for example two or three or more rotor rows. A single row of rotor blades 24 being visible here. These rotor vanes 24, also called third vanes 24 describe an annular row, called the third row. Despite the rotation of the rotor 12, the inclination in space of the chords of the rotor blades 24 remains invariable with respect to the axis of rotation 14. The third blades 24 can form a one-piece disc; that is to say, they are inseparable from their support rim 25. Such an arrangement is also known under the term “blisk”.

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 ; 28). Ces aubes sont statoriques en ce sens qu'elles sont montés sur le stator 22 et restent donc en contact de ce dernier. Les redresseurs sont associés au fan 16 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 compressor 4 comprises several rectifiers, for example at least two, or at least three or at least four rectifiers. Each rectifier includes an annular row of stator vanes (26; 28). These vanes are statoric in the sense that they are mounted on the stator 22 and therefore remain in contact with the latter. The rectifiers are associated with the fan 16 or with a row of rotor blades 24 to straighten their air flows, so as to convert the speed of the flow into static pressure.

Les aubes statoriques (26 ; 28) s'étendent essentiellement radialement depuis la virole externe 23 vers l'intérieur. Les aubes statoriques (26 ; 28) comprennent des premières aubes statoriques 26 à orientation fixe qui forment une première rangée annulaire, et des deuxièmes aubes statoriques 28 à orientation pilotée qui forment une deuxième rangée annulaire. Elles aubes statoriques peuvent également comprendre une quatrième rangée de quatrièmes aubes (non représentées), et optionnellement une cinquième rangée de cinquièmes aubes (non représentées). Ces autres rangées d'aubes peuvent être placées en aval des premières aubes 26, qui sont-elles même en aval des deuxièmes aubes 28. Chacune de ces rangées sont écartées axialement les unes des autres. Par exemple, les premières aubes 26 peuvent être séparées axialement des deuxièmes aubes 28 par la rangée annulaire des troisièmes aubes 24.The stator vanes (26; 28) extend essentially radially from the outer shell 23 inwards. The stator vanes (26; 28) include fixed orientation first stator vanes 26 which form a first annular row, and second stator vanes 28 with piloted orientation which form a second annular row. They stator vanes can also include a fourth row of fourth vanes (not shown), and optionally a fifth row of fifth vanes (not shown). These other rows of vanes can be placed downstream from the first vanes 26, which are themselves downstream from the second vanes 28. Each of these rows are axially spaced from one another. For example, the first vanes 26 can be axially separated from the second vanes 28 by the annular row of the third vanes 24.

Les deuxièmes aubes 28 sont également appelées aubes à calage variable, ou selon l'acronyme anglo-saxon « VSV » pour « Variable Stator Vane ». Leur particularité est que l'inclinaison de leurs cordes peut varier par rapport à l'axe de rotation 14 du compresseur 4, et ce pendant le fonctionnement de la turbomachine. Leurs faces intrados et extrados peuvent être plus ou moins exposées au flux primaire 18. Leur orientation peut être pilotée pendant le fonctionnement de la turbomachine, par exemple de manière à balayer un angle d'au moins 30°. Le stator du compresseur est mixte. Il comporte à la fois des aubes à orientation pilotée ; et donc modifiable ; et des aubes à orientation fixe. Certes, une seule rangée d'aubes à orientation pilotée est présentée, toutefois ce stator pourrait également recevoir d'avantage de rangées d'aubes à orientation pilotée.The second vanes 28 are also called variable-pitch vanes, or according to the acronym “VSV” for “Variable Stator Vane”. Their particularity is that the inclination of their cords can vary with respect to the axis of rotation 14 of the compressor 4, and this during the operation of the turbomachine. Their intrados and extrados faces can be more or less exposed to the primary flow 18. Their orientation can be controlled during the operation of the turbomachine, for example so as to sweep an angle of at least 30 °. The stator of the compressor is mixed. It includes both piloted orientation vanes; and therefore modifiable; and fixed orientation vanes. Admittedly, only one row of piloted orientation vanes is presented, however this stator could also receive more rows of piloted orientation vanes.

Les deuxièmes aubes 28 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 bords d'attaque et leur bords 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, et ceci grâce à une géométrie variable de leur aubage.The second vanes 28 can pivot relative to the flow 18, so that they more or less cover the fluid stream by virtue of their blades. They can intercept more the primary flow 18. The circumferential width which they occupy can vary. Their leading edges and their trailing edges can approach or move away from the blades of the same row. By being more or less inclined with respect to the general direction of flow, they more or less deflect the primary flow 18 to modulate the rectification of flow that they provide. Thus, the turbomachine and the compressor can follow different efficiency curves during operation, and this thanks to a variable geometry of their blades.

Le compresseur 4 peut comprendre des viroles internes (30 ; 32) suspendues aux extrémités internes des aubes statoriques (26 ; 28), dont une première virole interne 30 fixée aux première aubes 26, et une deuxième virole interne 32 par rapport à laquelle les deuxièmes aubes 28 sont articulées. Afin de permettre la rotation de ces dernières, celles-ci présentent des tourillons internes 34 engagés dans la deuxième virole interne 32. De même, elles présentent des tourillons externes 36 traversant la virole externe 23 au niveau de bossages 38. Les bossages 38 peuvent comprendre des deuxièmes orifices 40 permettant de former une liaison pivot avec les tourillons externes 36. Les tourillons (34 ; 36) peuvent former des tiges cylindriques, et peuvent être venus de matière avec leur pale. Des paliers (non représentés) peuvent être prévus autour des tourillons internes 34, ainsi qu'entre les deuxièmes orifices 40 et les tourillons externes 36. Ceux-ci se prolongent par des tiges de commandes auxquelles sont montés des leviers de commande 42 pilotés par une bague de synchronisation 44 qui pilote chacune des deuxièmes aubes 28 via leurs leviers de commande 42. Un actionneur (non représenté) de système de commande permet de piloter la bague de synchronisation 44, et donc l'orientation des deuxièmes aubes 28 dans le flux primaire 18.The compressor 4 may include internal ferrules (30; 32) suspended from the internal ends of the stator vanes (26; 28), including a first internal ferrule 30 fixed to the first vanes 26, and a second internal ferrule 32 with respect to which the second vanes 28 are articulated. In order to allow the rotation of the latter, these have internal journals 34 engaged in the second internal ferrule 32. Likewise, they have external journals 36 passing through the outer ferrule 23 at the level of bosses 38. The bosses 38 may include second orifices 40 making it possible to form a pivot connection with the external journals 36. The journals (34; 36) can form cylindrical rods, and can be integral with their blade. Bearings (not shown) may be provided around the internal journals 34, as well as between the second orifices 40 and the external journals 36. These are extended by control rods to which are mounted control levers 42 controlled by a synchronization ring 44 which controls each of the second blades 28 via their control levers 42. A control system actuator (not shown) makes it possible to control the synchronization ring 44, and therefore the orientation of the second blades 28 in the primary flow 18.

Les premières aubes 26 sont fixées et rigidement liées à la virole externe 23 via leurs tiges 46 qui sont introduites au travers d'orifices 48 décrivant une rangée, dite première rangée d'orifices 48. Un moyen de serrage (non représenté) contribue à figer l'orientation des premières aubes 26. Les orifices (40 ; 48) peuvent être réalisés pendant une même phase sur une même machine, si bien que leur positions respectives sont mieux maîtrisées, et l'implantation de leurs aubes (26 ; 28) respecte mieux la géométrie prédéfinie.The first blades 26 are fixed and rigidly linked to the outer shell 23 via their rods 46 which are introduced through orifices 48 describing a row, called the first row of orifices 48. A clamping means (not shown) helps to freeze the orientation of the first blades 26. The orifices (40; 48) can be produced during the same phase on the same machine, so that their respective positions are better controlled, and the implantation of their blades (26; 28) respects better the predefined geometry.

Le stator 22 comporte une paroi annulaire 50. Optionnellement, il comporte une bride de fixation amont 52, une bride de fixation aval (non représentée), et un joint annulaire 54 qui est appliqué à l'intérieur de la paroi annulaire 50 et qui coopère de manière étanche avec les troisièmes aubes 24 du rotor 12. La bride amont 52 forme l'extrémité amont de la paroi 50, et permet une fixation sur un carter de la turbomachine, par exemple le carter amont, ou le carter intermédiaire. La paroi 50 peut être venue de matière. Elle peut s'étendre tout le long axialement des deuxièmes aubes 28 et des premières aubes 26, et éventuellement tout le long des quatrièmes aubes. La paroi 50 forme un support de montage des aubes de stator (26 ; 28).The stator 22 comprises an annular wall 50. Optionally, it comprises an upstream fixing flange 52, a downstream fixing flange (not shown), and an annular seal 54 which is applied inside the annular wall 50 and which cooperates. in a sealed manner with the third blades 24 of the rotor 12. The upstream flange 52 forms the upstream end of the wall 50, and allows attachment to a casing of the turbomachine, for example the upstream casing, or the intermediate casing. The wall 50 may have come integrally. It can extend axially along the second vanes 28 and the first vanes 26, and possibly all along the fourth vanes. The wall 50 forms a mounting support for the stator vanes (26; 28).

Selon une option de l'invention, la surface interne 56 de la virole externe 23 présente un diamètre interne qui décroit vers l'aval et qui épouse les extrémités externes des troisièmes aubes 24 montées sur le rotor 12. Cette configuration impose donc de placer les troisièmes aubes 24 dans la virole externe 23 avant de monter les deuxièmes aubes 28 et leur virole interne 32. Le contraire ne serait pas techniquement possible car ces deuxièmes aubes 28 feraient obstacle à l'entrée du rotor 12 à l'intérieur de la virole externe 23.According to one option of the invention, the internal surface 56 of the external ferrule 23 has an internal diameter which decreases downstream and which matches the ends external third vanes 24 mounted on rotor 12. This configuration therefore requires placing the third vanes 24 in the outer shell 23 before mounting the second vanes 28 and their inner shell 32. The opposite would not be technically possible because these second vanes 28 would obstruct the entry of the rotor 12 inside the outer shell 23.

En complément, les deuxièmes aubes 28 sont ajustables. Elles peuvent pivoter sur elles-mêmes grâce à leur tourillons externes 36 qui sont ajustés aux orifices 40. Dès lors, leur montage s'effectue par introduction radiale, soit en suivant leurs axes de pivotement 58 qui deviennent leurs axes d'introduction.In addition, the second vanes 28 are adjustable. They can pivot on themselves by virtue of their external journals 36 which are adjusted to the orifices 40. Consequently, their assembly is carried out by radial introduction, or by following their pivot axes 58 which become their introduction axes.

Afin de permettre son montage, la deuxième virole interne 32 est scindée. Elle est divisée axialement en un élément amont 60 et en un élément aval 62 qui forment chacun des boucles fermées. Au moins un ou chacun de ces éléments (60 ; 62) est chacun monobloc, c'est-à-dire qu'il présente une continuité de matière circulaire. L'un d'eux peut être segmenté angulairement. Au moins l'un d'eux coopère de manière étanche avec le rotor 12 avec des léchettes. Lors de l'assemblage, l'élément aval 62 est placé en regard des troisièmes aubes 24. Puis les deuxièmes aubes 28 sont introduites en disposant leur tourillons internes 34 en face axialement et au niveau radialement de l'élément aval 62. Ensuite, l'élément amont 60 est rapporté axialement contre l'élément aval 62 en maintenant les tourillons internes 34. Ces derniers sont alors enfermés entre les éléments (60 ; 62) tout en formant une liaison pivot ; c'est-à-dire une liaison mécanique à un seul degré de liberté.In order to allow its assembly, the second internal ferrule 32 is split. It is divided axially into an upstream element 60 and into a downstream element 62 which each form closed loops. At least one or each of these elements (60; 62) is each in one piece, that is to say that it has a continuity of circular material. One of them can be angularly segmented. At least one of them cooperates in a sealed manner with the rotor 12 with wipers. During assembly, the downstream element 62 is placed opposite the third vanes 24. Then the second vanes 28 are introduced by placing their internal journals 34 facing axially and at the radial level of the downstream member 62. Then, the 'upstream element 60 is fitted axially against the downstream element 62 while maintaining the internal journals 34. The latter are then enclosed between the elements (60; 62) while forming a pivot connection; that is to say a mechanical connection with only one degree of freedom.

La virole externe 23 comprend une portion axiale 64 homogène. Cette portion axiale 64 peut être libre de bride annulaire, et peut présenter une surface extérieure 66 généralement tubulaire ou sensiblement tronconique. Cette surface extérieure 66 peut être continue axialement. La portion axiale 64 peut s'étendre sur la majorité de l'espace séparant les premières 26 et deuxièmes aubes 28, et peut montrer une réduction de diamètre des deuxièmes aubes 28 vers les premières aubes 26.The outer shell 23 comprises a homogeneous axial portion 64. This axial portion 64 may be free of an annular flange, and may have an exterior surface 66 which is generally tubular or substantially frustoconical. This outer surface 66 can be axially continuous. The axial portion 64 may extend over the majority of the space between the first 26 and second vanes 28, and may show a reduction in diameter from the second vanes 28 towards the first vanes 26.

La portion axiale 64 peut délimiter sur la paroi 50 un tronçon annulaire d'épaisseur constante. Eventuellement, l'épaisseur du tronçon annulaire peut varier axialement d'au plus 20%, ou au plus 10%. Ce tronçon annulaire est disposé entre les premières aubes 26 et les deuxièmes aubes 28, et peut s'étendre axialement sur la majorité de l'espace entre les premières aubes 26 et les deuxièmes aubes 28.The axial portion 64 can define on the wall 50 an annular section of constant thickness. Optionally, the thickness of the annular section can vary axially by at most 20%, or at most 10%. This annular section is disposed between the first blades 26 and the second blades 28, and can extend axially over the majority of the space between the first vanes 26 and the second vanes 28.

Claims (12)

  1. Assembly for an axial-flow turbomachine (2), in particular for a compressor (4; 6) of an axial-flow turbomachine (2), the assembly comprising:
    - a first annular row of first blades (26) of the stator (22) extending radially in the axial flow;
    - a second annular row of second blades (28) of the stator (22) with controlled orientation which extend radially in the axial flow, the second row of blades (28) being disposed upstream of the first row of blades (26);
    - an integral outer ferrule (23) on which the first blades (26) and the second blades (28) are mounted; and
    - a rotor (12) with a third annular row of third blades (24) disposed between the first blades (26) and the second blades (28);
    and
    an inner ferrule (32) mounted at the inner ends of the second blades (28), said inner ferrule (32) having a continuity of circular material, the inner ferrule (32) being axially divided into elements (60; 62) each having a continuity of circular material,
    characterized in that at least one of the elements (60; 62) cooperates with the rotor (12) in a sealed manner by means of rubbing strips.
  2. Assembly according to claim 1, characterised in that the outer ferrule (23) has a fastening flange (52) at its upstream end, optionally at the second row of blades (28), and optionally a fastening flange at its downstream end.
  3. Assembly according to any one of claims 1 or 2, characterised in that the outer ferrule (23) comprises a first annular row of ports (48) to which the first blades (26) are mounted, and a second annular row of ports (40) to which the second blades (28) are mounted.
  4. Assembly according to any one of claims 1 to 3, characterised in that the outer ferrule (23) comprises an annular wall (50) which is integrally formed and which optionally extends from the first blades (26) to the second blades (28).
  5. Assembly according to any one of claims 1 to 4, characterised in that at or between the first blades (26) and the second blades (28), the outer ferrule (23) comprises an axial portion (64) free of an annular flange, said axial portion (64) optionally comprising a generally tubular or substantially frustoconical outer surface (66).
  6. Assembly according to any one of claims 1 to 5, characterised in that the outer ferrule (23) comprises an annular section of constant thickness, or whose thickness varies by at most 30%, or at most 15%; said annular section being disposed between the first blades (26) and the second blades (28).
  7. Assembly according to claim 6, characterised in that the annular section extends axially over the majority of the space between the first blades (26) and the second blades (28).
  8. Assembly according to any one of claims 1 to 7, characterised in that it comprises an integral synchronising ring (44) disposed around the outer ferrule (23).
  9. Assembly according to any one of claims 1 to 8, characterised in that the outer ferrule (23) comprises an inner surface (56) of annular shape whose diameter decreases towards the downstream, in particular along at least one or each row of blades (24; 26; 28).
  10. Turbomachine (2) comprising a rotor (12) and a stator (22) with an assembly, characterised in that the assembly conforms to any one of claims 1 to 9, and the rotor (12) comprises the third annular row of third blades (24) forming an integral assembly.
  11. Turbomachine (2) according to claim 10, characterised in that it comprises a compressor (4; 6), the second row of blades (28) forming the row of blades upstream of said compressor (4; 6).
  12. Turbomachine (2) according to any one of claims 10 to 11, characterised in that it comprises a casing comprising an annular flow path through which the axial flow of the turbomachine passes, and an axial face; the outer ferrule (23) being mounted on said axial face, possibly around said annular flow path.
EP17186486.1A 2016-08-30 2017-08-16 Stator with adjustable vanes for the compressor of an axial turbine engine Active EP3290657B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
BE2016/5664A BE1024523B1 (en) 2016-08-30 2016-08-30 ADJUSTABLE AUTON STATOR FOR AXIAL TURBOMACHINE COMPRESSOR

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EP3290657A1 EP3290657A1 (en) 2018-03-07
EP3290657B1 true EP3290657B1 (en) 2021-02-24

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US (1) US10408059B2 (en)
EP (1) EP3290657B1 (en)
CN (1) CN107795526A (en)
BE (1) BE1024523B1 (en)
CA (1) CA2976932A1 (en)

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BE1026199B1 (en) * 2018-04-10 2019-11-12 Safran Aero Boosters S.A. EXTERIOR VIROLE IN TWO PARTS

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US20180058220A1 (en) 2018-03-01
CN107795526A (en) 2018-03-13
EP3290657A1 (en) 2018-03-07
CA2976932A1 (en) 2018-02-28
US10408059B2 (en) 2019-09-10
BE1024523B1 (en) 2018-03-29
BE1024523A1 (en) 2018-03-23

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