EP3290657B1 - Stator mit verstellbaren schaufeln fürden kompressor eines axialen gasturbinenmotors - Google Patents

Stator mit verstellbaren schaufeln fürden kompressor eines axialen gasturbinenmotors 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
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Active
Application number
EP17186486.1A
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English (en)
French (fr)
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EP3290657A1 (de
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/de
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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)

Claims (12)

  1. Baugruppe für eine Axialströmungsturbomaschine (2), insbesondere für einen Kompressor (4; 6) einer Axialströmungsturbomaschine (2), wobei die Baugruppe Folgendes umfasst:
    - eine erste ringförmige Anordnung von ersten Schaufeln (26) des Stators (22), die sich radial in der axialen Strömung erstrecken;
    - eine zweite ringförmige Anordnung von zweiten pilotorientierten Schaufeln (28) des Stators (22), die sich radial in der axialen Strömung erstrecken, wobei die zweite Anordnung stromaufwärts der ersten Anordnung angeordnet ist;
    - eine einteilige äußere Ummantelung (23), auf der die ersten Schaufeln (26) und die zweiten Schaufeln (28) montiert sind; und
    - einen Rotor (12) mit einer dritten ringförmigen Anordnung von dritten Schaufeln (24), die zwischen den ersten Schaufeln (26) und den zweiten Schaufeln (28) angeordnet sind; und
    einen inneren Klemmring (32), der an den inneren Enden der zweiten Schaufeln (28) angebracht ist, wobei der innere Klemmring (32) eine durchgehende Fläche aus kreisförmigem Material aufweist, wobei der innere Klemmring (32) axial in Elemente (60; 62) unterteilt ist, die jeweils eine durchgehende Fläche aus kreisförmigem Material aufweisen, dadurch gekennzeichnet, dass mindestens eines der Elemente (60; 62) mit dem Rotor (12) auf dichte Weise mittels Leckstellen zusammenwirkt.
  2. Baugruppe nach Anspruch 1, dadurch gekennzeichnet, dass der äußere Klemmring (23) an seinem stromaufwärtigen Ende einen Befestigungsflansch (52), gegebenenfalls an der zweiten Anordnung von Schaufeln (28), und gegebenenfalls einen Befestigungsflansch an seinem stromabwärtigen Ende aufweist.
  3. Baugruppe nach einem der Ansprüche 1 bis 2, dadurch gekennzeichnet, dass der äußere Klemmring (23) eine erste ringförmige Anordnung von Öffnungen (48), an denen die ersten Schaufeln (26) montiert sind, und eine zweite ringförmige Anordnung von Öffnungen (40), an denen die zweiten Schaufeln (28) montiert sind, aufweist.
  4. Baugruppe nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass der äußere Klemmring (23) eine ringförmige Wand (50) aufweist, die als ein Stück ausgebildet ist und sich möglicherweise von den ersten Schaufeln (26) zu den zweiten Schaufeln (28) erstreckt.
  5. Baugruppe nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass an oder zwischen den ersten Schaufeln (26) und den zweiten Schaufeln (28) der äußere Klemmring (23) einen axialen Abschnitt (64) aufweist, der frei von einem ringförmigen Flansch ist, wobei der axiale Abschnitt (64) wahlweise eine allgemein rohrförmige oder im Wesentlichen kegelstumpfförmige Außenfläche (66) aufweist.
  6. Baugruppe nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass der äußere Klemmring (23) einen ringförmigen Abschnitt mit konstanter Dicke aufweist oder dessen Dicke um höchstens 30 % oder höchstens 15 % variiert, wobei der ringförmige Abschnitt zwischen den ersten Schaufeln (26) und den zweiten Schaufeln (28) angeordnet ist.
  7. Baugruppe nach Anspruch 6, dadurch gekennzeichnet, dass sich der ringförmige Querschnitt axial über den größten Teil des Raumes zwischen den ersten Schaufeln (26) und den zweiten Schaufeln (28) erstreckt.
  8. Baugruppe nach einem der Ansprüche 1 bis 7, dadurch gekennzeichnet, dass sie einen einteiligen Synchronring (44) aufweist, der um den äußeren Klemmring (23) herum angeordnet ist.
  9. Baugruppe nach einem der Ansprüche 1 bis 8, dadurch gekennzeichnet, dass der äußere Klemmring (23) eine ringförmige Innenfläche (56) aufweist, deren Durchmesser stromabwärts abnimmt, insbesondere entlang mindestens einer oder jeder Anordnung von Schaufeln (24; 26; 28).
  10. Turbomaschine (2), die einen Rotor (12) und einen Stator (22) mit einer Baugruppe umfasst, dadurch gekennzeichnet, dass die Baugruppe einem der Ansprüche 1 bis 9 entspricht und der Rotor (12) die dritte ringförmige Anordnung dritter Schaufeln (24) umfasst, die eine integrale Baugruppe bilden.
  11. Turbomaschine (2) nach Anspruch 10, dadurch gekennzeichnet, dass sie einen Kompressor (4; 6) aufweist, wobei die zweite Schaufelanordnung (28) die Schaufelanordnung stromaufwärts des Kompressors (4; 6) bildet.
  12. Turbomaschine (2) nach einem der Ansprüche 10 bis 11, dadurch gekennzeichnet, dass sie ein Gehäuse aufweist, das einen ringförmigen Strömungsweg, der von der axialen Strömung der Turbomaschine durchströmt wird, und eine axiale Fläche aufweist, wobei der äußere Klemmring (23) auf der axialen Fläche, gegebenenfalls um den ringförmigen Strömungsweg herum, montiert ist.
EP17186486.1A 2016-08-30 2017-08-16 Stator mit verstellbaren schaufeln fürden kompressor eines axialen gasturbinenmotors Active EP3290657B1 (de)

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BE1026199B1 (fr) * 2018-04-10 2019-11-12 Safran Aero Boosters S.A. Virole exterieure en deux parties

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

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