EP3290657A1 - Stator mit verstellbaren schaufeln für den kompressor eines axialen gasturbinenmotors - Google Patents

Stator mit verstellbaren schaufeln für den kompressor eines axialen gasturbinenmotors Download PDF

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Publication number
EP3290657A1
EP3290657A1 EP17186486.1A EP17186486A EP3290657A1 EP 3290657 A1 EP3290657 A1 EP 3290657A1 EP 17186486 A EP17186486 A EP 17186486A EP 3290657 A1 EP3290657 A1 EP 3290657A1
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EP
European Patent Office
Prior art keywords
blades
row
annular
outer shell
assembly according
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP17186486.1A
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English (en)
French (fr)
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EP3290657B1 (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
    • 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
    • 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
    • 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 axial turbomachine.
  • the invention also relates to the assembly of an adjustable blade stator.
  • the invention also relates to an axial turbomachine, in particular an aircraft turbojet engine or an aircraft turboprop engine.
  • vanes can equip a stator housing turbojet compressor.
  • Such vanes may pivot during engine operation. Their arched blades tilt relative to the primary flow through which they adapt their action according to engine speed and flight conditions. The operating range 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, and on 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 vanes form a vane at best respecting a predefined geometry.
  • the document US 2014/0182292 A1 discloses a double flow turbofan.
  • the turbofan comprises a low pressure compressor provided with several rows of blades, including a row of stator vanes with variable geometry.
  • the different rows of stator vanes are supported by dedicated external ferrules; these different outer rings being fixed one after the other by means of radial annular flanges.
  • This configuration allows mounting in the presence of monobloc blisk.
  • the compressor is assembled by alternately fixing the rows of rotor blades and rows of stator vanes. Each of these rows forms a ring which is brought axially against its support and which covers the row radially. of blades present downstream.
  • this architecture is particularly cumbersome.
  • 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 vanes are integral with their circular supports. Due to the one-piece appearance of each row of rotor blades, the outer shell is necessarily split into two angular portions to allow mounting.
  • the object of the invention is to solve at least one of the problems posed by the prior art. More specifically, the invention aims to improve the efficiency of a turbomachine with a stator with controllable geometry. The invention also aims to provide a compact solution, resistant, lightweight, economical, reliable.
  • the subject of the invention is an assembly for an axial flow turbomachine stator, in particular for an axial flow turbomachine compressor stator, the assembly comprising: a first annular row of first stator vanes extending radially in the axial flow; and a second annular row of second steerable stator vanes which extend radially in the axial flow; remarkable in that it further comprises a one-piece outer shell on which the first blades and the second blades are mounted.
  • the second row of blades is arranged upstream of the first row of blades.
  • the outer ring has a fastening flange at its upstream end, possibly at the level of the second row of blades, and optionally an attachment flange at its downstream end.
  • the outer ring 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 blades 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 ring comprises an annular flange free axial portion, said portion optionally comprising a generally tubular or substantially frustoconical outer surface.
  • the outer shell 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 and the second blades.
  • the annular section extends axially over the majority of the space between the first blades and the second blades.
  • the assembly comprises a second inner ferrule mounted at the inner ends of the second blades, said second inner ferrule having a continuity of circular material.
  • the second inner ferrule is split axially into elements each having a continuity of circular material.
  • the assembly comprises a rotor with a third annular row of third blades disposed between the first blades and the second blades.
  • the assembly comprises a synchronization ring disposed around the outer shell.
  • the ring is arranged axially between the first blades and the second blades.
  • the outer shell comprises an inner surface of annular shape whose diameter decreases downstream, in particular along at least one or each row of blades.
  • the assembly further comprises a fourth annular row of fourth vanes, said fourth vanes being mounted on the outer one-piece shell.
  • the diameter of the inner surface decreases monotonically or continuously.
  • the outer shell has a continuity of circumferential material, and possibly over its entire axial length.
  • the outer shell has a continuity of material along axially first blades and second blades.
  • the outer shell is at least one piece of the first row of orifices in the second row of orifices.
  • the outer shell forms a continuous closed loop and / or monobloc and / or made of material.
  • the second blades are rotatably mounted in the orifices of the second row of orifices.
  • the orifices of the second row are configured to allow a guide 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 blades may vary with respect to the first blades and / or relative to the outer shell.
  • the orientation of the second blades may vary by at least 10 ° or 20 ° or 30 °.
  • the first blades and / or the fourth blades are fixed orientation, and / or each comprise an inner ferrule.
  • the fourth blades are disposed downstream of the first blades.
  • the second ferrule comprises means for guiding in rotation, in particular orifices, cooperating with the second blades.
  • the invention also relates to a turbomachine comprising a stator with an assembly, remarkable in that the assembly is in accordance with 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 ring being mounted on said axial face, possibly around said annular vein.
  • the turbomachine comprises a rotor with at least two rows of rotor blades, for example axially separated by the first annular row of first vanes or by the second annular row of second vanes, each row of vanes.
  • rotor blades forming at least two one-piece assemblies and / or two sets of material, optionally the at least two rows of rotor blades forming a single unit and / or piece of material.
  • the rows of stator vanes and rows of rotor vanes can be placed alternately.
  • each object of the invention is also applicable to the other objects of the invention.
  • each object of the invention is combinable with other objects.
  • the objects of the invention are also combinable with the embodiments of the description, which in addition are combinable with each other.
  • the invention makes it possible to improve the efficiency of the turbomachine. For this purpose, it allows a greater accuracy 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 assembly constraints, and preserves the simplicity of certain operations.
  • inner and outer refer to a positioning relative to the axis of rotation of an axial turbomachine.
  • the axial direction corresponds to the direction along the axis of rotation of the turbomachine.
  • the radial direction is perpendicular to the axis of rotation. Upstream and downstream are in reference to the main flow direction of the flow in the turbomachine.
  • Each blade, rotor and stator has a leading edge, a trailing edge, a pressure surface and an extrados surface; said surfaces connecting the leading edge to the trailing edge; just like the ropes of dawn.
  • the figure 1 represents in simplified manner an axial turbomachine. It is in this case a double-flow turbojet engine.
  • the turbojet engine 2 comprises a first compression level, called a low-pressure compressor 4, a second compression level, called a high-pressure compressor 6, a combustion chamber 8 and one or more levels of turbines 10.
  • the mechanical power the turbine 10 transmitted via the central shaft to the rotor 12 sets in motion the two compressors 4 and 6.
  • the latter comprise several rows of rotor blades associated with rows of stator vanes.
  • the rotation of the rotor about its axis of rotation 14 thus makes it possible to generate a flow of air and to compress it gradually until it reaches the combustion chamber 8.
  • a transmission 15 with an epicyclic reduction gear can be mounted in the rotor 12.
  • An inlet fan commonly referred to as fan, or fan, 16 is coupled to the rotor 12 and generates an air flow which splits into a primary flow 18 passing through the various levels mentioned above of the turbomachine, and a secondary flow 20 passing through a annular duct (partially shown) by generating a thrust useful to the propulsion of an aircraft.
  • the figure 2 is a sectional view of a compressor portion of an axial turbomachine such as that of the figure 1 .
  • the compressor may be a low-pressure compressor 4.
  • the compressor comprises a stator 22 with an outer shell 23 integral. She is in one piece. It describes a closed loop. It has a continuity of circular material and / or a circular homogeneity. It can be monobloc along its entire length. It can include a portion of matter.
  • the outer shell 23 is fitted around the axis of rotation 14 and surrounds the rotor 12.
  • the rotor 12 may comprise several rows of rotor blades 24, for example two or three or more rows of rotor. A single row of rotor blades 24 is here visible. These rotor vanes 24, also called third vanes 24 describe an annular row, called third row. Despite the rotation of the rotor 12, the inclination in the space of the ropes of the rotor blades 24 remains invariant with respect to the axis of rotation 14.
  • the third blades 24 can form a one-piece disc; that is to say that they are indissociable from their support rim 25. Such an arrangement is also known by the term "blisk".
  • the compressor 4 comprises several rectifiers, for example at least two, or at least three or at least four rectifiers.
  • Each rectifier comprises an annular row of stator vanes (26; 28). These blades are statoric in 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 vanes 24 to straighten their air flows, so as to convert the speed of the flow into static pressure.
  • the stator vanes (26; 28) extend substantially radially from the outer shell 23 inwardly.
  • the stator vanes (26; 28) comprise first fixed orientation stator vanes 26 which form a first annular row, and second pilot-controlled stator vanes 28 which form a second annular row.
  • the stator vanes may also include a fourth row of fourth vanes (not shown), and optionally a fifth row of fifth vanes (not shown). These other rows of blades can be placed downstream of the first blades 26, which are they even downstream of the second blades 28. Each of these rows are spaced axially from each other.
  • the first blades 26 can be axially separated from the second blades 28 by the annular row of the third blades 24.
  • the second blades 28 are also called variable-pitch blades, or according to the acronym "VSV” for "Variable Stator Vane”. Their particularity is that the inclination of their ropes can vary with respect to the axis of rotation 14 of the compressor 4, and during the operation of the turbomachine. Their faces intrados and extrados can be more or less exposed to the primary flow 18. Their orientation can be controlled during operation of the turbomachine, for example so as to scan an angle of at least 30 °.
  • the stator of the compressor is mixed. It comprises both pilot-driven vanes; and therefore modifiable; and fixed orientation vanes. While a single row of pilot-driven vanes is shown, however, this stator could also receive more rows of pilot-driven vanes.
  • the second blades 28 can pivot relative to the flow 18, so that they cover more or less fluid vein with their blades. They may further intercept the primary stream 18.
  • the circumferential width they occupy may vary. Their leading edges and their trailing edges may move toward or away from the blades of the same row. Being more or less inclined relative to the general direction of flow, they deviate more or less the primary flow 18 to modulate the flow recovery they provide.
  • the turbomachine and the compressor can follow different yield curves during operation, and this thanks to a variable geometry of their blades.
  • the compressor 4 may comprise internal ferrules (30; 32) suspended at the inner ends of the stator vanes (26; 28), including a first inner ferrule 30 fixed to the first blades 26 and a second inner ferrule 32 relative to which the second blades 28 are hinged. In order to allow the latter to rotate, they have internal pins 34 engaged in the second inner ferrule 32. Likewise, they have external trunnions 36 passing through the outer shell 23 at the level of bosses 38. The bosses 38 may comprise second ports 40 for forming a pivot connection with the external trunnions 36.
  • the trunnions (34; 36) can form cylindrical rods, and can be integral with their blade.
  • Bearings may be provided around the inner pins 34, and between the second orifices 40 and the external pins 36. These are extended by control rods which are mounted control levers 42 controlled by a synchronizing ring 44 which controls each of the second blades 28 via their control levers 42.
  • An actuator (not shown) for a control system makes it possible to drive the synchronization ring 44, and thus the orientation of the second blades 28 in the primary flow 18.
  • the first blades 26 are fixed and rigidly connected to the outer shell 23 via their rods 46 which are introduced through orifices 48 describing a row, said first row of orifices 48.
  • a clamping means helps to freeze the orientation of the first blades 26.
  • the orifices (40; 48) can be made 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 fastening flange 52, a downstream fastening 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 housing, or the intermediate casing.
  • the wall 50 can be made of material. It may extend axially along the second blades 28 and first blades 26, and possibly all along the fourth blades.
  • the wall 50 forms a mounting bracket for the stator vanes (26; 28).
  • the inner surface 56 of the outer shell 23 has an internal diameter which decreases downstream and which marries the ends external to the third blades 24 mounted on the rotor 12.
  • This configuration therefore requires placing the third blades 24 in the outer shell 23 before mounting the second blades 28 and their inner ferrule 32. The opposite would not be technically possible because these second blades 28 would impede the entry of the rotor 12 inside the outer shell 23.
  • the second blades 28 are adjustable. They can pivot on their own thanks to their external trunnions 36 which are adjusted to the orifices 40. Therefore, their assembly is carried out by radial introduction, or following their pivot axes 58 which become their insertion axes.
  • the second inner ferrule 32 is split. It is divided axially into an upstream element 60 and a downstream element 62 which each form closed loops. At least one or each of these elements (60; 62) is each one-piece, that is to say it has a continuity of circular material. One of them can be segmented angularly. At least one of them can cooperate sealingly with the rotor 12, for example with wipers.
  • the downstream element 62 is placed opposite the third blades 24.
  • the second blades 28 are introduced by arranging their internal pins 34 axially opposite and radially of the downstream element 62.
  • the upstream element 60 is axially connected to the downstream element 62 while maintaining the internal trunnions 34.
  • the outer shell 23 comprises a homogeneous axial portion 64.
  • This axial portion 64 may be free of annular flange, and may have an outer surface 66 generally tubular or substantially frustoconical. This outer surface 66 may be axially continuous.
  • the axial portion 64 may extend over the majority of the space between the first 26 and second blades 28, and may show a reduction in diameter of the second blades 28 to the first blades 26.
  • the axial portion 64 may define on the wall 50 an annular section of constant thickness.
  • the thickness of the annular section may 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 blades 26 and the second blades 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)
EP17186486.1A 2016-08-30 2017-08-16 Stator mit verstellbaren schaufeln fürden kompressor eines axialen gasturbinenmotors Active EP3290657B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
BE2016/5664A BE1024523B1 (fr) 2016-08-30 2016-08-30 Stator a aubes ajustables pour compresseur de turbomachine axiale

Publications (2)

Publication Number Publication Date
EP3290657A1 true EP3290657A1 (de) 2018-03-07
EP3290657B1 EP3290657B1 (de) 2021-02-24

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP17186486.1A Active EP3290657B1 (de) 2016-08-30 2017-08-16 Stator mit verstellbaren schaufeln fürden kompressor eines axialen gasturbinenmotors

Country Status (5)

Country Link
US (1) US10408059B2 (de)
EP (1) EP3290657B1 (de)
CN (1) CN107795526A (de)
BE (1) BE1024523B1 (de)
CA (1) CA2976932A1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3553322A1 (de) * 2018-04-10 2019-10-16 Safran Aero Boosters SA Einheit für ein axiales turbotriebwerk mit einem zweiteiligen aussenring

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102024128180A1 (de) * 2024-09-30 2026-04-02 MTU Aero Engines AG Elektrisches Anti-Vereisungssystem

Citations (4)

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EP3290657B1 (de) 2021-02-24
US20180058220A1 (en) 2018-03-01
BE1024523A1 (fr) 2018-03-23
CA2976932A1 (en) 2018-02-28
BE1024523B1 (fr) 2018-03-29
CN107795526A (zh) 2018-03-13
US10408059B2 (en) 2019-09-10

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