EP3290656B1 - Innenring und ausrichtbare leitschaufel eines kompressors eines axialen turbotriebwerks und herstellungsverfahren - Google Patents

Innenring und ausrichtbare leitschaufel eines kompressors eines axialen turbotriebwerks und herstellungsverfahren Download PDF

Info

Publication number
EP3290656B1
EP3290656B1 EP17186472.1A EP17186472A EP3290656B1 EP 3290656 B1 EP3290656 B1 EP 3290656B1 EP 17186472 A EP17186472 A EP 17186472A EP 3290656 B1 EP3290656 B1 EP 3290656B1
Authority
EP
European Patent Office
Prior art keywords
bearing
assembly
shroud
turbomachine
axial
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
EP17186472.1A
Other languages
English (en)
French (fr)
Other versions
EP3290656A1 (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
Original Assignee
Safran Aero Boosters SA
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Safran Aero Boosters SA filed Critical Safran Aero Boosters SA
Publication of EP3290656A1 publication Critical patent/EP3290656A1/de
Application granted granted Critical
Publication of EP3290656B1 publication Critical patent/EP3290656B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • 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
    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
    • F04D29/056—Bearings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/083—Sealings especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00—Components
    • F05B2240/10—Stators
    • F05B2240/12—Fluid guiding means, e.g. vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/50—Bearings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades

Definitions

  • the invention relates to the field of orientable blades of an axial turbomachine. More specifically, the invention relates to the pivot connection between an internal ferrule and a steerable vane of a turbomachine. The invention also relates to an axial turbomachine, in particular an aircraft turbojet or an aircraft turboprop.
  • the invention relates to an assembly for an axial turbomachine stator, a turbomachine and a method of assembling an assembly for a turbomachine stator.
  • orientable vanes can equip 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 and efficiency are thus extended.
  • the internal shroud which is suspended from the orientable vanes can be split into two axial parts. These two parts can come together in order to enclose the rotating bearings around the internal journals of the orientable vanes.
  • the document FR 3 009 335 A1 discloses a device for guiding a turbomachine variable pitch angle stator vanes.
  • the device comprises a casing from which a row of adjustable vanes starts radially.
  • An internal ferrule is attached to these adjustable vanes.
  • the internal ferrule is suspended from the adjustable vanes by means of cylindrical bushings fitted around the internal journals of the adjustable vanes.
  • the internal ferrule is assembled by axial approximation of its axial parts, while clamping the cylindrical bushes.
  • this assembly operation is complex as the provisional retention of the bushes in a part of the ferrule is unstable.
  • EP 2622 178 A2 shows the technical characteristics of the preamble of the independent claims.
  • the subject of the invention is an assembly for an axial turbomachine stator, in particular for a turbomachine compressor, the assembly comprising: a ferrule, optionally an internal ferrule, which is divided axially into two parts; a pocket formed in the ferrule; a bearing arranged in the pocket; and a steerable vane pivotally mounted in the bearing about a pivot axis; the ferrule comprising an interface for axially separating the parts which is axially offset from the pivot axis of the orientable vane; remarkable in that the bearing comprises a through orifice which is axially eccentric.
  • the bearing provides a seal between the orientable vane and the internal ferrule, optionally the bearing completely fills the pocket.
  • the separation interface axially delimits the bearing, one of the parts optionally comprising a flat circular surface in contact with the bearing.
  • the bearing is axially longer than it is wide along the circumference, and / or wider than it is radially thick.
  • the pocket comprises a sealed bottom, optionally in contact with the bearing.
  • the bearing comprises two generally parallel lateral faces, said faces possibly extending over the majority of the axial length of said bearing.
  • the pocket is predominantly or totally formed in one of the parts, optionally in the upstream part.
  • the downstream part comprises an annular seal, optionally with an abradable material, which is separated axially and / or radially from the bearing.
  • the bearing comprises an external face with a flat and circular surface.
  • the bearing comprises means for locking in rotation, in particular a flat face, cooperating with a pocket partition.
  • the bearing comprises a portion with radial extra thickness partially forming the outer surface of the shell.
  • the subject of the invention is also a turbomachine comprising an assembly for a stator, remarkable in that the assembly conforms to the invention, preferably the turbomachine comprises an intermediate casing with an internal hub.
  • the intermediate casing comprises a downstream face; the assembly being mounted on said downstream face.
  • one of the parts of the ferrule is in contact with the internal hub, and / or one of the parts of the ferrule is at a distance axially from the internal hub.
  • the subject of the invention is also a method of assembling an assembly for a turbomachine stator, the assembly comprising an outer shell, an inner shell with a pocket occupied by a rotating bearing in connection with an orientable blade, the inner shell. being split axially into a first part and into a second part, the method comprising the following steps: (b) placing a first shell part; (c) radial introduction of the orientable vane in a support; (d) radial engagement of the bearing within the steerable vane; the bearing comprising an axial guide face; remarkable in that the method further comprises a step (e) mounting the second part by sliding against the axial guide face of the bearing; the assembly being in accordance with the invention.
  • step (b) placing a first part, said part cooperates with a sealing device of the rotor of the turbomachine.
  • 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 subjects of the invention can also be combined with the embodiments of the description, which in addition can be combined with one another.
  • the invention optimizes the maintenance of the bearings by virtue of their asymmetry which has repercussions on the parts of the shell. Staggering the interface between the parts also allows more space to use a temporary socket holding tool. In addition, the contour of the bearings allows them to better save their place in the pockets.
  • the stator is more economical to produce.
  • the configuration of the ferrule parts like the filling character of the levels; increases the tightness and therefore the efficiency of the turbomachine.
  • the closed shape of the bottom of the pockets further increases the tightness, while increasing the rigidity of the corresponding part.
  • 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.
  • 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.
  • An inlet fan commonly referred to as a fan, or blower, 16 is coupled to the rotor 12 and generates an air flow which is divided into a primary flow 18 passing through the various aforementioned levels of the turbomachine, and a secondary flow 19 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 20 with a one-piece outer shell 22 which can form the outer casing of the compressor.
  • the outer shell 22 is in one piece. It describes a closed loop. It has a circular material continuity and / or a circular homogeneity. It can be in one piece over its entire length. It can include a portion coming from the material.
  • the rotor 12 may comprise several rows of rotor blades 24, for example two or three or more rotor rows (only one visible). 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 rotor blades 24 can form a single-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 comprises an annular row of stator vanes 26. These vanes are statoric in the sense that they are mounted on the stator 20 and therefore remain in contact with the latter.
  • the rectifiers are associated with the fan or with a row of rotor blades 24 to straighten their air flows, so as to convert the speed of the flow into static pressure.
  • the stator vanes 26 comprise stator vanes with piloted orientation 26. These orientable vanes 26 extend radially towards the inside of the outer shell 22 and describe an annular row. These orientable vanes 26 are also called variable-pitch vanes, or according to the acronym “VSV” for “Variable Stator Vane”. Their particularity is that they can pivot on themselves, so that the inclination of their cords can vary with respect to the axis of rotation 14 of the compressor 4, and this during its operation.
  • the orientable vanes 26 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 edge and their trailing edge 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 stator vanes can comprise other annular rows of vanes 28; these other blades possibly being fixed orientation or piloted orientation.
  • the stator 20 of the compressor 4 comprises an internal ferrule 30 suspended from the internal ends of the orientable vanes 26, but while retaining the pivoting nature of the orientable vanes 26.
  • the internal ferrule 30 is equipped with rotating bearings 32 which are mounted around internal journals 34 of the orientable vanes 26.
  • Radially opposite, the orientable vanes 26 have external journals 36 engaged in orifices 38, possibly formed through bosses 40.
  • the journals (34; 36) can form cylindrical rods, and can be integral with their blade.
  • the steerable vane control system is well known to those skilled in the art and will not be detailed further.
  • the stator 20 comprises an intermediate casing 42, forming part of the supporting structure of the turbomachine.
  • This intermediate casing 42 can receive a separating spout (not shown).
  • the intermediate casing 42 may comprise an outer portion 44, casing arms 46 forming supports passing through the primary flow 18, and an inner hub 48 which may join the inner ferrule 30.
  • the outer shell 22 may include an annular wall 50 and an upstream flange 52 fixed to the outer portion 44 of the intermediate casing 42.
  • the wall 50 may be integral. It can extend axially along the orientable vanes 26 and possibly the other vanes.
  • the internal surface 56 of the external ferrule 22 has an internal diameter which decreases downstream and which matches the external ends of the rotor blades 24. This configuration therefore requires placing the rotor blades 24 in the outer shell 22 before mounting the orientable vanes 26 and their inner shell 30. The opposite would not be physically possible because of the one-piece nature of the outer shell 22.
  • the inner shell 30 is split. It is divided axially into an upstream part 60 and into a downstream part 62. These parts can each form a closed loop. At least one or each part (60; 62) is in one piece, that is to say that it (s) present (s) a continuity of circular material. Alternatively, one of them is segmented angularly. However, a one-piece configuration improves the rigidity and the retention of the internal ferrule 30 via the internal journals 34, which form pivot connections; that is to say a mechanical connection with only one degree of freedom.
  • the figure 3 sketch a plan view of the inner ferrule 30 of the figure 2 , the levels not being shown for the sake of clarity.
  • the axis of rotation 14 is drawn.
  • the upstream part 60 and the downstream part 62 are shown from the outside.
  • the upstream part 60 has an annular row of pockets 64, four of them being shown.
  • the pockets 64 each have a closed bottom 66 allowing a seal against the downstream part 62. They can end against the axial separation interface 68 of the axial parts (60; 62).
  • the axial separation interface 68 may be a plane perpendicular to the axis of rotation 14, or be substantially conical.
  • the pockets 66 have the shapes of the upturned letter “U”, the bearings being of a shape complementary to that of these pockets 64. These pockets 64 are separated by watertight partitions 69.
  • the figure 4 illustrates the bearing 32 in an isometric view, the bearing possibly corresponding to the bearing shown in relation to the figures 2 and 3 .
  • the bearing 32 is in one piece. It has a semi-cylindrical upstream portion, and a rectangular downstream portion provided with lateral faces 70 for axial guidance. These faces 70 can be parallel.
  • An orifice 72 intended to receive the internal journal of the orientable vane is at the interface of the portions.
  • a flat disk-shaped surface 74 surrounds the orifice 72.
  • the bearing has a radial allowance 76, which is in elevation with respect to the planar surface 74. The allowance 76 may join an axial end of the bearing, for example. its flat downstream facet 78 which allows a locking in rotation against the downstream part of the shell.
  • the figure 5 corresponds to an enlargement of an area delimited by figure 2 .
  • the section of the internal ferrule 30 at the level of an orientable vane 26 and of its bearing 32 coincides with the pivot axis 80 of the internal journal 34.
  • the pivot axis 80 is distant from the axial interface 68 between the parts (60; 62). This makes it possible to better maintain the bearing 32 in one of the parts; in this case in the upstream part 60.
  • the distant aspect can be measured in the material of the ferrule 30.
  • the extra thickness 76 is flush with the outside of the shell 30.
  • the extra thickness 76 may partially form the outer surface 82 of the inner shell 30; outer surface 82 which makes it possible to delimit and guide the primary flow 18 in the turbomachine.
  • This extra thickness 76 makes it possible to fill a space in the shell 30 while accommodating its compactness.
  • the profile of the inner shell may have a length greater than or equal to twice its radial thickness.
  • the extra thickness 76 can form a separation between the downstream part 62 and the platen disc 84 of the orientable vane 26. In particular, it can slide against the cylindrical contour of the disc 84.
  • the rotor 12 cooperates in a sealed manner with the downstream part 62, possibly at the level of an abradable seal 86.
  • the bearing 32 does not overlap the annular seal 86 since the interface 68 separates them.
  • the figure 6 is a diagram of an assembly process for a turbomachine.
  • the entities of the turbomachine may correspond to those described in relation to the figures 1 to 5 .
  • the first part in place is in contact with the rotor, for example around and / or in contact with a seal of the rotor.
  • This joint can be a game of wicks.
  • the seal can center the downstream part with respect to the rotor.
  • the other part can be free of joint.
  • step (d) engagement 106 the bearing slides radially against the first part, in particular against the downstream part, and is fitted around the internal journal of the orientable vane.
  • step (e) assembly 108 the upstream part is translated axially while being guided by the guide faces. Since the bearings can rotate relative to the journals, they rotate so as to be centered in their pocket, which simplifies the approach of the upstream part.

Landscapes

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

Claims (15)

  1. Baugruppe für einen Stator (20) einer axialen Turbomaschine (2), insbesondere für einen Verdichter (4; 6) einer Turbomaschine (2), wobei die Anordnung umfasst:
    - eine Manschette (30), möglicherweise eine innere Manschette (30), die axial in zwei Teile (60; 62) geteilt ist;
    - eine in der Manschette (30) gebildete Tasche (64);
    - ein in der Tasche (64) angeordnetes Lager (32); und
    - eine verstellbare Schaufel (26), die im Lager (32) um eine Schwenkachse (80) schwenkbar gelagert ist;
    wobei die Manschette (30) eine Schnittstelle zur axialen Trennung (68) der Teile (60; 62) umfasst, wobei die Schwenkachse (80) der verstellbaren Schaufel (26) axial von der axialen Trennschnittstelle (68) beabstandet ist,
    dadurch gekennzeichnet, dass das Lager (32) eine durchgehende und axial exzentrisch axiale Öffnung (72) umfasst.
  2. Baugruppe nach Anspruch 1, dadurch gekennzeichnet, dass das Lager (32) die Dichtheit zwischen der verstellbaren Schaufel (26) und der Manschette (30) sicherstellt, wobei das Lager (32) optional die Tasche (64) vollständig ausfüllt.
  3. Baugruppe nach einem der Ansprüche 1 bis 2, dadurch gekennzeichnet, dass die Trennschnittstelle (68) das Lager (32) axial begrenzt, wobei eines der Teile (60; 62) optional eine flache kreisförmige Fläche aufweist, die mit dem Lager (32) in Kontakt steht.
  4. Baugruppe nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass das Lager (32) je nach Umfang axial länger als breit und / oder breiter als radial dick ist.
  5. Baugruppe nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass die Tasche (64) einen abgedichteten Boden (66) umfasst, der gegebenenfalls mit dem Lager (32) in Kontakt steht.
  6. Baugruppe nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass das Lager (32) zwei Seitenflächen (70) entlang des im Allgemeinen parallelen Umfangs umfasst, wobei sich die Flächen allenfalls über den größten Teil der axialen Länge des Lagers (32) erstrecken.
  7. Baugruppe nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, dass die Tasche (64) überwiegend oder vollständig in einem der Teile (60; 62) ausgebildet ist, gegebenenfalls im stromaufwärtigen Teil (60).
  8. Baugruppe nach einem der Ansprüche 1 bis 7, dadurch gekennzeichnet, dass der stromabwärtige Teil (62) eine ringförmige Dichtung (86) umfasst, gegebenenfalls mit einem abriebbaren Material, die axial und / oder radial vom Lager (32) beabstandet ist.
  9. Baugruppe nach einem der Ansprüche 1 bis 8, dadurch gekennzeichnet, dass das Lager (32) eine Außenfläche mit einer ebenen und kreisförmigen Fläche (74) zum Führen der Schaufel während der Rotation umfasst.
  10. Baugruppe nach einem der Ansprüche 1 bis 9, dadurch gekennzeichnet, dass das Lager (32) Mittel zur Drehverriegelung aufweist, insbesondere eine ebene Fläche (70; 78), die mit einer Trennwand (69) der Tasche (64) zusammenwirkt.
  11. Baugruppe nach einem der Ansprüche 1 bis 10, dadurch gekennzeichnet, dass das Lager (32) einen radial verdickten Abschnitt (76) umfasst, der teilweise die Außenfläche (82) der Manschette (30) bildet.
  12. Turbomaschine (2) umfassend eine Baugruppe für einen Stator, dadurch gekennzeichnet, dass die Baugruppe einem der Ansprüche 1 bis 11 entspricht, wobei die Turbomaschine (2) vorzugsweise ein Zwischengehäuse (42) mit einer internen Nabe (48) umfasst.
  13. Turbomaschine (2) nach Anspruch 12, dadurch gekennzeichnet, dass das Zwischengehäuse (42) eine stromabwärtige Fläche umfasst, wobei die Baugruppe an der stromabwärtigen Seite montiert ist, und einer der Teile (60; 62) der Manschette (30) in Kontakt mit der inneren Nabe (48) und / oder einer der Teile (60; 62) der Manschette (30) von der inneren Nabe (48) axial beabstandet.
  14. Verfahren zum Zusammenbau einer Baugruppe für einen Stator (20) einer Turbomaschine (2), wobei die Baugruppe eine äußere Manschette (22), eine innere Manschette (30) mit einer Tasche (64), die von einem Drehlager (32) in Verbindung mit einer verstellbaren Schaufel (26) besetzt ist, umfasst, wobei die innere Manschette (30) axial in einen ersten Teil und einen zweiten Teil geteilt ist, wobei das Verfahren die folgenden Schritte umfasst:
    (b)- Platzierung (102) eines ersten Teils (62) der inneren Manschette (30);
    (c)- Radiales Einsetzen (104) der verstellbaren Schaufel (26) in einen Träger;
    (d)- Radiales Einrasten (106) des Lagers (32) im Inneren der verstellbaren Schaufel (26); wobei das Lager (32) eine axiale Führungsfläche (70) umfasst,
    dadurch gekennzeichnet, dass das Verfahren darüber hinaus einen Schritt umfasst
    (e)- Montage (108) des zweiten Teils (60), der axial gegen die axiale Führungsfläche (70) des Lagers (32) gleitet, wobei die Baugruppe einem der Ansprüche 1 bis 11 entspricht.
  15. Verfahren nach Anspruch 14, dadurch gekennzeichnet, dass während des Schritts (b) des Anbringens (102) eines ersten Teils (62) dieses Teil mit einer Dichtungsvorrichtung des Turbomaschinenrotors (2) zusammenwirkt.
EP17186472.1A 2016-08-30 2017-08-16 Innenring und ausrichtbare leitschaufel eines kompressors eines axialen turbotriebwerks und herstellungsverfahren Active EP3290656B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
BE2016/5663A BE1024524B1 (fr) 2016-08-30 2016-08-30 Virole interne et aube orientable de compresseur de turbomachine axiale

Publications (2)

Publication Number Publication Date
EP3290656A1 EP3290656A1 (de) 2018-03-07
EP3290656B1 true EP3290656B1 (de) 2021-09-29

Family

ID=56888861

Family Applications (1)

Application Number Title Priority Date Filing Date
EP17186472.1A Active EP3290656B1 (de) 2016-08-30 2017-08-16 Innenring und ausrichtbare leitschaufel eines kompressors eines axialen turbotriebwerks und herstellungsverfahren

Country Status (5)

Country Link
US (1) US11512713B2 (de)
EP (1) EP3290656B1 (de)
CN (1) CN107795525B (de)
BE (1) BE1024524B1 (de)
CA (1) CA2976930A1 (de)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE1024605B1 (fr) * 2016-09-27 2018-04-26 Safran Aero Boosters S.A. Carter avec bras aspirant pour turbomachine axiale
US11028709B2 (en) * 2018-09-18 2021-06-08 General Electric Company Airfoil shroud assembly using tenon with externally threaded stud and nut
GB2596701A (en) * 2019-04-01 2022-01-05 Dasari Dileep Systems and methods for increasing the efficiency of axial ducted fans
CN110617117B (zh) * 2019-08-02 2022-04-08 中国航发贵阳发动机设计研究所 一种涡轮导向器喉道面积调节方法
DE102021129534A1 (de) 2021-11-12 2023-05-17 MTU Aero Engines AG Leitschaufelanordnung einer Strömungsmaschine und Verfahren zur Montage einer Leitschaufelanordnung

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB749577A (en) * 1952-07-10 1956-05-30 Havilland Engine Co Ltd Improvements in or relating to blade ring assemblies for axial flow compressors or turbines
US4792277A (en) * 1987-07-08 1988-12-20 United Technologies Corporation Split shroud compressor
US4834613A (en) * 1988-02-26 1989-05-30 United Technologies Corporation Radially constrained variable vane shroud
US5639212A (en) * 1996-03-29 1997-06-17 General Electric Company Cavity sealed compressor
FR2824593B1 (fr) * 2001-05-10 2003-07-18 Snecma Moteurs Agencement de support de pivots d'aubes de stator a deux parties d'anneau liees par un element interne
DE102006024085B4 (de) * 2006-05-23 2020-04-16 MTU Aero Engines AG Turboverdichter in Axialbauweise
US7713022B2 (en) * 2007-03-06 2010-05-11 United Technologies Operations Small radial profile shroud for variable vane structure in a gas turbine engine
US8500394B2 (en) * 2008-02-20 2013-08-06 United Technologies Corporation Single channel inner diameter shroud with lightweight inner core
US8858165B2 (en) * 2010-09-30 2014-10-14 Rolls-Royce Corporation Seal arrangement for variable vane
JP5747703B2 (ja) * 2011-07-13 2015-07-15 株式会社Ihi ターボ圧縮機
US10125789B2 (en) * 2013-02-15 2018-11-13 United Technologies Corporation Bushing arranged between a body and a shaft, and connected to the body
FR3009335B1 (fr) 2013-07-30 2015-09-04 Snecma Dispositif de guidage d'aubes de redresseur a angle de calage variable de turbomachine
JP5736443B1 (ja) * 2013-12-19 2015-06-17 川崎重工業株式会社 可変静翼機構

Also Published As

Publication number Publication date
CN107795525B (zh) 2022-01-04
EP3290656A1 (de) 2018-03-07
CN107795525A (zh) 2018-03-13
CA2976930A1 (en) 2018-02-28
BE1024524B1 (fr) 2018-03-26
US20180058471A1 (en) 2018-03-01
BE1024524A1 (fr) 2018-03-23
US11512713B2 (en) 2022-11-29

Similar Documents

Publication Publication Date Title
EP3290656B1 (de) Innenring und ausrichtbare leitschaufel eines kompressors eines axialen turbotriebwerks und herstellungsverfahren
EP3517731B1 (de) Anordnung mit einer ringförmigen durchlassöffnung zwischen einer stator- und einer rotorplattform einer strömungsmaschine und zugehöriges verfahren zur regelung der verdichterstabilität
EP2801702A1 (de) Stator-Innenring eines Turbotriebwerks mit Abriebmaterial
EP3477050B1 (de) Verdichter einer turbomaschine mit asymmetrisch konturiertem strömungsring
WO2022018380A1 (fr) Module de turbomachine equipe d'une helice et d'aubes de stator supportees par des moyens de maintien et turbomachine correspondante
EP3412876B1 (de) Kompressor mit variabler geometrie einer axialen strömungsmaschine
WO2017017392A1 (fr) Ensemble de redressement de flux d'air a performances aerodynamiques ameliorees
EP3290657B1 (de) Stator mit verstellbaren schaufeln fürden kompressor eines axialen gasturbinenmotors
EP3382242B1 (de) Bürstendichtung für rotor einer turbomaschine
FR3073891B1 (fr) Mat d'un ensemble propulsif
EP4025789B1 (de) Polyspherische nabe einer turbomaschine für verstellbare schaufeln
WO2021123146A1 (fr) Module pour turbomachine
EP3382155B1 (de) Dichtungssystem für eine strömungsmaschine, und zugehörige strömungsmaschine
BE1026325B1 (fr) Virole a profilage evolutif pour compresseur de turbomachine
BE1026006B1 (fr) Systeme d’aubes a calage variable pour compresseur de turbomachine
WO2024033065A1 (fr) Aube à calage variable de stator de turbomachine d'aéronef et turbomachine d'aéronef
BE1025666B1 (fr) Profil non-axisymetrique de carter pour compresseur turbomachine

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION HAS BEEN PUBLISHED

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20180829

RBV Designated contracting states (corrected)

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: EXAMINATION IS IN PROGRESS

17Q First examination report despatched

Effective date: 20201130

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: EXAMINATION IS IN PROGRESS

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20210322

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

Ref country code: AT

Ref legal event code: REF

Ref document number: 1434364

Country of ref document: AT

Kind code of ref document: T

Effective date: 20211015

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602017046663

Country of ref document: DE

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: FRENCH

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG9D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20211229

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210929

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210929

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210929

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20211229

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210929

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210929

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20210929

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1434364

Country of ref document: AT

Kind code of ref document: T

Effective date: 20210929

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210929

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20211230

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210929

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20220129

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210929

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210929

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20220131

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210929

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210929

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210929

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210929

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210929

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210929

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602017046663

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210929

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20220630

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210929

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210929

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210929

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20220816

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20220831

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20220831

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20220816

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20230720

Year of fee payment: 7

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20230720

Year of fee payment: 7

Ref country code: DE

Payment date: 20230720

Year of fee payment: 7

Ref country code: BE

Payment date: 20230720

Year of fee payment: 7

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20170816

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210929

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210929

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210929

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210929