EP3203035B1 - Système d'aube directrice d'une turbomachine - Google Patents

Système d'aube directrice d'une turbomachine Download PDF

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Publication number
EP3203035B1
EP3203035B1 EP17153139.5A EP17153139A EP3203035B1 EP 3203035 B1 EP3203035 B1 EP 3203035B1 EP 17153139 A EP17153139 A EP 17153139A EP 3203035 B1 EP3203035 B1 EP 3203035B1
Authority
EP
European Patent Office
Prior art keywords
guide vane
inner ring
turbomachine
circumferential direction
recess
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
EP17153139.5A
Other languages
German (de)
English (en)
Other versions
EP3203035A1 (fr
Inventor
Joachim Wulf
Frank Stiehler
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines AG
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 MTU Aero Engines AG filed Critical MTU Aero Engines AG
Publication of EP3203035A1 publication Critical patent/EP3203035A1/fr
Application granted granted Critical
Publication of EP3203035B1 publication Critical patent/EP3203035B1/fr
Active legal-status Critical Current
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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
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/003—Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
    • 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
    • F04D29/40—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
    • 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
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • 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
    • F05D2230/60—Assembly methods
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking

Definitions

  • the invention relates to a guide vane system for a turbomachine according to the preamble of claim 1.
  • the invention further relates to a turbomachine and a method for assembling a guide vane system for a turbomachine.
  • a guide wheel for a turbomachine in which guide vanes are arranged next to one another in the circumferential direction of the guide wheel and can be adjusted about their radially extending longitudinal axis.
  • An inner ring is arranged radially on the inside of the guide vanes.
  • the guide vanes are mounted at their radially inner end in respective recesses in the inner ring.
  • At least one of the guide vanes has a sliding surface that is essentially perpendicular to the longitudinal axis and is arranged radially on the inside. The sliding surface and the inner ring form a friction pair. Leakages in the bearing of the guide vane on the inner ring are thereby particularly reduced.
  • a locking pin arranged in a plane perpendicular to the longitudinal axis of the guide vane is positively connected in the radial direction to the radially inner end of the guide vane.
  • the adjustability of the guide vane, in particular the rotatability about the longitudinal axis of the guide vane, is made possible by means of a groove formed in the circumferential direction in the inner ring in which the securing pin is guided.
  • Each guide vane is secured with a locking pin assigned to it.
  • the guide vane is positively connected in the radial direction to the radially inner end of the guide vane by means of a rivet connection or screw connection arranged in a plane perpendicular to the longitudinal axis of the guide vane.
  • a screw arranged parallel to the longitudinal axis of the guide vane is designed to fix the inner ring to the radially inner end of the guide vane.
  • a fuse in the form of a riveted connection or screw connection is provided for each guide vane.
  • the object of the present invention is to improve the securing of a guide vane system for a turbomachine. Furthermore, it is an object of the invention to improve a turbomachine and to provide a particularly simple method for assembling a guide vane system for a turbomachine.
  • a guide vane system with the features of claim 1 a turbomachine with the features of claim 10 and by a method for assembling a guide vane system with the features of claim 11.
  • Advantageous refinements with expedient developments of the invention are specified in the respective subclaims, with advantageous refinements of the guide vane system, the turbomachine and the method for assembling the guide vane system as mutually advantageous refinements.
  • a first aspect of the invention relates to a guide vane system for a turbomachine with at least one guide vane rotatably mounted about an adjustment axis, which is arranged with a radially inner end region in a corresponding recess of an inner ring, the arrangement of the guide vane on the inner ring being positively secured by means of a securing element ,
  • the securing element is designed as an elongated element which is at least in a recess and / or through opening of the radially inner end region of the guide vane running in the circumferential direction of the turbomachine and at least in a recess and / or through opening running in the circumferential direction of the turbomachine Inner ring is arranged.
  • This securing represents a reliable positive connection of a guide vane journal to the inner ring.
  • a jumping off of the inner ring, for example in the case of so-called pump impulses, is therefore particularly unlikely or even completely impossible.
  • the respective recesses and / or through openings preferably do not open any additional leakage paths in the axial direction, since these run in the circumferential direction.
  • the positive connection of the inner ring with the guide vane also suppresses what is known as cording thermal deformation of the inner ring. This prevents unnecessary wear of respective sealing elements arranged on the inner ring.
  • the cording is caused in particular by transient thermal deformations of the inner ring and / or the guide vanes.
  • the guide vane system can be part of a guide vane ring, which is also referred to as a stator.
  • the guide vane system can comprise a plurality of guide vanes which are rotatably mounted about an adjustment axis and which are arranged next to one another in the circumferential direction.
  • the respective adjustment axis of the guide vanes preferably corresponds to a radial direction of the turbomachine.
  • the guide vane or the guide vanes are preferably mounted on the inner ring and / or the inner ring is held on the guide vanes.
  • the securing element is preferably designed to prevent relative radial movement of the guide vanes and the inner ring relative to one another, or at least to limit them to a certain maximum size, by the arrangement in the respective recesses and / or through openings.
  • the respective recesses and / or through openings can be designed such that either the guide vane with the securing element can be rotated together about the adjustment axis within the inner ring or the guide vane can be rotated without the securing element having to be rotated as well. This ensures that the guide vane can be adjusted and / or adjusted even with the safety device.
  • the guide vane can thus continue to be adjusted or rotated in a predetermined angular range, as a result of which the turbomachine can be operated with a particularly high degree of efficiency at every operating point.
  • the guide vane system is preferably installed in a low-pressure compressor or a high-pressure compressor of aircraft engines.
  • the guide vane of the guide vane system can have a truncated cone shape at its radially inner end region. This design is characterized by a very low radial height. This allows a leak-optimal design of the respective inner cavities of the inner ring and also of the turbomachine and thus overall a structurally favorable design of a rotor assembly. In the case of a radially inner end region, which is designed as a bearing journal and is encompassed by the inner ring, increased leakages can be expected. In particular, it may be necessary in this case to form the inner ring axially divided. In addition, the recesses and / or through openings can be aligned with one another.
  • respective through openings and / or recesses are arranged at least partially overlapping one another so that the securing element can be guided in the circumferential direction through this recess and / or through opening.
  • the through openings and / or recesses are preferably shaped such that the guide vane is still adjustable.
  • a securing element can be used to jointly secure a large number or all of the guide vanes.
  • a securing element can be inserted into the inner ring in the circumferential direction. This securing element can extend over the entire extent in the circumferential direction of the inner ring. This makes the guide vane system particularly quick and easy to install, and fewer parts are required.
  • the common securing of several guide vanes by means of a common securing element is only made possible in this simple form by aligning the respective recess and / or through opening in the circumferential direction of the turbomachine.
  • the recess of the guide vane is designed as an outer groove that extends at least partially around the radially inner end region of the guide vane.
  • a groove can be manufactured quickly and inexpensively.
  • such a groove does not restrict the adjustment range of the guide vane when rotating about the adjustment axis.
  • the groove running on the circumference of the radially inner end region of the guide vane has an advantageous effect on the vibration behavior of the guide vane during operation of the turbomachine.
  • the securing element can be supported radially outwards and / or inwards in the groove of the guide vane.
  • the securing element is designed as a securing wire which runs in the circumferential direction and is round or rectangular in cross section.
  • a fuse wire is a particularly inexpensive to manufacture and / or particularly light fuse element.
  • a locking wire can be adapted particularly easily to the shape or the radius of the inner ring.
  • the respective recesses and / or through openings can have a corresponding cross section at least in regions.
  • An angular, in particular a rectangular cross-section and an angular, in particular rectangular, safety wire can be manufactured particularly cost-effectively.
  • a round cross-section and / or a round safety wire are particularly robust. In particular, there are no voltage peaks due to sharp angles in the radially inner end region of the guide vane and / or in the inner ring.
  • the inner ring is undivided in the axial direction of the turbomachine.
  • Such an inner ring can be manufactured particularly cost-effectively, does not require any additional connecting elements in the axial direction during assembly and has no leakage through a gap running in the circumferential direction.
  • Such an axially undivided inner ring is particularly advantageous if the radially inner end region of the guide vane is frustoconical.
  • an end region shaped in this way can be inserted into the corresponding recess of the inner ring without any problems.
  • no additional sleeves are then required for mounting the guide vane on the inner ring.
  • the inner ring is divided into at least two inner ring segments in the circumferential direction of the turbomachine.
  • the guide vane system can have an inner ring with two inner ring segments extending over 180 °.
  • the inner ring it is also possible for the inner ring to be composed of four 90-degree inner ring segments.
  • An inner ring divided in the circumferential direction enables a particularly simple assembly of the turbomachine.
  • a particularly large inner ring can be provided in this way, the diameter of which is not limited to a maximum diameter of a component that can be manufactured by the respective production systems.
  • an inner ring divided in the circumferential direction enables the securing element to be inserted particularly easily.
  • the securing element can be easily inserted into an opening on an end face of the respective inner ring segments - that is to say a surface which points to the next inner ring segment in the case of the joined inner ring.
  • one securing element is provided for each inner ring segment.
  • the respective securing elements can be installed particularly easily in the case of inner rings divided in the circumferential direction.
  • a part of the guide vane system consisting of an inner ring segment, the respective assigned guide vanes and the associated securing element, can be assembled and then the inner ring and thus also the guide vane system can then simply be assembled by connecting these inner ring segments to the guide vanes held there and the already installed securing elements become.
  • the inner ring is at least partially manufactured by means of an additive manufacturing process.
  • This enables the production of an inner ring with particularly complex geometries, in particular with undercut recesses and / or through openings, which cannot be produced or can be produced only with great effort using conventional production methods.
  • the additive manufacturing process is particularly suitable for being able to produce an inner ring which is undivided in the axial direction and has complex recesses and / or through openings.
  • the respective guide vanes and / or the securing element to be produced at least partially by means of an additive manufacturing process. In particular, it is thus possible to manufacture the inner ring and the securing element and / or the guide vanes in a joint production, in particular in a single production step.
  • At least one sealing element is arranged radially on the inner ring.
  • a flow space of the turbomachine can be sealed against a shaft of the turbomachine arranged radially on the inside.
  • a seal carrier for holding the sealing element can be provided radially on the inside on the inner ring. This ensures easy replacement of the sealing element.
  • the recess and / or the through opening of the radially inner end region of the guide vane is at least partially elongated to correspond to the securing element and / or the recess and / or the through opening of the inner ring is at least partially elongate corresponding is formed to the fuse element.
  • the securing element can be supported in a particularly reliable manner on the respective recesses and / or through openings.
  • the guide vane Due to the corresponding elongated configurations of the recesses and / or through openings and the securing element, the guide vane is also held in a particularly precise position on the inner ring, as a result of which the so-called cording is particularly reduced.
  • a second aspect of the invention relates to a turbomachine, in particular an aircraft engine.
  • this turbomachine comprises at least one guide vane system according to the first aspect of the invention.
  • a third aspect of the invention relates to a method for assembling a guide vane system for a turbomachine.
  • the guide vane can preferably be rotatably supported on the turbomachine, in particular on an outer ring of the turbomachine or a guide vane ring.
  • Another step is to insert the radially inner end region of the guide vane into the Recess of the inner ring provided.
  • the securing element is then inserted into the recess and / or into the through opening of the inner ring and into the recess and / or into the through opening of the guide vane for positively securing the arrangement of the guide vane on the inner ring.
  • the guide vane may be necessary to align the guide vane after it has been introduced into the recess of the inner ring in such a way that the respective recesses and / or through openings are at least sufficiently overlapping that the securing element can be passed through.
  • the securing element is preferably inserted.
  • the securing element can be inserted into the respective recesses and / or through openings in the circumferential direction.
  • a securing element designed as a securing wire is only adapted to the shape of the inner ring curved in the circumferential direction by this insertion.
  • a sufficiently long securing element can be implemented through a plurality of recesses and / or through openings of a plurality of guide vanes, as a result of which these can be secured together with a single securing element.
  • the method according to the third aspect of the invention is therefore suitable for assembling a guide vane system according to the first aspect of the invention, the guide vane system being able to be assembled in a particularly simple manner in this way.
  • the method for mounting according to the third aspect of the invention can thus also be used as part of a method for mounting a turbomachine according to the second aspect of the invention.
  • the features and advantages resulting from the guide vane system according to the first aspect of the invention or from the turbomachine according to the second aspect of the invention can be found in the descriptions of the first and second aspects of the invention, the advantageous configurations of the first and second aspects of the invention being advantageous configurations of the third aspect of the invention and are to be viewed in reverse.
  • Fig. 1 shows in a meridian section a guide vane system 10 for a turbomachine with at least one guide vane 14 rotatably mounted about an adjustment axis 12, which is arranged with a radially inner end region 16 in a corresponding recess 18 of an inner ring 20.
  • the radially inner end region 16 is frustoconical.
  • the arrangement of the guide vane 14 on the inner ring 20 is positively secured by means of a securing element 22. This securing of the arrangement prevents the radially inner end region 16 of the guide vane 14 from jumping off the inner ring 20 or slipping out of its recess 18, for example due to so-called pump impacts.
  • the guide vane system 10 has an outer ring 24, on which the guide vane 14 is rotatably mounted by means of a bearing pin 26.
  • the turbomachine is preferably designed as an aircraft engine.
  • a coordinate system 30 is drawn in for orientation.
  • the arrow 32 marks the radial direction outwards of the turbomachine.
  • the arrow 34 marks the axial direction of the turbomachine. Since it is a meridian section, the circumferential direction of the turbomachine points in and out of the plane of the sheet and follows a curvature of the inner ring 20 2 to 6
  • the coordinate system 30 is also shown.
  • the circumferential direction of the turbomachine is indicated by arrow 46.
  • the guide vane system 10 forms part of a so-called guide vane ring or a so-called guide wheel of the turbomachine.
  • the guide vane ring comprises a plurality of guide vanes 14 arranged next to one another in the circumferential direction.
  • the guide vane system 10 or the guide vane ring is preferably part of a high-pressure or low-pressure compressor of the turbomachine.
  • a sealing element 36 is provided radially on the inside on the inner ring 20.
  • a flow space which is delimited by the outer ring 24 and the inner ring 20, can be sealed off from other parts of the turbomachine.
  • the sealing element 36 can be designed, for example, as a sliding brush seal, by means of which this flow space is sealed on a rotating shaft of the turbomachine.
  • the securing element 22 is designed as an elongate element which is arranged at least in a through opening 38 of the radially inner end region 16 of the guide vane 14 which runs in the circumferential direction of the turbomachine. Due to the orientation of the securing element 22 in the circumferential direction and also in the corresponding recesses and / or through openings 40 (see also Figure 2 ) a single or common securing two or more guide vanes 14 on the inner ring 20 is possible by means of a single securing element 22. As a result, this fuse is particularly easy to install and requires very few parts.
  • the inner ring 20 is held particularly reliably on the guide vane 14 due to the secured arrangement and respective transient thermal effects, which are also referred to as cording, are reduced. As a result, wear of the sealing element 36 during operation of the turbomachine is particularly low.
  • the guide vanes 14 and the inner ring 20 are supported radially against one another outwards and / or inwards via the securing element 22.
  • the through opening 40 or the through openings 40 of the inner ring 20 are shown in the schematic perspective view of the guide vane system 10 according to FIG Fig. 2 shown. It can also be seen there that the through opening 38 of the guide vane 14 and the through opening 40 of the inner ring 20 are aligned with one another for the assembly or insertion of the securing element 22. Since the respective through openings 38, 40 run in the circumferential direction, there is preferably no additional axial leakage due to the securing of the arrangement of the guide vane system 10.
  • the exemplary embodiment of the guide vane system 10 shown shows through openings 40 of the inner ring 20 which have a rectangular cross section.
  • a securing element 22 (not shown here) preferably likewise has a rectangular cross section in order to be able to be supported particularly well in the through opening 40.
  • the through opening 38 of the guide vane 14 can also have a rectangular cross section.
  • the cross sections 38, 40 of the through openings 38, 40 and the securing element 22 are designed in such a way that they have at least a minimum clearance overall in order to ensure the adjustability of the guide vane 14.
  • the through openings 38, 40 and / or the securing element 22 can also have a round cross section.
  • a round cross section leads to particularly low voltage peaks when subjected to a load, as a result of which the guide vane system 10 is particularly robust.
  • Other cross-sectional shapes can also be selected for the through openings 38, 40 and the securing element 22.
  • FIG. 3 shows the embodiment according to Fig. 1 ,
  • the securing element 22, like the through opening 38 in the radially inner end region 16 of the guide vane 14, is rectangular.
  • the cross section of the through opening 38 is opposite the cross section of the securing element 22 is enlarged in the axial direction. The adjustability of the guide vane 14 is thus ensured.
  • Fig. 4 shows an embodiment in which the securing element 22 is arranged in a recess 42 on the guide vane 14. According to the recess 42 Fig. 4 it is at least partially the groove that extends radially inside the end region 16 of the guide vane 14 on the outside. A corresponding groove for receiving a further area of the securing element 22 is formed on the inside of the recess 18 (not shown). This configuration in turn ensures that the guide vane 14 can continue to be rotated about the adjustment axis 12 without this rotation being blocked by the securing element 22.
  • the securing element 22 also has a round cross section.
  • Fig. 5 shows a recess 42 which is designed as a groove running completely around the radially inner end region 16.
  • a corresponding groove for receiving a further area of the securing element 22 is formed on the inside of the recess 18 (not shown).
  • the completely circumferential groove does not restrict an adjustment range when the guide vane 14 rotates.
  • the securing element 22 also has a round cross section.
  • Fig. 6 shows a further embodiment, in which the recess 42 similar to the recess 42 according to Fig. 4 is trained.
  • the recess 42 is rectangular.
  • the securing element 22 is rectangular in cross section here.
  • FIG. 2 An inner ring segment 44 of the inner ring 20 is shown. At least two of these inner ring segments 44 form the inner ring 20.
  • the inner ring 20 is divided in the circumferential direction.
  • the securing element 22 is simply guided in the circumferential direction through the respective through openings 40 of the inner ring segment 44.
  • the guide vanes 14 with their radially inner end region 16 have been arranged in the recess 18 of the inner ring segment 44.
  • a securing element 22 can be provided for each inner ring segment 44. The use of a single circumferential securing element 22 is also possible.
  • a securing wire 22 which is round or rectangular in cross section, as a securing element 22 over a sector of up to 180 degrees in the circumferential direction through the inner ring 20 or an inner ring segment 44 and to connect it positively to the frustoconical bearing journals of the guide vanes 14.
  • This securing wire can be provided as a straight wire and can only be adapted to a curvature of the inner ring 20 by threading.
  • the inner ring 20 or the inner ring segments 44 can also have respective recesses 42, for example in the form of a groove.
  • This groove could, for example, point radially inward, which then also allows the securing element 22 to be supported radially on the outside in such a groove in the inner ring 20.
  • a shape and / or a cross section of a through opening 40 or a recess 42 of the inner ring 20 may correspond to the shapes and / or cross sections of the securing element 22 and / or the recess 42 of the guide vane 14 and / or the through opening 38 of the guide vane 14.

Claims (11)

  1. Système d'aubes directrices (10) d'une turbomachine, comportant au moins une aube directrice (14) montée en rotation autour d'un axe de réglage (12) et agencée à une partie d'extrémité (16) radialement intérieure, dans un évidement (18) correspondant d'un anneau intérieur (20), l'agencement de l'aube directrice (40) étant fixé par liaison de forme à l'anneau intérieur (20) au moyen d'un élément de fixation (22), l'élément de fixation (22) étant réalisé sous la forme d'un élément allongé, qui est disposé au moins dans un évidement (42) s'étendant dans la direction circonférentielle de la turbomachine et/ou dans une ouverture de passage (38) s'étendant dans la direction circonférentielle de la turbomachine de la partie d'extrémité (16) radialement intérieure de l'aube directrice (14) et au moins dans un évidement s'étendant dans la direction circonférentielle de la turbomachine et/ou dans une ouverture de passage (40) de l'anneau intérieur (20) s'étendant dans la direction circonférentielle de la turbomachine, caractérisé en ce que deux aubes directrices (14) du système d'aubes directrices (10) sont fixées au moyen d'un élément de fixation (22) commun.
  2. Système d'aubes directrices (10) selon la revendication 1, caractérisé en ce que l'évidement (42) de l'aube directrice (14) est réalisé sous la forme d'une rainure s'étendant au moins partiellement vers l'extérieur autour de la partie d'extrémité (16) radialement intérieure de l'aube directrice (14).
  3. Système d'aubes directrices (10) selon l'une des revendications précédentes, caractérisé en ce que l'élément de fixation (22) est réalisé sous la forme d'un fil de sécurité rond ou angulaire en section transversale, s'étendant dans la direction circonférentielle.
  4. Système d'aubes directrices (10) selon l'une des revendications précédentes, caractérisé en ce que l'anneau intérieur (20) n'est pas divisé dans la direction axiale de la turbomachine.
  5. Système d'aubes directrices selon l'une des revendications précédentes (10), caractérisé en ce que l'anneau intérieur (20) est divisé en au moins deux segments d'anneau intérieur (44) dans la direction circonférentielle de la turbomachine.
  6. Système d'aubes directrices (10) selon la revendication 5, caractérisé en ce qu'un élément de fixation (22) respectif est prévu pour chaque segment d'anneau intérieur (44).
  7. Système d'aubes directrices (10) selon l'une des revendications précédentes, caractérisé en ce que l'anneau intérieur (20) est réalisé au moins partiellement au moyen d'un procédé de fabrication additive.
  8. Système d'aubes directrices (10) selon l'une des revendications précédentes, caractérisé en ce qu'au moins un élément d'étanchéité (36) est disposé radialement à l'intérieur de l'anneau intérieur (20).
  9. Système d'aubes directrices (10) selon l'une des revendications précédentes, caractérisé en ce que l'évidement (42) et/ou l'ouverture de passage (38) de la partie d'extrémité (16) radialement intérieure de l'aube directrice (14) est réalisé pour correspondre longitudinalement au moins par endroits à l'élément de fixation (22) et/ou l'évidement et/ou l'ouverture de passage (40) de l'anneau intérieur (20) est réalisé(e) pour correspondre longitudinalement au moins par endroits à l'élément de fixation (22).
  10. Turbomachine, notamment moteur d'avion, caractérisée en ce qu'elle présente au moins un système d'aubes directrices (10) selon l'une des revendications précédentes.
  11. Procédé de montage d'un système d'aubes directrices (10) d'une turbomachine, comprenant les étapes consistant à :
    - fournir au moins deux aubes directrices (14) pouvant être montées en rotation autour d'un axe de réglage (12) respectif et comportant chacune une partie d'extrémité (16) radialement intérieure qui présente au moins un évidement (42) s'étendant dans la direction circonférentielle de la turbomachine dans la position de montage de l'aube directrice (14) et/ou dans l'ouverture de passage (38) s'étendant dans la direction circonférentielle de la turbomachine, un anneau intérieur (26) comportant respectivement un évidement (18) correspondant à la partie d'extrémité (16) radialement intérieure de l'aube directrice (14) et comportant au moins un évidement s'étendant dans la direction circonférentielle de la turbomachine et/ou une ouverture de passage (40) s'étendant dans la direction circonférentielle de la turbomachine, et un élément de fixation (22) réalisé sous forme d'un élément allongé ;
    - insérer la partie d'extrémité (16) radialement intérieure de l'aube directrice (14) dans l'évidement (18) de l'anneau intérieur (20) ;
    - insérer l'élément de fixation (22) dans l'évidement (42) s'étendant dans la direction circonférentielle de la turbomachine et/ou dans l'ouverture de passage (38) de l'anneau intérieur (20) s'étendant dans la direction circonférentielle de la turbomachine et dans l'évidement s'étendant dans la direction circonférentielle de la turbomachine et/ou dans l'ouverture de passage (40) de l'aube directrice (14) s'étendant dans la direction circonférentielle de la turbomachine afin de fixer par liaison de forme l'agencement de l'aube directrice (14) à l'anneau intérieur (20) ; et caractérisé par
    - la fixation commune d'au moins deux aubes directrices (14) du système d'aubes directrices (10) au moyen de l'élément de fixation (22).
EP17153139.5A 2016-02-05 2017-01-25 Système d'aube directrice d'une turbomachine Active EP3203035B1 (fr)

Applications Claiming Priority (1)

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DE102016201766.7A DE102016201766A1 (de) 2016-02-05 2016-02-05 Leitschaufelsystem für eine Strömungsmaschine

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EP3203035A1 EP3203035A1 (fr) 2017-08-09
EP3203035B1 true EP3203035B1 (fr) 2020-01-15

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DE102016201766A1 (de) * 2016-02-05 2017-08-10 MTU Aero Engines AG Leitschaufelsystem für eine Strömungsmaschine
GB201616969D0 (en) * 2016-10-06 2016-11-23 Rolls Royce Plc Stator assembly for a gas turbine engine
DE102017207667A1 (de) * 2017-05-08 2018-11-08 Siemens Aktiengesellschaft Verfahren zum Instandhalten einer Strömungsmaschine
CN114658694A (zh) * 2020-12-23 2022-06-24 上海电气电站设备有限公司 一种燃气轮机可调导叶的装配方法

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DE10359730A1 (de) * 2003-12-19 2005-07-14 Mtu Aero Engines Gmbh Turbomaschine, insbesondere Gasturbine
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FR2875270B1 (fr) * 2004-09-10 2006-12-01 Snecma Moteurs Sa Retenue des clavettes de centrage des anneaux sous aubes de stator a calage variable d'un moteur a turbine a gaz
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DE102016201766A1 (de) 2017-08-10
EP3203035A1 (fr) 2017-08-09
US20170226887A1 (en) 2017-08-10
US10450888B2 (en) 2019-10-22

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