EP3170987B1 - Système de bague intérieure pour turbomachine - Google Patents

Système de bague intérieure pour turbomachine Download PDF

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Publication number
EP3170987B1
EP3170987B1 EP15194974.0A EP15194974A EP3170987B1 EP 3170987 B1 EP3170987 B1 EP 3170987B1 EP 15194974 A EP15194974 A EP 15194974A EP 3170987 B1 EP3170987 B1 EP 3170987B1
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EP
European Patent Office
Prior art keywords
inner ring
guide vane
bushing
ring system
radially
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.)
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Application number
EP15194974.0A
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German (de)
English (en)
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EP3170987A1 (fr
Inventor
Richard Scharl
Andreas Jakimov
Steffen Schlothauer
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
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MTU Aero Engines AG
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Publication date
Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Priority to EP15194974.0A priority Critical patent/EP3170987B1/fr
Publication of EP3170987A1 publication Critical patent/EP3170987A1/fr
Application granted granted Critical
Publication of EP3170987B1 publication Critical patent/EP3170987B1/fr
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    • 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
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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

Definitions

  • the invention relates to an inner ring system according to the preamble of patent claim 1. Furthermore, the invention relates to a turbomachine according to the preamble of patent claim 10 and a method for assembling an inner ring system according to the preamble of patent claim 11.
  • the EP 2 806 107 A1 shows an inner ring for a turbomachine, which has a blade arrangement with a plurality of adjustable guide blades.
  • the guide vanes are accommodated in an adjustable manner via a bushing arrangement with a plurality of bushings between ring segments of the inner ring.
  • the ring segments can be connected to one another by the bushing arrangement.
  • a cross-divided seal carrier is designed as a securing element and positively connected to the ring segments.
  • two opposing axial projections of the seal carrier engage in corresponding circumferential grooves in the ring segments and thus also fix the bushing arrangement radially on the ring segment arrangement.
  • the seal carrier can be elastically radially expanded in the assembled state in order to preload the bushes radially against the ring segments.
  • a circular blade stage is known, the blades of which have respective guide pins at their end region.
  • the guide pins are rotatably received in the respective bushings, the bushings being held between several sectors of a retaining ring.
  • the sectors are held together by a rail by the rail encompassing the sectors.
  • the EP 1 998 006 A2 describes a turbofan engine with a plurality of rotatably mounted guide vanes.
  • the guide vanes are arranged in a ring and are surrounded at the end by a shroud.
  • the cover band consists of a front segment and a rear segment, which enclose the ends of the guide vanes and are fixed at the ends by means of several bolts.
  • the cover band is surrounded in some areas by a seal carrier.
  • a holding device with a pressure surge protection is provided, which on a Air duct is held and which exerts a biasing force on the seal carrier by means of respective holding arms.
  • the EP 2 093 380 A2 discloses a turbomachine with a plurality of rotatably mounted guide vanes.
  • the guide vanes In a radial arrangement of the blades in the turbomachine, the guide vanes have respective inner regions. These inner regions are enclosed by a core part and are held in the axial, circumferential and radial directions by means of this core part in a channel of an inner shroud of the turbomachine.
  • the inner ring comprises a ring segment arrangement with at least two ring segments and a bushing arrangement with at least one bushing for mounting an adjustable guide vane of the guide vane arrangement, wherein a ring segment and a further ring segment of the ring segment arrangement can be connected to one another by the bushing arrangement.
  • the ring segment arrangement can be designed as an inner ring.
  • the ring segments can shift and / or deform during operation relative to one another and / or relative to the guide vane arrangement, in particular due to heating.
  • the object of the present invention is to provide an inner ring system for a turbomachine, by means of which the turbomachine can have a higher efficiency. Furthermore, it is an object of the present invention to provide a turbomachine with a higher degree of efficiency. It is also an object of the present invention to provide a method for assembling such an inner ring system for a turbomachine.
  • a first aspect of the invention relates to an inner ring system with at least one inner ring which is held on at least one guide vane of a turbomachine which is rotatably mounted about an adjustment axis, the inner ring being immovable with respect to the at least one guide vane on a radially inner pin of the at least one guide vane in the direction of the adjustment axis is fixed, wherein a radially inner end region of the pin of the at least one guide vane is designed as a plate-shaped fastening element which is arranged in a corresponding recess in the inner ring, the inner ring system comprising at least one bushing which engages around the plate-shaped fastening element at least in regions, and wherein the inner ring system comprises at least one seal carrier arranged at least partially radially on the inside on the inner ring, the inner ring starting radially inwards on the bushing and radially outwards on the seal carrier is supported.
  • the guide vane thus keeps the inner ring at a constant distance from a housing of the turbomachine, as a result of which the respective gaps can also maintain a specified size during operation of the turbomachine. This results in particularly low leakages, which means that a turbomachine equipped with the inner ring system can be more efficient.
  • the turbomachine can also include a plurality of guide vanes.
  • the guide blades can be part of a so-called guide blade ring which includes the guide blades, the inner ring and an outer ring.
  • the outer ring can also be designed as a shroud of the guide vane ring.
  • Rotating guide vanes are also referred to as adjustable guide vanes, adjustable vanes or adjustable guide vanes.
  • a central axis of the inner ring or the guide vane ring can also be referred to as the axial direction.
  • the adjustment axis can also be referred to as the radial direction or radial axis.
  • the axial direction preferably corresponds to an axis of rotation of the turbomachine or of respective rotors of the turbomachine.
  • the adjustment axis of the guide vanes or the radial axis, which is also the radial direction can also be referred to, preferably also corresponds to a radial direction or radial axis of respective rotors of the turbomachine.
  • Radial inside denotes a radial direction towards the axial axis or central axis from a reference point.
  • Radial outside accordingly designates a direction which points away from the axial axis.
  • a radially inner end region of the journal of the at least one guide vane is designed as a plate-shaped fastening element which is arranged in a corresponding recess in the inner ring.
  • the plate-shaped fastening element can be formed, for example, by thickening the pin of the guide vane.
  • the plate-shaped fastening element can also be referred to as a plate element.
  • the corresponding recess can, for example, at least partially surround the plate-shaped fastening element.
  • the inner ring system comprises at least one bushing which engages around the plate-shaped fastening element at least in regions. At least a portion of the socket preferably corresponds to a shape of the plate-shaped fastening element. For example, the socket can be pushed over the plate-shaped fastening element. Alternatively, the bushing can be axially divided and its individual pieces can be arranged around the fastening element for assembly.
  • the bushing can preferably be formed from a metal material and / or be produced in an additive manufacturing process. By means of the bushing, the inner ring or respective sections of the inner ring can be fixed to the guide vane particularly simply and inexpensively.
  • the bushing can also be exchanged particularly easily in the event of wear due to an adjustment of the guide vanes during operation of the turbomachine due to friction.
  • the respective guide vanes and / or the inner ring or inner ring parts no longer have to be replaced for maintenance. This makes the inner ring system particularly easy to maintain.
  • the inner ring system comprises at least one seal carrier arranged at least partially radially on the inside on the inner ring, the inner ring being supported radially inwards on the bushing and radially outwards on the seal carrier.
  • the seal carrier can also consist of a plurality of seal carrier segments. In particular, the number of seal carrier segments can correspond to a number of inner ring segments.
  • the seal carrier preferably consists of a metal material and / or is produced in an additive manufacturing process. For example, a rubbing medium is held on the seal carrier. This brushing medium can be replaced particularly easily and inexpensively together with the seal carrier.
  • the seal carrier can be used to immovably fix the inner ring together with the bush on the guide vane in the radial direction.
  • the seal carrier can be supported, for example, radially outward on the bushing and / or on the inner journal of the guide vane.
  • the inner ring can be immovably fixed in a particularly cost-effective manner, the fixing being particularly easy to assemble.
  • an axially acting spring force is applied to the inner ring by means of a spring element arranged on a side of the seal carrier facing the inner ring and / or the bushing.
  • the spring element can thus serve to prevent slipping. If the seal carrier is pushed onto the inner ring in the circumferential direction for assembly, the spring element can only be designed to be flexible in the direction of insertion. As a result, the spring element forms a type of loss protection.
  • an axially split inner ring and / or an axially split bushing can be held together particularly simply by means of the spring force. In this case, the bushing and / or the inner ring no longer have to be held together by means of an axial connection, for example in the form of at least one rivet, a screw element and / or a weld.
  • the inner ring is divided in the circumferential direction and / or that the inner ring comprises at least two, in particular three ring segments, each of the ring segments being immovable with respect to the inner pin of at least one guide vane in the direction of the adjustment axis respective guide vane is fixed.
  • the inner ring is divided circumferentially, includes he has several inner ring washers.
  • An inner ring divided in this way is particularly easy to mount on the guide vanes.
  • respective sections of the inner ring are lighter than a one-piece inner ring, which makes them easier to handle and can be produced in a smaller manufacturing device. The same applies to the respective ring segments of the inner ring.
  • ring segments can be so small that they can be produced particularly easily in an additive manufacturing process, for example by means of a selective laser melting process.
  • the inner ring can be formed, for example, by three 120 degree ring segments.
  • the respective ring segments are preferably of the same size.
  • the change in the width of this radial gap can lead to increased leakages and / or increased contact between the rotor and the abrading medium or the brush seal. This results in a correspondingly increased wear and / or increased leakage.
  • the guide vane ring and / or the inner ring can also be referred to as a stator.
  • the brushing medium can be designed, for example, as a coating on the inner ring or as a honeycomb structure.
  • a gap between a guide vane profile and the inner ring can change.
  • a gap which is enlarged as a result leads to a significant deterioration in the efficiency, in particular in the case of a compressor. This is also known as compressor efficiency.
  • a gap that is too small can lead to contacts between the profile of the guide vane and the inner ring, which can lead to significantly higher adjustment forces up to jamming when the guide vanes turn.
  • the deformation of the inner ring can be minimized.
  • the distance between a housing, in particular a compressor housing, and the inner ring remains the same for all guide blades.
  • the distance between the guide vane profile and the inner ring or the inner ring segments can also be kept essentially constant during the operation of the turbomachine.
  • the inner ring is at least partially manufactured by means of an additive manufacturing process.
  • Other elements of the inner ring system, in particular the respective guide vanes, can also be produced at least partially by means of the additive manufacturing process.
  • the additive manufacturing process can also be called a generative manufacturing process.
  • Using the additive manufacturing process particularly robust, light and / or geometrically complex parts can be manufactured inexpensively. This makes the additive manufacturing process particularly suitable for manufacturing the inner ring.
  • the size of parts that can be produced in an additive manufacturing process is often limited. Accordingly, it is advantageous if an inner ring produced in an additive manufacturing process is formed from a plurality of ring segments.
  • the seal carrier surrounds the bushing and / or the fastening element of the guide vane and / or the inner ring at least in regions.
  • the seal carrier can be supported in a particularly simple manner radially outward, as a result of which the inner ring can then also be supported radially outward on the seal carrier.
  • the seal carrier can hold a split inner ring and / or a split bush together.
  • the seal carrier can comprise respective hook-shaped elements which can be at least partially elastically deformable for tolerance compensation.
  • the bushing has at least one web on which the inner ring is supported in the radial direction towards the inside.
  • the web is a particularly robust and particularly cost-effective type of support.
  • the seal carrier has at least one web on which the inner ring is supported in the radial direction to the outside.
  • Such a web is also particularly robust and inexpensive to produce in the seal carrier.
  • the inner ring can therefore be supported particularly advantageously by means of the webs.
  • This positive locking of the inner ring which is immovable with respect to the at least one guide vane in the direction of its adjustment axis, is also virtually wear-free.
  • the at least one web of the seal carrier is arranged in a corresponding groove of the inner ring.
  • the combination of the web and groove allows the inner ring to be supported particularly reliably by means of the seal carrier.
  • the at least one web of the seal carrier rests radially on the outside of the bushing.
  • a through opening for the web can be provided in the inner ring.
  • the through opening can adjoin a partial area of the groove.
  • the inner ring and / or the bushing have an elongated hole opening, the at least one guide vane being rotated within by means of a rotary and / or translatory movement the slot opening can be locked.
  • the guide vane can be locked by means of the fastening element inserted into the recess.
  • the fastening element can be designed to correspond to the slot opening.
  • the guide vane can be rotated at an angle that lies outside a normal adjustment range. As a result, the fastening of the guide vane in the slot opening cannot be inadvertently released by adjusting the guide vane.
  • the guide vane can be fixed in the elongated hole opening, for example, by an at least partially asymmetrical fastening element.
  • a second aspect of the invention relates to a turbomachine, in particular an aircraft engine.
  • the turbomachine can also be designed as a gas turbine.
  • the turbomachine according to the second aspect of the invention has an inner ring system according to the first aspect of the invention.
  • the features and advantages resulting from the installation of the inner ring system according to the first aspect of the invention in the turbomachine can be found in the descriptions of the first aspect of the invention, advantageous configurations of the first aspect of the invention being regarded as advantageous configurations of the second aspect of the invention and vice versa.
  • the turbomachine according to the second aspect of the invention with the inner ring system according to the first aspect of the invention thus has an extremely high efficiency.
  • a third aspect of the invention relates to a method for assembling an inner ring system, in which at least one inner ring is arranged on at least one guide vane of a turbomachine rotatably mounted about an adjustment axis, the inner ring being immovable with respect to a radially inner pin of the at least one guide vane in the direction of the adjustment axis the at least one guide vane is fixed, a radially inner end region of the pin of the at least one guide vane being designed as a plate-shaped fastening element being arranged in a corresponding recess in the inner ring, the inner ring system comprising at least one bushing which engages around the plate-shaped fastening element at least in regions, and wherein the inner ring system comprises at least one seal carrier arranged at least partially radially on the inner ring, the Inner ring is supported radially inwards on the bushing and radially outwards on the seal carrier.
  • an axially acting spring force is applied to the inner ring by means of a spring element arranged on a side of the seal carrier facing the inner ring and / or the bushing.
  • the inner ring can be fixed immovably on the radially inner pin of the at least one guide vane in the direction of the adjustment axis with respect to the at least one guide vane, for example by first pushing the bushing onto the fastening element.
  • the respective sections of the bushing can simply be arranged around the fastening element in order to partially surround it.
  • a ring segment of the inner ring can be pushed in the circumferential direction over the bushing and the fastening element. If the inner ring or the ring segments are divided in the circumferential direction, these sections can also simply be placed around the fastening element and the bushing.
  • respective seal carrier segments can be pushed over the inner ring, the bushing and the fastening element of the guide vane, for example in the circumferential direction.
  • the inner ring is then immovably fixed with respect to the at least one guide vane in the direction of its adjustment axis.
  • the seal carrier or respective seal carrier segments can hold respective axially divided components of the inner ring system together.
  • at least one spring element can be arranged on the seal carrier, by means of which the spring force is exerted on the axially divided elements. This creates a frictional connection between the axially divided elements. A relative rotation of the axially divided elements with respect to one another can thereby be prevented particularly reliably.
  • Fig. 1 shows an inner ring system 10 according to the prior art in a schematic sectional view, which can also be referred to as a meridian view.
  • This inner ring system 10 comprises at least one inner ring 12 which is held on at least one guide vane 16 of a turbomachine which is rotatably mounted about an adjustment axis 14.
  • the adjustable guide vane 16 is also referred to as an adjustment vane or adjustment vane.
  • the inner ring system 10 comprises a plurality of guide vanes 16 which are arranged next to one another in a ring. This is also known as a guide vane ring.
  • the adjustment axis 14 corresponds to in Fig. 1 a radial direction of the turbomachine.
  • a rotor 20 is arranged radially on the inside and rotates about the axis of rotation 22 of the turbomachine.
  • the axis of rotation 22 can also be referred to as an axial axis or a central axis.
  • the guide vanes 16 are arranged symmetrically about the axis of rotation 22.
  • a seal carrier 24 is held on the inner ring 12 radially inside the inner ring 12.
  • an inlet covering 26 is attached, which consists for example of a honeycomb structure and is also referred to as a brushing medium can be.
  • a so-called sealing fin 28, which is arranged on the rotor 20, is contacted with this inlet lining 26.
  • the inner ring system 10 with the outer ring 18 can also be referred to as a stator.
  • the inner ring 12 and the seal carrier 24 are held movably along the adjustment axis 14 in the inner ring system 10 according to the prior art.
  • a hot gas stream flows along the guide vanes 16 through a gas channel 30.
  • the inner ring 12 is heated more strongly on a side facing the guide vane 16 than on a side facing away from the guide vane 16. This can lead to undesired thermal deformation of the inner ring 12. These deformations are also called the cording effect. On the one hand, this can lead to a change in the gap 32 between the inner ring 12 and the guide vane 16. If this gap 32 is enlarged, the efficiency of the turbomachine decreases.
  • the gaps 32 When the gap 32 is reduced, the forces which are necessary for rotating the guide vane 16 are increased. If necessary, the guide vane 16 can also jam.
  • the inner ring 12 comes into contact with the guide vane 16 when the guide vane 16 is adjusted, abrasion and thus wear can occur. Deformation of the inner ring 12 can also increase the gap 34 between the sealing fin 28 and the inlet lining 26. This can also lead to increased leakages between the rotor 20 and the inner ring system 10. The deformation of the inner ring 12 can also result in increased contact between the sealing fin 28 and the inlet lining 26, as a result of which corresponding wear is greater.
  • the negative effects of the described thermal deformation of the inner ring 64 are substantially reduced or avoided entirely.
  • the inner ring 64 in the inner ring system 40 according to the invention is fixed on a radially inner pin 42 of the at least one guide vane 66 in the direction of the adjustment axis 14 so as to be immovable with respect to the at least one guide vane 66.
  • the distance between a housing of the turbomachine and the inner ring 64 thus remains essentially the same during operation over the entire circumference of the inner ring 64 or with all guide vanes 66.
  • the inner ring 12 in the inner ring system 10 can move at least a short distance in the direction of the adjustment axis 14 with respect to the at least one guide vane 16 move.
  • the inner ring 64 can be divided in the circumferential direction.
  • the inner ring 64 can thus, for example, be divided into two along a plane lying in the adjustment axis 14. As a result, the inner ring 64 can simply be placed around the pin 42.
  • the inner ring 64 can also comprise at least two, in particular three, ring segments, wherein in each of the ring segments, at least one guide vane 66 is fixed immovably in relation to the respective guide vane 66 on an inner pin 42 in the direction of the adjustment axis 14.
  • the inner ring 64 can have three 120-degree ring segments.
  • the divisions of the inner ring 64 or the division planes of the inner ring 64 preferably correspond to divisions or division planes of the entire construction of the turbomachine. Then the inner ring 64 can be installed particularly easily. For example, the ring segments can be pushed onto the inner pins 42 in the circumferential direction.
  • a division of the inner ring 64 also offers advantages in the production of the inner ring 64.
  • the inner ring 64 is preferably produced in an additive process.
  • An example of such a process is a selective laser melting process.
  • the respective parts are often limited in size.
  • the maximum size of a component to be manufactured additively can be predetermined by a corresponding size of a powder bed.
  • This size limitation can be maintained by a correspondingly divided inner ring 64 and the additive manufacturing process can nevertheless be used for the production of inner rings with a large diameter.
  • Additively manufactured components can be particularly robust and light.
  • very complex geometries can be manufactured in the first place.
  • the inner ring system 40 is therefore also particularly suitable if a divided inner ring 64 is to be installed in a turbomachine.
  • the radially inner end region 44 of the pin 42 of the at least one guide vane 66 is designed as a plate-shaped fastening element 46.
  • This plate-shaped fastening element 46 is arranged in a corresponding recess 48 of the inner ring 64.
  • the inner ring 64 can be fixed immovably with respect to the guide vane 66 in the direction of the adjustment axis 14 with particularly simple means.
  • Such a simple means is, for example, the socket 50, which engages around the plate-shaped fastening element 46 at least in regions.
  • the bushing 50 can also be divided for example for assembly along a plane lying in the adjustment axis 14. Then the bushing 50 can simply be placed around the plate-shaped fastening element 46.
  • the socket 50 can also be designed as a type of rail.
  • the bushing 50 then comprises a plurality of curved rail elements which are pushed onto the respective plate-shaped fastening elements 46 of the guide vanes 66 in the circumferential direction.
  • the rail elements can then form a type of bush ring together, the rail elements also being able to be referred to as bush ring segments.
  • the turbomachine and in particular the guide vane ring should also be of split design.
  • a seal carrier 68 is arranged on the inner ring 64 at least partially radially on the inside. Also attached to this seal carrier 68 is an inlet covering 70, which consists, for example, of a honeycomb structure.
  • the radial direction in the examples shown of the inner ring system 40 corresponds to the adjustment axis 14. Radially outside is to be understood in the direction away from the axis of rotation 22 of the turbomachine, radially inwards in the direction towards this axis of rotation 22.
  • the inner ring 64 is supported radially inwards on the bush 50 and radially outwards on the seal carrier 68.
  • the inner ring 64 is immovably fixed with respect to the at least one guide vane 66 in the direction of its adjustment axis 14.
  • the socket 50 points for this at least one web 52 on which the inner ring 64 is supported in the radial direction inwards.
  • the seal carrier 68 also has at least one web 54 on which the inner ring 64 is supported in the radial direction to the outside.
  • the web 54 of the seal carrier 68 is arranged in a corresponding groove 56 of the inner ring 64.
  • the seal carrier 68 is supported radially outward on the bush 50 and thus the inner pin 42 of the guide vane 66.
  • the seal carrier 68 can also be used to support the inner ring 64 radially outward.
  • the seal carrier 68 thus encompasses the bushing 50, the fastening element 46 of the guide vane 66 and the inner ring 64 at least in regions.
  • Both the seal carrier 68 and the bushing 50 are formed from a metal material.
  • the seal carrier 68 and the bushing 50 are preferably also produced in an additive manufacturing process.
  • the bushing 50 and / or the inner ring 64 are divided in the circumferential direction, they are held together by the seal carrier 68.
  • a spring element 58 can be arranged on the seal carrier 68 on a side facing the inner ring 64 and / or the bushing 50. Two examples of such a spring element 58 are shown in the schematic detailed view of the seal carrier 68 in FIG 4 and 5 shown.
  • the spring element 58 can be arranged on the web 54. As a result, an axially acting spring force can hold the inner ring 64 and / or the bush 50 together.
  • the spring element 58 according to Fig.
  • the seal carrier 68 can only be pushed in the direction of the insertion direction 60 onto the inner pin 42 or the inner ring 64 and the bush 50.
  • the spring element 58 also acts as a type of loss protection.
  • the spring force causes parts of the bushing 50 and / or the inner ring 64 to not be able to rotate relative to one another.
  • respective inner rings 64 are therefore often also divided due to assembly. It is precisely these ring segments, which can also be referred to as half rings, that deform due to a temperature gradient during the operation of the turbomachine. This deformation can lead to undesired gaps and leaks, both on the inside toward the rotor 20 and between the inner ring 64 and a profile overhang of the respective guide vanes 66. These undesirable deformations are reduced or completely prevented by the construction of the inner ring system 40.
  • the inner ring 64 and / or the bushing 50 can have an elongated hole opening, wherein the at least one guide vane 66 can be locked within the elongated hole opening by means of a rotational and / or translatory movement.
  • the fastening element 46 of the guide vane 66 is pushed into the respective elongated hole openings of the bushing 50 and the inner ring 64 and secured against removal by rotation.
  • a corresponding geometry then holds the bushing 50 in position.
  • the geometry of the fastening element 46 can also cause the inner ring 64 to be immovably fixed, in particular by the fastening element 46 being braced against the bushing 50 and / or the inner ring 64 by locking.
  • the fastening element 46 which can also be referred to as a thickening at the inner end of the guide vane 66, is flattened laterally for this purpose, for example.
  • the guide vane 66 and the inner ring 64 and / or the bushing 50 can thus be connected to one another in the manner of a bayonet catch.
  • the bushing 50 is prevented from rotating relative to the inner ring 64 by a form-fitting element.
  • the guide vane 66 is brought at an angle that is outside its normal adjustment range in order to be able to be inserted into the respective elongated holes.
  • the seal carrier 68 can also consist of several short sections.
  • the geometry of the inner ring 64 and the seal carrier 68 in particular is slightly changed.
  • the two webs 54 of the seal carrier 68 are now offset radially from one another, as a result of which the assembly is particularly simplified.
  • the one web 54 of the seal carrier 68 is at least regionally long so that it rests on the bushing 50 radially on the outside. This additionally secures the socket 50.
  • the seal carrier 68 and / or the inner ring 64 is prevented from moving in the circumferential direction.
  • the inner ring 64 has a through opening 62 in the web, which rests on the bushing 50 radially on the outside.
  • the web 54 can also be longer only in some areas in the direction towards the adjustment axis 14. In other words, the web 54 has a type of pin in some areas, which protrudes through the inner ring 64 or the passage opening 62.

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

Claims (11)

  1. Système de bague intérieure (40) comprenant au moins une bague intérieure (64), qui est maintenue au niveau d'au moins une aube de guidage (66) d'une turbomachine, laquelle aube de guidage est montée en rotation autour d'un axe de déplacement (14), dans lequel la bague intérieure (64) est fixée à un tourillon (42) radialement intérieur de l'au moins une aube de guidage (66) dans la direction de l'axe de déplacement (14) de manière immobile par rapport à l'au moins une aube de guidage (66), une zone d'extrémité radialement intérieure (44) du tourillon (42) de l'au moins une aube de guidage (66) étant réalisée sous la forme d'un élément de fixation en forme de plaque (46) qui est disposé dans un évidement (48) correspondant de la bague intérieure (64), le système de bague intérieure (40) comprenant au moins une douille (50) qui entoure au moins par endroits l'élément de fixation en forme de plaque (46), et le système de bague intérieure (40) comprenant au moins un support de joint (68) disposé au niveau de la bague intérieure (64) au moins partiellement radialement à l'intérieur, la bague intérieure (64) reposant radialement vers l'intérieur sur la douille (50) et radialement vers l'extérieur sur le support de joint (68), caractérisé en ce que la bague intérieure (64) est sollicitée par une force élastique agissant axialement au moyen d'un élément de ressort (58) disposé sur un côté du support de joint (68) orienté vers la bague intérieure (64) et/ou vers la douille (50).
  2. Système de bague intérieure (40) selon la revendication 1, caractérisé en ce que la bague intérieure (64) est divisée dans la direction circonférentielle et/ou en ce que la bague intérieure (64) comprend au moins deux, en particulier trois segments de bague, chacun des segments de bague étant fixé à un tourillon (42) intérieur d'au moins une aube de guidage (66) dans la direction de l'axe de déplacement (14) de manière à être immobile par rapport à l'aube de guidage (66) respective.
  3. Système de bague intérieure (40) selon l'une des revendications 1 ou 2, caractérisé en ce que la bague intérieure (64) est réalisée au moins partiellement au moyen d'un procédé de fabrication additif.
  4. Système de bague intérieure (40) selon l'une des revendications précédentes, caractérisé en ce que le support de joint (68) entoure au moins par zones la douille (50) et/ou l'élément de fixation (46) de l'aube de guidage (66) et/ou la bague intérieure (64).
  5. Système de bague intérieure (40) selon l'une des revendications précédentes, caractérisé en ce que la douille (50) comporte au moins une traverse (52) sur laquelle la bague intérieure (64) repose dans une direction radiale vers l'intérieur.
  6. Système de bague intérieure (40) selon l'une des revendications précédentes, caractérisé en ce que le support de joint (68) comporte au moins une traverse (54) sur laquelle la bague intérieure (64) repose dans une direction radiale vers l'extérieur.
  7. Système de bague intérieure (40) selon la revendication 6, caractérisé en ce que l'au moins une traverse (54) du support de joint (68) est disposée dans une rainure (56) correspondante de la bague intérieure (64).
  8. Système de bague intérieure (40) selon l'une des revendications 6 ou 7, caractérisé en ce que l'au moins une traverse (54) du support de joint (68) repose sur la douille (50) radialement vers l'extérieur.
  9. Système de bague intérieure (40) selon l'une des revendications précédentes, caractérisé en ce que la bague intérieure (64) et/ou la douille (50) comportent une ouverture oblongue, l'au moins une aube de guidage (66) pouvant être verrouillée au moyen d'un mouvement de rotation et/ou de translation dans l'ouverture oblongue.
  10. Turbomachine, en particulier moteur d'aéronef, caractérisée en ce qu'elle comporte un système de bague intérieure (40) selon l'une des revendications précédentes.
  11. Procédé de montage d'un système de bague intérieure (40), dans lequel au moins une bague intérieure (64) est disposée au niveau d'au moins une aube de guidage (66) d'une turbomachine, laquelle aube de guidage est montée en rotation autour d'un axe de déplacement (14), la bague intérieure (64) étant fixée à un tourillon (42) radialement intérieur de l'au moins une aube de guidage (66) de manière à être immobile par rapport à l'au moins une aube de guidage (66) dans la direction de l'axe de déplacement (14), une zone d'extrémité radialement intérieure (44) du tourillon (42) de l'au moins une aube de guidage (66), réalisée sous la forme d'un élément de fixation (46) en forme de plaque, étant disposée dans un évidement (48) correspondant de la bague intérieure (64), le système de bague intérieure (40) comprenant au moins une douille (50) qui entoure au moins par zones l'élément de fixation (46) en forme de plaque, le système de bague intérieure (40) comprenant au moins un support de joint (68) disposé au niveau de la bague intérieure (64) au moins partiellement radialement à l'intérieur, la bague intérieure (64) reposant radialement vers l'intérieur sur la douille (50) et radialement vers l'extérieur sur le support de joint (68),
    caractérisé en ce que la bague intérieure (64) est sollicitée par une force élastique agissant axialement au moyen d'un élément de ressort (58) disposé sur un côté du support de joint (68) orienté vers la bague intérieure (64) et/ou la douille (50).
EP15194974.0A 2015-11-17 2015-11-17 Système de bague intérieure pour turbomachine Active EP3170987B1 (fr)

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EP15194974.0A EP3170987B1 (fr) 2015-11-17 2015-11-17 Système de bague intérieure pour turbomachine

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EP3170987B1 true EP3170987B1 (fr) 2020-02-19

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DE102021120384A1 (de) * 2021-08-05 2023-02-09 MTU Aero Engines AG Leitschaufelkranz für eine Strömungsmaschine, Strömungsmaschine und Verfahren zum Montieren eines Leitschaufelkranzes

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Publication number Priority date Publication date Assignee Title
FR2723614B1 (fr) * 1994-08-10 1996-09-13 Snecma Dispositif d'assemblage d'un etage circulaire d'aubes pivotantes.
US7854586B2 (en) * 2007-05-31 2010-12-21 United Technologies Corporation Inlet guide vane inner air seal surge retaining mechanism
US8500394B2 (en) * 2008-02-20 2013-08-06 United Technologies Corporation Single channel inner diameter shroud with lightweight inner core
EP2806107B1 (fr) 2013-05-22 2017-08-09 MTU Aero Engines AG Bague intérieure séparée

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