EP3613952B1 - Dispositif d'aube directrice variable, aube directrice, porte-joint et turbomachine - Google Patents

Dispositif d'aube directrice variable, aube directrice, porte-joint et turbomachine Download PDF

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Publication number
EP3613952B1
EP3613952B1 EP19191194.0A EP19191194A EP3613952B1 EP 3613952 B1 EP3613952 B1 EP 3613952B1 EP 19191194 A EP19191194 A EP 19191194A EP 3613952 B1 EP3613952 B1 EP 3613952B1
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EP
European Patent Office
Prior art keywords
guide vane
seal carrier
inner ring
guide
ring segment
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
EP19191194.0A
Other languages
German (de)
English (en)
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EP3613952A1 (fr
Inventor
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
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MTU Aero Engines AG
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Publication date
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Publication of EP3613952A1 publication Critical patent/EP3613952A1/fr
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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
    • F01D11/001—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
    • 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
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/55—Seals

Definitions

  • the present invention relates to a guide vane arrangement for a turbomachine with a rotation axis, in particular for a compressor or turbine stage of a gas turbine, the guide vane arrangement having a plurality of adjustable guide vanes rotatably mounted about an adjustment axis, at least one inner ring segment formed separately from the guide vanes and one separately from the comprises at least one inner ring segment formed seal carrier.
  • the present invention further relates to a guide vane, in particular an adjustable guide vane, for an aforementioned guide vane arrangement and a seal carrier for such a guide vane arrangement.
  • the present invention relates to a turbomachine, in particular a gas turbine, with at least one compressor or turbine stage with at least one guide vane arrangement.
  • the guide blade arrangements are, among other things, exposed to thermal loads, in particular partially changing and/or high temperature gradients, in particular due to the working fluid flowing through the guide blade arrangement and thus at least partially flowing on and/or around the inner ring segments and/or through, in particular grinding , seals that are arranged in the radial direction between the guide vanes and a rotor rotating relative to them.
  • thermal loads in particular partially changing and/or high temperature gradients, in particular due to the working fluid flowing through the guide blade arrangement and thus at least partially flowing on and/or around the inner ring segments and/or through, in particular grinding , seals that are arranged in the radial direction between the guide vanes and a rotor rotating relative to them.
  • gaps between the individual components can widen, in particular between the guide vanes and the inner ring or the corresponding inner ring segments, as well as between a sealing structure held by the seal carrier and the rotor, and as a result undesirable leaks, which have a detrimental effect on the efficiency the turbomachine.
  • the sealing effect that can be achieved depends largely on the gap widths of the respective sealing gaps that arise during operation. The larger the sealing gaps that result, the larger the leaks that occur and, as a result, the greater the efficiency losses that occur.
  • the overall sealing effect that can be achieved depends in particular on how the guide vanes are each connected with their radially inner end to the inner ring or corresponding inner ring segments, and on how the seal carrier, on which there is usually a sealing structure for sealing an annular gap around the rotor is attached around, designed and stored.
  • a guide vane arrangement with adjustable guide blades in which the inner ring has at least one groove extending in the axial direction, into which the seal carrier engages with a guide rail for attachment to the inner ring.
  • One object of an embodiment of the present invention is to provide an alternative guide vane arrangement, in particular an improved guide vane arrangement, in which, in particular, the gap widths of the individual sealing gaps change less during operation and which, as a result, in particular enables larger tolerance ranges and, in particular, simpler determination the maximum permissible tolerances for a desired operating behavior.
  • a further object of the invention is to provide an alternative, in particular improved, guide vane and an alternative, in particular improved, seal carrier for a guide vane arrangement, as well as an alternative, in particular improved, turbomachine.
  • a guide vane arrangement according to the invention for a turbomachine with a rotation axis in particular for a compressor or turbine stage of a gas turbine, comprises a plurality of adjustable guide vanes, in particular each rotatably mounted about an adjustment axis, at least one inner ring segment formed separately from the guide vanes and one Seal carrier formed separately from the at least one inner ring segment, wherein the at least one inner ring segment is attached to one or more guide blades, in particular to a maximum of four guide blades.
  • the seal carrier is mounted spoke-centered relative to the at least one inner ring segment, so that the seal carrier is positioned relative to the at least one inner ring segment in the direction of at least one adjustment axis of at least one guide vane and/or in the radial direction, based on the axis of rotation of the turbomachine in a functional state of use of the guide vane arrangement in a Turbo machine, is movably mounted.
  • an “adjustable guide vane” is understood to mean a guide vane which is designed and, in particular, is mounted in the guide vane arrangement in such a way that it can be adjusted by rotation about an adjustment axis, in particular its flow angle of attack, the adjustment axis being aligned with its Longitudinal axis can coincide, or can also be different from this, with the adjustment axis extending in particular essentially in the longitudinal direction of the guide vane.
  • a “seal carrier” in the sense of the present invention is understood to mean a support structure which is designed to be a sealing structure, in particular a sealing structure which is fundamentally known from the prior art, such as a brush sealing structure and/or one which is also fundamentally known from the prior art and to maintain the so-called “honeycomb” structure used in turbomachinery.
  • a “spoke-centered bearing” is understood to mean a bearing which is designed in such a way that the respective component mounted in this way, in the present case in particular the seal carrier, always revolves around an axis, in particular around an axis Axis that runs parallel to the axis of rotation of a turbomachine or centers around the axis of rotation itself, and which also enables compensation in the radial direction, based on the axis of rotation of a turbomachine. i.e.
  • a spoke-centered bearing in the sense of the present invention is understood to mean, in particular, a bearing which in particular has a degree of freedom in the radial direction and which acts self-centering with respect to an axis, in particular an axis running parallel to the axis of rotation of a turbomachine or to the axis of rotation itself , similar to a bicycle wheel, where the hub is mounted in the rim via spokes.
  • the direction specification “axial” refers, unless something else is explicitly stated, in particular a different axis, in the present case in the usual manner to a direction parallel to a main rotation or (main) machine axis of the turbomachine, the direction specification “circumferential direction " correspondingly, unless something else is explicitly stated, in particular another axis, to a direction of rotation about this rotation or (main) machine axis, the direction specification "radial”, unless something else is explicitly stated, in particular another axis a direction that is perpendicular to the axial and circumferential directions.
  • the direction specification “tangential” refers, in particular to another axis, to a direction which is perpendicular to the axial direction according to the aforementioned definition and the radial direction according to the aforementioned definition, in particular all directional information, if Unless otherwise explicitly stated, each refers to a functional installation state of the corresponding component in a turbomachine.
  • the spoke-centered mounting of the seal carrier according to the invention enables the seal in the area of the radially inner ends of the guide vanes between the guide vanes and the at least one inner ring segment to be decoupled from the seal against a rotor.
  • a guide vane arrangement according to the invention also has the advantage that the gap between a sealing structure attached to the seal carrier and the rotor can be designed and adjusted almost independently of the at least one inner ring segment and its attachment to the respective guide vanes.
  • the resulting sealing gaps between the at least one inner ring segment and the guide vanes to which the inner ring segment is attached can be designed separately and independently of the sealing gap between the seal carrier or a sealing structure attached to it and the rotor, which shortens the tolerance chains to be taken into account. in particular, divide it up, and as a result simplify it and, furthermore, generally less tight tolerances have to be adhered to.
  • a guide vane arrangement according to the invention has in particular a plurality of adjustable guide vanes which are arranged distributed in the circumferential direction, in particular evenly distributed in the circumferential direction, and are each mounted rotatably about an adjustment axis.
  • At least one guide vane is arranged in such a way that, in a functional state of use of the guide vane arrangement in a turbomachine, its adjustment axis is by more than 1°, preferably by more than 2°, in particular by more than 3°, at most however, is inclined by 5°, in particular at most by 4°, preferably by at most 3°, from a radial plane extending perpendicular to the axis of rotation of a turbomachine in the upstream direction.
  • each guide vane is assigned a separate inner ring segment.
  • a guide vane arrangement In an alternative embodiment of a guide vane arrangement according to the present invention, several guide blades, in particular two or three guide blades, but in particular a maximum of four guide blades, are assigned to a common inner ring segment. I.e.
  • an inner ring segment is attached to a plurality of guide vanes, but in particular to a maximum of four guide vanes. It is possible to attach it to more than four guide vanes. However, if the inner ring segment is attached to too many guide vanes, thermally induced stresses can occur, which can only be countered by larger gap dimensions between the inner ring segment and guide vanes, which will deteriorate the sealing effect in the vast majority of cases, which can be to the detriment of efficiency and should therefore be avoided.
  • the guide vane arrangement comprises a plurality of inner ring segments, which are arranged adjacent to one another in particular in the circumferential direction and in particular form an inner ring.
  • the individual inner ring segments are in particular designed in such a way that they have a type of shroud for delimiting a flow channel, in particular radially inwards, which surrounds the guide vanes in the area of their flow profiles, the individual inner ring segments being designed in particular in such a way that an inner shroud that is almost closed in the circumferential direction trains.
  • the individual inner ring segments are arranged at a sufficient distance from one another, particularly in the circumferential direction.
  • the seal carrier has at least one sealing structure, in particular at least one brush sealing structure and/or at least one honeycomb sealing structure for sealing, in particular at its radially inner end, based on a functional state of use of the guide vane arrangement in a turbomachine a rotor mounted rotatably about an axis of rotation.
  • At least one sealing structure is integral, i.e. H. one-piece, formed with the seal carrier.
  • the seal carrier is mounted in particular spoke-centered on the guide vanes and/or the at least one inner ring segment, in particular over at least three bearing points arranged distributed, in particular evenly distributed, in the circumferential direction.
  • the seal carrier is only mounted spoke-centered on the guide vanes.
  • At least one guide vane has, at its radially inner end, a fastening element, in particular a fastening pin, extending along the adjustment axis, and the at least one inner ring segment, which is fastened to this at least one guide vane, has at least one associated, appropriately designed fastening opening, the fastening element being the Guide vane, in particular in the direction of the adjustment axis, in particular extends through the at least one associated fastening opening of the inner ring segment.
  • a fastening element in particular a fastening pin
  • the seal carrier can also be mounted spoke-centered on the inner ring segments, in particular on at least three inner ring segments, for example as known from the prior art for a guide vane arrangement with fixed guide vanes and as, for example, in EP 2 696 039 A1 described, the corresponding radial grooves being arranged in particular in the circumferential direction between the fastening elements of the guide blades.
  • At least one inner ring segment is fastened to the fastening element of the guide vane by means of an axial securing means and in the direction of the adjustment axis secured to the fastening element, in particular with a defined play in the direction of the adjustment axis, in particular by means of a locking ring or a locking washer.
  • the at least one inner ring segment is fastened to one or more guide vanes with a defined play in the direction of the adjustment axis in such a way that the inner ring segment is in the frame due to a sufficient operating pressure present in an area radially within the inner ring segment
  • This play can be displaced outwards in the direction of the adjustment axis, in particular in such a way that the inner ring segment can be brought into contact with the associated guide vanes in the radial direction, so that a seal can be formed in the radial direction between the associated guide vanes and the inner ring segment, in particular with a sealing gap with a gap width of zero in the radial direction.
  • the associated guide vanes and the inner ring segment in particular have one or more correspondingly designed, in particular radial Shoulders and functional surfaces extending to the adjustment axis, in particular sealing surfaces.
  • the at least one inner ring segment is also attached to the respective guide vanes with a defined play in the axial direction and/or in the circumferential direction. In this way, tensions, particularly thermally caused tensions, can be avoided.
  • the guide vane is guided in the axial direction and/or in the circumferential direction in particular via the fastening elements of the vanes received by the seal carrier, whereby
  • a play between the guide vanes and the at least one inner ring segment in the axial direction and / or in the circumferential direction is in particular greater than between the guide vanes and the seal carrier in these directions.
  • the seal carrier has at least one guide vane receptacle into which the fastening element, in particular a fastening pin, of at least one guide vane engages in such a way that the fastening element of the guide vane is positioned along the adjustment axis and/or in the radial direction, based on the Rotation axis according to the invention in the state of use of the guide vane arrangement in a turbomachine, is movably mounted relative to the seal carrier in the guide vane receptacle of the seal carrier, the guide vane receptacle in the seal carrier being designed and arranged in particular concentrically to at least one fastening opening of at least one inner ring segment.
  • the fastening element of at least one guide vane can be movably mounted in the direction of the adjustment axis of the guide vane or in the radial direction in a particularly simple manner, but at the same time can be guided, in particular in the axial direction and in the circumferential direction, with respect to the axis of rotation of a turbomachine.
  • This makes it possible to form a particularly advantageous, spoke-centered storage of the seal carrier.
  • the spoke centering using fastening pins makes this possible, especially in comparison to a groove-guided spoke centering, such as that from the EP 2 696 039 A1 is known, a more precise guidance and thus an improved, in particular more precise centering.
  • the gap widths can be adjusted more precisely.
  • the at least one guide vane receptacle is designed as a cylindrical or cup-shaped or cylindrical or cup-like recess.
  • at least one guide vane receptacle can also be designed as a truncated cone-shaped or conical recess, for storage in the guide vane receptacle provided fastening element, in particular the respective fastening pin, in particular correspondingly, in particular correspondingly complementary, is designed to design the guide vane receptacle.
  • the fastening element of the guide vane engages, in particular in the direction of the adjustment axis, in particular with defined play in the axial direction and/or in the circumferential direction, in the guide vane receptacle of the seal carrier, the play in the direction of the adjustment axis in particular being at least is dimensioned so large that a thermally induced increase in length of the guide vane is possible without tension during operation.
  • the clearance should be chosen to be at most large enough so that the seal carrier is always securely mounted on the guide vanes during operation and, in particular, that the fastening elements slip out of the guide vane receptacles in the seal carrier is excluded.
  • the fastening element in particular in the form of a fastening pin, can also be assigned to the seal carrier and one or more guide vanes can each have a corresponding receptacle for the fastening element, in this case a "seal carrier receptacle" exhibit.
  • the seal carrier of a guide vane arrangement according to the invention can be designed in one piece or in several parts and can be divided axially in particular in the circumferential direction and/or in the axial direction or in a direction perpendicular to the adjustment axis of at least one guide vane, in particular all of the guide vanes, with the individual parts being preferred in the case of a split seal carrier are connected to one another by means of releasable connecting means, in particular by means of screws or the like.
  • the seal carrier is a circumferential seal carrier ring, wherein the Seal carrier ring is formed in one piece in the circumferential direction or has a plurality of seal carrier segments each extending only over a part in the circumferential direction, the seal carrier being composed in particular of several seal carrier segments each extending only over a part in the circumferential direction.
  • the division of the seal carrier in the circumferential direction enables a particularly simple assembly of a guide vane arrangement according to the invention, with the individual seal carrier segments being arranged in an overlapping manner, in particular in the circumferential direction, i.e. preferably by means of an overlap joint and not with a butt joint, the overlap surfaces in particular each being designed as wedge surfaces.
  • This allows a particularly good seal to be achieved in the axial direction on the seal carrier.
  • an advantageous flow of force in the seal carrier can be achieved in this way.
  • At least one seal carrier segment or seal carrier part is produced by an additive manufacturing process, in which case the seal carrier segment in particular does not extend over more than a circumferential angle of 60°.
  • the production using an additive manufacturing process enables a particularly flexible design of the seal carrier, since this type of production enables a particularly high degree of geometric freedom while at the same time having good mechanical and thermal properties.
  • the seal carrier in particular in a seal carrier ring or at least one seal carrier segment, is divided into at least one upstream seal carrier part and at least one downstream seal carrier part, the seal carrier in particular at least partially along a dividing plane running parallel to the adjustment axis of the guide vanes and / or is divided into an upstream seal carrier part and a downstream seal carrier part along a radial plane extending perpendicular to the axis of rotation.
  • the seal carrier is divided both in the circumferential direction into seal carrier segments and into an upstream and a downstream seal carrier part, with at least one seal carrier part or seal carrier segments being produced by an additive manufacturing process and/or in particular in the circumferential direction extends at most over a range of a circumferential angle of 60°.
  • the at least one upstream seal carrier part and at least one downstream seal carrier part are connected to one another, in particular releasably, in particular by means of at least one connecting means, in particular by means of at least one screw or by means of a rivet or the like in a direction perpendicular to the dividing plane of the seal carrier, wherein the at least one connecting means, based on a state of use according to the invention of the guide vane arrangement in a turbomachine, is arranged offset in the circumferential direction from the fastening elements of the guide vanes and in the radial direction, based on the axis of rotation of the turbomachine , in particular at the level of at least one fastening element of at least one guide vanes.
  • seal carrier parts can be quickly assembled, seal carriers can be put together, in particular releasably.
  • connecting means are arranged in the radial direction at the level of the fastening elements, in particular at the level of the fastening pins, a particularly compact, space-saving guide vane arrangement can be realized in the radial direction.
  • At least one inner ring segment and the seal carrier overlap at least partially, in particular downstream, based on a functional installation state in a turbomachine, in the direction of the adjustment axis or in the radial direction and in particular form one between them, based on the axis of rotation of a turbomachine in a functional state of use of the guide vane arrangement, has a sealing gap in the axial direction, the sealing gap itself extending in particular parallel to the adjustment axis of at least one guide vane, in particular parallel to the adjustment axis of the closest guide vane, or in the radial direction.
  • a seal acting in the axial direction can be realized in a particularly simple manner, in particular additionally, in particular downstream of the guide vane receptacles, which in particular also enables length compensation of the guide vane or a radial movement of the inner ring segment relative to the seal carrier, without the sealing effect in the axial direction direction to have a significant negative impact.
  • the additional sealing can further reduce leakage effects, which generally has a beneficial effect on the efficiency of a turbomachine.
  • the at least one inner ring segment and the seal carrier each have a sealing flange which extends in the radial direction with respect to the axis of rotation of a turbomachine, whereby the sealing flange of the inner ring segment extends in particular radially inwards, and the sealing flange of the seal carrier extends in particular radially outwards.
  • a particularly good seal in the axial direction can be achieved if the at least one inner ring segment is fastened to the respective guide vane with a defined clearance in the axial direction, and the clearance is dimensioned such that there is sufficient clearance in an area radially within the inner ring segment existing operating pressure, the inner ring segment can be brought into contact with its sealing flange against the sealing flange of the seal carrier in the axial direction within the scope of this play, in particular in such a way that a seal can be formed in the axial direction of the inner ring segment and the seal carrier, in particular with a sealing gap with a gap width from zero in the axial direction.
  • the guide vane arrangement has at least two inner ring segments formed separately from the guide vanes, the at least two inner ring segments being arranged adjacent to one another in the circumferential direction and with a compensating gap in the circumferential direction between them, the compensating gap being relative to the axis of rotation a turbomachine, in particular in the radial direction, with at least one sealing element being arranged between two inner ring segments arranged adjacently in the circumferential direction in the area of the compensating gap, in particular at least for at least partially sealing the compensating gap in the radial direction.
  • At least one sealing element extends in particular in the circumferential direction and at least partially in the axial direction, with at least one sealing element in particular being a sealing strip, in particular a sheet metal strip or the like, in particular made of spring steel, which in particular is in a correspondingly designed Groove is accommodated by two adjacent inner ring segments, in particular in such a way that a labyrinth gap is formed between the sealing element and the respective inner ring segment.
  • a turbomachine according to the invention in particular a gas turbine, with at least one compressor or turbine stage with a guide vane arrangement with guide vanes has, according to the invention, a guide vane arrangement according to the invention and/or at least one guide vane according to the invention and/or at least one seal carrier according to the invention.
  • Fig. 1 shows a highly schematic schematic representation of a section of an exemplary embodiment of a guide vane arrangement 100 according to the invention, looking in the circumferential direction U onto the guide vane arrangement 100, the guide vane arrangement 100 having an adjustable guide blade 10 according to the invention with a fastening pin 11 formed at its radially inner end, one on the guide blade 10 attached inner ring segment 30 and a seal carrier 20 according to the invention which is movably mounted on the fastening pin 11 in the radial direction R.
  • the guide vane 10 is in particular about an adjustment axis V, which in this case runs in the radial direction R, but could also run inclined to this by a few degrees, designed to be rotatable and rotatably mounted relative to the inner ring segment 30 and rotatably received by the seal carrier 20.
  • a sealing structure 21 designed in a manner known from the prior art in the form of a honeycomb sealing structure 21 is arranged for sealing against a rotor, not shown here, which in this exemplary embodiment, in particular integrally with the downstream Seal carrier part 20B is formed.
  • a circumferential groove 15 is introduced into the fastening pin 11, into which an axial securing means 40 in the form of a retaining ring 40 engages, the inner ring segment 30 being fastened to the guide vane 10 with a defined play in the direction of the adjustment axis V is.
  • the fastening pin 11 borders with its radially outer end on a shoulder 12 with a larger outer diameter, with the circumferential radial groove 15, based on the adjustment axis, for receiving the axial securing means 40 at a defined distance in the direction of the radially inner end of the fastening pin 11 from this paragraph 12 of the guide vane 10 is inserted into the fastening pin 11.
  • the play in the direction of the adjustment axis V between the guide vane 10 and the inner ring segment 30 in the radial direction, in particular in the area of a radially sealing sealing gap 13, is in particular dimensioned in such a way, in particular in connection with the geometric design of the inner ring segment 30, that by applying a Operating pressure p1 in an area radially within the inner ring segment 30, the inner ring segment 30 can be pressed outwards in the direction of the adjustment axis V and can be brought into contact with the guide vane 10 in the area of the radially sealing sealing gap 13, whereby a particularly good seal in the radial direction Direction R can be achieved in the area of the sealing gap 13.
  • the shoulder 12 of the guide vane has an end face facing the radially inner end of the guide vane 10 and extending in a radial plane perpendicular to the adjustment axis V, the end face being at least partially, preferably completely, designed as a sealing surface and one of the two Sealing surfaces of the radially sealing sealing gap 13 forms.
  • the inner ring segment 30 has a fastening opening, not specified here, through which the radially inner end of the guide vane 10, in particular the fastening pin 11, extends, the guide vane 10 having a corresponding shoulder as a stop in the radial direction towards the outside 12 and the inner ring segment 30 has a corresponding flange, not specified here.
  • the fastening pin 11 is guided with a defined play, symbolized by guide gap 23, in the axial direction A and in the circumferential direction U in the seal carrier 20, with both a peripheral surface 27 of the fastening pin 11 and an inner lateral surface of the guide vane receptacle 24 each having a friction reducing feature Coating and also have a hardened surface to reduce the risk of fretting (frictional wear).
  • the seal carrier 20 is spoke-centered in the direction of the adjustment axis V, which in this case coincides with the radial direction R, and is mounted movably on the guide vane 10 in the direction of the adjustment axis V.
  • the seal carrier 20 is divided in the axial direction A and has an upstream seal carrier part 20A and a downstream seal carrier part 20B, which are each connected to one another by means of a plurality of connecting means 22 distributed in the circumferential direction in the form of screws 22, the connecting means 22 are each arranged at the level of the fastening pins 11 in the radial direction R in order to enable a particularly compact and space-saving design of the guide vane arrangement 100 in the radial direction R (see Fig. 2 ).
  • seal carrier 20 In addition to the axial division of the seal carrier, 20, it is further divided in the circumferential direction U into several seal carrier segments (not shown), with the individual seal carrier segments each extending over no more than a circumferential angle range of 55°.
  • the individual seal carrier parts or segments are each manufactured using an additive manufacturing process.
  • seal carrier segments that adjoin one another in the circumferential direction are arranged to overlap one another in both the axial direction A and the circumferential direction U, the seal carrier segments being wedge-shaped in the overlap areas, which means that a particularly good sealing effect can be achieved in the overlap area, especially in the axial direction A and in the circumferential direction U.
  • the connecting means 22 connect two adjacent, upstream seal carrier parts 20A to each other as well as the two associated, downstream seal carrier parts 20B and these also to the two upstream seal carrier parts 20A.
  • a total of four individual parts of a seal carrier 20 are connected to one another with a connecting means 22, in particular a screw 22.
  • downstream seal carrier part 20B and the inner ring segment 30 each point to their downstream Side has a sealing flange 25 or 35 extending in the radial direction, which overlap in the radial direction R and in the circumferential direction U and form an axially acting sealing gap 26 between them.
  • the guide vane 10 is further connected to the inner support segment 30 in the area of its shoulder 12 in the axial direction A with a defined play, in particular with a defined axial play 14, by applying a corresponding operating pressure p1 in conjunction with the geometric dimensions of the inner ring segment 30, the inner ring segment 30 can be displaced in the axial direction A in the direction of the sealing flange 25 of the seal carrier 20, in particular can be brought into contact with the seal carrier 20, so that an axially acting sealing gap 26 is established with a gap width of zero and thus a seal Flow channel, which is designed to be flowed through by a hot gas flow with flow direction HS, is further improved radially inwards compared to an area radially inside the seal carrier 20. If hot gas should escape through the radially sealing sealing gap 13, it can still be prevented from further escaping radially inwards by the downstream, axially acting sealing gap 26.
  • the seal carrier 20 is mounted movably in the direction of the adjustment axis V or in this case also in the radial direction R relative to the guide vane 10 and the inner ring segment 30 attached to it. If there is a thermally induced change in length of the guide vane 10 during operation in a turbomachine, the fastening pin 11 can move freely in the guide vane receptacle 24 in the direction of the adjustment axis V or in the radial direction R, without this having a negative effect on a position of the Sealing structure 21 and thus on a sealing gap formed with a rotor, not shown here, in the radial direction.
  • a change in length of the guide blade 10 does not cause a change in the gap width of the axially acting sealing gap 26 between the downstream seal carrier part 20B and the inner ring segment 30.
  • a guide vane arrangement 100 enables advantageous gap widths over a wide operating range and thus high efficiencies over a wide operating range.
  • spoke-centered mounting of the seal carrier 20 according to the invention which is decoupled from the inner ring segment 30, causes a separation of the tolerance chain and thus a significantly simplified determination of the maximum permissible tolerances in order to determine the desired maximum gap widths or the maximum permissible for the desired maximum gap widths Tolerances.
  • Fig. 2 shows the guide vane arrangement 100 Fig. 1 looking in the axial direction A in the flow direction HS in an unwound state, in which it can be clearly seen in this illustration how two inner ring segments 30 are arranged relative to one another in the circumferential direction U with a defined compensating gap 50 between them to avoid tension in the circumferential direction, wherein in the area of the compensation gap 50 a sealing element 60 is arranged, in particular in the form of a sealing strip 60 made of spring steel, which is inserted into a groove in the two adjacent inner ring segments and extends in the axial direction A, in particular over the length of the inner ring segments 30 and over extends a certain distance in the circumferential direction U in order to effect a seal in the radial direction R between the inner ring segments 30.
  • the sealing element 60 forms a labyrinth gap with the associated inner ring segment 30.

Landscapes

  • 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. Dispositif d'aube directrice (100) pour une turbomachine comportant un axe de rotation, en particulier pour un étage de compresseur ou de turbine d'une turbine à gaz, comprenant :
    - plusieurs aubes directrices (10) réglables montées rotatives chacune autour d'un axe de réglage (V),
    - au moins un segment d'anneau intérieur (30) réalisé séparément des aubes directrices (10), et
    - un porte-joint (20) réalisé séparément de l'au moins un segment d'anneau intérieur (30),
    dans lequel l'au moins un segment d'anneau intérieur (30) est fixé à une ou plusieurs aubes directrices (10),
    caractérisé en ce que le porte-joint (20) est monté de manière centrée par rayons par rapport à l'au moins un segment d'anneau intérieur (30) de telle sorte que le porte-joint (20) est monté mobile par rapport à l'au moins un segment d'anneau intérieur (30) en direction de l'au moins un axe de réglage (V), à au moins une aube directrice (10) et/ou dans la direction radiale (R), par rapport à l'axe de rotation de la turbomachine dans un état d'utilisation conforme du dispositif d'aube directrice (100) dans une turbomachine.
  2. Dispositif d'aube directrice (100) selon la revendication 1,
    caractérisé en ce que le porte-joint (20) est monté de manière centrée par rayons sur les aubes directrices (10), en particulier sur au moins trois points d'appui répartis dans la direction circonférentielle (U).
  3. Dispositif d'aube directrice (100) selon la revendication 1 ou 2,
    caractérisé en ce qu'au moins une aube directrice (10) présente, au niveau de son extrémité radialement intérieure, un élément de fixation (11) s'étendant le long de l'axe de réglage (V), en particulier une cheville de fixation (11), et l'au moins un élément d'anneau intérieur (30) fixé à cette au moins une aube directrice (10) présente au moins une ouverture de fixation associée et réalisée de manière correspondante, dans lequel l'élément de fixation (11) traverse l'aube directrice (10) par l'au moins une ouverture de fixation associée du segment d'anneau intérieur (30).
  4. Dispositif d'aube directrice (100) selon la revendication 3,
    caractérisé en ce que l'au moins un segment d'anneau intérieur (30) est fixé à l'élément de fixation (11) à l'aide d'un moyen de sécurité axiale (40) et sécurisé sur l'élément de fixation (11) dans la direction de l'axe de réglage (V), en particulier à l'aide d'un anneau de sécurité (40) ou d'une rondelle de sécurité.
  5. Dispositif d'aube directrice (100) selon la revendication 3 ou 4,
    caractérisé en ce que le porte-joint (20) présente au moins un logement d'aube directrice (24) dans lequel l'élément de fixation (11), en particulier une cheville de fixation (11), d'au moins une aube directrice (10) s'engage, de telle sorte que l'élément de fixation (11) de l'aube directrice est monté le long de l'axe de réglage (V) et/ou dans la direction radiale (R), de façon mobile par rapport au porte-joint (20) dans le logement d'aube directrice (24) du porte-joint (20).
  6. Dispositif d'aube directrice (100) selon l'une des revendications précédentes, caractérisé en ce que le porte-joint (20) est un anneau de porte-joint réalisé de manière circonférentielle, dans lequel l'anneau de porte-joint est réalisé au moins partiellement d'une seule pièce dans la direction circonférentielle (U), ou présente plusieurs segments de porte-joint ne s'étendant chacun que sur une partie dans la direction circonférentielle (U), dans lequel le porte-joint (20) est constitué en particulier de plusieurs segments de porte-joint ne s'étendant que sur une partie dans la direction circonférentielle (U).
  7. Dispositif d'aube directrice (100) selon l'une des revendications précédentes, caractérisé en ce que le porte-joint (20) est divisé en au moins une partie de porte-joint (20A) en amont et au moins une partie de porte-joint (20B) en aval, dans lequel le porte-joint (20) est divisé en une partie de porte-joint (20A) en amont et une partie de porte-joint (20B) en aval, en particulier au moins partiellement le long d'un plan de division s'étendant parallèlement à l'axe de réglage (V) des aubes directrices (10) et/ou le long d'un plan radial s'étendant perpendiculairement à l'axe de rotation.
  8. Dispositif d'aube directrice (100) selon la revendication 7 ou 8,
    caractérisé en ce que la partie de porte-joint (20A) en amont et la partie de porte-joint (20B) en aval sont reliées l'une à l'autre à l'aide d'au moins un moyen de liaison (22), en particulier à l'aide d'au moins un moyen de liaison (22) s'étendant dans une direction perpendiculaire au plan de division du porte-joint (20), dans lequel l'au moins un moyen de liaison (22), par rapport à un état d'utilisation conforme du dispositif d'aube directrice (100) dans une turbomachine, est disposé dans la direction circonférentielle (U) avec un décalage par rapport aux éléments de fixation (11) des aubes directrices (10) et se trouve dans la direction radiale (R), en particulier à la hauteur d'au moins un élément de fixation (11) d'au moins une aube directrice (10).
  9. Dispositif d'aube directrice (100) selon l'une des revendications précédentes, caractérisé en ce que l'au moins un segment d'anneau intérieur (30) et le porte-joint (20) se chevauchent, par rapport à un état monté conforme dans une turbomachine, au moins partiellement en aval dans la direction de l'axe de réglage (V) et forment une fente de joint (26) agissant de manière étanche dans la direction axiale (A).
  10. Dispositif d'aube directrice (100) selon l'une des revendications précédentes, caractérisé en ce que le dispositif d'aube directrice (100) présente au moins deux éléments d'anneau intérieur (30) réalisés séparément des aubes directrices (10), dans lequel les au moins deux segments d'anneau intérieur (30) sont disposés adjacents l'un à l'autre dans la direction circonférentielle (U) et avec entre eux une fente de compensation (50) dans la direction circonférentielle (U), dans lequel, entre les deux segments d'anneau intérieur (30) disposés adjacents l'un à l'autre dans la direction circonférentielle (U), en particulier au moins un joint d'étanchéité (60) est disposé dans la zone de la fente de compensation (50), pour assurer l'étanchéité au moins partielle de la fente de compensation (50) dans la direction radiale.
  11. Turbomachine, en particulier turbine à gaz, comportant au moins un étage de compresseur ou de turbine comprenant un dispositif d'aube directrice (100) ayant des d'aubes directrices (10), caractérisée en ce que
    le dispositif d'aube directrice (100) est réalisé selon l'une quelconque des revendications 1 à 10.
EP19191194.0A 2018-08-20 2019-08-12 Dispositif d'aube directrice variable, aube directrice, porte-joint et turbomachine Active EP3613952B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102018213983.0A DE102018213983A1 (de) 2018-08-20 2018-08-20 Verstellbare Leitschaufelanordnung, Leitschaufel, Dichtungsträger und Turbomaschine

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EP3613952A1 EP3613952A1 (fr) 2020-02-26
EP3613952B1 true EP3613952B1 (fr) 2023-10-18

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US (1) US11300004B2 (fr)
EP (1) EP3613952B1 (fr)
DE (1) DE102018213983A1 (fr)
ES (1) ES2965895T3 (fr)

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CN114992167A (zh) * 2022-06-27 2022-09-02 哈尔滨工业大学 一种环形叶栅外通道的导叶安装角调节装置

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Also Published As

Publication number Publication date
ES2965895T3 (es) 2024-04-17
US11300004B2 (en) 2022-04-12
EP3613952A1 (fr) 2020-02-26
DE102018213983A1 (de) 2020-02-20
US20200056499A1 (en) 2020-02-20

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