EP3613952A1 - Dispositif d'aube directrice réglable, aube directrice, porte-joint et turbomachine - Google Patents

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

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Publication number
EP3613952A1
EP3613952A1 EP19191194.0A EP19191194A EP3613952A1 EP 3613952 A1 EP3613952 A1 EP 3613952A1 EP 19191194 A EP19191194 A EP 19191194A EP 3613952 A1 EP3613952 A1 EP 3613952A1
Authority
EP
European Patent Office
Prior art keywords
guide vane
seal carrier
inner ring
guide
turbomachine
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP19191194.0A
Other languages
German (de)
English (en)
Other versions
EP3613952B1 (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
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 EP3613952A1 publication Critical patent/EP3613952A1/fr
Application granted granted Critical
Publication of EP3613952B1 publication Critical patent/EP3613952B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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 an axis of rotation, in particular for a compressor or turbine stage of a gas turbine, the guide vane arrangement comprising a plurality of adjustable guide vanes which are rotatably mounted about an adjustment axis, at least one inner ring segment which is formed separately from the guide vanes and one separately from the latter comprises at least one inner ring segment formed seal carrier.
  • the present invention relates to a guide vane, in particular an adjustable guide vane, for a aforementioned guide vane arrangement and a seal carrier for such a guide vane arrangement.
  • the achievable sealing effect 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 resulting losses in efficiency.
  • the overall achievable sealing effect 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 how the seal carrier, on which a sealing structure for sealing an annular gap around the rotor is generally applied is attached around, designed and stored.
  • a guide vane arrangement according to the invention for a turbomachine with an axis of rotation in particular for a compressor or turbine stage of a gas turbine, comprises a plurality of adjustable guide vanes, in particular in each case 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, the at least one inner ring segment being fastened to one or more guide vanes, in particular to at most four guide vanes.
  • the seal carrier is mounted in a spoke-centered manner with respect to the at least one inner ring segment, so that the seal carrier with respect 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 one Turbo machine that is movably mounted.
  • an "adjustable guide vane” is understood to mean a guide vane which is designed for this purpose 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, the adjustment axis with its Longitudinal axis can coincide, or can also be different from this, 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 seal structure, in particular a seal structure which is fundamentally known from the prior art, such as a brush seal structure and / or a fundamentally also known and known from the prior art to hold 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, is always about an axis, in particular about a Axis that runs parallel to the axis of rotation of a turbomachine or is centered about the axis of rotation itself, and which also enables compensation in the radial direction, based on the axis of rotation of a turbomachine.
  • 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 is self-centering with respect to an axis, in particular one parallel to the axis of rotation of a turbomachine extending axis or to the axis of rotation itself acts, similar to a bicycle wheel, in which the hub is supported by spokes in the rim.
  • the "axial” direction refers to a direction parallel to a main rotation or (main) machine axis of the turbomachine, the direction information "circumferential direction” in the present case in the usual manner "Correspondingly, unless explicitly stated otherwise, in particular a different axis, to a direction of rotation about this axis of rotation or (main) machine, the direction" radial ", unless explicitly stated otherwise, in particular another axis a direction perpendicular to the axial and circumferential directions.
  • the spoke-centered mounting of the seal carrier according to the invention enables the seal in the region of the radially inner ends of the guide vanes to be decoupled between the guide vanes and the at least one inner ring segment from the seal with respect to 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 fastened can be designed separately and independently of the sealing gap between the seal carrier or a sealing structure fastened thereon and the rotor, thereby shortening the tolerance chains to be taken into account, in particular divide, and consequently simplify and, furthermore, less tight tolerances are to be observed overall.
  • 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 uniformly distributed in the circumferential direction, and are each rotatably mounted 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 by more than 1 °, preferably by more than 2 °, in particular by more than 3 °, at most however, is inclined in the upstream direction by 5 °, in particular at most 4 °, preferably by at most 3 °, from a radial plane extending perpendicular to the axis of rotation of a turbomachine.
  • a separate inner ring segment is in particular assigned to each guide vane.
  • a plurality of guide vanes in particular two or three guide vanes, but in particular, however, at most four guide vanes, are assigned to a common inner ring segment. That is,
  • an inner ring segment is fastened to a plurality of guide vanes, but in particular to a maximum of four guide vanes. Attachment to more than four guide vanes is possible. However, if the inner ring segment is attached to too many guide vanes, thermal stresses can occur, which can only be countered by larger gap dimensions between the inner ring segment and guide vanes, which in most cases will deteriorate the sealing effect, which can be a disadvantage of efficiency and therefore should 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 inward, which surrounds the guide vanes in the region of their flow profiles, the individual inner ring segments being in particular designed such that an inner shroud that is almost closed in the circumferential direction formed.
  • the individual inner ring segments are, however, in particular arranged at a sufficient distance from one another in the circumferential direction.
  • the seal carrier is in particular spoke center-mounted on the guide vanes and / or the at least one inner ring segment, in particular over at least three bearing points distributed in the circumferential direction, in particular evenly distributed.
  • the seal carrier is mounted in a spoke-centered manner only on the guide vanes.
  • At least one guide vane has at its radially inner end a fastening element, in particular a fastening pin, which extends along the adjustment axis, and the at least one inner ring segment which is fastened to this at least one guide vane, at least one associated, appropriately designed fastening opening, the fastening element of the guide vane, in particular in the direction of the adjustment axis, in particular extending 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 on the inner ring segments, in particular on at least three inner ring segments, in a spoke-centered manner, for example as is known from the prior art for a guide vane arrangement with fixed guide vanes and as for example in the 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 vanes.
  • the at least one inner ring segment is in this case with a defined one Game in the direction of the adjustment axis attached to one or more guide vanes, that the inner ring segment can be displaced outward in the direction of the adjustment axis within the scope of this play, in particular in such a way that the inner ring segment is in a radial direction Direction can be brought to bear on the associated guide vanes, 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 appropriately 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, tension, in particular thermally induced tension, 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 guide vanes received by the seal carrier, with a clearance between the guide vanes and the at least one inner ring segment being greater in the axial direction and / or in the circumferential direction 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, engages at least one guide vane in such a way that the fastening element of the guide vane is mounted movably with respect to the seal carrier in the guide vane receptacle of the seal carrier along the adjustment axis and / or in the radial direction, based on the state of use of the guide vane arrangement according to the invention in a turbomachine , wherein the guide vane receptacle is formed and arranged in the seal carrier in particular concentrically with at least one fastening opening of at least one inner ring segment.
  • the fastening element of at least one guide vane can be mounted so that it can move in the direction of the adjustment axis of the guide vane or in the radial direction, but at the same time, in particular in the axial direction and in the circumferential direction, relative to the axis of rotation of a turbomachine.
  • This enables a particularly advantageous, spoke-centered mounting of the seal carrier to be formed.
  • the spoke centering with the aid of fastening pins enables this, in particular in comparison to a slot-guided spoke centering, as for example from the EP 2 696 039 A1 is known, a more precise guidance and thus an improved, in particular more accurate centering.
  • the gap widths can be set more precisely as a result.
  • the at least one guide vane receptacle is designed as a cylindrical or cup-shaped or cylinder-like or cup-like recess.
  • at least one guide vane receptacle can also be designed as a frustoconical or conical recess, the fastening element provided for storage in the vane receptacle, in particular the respective fastening pin, in particular correspondingly corresponding, in particular correspondingly complementary, for the design of the vane receptacle.
  • the fastening element of the guide vane engages, in particular in the direction of the adjustment axis, in particular with a defined play in the axial direction and / or in the circumferential direction, into the guide vane receptacle of the seal carrier, the play in the direction of the adjustment axis being dimensioned in particular at least so large that a thermally induced length increase of the guide vane is possible without tension during operation.
  • the play should be selected at most so large that the seal carrier is always securely mounted on the guide blades during operation and in particular that the fastening elements cannot slip out of the guide blade receptacles in the seal carrier.
  • 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 formed in one part or in several parts and 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 guide vanes, can be axially divided, the individual parts being preferred in the case of a divided 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 circumferentially formed seal carrier ring, wherein the seal carrier ring is formed in one piece in the circumferential direction or has several seal carrier segments that only extend over a part in the circumferential direction, the seal carrier in particular consisting of several, each only is assembled over a part extending in the circumferential direction of the seal carrier segments.
  • the division of the seal carrier in the circumferential direction enables a particularly simple assembly of a guide vane arrangement according to the invention, the individual seal carrier segments being arranged to overlap 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.
  • the seal carrier 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.
  • 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 by an additive manufacturing process enables a particularly flexible configuration of the seal carrier, since this type of production enables a particularly high degree of geometric freedom with good mechanical and thermal properties at the same time.
  • the seal carrier in particular in the 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 division plane running parallel to the adjusting 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 also in an upstream and one downstream seal carrier part, wherein at least one seal carrier part or seal carrier segments is produced by an additive manufacturing process and / or extends in particular in the circumferential direction 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 detachably, in particular by means of at least one, 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 Connecting means extending in a direction perpendicular to the parting plane of the seal carrier, wherein the at least one connecting means, based on a state of use of the guide vane arrangement according to the invention in a turbomachine, is arranged offset in the circumferential direction to 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.
  • the individual seal carrier parts can be assembled quickly, in particular releasably.
  • connecting means are each arranged in the radial direction at the level of the fastening elements, in particular at the level of the fastening pins, a guide vane arrangement which is particularly compact in the radial direction and saves space can be realized.
  • At least one inner ring segment and the seal carrier overlap, in particular downstream, in relation to a functional installation state in a turbomachine, in the direction of the adjustment axis or in the radial direction, at least partially and in particular form one in relation to one another the axis of rotation of a turbomachine in a functional state of use of the guide vane arrangement, sealing gap acting in the axial direction , wherein the sealing gap itself extends 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 implemented in a particularly simple manner, in particular additionally, downstream of the guide vane receptacles, which in particular also enables a length compensation of the guide vane or a radial movement of the inner ring segment with respect to the seal carrier without the sealing effect in the axial direction Direction significantly negatively impact. Leakage effects can be reduced even further by the additional sealing, which generally has an advantageous effect on the efficiency of a turbomachine.
  • the at least one inner ring segment and the seal carrier in particular a downstream part of the seal carrier, and in particular in each case downstream of the respective guide vane receptacle, each have a sealing flange which extends in the radial direction with respect to the axis of rotation of a turbomachine, wherein the sealing flange of the inner ring segment extends in particular radially inward, and the sealing flange of the seal carrier in particular radially outward.
  • 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 play in the axial direction, and the play is dimensioned in such a way that there is sufficient space available radially within the inner ring segment 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 such 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 of Zero in the axial direction.
  • the guide vane arrangement has at least two inner ring segments which are 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 therebetween, the compensating gap being based on the axis of rotation a turbomachine, in particular in the radial direction, in particular at least one sealing element being arranged between two inner ring segments arranged adjacent in the circumferential direction in the region of the compensating gap, in particular at least for at least partially sealing the compensating gap in the radial direction.
  • the compensating gaps can be used to reduce tensions in the circumferential direction, in particular thermally-induced tensions due to thermally induced expansions of the inner ring segments, or even to avoid them altogether if the compensating gaps are appropriately large.
  • At least one sealing element extends in particular in the circumferential direction and at least partially in the axial direction, at least one sealing element being in particular a sealing strip, in particular a sheet metal strip or the like, in particular made of spring steel, which in particular is accommodated in a correspondingly formed groove in each case by two adjacent inner ring segments is, in particular such that a labyrinth gap is formed between the sealing element and the respective inner ring segment.
  • the guide vane for a turbomachine, which is, in particular, an adjustable guide vane, in particular for a compressor or turbine stage of a gas turbine, in particular for a guide vane arrangement according to the invention
  • the guide vane relating to a functional installation state of the guide vane in a turbomachine and with respect to an axis of rotation of the turbomachine has a radially outer end and a radially inner end, wherein in the region of the radially inner end of the guide vane an inner ring segment can be fastened to the guide vane and the guide vane along its radially inner end has an adjustment axis extending fastening pin, which is designed to cooperate with a fastening recess, in particular a fastening opening, of an inner ring segment which can be fastened to the guide vane, in particular to reach through a fastening opening, according to the invention, in the fastening pin, in each case with respect to the adjustment axis, in particular circumferential, radi
  • the fastening pin of the guide vane borders with its radially outer end to a shoulder with a larger outside diameter, the circumferential radial groove, with respect to the adjustment axis, for Recording the axial securing means with a defined distance in the direction of the radially inner end of the fastening pin from this shoulder of the guide vane is introduced into the fastening pin.
  • the fastening of an inner ring segment to the guide vane can be realized in a particularly simple manner, in particular with a defined play in the direction of the adjustment axis or with a defined play in the radial direction, based on an axis of rotation of a turbomachine.
  • the shoulder has an end face facing the radially inner end of the guide vane and extending in a radial plane perpendicular to the adjustment axis on, wherein the end face is at least partially, preferably completely, formed as a sealing surface.
  • a peripheral surface of the fastening pin is at least partially, preferably completely, as a functional surface on a side of the groove facing away from the shoulder and facing the radially further inward end of the fastening pin or the radially inner end of the guide vane formed, in particular as a guide surface, in particular as a sliding bearing surface.
  • the functional surface is designed in particular for guiding the fastening pin in a guide vane receptacle of a seal carrier, in particular for guiding the fastening pin in a seal carrier according to the invention, it being possible for the guide surface to have a functional coating, in particular a friction-reducing coating and / or a coating for increasing a surface hardness, in particular to prevent and / or reduce or even avoid fretting.
  • a guide vane equipped in this way enables a separation of the seal in the radial direction (via the end face of the shoulder) and a guide by means of different functional surfaces (end face of the shoulder for sealing in the radial direction relative to an inner ring segment, peripheral face of the fastening pin for guiding in the axial direction and circumferential direction) in the direction of the adjustment axis (over the circumferential surface of the fastening pin) and the seal towards the rotor.
  • a particularly good seal between the guide vanes and an associated inner ring segment attached to the guide vanes can be achieved, with in particular a sealing gap in the direction of the adjustment axis and / or in the radial direction, based on the axis of rotation of a turbomachine, almost independently of the current length of the guide vane, ie not significantly changed due to a change in length of the guide vane under temperature, in particular not significantly increased.
  • a sealing gap between a sealing structure held by the seal carrier and the rotor can also be set almost independently of a current guide vane length and thus independently of thermally induced changes in length of the guide vane occurring during operation.
  • a seal carrier according to the invention for a guide vane arrangement in particular for a guide vane arrangement with adjustable guide vanes, in particular a compressor or turbine stage of a gas turbine, in particular for a guide vane arrangement according to the invention, is designed for spoke-centered storage in a guide vane arrangement and, according to the invention, has at least one guide vane receptacle for receiving a fastening element, in particular a fastening pin, an adjustable guide vane, into which the fastening element, in particular a fastening pin, of a guide vane can engage in such a way that the fastening element of the guide vane can move along an adjustment axis or longitudinal axis of the guide vane and / or in the radial direction, based on an axis of rotation of a turbomachine in a functional state of use of the seal carrier in a turbomachine, relative to the seal carrier in the guide blade receptacle of the seal carrier is storable and in particular also rotatable about the adjustment axis.
  • 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 and / or at least one guide vane according to the invention and / or at least one seal carrier according to the invention.

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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)
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

Publications (2)

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

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EP19191194.0A Active EP3613952B1 (fr) 2018-08-20 2019-08-12 Dispositif d'aube directrice variable, aube directrice, porte-joint et turbomachine

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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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EP2696039A1 (fr) 2012-08-10 2014-02-12 MTU Aero Engines GmbH Étage de turbine à gaz
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ES2965895T3 (es) 2024-04-17
US11300004B2 (en) 2022-04-12
EP3613952B1 (fr) 2023-10-18
DE102018213983A1 (de) 2020-02-20
US20200056499A1 (en) 2020-02-20

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