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EP3379037B1 - Seal on the inner ring of a guide blade assembly - Google Patents

Seal on the inner ring of a guide blade assembly Download PDF

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Publication number
EP3379037B1
EP3379037B1 EP17162630.2A EP17162630A EP3379037B1 EP 3379037 B1 EP3379037 B1 EP 3379037B1 EP 17162630 A EP17162630 A EP 17162630A EP 3379037 B1 EP3379037 B1 EP 3379037B1
Authority
EP
European Patent Office
Prior art keywords
guide vane
sealing element
bearing
ring
bearing bodies
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP17162630.2A
Other languages
German (de)
French (fr)
Other versions
EP3379037A1 (en
Inventor
Werner Humhauser
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Priority to EP17162630.2A priority Critical patent/EP3379037B1/en
Priority to US15/933,410 priority patent/US10494944B2/en
Publication of EP3379037A1 publication Critical patent/EP3379037A1/en
Application granted granted Critical
Publication of EP3379037B1 publication Critical patent/EP3379037B1/en
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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • 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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • 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
    • F05D2240/50—Bearings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/55—Seals

Definitions

  • the present invention relates to a guide vane ring for a turbomachine, a flow machine and a method for assembling a guide vane ring.
  • Fluid flow machines such as aircraft engines and stationary gas turbines often have at least one guide vane ring to set optimal operating conditions.
  • This comprises an inner ring and a plurality of guide vanes, one end of which is arranged on the inner ring and which extend radially outward from this; the terms "radial”, “axial” and “in the circumferential direction” always refer in this document - unless otherwise stated - to a central geometric axis of the guide vane ring or the inner ring, which is not always formulated separately for better readability. If the respective information relates to individual parts of the guide vane ring, they are to be understood in relation to the intended alignment of the respective individual part in the guide vane ring.
  • a guide vane ring can in particular be designed to be adjustable: in this case, the guide vanes can be pivoted about an intended pivot axis which generally coincides with a longitudinal axis of the guide vanes and runs essentially radially.
  • the pivoting can take place via external adjustment components on the guide vanes, in particular by means of adjusting pins, which are inserted or inserted into associated receptacles in the housing and which can then interact with a corresponding adjustment device on the outer housing.
  • FIG EP 2 725200A1 An example of a guide vane ring in which guide vane bearing journals are received in bearing bushings is from FIG EP 2 725200A1 known.
  • an adjustable guide vane ring in which the guide vanes are each mounted in bearing bodies which have a cuboid basic shape and a bearing bore.
  • the inner ring is composed of two half-rings, which were pushed onto the bearing body in the circumferential direction.
  • Such a guide vane ring offers in particular the advantages of simple assembly.
  • the present invention has the object of providing a technique with which the avoidance of leakage can be further improved while maintaining simple assembly.
  • a guide vane ring according to the invention for a turbomachine comprises an inner ring with a receiving groove running in the circumferential direction on its radially outer surface, furthermore a plurality of guide vanes and a plurality of bearing bodies which are arranged in the receiving groove of the inner ring.
  • a radially inner end (for example a bearing element such as, in particular, a bearing journal) of the guide vanes is in each case inserted into a bearing body (or into a bore located therein).
  • the guide vane ring comprises at least one sealing element consisting at least partially of sheet metal for sealing at least one gap between the inner ring and at least one of the bearing bodies and / or between two bearing bodies.
  • the receiving channel has at least one groove on each of two mutually facing side walls into which a section of a respective sealing element is inserted.
  • a turbomachine according to the invention comprises a guide vane ring according to the invention in accordance with one of the embodiments disclosed in this document.
  • a method according to the invention is used to assemble a guide vane ring (in particular a guide vane ring according to the invention in accordance with one of the embodiments disclosed in this document). It comprises threading a plurality of bearing bodies into the Receiving groove of an inner ring segment of the guide vane ring. A radially inner end of one of several guide vanes of the guide vane ring is inserted into each of the bearing bodies. A gap between a side wall of the receiving channel and at least one of the bearing bodies and / or between two bearing bodies is sealed by at least one sealing element.
  • the method can also include (before threading the bearing bodies) inserting the respective radially inner ends of the guide vanes into the bearing bodies (or bores arranged therein).
  • the guide vanes are preferably inserted at their radially outer ends (for example with a respective adjusting pin) into respective bearings on the housing side.
  • a guide vane ring according to the invention, a turbomachine according to the invention and a method according to the invention make it possible to seal gaps on the inner ring and thus to significantly reduce leakage.
  • a recirculation of air can be reduced and thus an increase in the efficiency of the turbomachine can be brought about.
  • this also has a stabilizing effect on the arrangement of the inner ring and bearing bodies.
  • the radially inner ends of the guide vanes can be inserted into a separate, assigned bearing body, and / or the guide vane ring can comprise guide vanes, the radially inner ends of which are or will be inserted into a common bearing body (for example, in twos, threes or more with more guide vanes).
  • the guide vane ring can comprise just as many bearing bodies as there are guide blades or fewer bearing bodies than guide blades.
  • the guide vane ring can in particular be provided for a compressor stage of the turbomachine.
  • the at least one sealing element consists at least partially of sheet metal. This ensures a high level of durability.
  • the at least one sealing element is preferably arranged at least partially in a respective gap which it seals, and thus narrows and / or bridges this gap.
  • the receiving channel has at least one groove on two mutually facing lateral walls, into each of which a section of a respective associated sealing element is or will be inserted.
  • At least one of the bearing bodies can (additionally) have at least one groove into which a part (that is to say a section) of the at least one sealing element is or will be inserted.
  • a sealing element inserted into one or more groove (s) in this way is particularly solidly anchored, so that it remains fixed in spite of the vibrations that occur during operation of the turbomachine, and it causes the seal to be particularly effective.
  • the sealing element On one side opposite the section or part inserted into a respective groove, the sealing element can protrude freely into the gap or abut and / or be bent against a surface of the respective bearing body or a side wall of the receiving channel.
  • the sealing element can be inserted (for example drawn in) into a respective groove on both sides:
  • a variant of the present invention is particularly advantageous in which a gap between a side wall of the receiving channel and at least one bearing body is bridged by the at least one sealing element .
  • both the side wall of the receiving channel and at least one of the bearing bodies can each have a groove, and the at least one sealing element can (corresponding to a tongue and groove connection) on one side in the groove of the side wall of the receiving channel and on an opposite side be or will be inserted into the groove of the at least one bearing body.
  • a preferred embodiment variant of a method according to the invention comprises inserting the at least one sealing element into a groove arranged in at least one bearing body before the bearing body is threaded into the receiving channel.
  • the sealing element can be drawn into a groove, which is preferably present in a side wall of the receiving channel, or can abut or be bent over against the side wall.
  • At least two bearing bodies arranged one behind the other in the circumferential direction each have a groove on their contact surfaces into which a common sealing element is or will be inserted on opposite sides (corresponding to a tongue and groove connection).
  • the sealing element can bridge a gap between the bearing bodies over its entire longitudinal extension or partially, for example at least half the longitudinal extension or at least one third of the longitudinal extension of the gap.
  • the bearing bodies can preferably each have an essentially cuboid basic shape with a bore for a respective radially inner end of a guide vane;
  • a profile can also be formed on or in the basic shape, for example in the form of at least one (in particular in the axial direction) widened and / or narrowed area, for example at least one step, at least one web and / or - as mentioned above - at least one Groove, by means of which the bearing bodies can be or can be connected to one another (for example in a form-fitting manner) with the sealing element and / or with the inner ring.
  • the bearing bodies can for example consist at least partially of carbon. They can be made metal-free or comprise a coated metal.
  • the at least one sealing element in a groove of the at least one bearing body at least partially surrounds a bore into which the radially inner end of a guide vane is inserted.
  • a central axis of the bore or a longitudinal axis of the guide vane for example a central axis angle of at least 90 °, at least 120 ° or even at least 150 ° can be spanned or revolved for each sealing element.
  • the sealing element can, for example, have an essentially arcuate section with such a central axis angle.
  • This enables, on the one hand, an easy-to-manufacture and solid design of the sealing element in such a way that, starting from a side wall of the receiving channel, it extends particularly far into a gap between two bearing bodies arranged one behind the other in the circumferential direction, so that a particularly effective seal is achieved.
  • the arch shape prevents the bearing body and sealing element from shifting relative to one another in the circumferential direction.
  • the at least one sealing element can consist of a multiplicity of individual elements which are or can be arranged one behind the other in the circumferential direction.
  • the large number of individual elements can correspond to the number of bearing bodies or be a (preferably integer) multiple of this number.
  • the multitude of individual elements can be or will be connected to one another by the bearing bodies, for example by inserting each individual element into grooves of at least two bearing bodies (arranged one behind the other in the circumferential direction).
  • the at least one sealing element is designed as a coherent (preferably one-piece or monolithically designed) partial ring, for example as a ring sector (divided in the circumferential direction). It can span a central axis angle of the inner ring of at least 90 °, at least 120 ° or at least 180 °, i.e. at least a quarter, at least a third or at least half of the central axis of the inner ring.
  • the inner ring can have at least one damping element which is or can be arranged in the receiving groove between the inner ring and the plurality of bearing bodies.
  • the damping element can be designed, for example, as a spring element and / or designed to press the bearing body and the inner ring against one another in one section. In this way, a vibration-resistant fixing of the at least one sealing element can also be improved.
  • Such a damping element can be formed at least partially from metal and / or have a wavy structure; the waves (or their wave fronts) of such a structure can run axially or in the circumferential direction, for example.
  • FIG. 1 a portion of an adjustable guide vane ring 1 according to an embodiment of the present invention is shown; For a better understanding of the structure, individual elements are omitted regardless of an advantageous sequence of assembly steps.
  • the guide vane ring 1 comprises an inner ring 10, which is or will be composed of several (e.g. two) inner ring segments; Only part of the inner ring 10 is shown in the figure, namely one end of an inner ring segment which has a bore 14 for connection (by means of a pin, not shown, to be passed through) with one end of another ring segment, not shown.
  • the inner ring segment has an inlet opening into a receiving channel 11 for bearing body 20 running in the circumferential direction U;
  • the bearing bodies can be threaded one after the other onto the inner ring segment (and thus onto the inner ring) through this inlet opening.
  • several bearing bodies are already threaded into the receiving channel.
  • the guide vane ring 1 further comprises a plurality of guide vanes 30, each of which is inserted with its radially inner end 32 (which preferably comprises a bearing element such as a bearing journal) into an associated bearing body 20 (i.e. into a bore 21 located therein).
  • the respective radially inner end of the guide vanes and / or a surface of the bearing body in the bore can / can be coated to reduce friction and / or wear.
  • the foremost bearing body 20 shown is shown unequipped for the sake of clarity, i.e. without an inserted end of a guide vane.
  • the guide vanes each have a vane blade 31 and can be pivoted via an adjusting pin 33 which is set up to be inserted into corresponding receptacles in a housing (not shown).
  • Bearing body 20 and inner ring 10 are positively connected to one another in the exemplary embodiment shown in the figure, namely in the present case both in the axial direction X and in the radial direction R.
  • the receiving groove 11 has one in the axial direction X. enlarged area 12, in which a corresponding (not visible in the figure) projection of the bearing body 20 is inserted.
  • the guide vane ring 1 shown in the figure also comprises sealing elements 40a, 40b which are inserted opposite one another into respective grooves 15a, 15b in the side wall of the receiving channel 11.
  • an associated bearing body into which the sealing elements 40a, 40b visible in the figure are intended to engage, is not shown.
  • Such a bearing body has on its sides facing the side walls of the receiving channel 11 in each case grooves which are set up to receive the sealing elements 40a, 40b. These then each bridge a gap between the walls of the receiving channel 11 and the bearing body, in the present case over the full length of the respective gap.
  • the sealing elements 40a, 40b are preferably each designed as ring sectors (e.g. half rings) which partially encircle the central axis of the inner ring 10 along the receiving groove and (which is not visible in the figure) in corresponding grooves of the shown, in the circumferential direction U one behind the other arranged bearing body 20 continue.
  • the sealing elements 40a, 40b thus engage in grooves of adjacent bearing bodies on their contact surfaces (in particular on the contact surface 22 of the foremost bearing body in the figure) and thus also bridge a gap between bearing bodies arranged one behind the other in the circumferential direction. In the example shown, the sealing elements 40a, 40b together then bridge more than 80% of the longitudinal extent of this gap.
  • the sealing elements 40a, 40b are shown as flush with the end of the inner ring segment shown for a better overview.
  • the sealing elements protrude beyond a connection of inner ring segments, that is to say bridge this connection.
  • a bearing body can be arranged in such a way that it bridges the mentioned connection (which is also not shown in the figure) by being inserted partly into the receiving groove of a first inner ring segment and partly into the receiving groove of a second inner ring segment. In this way, leakage at the connection of the inner ring segments can be reduced in each case.
  • the sealing elements 40a, 40b each have an arcuate section which is designed to partially encircle a bore 21 arranged therein in a corresponding groove of a bearing body 20, into which the radially inner end of a respective guide vane is inserted;
  • each of the sealing elements 40a, 40b spans a central axis angle around a longitudinal axis of the respective guide vane which is more than 120 °. In this way, despite the existing bore, the sealing element can engage particularly deeply in the respective bearing body 20.
  • the arch shape prevents the bearing body and sealing element from shifting relative to one another in the circumferential direction.
  • the guide vane ring 1 furthermore comprises a damping element 50 which is arranged on a (radially inner) bottom of the receiving channel 11 between the inner ring 10 and the bearing bodies 20.
  • the damping element 50 is set up to bridge a connection between the inner ring segment and another inner ring segment, so that it can also serve as a damping element in the other inner ring segment.
  • the damping element 50 can be designed, for example, as a spring element (e.g. made of sheet metal), the spring force of which presses the bearing body 20 in the radial direction R outward.
  • the damping element is designed as a strip which has a wavy structure, the wavefronts of which run in the axial direction X.
  • the guide vane ring 1 comprises a seal 60 (in the present case designed as an inlet coating) for sealing a radial gap between the inner ring and an opposite rotor section (not shown).
  • the inner ring 10 acts as a seal carrier.
  • a guide vane ring 1 according to the invention comprises an inner ring 10, on the radially outer surface of which a receiving groove 11 runs in the circumferential direction U, a plurality of bearing bodies 20 which are arranged in the receiving groove of the inner ring, a plurality of guide vanes 30, each with its radially inner end 32 is inserted into one of the bearing bodies are, and at least one sealing element 40a, 40b for sealing at least one gap between the inner ring 10 and at least one of the bearing bodies and / or between two bearing bodies.
  • a turbomachine according to the invention comprises a guide vane ring 1 according to the invention.
  • a method according to the invention is used to assemble a guide vane ring 1.

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

Description

Die vorliegende Erfindung betrifft einen Leitschaufelkranz für eine Strömungsmaschine, eine Strömungsmaschine und ein Verfahren zur Montage eines Leitschaufelkranzes.The present invention relates to a guide vane ring for a turbomachine, a flow machine and a method for assembling a guide vane ring.

Strömungsmaschinen wie Flugzeugtriebwerke und stationäre Gasturbinen haben zur Einstellung optimaler Betriebsbedingungen häufig mindestens einen Leitschaufelkranz. Dieser umfasst einen Innenring und eine Mehrzahl an Leitschaufeln, deren eines Ende am Innenring angeordnet ist und die sich von diesem ausgehend radial nach außen erstrecken; die Bezeichnungen "radial", "axial" und "in Umfangsrichtung" beziehen sich in dieser Schrift - sofern nichts anderes angegeben ist - stets auf eine zentrale geometrische Achse des Leitschaufelkranzes bzw. des Innenrings, was zur besseren Lesbarkeit nicht immer extra ausformuliert ist. Sofern sich die jeweiligen Angaben auf Einzelteile des Leitschaufelkranzes beziehen, sind sie in Bezug auf die vorgesehene Ausrichtung des jeweiligen Einzelteils im Leitschaufelkranz zu verstehen.Fluid flow machines such as aircraft engines and stationary gas turbines often have at least one guide vane ring to set optimal operating conditions. This comprises an inner ring and a plurality of guide vanes, one end of which is arranged on the inner ring and which extend radially outward from this; the terms "radial", "axial" and "in the circumferential direction" always refer in this document - unless otherwise stated - to a central geometric axis of the guide vane ring or the inner ring, which is not always formulated separately for better readability. If the respective information relates to individual parts of the guide vane ring, they are to be understood in relation to the intended alignment of the respective individual part in the guide vane ring.

Ein Leitschaufelkranz kann insbesondere verstellbar ausgebildet sein: In diesem Falle sind die Leitschaufeln um eine vorgesehene Verschwenkungsachse verschwenkbar, die im Allgemeinen mit einer Längsachse der Leitschaufeln übereinstimmt und im Wesentlichen radial verläuft. Die Verschwenkung kann über äußere Verstellkomponenten an den Leitschaufeln, insbesondere mittels Verstellzapfen erfolgen, die in zugehörige Aufnahmen des Gehäuses eingesetzt bzw. einzusetzen sind und die dann mit einer entsprechenden Verstelleinrichtung am äußeren Gehäuse zusammenwirken können.A guide vane ring can in particular be designed to be adjustable: in this case, the guide vanes can be pivoted about an intended pivot axis which generally coincides with a longitudinal axis of the guide vanes and runs essentially radially. The pivoting can take place via external adjustment components on the guide vanes, in particular by means of adjusting pins, which are inserted or inserted into associated receptacles in the housing and which can then interact with a corresponding adjustment device on the outer housing.

Eine innere Stabilisierung der Leitschaufeln erfolgt bei bekannten Leitschaufelkränzen häufig über Lagerzapfen, die sich von einem jeweiligen Leitschaufelteller radial nach innen erstrecken und die in Lagerbuchsen des Innenrings geführt sein können.In known guide vane rings, internal stabilization of the guide vanes often takes place via bearing journals which extend radially inward from a respective guide vane disk and which can be guided in bearing bushings of the inner ring.

Ein Beispiel für einen Leitschaufelkranz, bei dem Leitschaufellagerzapfen in Lagerbuchsen aufgenommen sind, ist aus der EP 2 725200A1 bekannt.An example of a guide vane ring in which guide vane bearing journals are received in bearing bushings is from FIG EP 2 725200A1 known.

In der EP 2 696 041 A1 wird ein verstellbarer Leitschaufelkranz vorgeschlagen, bei dem die Leitschaufeln jeweils in Lagerkörpern gelagert sind, die eine quaderförmigen Grundform und eine Lagerbohrung aufweisen. Der Innenring ist dabei aus zwei Halbringen zusammengesetzt, die in Umfangsrichtung auf die Lagerkörper aufgeschoben wurden. Ein derartiger Leitschaufelkranz bietet insbesondere die Vorteile einer einfachen Montage.In the EP 2 696 041 A1 an adjustable guide vane ring is proposed in which the guide vanes are each mounted in bearing bodies which have a cuboid basic shape and a bearing bore. The inner ring is composed of two half-rings, which were pushed onto the bearing body in the circumferential direction. Such a guide vane ring offers in particular the advantages of simple assembly.

Allerdings können infolge von Fertigungstoleranzen bzw. Vibrationen Rezirkulationen von Luft durch Spalte an den Randflächen der Lagerkörper auftreten. Dadurch wird der Wirkungsgrad der Strömungsmaschine gemindert.However, as a result of manufacturing tolerances or vibrations, recirculation of air through gaps on the edge surfaces of the bearing body can occur. This reduces the efficiency of the turbomachine.

Die vorliegende Erfindung hat die Aufgabe, eine Technik bereitzustellen, mit der die Vermeidung von Leckage unter Beibehaltung der einfachen Montage weiter verbessert werden kann.The present invention has the object of providing a technique with which the avoidance of leakage can be further improved while maintaining simple assembly.

Die Aufgabe wird gelöst durch eine Leitschaufelkranz für eine Strömungsmaschine gemäß Anspruch 1, durch eine Strömungsmaschine gemäß Anspruch 7 und ein Verfahren zur Montage eines Leitschaufelkranzes gemäß Anspruch 8. Vorteilhafte Ausführungsformen sind in den Unteransprüchen, der Beschreibung und den Figuren offenbart.The object is achieved by a guide vane ring for a turbo machine according to claim 1, by a turbo machine according to claim 7 and a method for assembling a guide vane ring according to claim 8. Advantageous embodiments are disclosed in the subclaims, the description and the figures.

Ein erfindungsgemäßer Leitschaufelkranz für eine Strömungsmaschine umfasst einen Innenring mit einer an seiner radial äußeren Oberfläche in Umfangsrichtung verlaufenden Aufnahmerinne, ferner eine Mehrzahl an Leitschaufeln und eine Mehrzahl an Lagerkörpern, die in der Aufnahmerinne des Innenrings angeordnet sind. Ein radial inneres Ende (beispielsweise ein Lagerungselement wie insbesondere ein Lagerzapfen) der Leitschaufeln ist dabei jeweils in einen Lagerkörper (bzw. in eine darin befindliche Bohrung) eingesteckt. Darüber hinaus umfasst der Leitschaufelkranz mindestens ein mindestens teilweise aus Blech bestehendes Dichtungselement zur Abdichtung wenigstens eines Spalts zwischen dem Innenring und mindestens einem der Lagerkörper und/oder zwischen zwei Lagerkörpern. Die Aufnahmerinne weist dabei an zwei einander zugewandten seitlichen Wandungen je mindestens eine Nut auf, in die ein Abschnitt eines jeweiligen Dichtungselements eingesteckt ist.A guide vane ring according to the invention for a turbomachine comprises an inner ring with a receiving groove running in the circumferential direction on its radially outer surface, furthermore a plurality of guide vanes and a plurality of bearing bodies which are arranged in the receiving groove of the inner ring. A radially inner end (for example a bearing element such as, in particular, a bearing journal) of the guide vanes is in each case inserted into a bearing body (or into a bore located therein). In addition, the guide vane ring comprises at least one sealing element consisting at least partially of sheet metal for sealing at least one gap between the inner ring and at least one of the bearing bodies and / or between two bearing bodies. The receiving channel has at least one groove on each of two mutually facing side walls into which a section of a respective sealing element is inserted.

Eine erfindungsgemäße Strömungsmaschine umfasst einen erfindungsgemäßen Leitschaufelkranz gemäß einer der in dieser Schrift offenbarten Ausführungsformen.A turbomachine according to the invention comprises a guide vane ring according to the invention in accordance with one of the embodiments disclosed in this document.

Ein erfindungsgemäßes Verfahren dient einer Montage eines Leitschaufelkranzes (insbesondere eines erfindungsgemäßen Leitschaufelkranzes gemäß einer der in dieser Schrift offenbarten Ausführungsformen). Es umfasst ein Auffädeln einer Mehrzahl an Lagerkörpern in die Aufnahmerinne eines Innenringsegments des Leitschaufelkranzes. In die Lagerkörper ist jeweils ein radial inneres Ende einer von mehreren Leitschaufeln des Leitschaufelkranzes eingesetzt. Ein Spalt zwischen einer seitlichen Wandung der Aufnahmerinne und wenigstens einem der Lagerkörper und/oder zwischen zwei Lagerkörpern wird durch mindestens ein Dichtungselement abgedichtet. Das Verfahren kann zudem (vor dem Auffädeln der Lagerkörper) ein Einsetzen der jeweiligen radial inneren Enden der Leitschaufeln in die Lagerkörper (bzw. darin angeordnete Bohrungen) umfassen. Vorzugsweise sind die Leitschaufeln beim Auffädeln der Lagerkörper an ihren radial äußeren Enden (z.B. mit einem jeweiligen Verstellzapfen) in jeweilige gehäuseseitige Lagerungen eingesetzt.A method according to the invention is used to assemble a guide vane ring (in particular a guide vane ring according to the invention in accordance with one of the embodiments disclosed in this document). It comprises threading a plurality of bearing bodies into the Receiving groove of an inner ring segment of the guide vane ring. A radially inner end of one of several guide vanes of the guide vane ring is inserted into each of the bearing bodies. A gap between a side wall of the receiving channel and at least one of the bearing bodies and / or between two bearing bodies is sealed by at least one sealing element. The method can also include (before threading the bearing bodies) inserting the respective radially inner ends of the guide vanes into the bearing bodies (or bores arranged therein). When the bearing bodies are being threaded on, the guide vanes are preferably inserted at their radially outer ends (for example with a respective adjusting pin) into respective bearings on the housing side.

Ein erfindungsgemäßer Leitschaufelkranz, eine erfindungsgemäße Strömungsmaschine und ein erfindungsgemäßes Verfahren ermöglichen eine Abdichtung von Spalten am Innenring und damit eine deutliche Reduzierung von Leckage. Insbesondere kann eine Rezirkulation von Luft vermindert und so eine Erhöhung des Wirkungsgrades der Strömungsmaschine bewirkt werden. Infolge der zusätzlichen Reibung am Dichtungselement wirkt dieses zudem stabilisierend auf die Anordnung aus Innenring und Lagerkörpern.A guide vane ring according to the invention, a turbomachine according to the invention and a method according to the invention make it possible to seal gaps on the inner ring and thus to significantly reduce leakage. In particular, a recirculation of air can be reduced and thus an increase in the efficiency of the turbomachine can be brought about. As a result of the additional friction on the sealing element, this also has a stabilizing effect on the arrangement of the inner ring and bearing bodies.

Die radial inneren Enden der Leitschaufeln können in einen jeweils eigenen, zugeordneten Lagerkörper eingesteckt sein bzw. werden, und/oder der Leitschaufelkranz kann Leitschaufeln umfassen, deren radial innere Enden in einen gemeinsamen Lagerkörper eingesteckt sind bzw. werden (z.B. zu zweit, zu dritt oder mit mehr Leitschaufeln). Insbesondere kann der Leitschaufelkranz genauso viele Lagerkörper umfassen wie Leitschaufeln oder weniger Lagerkörper als Leitschaufeln.The radially inner ends of the guide vanes can be inserted into a separate, assigned bearing body, and / or the guide vane ring can comprise guide vanes, the radially inner ends of which are or will be inserted into a common bearing body (for example, in twos, threes or more with more guide vanes). In particular, the guide vane ring can comprise just as many bearing bodies as there are guide blades or fewer bearing bodies than guide blades.

Der Leitschaufelkranz kann insbesondere für eine Verdichterstufe der Strömungsmaschine vorgesehen sein.The guide vane ring can in particular be provided for a compressor stage of the turbomachine.

Das mindestens eine Dichtungselement besteht mindestens teilweise aus Blech. Dadurch kann eine hohe Haltbarkeit gewährleistet werden.The at least one sealing element consists at least partially of sheet metal. This ensures a high level of durability.

Vorzugsweise ist das mindestens eine Dichtungselement ist mindestens teilweise in einem jeweiligen Spalt angeordnet, den es abdichtet, und verengt und/oder überbrückt diesen damit. Die Aufnahmerinne weist an zwei einander zugewandten seitlichen Wandlungen jeweils wenigstens eine Nut auf, in die jeweils ein Abschnitt eines jeweiligen zugehörigen Dichtungselements eingesteckt ist bzw. wird.The at least one sealing element is preferably arranged at least partially in a respective gap which it seals, and thus narrows and / or bridges this gap. The receiving channel has at least one groove on two mutually facing lateral walls, into each of which a section of a respective associated sealing element is or will be inserted.

Analog kann (zusätzlich) mindestens einer der Lagerkörper wenigstens eine Nut aufweisen, in die ein Teil (also ein Abschnitt) des mindestens einen Dichtungselements eingesteckt ist bzw. wird.Analogously, at least one of the bearing bodies can (additionally) have at least one groove into which a part (that is to say a section) of the at least one sealing element is or will be inserted.

Ein derart in eine oder mehrere Nut(en) eingestecktes Dichtungselement ist besonders solide verankert, so dass es trotz der im Betrieb der Strömungsmaschine auftretenden Vibrationen fixiert bleibt, und es bewirkt eine besonders hohe Effektivität der Abdichtung.A sealing element inserted into one or more groove (s) in this way is particularly solidly anchored, so that it remains fixed in spite of the vibrations that occur during operation of the turbomachine, and it causes the seal to be particularly effective.

An einer Seite, die dem in eine jeweilige Nut eingesteckten Abschnitt bzw. Teil entgegengesetzt ist, kann das Dichtungselement frei in den Spalt ragen oder an eine(r) Oberfläche des jeweiligen Lagerkörpers bzw. an eine Seitenwandung der Aufnahmerinne anstoßen und/oder umgebogen werden.On one side opposite the section or part inserted into a respective groove, the sealing element can protrude freely into the gap or abut and / or be bent against a surface of the respective bearing body or a side wall of the receiving channel.

Alternativ kann das Dichtungselement an beiden Seiten in eine jeweilige Nut eingesteckt sein (beispielsweise eingezogen worden sein): Insbesondere vorteilhaft ist eine Variante der vorliegenden Erfindung, bei der ein Spalt zwischen einer seitlichen Wandung der Aufnahmerinne und mindestens einem Lagerkörper durch das mindestens eine Dichtungselement überbrückt wird. Beispielsweise können sowohl die seitliche Wandung der Aufnahmerinne als auch mindestens einer der Lagerkörper jeweils eine Nut aufweisen, und das mindestens eine Dichtungselements kann (entsprechend einer Nut-Feder-Verbindung) an einer Seite in die Nut der seitlichen Wandung der Aufnahmerinne und an einer gegenüberliegenden Seite in die Nut des mindestens einen Lagerkörpers eingesteckt sein bzw. werden.Alternatively, the sealing element can be inserted (for example drawn in) into a respective groove on both sides: A variant of the present invention is particularly advantageous in which a gap between a side wall of the receiving channel and at least one bearing body is bridged by the at least one sealing element . For example, both the side wall of the receiving channel and at least one of the bearing bodies can each have a groove, and the at least one sealing element can (corresponding to a tongue and groove connection) on one side in the groove of the side wall of the receiving channel and on an opposite side be or will be inserted into the groove of the at least one bearing body.

Eine bevorzugte Ausführungsvariante eines erfindungsgemäßen Verfahrens umfasst ein Einsetzen des mindestens einen Dichtungselements in eine in wenigstens einem Lagerkörper angeordnete Nut, bevor der Lagerkörper in die Aufnahmerinne aufgefädelt wird. Dabei kann das Dichtungselement beim Auffädeln in eine vorzugsweise in einer seitlichen Wandung der Aufnahmerinne vorhandene Nut eingezogen werden oder an der seitlichen Wandung anstoßen oder umgebogen werden.A preferred embodiment variant of a method according to the invention comprises inserting the at least one sealing element into a groove arranged in at least one bearing body before the bearing body is threaded into the receiving channel. In this case, the sealing element can be drawn into a groove, which is preferably present in a side wall of the receiving channel, or can abut or be bent over against the side wall.

Gemäß einer bevorzugten Ausführungsform der vorliegenden Erfindung weisen mindestens zwei in Umfangsrichtung hintereinander angeordnete Lagerkörper an ihren Kontaktflächen jeweils eine Nut auf, in die (entsprechend einer Nut-Feder-Verbindung) ein gemeinsames Dichtungselement an gegenüberliegenden Seiten eingesetzt ist bzw. wird. So kann das Dichtungselement einen Spalt zwischen den Lagerkörpern über dessen gesamte Längserstreckung oder teilweise, beispielsweise mindestens über die halbe Längserstreckung oder mindestens ein Drittel der Längserstreckung des Spaltes überbrücken.According to a preferred embodiment of the present invention, at least two bearing bodies arranged one behind the other in the circumferential direction each have a groove on their contact surfaces into which a common sealing element is or will be inserted on opposite sides (corresponding to a tongue and groove connection). Thus, the sealing element can bridge a gap between the bearing bodies over its entire longitudinal extension or partially, for example at least half the longitudinal extension or at least one third of the longitudinal extension of the gap.

Die Lagerkörper können vorzugsweise jeweils eine im Wesentlichen quaderförmige Grundform mit einer Bohrung für ein jeweiliges radial inneres Ende eine Leitschaufel aufweisen; an bzw. in der Grundform kann zudem ein Profil ausgebildet sein, beispielsweise in Form mindestens eines (insbesondere in axialer Richtung) erweiterten und/oder eines verengten Bereichs, z.B. mindestens einer Stufe, mindestens eines Stegs und/oder - wie oben erwähnt - mindestens einer Nut, mittels deren die Lagerkörper (beispielsweise formschlüssig) miteinander, mit dem Dichtungselement und/oder mit dem Innenring verbunden sein bzw. werden können. Die Lagerkörper können beispielsweise mindestens teilweise aus Kohlenstoff bestehen. Sie können metallfrei ausgebildet sein oder ein beschichtetes Metall umfassen.The bearing bodies can preferably each have an essentially cuboid basic shape with a bore for a respective radially inner end of a guide vane; A profile can also be formed on or in the basic shape, for example in the form of at least one (in particular in the axial direction) widened and / or narrowed area, for example at least one step, at least one web and / or - as mentioned above - at least one Groove, by means of which the bearing bodies can be or can be connected to one another (for example in a form-fitting manner) with the sealing element and / or with the inner ring. The bearing bodies can for example consist at least partially of carbon. They can be made metal-free or comprise a coated metal.

Gemäß einer vorteilhaften Ausführungsform der vorliegenden Erfindung umläuft das mindestens eine Dichtungselement in einer Nut des mindestens einen Lagerkörpers mindestens teilweise eine Bohrung, in die das radial innere Ende einer Leitschaufel eingesteckt ist. Bezogen auf eine zentrale Achse der Bohrung bzw. eine Längsachse der Leitschaufel kann bei jedem Dichtungselement dabei beispielsweise ein Mittelachsenwinkel von mindestens 90°, mindestens 120° oder sogar mindestens 150° umspannt bzw. umlaufen werden.According to an advantageous embodiment of the present invention, the at least one sealing element in a groove of the at least one bearing body at least partially surrounds a bore into which the radially inner end of a guide vane is inserted. In relation to a central axis of the bore or a longitudinal axis of the guide vane, for example a central axis angle of at least 90 °, at least 120 ° or even at least 150 ° can be spanned or revolved for each sealing element.

Insbesondere kann das Dichtungselement beispielsweise einen im Wesentlichen bogenförmigen Abschnitt mit einem derartigen Mittelachsenwinkel aufweisen. Dies ermöglicht zum einen eine einfach zu fertigende und solide Ausbildung des Dichtungselements derart, dass dieses sich ausgehend von einer seitlichen Wandung der Aufnahmerinne besonders weit in einen Spalt zwischen zwei in Umfangsrichtung hintereinander angeordneten Lagerkörpern hinein erstreckt, sodass eine besonders effektive Dichtung erreicht wird. Zum anderen verhindert die Bogenform, dass sich Lagerkörper und Dichtungselement in Umfangsrichtung gegeneinander verschieben. Das mindestens eine Dichtungselement kann aus einer Vielzahl an Einzelelementen bestehen, die in Umfangsrichtung hintereinander angeordnet sein bzw. werden können. Insbesondere kann die Vielzahl an Einzelelementen der Anzahl an Lagerkörpern entsprechen oder ein (vorzugsweise ganzzahliges) Vielfaches dieser Anzahl sein. Die Vielzahl an Einzelelementen kann durch die Lagerkörper miteinander verbunden sein bzw. werden, beispielsweise indem jedes Einzelelement in Nuten von mindestens zwei (in Umfangsrichtung hintereinander angeordneten) Lagerkörpern eingesteckt ist bzw. wird.In particular, the sealing element can, for example, have an essentially arcuate section with such a central axis angle. This enables, on the one hand, an easy-to-manufacture and solid design of the sealing element in such a way that, starting from a side wall of the receiving channel, it extends particularly far into a gap between two bearing bodies arranged one behind the other in the circumferential direction, so that a particularly effective seal is achieved. On the other hand, the arch shape prevents the bearing body and sealing element from shifting relative to one another in the circumferential direction. The at least one sealing element can consist of a multiplicity of individual elements which are or can be arranged one behind the other in the circumferential direction. In particular, the large number of individual elements can correspond to the number of bearing bodies or be a (preferably integer) multiple of this number. The multitude of individual elements can be or will be connected to one another by the bearing bodies, for example by inserting each individual element into grooves of at least two bearing bodies (arranged one behind the other in the circumferential direction).

Gemäß einer bevorzugten Ausführungsform ist das mindestens eine Dichtungselement als zusammenhängender (vorzugsweise einteilig bzw. monolithisch ausgebildeter) Teilring ausgebildet, beispielsweise als (in Umfangsrichtung geteilter) Ringsektor. Er kann dabei einen Mittelachsenwinkel des Innenrings von mindestens 90°, mindestens 120° oder mindestens 180° umspannen, die zentrale Achse des Innenrings also zu mindestens einem Viertel, mindestens einem Drittel bzw. mindestens zur Hälfte umlaufen. Insbesondere vorteilhaft ist eine Ausführungsform mit zwei als derartige Teilringe ausgebildeten Dichtungselementen, die an einander gegenüberliegenden Wandungen der Aufnahmerinne angeordnet sind bzw. werden.According to a preferred embodiment, the at least one sealing element is designed as a coherent (preferably one-piece or monolithically designed) partial ring, for example as a ring sector (divided in the circumferential direction). It can span a central axis angle of the inner ring of at least 90 °, at least 120 ° or at least 180 °, i.e. at least a quarter, at least a third or at least half of the central axis of the inner ring. An embodiment with two sealing elements designed as partial rings of this type, which are or will be arranged on mutually opposite walls of the receiving channel, is particularly advantageous.

Der Innenring kann wenigstens ein Dämpfungselement aufweisen, das in der Aufnahmerinne zwischen dem Innenring und der Mehrzahl an Lagerkörpern angeordnet sein bzw. werden kann. Das Dämpfungselement kann beispielsweise als Federelement ausgebildet und/oder dazu eingerichtet sein, die Lagerkörper und den Innenring in einem Abschnitt gegeneinander zu drücken. Auf diese Weise kann eine vibrationsresistente Fixierung auch des mindestens einen Dichtungselements verbessert werden. Ein derartiges Dämpfungselement kann mindestens teilweise aus Metall gebildet sein und/oder eine wellige Struktur aufweisen; die Wellen (bzw. deren Wellenfronten) einer derartigen Struktur können beispielsweise axial oder in Umfangsrichtung verlaufen.The inner ring can have at least one damping element which is or can be arranged in the receiving groove between the inner ring and the plurality of bearing bodies. The damping element can be designed, for example, as a spring element and / or designed to press the bearing body and the inner ring against one another in one section. In this way, a vibration-resistant fixing of the at least one sealing element can also be improved. Such a damping element can be formed at least partially from metal and / or have a wavy structure; the waves (or their wave fronts) of such a structure can run axially or in the circumferential direction, for example.

Im Folgenden werden bevorzugte Ausführungsbeispiele der Erfindung anhand einer Zeichnung näher erläutert. Es versteht sich, dass einzelne Elemente und Komponenten fakultativ sind und/oder auch anders kombiniert werden können als dargestellt.In the following, preferred exemplary embodiments of the invention are explained in more detail with reference to a drawing. It goes without saying that individual elements and components are optional and / or can also be combined differently than shown.

Es zeigt schematisch:

Figur 1:
einen Teil eines exemplarischen erfindungsgemäßen Leitschaufelkranzes in perspektivischer Darstellung.
It shows schematically:
Figure 1:
a part of an exemplary guide vane ring according to the invention in a perspective view.

In Figur 1 ist ein Teil eines verstellbaren Leitschaufelkranzes 1 gemäß einer Ausführungsform der vorliegenden Erfindung dargestellt; zum besseren Verständnis des Aufbaus sind dabei einzelne Elemente ungeachtet einer vorteilhaften Reihenfolge an Montageschritten weggelassen.In Figure 1 a portion of an adjustable guide vane ring 1 according to an embodiment of the present invention is shown; For a better understanding of the structure, individual elements are omitted regardless of an advantageous sequence of assembly steps.

Der Leitschaufelkranz 1 umfasst einen Innenring 10, der aus mehreren (z.B. zwei) Innenringsegmenten zusammengesetzt ist bzw. wird; in der Figur gezeigt ist lediglich ein Teil des Innenrings 10, nämlich ein Ende eines Innenringsegments, das eine Bohrung 14 zur Verbindung (mittels eines hindurchzuführenden, nicht dargestellten Stiftes) mit einem Ende eines anderen, nicht dargestellten Ringsegments aufweist. Das Innenringsegment weist an dem gezeigten Ende eine Eintrittsöffnung in eine in Umfangsrichtung U verlaufende Aufnahmerinne 11 für Lagerkörper 20 auf; bei der Montage können durch diese Eintrittsöffnung hindurch die Lagerkörper nacheinander auf das Innenringsegment (und damit auf den Innenring) aufgefädelt werden. Im in der Figur gezeigten Ausführungsbeispiel sind mehrere Lagerkörper bereits in der Aufnahmerinne aufgefädelt.The guide vane ring 1 comprises an inner ring 10, which is or will be composed of several (e.g. two) inner ring segments; Only part of the inner ring 10 is shown in the figure, namely one end of an inner ring segment which has a bore 14 for connection (by means of a pin, not shown, to be passed through) with one end of another ring segment, not shown. At the end shown, the inner ring segment has an inlet opening into a receiving channel 11 for bearing body 20 running in the circumferential direction U; During assembly, the bearing bodies can be threaded one after the other onto the inner ring segment (and thus onto the inner ring) through this inlet opening. In the embodiment shown in the figure, several bearing bodies are already threaded into the receiving channel.

Der Leitschaufelkranz 1 umfasst weiterhin eine Mehrzahl an Leitschaufeln 30, die jeweils mit ihrem radial inneren Ende 32 (das vorzugsweise ein Lagerelement wie beispielsweise einen Lagerzapfen umfasst) in einen zugehörigen Lagerkörper 20 (d.h. in eine darin befindliche Bohrung 21) eingesteckt sind. Das jeweilige radial innere Ende der Leitschaufeln und/oder eine Oberfläche der Lagerkörper in der Bohrung können/kann zur Reduktion von Reibung und/oder Verschleiß beschichtet sein. In der Figur ist der vorderste dargestellte Lagerkörper 20 zur Verdeutlichung unbestückt gezeigt, d.h. ohne ein eingestecktes Ende einer Leitschaufel.The guide vane ring 1 further comprises a plurality of guide vanes 30, each of which is inserted with its radially inner end 32 (which preferably comprises a bearing element such as a bearing journal) into an associated bearing body 20 (i.e. into a bore 21 located therein). The respective radially inner end of the guide vanes and / or a surface of the bearing body in the bore can / can be coated to reduce friction and / or wear. In the figure, the foremost bearing body 20 shown is shown unequipped for the sake of clarity, i.e. without an inserted end of a guide vane.

Die Leitschaufeln weisen jeweils ein Schaufelblatt 31 auf und können über einen Verstellzapfen 33 verschwenkt werden, der dazu eingerichtet ist, in entsprechende Aufnahmen eines (nicht dargestellten) Gehäuses eingesteckt zu werden.The guide vanes each have a vane blade 31 and can be pivoted via an adjusting pin 33 which is set up to be inserted into corresponding receptacles in a housing (not shown).

Lagerkörper 20 und Innenring 10 sind in dem in der Figur dargestellten Ausführungsbeispiel formschlüssig miteinander verbunden, und zwar vorliegend sowohl in axialer Richtung X als auch in radialer Richtung R. Dazu weist die Aufnahmerinne 11 einen in axialer Richtung X erweiterten Bereich 12 auf, in den ein entsprechender (in der Figur nicht sichtbarer) Vorsprung der Lagerkörper 20 jeweils eingesetzt ist.Bearing body 20 and inner ring 10 are positively connected to one another in the exemplary embodiment shown in the figure, namely in the present case both in the axial direction X and in the radial direction R. For this purpose, the receiving groove 11 has one in the axial direction X. enlarged area 12, in which a corresponding (not visible in the figure) projection of the bearing body 20 is inserted.

Der in der Figur dargestellte Leitschaufelkranz 1 umfasst zudem Dichtungselemente 40a, 40b, die einander gegenüber in jeweilige Nuten 15a, 15b in der seitlichen Wandung der Aufnahmerinne 11 eingesteckt sind. Zur Verdeutlichung ist ein zugehöriger Lagerkörper, in den einzugreifen die in der Figur sichtbaren Dichtungselemente 40a, 40b vorgesehen sind, nicht dargestellt. Ein derartiger Lagerkörper weist an seinen den seitlichen Wandungen der Aufnahmerinne 11 zugewandten Seiten jeweils Nuten auf, die dazu eingerichtet sind, die Dichtungselemente 40a, 40b aufzunehmen. Diese überbrücken dann jeweils einen Spalt zwischen den Wandungen der Aufnahmerinne 11 und dem Lagerkörper, und zwar vorliegend über die volle Längserstreckung des jeweiligen Spaltes.The guide vane ring 1 shown in the figure also comprises sealing elements 40a, 40b which are inserted opposite one another into respective grooves 15a, 15b in the side wall of the receiving channel 11. For the sake of clarity, an associated bearing body, into which the sealing elements 40a, 40b visible in the figure are intended to engage, is not shown. Such a bearing body has on its sides facing the side walls of the receiving channel 11 in each case grooves which are set up to receive the sealing elements 40a, 40b. These then each bridge a gap between the walls of the receiving channel 11 and the bearing body, in the present case over the full length of the respective gap.

Vorzugsweise sind die Dichtungselemente 40a, 40b jeweils als Ringsektoren (z.B. Halbringe) ausgebildet, die entlang der Aufnahmerinne die zentrale Achse des Innenrings 10 teilweise umlaufen und sich dabei (was in der Figur nicht sichtbar ist) in entsprechenden Nuten der gezeigten, in Umfangsrichtung U hintereinander angeordneten Lagerkörper 20 fortsetzen. Die Dichtungselemente 40a, 40b greifen damit in Nuten benachbarter Lagerkörper an deren Kontaktflächen (insbesondere an der Kontaktfläche 22 des in der Figur vordersten Lagerkörpers) ein und überbrücken damit auch einen Spalt zwischen in Umfangsrichtung hintereinander angeordneten Lagerkörpern. Im gezeigten Beispiel überbrücken die Dichtungselemente 40a, 40b zusammen dann mehr als 80% der Längserstreckung dieser Spalte.The sealing elements 40a, 40b are preferably each designed as ring sectors (e.g. half rings) which partially encircle the central axis of the inner ring 10 along the receiving groove and (which is not visible in the figure) in corresponding grooves of the shown, in the circumferential direction U one behind the other arranged bearing body 20 continue. The sealing elements 40a, 40b thus engage in grooves of adjacent bearing bodies on their contact surfaces (in particular on the contact surface 22 of the foremost bearing body in the figure) and thus also bridge a gap between bearing bodies arranged one behind the other in the circumferential direction. In the example shown, the sealing elements 40a, 40b together then bridge more than 80% of the longitudinal extent of this gap.

In der Figur sind die Dichtungselemente 40a, 40b zur besseren Übersicht als bündig mit dem Ende des gezeigten Innenringsegments abschließend dargestellt. Gemäß einer vorteilhaften (nicht dargestellten) Ausführungsform ragen die Dichtungselemente über eine Verbindung von Innenringsegmenten hinaus, überbrücken also diese Verbindung. Alternativ oder zusätzlich kann ein Lagerkörper so angeordnet sein, dass er die genannte Verbindung überbrückt (was ebenfalls nicht in der Figur dargestellt ist), indem er zu einem Teil in die Aufnahmerinne eines ersten Innenringsegments und zum Teil in die Aufnahmerinne eines zweiten Innenringsegments eingesetzt ist. Dadurch kann jeweils eine Leckage an der Verbindung der Innenringsegmente vermindert werden.In the figure, the sealing elements 40a, 40b are shown as flush with the end of the inner ring segment shown for a better overview. According to an advantageous embodiment (not shown), the sealing elements protrude beyond a connection of inner ring segments, that is to say bridge this connection. Alternatively or additionally, a bearing body can be arranged in such a way that it bridges the mentioned connection (which is also not shown in the figure) by being inserted partly into the receiving groove of a first inner ring segment and partly into the receiving groove of a second inner ring segment. In this way, leakage at the connection of the inner ring segments can be reduced in each case.

Die Dichtungselemente 40a, 40b weisen jeweils einen bogenförmigen Abschnitt auf, der dazu eingerichtet ist, in einer entsprechenden Nut eines Lagerkörpers 20 eine darin angeordnete Bohrung 21 teilweise zu umlaufen, in die das radial innere Ende einer jeweiligen Leitschaufel eingesetzt ist; im gezeigten Beispiel umspannt jedes der Dichtungselemente 40a, 40b dabei einen Mittelachsenwinkel um eine Längsachse der jeweiligen Leitschaufel, der mehr als 120° beträgt. Dadurch kann - trotz der vorhandenen Bohrung - ein besonders tiefes Eingreifen des Dichtungselements in den jeweiligen Lagerkörper 20 realisiert werden. Darüber hinaus verhindert die Bogenform, dass sich Lagerkörper und Dichtungselement in Umfangsrichtung gegeneinander verschieben.The sealing elements 40a, 40b each have an arcuate section which is designed to partially encircle a bore 21 arranged therein in a corresponding groove of a bearing body 20, into which the radially inner end of a respective guide vane is inserted; In the example shown, each of the sealing elements 40a, 40b spans a central axis angle around a longitudinal axis of the respective guide vane which is more than 120 °. In this way, despite the existing bore, the sealing element can engage particularly deeply in the respective bearing body 20. In addition, the arch shape prevents the bearing body and sealing element from shifting relative to one another in the circumferential direction.

Der Leitschaufelkranz 1 umfasst weiterhin ein Dämpfungselement 50, das an einem (radial innen liegenden) Boden der Aufnahmerinne 11 zwischen dem Innenring 10 und den Lagerkörpern 20 angeordnet ist. Gemäß einem vorteilhaften Ausführungsbeispiel ist das Dämpfungselement 50 dazu eingerichtet, eine Verbindung des Innenringsegments mit einem anderen Innenringsegment zu überbrücken, so dass es also auch im anderen Innenringsegment als Dämpfungselement dienen kann.The guide vane ring 1 furthermore comprises a damping element 50 which is arranged on a (radially inner) bottom of the receiving channel 11 between the inner ring 10 and the bearing bodies 20. According to an advantageous embodiment, the damping element 50 is set up to bridge a connection between the inner ring segment and another inner ring segment, so that it can also serve as a damping element in the other inner ring segment.

Das Dämpfungselement 50 kann beispielsweise als ein Federelement ausgebildet sein (z.B. aus einem Metallblech), dessen Federkraft die Lagerkörper 20 in radialer Richtung R außen drückt. Im gezeigten Beispiel ist das Dämpfungselement als ein Streifen ausgebildet, der eine wellige Struktur aufweist, deren Wellenfronten in axialer Richtung X verlaufen.The damping element 50 can be designed, for example, as a spring element (e.g. made of sheet metal), the spring force of which presses the bearing body 20 in the radial direction R outward. In the example shown, the damping element is designed as a strip which has a wavy structure, the wavefronts of which run in the axial direction X.

Mittels des Dämpfungselements 50 können Relativbewegungen zwischen Innenring 10 und Leitschaufeln 30 gedämpft werden.By means of the damping element 50, relative movements between the inner ring 10 and the guide vanes 30 can be damped.

Überdies umfasst der Leitschaufelkranz 1 im gezeigten Ausführungsbeispiel eine (vorliegend als Einlaufbelag ausgebildete) Dichtung 60 zum Abdichten eines Radialspaltes zwischen Innenring und einem (nicht dargestellten) gegenüberliegenden Rotorabschnitt. Der Innenring 10 wirkt dabei als ein Dichtungsträger.In addition, in the exemplary embodiment shown, the guide vane ring 1 comprises a seal 60 (in the present case designed as an inlet coating) for sealing a radial gap between the inner ring and an opposite rotor section (not shown). The inner ring 10 acts as a seal carrier.

Ein erfindungsgemäßer Leitschaufelkranz 1 umfasst einen Innenring 10, an dessen radial äußerer Oberfläche eine Aufnahmerinne 11 in Umfangsrichtung U verläuft, eine Mehrzahl an Lagerkörpern 20, die in der Aufnahmerinne des Innenrings angeordnet sind, eine Mehrzahl an Leitschaufeln 30, die jeweils mit ihrem radial inneren Ende 32 in einen der Lagerkörper einsteckt sind, und mindestens ein Dichtungselement 40a, 40b zur Abdichtung wenigstens eines Spalts zwischen dem Innenring 10 und mindestens einem der Lagerkörper und/oder zwischen zwei Lagerkörpern.A guide vane ring 1 according to the invention comprises an inner ring 10, on the radially outer surface of which a receiving groove 11 runs in the circumferential direction U, a plurality of bearing bodies 20 which are arranged in the receiving groove of the inner ring, a plurality of guide vanes 30, each with its radially inner end 32 is inserted into one of the bearing bodies are, and at least one sealing element 40a, 40b for sealing at least one gap between the inner ring 10 and at least one of the bearing bodies and / or between two bearing bodies.

Eine erfindungsgemäße Strömungsmaschine umfasst einen erfindungsgemäßen Leitschaufelkranz 1. Ein erfindungsgemäßes Verfahren dient einer Montage eines Leitschaufelkranzes 1.A turbomachine according to the invention comprises a guide vane ring 1 according to the invention. A method according to the invention is used to assemble a guide vane ring 1.

BezugszeichenReference number

11
LeitschaufelkranzGuide vane ring
1010
InnenringInner ring
1111
AufnahmerinneReceiving channel
1212th
erweiterter Bereich der Aufnahmerinneenlarged area of the receiving channel
1414th
Bohrung zur Verbindung von RingsegmentenHole for connecting ring segments
15a, 15b15a, 15b
Nut in seitlicher Wandung der AufnahmerinneGroove in the side wall of the receiving channel
2020th
LagerkörperBearing body
2121
Bohrungdrilling
2222nd
KontaktflächeContact area
3030th
Leitschaufelvane
3131
SchaufelblattShovel blade
3232
radial inneres Ende der Leitschaufelradially inner end of the guide vane
3333
VerstellzapfenAdjustment pin
40a, 40b40a, 40b
DichtungselementSealing element
5050
DämpfungselementDamping element
6060
Dichtungpoetry
RR.
radiale Richtungradial direction
UU
UmfangsrichtungCircumferential direction
XX
axiale Richtungaxial direction

Claims (10)

  1. Guide vane ring (1)for a turbomachine, comprising:
    an inner ring (10), on the radially outer surface of which a receiving channel (11) extends in the circumferential direction (U);
    a plurality of bearing bodies (20) which are arranged in the receiving channel of the inner ring;
    a plurality of guide vanes (30), each of which is inserted at the radially inner end (32) thereof into one of the bearing bodies; and
    at least one sealing element (40a, 40b) for sealing at least one gap between the inner ring (10) and at least one of the bearing bodies and/or between two bearing bodies, characterized in that the receiving channel has at least one groove (15a, 15b) in each case on two mutually facing lateral walls, into which groove a portion of a relevant sealing element (40a, 40b) is inserted, the at least one sealing element (40a, 40b) consisting at least partially of sheet metal.
  2. Guide vane ring according to any of the preceding claims, wherein at least one of the bearing bodies (20) has a groove into which a part of the at least one sealing element (40a, 40b) is inserted.
  3. Guide vane ring according to claim 2, wherein the at least one sealing element in the groove of the at least one bearing body at least partially surrounds a bore (21) of the bearing body, into which the radially inner end (32) of a guide vane is inserted.
  4. Guide vane ring according to any of the preceding claims, wherein the at least one sealing element (40a, 40b) bridges at least one gap between two bearing bodies.
  5. Guide vane ring according to any of the preceding claims, wherein the at least one sealing element (40a, 40b) is designed as a contiguous partial ring which spans a central axis angle of at least 90°, at least 120° or at least 180°.
  6. Guide vane ring according to any of the preceding claims, wherein the at least one sealing element consists of a large number of individual elements which are arranged one behind the other in the circumferential direction (U).
  7. Turbomachine comprising at least one guide vane ring (1) according to any of claims 1 to 6.
  8. Method for assembling a guide vane ring (1), comprising:
    threading a plurality of bearing bodies (20), into each of which a radially inner end (32) of a guide vane (30) is inserted, in a receiving channel (11)of an inner ring segment (10) of the guide vane ring, wherein a gap between a lateral wall of the receiving channel and at least one of the bearing bodies (20) and/or between two bearing bodies arranged one behind the other in the circumferential direction (U) is sealed by at least one sealing element (40a, 40b).
  9. Method according to claim 8, which also comprises inserting the at least one sealing element (40a, 40b) into a groove in the at least one bearing body before said bearing body is threaded in the receiving channel.
  10. Method according to either claim 8 or claim 9, wherein the at least one sealing element (40a, 40b) is drawn into a groove (15a, 15b) in a lateral wall of the receiving channel.
EP17162630.2A 2017-03-23 2017-03-23 Seal on the inner ring of a guide blade assembly Active EP3379037B1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP17162630.2A EP3379037B1 (en) 2017-03-23 2017-03-23 Seal on the inner ring of a guide blade assembly
US15/933,410 US10494944B2 (en) 2017-03-23 2018-03-23 Seal on the inner ring of a guide vane

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP17162630.2A EP3379037B1 (en) 2017-03-23 2017-03-23 Seal on the inner ring of a guide blade assembly

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EP3379037A1 EP3379037A1 (en) 2018-09-26
EP3379037B1 true EP3379037B1 (en) 2021-06-02

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US (1) US10494944B2 (en)
EP (1) EP3379037B1 (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11359509B1 (en) * 2020-11-23 2022-06-14 Pratt & Whitney Canada Corp. Variable guide vane assembly with bushing ring and biasing member
DE102021120384A1 (en) 2021-08-05 2023-02-09 MTU Aero Engines AG Guide vane ring for a turbomachine, turbomachine and method for assembling a guide vane ring
US12078071B1 (en) 2023-02-21 2024-09-03 Rolls-Royce Corporation Segmented compressor inner band for variable vanes in gas turbine engines
US11879480B1 (en) 2023-04-07 2024-01-23 Rolls-Royce North American Technologies Inc. Sectioned compressor inner band for variable pitch vane assemblies in gas turbine engines

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB749577A (en) * 1952-07-10 1956-05-30 Havilland Engine Co Ltd Improvements in or relating to blade ring assemblies for axial flow compressors or turbines
US4395195A (en) * 1980-05-16 1983-07-26 United Technologies Corporation Shroud ring for use in a gas turbine engine
US6682299B2 (en) * 2001-11-15 2004-01-27 General Electric Company Variable stator vane support arrangement
EP2696041B1 (en) 2012-08-07 2020-01-22 MTU Aero Engines AG Guide blade assembly of a gas turbine and assembly method
EP2725200B1 (en) * 2012-10-25 2018-06-06 MTU Aero Engines AG Guide blade assembly and fluid flow engine
EP3315728B1 (en) * 2016-10-26 2022-01-12 MTU Aero Engines AG Damped guide vane bearing

Non-Patent Citations (1)

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Title
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Publication number Publication date
EP3379037A1 (en) 2018-09-26
US20180274380A1 (en) 2018-09-27
US10494944B2 (en) 2019-12-03

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