EP0203287A1 - Vibration-absorbing element for the vanes of turbo machines - Google Patents

Vibration-absorbing element for the vanes of turbo machines Download PDF

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Publication number
EP0203287A1
EP0203287A1 EP86103322A EP86103322A EP0203287A1 EP 0203287 A1 EP0203287 A1 EP 0203287A1 EP 86103322 A EP86103322 A EP 86103322A EP 86103322 A EP86103322 A EP 86103322A EP 0203287 A1 EP0203287 A1 EP 0203287A1
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EP
European Patent Office
Prior art keywords
blades
supports
blade
rotor
damping element
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Granted
Application number
EP86103322A
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German (de)
French (fr)
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EP0203287B1 (en
Inventor
Josef Bättig
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BBC Brown Boveri AG Switzerland
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BBC Brown Boveri AG Switzerland
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/16—Form or construction for counteracting blade vibration
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/50—Vibration damping features

Definitions

  • the invention relates to a damping element for free-standing blades of a turbomachine, in which the rotor blades fastened in the rotor are connected to one another, preferably in the radially outer region.
  • Freestanding blades both from axially flowed turbines and from radially flowed compressors or turbines, are - at risk of vibration.
  • the individual blade of such turbomachines carries out natural vibrations which depend on the type of vibration to which it is exposed; Tangential bend, axial bend or torsion.
  • the invention is therefore based on the object of providing a suitable, easily installed damping system for all types of free-standing blades.
  • connection between two blades consists of an elastically deformable plate which is curved toward the rotor center and which is latched into anchorages on the suction side of one and on the pressure side of a second adjacent blade.
  • the advantage of the new measure in addition to the extraordinary simplicity, is to be seen in particular in the fact that the curved plates can be made relatively thin and thus have little impact on the flow, since the lateral stresses reduce the bending stresses.
  • the weakening of the blade cross-section is significantly less if the plates are anchored in recesses in the blade.
  • the plates are preformed with a double curvature. On the one hand, this simplifies the geometry of the anchoring in the blades and, on the other hand, maintains - the platelets a perfect guidance both through their overlying underside and through the almost play-free top side. Even with a pure two-point support, they cannot tip out of the anchorages.
  • the plates are oval and have two circular supports on their narrow sides.
  • This type of support allows axial assembly, in which the plates can only be deformed very little elastically before they snap into the corresponding receptacles in the blades.
  • this type of installation also enables relatively deep recesses in the bucket walls.
  • the platelets are essentially triangular and are therefore equipped with three supports, preferably one of the supports on the suction side and the two further supports on the pressure side of the blades, then a stable position is achieved due to the only three pressure points. If, moreover, seen in the axial direction, the support on the suction side of the blade is arranged between the two supports on the pressure side, then in the case of twisted blades the plates prevent the blades from unwinding during operation.
  • FIG. 1 The blading partially shown in FIG. 1 is that of a one-piece turbine impeller of an exhaust gas turbocharger.
  • the impeller consists essentially of the turbine disc 1, the twisted blades 2 integrated with it and the damping elements clamped between the blades, which are designed as plates 3. Because of the prevailing centrifugal force and temperature conditions, these platelets are made from a nickel-based alloy, for example from the material known under the brand name Nymonic 90. According to FIG. 2, they are oval, which also means elliptical-like shapes or rectangles with rounded, narrow sides. With their semi-circular supports 4 on both sides, they lie in correspondingly shaped recesses 5, 6 on the one hand in the suction side 2 'of a first blade, on the other hand in the pressure side 2 "of a second adjacent blade. The recesses can be machined out of the blades or, as in the present case can be cast by integral wheels directly with the impeller.
  • the plates preformed during production have a double curvature and are mounted in such a way that the curvature belly is directed towards the center of the turbine disk 1 (FIG. 1, FIG. 3).
  • the procedure for assembling the platelet is as follows: 'In the axial direction, the platelet is inserted between the inlet profiles of two adjacent blades, brought into abutment in the recess 5 on the suction side 2' and then pivoted into the recess 6 on the pressure side 2 " The recesses 5 and 6 are completely filled, so that the flow-limiting walls have no cavemen.
  • the required supporting force during operation results on the one hand from the assembly preload and on the other hand as a result of the elastic deformation of the plate and the blade (torsion). I.e. the blade is thereby subjected to torsion.
  • FIG. 4 and 5 show anchorages as they are possible when using simply curved plates 3 '.
  • the anchorage according to FIG. 4 is carried out in a not very deep recess 7 attached to the airfoil, while according to FIG. 5 the plate 3 'is supported on the underside of a nose 8 cast onto the airfoil.
  • Both solutions are suitable for assembly in the radial direction, in which the plates 3 'are elastically deformed when pressed in between the blades and then snap into the associated anchoring.
  • the centrifugal force has a caulking effect during operation, so that the platelets cannot detach from the respective anchoring.
  • Platelets of simple curvature and corresponding anchors can advantageously be used in the variant shown in FIG. 6.
  • the plate 3 'here has essentially a triangular shape with the three supports 4a, 4b and 4c.
  • the support 4a is supported on the suction side of the blade in the recess 7a; the supports 4b and 4c are anchored in the recesses 7b and 7c on the pressure side of the adjacent blade.
  • the connection 4a / 7a lies between the two connections 4b / 7b and 4c / 7c, which results in the advantage already mentioned that blade torsion due to centrifugal force is prevented.
  • every second plate could be arranged on a smaller or larger radius.
  • the pressure-side and suction-side recesses of a blade would then no longer be in the same radial blade plane and would therefore have an even less weakening of the cross-section.
  • the new measure can also be used in the inlet section of radial compressor wheels, where it can replace the complex, zigzag-shaped damper wires or, if necessary, the even more complex cover disk binding.

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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)
  • Gears, Cams (AREA)
  • Supercharger (AREA)

Abstract

Bei einem Dämpfungselement für freistehende Schaufeln einer Turbomaschine, bei der die im Rotor befestigten Laufschaufeln (2) untereinander vorzugsweise im radial äusseren Bereich miteinander verbunden sind, besteht die Verbindung zwischen zwei Schaufeln aus einem zum Rotorzentrum hin gekrümmten, elastisch verformbaren Plättchen (3), welches in Verankerungen (5, 6) an der Saugseite (2') der einen und an der Druckseite (2") einer zweiten benachbarten Schaufel einrastet. Die schaufelseitigen Verankerungselemente können entweder Ausnehmungen (5, 6) oder vorspringende Nasen sein, in oder an denen sich die Plättchen abstützen.In the case of a damping element for free-standing blades of a turbomachine, in which the rotor blades (2) fastened in the rotor are preferably interconnected in the radially outer area, the connection between two blades consists of an elastically deformable plate (3) which is curved towards the rotor center and which engages in anchors (5, 6) on the suction side (2 ') of one and on the pressure side (2 ") of a second adjacent blade. The blade-side anchoring elements can either be recesses (5, 6) or projecting lugs, in or on which the plates are supported.

Description

Die Erfindung betrifft ein Dämpfungselement für freistehende Schaufeln einer Turbomaschine, bei der die im Rotor befestigten Laufschaufeln untereinander vorzugsweise im radial äusseren Bereich miteinander verbunden sind.The invention relates to a damping element for free-standing blades of a turbomachine, in which the rotor blades fastened in the rotor are connected to one another, preferably in the radially outer region.

Freistehende Laufschaufeln sowohl von axial durchströmten Turbinen als auch von radial durchströmten Verdichtem oder Turbinen sind - schwingungsgefährdet. Im Betrieb führt die einzelne Schaufel von derartigen Turbomaschinen Eigenschwingungen aus, die von der Vibrationsart abhängen, der sie ausgesetzt ist; Tangentialbiegung, Axialbiegung oder Torsion.Freestanding blades, both from axially flowed turbines and from radially flowed compressors or turbines, are - at risk of vibration. In operation, the individual blade of such turbomachines carries out natural vibrations which depend on the type of vibration to which it is exposed; Tangential bend, axial bend or torsion.

Bekannte Lösungen zur Schwingungsdämpfung reichen von der Bandagierung mehrerer Schaufeln zu einem Paket über die vollumschlossene Bindung mittels Deckbändem an den Schaufelspitzen oder festen Bindeelementen an den Schaufelblättem in deren radial äusseren Bereich bis hin zum tangentialen oder zickzackförmigen Einfädeln von Dämpferdrähten oder Einlöten von Bindedrähten.Known solutions for vibration damping range from bandaging several blades into a package, through fully enclosed binding by means of shrouds on the blade tips or fixed binding elements on the blade blades in their radially outer area, through to the tangential or zigzag-shaped threading of damper wires or soldering of binding wires.

Die meisten Lösungen scheiden indessen aus, wenn man eine schwingungsdämpfende Massnahme bei den heute mit sehr hohen Umfangsgeschwindigkeiten arbeitenden, sogenannten Integralturbinen von Abgasturboladem ergreifen will. Bisher konnten diese einstückigen Laufräder nur mit angegossenen Bindeelementen versehen werden. Letzteres ist indessen ausserordentlich schwierig und infolgedessen kostspielig in der Herstellung.Most solutions, however, are ruled out if you want to take a vibration-damping measure in the so-called integral turbines of exhaust gas turbochargers, which operate at very high peripheral speeds today. Until now, these one-piece impellers could only be equipped with cast-on binding elements. However, the latter is extremely difficult and consequently expensive to manufacture.

Der Erfindung liegt deshalb die Aufgabe zugrunde, für alle Arten von freistehenden Schaufeln ein geeignetes, einfach zu montierendes Dämpfungssystem zu schaffen.The invention is therefore based on the object of providing a suitable, easily installed damping system for all types of free-standing blades.

Erfindungsgemäss wird dies dadurch erreicht, dass die Verbindung zwischen zwei Schaufeln aus einem, zum Rotorzentrum hin gekrümmten, elastisch verformbaren Plättchen besteht, welches in Verankerungen an der Saugseite der einen und an der Druckseite einer zweiten benachbarten Schaufel eingerastet ist.According to the invention, this is achieved in that the connection between two blades consists of an elastically deformable plate which is curved toward the rotor center and which is latched into anchorages on the suction side of one and on the pressure side of a second adjacent blade.

Der Vorteil der neuen Massnahme ist neben der ausserordentlichen Einfachheit insbesondere darin zu sehen, dass die gekrümmten Plättchen relativ dünn und damit wenig strömungsbeinträchtigend ausgebildet werden können, da durch die seitlichen Stützkräfte die Biegespannungen verringert werden. Im Vergleich zu den durch Bohrungen eingefädelten Dämpferdrähten mit wesentlich grösserem Querschnitt ist die Schwächung des Schaufelquerschnitts, falls die Verankerung der Plättchen in Aussparungen im Schaufelblatt stattfindet, bedeutend geringer.The advantage of the new measure, in addition to the extraordinary simplicity, is to be seen in particular in the fact that the curved plates can be made relatively thin and thus have little impact on the flow, since the lateral stresses reduce the bending stresses. Compared to the damper wires with a much larger cross-section threaded through bores, the weakening of the blade cross-section is significantly less if the plates are anchored in recesses in the blade.

Von Vorteil ist, wenn die Plättchen mit einer doppelten Krümmung vorgeformt sind. Zum einen vereinfacht sich dadurch die Geometrie der Verankerung in den Schaufeln, und zum andem erhalten - die Plättchen eine einwandfreie Führung sowohl durch ihre aufliegende Unterseite als auch durch die nahezu spielfreie Oberseite. Selbst bei einer reinen Zweipunktauflage können sie nicht aus den Verankerungen kippen.It is advantageous if the plates are preformed with a double curvature. On the one hand, this simplifies the geometry of the anchoring in the blades and, on the other hand, maintains - the platelets a perfect guidance both through their overlying underside and through the almost play-free top side. Even with a pure two-point support, they cannot tip out of the anchorages.

Es ist zweckmässig, wenn die Plättchen oval ausgebildet sind und an ihren Schmalseiten zwei kreisförmige Auflagen aufweisen. Diese Auflageart gestattet eine axiale Montage, bei welcher die Plättchen nur sehr wenig elastisch zu verformen sind, bevor sie in die entsprechenden Aufnahmen in den Schaufeln einrasten. Darüberhinaus ermöglicht diese Montageart auch verhältnismässig tiefe Aussparungen in den Schaufelwänden.It is expedient if the plates are oval and have two circular supports on their narrow sides. This type of support allows axial assembly, in which the plates can only be deformed very little elastically before they snap into the corresponding receptacles in the blades. In addition, this type of installation also enables relatively deep recesses in the bucket walls.

Sind die Plättchen im wesentlichen dreieckig ausgebildet und demzufolge mit drei Auflagem ausgerüstet, wobei vorzugsweise eines der Auflager an der Saugseite und die zwei weiteren Auflager an der Druckseite der Schaufeln angreifen, so wird damit infolge der nur drei Druckstellen eine stabile Lage erzielt. Wird darüberhinaus, in Axialrichtung gesehen, das Auflager an der Schaufelsaugseite zwischen den beiden Auflagem an der Druckseite angeordnet, so verhindern die Plättchen im Falle von verwundenen Schaufeln eine Entwindung der Schaufeln während des Betriebes.If the platelets are essentially triangular and are therefore equipped with three supports, preferably one of the supports on the suction side and the two further supports on the pressure side of the blades, then a stable position is achieved due to the only three pressure points. If, moreover, seen in the axial direction, the support on the suction side of the blade is arranged between the two supports on the pressure side, then in the case of twisted blades the plates prevent the blades from unwinding during operation.

In der Zeichnung sind mehrere Ausführungsbeispiele der Erfindung schematisch dargestellt. Es zeigen:

  • Fig. 1 eine Ansicht in Strömungsrichtung auf einen Segmentabschnitt eines Laufrades,
  • Fig. 2 einen Teilschnitt durch die Beschaufelung un mittelbar oberhalb einer ersten Ausführungsform von Därppfungselementen,
  • Fig. 3 bis Fig. 5 verschiedene Einspannvarianten für die Dämpfungselemente,
  • Fig. 6 einen Teilschnitt durch die Beschaufelung unmittelbar oberhalb einer zweiten Ausführungsform von Dämpfungselementen.
Several exemplary embodiments of the invention are shown schematically in the drawing. Show it:
  • 1 is a view in the flow direction of a segment section of an impeller,
  • 2 shows a partial section through the blading un directly above a first embodiment of damping elements,
  • 3 to 5 different clamping variants for the damping elements,
  • Fig. 6 is a partial section through the blading immediately above a second embodiment of damping elements.

In den Figuren sind nur die für das Verständnis der Erfindung erforderlichen Elemente dargestellt, wobei gleiche Elemente jeweils mit denselben Bezugszeichen versehen sind. Die in Fig. 1 teilweise dargestellte Beschaufelung sei jene eines einstückig hergestellten Turbinenlaufrades eines Abgasturboladers.In the figures, only the elements necessary for understanding the invention are shown, the same elements being provided with the same reference numerals. The blading partially shown in FIG. 1 is that of a one-piece turbine impeller of an exhaust gas turbocharger.

Das Laufrad besteht im wesentlichen aus der Turbinenscheibe 1, den mit dieser integrierten, verwundenen Laufschaufeln 2 und den zwischen den Schaufeln eingespannten Dämpfungselementen, welche als Plättchen 3 ausgebildet sind. Diese Plättchen sind aufgrund der herrschenden Fliehkraft-und Temperaturverhältnisse aus einer Nickel-Basis-Legierung gefertigt, beispielsweise aus dem unter dem Markennamen Nymonic 90 bekannten Material. Sie sind gemäss Fig. 2 oval, worunter auch ellipsenähnliche Formen oder Rechtecke mit abgerundeten schmalen Seiten verstanden werden. Mit ihren beidseitigen halbkreisförmigen Auflagen 4 liegen sie in entsprechend geformten Ausnehmungen 5, 6 einerseits in der Saugseite 2' einer ersten Schaufel, andererseits in der Druckseite 2" einer zweiten benachbarten Schaufel ein. Die Ausnehmungen können aus den Schaufeln herausgearbeitet sein oder wie im vorliegenden Fall von Integralrädern direkt mit dem Laufrad vergossen werden.The impeller consists essentially of the turbine disc 1, the twisted blades 2 integrated with it and the damping elements clamped between the blades, which are designed as plates 3. Because of the prevailing centrifugal force and temperature conditions, these platelets are made from a nickel-based alloy, for example from the material known under the brand name Nymonic 90. According to FIG. 2, they are oval, which also means elliptical-like shapes or rectangles with rounded, narrow sides. With their semi-circular supports 4 on both sides, they lie in correspondingly shaped recesses 5, 6 on the one hand in the suction side 2 'of a first blade, on the other hand in the pressure side 2 "of a second adjacent blade. The recesses can be machined out of the blades or, as in the present case can be cast by integral wheels directly with the impeller.

Die bei der Herstellung vorgeformten Plättchen weisen eine doppelte Krümmung auf und werden so montiert, dass der Krümmungsbauch gegen das Zentrum der Turbinenscheibe 1 gerichtet ist (Fig. 1, Fig. 3).The plates preformed during production have a double curvature and are mounted in such a way that the curvature belly is directed towards the center of the turbine disk 1 (FIG. 1, FIG. 3).

Anlässlich der Plättchenmontage wird wie folgt vorgegangen: ' In axialer Richtung wird das Plättchen zwischen die Eintrittsprofile zweier benachbarter Schaufeln eingeschoben, mit der Auflage in die Ausnehmung 5 auf der Saugseite 2' in Anschlag gebracht und dann in die Ausnehmung 6 auf der Druckseite 2" eingeschwenkt. Die Ausnehmungen 5 und 6 sind voll ausgefüllt, so dass die strömungsbegrenzenden Wandungen keinerlei Kavemen aufweisen.The procedure for assembling the platelet is as follows: 'In the axial direction, the platelet is inserted between the inlet profiles of two adjacent blades, brought into abutment in the recess 5 on the suction side 2' and then pivoted into the recess 6 on the pressure side 2 " The recesses 5 and 6 are completely filled, so that the flow-limiting walls have no cavemen.

Die erforderliche Stützkraft im Betrieb ergibt sich einerseits durch die Montagevorspannung und andererseits infolge der elastischen Deformation des Plättchens und der Schaufel (Torsion). D.h. die Schaufel wird dadurch auf Torsion beansprucht.The required supporting force during operation results on the one hand from the assembly preload and on the other hand as a result of the elastic deformation of the plate and the blade (torsion). I.e. the blade is thereby subjected to torsion.

Die Fig. 4 und 5 zeigen Verankerungen, wie sie möglich sind bei der Anwendung von einfach gekrümmten Plättchen 3'. Die Verankerung gemäss Fig. 4 wird in einer an den Schaufelblättem angebrachten, nicht sehr tiefgehenden Ausnehmung 7 vollzogen, während sich gemäss Fig. 5 das Plättchen 3' an der Unterseite einer am Schaufelblatt angegossenen Nase 8 abstützt. Beide Lösungen eignen sich für eine Montage in radialer Richtung, bei welcher die Plättchen 3' beim Einpressen zwischen die Schaufeln elastisch verformt werden und dann in die zugehörige Verankerung einrasten. Infolge der zum Rotorzentrum weisenden Plättchenkrümmung wirkt die Fliehkraft während des Betriebes verstemmend, so dass die Plättchen sich nicht aus der jeweiligen Verankerung herauslösen können.4 and 5 show anchorages as they are possible when using simply curved plates 3 '. The anchorage according to FIG. 4 is carried out in a not very deep recess 7 attached to the airfoil, while according to FIG. 5 the plate 3 'is supported on the underside of a nose 8 cast onto the airfoil. Both solutions are suitable for assembly in the radial direction, in which the plates 3 'are elastically deformed when pressed in between the blades and then snap into the associated anchoring. As a result of the curvature of the platelets pointing towards the rotor center, the centrifugal force has a caulking effect during operation, so that the platelets cannot detach from the respective anchoring.

Plättchen einfacher Krümmung und entsprechende Verankerungen können mit Vorteil bei der in Fig. 6 gezeigten Variante ihre Anwendung finden. Das Plättchen 3' weist hier im wesentlichen eine Dreiecksform auf mit den drei Auflagern 4a, 4b und 4c. Die Auflage 4a stützt sich an der Saugseite der Schaufel in der Ausnehmung 7a ab; die Auflagen 4b und 4c sind in den Ausnehmungen 7b und 7c auf der Druckseite der benachbarten Schaufel verankert. In Axialrichtung gesehen liegt die Verbindung 4a/7a zwischen den beiden Verbindungen 4b/7b und 4c/7c, woraus der bereits erwähnte Vorteil resultiert, dass eine Schaufeltorsion infolge Fliehkraft verhindert wird.Platelets of simple curvature and corresponding anchors can advantageously be used in the variant shown in FIG. 6. The plate 3 'here has essentially a triangular shape with the three supports 4a, 4b and 4c. The support 4a is supported on the suction side of the blade in the recess 7a; the supports 4b and 4c are anchored in the recesses 7b and 7c on the pressure side of the adjacent blade. Seen in the axial direction, the connection 4a / 7a lies between the two connections 4b / 7b and 4c / 7c, which results in the advantage already mentioned that blade torsion due to centrifugal force is prevented.

Selbstverständlich ist die Erfindung nicht auf die gezeigten und beschriebenen Ausführungsbeispiele beschränkt. In Abweichung zur kreisförmigen Bindung gemäss Fig. 1 könnte beispielsweise jedes zweite Plättchen auf einem kleineren oder grösseren Radius angeordnet sein. Die druck-und saugseitigen Ausnehmungen einer Schaufel befänden sich dann nicht mehr in der gleichen radialen Schaufelebene und würden damit noch weniger querschnittsschwächend wirken.Of course, the invention is not limited to the exemplary embodiments shown and described. In deviation from the circular bond according to FIG. 1, for example every second plate could be arranged on a smaller or larger radius. The pressure-side and suction-side recesses of a blade would then no longer be in the same radial blade plane and would therefore have an even less weakening of the cross-section.

Eine Anwendungsmöglichkeit für die neue Massnahme ist auch in der Einlaufpartie von Radialverdichterrädem gegeben, wo sie anstelle der aufwendigen, zickzackförmigen Dämpferdrähte oder ggfs. der noch aufwendigeren Deckscheibenbindung treten kann.The new measure can also be used in the inlet section of radial compressor wheels, where it can replace the complex, zigzag-shaped damper wires or, if necessary, the even more complex cover disk binding.

Claims (5)

1. Dämpfungselement für freistehende Schaufeln einer Turbomaschine, bei der die im Rotor (1) befestigten Laufschaufeln (2) untereinander vorzugsweise im radial äusseren Bereich miteinander verbunden sind, dadurch gekennzeichnet, dass die Verbindung zwischen zwei Schaufeln aus einem zum Rotorzentrum hin gekrümmten, elastisch verformbaren Plättchen (3, 3') besteht, welches in Verankerungen (5, 6, 7, 8) an der Saugseite (2') der einen und an der Druckseite (2") einer zweiten, benachbarten Schaufel eingerastet ist.1. Damping element for free-standing blades of a turbomachine, in which the rotor blades (1) fastened in the rotor (1) are interconnected, preferably in the radially outer region, characterized in that the connection between two blades from an elastically deformable one toward the rotor center Small plate (3, 3 '), which is engaged in anchors (5, 6, 7, 8) on the suction side (2') of one and on the pressure side (2 ") of a second, adjacent blade. 2. Dämpfungselement nach Anspruch 1, dadurch gekennzeichnet, dass das Plättchen (3) doppelt gekrümmt ist.2. Damping element according to claim 1, characterized characterized in that the plate (3) is double curved. 3. Dämpfungselement nach Anspruch 1, dadurch gekennzeichnet, dass das Plättchen (3) oval ist und zwei kreisförmige Auflager (4) aufweist.3. Damping element according to claim 1, characterized in that the plate (3) is oval and has two circular supports (4). 4. Dämpfungselement nach Anspruch 1, dadurch gekennzeichnet, dass das Ptättchen (3') im wesentlichen Dreiecksform mit drei Auflagem (4a -4c) aufweist, wobei eines der Auflager (4a) an der Saugseite (2') und die zwei weiteren Auflager (4b, 4c) an der Druckseite (2") der Schaufeln (2) angreifen.4. Damping element according to claim 1, characterized in that the platelet (3 ') has a substantially triangular shape with three supports (4a -4c), one of the supports (4a) on the suction side (2') and the two further supports ( 4b, 4c) on the pressure side (2 ") of the blades (2). 5. Dämpfungselement nach Anspruch 4, dadurch gekennzeichnet, dass in Axialrichtung gesehen das Auflager (4a) an der Schaufelsaugseite (2') zwischen den beiden Auflagern (4b, 4c) an der Druckseite (2") angeordnet ist.5. Damping element according to claim 4, characterized in that seen in the axial direction, the support (4a) on the blade suction side (2 ') between the two supports (4b, 4c) on the pressure side (2 ") is arranged.
EP86103322A 1985-05-31 1986-03-12 Vibration-absorbing element for the vanes of turbo machines Expired EP0203287B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH2309/85A CH667493A5 (en) 1985-05-31 1985-05-31 DAMPING ELEMENT FOR DETACHED TURBO MACHINE BLADES.
CH2309/85 1985-05-31

Publications (2)

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EP0203287A1 true EP0203287A1 (en) 1986-12-03
EP0203287B1 EP0203287B1 (en) 1989-06-07

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EP86103322A Expired EP0203287B1 (en) 1985-05-31 1986-03-12 Vibration-absorbing element for the vanes of turbo machines

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US (1) US4734010A (en)
EP (1) EP0203287B1 (en)
JP (1) JPS61277802A (en)
KR (1) KR910003259B1 (en)
CN (1) CN1003464B (en)
CH (1) CH667493A5 (en)
DE (1) DE3663837D1 (en)
IN (1) IN167278B (en)
SU (1) SU1477253A3 (en)

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GB2251897A (en) * 1991-01-15 1992-07-22 Rolls Royce Plc Bladed rotor
GB2441543A (en) * 2006-09-07 2008-03-12 Rolls Royce Plc A bridging element for reducing vibrations in an array of elongate components
WO2011081761A1 (en) * 2009-12-14 2011-07-07 Siemens Energy, Inc. Turbine blade damping device with controlled loading
WO2017184138A1 (en) * 2016-04-21 2017-10-26 Siemens Aktiengesellschaft Preloaded snubber assembly for turbine blades
WO2018157958A1 (en) * 2017-03-01 2018-09-07 Siemens Aktiengesellschaft Turbine stage having a coupling element

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US5201850A (en) * 1991-02-15 1993-04-13 General Electric Company Rotor tip shroud damper including damper wires
US5460488A (en) * 1994-06-14 1995-10-24 United Technologies Corporation Shrouded fan blade for a turbine engine
EP1557534A1 (en) * 2004-01-20 2005-07-27 Siemens Aktiengesellschaft Turbine blade and gas turbine with such a turbine blade
US7758311B2 (en) * 2006-10-12 2010-07-20 General Electric Company Part span shrouded fan blisk
JP2009007981A (en) * 2007-06-27 2009-01-15 Toshiba Corp Intermediate fixing and supporting structure for steam-turbine long moving blade train, and steam turbine
FR2922263B1 (en) * 2007-10-11 2009-12-11 Snecma TURBINE STATOR FOR AN AIRCRAFT TURBINE ENGINE INCORPORATING A VIBRATION DAMPING DEVICE
US8540488B2 (en) * 2009-12-14 2013-09-24 Siemens Energy, Inc. Turbine blade damping device with controlled loading
USRE45690E1 (en) 2009-12-14 2015-09-29 Siemens Energy, Inc. Turbine blade damping device with controlled loading
JP5558095B2 (en) * 2009-12-28 2014-07-23 株式会社東芝 Turbine blade cascade and steam turbine
US8398374B2 (en) * 2010-01-27 2013-03-19 General Electric Company Method and apparatus for a segmented turbine bucket assembly
US8790082B2 (en) * 2010-08-02 2014-07-29 Siemens Energy, Inc. Gas turbine blade with intra-span snubber
TWI418708B (en) * 2011-03-25 2013-12-11 Delta Electronics Inc Impeller structure
US9506353B2 (en) * 2012-12-19 2016-11-29 United Technologies Corporation Lightweight shrouded fan blade
US10465531B2 (en) 2013-02-21 2019-11-05 General Electric Company Turbine blade tip shroud and mid-span snubber with compound contact angle
CN103541459B (en) * 2013-11-08 2015-07-29 同济大学 A kind of mixing energy-eliminating shock-absorbing device
RU178381U1 (en) * 2017-08-16 2018-04-02 ФЕДЕРАЛЬНОЕ ГОСУДАРСТВЕННОЕ БЮДЖЕТНОЕ ОБРАЗОВАТЕЛЬНОЕ УЧРЕЖДЕНИЕ ВЫСШЕГО ОБРАЗОВАНИЯ "Брянский государственный технический университет" Shock absorber for damping vibrations of a stator of a turbojet engine
PT3604792T (en) 2018-08-03 2022-01-31 Ge Renewable Tech Pre-formed plug with inter-blade profiles for hydraulic turbines

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DE1161912B (en) * 1959-12-07 1964-01-30 Gen Electric Co Ltd Axial steam turbine impeller
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FR1363969A (en) * 1963-04-11 1964-06-19 Alsthom Cgee Turbine blade spacers

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Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2251897A (en) * 1991-01-15 1992-07-22 Rolls Royce Plc Bladed rotor
GB2251897B (en) * 1991-01-15 1994-11-30 Rolls Royce Plc A rotor
GB2441543A (en) * 2006-09-07 2008-03-12 Rolls Royce Plc A bridging element for reducing vibrations in an array of elongate components
GB2441543B (en) * 2006-09-07 2008-07-23 Rolls Royce Plc An array of components
WO2011081761A1 (en) * 2009-12-14 2011-07-07 Siemens Energy, Inc. Turbine blade damping device with controlled loading
US8616848B2 (en) 2009-12-14 2013-12-31 Siemens Energy, Inc. Turbine blade damping device with controlled loading
WO2017184138A1 (en) * 2016-04-21 2017-10-26 Siemens Aktiengesellschaft Preloaded snubber assembly for turbine blades
WO2018157958A1 (en) * 2017-03-01 2018-09-07 Siemens Aktiengesellschaft Turbine stage having a coupling element

Also Published As

Publication number Publication date
DE3663837D1 (en) 1989-07-13
JPS61277802A (en) 1986-12-08
CN86103683A (en) 1986-11-26
SU1477253A3 (en) 1989-04-30
US4734010A (en) 1988-03-29
CN1003464B (en) 1989-03-01
IN167278B (en) 1990-09-29
CH667493A5 (en) 1988-10-14
KR860009213A (en) 1986-12-20
EP0203287B1 (en) 1989-06-07
KR910003259B1 (en) 1991-05-25

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