EP1457642B1 - Device for fixing blades to the rotor - Google Patents

Device for fixing blades to the rotor Download PDF

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Publication number
EP1457642B1
EP1457642B1 EP04100742A EP04100742A EP1457642B1 EP 1457642 B1 EP1457642 B1 EP 1457642B1 EP 04100742 A EP04100742 A EP 04100742A EP 04100742 A EP04100742 A EP 04100742A EP 1457642 B1 EP1457642 B1 EP 1457642B1
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EP
European Patent Office
Prior art keywords
rotor
wedge
end piece
halves
installed state
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.)
Expired - Lifetime
Application number
EP04100742A
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German (de)
French (fr)
Other versions
EP1457642A3 (en
EP1457642A2 (en
Inventor
René Bachofner
Petra Fabijan
Wolfgang Kappis
Michael Müller
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General Electric Technology GmbH
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Alstom Technology AG
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Publication date
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Publication of EP1457642A2 publication Critical patent/EP1457642A2/en
Publication of EP1457642A3 publication Critical patent/EP1457642A3/en
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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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys

Definitions

  • the invention relates to the field of power plant technology. It relates to a rotor end for rotors of thermal turbomachinery according to the preamble of claim 1.
  • Thermal turbomachines such as turbines and compressors, consist essentially of a rotor-equipped rotor and a stator in which vanes are suspended.
  • the fixed guide vanes have the task of directing the flow of the gas to be compressed or to be relaxed to the rotating blade blading so that the energy conversion takes place with the best possible efficiency.
  • Both blades and vanes essentially comprise an airfoil and a blade root.
  • grooved in the stator and on the rotor shaft In these grooves, the feet of the blades are inserted and locked there.
  • a disadvantage of this prior art is that the wedge is due to the tilting moment of the two end halves, which is caused by the centrifugal force during operation, able to Anlagenbiegen the caulked lobes.
  • the wedge can thus fly out of the compressor and it can lead to a complete compressor damage.
  • the aim of the invention is to avoid the mentioned disadvantages of the prior art.
  • the invention is based on the object to develop a rotor-closing, which exerts no axial forces on the rotor, so that thereby an occurrence of axial forces caused by disturbing rotor vibrations is avoided.
  • this object is achieved in a rotor-end for rotors of thermal turbomachinery according to the preamble of claim 1, characterized in that the rotor-end is fixed in the axial direction of the two adjacent blades. Each of the two end halves of the rotor-end is fixed in the axial direction of the rotor, each with a connecting element on the two adjacent blades.
  • the connecting element may be formed straight or positive. If the end halves and adjacent blades form a positive assembly, this has the additional advantage that the adjacent blades do not pass through them from the tail end acting forces are screwed into the rotor, so that they do not jam in their thermal expansion.
  • the wedge has at its upper end two tabs which are separated from one another by a longitudinal slot and which are spread open when installed and in that the side surfaces of the end halves each have a recess in the upper region which, when installed, forms an approximately heart-shaped cavity, wherein the walls of this cavity are covered by the spread tabs of the wedge and the wedge is thereby firmly anchored in the end halves.
  • Spreading the wedge into the heart shape of the two end halves prevents the wedge from detaching from its anchorage during operation.
  • Fig. 1 shows a section through one of the Applicant known Rotor-End 1 after installation in a rotor. 2
  • the in Fig. 1 illustrated rotor end 1 consists of two end halves 4, 4 'with opposing side surfaces 5, 5' and a wedge 6, which at its upper, in the installed state of the rotor longitudinal axis end facing away from each other by a longitudinal slot 2 lobes 10, 10 ' having.
  • the side surfaces 5, 5 'of the end halves 4, 4' each have a recess in the upper region, which form a heart-shaped cavity 11 when installed, the walls of this cavity 11 of the spread tabs 10, 10 'of the caulked wedge. 6 are covered and the wedge 6 in this way form-fitting firmly anchored in the heart-shaped cavity 11.
  • the rotor end 1 or the end halves 4, 4 ' are supported on the rotor in the axial direction.
  • FIG. 2 is a plan view of a schematically illustrated inventive rotor-end 1 after installation with straight connecting elements 8, 8 ', 9, 9' shown. Not shown is the caulked wedge, which finally fills the remaining opening of the circumferential groove 3.
  • Each of the two end halves 4, 4 ' is in the axial direction of the rotor 2, each with a connecting element 8, 8', 9, 9 'on the two adjacent blades 7, 7' (also called final blades), namely at the blade roots , attached.
  • These four connecting elements 8, 8 ', 9, 9' now take the axial forces F instead of the rotor 2, which are caused by the centrifugal force and the caulked wedge. In this way, no axial forces on the rotor and disturbing rotor vibrations are avoided.
  • This form-fitting connection of the closing pieces and the adjacent blades is referred to as the closing package.
  • FIG. 4 another embodiment is shown.
  • the figure shows a final package, consisting of the two end halves 4, 4 ', the between the end halves located caulked wedge 6 and the two tail blades 7, 7 '.
  • the solution according to the invention is suitable for all blade rows in the circumferential groove. It is advantageously used whenever the rotor reacts sensitively to axial forces and thus disturbing vibrations can occur.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Shearing Machines (AREA)
  • Preliminary Treatment Of Fibers (AREA)
  • Treatment Of Fiber Materials (AREA)

Abstract

A rotor locking mechanism fits in a rotor's axial direction between first (7) and second (7') rotating blades. First (4) and second (4') locking halves each fasten on both adjacent rotating blades with first (8), second (8'), third (9) and fourth (9') clips in the rotor's axial direction.

Description

Technisches GebietTechnical area

Die Erfindung bezieht sich auf das Gebiet der Kraftwerkstechnik. Sie betrifft einen Rotor-Schluss für Rotoren thermischer Turbomaschinen gemäss dem Oberbegriff des Patentanspruches 1.The invention relates to the field of power plant technology. It relates to a rotor end for rotors of thermal turbomachinery according to the preamble of claim 1.

Stand der TechnikState of the art

Thermische Turbomaschinen, wie Turbinen und Verdichter, bestehen im wesentlichen aus einem mit Laufschaufeln bestückten Rotor und einem Stator, in den Leitschaufeln eingehängt sind.Thermal turbomachines, such as turbines and compressors, consist essentially of a rotor-equipped rotor and a stator in which vanes are suspended.

Die feststehenden Leitschaufeln haben die Aufgabe, den Strom des zu verdichtenden bzw. des zu entspannenden gasförmigen Mediums so auf die rotierende Laufbeschaufelung zu lenken, dass die Energieumwandlung mit bestmöglichem Wirkungsgrad erfolgt.The fixed guide vanes have the task of directing the flow of the gas to be compressed or to be relaxed to the rotating blade blading so that the energy conversion takes place with the best possible efficiency.

Sowohl Laufschaufeln und als auch Leitschaufeln weisen im wesentlichen ein Schaufelblatt und einen Schaufelfuss auf. Um die Laufschaufeln auf dem Rotor bzw. die Leitschaufeln im Stator befestigen zu können, sind im Stator und auf der Rotorwelle Nuten eingestochen. In diese Nuten werden die Füsse der Schaufeln eingeschoben und dort arretiert.Both blades and vanes essentially comprise an airfoil and a blade root. In order to secure the blades on the rotor or the stator vanes in the stator, grooved in the stator and on the rotor shaft. In these grooves, the feet of the blades are inserted and locked there.

Es ist bekannt, dass die meisten Verdichterschaufelreihen von Gasturbinenrotoren in Umfangsnuten angeordnet sind. Bei der Montage solcher Schaufelreihen muss für die letzten zu montierenden Schaufeln eine spezielle Lösung gefunden werden, da dann die verbleibende Einfüllöffnung zu klein geworden ist. Diese Restöffnung wird mit einem sogenannten Rotor-Schluss aufgefüllt wird. Der Rotor-Schluss besteht aus einem halbierten Zwischenstück (zwei Schlusshälften), und einem Keil, mit Hilfe dessen die Schlusshälften im Rotor verstemmt werden. Der Rotor-Schluss stützt sich somit in axialer Richtung am Rotor ab. Die beiden Schlusshälften weisen bei diesem bekannten Stand der Technik jeweils eine gerade ausgebildete Seitenfläche auf, die an ihrem oberen Ende mit der oberen Deckfläche der Schlusshälfte einen überstehenden Lappen bildet. Die genannten Seitenflächen stehen sich im eingebauten Zustand gegenüber, wobei sich dann zwischen ihnen der Keil befindet. Nachdem die beiden Schlusshälften und der Keil eingebaut sind, werden abschliessend die Lappen der beiden Schlusshälften über den Keil verstemmt.It is known that most compressor blade rows of gas turbine rotors are arranged in circumferential grooves. When assembling such rows of blades, a special solution must be found for the last blades to be mounted, since then the remaining filling opening has become too small. This residual opening is filled with a so-called rotor-end. The rotor end consists of a halved intermediate piece (two end halves), and a wedge, by means of which the end halves are caulked in the rotor. The rotor-end is thus supported in the axial direction of the rotor. In this known prior art, the two end halves each have a straight side surface which forms a protruding tab at its upper end with the upper cover surface of the end half. The side surfaces mentioned are opposite in the installed state, in which case the wedge is located between them. After the two end halves and the wedge are installed, the lobes of the two end halves are finally caulked over the wedge.

Nachteilig an diesem Stand der Technik ist, dass der Keil auf Grund des Kippmomentes der beiden Schlusshälften, welches durch die Fliehkraft während des Betriebes bewirkt wird, in der Lage ist, die verstemmten Lappen aufzubiegen. Der Keil kann somit aus dem Verdichter herausfliegen und es kann zu einem kompletten Verdichterschaden kommen.A disadvantage of this prior art is that the wedge is due to the tilting moment of the two end halves, which is caused by the centrifugal force during operation, able to aufzubiegen the caulked lobes. The wedge can thus fly out of the compressor and it can lead to a complete compressor damage.

Zwar kann dieser Nachteil durch die als EP 12 15 367 veröffentlichte Erfindung der Anmelderin beseitigt werden, bei welcher der Keil aufgestemmt wird und die Lappen des aufgestemmten Keiles in einem von den Seitenflächen der beiden Schlussstücke gebildeten herzförmigen Hohlraum verankert werden.Although this disadvantage can by as EP 12 15 367 Applicant's published invention in which the wedge is prized and anchored the flaps of the raised wedge in a heart-shaped cavity formed by the side surfaces of the two tails.

Ein Nachteil dieser technischen Lösungen besteht aber darin, dass die Schlussstücke einerseits durch die Fliehkraft während des Betriebes und anderseits durch das Verstemmen des Keiles Axialkräfte auf den Rotor ausüben. Bei der Suche nach den Ursachen für die häufig auftretenden Rotorvibrationen hat man festgestellt, dass diese Axialkräfte den Rotor verbiegen und dadurch nachteilig störende Schwingungen erzeugen können.A disadvantage of these technical solutions, however, is that the closing pieces exert axial forces on the rotor on the one hand by the centrifugal force during operation and on the other hand by the caulking of the wedge. In the search for the causes of the frequently occurring rotor vibrations, it has been found that these axial forces can bend the rotor and thereby disadvantageously generate disturbing vibrations.

Darstellung der ErfindungPresentation of the invention

Ziel der Erfindung ist es, die genannten Nachteile des Standes der Technik zu vermeiden. Der Erfindung liegt die Aufgabe zu Grunde, einen Rotor-Schluss zu entwickeln, welcher keine Axialkräfte auf den Rotor ausübt, so dass dadurch ein Auftreten von durch Axialkräften hervorgerufenen störenden Rotorvibrationen vermieden wird.The aim of the invention is to avoid the mentioned disadvantages of the prior art. The invention is based on the object to develop a rotor-closing, which exerts no axial forces on the rotor, so that thereby an occurrence of axial forces caused by disturbing rotor vibrations is avoided.

Erfindungsgemäss wird diese Aufgabe bei einem Rotor-Schluss für Rotoren thermischer Turbomaschinen gemäss Oberbegriff des Patentanspruches 1 dadurch gelöst, dass der Rotor-Schluss in axialer Richtung an den beiden benachbarten Laufschaufeln befestigt ist. Jede der beiden Schlusshälften des Rotor-Schlusses ist in axialer Richtung des Rotors mit je einem Verbindungselement an den beiden benachbarten Laufschaufeln befestigt.According to the invention this object is achieved in a rotor-end for rotors of thermal turbomachinery according to the preamble of claim 1, characterized in that the rotor-end is fixed in the axial direction of the two adjacent blades. Each of the two end halves of the rotor-end is fixed in the axial direction of the rotor, each with a connecting element on the two adjacent blades.

Die Vorteile der Erfindung bestehen darin, dass nunmehr die beiden Schaufeln, und nicht wie beim bekannten Stand der Technik der Rotor, die durch die Fliehkraft und den aufgestemmten Keil verursachten Axialkräfte aufnehmen. Dadurch werden vorteilhaft störende Schwingungen vermieden.The advantages of the invention are that now take the two blades, and not as in the prior art, the rotor, the axial forces caused by the centrifugal force and the wedge abutted wedge. As a result, disturbing vibrations are advantageously avoided.

Das Verbindungselement kann gerade oder formschlüssig ausgebildet sein. Wenn die Schlusshälften und die benachbarten Laufschaufeln eine formschlüssige Baugruppe bilden, so hat dies den zusätzlichen Vorteil, dass die benachbarten Schaufeln nicht durch die vom Schlussstück auf sie wirkenden Kräfte in den Rotor hineingedreht werden, so dass sie sich bei ihrer thermischen Dehnung nicht verklemmen.The connecting element may be formed straight or positive. If the end halves and adjacent blades form a positive assembly, this has the additional advantage that the adjacent blades do not pass through them from the tail end acting forces are screwed into the rotor, so that they do not jam in their thermal expansion.

Es ist zweckmässig, wenn der Keil an seinem oberen Ende zwei durch einen Längsschlitz voneinander getrennte Lappen aufweist, welche im eingebauten Zustand aufgespreizt sind und dass die Seitenflächen der Schlusshälften im oberen Bereich jeweils eine Ausnehmung aufweisen, welche im eingebauten Zustand einen etwa herzförmigen Hohlraum bilden, wobei die Wände dieses Hohlraumes von den aufgespreizten Lappen des Keiles bedeckt sind und der Keil dadurch in den Schlusshälften fest verankert ist. Durch das Aufspreizen des Keiles in die Herzform der beiden Schlusshälften wird vermieden, dass sich der Keil während des Betriebes aus seiner Verankerung lösen kann.It is expedient if the wedge has at its upper end two tabs which are separated from one another by a longitudinal slot and which are spread open when installed and in that the side surfaces of the end halves each have a recess in the upper region which, when installed, forms an approximately heart-shaped cavity, wherein the walls of this cavity are covered by the spread tabs of the wedge and the wedge is thereby firmly anchored in the end halves. Spreading the wedge into the heart shape of the two end halves prevents the wedge from detaching from its anchorage during operation.

Kurze Beschreibung der ZeichnungenBrief description of the drawings

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

Fig. 1
einen Schnitt durch einen der Anmelderin bekannten Rotor-Schluss nach Einbau in einen Verdichterrotor;
Fig. 2
eine Draufsicht eines schematisch dargestellten erfindungsgemässen Rotor-Schlusses mit geradem Verbindungselement nach Einbau in einen Verdichterrotor (ohne Keil);
Fig. 3
eine Draufsicht eines schematisch dargestellten erfindungsgemässen Rotor-Schlusses mit formschlüssigem Verbindungselement nach Einbau in einen Verdichterrotor (ohne Keil) und
Fig. 4
eine Draufsicht eines schematisch dargestellten erfindungsgemässen Rotor-Schlusses mit Keil mit geradem Verbindungdelement nach Einbau in einen Verdichterrotor.
In the drawing, several embodiments of the invention are shown. Show it:
Fig. 1
a section through a conventional rotor-end after installation in a compressor rotor;
Fig. 2
a plan view of a schematically illustrated inventive rotor-end with straight connecting element after installation in a compressor rotor (wedge);
Fig. 3
a plan view of a schematically illustrated inventive rotor-end with positive connection element after installation in a compressor rotor (without wedge) and
Fig. 4
a plan view of a schematically illustrated inventive rotor-end wedge with a straight Verbindungsdelement after installation in a compressor rotor.

In den Figuren sind jeweils gleiche Positionen mit den gleichen Bezugszeichen versehen. Die Wirkungsrichtung der Axialkraft ist mit Pfeilen bezeichnet.In the figures, the same positions are respectively provided with the same reference numerals. The direction of action of the axial force is indicated by arrows.

Wege zur Ausführung der ErfindungWays to carry out the invention

Nachfolgend wird die Erfindung anhand von Ausführungsbeispielen und der Fig. 1 bis 4 näher erläutert.Hereinafter, the invention with reference to embodiments and the Fig. 1 to 4 explained in more detail.

Fig. 1 zeigt einen Schnitt durch einen der Anmelderin bekannten Rotor-Schluss 1 nach dem erfolgten Einbau in einen Rotor 2. Fig. 1 shows a section through one of the Applicant known Rotor-End 1 after installation in a rotor. 2

Der in Fig. 1 dargestellte Rotor-Schluss 1 besteht aus zwei Schlusshälften 4, 4' mit sich gegenüberstehenden Seitenflächen 5, 5' und aus einem Keil 6, welcher an seinem oberen, im eingebauten Zustand der Rotorlängsachse abgewandten Ende zwei durch einen Längsschlitz voneinander getrennte Lappen 10, 10' aufweist. Die Seitenflächen 5, 5' der Schlusshälften 4, 4' weisen im oberen Bereich jeweils eine Ausnehmung auf, welche im eingebauten Zustand einen etwa herzförmigen Hohlraum 11 bilden, wobei die Wände dieses Hohlraumes 11 von den aufgespreizten Lappen 10, 10' des verstemmten Keiles 6 bedeckt sind und den Keil 6 auf diese Weise formschlüssig fest in dem herzförmigen Hohlraum 11 verankern. Bei dieser der Anmelderin bekannten Ausführungsform stützt sich der Rotor-Schluss 1 bzw. die Schlusshälften 4, 4' in axialer Richtung am Rotor ab.The in Fig. 1 illustrated rotor end 1 consists of two end halves 4, 4 'with opposing side surfaces 5, 5' and a wedge 6, which at its upper, in the installed state of the rotor longitudinal axis end facing away from each other by a longitudinal slot 2 lobes 10, 10 ' having. The side surfaces 5, 5 'of the end halves 4, 4' each have a recess in the upper region, which form a heart-shaped cavity 11 when installed, the walls of this cavity 11 of the spread tabs 10, 10 'of the caulked wedge. 6 are covered and the wedge 6 in this way form-fitting firmly anchored in the heart-shaped cavity 11. In this embodiment known to the Applicant, the rotor end 1 or the end halves 4, 4 'are supported on the rotor in the axial direction.

Ein Nachteil dieser technischen Lösungen besteht darin, dass die Schlussstücke 4, 4' einerseits durch die Fliehkraft während des Betriebes und anderseits durch das Verstemmen des Keiles 6 Axialkräfte F auf den Rotor 2 ausüben. Bei der Suche nach den Ursachen für die häufig auftretenden Rotorvibrationen hat man festgestellt, dass diese Axialkräfte F den Rotor 2 verbiegen und dadurch nachteilig störende Schwingungen erzeugen können.A disadvantage of these technical solutions is that the tail pieces 4, 4 'on the one hand by the centrifugal force during operation and on the other hand by the caulking of the wedge 6 exert axial forces F on the rotor 2. In the search for the causes of the frequently occurring rotor vibrations has been found that these axial forces F bend the rotor 2 and thereby can produce adverse disturbing vibrations.

Es wird daher eine technische Lösung (siehe Fig. 2 bis 4) vorgeschlagen, bei welcher der Rotor-Schluss sich in axialer Richtung nicht mehr am Rotor abstützt, sondern an den beiden benachbarten Schlussschaufeln, und zwar an den Schaufelfüssen.It will therefore be a technical solution (see Fig. 2 to 4 ), in which the rotor end is no longer supported on the rotor in the axial direction, but on the two adjacent closing blades, namely at the blade roots.

In Fig. 2 ist eine Draufsicht eines schematisch dargestellten erfindungsgemässen Rotor-Schlusses 1 nach dem Einbau mit geraden Verbindungselementen 8, 8', 9, 9' dargestellt. Nicht dargestellt ist der verstemmte Keil, welcher zum Abschluss die Restöffnung der Umfangsnut 3 füllt. Jede der beiden Schlusshälften 4, 4' ist in axialer Richtung des Rotors 2 mit je einem Verbindungselement 8, 8', 9, 9' an den beiden benachbarten Laufschaufeln 7, 7' (auch Schluss-Schaufeln genannt), und zwar an den Schaufelfüssen, befestigt. Diese vier Verbindungselemente 8, 8', 9, 9' nehmen nun anstelle des Rotors 2 die Axialkräfte F auf, welche durch die Fliehkraft und den verstemmten Keil hervorgerufen werden. Auf diese Weise wirken keine axialen Kräfte mehr auf den Rotor und störende Rotorvibrationen werden vermieden.In Fig. 2 is a plan view of a schematically illustrated inventive rotor-end 1 after installation with straight connecting elements 8, 8 ', 9, 9' shown. Not shown is the caulked wedge, which finally fills the remaining opening of the circumferential groove 3. Each of the two end halves 4, 4 'is in the axial direction of the rotor 2, each with a connecting element 8, 8', 9, 9 'on the two adjacent blades 7, 7' (also called final blades), namely at the blade roots , attached. These four connecting elements 8, 8 ', 9, 9' now take the axial forces F instead of the rotor 2, which are caused by the centrifugal force and the caulked wedge. In this way, no axial forces on the rotor and disturbing rotor vibrations are avoided.

Da bei den in Fig. 2 dargestellten geraden Verbindungselementen 8, 8', 9, 9' jedoch das Risiko besteht, dass die benachbarten Schaufeln 7, 7' durch die von den Schlusshälften 4, 4' auf sie wirkenden Kräfte in den Rotor 2 hineingedreht werden und sich bei ihrer thermischen Dehnung verklemmen, ist es besser, die Verbindungselemente 8, 8', 9, 9' so auszubilden, dass die Schlusshälften 4, 4' und die Schaufeln 7, 7' eine formschlüssige Baugruppe bilden, wie in Fig. 3 dargestellt ist. Der Formschluss wird hier durch eine schwalbenschwanzartige Verbinduing erreichtSince the in Fig. 2 shown straight connecting elements 8, 8 ', 9, 9', however, there is a risk that the adjacent blades 7, 7 'are rotated by the action of the end halves 4, 4' forces in the rotor 2 and in their thermal expansion jam, it is better, the connecting elements 8, 8 ', 9, 9' in such a way that the end halves 4, 4 'and the blades 7, 7' form a form-fitting assembly, as in Fig. 3 is shown. The positive connection is achieved here by a dovetail-like Verbinduing

Dieser formschlüssige Verbund der Schluss-Stücke und der benachbarten Schaufeln wird als Schluss-Paket bezeichnet.This form-fitting connection of the closing pieces and the adjacent blades is referred to as the closing package.

In Fig. 4 ist ein weiteres Ausführungsbeispiel dargestellt. Die Figur zeigt ein Schluss-Paket, bestehend aus den beiden Schlusshälften 4, 4', den sich zwischen den Schlusshälften befindenden verstemmten Keil 6 und den beiden Schluss-Schaufeln 7, 7'.In Fig. 4 another embodiment is shown. The figure shows a final package, consisting of the two end halves 4, 4 ', the between the end halves located caulked wedge 6 and the two tail blades 7, 7 '.

Selbstverständlich ist die Erfindung nicht auf die oben beschriebenen Ausführungsbeispiele beschränkt.Of course, the invention is not limited to the embodiments described above.

Die erfindungsgemässe Lösung eignet sich für alle Schaufelreihen in Umfangsnut. Sie kommt vorteilhaft immer dann zum Einsatz, wenn der Rotor empfindlich auf Axialkräfte reagiert und dadurch störende Schwingungen entstehen können.The solution according to the invention is suitable for all blade rows in the circumferential groove. It is advantageously used whenever the rotor reacts sensitively to axial forces and thus disturbing vibrations can occur.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

11
Rotor-SchlussRotor end
22
Rotorrotor
33
Umfangsnutcircumferential groove
4, 4'4, 4 '
Schlusshälftefinal half
5, 5'5, 5 '
Seitenfläche der SchlusshälfteSide surface of the end half
66
Keilwedge
7, 7'7, 7 '
Laufschaufelblade
8, 8'8, 8 '
Verbindungselementconnecting element
9, 9'9, 9 '
Verbindungselementconnecting element
10, 10'10, 10 '
Lappen des KeilesRag of the wedge
1111
herzförmiger Hohlraumheart-shaped cavity
FF
Axialkraftaxial force

Claims (4)

  1. Rotor end piece (1) for rotors (2) of thermal turbomachines with a circumferential slot (3), consisting of two end piece halves (4, 4') having side faces (5, 5') opposite one another in the installed state and of a wedge (6) which is pushed in between them and which, in the installed state, is anchored in the side faces (5, 5') of the end piece halves (4, 4') in a form-fitting manner, the rotor end piece (1) being arranged in the axial direction of the rotor (2) between two moving blades (7, 7'), characterized in that each of the end piece halves (4, 4') is fastened in the axial direction of the rotor to the two adjacent moving blades (7, 7') by means of one connection element (8, 8', 9, 9') each.
  2. Rotor end piece (1) according to Claim 1, characterized in that the connection element (8, 8', 9, 9') is straight.
  3. Rotor end piece (1) according to Claim 1, characterized in that the connection element (8, 8', 9, 9') is a form fit.
  4. Rotor end piece (1) according to one of Claims 1 to 3, characterized in that the wedge (6), at its top end remote from the rotor longitudinal axis in the installed state, has two lugs (10, 10') which are separated from one another by a longitudinal slot and which are spread out in the installed state, and in that the side faces (5, 5') of the end piece halves (4, 4') each have a recess in the top region, these recesses forming a roughly heart-shaped cavity (11) in the installed state, the walls of this cavity (11) being covered by the spread-out lugs (10, 10') of the wedge (6), and the wedge (6) being firmly anchored in the end piece halves (4, 4') as a result.
EP04100742A 2003-03-11 2004-02-25 Device for fixing blades to the rotor Expired - Lifetime EP1457642B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10310432 2003-03-11
DE10310432A DE10310432A1 (en) 2003-03-11 2003-03-11 Rotor end

Publications (3)

Publication Number Publication Date
EP1457642A2 EP1457642A2 (en) 2004-09-15
EP1457642A3 EP1457642A3 (en) 2006-07-26
EP1457642B1 true EP1457642B1 (en) 2009-04-01

Family

ID=32748182

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04100742A Expired - Lifetime EP1457642B1 (en) 2003-03-11 2004-02-25 Device for fixing blades to the rotor

Country Status (5)

Country Link
US (1) US7192256B2 (en)
EP (1) EP1457642B1 (en)
CN (1) CN1534167B (en)
AT (1) ATE427412T1 (en)
DE (2) DE10310432A1 (en)

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1698759B1 (en) * 2005-02-23 2015-06-03 Alstom Technology Ltd Rotor end piece
EP1698758B1 (en) * 2005-02-23 2015-11-11 Alstom Technology Ltd Axially split rotor end piece
US7435055B2 (en) * 2005-03-29 2008-10-14 Siemens Power Generation, Inc. Locking spacer assembly for a turbine engine
EP1803900A1 (en) 2006-01-02 2007-07-04 Siemens Aktiengesellschaft Closure unit for the remaining space between the first and the last blades of a bladed ring inserted in a circumferencial slot of a turbomachine, and corresponding turbomachine
EP1803899A1 (en) * 2006-01-02 2007-07-04 Siemens Aktiengesellschaft Blade locking assembly for a turbomachine
FR2921099B1 (en) * 2007-09-13 2013-12-06 Snecma DAMPING DEVICE FOR DRAWINGS OF COMPOSITE MATERIAL
US8545184B2 (en) * 2010-01-05 2013-10-01 General Electric Company Locking spacer assembly
US20110255978A1 (en) * 2010-04-16 2011-10-20 Brian Denver Potter Locking Assembly For Circumferential Attachments
CH703997A1 (en) * 2010-10-27 2012-04-30 Alstom Technology Ltd Blade assembly, in particular vane.
US9175572B2 (en) * 2012-04-16 2015-11-03 General Electric Company Turbomachine blade mounting system
US9341071B2 (en) * 2013-10-16 2016-05-17 General Electric Company Locking spacer assembly
EP2868868A1 (en) * 2013-11-05 2015-05-06 Siemens Aktiengesellschaft Mounting device and mounting method of a vane
EP3765715B1 (en) * 2018-04-18 2021-12-29 Siemens Energy Global GmbH & Co. KG Locking spacer assembly, blade assembly and method for installing a locking spacer
CN113586519B (en) * 2021-08-24 2023-09-26 中国联合重型燃气轮机技术有限公司 Locking device and gas compressor and gas turbine comprising same

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Publication number Priority date Publication date Assignee Title
DE271243C (en)
US1371327A (en) * 1920-07-21 1921-03-15 Schneider & Cie Turbine
NL56668C (en) * 1940-06-12
US2406703A (en) * 1944-06-08 1946-08-27 Allis Chalmers Mfg Co Turbine blade locking apparatus
FR974989A (en) * 1948-09-17 1951-02-28 Lock for blading drum-shaped rotors of axial compressors and steam or gas turbines
CH273791A (en) * 1949-05-25 1951-02-28 Tech Studien Ag Blade lock on blades of axial flow machines without filling pieces.
DD271243A3 (en) * 1987-10-01 1989-08-30 Goerlitzer Maschinenbau Veb SHOVEL LOCK ASSEMBLY WITH MINIMIZED SHOVEL LOCK
DE10134611A1 (en) * 2000-12-16 2002-06-27 Alstom Switzerland Ltd Fixing device for a blade mounting of a compressor or turbine stage of a gas turbine system comprises a blade having a counter-contour corresponding to a connecting element of a wedge element to produce a form-locking connection

Also Published As

Publication number Publication date
CN1534167B (en) 2010-05-26
CN1534167A (en) 2004-10-06
EP1457642A3 (en) 2006-07-26
DE10310432A1 (en) 2004-09-23
DE502004009253D1 (en) 2009-05-14
EP1457642A2 (en) 2004-09-15
US7192256B2 (en) 2007-03-20
US20040179945A1 (en) 2004-09-16
ATE427412T1 (en) 2009-04-15

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