EP2478187B1 - Blade fixation with locking device for turbine blades - Google Patents

Blade fixation with locking device for turbine blades Download PDF

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Publication number
EP2478187B1
EP2478187B1 EP10755152.5A EP10755152A EP2478187B1 EP 2478187 B1 EP2478187 B1 EP 2478187B1 EP 10755152 A EP10755152 A EP 10755152A EP 2478187 B1 EP2478187 B1 EP 2478187B1
Authority
EP
European Patent Office
Prior art keywords
rotor
turbine blade
groove
clamping piece
blade root
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.)
Not-in-force
Application number
EP10755152.5A
Other languages
German (de)
French (fr)
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EP2478187A1 (en
Inventor
Thomas Helmis
Heinrich STÜER
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Siemens AG
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Siemens AG
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Publication date
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Priority to EP10755152.5A priority Critical patent/EP2478187B1/en
Publication of EP2478187A1 publication Critical patent/EP2478187A1/en
Application granted granted Critical
Publication of EP2478187B1 publication Critical patent/EP2478187B1/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
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/30—Retaining components in desired mutual position
    • F05B2260/301—Retaining bolts or nuts
    • F05B2260/3011—Retaining bolts or nuts of the frangible or shear type
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position

Definitions

  • the invention relates to a rotor comprising at least one turbine blade and a securing device for axial and radial securing of the turbine blade, wherein the rotor comprises a blade groove and the turbine blade comprises a turbine blade root, wherein the blade groove and the turbine blade root are formed such that the turbine blade root is adapted in the blade groove is.
  • Blade fasteners are typically used to secure blades to a rotor of a turbomachine, particularly a steam turbine. Due to the comparatively fast rotation of the rotor, the blades arranged on the rotor are exposed to high centrifugal forces. The turbine blade root of the turbine blades must therefore withstand high forces and is urged radially outward in the blade groove. In addition to the centrifugal forces, strong vibration loads pose a further problem that can result in mechanical damage, material fatigue, corrosion and migration of the blade root within the blade groove. For fixing the turbine blade root within the blade groove, various solutions such as metal wedges, spring washers or sealing pieces are known.
  • the GB 2 410 531 discloses a mounting option on a gas turbine.
  • the EP-A 2 090 750 shows a turbomachine rotor and a mounting method.
  • the EP-A 0 597 586 discloses a gas turbine plant.
  • the invention has for its object to provide a blade mounting a turbomachine in which over a long period of operation, a precise and firm support of blades, in associated blade holders, is ensured.
  • a rotor comprising at least one turbine blade according to claim 1.
  • the securing device has a clamping piece which exerts a radial force from the rotor onto the turbine blade root.
  • the clamping piece is in this case arranged in a groove located in the rotor, wherein the groove may be the same as the groove in which the shear pin is arranged.
  • the size of the clamping piece is chosen such that a force is generated which acts in the radial direction. This means that the turbine blade is pressed against the support flanks of the blade groove. Up to a certain rotational frequency thus a movement of the blades in the groove is effectively prevented. From a certain rotational frequency, the centrifugal forces are so great that a movement is prevented by the concern with the support flanks. However, it is almost inevitable that the turbine blade vibrates despite labbefest Trent.
  • the attachment according to the invention also prevents a relative movement between the turbine blade root and the blade groove, whereby surface damage is reduced.
  • the clamping piece has an upper leg and a lower leg, wherein the upper leg bears against the turbine blade root and exerts a force in the radial direction against the turbine blade root.
  • the lower leg rests against the rotor and the shear pin rests on the lower leg.
  • the invention is characterized in that the upper leg and the lower leg substantially form a V-shape and by skillful material selection a spring force is exerted, which acts from the rotor to the turbine blade root in the radial direction.
  • the invention is based on the idea that both a radial and an axial securing can be arranged in a blade groove.
  • the shear pin is placed in a corresponding bore in the turbine blade root and is advantageously at an edge on the rotor. As a result, an axial movement of the turbine blade root is not possible. If a shear pin is arranged on both the leading edge and the trailing edge of the turbine blade root, an axial displacement of the turbine blade root in one direction as well as in the other direction is effectively prevented.
  • the shear pin is in this case installed in a groove arranged in the rotor.
  • the shear pin is installed after the turbine blade has been installed in the rotor in the corresponding blade groove.
  • a securing element is used, which is designed to secure the clamping piece.
  • the clamping piece as a locking plate formed and arranged between the clamping piece and the rotor.
  • FIG. 1 shows a side view of a portion of a rotor 1 of a turbomachine, in particular steam turbine, with a built-turbine blade 2.
  • the turbine blade 2 has a turbine blade root 3, which is adapted to a corresponding blade groove 4.
  • the turbine blade 2 is inserted in the axial direction 5 in the blade groove 4.
  • the blade groove 4 is formed as Tannenbaumschaufelnut and includes a plurality of support flanks. 6
  • the turbine blade 2 is secured in the blade groove 4 both in the axial direction 5 and in the radial direction 29.
  • the radial direction 29 substantially corresponds to the longitudinal orientation of the turbine blade 2 and the axial direction 5 substantially corresponds to the axis of rotation which is in the FIG. 1 not shown in detail.
  • the turbine blade root 3 is in this case designed such that it is adapted to the blade groove 4, d. H. in the axial direction 5 can be substantially shifted.
  • FIG. 2 is a sectional view through a portion of the rotor 1 shown.
  • the securing device 7 essentially comprises three components. These would be a shear pin 8, a clamping piece 9 and a securing element 10.
  • the securing device 7 is arranged in a corresponding groove 11 in the rotor 1. This groove 11 is formed both at the steam inlet side 12 and at the steam outlet side 13.
  • the installation of at least two securing devices 7, ie both at the steam inlet side 12 and at the steam outlet side 13, offers the advantage that the turbine blade 2 can no longer be displaced in the axial direction 5.
  • the operation and the installation of the securing device 7 are based on the FIG. 3 explained in more detail.
  • the shear pin 8 is cylindrical and has a length L which is less than the groove height 14 of the groove 11. This allows easy insertion of the shear pin 8 in the groove 11 is possible.
  • the shear pin 8 is placed in a bore 15 which is located in the blade root 3.
  • the bore 15 and the groove 11 are formed such that when installed, the shear pin 8 rests against an edge 16 in the rotor 1. A displacement of the turbine blade root 3 in the axial direction 5 is thus no longer possible.
  • FIGS. 4 and 5 Another element of the securing device 7 forms the clamping piece 9.
  • the clamping piece 9 with a base body 17 which is cuboid-shaped and an upper leg 18 and a lower leg 19 executed. Between the upper leg 18 and the lower leg 19, a gap 20 is formed.
  • the dimensions of the clamping piece 9 are chosen such that the height 21 of the clamping piece 9 is less than the groove height 14. An insertion of the clamping piece 9 in the blade groove 4 is therefore easily possible.
  • the dimensions are further chosen such that in the installed state, the upper leg 18 presses a force which resembles a spring force against the turbine blade root 3.
  • the upper leg 18 has for this purpose a projection 22 which is approximately one third of the length of the clamping piece 9.
  • Both the upper leg 18 and the lower leg 19 are designed wedge-shaped, ie from the main body 17 in the direction of legs 18, 19, the upper leg 18 and the lower leg 19 are tapered.
  • FIG. 6 shows a perspective view of the shear pin 8.
  • a third element of the securing device 7 is the securing element 10, which is designed as a locking plate.
  • the fuse element 10 is based on the FIG. 7 explained in more detail.
  • the securing element 10 is formed as an elongated sheet metal piece which is folded once at its tip 23 once, whereby a projection 28 is formed. When installed, this projection 28 abuts in a corresponding securing groove 24. As in FIG. 3 illustrated, thereby an axial displacement of the securing element 5 10 is effectively avoided.
  • the securing element 10 has an end piece 26 which relative to a main piece 25 is bent perpendicular to the bending point 27.
  • the safety device 7 is now installed as follows: first, the turbine blade 2 is introduced into the corresponding blade groove 4. Subsequently, the shear pin 8 is adjusted in the corresponding hole 15.
  • the securing element 10 is inserted in the unbent state and has at the tip 23 a projection 28 which is arranged in a corresponding securing groove 24.
  • the clamping piece 9 is pushed onto the securing element 10 in the groove 11 such that the shear pin 8 rests on the lower leg 19. Falling out of the shear pin 8 from the bore 15 is thereby avoided.
  • the securing element 10 is inserted in the unbent state and has at the tip 23 a projection 28 which is arranged in a corresponding securing groove 24.
  • the securing element 10 is finally bent at the bending point 27, whereby falling out of the clamping piece 9 from the groove 11 is effectively avoided.

Description

Die Erfindung betrifft einen Rotor, umfassend zumindest eine Turbinenschaufel und eine Sicherungseinrichtung zur axialen und radialen Sicherung der Turbinenschaufel, wobei der Rotor eine Schaufelnut und die Turbinenschaufel einen Turbinenschaufelfuß umfasst, wobei die Schaufelnut und der Turbinenschaufelfuß derart ausgebildet sind, dass der Turbinenschaufelfuß in der Schaufelnut angepasst ist.The invention relates to a rotor comprising at least one turbine blade and a securing device for axial and radial securing of the turbine blade, wherein the rotor comprises a blade groove and the turbine blade comprises a turbine blade root, wherein the blade groove and the turbine blade root are formed such that the turbine blade root is adapted in the blade groove is.

Schaufelbefestigungen werden in der Regel zum Befestigen von Laufschaufeln an einem Rotor einer Strömungsmaschine, insbesondere Dampfturbine verwendet. Durch die vergleichsweise schnelle Rotation des Rotors werden die auf dem Rotor angeordneten Laufschaufeln hohen Fliehkräften ausgesetzt. Der Turbinenschaufelfuß der Turbinenschaufeln muss daher hohen Kräften standhalten und wird in der Schaufelnut radial nach außen gedrängt. Neben den Fliehkräften stellen starke Schwingungsbelastungen ein weiteres Problem dar, die mechanische Beschädigungen, Materialermüdungen, Korrosion und eine Wanderbewegung des Schaufelfußes innerhalb der Schaufelnut zur Folge haben können. Zum Festlegen des Turbinenschaufelfußes innerhalb der Schaufelnut sind verschieden Lösungen wie beispielsweise Metallkeile, Federringe oder Abdichtungsstücke bekannt. Metallkeile stellen zwar axial als auch radial eine Arretierung des zugehörigen Schaufelfußes innerhalb einer Schaufelnut her, aber bei großen Laufschaufeln ist es mit solchen Metallkeilen schwierig, ausreichende Haltekräfte während der Rotation in radialer Richtung zu erzeugen. Tellerfedern erzeugen lediglich radiale Halterkräfte und erfordern zusätzlichen Aufwand für eine Arretierung in axialer Richtung der zugehörigen Schaufelnut. Ferner sind für Tellerfedern während der Montage aufwändige Messungen erforderlich. Als Abdichtungsstücke müssen immer zwei Teile vorgesehen sein, deren Montage darüber hinaus teilweise die Bearbeitung der Teile von Hand bedarf.Blade fasteners are typically used to secure blades to a rotor of a turbomachine, particularly a steam turbine. Due to the comparatively fast rotation of the rotor, the blades arranged on the rotor are exposed to high centrifugal forces. The turbine blade root of the turbine blades must therefore withstand high forces and is urged radially outward in the blade groove. In addition to the centrifugal forces, strong vibration loads pose a further problem that can result in mechanical damage, material fatigue, corrosion and migration of the blade root within the blade groove. For fixing the turbine blade root within the blade groove, various solutions such as metal wedges, spring washers or sealing pieces are known. While metal wedges provide locking of the associated blade root within a blade groove both axially and radially, with large blades it is difficult with such metal wedges to produce sufficient holding forces during rotation in the radial direction. Disc springs produce only radial holding forces and require additional effort for a locking in the axial direction of the associated blade groove. Furthermore, complex measurements are required for disc springs during assembly. As sealing pieces always two parts must be provided, In addition, their assembly partly requires the processing of the parts by hand.

Die GB 2 410 531 offenbart eine Befestigungsmöglichkeit an einer Gasturbine.The GB 2 410 531 discloses a mounting option on a gas turbine.

Die EP-A 2 090 750 zeigt einen Turbomaschinenrotor und ein Montageverfahren.The EP-A 2 090 750 shows a turbomachine rotor and a mounting method.

Die EP-A 0 597 586 offenbart eine Gasturbinenanlage.The EP-A 0 597 586 discloses a gas turbine plant.

Der Erfindung liegt die Aufgabe zugrunde, eine Schaufelbefestigung einer Strömungsmaschine bereitzustellen, bei der über einen langen Betriebszeitraum hinweg eine präzise und feste Halterung von Schaufeln, in zugehörigen Schaufelhaltern, sichergestellt ist.The invention has for its object to provide a blade mounting a turbomachine in which over a long period of operation, a precise and firm support of blades, in associated blade holders, is ensured.

Diese Aufgabe wird gelöst durch einen Rotor, umfassend zumindest eine Turbinenschaufel gemäß Anspruch 1.This object is achieved by a rotor comprising at least one turbine blade according to claim 1.

Die Sicherungseinrichtung weist ein Klemmstück auf, das eine radiale Kraft vom Rotor auf den Turbinenschaufelfuß ausübt. Das Klemmstück wird hierbei in einer im Rotor befindlichen Nut angeordnet, wobei die Nut dieselbe sein kann, wie die Nut, in der der Scherstift angeordnet ist. Die Größe des Klemmstücks ist derart gewählt, dass eine Kraft entsteht, die in radialer Richtung wirkt. Das bedeutet, dass die Turbinenschaufel gegen die Tragflanken der Schaufelnut gedrückt wird. Bis zu einer gewissen Rotationsfrequenz wird somit eine Bewegung der Schaufeln in der Nut wirksam verhindert. Ab einer gewissen Rotationsfrequenz sind die Fliehkräfte derart groß, dass eine Bewegung durch das Anliegen an den Tragflanken verhindert ist. Allerdings ist es nahezu unvermeidbar, dass die Turbinenschaufel trotz Fußbefestigung schwingt. Die erfindungsgemäße Befestigung verhindert zudem eine Relativbewegung zwischen dem Turbinenschaufelfuß und der Schaufelnut, wodurch Oberflächenschädigungen vermindert werden.The securing device has a clamping piece which exerts a radial force from the rotor onto the turbine blade root. The clamping piece is in this case arranged in a groove located in the rotor, wherein the groove may be the same as the groove in which the shear pin is arranged. The size of the clamping piece is chosen such that a force is generated which acts in the radial direction. This means that the turbine blade is pressed against the support flanks of the blade groove. Up to a certain rotational frequency thus a movement of the blades in the groove is effectively prevented. From a certain rotational frequency, the centrifugal forces are so great that a movement is prevented by the concern with the support flanks. However, it is almost inevitable that the turbine blade vibrates despite Fußbefestigung. The attachment according to the invention also prevents a relative movement between the turbine blade root and the blade groove, whereby surface damage is reduced.

Bis zu dieser Rotationsfrequenz ist ein axiales Verschieben der Turbinenschaufel möglich. Oberhalb der gewissen Rotationsfrequenz sind die Fliehkräfte derart hoch, dass ein axiales Verschieben vermieden ist, da die Reibkräfte, die in Folge der Fliehkraft wirken, ein Verschieben der Turbinenschaufel in der Schaufelnut wirksam verhindern.Up to this rotational frequency, an axial displacement of the turbine blade is possible. Above the certain rotational frequency, the centrifugal forces are so high that an axial displacement is avoided, since the frictional forces acting as a result of the centrifugal force effectively prevent a displacement of the turbine blade in the blade groove.

Das Klemmstück weist einen oberen Schenkel und einen unteren Schenkel auf, wobei der obere Schenkel am Turbinenschaufelfuß anliegt und gegen den Turbinenschaufelfuß eine Kraft in radialer Richtung ausübt. Der untere Schenkel liegt am Rotor an und der Scherstift liegt auf dem unteren Schenkel auf.The clamping piece has an upper leg and a lower leg, wherein the upper leg bears against the turbine blade root and exerts a force in the radial direction against the turbine blade root. The lower leg rests against the rotor and the shear pin rests on the lower leg.

Die Erfindung zeichnet sich dadurch aus, dass der obere Schenkel und der untere Schenkel im Wesentlichen eine V-Form bilden und durch geschickte Materialauswahl eine Federkraft ausgeübt wird, die vom Rotor auf den Turbinenschaufelfuß in radialer Richtung wirkt.The invention is characterized in that the upper leg and the lower leg substantially form a V-shape and by skillful material selection a spring force is exerted, which acts from the rotor to the turbine blade root in the radial direction.

Vorteilhafte Weiterbildungen sind in den Unteransprüchen angegeben.Advantageous developments are specified in the subclaims.

Die Erfindung geht von dem Gedanken aus, dass in einer Schaufelnut sowohl eine radiale als auch eine axiale Sicherung angeordnet werden kann. Der Scherstift wird in eine entsprechende Bohrung im Turbinenschaufelfuß angeordnet und liegt vorteilhafterweise an einer Kante am Rotor an. Dadurch ist eine axiale Bewegung des Turbinenschaufelfußes nicht möglich. Werden sowohl an der Vorderkante als auch an der Hinterkante des Turbinenschaufelfußes jeweils ein Scherstift angeordnet, so ist eine axiale Verschiebung des Turbinenschaufelfußes sowohl in die eine Richtung als auch in die andere Richtung wirksam verhindert.The invention is based on the idea that both a radial and an axial securing can be arranged in a blade groove. The shear pin is placed in a corresponding bore in the turbine blade root and is advantageously at an edge on the rotor. As a result, an axial movement of the turbine blade root is not possible. If a shear pin is arranged on both the leading edge and the trailing edge of the turbine blade root, an axial displacement of the turbine blade root in one direction as well as in the other direction is effectively prevented.

Der Scherstift wird hierbei in eine im Rotor angeordnete Nut eingebaut. Der Einbau des Scherstiftes erfolgt, nachdem die Turbinenschaufel in den Rotor in die entsprechende Schaufelnut eingebaut wurde.The shear pin is in this case installed in a groove arranged in the rotor. The shear pin is installed after the turbine blade has been installed in the rotor in the corresponding blade groove.

Um ein ungewolltes Lösen des Klemmstückes zu vermeiden, wird ein Sicherungselement verwendet, das zum Sichern des Klemmstückes ausgebildet ist. Dazu wird das Klemmstück als Sicherungsblech ausgebildet und zwischen dem Klemmstück und dem Rotor angeordnet. Durch Umbiegen des Sicherungsbleches an der Kante des Klemmstückes wird ein Verschieben des Klemmstückes vermieden, wobei gleichzeitig das Sicherungsblech in eine entsprechende Nut im Rotor angeordnet werden muss.To avoid accidental release of the clamping piece, a securing element is used, which is designed to secure the clamping piece. For this purpose, the clamping piece as a locking plate formed and arranged between the clamping piece and the rotor. By bending the locking plate at the edge of the clamping piece a displacement of the clamping piece is avoided, at the same time the locking plate must be arranged in a corresponding groove in the rotor.

Nachfolgend wird ein Ausführungsbeispiel der erfindungsgemäßen Lösung anhand der beigefügten schematischen Zeichnungen näher erläutert.An exemplary embodiment of the solution according to the invention will be explained in more detail below with reference to the attached schematic drawings.

Es zeigen:

Figur 1
eine Seitenansicht eines Rotors mit einer Turbinenschaufel im eingebauten Zustand;
Figur 2
eine Querschnittsansicht eines Teils eines Rotors mit eingebauter Turbinenschaufel;
Figur 3
eine vergrößerte Darstellung eines Ausschnitts aus Figur 2;
Figur 4
eine vergrößerte Darstellung eines Klemmstückes;
Figur 5
eine perspektivische Darstellung des Klemmstückes;
Figur 6
eine perspektivische Darstellung eines Scherstiftes;
Figur 7
eine perspektivische Darstellung eines Sicherungselementes.
Show it:
FIG. 1
a side view of a rotor with a turbine blade in the installed state;
FIG. 2
a cross-sectional view of a portion of a rotor with built-turbine blade;
FIG. 3
an enlarged view of a section from FIG. 2 ;
FIG. 4
an enlarged view of a clamping piece;
FIG. 5
a perspective view of the clamping piece;
FIG. 6
a perspective view of a shear pin;
FIG. 7
a perspective view of a fuse element.

Die Figur 1 zeigt eine Seitenansicht eines Teils eines Rotors 1 einer Strömungsmaschine, insbesondere Dampfturbine, mit einer eingebauten Turbinenschaufel 2. Die Turbinenschaufel 2 weist einen Turbinenschaufelfuß 3 auf, der an eine entsprechende Schaufelnut 4 angepasst ist. Die Turbinenschaufel 2 wird in axialer Richtung 5 in die Schaufelnut 4 eingeschoben. Die Schaufelnut 4 ist als Tannenbaumschaufelnut ausgebildet und umfasst mehrere Tragflanken 6.The FIG. 1 shows a side view of a portion of a rotor 1 of a turbomachine, in particular steam turbine, with a built-turbine blade 2. The turbine blade 2 has a turbine blade root 3, which is adapted to a corresponding blade groove 4. The turbine blade 2 is inserted in the axial direction 5 in the blade groove 4. The blade groove 4 is formed as Tannenbaumschaufelnut and includes a plurality of support flanks. 6

Die Turbinenschaufel 2 wird in der Schaufelnut 4 sowohl in axialer Richtung 5 als auch in radialer Richtung 29 gesichert. Die radiale Richtung 29 entspricht im Wesentlichen der Längsausrichtung der Turbinenschaufel 2 und die axiale Richtung 5 entspricht im Wesentlichen der Rotationsachse, die in der Figur 1 nicht näher dargestellt ist.The turbine blade 2 is secured in the blade groove 4 both in the axial direction 5 and in the radial direction 29. The radial direction 29 substantially corresponds to the longitudinal orientation of the turbine blade 2 and the axial direction 5 substantially corresponds to the axis of rotation which is in the FIG. 1 not shown in detail.

Zur Sicherung der Turbinenschaufel 2 wird eine Sicherungseinrichtung 7, die unterhalb des Turbinenschaufelfußes 3 angeordnet ist, realisiert. Der Turbinenschaufelfuß 3 ist hierbei derart ausgebildet, dass dieser an die Schaufelnut 4 angepasst ist, d. h. in axialer Richtung 5 sich im Wesentlichen verschieben lässt.To secure the turbine blade 2, a securing device 7, which is arranged below the turbine blade root 3, realized. The turbine blade root 3 is in this case designed such that it is adapted to the blade groove 4, d. H. in the axial direction 5 can be substantially shifted.

In der Figur 2 ist eine Schnittdarstellung durch einen Teil des Rotors 1 dargestellt. Die Sicherungseinrichtung 7 umfasst im Wesentlichen drei Bauteile. Dies wären zum einen ein Scherstift 8, ein Klemmstück 9 und ein Sicherungselement 10. Die Sicherungseinrichtung 7 ist in eine entsprechende Nut 11 im Rotor 1 angeordnet. Diese Nut 11 ist sowohl an der Dampfeintrittsseite 12 als auch an der Dampfaustrittsseite 13 ausgebildet. Der Einbau von zumindest zwei Sicherungseinrichtungen 7, d. h. sowohl an der Dampfeintrittsseite 12 als auch an der Dampfaustrittsseite 13, bietet den Vorteil, dass die Turbinenschaufel 2 sich in axialer Richtung 5 nicht mehr verschieben lässt. Die Funktionsweise sowie der Einbau der Sicherungseinrichtung 7 werden anhand der Figur 3 näher erläutert.In the FIG. 2 is a sectional view through a portion of the rotor 1 shown. The securing device 7 essentially comprises three components. These would be a shear pin 8, a clamping piece 9 and a securing element 10. The securing device 7 is arranged in a corresponding groove 11 in the rotor 1. This groove 11 is formed both at the steam inlet side 12 and at the steam outlet side 13. The installation of at least two securing devices 7, ie both at the steam inlet side 12 and at the steam outlet side 13, offers the advantage that the turbine blade 2 can no longer be displaced in the axial direction 5. The operation and the installation of the securing device 7 are based on the FIG. 3 explained in more detail.

Der Scherstift 8 ist zylindrisch ausgebildet und weist eine Länge L auf, die geringer ist als die Nuthöhe 14 der Nut 11. Dadurch ist ein problemloses Einschieben des Scherstiftes 8 in die Nut 11 möglich. Der Scherstift 8 wird in eine Bohrung 15, die sich im Schaufelfuß 3 befindet, eingebracht. Die Bohrung 15 und die Nut 11 werden dabei derart ausgebildet, dass im eingebauten Zustand der Scherstift 8 an einer Kante 16 im Rotor 1 anliegt. Ein Verschieben des Turbinenschaufelfußes 3 in axialer Richtung 5 ist somit nicht mehr möglich.The shear pin 8 is cylindrical and has a length L which is less than the groove height 14 of the groove 11. This allows easy insertion of the shear pin 8 in the groove 11 is possible. The shear pin 8 is placed in a bore 15 which is located in the blade root 3. The bore 15 and the groove 11 are formed such that when installed, the shear pin 8 rests against an edge 16 in the rotor 1. A displacement of the turbine blade root 3 in the axial direction 5 is thus no longer possible.

Ein weiteres Element der Sicherungseinrichtung 7 bildet das Klemmstück 9. In den Figuren 4 und 5 ist eine perspektivische und vergrößerte Darstellung des Klemmstückes 9 zu sehen. Im Wesentlichen ist das Klemmstück 9 mit einem Grundkörper 17, der quaderförmig ausgebildet ist und einem oberen Schenkel 18 und einem unteren Schenkel 19 ausgeführt. Zwischen dem oberen Schenkel 18 und dem unteren Schenkel 19 ist ein Spalt 20 gebildet. Die Abmessungen des Klemmstückes 9 sind derart gewählt, dass die Höhe 21 des Klemmstückes 9 geringer ist als die Nuthöhe 14. Ein Einschieben des Klemmstückes 9 in die Schaufelnut 4 ist daher problemlos möglich. Die Abmessungen sind weiterhin derart gewählt, dass im eingebauten Zustand der obere Schenkel 18 eine Kraft, die einer Federkraft ähnelt, gegen den Turbinenschaufelfuß 3 drückt. Der obere Schenkel 18 weist hierfür einen Vorsprung 22 auf, der ca. ein Drittel der Länge des Klemmstückes 9 beträgt. Sowohl der obere Schenkel 18 als auch der untere Schenkel 19 sind keilförmig ausgeführt, d. h. vom Grundkörper 17 in Richtung Schenkel 18, 19 verjüngen sich der obere Schenkel 18 und der untere Schenkel 19.Another element of the securing device 7 forms the clamping piece 9. In the FIGS. 4 and 5 is a perspective and enlarged view of the clamping piece 9 can be seen. In essence, the clamping piece 9 with a base body 17 which is cuboid-shaped and an upper leg 18 and a lower leg 19 executed. Between the upper leg 18 and the lower leg 19, a gap 20 is formed. The dimensions of the clamping piece 9 are chosen such that the height 21 of the clamping piece 9 is less than the groove height 14. An insertion of the clamping piece 9 in the blade groove 4 is therefore easily possible. The dimensions are further chosen such that in the installed state, the upper leg 18 presses a force which resembles a spring force against the turbine blade root 3. The upper leg 18 has for this purpose a projection 22 which is approximately one third of the length of the clamping piece 9. Both the upper leg 18 and the lower leg 19 are designed wedge-shaped, ie from the main body 17 in the direction of legs 18, 19, the upper leg 18 and the lower leg 19 are tapered.

Die Figur 6 zeigt eine perspektivische Darstellung des Scherstiftes 8. Ein drittes Element der Sicherungseinrichtung 7 ist das Sicherungselement 10, das als Sicherungsblech ausgeführt wird. Das Sicherungselement 10 wird anhand der Figur 7 näher erläutert. Im Wesentlichen ist das Sicherungselement 10 als länglich ausgebildetes Blechstück ausgebildet, das an seiner Spitze 23 einmal vollständig gefaltet ist, wodurch ein Vorsprung 28 entsteht. Im eingebauten Zustand liegt dieser Vorsprung 28 in einer entsprechenden Sicherungsnut 24 an. Wie in Figur 3 dargestellt, wird dadurch ein axiales Verschieben 5 des Sicherungselementes 10 wirksam vermieden. Des Weiteren weist das Sicherungselement 10 ein Endstück 26 auf, das gegenüber einem Hauptstück 25 senkrecht an der Biegungsstelle 27 gebogen ist.The FIG. 6 shows a perspective view of the shear pin 8. A third element of the securing device 7 is the securing element 10, which is designed as a locking plate. The fuse element 10 is based on the FIG. 7 explained in more detail. In essence, the securing element 10 is formed as an elongated sheet metal piece which is folded once at its tip 23 once, whereby a projection 28 is formed. When installed, this projection 28 abuts in a corresponding securing groove 24. As in FIG. 3 illustrated, thereby an axial displacement of the securing element 5 10 is effectively avoided. Furthermore, the securing element 10 has an end piece 26 which relative to a main piece 25 is bent perpendicular to the bending point 27.

Die Sicherungseinrichtung 7 wird nun folgendermaßen eingebaut: zunächst wird die Turbinenschaufel 2 in die entsprechende Schaufelnut 4 eingebracht. Anschließend wird der Scherstift 8 in die entsprechende Bohrung 15 angepasst. Das Sicherungselement 10 wird im ungebogenen Zustand eingeschoben und weist an der Spitze 23 einen Vorsprung 28 auf, der in eine entsprechende Sicherungsnut 24 angeordnet ist. Das Klemmstück 9 wird auf das Sicherungselement 10 derart in die Nut 11 geschoben, dass der Scherstift 8 auf dem unteren Schenkel 19 anliegt. Ein Herausfallen des Scherstiftes 8 aus der Bohrung 15 wird dadurch vermieden. Das Sicherungselement 10 wird im ungebogenen Zustand eingeschoben und weist an der Spitze 23 einen Vorsprung 28 auf, der in eine entsprechende Sicherungsnut 24 angeordnet ist. Das Sicherungselement 10 wird schließlich an der Biegestelle 27 gebogen, wodurch ein Herausfallen des Klemmstückes 9 aus der Nut 11 wirksam vermieden ist.The safety device 7 is now installed as follows: first, the turbine blade 2 is introduced into the corresponding blade groove 4. Subsequently, the shear pin 8 is adjusted in the corresponding hole 15. The securing element 10 is inserted in the unbent state and has at the tip 23 a projection 28 which is arranged in a corresponding securing groove 24. The clamping piece 9 is pushed onto the securing element 10 in the groove 11 such that the shear pin 8 rests on the lower leg 19. Falling out of the shear pin 8 from the bore 15 is thereby avoided. The securing element 10 is inserted in the unbent state and has at the tip 23 a projection 28 which is arranged in a corresponding securing groove 24. The securing element 10 is finally bent at the bending point 27, whereby falling out of the clamping piece 9 from the groove 11 is effectively avoided.

Claims (5)

  1. Rotor (1),
    comprising at least one turbine blade (2) and a locking device (7) for the axial and radial locking of the turbine blade (2),
    wherein the rotor (1) comprises a blade groove (4) and the turbine blade (2) comprises a turbine blade root (3), wherein the blade groove (4) and the turbine blade root (3) are designed in such a way that the turbine blade root (3) is fitted on the blade groove (4),
    wherein the locking device (7) has a clamping piece (9) which exerts a radial force from the rotor (1) onto the turbine blade root (3), characterized in that the clamping piece (9) is arranged in a groove (11) which is located on the side in the rotor (1),
    wherein the clamping piece (9) has an upper leg (18) and a lower leg (19),
    wherein the upper leg (18) butts against the turbine blade root (3) and exerts a force against the turbine blade root (3) in the radial direction (29),
    wherein the lower leg (18) butts against the rotor (1) and exerts a force against the rotor (1) in the radial direction (6),
    wherein the upper leg (18) and the lower leg (19) are of a V-shaped design,
    wherein the locking device (7) has a shear pin (8) which projects into a radially aligned hole (15) in the turbine blade root (3),
    wherein the shear pin (8) butts against the lower leg (19).
  2. Rotor (1) according to Claim 1,
    wherein the rotor (1) has a radially running edge (16), against which the shear pin (8) butts.
  3. Rotor (1) according to one of the preceding claims,
    wherein the locking device (7) has a locking element (10) for locking the clamping piece (9) in such a way that the clamping piece (9) is prevented from falling out of the groove (11).
  4. Rotor (1) according to Claim 3,
    wherein the locking element (10) is designed as a locking plate which is arranged between the clamping piece (9) and the rotor (1).
  5. Rotor (1) according to Claim 3 or 4,
    wherein the locking element (10) has a projection (28) which is arranged in a locking groove (24) which is located in the rotor (1).
EP10755152.5A 2009-09-17 2010-09-17 Blade fixation with locking device for turbine blades Not-in-force EP2478187B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP10755152.5A EP2478187B1 (en) 2009-09-17 2010-09-17 Blade fixation with locking device for turbine blades

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP09011885A EP2299060A1 (en) 2009-09-17 2009-09-17 Blade fixation with locking device for turbine blades
PCT/EP2010/063701 WO2011033063A1 (en) 2009-09-17 2010-09-17 Blade fastening having safety device for turbine blades
EP10755152.5A EP2478187B1 (en) 2009-09-17 2010-09-17 Blade fixation with locking device for turbine blades

Publications (2)

Publication Number Publication Date
EP2478187A1 EP2478187A1 (en) 2012-07-25
EP2478187B1 true EP2478187B1 (en) 2013-07-03

Family

ID=41566145

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Application Number Title Priority Date Filing Date
EP09011885A Withdrawn EP2299060A1 (en) 2009-09-17 2009-09-17 Blade fixation with locking device for turbine blades
EP10755152.5A Not-in-force EP2478187B1 (en) 2009-09-17 2010-09-17 Blade fixation with locking device for turbine blades

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP09011885A Withdrawn EP2299060A1 (en) 2009-09-17 2009-09-17 Blade fixation with locking device for turbine blades

Country Status (4)

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US (1) US8956122B2 (en)
EP (2) EP2299060A1 (en)
CN (1) CN102498264B (en)
WO (1) WO2011033063A1 (en)

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US20140199172A1 (en) 2013-01-11 2014-07-17 General Electric Company Turbomachine and method of handling turbomachine components
EP3048256A1 (en) * 2015-01-20 2016-07-27 Siemens Aktiengesellschaft Rotor comprising a turbine blade with a locking device
IT201600130088A1 (en) * 2016-12-22 2018-06-22 Nuovo Pignone Tecnologie Srl Turbine blade and fastening set
US10385874B2 (en) * 2017-05-08 2019-08-20 Solar Turbines Incorporated Pin to reduce relative rotational movement of disk and spacer of turbine engine
PL3650652T3 (en) * 2018-11-08 2022-05-02 Doosan Skoda Power S.R.O. Fastening of a turbine blade with tree-shaped root in a turbine rotor by means of a deformable fixation wedge and a securing element
KR102400013B1 (en) 2020-08-21 2022-05-18 두산에너빌리티 주식회사 Assembling structure of compressor blade seal and Gas turbine comprising the same and Assembling method of compressor blade seal
KR102478172B1 (en) * 2021-02-02 2022-12-14 두산에너빌리티 주식회사 Rotary machine, gas turbine including the same, assembling method of the same
KR102585387B1 (en) * 2021-08-19 2023-10-05 두산에너빌리티 주식회사 Blade fixing structure and rotor, compressor, gas turbine and blade fixing method including the same
JP7414941B1 (en) 2022-11-29 2024-01-16 株式会社東芝 Fixed structure of turbine rotor blades

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US2963271A (en) * 1956-07-19 1960-12-06 Gen Motors Corp Turbine blade locking
FR2323908A1 (en) * 1975-09-11 1977-04-08 Alsthom Cgee Fan blade root locking - using taper headed bolt bearing on rod in radial hole communicating with root slot
GB9223593D0 (en) 1992-11-11 1992-12-23 Rolls Royce Plc Gas turbine engine fan blade assembly
DE4441233A1 (en) * 1994-11-19 1996-05-23 Abb Management Ag Bladed rotor
GB2410531B (en) 2004-01-29 2006-03-01 Rolls Royce Plc Fan blade disk assembly
DE502004006777D1 (en) 2004-07-22 2008-05-21 Siemens Ag Securing device for a arranged on a rotatable rotor blade rotor of a turbomachine, turbomachine and method for assembling and disassembling a blade on a rotor disk of a turbomachine
EP1892380A1 (en) * 2006-08-25 2008-02-27 Siemens Aktiengesellschaft Turbine blade retention system
EP1905957A1 (en) * 2006-09-27 2008-04-02 Siemens Aktiengesellschaft Locking device of a turbine blade
FR2915510B1 (en) * 2007-04-27 2009-11-06 Snecma Sa SHOCK ABSORBER FOR TURBOMACHINE BLADES
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US9103221B2 (en) * 2012-02-16 2015-08-11 Alstom Technology Ltd System and method for blade retention

Also Published As

Publication number Publication date
CN102498264A (en) 2012-06-13
EP2299060A1 (en) 2011-03-23
US20120177499A1 (en) 2012-07-12
CN102498264B (en) 2015-02-25
EP2478187A1 (en) 2012-07-25
US8956122B2 (en) 2015-02-17
WO2011033063A1 (en) 2011-03-24

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