EP3212895B1 - Rotor comprising a turbine blade with a locking device - Google Patents

Rotor comprising a turbine blade with a locking device Download PDF

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Publication number
EP3212895B1
EP3212895B1 EP16700042.1A EP16700042A EP3212895B1 EP 3212895 B1 EP3212895 B1 EP 3212895B1 EP 16700042 A EP16700042 A EP 16700042A EP 3212895 B1 EP3212895 B1 EP 3212895B1
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EP
European Patent Office
Prior art keywords
rotor
turbine blade
recess
blade root
retaining piece
Prior art date
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Active
Application number
EP16700042.1A
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German (de)
French (fr)
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EP3212895A1 (en
Inventor
Andreas Rehnsch
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Siemens Energy Global GmbH and Co KG
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Siemens Energy Global GmbH and Co KG
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Publication of EP3212895A1 publication Critical patent/EP3212895A1/en
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Publication of EP3212895B1 publication Critical patent/EP3212895B1/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
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • 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
    • 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
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/34—Blade mountings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
    • 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
    • F05D2260/38—Retaining components in desired mutual position by a spring, i.e. spring loaded or biased towards a certain position

Definitions

  • the invention relates to a rotor comprising at least one turbine blade and a safety device for axially and radially securing the turbine blade, the rotor comprising a blade groove and the turbine blade comprising a turbine blade root, the blade groove and the turbine blade root being adapted to the blade groove, the safety device having a holding piece , which is arranged between the blade groove and the turbine blade root.
  • Blade fastenings are generally used to fasten rotor blades to a rotor of a turbomachine, in particular a steam turbine. Due to the comparatively high rotation of the rotor, the rotor 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 forced radially outward in the blade groove. In addition to the centrifugal forces, strong vibration loads represent a further problem that can result in mechanical damage and material fatigue. Corrosion and a wandering movement of the blade root due to the application of damping or vibrations within the blade groove pose further problems. Various solutions such as metal wedges, spring washers or sealing pieces are known for fixing the turbine blade root within the blade groove.
  • Metal wedges lock the associated blade root axially as well as radially within a blade groove, but with large rotor blades it is difficult with such metal wedges to generate sufficient holding forces during the rotation in the radial direction. Furthermore, metal wedges show a corrosive behavior during prolonged operation in the steam medium, which makes dismantling difficult.
  • Axially threaded rotor blades which are used in turbo machines such as steam turbines, for example, which, due to the operational stresses, require a construction which absorbs the axial operating forces of the turbine blade and holds the blade in its axial position.
  • Such fuses are also referred to as axial fuses.
  • two notches are arranged in such axial securing devices, which are designed to be superimposed on one another.
  • overlapping notches often show increased stress and thus mean limited applicability in turbo-machine construction. Examples of blade fastenings on a rotor of a turbo-machine are no longer available EP 1892380 A1 , US 2847187 A , US5431543 A and US 4668167 A known.
  • the invention is based on the object of providing a blade attachment in a turbo-machine, in which a precise and firm attachment of blades, the associated blade holders, is ensured over a long period of operation.
  • the object is achieved by a rotor according to claim 1.
  • the rotor comprises at least one turbine blade and a securing device for axially and radially securing the turbine blade, wherein the rotor comprises a blade groove and the turbine blade comprises a turbine blade root, the blade groove and the turbine blade root being adapted to the blade groove is, wherein the securing device has a holding piece which is arranged between the blade groove and the turbine blade root, wherein the holding piece has a projection which is arranged in a recess in the turbine blade root, the projection engaging in the recess such that a displacement of the holding piece in the axial direction is prevented, the securing device having a force spring which exerts a force acting in the radial direction from the rotor on the turbine blade.
  • the invention therefore proposes arranging a safety device in a space between the rotor and the turbine blade root.
  • This space is preferably arranged in the rotor.
  • the one formed by the space Notch shifted in a radially inner direction towards the axis of rotation. This means that the forces acting on the rotor are better distributed.
  • the holding piece is integrated directly into the blade root.
  • this is optionally pronounced on the front edge of the blade root or, preferably, on the rear edge of the blade root in the radially inner direction.
  • a development on the leading edge and trailing edge is possible here when implementing an axial recess, which continues to allow the modified blade to be pushed in axially.
  • the securing device has a metal sheet which is arranged in a second recess in the holding piece and in a rotor recess, the metal sheet engaging in the second recess and in the rotor recess in such a way that the sheet metal is prevented from shifting in the axial direction.
  • the sheet metal is arranged in a rotor recess and in a second recess in the holding piece and thus forms a lock for the holding piece so that it can be moved in the axial direction.
  • a force spring is arranged between the blade groove and the holding piece.
  • the force spring is advantageously arranged next to the holding piece between the blade groove and the blade root.
  • the blade root has a leading edge, seen in the axial direction, and a trailing edge, seen in the axial direction, opposite the leading edge, the holding piece protruding from the leading edge to the trailing edge.
  • a first locking plate is arranged on the front edge and a second locking plate is arranged on the rear edge.
  • a first force spring is arranged on the front edge and a second force spring is arranged on the rear edge.
  • the projection is elongated in the circumferential direction (with respect to the axis of rotation).
  • An elongated design is usually a comparatively simple manufacturing process, which will lead to cost savings here.
  • the rotor recess and the second recess are advantageously arranged one above the other in the radial direction.
  • Figure 1 shows a security device 1.
  • a part of a rotor 2 and a turbine blade root 3 can be seen.
  • the rotor has a blade groove 4.
  • This blade groove 4 can be a blade groove 4 formed parallel to an axis of rotation 5 of the rotor.
  • the blade groove 4 can also be a curved blade groove 4, which is then arranged on a leading edge in the axial direction 7.
  • the axis of rotation 5 and the axial direction 7 are arranged parallel to one another.
  • the rotor 2 rotates about the axis of rotation 5 at a rotational speed.
  • the turbine blade is adapted in the blade groove 4 so that there is as little clearance as possible between the turbine blade root 3 and the blade groove 4. Without a safety device 8, the turbine blade could be moved freely in the axial direction 7.
  • the rotor 2 and the turbine blade can be part of a turbo machine, for example a steam turbine.
  • a turbo machine starts up, the centrifugal forces are still comparatively low, and there are no centrifugal forces during transport. As a result, there is the possibility that the turbine blade can shift in the axial direction 7. This is prevented by a safety device 8. Above a certain rotation frequency, the centrifugal forces are so great that the turbine blade in the blade groove 4 presses against so-called supporting flanks 9 and thereby obtains a stable position. Above this specific rotation frequency, an axial displacement is difficult.
  • the safety device 8 is used to move the turbine blade effectively prevented in the axial 7 and radial direction.
  • the safety device 8 comprises a holding piece 10
  • Figures 1 to 5 show a first embodiment of the holding piece 10.
  • the holding piece 10 is arranged between the blade groove 4 and the turbine blade root 3.
  • the holding piece 10 comprises a front side 11 which is arranged on the front edge 6.
  • a rear side 12 is arranged on the opposite side to the front side 11 (only in Figure 2 visible).
  • the holding piece 10 has an upper side 13 and a lower side 14.
  • the top 13 is arranged opposite the bottom 14.
  • the top 13 rests on an underside of the turbine blade root 3, as in FIG Figure 2 is shown.
  • the front 11 and the front edge 6 are flush here.
  • the underside 14 of the holding piece 10 points in the direction of the axis of rotation 5.
  • the holding piece On the upper side 13, the holding piece has a projection 15 which, according to a first variant of the invention, is elongated in a circumferential direction 16.
  • the projection 15 has a rectangular cross section.
  • the projection 15 is formed over the entire upper side 13 and protrudes into a recess 17 in the turbine blade root 3.
  • the recess 17 is configured to be complementary to the projection 15. This means that the recess 17 also has an elongated shape and a right-angled cross section.
  • a displacement of the holding piece is no longer possible in the axial direction 7 when the projection is arranged in the recess 17, so that a displacement of the holding piece 10 in the axial direction 7 is prevented.
  • the security device 10 has a plate 19, which engages in a rotor recess 20 and in a second recess 21, so that a displacement of the sheet metal 19 in the axial direction 7 is prevented.
  • the second recess 21 is arranged in the holding piece 10.
  • the sheet 19 is pushed in from the side.
  • the sheet metal 19 is shaped such that it points in the circumferential direction 16.
  • the Figure 2 shows a cross-sectional view of this first variant of the holding piece 10 and the entire safety device 8.
  • Figures 3 and 4 show a perspective view of the holding piece 10 in its first variant.
  • the Figure 5 shows the sheet metal 19, which is formed in a circumferential direction 16.
  • the sheet metal has a sheet metal top side 22 which protrudes into the second recess 21.
  • the sheet metal underside 23 protrudes into the rotor recess 20.
  • the Figures 6 to 9 show a second variant of the safety device 8.
  • the difference between the securing device 8 according to the second variant and the securing device 8 of the first variant is that the projection 15 is not elongated, but is designed as a cylinder 24 and protrudes into a blind hole in the turbine blade root 3.
  • the cylinder 24 has a similar mode of operation as the projection 15 according to FIG. 1, namely that a displacement in the axial direction 7 is prevented.
  • FIGS. 7 and 8 show a perspective view of the holding piece 10 according to variant 2.
  • the Figure 9 shows the sheet 19 which is designed for variant 2, the sheet 19 according to variant 1 and variant 3 being identical.
  • the sheet metal 19 is arranged circumferentially in the circumferential direction 16 and is here segmented. This means that the sheet 19 consists of individual segments.
  • the sheet 19 is positively arranged in the rotor recess 20 and in the second recess.
  • the metal sheets 19 are introduced into a circumferential position via a milled opening in the circumferential groove and pushed to their final position. After the last segment has been introduced, the segments are connected to one another at the divisions by spot welding.
  • the force spring 18 is used to ensure that the turbine blade is in contact with the rotor 2 at a standstill, e.g. B. during transport.
  • the force spring 18 is designed, for example, as a plate spring.
  • the power spring 18 can also be designed as a clamping piece.
  • the Figures 10 to 13 show a third variant of the securing device 8.
  • the third variant is characterized in that the holding piece 10 and the force spring 18 are arranged next to one another in the axial direction 7. This means that the force spring 18 is arranged directly on the rotor 2 and directly on the turbine blade root 3 and the force is transmitted directly from the rotor 2 to the turbine blade root 3.
  • the holding piece 10 is arranged next to the power spring 18 in the axial direction 7.
  • the holding piece 10 also has a projection 15 and a second recess 21. According to the first variant, the projection 15 can be elongated. Likewise, the projection 15 according to the second variant can be designed as a cylinder.
  • the Figure 10 shows a cross-sectional view of the securing device 8 according to the third variant.
  • the Figures 11 and 12 show a perspective view of the holding piece 10.
  • FIGS Figure 13 shows a perspective view of the sheet metal 19.
  • the Figures 14 and 15 show a fourth variant of the securing device 8.
  • the securing device 8 according to the fourth variant is characterized in that the holding piece 10 is now formed from the front edge 6 of the turbine blade root 3 to the rear edge of the turbine blade root. This means that the holding piece 10 is arranged completely from the front edge 6 to the rear edge.
  • the holding piece 10 also has a projection 15 which is in a Recess 17 engages.
  • a plate 19 is also provided that engages in a second recess 21 and in a rotor recess 20.
  • the power spring 18 is also arranged between the holding piece 10 and the rotor 2.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

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 an die Schaufelnut angepasst ist, wobei die Sicherungseinrichtung ein Haltestück aufweist, das zwischen der Schaufelnut und dem Turbinenschaufelfuß angeordnet ist.The invention relates to a rotor comprising at least one turbine blade and a safety device for axially and radially securing the turbine blade, the rotor comprising a blade groove and the turbine blade comprising a turbine blade root, the blade groove and the turbine blade root being adapted to the blade groove, the safety device having a holding piece , which is arranged between the blade groove and the turbine blade root.

Schaufelbefestigungen werden in der Regel zum Befestigen von Laufschaufeln an einem Rotor einer Strömungsmaschine, insbesondere einer Dampfturbine verwendet. Durch die vergleichsweise hohe 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 zur Folge haben können. Korrosion und eine Wanderbewegung des Schaufelfußes durch die Dmpfbeaufschlagung oder Schwingungen innerhalb der Schaufelnut stellen weitere Probleme dar. Zum Festlegen des Turbinenschaufelfußes innerhalb der Schaufelnut sind verschiedene 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. Des Weiteren zeigen Metallkeile bei längerem Betrieb im Dampfmedium ein korrosives Verhalten, das die Demontage schwierig macht.Blade fastenings are generally used to fasten rotor blades to a rotor of a turbomachine, in particular a steam turbine. Due to the comparatively high rotation of the rotor, the rotor 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 forced radially outward in the blade groove. In addition to the centrifugal forces, strong vibration loads represent a further problem that can result in mechanical damage and material fatigue. Corrosion and a wandering movement of the blade root due to the application of damping or vibrations within the blade groove pose further problems. Various solutions such as metal wedges, spring washers or sealing pieces are known for fixing the turbine blade root within the blade groove. Metal wedges lock the associated blade root axially as well as radially within a blade groove, but with large rotor blades it is difficult with such metal wedges to generate sufficient holding forces during the rotation in the radial direction. Furthermore, metal wedges show a corrosive behavior during prolonged operation in the steam medium, which makes dismantling difficult.

Es sind axial gefädelte Laufschaufeln bekannt, die in Turbomaschinen wie beispielsweise Dampfturbinen, die aufgrund der Betriebsbeanspruchung eine Konstruktion benötigen, die die axialen Betriebskräfte der Turbinenschaufel aufnimmt und die Schaufel in ihrer axialen Position hält. Solche Sicherungen werden auch als axiale Sicherungen bezeichnet. In der Regel werden bei solchen axialen Sicherungen zwei Kerben angeordnet, die zueinander überlagert ausgebildet sind. Allerdings zeigen Überlagerungen von Kerben häufig eine erhöhte Beanspruchung und bedeuten somit eine begrenzte Anwendbarkeit im Turbomaschinenbau Beispiele von Schaufelbefestigungen an einem Rotor einer Strömungsmaschine sind aus EP 1892380 A1 , US 2847187 A , US5431543 A und US 4668167 A bekannt.Axially threaded rotor blades are known which are used in turbo machines such as steam turbines, for example, which, due to the operational stresses, require a construction which absorbs the axial operating forces of the turbine blade and holds the blade in its axial position. Such fuses are also referred to as axial fuses. As a rule, two notches are arranged in such axial securing devices, which are designed to be superimposed on one another. However, overlapping notches often show increased stress and thus mean limited applicability in turbo-machine construction. Examples of blade fastenings on a rotor of a turbo-machine are no longer available EP 1892380 A1 , US 2847187 A , US5431543 A and US 4668167 A known.

Der Erfindung liegt die Aufgabe zugrunde, eine Schaufelbefestigung bei einer Strömungsmaschine bereitzustellen, bei der über einen langen Betriebszeitraum hinweg eine präzise und feste Halterung von Schaufeln, den zugehörigen Schaufelhaltern, sichergestellt ist.The invention is based on the object of providing a blade attachment in a turbo-machine, in which a precise and firm attachment of blades, the associated blade holders, is ensured over a long period of operation.

Die Aufgabe wird gelöst durch einen Rotor gemäß Anspruch 1. Der Rotor umfasst 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 an die Schaufelnut angepasst ist, wobei die Sicherungseinrichtung ein Haltestück aufweist, das zwischen der Schaufelnut und dem Turbinenschaufelfuß angeordnet ist, wobei das Haltestück einen Vorsprung aufweist, der in eine Ausnehmung im Turbinenschaufelfuß angeordnet ist, wobei der Vorsprung in die Ausnehmung derart eingreift, dass ein Verschieben des Haltestücks in der axialen Richtung verhindert ist, wobei die Sicherungseinrichtung eine Kraftfeder aufweist, die eine in radialer Richtung wirkende Kraft von dem Rotor auf die Turbinenschaufel ausübt.The object is achieved by a rotor according to claim 1. The rotor comprises at least one turbine blade and a securing device for axially and radially securing the turbine blade, wherein the rotor comprises a blade groove and the turbine blade comprises a turbine blade root, the blade groove and the turbine blade root being adapted to the blade groove is, wherein the securing device has a holding piece which is arranged between the blade groove and the turbine blade root, wherein the holding piece has a projection which is arranged in a recess in the turbine blade root, the projection engaging in the recess such that a displacement of the holding piece in the axial direction is prevented, the securing device having a force spring which exerts a force acting in the radial direction from the rotor on the turbine blade.

Mit der Erfindung wird somit vorgeschlagen, in einen Raum zwischen dem Rotor und dem Turbinenschaufelfuß eine Sicherungseinrichtung anzuordnen. Dieser Raum ist vorzugszweise im Rotor angeordnet. Somit wird die durch den Raum gebildete Kerbe in eine radial innere Richtung zur Rotationsachse hin verschoben. Dadurch sind die angreifenden Kräfte auf den Rotor besser verteilt.The invention therefore proposes arranging a safety device in a space between the rotor and the turbine blade root. This space is preferably arranged in the rotor. Thus, the one formed by the space Notch shifted in a radially inner direction towards the axis of rotation. This means that the forces acting on the rotor are better distributed.

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

In einer Weiterbildung ist das Haltestück direkt in den Schaufelfuß integriert. Hierbei ist dies in axialer Richtung gesehen wahlweise an der Vorderkante des Schaufelfußes oder bevorzugterweise an der Hinterkante des Schaufelfußes in die radial innere Richtung ausgeprägt. Eine Ausprägung an der Vorderkante und Hinterkante ist hier möglich bei der Umsetzung einer axialen Ausnehmung, die das axiale Einschieben der modifizierten Schaufel weiterhin ermöglicht.In a further development, the holding piece is integrated directly into the blade root. Here, viewed in the axial direction, this is optionally pronounced on the front edge of the blade root or, preferably, on the rear edge of the blade root in the radially inner direction. A development on the leading edge and trailing edge is possible here when implementing an axial recess, which continues to allow the modified blade to be pushed in axially.

Gemäß der Erfindung weist die Sicherungseinrichtung ein Blech auf, das in einer zweiten Ausnehmung im Haltestück und in einer Rotorausnehmung angeordnet ist, wobei das Blech in die zweite Ausnehmung und in die Rotorausnehmung derart eingreift, dass ein Verschieben des Blechs in der axialen Richtung verhindert ist.According to the invention, the securing device has a metal sheet which is arranged in a second recess in the holding piece and in a rotor recess, the metal sheet engaging in the second recess and in the rotor recess in such a way that the sheet metal is prevented from shifting in the axial direction.

Somit wird ein wirksames Verschieben in axialer Richtung des Haltestücks wirksam vermieden. Das Blech wird hierbei in eine Rotorausnehmung und in eine zweite Ausnehmung im Haltestück angeordnet und bildet somit eine Sperre für das Haltestück um in axialer Richtung verschoben werden zu können.Effective displacement of the holding piece in the axial direction is thus effectively avoided. The sheet metal is arranged in a rotor recess and in a second recess in the holding piece and thus forms a lock for the holding piece so that it can be moved in the axial direction.

In einer vorteilhaften Weiterbildung ist zwischen der Schaufelnut und dem Haltestück eine Kraftfeder anordnet.In an advantageous development, a force spring is arranged between the blade groove and the holding piece.

Mit dieser Kraftfeder wird eine Kraft von dem Rotor auf den Turbinenschaufelfuß ausgeübt. Beim Transport sowie im Betrieb ist es wichtig, gerade bei niedrigen Rotationsgeschwindigkeiten eine Kraft auf den Turbinenschaufelfuß auszuüben, der in einer radialen Richtung wirkt. Dadurch ist ein Verschieben der Turbinenschaufel in axialer Richtung durch Reibungseffekte weiter vermieden. Ab einer bestimmten Rotationsgeschwindigkeit sind in radialer Richtung auf die Turbinenschaufel wirkende Fliehkräfte so groß, dass der Einfluss der Federkraft durch die Kraftfeder zu vernachlässigen ist.With this force spring, a force is exerted by the rotor on the turbine blade root. During transport as well as during operation, it is important, especially at low rotational speeds, to exert a force on the turbine blade root which acts in a radial direction. As a result, the turbine blade is displaced in the axial direction due to the effects of friction further avoided. From a certain rotational speed onwards, centrifugal forces acting on the turbine blade in the radial direction are so great that the influence of the spring force through the force spring can be neglected.

Vorteilhafterweise ist die Kraftfeder neben dem Haltestück zwischen der Schaufelnut und dem Schaufelfuß angeordnet.The force spring is advantageously arranged next to the holding piece between the blade groove and the blade root.

Dies ist eine besonders einfache und konstruktive Lösung, die durch einfache Mittel herstellbar ist.This is a particularly simple and constructive solution that can be produced by simple means.

In einer weiteren vorteilhaften Weiterbildung weist der Schaufelfuß eine in axialer Richtung gesehen angeordnete Vorderkante und in der axialen Richtung gesehen zur Vorderkante gegenüber angeordnete Hinterkante auf, wobei das Haltestück von der Vorderkante bis zur Hinterkante ragt.In a further advantageous development, the blade root has a leading edge, seen in the axial direction, and a trailing edge, seen in the axial direction, opposite the leading edge, the holding piece protruding from the leading edge to the trailing edge.

Hierbei wird nun erfindungsgemäß vorteilhafterweise vorgeschlagen, das Haltestück derart weiterzubilden, dass die Ausmaße in axialer Richtung derart sind, dass das Haltestück von der Vorderkante bis zur Hinterkante ragt.According to the invention, it is now advantageously proposed to further develop the holding piece in such a way that the dimensions in the axial direction are such that the holding piece protrudes from the front edge to the rear edge.

In einer weiteren vorteilhaften Weiterbildung ist ein erstes Sicherungsblech an der Vorderkante und ein zweites Sicherungsblech an der Hinterkante angeordnet.In a further advantageous development, a first locking plate is arranged on the front edge and a second locking plate is arranged on the rear edge.

Dadurch wird ein Verschieben in axialer Richtung des Haltestückes sowohl in die eine axiale Richtung als auch in die entgegengesetzt zeigende axiale Richtung wirksam verhindert.This effectively prevents the holding piece from being displaced in the axial direction both in one axial direction and in the opposite axial direction.

In einer weiteren vorteilhaften Weiterbildung ist eine erste Kraftfeder an der Vorderkante und eine zweite Kraftfeder an der Hinterkante angeordnet.In a further advantageous development, a first force spring is arranged on the front edge and a second force spring is arranged on the rear edge.

Dadurch können symmetrische Verteilungen von Kräften und Schwingungen weiter minimiert werden, die insbesondere beim Anfahren oder beim Transport auftreten.As a result, symmetrical distributions of forces and vibrations that occur in particular when starting up or during transport can be further minimized.

In einer weiteren vorteilhaften Weiterbildung ist der Vorsprung in Umfangsrichtung (bezogen auf die Rotationsachse) länglich ausgebildet.In a further advantageous development, the projection is elongated in the circumferential direction (with respect to the axis of rotation).

Eine längliche Ausbildung ist in der Regel ein vergleichsweise einfaches Herstellungsverfahren, was hier zu einer Kostenersparnis führen wird.An elongated design is usually a comparatively simple manufacturing process, which will lead to cost savings here.

Vorteilhafterweise sind die Rotorausnehmung und die zweite Ausnehmung in radialer Richtung übereinander angeordnet.The rotor recess and the second recess are advantageously arranged one above the other in the radial direction.

Durch die in radialer Richtung übereinander angeordnete Ausrichtung ist ein Verkippen des Blechs wirksam vermieden. Die oben beschriebenen Eigenschafen, Merkmale und Vorteile dieser Erfindung sowie die Art und Weise, wie diese erreicht werden, werden klarer und deutlicher verständlich im Zusammenhang mit der folgenden Beschreibung der Ausführungsbeispiele, die im Zusammenhang mit den Zeichnungen näher erläutert werden.Tilting of the sheet metal is effectively avoided by the alignment arranged one above the other in the radial direction. The above-described properties, features and advantages of this invention and the manner in which they are achieved will become clearer and more clearly understandable in connection with the following description of the exemplary embodiments, which are explained in more detail in connection with the drawings.

Ausführungsbeispiele der Erfindung werden nachfolgend anhand der Zeichnungen beschrieben. Diese sollen die Ausführungsbeispiele nicht maßgeblich darstellen, vielmehr ist die Zeichnung, wozu Erläuterungen dienlich, in schematisierter und/oder leicht verzehrter Form ausgeführt. Im Hinblick auf Ergänzungen der in der Zeichnung unmittelbar erkennbaren Lehren wird auf den einschlägigen Stand der Technik verwiesen.Embodiments of the invention are described below with reference to the drawings. These are not intended to represent the exemplary embodiments in a decisive manner; rather, the drawing, for which explanations are useful, is made in a schematic and / or slightly consumed form. With regard to additions to the teachings that can be seen directly in the drawing, reference is made to the relevant prior art.

Es zeigen:

Figur 1
eine perspektivische Ansicht einer Sicherungseinrichtung,
Figur 2
eine Querschnittsansicht einer ersten Variante der Sicherungseinrichtung,
Figur 3
eine perspektivische Darstellung des Haltestücks gemäß der ersten Variante aus Figur 2,
Figur 4
eine weitere perspektivische Darstellung des Haltestücks aus Figur 3,
Figur 5
eine perspektivische Darstellung eines Blechs,
Figur 6
eine Querschnittsansicht einer Sicherungseinrichtung gemäß einer zweiten Variante,
Figur 7
eine perspektivische Darstellung des Haltestücks gemäß der zweiten Variante aus Figur 6,
Figur 8
eine weitere perspektivische Darstellung des Haltestücks aus Figur 7,
Figur 9
eine perspektivische Darstellung des Blechs,
Figur 10
eine Querschnittsansicht einer Sicherungseinrichtung gemäß einer dritten Variante,
Figur 11
eine perspektivische Ansicht des Haltestücks gemäß der dritten Variante,
Figur 12
eine weitere perspektivische Ansicht des haltestücks gemäß Figur 11 für die dritte Variante,
Figur 13
Darstellung des Blechs für die dritte Variante,
Figur 14
Querschnittsansicht der Sicherungseinrichtung gemäß einer vierten Variante,
Figur 15
Querschnittsansicht eines Teils der Sicherungseinrichtung gemäß der vierten Variante.
Show it:
Figure 1
a perspective view of a safety device,
Figure 2
a cross-sectional view of a first variant of the safety device,
Figure 3
a perspective view of the holding piece according to the first variant Figure 2 ,
Figure 4
a further perspective view of the holding piece Figure 3 ,
Figure 5
a perspective view of a sheet metal,
Figure 6
a cross-sectional view of a security device according to a second variant,
Figure 7
a perspective view of the holding piece according to the second variant Figure 6 ,
Figure 8
a further perspective view of the holding piece Figure 7 ,
Figure 9
a perspective view of the sheet metal,
Figure 10
a cross-sectional view of a security device according to a third variant,
Figure 11
a perspective view of the holding piece according to the third variant,
Figure 12
a further perspective view of the holding piece according to FIG Figure 11 for the third variant,
Figure 13
Representation of the sheet for the third variant,
Figure 14
Cross-sectional view of the safety device according to a fourth variant,
Figure 15
Cross-sectional view of part of the securing device according to the fourth variant.

Figur 1 zeigt eine Sicherungseinrichtung 1. Gemäß Figur 1 ist ein Teil eines Rotors 2 und eines Turbinenschaufelfußes 3 zu sehen. Der Übersichtlichkeit wegen ist das Schaufelblatt der Turbinenschaufel nicht dargestellt. Der Rotor weist eine Schaufelnut 4 auf. Diese Schaufelnut 4 kann eine parallel zu einer Rotationsachse 5 des Rotors ausgebildete Schaufelnut 4 sein. Die Schaufelnut 4 kann ebenso eine gebogene Schaufelnut 4 sein, die dann an einer Vorderkante in axialer Richtung 7 angeordnet ist. Figure 1 shows a security device 1. According to Figure 1 a part of a rotor 2 and a turbine blade root 3 can be seen. For the sake of clarity, the blade of the turbine blade is not shown. The rotor has a blade groove 4. This blade groove 4 can be a blade groove 4 formed parallel to an axis of rotation 5 of the rotor. The blade groove 4 can also be a curved blade groove 4, which is then arranged on a leading edge in the axial direction 7.

Die Rotationsachse 5 und die axiale Richtung 7 sind parallel zueinander angeordnet. Der Rotor 2 rotiert um die Rotationsachse 5 mit einer Drehgeschwindigkeit. Die Turbinenschaufel ist in der Schaufelnut 4 angepasst, so dass möglichst wenig Spielraum zwischen dem Turbinenschaufelfuß 3 und der Schaufelnut 4 entsteht. Ohne Sicherungseinrichtung 8 könnte die Turbinenschaufel in der axialen Richtung 7 frei verschoben werden.The axis of rotation 5 and the axial direction 7 are arranged parallel to one another. The rotor 2 rotates about the axis of rotation 5 at a rotational speed. The turbine blade is adapted in the blade groove 4 so that there is as little clearance as possible between the turbine blade root 3 and the blade groove 4. Without a safety device 8, the turbine blade could be moved freely in the axial direction 7.

Der Rotor 2 und die Turbinenschaufel können Teil einer Turbomaschine, beispielsweise einer Dampfturbine sein. Während des Anfahrens einer Strömungsmaschine sind die Fliehkräfte noch vergleichsweise gering, beim Transport sind keinerlei Fliehkräfte vorhanden. Dadurch besteht die Möglichkeit, dass die Turbinenschaufel sich in der axialen Richtung 7 verschieben kann. Dies wird verhindert durch eine Sicherungseinrichtung 8. Ab einer gewissen Rotationsfrequenz sind die Fliehkräfte derart groß, dass die Turbinenschaufel in der Schaufelnut 4 gegen sogenannte Tragflanken 9 drückt und dadurch eine stabile Position erhält. Ab dieser bestimmten Rotationsfrequenz ist ein axiales Verschieben schwer möglich. Mit der Sicherungseinrichtung 8 ist ein Verschieben der Turbinenschaufel in axialer 7 und radialer Richtung wirksam verhindert. Die Sicherungseinrichtung 8 umfasst ein Haltestück 10. Die Figuren 1 bis 5 zeigen eine erste Ausführung des Haltestücks 10. Das Haltestück 10 wird zwischen der Schaufelnut 4 und dem Turbinenschaufelfuß 3 angeordnet. Das Haltestück 10 umfasst eine Vorderseite 11 auf, das an der Vorderkante 6 angeordnet ist. An der gegenüberliegenden Seite zur Vorderseite 11 ist eine Rückseite 12 angeordnet (lediglich in Figur 2 sichtbar). Das Haltestück 10 weist eine Oberseite 13 und eine Unterseite 14 auf. Die Oberseite 13 ist gegenüber der Unterseite 14 angeordnet. Die Oberseite 13 liegt an einer Unterseite des Turbinenschaufelfußes 3 an, wie es in der Figur 2 dargestellt ist. Die Vorderseite 11 und die Vorderkante 6 sind hierbei bündig. Die Unterseite 14 des Haltestücks 10 zeigt in Richtung der Rotationsachse 5.The rotor 2 and the turbine blade can be part of a turbo machine, for example a steam turbine. When a turbo machine starts up, the centrifugal forces are still comparatively low, and there are no centrifugal forces during transport. As a result, there is the possibility that the turbine blade can shift in the axial direction 7. This is prevented by a safety device 8. Above a certain rotation frequency, the centrifugal forces are so great that the turbine blade in the blade groove 4 presses against so-called supporting flanks 9 and thereby obtains a stable position. Above this specific rotation frequency, an axial displacement is difficult. The safety device 8 is used to move the turbine blade effectively prevented in the axial 7 and radial direction. The safety device 8 comprises a holding piece 10 Figures 1 to 5 show a first embodiment of the holding piece 10. The holding piece 10 is arranged between the blade groove 4 and the turbine blade root 3. The holding piece 10 comprises a front side 11 which is arranged on the front edge 6. A rear side 12 is arranged on the opposite side to the front side 11 (only in Figure 2 visible). The holding piece 10 has an upper side 13 and a lower side 14. The top 13 is arranged opposite the bottom 14. The top 13 rests on an underside of the turbine blade root 3, as in FIG Figure 2 is shown. The front 11 and the front edge 6 are flush here. The underside 14 of the holding piece 10 points in the direction of the axis of rotation 5.

Auf der Oberseite 13 weist das Haltestück einen Vorsprung 15 auf, der gemäß einer ersten Variante der Erfindung in einer Umfangsrichtung 16 länglich ausgebildet ist. Der Vorsprung 15 weist einen rechtwinkligen Querschnitt auf. Der Vorsprung 15 ist über die komplette Oberseite 13 ausgebildet und ragt in eine Ausnehmung 17 im Turbinenschaufelfuß 3. Die Ausnehmung 17 ist hierbei komplementär zum Vorsprung 15 ausgebildet. Das bedeutet, dass die Ausnehmung 17 ebenso eine längliche Form und einen rechtwinkligen Querschnitt aufweist.On the upper side 13, the holding piece has a projection 15 which, according to a first variant of the invention, is elongated in a circumferential direction 16. The projection 15 has a rectangular cross section. The projection 15 is formed over the entire upper side 13 and protrudes into a recess 17 in the turbine blade root 3. The recess 17 is configured to be complementary to the projection 15. This means that the recess 17 also has an elongated shape and a right-angled cross section.

Ein Verschieben des Haltestücks ist, wenn der Vorsprung in der Ausnehmung 17 angeordnet ist, in axialer Richtung 7 nicht mehr möglich, so dass ein Verschieben des Haltestücks 10 in der axialen Richtung 7 verhindert ist.A displacement of the holding piece is no longer possible in the axial direction 7 when the projection is arranged in the recess 17, so that a displacement of the holding piece 10 in the axial direction 7 is prevented.

Wie in Figur 2 dargestellt, ist zwischen der Unterseite 14 und dem Rotor 2 ein Raum, in dem eine Kraftfeder 18 angeordnet ist. Die Kraftfeder 18 führt zu einer Kraft von dem Rotor 2 auf das Haltestück 10 und schließlich dann auf den Turbinenschaufelfuß 3. Durch diese Kraft wird verhindert, dass das Haltestück 10 aus der Ausnehmung 17 springt. Zur weiteren Sicherung weist die Sicherungseinrichtung 10 ein Blech 19 auf, das in eine Rotorausnehmung 20 und in eine zweite Ausnehmung 21 eingreift, so dass ein Verschieben des Blechs 19 in axialer Richtung 7 verhindert ist. Die zweite Ausnehmung 21 ist im Haltestück 10 angeordnet. Das Blech 19 wird hierbei von der Seite eingeschoben. Das Blech 19 ist derart geformt, dass es in die Umfangsrichtung 16 zeigt.As in Figure 2 shown, between the bottom 14 and the rotor 2 is a space in which a power spring 18 is arranged. The force spring 18 leads to a force from the rotor 2 on the holding piece 10 and then finally on the turbine blade root 3. This force prevents the holding piece 10 from jumping out of the recess 17. For further security, the security device 10 has a plate 19, which engages in a rotor recess 20 and in a second recess 21, so that a displacement of the sheet metal 19 in the axial direction 7 is prevented. The second recess 21 is arranged in the holding piece 10. The sheet 19 is pushed in from the side. The sheet metal 19 is shaped such that it points in the circumferential direction 16.

Die Figur 2 zeigt eine Querschnittsansicht dieser ersten Variante des Haltestücks 10 und der gesamten Sicherungseinrichtung 8. Die Figuren 3 und 4 zeigen eine perspektivische Ansicht des Haltestücks 10 in seiner ersten Variante. Die Figur 5 zeigt das Blech 19, das in einer Umfangsrichtung 16 ausgebildet ist. Das Blech weist eine Blechoberseite 22, das in die zweite Ausnehmung 21 ragt. Die Blechunterseite 23 ragt in die Rotorausnehmung 20.The Figure 2 shows a cross-sectional view of this first variant of the holding piece 10 and the entire safety device 8. Figures 3 and 4 show a perspective view of the holding piece 10 in its first variant. The Figure 5 shows the sheet metal 19, which is formed in a circumferential direction 16. The sheet metal has a sheet metal top side 22 which protrudes into the second recess 21. The sheet metal underside 23 protrudes into the rotor recess 20.

Die Figuren 6 bis 9 zeigen eine zweite Variante der Sicherungseinrichtung 8.The Figures 6 to 9 show a second variant of the safety device 8.

Der Unterschied der Sicherungseinrichtung 8 gemäß der zweiten Variante gegenüber der Sicherungseinrichtung 8 der ersten Variante ist, dass der Vorsprung 15 nicht länglich ausgebildet ist, sondern als Zylinder 24 ausgeführt ist und in eine Sacklochbohrung im Turbinenschaufelfuß 3 hineinragt. Der Zylinder 24 hat hierbei eine ähnliche Wirkungsweise wie der Vorsprung 15 gemäß 1, nämlich dass ein Verschieben in axialer Richtung 7 verhindert wird.The difference between the securing device 8 according to the second variant and the securing device 8 of the first variant is that the projection 15 is not elongated, but is designed as a cylinder 24 and protrudes into a blind hole in the turbine blade root 3. The cylinder 24 has a similar mode of operation as the projection 15 according to FIG. 1, namely that a displacement in the axial direction 7 is prevented.

Die Figuren 7 und 8 zeigen eine perspektivische Ansicht des Haltestücks 10 gemäß der Variante 2.The Figures 7 and 8 show a perspective view of the holding piece 10 according to variant 2.

Die Figur 9 zeigt das Blech 19, das für die Variante 2 ausgebildet ist, wobei das Blech 19 gemäß Variante 1 und Variante 3 identisch ist.The Figure 9 shows the sheet 19 which is designed for variant 2, the sheet 19 according to variant 1 and variant 3 being identical.

Das Blech 19 ist in Umfangsrichtung 16 umlaufend angeordnet und ist hierbei segmentiert ausgeführt. Das bedeutet, dass das Blech 19 aus einzelnen Segmenten besteht. Das Blech 19 ist formschlüssig in der Rotorausnehmung 20 und in der zweiten Ausnehmung angeordnet. Die Bleche 19 werden über eine angefräste Öffnung der umlaufenden Nut an eine Umfangsposition eingeführt und an ihre finale Position geschoben, nach Einführen des letzten Segmentes werden die Segmente an den Teilungen miteinander durch Punktschweißung verbunden. Die Kraftfeder 18 dient zur Sicherstellung der Anlage der Turbinenschaufel an den Rotor 2 unter Stillstand, z. B. während des Transportes. Die Kraftfeder 18 ist beispielsweise als Tellerfeder ausgebildet. Die Kraftfeder 18 kann aber ebenso auch als Klemmstück ausgeführt werden.The sheet metal 19 is arranged circumferentially in the circumferential direction 16 and is here segmented. This means that the sheet 19 consists of individual segments. The sheet 19 is positively arranged in the rotor recess 20 and in the second recess. The metal sheets 19 are introduced into a circumferential position via a milled opening in the circumferential groove and pushed to their final position. After the last segment has been introduced, the segments are connected to one another at the divisions by spot welding. The force spring 18 is used to ensure that the turbine blade is in contact with the rotor 2 at a standstill, e.g. B. during transport. The force spring 18 is designed, for example, as a plate spring. The power spring 18 can also be designed as a clamping piece.

Die Figuren 10 bis 13 zeigen eine dritte Variante der Sicherungseinrichtung 8. Die dritte Variante zeichnet sich dadurch aus, dass das Haltestück 10 und die Kraftfeder 18 nebeneinander in axialer Richtung 7 angeordnet sind. Das bedeutet, dass die Kraftfeder 18 direkt auf dem Rotor 2 und direkt auf dem Turbinenschaufelfuß 3 angeordnet ist und die Kraft direkt vom Rotor 2 auf den Turbinenschaufelfuß 3 übertragen wird. Das Haltestück 10 ist in axialer Richtung 7 neben der Kraftfeder 18 angeordnet. Das Haltestück 10 weist ebenso einen Vorsprung 15 und eine zweite Ausnehmung 21 auf. Der Vorsprung 15 kann gemäß der ersten Variante länglich ausgebildet sein. Ebenso kann der Vorsprung 15 gemäß der zweiten Variante als Zylinder ausgebildet sein. Die Figur 10 zeigt eine Querschnittsansicht der Sicherungseinrichtung 8 gemäß der dritten Variante. Die Figuren 11 und 12 zeigen eine perspektivische Ansicht des Haltestücks 10. Die Figur 13 zeigt eine perspektivische Ansicht des Blechs 19.The Figures 10 to 13 show a third variant of the securing device 8. The third variant is characterized in that the holding piece 10 and the force spring 18 are arranged next to one another in the axial direction 7. This means that the force spring 18 is arranged directly on the rotor 2 and directly on the turbine blade root 3 and the force is transmitted directly from the rotor 2 to the turbine blade root 3. The holding piece 10 is arranged next to the power spring 18 in the axial direction 7. The holding piece 10 also has a projection 15 and a second recess 21. According to the first variant, the projection 15 can be elongated. Likewise, the projection 15 according to the second variant can be designed as a cylinder. The Figure 10 shows a cross-sectional view of the securing device 8 according to the third variant. The Figures 11 and 12 show a perspective view of the holding piece 10. FIGS Figure 13 shows a perspective view of the sheet metal 19.

Die Figuren 14 und 15 zeigen eine vierte Variante der Sicherungseinrichtung 8. Die Sicherungseinrichtung 8 gemäß der vierten Variante zeichnet sich dadurch aus, dass das Haltestück 10 nunmehr von der Vorderkante 6 des Turbinenschaufelfußes 3 bis zur Hinterkante des Turbinenschaufelfußes ausgebildet ist. Das bedeutet, dass das Haltestück 10 komplett von der Vorderkante 6 bis zur Hinterkante angeordnet ist. Das Haltestück 10 weist ebenso einen Vorsprung 15 auf, der in eine Ausnehmung 17 eingreift. Des Weiteren ist ebenso ein Blech 19 vorgesehen, dass in eine zweite Ausnehmung 21 und in eine Rotorausnehmung 20 eingreift. Die Kraftfeder 18 ist ebenso zwischen dem Haltestück 10 und dem Rotor 2 ausgeordnet.The Figures 14 and 15 show a fourth variant of the securing device 8. The securing device 8 according to the fourth variant is characterized in that the holding piece 10 is now formed from the front edge 6 of the turbine blade root 3 to the rear edge of the turbine blade root. This means that the holding piece 10 is arranged completely from the front edge 6 to the rear edge. The holding piece 10 also has a projection 15 which is in a Recess 17 engages. Furthermore, a plate 19 is also provided that engages in a second recess 21 and in a rotor recess 20. The power spring 18 is also arranged between the holding piece 10 and the rotor 2.

Obwohl die Erfindung im Detail durch das bevorzugte Ausführungsbeispiel näher illustriert und beschrieben wurde, so ist die Erfindung nicht durch die offenbarten Beispiele eingeschränkt und andere Variationen können vom Fachmann hieraus abgeleitet werden, solange diese den durch die Ansprüche definierten Schutzumfang der Erfindung nicht verlassen.Although the invention has been illustrated and described in detail by the preferred exemplary embodiment, the invention is not restricted by the disclosed examples and other variations can be derived therefrom by the person skilled in the art, as long as they do not depart from the scope of protection of the invention defined by the claims.

Claims (14)

  1. Rotor (2) for a continuous-flow machine, comprising at least one turbine blade
    and a securing device (1) for axially and radially securing the turbine blade,
    wherein the rotor (2) comprises a blade groove (4) and the turbine blade comprises a turbine blade root (3), wherein the turbine blade root (3) is adapted to the blade groove (4),
    wherein the securing device (1) has a retaining piece (10) which is arranged between the blade groove (4) and the turbine blade root (3),
    wherein the retaining piece (10) has a surface facing towards the turbine blade root (3),
    wherein the surface bears against the turbine blade root (3),
    wherein the retaining piece (10) has on the surface a projection (15) which is arranged in a recess (17) in the turbine blade root (4), wherein the projection (15) engages into the recess (17) in such a way that displacement of the retaining piece (10) in the axial direction (7) is prevented,
    wherein the securing device (1) has a force spring (18) which exerts on the turbine blade a force, acting in the radial direction, from the rotor (2),
    characterized in that
    the securing device (1) has a plate (19) which is arranged in a second recess (21) in the retaining piece (10) and in a rotor recess (20), wherein the plate (19) engages into the second recess (21) and into the rotor recess (20) in such a way that displacement of the plate (19) in the axial direction (7) is prevented.
  2. Rotor (2) according to Claim 1,
    wherein the force spring is formed as a separate component.
  3. Rotor (2) according to Claim 1 or 2,
    wherein the recess (17) is of complementary design with respect to the projection (15).
  4. Rotor (2) according to Claim 1, 2 or 3,
    wherein the projection is of rectangular cross section.
  5. Rotor according to Claim 1 or 2,
    wherein the force spring (18) is arranged between the blade groove (4) and the retaining piece (10).
  6. Rotor (2) according to Claim 1 or 2,
    wherein the force spring (18) is arranged next to the retaining piece (10), between the blade groove (4) and the blade root (3).
  7. Rotor (2) according to one of the preceding claims,
    wherein the blade root (3) has an arranged front edge (6), as seen in the axial direction (7), and a rear edge arranged opposite the front edge (6), as seen in the axial direction (7),
    wherein the retaining piece (10) extends from the front edge (6) to the rear edge.
  8. Rotor (2) according to Claim 7,
    wherein a first securing plate is arranged at the front edge (6) and a second securing plate is arranged at the rear edge.
  9. Rotor (2) according to Claim 7,
    wherein a first force spring (18) is arranged at the front edge (6) and a second force spring is arranged at the rear edge.
  10. Rotor (2) according to one of the preceding claims,
    wherein the projection (15) is of elongate design in a circumferential direction which is oriented with respect to the axis of rotation (5) of the rotor (2).
  11. Rotor (2) according to one of the preceding claims,
    wherein the rotor recess (20) and the second recess (21) are arranged one on top of the other in the radial direction.
  12. Rotor (2) according to one of the preceding claims,
    wherein the securing device (1) is arranged in a device recess in the rotor (2).
  13. Rotor (2) according to one of the preceding claims,
    wherein the force spring (18) is designed as a disc spring.
  14. Rotor (2) according to one of the preceding claims,
    wherein the retaining piece (10) is part of the turbine blade root (3).
EP16700042.1A 2015-01-20 2016-01-05 Rotor comprising a turbine blade with a locking device Active EP3212895B1 (en)

Applications Claiming Priority (2)

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EP15151806.5A EP3048256A1 (en) 2015-01-20 2015-01-20 Rotor comprising a turbine blade with a locking device
PCT/EP2016/050066 WO2016116285A1 (en) 2015-01-20 2016-01-05 Blade fastening mechanism having a securing device for turbine blades

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Publication Number Publication Date
EP3212895A1 EP3212895A1 (en) 2017-09-06
EP3212895B1 true EP3212895B1 (en) 2021-03-17

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EP (2) EP3048256A1 (en)
JP (1) JP6527959B2 (en)
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CN (1) CN107208490B (en)
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KR102236266B1 (en) 2017-11-17 2021-04-05 한화에어로스페이스 주식회사 Rotating apparatus
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KR102454379B1 (en) * 2020-09-08 2022-10-14 두산에너빌리티 주식회사 rotor and turbo-machine comprising the same
US11208903B1 (en) * 2020-11-20 2021-12-28 Solar Turbines Incorporated Stiffness coupling and vibration damping for turbine blade shroud
KR102478172B1 (en) 2021-02-02 2022-12-14 두산에너빌리티 주식회사 Rotary machine, gas turbine including the same, assembling method of the same
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FR2586061B1 (en) * 1985-08-08 1989-06-09 Snecma MULTIFUNCTIONAL LABYRINTH DISC FOR TURBOMACHINE ROTOR
JPS6469702A (en) 1987-09-09 1989-03-15 Hitachi Ltd Fixation of movable blade of axial flow rotary machine
JPH01237304A (en) * 1988-03-15 1989-09-21 Toshiba Corp Steam turbine bucket pushing-up device
US5236309A (en) 1991-04-29 1993-08-17 Westinghouse Electric Corp. Turbine blade assembly
US5431543A (en) * 1994-05-02 1995-07-11 Westinghouse Elec Corp. Turbine blade locking assembly
FR2807096B1 (en) * 2000-03-30 2002-05-31 Abb Alstom Power Nv ROTOR DISC OF TURBINE EQUIPPED WITH FINS ON FOOT AND TREE OF MOUNTING A FIN ON A DISC
EP1892380A1 (en) 2006-08-25 2008-02-27 Siemens Aktiengesellschaft Turbine blade retention system
EP1978211A1 (en) * 2007-04-04 2008-10-08 Siemens Aktiengesellschaft Assembly for axial protection on rotor blades in a rotor and gas turbine with such an assembly
EP2299060A1 (en) * 2009-09-17 2011-03-23 Siemens Aktiengesellschaft Blade fixation with locking device for turbine blades
JP5692994B2 (en) * 2009-12-08 2015-04-01 三菱重工業株式会社 Rotor blade fixing structure, rotating machine having the same, and rotor blade attaching / detaching method

Also Published As

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CN107208490B (en) 2019-08-06
US20180266259A1 (en) 2018-09-20
JP6527959B2 (en) 2019-06-12
CN107208490A (en) 2017-09-26
KR101942209B1 (en) 2019-01-24
EP3212895A1 (en) 2017-09-06
WO2016116285A1 (en) 2016-07-28
JP2018505994A (en) 2018-03-01
US10487674B2 (en) 2019-11-26
RU2668512C1 (en) 2018-10-01
EP3048256A1 (en) 2016-07-27
KR20170103010A (en) 2017-09-12

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