EP3788236B1 - Rotor comprising a rotor component arranged between two rotor disks - Google Patents

Rotor comprising a rotor component arranged between two rotor disks Download PDF

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Publication number
EP3788236B1
EP3788236B1 EP19752935.7A EP19752935A EP3788236B1 EP 3788236 B1 EP3788236 B1 EP 3788236B1 EP 19752935 A EP19752935 A EP 19752935A EP 3788236 B1 EP3788236 B1 EP 3788236B1
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EP
European Patent Office
Prior art keywords
rotor
annular projection
recesses
radially
retaining grooves
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP19752935.7A
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German (de)
French (fr)
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EP3788236A1 (en
Inventor
Peter Kury
Harald Hoell
Karsten Kolk
Vyacheslav Veitsman
Yulia Bagaeva
Christopher W. Ross
Peter Schröder
Andrew R. Waddell
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens Energy Global GmbH and Co KG
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Siemens Energy Global GmbH and Co KG
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Publication of EP3788236A1 publication Critical patent/EP3788236A1/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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and 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
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion 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
    • 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

Definitions

  • the invention relates to a rotor of a gas turbine, which has at least two rotor disks connected to one another, between which an annular rotor component is arranged.
  • annular rotor component for shielding the inner region of the rotor from the hot gas flowing through the gas turbine being arranged between the rotor disks.
  • the two rotor disks each have a plurality of rotor blades distributed on the outer circumference. Between the two rows of rotor blades there is a row with guide vanes distributed around the circumference, each of which is fastened to the stationary housing. Due to the rotation of the rotor, there is inevitably a gap between the guide vanes and the moving vanes. In principle, this made it possible for hot gas to enter the area radially inside the guide vanes.
  • an annular rotor component is arranged between the two adjacent rotor disks in order to keep the hot gas away from the interior of the rotor. For this purpose, this rotor component is mounted on both sides of the rotor disk.
  • the only task of the rotor component is to prevent hot gas from penetrating. Another function is usually not available. Accordingly, the mounting of the rotor component is kept simple in the usual way, with only one annular, axially extending shoulder engaging in a corresponding annular groove.
  • Unintentional rotation of the rotor component relative to the rotor disks is generally prevented in that there is an interference fit between the rotor component and one of the rotor disks in at least one location in the engagement of the annular shoulder in the annular groove.
  • two adjacent rotor disks each have an opposite annular, axially extending projection.
  • a rotor component for sealing the area between the two rotor disks is arranged between the rotor disks. This has a circumferential shoulder at each of the two axial ends, which rests against a projection of the corresponding rotor disk on the side pointing towards the rotor axis.
  • a projection In order to prevent a relative displacement of the rotor component relative to the rotor disks, provision is made in this case for a projection to have recesses into which engaging shoulders of the rotor component engage.
  • the object of the present invention is therefore to provide a rotor component by means of which the area between two rotor disks can be advantageously sealed and the blade retaining grooves of a rotor disk can be covered at least in sections.
  • the generic rotor is initially used in a gas turbine. Irrespective of this, however, it is also possible to use the embodiment of the rotor in another turbomachine, for example in a steam turbine.
  • At least the rotor has a first rotor disk and a second rotor disk which is directly and firmly connected to the first rotor disk.
  • the rotor disks each have a plurality of blade retaining grooves distributed on the outer circumference and penetrating the respective rotor disk axially. The blade retaining grooves are used here to hold moving blades.
  • first rotor disk has a peripheral radially below the blade retaining grooves, extending axially to the second Rotor disc towards extending first annular projection.
  • second rotor disk radially below the blade retaining grooves has a circumferential second annular projection that extends axially toward the first rotor disk.
  • An annular rotor component is arranged between the two rotor disks in the region of the blade retaining grooves and/or radially below the blade retaining grooves. This encloses sections of the rotor located within the rotor component, or sections of the two rotor disks.
  • the rotor component has a circumferential support section on each of its two axial ends. The first support section is located below the first annular projection on the side facing the rotor axis, and the second support section is located radially below the second annular projection. Provision can be made for the respective support section to rest against the annular projection with a press fit or leave a slight gap to the annular projection—while ensuring centering.
  • a coupling between the rotor component of the first rotor disk is produced radially outside of the annular projection, which coupling prevents relative displacement in the circumferential direction.
  • the first rotor disk has at least two first recesses distributed around the circumference.
  • the rotor component has complementary second engagement shoulders, which each engage in a corresponding first recess.
  • the first rotor disk has at least two first engagement shoulders distributed around the circumference.
  • the rotor component has complementary second recesses, so that the first engagement sections engage in the second recesses.
  • This embodiment brings about a reliable coupling between the rotor component and the rotor disks, so that a relative movement is prevented even if a press fit is lost. In this respect, no friction can occur between the components and negatively affect the service life.
  • the rotor component also has at least one circumferential, radially extending disk section. This is arranged at an axial end and can partially cover the rotor disk and the blade retaining grooves.
  • An advantageous stabilization of the rotor component, in particular the disk section, and an advantageous securing of the connection between the rotor component and the rotor disks is achieved according to the invention by the disk section having a first area with a first material thickness in the axial direction and radially outside the first area a second area with an increased material thickness and has at least twice the material thickness.
  • the rotor component has at one axial end an axially opening first annular groove enclosing the first annular projection and opposite at the other axial end an axially opening second annular groove enclosing the second annular projection.
  • the flanks of the respective ring groove located on the side pointing towards the rotor axis are formed by the support sections.
  • the centering of the rotor component relative to the rotor disks under the various operating states can be improved if a radially outer flank of the first annular groove or a radially outer flank of the first annular groove rests against the first annular projection Flank of the second annular groove rests against the second annular projection.
  • the first recesses in the first rotor disk and/or the second recesses in the rotor component can be realized in different ways.
  • the first rotor disk or the rotor component has a peripheral annular shoulder for this purpose.
  • the recess interrupts the peripheral ring shoulder.
  • the recess is delimited on both sides by projections which extend in sections in the circumferential direction.
  • an engaging shoulder is arranged on both sides of a respective recess.
  • a first engagement shoulder of the first rotor disk engages in a second recess of the rotor component and a second engagement shoulder of the rotor component engages in a first recess of the first rotor disk, mutually adjacent in the circumferential direction.
  • first engagement sections in the first rotor disk are each positioned centrally between two blade retaining grooves. Accordingly, it is advantageous if the first recesses are each arranged as an extension of the blade retaining grooves.
  • these advantageously have a length in the circumferential direction that is less than the smallest distance between two blade retaining grooves.
  • connection is placed immediately above the annular projection.
  • the first rotor disk has the first engagement shoulders on the radially outward-facing side of the annular projection.
  • the second recesses in the rotor component are complementary to this necessary.
  • the rotor component advantageously has a first annular groove in which the first annular projection engages. Consequently, the recess is to be arranged on the radially outer flank of the annular groove.
  • the first engagement shoulder and thus the second recess is preferably to be arranged at a distance from the axially free end of the annular projection. This avoids additional loading by the second recess in the area of the groove base of the first annular groove.
  • the engagement heels can be realized in different ways.
  • a reliable connection with the engagement shoulders is created when they are formed in one piece with the first rotor disk and in one piece with the rotor component.
  • a thickened area is advantageously arranged on the side pointing away from the directly adjacent, ground-breaking side in order to form the second region.
  • the arrangement of the second recesses and/or the second engagement shoulders on the rotor component takes place in a particularly advantageous manner in the second area of the disc section.
  • a rotor in a first exemplary embodiment is sketched in longitudinal section only in the area of the rotor component 11 .
  • the further design of the rotor can be selected using conventional embodiments.
  • the rotor has at least a first rotor disk 01 and a second rotor disk 06.
  • a circumferential, axially extending ring projection 03, 08 is arranged on each of these 01, 06.
  • the rotor component 11 Between the rotor disks 01, 06 is the rotor component 11, which 11 has a circumferential annular groove 12, 17 for attachment to the rotor disks 01, 06, with the first annular projection 03 in the first annular groove 12 and the second annular projection 08 in the second annular groove 17 intervenes.
  • a support section 13, 18 formed by the rotor component 11 is located radially below the respective annular projection 03, 08. These 13, 18 are supported on the respective annular projection 03, 08, at least in the event of centrifugal force.
  • the rotor component 11 has a circumferential, radially extending disk section 20 .
  • the coupling between the rotor component 11 and the first rotor disk 01 is located in the radially outer area.
  • first rotor disk 01 in a perspective view.
  • Circumferential ring projection 03 can be seen, as well as blade retaining grooves 02 that penetrate axially through first rotor disk 01 radially outside.
  • first engagement step 05 Between each two blade retaining grooves 02 is a first engagement step 05.
  • first engagement sections 05 there is a corresponding first recess.
  • the 3 12 shows the rotor component 11 which is complementary thereto.
  • the circumferential annular grooves 12, 17 can again be seen, with those arranged on the side pointing towards the rotor axis Support sections 13, 18.
  • the disk section 20, which extends radially at one axial end directly adjacent to the first rotor disk 01, is divided into a radially inner first area and a radially outer second area, with the second area having a cover 19 and thus at least twice the material thickness of the first area reached.
  • the second engagement projections 15 arranged on the rotor component 11 and the second recesses 14 in between are arranged opposite the cover 19 in the radially outer area.
  • Analog of the 1 show the 4 a rotor in a second exemplary embodiment.
  • the rotor has a first rotor disk 21 and a second rotor disk 26 .
  • a circumferential, axially extending ring projection 23, 28 is arranged.
  • the rotor component 31 is located between the rotor disks 21, 26 and has a circumferential annular groove 32, 37 in each case for attachment to the rotor disks 21, 26.
  • the rotor component 31 has a circumferential, radially extending disc section 40 .
  • the coupling between the rotor component 31 and the first rotor disk 21 is located immediately radially outside of the first annular projection 23.
  • the figure 5 shows the rotor component 31 in a perspective view.
  • the circumferential first annular groove 32 with the support sections arranged on the side pointing towards the rotor axis can again be seen.
  • the at one axial end immediately adjacent to the second rotor disk 26 radially extending Disk section 40 is analogous to that stated above.
  • the rotor component In contrast to the previous embodiment, provision is made in this case for the rotor component to have a peripheral annular shoulder 35 on the radially outer flank of the first annular groove 32 on the side facing the rotor axis. This 35 is interrupted several times by second recesses 34 distributed around the circumference.
  • the 6 shows the first rotor disk 21 in a perspective view.
  • the circumferential annular projection 23 and the blade retaining grooves 02 can be seen.
  • the first rotor disk 21 has the first engagement shoulders 25, which are complementary to the second recesses 34, on the radially outer side on the first annular projection 23.

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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 einer Gasturbine, welcher zumindest zwei miteinander verbundene Rotorscheiben aufweist, zwischen denen ein ringförmiges Rotorbauteil angeordnet ist.The invention relates to a rotor of a gas turbine, which has at least two rotor disks connected to one another, between which an annular rotor component is arranged.

Aus dem Stand der Technik sind verschiedene Ausführungen von Rotoren zur Verwendung bei Gasturbinen mit miteinander verbundenen Rotorscheiben bekannt, wobei zwischen den Rotorscheiben ein ringförmiges Rotorbauteil zur Abschirmung des inneren Bereichs des Rotors gegenüber dem die Gasturbine durchströmenden Heißgas angeordnet ist. Hierbei weisen die beiden Rotorscheiben jeweils am Außenumfang verteilt eine Mehrzahl Laufschaufeln auf. Zwischen den beiden Reihen an Laufschaufeln befindet sich eine Reihe mit im Umfang verteilt angeordneten Leitschaufeln, welche jeweils am ruhenden Gehäuse befestigt sind. Zwischen den Leitschaufeln und den Laufschaufeln ist hierbei aufgrund der Rotation des Rotors zwangsläufig ein Spalt vorhanden. Dieser ermöglichte grundsätzlich das Eintreten von Heißgas in den Bereich radial innerhalb der Leitschaufeln. Um das Heißgas vom inneren des Rotors abzuhalten wird bei einigen Gasturbinen zwischen den beiden benachbarten Rotorscheiben ein ringförmiges Rotorbauteil angeordnet wird. Hierzu wird dieses Rotorbauteil beidseitig an der Rotorscheibe gelagert.Various designs of rotors for use in gas turbines with rotor disks connected to one another are known from the prior art, an annular rotor component for shielding the inner region of the rotor from the hot gas flowing through the gas turbine being arranged between the rotor disks. In this case, the two rotor disks each have a plurality of rotor blades distributed on the outer circumference. Between the two rows of rotor blades there is a row with guide vanes distributed around the circumference, each of which is fastened to the stationary housing. Due to the rotation of the rotor, there is inevitably a gap between the guide vanes and the moving vanes. In principle, this made it possible for hot gas to enter the area radially inside the guide vanes. In some gas turbines, an annular rotor component is arranged between the two adjacent rotor disks in order to keep the hot gas away from the interior of the rotor. For this purpose, this rotor component is mounted on both sides of the rotor disk.

Das Rotorbauteil hat dem Grunde nach nur die Aufgabe, das Eindringen von Heißgas zu verhindern. Eine weitere Funktion ist in der Regel nicht vorhanden. Entsprechend wird in üblicher Weise die Lagerung des Rotorbauteils einfach gehalten, wobei lediglich ein ringförmiger, sich axial erstreckende Absatz in eine entsprechende ringförmige Nut eingreift.Basically, the only task of the rotor component is to prevent hot gas from penetrating. Another function is usually not available. Accordingly, the mounting of the rotor component is kept simple in the usual way, with only one annular, axially extending shoulder engaging in a corresponding annular groove.

Eine ungewollte Rotation des Rotorbauteils relativ zu den Rotorscheiben wird in aller Regel dadurch verhindert, dass an zumindest einer Stelle eine Presspassung zwischen dem Rotorbauteil und einer der Rotorscheiben im Eingriff des ringförmigen Absatzes in der ringförmigen Nut vorhanden ist.Unintentional rotation of the rotor component relative to the rotor disks is generally prevented in that there is an interference fit between the rotor component and one of the rotor disks in at least one location in the engagement of the annular shoulder in the annular groove.

Wenngleich die bekannten Ausführungen in aller Regel sich als tauglich erwiesen haben kann es jedoch zu Betriebszuständen kommen, bei denen die Presspassung nicht hinreichend eine relative Drehung des Rotorbauteils verhindern kann. Sofern hierbei keinerlei Schäden auftreten, wird dieses bei dem rotationsförmigen Rotorbauteil üblicherweise toleriert.Although the known designs have generally proven to be suitable, operating conditions can arise in which the interference fit cannot adequately prevent relative rotation of the rotor component. If no damage occurs, this is usually tolerated in the rotating rotor component.

Mit der Forderung der Erhöhung der Lebensdauer des Rotors wird jedoch eine ungewollte Relativbewegung zwischen dem Rotorbauteil und den Rotorscheiben kritisch gesehen, als dass hierdurch das Ziel einer Steigerung der Lebensdauer nicht gefährdet werden darf.With the requirement to increase the service life of the rotor, however, an undesired relative movement between the rotor component and the rotor disks is viewed critically, as this must not jeopardize the goal of increasing the service life.

Zur Lösung dieses Problems ist es beispielsweise aus der EP 0169800 A1 bekannt. Bei dieser Lösung weisen zwei benachbarte Rotorscheiben jeweils einen gegenüberliegenden ringförmigen sich axial erstreckenden Vorsprung auf. Zwischen den Rotorscheiben ist ein Rotorbauteil zur Abdichtung des Bereichs zwischen den beiden Rotorscheiben angeordnet. Dieser weist an den beiden axialen Enden jeweils einen umlaufenden Absatz auf, welche auf der zur Rotorachse weisenden Seite jeweils an einem Vorsprung der entsprechenden Rotorscheibe anliegen. Zur Verhinderung einer relativen Verschiebung des Rotorbauteils relativ zu den Rotorscheiben ist in diesem Fall vorgesehen, dass ein Vorsprung Ausnehmungen aufweist, in die Eingriffsabsätze des Rotorbauteils eingreifen.To solve this problem, it is, for example, from the EP 0169800 A1 known. In this solution, two adjacent rotor disks each have an opposite annular, axially extending projection. A rotor component for sealing the area between the two rotor disks is arranged between the rotor disks. This has a circumferential shoulder at each of the two axial ends, which rests against a projection of the corresponding rotor disk on the side pointing towards the rotor axis. In order to prevent a relative displacement of the rotor component relative to the rotor disks, provision is made in this case for a projection to have recesses into which engaging shoulders of the rotor component engage.

Aus der bekannten Ausführung ist es weiterhin bekannt, die Schaufelhaltenuten einer Rotorscheibe mit einer Seitenplatte abzudecken. Hierbei wird das Rotorbauteil eingesetzt, um die Seitenplatten zu fixieren.It is also known from the known design to cover the blade retaining grooves of a rotor disk with a side plate. Here, the rotor component is used to fix the side plates.

Wenngleich die bekannte Ausführung sich dem Grunde nach bewährt hat, so führt die Forderung nach einer höheren Dichtigkeit zu der Erkenntnis, dass eine einteilige Ausführung von Rotorbauteil und Seitenplatte vorteilhaft wäre. Jedoch ist bisher eine derartige Ausführung an den sich einstellenden Verformungen am Rotorbauteil gescheitert.Although the known design has basically proven itself, the demand for greater tightness leads to the finding that a one-piece design of the rotor component and side plate would be advantageous. However, such a design has hitherto failed due to the deformations that occur on the rotor component.

Aufgabe der vorliegenden Erfindung ist es daher ein Rotorbauteil zur Verfügung zu stellen, mittels der Bereich zwischen zwei Rotorscheiben vorteilhaft abgedichtet werden kann und zumindest abschnittsweise die Schaufelhaltenuten einer Rotorscheibe abgedeckt werden können.The object of the present invention is therefore to provide a rotor component by means of which the area between two rotor disks can be advantageously sealed and the blade retaining grooves of a rotor disk can be covered at least in sections.

Die gestellte Aufgabe wird durch eine erfindungsgemäße Ausführungsform nach der Lehre des Anspruchs 1 gelöst. Vorteilhafte Ausführungsformen sind Gegenstand der Unteransprüche.The stated object is achieved by an embodiment according to the invention according to the teaching of claim 1. Advantageous embodiments are the subject matter of the dependent claims.

Der gattungsgemäße Rotor dient zunächst mal zur Verwendung bei einer Gasturbine. Unabhängig hiervon ist es jedoch ebenso möglich, die Ausführungsform des Rotors bei einer anderen Strömungsmaschine, beispielsweise bei einer Dampfturbine, zur Anwendung zu bringen.The generic rotor is initially used in a gas turbine. Irrespective of this, however, it is also possible to use the embodiment of the rotor in another turbomachine, for example in a steam turbine.

Zumindest weist der Rotor eine erste Rotorscheibe und eine mit der ersten Rotorscheibe unmittelbar und fest verbundene zweite Rotorscheibe auf. Hierbei besitzen die Rotorscheiben am Außenumfang verteilt jeweils eine Mehrzahl von die jeweilige Rotorscheibe jeweils axial durchdringende Schaufelhaltenuten. Die Schaufelhaltenuten dienen hierbei zur Aufnahme von Laufschaufeln.At least the rotor has a first rotor disk and a second rotor disk which is directly and firmly connected to the first rotor disk. In this case, the rotor disks each have a plurality of blade retaining grooves distributed on the outer circumference and penetrating the respective rotor disk axially. The blade retaining grooves are used here to hold moving blades.

Weiterhin weist die erste Rotorscheibe radial unterhalb der Schaufelhaltenuten einen umlaufenden, sich axial zur zweiten Rotorscheibe hin erstreckenden ersten Ringvorsprung auf. Analog weist die zweite Rotorscheibe radial unterhalb der Schaufelhaltenuten einen umlaufenden, sich axial zur ersten Rotorscheibe hin erstreckenden zweiten Ringvorsprung auf.Furthermore, the first rotor disk has a peripheral radially below the blade retaining grooves, extending axially to the second Rotor disc towards extending first annular projection. Similarly, the second rotor disk radially below the blade retaining grooves has a circumferential second annular projection that extends axially toward the first rotor disk.

Zwischen den beiden Rotorscheiben im Bereich der Schaufelhaltenuten und/oder radial unterhalb der Schaufelhaltenuten ist ein ringförmiges Rotorbauteil angeordnet. Dieses umschließt den sich abschnittsweise innerhalb des Rotorbauteils befindenden Rotor, bzw. Abschnitte der beiden Rotorscheiben. Zur Zentrierung des Rotorbauteils relativ zu den Rotorscheiben sowie zugleich zur Befestigung weist das Rotorbauteil an seinen beiden axialen Enden jeweils einen umlaufenden Stützabschnitt auf. Hierbei befinden sich der erste Stützabschnitt auf der zur Rotorachse weisenden Seite unterhalb des ersten Ringvorsprungs und der zweite Stützabschnitt radial unterhalb des zweiten Ringvorsprungs. Dabei kann vorgesehen sein, dass der jeweilige Stützabschnitt mit einer Presspassung am Ringvorsprung anliegt oder einen geringfügigen Spalt - bei Gewährleistung der Zentrierung - zum Ringvorsprung lässt.An annular rotor component is arranged between the two rotor disks in the region of the blade retaining grooves and/or radially below the blade retaining grooves. This encloses sections of the rotor located within the rotor component, or sections of the two rotor disks. For centering the rotor component relative to the rotor disks and at the same time for fastening, the rotor component has a circumferential support section on each of its two axial ends. The first support section is located below the first annular projection on the side facing the rotor axis, and the second support section is located radially below the second annular projection. Provision can be made for the respective support section to rest against the annular projection with a press fit or leave a slight gap to the annular projection—while ensuring centering.

Zur Gewährleistung der Lebensdauer in der Verbindung zwischen dem Rotorbauteil und den Rotorscheiben wird radial außerhalb des Ringvorsprunges eine Kopplung zwischen dem Rotorbauteil der ersten Rotorscheibe hergestellt, welche eine relative Verschiebung in Umfangsrichtung verhindert.In order to ensure the service life in the connection between the rotor component and the rotor disks, a coupling between the rotor component of the first rotor disk is produced radially outside of the annular projection, which coupling prevents relative displacement in the circumferential direction.

Hierzu weist in einer ersten Ausführung die erste Rotorscheibe zumindest zwei am Umfang verteilt angeordnete erste Ausnehmungen auf. Demgegenüber besitzt das Rotorbauteil komplementäre zweite Eingriffsabsätze, welche jeweils in eine entsprechende erste Ausnehmung eingreifen.For this purpose, in a first embodiment, the first rotor disk has at least two first recesses distributed around the circumference. In contrast, the rotor component has complementary second engagement shoulders, which each engage in a corresponding first recess.

In einer zweiten Ausführung besitzt die erste Rotorscheibe zumindest zwei am Umfang verteilt angeordnete erste Eingriffsabsätze auf. Hierzu weist das Rotorbauteil komplementäre zweite Ausnehmungen, sodass die ersten Eingriffsabschnitts in den zweiten Ausnehmungen eingreifen.In a second embodiment, the first rotor disk has at least two first engagement shoulders distributed around the circumference. For this purpose, the rotor component has complementary second recesses, so that the first engagement sections engage in the second recesses.

Durch diese Ausführungsform wird eine zuverlässige Kopplung zwischen dem Rotorbauteil und den Rotorscheiben bewirkt, so dass eine Relativbewegung auch bei Verlust einer Presspassung verhindert wird. Insofern kann keine Reibung zwischen den Bauteilen auftreten und die Lebensdauer negativ beeinflussen.This embodiment brings about a reliable coupling between the rotor component and the rotor disks, so that a relative movement is prevented even if a press fit is lost. In this respect, no friction can occur between the components and negatively affect the service life.

Erfindungsgemäß wird nunmehr eine Abschirmung gegen das Heißgas dadurch verbessert, indem das Rotorbauteil weiterhin zumindest einen umlaufenden, sich radial erstreckenden Scheibenabschnitt aufweist. Dieser wird hierbei an einem axialen Ende angeordnet und kann abschnittsweise die Rotorscheibe und die Schaufelhaltenuten abdecken.According to the invention, shielding against the hot gas is now improved in that the rotor component also has at least one circumferential, radially extending disk section. This is arranged at an axial end and can partially cover the rotor disk and the blade retaining grooves.

Eine vorteilhafte Stabilisierung des Rotorbauteils, insbesondere des Scheibenabschnitts sowie eine vorteilhafte Sicherung der Verbindung zwischen dem Rotorbauteil und den Rotorscheiben wird erfindungsgemäß erreicht, indem der Scheibenabschnitt einen ersten Bereich mit einer ersten Materialstärke in axialer Richtung und radial außerhalb des ersten Bereichs einen zweiten Bereich mit einer erhöhten und hierbei zumindest 2-fachen Materialstärke aufweist.An advantageous stabilization of the rotor component, in particular the disk section, and an advantageous securing of the connection between the rotor component and the rotor disks is achieved according to the invention by the disk section having a first area with a first material thickness in the axial direction and radially outside the first area a second area with an increased material thickness and has at least twice the material thickness.

Zur vorteilhaften Verbindung des Rotorbauteils mit den Rotorscheiben weist das Rotorbauteil an einem axialen Ende eine sich axial öffnende, den ersten Ringvorsprung umschließende erste Ringnut und gegenüberliegend am anderen axialen Ende sich axial öffnende, den zweiten Ringvorsprung umschließende zweite Ringnut auf. Hierbei werden die sich auf der zur Rotorachse weisenden Seite befindenden Flanken der jeweiligen Ringnut von den Stützabschnitten gebildet.For the advantageous connection of the rotor component to the rotor disks, the rotor component has at one axial end an axially opening first annular groove enclosing the first annular projection and opposite at the other axial end an axially opening second annular groove enclosing the second annular projection. In this case, the flanks of the respective ring groove located on the side pointing towards the rotor axis are formed by the support sections.

Die Zentrierung des Rotorbauteils relativ zu den Rotorscheiben unter den verschiedenen Betriebszuständen kann verbessert werden, wenn weiterhin eine radial äußere Flanke der ersten Ringnut am ersten Ringvorsprung anliegt bzw. eine radial äu-βere Flanke der zweiten Ringnut am zweiten Ringvorsprung anliegt.The centering of the rotor component relative to the rotor disks under the various operating states can be improved if a radially outer flank of the first annular groove or a radially outer flank of the first annular groove rests against the first annular projection Flank of the second annular groove rests against the second annular projection.

Die ersten Ausnehmungen in der ersten Rotorscheibe und/oder die zweiten Ausnehmungen im Rotorbauteil können unterschiedlich realisiert werden. In einer einfachen Ausführungsform weist hierzu die erste Rotorscheibe bzw. das Rotorbauteil einen umlaufenden Ringabsatz auf. Entsprechend unterbricht hierbei die Ausnehmung den umlaufenden Ringabsatz.The first recesses in the first rotor disk and/or the second recesses in the rotor component can be realized in different ways. In a simple embodiment, the first rotor disk or the rotor component has a peripheral annular shoulder for this purpose. Correspondingly, the recess interrupts the peripheral ring shoulder.

In einer alternativen Ausführungsform wird die Ausnehmung beidseitig von sich abschnittsweise in Umfangsrichtung erstreckenden Vorsprüngen begrenzt.In an alternative embodiment, the recess is delimited on both sides by projections which extend in sections in the circumferential direction.

Besonders vorteilhaft ist es hierbei, wenn beidseitig einer jeweiligen Ausnehmung ein Eingriffsabsatz angeordnet ist. Insofern greifen somit wechselseitig in Umfangsrichtung benachbart ein erster Eingriffsabsatz der ersten Rotorscheibe in eine zweite Ausnehmung des Rotorbauteils und ein zweiter Eingriffsabsatz des Rotorbauteils in eine erste Ausnehmung der ersten Rotorscheibe ein.It is particularly advantageous here if an engaging shoulder is arranged on both sides of a respective recess. In this respect, a first engagement shoulder of the first rotor disk engages in a second recess of the rotor component and a second engagement shoulder of the rotor component engages in a first recess of the first rotor disk, mutually adjacent in the circumferential direction.

Zur vorteilhaften Anordnung der ersten Eingriffsabschnitte bei der ersten Rotorscheibe werden diese jeweils mittig zwischen zwei Schaufelhaltenuten positioniert. Entsprechend ist es vorteilhaft, wenn die ersten Ausnehmungen jeweils in Verlängerung der Schaufelhaltenuten angeordnet sind.For the advantageous arrangement of the first engagement sections in the first rotor disk, these are each positioned centrally between two blade retaining grooves. Accordingly, it is advantageous if the first recesses are each arranged as an extension of the blade retaining grooves.

Unabhängig von der radialen Positionierung der ersten Eingriffsabschnitte weisen diese vorteilhaft in Umfangsrichtung eine Länge geringer als der kleinste Abstand zwischen zwei Schaufelhaltenuten auf.Irrespective of the radial positioning of the first engagement sections, these advantageously have a length in the circumferential direction that is less than the smallest distance between two blade retaining grooves.

In einer alternativen Ausführung wird die Verbindung unmittelbar oberhalb des Ringvorsprungs angeordnet. Hierzu weist die erste Rotorscheibe auf der radial nach außen weisenden Seite des Ringvorsprungs die ersten Eingriffsabsätze auf. Komplementär hierzu sind die zweiten Ausnehmungen im Rotorbauteil erforderlich. Vorteilhaft besitzt in dieser Ausführungsform das Rotorbauteil eine erste Ringnut, in welcher der erste Ringvorsprung eingreift. Folglich ist die Ausnehmung an der radial außen liegenden Flanke der Ringnut anzuordnen. Dabei ist der erste Eingriffsabsatz und somit die zweite Ausnehmung vorzugsweise beabstandet vom axial freien Ende des Ringvorsprungs anzuordnen. Somit wird eine zusätzliche Belastung durch die zweite Ausnehmung im Bereich des Nutgrunds der ersten Ringnut vermieden.In an alternative embodiment, the connection is placed immediately above the annular projection. For this purpose, the first rotor disk has the first engagement shoulders on the radially outward-facing side of the annular projection. The second recesses in the rotor component are complementary to this necessary. In this embodiment, the rotor component advantageously has a first annular groove in which the first annular projection engages. Consequently, the recess is to be arranged on the radially outer flank of the annular groove. In this case, the first engagement shoulder and thus the second recess is preferably to be arranged at a distance from the axially free end of the annular projection. This avoids additional loading by the second recess in the area of the groove base of the first annular groove.

Die Eingriffsabsätze können auf unterschiedliche Weise realisiert werden. Eine zuverlässige Verbindung mit den Eingriffsabsätzen wird geschaffen, wenn diese einstückig mit der ersten Rotorscheibe bzw. einstückig mit dem Rotorbauteil gebildet sind.The engagement heels can be realized in different ways. A reliable connection with the engagement shoulders is created when they are formed in one piece with the first rotor disk and in one piece with the rotor component.

In einer alternativen Ausführung kommt es jedoch auch in Betracht, die Eingriffsabsätze unlösbar, bzw. durch Schweißen oder Löten, oder lösbar zu montieren. Hierbei ist jedoch zu berücksichtigen, dass die Lage des montierten Eingriffsabsatzes in jedem Fall sichergestellt ist. Weiterhin kann hiermit ggf. eine Schwächung des Bauteils (erste Rotorscheibe bzw. Rotorbauteil) mit dem Eingriffsabsatz einhergehen. Auch ist zu bedenken, dass mit einem montierten Eingriffsabsatz dieses eine andere Belastung unter Fliehkraft verursacht als ein einstückig gebildeter Eingriffsabsatz.In an alternative embodiment, however, it is also possible to mount the engaging shoulders in a non-detachable manner, or by welding or soldering, or in a detachable manner. In this case, however, it must be taken into account that the position of the mounted engagement shoulder is always ensured. Furthermore, a weakening of the component (first rotor disk or rotor component) can be associated with the engagement shoulder. It should also be borne in mind that with a mounted engagement shoulder, this causes a different stress under centrifugal force than an engagement shoulder formed in one piece.

Vorteilhafte wird hierzu zur Bildung des zweiten Bereichs auf der von der unmittelbar benachbarten wegweisenden Seite eine Aufdickung angeordnet. Dieses führt bei den auftretenden Fliehkräften aufgrund der ungleichmäßigen Masseverteilung zwischen dem ersten Bereich und dem zweiten Bereich zu einem geringfügigen Biegemoment des freien Endes des Scheibenabschnitts zur unmittelbar benachbarten Rotorscheibe weisend.For this purpose, a thickened area is advantageously arranged on the side pointing away from the directly adjacent, ground-breaking side in order to form the second region. With the centrifugal forces that occur, this leads to a slight bending moment of the free end of the disk section pointing to the immediately adjacent rotor disk due to the non-uniform distribution of mass between the first area and the second area.

Die Anordnung der zweiten Ausnehmungen und/oder der zweiten Eingriffsabätze an dem Rotorbauteil erfolgt hierbei in besonders vorteilhafter Weise im zweiten Bereich des Scheibenabschnitts.The arrangement of the second recesses and/or the second engagement shoulders on the rotor component takes place in a particularly advantageous manner in the second area of the disc section.

In den nachfolgenden Figuren werden zwei Ausführungsbeispiele für einen erfindungsgemäßen Rotor abschnittsweise im Bereich des Rotorbauteils skizziert. Es zeigen:

Fig. 1
abschnittsweise den Rotor im Längsschnitt im Bereich des Rotorbauteils in einer ersten Ausführungsform;
Fig. 2
die erste Rotorscheibe zur Ausführung aus Fig. 1;
Fig. 3
das Rotorbauteil zur Ausführung aus Fig. 1;
Fig. 4
abschnittsweise den Rotor im Längsschnitt im Bereich des Rotorbauteils in einer zweiten Ausführungsform;
Fig. 5
das Rotorbauteil zur Ausführung aus Fig. 4;
Fig. 6
die erste Rotorscheibe zur Ausführung aus Fig. 4;
In the following figures, two exemplary embodiments of a rotor according to the invention are outlined in sections in the area of the rotor component. Show it:
1
sections of the rotor in longitudinal section in the area of the rotor component in a first embodiment;
2
the first rotor disc for execution 1 ;
3
the rotor component for execution 1 ;
4
sections of the rotor in longitudinal section in the area of the rotor component in a second embodiment;
figure 5
the rotor component for execution 4 ;
6
the first rotor disc for execution 4 ;

In der Fig. 1 wird ein Rotor in einer ersten beispielhaften Ausführungsform im Längsschnitt lediglich im Bereich des Rotorbauteils 11 skizziert. Die weitere Ausführung des Rotors kann anhand üblicher Ausführungsformen gewählt werden. Zumindest weist der Rotor eine erste Rotorscheibe 01 und eine zweite Rotorscheibe 06 auf. An diesen 01, 06 ist jeweils ein umlaufender, sich axial erstreckender Ringvorsprung 03, 08 angeordnet.In the 1 a rotor in a first exemplary embodiment is sketched in longitudinal section only in the area of the rotor component 11 . The further design of the rotor can be selected using conventional embodiments. The rotor has at least a first rotor disk 01 and a second rotor disk 06. A circumferential, axially extending ring projection 03, 08 is arranged on each of these 01, 06.

Zwischen den Rotorscheiben 01, 06 befindet sich das Rotorbauteil 11, welches 11 zur Anbringung an den Rotorscheiben 01, 06 jeweils eine umlaufende Ringnut 12, 17 aufweist, wobei der erste Ringvorsprung 03 in die erste Ringnut 12 und der zweite Ringvorsprung 08 in die zweite Ringnut 17 eingreift. Radial unterhalb des jeweiligen Ringvorsprung 03, 08 befindet sich ein vom Rotorbauteil 11 gebildeter Stützabschnitt 13, 18. Diese 13, 18 stützen sich zumindest bei Fliehkraft am jeweiligen Ringvorsprung 03, 08 ab.Between the rotor disks 01, 06 is the rotor component 11, which 11 has a circumferential annular groove 12, 17 for attachment to the rotor disks 01, 06, with the first annular projection 03 in the first annular groove 12 and the second annular projection 08 in the second annular groove 17 intervenes. A support section 13, 18 formed by the rotor component 11 is located radially below the respective annular projection 03, 08. These 13, 18 are supported on the respective annular projection 03, 08, at least in the event of centrifugal force.

Weiterhin zu erkennen ist, dass das Rotorbauteil 11 einen umlaufenden sich radial erstreckenden Scheibenabschnitt 20 aufweist.It can also be seen that the rotor component 11 has a circumferential, radially extending disk section 20 .

Die Kopplung zwischen dem Rotorbauteil 11 und der ersten Rotorscheibe 01 befindet sich in diesem Ausführungsbeispiel im radial äußeren Bereich.In this exemplary embodiment, the coupling between the rotor component 11 and the first rotor disk 01 is located in the radially outer area.

Hierzu skizziert die Fig. 2 die erste Rotorscheibe 01 in perspektivischer Ansicht. Zu erkennen ist der umlaufende Ringvorsprung 03 sowie radial außerhalb die die erste Rotorscheibe 01 axial durchdringenden Schaufelhaltenuten 02. Zwischen jeweils 2 Schaufelhaltenuten 02 befindet sich ein erster Eingriffsabsatz 05. Zwischen jeweils zwei Eingriffsabschnitte 05 befindet sich eine entsprechende erste Ausnehmung.To this end, the 2 the first rotor disk 01 in a perspective view. Circumferential ring projection 03 can be seen, as well as blade retaining grooves 02 that penetrate axially through first rotor disk 01 radially outside. Between each two blade retaining grooves 02 is a first engagement step 05. Between each two engagement sections 05 there is a corresponding first recess.

Die Fig. 3 zeigt das hierzu komplementäre Rotorbauteil 11. Zu erkennen sind wiederum die umlaufenden Ringnuten 12, 17 mit denen sich auf der zur Rotorachse weisenden Seite angeordneten Stützabschnitte 13, 18. Der sich am einem axialen Ende unmittelbar benachbart zur ersten Rotorscheibe 01 radial erstreckende Scheibenabschnitt 20 wird unterteilt in einen radial inneren ersten Bereich und einen radial äußeren zweiten Bereich, wobei der zweite Bereich eine Aufdeckung 19 aufweist und hierdurch die zumindest doppelte Materialstärke des ersten Bereichs erreicht. Um bei auftretenden Fliehkräften eine sichere Kopplung zwischen dem Rotorbauteil 11 und der ersten Rotorscheibe 01 zu gewährleisten, werden in diesem Ausführungsbeispiel die am Rotorbauteil 11 angeordneten zweiten Eingriffsabätze 15 sowie die dazwischenliegenden zweiten Ausnehmungen 14 gegenüberliegend zur Aufdeckung 19 im radial äu-βeren Bereich angeordnet.The 3 12 shows the rotor component 11 which is complementary thereto. The circumferential annular grooves 12, 17 can again be seen, with those arranged on the side pointing towards the rotor axis Support sections 13, 18. The disk section 20, which extends radially at one axial end directly adjacent to the first rotor disk 01, is divided into a radially inner first area and a radially outer second area, with the second area having a cover 19 and thus at least twice the material thickness of the first area reached. In order to ensure a secure coupling between the rotor component 11 and the first rotor disk 01 when centrifugal forces occur, in this exemplary embodiment the second engagement projections 15 arranged on the rotor component 11 and the second recesses 14 in between are arranged opposite the cover 19 in the radially outer area.

Analog der Fig. 1 zeigt die Fig. 4 einen Rotor in einer zweiten beispielhaften Ausführungsform. Hierbei weist der Rotor eine erste Rotorscheibe 21 und eine zweite Rotorscheibe 26 auf. An diesen 21, 26 ist jeweils ein umlaufender, sich axial erstreckender Ringvorsprung 23, 28 angeordnet.Analog of the 1 show the 4 a rotor in a second exemplary embodiment. Here, the rotor has a first rotor disk 21 and a second rotor disk 26 . At these 21, 26 a circumferential, axially extending ring projection 23, 28 is arranged.

Zwischen den Rotorscheiben 21, 26 befindet sich das Rotorbauteil 31, welches 31 zur Anbringung an den Rotorscheiben 21, 26 jeweils eine umlaufende Ringnut 32, 37 aufweist.The rotor component 31 is located between the rotor disks 21, 26 and has a circumferential annular groove 32, 37 in each case for attachment to the rotor disks 21, 26.

Weiterhin zu erkennen ist, dass das Rotorbauteil 31 einen umlaufenden sich radial erstreckenden Scheibenabschnitt 40 aufweist.It can also be seen that the rotor component 31 has a circumferential, radially extending disc section 40 .

Die Kopplung zwischen dem Rotorbauteil 31 und der ersten Rotorscheibe 21 befindet sich unmittelbar radial außerhalb des ersten Ringvorsprungs 23.The coupling between the rotor component 31 and the first rotor disk 21 is located immediately radially outside of the first annular projection 23.

Die Fig. 5 zeigt das Rotorbauteil 31 in perspektivischer Ansicht. Zu erkennen ist wiederum die umlaufende erste Ringnut 32 mit dem sich auf der zur Rotorachse weisenden Seite angeordneten Stützabschnitte. Der sich am einem axialen Ende unmittelbar benachbart zur zweiten Rotorscheibe 26 radial erstreckende Scheibenabschnitt 40 ist analog wie zuvor ausgeführt.The figure 5 shows the rotor component 31 in a perspective view. The circumferential first annular groove 32 with the support sections arranged on the side pointing towards the rotor axis can again be seen. The at one axial end immediately adjacent to the second rotor disk 26 radially extending Disk section 40 is analogous to that stated above.

Im Gegensatz zur vorherigen Ausführung ist in diesem Fall vorgesehen, dass das Rotorbauteil an der radial außen liegenden Flanke der ersten Ringnut 32 auf der zur Rotorachse weisenden Seite einen umlaufenden Ringabsatz 35 aufweist. Dieser 35 wird mehrfach unterbrochen durch jeweils im Umfang verteilt angeordnete zweite Ausnehmungen 34.In contrast to the previous embodiment, provision is made in this case for the rotor component to have a peripheral annular shoulder 35 on the radially outer flank of the first annular groove 32 on the side facing the rotor axis. This 35 is interrupted several times by second recesses 34 distributed around the circumference.

Die Fig. 6 zeigt hierzu die erste Rotorscheibe 21 in perspektivischer Ansicht. Zu erkennen ist der umlaufende Ringvorsprung 23 sowie die Schaufelhaltenuten 02. Zur Realisierung der Kopplung weist die erste Rotorscheibe 21 auf der radial außen liegenden Seite am ersten Ringvorsprung 23 die zu den zweiten Ausnehmungen 34 komplementäre erste Eingriffsabsätze 25.The 6 shows the first rotor disk 21 in a perspective view. The circumferential annular projection 23 and the blade retaining grooves 02 can be seen. To implement the coupling, the first rotor disk 21 has the first engagement shoulders 25, which are complementary to the second recesses 34, on the radially outer side on the first annular projection 23.

Claims (9)

  1. Rotor, in particular of a gas turbine, with a first rotor disc (01, 21) which (01, 21) has, distributed on the circumference, a plurality of blade retaining grooves (02, 22) which axially penetrate the first rotor disc (01, 21) for receiving rotor blades, and, radially below the blade retaining grooves (02, 22), an axially extending circumferential annular projection (03, 23), and with a second rotor disc (06, 26) which is fastened to the first rotor disc (01, 21) and which (06, 26) has, distributed on the circumference, a plurality of blade retaining grooves which axially penetrate the second rotor disc (06, 26) for receiving rotor blades, and, radially below the blade retaining grooves, a circumferential second annular projection (08, 28) which extends axially with respect to the first annular projection (03, 23), and with a circumferential rotor component (11, 31) which (11, 31) is arranged between the rotor discs (01, 06, 21, 26) and has a first supporting portion (13), coming into contact with the first annular projection (03, 23) on the side which points towards the rotor axis, and a second supporting portion (18), coming into contact with the second annular projection (08, 28) on the side which points towards the rotor axis, the first rotor disc (01) having at least two first recesses which are arranged distributed on the circumference radially outside and/or on the radially outwardly pointing side of the first annular projection (03), and the rotor component (11) having second engagement shoulders (15) which engage in each case in the first recesses; and/or the rotor component (11, 31) having at least two second recesses (14, 34) which are arranged distributed on the circumference radially outside and/or on the radially outwardly pointing side of the first annular projection (03, 23), and the first rotor disc (01, 21) having first engagement shoulders (05, 25) which engage in each case in the second recesses (14, 34), characterized in that, at at least one axial end, the rotor component (11, 31) has a radially extending disc portion (20, 40) which (20, 40) covers the blade retaining grooves (02, 22) of a rotor disc (01, 26) at least in portions, and has a first region with a first material thickness and, radially outside the first region, a second region with a material thickness which is at least twice the first material thickness.
  2. Rotor according to Claim 1, characterized in that the rotor component (11, 31) has an axially opening first annular groove (12, 32) which encloses the first annular projection (03, 23), and/or an axially opening second annular groove (17, 37) which encloses the second annular projection (08, 28).
  3. Rotor according to Claim 2, characterized in that a radially outer flank of the first annular groove (12, 32) bears against the first annular projection (03, 23), and/or a radially outer flank of the second annular groove (17, 37) bears against the second annular projection (08, 28).
  4. Rotor according to one of Claims 1 to 3, characterized in that projections which extend axially and in portions in the circumferential direction are arranged on both sides of the recesses, and/or in that the recesses (34) are arranged in the circumferential annular shoulder (35).
  5. Rotor according to one of Claims 1 to 4, characterized in that the first engagement shoulders (05) are arranged on the first rotor disc (01), in each case between two blade retaining grooves (02) in the circumferential direction; and/or in that the first recesses are arranged on the first rotor disc (01), in each case in an extension of the blade retaining grooves (02).
  6. Rotor according to Claim 5, characterized in that the length of the first engagement shoulders (05) in the circumferential direction is in each case smaller than or equal to the smallest spacing between two blade retaining grooves (02).
  7. Rotor according to one of Claims 1 to 4, characterized in that the first engagement shoulders (25) are arranged on the first rotor disc (21) on the radially outwardly pointing side of the annular projection (23), spaced apart from the axially free end of the annular projection (23).
  8. Rotor according to one of Claims 1 to 7, characterized in that the second region is formed by way of a second portion (19) on the side which points away from the directly adjacent rotor disc (01, 26).
  9. Rotor according to Claim 8, characterized in that the engagement shoulders (15) and/or the recesses (14) are arranged in the second region.
EP19752935.7A 2018-08-02 2019-07-24 Rotor comprising a rotor component arranged between two rotor disks Active EP3788236B1 (en)

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US201862713572P 2018-08-02 2018-08-02
PCT/EP2019/069866 WO2020025406A1 (en) 2018-08-02 2019-07-24 Rotor comprising a rotor component arranged between two rotor disks

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EP (1) EP3788236B1 (en)
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GB201604473D0 (en) * 2016-03-16 2016-04-27 Rolls Royce Plc A bladed rotor arrangement and a lock plate for a bladed rotor arrangement
US10196916B2 (en) * 2016-04-08 2019-02-05 Siemens Aktiengesellschaft Rotor disk having an end-side sealing element
EP3287595A1 (en) * 2016-08-25 2018-02-28 Siemens Aktiengesellschaft Rotor with segmented sealing ring
EP3318724A1 (en) * 2016-11-04 2018-05-09 Siemens Aktiengesellschaft Sealing segment of a rotor and rotor
US10557356B2 (en) * 2016-11-15 2020-02-11 General Electric Company Combined balance weight and anti-rotation key
US10920598B2 (en) * 2017-05-02 2021-02-16 Rolls-Royce Corporation Rotor assembly cover plate

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KR102537955B1 (en) 2023-05-31
US20210310359A1 (en) 2021-10-07
EP3788236A1 (en) 2021-03-10
KR20210031984A (en) 2021-03-23
JP2021533304A (en) 2021-12-02
CN112534119A (en) 2021-03-19
WO2020025406A1 (en) 2020-02-06
US11339662B2 (en) 2022-05-24
CN112534119B (en) 2023-04-14
JP7092938B2 (en) 2022-06-28

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