EP2118446A1 - Turbine comprising at least one rotor that consists of rotor disks and a tie bolt - Google Patents

Turbine comprising at least one rotor that consists of rotor disks and a tie bolt

Info

Publication number
EP2118446A1
EP2118446A1 EP08716885A EP08716885A EP2118446A1 EP 2118446 A1 EP2118446 A1 EP 2118446A1 EP 08716885 A EP08716885 A EP 08716885A EP 08716885 A EP08716885 A EP 08716885A EP 2118446 A1 EP2118446 A1 EP 2118446A1
Authority
EP
European Patent Office
Prior art keywords
turbine according
rotor
tie rod
gas turbine
spacer
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.)
Granted
Application number
EP08716885A
Other languages
German (de)
French (fr)
Other versions
EP2118446B1 (en
Inventor
Francois Benkler
Ulrich Ehehalt
Harald Hoell
Walter Loch
Peter-Andreas Schneider
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 AG
Original Assignee
Siemens AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP08716885A priority Critical patent/EP2118446B1/en
Priority to PL08716885T priority patent/PL2118446T3/en
Publication of EP2118446A1 publication Critical patent/EP2118446A1/en
Application granted granted Critical
Publication of EP2118446B1 publication Critical patent/EP2118446B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/10—Anti- vibration means
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/182—Two-dimensional patterned crenellated, notched
    • 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
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/311—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being in line
    • 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
    • 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
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise

Definitions

  • the invention relates to a gas turbine according to the preamble of patent claim 1.
  • Multi-stage gas turbines with at least one rotor or rotor, which has arranged in several radial planes blades on the circumference of rotor disks are basically known in various embodiments.
  • Hollow shaft with there located radially outboard combustion chambers and finally extends through the turbine.
  • US 3,749,516 discloses a similarly constructed rotor of a double radial compressor.
  • the known rotor comprises a plurality of rotor disks and a centrally arranged hollow shaft.
  • a tie rod Centrally through the hollow shaft and through the rotor disks extends a tie rod, which clamps the rotor disks and the hollow shaft firmly together by end pieces screwed on end.
  • a sleeve with resilient unilaterally mounted struts is provided see, which are supported by a screw on the hollow shaft.
  • the invention has for its object to provide measures to in particular to prevent natural oscillations of the tie rod regardless of the constant during operation of the stationary gas turbine speed. All rotating parts of the gas turbine should form a stiff unit as possible.
  • the channel is annular and formed for the passage of a cooling medium and bounded by a separating tube radially outside, wherein the recesses serve as passage openings for the cooling medium.
  • the spacer according to the invention is a spring ring with coaxially extending passage openings. It increases the damping or stiffening of the tie rod in the rotor / rotor and is sufficiently stable to hold the tie rod in its desired position regardless of the speed. It is easy to assemble with sufficient preload in spite of its spring characteristics. The functionality is therefore ensured even at high speeds.
  • spacers further increases not only the natural frequency of the tie rod itself, but also the inherent rigidity of all parts.
  • spacers according to the invention are basically also used in the area of cooling and separating tubes which surround the tie rod in a certain axial section at a distance.
  • the spacers are here between the tie rod and the cooling medium leading, the annular channel outside bounding separating tube.
  • another ring channel in this regard between an inner or first separator tube and an outer or second separator tube may be formed so that then first spacers between tie rods and inner separator tube on the one hand and possibly second spacers between the inner separator tube and an outer separator tube are provided by means of which the tie rod against the radially outer , Rotor components belonging to the rotor components can be supported in places.
  • swingable length of the tie rod can be significantly shortened. With this measure, the distance between the natural frequency of the tie rod and the rotational frequency of the rotor can be increased, whereby its tendency to oscillate is substantially reduced. Safe operation of the gas turbine can thus be ensured.
  • Figure 1 is cut off and partly in section a part of the rotor / rotor of a multi-stage gas turbine
  • FIG 3 shows a perspective view as in FIG 2, but slightly obliquely from above;
  • a rotor 2 of a multi-stage gas turbine 1 according to the broken sectional view in FIG. 1 has rotor disks 5 arranged in several planes 3 and carrying rotor blades 4 on the circumference.
  • a tie rod 6 extends along centrally arranged recesses 7 in the rotor disks 5 through the left in FIG 1 located compressor part of the gas turbine 1 and is anchored in one of the rotor disks, not shown, or in a suitable Rotorendteil in a manner not shown.
  • the prestressed tie rod 6 presses together the rotor disks 5 and further rotor parts of the turbine unit in a basically known manner in a form-fitting manner.
  • Axially adjacent to the compressor of the gas turbine rotor disks 5 is a central hollow shaft 9, which rests with its opposite end, not shown, on one of the rotor parts of the turbine unit. Radially outside of this central hollow shaft 9 are located within the housing of the gas turbine, the combustion chambers.
  • At least one annular channel 10 or 11 is located between the central hollow shaft 9 and the tie rod 6.
  • the channels 10, 11 each serve to guide a cooling medium 12 from the compressor-side section of the rotor 2 to the turbine-side section.
  • the cooling medium 12 is symbolized in FIG 1 by means of an arrow.
  • the channel 12, which is annular in cross-section and guides the cooling medium 12, can be enclosed by a first or inner separating tube 13, through which the tie rod 6 extends centrally.
  • the further annular cooling channel 10 can be used to guide a cooling medium 12 between the first or inner separating tube 16 and a second and outer separating tube 14. orders be.
  • at least one spacer 15 is provided.
  • This spacer 15 is a resilient ring member and consists of at least one support ring 16, the radially extending support arms 17 and each support arm 17 each have a support leg 18 at its end, as shown in Figures 2 to 6 in conjunction with FIG.
  • the spacer 15 and the resilient ring member is in one piece, wherein the support arms 17 extend radially to the support ring 16 and end at support legs 18.
  • each support leg 18 has at its end a support surface 20 with which the spacer 15 or its support arm 17 bears against the inside of the separation tube 13.
  • the support arms 17 extend from the support ring 16 to the support feet each obliquely to the central axis M of the rotor 2. In this way, a fictitious hinge point is formed at the annular end of the support arm 17, around which the support arm 17 can pivot in the radial direction, if he bent accordingly by centrifugal forces becomes. Centrifugal forces cause by the fact that the support legs 18 do not solve by centrifugal force from their investment surface, but more according to a higher speed of the rotor 2 rest against its contact surface with spreading force, at the same time not the radial extent between the support ring 16 and support leg 18 with certainty can become smaller. This is true at least in the event that the support ring in the installed state radially inward and the support legs 18 are radially outward.
  • identical spacers 15 ' which may have only slightly different dimensions, are also provided for fixing the annular channel 10 for the cooling medium, as shown in FIG 1 is apparent.
  • the support ring 16 'lies outside on the first or inner separation pipe 13 and is supported with its support feet 18 'inside of the second or outer separation pipe 14.
  • the separating tube 14 also serves as a radially inner boundary to the central hollow shaft 9, as shown in FIG. 1.
  • the spacer 15 recesses 21 which extend radially to the tie rod 6 and to its center line M and coaxial with the tie rod 6 in the installed state.
  • the spacers 15 thereby fix not only the tie rod 6 and / or the two separation tubes 13 and 14 relative to the center line M of the rotor 2 and tie rod 6, but they also allow a free and unobstructed coaxial flow of the cooling medium 12.
  • the Recesses 21 each openings.
  • the spacer 15, 15 not only in one piece, but due to its design and due to the material used also resilient.
  • FIG 4 remains through the spacers 15 and their support arms 17 and their support legs 18 about half the ring cross-section to form free passages 21. It is thus about half the channel cross-section of the cooling medium to flow through.
  • the spacers 15, 15 ' fixed immovably on the circumference 22 of the tie rod 6 and the periphery 23 of a separating tube 13 in the radial direction.
  • the spacers 15, 15 'with their support ring 16, 16' expediently thermally shrunk onto the tie rod 6 carrying them, the separation tube 13.
  • the tie rod 6 and possibly also the inner separating tube 13, each of which carries spacers 15, 15 ', have stops 24, 25 for the spacers 15, 15'.
  • These stops 24, 25 are according to the in the figures illustrated embodiments each have a circumferential bead and define in the axial direction exactly the point at which the spacer 15, 15 'should rest during thermal shrinking.
  • spacers as the spacers 15 and 15 ' can also be arranged between the rotor disks 5 bearing on their circumference, the rotor blades 4 and the tie rod 6. In FIG. 1, this is indicated symbolically in the region of the recesses 7 by means of intersecting, dashed lines.
  • the first rotor disk in addition to the central hollow shaft may expediently be concretely connected to one or more spacers 15 of the type of interest here. Basically, the same can apply to other rotor disks 5, to which they are connected either directly to the tie rod 6 or the first or inner separation pipe 13.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Agricultural Chemicals And Associated Chemicals (AREA)
  • Breeding Of Plants And Reproduction By Means Of Culturing (AREA)

Abstract

The turbine (1) has a rotor (2) with blades (4) arranged on a periphery of disks (5) in radial planes (3), and a tie rod (6) extending along slots (7) in the disks. An annular spacer (15, 15') fixes a position of the tie rod relative to a center line (M) of the disks, and is arranged in a channel (10, 11). The spacer has through-openings, which are arranged radially relative to the tie rod or to its center line, and extend coaxially. The channel carries cooling medium and is limited by a separating pipe (13, 14) radially outwards, and the through-openings serve for flow of the medium.

Description

Beschreibungdescription
TURBINE MIT MINDESTENS EINEM ROTOR BESTEHEND AUS ROTORSCHEIBEN UND EINEM ZUGANKERTURBINE WITH AT LEAST ONE ROTOR CONSISTING OF ROTOR DISCS AND A ZUGANKER
Die Erfindung betrifft eine Gasturbine gemäß dem Oberbegriff von Patentanspruch 1.The invention relates to a gas turbine according to the preamble of patent claim 1.
Mehrstufige Gasturbinen mit mindestens einem Läufer bzw. Rotor, der in mehreren Radialebenen angeordnete Laufschaufeln am Umfang von Rotorscheiben aufweist, sind grundsätzlich in verschiedenartigen Ausführungsformen bekannt.Multi-stage gas turbines with at least one rotor or rotor, which has arranged in several radial planes blades on the circumference of rotor disks are basically known in various embodiments.
Ferner ist es bekannt, zumindest bei Gasturbinen, die einzelnen Rotorscheiben stirnflächig sowie formschlüssig so zu gestalten, dass sie sich mit Hilfe eines durch die Rotorscheiben erstreckenden Zugankers als Einheit zusammenhalten lassen. Mit zunehmender Baulänge nimmt allerdings die frei schwingende Länge, d. h. die ungestützte Länge des Zugankers, zu. Hierdurch verschieben sich die Eigenfrequenzen auf ein Niveau nahe der Rotationsfrequenz des Rotors, so dass im Betrieb bzw. beim Schleudern unzulässig hohe Schwingungsamplituden auftreten können. Diese können nicht nur den Zuganker, sondern auch die gesamte Gasturbine zerstören. Dies gilt insbesondere auch für Gasturbinen, bei denen sich der Zuganker durch den Verdichter, sodann durch eine mittlereFurthermore, it is known, at least in gas turbines, to design the individual rotor disks on the face and in a form-fitting manner such that they can be held together as a unit by means of a tie rod extending through the rotor disks. With increasing length, however, the free-swinging length, d. H. the unsupported length of the tie rod, too. As a result, the natural frequencies shift to a level close to the rotational frequency of the rotor, so that during operation or when spinning inadmissible high vibration amplitudes can occur. These can destroy not only the tie rod but also the entire gas turbine. This is especially true for gas turbines in which the tie rod through the compressor, then through a middle
Hohlwelle mit den dort radial außen befindlichen Brennkammern und schließlich durch die Turbine erstreckt.Hollow shaft with there located radially outboard combustion chambers and finally extends through the turbine.
Hierzu offenbart die US 3,749,516 einen ähnlich aufgebauten Läufer eines zweifachen Radialverdichters. Der daraus bekannte Läufer umfasst mehrere Rotorscheiben und eine mittig angeordnete Hohlwelle. Zentral durch die Hohlwelle und durch die Rotorscheiben erstreckt sich ein Zuganker, welcher durch endseitig aufgeschraubte Endstücke die Rotorscheiben und die Hohlwelle fest miteinander verspannen. Um den Zuganker in seiner Lage innerhalb des Rotors zu fixieren, ist an diesem eine Hülse mit federnden einseitig befestigten Streben vorge- sehen, welche über eine Schraube an der Hohlwelle abgestützt sind.For this purpose, US 3,749,516 discloses a similarly constructed rotor of a double radial compressor. The known rotor comprises a plurality of rotor disks and a centrally arranged hollow shaft. Centrally through the hollow shaft and through the rotor disks extends a tie rod, which clamps the rotor disks and the hollow shaft firmly together by end pieces screwed on end. In order to fix the tie rod in its position within the rotor, at this a sleeve with resilient unilaterally mounted struts is provided see, which are supported by a screw on the hollow shaft.
Der Erfindung liegt die Aufgabe zugrunde, Maßnahmen vorzu- sehen, um insbesondere Eigenschwingungen des Zugankers unabhängig von der im Betrieb des stationären Gasturbine konstanten Drehzahl zu verhindern. Alle sich drehenden Teile der Gasturbine sollen dabei eine möglichst steife Einheit bilden .The invention has for its object to provide measures to in particular to prevent natural oscillations of the tie rod regardless of the constant during operation of the stationary gas turbine speed. All rotating parts of the gas turbine should form a stiff unit as possible.
Zur Lösung dieser Aufgabe sieht die Erfindung mit den Merkmalen des kennzeichnenden Teils von Patentanspruch 1 vor, dass der Kanal ringförmig und zur Durchleitung eines Kühlmediums ausgebildet und von einem Trennrohr radial außen be- grenzt ist, wobei die Ausnehmungen als Durchtrittsöffnungen für das Kühlmedium dienen.To achieve this object, the invention with the features of the characterizing part of claim 1, that the channel is annular and formed for the passage of a cooling medium and bounded by a separating tube radially outside, wherein the recesses serve as passage openings for the cooling medium.
Grundsätzlich ist der Abstandshalter gemäß der Erfindung ein Federring mit sich koaxial erstreckenden Durchtrittsöff- nungen. Er erhöht die Dämpfung bzw. Versteifung des Zugankers im Läufer/Rotor und ist ausreichend stabil, um unabhängig von der Drehzahl den Zuganker in seiner Solllage zu halten. Er lässt sich einfach montieren, wobei eine ausreichende Vorspannung trotz seiner Federeigenschaften gegeben ist. Die Funktionsfähigkeit ist daher auch bei hohen Drehzahlen sichergestellt .In principle, the spacer according to the invention is a spring ring with coaxially extending passage openings. It increases the damping or stiffening of the tie rod in the rotor / rotor and is sufficiently stable to hold the tie rod in its desired position regardless of the speed. It is easy to assemble with sufficient preload in spite of its spring characteristics. The functionality is therefore ensured even at high speeds.
Die Verwendung von Abstandshaltern erhöht ferner nicht nur die Eigenfrequenz des Zugankers selbst, sondern auch die Eigensteifigkeit aller Teile.The use of spacers further increases not only the natural frequency of the tie rod itself, but also the inherent rigidity of all parts.
Dazu gehört auch, dass erfindungsgemäße Abstandshalter grundsätzlich auch im Bereich von Kühl- und Trennrohren verwendet werden, die den Zuganker in einem bestimmten axialen Ab- schnitt mit Abstand umgeben. Die Abstandshalter befinden sich hier zwischen dem Zuganker und dem das Kühlmedium führenden, den Ringkanal außen begrenzenden Trennrohr. Gegebenenfalls kann ein weiterer Ringkanal in diesem Zusammenhang zwischen einem inneren oder ersten Trennrohr und einem äußeren oder zweiten Trennrohr gebildet sein, so dass dann erste Abstandshalter zwischen Zuganker und innerem Trennrohr einerseits und ggf. zweite Abstandshalter zwischen dem inneren Trennrohr und einem äußeren Trennrohr vorgesehen sind, mittels denen der Zuganker gegen die radial weiter außen, zum Rotor gehörenden Rotorkomponenten stellenweise abgestützt werden kann. Durch die entlang seiner Erstreckung ggf. auch mehrfache Abstützung kann die freie, schwingbare Länge des Zugankers signifikant verkürzt werden. Mit dieser Maßnahme kann der Abstand zwischen der Eigenfrequenz des Zugankers und der Rotationsfrequenz des Rotors vergrößert werden, wodurch seine Schwingungsneigung wesentlich reduziert wird. Ein sicherer Betrieb der Gasturbine kann somit gewährleistet werden.This also includes that spacers according to the invention are basically also used in the area of cooling and separating tubes which surround the tie rod in a certain axial section at a distance. The spacers are here between the tie rod and the cooling medium leading, the annular channel outside bounding separating tube. Optionally, another ring channel in this regard between an inner or first separator tube and an outer or second separator tube may be formed so that then first spacers between tie rods and inner separator tube on the one hand and possibly second spacers between the inner separator tube and an outer separator tube are provided by means of which the tie rod against the radially outer , Rotor components belonging to the rotor components can be supported in places. By along its extent possibly also multiple support the free, swingable length of the tie rod can be significantly shortened. With this measure, the distance between the natural frequency of the tie rod and the rotational frequency of the rotor can be increased, whereby its tendency to oscillate is substantially reduced. Safe operation of the gas turbine can thus be ensured.
Es ist daher mit einfachen Mitteln möglich, die oben genannte Aufgabe erfolgreich zu lösen.It is therefore possible by simple means to successfully solve the above problem.
Weitere Merkmale der Erfindung gehen aus Unteransprüchen und der Zeichnung im Zusammenhang mit der Beschreibung hervor.Further features of the invention will become apparent from dependent claims and the drawings in conjunction with the description.
Die Erfindung wird nachstehend anhand von Ausführungsbeispielen, die in der Zeichnung dargestellt sind, näher beschrieben. Dabei zeigen:The invention will be described in more detail below with reference to embodiments shown in the drawing. Showing:
FIG 1 abgeschnitten sowie zum Teil im Schnitt einen Teil des Läufers/Rotors einer mehrstufigen Gasturbine;Figure 1 is cut off and partly in section a part of the rotor / rotor of a multi-stage gas turbine;
FIG 2 schräg von unten eine perspektivische Ansicht eines Abstandshalters in anderem Maßstab;2 obliquely from below a perspective view of a spacer on a different scale;
FIG 3 eine perspektivische Ansicht wie in FIG 2, jedoch leicht schräg von oben;3 shows a perspective view as in FIG 2, but slightly obliquely from above;
FIG 4 jeweils abgeschnitten eine Stirnansicht eines Abstandshalters auf einem Zuganker sowie ein inneres und ein äußeres Trennrohr zur Bildung eines ringförmigen Kanals für ein Kühlmedium, und FIG 5 einen Schnitt längs der Linie V-V in FIG 4.4 each cut away an end view of a spacer on a tie rod and an inner and an outer separator tube to form an annular channel for a cooling medium, and 5 shows a section along the line VV in FIG. 4
Ein Rotor 2 einer mehrstufigen Gasturbine 1 umfasst gemäß der abgebrochenen Schnitt-Darstellung in FIG 1 in mehreren Ebenen 3 angeordnete Rotorscheiben 5, die am Umfang Laufschaufeln 4 tragen. Ein Zuganker 6 erstreckt sich längs mittig angeordneter Ausnehmungen 7 in den Rotorscheiben 5 durch den in FIG 1 links befindlichen Verdichterteil der Gasturbine 1 und ist in einer der nicht dargestellten Rotorscheiben bzw. in einem geeigneten Rotorendteil in nicht dargestellter Weise verankert .A rotor 2 of a multi-stage gas turbine 1 according to the broken sectional view in FIG. 1 has rotor disks 5 arranged in several planes 3 and carrying rotor blades 4 on the circumference. A tie rod 6 extends along centrally arranged recesses 7 in the rotor disks 5 through the left in FIG 1 located compressor part of the gas turbine 1 and is anchored in one of the rotor disks, not shown, or in a suitable Rotorendteil in a manner not shown.
Der vorgespannte Zuganker 6 presst die Rotorscheiben 5 sowie weitere Rotorteile der Turbineneinheit in grundsätzlich bekannter Weise formschlüssig zusammen.The prestressed tie rod 6 presses together the rotor disks 5 and further rotor parts of the turbine unit in a basically known manner in a form-fitting manner.
Axial neben den zum Verdichter der Gasturbine gehörenden Rotorscheiben 5 befindet sich eine mittlere Hohlwelle 9, die mit ihrem gegenüberliegenden, nicht dargestellten Ende an einem der Rotorteile der Turbineneinheit anliegt. Radial außerhalb von dieser mittleren Hohlwelle 9 befinden sich innerhalb des Gehäuses der Gasturbine die Brennkammern.Axially adjacent to the compressor of the gas turbine rotor disks 5 is a central hollow shaft 9, which rests with its opposite end, not shown, on one of the rotor parts of the turbine unit. Radially outside of this central hollow shaft 9 are located within the housing of the gas turbine, the combustion chambers.
Zwischen der mittleren Hohlwelle 9 und dem Zuganker 6 befindet sich mindestens ein ringförmiger Kanal 10 bzw. 11. Die Kanäle 10, 11 dienen jeweils zur Führung eines Kühlmediums 12 vom verdichterseitigen Abschnitt des Rotors 2 zum turbinen- seitigen Abschnitt. Das Kühlmedium 12 ist in FIG 1 mit Hilfe eines Pfeils symbolisiert.At least one annular channel 10 or 11 is located between the central hollow shaft 9 and the tie rod 6. The channels 10, 11 each serve to guide a cooling medium 12 from the compressor-side section of the rotor 2 to the turbine-side section. The cooling medium 12 is symbolized in FIG 1 by means of an arrow.
Der das Kühlmedium 12 führende im Querschnitt ringförmige Kanal 11 kann von einem ersten oder inneren Trennrohr 13 umschlossen sein, durch den sich zentral der Zuganker 6 erstreckt. Zudem kann der weitere ringförmige Kühlkanal 10 zum Führen eines Kühlmediums 12 zwischen dem ersten oder inneren Trennrohr 16 und einem zweiten und äußerem Trennrohr 14 ange- ordnet sein. Zur exakten Lagefixierung des Zugankers 6 im inneren Trennrohr 13 ist mindestens ein Abstandshalter 15 vorgesehen. Dieser Abstandshalter 15 ist ein federelastisches Ringelement und besteht mindestens aus einem Stützring 16, der sich radial erstreckende Stützarme 17 und an jedem Stützarm 17 jeweils einen Stützfuß 18 an seinem Ende aufweist, wie aus den FIG 2 bis 6 in Verbindung mit FIG 1 hervorgeht.The channel 12, which is annular in cross-section and guides the cooling medium 12, can be enclosed by a first or inner separating tube 13, through which the tie rod 6 extends centrally. In addition, the further annular cooling channel 10 can be used to guide a cooling medium 12 between the first or inner separating tube 16 and a second and outer separating tube 14. orders be. For exact positional fixation of the tie rod 6 in the inner separation tube 13, at least one spacer 15 is provided. This spacer 15 is a resilient ring member and consists of at least one support ring 16, the radially extending support arms 17 and each support arm 17 each have a support leg 18 at its end, as shown in Figures 2 to 6 in conjunction with FIG.
Gemäß den in den Figuren dargestellten Ausführungsbeispielen ist der Abstandshalter 15 bzw. das federelastische Ringelement einstückig, wobei sich die Stützarme 17 radial zum Stützring 16 erstrecken und an Stützfüßen 18 enden. Gemäß Ausführungsbeispiel weist jeder Stützfuß 18 an seinem Ende eine Stützfläche 20 auf, mit der der Abstandshalter 15 bzw. sein Stützarm 17 jeweils an der Innenseite des Trennrohres 13 anliegt .According to the embodiments shown in the figures, the spacer 15 and the resilient ring member is in one piece, wherein the support arms 17 extend radially to the support ring 16 and end at support legs 18. According to the embodiment, each support leg 18 has at its end a support surface 20 with which the spacer 15 or its support arm 17 bears against the inside of the separation tube 13.
Die Stützarme 17 erstrecken sich vom Stützring 16 zu den Stützfüßen jeweils schräg zur Mittelachse M des Rotors 2. Hierdurch wird am ringseitigen Ende des Stützarmes 17 ein fiktiver Gelenkpunkt gebildet, um den der Stützarm 17 in radialer Richtung verschwenken kann, wenn er von Fliehkräften entsprechend gebogen wird. Fliehkräfte bewirken dadurch, dass die Stützfüße 18 sich durch Fliehkraft nicht von ihrer An- lagefläche lösen, sondern entsprechend einer höheren Drehzahl des Rotors 2 umso mehr an ihrer Anlagefläche mit Spreizkraft anliegen, wobei zugleich die radiale Erstreckung zwischen Stützring 16 und Stützfuß 18 mit Sicherheit nicht kleiner werden kann. Dies gilt zumindest für den Fall, dass sich der Stützring im eingebauten Zustand radial innen und die Stützfüße 18 radial außen befinden.The support arms 17 extend from the support ring 16 to the support feet each obliquely to the central axis M of the rotor 2. In this way, a fictitious hinge point is formed at the annular end of the support arm 17, around which the support arm 17 can pivot in the radial direction, if he bent accordingly by centrifugal forces becomes. Centrifugal forces cause by the fact that the support legs 18 do not solve by centrifugal force from their investment surface, but more according to a higher speed of the rotor 2 rest against its contact surface with spreading force, at the same time not the radial extent between the support ring 16 and support leg 18 with certainty can become smaller. This is true at least in the event that the support ring in the installed state radially inward and the support legs 18 are radially outward.
Grundsätzlich baugleiche Abstandshalter 15' , die gegebenenfalls lediglich etwas andere Abmessungen aufweisen, sind auch zur Festlegung des ringförmigen Kanals 10 für das Kühlmedium vorgesehen, wie aus FIG 1 hervorgeht. Der Stützring 16' liegt dabei außen auf dem ersten oder inneren Trennrohr 13 an und stützt sich mit seinen Stützfüßen 18' innen an dem zweiten oder äußeren Trennrohr 14 ab.Basically identical spacers 15 ', which may have only slightly different dimensions, are also provided for fixing the annular channel 10 for the cooling medium, as shown in FIG 1 is apparent. The support ring 16 'lies outside on the first or inner separation pipe 13 and is supported with its support feet 18 'inside of the second or outer separation pipe 14.
Das Trennrohr 14 dient dabei ferner als radial innere Be- grenzung zur mittleren Hohlwelle 9, wie aus FIG 1 hervorgeht.The separating tube 14 also serves as a radially inner boundary to the central hollow shaft 9, as shown in FIG. 1.
Aufgrund der Stützarme 17 weist der Abstandshalter 15 Ausnehmungen 21 auf, die sich im eingebauten Zustand radial zum Zuganker 6 bzw. zu seiner Mittellinie M sowie koaxial zum Zuganker 6 erstrecken. Die Abstandshalter 15 fixieren dadurch nicht nur den Zuganker 6 und/oder die beiden Trennrohre 13 und 14 relativ zur Mittellinie M von Rotor 2 und Zuganker 6, sondern sie ermöglichen auch eine freie und ungehinderte, koaxiale Strömung des Kühlmediums 12. Im eingebauten Zustand bilden die Ausnehmungen 21 jeweils Durchtrittsöffnungen.Due to the support arms 17, the spacer 15 recesses 21 which extend radially to the tie rod 6 and to its center line M and coaxial with the tie rod 6 in the installed state. The spacers 15 thereby fix not only the tie rod 6 and / or the two separation tubes 13 and 14 relative to the center line M of the rotor 2 and tie rod 6, but they also allow a free and unobstructed coaxial flow of the cooling medium 12. In the installed state form the Recesses 21 each openings.
Grundsätzlich ist der Abstandshalter 15, 15' nicht nur einstückig, sondern aufgrund seiner Gestaltung und aufgrund des verwendeten Werkstoffes auch federelastisch.Basically, the spacer 15, 15 'not only in one piece, but due to its design and due to the material used also resilient.
Gemäß dem in FIG 4 dargestellten Ausführungsbeispiel verbleibt durch die Abstandshalter 15 und ihre Stützarme 17 und ihre Stützfüße 18 etwa der halbe Ringquerschnitt zur Bildung von freien Durchtrittsöffnungen 21. Es steht somit etwa noch der halbe Kanalquerschnitt dem Kühlmedium zum Durchströmen zur Verfügung.According to the embodiment shown in FIG 4 remains through the spacers 15 and their support arms 17 and their support legs 18 about half the ring cross-section to form free passages 21. It is thus about half the channel cross-section of the cooling medium to flow through.
Unabhängig davon sind die Abstandshalter 15, 15' am Umfang 22 des Zugankers 6 bzw. am Umfang 23 des einen Trennrohres 13 in radialer Richtung unbeweglich fixiert. Dazu werden die Abstandshalter 15, 15' mit ihrem Stützring 16, 16' zweckmäßigerweise auf den sie tragenden Zuganker 6, das Trennrohr 13 thermisch aufgeschrumpft.Regardless of the spacers 15, 15 'fixed immovably on the circumference 22 of the tie rod 6 and the periphery 23 of a separating tube 13 in the radial direction. For this purpose, the spacers 15, 15 'with their support ring 16, 16' expediently thermally shrunk onto the tie rod 6 carrying them, the separation tube 13.
Schließlich können der Zuganker 6 und gegebenenfalls auch das innere Trennrohr 13, die jeweils Abstandshalter 15, 15' tragen, Anschläge 24, 25 für die Abstandshalter 15, 15' aufweisen. Diese Anschläge 24, 25 sind gemäß den in den Figuren dargestellten Ausführungsbeispielen jeweils ein umlaufender Wulst und definieren in axialer Richtung exakt diejenige Stelle, an der der Abstandshalter 15, 15' beim thermischen Aufschrumpfen anliegen soll.Finally, the tie rod 6 and possibly also the inner separating tube 13, each of which carries spacers 15, 15 ', have stops 24, 25 for the spacers 15, 15'. These stops 24, 25 are according to the in the figures illustrated embodiments each have a circumferential bead and define in the axial direction exactly the point at which the spacer 15, 15 'should rest during thermal shrinking.
Grundsätzlich gleichartige Abstandshalter wie die Abstandshalter 15 bzw. 15' können auch zwischen den an ihrem Umfang Laufschaufeln 4 tragenden Rotorscheiben 5 und dem Zuganker 6 angeordnet sein. In FIG 1 ist dies im Bereich der Ausneh- mungen 7 symbolisch mit Hilfe von sich kreuzenden, gestrichelten Linien angedeutet. Vor allem die erste Rotorscheibe neben der mittleren Hohlwelle kann zweckmäßigerweise mit einem oder mehreren Abstandshaltern 15 der hier interessierenden Art konkret verbunden sein. Grundsätzlich Gleiches kann aber auch für andere Rotorscheiben 5 gelten, wozu diese entweder unmittelbar mit dem Zuganker 6 oder dem ersten bzw. inneren Trennrohr 13 verbunden sind. In principle, similar spacers as the spacers 15 and 15 'can also be arranged between the rotor disks 5 bearing on their circumference, the rotor blades 4 and the tie rod 6. In FIG. 1, this is indicated symbolically in the region of the recesses 7 by means of intersecting, dashed lines. Above all, the first rotor disk in addition to the central hollow shaft may expediently be concretely connected to one or more spacers 15 of the type of interest here. Basically, the same can apply to other rotor disks 5, to which they are connected either directly to the tie rod 6 or the first or inner separation pipe 13.

Claims

Patentansprüche claims
1. Gasturbine (1), mit mindestens einem Rotor (2), der in mehreren Ebenen (3) angeordnete Laufschaufeln (4) am Umfang von Rotorscheiben (5) aufweist, wobei sich ein Zuganker (6) längs Ausnehmungen (7) in den Rotorscheiben (5) erstreckt und diese als Einheit (8) zusammenhält, und wobei der Rotor (2) ferner grundsätzlich weitere1. gas turbine (1), with at least one rotor (2) arranged in several levels (3) blades (4) on the circumference of rotor discs (5), wherein a tie rod (6) along recesses (7) in the Rotor discs (5) extends and holds them together as a unit (8), and wherein the rotor (2) further more fundamentally
Rotorkomponenten einschließlich mindestens eines den Zuganker (6) ringförmig umgreifenden Kanals (10, 11) aufweist, wobei in zumindest einem Kanal (10, 11) mindestens ein ringförmig gestalteter Abstandshalter (15, 15') zur Fixierung der Lage des Zugankers (6) relativ zur Mittellinie (M) des Rotors (5) vorgesehen ist und der Abstandshalter (15, 15') Ausnehmungen (21) aufweist, die radial zum Zuganker (6) bzw. zu seiner Mittellinie (M) angeordnet sind und sich koaxial erstrecken, dadurch gekennzeichnet, der Kanal (10, 11) bzw. die Kanäle (10, 11) zur Durchleitung eines Kühlmediums (12) ausgebildet und von einem Trennrohr (13, 14) radial außen begrenzt ist, wobei die Ausnehmungen (21) als Durchtrittsöffnungen für das Kühl- medium (12) dienen.Rotor components including at least one of the tie rod (6) annularly encompassing channel (10, 11), wherein in at least one channel (10, 11) at least one ring-shaped spacer (15, 15 ') for fixing the position of the tie rod (6) relative is provided to the center line (M) of the rotor (5) and the spacer (15, 15 ') recesses (21) which are radially to the tie rod (6) or to its center line (M) and extend coaxially, characterized characterized in that the channel (10, 11) or the channels (10, 11) for the passage of a cooling medium (12) and by a separating tube (13, 14) is limited radially outwardly, wherein the recesses (21) as passage openings for the Cooling medium (12) serve.
2. Gasturbine nach Anspruch 1, dadurch gekennzeichnet, dass der Abstandshalter (15, 15') einstückig ist.2. Gas turbine according to claim 1, characterized in that the spacer (15, 15 ') is in one piece.
3. Gasturbine nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass der Abstandshalter (15, 15') federelastisch ist 3. Gas turbine according to claim 1 or 2, characterized in that the spacer (15, 15 ') is resilient
4. Gasturbine nach Anspruch 1, 2 oder 3, dadurch gekennzeichnet, dass im Rotor (2) mehrere Kanäle (10, 11) angeordnet sind, die von jeweils einem Trennrohr (13, 14) oder von einer mittleren Hohlwelle (9) radial außen begrenzt sind.4. Gas turbine according to claim 1, 2 or 3, characterized in that in the rotor (2) a plurality of channels (10, 11) are arranged, each of a separating tube (13, 14) or from a central hollow shaft (9) radially outwardly are limited.
5. Gasturbine nach einen der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass der Abstandshalter (15, 15') am Umfang (22, 23) des5. Gas turbine according to one of the preceding claims, characterized in that the spacer (15, 15 ') on the circumference (22, 23) of the
Zugankers (6) und/oder des den Kanal (10, 11) für das Kühlmedium begrenzenden Trennrohres (13, 14) mindestens in radialer Richtung unbeweglich fixiert ist.Tie rod (6) and / or of the channel (10, 11) for the cooling medium limiting separation tube (13, 14) is fixed immovably at least in the radial direction.
6. Gasturbine nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass mindestens ein Anschlag (24, 25) am Zuganker (6) und/oder am Trennrohr (13, 14) zur axialen Lagefixierung des Abstandshalters (15, 15') vorgesehen ist.6. Gas turbine according to one of the preceding claims, characterized in that at least one stop (24, 25) on the tie rod (6) and / or on the separation pipe (13, 14) for axially fixing the position of the spacer (15, 15 ') is provided.
7. Turbine nach Anspruch 6, dadurch gekennzeichnet, dass ein Wulst als Anschlag (24, 25) am Zuganker (6) und/oder am inneren Trennrohr (13) zur Lagefixierung vorgesehen ist.7. Turbine according to claim 6, characterized in that a bead is provided as a stop (24, 25) on the tie rod (6) and / or on the inner separating tube (13) for fixing the position.
8. Gasturbine nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass der Zuganker (6) den inneren ringförmigen Kanal (11) radial innen begrenzt und das erste Trenn- bzw. Innenrohr (13) den Kanal (10) außen begrenzt.8. Gas turbine according to one of the preceding claims, characterized in that the tie rod (6) the inner annular channel (11) radially inwardly limited and the first separation or inner tube (13) the channel (10) outside limits.
9. Gasturbine nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass ein äußerer ringförmiger Kanal (10) das innere erste Trennbzw. Innenrohr (13) umgreift und von dem zweiten Trennbzw. Außenrohr (14) außen begrenzt ist. 9. Gas turbine according to one of the preceding claims, characterized in that an outer annular channel (10), the inner first Trennbzw. Inner tube (13) engages around and from the second Trennbzw. Outer tube (14) is limited outside.
10. Gasturbine nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass gleichartige Abstandshalter (15, 15') ebenso wie für den Zuganker (6) zugleich zwischen Innenrohr (13) und Außenrohr (14) des ringförmigen Kühlkanals (10) angeordnet sind.10. Gas turbine according to one of the preceding claims, characterized in that similar spacers (15, 15 ') as well as for the tie rod (6) at the same time between the inner tube (13) and outer tube (14) of the annular cooling channel (10) are arranged.
11. Gasturbine nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass der Abstandshalter (15') innenrohrseitig im ringförmigen Kühlkanal (10) angeordnet und lagefixiert ist.11. Gas turbine according to one of the preceding claims, characterized in that the spacer (15 ') inner tube side in the annular cooling channel (10) is arranged and fixed in position.
12. Gasturbine nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass der Abstandshalter (15) ein Ringelement ist und mindestens einen Stützring (16) mit sich radial erstreckenden Stützarmen (17) umfasst, die Stützflächen (20) an ihren Enden aufweisen .12. Gas turbine according to one of the preceding claims, characterized in that the spacer (15) is a ring member and at least one support ring (16) with radially extending support arms (17), the support surfaces (20) at their ends.
13. Gasturbine nach Anspruch 12, dadurch gekennzeichnet, dass zwischen benachbarten Stützarmen (17) des Stützrings (16) die Durchtrittsöffnungen (21) für das Kühlmedium (12) angeordnet sind, derartig, dass zum Durchströmen des Kühlmediums etwa der halbe Ringquerschnitt des Kanals (10, 11) zur Verfügung steht.13. A gas turbine according to claim 12, characterized in that between adjacent support arms (17) of the support ring (16), the passage openings (21) for the cooling medium (12) are arranged, such that for the passage of the cooling medium about half the annular cross-section of the channel ( 10, 11) is available.
14. Turbine nach Anspruch 12 oder 13, dadurch gekennzeichnet, dass die Stützflächen (20) an den freien Enden der Stützarme (17) an Stützfüßen (18) angeordnet sind.14. Turbine according to claim 12 or 13, characterized in that the support surfaces (20) at the free ends of the support arms (17) are arranged on support feet (18).
15. Turbine nach Anspruch 12, 13 oder 14, dadurch gekennzeichnet, dass sich die Stützarme (17) vom Stützring (16) zu den Stütz- fußen (18) schräg zur Mittellinie (M) des Rotors (2) erstrecken . 15. A turbine according to claim 12, 13 or 14, characterized in that the support arms (17) from the support ring (16) to the support feet (18) extend obliquely to the center line (M) of the rotor (2).
16. Turbine nach einem der vorangehenden Ansprüche, dadurch gekennzeichnet, dass der Abstandshalter (15, 15') auf dem ihn tragenden Zuganker (6) und/oder dem Trennrohr (13) aufgeschrumpft ist.16. Turbine according to one of the preceding claims, characterized in that the spacer (15, 15 ') is shrunk on the tie rod carrying it (6) and / or the separating tube (13).
17. Turbine nach mindestens einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass mindestens ein Abstandshalter (15) zwischen Zuganker (6) und mindestens einer der Rotorscheiben (5) vorgesehen sind, die Laufschaufeln (4) an ihrem Umfang tragen. 17. Turbine according to at least one of the preceding claims, characterized in that at least one spacer (15) between tie rods (6) and at least one of the rotor discs (5) are provided, the blades (4) carry on its circumference.
EP08716885A 2007-03-12 2008-02-15 Turbine comprising at least one rotor that consists of rotor disks and a tie bolt Not-in-force EP2118446B1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP08716885A EP2118446B1 (en) 2007-03-12 2008-02-15 Turbine comprising at least one rotor that consists of rotor disks and a tie bolt
PL08716885T PL2118446T3 (en) 2007-03-12 2008-02-15 Turbine comprising at least one rotor that consists of rotor disks and a tie bolt

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP07005082A EP1970533A1 (en) 2007-03-12 2007-03-12 Turbine with at least one rotor with rotor disks and a tie bolt
PCT/EP2008/051880 WO2008110430A1 (en) 2007-03-12 2008-02-15 Turbine comprising at least one rotor that consists of rotor disks and a tie bolt
EP08716885A EP2118446B1 (en) 2007-03-12 2008-02-15 Turbine comprising at least one rotor that consists of rotor disks and a tie bolt

Publications (2)

Publication Number Publication Date
EP2118446A1 true EP2118446A1 (en) 2009-11-18
EP2118446B1 EP2118446B1 (en) 2010-06-30

Family

ID=38308725

Family Applications (2)

Application Number Title Priority Date Filing Date
EP07005082A Withdrawn EP1970533A1 (en) 2007-03-12 2007-03-12 Turbine with at least one rotor with rotor disks and a tie bolt
EP08716885A Not-in-force EP2118446B1 (en) 2007-03-12 2008-02-15 Turbine comprising at least one rotor that consists of rotor disks and a tie bolt

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP07005082A Withdrawn EP1970533A1 (en) 2007-03-12 2007-03-12 Turbine with at least one rotor with rotor disks and a tie bolt

Country Status (10)

Country Link
US (1) US8506239B2 (en)
EP (2) EP1970533A1 (en)
JP (1) JP4954299B2 (en)
CN (1) CN101631931B (en)
AT (1) ATE472670T1 (en)
DE (1) DE502008000876D1 (en)
ES (1) ES2348110T3 (en)
PL (1) PL2118446T3 (en)
RU (1) RU2429350C2 (en)
WO (1) WO2008110430A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2022049064A1 (en) 2020-09-03 2022-03-10 Siemens Gas And Power Gmbh & Co. Kg Rotor assembly for a gas turbine

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140064946A1 (en) * 2012-09-06 2014-03-06 Solar Turbines Incorporated Gas turbine engine compressor undercut spacer
GB201309952D0 (en) * 2013-06-04 2013-07-17 Siemens Ag Shaft arrangement
FR3013766B1 (en) * 2013-11-25 2017-11-10 Snecma TURBOMACHINE COMPRISING A SHAFT AND ASSOCIATED FOURREAU TUBE
WO2015081037A1 (en) * 2013-11-26 2015-06-04 General Electric Company Radial tie-bolt support spring
KR101509382B1 (en) * 2014-01-15 2015-04-07 두산중공업 주식회사 Gas turbine having damping clamp
CN105065121A (en) * 2015-07-09 2015-11-18 中国航空工业集团公司沈阳发动机设计研究所 Disk cavity air distributor device of heavy duty gas turbine
KR101675269B1 (en) * 2015-10-02 2016-11-11 두산중공업 주식회사 Gas Turbine disk
EP3269926B1 (en) * 2016-07-07 2020-10-07 Doosan Heavy Industries & Construction Co., Ltd. Disk assembly and turbine including the same
KR101871060B1 (en) 2016-11-17 2018-06-25 두산중공업 주식회사 Gas Turbine
CN108561186A (en) * 2017-12-29 2018-09-21 无锡宝宏船舶机械有限公司 Turbine pan bottom is capped the turbine rotor shaft of air permeable protective cover
FR3080150B1 (en) * 2018-04-13 2020-09-04 Safran Aircraft Engines TURBOMACHINE INCLUDING A DEVICE FOR IMPROVING THE COOLING OF ROTOR DISCS BY A FLOW OF AIR
GB201917397D0 (en) 2019-11-29 2020-01-15 Siemens Ag Method of assembling and disassembling a gas turbine engine module and an assembly therefor
US11959485B2 (en) * 2020-05-14 2024-04-16 Siemens Energy Global GmbH & Co. KG Compressor rotor structure and method for arranging said rotor structure
CN113898414B (en) * 2021-12-09 2022-03-18 成都中科翼能科技有限公司 Reinforcing structure for preventing thermal vibration deformation of high-pressure rotor of gas turbine

Family Cites Families (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH265291A (en) * 1945-01-16 1949-11-30 Power Jets Res & Dev Ltd Rotor for axial flow machines.
GB800524A (en) * 1955-11-23 1958-08-27 Svenska Turbinfab Ab Improvements in and relating to rotary compressors of the axial flow type
US3304052A (en) * 1965-03-30 1967-02-14 Westinghouse Electric Corp Rotor structure for an elastic fluid utilizing machine
US3680979A (en) * 1970-10-07 1972-08-01 Carrier Corp Rotor structure for turbo machines
US3749516A (en) * 1971-10-06 1973-07-31 Carrier Corp Rotor structure for turbo machines
SE375583B (en) * 1973-05-22 1975-04-21 United Turbine Ab & Co
FR2544387B1 (en) * 1983-04-15 1985-06-14 Snecma APPARATUS FOR TRANSFERRING A FULL TURBINE MODULE FROM A BALANCING MACHINE TO A MOTOR AND VICE VERSA, AND METHOD FOR OPERATING SAID APPARATUS
US5022818A (en) * 1989-02-21 1991-06-11 Westinghouse Electric Corp. Compressor diaphragm assembly
JPH051567A (en) * 1991-06-26 1993-01-08 Ishikawajima Harima Heavy Ind Co Ltd Gas turbine
FR2690482B1 (en) * 1992-04-23 1994-06-03 Snecma CIRCUIT FOR VENTILATION OF COMPRESSOR AND TURBINE DISCS.
JPH08284688A (en) * 1995-04-18 1996-10-29 Hitachi Ltd Gas turbine and gas turbine combustion device
DE19531290A1 (en) * 1995-08-25 1997-02-27 Abb Management Ag Rotor for thermal turbomachinery
JP3652780B2 (en) * 1996-04-08 2005-05-25 三菱重工業株式会社 Turbine cooling system
JPH10266802A (en) * 1997-03-21 1998-10-06 Toshiba Corp Gas turbine rotor
JP3486329B2 (en) * 1997-09-11 2004-01-13 三菱重工業株式会社 Sealing device between bolt holes and bolts in gas turbine disks
FR2817289B1 (en) * 2000-11-30 2003-01-31 Snecma Moteurs DEVICE FOR CENTERING A TUBE IN A TURBINE SHAFT
JP2003120209A (en) * 2001-10-10 2003-04-23 Mitsubishi Heavy Ind Ltd Sealing structure of spindle bolt and gas turbine
RU2230195C2 (en) 2002-05-30 2004-06-10 Открытое акционерное общество "Авиадвигатель" Multistage turbine rotor
US6773229B1 (en) * 2003-03-14 2004-08-10 General Electric Company Turbine nozzle having angel wing seal lands and associated welding method
EP1843009A1 (en) * 2006-04-06 2007-10-10 Siemens Aktiengesellschaft Stator vane segment for a turbomachine, associated manufacturing method and turbomachine
EP2172620B1 (en) * 2007-06-22 2016-11-30 Mitsubishi Hitachi Power Systems, Ltd. Stator blade ring for an axial compressor

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2008110430A1 *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2022049064A1 (en) 2020-09-03 2022-03-10 Siemens Gas And Power Gmbh & Co. Kg Rotor assembly for a gas turbine
US12037919B2 (en) 2020-09-03 2024-07-16 Siemens Energy Global GmbH & Co. KG Rotor assembly for a gas turbine

Also Published As

Publication number Publication date
ATE472670T1 (en) 2010-07-15
WO2008110430A1 (en) 2008-09-18
US20100143149A1 (en) 2010-06-10
JP4954299B2 (en) 2012-06-13
US8506239B2 (en) 2013-08-13
RU2009137599A (en) 2011-04-20
CN101631931B (en) 2013-02-13
EP1970533A1 (en) 2008-09-17
PL2118446T3 (en) 2010-11-30
JP2010520968A (en) 2010-06-17
CN101631931A (en) 2010-01-20
RU2429350C2 (en) 2011-09-20
EP2118446B1 (en) 2010-06-30
DE502008000876D1 (en) 2010-08-12
ES2348110T3 (en) 2010-11-30

Similar Documents

Publication Publication Date Title
EP2118446B1 (en) Turbine comprising at least one rotor that consists of rotor disks and a tie bolt
EP2084369B1 (en) Guiding device of a flow machine and guide vane for such a guiding device
DE3444587C2 (en) Retaining plate for axially holding rotor blades on an impeller disk
DE1551180A1 (en) Guide vane ring for turbo machines, especially gas turbine engines
DE2800862A1 (en) COMPRESSOR ROTOR STAGE FOR GAS TURBINE ENGINES
DE3008889A1 (en) BLADED ROTOR FOR A GAS TURBINE ENGINE
DE102014220317A1 (en) Aircraft gas turbine engine with shock absorbing element for fan blade loss
EP3092371B1 (en) Rotor with axially secured support ring
EP3545205B1 (en) Rotation system with radial gas bearing
EP2880264A1 (en) Rotor for an axial flow turbomachine and double nut for connecting two tie-rod elements
WO2008110431A1 (en) Rotor for a gas turbine
EP2041397B1 (en) Reduction of the amplitude of rotor flexural vibrations
DE2441249C3 (en) Axial impeller for high-speed turbo machines
EP2994614A1 (en) Rotor for a thermal turbomachine
EP1676980A1 (en) Turbocharger with variable geometry turbine and manufacturing method
EP2994615B1 (en) Rotor for a thermal turbomachine
EP3121385A1 (en) Rotor device of an aircraft engine with damping device between rotor blades
DE3913343C2 (en) Retaining sleeve for roller and needle bearings
CH663447A5 (en) TURBO MACHINE WITH AT LEAST ONE RADIAL FLOWED WHEEL.
EP1970528A1 (en) Rotor of a thermal fluid flow engine
WO2008116738A1 (en) Gas turbine comprising a tie-rod with interior ventilation
DE69820536T2 (en) Bearing construction for a turbocharger
DE102007024433A1 (en) Multi-stage Cone Fan Motor Assembly
EP2840230A1 (en) Rotor for a thermal flow engine
DE60215327T2 (en) TURBINE OR COMPRESSOR DEVICE AND METHOD FOR ASSEMBLING THE DEVICE

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20090804

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MT NL NO PL PT RO SE SI SK TR

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

DAX Request for extension of the european patent (deleted)
AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MT NL NO PL PT RO SE SI SK TR

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: NV

Representative=s name: SIEMENS SCHWEIZ AG

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REF Corresponds to:

Ref document number: 502008000876

Country of ref document: DE

Date of ref document: 20100812

Kind code of ref document: P

REG Reference to a national code

Ref country code: NL

Ref legal event code: VDEP

Effective date: 20100630

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20100630

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20100630

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20100930

LTIE Lt: invalidation of european patent or patent extension

Effective date: 20100630

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20100630

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20100630

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20100630

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20100630

REG Reference to a national code

Ref country code: PL

Ref legal event code: T3

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20100630

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20100630

REG Reference to a national code

Ref country code: IE

Ref legal event code: FD4D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20100630

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20100630

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20101030

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20100630

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20100630

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20100630

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20100630

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20101001

26N No opposition filed

Effective date: 20110331

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502008000876

Country of ref document: DE

Effective date: 20110330

BERE Be: lapsed

Owner name: SIEMENS A.G.

Effective date: 20110228

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20110228

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20111102

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20110228

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20100630

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20110228

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20110215

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20100630

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20100930

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20100630

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20100630

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 472670

Country of ref document: AT

Kind code of ref document: T

Effective date: 20130215

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20130215

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: CH

Payment date: 20150504

Year of fee payment: 8

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: ES

Payment date: 20160328

Year of fee payment: 9

Ref country code: IT

Payment date: 20160225

Year of fee payment: 9

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20160208

Year of fee payment: 9

Ref country code: PL

Payment date: 20160122

Year of fee payment: 9

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20160420

Year of fee payment: 9

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160229

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160229

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502008000876

Country of ref document: DE

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20170215

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170901

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170215

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170215

REG Reference to a national code

Ref country code: ES

Ref legal event code: FD2A

Effective date: 20180705

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170216

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PL

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170215