EP1970533A1 - Turbine with at least one rotor with rotor disks and a tie bolt - Google Patents

Turbine with at least one rotor with rotor disks and a tie bolt Download PDF

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Publication number
EP1970533A1
EP1970533A1 EP07005082A EP07005082A EP1970533A1 EP 1970533 A1 EP1970533 A1 EP 1970533A1 EP 07005082 A EP07005082 A EP 07005082A EP 07005082 A EP07005082 A EP 07005082A EP 1970533 A1 EP1970533 A1 EP 1970533A1
Authority
EP
European Patent Office
Prior art keywords
tie rod
turbine according
spacer
rotor
turbine
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.)
Withdrawn
Application number
EP07005082A
Other languages
German (de)
French (fr)
Inventor
Francois Dr. 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 EP07005082A priority Critical patent/EP1970533A1/en
Priority to CN2008800083079A priority patent/CN101631931B/en
Priority to ES08716885T priority patent/ES2348110T3/en
Priority to PL08716885T priority patent/PL2118446T3/en
Priority to RU2009137599/06A priority patent/RU2429350C2/en
Priority to AT08716885T priority patent/ATE472670T1/en
Priority to EP08716885A priority patent/EP2118446B1/en
Priority to US12/530,473 priority patent/US8506239B2/en
Priority to PCT/EP2008/051880 priority patent/WO2008110430A1/en
Priority to JP2009553094A priority patent/JP4954299B2/en
Priority to DE502008000876T priority patent/DE502008000876D1/en
Publication of EP1970533A1 publication Critical patent/EP1970533A1/en
Withdrawn legal-status Critical Current

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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
    • F01D5/02—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 turbine according to the preamble of claim 1.
  • Multi-stage turbines and in particular thermal turbomachines with at least one rotor or rotor, which has arranged in a plurality of radial planes blades on the circumference of rotor disks are basically known in various embodiments. These include steam turbines as well as gas turbines.
  • the invention has for its object to provide measures to prevent in particular natural oscillations of the tie rod regardless of the speed and especially at high speeds. All rotating parts of the turbine should form a static unit.
  • the invention with the features of the characterizing part of claim 1 provides that at least one ring-shaped spacer is provided for fixing the position of the tie rod relative to the center line of the rotor and that the spacer has passage openings which are arranged radially to the tie rod or to its center line and extend coaxially.
  • the spacer according to the invention or according to the embodiment, a spring ring with coaxially extending through 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 are generally used in the field of cooling and separation pipes that surround the tie rods at a distance.
  • the spacers are here between the tie rod and the cooling medium leading, forming a ring channel separator tube.
  • the annular channel may in this context also be formed by an inner or first separator tube and an outer or second separator tube, so that then first spacers between tie rods and inner separator tube on the one hand and second spacers between the inner separator tube and an outer separator tube are provided.
  • a multi-stage turbine 1 in the form of a thermal turbomachine or even more specific in the form of a gas turbine according to the aborted representation in FIG. 1 a rotor 2, which has blades 4 arranged on several levels 3 on the circumference of rotor disks 5.
  • a tie rod 6 extends along centrally arranged recesses 7 in the rotor disks 5 through the in FIG. 1 Located on the left compressor section of the turbine 1 and is anchored in one of the rotor disks, not shown, or in a suitable Rotorendteil in a manner not shown.
  • the tie rod 6 holds the rotor discs 5 and other parts of the turbine 1 and its rotor in a basically known manner form-fitting together.
  • a middle hollow shaft 9 Axially next to the compressor of the gas turbine rotor disks 5 is a middle hollow shaft 9. Radially outside of this central hollow shaft 9 are the combustion chambers of the gas turbine.
  • At least one annular channel 10 and 11 serves to guide a cooling medium 12, the in FIG. 1 symbolized with the help of an arrow.
  • the cooling medium 12 leading annular channel 10 is basically formed by a first or inner separation pipe 13 and a second or outer separation pipe 14.
  • the inner separation tube 13 surrounds the tie rod 6 with an annular gap 11 or an annular channel 11.
  • 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 the FIGS. 2 to 6 combined with FIG. 1 evident.
  • 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 at its end a support surface 20 with which the spacer 15 and its support arm 17 respectively rests.
  • 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 ring-side end of the support arm 17, around which the support arm 17 can pivot in the radial direction, if it is acted upon by centrifugal forces accordingly becomes. Centrifugal forces thereby that the support legs 18 do not solve by centrifugal force of their contact surface, but according to a higher speed of the rotor 2 more abut their contact surface with spreading force, at the same time the radial extent between support ring 16 and support leg 18 can not be smaller with certainty. 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 FIG. 1 evident.
  • the support ring 16 ' bears against the outside on the first or inner separation tube 13 and is supported with its support feet 18' on the inside of the second or outer separation tube 14.
  • the separating tube 14 also serves as a radially inner boundary for the central hollow shaft 9, as seen from FIG. 1 evident.
  • 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 illustrated embodiment 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 therefore still 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 embodiments shown in the figures each a circumferential bead and define in the axial direction exactly the point at which the spacer 15, 15 'should rest during thermal shrinking.
  • first rotor disk in addition to the central hollow shaft may expediently be connected in concrete terms to one or more spacers 15 of the type of interest here with the first or inner separating pipe 13 which forms the annular channel. 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.

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  • 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

Die Erfindung betrifft eine Turbine gemäß Oberbegriff von Patentanspruch 1.The invention relates to a turbine according to the preamble of claim 1.

Mehrstufige Turbinen, und hier insbesondere thermische Strömungsmaschinen mit mindestens einem Läufer bzw. Rotor, der in mehreren Radialebenen angeordnete Laufschaufeln am Umfang von Rotorscheiben aufweist, sind grundsätzlich in verschiedenartigen Ausführungsformen bekannt. Dazu gehören Dampfturbinen ebenso wie Gasturbinen.Multi-stage turbines, and in particular thermal turbomachines with at least one rotor or rotor, which has arranged in a plurality of radial planes blades on the circumference of rotor disks are basically known in various embodiments. These include steam turbines as well as gas turbines.

Ferner ist es bekannt, zumindest bei Gasturbinen die einzelnen Rotorscheiben mit den Laufschaufeln stirnflächig sowie formschlüssig so zu gestalten, dass sie sich mit Hilfe eines 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 Turbine zerstören. Dies gilt insbesondere auch für Gasturbinen, bei denen sich der Zuganker durch die Verdichterstufe, sodann durch eine mittlere Hohlwelle mit den dort radial außen befindlichen Brennkammern und schließlich durch die Turbinenstufe erstreckt.Furthermore, it is known, at least for gas turbines, to design the individual rotor disks with the rotor blades in an end-face-like manner and in a form-fitting manner such that they can be held together as a unit by means of a tie rod. 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 turbine. This also applies in particular to gas turbines in which the tie rod extends through the compressor stage, then through a central hollow shaft with the combustion chambers located radially out there and finally through the turbine stage.

Der Erfindung liegt die Aufgabe zugrunde, Maßnahmen vorzusehen, um insbesondere Eigenschwingungen des Zugankers unabhängig von der Drehzahl und insbesondere bei hohen Drehzahlen zu verhindern. Alle sich drehenden Teile der Turbine sollen dabei eine statische Einheit bilden.The invention has for its object to provide measures to prevent in particular natural oscillations of the tie rod regardless of the speed and especially at high speeds. All rotating parts of the turbine should form a static unit.

Zur Lösung dieser Aufgabe sieht die Erfindung mit den Merkmalen des kennzeichnenden Teiles von Patentanspruch 1 vor, dass mindestens ein ringförmig gestalteter Abstandshalter zur Fixierung der Lage des Zugankers relativ zur Mittellinie des Rotors vorgesehen ist und dass der Abstandshalter Durchtrittsöffnungen aufweist, die radial zum Zuganker bzw. zu seiner Mittellinie angeordnet sind und sich koaxial erstrecken.To solve this problem, the invention with the features of the characterizing part of claim 1 provides that at least one ring-shaped spacer is provided for fixing the position of the tie rod relative to the center line of the rotor and that the spacer has passage openings which are arranged radially to the tie rod or to its center line and extend coaxially.

Grundsätzlich ist der Abstandshalter gemäß der Erfindung bzw. gemäß Ausführungsbeispiel ein Federring mit sich koaxial erstreckenden Durchtrittsöffnungen. 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.Basically, the spacer according to the invention or according to the embodiment, a spring ring with coaxially extending through 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 erfindungsgemäß baugleiche Abstandshalter grundsätzlich auch im Bereich von Kühl- und Trennrohren verwendet werden, die den Zuganker mit Abstand umgeben. Die Abstandshalter befinden sich hier zwischen dem Zuganker und dem das Kühlmedium führenden, einen Ringkanal bildenden Trennrohr. Gegebenenfalls können der Ringkanal in diesem Zusammenhang auch von einem inneren oder ersten Trennrohr und einem äußeren oder zweiten Trennrohr gebildet werden, so dass dann erste Abstandshalter zwischen Zuganker und innerem Trennrohr einerseits und zweite Abstandshalter zwischen dem inneren Trennrohr und einem äußeren Trennrohr vorgesehen sind.This also includes that according to the invention identical spacers are generally used in the field of cooling and separation pipes that surround the tie rods at a distance. The spacers are here between the tie rod and the cooling medium leading, forming a ring channel separator tube. Optionally, the annular channel may in this context also be formed by an inner or first separator tube and an outer or second separator tube, so that then first spacers between tie rods and inner separator tube on the one hand and second spacers between the inner separator tube and an outer separator tube are provided.

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 subclaims 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:

FIG 1
abgeschnitten sowie zum Teil im Schnitt einen Teil des Läufers/Rotors einer mehrstufigen Turbine;
FIG 2
schräg von unten eine perspektivische Ansicht eines Abstandshalters in anderem Maßstab;
FIG 3
eine perspektivische Ansicht wie in FIG 2, jedoch leicht schräg von oben;
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.
The invention will be described in more detail below with reference to embodiments shown in the drawing. Showing:
FIG. 1
cut off and partly in section a part of the rotor / rotor of a multi-stage turbine;
FIG. 2
obliquely from below a perspective view of a spacer on a different scale;
FIG. 3
a perspective view as in FIG. 2 but slightly diagonally from above;
FIG. 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
FIG. 5
a section along the line VV in FIG. 4 ,

Eine mehrstufige Turbine 1 in Gestalt einer thermischen Strömungsmaschine bzw. noch etwas konkreter in Gestalt einer Gasturbine umfasst gemäß der abgebrochenen Darstellung in FIG 1 einen Rotor 2, der in mehreren Ebenen 3 angeordnete Laufschaufeln 4 am Umfang von Rotorscheiben 5 aufweist. Ein Zuganker 6 erstreckt sich längs mittig angeordneter Ausnehmungen 7 in den Rotorscheiben 5 durch den in FIG 1 links befindlichen Verdichterteil der Turbine 1 und ist in einer der nicht dargestellten Rotorscheiben bzw. in einem geeigneten Rotorendteil in nicht dargestellter Weise verankert.A multi-stage turbine 1 in the form of a thermal turbomachine or even more specific in the form of a gas turbine according to the aborted representation in FIG. 1 a rotor 2, which has blades 4 arranged on several levels 3 on the circumference of rotor disks 5. A tie rod 6 extends along centrally arranged recesses 7 in the rotor disks 5 through the in FIG. 1 Located on the left compressor section of the turbine 1 and is anchored in one of the rotor disks, not shown, or in a suitable Rotorendteil in a manner not shown.

Der Zuganker 6 hält die Rotorscheiben 5 sowie weitere Teile der Turbine 1 bzw. ihres Rotors in grundsätzlich bekannter Weise formschlüssig zusammen.The tie rod 6 holds the rotor discs 5 and other parts of the turbine 1 and its rotor in a basically known manner form-fitting together.

Axial neben den zum Verdichter der Gasturbine gehörenden Rotorscheiben 5 befindet sich eine mittlere Hohlwelle 9. Radial außerhalb von dieser mittleren Hohlwelle 9 befinden sich die Brennkammern der Gasturbine.Axially next to the compressor of the gas turbine rotor disks 5 is a middle hollow shaft 9. Radially outside of this central hollow shaft 9 are the combustion chambers of the gas turbine.

Zwischen der mittleren Hohlwelle 9 und dem Zuganker 6 befindet sich mindestens ein ringförmiger Kanal 10 bzw. 11 und dient zur Führung eines Kühlmediums 12, das in FIG 1 mit Hilfe eines Pfeils symbolisiert ist.Between the central hollow shaft 9 and the tie rod 6 is at least one annular channel 10 and 11 and serves to guide a cooling medium 12, the in FIG. 1 symbolized with the help of an arrow.

Der das Kühlmedium 12 führende ringförmige Kanal 10 wird grundsätzlich von einem ersten oder inneren Trennrohr 13 und einem zweiten oder äußeren Trennrohr 14 gebildet. Das innere Trennrohr 13 umgibt mit einem Ringspalt 11 bzw. einem ringförmigen Kanal 11 den Zuganker 6. 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 cooling medium 12 leading annular channel 10 is basically formed by a first or inner separation pipe 13 and a second or outer separation pipe 14. The inner separation tube 13 surrounds the tie rod 6 with an annular gap 11 or an annular channel 11. For the 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 the FIGS. 2 to 6 combined with FIG. 1 evident.

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 aufliegt.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 embodiment, each support leg 18 at its end a support surface 20 with which the spacer 15 and its support arm 17 respectively rests.

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 beaufschlagt wird. Fliehkräfte bewirken dadurch, dass die Stützfüße 18 sich durch Fliehkraft nicht von ihrer Anlagefläche 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 ring-side end of the support arm 17, around which the support arm 17 can pivot in the radial direction, if it is acted upon by centrifugal forces accordingly becomes. Centrifugal forces thereby that the support legs 18 do not solve by centrifugal force of their contact surface, but according to a higher speed of the rotor 2 more abut their contact surface with spreading force, at the same time the radial extent between support ring 16 and support leg 18 can not be smaller with certainty. 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 FIG. 1 evident. The support ring 16 'bears against the outside on the first or inner separation tube 13 and is supported with its support feet 18' on the inside of the second or outer separation tube 14.

Das Trennrohr 14 dient dabei ferner als radial innere Begrenzung für die mittlere Hohlwelle 9, wie aus FIG 1 hervorgeht.The separating tube 14 also serves as a radially inner boundary for the central hollow shaft 9, as seen from FIG. 1 evident.

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 in FIG. 4 illustrated embodiment 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 therefore still 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 embodiments shown in the figures each 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 Ausnehmungen 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 mit dem ersten oder inneren Trennrohr 13, das den ringförmigen Kanal bildet, 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 connected in concrete terms to one or more spacers 15 of the type of interest here with the first or inner separating pipe 13 which forms the annular channel. 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 (16)

Turbine,
insbesondere thermische Strömungsmaschine 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 ferner grundsätzlich weitere Rotor- und Turbinenkomponenten einschließlich mindestens einen Kanals (10) für ein Kühlmedium (12) vorgesehen sind,
dadurch gekennzeichnet, dass
mindestens ein ringförmig gestalteter Abstandshalter (15, 15') zur Fixierung der Lage des Zugankers (6) relativ zur Mittellinie (M) des Rotors (5) vorgesehen ist und
dass der Abstandshalter (15, 15') Ausnehmungen (21) aufweist, die radial zum Zuganker (6) bzw. zu seiner Mittellinie (M) angeordnet sind und sich koaxial erstrecken.Turbine,
in particular thermal turbomachine with at least one rotor (2) which has blades (4) arranged in several planes (3) on the circumference of rotor disks (5), a tie rod (6) being arranged along recesses (7) in the rotor disks (5) extends and holds them together as a unit (8),
and further comprising further rotor and turbine components including at least one channel (10) for a cooling medium (12),
characterized in that
at least one annular shaped spacer (15, 15 ') for fixing the position of the tie rod (6) relative to the center line (M) of the rotor (5) is provided and
in that the spacer (15, 15 ') has recesses (21) which are arranged radially to the tie rod (6) or to its center line (M) and extend coaxially. Turbine nach Anspruch 1,
dadurch gekennzeichnet, dass
der Abstandshalter (15, 15') einstückig ist.Turbine according to claim 1,
characterized in that
the spacer (15, 15 ') is in one piece. Turbine nach Anspruch 1 oder 2,
dadurch gekennzeichnet, dass
der Abstandshalter (15, 15') federelastisch ist.Turbine according to claim 1 or 2,
characterized in that
the spacer (15, 15 ') is resilient. Turbine nach Anspruch 1, 2 oder 3,
dadurch gekennzeichnet, dass
der Abstandshalter (15, 15') am Umfang (22, 23) des Zugankers (6) und/oder eines einen Kanal (10) für ein Kühlmedium bildenden Trennrohres (13) mindestens in radialer Richtung unbeweglich fixiert ist.Turbine according to claim 1, 2 or 3,
characterized in that
the spacer (15, 15 ') on the circumference (22, 23) of the tie rod (6) and / or a separating tube (13) forming a channel (10) for a cooling medium is fixed immovably at least in the radial direction. Turbine nach einem der vorhergehenden Ansprüche,
dadurch gekennzeichnet, dass
mindestens ein Anschlag (24, 25) am Zuganker (6) und/oder am Trennrohr (13) zur axialen Lagefixierung des Abstandshalters (15, 15') vorgesehen ist.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 separating tube (13) for axially fixing the position of the spacer (15, 15 ') is provided. Turbine nach Anspruch 5,
dadurch gekennzeichnet, dass
eine Verdickung/ein Wulst als Anschlag (24, 25) am Zuganker (6) und/oder am inneren Trennrohr (13) zur Lagefixierung vorgesehen ist.Turbine according to claim 5,
characterized in that
a thickening / 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. Turbine nach einem der vorhergehenden Ansprüche,
dadurch gekennzeichnet, dass
die Ausnehmungen (21) im eingebauten Zustand des Abstandshalters (15, 15') Durchtrittsöffnungen (21) für ein Kühlmedium (12) bilden.Turbine according to one of the preceding claims,
characterized in that
the recesses (21) in the installed state of the spacer (15, 15 ') form passage openings (21) for a cooling medium (12). Turbine nach einem der vorhergehenden Ansprüche,
dadurch gekennzeichnet, dass
der Zuganker (6) in einem Kanal (10) angeordnet ist, der von mindestens einem ein Kühlmedium (12) führenden Trennrohr (13) gebildet ist.Turbine according to one of the preceding claims,
characterized in that
the tie rod (6) is arranged in a channel (10) which is formed by at least one separating tube (13) carrying a cooling medium (12). Turbine nach Anspruch 8,
dadurch gekennzeichnet, dass
der Zuganker (6) in einem ein Kühlmedium (12) führenden, ringförmigen Kanal (10) angeordnet ist, der von einem ersten Trenn- bzw. Innenrohr (13) und einem zweiten Trenn- bzw. Außenrohr (14) gebildet ist.Turbine according to claim 8,
characterized in that
the tie rod (6) is arranged in an annular channel (10) leading to a cooling medium (12), which is formed by a first separating or inner tube (13) and a second separating or outer tube (14). Turbine 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.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 the outer tube (14) of the annular cooling channel (10) are arranged. Turbine nach mindestens einem der vorhergehenden Ansprüche,
dadurch gekennzeichnet, dass
der Abstandshalter (15') innenrohrseitig im ringförmigen Kühlkanal (10) angeordnet und lagefixiert ist.Turbine according to at least 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. Turbine nach mindestens 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.Turbine according to at least one of the preceding claims,
characterized in that
the spacer (15) is a ring element and comprises at least one support ring (16) with radially extending support arms (17) having support surfaces (20) at their ends. Turbine nach Anspruch 12,
dadurch gekennzeichnet, dass
die Stützflächen (20) an den freien Enden der Stützarme (17) an Stützfüßen (18) angeordnet sind.Turbine according to claim 12,
characterized in that
the support surfaces (20) at the free ends of the support arms (17) are arranged on support feet (18). Turbine nach Anspruch 13,
dadurch gekennzeichnet, dass
sich die Stützarme (17) vom Stützring (16) zu den Stützfüßen (18) schräg zur Mittellinie (M) des Rotors (2) erstrecken.Turbine according to claim 13,
characterized in that
extending the support arms (17) from the support ring (16) to the support legs (18) obliquely to the center line (M) of the rotor (2). Turbine nach Anspruch 12, 13 oder 14,
dadurch gekennzeichnet, dass
der Abstandshalter (15, 15') mit seinem Stützring (16) auf dem ihn tragenden Zuganker (6) und/oder dem Trennrohr (13) thermisch aufgeschrumpft ist.Turbine according to claim 12, 13 or 14,
characterized in that
the spacer (15, 15 ') with its supporting ring (16) is thermally shrunk on the tie rod (6) and / or the separating tube (13) carrying it. 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.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.
EP07005082A 2007-03-12 2007-03-12 Turbine with at least one rotor with rotor disks and a tie bolt Withdrawn EP1970533A1 (en)

Priority Applications (11)

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
CN2008800083079A CN101631931B (en) 2007-03-12 2008-02-15 Turbine comprising at least one rotor that consists of rotor disks and a tie bolt
ES08716885T ES2348110T3 (en) 2007-03-12 2008-02-15 TURBINE THAT INCLUDES, AT LEAST, A ROTOR CONSTITUTED BY ROTOR DISCS AND A RIOSTRA.
PL08716885T PL2118446T3 (en) 2007-03-12 2008-02-15 Turbine comprising at least one rotor that consists of rotor disks and a tie bolt
RU2009137599/06A RU2429350C2 (en) 2007-03-12 2008-02-15 Turbine with at least one rotor consisting of rotor disks and coupling bolt
AT08716885T ATE472670T1 (en) 2007-03-12 2008-02-15 TURBINE WITH AT LEAST ONE ROTOR CONSISTING OF ROTOR DISCS AND A TIE ROD
EP08716885A EP2118446B1 (en) 2007-03-12 2008-02-15 Turbine comprising at least one rotor that consists of rotor disks and a tie bolt
US12/530,473 US8506239B2 (en) 2007-03-12 2008-02-15 Turbine with at least one rotor which comprises 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
JP2009553094A JP4954299B2 (en) 2007-03-12 2008-02-15 Gas turbine having at least one rotor comprising a turbine disk and a connecting rod
DE502008000876T DE502008000876D1 (en) 2007-03-12 2008-02-15 TURBINE WITH AT LEAST ONE ROTOR CONSISTING OF ROTOR DISCS AND A ZUGANKER

Applications Claiming Priority (1)

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

Publications (1)

Publication Number Publication Date
EP1970533A1 true EP1970533A1 (en) 2008-09-17

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 After (1)

Application Number Title Priority Date Filing Date
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

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)

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EP2896784A1 (en) * 2014-01-15 2015-07-22 Doosan Heavy Industries & Construction Co., Ltd. Gas turbine having damping clamp
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

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Also Published As

Publication number Publication date
PL2118446T3 (en) 2010-11-30
RU2429350C2 (en) 2011-09-20
US8506239B2 (en) 2013-08-13
DE502008000876D1 (en) 2010-08-12
ES2348110T3 (en) 2010-11-30
JP4954299B2 (en) 2012-06-13
CN101631931A (en) 2010-01-20
RU2009137599A (en) 2011-04-20
US20100143149A1 (en) 2010-06-10
EP2118446B1 (en) 2010-06-30
JP2010520968A (en) 2010-06-17
ATE472670T1 (en) 2010-07-15
CN101631931B (en) 2013-02-13
EP2118446A1 (en) 2009-11-18
WO2008110430A1 (en) 2008-09-18

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