EP1621735A2 - Gas turbine rotor - Google Patents

Gas turbine rotor Download PDF

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Publication number
EP1621735A2
EP1621735A2 EP05106088A EP05106088A EP1621735A2 EP 1621735 A2 EP1621735 A2 EP 1621735A2 EP 05106088 A EP05106088 A EP 05106088A EP 05106088 A EP05106088 A EP 05106088A EP 1621735 A2 EP1621735 A2 EP 1621735A2
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EP
European Patent Office
Prior art keywords
sealing
blade
air
gas turbine
turbine rotor
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
EP05106088A
Other languages
German (de)
French (fr)
Other versions
EP1621735B1 (en
EP1621735A3 (en
Inventor
Richard Whitton
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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Publication date
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Publication of EP1621735A2 publication Critical patent/EP1621735A2/en
Publication of EP1621735A3 publication Critical patent/EP1621735A3/en
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Publication of EP1621735B1 publication Critical patent/EP1621735B1/en
Expired - Fee Related 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/50—Vibration damping features

Definitions

  • the invention relates to a gas turbine rotor, which comprises a disc with turbine blades held in transverse grooves at their peripheral edge, which consist of an airfoil, a blade platform and a blade root fixed in the respective transverse groove, wherein the airfoils have hollow spaces through which cooling air flows and in the opposing ones Side surfaces of the blade platforms each have a recess for receiving a gap between the blade platforms bridging sealing and damping element is formed.
  • Gas turbine rotors of the type described above are known, for example, from US Pat. No. 6,561,764 B1.
  • these gas turbine rotors are disadvantageous in relation to the sealing and damping elements in that the sealing with a single mechanical seal is not completely successful and thus over the remaining gap between the blade platforms hot gas in the area below the blade platforms and thus in the mounting region of the turbine blades on Peripheral edge of the disc passes. The result is a reduction in the life of the disc.
  • the invention has for its object to form a gas turbine rotor of the type described above with low manufacturing effort so that hot gas leakage over the gap between the blade platformsverhindert or reduced and thus the life of the rotor disk is increased.
  • the basic idea of the invention consists in that a part of the cooling air introduced into the cavities of the respective airfoil for its interior cooling and film cooling is continuously directed into the gap between adjacent airfoil platforms and aerodynamically seals them, or at least reduces the hot gas leakage or the Gap possibly penetrating hot gas cools. As a result, excessive heat load of the rotor disk is prevented and consequently prolongs their life.
  • the supply of cooling air or sealing air into the gap via at least one air duct which starts from the interior of the airfoil and opens at least one of the side surfaces of the blade platform.
  • the air flow can be introduced at an axial distance from the mechanical sealing element in the gap or in Combination with the mechanical sealing and damping element and strengthen its sealing effect.
  • At least one distribution groove are formed in the side surfaces of the blade platforms in order to distribute the sealing air in the gap targeted.
  • the sealing and damping elements respectively arranged between the opposite side surfaces 6 of adjacent blade platforms 7 are intended on the one hand to limit the vibration of the rotor blades and, on the other hand, to limit the contact of the turbine disk with the hot gas.
  • the arrangement of the sealing and damping element is due to the structural design of the blade platforms 7 and manufacturing reasons limited to a certain - straight - area of the respective side surface.
  • the remaining free gap between the side surfaces 6 of the blade platforms 7 is shielded with respect to the hot gas atmosphere with a continuous sealing air flow (arrow C), which is supplied from a cavity 5 of the airfoil 4.
  • the sealing air is supplied via an air channel 9, which opens directly on a side surface of the platforms, in a gap under the influence of hot gas gap, which is not mechanically sealed by a sealing and damping element.
  • the air inlet is provided axially separated from the mechanical sealing and damping element.
  • the sealing air outlet opening can also be arranged in conjunction with the sealing and damping element so that its sealing effect is enhanced.
  • a single air channel 9 is provided with a round cross-section. But it can also be arranged two or more air ducts, which may also have any cross-sectional shape and can also lead to both side surfaces 6 one and the same blade platform 7.
  • the sealing air entering between the side surfaces 6 of respectively adjacent platforms 7 is distributed in the gap and seals it against the hot air.
  • the air duct 9 can also open into a distribution groove 10 formed in the side surface 6 of the platform 7 so as to distribute the sealing air in the gap between the opposing side surfaces 6 in a targeted manner.
  • the distribution grooves 10 may have any shape. It can be formed in a side surface and a plurality of distribution grooves.

Abstract

The gas turbine rotor has blades (4) with inner space cooled and a mechanical sealing and damping component between the opposing side surfaces (6) of the adjacent blade platforms (7). The gap between the side surfaces is additionally dynamically sealed in relation to the hot gas flow. Cooling air is conducted via a cooling channel (9) out of a hollow space (5) of the rotor blades into the gap between the side surfaces.

Description

Die Erfindung betrifft einen Gasturbinenrotor, der eine Scheibe mit an deren Umfangsrand in Quernuten gehaltenen Turbinenlaufschaufeln, die aus einem Schaufelblatt, einer Schaufelplattform und einem in der jeweiligen Quernut fixierten Schaufelfuß bestehen, umfasst, wobei die Schaufelblätter von Kühlluft durchströmte Hohlräume aufweisen und in den einander gegenüberliegenden Seitenflächen der Schaufelplattformen jeweils eine Ausnehmung zur Aufnahme eines den Spalt zwischen den Schaufelplattformen überbrückenden Dichtungs- und Dämpfungselements ausgebildet ist.The invention relates to a gas turbine rotor, which comprises a disc with turbine blades held in transverse grooves at their peripheral edge, which consist of an airfoil, a blade platform and a blade root fixed in the respective transverse groove, wherein the airfoils have hollow spaces through which cooling air flows and in the opposing ones Side surfaces of the blade platforms each have a recess for receiving a gap between the blade platforms bridging sealing and damping element is formed.

Gasturbinenrotoren der eingangs beschriebenen Art sind beispielsweise aus der US 6 561 764 B1 bekannt. Die zwischen den Seitenflächen der Schaufelplattformen angeordneten Dichtungs- und Dämpfungselemente sollen einerseits die Ventilationsverluste minimieren und die Schwingungen der Turbinenlaufschaufeln verringern. Diese Gasturbinenrotoren sind jedoch in Bezug auf die Dichtungs- und Dampfungselemente insofern nachteilig, als die Abdichtung mit einer einzigen mechanischen Dichtung nicht vollständig gelingt und somit über den verbleibenden Spalt zwischen den Schaufelplattformen Heißgas in den Bereich unterhalb der Schaufelplattformen und damit in den Befestigungsbereich der Turbinenlaufschaufeln am Umfangsrand der Scheibe gelangt. Die Folge ist eine Verringerung der Lebensdauer der Scheibe. Die Anordnung von zusätzlichen mechanischen Dichtungselementen zwischen den Schaufelplattformen in den Bereichen, in denen das Dichtungs- und Dämpfungselement nicht wirksam ist, erfordert jedoch einen erheblichen fertigungstechnischen Aufwand und kann zudem zu Spannungen führen.Gas turbine rotors of the type described above are known, for example, from US Pat. No. 6,561,764 B1. The arranged between the side surfaces of the blade platforms sealing and damping elements on the one hand to minimize the ventilation losses and reduce the vibrations of the turbine blades. However, these gas turbine rotors are disadvantageous in relation to the sealing and damping elements in that the sealing with a single mechanical seal is not completely successful and thus over the remaining gap between the blade platforms hot gas in the area below the blade platforms and thus in the mounting region of the turbine blades on Peripheral edge of the disc passes. The result is a reduction in the life of the disc. The arrangement of additional mechanical sealing elements between the blade platforms in the areas where the sealing and damping element is not effective, but requires a considerable manufacturing effort and can also lead to tensions.

Der Erfindung liegt die Aufgabe zugrunde, einen Gasturbinenrotor der eingangs beschriebenen Art mit geringem fertigungstechnischen Aufwand so auszubilden, dass Heißgasleckagen über den Spalt zwischen den Schaufelplattformenverhindert oder reduziert werden und damit die Lebensdauer der Rotorscheibe erhöht wird.The invention has for its object to form a gas turbine rotor of the type described above with low manufacturing effort so that hot gas leakage over the gap between the blade platformsverhindert or reduced and thus the life of the rotor disk is increased.

Erfindungsgemäß wird die Aufgabe mit einem gemäß den Merkmalen des Patentanspruchs 1 ausgebildeten Gasturbinenrotor gelöst. Aus den Unteransprüchen ergeben sich weitere Merkmale und vorteilhafte Ausgestaltungen der Erfindung.According to the invention the object is achieved with a trained according to the features of claim 1 gas turbine rotor. From the dependent claims, further features and advantageous embodiments of the invention.

Der Grundgedanke der Erfindung besteht mit anderen Worten darin, dass ein Teil der in die Hohlräume des jeweiligen Schaufelblattes zu dessen Innenraum- und Filmkühlung eingebrachten Kühlluft kontinuierlich in den Spalt zwischen benachbarten Schaufelplattformen geleitet wird und diesen aerodynamisch abdichtet, zumindest aber die Heißgasleckage reduziert oder das den Spalt gegebenenfalls durchdringende Heißgas abkühlt. Dadurch wird eine zu hohe Wärmebelastung der Rotorscheibe verhindert und folglich deren Lebensdauer verlängert.In other words, the basic idea of the invention consists in that a part of the cooling air introduced into the cavities of the respective airfoil for its interior cooling and film cooling is continuously directed into the gap between adjacent airfoil platforms and aerodynamically seals them, or at least reduces the hot gas leakage or the Gap possibly penetrating hot gas cools. As a result, excessive heat load of the rotor disk is prevented and consequently prolongs their life.

Die Zufuhr der Kühlluft bzw. Dichtungsluft in den Spalt erfolgt über mindestens einen Luftkanal, der vom Innenraum des Schaufelblattes ausgeht und an mindestens einer der Seitenflächen der Schaufelplattform mündet. Das heißt, in den Spalt können beidseitig und an unterschiedlichen Stellen auch mehrere Luftkanäle münden. Der Luftstrom kann in axialem Abstand von dem mechanischen Dichtungselement in den Spalt eingeführt werden oder auch in Kombination mit dem mechanischen Dichtungs- und Dämpfungselement wirken und dessen Dichtwirkung verstärken.The supply of cooling air or sealing air into the gap via at least one air duct, which starts from the interior of the airfoil and opens at least one of the side surfaces of the blade platform. This means that several air channels can open into the gap on both sides and at different points. The air flow can be introduced at an axial distance from the mechanical sealing element in the gap or in Combination with the mechanical sealing and damping element and strengthen its sealing effect.

In vorteilhafter Weiterbildung der Erfindung sind in die Seitenflächen der Schaufelplattformen jeweils mindestens eine Verteilungsnut eingeformt, um die Dichtungsluft im Spalt gezielt verteilen zu können.In an advantageous embodiment of the invention, in each case at least one distribution groove are formed in the side surfaces of the blade platforms in order to distribute the sealing air in the gap targeted.

Ein Ausführungsbeispiel der Erfindung wird anhand der Zeichnung näher erläutert. Es zeigen:

Fig. 1
eine Seitenansicht einer aus einem Schaufelblatt und einer Schaufelplattform bestehenden, lin einem Turbinengehäuse angeordneten Turbinenlaufschaufel, deren Schaufelfuß in einer Rotorscheibe gehalten ist;
Fig. 2
einen Schnitt AA der Turbinenlaufschaufel nach Fig. 1; und
Fig. 3
eine detaillierte Darstellung der mit Kühlluft abgedichteten Seitenfläche der Schaufelplattform in dem mechanisch nicht abgedichteten Bereich.
An embodiment of the invention will be explained in more detail with reference to the drawing. Show it:
Fig. 1
a side view of an existing of a blade and a blade platform, lin turbine housing arranged turbine blade, the blade root is held in a rotor disk;
Fig. 2
a section AA of the turbine blade of FIG. 1; and
Fig. 3
a detailed representation of the cooling air sealed side surface of the blade platform in the mechanically unsealed area.

Am Umfang einer Rotorscheibe 1 ist in Quernuten (nicht dargestellt) eine Mehrzahl Turbinenlaufschaufeln - jeweils über deren Schaufelfuß 2 - lösbar angebracht. Über in der Rotorscheibe 1 ausgebildete Kühlluftbohrungen 3, an die sich Bohrungen (nicht dargestellt) im Schaufelfuß 2 anschließen, gelangt vom Verdichter abgezweigte Kühlluft (Pfeil A) in die in dem jeweiligen Schaufelblatt 4 ausgebildeten Hohlräume 5. Auf diese Weise wird das dem Heißgasstrom (Pfeil B) ausgesetzte Schaufelblatt 4 durch eine Innenkühlung und eine Filmkühlung gekühlt. In einem mittleren Bereich der Seitenflächen 6 der Plattformen 7 der Turbinenlaufschaufeln sind Ausnehmungen 8 zur Aufnahme eines Dichtungs- und Dämpfungselements (nicht dargestellt) ausgebildet. Die jeweils zwischen den gegenüberliegenden Seitenflächen 6 benachbarter Schaufelplattformen 7 angeordneten Dichtungs- und Dämpfungselemente sollen einerseits die Vibration der Laufschaufeln und andererseits den Kontakt der Turbinenscheibe mit dem Heißgas begrenzen. Die Anordnung des Dichtungs- und Dämpfungselements ist aufgrund der konstruktiven Ausbildung der Schaufelplattformen 7 und aus fertigungstechnischen Gründen auf einen bestimmten - geraden - Bereich der jeweiligen Seitenfläche beschränkt. Der verbleibende freie Spalt zwischen den Seitenflächen 6 der Schaufelplattformen 7 wird mit einem kontinuierlichen Dichtungsluftstrom (Pfeil C), der aus einem Hohlraum 5 des Schaufelblattes 4 zugeführt wird, gegenüber der Heißgasatmosphäre abgeschirmt. Die Dichtungsluftzufuhr erfolgt über einen Luftkanal 9, der unmittelbar an einer Seitenfläche der Plattformen mündet, und zwar in einem unter Heißgaseinfluss stehenden Spaltbereich, der nicht mechanisch durch ein Dichtungs- und Dämpfungselement abgedichtet ist. In dem vorliegenden Ausführungsbeispiel ist der Luftzutritt axial getrennt von dem mechanischen Dichtungs- und Dämpfungselement vorgesehen. Die Dichtungsluftaustrittsöffnung kann aber auch in Verbindung mit dem Dichtungs- und Dämpfungselement so angeordnet sein, dass dessen Dichtwirkung verstärkt wird.At the periphery of a rotor disk 1 (not shown) in transverse grooves a plurality of turbine blades - in each case via the blade root 2 - releasably attached. About formed in the rotor disk 1 cooling air holes 3, to which holes (not shown) in the blade root 2, passes from the compressor branched cooling air (arrow A) formed in the respective airfoil 4 cavities 5. In this way, the hot gas stream ( Arrow B) exposed blade 4 cooled by an internal cooling and a film cooling. In a central region of the side surfaces 6 of the platforms 7 of the turbine blades are recesses 8 for receiving a sealing and damping element (not shown) is formed. The sealing and damping elements respectively arranged between the opposite side surfaces 6 of adjacent blade platforms 7 are intended on the one hand to limit the vibration of the rotor blades and, on the other hand, to limit the contact of the turbine disk with the hot gas. The arrangement of the sealing and damping element is due to the structural design of the blade platforms 7 and manufacturing reasons limited to a certain - straight - area of the respective side surface. The remaining free gap between the side surfaces 6 of the blade platforms 7 is shielded with respect to the hot gas atmosphere with a continuous sealing air flow (arrow C), which is supplied from a cavity 5 of the airfoil 4. The sealing air is supplied via an air channel 9, which opens directly on a side surface of the platforms, in a gap under the influence of hot gas gap, which is not mechanically sealed by a sealing and damping element. In the present embodiment, the air inlet is provided axially separated from the mechanical sealing and damping element. However, the sealing air outlet opening can also be arranged in conjunction with the sealing and damping element so that its sealing effect is enhanced.

In der hier beschriebenen Ausführungsform ist ein einziger Luftkanal 9 mit rundem Querschnitt vorgesehen. Es können aber auch zwei oder auch mehrere Luftkanäle angeordnet sein, die zudem eine beliebige Querschnittform aufweisen können und auch zu beiden Seitenflächen 6 ein und derselben Schaufelplattform 7 führen können.In the embodiment described here, a single air channel 9 is provided with a round cross-section. But it can also be arranged two or more air ducts, which may also have any cross-sectional shape and can also lead to both side surfaces 6 one and the same blade platform 7.

Die zwischen den Seitenflächen 6 jeweils benachbarter Plattformen 7 eintretende Dichtungsluft verteilt sich in dem Spalt und dichtet diesen gegenüber der Heißluft ab.The sealing air entering between the side surfaces 6 of respectively adjacent platforms 7 is distributed in the gap and seals it against the hot air.

Zumindest wird aber gegebenenfalls in den Spalt eintretende Heißluft durch die kältere Dichtungsluft abgekühlt. Auf diese Weise wird der Zutritt von Heißgas in den Bereich unterhalb der Plattformen verhindert oder zumindest reduziert, so dass die Befestigung der Turbinenlaufschaufel an der Rotorscheibe und der Umfangsrand der Rotorscheibe 1 nicht überhitzt und dadurch deren Lebensdauer nicht verringert wird. Auf zusätzliche mechanische Dichtelemente, deren Fertigung und Halterung im Randbereich der Schaufelplattformen mit einem erheblichen Aufwand verbunden ist, kann verzichtet werden.At least, however, if necessary, hot air entering the gap is cooled by the colder sealing air. In this way, the access of hot gas to the area below the platforms is prevented or at least reduced, so that the attachment of the turbine blade to the rotor disk and the peripheral edge of the rotor disk 1 is not overheated and thereby their life is not reduced. On additional mechanical sealing elements whose production and support in the edge region of the blade platforms associated with a considerable effort, can be dispensed with.

Wie die Zeichnung, insbesondere Fig. 3, zeigt, kann der Luftkanal 9 auch in eine in die Seitenfläche 6 der Plattform 7 eingeformte Verteilungsnut 10 münden, um so die Dichtungsluft gezielt in dem Spalt zwischen den gegenüberliegenden Seitenflächen 6 zu verteilen. Die Verteilungsnuten 10 können eine beliebige Form haben. Es können in einer Seitenfläche auch mehrere Verteilungsnuten ausgebildet sein.As the drawing shows, in particular FIG. 3, the air duct 9 can also open into a distribution groove 10 formed in the side surface 6 of the platform 7 so as to distribute the sealing air in the gap between the opposing side surfaces 6 in a targeted manner. The distribution grooves 10 may have any shape. It can be formed in a side surface and a plurality of distribution grooves.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

11
Rotorscheiberotor disc
22
Schaufelfußblade
33
KühlluftbohrungCooling air hole
44
Schaufelblattairfoil
55
Hohlraum in 4Cavity in 4
66
Seitenfläche v. 7Side surface of v. 7
77
Schaufelplattformblade platform
88th
Ausnehmungrecess
99
Luftkanalair duct
1010
Verteilungsnutdistribution groove
Pfeil AArrow A.
Kühlluft v. VerdichterCooling air v. compressor
Pfeil BArrow B
HeißgasstromHot gas stream
Pfeil CArrow C
DichtungsluftstromSealing air flow

Claims (4)

Gasturbinenrotor, der eine Rotorscheibe (1) mit an deren Umfangsrand in Quernuten gehaltenen Turbinenlaufschaufeln, die aus einem Schaufelblatt (4), einer Schaufelplattform (7) und einem in der jeweiligen Quernut fixierten Schaufelfuß (2) bestehen, umfasst, wobei die Schaufelblätter (4) von Kühlluft durchströmte Hohlräume (5) aufweisen und in den einander gegenüberliegenden Seitenflächen (6) der Schaufelplattformen (7) jeweils eine Ausnehmung (8) zur Aufnahme eines den Spalt zwischen den Schaufelplattformen (7) überbrückenden Dichtungs- und Dämpfungselements ausgebildet ist, gekennzeichnet durch mindestens einen mit dem Hohlraum (5) in dem Schaufelblatt (4) verbundenen Luftkanal (9), der zur zusätzlichen aerodynamischen Abdichtung des Spaltes mit einem Luftvolumen zwischen den Schaufelplattformen (7) an mindestens einer von deren Seitenflächen (6)) mündet.A gas turbine rotor comprising a rotor disk (1) with turbine blades held transversally at its peripheral edge and comprising a blade (4), a blade platform (7) and a blade root (2) fixed in the respective transverse groove, the blades (4 ) by cooling air flowed through cavities (5) and in the opposite side surfaces (6) of the blade platforms (7) each having a recess (8) for receiving a gap between the blade platforms (7) bridging sealing and damping element is formed, characterized by at least one air duct (9) connected to the cavity (5) in the airfoil (4) and opening on at least one of its side surfaces (6) for additional aerodynamic sealing of the air volume gap between the airfoils (7). Gasturbinenrotor nach Anspruch 1, dadurch gekennzeichnet, dass der Luftkanal (9) in eine in die Seitenfläche (6) der Schaufelplattform (7) eingeformte Luftverteilungsnut (10) mündet.Gas turbine rotor according to claim 1, characterized in that the air duct (9) opens into an air distribution groove (10) formed in the side surface (6) of the blade platform (7). Gasturbinenrotor nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass der Luftkanal (9) und/oder die Luftverteilungsnut (10) so angeordnet sind, das die Dichtungsluftzufuhr axial getrennt von dem Dichtungs- und Dämpfungselement erfolgt.Gas turbine rotor according to claim 1 or 2, characterized in that the air duct (9) and / or the Luftverteilungsnut (10) are arranged so that the sealing air supply takes place axially separated from the sealing and damping element. Gasturbinenrotor nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass der Luftkanal (9)und/oder die Luftverteilungsnut (10) so angeordnet sind, dass die Dichtungsluftzufuhr auch im Bereich des Dichtungs- und Dämpfungselements erfolgt.Gas turbine rotor according to claim 1 or 2, characterized in that the air duct (9) and / or the Luftverteilungsnut (10) are arranged so that the sealing air supply also takes place in the region of the sealing and damping element.
EP05106088A 2004-07-28 2005-07-05 Gas turbine rotor Expired - Fee Related EP1621735B1 (en)

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DE102004037331A DE102004037331A1 (en) 2004-07-28 2004-07-28 Gas turbine rotor

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EP1621735A2 true EP1621735A2 (en) 2006-02-01
EP1621735A3 EP1621735A3 (en) 2008-12-17
EP1621735B1 EP1621735B1 (en) 2010-02-24

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EP (1) EP1621735B1 (en)
DE (2) DE102004037331A1 (en)

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Also Published As

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DE502005009070D1 (en) 2010-04-08
EP1621735B1 (en) 2010-02-24
DE102004037331A1 (en) 2006-03-23
US20060024166A1 (en) 2006-02-02
US7874803B2 (en) 2011-01-25
EP1621735A3 (en) 2008-12-17

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