EP1584793B1 - Turbine blade retaining system to axially lock a turbine blade - Google Patents

Turbine blade retaining system to axially lock a turbine blade Download PDF

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Publication number
EP1584793B1
EP1584793B1 EP05006648A EP05006648A EP1584793B1 EP 1584793 B1 EP1584793 B1 EP 1584793B1 EP 05006648 A EP05006648 A EP 05006648A EP 05006648 A EP05006648 A EP 05006648A EP 1584793 B1 EP1584793 B1 EP 1584793B1
Authority
EP
European Patent Office
Prior art keywords
turbine
locking
turbine disk
blade
turbine blade
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.)
Not-in-force
Application number
EP05006648A
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German (de)
French (fr)
Other versions
EP1584793A2 (en
EP1584793A3 (en
Inventor
Joana Negulescu
Peter Davison
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
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP1584793A2 publication Critical patent/EP1584793A2/en
Publication of EP1584793A3 publication Critical patent/EP1584793A3/en
Application granted granted Critical
Publication of EP1584793B1 publication Critical patent/EP1584793B1/en
Not-in-force 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/326—Locking of axial insertion type blades by other means
    • 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
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member

Definitions

  • the invention relates to a turbine disk with a turbine blade locking device for axial securing of a turbine blade on the turbine disk.
  • a fuse is required.
  • Such fuses show, for example, the EP 0 610 668 B1 , the US 5,135,354 , the US 5,518,369 , the US 3,986,779 or US 4,527,952 ,
  • Another disadvantage is that the overall construction has a higher weight and that the production and assembly are associated with not inconsiderable costs.
  • Another disadvantage is that the functionality and reliability is not always secured or that relatively expensive control measures are required to verify the correct installation.
  • the invention has for its object to provide a turbine blade locking device of the type mentioned, which has a high level of reliability and safety with a simple structure, simple cost manufacturability and ease of installation.
  • a locking groove is introduced, which passes through the groove for insertion of the blade root and which extends in the radial direction in the plane of the turbine disk.
  • a locking pin is inserted, which thus extends substantially in the circumferential direction of the turbine disk.
  • the locking pin is, due to the groove, displaceable in the radial direction.
  • On the underside of the blade a notch or a groove is made, into which at least a part of the locking pin (with respect to its length or with respect to its diameter) can be inserted.
  • an elastic element for insertion of the locking pin in the notch of the blade root after installation of the turbine blade is an elastic element, which is arranged below the locking pin and biases this radially outward.
  • the centrifugal forces cause a radially outwardly directed bias or movement of the locking bolt, so that it is securely positioned in the notch or groove of the underside of the blade root.
  • a tailor-made positioning of the blade root takes place relative to the turbine disk.
  • the axial positioning takes place in both axial directions. In this way, the present invention differs from the prior art, since there is often blocked an axial direction by stops, lugs or the like, while the other axial direction by the mentioned additional locking elements (sheets, etc.) takes place.
  • the forces are introduced in the axial direction of the blade root by the locking pin on the turbine disk. This ensures a safe power transmission.
  • the locking groove according to the invention preferably has a rectangular shape. Furthermore, it is advantageous if the locking pin is provided with a cylindrical cross section, since this is then inserted into a round cross section of the notch of the blade root. For a secure load transfer To ensure, it is advantageous if the end portions of the locking bolt have a substantially rectangular cross-section or are milled.
  • the elastic element may be designed in the form of a spring, which, after the insertion of the blade root into a corresponding groove of the turbine disk, is pushed under the locking bolt in order to push it upwards.
  • the Fig. 1 shows a turbine blade 1, which is integrally provided with a blade root 3. This is profiled fir-tree, as it is already known from the prior art.
  • a transversely extending notch 9 is formed, which may have a semi-circular cross-section matching a cylindrical cross-section of a locking pin 5.
  • the Fig. 1 further shows an elastic element 5, which is designed in the form of a spring and serves to introduce the locking pin 4 in the notch or groove 9.
  • the Fig. 2 shows the associated region of a turbine disk 6. This has a plurality of profiled, extending in the axial direction of grooves 10, which are each formed by lateral disk fingers 7. In the radial direction and in the plane of the turbine disk 6 each have a locking groove 8 is formed, in which the locking pin 4 is inserted, as in Fig. 2 is shown. On the representation of the elastic element 5 was in Fig. 2 omitted for clarity.
  • the Fig. 3 shows a schematic partial sectional view in the assembled state. It can be seen that the locking pin 4 is received with a majority of its cross section in the notch or groove 9. Furthermore, it is shown that the blade root 3 can usually be provided with at least one cooling channel 2. The design of the cooling channel 2 is not affected by the locking device according to the invention.
  • the locking pins 4 are inserted into the associated locking grooves 8. It is a matter of definition whether two lateral locking grooves 8 are provided in each groove 10 or whether a single locking groove 8 corresponding to the length of the locking bolt 4 is formed.
  • the invention relates to both such Ausmonys- and definition variants. After inserting the locking pin 4, this is at the bottom the locking groove 8, so that the blade root 3 is inserted into the groove 10 of the turbine disk 6. Subsequently, the elastic member 5 is inserted together with the blade (since it is attached to the blade root), so that the locking pin is pressed in the radial direction outwardly into the notch or groove 9 of the blade root 3.
  • a device for disassembly or removal of the turbine blade, a device is used by means of which the locking pins 4 are expressed radially downwards from the notch 9 of the blade root 3, so that it can be pushed out in the axial direction.

Landscapes

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

Description

Die Erfindung betrifft eine Turbinenscheibe mit einer Turbinenschaufelarretiervorrichtung zur axialen Sicherung einer Turbinenschaufel an der Turbinenscheibe.The invention relates to a turbine disk with a turbine blade locking device for axial securing of a turbine blade on the turbine disk.

Aus dem Stand der Technik ist es bekannt, die Schaufelfüße von Turbinenschaufeln zu profilieren, um dabei die radial gerichteten Kräfte während des Betriebs einer Gasturbine zu übernehmen.From the prior art, it is known to profile the blade roots of turbine blades to thereby take over the radially directed forces during operation of a gas turbine.

Um eine axiale Bewegung des Schaufelfußes relativ zu der Turbinenscheibe zu verhindern, ist eine Sicherung erforderlich. Derartige Sicherungen zeigen beispielsweise die EP 0 610 668 B1 , die US 5,135,354 , die US 5,518,369 , die US 3,986,779 oder US 4,527,952 .To prevent axial movement of the blade root relative to the turbine disk, a fuse is required. Such fuses show, for example, the EP 0 610 668 B1 , the US 5,135,354 , the US 5,518,369 , the US 3,986,779 or US 4,527,952 ,

Bei den aus dem Stand der Technik bekannten Konstruktionen werden üblicherweise blechartige Elemente eingelegt, die zusammen mit Anschlägen an den Schaufelfüßen oder den Turbinenscheiben die axiale Fixierung bewirken. Als nachteilig erweist sich dabei der hohe Montageaufwand sowie die Gefahr, dass sich diese Arretierungen lösen oder dass diese nicht passgenau montiert sind, sodass sich zumindest geringfügige axiale Verschiebungen zwischen dem Schaufelfuß und der Turbinenscheibe ergeben können.In the constructions known from the prior art usually sheet-like elements are inserted, which cause the axial fixation together with stops on the blade roots or the turbine disks. The disadvantage here is the high assembly costs and the risk that these locks solve or that they are not mounted accurately, so that at least slight axial displacements between the blade root and the turbine disk may result.

Im Einzelnen werden beim Stand der Technik Deckplatten, Arretierungsringe oder Arretierungsbleche oder eine Kombination von diesen verwendet, die bei der Montage verformt, beispielsweise gebogen werden müssen.In particular, in the prior art cover plates, locking rings or locking plates or a combination of these used, which deformed during assembly, for example, must be bent.

Als weiterer Nachteil ergibt sich, dass die Gesamtkonstruktion ein höheres Gewicht aufweist und dass die Herstellung und die Montage mit nicht unerheblichen Kosten verbunden sind.Another disadvantage is that the overall construction has a higher weight and that the production and assembly are associated with not inconsiderable costs.

Ein weiterer Nachteil besteht darin, dass die Funktionsfähigkeit und Zuverlässigkeit nicht immer gesichert ist bzw. dass relativ aufwendige Kontrollmaßnahmen erforderlich sind, um die korrekte Montage zu überprüfen.Another disadvantage is that the functionality and reliability is not always secured or that relatively expensive control measures are required to verify the correct installation.

Der Erfindung liegt die Aufgabe zugrunde, eine Turbinenschaufelarretiervorrichtung der eingangs genannten Art zu schaffen, welche bei einfachem Aufbau, einfacher kostengünstiger Herstellbarkeit und einfacher Montage ein hohes Maß an Zuverlässigkeit und Sicherheit aufweist.The invention has for its object to provide a turbine blade locking device of the type mentioned, which has a high level of reliability and safety with a simple structure, simple cost manufacturability and ease of installation.

Erfindungsgemäß wird die Aufgabe durch die Merkmalskombination des Hauptanspruchs gelöst, die Unteransprüche zeigen weitere vorteilhafte Ausgestaltungen der Erfindung.According to the invention the object is achieved by the feature combination of the main claim, the subclaims show further advantageous embodiments of the invention.

Erfindungsgemäß ist somit vorgesehen, dass in die Turbinenscheibe eine Arretierungsnut eingebracht ist, welche die Nut zum Einschieben des Schaufelfußes durchgreift und welche sich in radialer Richtung in der Ebene der Turbinenscheibe erstreckt. In die Nut ist ein Arretierungsbolzen eingelegt, welcher sich somit im Wesentlichen in Umfangsrichtung der Turbinenscheibe erstreckt. Der Arretierungsbolzen ist, bedingt durch die Nut, in radialer Richtung verschiebbar. An dem Schaufelfuß ist an seiner Unterseite eine Kerbe oder eine Nut eingebracht, in welche zumindest ein Teil des Arretierungsbolzens (bezüglich seiner Länge bzw. bezüglich seines Durchmessers) einschiebbar ist. Zum Einschieben des Arretierungsbolzens in die Kerbe des Schaufelfußes nach erfolgter Montage der Turbinenschaufel dient ein elastisches Element, welches unterhalb des Arretierungsbolzens angeordnet ist und diesen radial nach außen vorspannt.According to the invention it is thus provided that in the turbine disk a locking groove is introduced, which passes through the groove for insertion of the blade root and which extends in the radial direction in the plane of the turbine disk. In the groove, a locking pin is inserted, which thus extends substantially in the circumferential direction of the turbine disk. The locking pin is, due to the groove, displaceable in the radial direction. On the underside of the blade, a notch or a groove is made, into which at least a part of the locking pin (with respect to its length or with respect to its diameter) can be inserted. For insertion of the locking pin in the notch of the blade root after installation of the turbine blade is an elastic element, which is arranged below the locking pin and biases this radially outward.

Beim Betrieb der Gasturbine bewirken die Zentrifugalkräfte eine radial nach außen gerichtete Vorspannung oder Bewegung des Arretierungsbolzens, sodass dieser sicher in der Kerbe oder Nut der Unterseite des Schaufelfußes positioniert ist. Während des Betriebs erfolgt somit eine passgenaue Positionierung des Schaufelfußes relativ zu der Turbinenscheibe. Dabei erfolgt die axiale Positionierung in beiden Axialrichtungen. Hierdurch unterscheidet sich die vorliegende Erfindung vom Stand der Technik, da dort vielfach eine Axialrichtung durch Anschläge, Nasen oder Ähnliches blockiert wird, während die andere Axialrichtung durch die erwähnten zusätzlichen Arretierungselemente (Bleche etc.) erfolgt.During operation of the gas turbine, the centrifugal forces cause a radially outwardly directed bias or movement of the locking bolt, so that it is securely positioned in the notch or groove of the underside of the blade root. During operation, a tailor-made positioning of the blade root takes place relative to the turbine disk. The axial positioning takes place in both axial directions. In this way, the present invention differs from the prior art, since there is often blocked an axial direction by stops, lugs or the like, while the other axial direction by the mentioned additional locking elements (sheets, etc.) takes place.

Erfindungsgemäß werden die Kräfte in axialer Richtung vom Schaufelfuß durch den Arretierungsbolzen auf die Turbinenscheibe eingeleitet. Hierdurch ist eine sichere Kraftübertragung gewährleistet.According to the invention, the forces are introduced in the axial direction of the blade root by the locking pin on the turbine disk. This ensures a safe power transmission.

Erfindungsgemäß ergibt sich somit der Vorteil, dass die Lebensdauer und die Zuverlässigkeit der Gasturbine ganz erheblich gesteigert werden können. Es erfolgt zudem eine einfache Montage ohne zusätzliche kritische Bauteile. Weiterhin kann die sichere Montage in einfacher Weise überprüft werden. Zusätzliche Abdeckbleche oder Rückhalteelemente werden überflüssig.According to the invention thus results in the advantage that the life and reliability of the gas turbine can be increased quite considerably. There is also a simple installation without additional critical components. Furthermore, the safe installation can be checked in a simple manner. Additional cover plates or retaining elements are unnecessary.

Insgesamt ergibt sich somit eine Reduzierung des Turbinengewichts und damit der Kosten zur Herstellung der Gasturbine.Overall, this results in a reduction of the turbine weight and thus the cost of producing the gas turbine.

Die Arretierungsnut weist erfindungsgemäß bevorzugter Weise eine rechteckige Form auf. Weiterhin ist es günstig, wenn der Arretierungsbolzen mit einem zylindrischen Querschnitt versehen ist, da dieser dann in einen runden Querschnitt der Kerbe des Schaufelfußes einlegbar ist. Um eine sichere Lastübertragung sicherzustellen, ist es vorteilhaft, wenn die Endbereiche des Arretierungsbolzens einen im Wesentlichen rechteckigen Querschnitt aufweisen oder eben gefräst sind.The locking groove according to the invention preferably has a rectangular shape. Furthermore, it is advantageous if the locking pin is provided with a cylindrical cross section, since this is then inserted into a round cross section of the notch of the blade root. For a secure load transfer To ensure, it is advantageous if the end portions of the locking bolt have a substantially rectangular cross-section or are milled.

Das elastische Element kann erfindungsgemäß in Form einer Feder ausgebildet sein, die nach dem Einschieben des Schaufelfußes in einer entsprechenden Nut der Turbinenscheibe unter den Arretierungsbolzen geschoben wird, um diesen nach oben zu drücken.According to the invention, the elastic element may be designed in the form of a spring, which, after the insertion of the blade root into a corresponding groove of the turbine disk, is pushed under the locking bolt in order to push it upwards.

Im Folgenden wird die Erfindung anhand eines Ausführungsbeispiels in Verbindung mit der Zeichnung beschrieben. Dabei zeigt:

Fig. 1
eine vereinfachte, isometrische Ansicht einer erfindungsgemäßen Turbinenschaufel mit Schaufelfuß,
Fig. 2
eine vereinfachte, isometrische Teil-Ansicht einer Turbinenscheibe mit Arretierungsnut und zugeordnetem Arretierungsbolzen, und
Fig. 3
eine schematische Schnittansicht im montierten Zustand.
In the following the invention will be described by means of an embodiment in conjunction with the drawing. Showing:
Fig. 1
a simplified, isometric view of a turbine blade according to the invention with blade root,
Fig. 2
a simplified, isometric partial view of a turbine disk with locking groove and associated locking pin, and
Fig. 3
a schematic sectional view in the mounted state.

Die Fig. 1 zeigt eine Turbinenschaufel 1, welche einstückig mit einem Schaufelfuß 3 versehen ist. Dieser ist tannenbaumartig profiliert, so wie dies aus dem Stand der Technik vorbekannt ist.The Fig. 1 shows a turbine blade 1, which is integrally provided with a blade root 3. This is profiled fir-tree, as it is already known from the prior art.

Am unteren Endbereich des Schaufelfußes 3 ist eine sich quer erstreckende Kerbe 9 ausgebildet, welche passend zu einem zylindrischen Querschnitt eines Arretierungsbolzens 5 einen halbrunden Querschnitt aufweisen kann.At the lower end portion of the blade root 3, a transversely extending notch 9 is formed, which may have a semi-circular cross-section matching a cylindrical cross-section of a locking pin 5.

Die Fig. 1 zeigt weiterhin ein elastisches Element 5, welches in Form einer Feder ausgebildet ist und dazu dient, den Arretierungsbolzen 4 in die Kerbe oder Nut 9 einzubringen.The Fig. 1 further shows an elastic element 5, which is designed in the form of a spring and serves to introduce the locking pin 4 in the notch or groove 9.

Die Fig. 2 zeigt den zugeordneten Bereich einer Turbinenscheibe 6. Diese weist mehrere profilierte, sich in Axialrichtung erstreckende Nuten 10 auf, welche jeweils von seitlichen Scheibenfingern 7 gebildet sind. In radialer Richtung und in der Ebene der Turbinenscheibe 6 ist jeweils eine Arretierungsnut 8 ausgebildet, in welche der Arretierungsbolzen 4 einlegbar ist, so wie dies in Fig. 2 dargestellt ist. Auf die Darstellung des elastischen Elements 5 wurde in Fig. 2 der Übersichtlichkeit halber verzichtet.The Fig. 2 shows the associated region of a turbine disk 6. This has a plurality of profiled, extending in the axial direction of grooves 10, which are each formed by lateral disk fingers 7. In the radial direction and in the plane of the turbine disk 6 each have a locking groove 8 is formed, in which the locking pin 4 is inserted, as in Fig. 2 is shown. On the representation of the elastic element 5 was in Fig. 2 omitted for clarity.

Die Fig. 3 zeigt eine schematische Teil-Schnittansicht im montierten Zustand. Dabei ist ersichtlich, dass der Arretierungsbolzen 4 mit einem Großteil seines Querschnitts in der Kerbe oder Nut 9 aufgenommen ist. Weiterhin ist dargestellt, dass der Schaufelfuß 3 in üblicherweise mit zumindest einem Kühlkanal 2 versehen sein kann. Die Ausgestaltung des Kühlkanals 2 wird durch die erfindungsgemäße Arretiervorrichtung nicht beeinträchtigt.The Fig. 3 shows a schematic partial sectional view in the assembled state. It can be seen that the locking pin 4 is received with a majority of its cross section in the notch or groove 9. Furthermore, it is shown that the blade root 3 can usually be provided with at least one cooling channel 2. The design of the cooling channel 2 is not affected by the locking device according to the invention.

Weiterhin zeigt die Fig. 3 das zur radialen Vorspannung des Arretierungsbolzens 4 dienende elastische Element 5.Furthermore, the shows Fig. 3 the radial prestressing of the locking pin 4 serving elastic element. 5

Zur Montage werden die Arretierungsbolzen 4 in die zugeordneten Arretierungsnuten 8 eingeschoben. Es ist dabei eine Frage der Definition, ob bei jeder Nut 10 jeweils zwei seitliche Arretierungsnuten 8 vorgesehen sind oder ob eine einzige, der Länge des Arretierungsbolzens 4 entsprechende Arretierungsnut 8 ausgebildet ist. Die Erfindung bezieht sich auf beide derartige Ausgestaltungs- und Definitionsvarianten. Nach dem Einlegen des Arretierungsbolzens 4 befindet sich dieser am Grund der Arretierungsnut 8, sodass der Schaufelfuß 3 in die Nut 10 der Turbinenscheibe 6 einschiebbar ist. Nachfolgend wird das elastische Element 5 zusammen mit der Schaufel (da es am Schaufelfuß befestigt ist) eingeschoben, sodass der Arretierungsbolzen in radialer Richtung nach außen in die Kerbe oder Nut 9 des Schaufelfußes 3 eingedrückt wird.For assembly, the locking pins 4 are inserted into the associated locking grooves 8. It is a matter of definition whether two lateral locking grooves 8 are provided in each groove 10 or whether a single locking groove 8 corresponding to the length of the locking bolt 4 is formed. The invention relates to both such Ausgestaltungs- and definition variants. After inserting the locking pin 4, this is at the bottom the locking groove 8, so that the blade root 3 is inserted into the groove 10 of the turbine disk 6. Subsequently, the elastic member 5 is inserted together with the blade (since it is attached to the blade root), so that the locking pin is pressed in the radial direction outwardly into the notch or groove 9 of the blade root 3.

Zur Demontage bzw. zum Ausbau der Turbinenschaufel wird eine Vorrichtung eingesetzt, mittels derer die Arretierungsbolzen 4 radial nach unten aus der Kerbe 9 des Schaufelfußes 3 ausgedrückt werden, sodass dieser in axialer Richtung herausschiebbar ist.For disassembly or removal of the turbine blade, a device is used by means of which the locking pins 4 are expressed radially downwards from the notch 9 of the blade root 3, so that it can be pushed out in the axial direction.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

11
Turbinenschaufelturbine blade
22
Kühlkanalcooling channel
33
Schaufelfußblade
44
Arretierungsbolzenlocking bolt
55
Elastisches ElementElastic element
66
Turbinenscheibeturbine disk
77
Scheibenfingerdisc finger
88th
Arretierungsnutlocking groove
99
Kerbescore
1010
Axiale Nut am ScheibenkranzAxial groove on the disc rim

Claims (3)

  1. Turbine disk with a turbine-blade locking device for axial retention of a turbine blade (1), inserted in an axial, profiled slot (10) of a turbine disk (6),
    with the turbine disk (6) being provided with a rectangularly shaped locking groove (8) passing through the slot (10) and extending radially in the plane of the turbine disk (6),
    with a locking pin (4) being inserted in the locking groove (8), which pin is provided with a cylindrical cross-section,
    with the blade root (3) being provided at its bottom side with a notch (9) aligning with the locking groove (8) in the assembled state, and
    with an elastic element (5) being arranged radially below the locking pin (4) which pre-loads the latter in the radially outward direction,
    characterized in that the elastic element (5) is attached to the blade root.
  2. Turbine disk in accordance with Claim 1, characterized in that the end areas of the locking pin (4) are given a substantially rectangular cross-section.
  3. Turbine disk in accordance with Claim 1 or 2, characterized in that the elastic element (5) is provided in the form of a spring.
EP05006648A 2004-04-07 2005-03-24 Turbine blade retaining system to axially lock a turbine blade Not-in-force EP1584793B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102004017193A DE102004017193A1 (en) 2004-04-07 2004-04-07 Turbinenschaufelarretiervorrichtung
DE102004017193 2004-04-07

Publications (3)

Publication Number Publication Date
EP1584793A2 EP1584793A2 (en) 2005-10-12
EP1584793A3 EP1584793A3 (en) 2011-02-02
EP1584793B1 true EP1584793B1 (en) 2012-07-25

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EP05006648A Not-in-force EP1584793B1 (en) 2004-04-07 2005-03-24 Turbine blade retaining system to axially lock a turbine blade

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US (1) US7442011B2 (en)
EP (1) EP1584793B1 (en)
DE (1) DE102004017193A1 (en)

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US8784052B2 (en) * 2010-05-10 2014-07-22 Hamilton Sundstrand Corporation Ceramic gas turbine shroud
US8764402B2 (en) * 2011-06-09 2014-07-01 General Electric Company Turbomachine blade locking system
US20130017092A1 (en) * 2011-07-11 2013-01-17 General Electric Company Rotor assembly for gas turbines
US9051845B2 (en) 2012-01-05 2015-06-09 General Electric Company System for axial retention of rotating segments of a turbine
JP5538468B2 (en) * 2012-03-30 2014-07-02 株式会社日立製作所 Method of machining pin joint of turbine rotor blade and turbine rotor, and turbine rotor blade
US9470092B2 (en) 2013-01-02 2016-10-18 General Electric Company System and method for attaching a rotating blade in a turbine
CN114458391A (en) * 2022-02-22 2022-05-10 中国联合重型燃气轮机技术有限公司 Turbine blade locking assembly

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Publication number Publication date
DE102004017193A1 (en) 2005-10-27
US20050226729A1 (en) 2005-10-13
US7442011B2 (en) 2008-10-28
EP1584793A2 (en) 2005-10-12
EP1584793A3 (en) 2011-02-02

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