EP1584793B1 - Dispositif pour la fixation axiale d'aubes de turbine - Google Patents

Dispositif pour la fixation axiale d'aubes de turbine 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.)
Expired - Fee Related
Application number
EP05006648A
Other languages
German (de)
English (en)
Other versions
EP1584793A2 (fr
EP1584793A3 (fr
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/fr
Publication of EP1584793A3 publication Critical patent/EP1584793A3/fr
Application granted granted Critical
Publication of EP1584793B1 publication Critical patent/EP1584793B1/fr
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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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)

Claims (3)

  1. Disque de turbine comprenant un dispositif de blocage d'aube de turbine destiné à bloquer axialement une aube de turbine (1), laquelle est insérée dans une rainure profilée (10) d'un disque de turbine (6), ladite rainure s'étendant dans le sens axial,
    sachant que le disque de turbine (6) est muni d'une gorge de blocage (8) s'engageant dans la rainure (10), s'étendant radialement dans le plan du disque de turbine (6) et présentant une forme rectangulaire,
    que dans la gorge de blocage (8) est placé un goujon de blocage (4) doté d'une section transversale cylindrique,
    que la partie inférieure du pied d'aube (3) est munie d'une entaille (9) affleurant la gorge de blocage (8) à l'état monté, et
    que dans le sens radial est disposé un élément élastique (5) sous le goujon de blocage (4) précontraignant celui-ci radialement vers l'extérieur,
    caractérisé en ce que l'élément élastique (5) est fixé au pied d'aube.
  2. Disque de turbine selon la revendication n° 1, caractérisé en ce que les extrémités du goujon de blocage (4) présentent une section transversale rectangulaire pour l'essentiel.
  3. Disque de turbine selon la revendication n° 1 ou n° 2, caractérisé en ce que l'élément élastique (5) est conçu sous forme d'un ressort.
EP05006648A 2004-04-07 2005-03-24 Dispositif pour la fixation axiale d'aubes de turbine Expired - Fee Related EP1584793B1 (fr)

Applications Claiming Priority (2)

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

Publications (3)

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

Family

ID=34895510

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05006648A Expired - Fee Related EP1584793B1 (fr) 2004-04-07 2005-03-24 Dispositif pour la fixation axiale d'aubes de turbine

Country Status (3)

Country Link
US (1) US7442011B2 (fr)
EP (1) EP1584793B1 (fr)
DE (1) DE102004017193A1 (fr)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1860280A1 (fr) * 2006-04-07 2007-11-28 Siemens Aktiengesellschaft Dispositif de verrouillage d'une aube de turbine comprenant un élément de verrouillage
DE102006054154B4 (de) * 2006-11-16 2014-03-13 Man Diesel & Turbo Se Abgasturbolader
GB0914969D0 (en) * 2009-08-28 2009-09-30 Rolls Royce Plc An aerofoil blade assembly
US8523529B2 (en) * 2009-11-11 2013-09-03 General Electric Company Locking spacer assembly for a circumferential entry airfoil attachment system
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 (ja) * 2012-03-30 2014-07-02 株式会社日立製作所 タービン動翼とタービンロータのピン結合部の加工方法及びタービン動翼
US9470092B2 (en) 2013-01-02 2016-10-18 General Electric Company System and method for attaching a rotating blade in a turbine

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2846183A (en) * 1952-07-18 1958-08-05 William C Morgan Retaining devices for turbine blades
US2912223A (en) * 1955-03-17 1959-11-10 Gen Electric Turbine bucket vibration dampener and sealing assembly
CH408056A (de) 1962-11-23 1966-02-28 Goerlitzer Maschinenbau Veb Befestigung der Laufschaufeln von Kreiselmaschinen, insbesondere für trommelartige Verdichterläufer von Gasturbinen
DE1159964B (de) * 1959-12-18 1963-12-27 Goerlitzer Maschb Veb Befestigung der Laufschaufeln von Kreiselmaschinen
CH572155A5 (fr) * 1974-05-27 1976-01-30 Bbc Sulzer Turbomaschinen
FR2507679A1 (fr) * 1981-06-12 1982-12-17 Snecma Dispositif de verrouillage d'une aube de rotor de turbomachine
US4820127A (en) * 1988-01-29 1989-04-11 Westinghouse Electric Corp. Blade support and blade assembly
GB9223593D0 (en) * 1992-11-11 1992-12-23 Rolls Royce Plc Gas turbine engine fan blade assembly
US5720596A (en) * 1997-01-03 1998-02-24 Westinghouse Electric Corporation Apparatus and method for locking blades into a rotor

Also Published As

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

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