EP1584793A2 - Dispositif pour la fixation d'aubes de turbine - Google Patents

Dispositif pour la fixation d'aubes de turbine Download PDF

Info

Publication number
EP1584793A2
EP1584793A2 EP05006648A EP05006648A EP1584793A2 EP 1584793 A2 EP1584793 A2 EP 1584793A2 EP 05006648 A EP05006648 A EP 05006648A EP 05006648 A EP05006648 A EP 05006648A EP 1584793 A2 EP1584793 A2 EP 1584793A2
Authority
EP
European Patent Office
Prior art keywords
locking
groove
locking pin
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.)
Granted
Application number
EP05006648A
Other languages
German (de)
English (en)
Other versions
EP1584793A3 (fr
EP1584793B1 (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
Anticipated expiration legal-status Critical
Expired - Lifetime 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 blade locking device for axial securing of a turbine blade on the turbine disk.
  • cover plates, locking rings or locking plates or a combination used by these which deformed during assembly, for example must be bent.
  • Another disadvantage is that the overall construction has a higher weight and that the production and the Assembly associated with not inconsiderable costs.
  • Another disadvantage is that the functionality and reliability is not always guaranteed or that relatively complex control measures are required to the check correct installation.
  • the invention is based on the object, a turbine blade locking device of the type mentioned above, which with a simple structure, simple cost-effective manufacturability and easy assembly a high level of reliability and safety.
  • a locking groove is introduced, which the groove for inserting the blade root passes through and which itself extends in the radial direction in the plane of the turbine disk.
  • a locking pin is inserted, which thus substantially in the circumferential direction of the turbine disk extends.
  • the locking pin is conditional through the groove, displaceable in the radial direction.
  • To the Shovel foot is at its bottom a notch or groove introduced, in which at least a part of the locking pin (in terms of its length or in terms of its diameter) is insertable.
  • an elastic element which below the locking pin is arranged and this radially pretensions to the outside.
  • the centrifugal forces cause a radially outward bias or movement of the Locking bolt, so that safely in the notch or Groove the bottom of the blade root is positioned. While the operation is thus a tailor - made positioning of the Blade foot relative to the turbine disk. This takes place the axial positioning in both axial directions. hereby The present invention differs from the prior art Technology, since there often an axial direction by stops, Noses or the like is blocked while the other axial direction by the mentioned additional locking elements (Sheets etc.) takes place.
  • the locking groove according to the invention has a preferred manner a rectangular shape. Furthermore, it is advantageous if the Locking bolt provided with a cylindrical cross section is, since this then in a round cross-section of the notch of the blade root is inserted. For a secure load transfer To ensure it is beneficial when the end areas the locking bolt is a substantially rectangular Have cross-section or just milled.
  • the elastic element according to the invention in the form of a spring be formed after the insertion of the blade root in a corresponding groove of the turbine disk under the Locking pin is pushed to this up to press.
  • Fig. 1 shows a turbine blade 1, which in one piece is provided with a blade root 3. This is fir-tree-like profiled, as previously known from the prior art is.
  • a transversely extending notch 9 which fits to a cylindrical Cross section of a locking pin 5 a may have a semicircular cross-section.
  • Fig. 1 further shows an elastic element 5, which is formed in the form of a spring and serves to the locking pin 4 in the notch or groove 9 bring.
  • FIG. 2 shows the associated area of a turbine disk 6. This has several profiled, in the axial direction extending grooves 10, which each of lateral Disc fingers 7 are formed. In the radial direction and in the plane of the turbine disk 6 is in each case a locking groove 8, in which the locking pin 4 can be inserted is as shown in Fig. 2. On the presentation of the elastic element 5 was in Fig. 2 for clarity half omitted.
  • Fig. 3 shows a schematic partial sectional view in the mounted Status. It can be seen that the locking pin 4 with much of its cross section in the notch or groove 9 is received. Furthermore, it is shown that the blade root 3 in usually with at least one cooling channel 2 can be provided. The embodiment of the cooling channel 2 is not affected by the locking device according to the invention.
  • Fig. 3 shows the radial bias of the Locking bolt 4 serving elastic element 5.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP05006648A 2004-04-07 2005-03-24 Dispositif pour la fixation axiale d'aubes de turbine Expired - Lifetime 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 true EP1584793A2 (fr) 2005-10-12
EP1584793A3 EP1584793A3 (fr) 2011-02-02
EP1584793B1 EP1584793B1 (fr) 2012-07-25

Family

ID=34895510

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05006648A Expired - Lifetime 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)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102817640A (zh) * 2011-06-09 2012-12-12 通用电气公司 涡轮机叶片锁定系统
CN119508268A (zh) * 2024-11-14 2025-02-25 中国联合重型燃气轮机技术有限公司 一种压气机叶根安装结构、压气机以及安装方法

Families Citing this family (11)

* 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
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
IT202100029963A1 (it) 2021-11-26 2023-05-26 Ge Avio Srl Motore a turbina a gas comprendente un complesso di pale rotanti.
CN114458391A (zh) * 2022-02-22 2022-05-10 中国联合重型燃气轮机技术有限公司 一种透平叶片锁紧组件

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
DE1159964B (de) * 1959-12-18 1963-12-27 Goerlitzer Maschb Veb Befestigung der Laufschaufeln von Kreiselmaschinen
CH408056A (de) 1962-11-23 1966-02-28 Goerlitzer Maschinenbau Veb Befestigung der Laufschaufeln von Kreiselmaschinen, insbesondere für trommelartige Verdichterläufer von Gasturbinen
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

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102817640A (zh) * 2011-06-09 2012-12-12 通用电气公司 涡轮机叶片锁定系统
EP2532835A3 (fr) * 2011-06-09 2013-08-07 General Electric Company Système de verrouillage d'aube de turbomachine
US8764402B2 (en) 2011-06-09 2014-07-01 General Electric Company Turbomachine blade locking system
CN102817640B (zh) * 2011-06-09 2016-02-24 通用电气公司 涡轮机叶片锁定系统
CN119508268A (zh) * 2024-11-14 2025-02-25 中国联合重型燃气轮机技术有限公司 一种压气机叶根安装结构、压气机以及安装方法

Also Published As

Publication number Publication date
US7442011B2 (en) 2008-10-28
DE102004017193A1 (de) 2005-10-27
EP1584793A3 (fr) 2011-02-02
EP1584793B1 (fr) 2012-07-25
US20050226729A1 (en) 2005-10-13

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