EP1457642B1 - Dispositif de fixation d'aubes sur un rotor - Google Patents

Dispositif de fixation d'aubes sur un rotor Download PDF

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Publication number
EP1457642B1
EP1457642B1 EP04100742A EP04100742A EP1457642B1 EP 1457642 B1 EP1457642 B1 EP 1457642B1 EP 04100742 A EP04100742 A EP 04100742A EP 04100742 A EP04100742 A EP 04100742A EP 1457642 B1 EP1457642 B1 EP 1457642B1
Authority
EP
European Patent Office
Prior art keywords
rotor
wedge
end piece
halves
installed state
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 - Lifetime
Application number
EP04100742A
Other languages
German (de)
English (en)
Other versions
EP1457642A2 (fr
EP1457642A3 (fr
Inventor
René Bachofner
Petra Fabijan
Wolfgang Kappis
Michael Müller
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP1457642A2 publication Critical patent/EP1457642A2/fr
Publication of EP1457642A3 publication Critical patent/EP1457642A3/fr
Application granted granted Critical
Publication of EP1457642B1 publication Critical patent/EP1457642B1/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
    • F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor
    • 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
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
    • 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

Definitions

  • the invention relates to the field of power plant technology. It relates to a rotor end for rotors of thermal turbomachinery according to the preamble of claim 1.
  • Thermal turbomachines such as turbines and compressors, consist essentially of a rotor-equipped rotor and a stator in which vanes are suspended.
  • the fixed guide vanes have the task of directing the flow of the gas to be compressed or to be relaxed to the rotating blade blading so that the energy conversion takes place with the best possible efficiency.
  • Both blades and vanes essentially comprise an airfoil and a blade root.
  • grooved in the stator and on the rotor shaft In these grooves, the feet of the blades are inserted and locked there.
  • a disadvantage of this prior art is that the wedge is due to the tilting moment of the two end halves, which is caused by the centrifugal force during operation, able to Anlagenbiegen the caulked lobes.
  • the wedge can thus fly out of the compressor and it can lead to a complete compressor damage.
  • the aim of the invention is to avoid the mentioned disadvantages of the prior art.
  • the invention is based on the object to develop a rotor-closing, which exerts no axial forces on the rotor, so that thereby an occurrence of axial forces caused by disturbing rotor vibrations is avoided.
  • this object is achieved in a rotor-end for rotors of thermal turbomachinery according to the preamble of claim 1, characterized in that the rotor-end is fixed in the axial direction of the two adjacent blades. Each of the two end halves of the rotor-end is fixed in the axial direction of the rotor, each with a connecting element on the two adjacent blades.
  • the connecting element may be formed straight or positive. If the end halves and adjacent blades form a positive assembly, this has the additional advantage that the adjacent blades do not pass through them from the tail end acting forces are screwed into the rotor, so that they do not jam in their thermal expansion.
  • the wedge has at its upper end two tabs which are separated from one another by a longitudinal slot and which are spread open when installed and in that the side surfaces of the end halves each have a recess in the upper region which, when installed, forms an approximately heart-shaped cavity, wherein the walls of this cavity are covered by the spread tabs of the wedge and the wedge is thereby firmly anchored in the end halves.
  • Spreading the wedge into the heart shape of the two end halves prevents the wedge from detaching from its anchorage during operation.
  • Fig. 1 shows a section through one of the Applicant known Rotor-End 1 after installation in a rotor. 2
  • the in Fig. 1 illustrated rotor end 1 consists of two end halves 4, 4 'with opposing side surfaces 5, 5' and a wedge 6, which at its upper, in the installed state of the rotor longitudinal axis end facing away from each other by a longitudinal slot 2 lobes 10, 10 ' having.
  • the side surfaces 5, 5 'of the end halves 4, 4' each have a recess in the upper region, which form a heart-shaped cavity 11 when installed, the walls of this cavity 11 of the spread tabs 10, 10 'of the caulked wedge. 6 are covered and the wedge 6 in this way form-fitting firmly anchored in the heart-shaped cavity 11.
  • the rotor end 1 or the end halves 4, 4 ' are supported on the rotor in the axial direction.
  • FIG. 2 is a plan view of a schematically illustrated inventive rotor-end 1 after installation with straight connecting elements 8, 8 ', 9, 9' shown. Not shown is the caulked wedge, which finally fills the remaining opening of the circumferential groove 3.
  • Each of the two end halves 4, 4 ' is in the axial direction of the rotor 2, each with a connecting element 8, 8', 9, 9 'on the two adjacent blades 7, 7' (also called final blades), namely at the blade roots , attached.
  • These four connecting elements 8, 8 ', 9, 9' now take the axial forces F instead of the rotor 2, which are caused by the centrifugal force and the caulked wedge. In this way, no axial forces on the rotor and disturbing rotor vibrations are avoided.
  • This form-fitting connection of the closing pieces and the adjacent blades is referred to as the closing package.
  • FIG. 4 another embodiment is shown.
  • the figure shows a final package, consisting of the two end halves 4, 4 ', the between the end halves located caulked wedge 6 and the two tail blades 7, 7 '.
  • the solution according to the invention is suitable for all blade rows in the circumferential groove. It is advantageously used whenever the rotor reacts sensitively to axial forces and thus disturbing vibrations can occur.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Treatment Of Fiber Materials (AREA)
  • Shearing Machines (AREA)
  • Preliminary Treatment Of Fibers (AREA)

Claims (4)

  1. Fermeture de rotor (1) pour des rotors (2) de turbomachines thermiques avec rainure périphérique (3), comprenant deux moitiés de fermeture (4, 4') avec des faces latérales (5, 5') se faisant face dans l'état monté et une clavette (6) intercalée, qui est ancrée dans l'état monté par complémentarité de formes dans les faces latérales (5, 5') des moitiés de fermeture (4, 4'), la fermeture de rotor (1) étant disposée dans la direction axiale du rotor (2) entre deux ailettes mobiles (7, 7'), caractérisée en ce que chacune des moitiés de fermeture (4, 4') est fixée dans la direction axiale du rotor avec à chaque fois un élément de liaison (8, 8', 9, 9') sur les deux ailettes mobiles (7, 7') voisines.
  2. Fermeture de rotor (1) selon la revendication 1, caractérisée en ce que l'élément de liaison (8, 8', 9, 9') est droit.
  3. Fermeture de rotor (1) selon la revendication 1, caractérisée en ce que l'élément de liaison (8, 8', 9, 9') est complémentaire au niveau de la forme.
  4. Fermeture de rotor (1) selon l'une quelconque des revendications 1 à 3, caractérisée en ce que la clavette (6) présente sur son extrémité supérieure, opposée à l'axe longitudinal du rotor dans l'état monté, deux pattes (10, 10') séparées l'une de l'autre par une fente longitudinale, qui sont écartées dans l'état monté, et en ce que les faces latérales (5, 5') des moitiés de fermeture (4, 4') présentent chacune dans la zone supérieure un évidement qui forme dans l'état monté une cavité (11) approximativement en forme de coeur, les parois de cette cavité (11) étant couvertes par les pattes (10, 10') écartées de la clavette (6) et la clavette (6) étant ainsi ancrée fixement dans les moitiés de fermeture (4, 4').
EP04100742A 2003-03-11 2004-02-25 Dispositif de fixation d'aubes sur un rotor Expired - Lifetime EP1457642B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10310432 2003-03-11
DE10310432A DE10310432A1 (de) 2003-03-11 2003-03-11 Rotor-Schluss

Publications (3)

Publication Number Publication Date
EP1457642A2 EP1457642A2 (fr) 2004-09-15
EP1457642A3 EP1457642A3 (fr) 2006-07-26
EP1457642B1 true EP1457642B1 (fr) 2009-04-01

Family

ID=32748182

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04100742A Expired - Lifetime EP1457642B1 (fr) 2003-03-11 2004-02-25 Dispositif de fixation d'aubes sur un rotor

Country Status (5)

Country Link
US (1) US7192256B2 (fr)
EP (1) EP1457642B1 (fr)
CN (1) CN1534167B (fr)
AT (1) ATE427412T1 (fr)
DE (2) DE10310432A1 (fr)

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1698759B1 (fr) 2005-02-23 2015-06-03 Alstom Technology Ltd Fermeture de rotor
EP1698758B1 (fr) * 2005-02-23 2015-11-11 Alstom Technology Ltd Fermeture de rotor à fente axiale
US7435055B2 (en) * 2005-03-29 2008-10-14 Siemens Power Generation, Inc. Locking spacer assembly for a turbine engine
EP1803900A1 (fr) * 2006-01-02 2007-07-04 Siemens Aktiengesellschaft Ensemble de fermeture pour clore l'interstice restant entre la première et la dernière des aubes d'un anneau aubagé disposées dans la rainure circonférencielle d'une turbomachine, et turbomachine correspondante
EP1803899A1 (fr) 2006-01-02 2007-07-04 Siemens Aktiengesellschaft Ensemble de verrouillage d'aube pour une turbomachine
FR2921099B1 (fr) * 2007-09-13 2013-12-06 Snecma Dispositif d'amortissement pour aube en materiau composite
US8545184B2 (en) * 2010-01-05 2013-10-01 General Electric Company Locking spacer assembly
US20110255978A1 (en) * 2010-04-16 2011-10-20 Brian Denver Potter Locking Assembly For Circumferential Attachments
CH703997A1 (de) * 2010-10-27 2012-04-30 Alstom Technology Ltd Schaufelanordnung, insbesondere Leitschaufelanordnung.
US9175572B2 (en) * 2012-04-16 2015-11-03 General Electric Company Turbomachine blade mounting system
US9341071B2 (en) * 2013-10-16 2016-05-17 General Electric Company Locking spacer assembly
EP2868868A1 (fr) * 2013-11-05 2015-05-06 Siemens Aktiengesellschaft Dispositif de montage et procédé de montage d'une aube statorique
CN111954751B (zh) * 2018-04-18 2022-06-21 西门子能源全球两合公司 锁定间隔器组件、相对应的叶片组件、用于安装锁定间隔器的方法
CN113586519B (zh) * 2021-08-24 2023-09-26 中国联合重型燃气轮机技术有限公司 锁紧装置及包括该锁紧装置的压气机、燃气轮机

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE271243C (fr)
US1371327A (en) * 1920-07-21 1921-03-15 Schneider & Cie Turbine
NL56668C (fr) * 1940-06-12
US2406703A (en) * 1944-06-08 1946-08-27 Allis Chalmers Mfg Co Turbine blade locking apparatus
FR974989A (fr) * 1948-09-17 1951-02-28 Verrou pour l'aubage des rotors en forme de tambour de compresseurs axiaux et de turbines à vapeur ou à gaz
CH273791A (de) * 1949-05-25 1951-02-28 Tech Studien Ag Schaufelschloss an füllstücklosen Laufschaufelungen von Axialströmungsmaschinen.
DD271243A3 (de) * 1987-10-01 1989-08-30 Goerlitzer Maschinenbau Veb Schaufelschlossanordnung mit minimierter schaufelschlossluecke
DE10134611A1 (de) * 2000-12-16 2002-06-27 Alstom Switzerland Ltd Fixiervorrichtung für eine Beschaufelung einer Strömungsmaschine

Also Published As

Publication number Publication date
DE502004009253D1 (de) 2009-05-14
US7192256B2 (en) 2007-03-20
US20040179945A1 (en) 2004-09-16
CN1534167B (zh) 2010-05-26
DE10310432A1 (de) 2004-09-23
CN1534167A (zh) 2004-10-06
EP1457642A2 (fr) 2004-09-15
EP1457642A3 (fr) 2006-07-26
ATE427412T1 (de) 2009-04-15

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