EP1723312B1 - Fermeture de rotor - Google Patents

Fermeture de rotor Download PDF

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Publication number
EP1723312B1
EP1723312B1 EP05716827A EP05716827A EP1723312B1 EP 1723312 B1 EP1723312 B1 EP 1723312B1 EP 05716827 A EP05716827 A EP 05716827A EP 05716827 A EP05716827 A EP 05716827A EP 1723312 B1 EP1723312 B1 EP 1723312B1
Authority
EP
European Patent Office
Prior art keywords
end piece
rotor
halves
circumferential slot
another
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
EP05716827A
Other languages
German (de)
English (en)
Other versions
EP1723312A1 (fr
Inventor
René Bachofner
Wolfgang Kappis
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 EP1723312A1 publication Critical patent/EP1723312A1/fr
Application granted granted Critical
Publication of EP1723312B1 publication Critical patent/EP1723312B1/fr
Not-in-force 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
    • F01D5/3023—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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding

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 patent claim 1 and a method for assembling the rotor end.
  • Thermal turbomachines such as turbines and compressors, consist essentially of a rotor-equipped rotor and a stator in which vane n are suspended.
  • the fixed guide vanes have the task of directing the flow of the compressed or the gaseous medium to be relaxed on the rotating rotor 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 Applicant is also known rotor end for rotors of thermal turbomachinery with circumferential groove, which is known from two end halves with in the installed state opposite side surfaces and adjacent top surfaces, in which the side surfaces of the end halves form fit, by means of a known dovetail Imposition, are interconnected.
  • the two Final halves are locally welded together in the area in which the side surfaces and the top surfaces of the two end halves adjoin one another. This is to achieve a solid anchoring of the rotor end in the installed state. At high loads, this anchoring is often not enough.
  • 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-end, which can be easily manufactured and assembled and in which a detachment during operation is prevented, so that the occurrence of compressor damage is avoided.
  • this object is achieved with a rotor end for rotors of thermal turbomachinery in that the rotor end consists of two end halves and a complete tail adapter, the tail halves are connected by dovetail attachment of the adjacent two side surfaces form-fitting together and the two imposed end halves are firmly connected to the entire final intermediate piece over a weld in the area of the top surfaces.
  • the rotor-end is anchored in the installed state both positive and cohesive and thus extremely firmly anchored.
  • the items of the inventive rotor-end are easy to prepare and the assembly is not complicated compared to the known prior art. Releasing during operation is prevented with certainty, so that the occurrence of compressor damage is avoided
  • Fig. 1 and Fig. 2 show the side views of the "items" of a eferrenungsdorfe rotor-end for a compressor rotor before installation, and indeed shows Fig. 1 the two end halves 1, 1 'and Fig. 2 the whole final intermediate 2.
  • opposite side surfaces 3, 3 'of the end halves 1, 1' are designed such that they allow a known dovetail suspension of the end halves 1, 1 '.
  • the first end half 1 has a recess 4 in the side surface 3, while the side surface 3 "of the second end half 1 'has a projection 5 which fits precisely into this recess 4 (FIG. Fig. 1 ).
  • An assembly (hanging) of the two parts 1 and 1 'therefore leads to a positive connection ( Fig. 3d ).
  • a weld seam preparation 8 is provided in the region of the cover surfaces 6, 6' of the two end halves 1, 1 'and the top surface 7 of the closing intermediate piece 2 , in which then a weld 9 is welded.
  • a first step the entire final intermediate piece 2 is first installed in the circumferential groove 10. Then, the first end half 1 is inserted from above into the circumferential groove 10 ( Fig. 3a ) and in a third step laterally displaced in the circumferential groove 10 until it is anchored in the rotor 11 ( Fig. 3b ). Thereafter, in a fourth step, the second end half 1 'is mounted next to the already installed first end half 1 ( Fig. 3c ) and pushed in a fifth step so far in the opposite side of the circumferential groove 10 until the two end halves 1, 1 'are positively connected. The two parts 1, 1 'are thus imposed on the dovetail Fig. 3d ). Finally, in a sixth step, the two form-fitting connected end halves 1, 1 'and the entire closing intermediate piece 2 are secured in the region of the cover surfaces 6, 6, 7 by means of a welded seam 9.
  • the rotor-end is firmly anchored in the installed state positively and cohesively. This anchoring of the rotor end prevents disengagement during operation and thereby causing damage to the turbomachine.
  • the items of the inventive rotor-end are easy to produce, you need no additional wedge more, and the assembly is not complicated compared to the prior art.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Permanent Magnet Type Synchronous Machine (AREA)

Claims (2)

  1. Fermeture de rotor pour rotors (11) de turbomachines thermiques comprenant une rainure périphérique (10), constituée de deux moitiés de fermeture (1, 1') avec des surfaces latérales (3, 3') opposées dans l'état installé et des surfaces de couverture adjacentes (6, 6'), les surfaces latérales (3, 3') des moitiés de fermeture (1, 1') étant connectées les unes aux autres par engagement par coopération de forme au moyen d'un assemblage en queue d'aronde, caractérisée en ce que la fermeture de rotor se compose en outre d'une pièce intermédiaire de fermeture entière (2) avec une surface de couverture (7) et en ce que les deux moitiés de fermeture assemblées (1, 1') sont connectées fixement à la pièce intermédiaire de fermeture entière (2) par le biais d'un joint de soudure (9) dans la région des surfaces de couverture (6, 6', 7).
  2. Procédé de montage d'une fermeture de rotor selon la revendication 1 dans une ouverture résiduelle (13) d'une rainure périphérique (10) d'un rotor (11) d'une turbomachine thermique, caractérisé en ce que
    a) dans une première étape, la pièce intermédiaire de fermeture entière (2) est montée dans l'ouverture résiduelle (13),
    b) dans une deuxième étape, la première moitié de fermeture (1) est introduite par le haut dans la rainure périphérique (10) du rotor (11),
    c) dans une troisième étape, cette première moitié de fermeture (1) est poussée latéralement dans la rainure périphérique (10), jusqu'à ce qu'elle soit ancrée dans le rotor (11),
    d) dans une quatrième étape, la deuxième moitié de fermeture (1') est introduite par le haut dans la rainure périphérique (10) du rotor (11) à côté de la première moitié de fermeture (1) déjà installée,
    e) dans une cinquième étape, la deuxième moitié de fermeture (1') est poussée dans la direction opposée de la rainure périphérique (10) jusqu'à ce que la première moitié de fermeture (1) et la deuxième moitié de fermeture (1') soient assemblées l'une à l'autre par engagement par coopération de forme par le biais de l'assemblage en queue d'aronde, et
    f) dans une sixième étape, finalement, les deux moitiés de fermeture (1, 1') assemblées par engagement par coopération de forme sont soudées à la pièce intermédiaire de fermeture entière (2) dans la région des surfaces de couverture (6, 6', 7).
EP05716827A 2004-03-08 2005-02-28 Fermeture de rotor Not-in-force EP1723312B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102004011508A DE102004011508A1 (de) 2004-03-08 2004-03-08 Rotor-Schluss
PCT/EP2005/050839 WO2005085599A1 (fr) 2004-03-08 2005-02-28 Fermeture de rotor

Publications (2)

Publication Number Publication Date
EP1723312A1 EP1723312A1 (fr) 2006-11-22
EP1723312B1 true EP1723312B1 (fr) 2008-12-10

Family

ID=34895086

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05716827A Not-in-force EP1723312B1 (fr) 2004-03-08 2005-02-28 Fermeture de rotor

Country Status (8)

Country Link
US (1) US7309214B2 (fr)
EP (1) EP1723312B1 (fr)
AT (1) ATE417187T1 (fr)
CA (1) CA2558838C (fr)
DE (2) DE102004011508A1 (fr)
ES (1) ES2318466T3 (fr)
TW (1) TWI341899B (fr)
WO (1) WO2005085599A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8176598B2 (en) * 2009-08-03 2012-05-15 General Electric Company Locking spacer assembly for a circumferential dovetail rotor blade attachment system
US20110255978A1 (en) * 2010-04-16 2011-10-20 Brian Denver Potter Locking Assembly For Circumferential Attachments
US20160186592A1 (en) * 2014-12-31 2016-06-30 General Electric Company Flowpath boundary and rotor assemblies in gas turbines

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
NL81240C (fr) * 1951-08-31 1955-11-15
DE1019318B (de) * 1954-04-28 1957-11-14 Siemens Ag Deckbandbefestigung an Turbinenschaufeln mittels Bajonettverschlusses
CH349624A (de) * 1957-03-05 1960-10-31 Oerlikon Maschf Axiale Strömungsmaschine
DE2002469C3 (de) * 1970-01-21 1978-03-30 Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen Laufschaufelbefestigung in einer schwalbenschwanzförmigen Umfangsnut eines Läufers axial durchströmter Strömungsmaschinen, insbesondere Gasturbinenstrahltriebwerke
DE2151369A1 (de) * 1971-10-15 1973-04-19 Bosch Gmbh Robert Zu einer blockeinheit verschweisste zellengefaesse fuer akkumulatoren
EP1028231B1 (fr) * 1999-02-12 2003-09-03 ALSTOM (Switzerland) Ltd Fixation d'aubes de rotor d'une turbomachine
WO2001067228A1 (fr) * 2000-03-09 2001-09-13 Koninklijke Philips Electronics N.V. Procede permettant d'interagir avec un systeme electronique grand public
DE10346239A1 (de) * 2003-10-06 2005-04-21 Alstom Technology Ltd Baden Verfahren zur Fixierung für die Beschaufelung einer Strömungsmaschine und Fixiervorrichtung
US6929453B2 (en) * 2003-12-11 2005-08-16 Siemens Westinghouse Power Corporation Locking spacer assembly for slotted turbine component

Also Published As

Publication number Publication date
US20070041840A1 (en) 2007-02-22
TW200535323A (en) 2005-11-01
ATE417187T1 (de) 2008-12-15
CA2558838C (fr) 2012-06-12
DE102004011508A1 (de) 2005-09-29
TWI341899B (en) 2011-05-11
US7309214B2 (en) 2007-12-18
CA2558838A1 (fr) 2005-09-15
WO2005085599A1 (fr) 2005-09-15
EP1723312A1 (fr) 2006-11-22
ES2318466T3 (es) 2009-05-01
DE502005006205D1 (de) 2009-01-22

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