EP1698759B1 - Fermeture de rotor - Google Patents

Fermeture de rotor Download PDF

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Publication number
EP1698759B1
EP1698759B1 EP06110072.3A EP06110072A EP1698759B1 EP 1698759 B1 EP1698759 B1 EP 1698759B1 EP 06110072 A EP06110072 A EP 06110072A EP 1698759 B1 EP1698759 B1 EP 1698759B1
Authority
EP
European Patent Office
Prior art keywords
rotor
end piece
halves
blade
tabs
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
EP06110072.3A
Other languages
German (de)
English (en)
Other versions
EP1698759A3 (fr
EP1698759A2 (fr
Inventor
René Bachofner
Pietro Grigioni
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 EP1698759A2 publication Critical patent/EP1698759A2/fr
Publication of EP1698759A3 publication Critical patent/EP1698759A3/fr
Application granted granted Critical
Publication of EP1698759B1 publication Critical patent/EP1698759B1/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
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • 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

Definitions

  • the invention relates to the field of thermal turbomachinery, in particular it relates to a rotor end for rotors according to the preamble of claim 1. Furthermore, an assembly method for a rotor according to the invention is given.
  • Thermal turbomachinery with axial turbines and axial compressors have a rotor equipped with blades and a stator, are mounted in the guide vanes for flow guidance.
  • the stationary guide vanes have the task of directing the flow of the gas medium to be compressed or to be relaxed in such a way onto the rotating running blading of the respective compressor stage or the respective turbine stage that the energy conversion takes place with the best possible efficiency.
  • Both blades and vanes essentially comprise a profiled airfoil and a blade root.
  • grooved in the stator and on the rotor shaft are the Feet of the blades inserted and locked there.
  • compressor blade rows of gas turbine rotors are arranged in circumferential grooves, which often have a T-shaped cross-section.
  • blades and spacers alternate here.
  • a special solution must be found for the last blades to be mounted, since then the remaining filling opening for a complete intermediate piece is too small. This residual opening is therefore filled with a so-called rotor-end.
  • the known rotor closure consists of a halved intermediate piece, that is to say of two halves divided in the circumferential direction with respect to the rotor, and a wedge with the aid of which the end halves are caulked axially in the rotor.
  • the two end halves in the known prior art according to the DE 812 337 each have a straight side surface formed.
  • the side surfaces mentioned are opposite in the installed state, in which case the wedge is located between them.
  • the invention is based on the technical problem of providing a rotor end which is as simple and inexpensive as possible during assembly and production.
  • a rotor end for a rotor of a thermal turbomachine with at least one circumferential groove are provided in the blades, in particular with a hammer base, and intermediate pieces, wherein between an end blade and an end piece a residual gap is formed, in which two end halves are arranged each integrally with these associated locking tabs, which are in engagement with the end blade or with the tail, and the end halves below the lobes relief slots, wherein the tabs are arranged on the parting plane of the end halves.
  • no wedge is present, i. no forces are applied to the rotor in the axial direction. This is possible due to the design-related low residual gap.
  • the proposed rotor-end is safe and does not cause rotor vibrations.
  • the relief slots contribute to the easy manual flexibility of the lobes and thus to the easy installation of the rotor closure. In addition, this prevents that the closing halves twist when bending the cloth.
  • An advantageous development of the invention provides that the end blade and the end piece in the foot region on the side facing the remaining gap each having a recess into which the lobes of the end halves are inserted. Through the recess, the end blade and the end piece differ from the other runners and intermediate pieces.
  • the recess may for example be designed in the shape of a cylinder segment and removed by means of a grinding tool.
  • end halves have a material thickness of 3 mm to 5 mm. Hierduch manually bending the cloth is possible with a simple assembly tool.
  • the end halves are made of a chromium-molybdenum-vanadium alloy. This ensures the desired strength of the rotor end.
  • a method for mounting a rotor closure in a circumferential groove, which has two end halves has the following steps: inserting the two end halves in the remaining gap, together with supports, so that the end halves are offset from one another; Inserting a tool in the parting plane between the two end halves; Bending the flaps into the recesses of the end blade and the tail; Remove the supports.
  • An advantageous development of the method according to the invention for mounting a rotor closure further comprises the following steps: Turning the tool through 90 °, so that the tabs protrude far enough into the recess.
  • FIG. 1 shows a section in the rotor longitudinal direction through a rotor-1 according to the invention after installation in a compressor rotor 6.
  • FIG. 2 shows a partial section along the line II - II FIG. 1 ,
  • the remaining gap 15 present between an end blade 2 and an end piece 11 is filled by two end halves 4, 4.
  • the flat end halves 4, 4 essentially have a cross-section which corresponds to a so-called hammer foot or two-pointed foot, with a rectangular area being excluded above the parting plane 5.
  • bendable tabs 8, 8 are arranged. Below the tabs 8, 8, the closing halves 4, 4 have relief slots 10, 10.
  • the end blade 2 and the end piece 11 have in the foot region on the side facing the remaining gap 15 each have a recess 9, 12, in which the tabs 8, 8 of the end halves 4, 4 are introduced by bending. Through the recessed into the recesses 9, 12 tabs 8, 8 of the rotor 1 is locked and secured against falling out.
  • FIG. 3 shows an enlarged detail view of the two end halves 4, 4.
  • the end halves 4, 4 with their parting plane 5 across the dividing plane 5 above a rectangular surface is cut out, the access to the two arranged on the upper edge of the parting plane 5 with a flap Tool allows.
  • Below the tabs 8, 8 horizontal relief slots 10 are provided, each beginning in the parting plane 5 and terminate in a bore.
  • the outer contour of the end halves 4, 4 is designed so that they can be inserted into a T-shaped circumferential groove 3 of a rotor 6 and find support therein.
  • FIG. 4 which shows a plan view of the end halves 4, 4 FIG. 3 shows, the end halves only a small thickness of 3 mm to 5 mm. This makes it possible that the tabs 8,8 can still be bent manually.
  • FIG. 5 shows a partial section similar to that Fig. 2 corresponds, but with introduced during assembly supports.
  • a residual gap 15 remains.
  • This residual gap 15 can only be taken from two divided in the circumferential direction of the groove 3 end halves 4, 4 existing rotor end 1 with supports 14, 14.
  • the supports 14, 14 serve only as an assembly aid of the two 3mm to 5mm thick end halves 4, 4, which are made of a chromium-molybdenum-vanadium alloy.
  • the supports 14, 14 are just as thick as the end halves 4, 4 or slightly thinner.
  • a corresponding mounting tool 13 such as a screwdriver or a flat chisel, which is about 10 mm - 15 mm inserted into the parting plane 5 between the two end halves 4,4, the two tabs 8, 8 are bent out of the final plane.
  • the tool 13 is preferably rotated by 90 ° so that the tabs 8, 8 protrude far enough into the recess on the blade root 9 or into the recess on the tail base 12.
  • the respective recesses 9, 12 are incorporated as a cylinder-segment-like depressions in the end blade foot 7 and the End Culturefuss, whereby the components differ from the other blades and spacers. Subsequently, the only required for the installation supports 14, 14 are removed and the minimum gap evenly distributed over the circumference.
  • the final configuration reached is in Figures 1 and 2 shown and described.
  • the disassembly is carried out by drilling away or grinding away the lobes 8, 8 and removal of the end halves 4,4.

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)

Claims (6)

  1. Fermeture de rotor (1) pour un rotor (6) d'une turbomachine thermique comprenant au moins une rainure périphérique (3) dans laquelle sont prévues des aubes mobiles et des pièces intermédiaires, la fermeture de rotor (1) comprenant une aube d'extrémité (2) et une pièce d'extrémité (11), et un interstice résiduel (15) étant formé entre l'aube d'extrémité (2) et la pièce d'extrémité (11), dans lequel sont montées deux moitiés de fermeture (4, 4) pourvues respectivement de pattes de fixation (8, 8) disposées d'une seule pièce sur celles-ci, lesquelles pattes de fixation sont en prise avec l'aube d'extrémité (2), respectivement avec la pièce d'extrémité (11),
    caractérisée en ce que
    les moitiés de fermeture (4, 4) comprennent des fentes de détente (10, 10) en dessous des pattes (8, 8), et
    en ce que les pattes (8, 8) sont disposées sur un plan de séparation (5) des moitiés de fermeture (4, 4).
  2. Fermeture de rotor (1) selon la revendication 1,
    caractérisée en ce que
    l'aube d'extrémité (2) et la pièce d'extrémité (11) comprennent respectivement un évidement (9, 12) dans la région de pied sur le côté tourné vers l'interstice résiduel (15), dans lequel évidement les pattes (8, 8) des moitiés de fermeture (4, 4) peuvent être introduites.
  3. Fermeture de rotor (1) selon l'une quelconque des revendications 1 et 2,
    caractérisée en ce que
    les moitiés de fermeture (4, 4) présentent une épaisseur de matériau de 3 mm à 5 mm.
  4. Fermeture de rotor (1) selon l'une quelconque des revendications précédentes,
    caractérisée en ce que
    les moitiés de fermeture (4, 4) sont fabriquées à partir d'un alliage chrome-molybdène-vanadium.
  5. Procédé de montage d'une fermeture de rotor dans une rainure périphérique entre une aube d'extrémité et une pièce d'extrémité des deux moitiés de fermeture pourvues respectivement de pattes de fixation disposées d'une seule pièce sur celles-ci, le procédé comprenant les étapes suivantes :
    - insertion des deux moitiés de fermeture dans l'interstice résiduel, conjointement avec des supports, de telle sorte que les moitiés de fermeture soient décalées l'une par rapport à l'autre ;
    - introduction d'un outil dans un plan de séparation entre les deux moitiés de fermeture ;
    - pliage des pattes de fixation dans des évidements de l'aube d'extrémité et de la pièce d'extrémité ;
    - retrait des supports.
  6. Procédé de montage d'une fermeture de rotor selon la revendication 5, le procédé comprenant en outre l'étape suivante :
    - rotation de l'outil de 90°, afin que les pattes de fixation pénètrent suffisamment loin dans l'évidement.
EP06110072.3A 2005-02-23 2006-02-17 Fermeture de rotor Not-in-force EP1698759B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH3232005 2005-02-23

Publications (3)

Publication Number Publication Date
EP1698759A2 EP1698759A2 (fr) 2006-09-06
EP1698759A3 EP1698759A3 (fr) 2012-04-04
EP1698759B1 true EP1698759B1 (fr) 2015-06-03

Family

ID=34974751

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06110072.3A Not-in-force EP1698759B1 (fr) 2005-02-23 2006-02-17 Fermeture de rotor

Country Status (2)

Country Link
US (1) US7367778B2 (fr)
EP (1) EP1698759B1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9828865B2 (en) 2012-09-26 2017-11-28 United Technologies Corporation Turbomachine rotor groove
US10677247B2 (en) * 2016-01-07 2020-06-09 Stein Seal Company Slurry seal assembly
US10465699B2 (en) * 2017-01-26 2019-11-05 DOOSAN Heavy Industries Construction Co., LTD Compressor blade locking mechanism in disk with tangential groove

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE724549C (de) * 1939-12-09 1942-08-29 Aeg Schaufelschloss fuer eine unter Verwendung von Zwischenstuecken hergestellte Turbinenbeschaufelung
US2410588A (en) * 1942-06-23 1946-11-05 Northrop Aircraft Inc Turbine blade and assembly thereof
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.
DE1040047B (de) * 1954-12-23 1958-10-02 Maschf Augsburg Nuernberg Ag Befestigung der Schlussschaufel eines Laufrades fuer Axial-Kreiselmaschinen
GB980337A (en) * 1962-05-08 1965-01-13 Power Jets Res & Dev Ltd Improvements in or relating to a rotor for a compressor turbine or like bladed fluidflow machine
US3383094A (en) * 1967-01-19 1968-05-14 Gen Electric Rotor blade locking means
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
US4633554A (en) * 1985-08-08 1987-01-06 Westinghouse Electric Corp. Method for repairing a steam turbine or generator rotor
DD271243A3 (de) * 1987-10-01 1989-08-30 Goerlitzer Maschinenbau Veb Schaufelschlossanordnung mit minimierter schaufelschlossluecke
US4915587A (en) * 1988-10-24 1990-04-10 Westinghouse Electric Corp. Apparatus for locking side entry blades into a rotor
DE10134611A1 (de) 2000-12-16 2002-06-27 Alstom Switzerland Ltd Fixiervorrichtung für eine Beschaufelung einer Strömungsmaschine
DE10310432A1 (de) 2003-03-11 2004-09-23 Alstom Technology Ltd Rotor-Schluss

Also Published As

Publication number Publication date
EP1698759A3 (fr) 2012-04-04
US20060257248A1 (en) 2006-11-16
US7367778B2 (en) 2008-05-06
EP1698759A2 (fr) 2006-09-06

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