WO2010040339A1 - Procédé de montage d'une couronne d'aubes pour un rotor et couronne d'aubes correspondante - Google Patents

Procédé de montage d'une couronne d'aubes pour un rotor et couronne d'aubes correspondante Download PDF

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Publication number
WO2010040339A1
WO2010040339A1 PCT/DE2009/001387 DE2009001387W WO2010040339A1 WO 2010040339 A1 WO2010040339 A1 WO 2010040339A1 DE 2009001387 W DE2009001387 W DE 2009001387W WO 2010040339 A1 WO2010040339 A1 WO 2010040339A1
Authority
WO
WIPO (PCT)
Prior art keywords
blade
rotor
blade ring
rotor blades
carriage
Prior art date
Application number
PCT/DE2009/001387
Other languages
German (de)
English (en)
Inventor
Robert Schmidt
Original Assignee
Mtu Aero Engines Gmbh
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 Mtu Aero Engines Gmbh filed Critical Mtu Aero Engines Gmbh
Publication of WO2010040339A1 publication Critical patent/WO2010040339A1/fr

Links

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
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
    • 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
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins

Definitions

  • the invention relates to a method for mounting a blade ring for a rotor, in particular for a turbine disk or a turbine ring of a turbine stage of a turbomachine, and a blade ring specified in the preamble of claim 13.
  • Blades for rotors are known from the prior art.
  • Such a blade ring usually comprises a plurality of individual rotor blades and may be formed, for example, as a turbine disk (blisk) or turbine ring (bling).
  • the rotor blades with a pre-tension (pre-twist) to each other so that they do not hit each other when the rotor is started up, for example in a turbine.
  • pre-twist a pre-tension
  • the individual rotor blades can not be arranged gap-free so far because of the pre-twist, since the last rotor blade can not be mounted.
  • An exact positioning of the rotor blades in the blade ring is also not possible, so that the blade ring can not be mounted or stretched over its entire o construction diameter.
  • a method for mounting a blade ring for a rotor at least the steps of arranging a plurality of rotor blades in the form of at least two blade ring segments on a holding device, wherein between the at least two blade ring segments at least two intermediate spaces are left open, generate a prestress in at least one Rotor blade, providing at least two Golfrotorschaufeln for each gap, wherein the space provided for each space Birotorschaufeln are each juxtaposed, generating a bias in at least one Golfrotorschaufel and forming the Schaufelkranzes by arranging the Gearrotorschaufeln performed in the associated spaces.
  • the blade ring can be mounted with prestressed rotor blades, wherein in addition an exact positioning of the individual rotor blades in the blade ring is ensured.
  • the blade ring can be joined together gap-free to form a defined construction diameter, which is necessary for further processing steps - for example, joining or
  • the bias voltage is generated in all rotor blades and / or in all Medrotorschaufeln. This ensures a particularly high rigidity of the blade ring and a correspondingly trouble-free start-up behavior.
  • the prestressing is produced by clamping the at least one rotor blade on the holding device and / or the at least one filler rotor blade on a carriage. This represents a particularly process-reliable and precise possibility for generating the desired bias of the rotor blade or the filler rotor blade.
  • the twisting can be performed, for example, by clamping the rotor or filler rotor blade at its inner and outer diameter and then twisting.
  • the rotor blades are arranged in the form of at least two blade ring segments with the same center angle and / or in the form of at least three, preferably at least four, 0 blade ring segments. This allows a reliable and easy to automate assembly of the blade ring, wherein the respective number of blade ring segments can be selected, for example, depending on the later blade ring diameter.
  • the filler rotor blade provided initially initially arranged next to each other on the carriage and the bias is generated by clamping the Greinerschaufeln on the carriage.
  • the carriage can thus be used advantageously as a clamping and positioning device, whereby a particularly fast, easy and inexpensive installation is possible.
  • the holding device used and the carriage 5 used are formed corresponding to each other.
  • the filler rotor blades are arranged by positioning the carriage on the holding device in its associated space. As a result, the filler rotor blades can be introduced quickly and automatically into their assigned intermediate space and precisely positioned.
  • the blade ring can be mounted particularly cost-effectively due to the reduced variety of parts. In addition, this makes it particularly easy to ensure a uniform mass distribution over the circumference of the blade ring.
  • the blade ring is joined after forming, in particular welded.
  • electron beam or laser welding methods can be used for welding.
  • a further aspect of the invention relates to a blade ring for a rotor, in particular a turbine disk or a turbine ring of a turbine stage of a fluid machine, with a plurality of rotor blades, wherein a bias of at least a portion of the rotor blades is made possible by the blade ring at least two spaced apart Blade rim segments comprises, between which at least two Rudrotorschaufeln are arranged. This also ensures accurate positioning of the individual rotor blades in the blade ring. Further advantages can be found in the previous descriptions.
  • the blade ring is mounted and / or manufactured by means of a method according to one of the preceding embodiments.
  • the features presented in connection with the method according to the invention and their advantages apply - as far as applicable - to the blade ring according to the invention. Further advantages, features and details of the invention will become apparent from the following description of an exemplary embodiment and with reference to the drawings, in which the same or functionally identical elements are provided with identical reference numerals 5. Showing:
  • Figure 1 is a schematic perspective view of four arranged on a holding device blade ring segments, between which four spaces are left free. 0
  • Fig. 2 is a schematic perspective view of a carriage with a removable positioning stop, with two filler rotor blades arranged side by side on the carriage;
  • Fig. 3 is a schematic perspective view of the carriage shown in Fig. 2, with the locating stop removed;
  • Fig. 4 is a schematic perspective view of a gap between two of the blade ring segments shown in Fig. 1 into which the carriage with the filler blades is moved;
  • Fig. 5 is a schematic perspective view of a blade ring formed by arranging the filler rotor blades in the spaces between the blade ring segments;
  • Fig. 6 is a schematic and fragmentary perspective view of a plurality of rotor blades of the blade ring shown in Fig. 5, which are welded together.
  • FIG. 1 shows a schematic perspective view of four blade ring segments 12a-d of a blade ring 11 (see Fig. 5) arranged on a holding device 10, between which four spaces 14a-d are released.
  • the vane segments 12a-d having center angles ⁇ of about 80 ° each include a plurality of rotor blades 16, all of the rotor blades 16 being clamped at their respective inside and outside diameters to the fixture 10 and having a pre-twist of between 1 ° and 3 ° Be biased.
  • the fixture 10 includes positioning stops 18 so that the individual rotor blades 16 can be precisely positioned in the respective vane segment 12a-d. In principle, however, fewer or more than four blade ring segments 12 with a corresponding number of intermediate spaces 14 can be provided, for example in the case of blade rings 11 with differing diameters.
  • two filler rotor blades 20 are provided for each gap 14a-d.
  • the Golfrotorschaufeln 20 are first clamped side by side on a carriage 22 and biased analogously to the rotor blades 16 by generating a pre-twist of about l ° -3 °.
  • the carriage 22 also includes positioning stops 18, whereby the relative position of the Artrotorschaufeln 20 is precisely adjustable and the Greporschaufeln 20 are gap-free next to each other can be arranged.
  • the positioning stops 18 are designed to be removable in the present embodiment. In principle, it may be provided that 20 rotor blades 16 are used as filling rotor blades. Alternatively or additionally, it may be provided that, depending on the size of the intermediate space 14, three or more filling rotor blades 20 are arranged next to one another.
  • FIG. 3 shows a schematic perspective view of the carriage 22 shown in FIG. 2 with the prestressed filler rotor blades 20.
  • Fig. 4 shows a schematic perspective view of the gap 14b between the blade ring segments 12b, 12c, in which the carriage 22 is moved with the Gearrotorschaufeln 20 according to arrow IV.
  • the holding device 10 and the slide 22 are to die- sem purpose corresponding to each other, so that the carriage 22 defined in a corresponding sliding guide of the holding device 10 can be inserted.
  • the blade ring 11 shown in schematic perspective view in FIG. 5 can be assembled gap-free to form a defined construction diameter and thus completely formed. Subsequently, if necessary, the concentricity of the blade ring 11 can be rectified.
  • FIG. 6 shows a schematic and partial perspective view of a plurality of rotor blades 16 of the blade ring 11 shown in FIG. 5, which are welded together by means of an electron beam welding method to form a plurality of weld seams 24a, 24b.
  • VIa is an area without contamination by mechanical processing, detergent residues or the like.
  • the arrows VIb mark areas which have such impurities and can thereby lead to the formation of a residual gap. Therefore, first radial welds 24a are generated having a depth of at least 60% of a top bead width of the axial weld 24b. In the present exemplary embodiment, a depth of approximately 5-6 mm is generated.
  • the radial welds 24a are welded over in accordance with arrow VIc and the axial weld 24b is produced.
  • the axial weld 24b comes in this way in the area marked with arrow VId not in contact with the possibly present impurities, which excludes a pore or defect formation and ensures a corresponding high joint quality.

Landscapes

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

Abstract

L'invention concerne un procédé de montage d'une couronne d'aubes (11) pour rotor, destinée notamment à un disque de turbine ou un anneau de turbine d'un étage turbine d'une turbomachine. Ce procédé comprend les étapes suivante : installation d'une pluralité d'aubes de rotor (16) sous la forme d'au moins deux segments (12a-d) de couronne d'aubes sur un dispositif de maintien (10), au moins deux interstices (14a-d) étant laissés libres (14a-d) entre lesdits au moins deux segments (12a-d) de couronne d'aubes; production d'une précontrainte dans au moins une aube de rotor (16); préparation d'au moins deux aubes de rotor de remplissage (20) pour chaque interstice (14a-d), les aubes de rotor de remplissage (20) prévues pour chaque interstice étant respectivement juxtaposées; génération d'une précontrainte dans au moins une aube de rotor de remplissage (20) et formation de la couronne d'aubes (11) par installation de l'aube de rotor de remplissage (20) dans les interstices (14a-d) associés. L'invention concerne également une couronne d'aubes (11) pour le rotor.
PCT/DE2009/001387 2008-10-09 2009-10-07 Procédé de montage d'une couronne d'aubes pour un rotor et couronne d'aubes correspondante WO2010040339A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE200810051935 DE102008051935A1 (de) 2008-10-09 2008-10-09 Verfahren zum Montieren eines Schaufelkranzes für einen Rotor und Schaufelkranz hierzu
DE102008051935.9 2008-10-09

Publications (1)

Publication Number Publication Date
WO2010040339A1 true WO2010040339A1 (fr) 2010-04-15

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/DE2009/001387 WO2010040339A1 (fr) 2008-10-09 2009-10-07 Procédé de montage d'une couronne d'aubes pour un rotor et couronne d'aubes correspondante

Country Status (2)

Country Link
DE (1) DE102008051935A1 (fr)
WO (1) WO2010040339A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2644833A1 (fr) 2012-03-26 2013-10-02 Alstom Technology Ltd Anneau de support
US9347326B2 (en) 2012-11-02 2016-05-24 General Electric Company Integral cover bucket assembly
US20170081963A1 (en) * 2014-05-12 2017-03-23 Siemens Aktiengesellschaft Method for assembling a turbine assembly

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109968084B (zh) * 2019-04-04 2020-07-17 哈尔滨汽轮机厂有限责任公司 一种燃气轮机导叶车削内孔用夹紧装置
CN111451738B (zh) * 2020-04-22 2021-09-07 南京丛迈信息科技有限公司 一种用于燃气轮机中叶轮的组装装置

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB720802A (en) * 1953-03-10 1954-12-29 Parsons C A & Co Ltd Improvements in and relating to assembly of blades for turbines and compressors
DE1426778B1 (de) * 1962-07-11 1969-11-20 Bbc Brown Boveri & Cie Verfahren zum Montieren einer Reihe biegungssteifer Schaufeln mit Deckplatten
EP1028232A1 (fr) * 1999-02-12 2000-08-16 ABB Alstom Power (Schweiz) AG Fixation d'aubes de rotor d'une turbomachine
US6158104A (en) * 1999-08-11 2000-12-12 General Electric Co. Assembly jig for use with integrally covered bucket blades
US20060177314A1 (en) * 2004-09-16 2006-08-10 Yutaka Yamashita Turbine rotor blade and turbine

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE6601212U (de) * 1968-03-22 1969-02-27 Siemens Ag Laufschaufelbefestigung fuer turbomaschinen
GB2112465B (en) * 1981-12-30 1985-04-11 Rolls Royce Turbomachine rotor
GB2132512A (en) * 1982-12-24 1984-07-11 Rolls Royce Welded stator vane assemblies for turbomachines
CH678750A5 (fr) * 1989-03-22 1991-10-31 Escher Wyss Ag

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB720802A (en) * 1953-03-10 1954-12-29 Parsons C A & Co Ltd Improvements in and relating to assembly of blades for turbines and compressors
DE1426778B1 (de) * 1962-07-11 1969-11-20 Bbc Brown Boveri & Cie Verfahren zum Montieren einer Reihe biegungssteifer Schaufeln mit Deckplatten
EP1028232A1 (fr) * 1999-02-12 2000-08-16 ABB Alstom Power (Schweiz) AG Fixation d'aubes de rotor d'une turbomachine
US6158104A (en) * 1999-08-11 2000-12-12 General Electric Co. Assembly jig for use with integrally covered bucket blades
US20060177314A1 (en) * 2004-09-16 2006-08-10 Yutaka Yamashita Turbine rotor blade and turbine

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2644833A1 (fr) 2012-03-26 2013-10-02 Alstom Technology Ltd Anneau de support
CN104220703A (zh) * 2012-03-26 2014-12-17 阿尔斯通技术有限公司 承载环
US10012094B2 (en) 2012-03-26 2018-07-03 Ansaldo Energia Switzerland AG Carrier ring
US9347326B2 (en) 2012-11-02 2016-05-24 General Electric Company Integral cover bucket assembly
US20170081963A1 (en) * 2014-05-12 2017-03-23 Siemens Aktiengesellschaft Method for assembling a turbine assembly

Also Published As

Publication number Publication date
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