EP1342882A2 - Procédé de fabrication d'un rotor soudé de turbomachine - Google Patents

Procédé de fabrication d'un rotor soudé de turbomachine Download PDF

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Publication number
EP1342882A2
EP1342882A2 EP03100886A EP03100886A EP1342882A2 EP 1342882 A2 EP1342882 A2 EP 1342882A2 EP 03100886 A EP03100886 A EP 03100886A EP 03100886 A EP03100886 A EP 03100886A EP 1342882 A2 EP1342882 A2 EP 1342882A2
Authority
EP
European Patent Office
Prior art keywords
rotor
hollow channel
welded
rotor disks
disks
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
EP03100886A
Other languages
German (de)
English (en)
Other versions
EP1342882B1 (fr
EP1342882A3 (fr
Inventor
Wilhelm Endres
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.)
GE Vernova GmbH
Original Assignee
Alstom Technology AG
Alstom Schweiz 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, Alstom Schweiz AG filed Critical Alstom Technology AG
Priority to DE59813544T priority Critical patent/DE59813544D1/de
Publication of EP1342882A2 publication Critical patent/EP1342882A2/fr
Publication of EP1342882A3 publication Critical patent/EP1342882A3/fr
Application granted granted Critical
Publication of EP1342882B1 publication Critical patent/EP1342882B1/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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F01D5/063—Welded rotors
    • 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
    • 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
    • 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
    • Y10T29/49323—Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles
    • 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
    • Y10T29/49325—Shaping integrally bladed rotor

Definitions

  • the invention relates to a method for producing a welded rotor of a turbomachine according to the preamble of claim 1.
  • a welded rotor of the generic type for a turbomachine, for example for a gas turbine plant, is described in European publication EP-A1-0 844 367.
  • the rotor has hollow channels which extend circumferentially about the rotor axis between two rotor disks welded to one another.
  • the hollow channels rotating around the rotor axis reference is made to the above-mentioned European publication, to which reference is also made with regard to all details not shown in further detail which are necessary for the technical understanding of the cooling system on which the welded rotor is based.
  • a specially designed insert ring is provided, which at least partially delimits each hollow channel on one side and is welded to the rotor disks by means of corresponding weld seams.
  • the structural design of the cavity geometry and the shape of the insert rings are selected in such a way that conventional welding techniques can be used to produce the weld seams.
  • this corresponds to the desire for the simplest possible manufacturing techniques and conditions, but the production of the insert rings, which are specially adapted to the geometry of the hollow channels, requires high precision and alignment accuracy during assembly, which in turn leads to a considerable measure of manufacturing costs accept.
  • the insert rings also each have a spacer which projects into the interior of the hollow channel and hinders the free propagation of the cooling medium within the hollow channel.
  • the invention has for its object to develop a method for producing a welded rotor of a turbomachine such that, on the one hand, the individual parts required for the assembly of the rotor are as simple and inexpensive to manufacture as possible, and on the other hand, they are conveniently available within the rotor to be welded.
  • the advantages obtained, for example, with the aid of electron beam welding, should be able to be fully utilized with the method according to the invention.
  • the manufacturing process should work reliably at a higher process speed, than is the case with the previously known methods for producing generic, welded rotors.
  • Two directly adjacent rotor disks are firmly attached to one another along their mutual contact surfaces, preferably along a weld seam, for example using conventional welding techniques.
  • the two adjacent rotor disks in the assembled state enclose a hollow channel, the peripheral outer side of which, facing away from the rotor axis, is at least partially open.
  • the rotor disks are also designed such that they enclose a gap which faces away from the rotor, directly adjoins the cavity and into which an annular element consisting of at least two partial elements is introduced.
  • Both ring parts are then firmly attached to one another by means of electron beam welding at their abutting surfaces within the gap.
  • the side flanks of the partial elements of the ring element inserted into the gap are firmly welded to the respective rotor disks by means of electron beam welding.
  • centering lips are provided at the points to be welded, within which the welding beam is guided.
  • the inventive manufacturing method described above relates to a simplified assembly of welded rotors, which provide cooling channels within the rotor shaft for cooling purposes, through which cooling steam is driven. It is of decisive advantage to take advantage of the advantages associated with electron welding technology.
  • Fig. 1 shows a highly schematic representation of a cross section through the adjacent areas of two rotor disks 1, 2 to the hollow channel 5 through which a cooling medium is driven.
  • the hollow channel 5 is delimited on the one hand by the rotor disks 1 and 2, which are firmly connected to one another under the hollow channel 5 via a weld seam 3.
  • cooling channels 4 open, which pass through the rotor disks 1 and 2 accordingly and are introduced or discharged into the hollow channel 5 by the coolant.
  • the cavity 5 enclosed by the two rotor disks 1 and 2 is designed to be open in the region 6 on its peripheral outside.
  • the rotor disks 1 and 2 enclose a gap 7 on the side facing away from the rotor, adjacent to the hollow channel, through which the welding beam required for producing the weld seam 3 for electron beam welding can be directed in order to weld the two rotor disks.
  • a preferably two-part ring element 8 is inserted radially from the outside into the gap 7, which is firmly welded to its abutting edges 9 by means of electron beam welding. Electron beam welding can also produce a fixed connection along the peripheral seams 10 and in this way establish a fixed connection between the ring elements 8 and the rotor disks 1 and 2.
  • centering lips 11 are provided along the separating edges to be welded, which serve to avoid welding spots, which are often associated with bead and material droplet formation directly on the welding groove.
  • FIG. 2 shows a detailed representation of the lower end of the peripheral seam 10 according to FIG. 1.
  • the centering lip 11 At the lower end of the peripheral seam 10 of the rotor disk 1 there is a small projection, referred to as the centering lip 11, which projects slightly beyond the ring element 8 on its underside. When welding, the centering lip 11 is not completely welded through, as can be seen from the detailed illustration according to FIG. 2.
  • known relief grooves can also be provided in order to reduce the mechanical stresses on the individual welding grooves. Relief grooves are concave contours that directly adjoin a weld seam elevation and serve a smooth transition from the weld seam to the contour of the adjoining molded part.
  • the method according to the invention described above leads to welded rotors with circumferential hollow channels, in which there are no surface elements which prevent the cooling medium within the cavity from spreading out.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Welding Or Cutting Using Electron Beams (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP03100886A 1998-12-10 1998-12-10 Procédé de fabrication d'un rotor soudé de turbomachine Expired - Lifetime EP1342882B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DE59813544T DE59813544D1 (de) 1998-12-10 1998-12-10 Verfahren zur Herstellung eines geschweissten Rotors einer Strömungsmaschine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP98811218A EP1008722B1 (fr) 1998-12-10 1998-12-10 Procédé de fabrication par soudage d'un rotor de turbomachine

Related Parent Applications (3)

Application Number Title Priority Date Filing Date
EP98811218.1 Division 1998-12-10
EP98811218A Division EP1008722B1 (fr) 1998-12-10 1998-12-10 Procédé de fabrication par soudage d'un rotor de turbomachine
EP98811218A Division-Into EP1008722B1 (fr) 1998-12-10 1998-12-10 Procédé de fabrication par soudage d'un rotor de turbomachine

Publications (3)

Publication Number Publication Date
EP1342882A2 true EP1342882A2 (fr) 2003-09-10
EP1342882A3 EP1342882A3 (fr) 2004-05-06
EP1342882B1 EP1342882B1 (fr) 2006-05-17

Family

ID=8236478

Family Applications (2)

Application Number Title Priority Date Filing Date
EP98811218A Expired - Lifetime EP1008722B1 (fr) 1998-12-10 1998-12-10 Procédé de fabrication par soudage d'un rotor de turbomachine
EP03100886A Expired - Lifetime EP1342882B1 (fr) 1998-12-10 1998-12-10 Procédé de fabrication d'un rotor soudé de turbomachine

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP98811218A Expired - Lifetime EP1008722B1 (fr) 1998-12-10 1998-12-10 Procédé de fabrication par soudage d'un rotor de turbomachine

Country Status (3)

Country Link
US (2) US6519849B2 (fr)
EP (2) EP1008722B1 (fr)
DE (1) DE59809583D1 (fr)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10348422B4 (de) 2003-10-14 2015-04-23 Alstom Technology Ltd. Thermisch belastetes Bauteil, sowie Verfahren zur Herstellung eines solchen Bauteils
US7281901B2 (en) * 2004-12-29 2007-10-16 Caterpillar Inc. Free-form welded power system component
US7473475B1 (en) * 2005-05-13 2009-01-06 Florida Turbine Technologies, Inc. Blind weld configuration for a rotor disc assembly
US20070189894A1 (en) * 2006-02-15 2007-08-16 Thamboo Samuel V Methods and apparatus for turbine engine rotors
EP1895094B1 (fr) * 2006-08-25 2010-09-29 Siemens Aktiengesellschaft Rotor avec cordon de soudure refroidi par tourbillon
US20090060735A1 (en) * 2007-08-31 2009-03-05 General Electric Company Turbine rotor apparatus and system
US8997498B2 (en) 2011-10-12 2015-04-07 General Electric Company System for use in controlling the operation of power generation systems

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE787441A (fr) * 1971-08-23 1973-02-12 Alsthom Cgee Rotor soude
CH563833A5 (fr) * 1974-10-28 1975-07-15 Bbc Brown Boveri & Cie
GB1549070A (en) * 1977-12-12 1979-08-01 Rolls Royce Gas turbine engine compressor rotor construction
AT374397B (de) * 1980-07-21 1984-04-10 Puschner Manfred Dr Verfahren zur kontinuierlichen herstellung von fuelldraehten, fuelldrahtelektroden od. dgl.
US4598449A (en) * 1981-12-21 1986-07-08 United Technologies Corporation Beam for a containment structure
US5221821A (en) * 1992-01-10 1993-06-22 Crompton & Knowles Corporation Method for producing an extruder barrel assembly
DE4324034A1 (de) * 1993-07-17 1995-01-19 Abb Management Ag Gasturbine mit gekühltem Rotor
US5593274A (en) * 1995-03-31 1997-01-14 General Electric Co. Closed or open circuit cooling of turbine rotor components
JP2941698B2 (ja) * 1995-11-10 1999-08-25 三菱重工業株式会社 ガスタービンロータ
GB2307520B (en) * 1995-11-14 1999-07-07 Rolls Royce Plc A gas turbine engine
US5632600A (en) * 1995-12-22 1997-05-27 General Electric Company Reinforced rotor disk assembly
DE19648185A1 (de) * 1996-11-21 1998-05-28 Asea Brown Boveri Geschweisster Rotor einer Strömungsmaschine
DE19713268B4 (de) * 1997-03-29 2006-01-19 Alstom Gekühlte Gasturbinenschaufel
DE19738065A1 (de) * 1997-09-01 1999-03-04 Asea Brown Boveri Turbinenschaufel einer Gasturbine
DE59813488D1 (de) * 1998-07-14 2006-05-24 Alstom Technology Ltd Baden Berührungsloses Abdichten von Spalten Gasturbinen

Also Published As

Publication number Publication date
US6687994B2 (en) 2004-02-10
US20030084568A1 (en) 2003-05-08
EP1342882B1 (fr) 2006-05-17
EP1342882A3 (fr) 2004-05-06
US20020092165A1 (en) 2002-07-18
EP1008722A1 (fr) 2000-06-14
EP1008722B1 (fr) 2003-09-10
US6519849B2 (en) 2003-02-18
DE59809583D1 (de) 2003-10-16

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