EP0745756A1 - Dispositif et méthode de montage d'aubes de rotor - Google Patents

Dispositif et méthode de montage d'aubes de rotor Download PDF

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Publication number
EP0745756A1
EP0745756A1 EP96810313A EP96810313A EP0745756A1 EP 0745756 A1 EP0745756 A1 EP 0745756A1 EP 96810313 A EP96810313 A EP 96810313A EP 96810313 A EP96810313 A EP 96810313A EP 0745756 A1 EP0745756 A1 EP 0745756A1
Authority
EP
European Patent Office
Prior art keywords
rotor
blades
axial
assembly
circumferential groove
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
EP96810313A
Other languages
German (de)
English (en)
Other versions
EP0745756B1 (fr
Inventor
Peter Hartmann
Michael Hock
Alfred Krähenbühl
Beat Von Arx
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 Switzerland GmbH
Original Assignee
ABB Management 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 ABB Management AG filed Critical ABB Management AG
Publication of EP0745756A1 publication Critical patent/EP0745756A1/fr
Application granted granted Critical
Publication of EP0745756B1 publication Critical patent/EP0745756B1/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
    • F01D5/12—Blades
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • 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
    • Y10T29/37—Impeller making apparatus
    • 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
    • Y10T29/49826—Assembling or joining
    • Y10T29/49895—Associating parts by use of aligning means [e.g., use of a drift pin or a "fixture"]
    • 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
    • Y10T29/53—Means to assemble or disassemble
    • Y10T29/53961—Means to assemble or disassemble with work-holder for assembly

Definitions

  • the invention relates to a device and a method for assembling rotor blades with essentially axial feet in the corresponding axial grooves of a rotor of a turbomachine.
  • Devices and methods of this type for mounting rotor blades with essentially axial feet in the corresponding axial grooves of a rotor of a turbomachine are known. They are required for the assembly of blades of a row of blades, the blades of which, for example. with specially shaped cover bands, platforms or with shovel feet with overlaps.
  • a special blade is required. These special blades are very expensive to manufacture and assembly requires special effort, or is not always possible for technical reasons. The use of special blades is logistically very complex.
  • the invention has for its object to simplify the assembly of blades with axial feet in a device for mounting blades and the associated method of the type mentioned.
  • the mounting device consists of a radially outer head part with at least one axial groove, which essentially corresponds to the axial foot of the rotor blade, and a radially inner foot part for mounting in a groove running around the rotor.
  • each row of blades is assembled individually, the row of blades can be designed with different numbers of blades per row and with different axial feet.
  • blades 1, consisting of blade root 1A and blade 1B, are inserted in axial grooves 11a of a rotor 10.
  • a platform 3 is arranged between the blade root 1A and the airfoil 1B. At the contact surfaces of these platforms, sealing takes place via sealing strips 5, which are inserted in sealing grooves 4.
  • FIG. 3 shows a one-piece assembly device 6, consisting of a foot part 7 and a head part 8.
  • a head part 8 In the head part 8 there is an axial groove 11b formed in accordance with the axial groove 11a.
  • a blade root 1A of a moving blade 1 is now inserted into the axial groove 11b.
  • the assembly device 6 together with the blade 1 is inserted radially into a circumferential groove 12a of the rotor 10, for which purpose the foot part 7 of the assembly device is shaped in accordance with the circumferential groove 12a.
  • a filling opening (not shown) is provided in the circumferential groove 12a, or the foot part 6 is screwed into the circumferential groove 12a with a ninety degree rotation.
  • the circumferential groove 12a otherwise serves to receive heat accumulation segments 9 and therefore does not have to be specially manufactured.
  • the heat accumulation segments 9 protect the rotor 10 between the rotor blade rows R. All the rotor blades 1 of a blade row R are now successively inserted radially into the circumferential groove 12a with the mounting device 6.
  • the sealing strips 5 are each inserted into the sealing grooves 4 of the platforms 3 before the blades 1 are pushed together along the circumferential groove 12a by means of the mounting device 6. Because the sealing strips 5 do not have to be inserted axially into the sealing grooves 4 after the blades 1 have been mounted on the rotor 10, they can be of essentially any shape. By pushing the mounting devices 6 in the circumferential direction and taking advantage of the tangential play, the sealing strips 5 can also be inserted into the sealing groove in the last radially inserted blade 2. After that the assembly devices are displaced in the circumferential direction so that the axial grooves 11b of the assembly devices come to lie exactly in front of the axial grooves 11a in the rotor.
  • annular auxiliary device 21 can be mounted on the rotor according to FIG. This is done by a detachable connection, preferably by means of screws 20.
  • the assembly of the rotor blades 1 by means of the assembly device 6 then takes place in exactly the same way as described above for the circumferential groove 12a.
  • FIG. 6 and 7 show an economically particularly advantageous embodiment of a mounting device 6A, consisting of a head part 31 and a foot part 30. It consists of a flat material, e.g. made of sheet metal. The parts 30 and 31 can be cut out of the flat material, for example. by punching out or laser cutting. The foot part 30 then only has to be reshaped. The two parts of the head part 31 are connected to the foot part 30 via a seam 32.
  • the assembly device 6A is used here for the simultaneous and rapid assembly of two moving blades 1 with oblique axial feet. For this purpose, two oblique axial grooves 33 are arranged in the mounting device 6A in order to accommodate two blade roots.
  • the mounting device can be used anywhere with any axial grooves.
  • the number of axial grooves per mounting device is essentially arbitrary. It hangs bsw. from the bucket size, the bucket weight, the rotor diameter and the size of the filling opening.
  • the execution of the assembly device is arbitrary, for example.
  • the foot part can also be made from a solid material, the head part from a flat material as in Figures 6 and 7, or vice versa.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP96810313A 1995-06-02 1996-05-17 Dispositif et méthode de montage d'aubes de rotor Expired - Lifetime EP0745756B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19520274 1995-06-02
DE19520274A DE19520274A1 (de) 1995-06-02 1995-06-02 Vorrichtung und Verfahren zur Montage von Laufschaufeln

Publications (2)

Publication Number Publication Date
EP0745756A1 true EP0745756A1 (fr) 1996-12-04
EP0745756B1 EP0745756B1 (fr) 2000-03-22

Family

ID=7763517

Family Applications (1)

Application Number Title Priority Date Filing Date
EP96810313A Expired - Lifetime EP0745756B1 (fr) 1995-06-02 1996-05-17 Dispositif et méthode de montage d'aubes de rotor

Country Status (6)

Country Link
US (1) US5737816A (fr)
EP (1) EP0745756B1 (fr)
JP (1) JPH08326504A (fr)
KR (1) KR970001851A (fr)
CN (1) CN1087389C (fr)
DE (2) DE19520274A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2230385A1 (fr) * 2008-01-16 2010-09-22 Mitsubishi Heavy Industries, Ltd. Pale de rotor de turbine
EP2354456A3 (fr) * 2009-12-30 2011-12-21 General Electric Company Accessoire et procédé d'assemblage d'aubes de turbine articulées
FR3008448A1 (fr) * 2013-07-15 2015-01-16 Snecma Dispositif de depose pour aubes
EP3043029A1 (fr) * 2015-01-12 2016-07-13 General Electric Company Dispositif de montage et procédé d'installation d'aubes de turbines
US10851661B2 (en) 2017-08-01 2020-12-01 General Electric Company Sealing system for a rotary machine and method of assembling same

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5758416A (en) * 1996-12-05 1998-06-02 General Electric Company Method for repairing a turbine engine vane segment
US6061886A (en) * 1997-07-11 2000-05-16 Honda Giken Kogyo Kabushiki Kaisha Turbine blade fitting apparatus and fitting method
EP1028231B1 (fr) 1999-02-12 2003-09-03 ALSTOM (Switzerland) Ltd Fixation d'aubes de rotor d'une turbomachine
US7353588B2 (en) * 2003-06-20 2008-04-08 General Electric Company Installation tool for assembling a rotor blade of a gas turbine engine fan assembly
DE10346384A1 (de) * 2003-09-29 2005-04-28 Rolls Royce Deutschland Turbinenschaufelkranz
DE102004016174A1 (de) * 2004-03-30 2005-10-20 Alstom Technology Ltd Baden Spaltdichtung zum Abdichten eines Spalts zwischen zwei benachbarten Bauteilen
US7975354B2 (en) * 2007-02-08 2011-07-12 United Technologies Corporation Bladed disk assembly method and impact device
DE102007039175A1 (de) * 2007-08-20 2009-07-02 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenschaufel
CN101285401B (zh) * 2008-06-03 2010-06-02 东方电气集团东方汽轮机有限公司 枞树型叶根汽轮机动叶片及其锁口叶片
US10883386B2 (en) * 2017-06-21 2021-01-05 Mitsubishi Hitachi Power Systems Americas, Inc. Methods and devices for turbine blade installation alignment
FR3090030B1 (fr) * 2018-12-12 2020-11-20 Safran Aircraft Engines Dispositif de maintien pour le démontage d’une roue à aubes de turbomachine et procédé l’utilisant
US11808164B1 (en) * 2022-08-19 2023-11-07 Pratt & Whitney Canada Corp. Simultaneously assembling rotor blades from a gas turbine engine rotor disk

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1720729A (en) * 1928-03-29 1929-07-16 Westinghouse Electric & Mfg Co Blade fastening
US4016636A (en) * 1974-07-23 1977-04-12 United Technologies Corporation Compressor construction
US4094615A (en) * 1976-12-27 1978-06-13 Electric Power Research Institute, Inc. Blade attachment structure for gas turbine rotor
US5026032A (en) * 1990-02-22 1991-06-25 Southern California Edison Blade assembly tool

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA522707A (fr) * 1956-03-13 O. Creek John Methode et appareil pour fabriquer des lames creuses
FR536847A (fr) * 1920-05-25 1922-05-10 Perfectionnements à la fabrication des aubes de turbines
US2240743A (en) * 1937-11-26 1941-05-06 Allis Chalmers Mfg Co Apparatus for attaching turbine blades
NL295111A (fr) * 1962-07-11
US4171799A (en) * 1978-06-26 1979-10-23 Elko George A Frame assembly jig
GB2171150B (en) * 1985-02-12 1989-07-26 Rolls Royce Plc Bladed rotor assembly for a turbomachine
US4702673A (en) * 1985-10-18 1987-10-27 General Electric Company Method for assembly of tangential entry dovetailed bucket assemblies on a turbomachine bucket wheel
US4904160A (en) * 1989-04-03 1990-02-27 Westinghouse Electric Corp. Mounting of integral platform turbine blades with skewed side entry roots
US4944082A (en) * 1989-04-27 1990-07-31 Hewlett Packard Co. Method of providing a sheet metal housing with precisely positioned mounting references
US5257442A (en) * 1989-09-07 1993-11-02 Honda Giken Kabushiki Kaisha Apparatus for assembling workpieces
US5001830A (en) * 1989-10-23 1991-03-26 Westinghouse Electric Corp. Method for assembling side entry control stage blades in a steam turbine

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1720729A (en) * 1928-03-29 1929-07-16 Westinghouse Electric & Mfg Co Blade fastening
US4016636A (en) * 1974-07-23 1977-04-12 United Technologies Corporation Compressor construction
US4094615A (en) * 1976-12-27 1978-06-13 Electric Power Research Institute, Inc. Blade attachment structure for gas turbine rotor
US5026032A (en) * 1990-02-22 1991-06-25 Southern California Edison Blade assembly tool

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2230385A1 (fr) * 2008-01-16 2010-09-22 Mitsubishi Heavy Industries, Ltd. Pale de rotor de turbine
EP2230385A4 (fr) * 2008-01-16 2011-03-16 Mitsubishi Heavy Ind Ltd Pale de rotor de turbine
EP2354456A3 (fr) * 2009-12-30 2011-12-21 General Electric Company Accessoire et procédé d'assemblage d'aubes de turbine articulées
FR3008448A1 (fr) * 2013-07-15 2015-01-16 Snecma Dispositif de depose pour aubes
WO2015007979A1 (fr) * 2013-07-15 2015-01-22 Snecma Dispositif de dépose pour aubes et procédé de dépose correspondant
US10533434B2 (en) 2013-07-15 2020-01-14 Safran Aircraft Engines Dismantling device for blades and corresponding dismantling method
EP3043029A1 (fr) * 2015-01-12 2016-07-13 General Electric Company Dispositif de montage et procédé d'installation d'aubes de turbines
US10125635B2 (en) 2015-01-12 2018-11-13 General Electric Company Fixture and method for installing turbine buckets
US10851661B2 (en) 2017-08-01 2020-12-01 General Electric Company Sealing system for a rotary machine and method of assembling same

Also Published As

Publication number Publication date
JPH08326504A (ja) 1996-12-10
KR970001851A (ko) 1997-01-24
DE19520274A1 (de) 1996-12-05
US5737816A (en) 1998-04-14
EP0745756B1 (fr) 2000-03-22
DE59604723D1 (de) 2000-04-27
CN1087389C (zh) 2002-07-10
CN1144877A (zh) 1997-03-12

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