US20150247406A1 - Method for assembling and disassembling a rotor having a number of rotor components of an axial flow turbomachine and such a rotor - Google Patents

Method for assembling and disassembling a rotor having a number of rotor components of an axial flow turbomachine and such a rotor Download PDF

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Publication number
US20150247406A1
US20150247406A1 US14/425,016 US201314425016A US2015247406A1 US 20150247406 A1 US20150247406 A1 US 20150247406A1 US 201314425016 A US201314425016 A US 201314425016A US 2015247406 A1 US2015247406 A1 US 2015247406A1
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US
United States
Prior art keywords
rotor
counter
connector
components
bearing
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.)
Abandoned
Application number
US14/425,016
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English (en)
Inventor
Karin Costamagna
Sascha Dungs
Harald Hoell
Henrik Hull
Karsten Kolk
Ulf Laudage
Harald Nimptsch
Peter Schröder
Vyacheslav Veitsman
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.)
Siemens AG
Siemens Energy AB
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Assigned to SIEMENS INDUSTRIAL TURBOMACHINERY A.B. reassignment SIEMENS INDUSTRIAL TURBOMACHINERY A.B. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: HULL, HENRIK
Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: SIEMENS INDUSTRIAL TURBOMACHINERY A.B.
Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: Schröder, Peter, HOELL, HARALD, KOLK, KARSTEN, LAUDAGE, Ulf, VEITSMAN, VYACHESLAV, DUNGS, SASCHA, COSTAMAGNA, Karin, NIMPTSCH, HARALD
Publication of US20150247406A1 publication Critical patent/US20150247406A1/en
Abandoned 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
    • F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/31—Retaining bolts or nuts
    • 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
    • Y10T29/49318—Repairing or disassembling
    • 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

Definitions

  • the invention relates to a rotor for an axial flow turbomachine, comprising a number of multiple disk-shaped or drum-shaped rotor components and at least one tie-rod extending through the rotor components, with a counter-bearing being screwed onto each of the projecting ends of this tie-rod in order to axially clamp the rotor components arranged therebetween.
  • EP 2 415 967 A1 discloses the same for a static gas turbine which likewise comprises a rotor—embodied with a disk construction—with a compressor section and a turbine section, whose respective central tie-rods are screwed into a central shaft connecting the former two to one another.
  • the compressor disks are clamped between a first pre-clamping screw nut—screwed onto the end—and the central shaft, and the turbine disks are also clamped between the central shaft and a second pre-clamping screw nut—also screwed onto the end, wherein the pre-clampings of the compressor section and turbine section are independent of one another.
  • the invention first proposes, when assembling the rotor, clamping the rotor components of a modular rotor of a turbomachine in multiple steps.
  • those rotor components which are arranged in a first rotor section hereinafter called the first rotor components—are clamped between a first counter-bearing and a connector.
  • the counter-bearing and the connector are screwed onto a tie-rod until all the first rotor components arranged therebetween are pressed securely against one another by these two.
  • those rotor components which are to be assigned to a second rotor section hereinafter referred to as second rotor components—are then threaded onto the connector side of the tie-rod.
  • a second counter-bearing is then screwed onto the free end of the tie-rod, with the aid of which counter-bearing the second rotor components and also the first rotor components are clamped between the two counter-bearings.
  • the clamping between the first counter-bearing and the connector is then released, such that once the rotor is assembled the connector participates only slightly or not at all in clamping. All of the rotor components are then clamped by the two counter-bearings, in conjunction with the tie-rod, in the manner of brackets.
  • the rotor comprises, along its longitudinal extent, a first rotor end section, at least a further rotor section and a second rotor end section, wherein the connector, as seen axially, is arranged in one of the further rotor sections.
  • the first rotor section defined for the method, encompasses the first rotor end section and the further rotor section, whereas the second rotor section corresponds to the second rotor end section.
  • the temporary and final clampings are matched to each other such that, with the rotor components being finally clamped between the two counter-bearings, the initial clamping of the counter-bearing and the connection element is at least partially—or entirely—released.
  • a modular rotor having a disk construction should be used, which modular rotor should further also be clamped to the turbine rotor and with the aid of tie-rods.
  • the connector may be designed as a screw nut. Instead, it is of course also conceivable for the connector to be connected in one piece with the tie-rod.
  • the connector has multiple openings for guiding a fluid from one of the rotor (end) sections through to another of the rotor (end) sections.
  • the respective connector has a circumferential shaft collar which is arranged on the circumference and in which are arranged the openings as throughflow openings for cooling fluid.
  • the connector can also be used to create a support for the tie-rod in order to reduce vibrations when the turbomachine is in operation. To that end, only a radial support for at least one of the rotor components at the relevant connector is necessary.
  • the rotor is designed as a gas turbine rotor
  • the first rotor end section is designed as a compressor rotor
  • the further rotor section is designed as a central rotor section
  • the second rotor end section is designed as a turbine rotor.
  • the central rotor section can be formed solely from a hollow shaft or from multiple bladeless rotor disks and the rotor end sections from rotor disks.
  • FIG. 5 shows, in a perspective representation, the connection element of FIG. 4 and
  • the rotor 10 comprises a number of rotor disks 12 , which in this case are also termed disk-shaped rotor components 14 .
  • the rotor 10 further comprises a drum-shaped rotor component 16 which in the exemplary embodiment is termed central hollow shaft 18 .
  • central hollow shaft 18 there is also a forward hollow shaft 22 , screwed onto the end of a tie-rod 20 , and a rear hollow shaft 24 , screwed on at the opposite end.
  • the forward hollow shaft 22 is also termed first counter-bearing 26 and the rear hollow shaft 24 is termed second counter-bearing 28 .
  • connection 34 formed as a screw nut 35 is screwed onto the tie-rod 20 within the rotor 10 in order to clamp, only while the rotor is being assembled or dismantled, the rotor components 14 , 16 arranged in a section of the rotor 10 .
  • FIGS. 2 to 4 show, in longitudinal section, a detail from the transition region between the further rotor section 40 and the second rotor end section 42 .
  • the screw nut 35 is screwed onto the tie-rod 20 .
  • the central hollow shaft 18 is arranged radially adjacent to the screw nut 35 .
  • the screw nut 35 has a conical face 50 whose gradient matches an inward-oriented face 52 of the central hollow shaft 18 .
  • a smaller shaft collar 54 is provided centrally between the two screw openings 37 of the screw nut 35 , the side face 56 of which collar bears against a side face 58 —parallel thereto—of the central hollow shaft 18 .
  • the first counter-bearing 26 is first screwed onto the end of the tie-rod 20 .
  • This subassembly is then set upright such that the individual disk-shaped or drum-shaped rotor components 14 , 16 can be placed onto the first counter-bearing 26 from above.
  • the screw nut 35 is screwed onto that end of the tie-rod element 30 which has been left free, until the rotor components 14 , 16 located between the screw nut 35 and the first counter-bearing 26 are clamped together.
  • the rotor disks 12 provided for the turbine rotor 48 are then threaded on and placed onto the turbine-side end of the tie-rod 20 from above.
  • the second counter-bearing 28 is screwed onto that end of the tie-rod 20 which has been left free.
  • the entire tie-rod 20 is stretched elastically such that the clamping of the screw nut 35 or, as the case may be, of the connector 34 and the first counter-bearing 26 is released.
  • FIG. 4 shows a further exemplary embodiment for clamping the rotor components 14 , 16 between a first counter-bearing (not shown in FIG. 4 ) and the connector 34 .
  • the connector 34 is again configured as a screw nut 35 with two mutually opposite screw openings 37 .
  • a larger shaft collar 54 is provided on the outer circumference, centrally between the screw openings 37 , in which collar are provided, distributed evenly about the circumference, openings 64 for guiding through a cooling fluid.
  • the two parallel side faces 56 of the shaft collar 54 transition, via a radius, into curved, tapered flanks 57 which end at the screw openings 37 .
  • FIG. 5 shows this screw nut 35 with the screw opening 37 and four evenly distributed throughflow openings 64 in a perspective representation.
  • FIGS. 2 to 6 all show gas turbine rotors 10 in which the second counter-bearing 28 is not yet screwed onto the second tie-rod element 32 , such that only those rotor components 14 , 16 depicted to the left of the screw nut 35 in FIGS. 2 to 6 are clamped with the first counter-bearing 26 and those rotor components 14 , 16 depicted to the right thereof are not.
  • the invention thus relates to a rotor 10 for an axial flow turbomachine, comprising a number of multiple disk-shaped or drum-shaped rotor components 14 , 16 and at least one pin-shaped tie-rod 20 extending through the rotor components 14 , 16 , with a counter-bearing 26 , 28 being screwed onto each of the projecting ends of this tie-rod in order to axially clamp the rotor components 14 , 16 arranged therebetween.
  • a connector 34 is screwed onto the tie-rod 20 between the two counter-bearings 26 , 28 , by means of which connector 34 , after one of the two counter-bearings 28 has been released, those rotor components 14 , 16 arranged between the connector 34 and the other of the two counter-bearings 26 are clamped together.

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)
US14/425,016 2012-09-07 2013-09-06 Method for assembling and disassembling a rotor having a number of rotor components of an axial flow turbomachine and such a rotor Abandoned US20150247406A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE102012215886.3 2012-09-07
DE102012215886 2012-09-07
PCT/EP2013/068507 WO2014037523A1 (de) 2012-09-07 2013-09-06 Verfahren zum zusammensetzen bzw. lösen eines eine anzahl von rotorbauteilen umfassenden rotors einer axial durchströmbaren turbomaschine und derartiger rotor

Publications (1)

Publication Number Publication Date
US20150247406A1 true US20150247406A1 (en) 2015-09-03

Family

ID=49182221

Family Applications (2)

Application Number Title Priority Date Filing Date
US14/425,016 Abandoned US20150247406A1 (en) 2012-09-07 2013-09-06 Method for assembling and disassembling a rotor having a number of rotor components of an axial flow turbomachine and such a rotor
US14/425,013 Abandoned US20150260044A1 (en) 2012-09-07 2013-09-06 Rotor for an axial flow turbomachine and double nut for connecting two tie-rod elements

Family Applications After (1)

Application Number Title Priority Date Filing Date
US14/425,013 Abandoned US20150260044A1 (en) 2012-09-07 2013-09-06 Rotor for an axial flow turbomachine and double nut for connecting two tie-rod elements

Country Status (12)

Country Link
US (2) US20150247406A1 (enrdf_load_stackoverflow)
EP (2) EP2880264A1 (enrdf_load_stackoverflow)
JP (2) JP2015527534A (enrdf_load_stackoverflow)
KR (2) KR20150047509A (enrdf_load_stackoverflow)
CN (2) CN104619954B (enrdf_load_stackoverflow)
BR (2) BR112015004983A2 (enrdf_load_stackoverflow)
CA (2) CA2884126A1 (enrdf_load_stackoverflow)
IN (2) IN2015DN00890A (enrdf_load_stackoverflow)
MX (1) MX2015002944A (enrdf_load_stackoverflow)
RU (2) RU2015112596A (enrdf_load_stackoverflow)
SA (2) SA515360112B1 (enrdf_load_stackoverflow)
WO (2) WO2014037521A1 (enrdf_load_stackoverflow)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10718212B2 (en) 2015-12-16 2020-07-21 Siemens Aktiengesellschaft Rotor for a turbomachine

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2927425A1 (de) * 2014-03-31 2015-10-07 Siemens Aktiengesellschaft Läufer für eine Gasturbine mit Verdrehsicherung für eine Wellenmutter
EP2980354A1 (de) * 2014-07-30 2016-02-03 Siemens Aktiengesellschaft Läufer für eine Gasturbine und zugehörige Gasturbine
RU2567887C1 (ru) * 2014-08-08 2015-11-10 Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг России) Ротор компрессора газотурбинного двигателя
DE102014220294A1 (de) 2014-10-07 2016-04-07 Siemens Aktiengesellschaft Spannsystem zum Vorspannen eines Zugangs einer Strömungskraftmaschine
IT201600123382A1 (it) * 2016-12-05 2018-06-05 Ansaldo Energia Spa Metodo e dispositivo per controllare il posizionamento di almeno un disco rotorico attorno ad un tirante di un rotore di una turbina a gas
US11131195B2 (en) 2019-03-14 2021-09-28 Raytheon Technologies Corporation Tie shaft assembly for a gas turbine engine
US11105204B2 (en) 2019-06-11 2021-08-31 Pratt & Whitney Canada Corp. Turbine assembly

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US3970398A (en) * 1975-08-04 1976-07-20 United Technologies Corporation Shaft coupling
GB2452932A (en) * 2007-09-19 2009-03-25 Siemens Ag Turbine or turbomachine with axial shaft-mounted compressor and turbine blades
US20100272504A1 (en) * 2005-11-17 2010-10-28 Schlumberger Technology Corporation Pump apparatus, systems and methods
US8186939B2 (en) * 2009-08-25 2012-05-29 Pratt & Whitney Canada Corp. Turbine disc and retaining nut arrangement
US8794923B2 (en) * 2010-10-29 2014-08-05 United Technologies Corporation Gas turbine engine rotor tie shaft arrangement
US9279327B2 (en) * 2010-08-03 2016-03-08 Siemens Aktiengesellschaft Gas turbine engine comprising a tension stud
US20160319820A1 (en) * 2013-12-18 2016-11-03 Nuovo Pignone Srl Method of assembling a set of impellers through tie rods impeller and turbomachine

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GB308260A (en) * 1928-03-20 1930-06-16 Albert Paul Streit Improvements in locking stretchers for tensioning wires and the manufacture thereof
JPS6058680U (ja) * 1983-09-29 1985-04-24 ジャパンライフ株式会社 プラグとソケット
FR2640014A1 (fr) * 1988-12-01 1990-06-08 Linz Emile Tendeur de cables
US5454662A (en) * 1993-11-23 1995-10-03 Animal Enclosure Systems Connector for coupling the pipes of a pipe corral
JP3733573B2 (ja) * 1995-03-03 2006-01-11 石川島播磨重工業株式会社 ガスタービンとその組立方法
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US7409819B2 (en) * 2004-10-29 2008-08-12 General Electric Company Gas turbine engine and method of assembling same
US7584621B2 (en) * 2005-08-05 2009-09-08 Siemens Energy, Inc. Radially expanding turbine engine exhaust cylinder interface
DE102005052819A1 (de) * 2005-11-05 2007-05-10 Mtu Aero Engines Gmbh Turbomaschine, insbesondere Gasturbine
JP4801564B2 (ja) * 2006-11-17 2011-10-26 三菱重工業株式会社 締結装置
EP1970530A1 (de) * 2007-03-12 2008-09-17 Siemens Aktiengesellschaft Läufer einer thermischen Strömungsmaschine sowie thermische Strömungsmaschine

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Publication number Priority date Publication date Assignee Title
US3970398A (en) * 1975-08-04 1976-07-20 United Technologies Corporation Shaft coupling
US20100272504A1 (en) * 2005-11-17 2010-10-28 Schlumberger Technology Corporation Pump apparatus, systems and methods
GB2452932A (en) * 2007-09-19 2009-03-25 Siemens Ag Turbine or turbomachine with axial shaft-mounted compressor and turbine blades
US8186939B2 (en) * 2009-08-25 2012-05-29 Pratt & Whitney Canada Corp. Turbine disc and retaining nut arrangement
US9279327B2 (en) * 2010-08-03 2016-03-08 Siemens Aktiengesellschaft Gas turbine engine comprising a tension stud
US8794923B2 (en) * 2010-10-29 2014-08-05 United Technologies Corporation Gas turbine engine rotor tie shaft arrangement
US20160319820A1 (en) * 2013-12-18 2016-11-03 Nuovo Pignone Srl Method of assembling a set of impellers through tie rods impeller and turbomachine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10718212B2 (en) 2015-12-16 2020-07-21 Siemens Aktiengesellschaft Rotor for a turbomachine

Also Published As

Publication number Publication date
CN104603396B (zh) 2016-08-24
BR112015004993A2 (pt) 2017-07-04
EP2888448A1 (de) 2015-07-01
IN2015DN00890A (enrdf_load_stackoverflow) 2015-06-12
WO2014037523A1 (de) 2014-03-13
JP2015527534A (ja) 2015-09-17
SA515360111B1 (ar) 2016-02-24
JP2015528539A (ja) 2015-09-28
KR20150047508A (ko) 2015-05-04
MX2015002944A (es) 2015-06-02
CA2884126A1 (en) 2014-03-13
CA2884133A1 (en) 2014-03-13
RU2015109757A (ru) 2016-10-27
SA515360112B1 (ar) 2015-12-20
WO2014037521A1 (de) 2014-03-13
RU2015112596A (ru) 2016-10-27
CN104603396A (zh) 2015-05-06
EP2880264A1 (de) 2015-06-10
BR112015004983A2 (pt) 2017-07-04
CN104619954A (zh) 2015-05-13
IN2015DN01253A (enrdf_load_stackoverflow) 2015-06-26
CN104619954B (zh) 2016-08-24
US20150260044A1 (en) 2015-09-17
KR20150047509A (ko) 2015-05-04

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AS Assignment

Owner name: SIEMENS AKTIENGESELLSCHAFT, GERMANY

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:SIEMENS INDUSTRIAL TURBOMACHINERY A.B.;REEL/FRAME:035191/0107

Effective date: 20150126

Owner name: SIEMENS INDUSTRIAL TURBOMACHINERY A.B., SWEDEN

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:HULL, HENRIK;REEL/FRAME:035191/0098

Effective date: 20150126

Owner name: SIEMENS AKTIENGESELLSCHAFT, GERMANY

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:COSTAMAGNA, KARIN;DUNGS, SASCHA;HOELL, HARALD;AND OTHERS;SIGNING DATES FROM 20150212 TO 20150223;REEL/FRAME:035191/0187

STCB Information on status: application discontinuation

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