US20150260044A1 - Rotor for an axial flow turbomachine and double nut for connecting two tie-rod elements - Google Patents

Rotor for an axial flow turbomachine and double nut for connecting two tie-rod elements Download PDF

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Publication number
US20150260044A1
US20150260044A1 US14/425,013 US201314425013A US2015260044A1 US 20150260044 A1 US20150260044 A1 US 20150260044A1 US 201314425013 A US201314425013 A US 201314425013A US 2015260044 A1 US2015260044 A1 US 2015260044A1
Authority
US
United States
Prior art keywords
rotor
tie
counter
rod
connector
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
US14/425,013
Other languages
English (en)
Inventor
Karin Costamagna
Sascha Dungs
Harald Hoell
Henrik Hull
Karsten Kolk
Ulf Laudage
Harald Nimptsch
Peter Schroder
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
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 AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: NIMPTSCH, HARALD, COSTAMAGNA, Karin, DUNGS, SASCHA, HOELL, HARALD, KOLK, KARSTEN, LAUDAGE, Ulf, Schröder, Peter, VEITSMAN, VYACHESLAV
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.
Publication of US20150260044A1 publication Critical patent/US20150260044A1/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.
  • Such rotors are very well known from the comprehensive available prior art relating to static gas turbines.
  • a rotor of the type mentioned in the introduction is shown in the book “Stationare Gasturbinen” [“Static Gas Turbines”] (Eds Christoph Lechner and Jorg Seume), on page 629 .
  • the rotor is designed as what is termed a disk construction, wherein the rotor disks bear blades, either for the compressor or for the turbine unit of the gas turbine, on their outer circumference.
  • a central hollow shaft as a drum-shaped component is arranged between the compressor disks and the turbine disks.
  • a central tie-rod extends through all the rotor components and, with the aid of two counter-bearings, the forward hollow shaft and the rear hollow shaft, clamps together the rotor components arranged between these two hollow shafts.
  • the tie-rod is stretched elastically up to its yield point, thus clamping together the individual rotor components.
  • tie-rods wherein for example twelve tie-rods are arranged evenly distributed at the same radius.
  • the multi-part tie-rod comprises two tension sleeves and a compression sleeve.
  • the invention has an object of proposing an alternative construction of rotors for an axial flow turbomachine.
  • the invention has a further object of providing the components necessary therefor.
  • the object relating to the rotor may be achieved with a rotor according to the features of the claims.
  • the object relating to the components may be achieved with a double nut according to the features of the claims.
  • tie-rods differs from the current embodiment of tie-rods in that the latter are of one-piece design. According to aspects of the invention, it is now provided that the tie-rod or tie-rods is or are divided axially into at least two tie-rod elements, wherein the directly adjacent tie-rod elements are in each case releasably connected to one another by a connector.
  • 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 connector and one of the rotor components are configured such that, after the counter-bearing arranged on the second rotor end section has been released, the connector adjacent to the second rotor end section, with the counter-bearing arranged on the first rotor end section, clamps together the rotor components arranged therebetween.
  • a particular advantage of this configuration is that, in a first assembly step, those rotor components which are threaded onto the first tie-rod element can already be clamped by one of the two counter-bearings and the connector, although the rotor is not yet completely stocked with rotor components. Only once the second or further tie-rod element has been attached are the further disk-shaped or drum-shaped rotor components to be threaded thereon, after which the second counter-bearing can then be screwed onto the end of the second or further tie-rod element, whereby all the disk-shaped or drum-shaped rotor components of the rotor can finally be clamped together.
  • the clamping which acts in the interim from one of the two counter-bearings and the connector on a part of the disk-shaped or drum-shaped rotor components is then released again.
  • the elastic stretching characteristics of the two tie-rod elements are matched to each other such that, with the rotor components being clamped between the two counter-bearings, the initial clamping of the counter-bearing and the connector is at least partially—or entirely—released.
  • the connector is designed as a screw nut into which are screwed the mutually opposing ends of axially adjacent tie-rod elements.
  • a tie-rod element can also have, at one end, an internal thread as the connection for screwing onto another tie-rod element.
  • 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.
  • the double nut for connecting two tie-rod elements has, centrally between the two screw openings, an inward-oriented ring or a separating web which prevents the tie-rod elements from being screwed too far into the double nut.
  • FIG. 1 shows a partial longitudinal section through a rotor according to the invention for a static axial flow turbomachine
  • FIG. 2 shows a detail from the longitudinal section of FIG. 1 , in the region of two mutually connected tie-rod elements;
  • FIG. 3 shows the same detail of FIG. 2 , according to an alternative exemplary embodiment
  • FIG. 4 shows a connection element for connecting two tie-rod elements with a shaft collar arranged at the circumference
  • FIG. 5 shows, in a perspective representation, the connection element of FIG. 4 and
  • FIG. 6 shows a connection element bearing radially against the rotor component, in the longitudinal section of FIG. 2 .
  • FIG. 1 shows a partial longitudinal section through the rotor 10 of an axial flow turbomachine.
  • the rotor 10 is configured as a gas turbine rotor, wherein the remaining constituents of the gas turbine are not represented in more detail here.
  • the construction of the rotor 10 is fundamentally modular and is to be termed disk construction.
  • 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 .
  • the two counter-bearings 26 , 28 clamp the rotor components 14 , 16 together and press them securely against one another. In order to achieve this, the entire tie-rod 20 is stretched elastically by the two counter-bearings 26 , 28 .
  • the tie-rod 20 comprises two separately manufactured tie-rod elements 30 , 32 .
  • the tie-rod 20 also comprises a connector 34 which releasably connects the two one-piece tie-rod elements 30 , 32 to one another.
  • the connector 34 is designed as a screw nut or as a double nut which has, centrally between its two screw openings 37 ( FIG. 5 ), an inward-oriented ring 36 .
  • the rotor 10 can theoretically be split axially into a first rotor end section 38 , a further rotor section 40 and a second rotor end section 42 , wherein the connector 34 , seen axially, is arranged in the further rotor section 40 .
  • the first rotor end section 38 is designed as a compressor rotor 44
  • the second rotor end section 42 is designed as a turbine rotor 48 .
  • a combustion chamber of the gas turbine is arranged radially outside the rotor 10 .
  • FIGS. 2 , 3 and 4 show various exemplary embodiments.
  • FIGS. 2 , 3 and 4 show various exemplary embodiments.
  • 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 .
  • Represented are the two tie-rod elements 30 and 32 and, as connector 34 , a double nut 35 connecting the two ends of the former to one another.
  • the central hollow shaft 18 is arranged radially adjacent to the double nut 35 .
  • the double 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 double 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 element 30 .
  • 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 double nut 35 is screwed onto that end of the tie-rod element 30 which has been left free, wherein in the process the rotor components 14 , 16 located between the double nut 35 and the first counter-bearing 26 are clamped together.
  • the second tie-rod element 32 is then screwed into the double nut 35 , after which the rotor disks 12 provided for the turbine rotor 48 can be threaded on and placed onto the second tie-rod element 32 from above. Finally, the second counter-bearing 28 is screwed onto that end of the tie-rod element 32 which has been left free. In so doing, the entire tie-rod 20 is stretched elastically such that the clamping of the double nut 35 or, as the case may be, of the connector 34 and the first counter-bearing 26 is released.
  • axial bores 60 can be provided both in the central hollow shaft 18 and in the double nut 35 , by means of which bores a cooling device can be guided from one rotor (end) section to another rotor (end) section.
  • FIG. 3 shows the same detail as FIG. 2 , but in which the construction for axially clamping in the region of the double nut 35 and of the central hollow shaft 18 is slightly modified in comparison with the construction of FIG. 2 .
  • the radial overlap between the double nut and the central hollow shaft 18 is achieved here with the use of a sleeve 62 which is arranged therebetween and is provided with a flange.
  • 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 double 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 double 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 double 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.
  • the tie-rod 20 comprises at least two axially adjacent tie-rod elements 30 , 32 which are in each case releasably connected to one another by a connector 34 .

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

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE102012215886 2012-09-07
DE102012215886.3 2012-09-07
PCT/EP2013/068505 WO2014037521A1 (de) 2012-09-07 2013-09-06 Rotor für eine axial durchströmbare turbomaschine und doppelmutter zum verbinden zweier zugankerelemente

Publications (1)

Publication Number Publication Date
US20150260044A1 true US20150260044A1 (en) 2015-09-17

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 Before (1)

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

Country Status (12)

Country Link
US (2) US20150247406A1 (ko)
EP (2) EP2880264A1 (ko)
JP (2) JP2015528539A (ko)
KR (2) KR20150047509A (ko)
CN (2) CN104619954B (ko)
BR (2) BR112015004983A2 (ko)
CA (2) CA2884126A1 (ko)
IN (2) IN2015DN00890A (ko)
MX (1) MX2015002944A (ko)
RU (2) RU2015112596A (ko)
SA (2) SA515360111B1 (ko)
WO (2) WO2014037523A1 (ko)

Cited By (2)

* 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
US11105204B2 (en) 2019-06-11 2021-08-31 Pratt & Whitney Canada Corp. Turbine assembly

Families Citing this family (6)

* 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

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US7584621B2 (en) * 2005-08-05 2009-09-08 Siemens Energy, Inc. Radially expanding turbine engine exhaust cylinder interface
US20120107098A1 (en) * 2010-10-29 2012-05-03 United Technologies Corporation Gas turbine engine rotor tie shaft arrangement

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US7584621B2 (en) * 2005-08-05 2009-09-08 Siemens Energy, Inc. Radially expanding turbine engine exhaust cylinder interface
US20120107098A1 (en) * 2010-10-29 2012-05-03 United Technologies Corporation Gas turbine engine rotor tie shaft arrangement

Cited By (2)

* 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
US11105204B2 (en) 2019-06-11 2021-08-31 Pratt & Whitney Canada Corp. Turbine assembly

Also Published As

Publication number Publication date
CN104619954B (zh) 2016-08-24
BR112015004993A2 (pt) 2017-07-04
WO2014037523A1 (de) 2014-03-13
EP2888448A1 (de) 2015-07-01
CN104603396A (zh) 2015-05-06
IN2015DN01253A (ko) 2015-06-26
RU2015112596A (ru) 2016-10-27
BR112015004983A2 (pt) 2017-07-04
SA515360112B1 (ar) 2015-12-20
MX2015002944A (es) 2015-06-02
KR20150047508A (ko) 2015-05-04
IN2015DN00890A (ko) 2015-06-12
EP2880264A1 (de) 2015-06-10
WO2014037521A1 (de) 2014-03-13
JP2015527534A (ja) 2015-09-17
KR20150047509A (ko) 2015-05-04
CA2884126A1 (en) 2014-03-13
CN104603396B (zh) 2016-08-24
CN104619954A (zh) 2015-05-13
RU2015109757A (ru) 2016-10-27
CA2884133A1 (en) 2014-03-13
US20150247406A1 (en) 2015-09-03
SA515360111B1 (ar) 2016-02-24
JP2015528539A (ja) 2015-09-28

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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:035190/0992

Effective date: 20150316

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

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:HULL, HENRIK;REEL/FRAME:035190/0961

Effective date: 20150203

Owner name: SIEMENS AKTIENGESELLSCHAFT, GERMANY

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:COSTAMAGNA, KARIN;DUNGS, SASCHA;HOELL, HARALD;AND OTHERS;SIGNING DATES FROM 20150120 TO 20150124;REEL/FRAME:035190/0910

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION