EP3017147B1 - Rotor pour turbine - Google Patents

Rotor pour turbine Download PDF

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Publication number
EP3017147B1
EP3017147B1 EP14734797.5A EP14734797A EP3017147B1 EP 3017147 B1 EP3017147 B1 EP 3017147B1 EP 14734797 A EP14734797 A EP 14734797A EP 3017147 B1 EP3017147 B1 EP 3017147B1
Authority
EP
European Patent Office
Prior art keywords
rotor
tie rod
turbine
groove
coupling element
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.)
Not-in-force
Application number
EP14734797.5A
Other languages
German (de)
English (en)
Other versions
EP3017147A2 (fr
Inventor
Karin COSTAMAGNA
Sascha Dungs
Harald Hoell
Kevin KAMPKA
Karsten Kolk
Ulf LAUDAGE
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
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
Publication of EP3017147A2 publication Critical patent/EP3017147A2/fr
Application granted granted Critical
Publication of EP3017147B1 publication Critical patent/EP3017147B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • 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
    • F01D5/025—Fixing blade carrying members on shafts
    • 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
    • F01D5/026—Shaft to shaft connections
    • 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
    • F01D5/10—Anti- vibration means
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/24—Rotors for turbines
    • 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
    • F05D2240/00—Components
    • F05D2240/60—Shafts
    • 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

Definitions

  • the invention relates to a rotor for a turbine, comprising a number of aligned in the axial direction, via a tie rod rotor components, wherein on one of the rotor components, a circumferentially extending, axially open groove is disposed, wherein in the groove around the tie rod circumferential coupling element is arranged to support the tie rod.
  • a turbine is a turbomachine that converts the internal energy (enthalpy) of a flowing fluid (liquid or gas) into rotational energy and ultimately into mechanical drive energy.
  • the fluid flow is removed by the vortex-free as possible laminar flow around the turbine blades a portion of its internal energy, which passes to the blades of the turbine.
  • the turbine shaft is rotated, the usable power is delivered to a coupled machine, such as a generator.
  • Blades and shaft are parts of the movable rotor or rotor of the turbine, which is arranged within a housing.
  • blades are mounted on the axle. Blades mounted in a plane each form a paddle wheel or impeller. The blades are slightly curved profiled, similar to an aircraft wing. Before each impeller is usually a stator. These vanes protrude from the housing into the flowing medium and cause it to spin. The swirl generated in the stator (kinetic energy) is used in the following impeller to set the shaft on which the impeller blades are mounted in rotation. The stator and the impeller together are called stages. Often several such stages are connected in series.
  • the rotor of a turbine is held together in the axial direction usually by means of a tie rod.
  • the individual rotor components such as turbine disks, rotor disks and hollow shafts are lined up and clamped by a tie rod.
  • the rotor disks are positively connected to each other by a Hirth toothing, so that torque can be transmitted between the individual elements.
  • the tie rod is held by supports which are used in the various compressor and Turbinenradin and in the cooling air separation tube.
  • supports which are used in the various compressor and Turbinenradin and in the cooling air separation tube.
  • annular, conically tapered coupling elements are provided, which engage in an introduced on the respective rotor component, extending in the circumferential direction, and opened in the axial direction groove.
  • the coupling elements are heated during assembly, so that they in the groove of the respective rotor component such.
  • B. a wheel disc are connected to a shrinkage. Due to the conical shape, the coupling elements surround the tie rod flush at their smallest diameter and likewise have a shrinkage there.
  • This object is achieved by the serving for the radial support of the tie rod relative to the other rotor components coupling element is arranged on a holding element connected to the tie rod.
  • the invention is based on the consideration that a particularly stable support of the tie rod would be possible if the fixation of the coupling element, d. H. of the engaging in the respective rotor member part in the groove would no longer be guaranteed solely by shrinking and thus a non-positive connection to the tie rod itself. Instead, a positive connection should be provided instead. This can be achieved with technically simple means, if provided on the tie rod with this holding elements, on which the coupling element is arranged.
  • the coupling element is designed annular. This results in a particularly easy to manufacture and to be mounted support the tie rod. Due to the fact that the coupling element is arranged on a separate holding element on the tie rod, no compelling conical shape is required any longer, but rather the coupling element can form a ring in a simple cylinder jacket shape.
  • the groove in the respective rotor component is advantageously designed to be completely circumferential around the tie rod.
  • the coupling element can be in simple groove shape along the entire circumference in the groove, which improves the stability.
  • a circumferentially extending, in the axial direction to the first groove open towards the second groove is arranged, in which engages the coupling element to the respective holding element.
  • the groove of the retaining element lies the groove in the respective rotor component in the axial direction opposite.
  • the ring-shaped coupling element thus engages on a first axial side in the groove on the rotor component, on the other axial side in the groove of the holding element.
  • a plurality of retaining elements is arranged along the circumference of the tie rod.
  • the number of holding elements can be adjusted as needed: The more holding elements are provided, the better the support of the tie rod. However, a smaller number of support members may be advantageous in terms of weight and assembly complexity.
  • the respective holding element is a nut screwed to the tie rod.
  • a turbine advantageously comprises such a described rotor.
  • the turbine is designed as a gas turbine.
  • the thermal and mechanical stresses are particularly high, so that the described embodiment of the support of the tie rod offers particular advantages in terms of stability.
  • a power plant advantageously comprises such a turbine.
  • the advantages achieved by the invention are in particular that by supporting the tie rod not by shrinking the coupling element on the tie rod itself, but on attachment to a separate retaining element on the tie rod a particularly stable and technically easy to implement avoiding vibrations of the tie rod is made possible.
  • an internal cooling air supply is made possible, since passages remain between the retaining elements.
  • a tie rod support is realized without the need for additional axial securing components. The risk of a temporary transient loss of contact is eliminated.
  • the FIG. 1 shows a turbine 100, here a gas turbine, in a longitudinal partial section.
  • the gas turbine 100 has inside a rotatably mounted around a rotation axis 102 (axial direction) rotor 103, which is also referred to as a turbine runner.
  • a rotation axis 102 axial direction
  • rotor 103 which is also referred to as a turbine runner.
  • the annular combustion chamber 106 communicates with an annular hot gas channel 111.
  • the annular combustion chamber 106 communicates with an annular hot gas channel 111.
  • there form for example, four successive turbine stages 112, the turbine 108.
  • Each turbine stage 112 is formed of two blade rings.
  • a series of vanes 120 follows in the hot gas duct 111 of a row of vanes 115.
  • the vanes 130 are fastened to the stator 143, whereas the rotor blades 120 of a row 125 are attached to the rotor 103 by means of a turbine disk 133.
  • the rotor blades 120 thus form components of the rotor or rotor 103.
  • Coupled to the rotor 103 is a generator or a working machine (not shown).
  • air 135 is sucked and compressed by the compressor 105 through the intake housing 104.
  • the compressed air provided at the turbine-side end of the compressor 105 is supplied to the burners 107 where it is mixed with a fuel.
  • the mixture is then burned to form the working fluid 113 in the combustion chamber 110.
  • the working medium 113 flows along the hot gas channel 111 past the guide vanes 130 and the rotor blades 120.
  • the working medium 113 expands in a pulse-transmitting manner, so that the rotor blades 120 drive the rotor 103 and drive the machine coupled to it.
  • the components exposed to the hot working medium 113 are subject to thermal loads during operation of the gas turbine 100.
  • the guide vanes 130 and rotor blades 120 seen in the flow direction of the working medium 113 first Turbine stage 112 is most thermally stressed in addition to the heat shield bricks lining the annular combustor 106. In order to withstand the temperatures prevailing there, they are cooled by means of a coolant.
  • Each vane 130 has a vane root (not shown here) facing the inner casing 138 of the turbine 108 and a vane head opposite the vane root.
  • the Leitschaufelkopf faces the rotor 103 and fixed to a sealing ring 140 of the stator 143.
  • Each sealing ring 140 encloses the shaft of the rotor 103.
  • the turbine disks 130 and other components not described in more detail, such as hollow shafts are connected via a tie rod 144. To avoid vibrations of the tie rod 144 this is supported on the rotor components, as shown in the schematic diagram of the FIG. 2 is shown.
  • FIG. 2 shows a longitudinal section (with respect to the axis 102) by the tie rod 144 at its radial outer edge.
  • a thread 146 is introduced, which protrudes radially from the tie rod 144.
  • a nut 148 is screwed as a holding element. Analogous combinations of thread 146 and nut 148 are arranged along the circumference of tie rod 144 at regular intervals.
  • the nut 148 has a groove 150, which is open in the axial direction, namely the turbine disk 130 facing.
  • An annular coupling element is arranged in the manner of a tongue and groove connection in the two grooves 150, 152 and thus fixes the tie rod 144 in the radial direction.
  • the turbine disk 130 is fixed by the tension of the tie rod 144, the nut 148 via the thread 146.
  • Appropriate supports may be provided in different axial regions of the tie rod 144 on each rotor component.
  • the nut 148 has a central opening 156 passing through in the axial direction. As well as between the individual nuts 148, cooling air can pass through this opening 156, as a result of which an internal cooling air line for cooling the tie rod 144 is possible.
  • FIG. 3 shows a longitudinal section of the area around the coupling element 154 in detail.
  • the nut 148 here still has a projection 158 which rests against the turbine disk 130 and realizes a stabilization in the axial direction.
  • nut 148 and coupling element 154 are heated. Upon cooling, the nut 148 and coupling member 154 therefore shrink so that movement of the coupling member 154 and the groove 150 toward the axle 102 occurs. As a result, the coupling element 154 rests on the radial inner side of the groove 152 of the turbine disk 130 and on the radial outer side of the groove 150 of the nut 148. This results in a preload that counteracts the centrifugal force generated during operation.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (10)

  1. Rotor (103) pour une turbine (100) comprenant un certain nombre de pièces (130) de rotor, rangées dans la direction axiale et reliées par un tirant (144), une rainure (152), ouverte dans la direction axiale et s'étendant dans la direction périphérique, étant prévue sur l'une des pièces (130) de rotor, un élément (154) de couplage, pour l'appui radial, empêchant les vibrations du tirant et faisant le tour du tirant (144), étant disposé dans la rainure (152), l'élément (154) de couplage étant monté sur un élément (150) de maintien relié au tirant (144).
  2. Rotor (103) suivant la revendication 1,
    dans lequel l'élément (154) de couplage est annulaire.
  3. Rotor (103) suivant l'une des revendications précédentes,
    dans lequel la rainure (152) entoure complètement le tirant (144).
  4. Rotor (103) suivant l'une des revendications précédentes,
    dans lequel, sur l'élément (148) de maintien, est prévue une deuxième rainure (150) s'étendant dans la direction périphérique, ouverte dans la direction axiale en direction de la première rainure (152) et dans laquelle pénètre l'élément (154) de couplage.
  5. Rotor (103) suivant l'une des revendications précédentes,
    dans lequel une pluralité d'éléments (148) de maintien est disposée le long du pourtour du tirant (144).
  6. Rotor (103) suivant l'une des revendications précédentes,
    dans lequel l'élément (148) de maintien est un écrou (148) vissé au tirant (144).
  7. Procédé de fabrication d'un rotor (103) suivant l'une des revendications précédentes,
    dans lequel on monte l'élément (148) de couplage et/ou l'élément (154) de maintien à l'état préchauffé.
  8. Turbine (100) comprenant un rotor (103) suivant l'une des revendications 1 à 6 et/ou un rotor fabriqué suivant la revendication 7.
  9. Turbine (100) suivant la revendication 8, qui est conçue en turbine (100) à gaz.
  10. Centrale électrique ayant une turbine (100) suivant la revendication 8 ou 9.
EP14734797.5A 2013-07-04 2014-06-30 Rotor pour turbine Not-in-force EP3017147B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102013213115.1A DE102013213115A1 (de) 2013-07-04 2013-07-04 Rotor für eine Turbine
PCT/EP2014/063812 WO2015000830A2 (fr) 2013-07-04 2014-06-30 Rotor pour turbine

Publications (2)

Publication Number Publication Date
EP3017147A2 EP3017147A2 (fr) 2016-05-11
EP3017147B1 true EP3017147B1 (fr) 2017-04-12

Family

ID=51062810

Family Applications (1)

Application Number Title Priority Date Filing Date
EP14734797.5A Not-in-force EP3017147B1 (fr) 2013-07-04 2014-06-30 Rotor pour turbine

Country Status (6)

Country Link
US (1) US10174618B2 (fr)
EP (1) EP3017147B1 (fr)
JP (1) JP2016524082A (fr)
CN (1) CN105358797A (fr)
DE (1) DE102013213115A1 (fr)
WO (1) WO2015000830A2 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3293354B1 (fr) * 2016-09-07 2021-04-14 Ansaldo Energia IP UK Limited Élément d'aubage de turbomachine et procédé de montage d'un tel élément
KR101967067B1 (ko) * 2017-10-27 2019-04-09 두산중공업 주식회사 토크튜브 및 이를 포함하는 가스 터빈
KR20220078706A (ko) * 2019-10-18 2022-06-10 지멘스 에너지 글로벌 게엠베하 운트 코. 카게 2개의 로터 디스크들 사이에 배열된 로터 구성 요소를 구비한 로터

Family Cites Families (17)

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Publication number Priority date Publication date Assignee Title
GB858763A (en) * 1957-06-14 1961-01-18 Napier & Son Ltd Rotors for multi-stage axial flow compressors or turbines
US3680979A (en) * 1970-10-07 1972-08-01 Carrier Corp Rotor structure for turbo machines
DE2643886C2 (de) * 1976-09-29 1978-02-09 Kraftwerk Union AG, 4330 Mülheim Gasturbinentäufer in Scheibenbauart
JPS5939903A (ja) * 1982-08-30 1984-03-05 Toshiba Corp 蒸気タ−ビンロ−タ
US5537814A (en) 1994-09-28 1996-07-23 General Electric Company High pressure gas generator rotor tie rod system for gas turbine engine
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
JP3636336B2 (ja) 1996-05-28 2005-04-06 富士電機システムズ株式会社 軸流排気タービン
DE19821889B4 (de) 1998-05-15 2008-03-27 Alstom Verfahren und Vorrichtung zur Durchführung von Reparatur- und/oder Wartungsarbeiten im Innengehäuse einer mehrschaligen Turbomaschine
JP4007062B2 (ja) * 2002-05-22 2007-11-14 株式会社日立製作所 ガスタービン及びガスタービン発電装置
US7470115B2 (en) 2004-07-13 2008-12-30 Honeywell International Inc. Outer diameter nut piloting for improved rotor balance
US7452188B2 (en) * 2005-09-26 2008-11-18 Pratt & Whitney Canada Corp. Pre-stretched tie-bolt for use in a gas turbine engine and method
WO2008012195A1 (fr) 2006-07-24 2008-01-31 Siemens Aktiengesellschaft Procédé pour dévisser une moitié annulaire d'un distributeur de forme globale annulaire hors d'une moitié inférieure de boîtier d'une turbomachine stationnaire à écoulement axial, dispositif de montage, assemblage de dispositif de montage et demi-secteur annulaire auxiliaire
JP5145408B2 (ja) 2008-02-28 2013-02-20 三菱重工業株式会社 ガスタービン及びガスタービンの車室開放方法
US8677591B2 (en) 2008-04-28 2014-03-25 General Electric Company Methods and system for disassembling a machine
US8650885B2 (en) 2009-12-22 2014-02-18 United Technologies Corporation Retaining member for use with gas turbine engine shaft and method of assembly
ITMI20101918A1 (it) * 2010-10-20 2012-04-21 Ansaldo Energia Spa Impianto a turbina a gas per la produzione di energia elettrica, provvisto di un'apparecchiatura per il monitoraggio di parti rotanti
EP2565387A1 (fr) * 2011-08-29 2013-03-06 Siemens Aktiengesellschaft Turbomachine avec un capteur de température

Also Published As

Publication number Publication date
DE102013213115A1 (de) 2015-01-22
JP2016524082A (ja) 2016-08-12
WO2015000830A2 (fr) 2015-01-08
WO2015000830A3 (fr) 2015-02-26
US10174618B2 (en) 2019-01-08
EP3017147A2 (fr) 2016-05-11
CN105358797A (zh) 2016-02-24
US20160130948A1 (en) 2016-05-12

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