EP1970530A1 - Rotor d'une turbomachine thermique et turbomachine thermique - Google Patents

Rotor d'une turbomachine thermique et turbomachine thermique Download PDF

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Publication number
EP1970530A1
EP1970530A1 EP07005079A EP07005079A EP1970530A1 EP 1970530 A1 EP1970530 A1 EP 1970530A1 EP 07005079 A EP07005079 A EP 07005079A EP 07005079 A EP07005079 A EP 07005079A EP 1970530 A1 EP1970530 A1 EP 1970530A1
Authority
EP
European Patent Office
Prior art keywords
rotor
support wheel
tie rod
parts
turbine
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.)
Withdrawn
Application number
EP07005079A
Other languages
German (de)
English (en)
Inventor
Guido Dr. Ahaus
Francois Dr. Benkler
Ulrich Ehehalt
Harald Hoell
Karsten Dr. Kolk
Walter Loch
Harald Nimptsch
Oliver Dr. Schneider
Peter-Andreas Schneider
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
Priority to EP07005079A priority Critical patent/EP1970530A1/fr
Priority to JP2009553093A priority patent/JP5027890B2/ja
Priority to EP08716878A priority patent/EP2118445B1/fr
Priority to US12/530,501 priority patent/US8641365B2/en
Priority to RU2009137604/06A priority patent/RU2419724C1/ru
Priority to CN2008800083276A priority patent/CN101631932B/zh
Priority to PCT/EP2008/051872 priority patent/WO2008110429A1/fr
Priority to AT08716878T priority patent/ATE538287T1/de
Publication of EP1970530A1 publication Critical patent/EP1970530A1/fr
Withdrawn legal-status Critical Current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
    • 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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling

Definitions

  • the invention relates to a rotor of a thermal fluid machine with a number of individual, held together by a tie rod and assembled into a unit rotor parts.
  • the invention further relates to a thermal turbomachine with such a rotor.
  • the thermal turbomachinery includes steam and gas turbines as well as rotary compressors and jet engines. These usually have a rotatably mounted rotor surrounded by a stationary housing.
  • the fixed components of a thermal turbomachine are collectively referred to as a stator.
  • a flow channel extending in the axial direction of the turbomachine for a compressible flow medium is arranged.
  • On the rotor usually in the flow channel projecting and combined into groups of blades or rows of blades blades are attached.
  • the blades serve to drive the rotor shaft by momentum transfer from a hot and pressurized flow medium.
  • the thermal energy of the flow medium is thus converted in its relaxation in mechanical energy that can be used for example to drive an electric generator.
  • a compressor unit and a turbine unit are arranged on a common shaft.
  • the compressor also called a compressor, draws in cold ambient air, compresses it and then feeds it to a combustion chamber where it is burned together with an injected fuel.
  • the hot combustion gases eventually flow under high pressure and at high speed into the turbine unit and drive them. Part of the mechanical energy thus generated is used to drive the compressor, the remaining part being available as usable energy.
  • the rotor of a gas turbine is also referred to as a rotor, which is exposed to a high mechanical and thermal stress. Mainly due to the high temperature of the working medium and the forces acting on the rotor forces during operation of the gas turbine, the rotor component is heavily stressed. Nevertheless, in order to be able to ensure operational safety on the one hand and to keep the manufacturing costs of the runner within acceptable limits on the other hand, a large number of design options have been proposed in the past.
  • a proposed embodiment of the rotor for example, by the production of a part feasible.
  • a production method is comparatively complicated in the manufacturing process.
  • no order-independent prefabrication and no parallel processing of individual parts is possible, resulting in high production throughput times.
  • a larger axial distance between the impeller discs must be accepted in order to be able to work with the corresponding tools.
  • these production-related relatively large distances between the wheels worsen the rotor dynamics.
  • the runner can also be composed of individual rotor parts, wherein the individual rotor parts via a tie rod are held together.
  • the tie rod is guided by an axially extending recess in the rotor parts, whereby the rotor parts can be clamped together.
  • the rotor of the gas turbine is arranged at the end by suitable bearings in the housing of the turbine.
  • vibrations of the rotor component occur whose frequency u. a. from the distance between the two thrust bearings, d. H. is dependent on the free-swinging length of the rotor, in particular of the free-swinging length of the tie rod, in such a construction.
  • With increasing length of the gas turbine and the free-swinging length of the tie rod increases, which causes its natural frequency shifts to a lower level near the rotational frequency of the rotor component. This frequency shift can lead to impermissibly high vibration amplitudes during operation of the gas turbine, which impair the function of the rotor and can lead to damage to the turbine.
  • the invention is therefore based on the object to provide a rotor of the type mentioned, which ensures safe operation of the gas turbine even with increasing overall length. Furthermore, the oscillation amplitudes of the tie rod should be kept as small as possible, in particular in the region of the central hollow shaft.
  • tie rod is supported by the composite of the surrounding rotor components consisting of tie rods, damping cone and discs.
  • the support wheel represents a further supporting rotor component.
  • the invention is based on the consideration that, especially for a reduction of the oscillation of the tie rod this should be supported on the stator component, wherein the thermally induced different expansions of the rotor components should still be compensated.
  • the fact should be taken into account that due to the increasing requirements with respect to the performance of the turbine whose length increases, whereby the natural frequency of the tie rod approaches the operating speed of the gas turbine. This is achieved in that the tie rod is supported by the composite of the surrounding rotor components consisting of tie rods, damping cone and discs.
  • the support wheel represents a further supporting rotor component, wherein the support wheel is preferably connected in the axial direction of the rotor in an area with the tie rod, in which the amplitudes of the vibrations occurring during operation of the turbine reach their maximum values.
  • the support of the tie rod is preferably achieved by the support wheel is non-positively and / or positively connected to the tie rod.
  • the support wheel can be shrunk on the tie rod.
  • This type of connection is particularly suitable, since thus a particularly rigid connection between the support wheel and the tie rod is made possible in a simple manner.
  • the thermally induced different expansions of the rotor components occurring during operation of the gas turbine, in particular between the support wheel and the tie rod, can be compensated in an advantageous manner, preferably by providing at least one of the rotor components with a profile.
  • the connection between the tie rod and the support wheel to be set elastically, such that the difference in volume due to the different heating of the Rotor components is largely compensated.
  • the hub is provided with a convex profile. With such a connection side compliant hub shape, stresses and cracks in the rotor component can be prevented.
  • the support wheel is connected to two adjacently arranged rotor parts by means of a Hirth gearing.
  • a Hirth gearing Using such an axially effective connection, the torques acting on the rotor can be transmitted via the support wheel.
  • a radial guide for receiving different thermal and centrifugal deformations is ensured by means of the Hirth gearing. In particular, thus the occurrence of vibrations during operation of the gas turbine due to a thermally induced non-uniform expansion of the support wheel can be reduced.
  • the support wheel is provided with cooling holes, which are preferably arranged uniformly around the hub.
  • a rib structure is formed due to the recesses introduced for cooling in the support wheel, which allows the flow through a cooling medium.
  • the introduced openings increases the surface of the support wheel, and by means of such formed cooling air openings a trouble transport of the cooling air is made possible within the rotor.
  • the cooling air separation pipes thus realize an improved heat dissipation, and on the other hand, the heat capacity of this rotor component can be reduced.
  • the cooling medium in particular cooling air
  • the tie rod can be guided for a suitable cooling by a number of cooling separation tubes, which divide the channel formed between the tie rod and the rotor parts in a number of sub-cooling channels. This ensures that the cooling of the rotor components in particular the cooling demand of the respective turbine stage can be carried out accordingly.
  • the cooling air separation tubes are divided to receive the support wheel, such that their pointing in the direction of the support wheel ends can be performed in designated provided in the support wheel receiving grooves.
  • the support wheel is preferably in the region of the central hollow shaft, d. H. at the place of maximum deflection of the tie rod in case of possibly occurring Glasankerschwingungen connected to this.
  • this area may be between the compressor stage and the turbine stage. This allows a support of the tie rod to a vibration particularly effective position.
  • the advantages achieved by the invention are, in particular, that a particularly reliable operation of the gas turbine is made possible by the support wheel connected to the tie rod with their increasing overall length.
  • the vibration amplitudes can be kept particularly small by the appropriate support of the tie rod.
  • a targeted increase in the natural frequency of the tie rod with comparatively little effort can be realized through this system.
  • the thermally induced relative movements between the tie rod and trained as a support wheel rotor part can be compensated particularly well.
  • due to the high thermal load of Rotor component necessary cooling ensured by means of a running in the axial direction of the rotor cooling air.
  • FIG. 1 A rotor 2 of a gas turbine with a number of individual, held together by a tie rod 4 and assembled into a unit rotor parts 6 is in FIG. 1 shown.
  • the respective rotor parts 6 are on the connection side provided with symmetrical to the central axis M of the rotor 2 recesses, wherein the resulting contours are formed corresponding to the contours of the respective adjacent rotor part 6, whereby a concentric alignment of the rotor parts 6 to the central axis M is effected.
  • Each of the rotor parts 6 is provided for the passage of the tie rod 4 with an axially extending bore 10, wherein the tie rod is screwed end to a rotor part 6 and thus all interposed rotor parts 6 are held together.
  • the introduced into the rotor parts 6 recesses 8 serve to guide a cooling medium for cooling the rotor components by cooling air over a between the tension rod 4 and the rotor part 6 formed cooling channel is supplied.
  • damping cone and discs is inserted between two rotor parts 6, preferably between a two-part central hollow shaft 11, a support wheel 14, not shown here.
  • the support wheel 14 constitutes a further supporting rotor component.
  • the rotor parts 6 and the support wheel 14 are clamped together by tie rods 4, wherein the support wheel 14 is additionally positively and / or positively connected to the tie rod 4.
  • a serration 18 is provided on both sides of the outer rim of the support wheel 14 on both sides.
  • the consisting of two axial pipe sections middle hollow shaft 11 is then on both sides of the support wheel 14 with a corresponding Hirth toothing.
  • the hub 16 of the support wheel 14 zuganker will a profile with a spherical shape. This can be realized in a particularly simple manner by a centrally inserted into the hub 16 circumferential groove 20 and by the rounding of the front side to the tie rod circumferential edges.
  • This zuganker workede profile of the hub 16 allows compensation occurring during operation of the gas turbine differential deformations of tie rod 4 and support wheel 14. Furthermore, this redistribution of stresses from the center of the hub 16 toward the end faces of the support wheel 14. Further occurs However, increased stress in the region of the end faces is comparatively uncritical, so that the reliability of the gas turbine can be substantially increased by the zuganker motif compliant shape.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP07005079A 2007-03-12 2007-03-12 Rotor d'une turbomachine thermique et turbomachine thermique Withdrawn EP1970530A1 (fr)

Priority Applications (8)

Application Number Priority Date Filing Date Title
EP07005079A EP1970530A1 (fr) 2007-03-12 2007-03-12 Rotor d'une turbomachine thermique et turbomachine thermique
JP2009553093A JP5027890B2 (ja) 2007-03-12 2008-02-15 ガスタービンのロータ
EP08716878A EP2118445B1 (fr) 2007-03-12 2008-02-15 Rotor d'une turbine à gaz
US12/530,501 US8641365B2 (en) 2007-03-12 2008-02-15 Rotor of a gas turbine
RU2009137604/06A RU2419724C1 (ru) 2007-03-12 2008-02-15 Ротор газовой турбины и тепловая лопаточная машина с таким ротором
CN2008800083276A CN101631932B (zh) 2007-03-12 2008-02-15 燃气轮机的转子
PCT/EP2008/051872 WO2008110429A1 (fr) 2007-03-12 2008-02-15 Rotor d'une turbine à gaz
AT08716878T ATE538287T1 (de) 2007-03-12 2008-02-15 Läufer einer gasturbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP07005079A EP1970530A1 (fr) 2007-03-12 2007-03-12 Rotor d'une turbomachine thermique et turbomachine thermique

Publications (1)

Publication Number Publication Date
EP1970530A1 true EP1970530A1 (fr) 2008-09-17

Family

ID=38329568

Family Applications (2)

Application Number Title Priority Date Filing Date
EP07005079A Withdrawn EP1970530A1 (fr) 2007-03-12 2007-03-12 Rotor d'une turbomachine thermique et turbomachine thermique
EP08716878A Not-in-force EP2118445B1 (fr) 2007-03-12 2008-02-15 Rotor d'une turbine à gaz

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP08716878A Not-in-force EP2118445B1 (fr) 2007-03-12 2008-02-15 Rotor d'une turbine à gaz

Country Status (7)

Country Link
US (1) US8641365B2 (fr)
EP (2) EP1970530A1 (fr)
JP (1) JP5027890B2 (fr)
CN (1) CN101631932B (fr)
AT (1) ATE538287T1 (fr)
RU (1) RU2419724C1 (fr)
WO (1) WO2008110429A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2933433A1 (fr) * 2014-04-15 2015-10-21 Siemens Aktiengesellschaft Procédé de montage et/ou de démontage d'une section de rotor d'une turbomachine, dispositif de montage et disque de rotor associés
EP3054089A1 (fr) * 2015-02-05 2016-08-10 Siemens Aktiengesellschaft Rotor creux d'une turbomachine avec bouclier thermique

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FR2930588B1 (fr) 2008-04-24 2010-06-04 Snecma Rotor de compresseur d'une turbomachine comportant des moyens de prelevement d'air centripete
US8180614B2 (en) * 2008-12-31 2012-05-15 Schlumberger Technology Corporation Modeling vibration effects introduced by mud motor
US8517687B2 (en) * 2010-03-10 2013-08-27 United Technologies Corporation Gas turbine engine compressor and turbine section assembly utilizing tie shaft
ITBS20120008A1 (it) * 2012-01-20 2013-07-21 Turboden Srl Metodo e turbina per espandere un fluido di lavoro organico in un ciclo rankine
WO2014014535A2 (fr) * 2012-04-27 2014-01-23 General Electric Company Accélérateur d'air sur le tirant d'assemblage à l'intérieur d'un alésage de disque de turbine
EP2700798A1 (fr) * 2012-08-21 2014-02-26 Siemens Aktiengesellschaft Turbomachine comprenant un rotor et un boîtier
CA2884133A1 (fr) * 2012-09-07 2014-03-13 Siemens Aktiengesellschaft Procede permettant d'assembler ou de desassembler un rotor comportant une pluralite d'elements de rotor pour une turbomachine a ecoulement axial et rotor de ce type
CA2896870C (fr) * 2012-12-31 2019-04-16 Rolls-Royce Corporation Systemes, procedes et appareils permettant une interconnexion de composants rotatifs
EP2826957A1 (fr) * 2013-07-17 2015-01-21 Siemens Aktiengesellschaft Rotor pour une turbomachine thermique
EP2826956A1 (fr) * 2013-07-17 2015-01-21 Siemens Aktiengesellschaft Rotor pour une turbomachine thermique
CN103603693A (zh) * 2013-12-05 2014-02-26 罗亚军 空心轴新动力发动机
KR101509382B1 (ko) * 2014-01-15 2015-04-07 두산중공업 주식회사 댐핑 클램프를 구비한 가스 터빈
DE102015212502A1 (de) * 2015-07-03 2017-01-05 Siemens Aktiengesellschaft Verfahren zum Reinigen einer Radscheibenanordnung und/oder an dieser gehaltener Schaufeln
KR101744411B1 (ko) 2015-10-15 2017-06-20 두산중공업 주식회사 가스터빈의 냉각장치
KR101788413B1 (ko) 2015-12-01 2017-10-19 두산중공업 주식회사 디스크 조립체 및 그를 포함하는 터빈
KR101834647B1 (ko) * 2016-07-07 2018-04-13 두산중공업 주식회사 디스크 조립체 및 그를 포함하는 터빈
EP3269926B1 (fr) * 2016-07-07 2020-10-07 Doosan Heavy Industries & Construction Co., Ltd. Ensemble de disque et turbine le comprenant
KR101794451B1 (ko) 2016-07-07 2017-11-06 두산중공업 주식회사 디스크 조립체 및 그를 포함하는 터빈
KR101772334B1 (ko) 2016-07-07 2017-08-28 두산중공업 주식회사 디스크 조립체 및 그를 포함하는 터빈
CN106121733B (zh) * 2016-08-12 2019-01-11 上海电气燃气轮机有限公司 一种用于重型燃气轮机的混合转子结构及组装方法
CN107269316A (zh) * 2017-08-17 2017-10-20 中南大学 一种燃气轮机中心拉杆式转子的锥形轮盘结构
US10934844B2 (en) 2018-05-31 2021-03-02 Rolls-Royce Corporation Gas turbine engine with fail-safe shaft scheme
CN113978901B (zh) * 2021-11-08 2023-01-31 安徽晋煤中能化工股份有限公司 一种汽轮机转子运输固定装置
WO2024199727A1 (fr) * 2023-03-31 2024-10-03 Nuovo Pignone Tecnologie - S.R.L. Détendeur et cycle thermodynamique utilisant le détendeur

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GB703489A (en) * 1950-03-23 1954-02-03 United Aircraft Corp Improvements in or relating to axial-flow compressor or turbine rotors
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US2798383A (en) * 1955-05-25 1957-07-09 Gen Motors Corp Rotor balancing bolt lock
CH344737A (de) * 1955-11-23 1960-02-29 Svenska Turbinfab Ab Rotor für doppelflutige Axialströmungsmaschine
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JPS5870096A (ja) * 1981-10-23 1983-04-26 Hitachi Ltd 軸流圧縮機のスタツクドロ−タ

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2933433A1 (fr) * 2014-04-15 2015-10-21 Siemens Aktiengesellschaft Procédé de montage et/ou de démontage d'une section de rotor d'une turbomachine, dispositif de montage et disque de rotor associés
WO2015158513A1 (fr) * 2014-04-15 2015-10-22 Siemens Aktiengesellschaft Procédé de montage et/ou de démontage d'une partie de rotor d'une turbomachine, dispositif de montage et disque de rotor associés
EP3054089A1 (fr) * 2015-02-05 2016-08-10 Siemens Aktiengesellschaft Rotor creux d'une turbomachine avec bouclier thermique

Also Published As

Publication number Publication date
US8641365B2 (en) 2014-02-04
US20100166559A1 (en) 2010-07-01
WO2008110429A1 (fr) 2008-09-18
EP2118445B1 (fr) 2011-12-21
ATE538287T1 (de) 2012-01-15
JP5027890B2 (ja) 2012-09-19
RU2419724C1 (ru) 2011-05-27
CN101631932A (zh) 2010-01-20
EP2118445A1 (fr) 2009-11-18
JP2010520967A (ja) 2010-06-17
CN101631932B (zh) 2013-01-16

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