EP1577493A1 - Strömungsmaschine und Rotor für eine Strömungsmaschine - Google Patents

Strömungsmaschine und Rotor für eine Strömungsmaschine Download PDF

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Publication number
EP1577493A1
EP1577493A1 EP04006393A EP04006393A EP1577493A1 EP 1577493 A1 EP1577493 A1 EP 1577493A1 EP 04006393 A EP04006393 A EP 04006393A EP 04006393 A EP04006393 A EP 04006393A EP 1577493 A1 EP1577493 A1 EP 1577493A1
Authority
EP
European Patent Office
Prior art keywords
rotor
rings
compressor
turbomachine
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Withdrawn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
EP04006393A
Other languages
German (de)
English (en)
French (fr)
Inventor
Harald Hoell
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 EP04006393A priority Critical patent/EP1577493A1/de
Priority to EP14002196.5A priority patent/EP2787168B1/de
Priority to RU2006136413/06A priority patent/RU2347912C2/ru
Priority to JP2007503243A priority patent/JP4722120B2/ja
Priority to EP05715935.2A priority patent/EP1725741B1/de
Priority to PCT/EP2005/002559 priority patent/WO2005093219A1/de
Priority to CN2005800085028A priority patent/CN101010486B/zh
Priority to US10/593,030 priority patent/US7585148B2/en
Publication of EP1577493A1 publication Critical patent/EP1577493A1/de
Withdrawn legal-status Critical Current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
    • F01D5/026—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
    • 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
    • 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
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
    • F01D5/043—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type
    • F01D5/048—Form or construction
    • 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
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
    • F01D5/088—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor in a closed cavity
    • 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
    • F05D2260/40—Transmission of power
    • F05D2260/403—Transmission of power through the shape of the drive components
    • F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing

Definitions

  • the invention relates to a rotor for a turbomachine, with a coaxial to its axis of rotation Hollow shaft, which on both sides frontally to two axially supports opposite portions of the rotor and a encloses inner cavity. Furthermore, the invention relates a turbomachine with such a rotor.
  • Figure 3 shows a gas turbine 1, which, along a rotatably mounted about a rotation axis 2 rotor 3, a compressor 5, a combustion chamber 6 and a turbine unit 11 has.
  • vanes 12, 35 on the housing and Blades 15, 37 on the rotor 3 each with the formation of Blade rings 17, 19, 36, 38 attached.
  • a vane ring 19, 36 forms with the blade ring 17, 38 a Compressor 21 and a turbine stage 34, wherein a plurality Stages are connected in series.
  • the blades 15 a ring 17, 38 are on the rotor 3 by means of an annular, centrally perforated disc 26, 39 attached.
  • central tie rod 7 By the central opening extends in the axial direction central tie rod 7, the turbine disks 39 and Compressor discs 26 clamped together. Furthermore, to Bridging caused by the combustion chamber 6 Distance between compressor 5 and turbine unit 11 between the compressor disk 26 of the last compressor stage 21 and the turbine disk 39 of the first turbine stage 34 a hollow shaft 13 is arranged.
  • the compressor 5 sucks ambient air and compacts them.
  • the compressed air is mixed with a fuel and fed to the combustion chamber 6, in which the mixture to a hot working medium M is burned.
  • the latter flows from the combustion chamber 6 in the Turbine unit 11 and drives by means of the blades 15 the rotor 3 of the gas turbine 1, which the compressor 5 and a work machine, for example, drives a generator.
  • the hollow shaft has the required for the compression of the ambient air in the compressor Energy from the turbine disk of the first turbine stage to the compressor disk of the last compressor stage transfer.
  • combustion chamber is located radially adjacent to the hollow shaft the gas turbine, which this axial region of the rotor Operation may heat unacceptably.
  • too thermal stresses occur which the strength like also can weaken stiffness of the hollow shaft, so that the occurring mechanical stress premature fatigue of the material of the hollow shaft can cause.
  • the object of the invention is therefore to provide a rotor for a Specify turbomachine, which has a longer life and a lower susceptibility to mechanical defects having. It is another object of the invention, this a Specify turbomachine.
  • the invention with the above Rotor mentioned that the hollow shaft in the axial direction of the Rotor is formed of several adjacent rings and that the contiguous and the sections adjacent rings limit the cavity to the outside.
  • the invention is based on the consideration that both mechanically and thermally highly loaded and previously one-piece Hollow shaft through several contiguous rings is replaced. Through this fundamental constructive Reshaping can be the mechanical stresses reduce considerably. In the area of rings with high Material temperatures due to the radially outward arranged combustion chamber, the voltages and reduces the resulting creep deformations. As a result, the life of each ring is greater than that of one-piece hollow shaft.
  • the one-piece hollow shaft by transmission of Energy required by the compressor over its axial length especially stressed on torsion.
  • the axial length of a ring with respect to the one-piece Hollow shaft greatly shortened, making the ring essential is less subject to torsion. Therefore be with the Invention further reduces the mechanical loads.
  • the rings cause a better thermal Isolation of the cavity with respect to a radially further outside lying outside area, allowing colder air in the cavity pending the surfaces of the component. This will be the thermal stress of the rings further reduced, which is a higher mechanical load allows.
  • 26NiCrMo26145mod used for the rings can be compared to that of the one-piece hollow shaft from the prior art.
  • the rotor at least one tie rod running parallel to the axis of rotation on.
  • the sections of the rotor are each by a Was formed, wherein the at least one tie rod for Bracing the discs and the rings through them extends.
  • the tie rod extends centrally through the discs and through the rings.
  • the centric to the axis of rotation arranged tie rods the stacked rings and discs of the Compressor and the turbine unit tense and at the same time used for axial and radial bearings of the rotor become.
  • the rotor a plurality of spaced apart from the axis of rotation tie rods, which through the discs and the rings.
  • the application the multi-piece hollow shaft is thus also on Rotors applicable, which the tension with several Tie rod provides.
  • each has Ring and each section form-fitting means of transmission the torque of the rotor of one of the two sections to the opposite section.
  • One as Slip known lossy relative movement in the circumferential direction between the immediately adjacent rings or between a ring and a section can thus be effective be avoided.
  • the means for transmitting the Torque at the ends of the ring and the Sections as spur toothing in the manner of a Hirth toothing educated This positive engagement allows a slip-free operation of the rotor.
  • one of the two disks as a compressor disk and the other as Turbine disk is formed, which is used to compact the sucked ambient air at the compressor required Power lossless from the turbine unit to the compressor transmitted by means of the interposed rings.
  • each ring is I-shaped in cross-section formed, wherein the web of the I-shape in the radial direction of the Rotor runs.
  • At each end of the dock is an in Arranged axially extending flange, the having frontal areas, where the means for Transmission of the torque are provided.
  • the I-shaped Cross-section allows a particularly stiff, lightweight and mechanically resilient design of the ring with enough large end faces to provide the spur toothing.
  • the cavity in the axial direction of a cooling medium flow through.
  • the Sealants can be attached to the flanges of the rings be provided on which no means of transmission of the Torque are provided.
  • a flange of the ring in its radial material thickness comparatively wide be designed, which then transmits the torque, and the other flange be designed comparatively narrow, the then only for sealing the cavity to the outside serves.
  • the cooling air cools the rings so that the reduced mean component temperature.
  • the invention leads to the solution of the above-mentioned Turbomachine directed task, the rotor after one of claims 1 to 9 is formed.
  • the Turbomachine is designed as a gas turbine and in the the gas turbine along the rotor sequentially one Compressor, at least one combustion chamber and one Turbine unit, wherein one of the two sections by a compressor disk arranged in the compressor and the other section through one in the turbine unit arranged turbine disk is formed.
  • Figure 1 shows a rotor 3 of a gas turbine 1 with a central tie rod 7 in a longitudinal section in the area between compressor 5 and turbine unit 11. From the Compressor 5 is a flow channel 23 with only the last compressor stage 21 shown. Along the around the Rotary axis 2 rotatable rotor 3 follows a compressor output 25 a diffuser 27 and a combustion chamber 29. The latter has a combustion chamber 31 which enters a hot gas channel 33 a turbine unit 11 opens.
  • the hot gas passage 33 has vanes 35 and further Downstream blades 37 on.
  • the fixed ones Guide vanes 35 are connected to the housing of the gas turbine. 1 whereas the blades 37 are connected to one Turbine disc 39 are attached.
  • the rotor 3 has between the compressor disk 26 and the Turbine disc 39 instead of those known from the prior art integral hollow shaft three axially on each other following rings 43 on.
  • each ring 43 in cross section I-shaped, so that two in the axial direction of the tie rod 7 extending flanges 45, 46 via a radial direction extending web 47 are interconnected.
  • the cavity 51 is annular in cross section.
  • the Hirth gearing At the end faces 55 of the radially outer flanges 45 is arranged the Hirth gearing, with which the Torque of the rotor 3 from the turbine disk 39 via the Rings 43 is passed to the compressor disk 26. To have the end faces 57 of the turbine disk 39 and the Compressor 26 also the Hirth gearing on.
  • the radially inner flanges 46 of the rings 43 indicate their end faces 59 labyrinthine seals 61, which the cavity 51 against the outer region 61st caulk.
  • FIG. 2 shows a rotor 3 of a gas turbine 1 with several Tie rods 8 in a longitudinal section in the area between Compressor 5 and turbine unit 11.
  • FIG. 2 shows the compressor 5, the combustion chamber 6, the turbine unit 11 and the compressor disks 26, Turbine disks 39 and rings 43 assembled rotor 3.
  • the central tie rod 7 shown in FIG in Figure 2 one of a plurality of the axis of rotation 2 spaced decentral tie rods 8 shown.
  • the decentralized tie rod 8 is spaced apart from the axis of rotation 2, that the webs 47 of the rings 43 are penetrated by him. Alternatively could also be the distance chosen so that the tie rod 8 pierces the flanges 45 of the rings.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP04006393A 2004-03-17 2004-03-17 Strömungsmaschine und Rotor für eine Strömungsmaschine Withdrawn EP1577493A1 (de)

Priority Applications (8)

Application Number Priority Date Filing Date Title
EP04006393A EP1577493A1 (de) 2004-03-17 2004-03-17 Strömungsmaschine und Rotor für eine Strömungsmaschine
EP14002196.5A EP2787168B1 (de) 2004-03-17 2005-03-10 Rotor einer Strömungsmaschine mit einer Hohlwelle
RU2006136413/06A RU2347912C2 (ru) 2004-03-17 2005-03-10 Машина для превращения кинетической энергии потока в механическую энергию и ротор для этой машины
JP2007503243A JP4722120B2 (ja) 2004-03-17 2005-03-10 流体機械とそのロータ
EP05715935.2A EP1725741B1 (de) 2004-03-17 2005-03-10 Rotor für eine strömungsmaschine
PCT/EP2005/002559 WO2005093219A1 (de) 2004-03-17 2005-03-10 Strömungsmaschine und rotor für eine strömungsmaschine
CN2005800085028A CN101010486B (zh) 2004-03-17 2005-03-10 涡轮机及涡轮机的转子
US10/593,030 US7585148B2 (en) 2004-03-17 2005-03-10 Non-positive-displacement machine and rotor for a non-positive-displacement machine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04006393A EP1577493A1 (de) 2004-03-17 2004-03-17 Strömungsmaschine und Rotor für eine Strömungsmaschine

Publications (1)

Publication Number Publication Date
EP1577493A1 true EP1577493A1 (de) 2005-09-21

Family

ID=34833623

Family Applications (3)

Application Number Title Priority Date Filing Date
EP04006393A Withdrawn EP1577493A1 (de) 2004-03-17 2004-03-17 Strömungsmaschine und Rotor für eine Strömungsmaschine
EP05715935.2A Active EP1725741B1 (de) 2004-03-17 2005-03-10 Rotor für eine strömungsmaschine
EP14002196.5A Active EP2787168B1 (de) 2004-03-17 2005-03-10 Rotor einer Strömungsmaschine mit einer Hohlwelle

Family Applications After (2)

Application Number Title Priority Date Filing Date
EP05715935.2A Active EP1725741B1 (de) 2004-03-17 2005-03-10 Rotor für eine strömungsmaschine
EP14002196.5A Active EP2787168B1 (de) 2004-03-17 2005-03-10 Rotor einer Strömungsmaschine mit einer Hohlwelle

Country Status (6)

Country Link
US (1) US7585148B2 (ru)
EP (3) EP1577493A1 (ru)
JP (1) JP4722120B2 (ru)
CN (1) CN101010486B (ru)
RU (1) RU2347912C2 (ru)
WO (1) WO2005093219A1 (ru)

Cited By (3)

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Publication number Priority date Publication date Assignee Title
JP2010520967A (ja) * 2007-03-12 2010-06-17 シーメンス アクチエンゲゼルシヤフト ガスタービンのロータ
EP2687680A3 (en) * 2012-07-20 2014-08-27 Kabushiki Kaisha Toshiba Axial turbine and power plant
EP3156593A1 (en) * 2015-10-15 2017-04-19 Doosan Heavy Industries & Construction Co., Ltd. Cooling apparatus of gas turbine

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Publication number Priority date Publication date Assignee Title
US20120014790A1 (en) * 2009-04-01 2012-01-19 Wolfgang Zacharias Rotor for a turbomachine
IT1399904B1 (it) * 2010-04-21 2013-05-09 Nuovo Pignone Spa Rotore impilato con tirante e flangia imbullonata e metodo
US9133729B1 (en) * 2011-06-08 2015-09-15 United Technologies Corporation Flexible support structure for a geared architecture gas turbine engine
US20130264779A1 (en) * 2012-04-10 2013-10-10 General Electric Company Segmented interstage seal system
US9032738B2 (en) * 2012-04-25 2015-05-19 Siemens Aktiengeselischaft Gas turbine compressor with bleed path
KR101665887B1 (ko) * 2015-09-23 2016-10-12 두산중공업 주식회사 가스터빈의 냉각장치
JP6554736B2 (ja) * 2015-10-23 2019-08-07 三菱日立パワーシステムズ株式会社 ガスタービンロータ、ガスタービン、及びガスタービン設備
KR101747550B1 (ko) * 2015-12-01 2017-06-27 두산중공업 주식회사 디스크 조립체 및 그를 포함하는 터빈
KR101788413B1 (ko) * 2015-12-01 2017-10-19 두산중공업 주식회사 디스크 조립체 및 그를 포함하는 터빈
FR3047075B1 (fr) * 2016-01-27 2018-02-23 Safran Aircraft Engines Piece de revolution pour banc d'essai de turbine ou pour turbomachine, banc d'essais de turbines comprenant ladite piece, et procede les utilisant
EP3214266A1 (de) 2016-03-01 2017-09-06 Siemens Aktiengesellschaft Rotor einer gasturbine mit kühlluftführung
US10830146B2 (en) * 2016-03-01 2020-11-10 Siemens Aktiengesellschaft Compressor bleed cooling system for mid-frame torque discs downstream from a compressor assembly in a gas turbine engine
EP3219911A1 (de) * 2016-03-17 2017-09-20 Siemens Aktiengesellschaft Rotor einer gasturbine mit verschraubten rotorscheiben
US10024170B1 (en) * 2016-06-23 2018-07-17 Florida Turbine Technologies, Inc. Integrally bladed rotor with bore entry cooling holes
EP3269926B1 (en) * 2016-07-07 2020-10-07 Doosan Heavy Industries & Construction Co., Ltd. Disk assembly and turbine including the same
KR101794451B1 (ko) 2016-07-07 2017-11-06 두산중공업 주식회사 디스크 조립체 및 그를 포함하는 터빈
KR101834647B1 (ko) * 2016-07-07 2018-04-13 두산중공업 주식회사 디스크 조립체 및 그를 포함하는 터빈
KR101772334B1 (ko) 2016-07-07 2017-08-28 두산중공업 주식회사 디스크 조립체 및 그를 포함하는 터빈
KR101882107B1 (ko) * 2016-12-22 2018-07-25 두산중공업 주식회사 가스터빈
FR3063775B1 (fr) * 2017-03-07 2022-05-06 Ifp Energies Now Turbopompe pour un circuit fluidique, notamment pour un circuit ferme en particulier de type a cycle de rankine
EP3754168B1 (en) * 2018-02-20 2023-03-29 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Supercharger
US10794190B1 (en) 2018-07-30 2020-10-06 Florida Turbine Technologies, Inc. Cast integrally bladed rotor with bore entry cooling
US11428104B2 (en) 2019-07-29 2022-08-30 Pratt & Whitney Canada Corp. Partition arrangement for gas turbine engine and method

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JPS63253125A (ja) * 1987-04-08 1988-10-20 Hitachi Ltd ガスタ−ビンの冷却空気求心加速装置
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US2861823A (en) * 1953-12-24 1958-11-25 Power Jets Res & Dev Ltd Bladed rotors for compressors, turbines and the like
DE1023933B (de) * 1954-03-08 1958-02-06 Canadian Patents Dev Wellenkupplung, insbesondere fuer Gasturbinentriebwerke
US2741454A (en) * 1954-09-28 1956-04-10 Clifford R Eppley Elastic fluid machine
GB836920A (en) * 1957-05-15 1960-06-09 Napier & Son Ltd Rotors for multi-stage axial flow compressors or turbines
JPS63253125A (ja) * 1987-04-08 1988-10-20 Hitachi Ltd ガスタ−ビンの冷却空気求心加速装置
EP0965726A1 (en) * 1996-11-29 1999-12-22 Hitachi, Ltd. Refrigerant recovery type gas turbine

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PATENT ABSTRACTS OF JAPAN vol. 0130, no. 45 (M - 792) 2 February 1989 (1989-02-02) *

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2010520967A (ja) * 2007-03-12 2010-06-17 シーメンス アクチエンゲゼルシヤフト ガスタービンのロータ
US8641365B2 (en) 2007-03-12 2014-02-04 Siemens Aktiengesellschaft Rotor of a gas turbine
EP2687680A3 (en) * 2012-07-20 2014-08-27 Kabushiki Kaisha Toshiba Axial turbine and power plant
EP3156593A1 (en) * 2015-10-15 2017-04-19 Doosan Heavy Industries & Construction Co., Ltd. Cooling apparatus of gas turbine
US10450864B2 (en) 2015-10-15 2019-10-22 DOOSAN Heavy Industries Construction Co., LTD Gas turbine cooling apparatus

Also Published As

Publication number Publication date
US7585148B2 (en) 2009-09-08
EP2787168A3 (de) 2015-04-15
RU2006136413A (ru) 2008-04-27
CN101010486A (zh) 2007-08-01
RU2347912C2 (ru) 2009-02-27
EP2787168B1 (de) 2016-01-06
JP2007529668A (ja) 2007-10-25
WO2005093219A1 (de) 2005-10-06
EP1725741A1 (de) 2006-11-29
JP4722120B2 (ja) 2011-07-13
US20080159864A1 (en) 2008-07-03
EP1725741B1 (de) 2014-09-24
CN101010486B (zh) 2011-06-01
EP2787168A2 (de) 2014-10-08

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