EP1321626A1 - Rotor de turbine à gaz - Google Patents

Rotor de turbine à gaz Download PDF

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Publication number
EP1321626A1
EP1321626A1 EP01130725A EP01130725A EP1321626A1 EP 1321626 A1 EP1321626 A1 EP 1321626A1 EP 01130725 A EP01130725 A EP 01130725A EP 01130725 A EP01130725 A EP 01130725A EP 1321626 A1 EP1321626 A1 EP 1321626A1
Authority
EP
European Patent Office
Prior art keywords
turbine
compressor
disks
disk
steam
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Withdrawn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
EP01130725A
Other languages
German (de)
English (en)
Inventor
Peter Tiemann
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 EP01130725A priority Critical patent/EP1321626A1/fr
Priority to PCT/EP2002/013621 priority patent/WO2003054355A1/fr
Publication of EP1321626A1 publication Critical patent/EP1321626A1/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Withdrawn legal-status Critical Current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
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
    • 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
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/232—Heat transfer, e.g. cooling characterized by the cooling medium
    • F05D2260/2322—Heat transfer, e.g. cooling characterized by the cooling medium steam

Definitions

  • the invention relates to a gas turbine with compressor and Turbine disks that are fastened together.
  • the object of the invention is a technical solution to indicate how the many different discs of a rotor assembled or held together in a gas turbine can be, without reducing the rotor rigidity a simple exchange of blades in hot gas duct without Unstacking of the compressor blades can be guaranteed can.
  • the core of the solution to this problem according to the invention is a Multiple mounting disc between a compressor disc and a turbine disc.
  • the multiple mounting washer is central with the Compressor discs of the compressor and decentrally with the Turbine disks attached in the turbine area so that the advantageous type of fastening used in the compressor area can be and the decentralized attachment with their Advantages for easy replacement of turbine disks is limited to the turbine area only.
  • FIG. 1 schematically shows a gas turbine 1 in a longitudinal section.
  • a compressor 7, a combustion chamber 10 and a turbine part 13 are arranged one behind the other along a tie rod 4.
  • the turbine part 13 has a hot gas duct 16.
  • Gas turbine blades 20 are arranged in the hot gas duct 16.
  • Guide vane and rotor blade rings are alternately provided in succession.
  • the gas turbine blades 20 are cooled, for example, by a combined air and / or steam cooling.
  • compressor air is taken, for example, from the compressor 7 and fed to the gas turbine blades 20 via an air duct 23.
  • Steam is also supplied to the gas turbine blades 20, for example, via a steam feed 26. This steam preferably originates from a steam turbine of a combined gas and steam process.
  • FIG. 2 shows the tie rod 4, for example according to FIG. 1, in a partial section, which extends from the compressor 7 to its end 5, where the turbine part 13 begins.
  • At least one compressor disk 29 is present in the compressor 7, on the circumference of which a blade ring made of compressor blades 32 is arranged. If several compressor disks 29 are present, adjacent compressor disks 29 have mechanical contact with one another so that they rotate with one another.
  • the compressor disks 29 are fastened on the tie rod 4 by means of a central fastening, for example a continuous fastening screw (not shown) on the tie rod 4.
  • Central fastening means screwing on both sides on a central screw axis, ie coaxially on the turbine axis. Other types of fastening besides the fastening screw such as welding etc.
  • the last, that is to say the turbine part 13 closest to the compressor disk 30 is followed by a multiple mounting disk 35, which is also in mechanical contact with the compressor disk 30.
  • the multiple fastening disc 35 is fastened to the tie rod 4 centrally with the compressor discs 29, 30.
  • the intermediate piece 38 is, for example, a ring, but can also be a disc.
  • the multiple mounting plate 35 can also be designed so that they are with the intermediate pieces 38th is formed in one piece.
  • the at least one turbine disk 41 to which gas turbine blades 56 are fastened, has a plurality of decentralized bores 53 through which the turbine disks 41 are connected to one another, for example by a fastening screw 44.
  • Decentralized fastening means that there is a radial distance between the axis of the fastening means and the axis of rotation 2.
  • the at least one fastening screw 44 in turn connects the multiple fastening disk 35 to the turbine disks 41 and the intermediate pieces 38 which may be present, ie the multiple fastening disk 35 and the intermediate pieces 35 which may be present have corresponding decentralized bores 53 for the fastening screw 44.
  • the fastening screw 44 engages at one end 45 on the multiple fastening disk 35 and one end piece 47 in the turbine part 13, the end piece 47 being mounted, for example, on a bearing or being a bearing itself.
  • the tie rod 4 has, for example, at its end 5 a ramp piece 50 with a conical bevel 51 as Sealing surface on which the multiple mounting plate 35 its rear end, i.e. the end near the turbine part 13, is applied.
  • the tension of the tie rod 4 with the Compressor disks 29, 30 are e.g. over a Screwing in the left part of the, not shown Tie rod 4 or by means of a tie rod 4 screwed on ramp piece 50.
  • the multiple mounting washer 35 and the turbine washers 41 have at least one bore 53 through which also steam can be directed to the gas turbine blades 56th is forwarded and cools it effectively with steam.
  • the arrangement shown has further advantages over previous solutions. It is possible to use a rear hollow shaft 63 for steam cooling. Steam enters the hollow shaft 63 via a steam inlet 60 from the steam feed (FIG. 1) and is guided to the blades in the hot gas duct 16 and cools the blades 20 there. The steam is returned to the steam circuit via a steam outlet 66. Likewise, smaller peripheral speeds of a seal at the transition point for the steam flow between the rotor and stator are of great advantage.

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)
EP01130725A 2001-12-21 2001-12-21 Rotor de turbine à gaz Withdrawn EP1321626A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP01130725A EP1321626A1 (fr) 2001-12-21 2001-12-21 Rotor de turbine à gaz
PCT/EP2002/013621 WO2003054355A1 (fr) 2001-12-21 2002-12-02 Turbine a gaz a disque en fixation multiple

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP01130725A EP1321626A1 (fr) 2001-12-21 2001-12-21 Rotor de turbine à gaz

Publications (1)

Publication Number Publication Date
EP1321626A1 true EP1321626A1 (fr) 2003-06-25

Family

ID=8179664

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01130725A Withdrawn EP1321626A1 (fr) 2001-12-21 2001-12-21 Rotor de turbine à gaz

Country Status (2)

Country Link
EP (1) EP1321626A1 (fr)
WO (1) WO2003054355A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1749979A2 (fr) * 2005-08-02 2007-02-07 Nuovo Pignone S.P.A. Système de déplacement pour l'inspection d'une turbine à gaz et turbine à gaz équipée d'un tel système
WO2009118036A1 (fr) * 2008-03-26 2009-10-01 Man Turbo Ag Rotor de turbine à gaz
DE102008060571A1 (de) 2008-12-04 2010-06-10 Mtu Aero Engines Gmbh Montagevorrichtung für ein Rotorsystem einer Axial-Strömungsmaschine
CN104204410A (zh) * 2012-03-27 2014-12-10 西门子公司 用于涡轮转子盘的感应加热的系统

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB610314A (en) * 1945-01-16 1948-10-14 Power Jets Res & Dev Ltd Improvements relating to the construction of rotors for compressors and turbines
US5860789A (en) * 1996-03-19 1999-01-19 Hitachi, Ltd. Gas turbine rotor
US6094905A (en) * 1996-09-25 2000-08-01 Kabushiki Kaisha Toshiba Cooling apparatus for gas turbine moving blade and gas turbine equipped with same
US6267553B1 (en) * 1999-06-01 2001-07-31 Joseph C. Burge Gas turbine compressor spool with structural and thermal upgrades

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB610314A (en) * 1945-01-16 1948-10-14 Power Jets Res & Dev Ltd Improvements relating to the construction of rotors for compressors and turbines
US5860789A (en) * 1996-03-19 1999-01-19 Hitachi, Ltd. Gas turbine rotor
US6094905A (en) * 1996-09-25 2000-08-01 Kabushiki Kaisha Toshiba Cooling apparatus for gas turbine moving blade and gas turbine equipped with same
US6267553B1 (en) * 1999-06-01 2001-07-31 Joseph C. Burge Gas turbine compressor spool with structural and thermal upgrades

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1749979A2 (fr) * 2005-08-02 2007-02-07 Nuovo Pignone S.P.A. Système de déplacement pour l'inspection d'une turbine à gaz et turbine à gaz équipée d'un tel système
WO2009118036A1 (fr) * 2008-03-26 2009-10-01 Man Turbo Ag Rotor de turbine à gaz
DE102008060571A1 (de) 2008-12-04 2010-06-10 Mtu Aero Engines Gmbh Montagevorrichtung für ein Rotorsystem einer Axial-Strömungsmaschine
WO2010063272A1 (fr) 2008-12-04 2010-06-10 Mtu Aero Engines Gmbh Dispositif de montage comportant un tirant et procédé correspondant pour un système de rotor d'une turbomachine axiale
US8764390B2 (en) 2008-12-04 2014-07-01 Mtu Aero Engines Gmbh Assembly mechanism comprising a tension anchor and corresponding method for a rotor system of an axial turbo engine
CN104204410A (zh) * 2012-03-27 2014-12-10 西门子公司 用于涡轮转子盘的感应加热的系统

Also Published As

Publication number Publication date
WO2003054355A1 (fr) 2003-07-03

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