EP1321626A1 - Gasturbine rotor - Google Patents

Gasturbine rotor 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
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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Withdrawn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
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German (de)
French (fr)
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/en
Priority to PCT/EP2002/013621 priority patent/WO2003054355A1/en
Publication of EP1321626A1 publication Critical patent/EP1321626A1/en
Withdrawn legal-status Critical Current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.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Gas turbine comprises a compressor part (7) and a turbine part (13) that are rotationally fixed together. A tie rod (4) and compressor disks (29) are provided in the compressor part, and turbine disks (41) in the turbine part. The compressor disks are fixed centrally on the tie rod. The turbine disks are decentrally fixed. The gas turbine also comprises a multi-fixing disk (35) between a rear compressor disk and a front turbine disk. The multifixing disk is fixed centrally to the compressor disks. <??>Preferred Features: The multi-fixing disk is fixed decentrally to the turbine disks. An intermediate part (38) is arranged between the multi-fixing disk and a turbine disk to adjust the distance between the disks. A decentral bore (53) in the turbine disks allows the introduction of steam to the turbine blades for cooling.

Description

Die Erfindung betrifft eine Gasturbine mit Verdichter- und Turbinenscheiben, die miteinander befestigt sind.The invention relates to a gas turbine with compressor and Turbine disks that are fastened together.

Es ist allgemein bekannt, alle Scheiben für die Turbine samt zugehörigen Verdichter auf einen Zuganker entweder zentral oder dezentral zu befestigen, wobei diese zwei Befestigungsarten ihre jeweiligen Vor- und Nachteile haben. Der Vorteil der zentralen Befestigung liegt in der einfachen Bauweise, was Kosten und Gewicht spart, niedrige Spannungen nahe einer Trommel und einfache Dichtungsmöglichkeiten. Bei einem Austausch von Schaufeln im Heissgaskanal müssen jedoch auch die Schaufeln im Verdichterkanal entstapelt werden.
Bei der dezentralen Befestigung ist der Rotor teilbar, führt jedoch mittels eines Multizugankers u.a. zu einer Reduzierung der Rotorsteifigkeit im Bereich der ersten drei Verdichterscheiben.It is generally known to fasten all the disks for the turbine together with the associated compressor to a tie rod either centrally or decentrally, these two types of fastening having their respective advantages and disadvantages. The advantage of the central fastening is the simple construction, which saves costs and weight, low tensions near a drum and simple sealing options. When replacing blades in the hot gas duct, however, the blades in the compressor duct must also be unstacked.
With decentralized fastening, the rotor can be divided, but using a multi-tie rod leads to a reduction in rotor rigidity in the area of the first three compressor disks.

Die Aufgabe der Erfindung ist es, eine technische Lösung anzugeben, wie die vielen verschiedenen Scheiben eines Rotors bei einer Gasturbine zusammengefügt bzw. zusammengehalten werden können, wobei ohne Reduzierung der Rotorsteifigkeit ein einfacher Austausch von Schaufeln in Heißgaskanal ohne Entstapelung der Verdichterbeschaufelung gewährleistet werden kann.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.

Kern der erfindungsgemässen Lösung dieser Aufgabe ist eine Mehrfachbefestigungsscheibe zwischen einer Verdichterscheibe und einer Turbinenscheibe.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.

Die Mehrfachbefestigungsscheibe ist dabei zentral mit den Verdichterscheiben des Verdichters und dezentral mit den Turbinenscheiben im Turbinenbereich befestigt, so dass die vorteilhafte Befestigungsart im Verdichterbereich ausgenutzt werden kann und die dezentrale Befestigung mit ihren Vorteilen für einen leichten Austausch von Turbinenscheiben ausschließlich auf den Turbinenbereich beschränkt ist.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.

Zwischen der Mehrfachbefestigungsscheibe und den Scheiben im Turbinenbereich ist vorteilhafterweise zumindest eine Zwischenscheibe vorhanden, um einen gewünschten Abstand zwischen Turbinen- und Verdichterbereich einzustellen.Between the multiple mounting washer and the washers in the Turbine area is advantageously at least one Washer available to a desired distance between the turbine and compressor area.

Bei einer Reparatur bzw. bei einem Austausch des Turbinenteils muss dadurch nicht der ganze Verdichterbereich mit seinen Scheiben entstapelt werden.When repairing or replacing the This means that the turbine section does not have to cover the entire compressor area to be unstacked with its slices.

Durch eine Bohrung einer dezentralen Schraube im Turbinenbereich kann vorteilhaft Dampf geleitet werden, um die Turbinenschaufeln im Turbinenbereich mittels Dampfkühlung zu kühlen, so dass keine zusätzliche Leitung für die Dampfkühlung notwendig ist.By drilling a decentralized screw in the Turbine area can advantageously be directed to steam the turbine blades in the turbine area by means of steam cooling to cool so that no additional line for the Steam cooling is necessary.

Die Erfindung wird beispielhaft anhand der Zeichnung näher erläutert.The invention is illustrated by way of example with reference to the drawing explained.

Es zeigen

  • Figur 1 eine Gasturbine,
  • Figur 2 im axialen Lösungsschnitt einen Zuganker mit Scheiben im Verdichterbereich und Turbinenbereich.
    • Show it
  • 1 shows a gas turbine,
  • Figure 2 in axial solution section a tie rod with disks in the compressor area and turbine area.

    • Gleiche Bezugszeichen haben bei den verschiedenen Figuren die gleiche Bedeutung.The same reference numerals have the different figures same meaning.

    Figur 1 zeigt schematisch in einem Längsschnitt eine Gasturbine 1.
    Entlang eines Zugankers 4 sind ein Verdichter 7, eine Brennkammer 10 und ein Turbinenteil 13 hintereinander angeordnet. Das Turbinenteil 13 weist einen Heissgaskanal 16 auf. Im Heissgaskanal 16 sind Gasturbinenschaufeln 20 angeordnet. Leitschaufel- und Laufschaufelkränze sind wechselnd aufeinanderfolgend vorgesehen. Die Gasturbinenschaufeln 20 werden beispielsweise über eine kombinierte Luft- und/oder Dampfkühlung gekühlt. Dazu wird beispielsweise dem Verdichter 7 Verdichterluft entnommen und über eine Luftführung 23 den Gasturbinenschaufeln 20 zugeführt. Über eine Dampfzuführung 26 wird den Gasturbinenschaufeln 20 bspw. auch Dampf zugeführt. Vorzugsweise stammt dieser Dampf aus einer Dampfturbine eines kombinierten Gas und Dampfprozesses.    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. For this purpose, 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.

    Figur 2 zeigt den Zuganker 4 bspw. gemäss Figur 1 im Teilausschnitt, der sich vom Verdichter 7 bis zu seinem Ende 5, wo das Turbinenteil 13 beginnt, erstreckt.
    Im Verdichter 7 ist zumindest eine Verdichterscheibe 29 vorhanden, an deren Umfang ein Schaufelkranz aus Verdichterschaufeln 32 angeordnet ist.
    Sind mehrere Verdichterscheiben 29 vorhanden, so haben benachbarte Verdichterscheiben 29 mechanischen Kontakt miteinander, so dass sie sich miteinander drehen.
    Die Verdichterscheiben 29 sind auf dem Zuganker 4 mittels einer zentralen Befestigung, beispielsweise einer durchgehenden Befestigungsschraube (nicht dargestellt) auf dem Zuganker 4 befestigt. Zentrale Befestigung bedeutet eine beidseitige Verschraubung auf einer zentralen Schraubenachse, d.h. koaxial auf der Turbinenachse.
    Andere Befestigungsarten neben der Befestigungsschraube wie z.B. Schweissen u.ä. sind zwar möglich, aber mangels Lösbarkeit nicht bevorzugt.
    An die letzte, d.h. dem Turbinenteil 13 am nächsten liegende Verdichterscheibe 30 schließt sich eine Mehrfachbefestigungsscheibe 35 an, die ebenfalls mit der Verdichterscheibe 30 mechanischen Kontakt hat. Die Mehrfachbefestigungsscheibe 35 ist mit den Verdichterscheiben 29, 30 zentral auf den Zuganker 4 befestigt.     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. are possible, but are not preferred because they cannot be solved.
    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.

    An die Mehrfachbefestigungsscheibe 35 zum Turbinenteil 13 hin schließt sich beispielsweise, aber nicht notwendigerweise, zumindest ein Zwischenstück 38 an, wodurch ein Abstand zwischen der Mehrfachbefestigungsscheibe 35 und der ersten und zumindest einen Turbinenscheibe 41 eingestellt werden kann. Das Zwischenstück 38 ist bspw. ein Ring, kann aber auch eine Scheibe sein. Die Mehrfachbefestigungsscheibe 35 kann auch so gestaltet sein, dass sie mit den Zwischenstücken 38 einteilig ausgebildet ist.Towards the multiple mounting plate 35 toward the turbine part 13 closes, for example, but not necessarily, at least one intermediate piece 38, creating a distance between the multiple mounting plate 35 and the first and at least one turbine disk 41 can be adjusted can. 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.

    Die zumindest eine Turbinenscheibe 41, an der Gasturbinenschaufeln 56 befestigt sind, weist mehrere dezentrale Bohrungen 53 auf, durch die die Turbinenscheiben 41 bspw. durch jeweils eine Befestigungsschraube 44 miteinander verbunden werden. Dezentrale Befestigung bedeutet, dass ein radialer Abstand der Achse des Befestigungmittels von der Drehachse 2 vorhanden ist.
    Die zumindest eine Befestigungsschraube 44 verbindet die Mehrfachbefestigungsscheibe 35 wiederum mit den Turbinenscheiben 41 und die ggf. vorhandenen Zwischenstücke 38, d.h., die Mehrfachbefestigungsscheibe 35 und die ggf. vorhandenen Zwischenstücke 35 weisen entsprechende dezentrale Bohrungen 53 für die Befestigungsschraube 44 auf. Die Befestigungsschraube 44 greift jeweils an einem Ende 45 an der Mehrfachbefestigungsscheibe 35 und einem Endstück 47 im Turbinenteil 13 an, wobei das Endstück 47 beispielsweise an einem Lager gelagert ist oder selbst ein Lager ist.    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.

    Der Zuganker 4 weist bspw. an seinem Ende 5 beispielsweise ein Rampenstück 50 mit einer konischen Schräge 51 als Dichtfläche auf, an dem die Mehrfachbefestigungsscheibe 35 an ihrem hinterem Ende, d.h. dem Turbinenteil 13 nahen Ende, anliegt. Die Verspannung des Zugankers 4 mit den Verdichterscheiben 29, 30 erfolgt z.B. über eine Verschraubung im linken, nicht dargestellten Teil des Zugankers 4 oder mittels eines auf den Zuganker 4 aufgeschraubten Rampenstück 50.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.

    Die Mehrfachbefestigungsscheibe 35 und die Turbinenscheiben 41 weisen zumindest eine Bohrung 53 auf, durch die auch Dampf geleitet werden kann, der zu den Gasturbinenschaufeln 56 weitergeleitet wird und diese mittels Dampf effektiv kühlt.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.

    Die gezeigte Anordnung hat noch weitere Vorteile gegenüber den bisherigen Lösungsformen.
    Es besteht die Möglichkeit eine hintere Hohlwelle 63 für die Dampfkühlung einzusetzen.
    Über einen Dampfeintritt 60 tritt Dampf aus der Dampfzuführung (Fig. 1) 26 in die Hohlwelle 63 ein und wird zu den Schaufeln im Heissgaskanal 16 geführt und kühlt dort die Schaufeln 20. Über einen Dampfaustritt 66 wird der Dampf in den Dampfkreislauf zurückgeführt.
    Ebenso sind kleinere Umfangsgeschwindigkeiten einer Dichtung an der Übergangsstelle für die Dampfführung zwischen Rotor und Stator von großem Vorteil.     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.

    BezugszeichenlisteLIST OF REFERENCE NUMBERS

    11
    Gasturbinegas turbine
    22
    Drehachseaxis of rotation
    44
    Zugankertie rods
    55
    Ende von 4End of 4
    77
    Verdichtercompressor
    1010
    Brennkammercombustion chamber
    1313
    Turbinenteilturbine part
    1616
    HeißgaskanalHot gas duct
    2020
    GasturbinenschaufelnGas turbine blades
    2323
    Luftführungair duct
    2626
    Dampfzuführungsteam supply
    2929
    Verdichterscheibecompressor disk
    3030
    Verdichterscheibecompressor disk
    3232
    Verdichterschaufelcompressor blade
    3535
    MehrfachbefestigungsscheibeMultiple mounting disk
    3838
    Zwischenstückconnecting piece
    4141
    Turbinenschaufelturbine blade
    4444
    Befestigungsschraubefixing screw
    4545
    Ende von 35End of 35
    4747
    Endstücktail
    5050
    RampenstückRampenstück
    5151
    Schrägeslope
    5353
    Bohrungdrilling
    5656
    Turbinenschaufelturbine blade
    6060
    Dampfeintrittsteam inlet
    6363
    Hohlwellehollow shaft
    6666
    Dampfaustrittsteam outlet

    Claims (4)

    Gasturbine, mit drehfest miteinander verbundenem Verdichterteil (27) und Turbinenteil (13),mit einem Zuganker (4) mit Verdichterscheiben (29) im Verdichterteil (7), mit Turbinenscheiben (41) im Turbinenteil (13), wobei die Verdichterscheiben (29) zentral am Zuganker (4) befestigt sind,
    wobei die Turbinenscheiben (41) dezentral befestigt sind, mit einer Mehrfachbefestigungsscheibe (35) zwischen einer hinteren Verdichterscheibe (29) und einer vorderen Turbinenscheibe (41),
    wobei die Mehrfachbefestigungsscheibe (35) zentral mit den Verdichterscheiben (29) befestigt ist.    Gas turbine, with a compressor part (27) and turbine part (13) connected in a rotationally fixed manner, with a tie rod (4) with compressor disks (29) in the compressor part (7), with turbine disks (41) in the turbine part (13), the compressor disks (29) are centrally attached to the tie rod (4),
    wherein the turbine disks (41) are attached decentrally, with a multiple attachment disk (35) between a rear compressor disk (29) and a front turbine disk (41),
    wherein the multiple mounting plate (35) is attached centrally to the compressor plates (29).         Turbine nach Anspruch 1,
    dadurch gekennzeichnet, dass
    die Mehrfachbefestigungsscheibe (35) dezentral mit den Turbinenscheiben (41) befestigt ist.    Turbine according to claim 1,
    characterized in that
    the multiple mounting disc (35) is attached decentrally to the turbine discs (41).         Turbine nach Anspruch 1 oder 2,
    dadurch gekennzeichnet, dass
    zwischen der Mehrfachbefestigungsscheibe (35) und einer Turbinenscheibe (41) zumindest ein Zwischenstück (38) angeordnet ist, um einen gewissen Abstand zwischen diesen einzustellen.    Turbine according to claim 1 or 2,
    characterized in that
    at least one intermediate piece (38) is arranged between the multiple fastening disk (35) and a turbine disk (41) in order to set a certain distance between them.         Turbine nach Anspruch 1,
    dadurch gekennzeichnet, dass
    über eine dezentrale Bohrung (53) der Turbinenscheiben (41) eine Zuleitung von Dampf zu den Turbinenschaufeln (56) möglich ist, um die Turbinenschaufeln (56) mit Dampf zu kühlen.    Turbine according to claim 1,
    characterized in that
    A supply of steam to the turbine blades (56) is possible via a decentralized bore (53) in the turbine disks (41) in order to cool the turbine blades (56) with steam.
    EP01130725A 2001-12-21 2001-12-21 Gasturbine rotor Withdrawn EP1321626A1 (en)

    Priority Applications (2)

    Application Number Priority Date Filing Date Title
    EP01130725A EP1321626A1 (en) 2001-12-21 2001-12-21 Gasturbine rotor
    PCT/EP2002/013621 WO2003054355A1 (en) 2001-12-21 2002-12-02 Gas turbine with a multiple fixing disk

    Applications Claiming Priority (1)

    Application Number Priority Date Filing Date Title
    EP01130725A EP1321626A1 (en) 2001-12-21 2001-12-21 Gasturbine rotor

    Publications (1)

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

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    Family Applications (1)

    Application Number Title Priority Date Filing Date
    EP01130725A Withdrawn EP1321626A1 (en) 2001-12-21 2001-12-21 Gasturbine rotor

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    EP (1) EP1321626A1 (en)
    WO (1) WO2003054355A1 (en)

    Cited By (4)

    * Cited by examiner, † Cited by third party
    Publication number Priority date Publication date Assignee Title
    EP1749979A2 (en) * 2005-08-02 2007-02-07 Nuovo Pignone S.P.A. Movement system for the inspection of a gas turbine and gas turbine equipped with such a system
    WO2009118036A1 (en) * 2008-03-26 2009-10-01 Man Turbo Ag Turbine rotor for a gas turbine
    WO2010063272A1 (en) 2008-12-04 2010-06-10 Mtu Aero Engines Gmbh Assembly mechanism comprising a tension anchor and corresponding method for a rotor system of an axial turbo engine
    CN104204410A (en) * 2012-03-27 2014-12-10 西门子公司 A system for inductive heating of turbine rotor disks

    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 (en) * 2005-08-02 2007-02-07 Nuovo Pignone S.P.A. Movement system for the inspection of a gas turbine and gas turbine equipped with such a system
    WO2009118036A1 (en) * 2008-03-26 2009-10-01 Man Turbo Ag Turbine rotor for a gas turbine
    WO2010063272A1 (en) 2008-12-04 2010-06-10 Mtu Aero Engines Gmbh Assembly mechanism comprising a tension anchor and corresponding method for a rotor system of an axial turbo engine
    DE102008060571A1 (en) 2008-12-04 2010-06-10 Mtu Aero Engines Gmbh Mounting device for a rotor system of an axial flow machine
    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 (en) * 2012-03-27 2014-12-10 西门子公司 A system for inductive heating of turbine rotor disks

    Also Published As

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

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