EP2496793A1 - Welded rotor of a gas turbine engine compressor - Google Patents

Welded rotor of a gas turbine engine compressor

Info

Publication number
EP2496793A1
EP2496793A1 EP10771153A EP10771153A EP2496793A1 EP 2496793 A1 EP2496793 A1 EP 2496793A1 EP 10771153 A EP10771153 A EP 10771153A EP 10771153 A EP10771153 A EP 10771153A EP 2496793 A1 EP2496793 A1 EP 2496793A1
Authority
EP
European Patent Office
Prior art keywords
rotor
disks
discs
last
flow direction
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.)
Granted
Application number
EP10771153A
Other languages
German (de)
French (fr)
Other versions
EP2496793B1 (en
Inventor
Ernst Pauli
Thomas Kramer
Holger Kiewel
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP2496793A1 publication Critical patent/EP2496793A1/en
Application granted granted Critical
Publication of EP2496793B1 publication Critical patent/EP2496793B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F01D5/063—Welded rotors
    • 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
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49323—Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles

Definitions

  • the present invention relates to welded rotors for gas turbine compressors, and to a method for their production.
  • Rotors for gas turbines usually consist of several discs, either joined together by means of screw or
  • EP984138 discloses a rotor for a gas turbine
  • cooling flows are through air ducts through the vanes and through
  • EP844367 discloses a welded rotor for a turbomachine with a plurality of rotor disks, which in each case between welds
  • Cooling medium is guided by the rotor itself radially outward to the blade roots.
  • EP1705339 discloses a rotor for a gas turbine with radial run
  • Cooling air ducts which have an elliptical cross-section.
  • a rotor 1 for a gas turbine with rotor axis 2 has a plurality of rotor disks 3, 4 and 5, which are connected by welds 6 between internal cavities H and KT, which are formed by the axial joining of the discs, and the rotor surface.
  • the last rotor disk 3 also has a recess 7 on its surface. This recess is supplied to cooling air from outside the rotor. Heat from the center region of the last disc 3 of the compressor rotor is removed in the direction of arrow 8 and finally via the cooled recess.
  • the heat dissipation 8 is favored by the fact that the rotor disk is made massive in the axial direction.
  • EP193161 15 discloses a welded disc rotor for a steam turbine.
  • the rotor disks each have recesses extending radially outwardly from the center thereof on the rotor axis, so that after the welding together of the disks, a cavity on and around the Rotor axis forms.
  • the rotor is cooled at the rotor surface by a supplied vapor stream.
  • the object of the present invention is to provide a rotor for a gas turbine compressor which is welded from a plurality of rotor disks
  • the material temperature of the compressor rotor disks during operation can be maintained at or below a predetermined level, so that a predetermined service life can be expected.
  • the rotor in comparison to rotors of the prior art, with regard to its production and possibilities for its testing in the
  • a coolable, welded gas turbine compressor rotor with a plurality of axially juxtaposed and welded together rotor disks is shown, wherein each rotor disk extends over at least three blade stages.
  • the rotor in addition to the welded-together rotor disks, the rotor has two or more rotor disks which are butt-joined to one another in a center region around and on the axis of rotation of the rotor disks, the center region comprising the rotor axis and extending radially outward from the axis.
  • the two rotor disks in the flow direction are welded together in a radially outer region, this radially outer region being radially outside the center region, comprising the rotor surface and extending radially inwardly from the surface. Between the center region with the butt joint and the welded, radially outer region extends an annular space.
  • the last in the direction of flow and blunt pushed to the second last rotor disks rotor disk has to dissipate heat from the center region of the rotor disk to the surface at its radially outer surface a recess which extends over the circumference of Rotor disc extends and can be cooled by an externally supplied cooling medium.
  • the recess is at the last, the highest
  • Center region ensures in particular an increased heat flow from the central region of the rotor to the rotor surface.
  • the invention is particularly advantageous in the last rotor disk of a compressor or in the rotor disks which are exposed to higher temperatures.
  • the rotor has two or more in the highest temperature range
  • Rotor disks which are smaller than the rotor disks of the prior art, i. are less thick. Nevertheless, they extend over at least three blade stages. Due to their smaller size, these are easier to manufacture. In particular, their forgeability is improved and the achievable degree of deformation is increased.
  • the individual rotor discs are easier to test in the forging process, since the smaller thickness of the discs, the sound path is shortened during the test and thereby measurement results can be achieved with higher resolution.
  • Coolable rotor according to the invention is the most effective at the last and the highest temperatures exposed point of the rotor.
  • the rotor disks according to the invention can also be arranged at any convenient location of the rotor at which cooling due to the
  • the rotor additionally has a layer with a heat-conducting material between the butted rotor disks in the center region of the disks.
  • this layer is attached to the surface of one of the two rotor disks.
  • the thermally conductive material is, for example, a metal with higher
  • All of the embodiments of the inventive rotor shown are not limited to two rotor discs, but can be applied in a suitable manner to a plurality of rotor disks of the rotor.
  • a plurality of rotor disks are welded together.
  • At least two rotor disks are provided which each have an annular, extending around the axis of rotation of the disks
  • the rotor disks are arranged at the last and second last position of the rotor in the flow direction and welded together in a radially outer region which extends from the annular space radially outward to the outer surface of the disks and in a radial center region extending from the rotor disk center Rotation axis of the disks radially outward to extends to the annulus, butt joined together.
  • Flow direction last location rotor disk mounted a coolable recess extending over the circumference of the rotor disk.
  • the two rotor disks are welded together in the radially outer region and then through
  • the butted rotor disks are placed at the location of the highest expected material temperatures of the rotor.
  • a layer of heat-conducting material is applied in the center region of at least one of the two last rotor disks in the flow direction. Thereafter, the two rotor disks are welded together in their radially outer region. In the center area around the axis of rotation of the discs they are in turn butted together.
  • FIG. 1 in cross section a welded gas turbine compressor rotor of the prior art.
  • Figure 2 in cross section a first embodiment of a part of a welded gas turbine compressor rotor, in particular the rotor disks according to the invention.
  • Figure 3 in cross section a second embodiment of a part of a welded gas turbine compressor rotor according to the invention.
  • FIG. 4 shows in cross section a third embodiment of a part of a welded gas turbine compressor rotor, in particular the rotor disks according to the invention.
  • FIG. 2 shows in longitudinal cross-section a gas turbine compressor rotor 1 with rotor axis 2.
  • the rotor 1 comprises a plurality of rotor disks, of which only rotor disks 3, 4 and 5 are shown in the figure.
  • the rotor discs are each designed so that they at least three blade stages of the
  • Rotor disks 4 and 5 each have a recess in their middle, which form a cavity H after joining the disks together the cavity H and the radially outer surface of the discs 4 and 5
  • the rotor disk 3 of the rotor of the prior art is realized according to the invention by two individual, compared to less solid rotor disks 3a and 3b.
  • the rotor disks 3a and 3b are the rotor disks of a compressor arranged in the flow direction at the last and second-last positions. These have in their center region at their axially facing sides each one
  • the rotor disk 3b is connected to the adjacent rotor disk 4 by means of a weld seam 6 'in the same way as the rotor disks 4 and 5
  • the rotor disks 3a and 3b are interconnected in a radially outer region 9 'by the weld seam 10 which extends from the annular space H "to the surface of the rotor
  • Rotation axis 2 of the rotor discs 3a and 3b are the mutually facing surfaces of the discs butted together.
  • the center region 9 of the rotor is, for example, the region containing the
  • FIG. 3 shows the same rotor as in FIG. 2, but with the additional feature on the rotor disk 3a, which is arranged last in the flow direction on the rotor. It has on its surface a recess 7 or annular groove which extends over the circumference of the rotor disk and can be cooled from the outside by a suitable cooling medium, such as cooling air or cooling steam.
  • a suitable cooling medium such as cooling air or cooling steam.
  • FIG. 4 shows an expanded embodiment of the rotor 1 according to the invention, again comprising rotor disks 3a, 3b, 4, 5.
  • the rotor disks 3a and 3b each have an annular recess on their sides facing each other axially, which form an annular space H "during assembly
  • a center region 9 on the mutually facing surfaces of the rotor disks 3a, 3b extends over the region which is surrounded by the annular space H ".
  • the expanded version differs from the rotor of FIGS. 2 and 3 in the realization of the heat transfer in the center region 9 of the rotor disks 3a and 3b.
  • the rotor disk 3a or 3b has in her
  • Center region 9 a layer 1 1 of a thermally conductive material. This layer 1 1 and the surface of the center region 9 of the rotor disc 3b are in turn butted together.
  • the layer 1 1 consists for example of a suitable metal having a thermal conductivity greater than that of the rotor material.

Landscapes

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

Abstract

The invention relates to a rotor (1) and a corresponding production method of a gas turbine compressor, comprising a plurality of rotor discs (3a, 3b, 4, 5) welded together, of which two or more rotor discs (3a, 3b) are welded together in a radially exterior area (9') and abut each other in a radially interior center area (9). A heat flow (8) radially outward from the center of the rotors (1) is achieved by means of the abutted joining to two rotor discs (3a, 3b), so that the material temperature of the rotor (1) during operation can be maintained below a prescribed level. The operating service life of the rotor (1) can thus be increased. The welded and abutting rotor discs (3a, 3b) according to the invention can be used at the last position in the flow direction of the compressor, wherein a rotor disc (3a) additionally comprises a recess (7) at the surface thereof that can be cooled from the outside.

Description

GESCHWEISSTER ROTOR EINES GASTURBINENTRIEBWERKVERDICHTERS  WELDED ROTOR OF A GAS TURBINE LINE COMPRESSOR
Technisches Gebiet Technical area
Die vorliegende Erfindung betrifft geschweisste Rotoren für Gasturbinen- Verdichter, sowie ein Verfahren zu deren Herstellung. The present invention relates to welded rotors for gas turbine compressors, and to a method for their production.
Stand der Technik State of the art
Rotoren für Gasturbinen bestehen in der Regel aus mehreren Scheiben, die entweder mithilfe von Schraubverbindungen zusammengefügt oder Rotors for gas turbines usually consist of several discs, either joined together by means of screw or
zusammengeschweisst werden. Um Überhitzungen während des Betriebs und dadurch verursachte Verringerung der Betriebslebensdauer der Rotoren zu vermeiden, werden die Rotoren aktiv gekühlt. Dabei wird zwischen Kühlmethoden für mit Schrauben verbundenen Rotoren und geschweisste Rotoren be welded together. To prevent overheating during operation and thereby reducing the service life of the rotors, the rotors are actively cooled. Here, there is a question of cooling methods for screw-connected rotors and welded rotors
unterschieden. Die Kühlmethoden für verschraubte Rotoren sind bei distinguished. The cooling methods for bolted rotors are included
geschweissten Rotoren nur bedingt anwendbar, weil die Rotorscheiben bei geschweissten Rotoren im Vergleich zu geschraubten Rotoren massiver sind und eine Innenkühlung durch Bohrungen schwieriger zu realisieren wäre. welded rotors only partially applicable, because the rotor disks are solid in welded rotors compared to screwed rotors and internal cooling would be more difficult to implement by drilling.
Für geschweisste Rotoren sind verschiedene Kühlvorrichtungen mit Kühlkanälen und -räumen in- und ausserhalb des Rotors bekannt. For welded rotors various cooling devices with cooling channels and spaces inside and outside the rotor are known.
Beispielsweise offenbart EP984138 einen Rotor für eine Gasturbine,  For example, EP984138 discloses a rotor for a gas turbine,
insbesondere Verdichter, dessen Oberfläche durch Kühlströme beaufschlagt wird. Die Kühlströme werden über Luftkanäle durch die Leitschaufeln und durch in particular compressor whose surface is acted upon by cooling currents. The cooling flows are through air ducts through the vanes and through
Öffnungen in deren Schaufelspitzen direkt zur Rotoroberfläche geführt. Openings in their blade tips led directly to the rotor surface.
EP844367 offenbart einen geschweissten Rotor für eine Strömungsmaschine mit mehreren Rotorscheiben, die zwischen Schweissnähten jeweils einen EP844367 discloses a welded rotor for a turbomachine with a plurality of rotor disks, which in each case between welds
ringförmigen Hohlraum aufweisen zwecks Durchströmung eines Kühldampfs. Das Kühlmedium wird durch den Rotor selbst radial auswärts zu den Schaufelfüssen geführt. annular cavity for the purpose of flow through a cooling steam. The Cooling medium is guided by the rotor itself radially outward to the blade roots.
EP1705339 offenbart einen Rotor für eine Gasturbine mit radial verlaufen  EP1705339 discloses a rotor for a gas turbine with radial run
Kühlluftkanälen, wobei diese einen elliptischen Querschnitt aufweisen. Cooling air ducts, which have an elliptical cross-section.
Bei Rotoren für Gasturbinen sind insbesondere die, in Strömungsrichtung der zu verdichtenden Luft, letzten Rotorscheiben im Kompressor aufgrund der In rotors for gas turbines in particular, in the flow direction of the air to be compressed, the last rotor disks in the compressor due to the
Verdichtung der Luft hohen Betriebstemperaturen ausgesetzt. Die Temperatur steigt dabei die Temperatur über die Länge des Kompressors stetig an, wobei die Wärme radial in den Rotor eindringt. In den genannten letzten Rotorscheiben ist eine aktive Kühlung notwendig, um die Materialtemperatur unter einem gewissen Niveau zu halten und eine entsprechend zu erwartende Betriebslebensdauer des Rotors zu erreichen. Eine bekannte Technik zur Kühlung der letzten Rotorscheibe eines Verdichters ist in Figur 1 dargestellt. Compaction of the air is exposed to high operating temperatures. The temperature increases while the temperature over the length of the compressor steadily, the heat penetrates radially into the rotor. Active cooling is necessary in the last rotor disks mentioned in order to keep the material temperature below a certain level and to achieve a corresponding expected service life of the rotor. A known technique for cooling the last rotor disk of a compressor is shown in FIG.
Ein Rotor 1 für eine Gasturbine mit Rotorachse 2 weist mehrere Rotorscheiben 3, 4 und 5 auf, die durch Schweissnähte 6 zwischen inneren Hohlräumen H und KT, die durch das axiale Zusammenfügen der Scheiben gebildet werden, und der Rotoroberfläche miteinander verbunden sind. Die letzte Rotorscheibe 3 weist zudem an ihrer Oberfläche eine Ausnehmung 7 auf. Dieser Ausnehmung wird Kühlluft von ausserhalb des Rotors zugeführt. Wärme aus dem Mittenbereich der letzten Scheibe 3 des Kompressorrotors wird in Richtung des Pfeils 8 und schliesslich über die gekühlte Ausnehmung entzogen. Der Wärmeabfluss 8 wird dabei dadurch begünstigt, wenn die Rotorscheibe in axialer Richtung massiv ausgestaltet ist. Einer massiven Ausgestaltung in axialer Richtung sind jedoch aufgrund der Fertigungstechnik solcher Rotoren sowie der Notwendigkeit, diese im Schmiedeprozess prüfen zu können, Grenzen gesetzt. EP193161 15 offenbart einen aus geschweissten Scheiben bestehenden Rotor für eine Dampfturbine. Die Rotorscheiben weisen jeweils Ausnehmungen auf, die sich von deren Mitte an der Rotorachse radial auswärts erstrecken, sodass nach dem Zusammenschweissen der Scheiben sich ein Hohlraum an der und um die Rotorachse bildet. Der Rotor wird an der Rotoroberfläche durch einen zugeführten Dampfstrom gekühlt. A rotor 1 for a gas turbine with rotor axis 2 has a plurality of rotor disks 3, 4 and 5, which are connected by welds 6 between internal cavities H and KT, which are formed by the axial joining of the discs, and the rotor surface. The last rotor disk 3 also has a recess 7 on its surface. This recess is supplied to cooling air from outside the rotor. Heat from the center region of the last disc 3 of the compressor rotor is removed in the direction of arrow 8 and finally via the cooled recess. The heat dissipation 8 is favored by the fact that the rotor disk is made massive in the axial direction. However, a massive configuration in the axial direction are limited due to the manufacturing technology of such rotors and the need to be able to test them in the forging process. EP193161 15 discloses a welded disc rotor for a steam turbine. The rotor disks each have recesses extending radially outwardly from the center thereof on the rotor axis, so that after the welding together of the disks, a cavity on and around the Rotor axis forms. The rotor is cooled at the rotor surface by a supplied vapor stream.
Darstellung der Erfindung Presentation of the invention
Der vorliegenden Erfindung ist die Aufgabe gestellt, einen aus einer Mehrzahl von Rotorscheiben geschweissten Rotor für einen Gasturbinenverdichter The object of the present invention is to provide a rotor for a gas turbine compressor which is welded from a plurality of rotor disks
vorzuschlagen, bei dem die Materialtemperatur der Kompressorrotorscheiben während des Betriebs auf oder unter einem vorbestimmten Niveau gehalten werden kann, sodass eine vorbestimmte Betriebslebensdauer erwartet werden kann. Zugleich soll der Rotor, im Vergleich zu Rotoren des Standes der Technik, im Hinblick auf dessen Fertigung und Möglichkeiten zu dessen Prüfung im to propose that the material temperature of the compressor rotor disks during operation can be maintained at or below a predetermined level, so that a predetermined service life can be expected. At the same time, the rotor, in comparison to rotors of the prior art, with regard to its production and possibilities for its testing in the
Schmiedeprozess verbessert sein. Zudem ist es Aufgabe der Erfindung ein Verfahren zu Herstellung eines solchen Rotors vorzuschlagen. Forging process improved. In addition, it is an object of the invention to propose a method for producing such a rotor.
Es wird ein kühlbarer, geschweisster Gasturbinenverdichter-Rotor mit einer Mehrzahl axial nebeneinander angeordneten und zusammengeschweissten Rotorscheiben aufgezeigt, wobei jede Rotorscheibe sich über mindestens drei Schaufelstufen erstreckt. Erfindungsgemäss weist der Rotor zusätzlich zu den zusammengeschweissten Rotorscheiben zwei oder mehr Rotorscheiben auf, die in einem Zentrumsbereich um die und an der Rotationsachse der Rotorscheiben stumpf aneinander gefügt sind, wobei der Zentrumsbereich die Rotorachse umfasst und sich von der Achse radial auswärts erstreckt. Zudem sind die zwei in Strömungsrichtung letzten Rotorscheiben in einem radial äusseren Bereich zusammengeschweisst, wobei dieser radial äussere Bereich radial ausserhalb des Zentrumsbereichs ist, die Rotoroberfläche umfasst und sich von der Oberfläche radial einwärts erstreckt. Zwischen dem Zentrumsbereich mit der stumpfen Aneinanderfügung und dem geschweissten, radial äusseren Bereich erstreckt sich ein Ringraum. Die in Strömungsrichtung letzte und stumpf an die zweitletzte Rotorscheiben gestossene Rotorscheibe weist zur Abführung von Wärme aus dem Zentrumsbereich der Rotorscheibe an die Oberfläche an ihrer radial äusseren Oberfläche eine Ausnehmung auf, die sich über den Umfang der Rotorscheibe erstreckt und durch ein von aussen zugeführtes Kühlmedium kühlbar ist. A coolable, welded gas turbine compressor rotor with a plurality of axially juxtaposed and welded together rotor disks is shown, wherein each rotor disk extends over at least three blade stages. According to the invention, in addition to the welded-together rotor disks, the rotor has two or more rotor disks which are butt-joined to one another in a center region around and on the axis of rotation of the rotor disks, the center region comprising the rotor axis and extending radially outward from the axis. In addition, the two rotor disks in the flow direction are welded together in a radially outer region, this radially outer region being radially outside the center region, comprising the rotor surface and extending radially inwardly from the surface. Between the center region with the butt joint and the welded, radially outer region extends an annular space. The last in the direction of flow and blunt pushed to the second last rotor disks rotor disk has to dissipate heat from the center region of the rotor disk to the surface at its radially outer surface a recess which extends over the circumference of Rotor disc extends and can be cooled by an externally supplied cooling medium.
Zweckmässigerweise ist die Ausnehmung an der letzten, den höchsten  Conveniently, the recess is at the last, the highest
Temperaturen ausgesetzten Rotorscheibe angebracht. Die kühlbare Ausnehmung zusammen mit der stumpfen Aneinanderfügung der Rotorscheiben im Temperatures exposed rotor disk attached. The coolable recess together with the butting of the rotor discs in the
Zentrumsbereich gewährleistet insbesondere einen erhöhten Wärmeabfluss aus dem Mittenbereich des Rotors zur Rotoroberfläche hin.  Center region ensures in particular an increased heat flow from the central region of the rotor to the rotor surface.
Die Erfindung ist insbesondere bei der letzten Rotorscheibe eines Verdichters oder bei den Rotorscheiben, die höheren Temperaturen ausgesetzt sind, vorteilhaft. The invention is particularly advantageous in the last rotor disk of a compressor or in the rotor disks which are exposed to higher temperatures.
Der Rotor weist im Bereich der höchsten Temperaturen zwei oder mehr  The rotor has two or more in the highest temperature range
Rotorscheiben auf, die im Vergleich zu den Rotorscheiben des Standes der Technik kleiner, d.h. weniger dick ausgebildet sind. Dennoch erstrecken sie sich über mindestens drei Schaufelstufen. Aufgrund ihrer kleineren Grösse sind diese einfacher herzustellen. Insbesondere ist ihre Schmiedbarkeit verbessert und der erreichbare Umformgrad erhöht. Rotor disks, which are smaller than the rotor disks of the prior art, i. are less thick. Nevertheless, they extend over at least three blade stages. Due to their smaller size, these are easier to manufacture. In particular, their forgeability is improved and the achievable degree of deformation is increased.
Zudem sind die einzelnen Rotorscheiben im Schmiedeprozess einfacher zu prüfen, da durch die kleinere Dicke der Scheiben der Schallweg bei der Prüfung verkürzt ist und dadurch Messresultate mit höherer Auflösung erreicht werden können. In addition, the individual rotor discs are easier to test in the forging process, since the smaller thickness of the discs, the sound path is shortened during the test and thereby measurement results can be achieved with higher resolution.
Die stumpfe stossend Aneinanderfügung über den radial inneren Zentrumsbereich der zwei, in Strömungsrichtung letzten Rotorscheiben bewirken einen Wärmefluss aus dem Zentrumsbereich des Rotors an die radial äussere Oberfläche desThe blunt butting over the radially inner center region of the two, in the flow direction last rotor disks cause a heat flow from the center region of the rotor to the radially outer surface of the rotor
Rotors, wo sie über die Ausnehmung abgeführt werden kann. Dadurch wird das insbesondere bei Gasturbineverdichtern auftretende Problem der übermässigen Erwärmung des Rotors an der in Strömungsrichtung letzten Stelle des Rotors gelöst. Die Materialtemperatur des Rotors während des Betriebs kann dadurch unter einem vorbestimmten Niveau gehalten werden und somit die Rotor, where it can be removed via the recess. As a result, the problem of excessive heating of the rotor, which occurs in particular in gas turbine compressors, is solved at the last point of the rotor in the flow direction. The material temperature of the rotor during operation can thereby be kept below a predetermined level and thus the
Betriebslebensdauer des Rotors erhöht werden. Die Ausführung des Operating life of the rotor can be increased. The execution of the
erfindungsgemässen kühlbaren Rotors ist an der letzten und den höchsten Temperaturen ausgesetzten Stelle des Rotors am wirksamsten. Die erfindungsgemässen Rotorscheiben können auch an jeder zweckmässigen Stelle des Rotors angeordnet werden, an der eine Kühlung aufgrund der Coolable rotor according to the invention is the most effective at the last and the highest temperatures exposed point of the rotor. The rotor disks according to the invention can also be arranged at any convenient location of the rotor at which cooling due to the
Temperaturverhältnisse gleichsam notwendig oder wirksam ist. Temperature conditions as it is necessary or effective.
In einer weiteren Ausführung der Erfindung weist der Rotor zusätzlich zwischen den stumpf aneinander gestossenen Rotorscheiben im Zentrumsbereich der Scheiben eine Schicht mit einem wärmeleitendem Material auf. Beispielsweise ist diese Schicht an der Oberfläche einer der beiden Rotorscheiben angebracht. Für das wärmeleitende Material ist zum Beispiel ein Metall mit höherer In a further embodiment of the invention, the rotor additionally has a layer with a heat-conducting material between the butted rotor disks in the center region of the disks. For example, this layer is attached to the surface of one of the two rotor disks. For the thermally conductive material is, for example, a metal with higher
Wärmeleitfähigkeit als die des Rotorstahls geeignet. Thermal conductivity than that of the rotor steel suitable.
Durch den Einsatz eines wärmeleitenden Bestandteils wird der Wärmefluss aus der Mitte der Rotorscheibe, also aus dem Bereich um die Rotationsachse und von der ersten zur zweiten aneinander gestossenen Rotorscheiben zur äusserenThrough the use of a thermally conductive component, the heat flow from the center of the rotor disk, ie from the area around the axis of rotation and from the first to the second abutting rotor disks to the outside
Oberfläche des Rotors weiter begünstigt und die zu erwartende Lebensdauer des Rotors weiter erhöht. Surface of the rotor favors and further increases the expected life of the rotor.
Sämtliche der aufgezeigten Ausführungen des erfindungsgemässen Rotors sind nicht nur auf zwei Rotorscheiben beschränkt, sondern lassen sich in geeigneter Weise auf mehrere Rotorscheiben des Rotors anwenden. All of the embodiments of the inventive rotor shown are not limited to two rotor discs, but can be applied in a suitable manner to a plurality of rotor disks of the rotor.
In einem Verfahren zur Herstellung eines kühlbaren Gasturbinen-Verdichter- Rotors wird eine Mehrzahl von Rotorscheiben zusammengeschweisst. In a method of manufacturing a coolable gas turbine compressor rotor, a plurality of rotor disks are welded together.
Erfindungsgemäss werden mindestens zwei Rotorscheiben bereit gestellt, die je eine ringförmige, sich um die Rotationsachse der Scheiben erstreckende According to the invention, at least two rotor disks are provided which each have an annular, extending around the axis of rotation of the disks
Ausnehmung aufweisen, sodass ein Ringraum zwischen den Rotorscheiben entsteht, wenn die Rotorscheiben axial nebeneinander angeordnet werden. Die Rotorscheiben werden an der in Strömungsrichtung letzten und zweitletzten Stelle des Rotors angeordnet und in einem radial äusseren Bereich, der sich von dem Ringraum radial auswärts bis zur äusseren Oberfläche der Scheiben erstreckt, zusammengeschweisst und in einem radialen Zentrumsbereich, der sich von der Rotorscheibenmitte oder der Rotationsachse der Scheiben radial auswärts bis zum Ringraum erstreckt, stumpf aneinander gefügt. Zudem wird an der in Have recess, so that an annular space between the rotor discs is formed when the rotor discs are arranged axially side by side. The rotor disks are arranged at the last and second last position of the rotor in the flow direction and welded together in a radially outer region which extends from the annular space radially outward to the outer surface of the disks and in a radial center region extending from the rotor disk center Rotation axis of the disks radially outward to extends to the annulus, butt joined together. In addition, at the in
Strömungsrichtung letzten Stelle angeordneten Rotorscheibe eine kühlbare Ausnehmung angebracht, die sich über den Umfang der Rotorscheibe erstreckt. Hierfür werden in einer Ausführung des Verfahrens die zwei Rotorscheiben im radial äusseren Bereich zusammengeschweisst und sodann durch Flow direction last location rotor disk mounted a coolable recess extending over the circumference of the rotor disk. For this purpose, in an embodiment of the method, the two rotor disks are welded together in the radially outer region and then through
Schweissschrumpf zusammengezogen. Welded shrinkage contracted.
Durch den Schweissschrumpf entsteht eine Druckeigenspannung, welche eine erhöhte Betriebslebensdauer des Rotors ermöglicht. Due to the welding shrinkage creates a compressive residual stress, which allows an increased service life of the rotor.
In einer Ausführung werden die stumpf aneinander gestossenen Rotorscheiben an der Stelle der höchsten zu erwartenden Materialtemperaturen des Rotors angeordnet. In one embodiment, the butted rotor disks are placed at the location of the highest expected material temperatures of the rotor.
In einer weiteren Ausführung des Verfahrens wird im Zentrumsbereich zumindest einer der zwei in Strömungsrichtung letzten Rotorscheiben eine Schicht eines wärmeleitenden Materials aufgetragen. Danach werden die beiden Rotorscheiben in deren radial äusseren Bereich zusammengeschweisst. Im Zentrumsbereich um die Rotationsachse der Scheiben werden sie wiederum stumpf aneinander gefügt. In a further embodiment of the method, a layer of heat-conducting material is applied in the center region of at least one of the two last rotor disks in the flow direction. Thereafter, the two rotor disks are welded together in their radially outer region. In the center area around the axis of rotation of the discs they are in turn butted together.
Kurze Beschreibung der Zeichnungen Es zeigen Brief description of the drawings It shows
Figur 1 im Querschnitt einen geschweissten Gasturbinenverdichter-Rotor des Standes der Technik.  Figure 1 in cross section a welded gas turbine compressor rotor of the prior art.
Figur 2 im Querschnitt eine erste Ausführung eines Teils eines geschweissten Gasturbinenverdichter-Rotors, insbesondere der Rotorscheiben gemäss der Erfindung. Figur 3 im Querschnitt eine zweite Ausführung eines Teils eines geschweissten Gasturbinenverdichter-Rotors gemäss der Erfindung. Figure 2 in cross section a first embodiment of a part of a welded gas turbine compressor rotor, in particular the rotor disks according to the invention. Figure 3 in cross section a second embodiment of a part of a welded gas turbine compressor rotor according to the invention.
Figur 4 im Querschnitt eine dritte Ausführung eines Teils eines geschweissten Gasturbinenverdichter-Rotors, insbesondere der Rotorscheiben gemäss der Erfindung. 4 shows in cross section a third embodiment of a part of a welded gas turbine compressor rotor, in particular the rotor disks according to the invention.
Gleiche Bezugszeichen in den verschiedenen Figuren bedeuten jeweils gleiche Bestandteile. Like reference numerals in the various figures indicate like components.
Ausführung der Erfindung Embodiment of the invention
Figur 2 zeigt im Längsquerschnitt einen Gasturbinenverdichter-Rotor 1 mit Rotorachse 2. Der Rotor 1 umfasst eine Mehrzahl von Rotorscheiben, wovon in der Figur lediglich Rotorscheiben 3, 4 und 5 dargestellt sind. Die Rotorscheiben sind jeweils so ausgeführt, dass sie mindestens drei Schaufelstufen des FIG. 2 shows in longitudinal cross-section a gas turbine compressor rotor 1 with rotor axis 2. The rotor 1 comprises a plurality of rotor disks, of which only rotor disks 3, 4 and 5 are shown in the figure. The rotor discs are each designed so that they at least three blade stages of the
Verdichters aufnehmen können. Sie unterscheiden sich dadurch von Can accommodate compressor. They differ from it by
Rotorscheiben eines sogenannt„laminar" ausgeführten Rotors, die sich über nur eine Schaufelstufe erstrecken. Rotorscheiben 4 und 5 weisen je in ihrer Mitte eine Ausnehmung auf, die nach Zusammenfügen der Scheiben einen Hohlraum H bilden. Die Rotorscheiben 4 und 5 sind durch Schweissnaht 6 zwischen dem Hohlraum H und der radial äusseren Oberfläche der Scheiben 4 und 5 Rotor disks 4 and 5 each have a recess in their middle, which form a cavity H after joining the disks together the cavity H and the radially outer surface of the discs 4 and 5
miteinander verbunden. Die Rotorscheibe 3 des Rotors des Standes der Technik ist erfindungsgemäss durch zwei einzelne, im Vergleich weniger massiv ausgebildete Rotorscheiben 3a und 3b realisiert. In dem gezeigten Beispiel sind die Rotorscheiben 3a und 3b die in Strömungsrichtung an letzter und zweitletzter Stelle angeordnete Rotorscheiben eines Verdichters. Diese weisen in ihrem Zentrumsbereich an ihren einander axial zugewandten Seiten je eine connected with each other. The rotor disk 3 of the rotor of the prior art is realized according to the invention by two individual, compared to less solid rotor disks 3a and 3b. In the example shown, the rotor disks 3a and 3b are the rotor disks of a compressor arranged in the flow direction at the last and second-last positions. These have in their center region at their axially facing sides each one
Ausnehmung auf, die bei ihrer Zusammenfügung einen Ringraum H" bilden. Die Rotorscheibe 3b ist mit der benachbarten Rotorscheibe 4 mittels einer Schweissnaht 6' auf gleiche Weise wie die Rotorscheiben 4 und 5 The rotor disk 3b is connected to the adjacent rotor disk 4 by means of a weld seam 6 'in the same way as the rotor disks 4 and 5
zusammengefügt. Sie weist stromaufseitig ebenfalls eine Ausnehmung auf, die bei Zusammenfügung mit Scheibe 4 den Hohlraum H' bildet, der dem Hohlraum H ähnlich ist. together. It also has upstream of a recess, the when assembled with disc 4 forms the cavity H ', which is similar to the cavity H.
Die Rotorscheiben 3a und 3b sind in einem radial äusseren Bereich 9' durch die Schweissnaht 10 miteinander verbunden, die sich vom Ringraum H" bis zur Oberfläche des Rotors erstreckt. In einem Zentrumsbereich 9 um die The rotor disks 3a and 3b are interconnected in a radially outer region 9 'by the weld seam 10 which extends from the annular space H "to the surface of the rotor
Rotationsachse 2 der Rotorscheiben 3a und 3b sind die einander zugewandten Oberflächen der Scheiben stumpf aneinander gestossen. Rotation axis 2 of the rotor discs 3a and 3b are the mutually facing surfaces of the discs butted together.
Der Zentrumsbereich 9 des Rotors ist beispielsweise der Bereich, der die The center region 9 of the rotor is, for example, the region containing the
Rotationsachse umfass und sich um die Rotationsachse der Scheiben und über den radial inneren Bereich erstreckt und der von der ringförmigen Ausnehmung an den einander zugewandten Seiten der Rotorscheiben 3a und 3b umgeben ist. Aus diesem Zentrumsbereich ist auch die Wärme abzuführen ist, um eine Überhitzung des Rotors zu vermeiden. Nach Zusammenfügen der Rotorscheiben 3a und 3b bilden die ringförmigen Ausnehmungen der Scheiben den Ringraum H". Der radial äussere Bereich 9' erstreckt sich beispielsweise zwischen den inneren Includes axis of rotation and extends around the axis of rotation of the discs and over the radially inner region and is surrounded by the annular recess on the facing sides of the rotor discs 3a and 3b. From this center area, the heat is dissipate, in order to avoid overheating of the rotor. After joining the rotor disks 3a and 3b, the annular recesses of the disks form the annular space H ". The radially outer region 9 'extends, for example, between the inner ones
Ausnehmungen der Scheiben oder dem Ringraum H" und der Rotoroberfläche. Die stumpfe Aneinanderfügung gewährleistet einen Wärmefluss 8 aus dem Recesses of the disks or the annular space H "and the rotor surface. The butt joint ensures a heat flow 8 from the
Zentrumsbereich 9 der Rotorscheibe 3b über die Rotorscheibe 3a und radial nach aussen zur Rotoroberfläche, wo die Wärme abgeführt werden kann. Center region 9 of the rotor disc 3b via the rotor disk 3a and radially outward to the rotor surface, where the heat can be dissipated.
Figur 3 zeigt den gleichen Rotor wie in Figur 2, jedoch mit dem zusätzlichen Merkmal an der Rotorscheibe 3a, die in Strömungsrichtung am Rotor an letzter Stelle angeordnet ist. Sie weist an ihrer Oberfläche eine Ausnehmung 7 oder Ringnut auf, die sich über den Umfang der Rotorscheibe erstreckt und von aussen durch ein geeignetes Kühlmedium gekühlt werden kann, wie zum Beispiel Kühlluft oder Kühldampf. Die Wärme, die aus dem Zentrumsbereich 9 der Rotorscheiben 3a und 3b an die Oberfläche geleitet wird, wird mit erhöhter Wirksamkeit über die Ausnehmung 7 abgeführt. FIG. 3 shows the same rotor as in FIG. 2, but with the additional feature on the rotor disk 3a, which is arranged last in the flow direction on the rotor. It has on its surface a recess 7 or annular groove which extends over the circumference of the rotor disk and can be cooled from the outside by a suitable cooling medium, such as cooling air or cooling steam. The heat, which is conducted from the center region 9 of the rotor disks 3a and 3b to the surface, is discharged via the recess 7 with increased effectiveness.
In einer besonders wirksamen Ausführung der Erfindung ist die Ausnehmung 7 der Rotorscheibe 3a mit einer elliptischen Querschnittskontur ausgeführt. Figur 4 zeigt eine erweiterte Ausführung des erfindungsgemässen Rotors 1 bestehend wiederum aus Rotorscheiben 3a, 3b, 4, 5. Die Rotorscheiben 3a und 3b weisen wiederum an ihren einander axial zugewandten Seiten je eine ringförmige Ausnehmung auf, die bei der Zusammenfügung einen Ringraum H" bilden. Ein Zentrumsbereich 9 an den einander zugewandten Oberflächen der Rotorscheiben 3a, 3b erstreckt sich über den Bereich, der vom Ringraum H" umgeben wird. Die erweiterte Ausführung unterscheidet sich von dem Rotor von Figur 2 und 3 in der Realisierung des Wärmeübergangs im Zentrumsbereich 9 der Rotorscheiben 3a und 3b. Die Rotorscheibe 3a oder 3b weist in ihrem In a particularly effective embodiment of the invention, the recess 7 of the rotor disk 3a is designed with an elliptical cross-sectional contour. FIG. 4 shows an expanded embodiment of the rotor 1 according to the invention, again comprising rotor disks 3a, 3b, 4, 5. The rotor disks 3a and 3b each have an annular recess on their sides facing each other axially, which form an annular space H "during assembly A center region 9 on the mutually facing surfaces of the rotor disks 3a, 3b extends over the region which is surrounded by the annular space H ". The expanded version differs from the rotor of FIGS. 2 and 3 in the realization of the heat transfer in the center region 9 of the rotor disks 3a and 3b. The rotor disk 3a or 3b has in her
Zentrumsbereich 9 eine Schicht 1 1 eines wärmeleitenden Materials auf. Diese Schicht 1 1 und die Oberfläche des Zentrumsbereichs 9 der Rotorscheibe 3b sind wiederum stumpf aneinander gefügt. Center region 9 a layer 1 1 of a thermally conductive material. This layer 1 1 and the surface of the center region 9 of the rotor disc 3b are in turn butted together.
Die Schicht 1 1 besteht beispielsweise aus einem geeigneten Metall mit einer Wärmeleitfähigkeit grösser als die des Rotormaterials. The layer 1 1 consists for example of a suitable metal having a thermal conductivity greater than that of the rotor material.
Bezugszeichenliste LIST OF REFERENCE NUMBERS
1 Rotor 1 rotor
2 Rotorachse 2 rotor axis
4,5 Rotorscheiben, geschweisst  4.5 rotor disks, welded
3 letzte Rotorscheibe  3 last rotor disc
3a, 3b Rotorscheiben, stumpf aneinander gefügt und geschweisst 3a, 3b rotor disks, butt joined to each other and welded
6, 6' Schweissnaht 6, 6 'weld
7 Ausnehmung 7 recess
8 Wärmefluss  8 heat flow
9 Zentrumsbereich  9 center area
9' radial äusserer Bereich  9 'radially outer region
10 Schweissnaht  10 weld
1 1 wärmeleitende Schicht 1 1 heat-conducting layer
H, H' Hohlraum  H, H 'cavity
H" Ringraum  H "annulus

Claims

Patentansprüche claims
1 . Kühlbarer Gasturbinenverdichter-Rotor (1 ) mit einer Mehrzahl von zusammengeschweissten Rotorscheiben (3a, 3b, 4, 5), wobei jede Rotorscheibe (3a, 3b, 4, 5) sich über mindestes drei Schaufelstufen erstreckt, wovon 1 . A refrigerated gas turbine compressor rotor (1) having a plurality of welded together rotor disks (3a, 3b, 4, 5), each rotor disk (3a, 3b, 4, 5) extending over at least three blade stages, of which
mindestens zwei Rotorscheiben (3a, 3b) axial nebeneinander und in at least two rotor disks (3a, 3b) axially next to each other and in
Strömungsrichtung an der letzten und zweitletzten Stelle des Rotors (1 ) angeordnet sind, Flow direction are arranged at the last and second last position of the rotor (1),
dadurch gekennzeichnet, dass characterized in that
die Rotorscheiben (3a, 3b) einen Zentrumsbereich (9) aufweisen, der die the rotor disks (3a, 3b) have a center region (9) which surrounds the
Rotationsachse (2) des Rotors (1 ) umfasst und sich von der Rotationsachse (2) radial auswärts erstreckt, und die Rotorscheiben (3a, 3b) einen radial äusseren Bereich (9') aufweisen, der die radial äussere Oberfläche des Rotors umfasst und sich radial einwärts erstreckt, und Axis of rotation (2) of the rotor (1) and extending radially outwards from the axis of rotation (2), and the rotor discs (3a, 3b) have a radially outer region (9 ') which surrounds the radially outer surface of the rotor and extends radially inwardly, and
zur Abführung von Wärme aus dem Zentrumsbereich (9) der zwei, in for dissipating heat from the center area (9) of the two, in
Strömungsrichtung letzten Rotorscheiben (3a, 3b) die zwei, in Strömungsrichtung letzten Rotorscheiben (3a, 3b) in ihrem Zentrumsbereich (9) stumpf aneinander gestossen sind und in ihrem radial äusseren Bereich (9') der Rotorscheiben (3a, 3b), zusammengeschweisst sind und Flow direction last rotor discs (3a, 3b), the two, in the flow direction last rotor discs (3a, 3b) butted in their central region (9) butt together and in its radially outer region (9 ') of the rotor discs (3a, 3b), welded together and
zwischen dem Zentrumsbereich (9) und dem radial äusseren Bereich (9') der zwei, in Strömungsrichtung letzten Rotorscheiben (3a, 3b) sich ein Ringraum (H") erstreckt, und die in Strömungsrichtung letzte der zwei stumpf aneinander gestossenen Rotorscheiben (3a, 3b) an ihrer radial äusseren Oberfläche eine Ausnehmung (7) aufweist, die durch ein von aussen zugeführtes Kühlmedium kühlbar ist und die sich über den Umfang der Rotorscheibe erstreckt. between the center region (9) and the radially outer region (9 ') of the two, in the direction of flow last rotor discs (3a, 3b) an annular space (H ") extends, and in the flow direction last of the two blunt abutting rotor discs (3a, 3b) has on its radially outer surface a recess (7) which can be cooled by an externally supplied cooling medium and which extends over the circumference of the rotor disk.
2. Rotor (1 ) nach Anspruch 1 2. Rotor (1) according to claim 1
dadurch gekennzeichnet, dass characterized in that
zwischen den stumpf aneinander gestossenen Rotorscheiben (3a, 3b) in deren Zentrumsbereich (9) eine Schicht (1 1 ) mit einem wärmeleitenden Material angeordnet ist. between the butted rotor discs (3a, 3b) in the central region (9) a layer (1 1) is arranged with a thermally conductive material.
3. Rotor (1 ) nach Anspruch 2 3. rotor (1) according to claim 2
dadurch gekennzeichnet, dass characterized in that
die Schicht (1 1 ) auf die Oberfläche einer der stumpf aneinander gestossenen Rotorscheiben (3a, 3b) aufgetragen ist. the layer (1 1) is applied to the surface of one of the blunt abutting rotor disks (3a, 3b).
4. Rotor (1 ) nach Anspruch 2 oder 3 4. rotor (1) according to claim 2 or 3
dadurch gekennzeichnet, dass characterized in that
die Ausnehmung (7) eine elliptische Querschnittskontur aufweist. the recess (7) has an elliptical cross-sectional contour.
5. Rotor (1 ) nach einem der vorangehenden Ansprüche 1 bis 4 5. rotor (1) according to one of the preceding claims 1 to 4
dadurch gekennzeichnet, dass characterized in that
die stumpf aneinander gestossenen Rotorscheiben (3a, 3b) an einer Stelle am Rotor mit einer der höchsten Materialtemperatur im gesamten Rotor angeordnet ist. the bluntly abutted rotor disks (3a, 3b) is arranged at one point on the rotor with one of the highest material temperature in the entire rotor.
6. Verfahren zur Herstellung eines Gasturbinenverdichter-Rotors (1 ), wobei eine Mehrzahl von Rotorscheiben (4, 5) zusammengeschweisst werden, die sich über mindestens drei Schaufelstufen des Verdichters erstrecken 6. A method of manufacturing a gas turbine compressor rotor (1), wherein a plurality of rotor disks (4, 5) are welded together, which extend over at least three blade stages of the compressor
dadurch gekennzeichnet, dass characterized in that
mindestens zwei Rotorscheiben (3a, 3b) bereit gestellt werden, die je eine ringförmige, sich um die Rotationsachse der Scheiben erstreckende Ausnehmung aufweisen und die Rotorscheiben axial nebeneinander angeordnet werden, sodass ein Ringraum zwischen den Rotorscheiben entsteht, und at least two rotor disks (3a, 3b) are provided, each having an annular, extending around the axis of rotation of the disks recess and the rotor disks are arranged axially adjacent to each other, so that an annular space between the rotor disks is formed, and
die Rotorscheiben (3a, 3b) an der in Strömungsrichtung letzten und zweitletzten Stelle des Rotors (1 ) angeordnet werden und the rotor disks (3a, 3b) are arranged at the flow direction last and second last position of the rotor (1) and
in einem radial äusseren Bereich (9'), der sich von dem Ringraum (H") radial auswärts bis zur äusseren Oberfläche der Scheiben (3a, 3b) erstreckt, in a radially outer region (9 ') extending radially outward from the annulus (H ") to the outer surface of the discs (3a, 3b),
zusammengeschweisst werden und be welded together and
in einem radialen Zentrumsbereich (9), der sich von der Rotorscheibenmitte oder der Rotationsachse (2) der Scheiben (3a, 3b) radial auswärts bis zum Ringraum (H") erstreckt, stumpf aneinander gefügt werden, und an der äusseren Oberfläche der in Strömungsrichtung letzten Stelle angeordneten Rotorscheibe (3a) eine Ausnehmung (7) realisiert wird. in a radial center region (9) which extends radially outwardly from the rotor disk center or the axis of rotation (2) of the disks (3a, 3b) to the annular space (H "), and A recess (7) is realized on the outer surface of the rotor disk (3a) arranged last in the flow direction.
7. Verfahren nach Anspruch 6 7. The method according to claim 6
dadurch gekennzeichnet, dass characterized in that
die stumpf aneinander gestossenen Rotorscheiben (3a, 3b) durch the blunt abutting rotor discs (3a, 3b)
Schweissschrumpf zusammengezogen werden. Weld shrinkage be contracted.
8. Verfahren nach Anspruch 6 oder 7 8. The method according to claim 6 or 7
dadurch gekennzeichnet, dass characterized in that
vor dem stumpf aneinander Stossen und Schweissen der Rotorscheiben (3a, 3b) im Zentrumsbereich (9) um die Rotationsachse der Rotorscheiben (3a, 3b) zwischen den Rotorscheiben (3a, 3b) eine Schicht (1 1 ) mit einem wärmeleitenden Material angeordnet wird. Before the butting together and welding of the rotor disks (3a, 3b) in the center region (9) about the axis of rotation of the rotor disks (3a, 3b) between the rotor disks (3a, 3b) a layer (1 1) is arranged with a thermally conductive material.
EP10771153.3A 2009-11-04 2010-10-29 Welded rotor of a gas turbine engine compressor Not-in-force EP2496793B1 (en)

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CH01699/09A CH702191A1 (en) 2009-11-04 2009-11-04 Welded rotor.
PCT/EP2010/066501 WO2011054758A1 (en) 2009-11-04 2010-10-29 Welded rotor of a gas turbine engine compressor

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Publication number Publication date
CH702191A1 (en) 2011-05-13
JP2013510259A (en) 2013-03-21
US20120275926A1 (en) 2012-11-01
JP5559343B2 (en) 2014-07-23
EP2496793B1 (en) 2015-09-09
CN102667064B (en) 2015-01-14
WO2011054758A4 (en) 2011-08-18
US8517676B2 (en) 2013-08-27
CN102667064A (en) 2012-09-12
WO2011054758A1 (en) 2011-05-12

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