EP2496793A1 - Rotor soudé d'un compresseur de groupe motopropulseur de turbines à gaz - Google Patents

Rotor soudé d'un compresseur de groupe motopropulseur de turbines à gaz

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)
English (en)
Other versions
EP2496793B1 (fr
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/fr
Application granted granted Critical
Publication of EP2496793B1 publication Critical patent/EP2496793B1/fr
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

L'invention concerne un rotor (1) et un procédé de production correspondant d'un compresseur de turbines à gaz, comprenant une pluralité de disques de rotor (3a, 3b, 4, 5) soudés entre eux, deux ou plusieurs disques de rotor (3a, 3b) étant soudés entre eux dans une zone extérieure radiale (9'), et assemblés bout à bout dans une zone centrale intérieure radiale. Du fait de l'assemblage bout à bout de deux disques de rotor (3a, 3b), un flux thermique (8) s'écoule à partir du centre du rotor (1), radialement vers l'extérieur, de sorte que la température du matériau du rotor (1) peut être maintenue, pendant le fonctionnement, inférieure à un niveau prédéterminé. De ce fait, la durée de service du rotor (1) peut être accrue. Les disques de rotor (3a, 3b) soudés et assemblés bout à bout selon l'invention, sont utilisables en dernier lieu dans le sens d'écoulement du compresseur, un disque de rotor (3a) présentant en outre à sa surface, un évidement (7) qui peut être refroidi de l'extérieur.
EP10771153.3A 2009-11-04 2010-10-29 Rotor soudé d'un compresseur de groupe motopropulseur de turbines à gaz Not-in-force EP2496793B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH01699/09A CH702191A1 (de) 2009-11-04 2009-11-04 Geschweisster Rotor.
PCT/EP2010/066501 WO2011054758A1 (fr) 2009-11-04 2010-10-29 Rotor soudé d'un compresseur de groupe motopropulseur de turbines à gaz

Publications (2)

Publication Number Publication Date
EP2496793A1 true EP2496793A1 (fr) 2012-09-12
EP2496793B1 EP2496793B1 (fr) 2015-09-09

Family

ID=41611368

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10771153.3A Not-in-force EP2496793B1 (fr) 2009-11-04 2010-10-29 Rotor soudé d'un compresseur de groupe motopropulseur de turbines à gaz

Country Status (6)

Country Link
US (1) US8517676B2 (fr)
EP (1) EP2496793B1 (fr)
JP (1) JP5559343B2 (fr)
CN (1) CN102667064B (fr)
CH (1) CH702191A1 (fr)
WO (1) WO2011054758A1 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140137712A1 (en) * 2012-11-20 2014-05-22 General Electric Company Lathe center
EP2826956A1 (fr) * 2013-07-17 2015-01-21 Siemens Aktiengesellschaft Rotor pour une turbomachine thermique
US10385433B2 (en) 2016-03-16 2019-08-20 Honeywell International Inc. Methods for processing bonded dual alloy rotors including differential heat treatment processes
CN106121733B (zh) * 2016-08-12 2019-01-11 上海电气燃气轮机有限公司 一种用于重型燃气轮机的混合转子结构及组装方法

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DE879343C (de) * 1942-05-22 1953-06-11 Vorkauf Heinrich Laeufer fuer fluessigkeitsgekuehlte Gasturbinen
US2462600A (en) * 1943-01-16 1949-02-22 Jarvis C Marble Turbine
US2657008A (en) * 1947-08-07 1953-10-27 Atkinson Joseph Turbine or like rotor
FR2567069B1 (fr) 1984-07-03 1986-12-05 Lhomme Sa Procede et dispositif de fabrication d'un tube de carton calibre a tres faible rugosite de surface et haute stabilite dimensionnelle
DE4239710A1 (de) * 1992-11-26 1994-06-01 Abb Patent Gmbh Läufer einer Turbine
DE4324034A1 (de) 1993-07-17 1995-01-19 Abb Management Ag Gasturbine mit gekühltem Rotor
DE19648185A1 (de) * 1996-11-21 1998-05-28 Asea Brown Boveri Geschweisster Rotor einer Strömungsmaschine
JP3999402B2 (ja) * 1998-06-09 2007-10-31 三菱重工業株式会社 蒸気タービンの異材溶接ロータ
DE19839592A1 (de) 1998-08-31 2000-03-02 Asea Brown Boveri Strömungsmaschine mit gekühlter Rotorwelle
DE10112062A1 (de) * 2001-03-14 2002-09-19 Alstom Switzerland Ltd Verfahren zum Zusammenschweißen zweier thermisch unterschiedlich belasteter Teile sowie nach einem solchen Verfahren hergestellte Turbomaschine
US7119461B2 (en) * 2003-03-25 2006-10-10 Pratt & Whitney Canada Corp. Enhanced thermal conductivity ferrite stator
EP1705339B1 (fr) 2005-03-23 2016-11-30 General Electric Technology GmbH Arbre de rotor, particulièrement pour une turbine à gaz
JP4793087B2 (ja) * 2006-05-11 2011-10-12 三菱電機株式会社 圧縮機の製造方法
JP5049578B2 (ja) * 2006-12-15 2012-10-17 株式会社東芝 蒸気タービン
CH700176B1 (de) * 2007-03-02 2010-07-15 Alstom Technology Ltd Rotor für einen Generator.
JP2009103097A (ja) * 2007-10-25 2009-05-14 Mitsubishi Heavy Ind Ltd ガスタービン、及びガスタービン用ロータ

Non-Patent Citations (1)

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Title
See references of WO2011054758A1 *

Also Published As

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

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