EP0844367B1 - Rotor soudé pour une turbomachine - Google Patents

Rotor soudé pour une turbomachine Download PDF

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Publication number
EP0844367B1
EP0844367B1 EP97810814A EP97810814A EP0844367B1 EP 0844367 B1 EP0844367 B1 EP 0844367B1 EP 97810814 A EP97810814 A EP 97810814A EP 97810814 A EP97810814 A EP 97810814A EP 0844367 B1 EP0844367 B1 EP 0844367B1
Authority
EP
European Patent Office
Prior art keywords
rotor
cooling medium
web
holes
rotor according
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.)
Expired - Lifetime
Application number
EP97810814A
Other languages
German (de)
English (en)
Other versions
EP0844367A1 (fr
Inventor
Wilhelm Dr. Endres
Fritz Schaub
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.)
Alstom SA
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Alstom SA
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 SA filed Critical Alstom SA
Publication of EP0844367A1 publication Critical patent/EP0844367A1/fr
Application granted granted Critical
Publication of EP0844367B1 publication Critical patent/EP0844367B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D5/06—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
    • 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

Definitions

  • the present invention relates to a welded rotor a turbomachine according to the preamble of claim 1.
  • the rotor internal Intermediate channels for the flow of the cooling medium in the plane of the radial or quasi-radial Weld seams must have annular cavities, which indispensable for the flow and transfer of the cooling medium to the blades to be cooled are necessary, whereby the type of welding bridging of the radial or quasi-radial welding seams in the area of these Cavities weight the operational quality of such a rotor influence.
  • FR 876.194 describes a welded rotor for a steam turbine or for known a gas turbine.
  • This rotor is made up of rotor disks 1 which are connected to one another by means of weld seams 8 and form the rotor body. Cavities are arranged between these rotor disks Cooling channels 13 are interconnected. The cavities become radial outside through the weld seams 8 and radially inside through the (composite) rotor shaft limited.
  • the invention seeks to remedy this.
  • the invention how it is characterized in the claims, the task lies based on one with a cooling medium that is efficient per se propose precautions for the cooled rotor of the type mentioned at the outset, which fix the above disadvantages capital.
  • the leadership is proposed according to the invention of the cooling medium in a gas turbine rotor thus take place let this start from one mostly in the center of the wave at the end of the axial feed radial or quasi-radial lead to the outside, then this cooling medium axially or quasi-axially to the individual feet of the ones to be cooled To make blades flow, and in a similar way and Way backflow until cooling steam emerges from the rotor to be designed so that this coolant outlet preferably is an annular channel concentric with the cooling medium inlet runs.
  • the main advantage of the invention is that even with a disc made of welded together Rotor for a gas turbine cooling with a Amount of steam can be carried out, the cooling circuit is hermetically sealed inside the rotor, and it only through forged material or weld metal.
  • the one in the area of the weld seams existing annular cavities for the Transfer of the cooling medium to the individual to be cooled Blades are made without affecting the mechanical Properties of these weld seams.
  • the Design of these cavities kept so that the continuation the radial or quasi-radial welding seams can be carried out optimally in terms of welding technology.
  • the internal cooling system is therefore tangential Cooling channels are formed which run in the circumferential direction, in such a way that the cooling medium is distributed around the circumference and opens into axial or oblique cooling channels.
  • intermediate ring-shaped cavities are the ones that impose themselves there Bridging and continuing the radial or quasi-radial to accomplish running weld seams with an insert ring, preferably with one in the cavity protruding web is provided.
  • This insert ring takes over then the centering and the radial support at Welding the continuation weld.
  • the bridge points over it holes on the outside, which are on the largest radius of the web and through which the coolant inside can flow through the respective annular cavity.
  • Radial slots catch the thermal expansion of the webs on, using the holes above to drain the condensed water the ends of said slots before stress concentration protects.
  • Another advantage of the invention is that these slits in the web at least the tangential elongation of the same during the start-up process of the system capital.
  • Fig. 1 shows an internal cooling system, as is the case with rotors of turbomachines, in particular of gas turbines for use arrives.
  • the rotor 1 is equipped with blades 2 from a number of welded disks like this the course of the weld seams 6 emerges. Between Blades 2 are guide vanes 3, which are used for Stator belong to this flow machine.
  • a system from flowed with a cooling medium 14 and in the circumferential direction of the rotor 1 distributed channels runs through the axial extent of the rotor 1, such that the rotor blades 2 therefore, by means of appropriately provided branches, either can be cooled in parallel or in series.
  • Fig. 1 shows in this regard, based on the cooling of the blades 2 of a series connection.
  • Main cooling medium cavity 12 branches at least one inflow channel 4 starting from the center of the rotor 1 leads to the outside. In the area of the rotor outer surface 13 for each inflow channel 4, preferably a non-visible one Separator of dust particles assigned. The said inflow channel 4 then goes in downstream of such a separator one running essentially axially or quasi-axially another inflow channel 9 over.
  • This inflow channel 9 ends at the end of the rotor 1 equipped with blades in an internal rotor annular cavity 5, from where via a branch channel 7 a first blade 2 respectively. Blade row is cooled.
  • Cooling medium 14 happens from the cooled blade 2 via a further branch channel 8, which in turn is intermediate into another rotor-shaped annular cavity 5a opens, from here the cooling of the remaining Make blades gradually in an analogous manner goes.
  • This outflow channel 10 then goes in the area of the not visible Separator in a radial or quasi-radial Backflow channel 11 over which the cooling medium 15 to a promotes further, not visible consumers or leads out of the rotor 1.
  • steam is preferably used, for example at a combined system (gas / steam system) in any case sufficient Quantity and quality regarding cooling efficiency available stands.
  • Fig. 2 shows the part highlighted in Fig. 1 in the area of internal annular cavity 5a and that in FIG. 1 not visible continuation of the rotor welding, the through said cavity 5a in a radial course is interrupted.
  • a via weld seams 21 with the rotor 1 connected annular insert ring 20, which is attached from the outside can be with one each in the cavity 5a protruding web 25 provided the centering and radial support during welding.
  • the web 25 of the Insert ring 20 is further provided with holes 22, so that the cooling medium 14 is passed within the cavity 5a can be.
  • FIG. 3 is an axial view of the insert ring according to FIG. 2 and shows the arrangement of the holes 22 for the flow of the cooling medium within the cavity (see FIGS. 1 and 2, Pos. 5, 5a, 5b).
  • These holes 22 are the largest on the outside Radius of the web 25 arranged.
  • Radially extending from the holes 22 Slots 24 protect the webs 25 in particular from tangential thermal expansion occurring during the start-up process as well as in the transient load ranges of the plant. turn the ends of these slots 24 through said holes 22 protected against stress concentration.
  • the insert ring 20 with web 25 consists of at least 2 in the circumferential direction Share what makes them easy to install from the outside, and then lightly together with longitudinal weld seams 23 can be connected.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Butt Welding And Welding Of Specific Article (AREA)

Claims (9)

  1. Rotor soudé pour une turbomachine, qui est parcouru par le biais de canaux d'alimentation et de sortie (9, 10) internes au rotor, par un fluide de refroidissement (14), le rotor (1) se composant d'une pluralité de disques (1a, 1b, 1c, 1d), et les disques adjacents (1a, 1b, 1c, 1d) étant reliés les uns aux autres par le biais de cordons de soudure (6) s'étendant radialement ou quasi radialement, caractérisé en ce qu'entre chaque cordon de soudure (6) et entre chaque prolongement de cordon de soudure (6a) respectif, appartenant radialement vers l'extérieur à chaque cordon de soudure (6), reliant les disques voisins (1a, 1b, 1c, 1d), est disposé à chaque fois un espace creux (5, 5a, 5b) de forme annulaire interne au rotor, parcouru par le fluide de refroidissement (14), en ce que chaque espace creux (5, 5a, 5b) est entouré par au moins une bague d'insertion (20) s'étendant dans la direction périphérique, et en ce que le prolongement de cordon de soudure (6a) est monté sur la bague d'insertion (20).
  2. Rotor selon la revendication 1, caractérisé en ce que le fluide de refroidissement (14) est de la vapeur.
  3. Rotor selon la revendication 1, caractérisé en ce que les espaces creux (5, 5a, 5b) présentent une largeur axiale plus grande que celle des cordons de soudure (6) et des prolongements de cordons de soudure (6a).
  4. Rotor selon la revendication 1, caractérisé en ce que la bague d'insertion (20) présente une ailette (25) pénétrant à l'intérieur de l'espace creux (5, 5a, 5b), laquelle assure le centrage et le support radial du prolongement de cordon de soudure (6a).
  5. Rotor selon la revendication 4, caractérisé en ce que l'ailette (25) est pourvue de trous (22) pour le passage du fluide de refroidissement (14) à l'intérieur de l'espace creux (5, 5a, 5b).
  6. Rotor selon les revendications 1 et 5, caractérisé en ce que l'arrivée du fluide de refroidissement (14) dans les espaces creux (5, 5a, 5b) et sa sortie présentent un rayon plus grand depuis le centre du rotor (1), par rapport au plan de l'écoulement du fluide de refroidissement (14) à travers les trous (22) de l'ailette (25).
  7. Rotor selon la revendication 5, caractérisé en ce que les trous (22) sont disposés sur le plus grand rayon de l'ailette (25).
  8. Rotor selon la revendication 5, caractérisé en ce que les trous (22) sont tangents, par leur partie extérieure, au plus grand rayon de l'ailette (25).
  9. Rotor selon la revendication 5, caractérisé en ce que l'ailette (25) en relation fonctionnelle avec les trous (22) présente des fentes (24) orientées radialement ou quasi radialement vers le centre du rotor.
EP97810814A 1996-11-21 1997-10-31 Rotor soudé pour une turbomachine Expired - Lifetime EP0844367B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19648185A DE19648185A1 (de) 1996-11-21 1996-11-21 Geschweisster Rotor einer Strömungsmaschine
DE19648185 1996-11-21

Publications (2)

Publication Number Publication Date
EP0844367A1 EP0844367A1 (fr) 1998-05-27
EP0844367B1 true EP0844367B1 (fr) 2002-04-10

Family

ID=7812337

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97810814A Expired - Lifetime EP0844367B1 (fr) 1996-11-21 1997-10-31 Rotor soudé pour une turbomachine

Country Status (3)

Country Link
US (1) US5993154A (fr)
EP (1) EP0844367B1 (fr)
DE (2) DE19648185A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6519849B2 (en) 1998-12-10 2003-02-18 Alstom (Switzerland) Ltd Method for the manufacture of a welded rotor of a fluid-flow machine
US8517676B2 (en) 2009-11-04 2013-08-27 Alstom Technology Ltd Welded rotor of a gas turbine engine compressor

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP4777489B2 (ja) * 1997-03-31 2011-09-21 ザ チルドレンズ メディカル センター コーポレーション アポトーシス性酵素を不活性化するためのニトロシル化
US6393831B1 (en) 2000-11-17 2002-05-28 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Exoskeletal engine
DE10355738A1 (de) * 2003-11-28 2005-06-16 Alstom Technology Ltd Rotor für eine Turbine
JP5049578B2 (ja) * 2006-12-15 2012-10-17 株式会社東芝 蒸気タービン
US20090060735A1 (en) * 2007-08-31 2009-03-05 General Electric Company Turbine rotor apparatus and system
US20110262277A1 (en) * 2008-12-18 2011-10-27 Volvo Aero Corporation Gas turbine composite workpiece to be used in gas turbine engine
EP3486430A1 (fr) * 2017-11-17 2019-05-22 Siemens Aktiengesellschaft Étage de rotor de turbine formé intégralement
US10927767B2 (en) 2018-09-24 2021-02-23 Rolls-Royce Corporation Exoskeletal gas turbine engine

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR876194A (fr) * 1939-08-04 1942-10-29 Sulzer Ag Rotor soudé pour turbines à vapeur ou à gaz
US2369051A (en) * 1942-07-10 1945-02-06 Sulzer Ag Welded turbine rotor
GB612097A (en) * 1946-10-09 1948-11-08 English Electric Co Ltd Improvements in and relating to the cooling of gas turbine rotors
GB646483A (en) * 1948-04-13 1950-11-22 Hubert Thomas Lewis Improvements in and relating to turbine and like rotors
US2637521A (en) * 1949-03-01 1953-05-05 Elliott Co Gas turbine rotor and method of welding rotor disks together
DE4324034A1 (de) * 1993-07-17 1995-01-19 Abb Management Ag Gasturbine mit gekühltem Rotor
US5593274A (en) * 1995-03-31 1997-01-14 General Electric Co. Closed or open circuit cooling of turbine rotor components

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6519849B2 (en) 1998-12-10 2003-02-18 Alstom (Switzerland) Ltd Method for the manufacture of a welded rotor of a fluid-flow machine
US6687994B2 (en) 1998-12-10 2004-02-10 Alstom Technology Ltd. Method for the manufacture of a welded rotor of a fluid-flow machine
US8517676B2 (en) 2009-11-04 2013-08-27 Alstom Technology Ltd Welded rotor of a gas turbine engine compressor

Also Published As

Publication number Publication date
US5993154A (en) 1999-11-30
EP0844367A1 (fr) 1998-05-27
DE59706955D1 (de) 2002-05-16
DE19648185A1 (de) 1998-05-28

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