EP1143108A1 - Méthode de fabrication d'un segment statorique à ailettes et segment statorique à ailettes - Google Patents

Méthode de fabrication d'un segment statorique à ailettes et segment statorique à ailettes Download PDF

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Publication number
EP1143108A1
EP1143108A1 EP00107572A EP00107572A EP1143108A1 EP 1143108 A1 EP1143108 A1 EP 1143108A1 EP 00107572 A EP00107572 A EP 00107572A EP 00107572 A EP00107572 A EP 00107572A EP 1143108 A1 EP1143108 A1 EP 1143108A1
Authority
EP
European Patent Office
Prior art keywords
guide vane
ring
guide
recesses
turbine
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Withdrawn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
EP00107572A
Other languages
German (de)
English (en)
Inventor
Karlheinz Dipl.-Ing. Heine
Joachim Dipl.-Ing. Schulz
Werner Dipl.-Ing. Heine
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 EP00107572A priority Critical patent/EP1143108A1/fr
Publication of EP1143108A1 publication Critical patent/EP1143108A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F01D9/044—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators permanently, e.g. by welding, brazing, casting or the like
    • 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
    • F05D2230/60—Assembly methods

Definitions

  • the invention relates to a method for producing a Guide vane component and a guide vane component for one Turbine, especially for a high pressure or medium pressure stage a turbine.
  • thermal Turbomachinery used, for example gas and steam turbines.
  • the blading has an effect Wing-like profiles that are in annular guide and Blade grilles are arranged as a transmission element.
  • a guide vane and rotor vane grate each form a work stage. Since the ability to implement a stage is limited, in As a rule, turbines have several stages, depending on the thermal gradient of the working medium.
  • the guide vanes of a turbine are arranged in a ring and form a vane ring.
  • this is formed from individual guide vane parts, in which the actual Airfoil usually made of profile material, in the blade root area by means of spacers and Bucket head area is fixed using a shroud.
  • the spacers have the particular task of doing the necessary Distance between the guide vanes and the rotational position to ensure the guide vanes.
  • the twist position is set using the so-called opening angle and is essential for the flow control.
  • the mutual The distance between the individual blades is also called Called division.
  • the invention has for its object a method for Production of a guide vane component and a guide vane component specify where easy manufacture is possible is.
  • the first ring is in particular an outer ring and the second ring an inner ring arranged concentrically to the outer ring.
  • the main difference from the conventional one Process can be seen in the fact that the guide vane ring, in particular its outer ring, not from the multitude described above Guide vane parts, in particular intermediate pieces, is built up. Rather, the outer ring is in the making initially in one piece. This makes it much faster and also enables easier assembly. Due to the The individual guide vanes are simple and with recesses mountable with high accuracy.
  • the outer ring recesses with a to the guide vane profile customized profiles incorporated so that the guide vanes held in the exact position in the outer ring.
  • the position of each in an advantageous manner Set guide vanes to each other with high accuracy.
  • the recesses in the outer ring are preferably profiled in such a way that that is, with one adapted to the guide vane profile Profile formed that the rotational position of the guide vane is fixed with respect to the axial axis of the outer ring.
  • the profiled configuration of the recesses is therefore particularly both the pitch and the so-called opening angle determined with high accuracy and precision.
  • this manufacturing method in particular for manufacturing a Guide vane component for a high pressure or medium pressure stage a turbine. These usually point in comparison very small guide vanes at a low pressure level on.
  • the guide vanes in the recesses in particular by means of laser welding or electron beam welding welded.
  • the laser for cutting the recesses or the laser for welding is the material thickness to choose differently of the outer ring.
  • Enabling lasers of conventional power is in a preferred embodiment on the outer ring around it Support ring attached. This is particularly true after completion of the guide vane ring attached to the outer ring and gives the guide vane ring a sufficiently high mechanical Strength.
  • the guide vane component i.e. the guide vane ring or the vane segment
  • the guide vane component i.e. the guide vane ring or the vane segment
  • the fully automatic production is made possible by the simple manufacturing process, where the individual guide vanes with the two rings are welded, being in recesses of the outer ring be introduced.
  • a guide vane component for a turbine in particular for a high pressure or medium pressure stage of a turbine in which a vane between a first ring segment and a Another ring segment is arranged and in particular formed as an opening of the first ring segment with its first end and on the second ring segment is attached to its second end.
  • the first ring segment is preferably an outer ring segment, and the second Ring segment an inner ring segment.
  • a turbine 1, in particular one Power plant turbine for a power plant for the generation of energy is designed for an output of up to more than one gigawatt, a high pressure part 1A and a low pressure part 1B. This is in the direction of flow of a drive medium which Flows through turbine 1, downstream of the high pressure part 1A.
  • the drive medium namely steam in the case of a steam turbine and gas in the case of a gas turbine, the pipe 5 High pressure and low pressure part 1A, 1B supplied and discharged.
  • the Drive medium drives the shaft 3 by means of it Blades on.
  • the drive medium is through the turbine 1 passed over fixed guide vanes.
  • the blades and guide vanes of the high pressure and low pressure part 1A, 1B are not shown in FIG. 1.
  • the Guide blades and the blades of a turbine stage are usually arranged side by side in the circumferential direction and each form a blade ring. This changes in the axial direction 8 of the turbine 1 guide vane rings and moving vane rings from.
  • a production method is described with reference to FIG. 2, that ensures high dimensional accuracy and positioning accuracy.
  • a process step A of the manufacturing process becomes a first ring, namely an outer ring 2 manufactured.
  • a flat steel becomes one Ring curved.
  • This ring will then be more appropriate Machined to form the outer ring 2.
  • the two ends of the flat steel become together
  • the ring is welded and the ring is annealed.
  • the surfaces of the ring are treated as needed, for example Grooves screwed in.
  • the outer ring 2 several recesses 4 mainly in the form of openings incorporated.
  • the recesses 4 are circumferential around the entire Outer ring 2 introduced. Are in the embodiment only four recesses 4 are shown.
  • the recesses 4 designed as openings serve for Pickup and for precise positioning of the guide vanes 6.
  • the recesses 4 have a guide vane 6 customized profile.
  • the recesses 4 are in particular by means of laser welding or water jet processes incorporated into the outer ring 2 precisely and in accordance with the profile.
  • the guide vanes 6 are successively inserted into the recesses 4 assigned to them and arranged between the outer ring 2 and an inner ring 10.
  • the guide vanes 6 are preferably from the outside pushed through the recesses 4 in the direction of the inner ring 10. Because of the profiled design of the recesses 4, the individual guide blades 6 in the recesses 4 positioned in a fixed position and secure against rotation. So that is both Distance, the so-called division, of adjacent guide vanes 6 fixed to each other as well as their so-called opening angle in relation to the axial axis 8 of the outer ring 2.
  • the opening angle gives the position or rotational position of the cross-sectional profile of the guide vanes 6 with respect to the axial axis 8.
  • a vane ring 16 formed of an outer ring 2, an inner ring 10 and guide vanes evenly spaced apart therebetween 6 has.
  • the guide vanes 6 extend around the entire, between the inner ring 10 and the outer ring 2 formed ring surface.
  • a support ring 18 is applied, which around the outer ring 2 preferably runs around completely as a closed ring.
  • This support ring 18 serves to increase the mechanical strength of the vane ring 16.
  • 10 can also be on this support ring 18 to be dispensed with.
  • the outer ring 2 is clear stronger than in the variant with support ring 18.
  • a last step E the guide vane ring 16 divided into several guide vane segments 20, wherein only one guide vane segment 20 is shown in FIG. 2, which has four guide vanes 6.
  • the division of the Guide vane ring 16 takes place in guide vane segments 20 through suitable separation processes.
  • the guide vane segments 20 each have a first ring segment, namely an outer ring segment 24, and a second ring segment, namely a Inner ring segment 22, with the individual guide blades 6 from the inner ring segment 22 to the recesses 4 of the outer ring segment 24 are enough.
  • the method step E is shown the support ring 18 omitted for clarity.
  • the division of the guide vane ring 16 into several guide vane segments 20 is preferably done after attachment the support ring 18.
  • the size of the individual guide vane segments 20 depends after their thermal stress during the operation of the turbine. It is essential that due to the thermal Load between the individual guide vane segments 20 sufficient expansion gaps are provided.
  • the individual process steps, in particular the process steps B and C and then attaching the Guide vanes 6 are preferably automatic, in particular fully automatic.
  • the manufacturing process described it is very well suited for automatic production. With automatic production, a significantly higher one Accuracy and productivity achieved when doing this manually conventional type is possible. This will change the flow conditions in the turbine compared to the conventional manufacturing process improved. Because of compared to the guide vanes of a low-pressure part comparatively small guide vanes of a high pressure or medium pressure part points out the new procedure especially for one High-pressure or medium-pressure stage assembly advantages on.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP00107572A 2000-04-07 2000-04-07 Méthode de fabrication d'un segment statorique à ailettes et segment statorique à ailettes Withdrawn EP1143108A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP00107572A EP1143108A1 (fr) 2000-04-07 2000-04-07 Méthode de fabrication d'un segment statorique à ailettes et segment statorique à ailettes

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP00107572A EP1143108A1 (fr) 2000-04-07 2000-04-07 Méthode de fabrication d'un segment statorique à ailettes et segment statorique à ailettes

Publications (1)

Publication Number Publication Date
EP1143108A1 true EP1143108A1 (fr) 2001-10-10

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EP00107572A Withdrawn EP1143108A1 (fr) 2000-04-07 2000-04-07 Méthode de fabrication d'un segment statorique à ailettes et segment statorique à ailettes

Country Status (1)

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EP (1) EP1143108A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1512832A1 (fr) * 2003-09-02 2005-03-09 Alstom Technology Ltd Méthode de fabrication d'un rotor de turbine avec étage régulateur
FR2904033A1 (fr) * 2006-07-19 2008-01-25 Snecma Sa Ensemble diffuseur-redresseur pour une turbomachine
FR2931715A1 (fr) * 2008-05-30 2009-12-04 Snecma Procede de fabrication d'une piece de turbomachine telle qu'un redresseur de compresseur.
US8075265B2 (en) 2006-10-28 2011-12-13 Man Diesel & Turbo Se Guiding device of a flow machine and guide vane for such a guiding device
EP2979808A1 (fr) * 2014-07-31 2016-02-03 Techspace Aero S.A. Procédé de réalisation d'un stator de compresseur de turbomachine axiale

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4509238A (en) * 1983-03-21 1985-04-09 General Electric Company Method for fabricating a steam turbine diaphragm
US4643636A (en) * 1985-07-22 1987-02-17 Avco Corporation Ceramic nozzle assembly for gas turbine engine
US5474419A (en) * 1992-12-30 1995-12-12 Reluzco; George Flowpath assembly for a turbine diaphragm and methods of manufacture
US5788456A (en) * 1997-02-21 1998-08-04 Dresser-Rand Company Turbine diaphragm assembly and method thereof
US5797725A (en) * 1997-05-23 1998-08-25 Allison Advanced Development Company Gas turbine engine vane and method of manufacture
EP0947666A2 (fr) * 1998-03-28 1999-10-06 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Anneau des aubes de guidage pour un turboréacteur et sa méthode de fabrication

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4509238A (en) * 1983-03-21 1985-04-09 General Electric Company Method for fabricating a steam turbine diaphragm
US4643636A (en) * 1985-07-22 1987-02-17 Avco Corporation Ceramic nozzle assembly for gas turbine engine
US5474419A (en) * 1992-12-30 1995-12-12 Reluzco; George Flowpath assembly for a turbine diaphragm and methods of manufacture
US5788456A (en) * 1997-02-21 1998-08-04 Dresser-Rand Company Turbine diaphragm assembly and method thereof
US5797725A (en) * 1997-05-23 1998-08-25 Allison Advanced Development Company Gas turbine engine vane and method of manufacture
EP0947666A2 (fr) * 1998-03-28 1999-10-06 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Anneau des aubes de guidage pour un turboréacteur et sa méthode de fabrication

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1512832A1 (fr) * 2003-09-02 2005-03-09 Alstom Technology Ltd Méthode de fabrication d'un rotor de turbine avec étage régulateur
FR2904033A1 (fr) * 2006-07-19 2008-01-25 Snecma Sa Ensemble diffuseur-redresseur pour une turbomachine
EP1882821A1 (fr) * 2006-07-19 2008-01-30 Snecma Ensemble diffuseur-redresseur pour une turbomachine
US7955051B2 (en) 2006-07-19 2011-06-07 Snecma Diffuser/guide vane assembly for a turbomachine
RU2463484C2 (ru) * 2006-07-19 2012-10-10 Снекма Узел диффузор-выпрямитель для турбомашины и турбомашина, содержащая диффузор-выпрямитель
US8075265B2 (en) 2006-10-28 2011-12-13 Man Diesel & Turbo Se Guiding device of a flow machine and guide vane for such a guiding device
FR2931715A1 (fr) * 2008-05-30 2009-12-04 Snecma Procede de fabrication d'une piece de turbomachine telle qu'un redresseur de compresseur.
EP2979808A1 (fr) * 2014-07-31 2016-02-03 Techspace Aero S.A. Procédé de réalisation d'un stator de compresseur de turbomachine axiale
WO2016015980A1 (fr) * 2014-07-31 2016-02-04 Techspace Aero S.A. Procede de realisation d'un stator de compresseur de turbomachine axiale
US10436220B2 (en) 2014-07-31 2019-10-08 Safran Aero Boosters Sa Method for producing a compressor stator of an axial turbomachine

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