EP1491723B2 - Procédé de modification de la géométrie d'emboîtement des viroles d'aubes de turbine - Google Patents

Procédé de modification de la géométrie d'emboîtement des viroles d'aubes de turbine Download PDF

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Publication number
EP1491723B2
EP1491723B2 EP04102733A EP04102733A EP1491723B2 EP 1491723 B2 EP1491723 B2 EP 1491723B2 EP 04102733 A EP04102733 A EP 04102733A EP 04102733 A EP04102733 A EP 04102733A EP 1491723 B2 EP1491723 B2 EP 1491723B2
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EP
European Patent Office
Prior art keywords
coupling
geometry
removal
application
modified
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
EP04102733A
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German (de)
English (en)
Other versions
EP1491723A1 (fr
EP1491723B1 (fr
Inventor
Hartmut Hähnle
Christoph Nagler
Ingo Schwarz
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.)
GE Vernova GmbH
Original Assignee
Alstom Technology AG
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Publication date
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Application filed by Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP1491723A1 publication Critical patent/EP1491723A1/fr
Application granted granted Critical
Publication of EP1491723B1 publication Critical patent/EP1491723B1/fr
Publication of EP1491723B2 publication Critical patent/EP1491723B2/fr
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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
    • F01D5/005—Repairing methods or devices
    • 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
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • 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
    • Y10T29/49318—Repairing or disassembling
    • 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
    • Y10T29/49336—Blade 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
    • Y10T29/49716—Converting

Definitions

  • the invention relates to a method for modifying the coupling geometry in shroud segments of turbine blades.
  • the type of coupling i.
  • the coupling angle and the coupling surface is essential for the performance of the turbine blades, and in particular for the wear behavior in the area of the coupling, because of the transmission of the coupling forces. Due to the o.g. Factors that affect the shroud coupling, even minor changes in the turbine design of individual turbine stages, for example, by converting a turbine stage or changed operating conditions, can lead to undesirably high wear on existing turbine stages. If it is determined on the basis of operating experience that the wear in the coupling region of two turbine shroud segments is impermissibly high, so far only a repair of the turbine blade in the coupling region takes place.
  • the coupling region is usually coated with chromium carbide. In extreme cases, individual blades or blade groups must be replaced. In addition, reduce the maintenance intervals in unfavorable cases, which reduces the efficiency of the system.
  • US-4,291,448-A discloses a method of repairing occluded shroud segments by grinding the affected zones and applying additional material to restore the original coupling geometry.
  • the invention is therefore based on the object to avoid the above-mentioned disadvantages of the prior art and to provide a method for modifying the coupling angle in shroud segments of turbine blades, which improves the wear behavior in the coupling region and the life of the shroud segments of turbine blades on effective and cost-effective Way extended.
  • the modification should be carried out either on existing turbine blades or on new parts that are interchangeable with turbine blades that have reached the end of their life.
  • the method according to the invention for modifying the coupling geometry in the case of shroud segments of turbine blades has the following steps: Calculation of a Modified Coupling Geometry.
  • simulations are used in which the changed flow conditions in a modernized turbomachine and its effects on the relevant turbine stage can be analyzed.
  • the angle data are measured from the circumferential direction. It is important that an increase in the coupling angle is aimed for when the coupling forces transmitted are too small. Conversely, if transmission forces are too great, the aim is to reduce the coupling angle.
  • the method according to the invention avoids the disadvantages of the prior art and improves the wear behavior in the coupling region. Furthermore, the service life of the turbine blades is extended in an effective and cost-effective manner
  • an advantageous development of the method according to the invention provides that the application zones are previously processed in such a way that an improved application cross-section is provided. This is done, for example, by removing material at a point of the shroud segment, which provides a sufficiently large cross-section to order material safely and reliably connect.
  • this also angular cross-sections can be defined, which are advantageous for manufacturing reasons, since the application material is connected on several sides with the original shroud segment.
  • a particularly advantageous embodiment of the method provides that the change in the coupling angle is ⁇ 25 °. This angle has proved to be advantageous in experiments for changing coupling angles from 15 ° to 40 °.
  • Yet another advantageous embodiment of the method according to the invention provides that the application of additional material takes place by means of build-up welding.
  • the deposition welding has proven by laser.
  • Yet another advantageous embodiment of the method according to the invention provides that the removal of excess material takes place by means of grinding. If larger segments are to be separated, a cut-off grinder, for example, can be used here.
  • a further method for modifying an existing casting mold for a turbine blade with a shroud segment, for a modified geometry of the coupling angle comprises the following steps: calculating a modified coupling geometry; Removal of mold material located within the modified coupling geometry; and / or applying additional non-existent mold material outside the modified coupling geometry; Post-processing of the removal and / or order zones.
  • these modifications are the reverse steps, as in the inventive method according to claim 1, since this is a negative mold.
  • Such modification of existing molds is helpful in making replacement turbine blades that would otherwise have to be subsequently modified. This presents a cost effective way to further utilize existing molds without sacrificing the benefits of the modified coupling geometry:
  • an advantageous embodiment of the method according to the invention provides that the modified coupling geometry has a change in the coupling angle by at least ⁇ 5 °, preferably ⁇ 15 ° to ⁇ 40 °. It is particularly advantageous if the change in the coupling angle is ⁇ 25 °.
  • FIG. 1 shows a perspective view of a grid model of a turbine blade 1 with a shroud segment 7.
  • the turbine blade 1 has at its upper end a blade head 2 and at its lower end a blade root 3, which continues in a shaft 4 (only indicated).
  • a shaft 4 (only indicated).
  • the blade profile leading edge 5 and on the right side of the drawing the blade profile trailing edge 6 is shown
  • the shroud segment 7 extends on the blade head 2 substantially transversely to the running between the blade profile leading edge 5 and the blade profile trailing edge 6 chord and parallel to the circumferential direction U.
  • the shroud segment 7 does not extend over the entire blade depth, but only on an area in the middle of the blade.
  • the transition between the shroud segment 7 and the blade head 2 is determined by transition radii.
  • 7 contact surfaces 8, 9 are provided on the side surfaces of the shroud segment, which abut against contact surfaces of adjacent shroud segments during operation.
  • FIGS. 3a and 3b show a schematic plan view of the coupling region of shroud segments 7 from the pressure side and suction side without modification.
  • FIG. 3a represents pressure-side end of the shroud segment 7 shows approximately centrally disposed a fin 11, which serves as a sealing ridge between the housing inner wall of the turbine housing and the built-up of the shroud segments 7 turbine shroud.
  • the contact surface 8 of the shroud segment 7, the mutual support of adjacent turbine blades serves, in the present embodiment, before the modification at an angle of 15 ° measured from the circumferential direction. Furthermore, the stepped or Z-shaped side edge of the shroud segment can be clearly seen without modification.
  • the suction-side end of the shroud segment 7 likewise shows an approximately centrally arranged fin 11.
  • the contact surface 9, which forms the long connecting line between the upper and the lower horizontal Z-bars, also has an angle of 15 °, measured on the suction-side shroud segment 7 the circumferential direction, on.
  • the calculated in the present embodiment optimum angle for the modified pressure-side and suction-side contact surfaces is measured at 40 ° from the circumferential direction.
  • the desired angle change is thus 25 ° each.
  • the corresponding shroud sections are prepared so that an optimal cross-section for the application of new shroud material is provided by previous material removal.
  • These preparation areas are in FIGS. 3a and 3b bounded by dashed lines and the outer contour and identified by reference numeral 10.
  • the removal of material takes place by a grinding process. In principle, however, every other suitable removal method is possible.
  • FIGS. 4a and 4b show a schematic plan view of the coupling region of the shroud segments 7 of the pressure and suction side with modified coupling geometry. Again, the fins 11 are shown, which are parallel to the circumferential direction shown by arrow U. The contact surfaces 8, 9 extend at an angle of 40 °, measured from the circumferential direction.
  • FIGS. 4a and 4b are the application surfaces 13, in which additional shroud material was applied, shown in dashed lines within the shroud contour.
  • the removal surfaces 12, ie zones in which excess shroud material has been removed, are bounded outside the shroud contour by dashed lines.
  • FIG. 4b is clearly illustrated by the material removal and the material application induced angle change from 15 ° to 40 °.
  • the removal of material by means of cut-off grinding and the material application by means of build-up welding is carried out.
  • any suitable order and removal method can be used.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Hydraulic Turbines (AREA)

Claims (10)

  1. Procédé pour modifier la géométrie d'emboîtement des viroles (7) d'aubes de turbines (1), dans lequel le procédé comprend les étapes suivantes :
    - calcul d'une géométrie d'emboîtement modifiée ;
    - enlèvement du matériau des viroles (12) situé en dehors de la géométrie d'emboîtement modifiée ; et/ou
    - revêtement de matériau supplémentaire (13) n'existant pas à l'intérieur de la géométrie d'emboîtement modifiée ;
    - post-usinage des zones d'enlèvement et/ou de revêtement, dans lequel la géométrie d'emboîtement modifiée présente une variation de l'angle d'emboîtement d'au moins ±5°, de préférence de ±15° à ±40°.
  2. Procédé selon la revendication 1, dans lequel les zones de revêtement sont pré-usinées de manière à fournir une section transversale de revêtement améliorée.
  3. Procédé selon la revendication 1, dans lequel la variation de l'angle d'emboîtement est de ±25°.
  4. Procédé selon l'une quelconque des revendications précédentes, dans lequel le revêtement de matériau supplémentaire s'effectue au moyen d'un rechargement par soudage.
  5. Procédé selon l'une quelconque des revendications précédentes, dans lequel l'enlèvement de matériau excessif s'effectue par meulage.
  6. Procédé pour modifier un moule de coulée existant pour une aube de turbine comprenant une virole, pour une géométrie modifiée de l'angle d'emboîtement, dans lequel le procédé comprend les étapes suivantes :
    - calcul d'une géométrie d'emboîtement modifiée ;
    - enlèvement de matériau du moule de coulée se trouvant à l'intérieur de la géométrie d'emboîtement modifiée ; et/ou
    - revêtement de matériau du moule de coulée supplémentaire non présent en dehors de la géométrie d'emboîtement modifiée ;
    - post-usinage des zones d'enlèvement et/ou de revêtement.
  7. Procédé selon la revendication 6, dans lequel la géométrie d'emboîtement modifiée présente une variation de l'angle d'emboîtement d'au moins ±5°, de préférence de ±15° à ±40°.
  8. Procédé selon la revendication 7, dans lequel la variation de l'angle d'emboîtement est de ±25°.
  9. Procédé selon l'une quelconque des revendications 6 à 8, dans lequel le revêtement de matériau supplémentaire s'effectue au moyen d'un rechargement par soudage.
  10. Procédé selon l'une quelconque des revendications 6 à 9, dans lequel l'enlèvement de matériau excessif s'effectue par meulage.
EP04102733A 2003-06-23 2004-06-15 Procédé de modification de la géométrie d'emboîtement des viroles d'aubes de turbine Expired - Lifetime EP1491723B2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10328310 2003-06-23
DE10328310A DE10328310A1 (de) 2003-06-23 2003-06-23 Verfahren zum Modifizieren der Kopplungsgeometrie bei Deckbandsegmenten von Turbinenlaufschaufeln

Publications (3)

Publication Number Publication Date
EP1491723A1 EP1491723A1 (fr) 2004-12-29
EP1491723B1 EP1491723B1 (fr) 2006-08-23
EP1491723B2 true EP1491723B2 (fr) 2009-05-06

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ID=33394958

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EP04102733A Expired - Lifetime EP1491723B2 (fr) 2003-06-23 2004-06-15 Procédé de modification de la géométrie d'emboîtement des viroles d'aubes de turbine

Country Status (4)

Country Link
US (2) US7644498B2 (fr)
EP (1) EP1491723B2 (fr)
AT (1) ATE337470T1 (fr)
DE (2) DE10328310A1 (fr)

Families Citing this family (12)

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Publication number Priority date Publication date Assignee Title
CH699984A1 (de) * 2008-11-27 2010-05-31 Alstom Technology Ltd Verfahren zur Optimierung der Kontaktflächen von aneinander anstossenden Deckbandsegmenten benachbarter Schaufeln einer Gasturbine.
US9151166B2 (en) 2010-06-07 2015-10-06 Rolls-Royce North American Technologies, Inc. Composite gas turbine engine component
US20140147284A1 (en) * 2012-11-27 2014-05-29 General Electric Company Method for modifying an airfoil shroud
US20140147283A1 (en) * 2012-11-27 2014-05-29 General Electric Company Method for modifying a airfoil shroud and airfoil
US10465531B2 (en) * 2013-02-21 2019-11-05 General Electric Company Turbine blade tip shroud and mid-span snubber with compound contact angle
GB2526217B (en) 2013-03-15 2020-11-04 Intel Corp Mobile computing device technology and systems and methods utilizing the same
US9091277B1 (en) 2014-04-25 2015-07-28 Computer Assisted Manufacturing Technology Corporation Systems and methods for manufacturing a shrouded impeller
EP3029267A1 (fr) * 2014-12-04 2016-06-08 Siemens Aktiengesellschaft Procédé de fabrication d'un amortisseur d'oscillations pour une aube de turbine au moyen de rechargement par soudage laser
CN106475733B (zh) * 2016-10-11 2018-11-13 吉林大学 一种分区构建仿生耦合表面修复废旧机床导轨及其方法
US11511372B2 (en) 2017-04-28 2022-11-29 Fluid Handling Llc Technique to improve the performance of a pump with a trimmed impeller using additive manufacturing
DE102018201265A1 (de) 2018-01-29 2019-08-01 MTU Aero Engines AG Deckbandsegment zur Anordnung an einer Schaufel einer Strömungsmaschine und Schaufel
CN121289949B (zh) * 2025-12-09 2026-04-03 中国航发湖南动力机械研究所 可调导叶角度修复方法、可调导叶及航空发动机

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US4400915A (en) † 1980-06-02 1983-08-30 United Technologies Corporation Fixture for restoring a face on the shroud of a rotor blade
US4589175A (en) † 1980-06-02 1986-05-20 United Technologies Corporation Method for restoring a face on the shroud of a rotor blade
US4657171A (en) † 1985-06-13 1987-04-14 General Electric Company Repair of a member having a projection
US4893388A (en) † 1988-12-08 1990-01-16 Westinghouse Electric Corp. Method of modifying turbine rotor discs
EP0389913B1 (fr) † 1989-03-28 1998-06-17 Refurbished Turbine Components Limited Méthode de réparation des aubes de turbine

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US4291448A (en) * 1977-12-12 1981-09-29 Turbine Components Corporation Method of restoring the shrouds of turbine blades
DE3517283A1 (de) * 1985-05-14 1986-11-20 MAN Gutehoffnungshütte GmbH, 4200 Oberhausen Bindung von laufschaufeln einer thermischen turbomaschine
CH666722A5 (de) * 1985-07-05 1988-08-15 Bbc Brown Boveri & Cie Laufschaufelkranz einer axial durchstroemten turbomaschine.
US4822248A (en) * 1987-04-15 1989-04-18 Metallurgical Industries, Inc. Rebuilt shrouded turbine blade and method of rebuilding the same
DE3862891D1 (de) * 1987-05-04 1991-06-27 Siemens Ag Verfahren zum herstellen von profilteilen durch schleifen und entsprechend hergestellte turbomaschinenschaufel.
JP3034417B2 (ja) * 1994-02-18 2000-04-17 株式会社東芝 軸流タービンの動翼制振装置
AUPO879497A0 (en) * 1997-08-26 1997-09-18 Warman International Limited Pump impeller and method
US6464128B1 (en) * 1999-05-28 2002-10-15 General Electric Company Braze repair of a gas turbine engine stationary shroud
US6701616B2 (en) * 2002-06-28 2004-03-09 General Electric Company Method of repairing shroud tip overlap on turbine buckets

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4400915A (en) † 1980-06-02 1983-08-30 United Technologies Corporation Fixture for restoring a face on the shroud of a rotor blade
US4589175A (en) † 1980-06-02 1986-05-20 United Technologies Corporation Method for restoring a face on the shroud of a rotor blade
US4657171A (en) † 1985-06-13 1987-04-14 General Electric Company Repair of a member having a projection
US4893388A (en) † 1988-12-08 1990-01-16 Westinghouse Electric Corp. Method of modifying turbine rotor discs
EP0389913B1 (fr) † 1989-03-28 1998-06-17 Refurbished Turbine Components Limited Méthode de réparation des aubes de turbine

Also Published As

Publication number Publication date
US7644498B2 (en) 2010-01-12
DE10328310A1 (de) 2005-01-13
DE502004001246D1 (de) 2006-10-05
EP1491723A1 (fr) 2004-12-29
US20100077586A1 (en) 2010-04-01
EP1491723B1 (fr) 2006-08-23
US20050097741A1 (en) 2005-05-12
US8006381B2 (en) 2011-08-30
ATE337470T1 (de) 2006-09-15

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