EP1491723A1 - 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
EP1491723A1
EP1491723A1 EP04102733A EP04102733A EP1491723A1 EP 1491723 A1 EP1491723 A1 EP 1491723A1 EP 04102733 A EP04102733 A EP 04102733A EP 04102733 A EP04102733 A EP 04102733A EP 1491723 A1 EP1491723 A1 EP 1491723A1
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EP
European Patent Office
Prior art keywords
coupling
geometry
removal
modified
coupling geometry
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
EP04102733A
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German (de)
English (en)
Other versions
EP1491723B2 (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.)
General Electric Technology 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
Anticipated expiration legal-status Critical
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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 ie the coupling angle and the coupling surface
  • the type of coupling is of essential importance for the operating behavior of the turbine blades, and here in particular for the wear behavior in the area of the coupling, because of the transmission of the coupling forces. Due to the The above-mentioned factors, which influence the cover band coupling, can lead to undesirably high wear on existing turbine stages, even minor changes to the turbine design of individual turbine stages, for example by retrofitting a turbine stage or changing operating conditions. If, based on operating experience, it is found that the wear in the coupling area of two turbine shroud segments is inadmissibly high, the turbine blade has so far only been repaired in the coupling area.
  • the coupling area is usually coated with chromium carbide. In extreme cases, individual blades or blade groups have to be replaced. In unfavorable cases, the maintenance intervals are also shortened, which reduces the economic efficiency of the system.
  • the invention is therefore based on the object of avoiding the abovementioned disadvantages of the prior art and of providing a method for modifying the coupling angle in the case of shroud segments of turbine blades, which improves the wear behavior in the coupling region and the service life of the shroud segments of turbine blades to be effective and inexpensive Way extended.
  • the modification should either be possible on existing turbine blades or on new parts that can be exchanged for turbine blades that have reached the end of their service 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: calculating a modified coupling geometry.
  • simulations are used in which the changed flow conditions in a modernized turbomachine and their effects on the relevant turbine stage can be analyzed.
  • Post-processing may be necessary, in particular after the material has been applied, since this enables the desired surface quality to be achieved. In this way, for example, the coupling angle and the coupling surface or only the coupling angle or only the coupling surface can be varied.
  • An advantageous development of the method according to the invention provides that the order zones are processed in advance in such a way that an improved order cross section is made available. This is done, for example, by removing material at a point on the shroud segment that has a sufficiently large cross-section to securely and reliably connect application material. In addition, this also enables angular cross sections to be defined, which are advantageous for manufacturing reasons, since the application material is connected to the original shroud segment on several sides.
  • An advantageous embodiment of the method according to the invention further provides that the modified coupling geometry changes the coupling angle by at least 5 °, preferably ⁇ 15 ° to ⁇ 40 °.
  • the angle information is measured from the circumferential direction. It is important to aim at increasing the coupling angle if the coupling forces are too small. Conversely, if the transmission forces are too great, the aim is to reduce the coupling angle.
  • the change in the coupling angle is ⁇ 25 °.
  • this angle has proven to be advantageous for changing coupling angles from 15 ° to 40 °.
  • 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.
  • build-up welding for example, laser deposition welding has proven itself.
  • Another advantageous embodiment of the method according to the invention provides that excess material is removed by means of grinding. If larger segments are to be separated, a cut-off machine can be used here, for example.
  • a further method according to the invention for modifying an existing casting mold for a turbine blade with a shroud segment, for a changed geometry of the coupling angle has the following steps: calculating a modified coupling geometry; Removing mold material located within the modified coupling geometry; and / or applying additional, nonexistent ones Mold material outside the modified coupling geometry; Reworking the removal and / or order zones.
  • These modifications are essentially the reverse of the steps as in the method according to the invention as claimed in claim 1, since this is a negative form.
  • Such a modification of existing molds is helpful if replacement turbine blades are to be produced, which would otherwise have to be modified subsequently. In this way, an inexpensive possibility for the further use of already existing casting molds is presented, without having to forego the advantages of the modified coupling geometry.
  • An advantageous embodiment of the method according to the invention provides that the modified coupling geometry changes 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 rotor blade 1 with a shroud segment 7.
  • the turbine rotor blade 1 has a blade head 2 at its upper end and a blade root 3 at its lower end, 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 cover band segment 7 on the blade head 2 runs essentially transversely to the chord running between the blade profile leading edge 5 and the blade profile trailing edge 6 and parallel to the circumferential direction U.
  • the cover band segment 7 does not extend the entire bucket depth, but only to an area in the middle of the bucket.
  • 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 on contact surfaces of adjacent shroud segments during operation.
  • FIGS. 3a and 3b show a schematic top view of the coupling area of shroud segments 7 from the pressure side and suction side without modification.
  • the contact surface 8 of the shroud segment 7, which serves to mutually support adjacent turbine blades, has an angle of 15 ° measured from the circumferential direction before the modification. 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 shown in FIG. 3b also shows a fin 11 arranged approximately in the middle °, measured from the circumferential direction.
  • the optimum angle calculated in the present exemplary embodiment for the modified pressure-side and suction-side contact surfaces is 40 ° in each case measured from the circumferential direction.
  • the desired change in angle is thus 25 ° in each case.
  • material must be removed in some places and material added in other places.
  • the corresponding cover band sections are prepared in such a way that an optimal cross-section for the application of new cover band material is made available by previous material removal.
  • These preparation areas are delimited in FIGS. 3a and 3b by dashed lines and the outer contour and are identified by reference number 10.
  • the material is removed by a grinding process. In principle, however, any other suitable removal process is possible.
  • FIGS. 4a and 4b show a schematic plan view of the coupling area of the shroud segments 7 from the pressure and suction side with modified coupling geometry.
  • the fins 11 are shown, which run parallel to the circumferential direction shown by arrow U.
  • the contact surfaces 8, 9 run at an angle of 40 °, measured from the circumferential direction.
  • FIGS. 4a and 4b the application areas 13, in which additional cover tape material has been applied, are shown in dashed lines within the cover tape contour.
  • the removal areas 12, i.e. Zones in which excess shroud material has been removed are delimited outside the shroud contour with dashed lines.
  • FIG. 4b clearly shows the change in angle caused by the material removal and the material application from 15 ° to 40 °.
  • the material has been removed by means of cut-off grinding and the material has been applied by means of build-up welding, here using the TIG welding process.
  • any suitable order and removal procedure can be used.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Hydraulic Turbines (AREA)
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 true EP1491723A1 (fr) 2004-12-29
EP1491723B1 EP1491723B1 (fr) 2006-08-23
EP1491723B2 EP1491723B2 (fr) 2009-05-06

Family

ID=33394958

Family Applications (1)

Application Number Title Priority Date Filing Date
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)

Cited By (3)

* Cited by examiner, † Cited by third party
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.
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
CN106475733A (zh) * 2016-10-11 2017-03-08 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

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
RU2625952C2 (ru) 2013-03-15 2017-07-19 Интел Корпорейшн Технология мобильного вычислительного устройства и система и способы, использующие ее
US9091277B1 (en) 2014-04-25 2015-07-28 Computer Assisted Manufacturing Technology Corporation Systems and methods for manufacturing a shrouded impeller
CN110799755B (zh) 2017-04-28 2023-11-10 流体处理有限责任公司 使用增材制造以改进具有修整的叶轮的泵的性能的技术
DE102018201265A1 (de) 2018-01-29 2019-08-01 MTU Aero Engines AG Deckbandsegment zur Anordnung an einer Schaufel einer Strömungsmaschine und Schaufel

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4291448A (en) * 1977-12-12 1981-09-29 Turbine Components Corporation Method of restoring the shrouds of turbine blades
US5511948A (en) * 1994-02-18 1996-04-30 Kabushiki Kaisha Toshiba Rotor blade damping structure for axial-flow turbine
US6464128B1 (en) * 1999-05-28 2002-10-15 General Electric Company Braze repair of a gas turbine engine stationary shroud

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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
DE3517283A1 (de) * 1985-05-14 1986-11-20 MAN Gutehoffnungshütte GmbH, 4200 Oberhausen Bindung von laufschaufeln einer thermischen turbomaschine
US4657171A (en) † 1985-06-13 1987-04-14 General Electric Company Repair of a member having a projection
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
ATE63709T1 (de) * 1987-05-04 1991-06-15 Siemens Ag Verfahren zum herstellen von profilteilen durch schleifen und entsprechend hergestellte turbomaschinenschaufel.
US4893388A (en) † 1988-12-08 1990-01-16 Westinghouse Electric Corp. Method of modifying turbine rotor discs
DE69032417T2 (de) † 1989-03-28 1999-02-11 Refurbished Turbine Components Ltd., Droitwich, Hereford And Worchester Reparaturverfahren für Turbinenschaufeln
AUPO879497A0 (en) * 1997-08-26 1997-09-18 Warman International Limited Pump impeller and method
US6701616B2 (en) * 2002-06-28 2004-03-09 General Electric Company Method of repairing shroud tip overlap on turbine buckets

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4291448A (en) * 1977-12-12 1981-09-29 Turbine Components Corporation Method of restoring the shrouds of turbine blades
US5511948A (en) * 1994-02-18 1996-04-30 Kabushiki Kaisha Toshiba Rotor blade damping structure for axial-flow turbine
US6464128B1 (en) * 1999-05-28 2002-10-15 General Electric Company Braze repair of a gas turbine engine stationary shroud

Cited By (6)

* Cited by examiner, † Cited by third party
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.
WO2010060867A1 (fr) * 2008-11-27 2010-06-03 Alstom Technology Ltd. Procédé d'optimisation des surfaces de contact de segments d'enveloppe (14) adjacents entre eux, d'aubes voisines d'une turbine à gaz
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
WO2016087337A1 (fr) * 2014-12-04 2016-06-09 Siemens Aktiengesellschaft Procédé de fabrication d'un amortisseur de vibrations pour aube de turbine par génération de laser
CN106475733A (zh) * 2016-10-11 2017-03-08 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
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

Also Published As

Publication number Publication date
EP1491723B2 (fr) 2009-05-06
US20050097741A1 (en) 2005-05-12
ATE337470T1 (de) 2006-09-15
EP1491723B1 (fr) 2006-08-23
DE502004001246D1 (de) 2006-10-05
US20100077586A1 (en) 2010-04-01
DE10328310A1 (de) 2005-01-13
US8006381B2 (en) 2011-08-30
US7644498B2 (en) 2010-01-12

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