EP1862638A1 - Procédé pour la réparation d'un rotor d'une turbine à gaz et rotor d'une turbine à gaz - Google Patents

Procédé pour la réparation d'un rotor d'une turbine à gaz et rotor d'une turbine à gaz Download PDF

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Publication number
EP1862638A1
EP1862638A1 EP07107597A EP07107597A EP1862638A1 EP 1862638 A1 EP1862638 A1 EP 1862638A1 EP 07107597 A EP07107597 A EP 07107597A EP 07107597 A EP07107597 A EP 07107597A EP 1862638 A1 EP1862638 A1 EP 1862638A1
Authority
EP
European Patent Office
Prior art keywords
bridge segments
rotor
axis
segments
new bridge
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
EP07107597A
Other languages
German (de)
English (en)
Other versions
EP1862638B1 (fr
Inventor
Nils Lawin
Bernd Hermann Meixner
Heinz-Günter Löser
Guenter Karl-Heinz Gnirss
Daniel Patrick Vogler
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 EP1862638A1 publication Critical patent/EP1862638A1/fr
Application granted granted Critical
Publication of EP1862638B1 publication Critical patent/EP1862638B1/fr
Not-in-force legal-status Critical Current
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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • 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
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor

Definitions

  • the present invention relates to the field of gas turbines. It relates to a method for repairing the rotor of a gas turbine according to the preamble of claim 1 and to a rotor according to the preamble of claim 8.
  • a plurality of blade receptacles 18 are arranged in succession, in addition to heat accumulator support 14 for attachment of (not shown) heat damper segments are provided.
  • heat accumulator support 14 for attachment of (not shown) heat damper segments are provided.
  • annular, closed cooling air groove 16 with a groove bottom 16a, which is supplied with cooling air via axial bores 17.
  • Thedeluftnut 16 is spanned by a welded bridge construction.
  • the heat accumulation segments are installed to protect the rotor 10 from direct hot gas.
  • a repair measure makes it possible to remanufacture by removing the damaged area in the groove bottom 16a.
  • two repair measures have been developed, a temporary and a long-lasting repair (also referred to in the document mentioned above as "micro” repair and "macro” repair).
  • the main difference between the two repair measures is the open bridge construction for the temporary repair and a re-welded bridge construction for the long-lasting repair. In order to ensure access for the tool, it is necessary to sever the heat shield bridges for the execution of the repair measure.
  • a disadvantage of the known repair measures that in the temporary repair measure no pressure forces can be transmitted above the groove, and that the rewelding of the heat shield bridge in the process of long-lasting repair measure is time consuming and expensive. Among other things, a heat treatment is required to reduce residual stresses during welding. Furthermore, an on-site implementation in the long-term repair measure is not possible.
  • An embodiment of the method according to the invention is characterized in that the new bridge segments are additionally secured against radially outward acting forces.
  • the new bridge segments are additionally secured against radially outward acting forces.
  • the groove-like recesses may each be formed as annular grooves which extend concentrically to an axial axis of rotation, wherein the mounting feet of the new bridge segments have a corresponding ring shape, and in the assembly of the new bridge segments, the new bridge segments with the mounting feet about the axis of rotation be screwed into the annular grooves.
  • the groove-like recesses may each be formed as annular grooves which extend concentrically to a radial axis of rotation, wherein the mounting feet of the bridge segments have a corresponding annular shape, and screwed during assembly of the new bridge segments, the new bridge segments with the mounting feet about the axis of rotation in the annular grooves become.
  • the abutting connecting walls of the new bridge segments and the heat spine carrier can be designed as concentric with the axis of rotation oriented cylindrical surfaces.
  • An embodiment of the rotor according to the invention is characterized in that the bridge segments are additionally secured against radially outwardly acting forces, that for securing the new bridge segments against radially outward acting forces a positive connection between the heat spine carrier and the new bridge segments is provided, and that for the production the positive connection in the cooling air groove are provided laterally in the axial direction groove-like recesses, in which engage the bridge segments with issued in the axial direction mounting feet.
  • the groove-like recesses may each be formed as annular grooves which extend concentrically to an axial axis of rotation, wherein the mounting feet of the bridge segments have a corresponding annular shape.
  • the bridge segments and the heat spine carrier are preferably designed as cylindrical surfaces oriented concentrically to the axis of rotation.
  • the basic idea of the present invention is to simplify the repair-related installation of heat spine bridges by jamming the bridge segments in the GT rotor.
  • bridge segments are used there by clamping, where a welded bridge connection was present before the cooling air groove was removed. This can be done in different ways.
  • FIG. 3-5 an embodiment of the inventive method is shown.
  • the figures show a perspective view of a section of a rotor 10 of a gas turbine, which has a rotating blade receptacle 18.
  • a heat accumulator carrier 14 is arranged next to the rotor blade receptacle 18, which is cut by the circumferential, curveddeluftnut 16 '. Extending in the axial direction are distributed around the circumference of the rotor 10 in the heat accumulation segment carrier 14 heat accumulation receptacles 15, can be inserted into the heat accumulation segments, not shown.
  • the radially outwardly projecting portions 28 of the heat accumulator support 14 located between the heat accumulator receivers 15 are cut by the cooling air groove 16 '.
  • the cut-through areas are bridged by new bridge segments 20 inserted by clamping, which are adapted to the left-standing sections 28 in the cross-sectional profile.
  • the end faces of the bridge segments 20 are oriented flat and perpendicular to the axis 11 of the rotor 10. The same applies to the connection levels of the remaining portions 28 of the heat spine carrier 14.
  • the new bridge segments 20 are additionally secured against radially outwardly acting forces.
  • FIGS. 3-5 are groove-like recesses introduced laterally opposite in the axial direction for producing the positive connection in the spiraldeluftnut 16, which are each formed as annular grooves 23, 24 and concentric with (in Figs. 2-5 not drawn) axial axis of rotation.
  • the annular grooves 23, 24 engage the new bridge segments 20 with issued in the axial direction, formed on the end faces mounting feet 21, 22 a.
  • the mounting feet 21, 22 of the new bridge segments 20 have a corresponding ring shape, so that during assembly of the new bridge segments 20 they must be screwed with the mounting feet 21, 22 about the axial axis of rotation in the annular grooves 23, 24, as shown in FIG. 4 is shown for a second bridge segment 20.
  • the groove-like recesses are each formed as annular grooves 23 ', 24', which extend concentrically to a radial axis of rotation 27.
  • the mounting feet 21 ', 22' at the end faces of the new bridge segments 20 ' have a corresponding ring shape, so that during assembly of the new bridge segments 20' with the mounting feet 21 ', 22' about the axis of rotation 27 in the annular grooves 23 ', 24 'are screwed in, as shown in Fig. 6 for a second bridge segment 20.
  • the adjoining connecting walls 25, 26 of the new bridge segments 20 'and of the heat accumulator carrier 14 are designed as cylindrical surfaces oriented concentrically to the axis of rotation 27.
  • the invention allows welded gas turbine rotors, in which bridge segments with the aim of improving the rigidity and thus the cyclic life of the rotor, without a welded joint can be installed.
  • bridge segments with the aim of improving the rigidity and thus the cyclic life of the rotor, without a welded joint can be installed.
  • an optimization of the load distribution in life-time-determined areas on turned grooves and a seal against cooling air leakage is achieved in a simplified manner.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP07107597A 2006-06-01 2007-05-07 Procédé pour la réparation d'un rotor d'une turbine à gaz et rotor d'une turbine à gaz Not-in-force EP1862638B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH8872006 2006-06-01

Publications (2)

Publication Number Publication Date
EP1862638A1 true EP1862638A1 (fr) 2007-12-05
EP1862638B1 EP1862638B1 (fr) 2009-07-01

Family

ID=36940226

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07107597A Not-in-force EP1862638B1 (fr) 2006-06-01 2007-05-07 Procédé pour la réparation d'un rotor d'une turbine à gaz et rotor d'une turbine à gaz

Country Status (4)

Country Link
EP (1) EP1862638B1 (fr)
AT (1) ATE435358T1 (fr)
DE (1) DE502007000968D1 (fr)
DK (1) DK1862638T3 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2189233A1 (fr) 2008-11-19 2010-05-26 Alstom Technology Ltd Procédé d'usinage d'un rotor d'une turbine à gaz

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB801689A (en) * 1954-09-10 1958-09-17 Henschel & Sohn Ges Mit Beschr Improved cooled gas turbine rotor for high gas-temperatures
EP1018594A2 (fr) * 1999-01-06 2000-07-12 General Electric Company Couvercle pour le rotor d'une turbine

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB801689A (en) * 1954-09-10 1958-09-17 Henschel & Sohn Ges Mit Beschr Improved cooled gas turbine rotor for high gas-temperatures
EP1018594A2 (fr) * 1999-01-06 2000-07-12 General Electric Company Couvercle pour le rotor d'une turbine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
N. LAWIN, G. GNIRSS: "lebendauerüberwachung für GT13B-D3A Gasturbinenrotoren-Erkenntnisse, Diagnose und einsatzspezifisch Lösung", VGB POWERTECH FACHTAGUNG, 11 May 2005 (2005-05-11), Dresden, pages 1 - 21, XP002399277, Retrieved from the Internet <URL:http://www.power.alstom.com/home/events/past_events/vgb_fachtagung/_files/file_18039_58408.pdf> [retrieved on 20060918] *

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2189233A1 (fr) 2008-11-19 2010-05-26 Alstom Technology Ltd Procédé d'usinage d'un rotor d'une turbine à gaz
CH699996A1 (de) * 2008-11-19 2010-05-31 Alstom Technology Ltd Verfahren zum bearbeiten eines gasturbinenläufers.
US8281486B2 (en) 2008-11-19 2012-10-09 Alstom Technology Ltd. Method for machining a gas turbine rotor

Also Published As

Publication number Publication date
DE502007000968D1 (de) 2009-08-13
EP1862638B1 (fr) 2009-07-01
ATE435358T1 (de) 2009-07-15
DK1862638T3 (da) 2009-08-24

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