EP1284337B1 - Procédé d'usinage d'une ailette de turbine à gaz - Google Patents

Procédé d'usinage d'une ailette de turbine à gaz Download PDF

Info

Publication number
EP1284337B1
EP1284337B1 EP02405661A EP02405661A EP1284337B1 EP 1284337 B1 EP1284337 B1 EP 1284337B1 EP 02405661 A EP02405661 A EP 02405661A EP 02405661 A EP02405661 A EP 02405661A EP 1284337 B1 EP1284337 B1 EP 1284337B1
Authority
EP
European Patent Office
Prior art keywords
roughness
turbine blade
gas turbine
protective layer
ceramic
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
EP02405661A
Other languages
German (de)
English (en)
Other versions
EP1284337A1 (fr
Inventor
Gordon Anderson
Reinhard Fried
Michael Lötzerich
Markus Oehl
Stefan Schlechtriem
Jörg Stengele
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 EP1284337A1 publication Critical patent/EP1284337A1/fr
Application granted granted Critical
Publication of EP1284337B1 publication Critical patent/EP1284337B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for 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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • 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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/286—Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion
    • 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
    • F05D2230/10—Manufacture by removing material
    • 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
    • F05D2230/90—Coating; Surface treatment
    • 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
    • F05D2250/00—Geometry
    • F05D2250/60—Structure; Surface texture
    • 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
    • F05D2250/00—Geometry
    • F05D2250/60—Structure; Surface texture
    • F05D2250/62—Structure; Surface texture smooth or fine
    • 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
    • F05D2250/00—Geometry
    • F05D2250/60—Structure; Surface texture
    • F05D2250/62—Structure; Surface texture smooth or fine
    • F05D2250/621—Structure; Surface texture smooth or fine polished
    • 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
    • F05D2260/221—Improvement of heat transfer
    • 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
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/21—Oxide ceramics
    • F05D2300/2118—Zirconium oxides
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/611—Coating
    • 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
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12451—Macroscopically anomalous interface between layers
    • 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
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24355—Continuous and nonuniform or irregular surface on layer or component [e.g., roofing, etc.]
    • 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
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24942—Structurally defined web or sheet [e.g., overall dimension, etc.] including components having same physical characteristic in differing degree
    • 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
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/31—Surface property or characteristic of web, sheet or block

Definitions

  • the invention relates to a method for processing a ceramic Protective layer coated gas turbine part according to the preamble of the independent Claim. Such a procedure is over US-A-4,576,874.
  • a first protective layer of the turbine blade consists of a metallic one Alloy such as MCrAlY, where M is Ni, Co or Fe. This kind of metallic Coating serves as protection against oxidation.
  • a second, rougher coating from MCrAlY is applied to it with other coating parameters. This layer is also called "bond-coating".
  • Such coatings are numerous from the prior art and for example from US-A-3,528,861 or US-A-4,585,481.
  • TBC Thermal Barrier Coating
  • Ceramic coatings and methods for Coating are for example from the documents EP-A2-441 095, EP-A1-937,787, US-A-5,972,424, US-A-4,055,705, US-A-4,248,940, US-A-4,321,311, US-A-4,676,994, US-A-5,894,053.
  • the applied protective layers have in usually a relatively high surface roughness. This surface roughness but influences the heat transfer in a positive way, so that the base material is subjected to thermal stress with increasing roughness. To avoid this is a method for smoothing the surface, for example, from Scripture EP-A2-1 088 908 known. On the other hand, however, a polished one influences Surface the flow behavior and in particular the separation behavior negative.
  • EP-A1-1 081 332 discloses a turbine blade which is characterized that a strip with increased roughness is attached downstream. These Measure has a positive effect on the detachment behavior.
  • US-A-4,576,874 discloses a process for applying a ceramic protective layer.
  • WO97 / 21907 discloses a turbine blade suitable for use in the wet steam region is provided by Vorend- and final stages of steam turbines and a Erosion wear is caused by impacting water droplets and in the area the inlet edges and parts of the airfoil is treated so that a Reduction of erosion wear results.
  • a particularly advantageous possibility To reduce the erosive effect is that the blade in the area of its leading edge and its blade back or in at least a portion of which has a surface roughness which is opposite to the Surface roughness of the front of the airfoil is significantly enhanced.
  • this object is achieved in a method according to the claim 1 solved by the roughness of the already applied reduced ceramic layer on the base material at least a first place and at least a second place the original roughness of ceramic layer is maintained.
  • the gas turbine section is a turbine blade coated with Y stabilized Zr oxide.
  • the roughness can only at least one downstream point of the Turbine blade are maintained while the remaining surface of the turbine blade smoothed.
  • the heat transfer is thus advantageously reduced, so that the heat transfer is deteriorated here, and with the same cooling performance improves the base material is cooled.
  • the ceramic Protective layer rough, so that there is some turbulence generated and the flow longer. The efficiency of the entire system is through this simple Measures advantageously increased.
  • FIG. 1 schematically shows a section through a turbine blade 1 of FIG Gas turbine.
  • the turbine blade 1 is on the surface 2 with a ceramic Protective layer 3 has been coated.
  • the ceramic protective layer 3 (Engl Barrier Coating, TBC), which is Y stabilized Zr oxide, serves as Protection against the turbine blade 1 flowing around hot gas 4, whose streamlines are visible in the figure 1.
  • Such ceramic coatings and methods of coating are, for example from the documents EP-A2-441 095, EP-A1-937,787, US-A-5,972,424, U.S. Patent Nos. 4,055,705; 4,248,940; 321,311; 4,676,994; 5,894,053 known. It is known that the applied protective layer has a certain surface roughness having.
  • the average roughness (R a , average roughness) at the first location 5 can be reduced to a maximum of 1/3 of the original average roughness.
  • the roughness R T will thus reduce, for example, from about 50 ⁇ m to 20 ⁇ m.
  • Such a smoothing of the TBC surface lowers the heat transfer coefficient by 20% to 30%. This therefore brings a significantly improved protection of the base material 1 used before the hot gases 4 at these points. 5
  • the roughness of the ceramic Protective layer 3 at least one downstream location 6, at which the detachment the hot gas flow takes place be maintained.
  • the detachment area 7 becomes thus overall smaller in comparison with a completely smooth surface, because at the risk of detachment 6 a certain turbulence, the detachment counteracts, is preserved.
  • the remaining ceramic protective layer 3 is smoothed for the purpose of a deteriorated heat transfer, ie reduced to a maximum of 1/3 of the original roughness.
  • On the smooth ground parts of the surface of the heat transfer is thus advantageously reduced, so that the heat transfer is further deteriorated here, and thus - with the same cooling performance - the base material is cooled improved.
  • the digits are 6 but not connected, but independently. This measure further serves to positively influence the detachment behavior. Between these places 6 becomes roughness for the purpose of deteriorated heat transfer again completely reduced.

Claims (5)

  1. Procédé d'usinage d'une couche de protection céramique (3), qui est appliquée sur la surface (2) d'une partie de turbine à gaz (1), la couche de protection céramique (3) présentant après son application sur la partie de turbine à gaz (1) une certaine rugosité,
    caractérisé en ce que
    la rugosité de la couche céramique déjà appliquée (3) sur le matériau de base (1) est réduite en au moins un premier endroit (5) et la rugosité initiale de la couche céramique (3) est maintenue en au moins un deuxième endroit (6).
  2. Procédé d'usinage selon la revendication 1,
    caractérisé en ce que
    la rugosité de la couche céramique appliquée (3) est réduite au premier endroit (5) jusqu'à au maximum 1/3 de la rugosité moyenne initiale.
  3. Procédé d'usinage selon l'une quelconque des revendications 1 ou 2,
    caractérisé en ce que
    la partie de turbine à gaz (1) est une aube de turbine (1) et la rugosité n'est maintenue qu'en au moins un endroit (6) sur l'aube de turbine (1) opposé à l'écoulement et susceptible de décollement, et la rugosité est réduite sur la surface restante (2) de l'aube de turbine (1).
  4. Procédé d'usinage selon la revendication 3,
    caractérisé en ce que
    la partie de turbine à gaz (1) est revêtue d'oxyde de Zr stabilisé à l'ytrine.
  5. Procédé d'usinage selon l'une quelconque des revendications précédentes,
    caractérisé en ce que
    la rugosité est réduite par meulage, sablage, polissage, trowalisage, brossage ou d'une autre manière appropriée.
EP02405661A 2001-08-14 2002-07-30 Procédé d'usinage d'une ailette de turbine à gaz Expired - Lifetime EP1284337B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH14992001 2001-08-14
CH14992001 2001-08-14

Publications (2)

Publication Number Publication Date
EP1284337A1 EP1284337A1 (fr) 2003-02-19
EP1284337B1 true EP1284337B1 (fr) 2005-04-06

Family

ID=4565523

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02405661A Expired - Lifetime EP1284337B1 (fr) 2001-08-14 2002-07-30 Procédé d'usinage d'une ailette de turbine à gaz

Country Status (3)

Country Link
US (1) US6773753B2 (fr)
EP (1) EP1284337B1 (fr)
DE (1) DE50202696D1 (fr)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10337019A1 (de) * 2003-08-12 2005-03-10 Alstom Technology Ltd Baden Verfahren zur Bearbeitung einer beschichteten Gasturbinenschaufel
EP1989399B1 (fr) * 2006-02-24 2012-02-08 MT Coatings, LLC Revêtement rugosifié pour composants de moteur de turbine à gaz
WO2008049460A1 (fr) * 2006-10-24 2008-05-02 Siemens Aktiengesellschaft PROCÉDÉ POUR RÉGLER LA RUGOSITÉ de surface LORS D'UNE OPÉRATION DE REVÊTEMENT À BASSE TEMPÉRATURE, ET ÉLÉMENT DE CONSTRUCTION
JP4793250B2 (ja) * 2006-12-21 2011-10-12 株式会社Ｉｈｉ タービン翼
EP2725235A1 (fr) * 2012-10-24 2014-04-30 Siemens Aktiengesellschaft Profil diversement rugueux et procédés associés de fabrication
US20150114006A1 (en) * 2013-10-29 2015-04-30 General Electric Company Aircraft engine strut assembly and methods of assembling the same
CN104314618B (zh) * 2014-10-09 2015-08-19 中国科学院工程热物理研究所 一种低压涡轮叶片结构及降低叶片损失的方法
US10252395B2 (en) 2015-02-16 2019-04-09 United Technologies Corporation Ceramic coating polishing method
EP3680607A1 (fr) * 2019-01-08 2020-07-15 Rolls-Royce plc Mesure de la rugosité de surface

Family Cites Families (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB580806A (en) * 1941-05-21 1946-09-20 Alan Arnold Griffith Improvements in compressor, turbine and like blades
US3528861A (en) 1968-05-23 1970-09-15 United Aircraft Corp Method for coating the superalloys
US4248940A (en) 1977-06-30 1981-02-03 United Technologies Corporation Thermal barrier coating for nickel and cobalt base super alloys
CH616960A5 (en) * 1976-02-25 1980-04-30 Sulzer Ag Components resistant to high-temperature corrosion.
US4055705A (en) 1976-05-14 1977-10-25 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Thermal barrier coating system
US4321311A (en) 1980-01-07 1982-03-23 United Technologies Corporation Columnar grain ceramic thermal barrier coatings
US4585481A (en) 1981-08-05 1986-04-29 United Technologies Corporation Overlays coating for superalloys
US4676994A (en) 1983-06-15 1987-06-30 The Boc Group, Inc. Adherent ceramic coatings
US4576874A (en) * 1984-10-03 1986-03-18 Westinghouse Electric Corp. Spalling and corrosion resistant ceramic coating for land and marine combustion turbines
US5087477A (en) 1990-02-05 1992-02-11 United Technologies Corporation Eb-pvd method for applying ceramic coatings
US5209644A (en) * 1991-01-11 1993-05-11 United Technologies Corporation Flow directing element for the turbine of a rotary machine and method of operation therefor
US5484980A (en) * 1993-02-26 1996-01-16 General Electric Company Apparatus and method for smoothing and densifying a coating on a workpiece
DE19545025A1 (de) 1995-12-02 1997-06-05 Abb Research Ltd Verfahren zur Aufbringung einer metallischen Haftschicht für keramische Wärmedämmschichten auf metallische Bauteile
DE19546008A1 (de) * 1995-12-09 1997-06-12 Abb Patent Gmbh Turbinenschaufel, die für den Einsatz im Naßdampfbereich von Vorend- und Endstufen von Turbinen vorgesehen ist
US6060177A (en) 1998-02-19 2000-05-09 United Technologies Corporation Method of applying an overcoat to a thermal barrier coating and coated article
US6103315A (en) * 1998-04-13 2000-08-15 General Electric Co. Method for modifying the surface of a thermal barrier coating by plasma-heating
US5972424A (en) 1998-05-21 1999-10-26 United Technologies Corporation Repair of gas turbine engine component coated with a thermal barrier coating
GB9920564D0 (en) * 1999-08-31 1999-11-03 Rolls Royce Plc Axial flow turbines
US6294261B1 (en) 1999-10-01 2001-09-25 General Electric Company Method for smoothing the surface of a protective coating

Also Published As

Publication number Publication date
US6773753B2 (en) 2004-08-10
EP1284337A1 (fr) 2003-02-19
DE50202696D1 (de) 2005-05-12
US20030035968A1 (en) 2003-02-20

Similar Documents

Publication Publication Date Title
EP0972128B1 (fr) Structure superficielle pour la paroi d'un canal d'ecoulement ou d'une aube de turbine
DE4436186C2 (de) Turbinen- oder Kompressorschaufel mit einer spannungsreduzierten Spitze
DE69838081T2 (de) Turbinenschaufel
EP2093012B1 (fr) Méthode pour l'usinage d'un anneau d'un rotor d'une turbine à gaz avec des aubes integrées
WO1997021907A1 (fr) Aube de turbine pour utilisation dans la zone de vapeur humide du dernier et de l'avant-dernier etage de turbines
EP1284337B1 (fr) Procédé d'usinage d'une ailette de turbine à gaz
DE3102575A1 (de) "spitzenkappe fuer eine rotorschaufel und verfahren zum austauschen derselben"
DE102012106175A1 (de) Strukturierte schleifend abtragbare Beschichtungen für Oberflächen stationärer Dampfturbinenkomponenten
DE102005055391A1 (de) Wärmedämmschicht für die Seitenflächen von Turbinenschaufelplattformen und Aufbringverfahren
DE10202810B4 (de) Turbinenlaufschaufel für den Läufer eines Gasturbinentriebwerks
EP3324002B1 (fr) Système d'étanchéité pour une turbomachine et turbomachine axiale
DE19933445C2 (de) Dichtring für nicht- hermetische Fluiddichtungen
WO2009129786A1 (fr) Chemin d'écoulement reproduit d'une turbomachine axiale destiné à réduire l'écoulement secondaire
EP1820872B1 (fr) Procédé de préparation des aubes de turbomachine avec une bande de masquage ayant un connecteur pour un traitement complémentaire, et aube de turbomachine correspondante
EP1812199A1 (fr) Procede de reparation d'aubes de turbomachines
DE102007051096A1 (de) Materialabtragung am Schaufel- /Scheiben-Schwalbenschwanz zur Spannungsreduktion an der Schaufel/Scheibe (7FA, Stufe 1)
DE102008037554A1 (de) Schwalbenschwanzbefestigung zur Verwendung mit Turbinenanordnungen und Verfahren zur Montage von Turbinenanordnungen
DE112015003695T5 (de) Dampfturbinenrotorblatt, Verfahren zum Herstellen eines Dampfturbinenrotorblatts, und Dampfturbine
DE69933797T2 (de) Gasturbinenrotorstufe und -rotorschaufel mit beschichtetem Rotorschaufelfuss und Beschichtungsverfahren für einen solchen Rotorschaufelfuss
EP3246430B1 (fr) Procédé de fabrication d'aubes ou de système d'aubes d'une turbomachine comprenant des couches de protection contre l'érosion et composant ainsi fabriqué
DE102016201523A1 (de) Schaufel einer Strömungsmaschine mit Schaufelfusswärmedämmung
EP2410132B1 (fr) Aube de compresseur d'une turbine à gaz équipée d'une structure du bord d'attaque autoaiguisante
DE10319020B4 (de) Verfahren zum Verrunden von Kanten an Schaufeln von Turbomaschinen
WO2002020949A1 (fr) Turbomachine dotee d'une aube
DE102004018585B4 (de) Triebwerkeinlaufkonus für ein Gasturbinentriebwerk

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR IE IT LI LU MC NL PT SE SK TR

AX Request for extension of the european patent

Extension state: AL LT LV MK RO SI

17P Request for examination filed

Effective date: 20030728

AKX Designation fees paid

Designated state(s): DE GB

17Q First examination report despatched

Effective date: 20031001

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: ALSTOM TECHNOLOGY LTD

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

RTI1 Title (correction)

Free format text: METHOD FOR MACHINING A COATED GAS TURBINE BLADE

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE GB

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REF Corresponds to:

Ref document number: 50202696

Country of ref document: DE

Date of ref document: 20050512

Kind code of ref document: P

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 20050609

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20060110

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20150721

Year of fee payment: 14

Ref country code: DE

Payment date: 20150721

Year of fee payment: 14

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 50202696

Country of ref document: DE

Representative=s name: ROESLER, UWE, DIPL.-PHYS.UNIV., DE

Ref country code: DE

Ref legal event code: R081

Ref document number: 50202696

Country of ref document: DE

Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH, CH

Free format text: FORMER OWNER: ALSTOM TECHNOLOGY LTD., BADEN, CH

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 50202696

Country of ref document: DE

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20160730

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170201

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160730