EP2604797A1 - Aube de rotor dotée d'un agencement de nervures ayant un revêtement abrasif - Google Patents

Aube de rotor dotée d'un agencement de nervures ayant un revêtement abrasif Download PDF

Info

Publication number
EP2604797A1
EP2604797A1 EP11193177.0A EP11193177A EP2604797A1 EP 2604797 A1 EP2604797 A1 EP 2604797A1 EP 11193177 A EP11193177 A EP 11193177A EP 2604797 A1 EP2604797 A1 EP 2604797A1
Authority
EP
European Patent Office
Prior art keywords
coating
rib
blade
ribs
sprayed
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
EP11193177.0A
Other languages
German (de)
English (en)
Other versions
EP2604797B1 (fr
Inventor
Alexander Böck
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
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 MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Priority to ES11193177T priority Critical patent/ES2773743T3/es
Priority to EP11193177.0A priority patent/EP2604797B1/fr
Priority to US13/709,322 priority patent/US9797264B2/en
Publication of EP2604797A1 publication Critical patent/EP2604797A1/fr
Application granted granted Critical
Publication of EP2604797B1 publication Critical patent/EP2604797B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C24/00—Coating starting from inorganic powder
    • C23C24/02—Coating starting from inorganic powder by application of pressure only
    • C23C24/04—Impact or kinetic deposition of particles
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/01—Selective coating, e.g. pattern coating, without pre-treatment of the material to be coated
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • 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
    • 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
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • F05D2230/311—Layer deposition by torch or flame spraying
    • 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
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • F05D2230/312—Layer deposition by plasma spraying
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/126—Baffles or ribs

Definitions

  • the present invention relates to a blade, in particular for a compressor or turbine stage of a gas turbine, with a radially outer rib arrangement having at least one rib on which a coating is arranged, a turbomachine, in particular a gas turbine, with at least one such blade and a method for Coating a rib assembly of a blade.
  • the object of the present invention is to provide an improved turbomachine.
  • a blade with the features of claim 1 is proposed, which can preferably be used in at least one compressor and / or turbine stage of a gas turbine.
  • Claim 8 provides a turbomachine, in particular a gas turbine, with a blade arrangement with such blades under protection, claim 9 a method for coating ribs of a blade. Preferred developments are subject of the dependent claims.
  • One aspect of the present invention is based on the idea of providing not or not only a harder, but also a larger surface area by a rib coating.
  • a moving blade has a radially outer rib arrangement with one or more ribs arranged one behind the other, in particular in the axial direction.
  • the term axial direction refers in particular to a coordinate direction which is aligned with an axis of rotation of the blade or turbomachine, in particular a gas turbine, as a radial direction corresponding to a direction which extends perpendicularly away from the axis of rotation, as the circumferential direction a direction which extends perpendicular to the axis of rotation and a radial direction, in particular in the direction of rotation of the blade or turbomachine, in particular gas turbine.
  • a coating is arranged on at least one, preferably two or more, in particular adjacent, and preferably on all ribs of the rib arrangement.
  • This is preferably made of metal, plastic and / or ceramic, it has a greater hardness in a preferred embodiment than the rib itself.
  • Hardness in the present case is in particular a hardness according to Vickers, Rockwell, Brinell or a similar test protocol.
  • one or more, preferably all, coatings of the rib arrangement have in each case an outer contour in a meridian section which extends in the radial direction outside, ie extended with increasing radial distance from the axis of rotation, axially or in the axial direction.
  • a meridian section is understood in particular as meaning a cross section which contains the axial direction and a radial direction.
  • An outer contour can expand in a radially outward direction in a preferred embodiment monotonously, in particular strictly monotone. This is understood in the present case in particular that a distance in the axial direction between the two outer edges of the outer contour with increasing radial distance from the axis of rotation, at least substantially, always remains at least equal (monotonous) or even always increases (strictly monotonous). Equally, however, outer contours are also included whose outer flanks approach each other in limited radial areas.
  • an outer contour that widens outward in the radial direction is understood to mean, in particular, an outer contour with two mutually opposite outer flanks whose distance in the axial direction is smaller at a first, smaller distance from the axis of rotation than at a second, larger distance from the axis of rotation ,
  • a gap between mutually facing flanks of adjacent coatings of adjacent ribs of the rib arrangement corresponds at most to an axial width of a radially outer end side of one of the two adjacent ribs.
  • the axial width is referred to in particular as the distance between an axial front and rear edge of a radially outer end face of a rib. Due to the preferred limitation of the gap on the end-side axial width of a rib, the leakage in the space between adjacent ribs can be reduced to an uncritical for the degree of efficiency.
  • a gap between mutually facing flanks of adjacent coatings of adjacent ribs of the rib arrangement corresponds to at most 75% and preferably at most 50% of such an axial width.
  • smaller gaps between coatings are preferred, with a gap advantageously having a certain minimum, which may be at least 20% of an axial width of a radially outer face of one of the two adjacent ribs, in particular, to avoid spalling of the coating.
  • one or more, in particular all ribs of the rib arrangement are inclined in the circumferential direction by an angle which is not equal to 0 ° and less than 10 °, in particular less than 5 ° and preferably less than 3 °.
  • two or more, in particular all ribs of the rib arrangement in the radial direction on outer end faces which lie, at least substantially, at the same radial height. Starting from these end faces, the ribs extend in the radial direction at different depths inwards, i. are differently high in the radial direction. This allows on the one hand the formation of small gaps between the ribs and on the other an adaptation to blades with varying radial height.
  • outer end faces of two or more, in particular all the ribs of the rib arrangement have a different radial height, in particular - at least substantially - lie on a virtual conical surface.
  • two or more, in particular all ribs of the rib arrangement in the radial direction may be of different heights.
  • the fin assembly is disposed on a shroud of the blade.
  • a shroud is presently understood in particular a flange, the extends in the axial and circumferential direction and rests in a preferred development form-fitting on shrouds in the circumferential direction of adjacent blades.
  • the shroud can be inclined in a preferred development in the axial direction to carry the above-explained ribs of different heights.
  • a method for coating one or preferably, in particular temporally parallel or sequentially, a plurality of ribs of a radially outer rib arrangement of a blade is proposed, which is particularly suitable for coating a blade according to the above-described aspect.
  • a coating material from at least two opposing injection directions is sprayed onto the fin arrangement, in particular plasma sprayed, flame-sprayed, in particular high-speed flame-sprayed, detonation-sprayed, cold-gas sprayed, arc-sprayed, and / or laser-sprayed.
  • plasma spraying means, in particular, that, for example in a plasma torch, a voltage is generated between anode (s) and cathode (s) by a voltage and gas or gas mixture is passed through the arc and ionized in this case. The dissociation or subsequent ionization produces a highly heated, electrically conductive gas of positive ions and electrons.
  • the plasmajet produced powdered coating material can be injected, which is melted by the high plasma temperature.
  • the plasma stream entrains the powder particles and throws them onto the blade to be coated.
  • the plasma coating is carried out in normal atmosphere, inert atmosphere, in vacuum or under water.
  • the spraying directions are opposite, but equal in magnitude, inclined to the radial direction, preferably by a spray angle, the amount rete- ⁇ ig greater than 20 °, in particular greater than 40 °, and / or less than 70 °, in particular less than 50 ° is.
  • the coating material can be sprayed successively or simultaneously from the two injection directions.
  • one or more coatings are post-processed, simultaneously or sequentially, after spraying the coating material.
  • a radially outer end face of the coatings can for example be ground, polished or otherwise reworked.
  • Fig. 3 shows a meridian section of a gas turbine stage according to an embodiment of the present invention with a blade 5, on the oblique shroud 1, a rib arrangement is arranged with five axially arranged behind the other ribs 2.
  • the rib assembly 2 radially opposite a honeycomb-like sealing surface 4 is arranged.
  • a sealing surface 4 ' In the otherwise matching execution of the Fig. 4 is provided instead of the honeycomb a sealing surface 4 'with one or two (dashed) counter rib (s).
  • Fig. 2 shows an enlarged detail of the shroud 1 with the rib assembly.
  • ribs 2 which are on the same Radial height, so that the ribs have different heights due to the oblique shroud 1, each arranged a coating 3.
  • This coating 3 is produced by sequential plasma spraying first in a first spraying direction S 1 , and then in an opposite or mirror-symmetrical second spraying direction S 2 , as in FIG Fig. 2 indicated by arrows applied.
  • the ribs 2 coatings 3 which in the meridian section of Fig. 2 have an outer contour which widens outward in the radial direction.
  • the axial distance grows with increasing radial distance from a rotational axis of the gas turbine (from bottom to top in Fig. 2 ) the axial distance (horizontal in Fig. 2 ) between outer edges 3.1 of the outer contour of a coating 3, the coating is wider radially outward in the axial direction.
  • a gap s between the outer flanks of adjacent coatings decreases and, radially outward, only about 75% of the axial width b of the radially outer end side of the wider of the two adjacent ribs 2 (left in FIG Fig. 2 ).
  • the ribs 2 are inclined ⁇ against the circumferential direction U by an angle which is 2 ° in the embodiment.
  • the circumferential direction U and a radial direction R are indicated in the figures, wherein Fig. 2 to 4 one section each horizontal to the plane of the Fig. 1 can thus represent an axial direction in all figures horizontally from left to right.
  • the spray coating is not shown.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Coating By Spraying Or Casting (AREA)
EP11193177.0A 2011-12-13 2011-12-13 Aube de rotor dotée d'un agencement de nervures avec revêtement abrasif Active EP2604797B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
ES11193177T ES2773743T3 (es) 2011-12-13 2011-12-13 Paleta que tiene un conjunto de nervaduras con un recubrimiento abrasivo
EP11193177.0A EP2604797B1 (fr) 2011-12-13 2011-12-13 Aube de rotor dotée d'un agencement de nervures avec revêtement abrasif
US13/709,322 US9797264B2 (en) 2011-12-13 2012-12-10 Rotating blade having a rib arrangement with a coating

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP11193177.0A EP2604797B1 (fr) 2011-12-13 2011-12-13 Aube de rotor dotée d'un agencement de nervures avec revêtement abrasif

Publications (2)

Publication Number Publication Date
EP2604797A1 true EP2604797A1 (fr) 2013-06-19
EP2604797B1 EP2604797B1 (fr) 2020-01-22

Family

ID=45400930

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11193177.0A Active EP2604797B1 (fr) 2011-12-13 2011-12-13 Aube de rotor dotée d'un agencement de nervures avec revêtement abrasif

Country Status (3)

Country Link
US (1) US9797264B2 (fr)
EP (1) EP2604797B1 (fr)
ES (1) ES2773743T3 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3121307A1 (fr) 2015-07-20 2017-01-25 MTU Aero Engines GmbH Blindage et procédé de réalisation d'un blindage
EP3260664A1 (fr) * 2016-06-24 2017-12-27 MTU Aero Engines GmbH Zone annulaire extérieure épaissie radialement d'une ailette d'étanchéité
EP3324002A1 (fr) * 2016-11-18 2018-05-23 MTU Aero Engines AG Système d'étanchéité pour une turbomachine axiale et turbomachine axiale

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE112018000960B4 (de) * 2017-02-23 2024-07-18 Mitsubishi Heavy Industries, Ltd. Turbinenlaufschaufel und gasturbine
FR3073595B1 (fr) * 2017-11-15 2020-02-07 Safran Helicopter Engines Joint a labyrinthe comprenant une lechette dotee d'un deflecteur
JP7086595B2 (ja) * 2017-12-28 2022-06-20 三菱重工航空エンジン株式会社 航空機用ガスタービン
EP3865660B1 (fr) 2020-02-11 2024-04-17 MTU Aero Engines AG Procédé d'usinage d'une pale et pale pour turbomachine

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5794338A (en) * 1997-04-04 1998-08-18 General Electric Company Method for repairing a turbine engine member damaged tip
EP1083299A2 (fr) * 1999-09-07 2001-03-14 General Electric Company Segments d'anneau de recouvrement pour aubes de turbomachines refroidis par l'intérieur
JP2005127276A (ja) * 2003-10-27 2005-05-19 Hitachi Ltd タービン用動翼及びタービン
EP1550741A1 (fr) 2002-10-09 2005-07-06 Ishikawajima-Harima Jukogyo Kabushiki Kaisha Rotor et procede de revetement destine a celui-ci
WO2005061854A1 (fr) * 2003-12-17 2005-07-07 Watson Cogeneration Company Lisses de coiffe d'extremite de turbine a gaz
US20060171813A1 (en) * 2005-02-01 2006-08-03 Honeywell International, Inc. Turbine blade tip and shroud clearance control coating system
US20070134096A1 (en) * 2005-11-15 2007-06-14 Snecma Method of making a rim situated at the free end of a blade, a blade obtained by the method, and a turbomachine fitted with the blade
EP2372093A1 (fr) * 2010-03-31 2011-10-05 Alstom Technology Ltd Forme du joint d'étanchéité sur la plateforme d'une aube de turbine

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4390320A (en) * 1980-05-01 1983-06-28 General Electric Company Tip cap for a rotor blade and method of replacement
US4884820A (en) * 1987-05-19 1989-12-05 Union Carbide Corporation Wear resistant, abrasive laser-engraved ceramic or metallic carbide surfaces for rotary labyrinth seal members
US5038014A (en) * 1989-02-08 1991-08-06 General Electric Company Fabrication of components by layered deposition
US5453329A (en) * 1992-06-08 1995-09-26 Quantum Laser Corporation Method for laser cladding thermally insulated abrasive particles to a substrate, and clad substrate formed thereby
US6476343B2 (en) * 1996-07-08 2002-11-05 Sandia Corporation Energy-beam-driven rapid fabrication system
US6190124B1 (en) * 1997-11-26 2001-02-20 United Technologies Corporation Columnar zirconium oxide abrasive coating for a gas turbine engine seal system
DE19933445C2 (de) * 1999-07-16 2001-12-13 Mtu Aero Engines Gmbh Dichtring für nicht- hermetische Fluiddichtungen
US6224337B1 (en) * 1999-09-17 2001-05-01 General Electric Company Thermal barrier coated squealer tip cavity
US6558119B2 (en) * 2001-05-29 2003-05-06 General Electric Company Turbine airfoil with separately formed tip and method for manufacture and repair thereof
FR2825411B1 (fr) * 2001-05-31 2003-09-19 Snecma Moteurs Aube de turbine avec lechette d'etancheite
US7587818B2 (en) * 2004-12-23 2009-09-15 General Electric Company Repair of gas turbine blade tip without recoating the repaired blade tip
EP2316988B1 (fr) * 2009-11-02 2015-07-08 Alstom Technology Ltd Aube de turbine résistant à l'usure et à l'oxydation

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5794338A (en) * 1997-04-04 1998-08-18 General Electric Company Method for repairing a turbine engine member damaged tip
EP1083299A2 (fr) * 1999-09-07 2001-03-14 General Electric Company Segments d'anneau de recouvrement pour aubes de turbomachines refroidis par l'intérieur
EP1550741A1 (fr) 2002-10-09 2005-07-06 Ishikawajima-Harima Jukogyo Kabushiki Kaisha Rotor et procede de revetement destine a celui-ci
JP2005127276A (ja) * 2003-10-27 2005-05-19 Hitachi Ltd タービン用動翼及びタービン
WO2005061854A1 (fr) * 2003-12-17 2005-07-07 Watson Cogeneration Company Lisses de coiffe d'extremite de turbine a gaz
US20060171813A1 (en) * 2005-02-01 2006-08-03 Honeywell International, Inc. Turbine blade tip and shroud clearance control coating system
US20070134096A1 (en) * 2005-11-15 2007-06-14 Snecma Method of making a rim situated at the free end of a blade, a blade obtained by the method, and a turbomachine fitted with the blade
EP2372093A1 (fr) * 2010-03-31 2011-10-05 Alstom Technology Ltd Forme du joint d'étanchéité sur la plateforme d'une aube de turbine

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3121307A1 (fr) 2015-07-20 2017-01-25 MTU Aero Engines GmbH Blindage et procédé de réalisation d'un blindage
DE102015213555A1 (de) 2015-07-20 2017-03-09 MTU Aero Engines AG Dichtrippenpanzerung und Verfahren zur Herstellung derselben
EP3260664A1 (fr) * 2016-06-24 2017-12-27 MTU Aero Engines GmbH Zone annulaire extérieure épaissie radialement d'une ailette d'étanchéité
DE102016211337A1 (de) * 2016-06-24 2017-12-28 MTU Aero Engines AG Verdickter radial äußerer Ringbereich eines Dichtfins
EP3324002A1 (fr) * 2016-11-18 2018-05-23 MTU Aero Engines AG Système d'étanchéité pour une turbomachine axiale et turbomachine axiale
DE102016222720A1 (de) * 2016-11-18 2018-05-24 MTU Aero Engines AG Dichtungssystem für eine axiale Strömungsmaschine und axiale Strömungsmaschine

Also Published As

Publication number Publication date
US9797264B2 (en) 2017-10-24
ES2773743T3 (es) 2020-07-14
EP2604797B1 (fr) 2020-01-22
US20130149165A1 (en) 2013-06-13

Similar Documents

Publication Publication Date Title
EP2604797B1 (fr) Aube de rotor dotée d'un agencement de nervures avec revêtement abrasif
DE4436186C2 (de) Turbinen- oder Kompressorschaufel mit einer spannungsreduzierten Spitze
DE69604154T2 (de) Abreibbare spaltabdichtung für turbomaschinen
EP2604792B1 (fr) Procédé de réparation d'un composant d'une turbomachine et composant réparé associé
DE102012106175A1 (de) Strukturierte schleifend abtragbare Beschichtungen für Oberflächen stationärer Dampfturbinenkomponenten
WO2016087140A1 (fr) Procédé de fabrication d'une aube mobile et aube ainsi obtenue
DE10121019A1 (de) Gasturbinendichtung
EP3054106B1 (fr) Composant de turbine à gaz
EP2302174A2 (fr) Turbine à gaz avec un joint à labyrinthe de la virole
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
EP3093372B1 (fr) Procede de recouvrement destine a produire une combinaison de blindage d'extremite d'aubes et couche de protection contre l'erosion
EP3324002A1 (fr) Système d'étanchéité pour une turbomachine axiale et turbomachine axiale
EP3241995B1 (fr) Segment d'aube directrice pour une turbo-machine
DE102009055913A1 (de) Labyrinthdichtung aus in eine Einlaufschicht eingreifenden Dichtringen
EP2984294B1 (fr) Aube de turbine avec arête de plate-forme étagée et biseauté
DE102009055914A1 (de) Dichtringe für eine Labyrinthdichtung
DE19730008C1 (de) Panzerung für ein metallisches Triebwerksbauteil und Verfahren zu ihrer Herstellung
DE102009040298A1 (de) Strömungsmaschine und Verfahren zur Erzeugung eines strukturierten Einlaufbelags
EP3312388B1 (fr) Pièce de rotor, compresseur, turbine et procédé de fabrication associés
EP3246430A1 (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
EP3628030A1 (fr) Procédé d'entretien d'une turbomachine
DE102006058678A1 (de) Verfahren und Vorrichtung zum Oberflächenstrahlen eines Teilelements eines Bauteils einer Gasturbine
DE102017204243A1 (de) Dichtfin mit zumindest einer gewölbten Seitenflanke
EP3260664A1 (fr) Zone annulaire extérieure épaissie radialement d'une ailette d'étanchéité
DE112020001189T5 (de) Turbinenlaufschaufel und Kontaktoberflächenherstellungsverfahren

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

17P Request for examination filed

Effective date: 20121210

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

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

Owner name: MTU AERO ENGINES AG

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

Free format text: STATUS: EXAMINATION IS IN PROGRESS

17Q First examination report despatched

Effective date: 20161107

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

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

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20190801

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

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

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1227032

Country of ref document: AT

Kind code of ref document: T

Effective date: 20200215

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502011016416

Country of ref document: DE

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20200122

REG Reference to a national code

Ref country code: ES

Ref legal event code: FG2A

Ref document number: 2773743

Country of ref document: ES

Kind code of ref document: T3

Effective date: 20200714

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

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

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200614

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200122

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200122

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200422

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200122

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

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200422

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200423

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200122

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200122

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200122

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200522

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502011016416

Country of ref document: DE

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

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200122

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200122

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200122

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200122

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200122

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200122

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200122

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: 20201023

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

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200122

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

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200122

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200122

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502011016416

Country of ref document: DE

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

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

Effective date: 20201213

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

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200122

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20201231

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

Ref country code: IE

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

Effective date: 20201213

Ref country code: FR

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

Effective date: 20201231

Ref country code: LU

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

Effective date: 20201213

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

Ref country code: LI

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

Effective date: 20201231

Ref country code: DE

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

Effective date: 20210701

Ref country code: GB

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

Effective date: 20201213

Ref country code: CH

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

Effective date: 20201231

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 1227032

Country of ref document: AT

Kind code of ref document: T

Effective date: 20201213

REG Reference to a national code

Ref country code: ES

Ref legal event code: FD2A

Effective date: 20220222

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

Ref country code: AT

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

Effective date: 20201213

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

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200122

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200122

Ref country code: ES

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

Effective date: 20201214

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200122

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

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200122

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200122

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

Ref country code: BE

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

Effective date: 20201231