EP0702130A2 - Extrémité d'aube avec un revêtement coupant - Google Patents

Extrémité d'aube avec un revêtement coupant Download PDF

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Publication number
EP0702130A2
EP0702130A2 EP95113444A EP95113444A EP0702130A2 EP 0702130 A2 EP0702130 A2 EP 0702130A2 EP 95113444 A EP95113444 A EP 95113444A EP 95113444 A EP95113444 A EP 95113444A EP 0702130 A2 EP0702130 A2 EP 0702130A2
Authority
EP
European Patent Office
Prior art keywords
component
run
pad
cutting edges
profiled
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
EP95113444A
Other languages
German (de)
English (en)
Other versions
EP0702130B1 (fr
EP0702130A3 (fr
Inventor
Johannes Dr. Schröder
Thomas Dr. Uihlein
Hans Weber
Herbert Fischer
Erwin Fischhaber
Norbert Legrand
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 Motoren und Turbinen Union Muenchen 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 Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
Publication of EP0702130A2 publication Critical patent/EP0702130A2/fr
Publication of EP0702130A3 publication Critical patent/EP0702130A3/fr
Application granted granted Critical
Publication of EP0702130B1 publication Critical patent/EP0702130B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • 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
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • 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
    • 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
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/21—Oxide ceramics
    • 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.]
    • Y10T428/24372—Particulate matter
    • Y10T428/24413—Metal or metal compound
    • 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.]
    • Y10T428/24802—Discontinuous or differential coating, impregnation or bond [e.g., artwork, printing, retouched photograph, etc.]
    • Y10T428/24926—Discontinuous or differential coating, impregnation or bond [e.g., artwork, printing, retouched photograph, etc.] including ceramic, glass, porcelain or quartz layer
    • 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
    • Y10T428/25—Web or sheet containing structurally defined element or component and including a second component containing structurally defined particles
    • Y10T428/256—Heavy metal or aluminum or compound thereof
    • 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
    • Y10T428/25—Web or sheet containing structurally defined element or component and including a second component containing structurally defined particles
    • Y10T428/256—Heavy metal or aluminum or compound thereof
    • Y10T428/257—Iron oxide or aluminum oxide

Definitions

  • Another preferred ceramic material for the tarnish is Al2O3, which is known as corundum and can be used accordingly inexpensively.
  • Mixed oxides can also be used for the startup covering according to the invention.
  • FIG. 2 shows a photographic enlargement of a blade tip armor according to the invention on a scale of about 5: 1.
  • the blade and blade root are clearly recognizable.
  • On the tip of the airfoil there is a profiled rubbing surface that is brightly opposite the interstices showing the blade contour to discharge the abrasion of an inlet coating into which this starting coating is incorporated during the brushing process.
  • a scale-like structure can be clearly seen on the tip of the blade.
  • This scale-like structure consists in this embodiment of ZrO27Y2O3 thermally sprayed through a wire mesh mask.
  • the wire thickness of the wire mesh mask is 0.22 mm with a clear mesh width of 0.4 mm.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Plasma & Fusion (AREA)
  • Physics & Mathematics (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Coating By Spraying Or Casting (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Laminated Bodies (AREA)
  • Paints Or Removers (AREA)
EP95113444A 1994-09-16 1995-08-26 Procédé pour la production d'un revêtement abrasif pour des constituants métalliques de propulseurs Expired - Lifetime EP0702130B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4432998 1994-09-16
DE4432998A DE4432998C1 (de) 1994-09-16 1994-09-16 Anstreifbelag für metallische Triebwerkskomponente und Herstellungsverfahren

Publications (3)

Publication Number Publication Date
EP0702130A2 true EP0702130A2 (fr) 1996-03-20
EP0702130A3 EP0702130A3 (fr) 1998-06-10
EP0702130B1 EP0702130B1 (fr) 2003-04-23

Family

ID=6528373

Family Applications (1)

Application Number Title Priority Date Filing Date
EP95113444A Expired - Lifetime EP0702130B1 (fr) 1994-09-16 1995-08-26 Procédé pour la production d'un revêtement abrasif pour des constituants métalliques de propulseurs

Country Status (5)

Country Link
US (2) US5756217A (fr)
EP (1) EP0702130B1 (fr)
AT (1) ATE238489T1 (fr)
DE (2) DE4432998C1 (fr)
ES (1) ES2196035T3 (fr)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR100466836B1 (ko) * 2000-08-09 2005-01-17 로렐세이키 가부시키가이샤 시각장애자용 정보입출력장치
EP1764478A2 (fr) 2005-09-19 2007-03-21 General Electric Company Aube de turbine à vapeur et procédé associé
EP1808508A1 (fr) * 2006-01-17 2007-07-18 Siemens Aktiengesellschaft Composant disposé dans le conduit d'écoulement d'une turbomachine et procédé de pulvérisation pour produire un revêtement.
EP1820938A1 (fr) * 2006-02-20 2007-08-22 ABB Turbo Systems AG Eléments de nettoyage sur les extrémités des aubes d' une turbine
EP1925779A1 (fr) * 2006-11-23 2008-05-28 Siemens Aktiengesellschaft Composant de guidage d'écoulement et méthode de fabrication associée
DE102009012945A1 (de) 2009-03-12 2010-09-16 Mtu Aero Engines Gmbh Verfahren zur Herstellung einer abrasiven Beschichtung und Bauteil für eine Turbomaschine
EP2309098A1 (fr) * 2009-09-30 2011-04-13 Siemens Aktiengesellschaft Profil et aube directrice, aube rotorique, turbine à gaz et turbomachine associées
WO2011088817A1 (fr) * 2010-01-22 2011-07-28 Mtu Aero Engines Gmbh Revêtement de surface structuré par projection cinétique à gaz froid
EP2617949A3 (fr) * 2012-01-23 2014-12-31 MTU Aero Engines GmbH Agencement d'étanchéité pour turbomachines
FR3026428A1 (fr) * 2014-09-30 2016-04-01 Snecma Aube de rotor de turbomachine a lechettes radiales
EP3006672A1 (fr) * 2014-10-10 2016-04-13 Universität Stuttgart Dispositif destiné à influencer l'écoulement dans une turbomachine

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US6004362A (en) * 1998-02-02 1999-12-21 Lockheed Martin Energy Systems Method for forming an abrasive surface on a tool
DE10047307A1 (de) * 2000-09-25 2002-08-01 Alstom Switzerland Ltd Dichtungsanordnung
DE10140742B4 (de) * 2000-12-16 2015-02-12 Alstom Technology Ltd. Vorrichtung zur Dichtspaltreduzierung zwischen einer rotierenden und einer stationären Komponente innerhalb einer axial durchströmten Strömungsmaschine
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WO2003010419A1 (fr) * 2001-07-23 2003-02-06 Alstom Technology Ltd Dispositif pour reduire la fente d'etancheite entre composant mobile et composant stationnaire a l'interieur d'une turbomachine
DE10340147B4 (de) * 2002-08-27 2014-04-10 Kyocera Corp. Trockenätzverfahren und Trockenätzvorrichtung
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US8845283B2 (en) * 2010-11-29 2014-09-30 General Electric Company Compressor blade with flexible tip elements and process therefor
EP2458157B1 (fr) * 2010-11-30 2015-10-14 Techspace Aero S.A. Abradable de virole intérieure de stator
US8888446B2 (en) * 2011-10-07 2014-11-18 General Electric Company Turbomachine rotor having patterned coating
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US9909428B2 (en) * 2013-11-26 2018-03-06 General Electric Company Turbine buckets with high hot hardness shroud-cutting deposits
US9249680B2 (en) 2014-02-25 2016-02-02 Siemens Energy, Inc. Turbine abradable layer with asymmetric ridges or grooves
US8939716B1 (en) 2014-02-25 2015-01-27 Siemens Aktiengesellschaft Turbine abradable layer with nested loop groove pattern
US9151175B2 (en) 2014-02-25 2015-10-06 Siemens Aktiengesellschaft Turbine abradable layer with progressive wear zone multi level ridge arrays
WO2016133987A2 (fr) 2015-02-18 2016-08-25 Siemens Aktiengesellschaft Formation de passages de refroidissement dans des pièces coulées en superalliage d'une turbine à combustion
CN106232946B (zh) 2014-02-25 2018-04-27 西门子公司 具有气流引导的像素化表面特征样式的涡轮机可磨耗层
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US9243511B2 (en) 2014-02-25 2016-01-26 Siemens Aktiengesellschaft Turbine abradable layer with zig zag groove pattern
US11105216B2 (en) * 2014-05-15 2021-08-31 Nuovo Pignone Srl Method of manufacturing a component of a turbomachine, component of a turbomachine and turbomachine
US9932839B2 (en) 2014-06-04 2018-04-03 United Technologies Corporation Cutting blade tips
US11066937B2 (en) 2014-06-04 2021-07-20 Raytheon Technologies Corporation Cutting blade tips
US9982358B2 (en) * 2014-06-04 2018-05-29 United Technologies Corporation Abrasive tip blade manufacture methods
DE102014212652A1 (de) * 2014-06-30 2016-01-14 MTU Aero Engines AG Strömungsmaschine
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FR3029813B1 (fr) * 2014-12-16 2019-07-19 Airbus Operations (S.A.S.) Procede de fabrication d'un revetement microstructure
WO2016133583A1 (fr) 2015-02-18 2016-08-25 Siemens Aktiengesellschaft Anneau de cerclage de turbine ayant couche abradable présentant des crêtes dotées de trous
CN108431290B (zh) 2015-11-10 2021-03-23 欧瑞康表面处理解决方案股份公司普费菲孔 涡轮间隙控制涂层和方法
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FR3065482B1 (fr) * 2017-04-20 2019-07-05 Safran Aircraft Engines Element d'anneau d'etancheite pour turbine comportant une cavite inclinee dans un materiau abradable
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Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR100466836B1 (ko) * 2000-08-09 2005-01-17 로렐세이키 가부시키가이샤 시각장애자용 정보입출력장치
EP1764478A2 (fr) 2005-09-19 2007-03-21 General Electric Company Aube de turbine à vapeur et procédé associé
EP1764478A3 (fr) * 2005-09-19 2008-10-29 General Electric Company Aube de turbine à vapeur et procédé associé
WO2007082823A1 (fr) 2006-01-17 2007-07-26 Siemens Aktiengesellschaft Élément à disposer dans un canal d'écoulement d'une turbomachine et procédé de pulvérisation pour réaliser un revêtement
EP1808508A1 (fr) * 2006-01-17 2007-07-18 Siemens Aktiengesellschaft Composant disposé dans le conduit d'écoulement d'une turbomachine et procédé de pulvérisation pour produire un revêtement.
US8277194B2 (en) 2006-01-17 2012-10-02 Siemens Aktiengesellschaft Component to be arranged in the flow channel of a turbomachine and spraying method for producing the coating
EP1820938A1 (fr) * 2006-02-20 2007-08-22 ABB Turbo Systems AG Eléments de nettoyage sur les extrémités des aubes d' une turbine
EP1925779A1 (fr) * 2006-11-23 2008-05-28 Siemens Aktiengesellschaft Composant de guidage d'écoulement et méthode de fabrication associée
DE102009012945A1 (de) 2009-03-12 2010-09-16 Mtu Aero Engines Gmbh Verfahren zur Herstellung einer abrasiven Beschichtung und Bauteil für eine Turbomaschine
EP2309098A1 (fr) * 2009-09-30 2011-04-13 Siemens Aktiengesellschaft Profil et aube directrice, aube rotorique, turbine à gaz et turbomachine associées
WO2011088817A1 (fr) * 2010-01-22 2011-07-28 Mtu Aero Engines Gmbh Revêtement de surface structuré par projection cinétique à gaz froid
EP2617949A3 (fr) * 2012-01-23 2014-12-31 MTU Aero Engines GmbH Agencement d'étanchéité pour turbomachines
US10385783B2 (en) 2012-01-23 2019-08-20 MTU Aero Engines AG Turbomachine seal arrangement
FR3026428A1 (fr) * 2014-09-30 2016-04-01 Snecma Aube de rotor de turbomachine a lechettes radiales
EP3006672A1 (fr) * 2014-10-10 2016-04-13 Universität Stuttgart Dispositif destiné à influencer l'écoulement dans une turbomachine

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ES2196035T3 (es) 2003-12-16
DE4432998C1 (de) 1996-04-04
US6171351B1 (en) 2001-01-09
DE59510655D1 (de) 2003-05-28
ATE238489T1 (de) 2003-05-15
EP0702130B1 (fr) 2003-04-23
US5756217A (en) 1998-05-26
EP0702130A3 (fr) 1998-06-10

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