EP1247874A1 - Construction composite avec matériaux métalliques et non-métalliques - Google Patents

Construction composite avec matériaux métalliques et non-métalliques Download PDF

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Publication number
EP1247874A1
EP1247874A1 EP02405227A EP02405227A EP1247874A1 EP 1247874 A1 EP1247874 A1 EP 1247874A1 EP 02405227 A EP02405227 A EP 02405227A EP 02405227 A EP02405227 A EP 02405227A EP 1247874 A1 EP1247874 A1 EP 1247874A1
Authority
EP
European Patent Office
Prior art keywords
rivets
metallic
composite structure
metallic material
base body
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.)
Ceased
Application number
EP02405227A
Other languages
German (de)
English (en)
Inventor
Reinhard Fried
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 Schweiz 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 Schweiz AG filed Critical Alstom Schweiz AG
Publication of EP1247874A1 publication Critical patent/EP1247874A1/fr
Ceased legal-status Critical Current

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Classifications

    • 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
    • C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C7/00—Patterns; Manufacture thereof so far as not provided for in other classes
    • B22C7/02—Lost patterns
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/02—Sand moulds or like moulds for shaped castings
    • B22C9/04—Use of lost patterns
    • 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
    • F01D5/284—Selection of ceramic materials
    • 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
    • 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.]
    • Y10T428/24479—Structurally defined web or sheet [e.g., overall dimension, etc.] including variation in thickness
    • Y10T428/24612—Composite web or sheet

Definitions

  • the invention relates to a cast composite structure between metallic and non-metallic materials, especially for the gas and Steam turbine construction and a method for producing this composite structure.
  • a metallic surface of a base body by means of plasma or flame spraying an adhesive layer with as rough as possible Sprayed on surface.
  • the roughness of the surface serves the form-fitting Anchoring those that are also plasma or flame sprayed onto this surface
  • Thermal insulation layer made of a non-metallic material. Because of the very different coefficients of thermal expansion between metals and These connections succeed in non-metallic materials, such as ceramics usually only up to a layer thickness of ⁇ 500 ⁇ m.
  • thermal barrier coating also called thermal barrier coating (TBC).
  • TBC thermal barrier coating
  • Known methods for producing holding structures for ceramic Thermal insulation layers are in addition to the described plasma or Flame spraying of adhesive layers, for example die sinking EDM Laser water jet electron beam modeling, soldering and sintering Particles (DE 195 45 025 A1) or the production of a co-molded, in essential network-like skeleton structure on the surface of the base body (EP 0 935 009 A1).
  • the cast-on structure known from the publication EP 0 935 009 A1 provides a continuous network within which is then after coating individual ceramic islands.
  • the welded structures show against it a continuous ceramic net on with individual metal islands, which is positive affects the properties of the layer. So are the lower ones in particular Heat conduction, the lower metal surface exposed to oxidation and the better anchoring of the ceramic layer in the welded structures in the Comparison to the cast net-like structures.
  • the invention tries to overcome the mentioned disadvantage of the known cast avoid net-like structure. It is based on the task of one cast composite structure between metallic and non-metallic Materials, especially for gas and steam turbine construction and a To create a method for producing these composite structures, in which on the one hand, a large layer thickness of a non-metallic material is stable adhesive and insensitive to impact on a metallic material is applied and on the other hand less heat conduction and less metal surface exposed to oxidation compared to the known state of technology is achieved.
  • this is the case with a composite structure between metallic and non-metallic materials in which on a surface of one Base material forming metallic material is arranged on an adhesive layer which the non-metallic material is applied as a cover layer, and the Adhesive layer made of separate spherical or webs arranged side by side and head-shaped mushroom-shaped rivets, by one on the Surface of the base body molded from the said support structure Rivets solved.
  • this is done in a method for producing the Composite structures according to the preamble of claim 8 solved in that that the Rivets using the known wax model casting process with the Base body to be cast.
  • the composite structures according to the invention continuous non-metal mesh, in particular ceramic mesh, with individual Metal islands have a positive effect on the properties of the layer effect. So are in particular the lower heat conduction, the lower the Metal surface exposed to oxidation and better anchoring of the Ceramic layer in the cast holding structures according to the invention compared to the cast net or to name grid-like holding structures.
  • 1 to 7 are the individual steps of the inventive The method is shown schematically, the inventive according to FIG. 7 Composite structure with mushroom-shaped rivets is shown as an example. 8 is one another embodiment of the invention shown with spherical rivets.
  • an adhesive layer 3 is applied to the surface of a metallic base body 2 applied, formed from individual anchor points, here called Rivets 4 is then applied to a non-metallic material 5 becomes.
  • Rivets 4 is then applied to a non-metallic material 5 becomes.
  • a characteristic of the present invention is that the holding structure (Adhesive layer 3) on the surface 10 of the base body 2 together with the Base body 2 is cast and consists of said rivets 4.
  • Material for the base body 2 and the rivets 4 are, for example, IN 738, IN 939, MA 6000, PM 2000, CMSX-4 and MARM 247 can be used.
  • the prefabricated rivets 4 either have a mushroom-shaped structure and have then a web 8 and a head 9 on (Fig. 7) or they are spherical trained (Fig. 8).
  • the shape of the rivets 4 can vary, i. H. you can different web heights and different web or head diameters to have.
  • the molded mushroom-shaped rivets 4 have one Head diameter 12 of approximately 0.8 mm to 3 mm and a web diameter 13 from approx. 0.5 mm to 2 mm, and a height 11 of approx. 1 mm to 10 mm exhibit. Then there are very good anchorage options for later given non-metallic layer to be applied.
  • the co-molded spherical rivets 4 preferably have a diameter 12 from about 0.5 mm to 3 mm, because then also good Anchoring options for the non-metallic material to be applied 5 available.
  • the special shape of the Rivets 4 ensures that a corresponding Surface roughness is created, which in the liquid state to be applied non-metallic material 5 with a positive connection the metallic base body 2, i.e. that of the rivets 4 corresponding undercuts 6 in the form of free spaces between the rivets 4 and the base body 2 are formed, into which the non-metallic material 5 flows in or claws and thus a firm connection of the non-metallic material 5 with the metallic material, in particular the Base body 2 is produced.
  • Application of the non-metallic material 5, z. B. ceramics can via known processes, such as the plasma or Flame spraying.
  • a large layer thickness 7 causes, for example, a significant reduction in the Cooling air consumption is achieved, which increases the efficiency of the gas turbine is significantly increased.
  • Adhesive layer 3 are formed as is known from the prior art Applying solder pastes with additional elements or the like is known. So it can be said that depending on the shape and size of the Rivets 4 a corresponding layer thickness 7 for the non-metallic material 5 on the Base body 2 can be applied.
  • the applied non-metallic Material 5 can withstand a sufficient foreign body impact without the non-metallic material 5 from the metallic material, that is from Basic body 2 to separate or jump off.
  • the non-metallic material 5 by a Foreign body impact can still be blasted off, so it must be ensured that only a slight destruction of the surface of the composite structure 1 takes place.
  • Due to the special production of the adhesive layer 3, in particular the special design of the mushroom-shaped rivets 4, is achieved in one Foreign matter impact is only blown off that material that over the Rivets 4 protrudes, but the non-metallic material 5 between the Rivets 4 is not separated from the composite structure 1. This will only small points of attack formed over the rivets 4 on the base body 2.
  • the layer thickness 7 for the non-metallic material 5 which, for example, ceramic material, preferably yttrium-stabilized Zirconium oxide is between 1 mm and 20 mm, because of that the Thermal insulation layer even very high temperature differences without problems resists.
  • the distance 14 between two adjacent heads 9 of the rivets 4 should preferably about 1 to 5 times the diameter 12 of the head 9 be. Larger distances are also conceivable.
  • a thermal insulation panel coated in this way was subjected to a thermal shock test subjected from 1200 ° C to room temperature.
  • On the TBC side by means of Flame heated (1200 ° C), cooled on the body side by means of compressed air (900 ° C). There were 850 thermal cycles completed without one The TBC layer came off. This shows the excellent ones Anchoring options of the ceramic material 5 in the with the Base body 2 co-molded rivets 4 existing adhesive layer 3.
  • Rivets 4 in addition to the co-molded mushroom-shaped described Rivets 4 also spherical rivets 4 can be used (Fig. 8).

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Plasma & Fusion (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Physics & Mathematics (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Connection Of Plates (AREA)
  • Ceramic Products (AREA)
  • Coating By Spraying Or Casting (AREA)
EP02405227A 2001-04-06 2002-03-22 Construction composite avec matériaux métalliques et non-métalliques Ceased EP1247874A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10117127A DE10117127B4 (de) 2001-04-06 2001-04-06 Verbundaufbau zwischen metallischen und nichtmetallischen Materialien
DE10117127 2001-04-06

Publications (1)

Publication Number Publication Date
EP1247874A1 true EP1247874A1 (fr) 2002-10-09

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP02405227A Ceased EP1247874A1 (fr) 2001-04-06 2002-03-22 Construction composite avec matériaux métalliques et non-métalliques

Country Status (4)

Country Link
US (1) US20020146541A1 (fr)
EP (1) EP1247874A1 (fr)
JP (1) JP2002336935A (fr)
DE (1) DE10117127B4 (fr)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1275748A2 (fr) * 2001-07-13 2003-01-15 ALSTOM (Switzerland) Ltd Revêtement resistant aux temperatures elevées avec des bosses localles enrobées et son procédé de fabrication
EP1481747A2 (fr) * 2003-05-27 2004-12-01 Alstom Technology Ltd Procédé de fabrication d'une pièce chargée par chaleur et piéce
EP1645660A1 (fr) * 2004-10-07 2006-04-12 Siemens Aktiengesellschaft Système de revêtement
GB2427845A (en) * 2001-05-22 2007-01-10 Howmet Res Corp A cast metallic article
WO2007087989A1 (fr) * 2006-02-02 2007-08-09 Daimler Ag Conditionnement de surface pour couCHEs de pulvérisation thermique
EP2395129A1 (fr) * 2010-06-08 2011-12-14 United Technologies Corporation Agencement d'un revêtement en céramique et procédé de production correspondant
WO2012131100A1 (fr) * 2011-04-01 2012-10-04 Rolls-Royce Deutschland Ltd & Co Kg Procédé de fabrication d'une pièce, la pièce même et turbomachine munie d'une telle pièce
DE102005050873B4 (de) * 2005-10-21 2020-08-06 Rolls-Royce Deutschland Ltd & Co Kg Verfahren zur Herstellung einer segmentierten Beschichtung und nach dem Verfahren hergestelltes Bauteil

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US20030031720A1 (en) * 2000-02-24 2003-02-13 Tobias Laich Method for producing pharmaceutical dosage forms
DE10117128A1 (de) * 2001-04-06 2002-10-10 Alstom Switzerland Ltd Verfahren zur Herstellung von Verbundaufbauten zwischen metallischen und nichtmetallischen Materialien
US7066235B2 (en) * 2002-05-07 2006-06-27 Nanometal, Llc Method for manufacturing clad components
EP1452688A1 (fr) * 2003-02-05 2004-09-01 Siemens Aktiengesellschaft Rotor pour une turbine à vapeur, procédé et utilisation de refroidissement d'un tel rotor
DE10357180A1 (de) * 2003-12-08 2005-06-30 Alstom Technology Ltd Verbundaufbau zwischen metallischen und nichtmetallischen Materialien
US7672705B2 (en) * 2004-07-19 2010-03-02 Resonant Medical, Inc. Weighted surface-to-surface mapping
US8065848B2 (en) 2007-09-18 2011-11-29 Tac Technologies, Llc Structural member
US7721496B2 (en) * 2004-08-02 2010-05-25 Tac Technologies, Llc Composite decking material and methods associated with the same
US8266856B2 (en) 2004-08-02 2012-09-18 Tac Technologies, Llc Reinforced structural member and frame structures
JP4911012B2 (ja) * 2007-12-17 2012-04-04 住友金属鉱山株式会社 貴金属インゴット鋳造用耐熱鋳鋼鋳型およびこれを用いた貴金属インゴットの鋳造方法
US8852720B2 (en) * 2009-07-17 2014-10-07 Rolls-Royce Corporation Substrate features for mitigating stress
WO2011085376A1 (fr) 2010-01-11 2011-07-14 Rolls-Royce Corporation Éléments d'atténuation d'une contrainte thermique ou mécanique sur un revêtement anticorrosion protégeant de l'environnement
DE102011077620A1 (de) * 2011-06-16 2012-12-20 Rolls-Royce Deutschland Ltd & Co Kg Bauelement, Verfahren zur Herstellung eines Bauelementes und Flugzeugtriebwerk mit einem Bauelement
DE102011085801A1 (de) * 2011-11-04 2013-05-08 Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. Bauelement und Turbomaschine mit einem Bauelement
EP2592174A1 (fr) * 2011-11-14 2013-05-15 Siemens Aktiengesellschaft Système de couche doté d'une surface de substrat structurée et son procédé de fabrication
US10040094B2 (en) 2013-03-15 2018-08-07 Rolls-Royce Corporation Coating interface
EP2789597B1 (fr) * 2013-04-12 2017-11-15 Ansaldo Energia IP UK Limited Méthode pour obtenir une configuration pour assembler un matériau d'isolation thermique en céramique à une structure métallique
US8939706B1 (en) 2014-02-25 2015-01-27 Siemens Energy, Inc. Turbine abradable layer with progressive wear zone having a frangible or pixelated nib surface
US9243511B2 (en) 2014-02-25 2016-01-26 Siemens Aktiengesellschaft Turbine abradable layer with zig zag groove pattern
CN106030039A (zh) 2014-02-25 2016-10-12 西门子公司 具有深度变化材料性质的涡轮机部件热障涂层
US9151175B2 (en) 2014-02-25 2015-10-06 Siemens Aktiengesellschaft Turbine abradable layer with progressive wear zone multi level ridge arrays
EP3029274B1 (fr) 2014-10-30 2020-03-11 United Technologies Corporation Liaison pulvérisée thermiquement d'une structure en céramique à un substrat
JP6183382B2 (ja) * 2015-01-08 2017-08-23 マツダ株式会社 周面の溝構造及びその加工方法
EP3259452A2 (fr) 2015-02-18 2017-12-27 Siemens Aktiengesellschaft Formation de passages de refroidissement dans des pièces coulées en superalliage d'une turbine à combustion
WO2016133581A1 (fr) 2015-02-18 2016-08-25 Siemens Aktiengesellschaft Carénage de turbine à couche abradable ayant des arêtes et rainures composites non fléchies à trois angles
US10995620B2 (en) * 2018-06-21 2021-05-04 General Electric Company Turbomachine component with coating-capturing feature for thermal insulation
US11492974B2 (en) * 2020-05-08 2022-11-08 Raytheon Technologies Corporation Thermal barrier coating with reduced edge crack initiation stress and high insulating factor

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WO1996033837A1 (fr) * 1995-04-25 1996-10-31 Mdc Max Dätwyler Bleienbach Ag Procede permettant de preparer la surface d'une piece comportant un materiau support metallique, et piece munie d'un materiau support metallique
DE19545025A1 (de) * 1995-12-02 1997-06-05 Abb Research Ltd Verfahren zur Aufbringung einer metallischen Haftschicht für keramische Wärmedämmschichten auf metallische Bauteile
EP0921209A2 (fr) * 1997-11-26 1999-06-09 Rolls-Royce Plc Pièce en superalliage revêtue et méthode pour appliquer un revêtement sur un article en superalliage
US20010004436A1 (en) * 1999-12-20 2001-06-21 Sulzer Metco Ag Profiled surface used as an abradable in flow machines

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2427845A (en) * 2001-05-22 2007-01-10 Howmet Res Corp A cast metallic article
GB2427845B (en) * 2001-05-22 2007-02-14 Howmet Res Corp Cast metallic article
EP1275748A3 (fr) * 2001-07-13 2004-01-07 ALSTOM (Switzerland) Ltd Revêtement resistant aux temperatures elevées avec des bosses localles enrobées et son procédé de fabrication
EP1275748A2 (fr) * 2001-07-13 2003-01-15 ALSTOM (Switzerland) Ltd Revêtement resistant aux temperatures elevées avec des bosses localles enrobées et son procédé de fabrication
EP1481747A3 (fr) * 2003-05-27 2007-05-02 Alstom Technology Ltd Procédé de fabrication d'une pièce chargée par chaleur et piéce
EP1481747A2 (fr) * 2003-05-27 2004-12-01 Alstom Technology Ltd Procédé de fabrication d'une pièce chargée par chaleur et piéce
EP1645660A1 (fr) * 2004-10-07 2006-04-12 Siemens Aktiengesellschaft Système de revêtement
DE102005050873B4 (de) * 2005-10-21 2020-08-06 Rolls-Royce Deutschland Ltd & Co Kg Verfahren zur Herstellung einer segmentierten Beschichtung und nach dem Verfahren hergestelltes Bauteil
WO2007087989A1 (fr) * 2006-02-02 2007-08-09 Daimler Ag Conditionnement de surface pour couCHEs de pulvérisation thermique
US8209831B2 (en) 2006-02-02 2012-07-03 Daimler Ag Surface conditioning for thermal spray layers
EP2395129A1 (fr) * 2010-06-08 2011-12-14 United Technologies Corporation Agencement d'un revêtement en céramique et procédé de production correspondant
US8535783B2 (en) 2010-06-08 2013-09-17 United Technologies Corporation Ceramic coating systems and methods
WO2012131100A1 (fr) * 2011-04-01 2012-10-04 Rolls-Royce Deutschland Ltd & Co Kg Procédé de fabrication d'une pièce, la pièce même et turbomachine munie d'une telle pièce
US9908173B2 (en) 2011-04-01 2018-03-06 Rolls-Royce Deutschland & Co Kg Method for producing a component, component and turbomachine having a component

Also Published As

Publication number Publication date
DE10117127A1 (de) 2002-10-10
US20020146541A1 (en) 2002-10-10
DE10117127B4 (de) 2009-12-31
JP2002336935A (ja) 2002-11-26

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