EP1481747A2 - Procédé de fabrication d'une pièce chargée par chaleur et piéce - Google Patents

Procédé de fabrication d'une pièce chargée par chaleur et piéce Download PDF

Info

Publication number
EP1481747A2
EP1481747A2 EP04102328A EP04102328A EP1481747A2 EP 1481747 A2 EP1481747 A2 EP 1481747A2 EP 04102328 A EP04102328 A EP 04102328A EP 04102328 A EP04102328 A EP 04102328A EP 1481747 A2 EP1481747 A2 EP 1481747A2
Authority
EP
European Patent Office
Prior art keywords
metallic
component
blade
heat
mold
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.)
Withdrawn
Application number
EP04102328A
Other languages
German (de)
English (en)
Other versions
EP1481747A3 (fr
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 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 EP1481747A2 publication Critical patent/EP1481747A2/fr
Publication of EP1481747A3 publication Critical patent/EP1481747A3/fr
Withdrawn legal-status Critical Current

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D19/00—Casting in, on, or around objects which form part of the product
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D19/00—Casting in, on, or around objects which form part of the product
    • B22D19/04—Casting in, on, or around objects which form part of the product for joining parts
    • 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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • 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
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/203—Heat transfer, e.g. cooling by transpiration cooling
    • 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
    • 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

Definitions

  • the invention relates to a method for producing a heat-stressed component according to the preamble of the independent claim. Furthermore concerns the invention a heat-stressed component, in particular a blade of a gas turbine.
  • Cooling technology can be improved to the material temperatures when operating in keep a safe area.
  • cooling channels are used, which e.g. be fed from the compressor with cooling fluid. It tries to get one the greatest possible cooling effect with the smallest possible losses in terms of Achieve overall system performance.
  • the front edge of a gas turbine blade is particularly one exposed to high temperatures.
  • material temperatures i.e. to lower the front edge considerably to cool intensively or to isolate heat, for example by impingement cooling or film cooling and / or ceramic protective layers (thermal Barrier Coating TBC).
  • the blade of a turbomachine is known from US Pat. No. 6,183,198 consists essentially of two side walls, which on the front edge and on the trailing edge of the blade are joined together so that one is in the longitudinal direction the vane expanding cavity is formed. At the front edge The blade has film cooling holes attached to the leading edge of the Cool the shovel. However, film cooling lowers due to the high consumption in cooling air the efficiency of the process.
  • Ceramic guide vanes are known from US Pat. No. 6,200,092 B1, in which a Front edge element is connected to the rear edge area and bands.
  • the leading edge elements preferably consist of a ceramic matrix with ceramic fibers arranged therein, the trailing edge elements from a Ceramic matrix without fibers.
  • ceramic blades are very expensive in production, are problematic in handling and very fragile against tensile stress.
  • the invention has for its object the disadvantages of the prior art to overcome and a method for producing a heat-stressed component To provide, which the manufacture of a component with high thermal resistance Areas allowed at low cost and good manageability.
  • the advantages of the invention can be seen, inter alia, in that the Design of parts of the heat-stressed component with a non-metallic Body these areas very high temperatures and thus a high can be exposed to thermal stress.
  • the non-metallic body By pouring the non-metallic body in the metallic base body of the heat-loaded Component, a secure connection of the two components can be guaranteed.
  • the component can be designed so that the non-metallic component does not have to absorb tensile stress, which increases the life of the Component increased.
  • the heat-loaded component is a scoop a thermal turbo machine and the non-metallic, porous body the front edge of the blade and / or on its rear edge and / or on its Platform is arranged. This will be an inexpensive way to increase Efficiency of heat engines stated and this with a simple Manufacturing process.
  • the airfoil 1 shows an airfoil 1 of a thermal fluid machine in cross section.
  • the airfoil 1 has a leading edge region 3, a trailing edge region 4, a suction-side wall 5 and a pressure-side wall 6, the suction-side 5 and the pressure-side wall 6 being connected to one another at least in the region of the leading edge 3 and the trailing edge 4, as a result of which a cavity 2 is formed.
  • the leading edge region 3 is acted upon first by the fluids flowing around the airfoil 1 and is therefore exposed to high temperature loads.
  • the cavity 2 runs essentially in the radial direction through the airfoil 1 and serves as a cooling fluid passage for a cooling fluid 7.
  • the front edge of the blade is formed by a non-metallic, preferably ceramic, body 8, which preferably has an open porosity.
  • This ceramic body 8 is connected to the airfoil 1 via holding structures 9.
  • the ceramic body 8 can be produced, for example, by means of slip casting in order to produce an open-pore porosity in the ceramic body 8.
  • the slip casting contains a lot of water and / or binders, which gasify during sintering. This leaves open-pore cavities if sintering is not carried out tightly, ie the sintering temperature is not too high.
  • the slip casting can also be mixed with plastic balls, such as polystyrene, which burn during sintering and thus create an open-pore porosity.
  • the slip casting may also contain bound gases which lead to foaming of the slip at high temperature.
  • porous ceramics The production of porous ceramics is known and specifically adjustable parameters are pore size, pore size distribution and the proportion of open or closed porosity.
  • An yttrium-stabilized zirconium oxide is preferably used as the material for the ceramic body 8, for example with a composition of 2.5% by weight HfO 2 , 7-9% by weight Y 2 O 3 , remainder ZrO 2 and impurities.
  • Materials from the groups of perovskites, spinels, pyrochlores and simple oxides meet the basic requirements that are placed on a material that can be used as a thermal insulation layer 8. These requirements are: low thermal conductivity, high melting point, no phase change in the area of the operating temperatures and a thermal expansion coefficient adapted to the metallic base material.
  • the adjustment of the coefficient of expansion is not of the same importance as with conventional composites.
  • non-oxide ceramic materials such as Si 3 N 4 , SiC, C / C, etc. can also be used.
  • these oxidation protection layers such as mullite (3Al 2 O 3 "2SiO 2 ), yttrium silicates, zircon, etc. being applied, for example by plasma spraying.
  • Long fiber composite systems can also be used, and the matrix can be porous. Such systems can consist, for example, of a matrix of mullite and aluminum silicate fibers, the system being produced by pressureless sintering and hot pressing.
  • a PVD (Physical Vapor Deposition) process can also be used to manufacture the ceramic body, which process is usually only used for thin layers.
  • a thermal insulation layer is formed from stem-shaped ZrO 2 crystals, which are held by the macroscopic holding structures described below.
  • Such a ceramic body 8 can be arranged at all points which are exposed to high temperature loads, so also on the rear edge 4 of the airfoil 1 or not shown on the platforms of the airfoil. Cooling fluid 7 is conducted to the ceramic body 8 via openings 10 in the metallic part of the airfoil 1 via the cavity 2. This cooling fluid can now emerge from the front edge 3 via the porous ceramic body 8 and thus generates perspiration cooling at the front edge 3. The ceramic body thus relieves the front edge thermally and achieves a high thermal shock resistance. Such a blade can also be reconditioned.
  • the porous ceramic body 8 is in the manufacture of the airfoil 1, respectively the shovel, by casting using the lost wax process, inserted as a pre-produced ceramic part in the wax mold.
  • the wax form recesses arranged, in which ceramic body 8 egg n-inserted can be. Any undercuts are made with wax closed. Then the wax mold and the ceramic part become more liquid Ceramics, e.g. Ceramic slip enveloped. The dried form is heat treated and melted or burned out the wax.
  • the porous Ceramic part 8 is now held by the mold, and this mold is with poured out liquid metallic material.
  • Can as a metallic material any metallic materials of the prior art for use come that used for the production of thermally stressed components and meet the desired requirements.
  • thermally highly stable super alloys e.g. Iron-nickel superalloy IN 706 type, nickel-based superalloys, single crystal and directionally solidifiable Alloys etc. used.
  • Other such alloys are particular IN738, IN792, IN939, GTD111, MAR M247, CM247LC DS, CMSX-2 / -3 SX, MC-2, CMSX-4 / MK-4, PWA1484, etc.
  • the blade is then removed from the mold and reworked if necessary.
  • other casting methods can also be used, such as prefabricated casting molds, in which the ceramic body is then inserted.
  • the porous ceramic body 8 forms the front edge 3 of the airfoil 1.
  • the body is not straight, but with protrusions 11 as holding structures designed, which may also have undercuts. Through this interlocking will have a good mechanical connection of ceramic body with achieved the metallic part of the airfoil 1. It also makes this Area that prevents cracking and spreading.
  • cavities 12 are arranged in the areas in which the connection should take place between metallic and non-metallic body 8.
  • This Cavities preferably have a shape such that they are in the transition region to the metallic material an opening 13 with a narrower Have cross-section as the inner cavity 14 inside the ceramic Body 8.
  • metallic material flows into the Cavities 12 of the ceramic body, so that through the opening 13 with a narrower Cross-section as the inner cavity 14 creates an undercut and the ceramic body cannot be detached from the metallic part of the blade is connected.
  • the cavities 12 usually have a depth of 0.2 mm to 10mm, in particular from 0.5mm to 10mm, with natural pores usually have a size of 0.01 mm to 0.5 mm.
  • FIG. 6 and 7 is a cast airfoil 1 with a porous ceramic Body 8 shown in FIG. 5.
  • the cavities 12 are here with the metallic Material of the airfoil 1 filled, which is the mechanical Connection between the airfoil 1 and ceramic body 8 results.
  • the ceramic body 8 can also be configured with projections 11 here to improve the mechanical connection.
  • FIGS. 8 and 9 show a possibility for subsequently arranging a porous ceramic body 8 on the front edge of an airfoil or for replacing a defective ceramic body 8 according to FIGS. 1 to 7.
  • the undercuts in the previously shown cast variants can hinder the subsequent installation of a ceramic body 8, so that the airfoil 1 may have to be pre-processed. Due to the design of the body 8, however, it is also possible to insert it from the side and to achieve a certain mechanical connection with the metallic part of the airfoil 1 by means of projections 11.
  • the ceramic body 8 can additionally be connected to the metallic base body by means of soldering at soldering points 15.
  • the soldering points 15 are preferably designed such that they protrude and can be partially ground off after the soldering process in order to be able to remove the heat-affected zone of the soldering process.
  • the holding element 16 is preferably made of a metallic material and preferably of the same metallic material as the metallic blade.
  • other metallic coating materials can also be used for the holding elements 16.
  • MCrALY is preferably used, where M can be Ni and / or Co.
  • Such MCrALY alloys have, for example, a composition of (each in% by weight): SV34 with 11.8 to 12.8% Cr, 23.5 to 24.5% Co, 11.6 to 12.2% Al, 2.8 to 3% Re, 0.8 to 1.2% Si, 0.4 up to 0.6% Y, 0.4 to 0.6% Ta, balance Ni and impurities or SV20 with 25% Cr, 5.5% Al, 3% Si, 1% Ta, 0.5% Y, balance Ni and impurities or Haynes 214 with 16% Cr, 4.5% Al, 2.5% Fe, balance Ni and impurities, etc.
  • the holding elements 16 are e.g. welded to the metal blade material and engage and prevent recesses 17 in the porous body 8 mechanically falling out of the body 8. The projections 11 are then not needed.
  • holding elements 16 are shown in detail.
  • Such holding elements 16 are essentially known from the prior art, for example from DE 100 57 187 A1. These holding elements are applied to the surface of the metallic base body of the blade by means of welding, riveting or casting processes.
  • the material of the holding elements 16 can be chosen to be essentially identical to the metallic material of the base body of the blade. However, other metallic coating materials can also be used for the holding elements.
  • MCrALY is preferably used, where M can be Ni and / or Co.
  • Such MCrALY alloys have, for example, a composition of (each in% by weight): SV34 with 11.8 to 12.8% Cr, 23.5 to 24.5% Co, 11.6 to 12.2% Al, 2.8 to 3% Re, 0.8 to 1.2% Si, 0.4 up to 0.6% Y, 0.4 to 0.6% Ta, balance Ni and impurities or SV20 with 25% Cr, 5.5% Al, 3% Si, 1% Ta, 0.5% Y, balance Ni and impurities or Haynes 214 with 16% Cr, 4.5% Al, 2.5% Fe, balance Ni and impurities, etc.
  • the holding elements 16 are designed such that an undercut 18 is produced becomes. This undercut is shown in FIGS. 11 and 13 by a spherical holding element 16 or according to FIG. 12 by a mushroom-shaped holding element 16 generated. These mushroom-shaped holding elements 16 are by a Neck 21 and a head 22 are formed, the neck 21 having a smaller diameter has as the head 22. This mushroom-shaped design of the holding elements 16 can layer thicknesses 19 of the non-metallic coating body 8 of up to 10 mm can be achieved. 10 is a plan view of a possible arrangement of the holding elements 16 on the surface of the metallic Basic body shown.
  • a corresponding surface roughness is created by the holding elements 16 achieved the surface of the metallic base body, whereby with that in the liquid Condition or non-metallic applied by plasma or flame spraying Material of the coating body 8 achieved a positive connection becomes.
  • the undercuts 18 described above cling to one another the non-metallic material of the coating body with the metallic Body.
  • the method described above can also be used in the repair and Reconditioning of blades are used by holes 20 in the metallic base are first filled, then the holding elements 16 are attached and then applied the non-metallic coating 8 becomes.
  • holding elements 16 These also have a neck 21 and a head 22, which, however, is trapezoidal here is formed.
  • the neck 21 also has a smaller diameter on than the trapezoidal head 22.
  • the neck 21 cannot additionally here have only one head 22 at the end of the neck 21, but additional bulges 23, by means of which further undercuts are formed. Thereby can with long necks 21 the claw between non-metallic coating body 8 and the metallic base body can be further improved.
  • Such holding elements 16, as described in FIG. 6, can also be welded on, riveted or produced in the casting process.
  • the further bulges 23 can of course also be arranged in the neck region in the mushroom-shaped configuration of the holding elements 16 according to FIG. 12.
  • metallic or non-metallic materials can also be arranged to absorb the different expansions.
  • a ceramic tile or knitted fabric with solder can be applied as an intermediate layer. This compensates for the different expansions of the materials used for the metallic part of the blade and the non-metallic coating body.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Molds, Cores, And Manufacturing Methods Thereof (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP04102328A 2003-05-27 2004-05-26 Procédé de fabrication d'une pièce chargée par chaleur et piéce Withdrawn EP1481747A3 (fr)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
CH9492003 2003-05-27
CH9492003 2003-05-27
CH9622003 2003-05-28
CH9622003 2003-05-28

Publications (2)

Publication Number Publication Date
EP1481747A2 true EP1481747A2 (fr) 2004-12-01
EP1481747A3 EP1481747A3 (fr) 2007-05-02

Family

ID=33132420

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04102328A Withdrawn EP1481747A3 (fr) 2003-05-27 2004-05-26 Procédé de fabrication d'une pièce chargée par chaleur et piéce

Country Status (1)

Country Link
EP (1) EP1481747A3 (fr)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008141927A1 (fr) * 2007-05-24 2008-11-27 Napier Turbochargers Limited Turbocompresseur à gaz d'échappement comprenant un boîtier à double paroi
EP2100680A1 (fr) * 2008-02-29 2009-09-16 Siemens Aktiengesellschaft Procédé destiné à la fabrication d'un composant
DE102008058142A1 (de) * 2008-11-20 2010-05-27 Mtu Aero Engines Gmbh Verfahren zum Herstellen und/oder Reparieren eines Rotors einer Strömungsmaschine und Rotor hierzu
DE102008058141A1 (de) * 2008-11-20 2010-05-27 Mtu Aero Engines Gmbh Verfahren zum Herstellen einer Schaufel für einen Rotor einer Strömungsmaschine
GB2504833A (en) * 2012-06-11 2014-02-12 Snecma A method of making a turbine blade with a trailing edge less than 1 mm thick
FR3055352A1 (fr) * 2016-08-29 2018-03-02 Safran Aircraft Engines Aube pour turbomachine dotee d'une structure reduisant les risques d'apparition de criques
WO2018196957A1 (fr) * 2017-04-25 2018-11-01 Siemens Aktiengesellschaft Aube de turbine dotée d'une partie céramique et procédé de fabrication ou de réparation d'une aube de turbine de ce type
CN110030044A (zh) * 2017-12-22 2019-07-19 安萨尔多能源英国知识产权有限公司 用于燃气涡轮构件的热保护系统及方法
EP3816398A1 (fr) * 2019-11-04 2021-05-05 Raytheon Technologies Corporation Profil aérodynamique ayant des gaines avec un joint à rigidité continue
US11215054B2 (en) 2019-10-30 2022-01-04 Raytheon Technologies Corporation Airfoil with encapsulating sheath
FR3129431A1 (fr) * 2021-11-19 2023-05-26 Safran Aube de rotor pour une turbomachine d’aeronef

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3821005A1 (de) * 1988-06-22 1989-12-28 Mtu Muenchen Gmbh Metall-keramik-verbundschaufel
US5721057A (en) * 1993-02-04 1998-02-24 Mtu Motoren-Und Turbinen-Union Munchen Gmgh Ceramic, heat insulation layer on metal structural part and process for its manufacture
DE19803589A1 (de) * 1998-01-30 1999-08-12 Voith Hydro Gmbh & Co Kg Verfahren zum Herstellen eines Bauteiles einer Strömungsmaschine
DE19848104A1 (de) * 1998-10-19 2000-04-20 Asea Brown Boveri Turbinenschaufel
JP2001038461A (ja) * 1999-07-27 2001-02-13 Ishikawajima Harima Heavy Ind Co Ltd 鋳造による部品接合方法
DE10057187A1 (de) * 2000-11-17 2002-05-23 Alstom Switzerland Ltd Verfahren für die Herstellung von Verbundaufbauten zwischen metallischen und nichtmetallischen Materialien
US6412541B2 (en) * 2000-05-17 2002-07-02 Alstom Power N.V. Process for producing a thermally loaded casting
EP1247874A1 (fr) * 2001-04-06 2002-10-09 ALSTOM (Switzerland) Ltd Construction composite avec matériaux métalliques et non-métalliques

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3821005A1 (de) * 1988-06-22 1989-12-28 Mtu Muenchen Gmbh Metall-keramik-verbundschaufel
US5721057A (en) * 1993-02-04 1998-02-24 Mtu Motoren-Und Turbinen-Union Munchen Gmgh Ceramic, heat insulation layer on metal structural part and process for its manufacture
DE19803589A1 (de) * 1998-01-30 1999-08-12 Voith Hydro Gmbh & Co Kg Verfahren zum Herstellen eines Bauteiles einer Strömungsmaschine
DE19848104A1 (de) * 1998-10-19 2000-04-20 Asea Brown Boveri Turbinenschaufel
JP2001038461A (ja) * 1999-07-27 2001-02-13 Ishikawajima Harima Heavy Ind Co Ltd 鋳造による部品接合方法
US6412541B2 (en) * 2000-05-17 2002-07-02 Alstom Power N.V. Process for producing a thermally loaded casting
DE10057187A1 (de) * 2000-11-17 2002-05-23 Alstom Switzerland Ltd Verfahren für die Herstellung von Verbundaufbauten zwischen metallischen und nichtmetallischen Materialien
EP1247874A1 (fr) * 2001-04-06 2002-10-09 ALSTOM (Switzerland) Ltd Construction composite avec matériaux métalliques et non-métalliques

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008141927A1 (fr) * 2007-05-24 2008-11-27 Napier Turbochargers Limited Turbocompresseur à gaz d'échappement comprenant un boîtier à double paroi
EP2100680A1 (fr) * 2008-02-29 2009-09-16 Siemens Aktiengesellschaft Procédé destiné à la fabrication d'un composant
DE102008058142A1 (de) * 2008-11-20 2010-05-27 Mtu Aero Engines Gmbh Verfahren zum Herstellen und/oder Reparieren eines Rotors einer Strömungsmaschine und Rotor hierzu
DE102008058141A1 (de) * 2008-11-20 2010-05-27 Mtu Aero Engines Gmbh Verfahren zum Herstellen einer Schaufel für einen Rotor einer Strömungsmaschine
GB2504833A (en) * 2012-06-11 2014-02-12 Snecma A method of making a turbine blade with a trailing edge less than 1 mm thick
GB2504833B (en) * 2012-06-11 2016-03-30 Snecma A casting method for obtaining a part including a slender portion
US9962763B2 (en) 2012-06-11 2018-05-08 Snecma Casting method for obtaining a part including a tapering portion
GB2555211B (en) * 2016-08-29 2021-10-20 Safran Aircraft Engines Turbomachine vane provided with a structure reducing the risk of cracks
FR3055352A1 (fr) * 2016-08-29 2018-03-02 Safran Aircraft Engines Aube pour turbomachine dotee d'une structure reduisant les risques d'apparition de criques
WO2018196957A1 (fr) * 2017-04-25 2018-11-01 Siemens Aktiengesellschaft Aube de turbine dotée d'une partie céramique et procédé de fabrication ou de réparation d'une aube de turbine de ce type
CN110030044A (zh) * 2017-12-22 2019-07-19 安萨尔多能源英国知识产权有限公司 用于燃气涡轮构件的热保护系统及方法
CN110030044B (zh) * 2017-12-22 2023-11-28 安萨尔多能源英国知识产权有限公司 用于燃气涡轮构件的热保护系统及方法
US11215054B2 (en) 2019-10-30 2022-01-04 Raytheon Technologies Corporation Airfoil with encapsulating sheath
EP3816399B1 (fr) * 2019-10-30 2024-09-18 RTX Corporation Pale comportant une gaine d'encapsulation
EP3816398A1 (fr) * 2019-11-04 2021-05-05 Raytheon Technologies Corporation Profil aérodynamique ayant des gaines avec un joint à rigidité continue
US11466576B2 (en) 2019-11-04 2022-10-11 Raytheon Technologies Corporation Airfoil with continuous stiffness joint
FR3129431A1 (fr) * 2021-11-19 2023-05-26 Safran Aube de rotor pour une turbomachine d’aeronef

Also Published As

Publication number Publication date
EP1481747A3 (fr) 2007-05-02

Similar Documents

Publication Publication Date Title
EP3191244B1 (fr) Procédé de production d'une aube mobile et aube obtenue
EP1645347B1 (fr) Procédé de fabrication d'une pièce moulée à charge thermique élevée
RU2240203C2 (ru) Литейный стержень для литья по выплавляемым моделям (варианты), сборка литейный стержень - оболочковая форма, литейная форма и отливка, полученные с использованием этого стержня
EP2663414B1 (fr) Procédé de fabrication générative d'un élément à système d'amortissement intégré pour turbomachine et élément à système d'amortissement intégré pour turbomachine fabriqué de façon générative
DE60107046T2 (de) Reparaturmethode für turbinenschaufeln und turbinenschaufel
DE3019920C2 (de) Einrichtung zur äußeren Ummantelung der Laufschaufeln von Axialturbinen für Gasturbinentriebwerke
WO2005049312A1 (fr) Systeme stratifie haute temperature de dissipation thermique et procede de production de ce systeme
DE102014111837A1 (de) Gasturbinenbauteile mit porösen Kühlungsmerkmalen
DE102011057071A1 (de) Schaufelblattkomponente einer Turbomaschine und Kühlverfahren für diese
EP2853688A2 (fr) Aube pour une turbine à gaz
DE102011056905A1 (de) Kühlkanalsysteme für mit Beschichtungen überzogene Hochtemperaturkomponenten und zugehörige Verfahren
EP1819905A1 (fr) Système de couches, utilisation et procédé pour la fabrication d'un système multicouche
EP1707301B1 (fr) Procédé pour appliquer des mats de fibres sur la surface ou dans une cavité d'un composant
WO2007134883A1 (fr) Procédé pour la réparation d'un composant et composant
EP2101938B1 (fr) Procédé de fabrication d'un modèle pour la reproduction par la technique de la coulée fine d'un composant qui présente au moins un espace creux
EP1481747A2 (fr) Procédé de fabrication d'une pièce chargée par chaleur et piéce
EP2196276A1 (fr) Corps de moulage destiné au soudage, agencement de corps de moulage, un procédé ainsi qu'un composant
EP1835045A1 (fr) Procédé d'obtention d'une pièce revêtue
WO2011058043A1 (fr) Composant de turbine modulaire et procédé pour sa fabrication
EP1942250A1 (fr) Composant doté d'évidements s'étendant obliquement sur la surface et procédé de fonctionnement d'une turbine
WO2006056524A1 (fr) Procede pour fabriquer un modele perdu et noyau place a l'interieur
EP2002085A1 (fr) Segment d'aubes fixes d'une turbomachine thermique, procédé de fabrication associé et turbomachine thermique
WO2006040220A1 (fr) Procede de production d'un systeme stratifie
EP1674174B1 (fr) Procédé de fabrication d'un moule de fonderie
US8846206B2 (en) Injection molded component

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

Kind code of ref document: A2

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

AX Request for extension of the european patent

Extension state: AL HR LT LV MK

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

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

AX Request for extension of the european patent

Extension state: AL HR LT LV MK

17P Request for examination filed

Effective date: 20071016

AKX Designation fees paid

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

17Q First examination report despatched

Effective date: 20091016

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

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20100227