EP1529580B1 - Moule de fonderie - Google Patents

Moule de fonderie Download PDF

Info

Publication number
EP1529580B1
EP1529580B1 EP03024967A EP03024967A EP1529580B1 EP 1529580 B1 EP1529580 B1 EP 1529580B1 EP 03024967 A EP03024967 A EP 03024967A EP 03024967 A EP03024967 A EP 03024967A EP 1529580 B1 EP1529580 B1 EP 1529580B1
Authority
EP
European Patent Office
Prior art keywords
wall
projection
casting mould
turbine
component
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP03024967A
Other languages
German (de)
English (en)
Other versions
EP1529580A1 (fr
Inventor
Thomas Beck
Georg Dr. Bostanjoglo
Uwe Dr. Paul
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.)
Siemens AG
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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 Siemens AG, Siemens Corp filed Critical Siemens AG
Priority to DE50311059T priority Critical patent/DE50311059D1/de
Priority to EP03024967A priority patent/EP1529580B1/fr
Priority to US10/977,736 priority patent/US7237595B2/en
Publication of EP1529580A1 publication Critical patent/EP1529580A1/fr
Application granted granted Critical
Publication of EP1529580B1 publication Critical patent/EP1529580B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/22—Moulds for peculiarly-shaped castings
    • B22C9/24—Moulds for peculiarly-shaped castings for hollow articles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • 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
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/10—Cores; Manufacture or installation of cores

Definitions

  • the invention relates to a casting mold according to claim 1.
  • Formed as a hollow body components with complex shaped geometries and complex through-holes in the region of an outer wall of the component can be prepared in various ways.
  • a casting mold is produced with a wax model of the component in a first step, which is at least partially the negative of the component to be produced by the wax model is coated with ceramic.
  • the EP 0 559 251 B1 shows a method of manufacturing a component with through-holes, wherein placeholders are separately introduced in the mold.
  • the object is achieved by a mold according to claim 1, which is used for the production of the casting.
  • a mold which has corresponding projections, which at least partially represent the negative of a hole.
  • FIG. 1 shows a component 1, for example, at least partially has a cavity 31 and can be produced with the mold according to the invention. Therefore, the component 1 has walls 4, in particular an outer wall 4. In the wall 4, at least one hole 13, here a through hole 13 is formed.
  • the component 1 may be metallic or ceramic, for example.
  • it is a turbine component 1 of a gas turbine 100 (FIG. Fig. 7 ) or steam turbine 300, 303 (FIG. Fig. 9 ). This is, for example, a turbine blade 120, 130, 354, 357 (FIG. Fig. 7 . 9 ) or a combustor liner 155 (FIG. Fig.
  • through holes 13 are used, for example, to cool the component 1 by film cooling.
  • the through hole 13 consists for example of a round or oval-shaped hole part 7, which widens from the cavity 31 to the outer surface 11 of the wall 4 to a diffuser 10.
  • Such components 1 with complex geometries of a through hole 13, 7 + 10, can be made easier and faster with the inventive method.
  • the wall is eg. 2 to 6mm, in particular 3 to 4mm thick.
  • the hole part 7 has a diameter of 0.3 to 1.2 mm, in particular 0.6 to 0.8 mm.
  • the diffuser 10 is formed on the surface, for example, trapezoidal and has dimensions of 1.5 to 5mm x 1.5 to 5mm and goes into the wall 4 to a depth of 1 to 1.5mm.
  • FIG. 2 schematically shows a part of a mold 16 according to the prior art, which consists of an inner wall 25, in particular of a mold core 25 (for example, the cavity 31 of the component 1), and an outer wall 28 consists.
  • material 22 for example, metal
  • the core 25 forms, for example, a part of the cavity 31 of the component 1.
  • At least one projection 19 is formed as in FIGS. 3, 4 and 5 you can see.
  • the protrusion 19 extends at least partially from an inner surface 20 of the inner wall 25 to an inner surface 21 of the outer wall 28.
  • the projection 19 extends continuously from the inner surface 20 to the inner surface 21.
  • the projection 19 has been formed by pouring ceramics of a through hole 13 in the wax pattern of the component 1 or by inserting correspondingly shaped pins, such as ceramic pins, into the walls 25, 28 of the mold 16. Also, in the wax model of the component, the through holes 13 can be formed by means of sliders or pins formed in accordance with the part 7 or 10 of the hole.
  • the projection 19 in the gap 26 prevents filling with material 22 during casting, so that after removal of the mold 16 with its inner wall 25 and its outer wall 28 and the projection 19 at least partially results in a through hole 13.
  • the projection 19 is constructed, for example, as follows.
  • a first projection area 34 represents the round or oval ( Fig. 6 ) Hole part 7 of the through hole 13.
  • a second projection region 37 represents the diffuser 10.
  • the projection 19 can also be round or oval over its entire cross section and, for example, also be constant in its cross-sectional area.
  • FIG. 3 shows an embodiment of a mold 16 according to the invention.
  • the projection 19 does not extend continuously from an inner surface 20 of the inner wall 25 to an inner surface 21 of the outer wall 28.
  • the projection 19 is formed only on the inner surface 20 of the inner wall 25 and extends to a certain distance d to the inner surface 21 of the outer wall 28th When filling the cavity 26 with material 22 so no complete passage opening 13 is formed.
  • material 22 is present after the casting of the component 1.
  • the area is correspondingly thin, in particular membrane-like, so that it can be easily removed in a very short time. It can also be said that the passage opening 13 of the component 1 to be produced is still somewhat closed.
  • the projection 19 can also have a support connection 40 (indicated by dashed lines) in order to support the projection 19, which projects freely into the intermediate space 26, against the outer wall 28.
  • the support connection 40 is smaller in cross section than the cross section of the projection 19, which is opposite to the outer wall 28.
  • the support connection 40 thus represents only a part of the through hole 13 to be produced.
  • the projection 19 again has two regions 34, 37 'in this example.
  • the complex geometry of the diffuser is laborious nachzubeused. This is omitted here for the most part, since only a relatively small upper portion of the diffuser 10 is to be reworked by removing material. Since, in particular, the areas lying deeper in the wall 4 mean considerable expenditure, for example in laser guidance, this casting mold has considerable advantages.
  • FIG. 4 shows a further embodiment of an inventively designed mold 16th
  • the projection 19 is formed only on the inner surface 21 of the outer wall 28.
  • the projection 19 represents the negative 37 of the diffuser 10 of the through-opening 13 to be produced.
  • the diffuser 10 has a more complex geometry than a simple symmetrical hole and would therefore be very complicated to produce in case of subsequent incorporation.
  • a simple hole 7 ( Fig. 1 ) are incorporated from the diffuser region 10 in the component 1 in the wall 4. This can be done by laser processing or radio wire erosion as well as other methods.
  • a corresponding support connection 40 between the projection 19, 37 and the inner wall 25 may be present.
  • FIG. 5 shows a further embodiment of an inventively designed mold 16th
  • a second projection 19 ' is formed on the inner surface 20 of the inner wall 25.
  • the projection 19 ', 34' forms a further part of this passage opening 13, namely the area of the hole part 7.
  • the projection 19, 37 represents the region of the diffuser 10 of the component 1 to be produced.
  • FIG. 6 shows the top view of an outer wall 28 of a mold 16 designed according to the invention.
  • the reference numeral 34 indicates the area from which the hole 7 will be formed.
  • the reference numeral 37 designates the region of the projection 19, which represents the diffuser region 10 of the through-hole 13 to be produced.
  • FIG. 7 shows by way of example a gas turbine 100 in a longitudinal partial section.
  • the gas turbine 100 has inside a rotatably mounted about a rotation axis 102 rotor 103, which is also referred to as a turbine runner.
  • a compressor 105 for example a toroidal combustion chamber 110, in particular annular combustion chamber 106, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109.
  • the annular combustion chamber 106 communicates with an annular annular hot gas channel 111, for example.
  • There, for example, four successive turbine stages 112 form the turbine 108.
  • Each turbine stage 112 is formed from two blade rings.
  • a series 125 formed of rotor blades 120 follows.
  • the vanes 130 are attached to the stator 143, whereas the blades 120 of a row 125 are mounted on the rotor 103 by means of a turbine disk 133. Coupled to the rotor 103 is a generator or work machine (not shown).
  • air 105 is sucked in and compressed by the compressor 105 through the intake housing 104.
  • the compressed air provided at the turbine-side end of the compressor 105 is supplied to the burners 107 where it is mixed with a fuel.
  • the mixture is then burned to form the working fluid 113 in the combustion chamber 110.
  • the working medium 113 flows along the hot gas channel 111 past the guide vanes 130 and the rotor blades 120.
  • the working medium 113 expands in a pulse-transmitting manner so that the rotor blades 120 drive the rotor 103 and drive the machine coupled to it.
  • the components exposed to the hot working medium 113 are subject to thermal loads during operation of the gas turbine 100.
  • the guide vanes 130 and rotor blades 120 of the first turbine stage 112, viewed in the direction of flow of the working medium 113, are subjected to the greatest thermal stress in addition to the heat shield bricks lining the annular combustion chamber 106. In order to withstand the temperatures prevailing there, they are cooled by means of a coolant.
  • the turbine blade 120, 130 is still air-cooled and has film cooling holes 13 which are connected to the mold 16 (FIG. Fig. 2 ) in the cast and / or directionally solidified turbine blade 120, 130.
  • the vane 130 has a guide vane foot (not shown here) facing the inner housing 138 of the turbine 108 and a vane head opposite the vane foot.
  • the vane head faces the rotor 103 and fixed to a mounting ring 140 of the stator 143.
  • the FIG. 8 shows by way of example a combustion chamber 110 of a gas turbine.
  • the combustion chamber 110 is configured, for example, as a so-called annular combustion chamber, in which a plurality of burners 102 arranged around the turbine shaft 103 in the circumferential direction open into a common combustion chamber space.
  • the combustion chamber 110 is configured in its entirety as an annular structure, which is positioned around the turbine shaft 103 around.
  • the combustion chamber 110 is designed for a comparatively high temperature of the working medium M of about 1000 ° C to 1600 ° C.
  • the combustion chamber wall 153 is provided on its side facing the working medium M side with an inner lining formed from heat shield elements 155.
  • Each heat shield element 155 is equipped on the working medium side with a particularly heat-resistant protective layer or made of high-temperature-resistant material. Due to the high temperatures in the interior of the combustion chamber 110, a cooling system is additionally provided for the heat shield elements 155 or for their holding elements. Often the heat shield elements 155 have film cooling holes 13 or fuel passageways in the combustion chamber 110 which are created in the heat shield element 155 with the mold 16 of the invention.
  • the combustion chamber 110 is designed in particular for detecting losses of the heat shield elements 155.
  • a number of temperature sensors 158 are positioned between the combustion chamber wall 153 and the heat shield elements 155.
  • a steam turbine 300, 303 with a turbine shaft 309 extending along a rotation axis 306 is shown.
  • the steam turbine has a high-pressure turbine section 300 and a medium-pressure turbine section 303, each having an inner housing 312 and an outer housing 315 enclosing this.
  • the high-pressure turbine part 300 is designed, for example, in Topfbauart.
  • the medium-pressure turbine section 303 is double-flow. It is also possible for the medium-pressure turbine section 303 to be single-flow.
  • a bearing 318 is arranged between the high-pressure turbine section 300 and the medium-pressure turbine section 303, wherein the turbine shaft 309 has a bearing area 321 in the bearing 318.
  • the turbine shaft 309 is supported on another bearing 324 adjacent to the high pressure turbine sub 300.
  • the high-pressure turbine section 300 has a shaft seal 345.
  • the turbine shaft 309 is sealed from the outer housing 315 of the medium-pressure turbine section 303 by two further shaft seals 345.
  • the turbine shaft 309 in the high-pressure turbine section 300 has the high-pressure impeller blade 354, 357.
  • the middle-pressure blast turbine 303 has a central steam inflow region 333.
  • the turbine shaft 309 Associated with the steam inflow region 333, the turbine shaft 309 has a radially symmetrical shaft shield 363, a cover plate, on the one hand for dividing the steam flow into the two flows of the medium-pressure turbine section 303 and for preventing direct contact of the hot steam with the turbine shaft 309.
  • the turbine shaft 309 has in the medium-pressure turbine section 303 a second blading area 366 with the medium-pressure blades 354, 342.
  • the hot steam flowing through the second blading area 366 flows out of the medium-pressure turbine section 303 from a discharge connection 369 to a downstream low-pressure turbine, not shown.
  • the turbine shaft 309 is composed of two sub-turbine shafts 309a and 309b, which are fixedly connected to one another in the region of the bearing 318.
  • Each turbine shaft 309a, 309b has a cooling line 372 formed as a central bore 372a along the axis of rotation 306.
  • the cooling line 372 is connected to the steam outlet region 351 via an inflow line 375 having a radial bore 375a.
  • the coolant line 372 with a cavity not shown below the shaft shield 363 connected.
  • the inflow lines 375 are designed as radial bores 375a, whereby "cold" steam from the high-pressure turbine part 300 can flow into the central bore 372a.
  • the vapor passes through the storage area 321 into the medium-pressure turbine section 303 and there to the mantle surface 330 of the turbine shaft 309 in the steam inflow area 333.
  • the steam flowing through the cooling line has a significantly lower temperature as the reheated steam flowing into the Dampfeinström Siemens 333, so that an effective cooling of the first blade rows 342 of the medium-pressure turbine section 303 and the mantle surface 330 is ensured in the region of these blade rows 342.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (10)

  1. Moule ( 16 ) de fonderie pour la fabrication d'un élément ( 1 ),
    le moule ( 16 ) de fonderie ayant à l'intérieur ( 26 ) une paroi ( 25 ) intérieure et une paroi ( 28 ) extérieure,
    dans lequel le moule ( 16 ) de fonderie a à l'intérieur ( 26 ) au moins une saillie ( 19, 19' ),
    dans lequel la saillie ( 19 ) ne s'étend qu'en partie entre la paroi ( 25 ) intérieure et la paroi ( 28 ) extérieure de sorte que la saillie ( 19, 19' ) donne dans une paroi ( 4, 28 ) extérieure au plus une partie du trou ( 13 ) extérieur à fabriquer de l'élément ( 1 ).
  2. Moule de fonderie suivant la revendication 1,
    caractérisé en ce que la saillie ( 19 ) n'est formée que sur la paroi ( 25 ) intérieure.
  3. Moule de fonderie suivant la revendication 1,
    caractérisé en ce que la saillie ( 19 ) n'est formée que sur la paroi ( 28 ) extérieure.
  4. Moule de fonderie selon la revendication 1,
    caractérisé en ce qu'une saillie ( 19' ) est formée sur la paroi ( 25 ) intérieure et en ce que une autre saillie ( 19 ) est formée de manière opposée sur la paroi ( 28 ) extérieure, les saillies ( 19, 19' ) étant à une certaine distance l'une de l'autre.
  5. Moule de fonderie suivant la revendication 2,
    caractérisé en ce que la saillie ( 19 ) est reliée à la paroi ( 28 ) opposée par une liaison ( 40 ) d'appui, la liaison ( 40 ) d'appui ne constituant qu'une partie de la section transversale de l'ouverture ( 7, 13, 10 ) traversante à fabriquer.
  6. Utilisation d'un moule de fonderie suivant la revendication 1, 2, 3 ou 4, qui sert à la fabrication d'un élément ( 1 ) qui a un trou ( 13 ) traversant ayant une géométrie complexe s'écartant d'une forme circulaire ou d'une forme ovale.
  7. Utilisation d'un moule de fonderie suivant la revendication 5,
    caractérisée en ce que le trou ( 13 ) traversant constitue un trou de refroidissement par pellicule,
    qui a un diffuseur ( 10 ),
    qui est formé par une saillie ( 19, 37 ) correspondante sur une paroi ( 28 ) extérieure du moule ( 16 ) de fonderie.
  8. Utilisation d'un moule de fonderie suivant la revendication 6,
    caractérisée en ce que le moule ( 16 ) de fonderie est utilisé pour la fabrication d'un élément ( 120, 130, 155, 354, 357 ) d'une turbine ( 100 ) à gaz ou d'une turbine ( 300, 303 ) à vapeur.
  9. Utilisation d'un moule de fonderie suivant la revendication 8,
    caractérisée en ce que l'élément ( 1 ) de turbine est une aube ( 120, 130, 354, 357 ) de turbine.
  10. Utilisation d'un moule de fonderie suivant la revendication 8,
    caractérisée en ce que l'élément ( 1 ) de turbine est un revêtement ( 155 ) de chambre de combustion.
EP03024967A 2003-10-29 2003-10-29 Moule de fonderie Expired - Lifetime EP1529580B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
DE50311059T DE50311059D1 (de) 2003-10-29 2003-10-29 Gussform
EP03024967A EP1529580B1 (fr) 2003-10-29 2003-10-29 Moule de fonderie
US10/977,736 US7237595B2 (en) 2003-10-29 2004-10-28 Casting mold

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP03024967A EP1529580B1 (fr) 2003-10-29 2003-10-29 Moule de fonderie

Publications (2)

Publication Number Publication Date
EP1529580A1 EP1529580A1 (fr) 2005-05-11
EP1529580B1 true EP1529580B1 (fr) 2009-01-07

Family

ID=34429245

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03024967A Expired - Lifetime EP1529580B1 (fr) 2003-10-29 2003-10-29 Moule de fonderie

Country Status (3)

Country Link
US (1) US7237595B2 (fr)
EP (1) EP1529580B1 (fr)
DE (1) DE50311059D1 (fr)

Families Citing this family (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7325587B2 (en) * 2005-08-30 2008-02-05 United Technologies Corporation Method for casting cooling holes
US20080005903A1 (en) * 2006-07-05 2008-01-10 United Technologies Corporation External datum system and film hole positioning using core locating holes
US20090000754A1 (en) * 2007-06-27 2009-01-01 United Technologies Corporation Investment casting cores and methods
CH700320A1 (de) * 2009-01-30 2010-07-30 Alstom Technology Ltd Verfahren zum herstellen eines bauteils einer gasturbine.
US20110088379A1 (en) * 2009-10-15 2011-04-21 General Electric Company Exhaust gas diffuser
DE102010025678A1 (de) * 2010-06-30 2012-01-05 Voith Patent Gmbh Stator und Verfahren zum Herstellen eines Stators
US9249687B2 (en) 2010-10-27 2016-02-02 General Electric Company Turbine exhaust diffusion system and method
US20130280093A1 (en) 2012-04-24 2013-10-24 Mark F. Zelesky Gas turbine engine core providing exterior airfoil portion
US9957813B2 (en) * 2013-02-19 2018-05-01 United Technologies Corporation Gas turbine engine airfoil platform cooling passage and core
EP3157694B1 (fr) * 2014-06-18 2020-07-29 Mikro Systems Inc. Moulage à la cire perdue d'aube de turbine à l'aide de saillies de formation de trous en forme de film pour le réglage intégré de l'épaisseur de paroi
US10137499B2 (en) 2015-12-17 2018-11-27 General Electric Company Method and assembly for forming components having an internal passage defined therein
US10099276B2 (en) 2015-12-17 2018-10-16 General Electric Company Method and assembly for forming components having an internal passage defined therein
US10099283B2 (en) 2015-12-17 2018-10-16 General Electric Company Method and assembly for forming components having an internal passage defined therein
US9968991B2 (en) 2015-12-17 2018-05-15 General Electric Company Method and assembly for forming components having internal passages using a lattice structure
US10046389B2 (en) 2015-12-17 2018-08-14 General Electric Company Method and assembly for forming components having internal passages using a jacketed core
US10150158B2 (en) 2015-12-17 2018-12-11 General Electric Company Method and assembly for forming components having internal passages using a jacketed core
US9987677B2 (en) 2015-12-17 2018-06-05 General Electric Company Method and assembly for forming components having internal passages using a jacketed core
US10118217B2 (en) 2015-12-17 2018-11-06 General Electric Company Method and assembly for forming components having internal passages using a jacketed core
US9579714B1 (en) 2015-12-17 2017-02-28 General Electric Company Method and assembly for forming components having internal passages using a lattice structure
US10099284B2 (en) 2015-12-17 2018-10-16 General Electric Company Method and assembly for forming components having a catalyzed internal passage defined therein
CN109070193B (zh) * 2016-03-24 2020-10-09 西门子股份公司 制造具有用于熔模铸造的突出镶铸冷却结构的混合芯部的方法
US10335853B2 (en) 2016-04-27 2019-07-02 General Electric Company Method and assembly for forming components using a jacketed core
US10286450B2 (en) 2016-04-27 2019-05-14 General Electric Company Method and assembly for forming components using a jacketed core
US10830052B2 (en) 2016-09-15 2020-11-10 Honeywell International Inc. Gas turbine component with cooling aperture having shaped inlet and method of forming the same
US10315248B2 (en) 2016-11-17 2019-06-11 General Electric Company Methods and apparatuses using cast in core reference features
US10927705B2 (en) 2018-08-17 2021-02-23 Raytheon Technologies Corporation Method for forming cooling holes having separate complex and simple geometry sections
US11998974B2 (en) * 2022-08-30 2024-06-04 General Electric Company Casting core for a cast engine component
CN121607574B (zh) * 2026-01-29 2026-04-14 上海万泽精密铸造有限公司 引入电子束打孔的空腔燃机花边螺钉精密铸造加工工艺

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3646185A (en) * 1967-03-13 1972-02-29 Irving C Jennings Method of casting a diffuser element
FR2731639A1 (fr) * 1976-12-07 1996-09-20 Rolls Royce Plc
US4565490A (en) * 1981-06-17 1986-01-21 Rice Ivan G Integrated gas/steam nozzle
US4669957A (en) * 1985-12-23 1987-06-02 United Technologies Corporation Film coolant passage with swirl diffuser
US5295530A (en) * 1992-02-18 1994-03-22 General Motors Corporation Single-cast, high-temperature, thin wall structures and methods of making the same
US5296308A (en) * 1992-08-10 1994-03-22 Howmet Corporation Investment casting using core with integral wall thickness control means
US5465780A (en) * 1993-11-23 1995-11-14 Alliedsignal Inc. Laser machining of ceramic cores
US5623985A (en) * 1996-03-13 1997-04-29 Pcc Airfoils, Inc. Apparatus and method for molding an article
US5609779A (en) * 1996-05-15 1997-03-11 General Electric Company Laser drilling of non-circular apertures
US5950705A (en) * 1996-12-03 1999-09-14 General Electric Company Method for casting and controlling wall thickness
DE19821770C1 (de) * 1998-05-14 1999-04-15 Siemens Ag Verfahren und Vorrichtung zur Herstellung eines metallischen Hohlkörpers
US6340047B1 (en) * 1999-03-22 2002-01-22 General Electric Company Core tied cast airfoil
DE19939179B4 (de) * 1999-08-20 2007-08-02 Alstom Kühlbare Schaufel für eine Gasturbine
DE10053356A1 (de) * 2000-10-27 2002-05-08 Alstom Switzerland Ltd Gekühltes Bauteil, Gusskern für die Herstellung eines solchen Bauteils, sowie Verfahren zum Herstellen eines solchen Bauteils
GB2373319B (en) * 2001-03-12 2005-03-30 Rolls Royce Plc Combustion apparatus
US6932571B2 (en) * 2003-02-05 2005-08-23 United Technologies Corporation Microcircuit cooling for a turbine blade tip

Also Published As

Publication number Publication date
US7237595B2 (en) 2007-07-03
US20060032604A1 (en) 2006-02-16
DE50311059D1 (de) 2009-02-26
EP1529580A1 (fr) 2005-05-11

Similar Documents

Publication Publication Date Title
EP1529580B1 (fr) Moule de fonderie
DE60132521T2 (de) Turbinenleitschaufeln mit lötmittelfreien Übergangskragen
DE60129779T2 (de) Anbringung von Kühlkanälen in Turbinenteilen
EP1682342B1 (fr) Systeme stratifie pour dissipation de chaleur a haute temperature et methode de fabrication
DE60024517T2 (de) Turbinenwand mit Rillen an der Innenseite
DE102009044102A1 (de) Geteilte Verkleidung für eine Gasturbine
CA2742004C (fr) Dispositif de suspension de carenage comportant un passage de refroidissement par diffusion
EP1669545A1 (fr) Système de couches, utilisation et procédé pour la fabrication d'un système multicouche
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
EP1813378A2 (fr) Procédé de fabrication d'un trou
DE102013111223A1 (de) Kühlfilmlochplateau für Heißgaspfadkomponente
EP2733310A1 (fr) Surface modifiée autour d'un trou
EP1522373B1 (fr) Procédé de fabrication d'un trou
US10259039B2 (en) Gas turbine engine component cooling passage and space casting core
EP2213759A1 (fr) Procédé de revêtement d'un composant à trous de refroidissement par film et composant
EP1510654A1 (fr) Matrice unitaire d'aubes de turbine et procédé de fabrication d' une matrice unitaire d'aubes de turbine
EP1835045A1 (fr) Procédé d'obtention d'une pièce revêtue
EP1920858B1 (fr) Procédé de fabrication d'un moule
DE112020001189T5 (de) Turbinenlaufschaufel und Kontaktoberflächenherstellungsverfahren
EP1661640A1 (fr) Fabrication d'un modèle perdu et noyaux incorporé dans le modèle
WO2006079441A1 (fr) Composant presentant un meplat dans un alesage
EP1658913A1 (fr) Procédé et pièce de coulée
EP2419229A1 (fr) Procédé de fabrication d'un moule négatif pour la coulée d'une aube de turbine et moule pour la fabrication d'un modèle à la cire d'aube de turbine
EP1927416A1 (fr) Procédé de fabrication d'une pièce coulée avec marquage, pièce coulée et groupe de pièces coulées

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: 20040601

AK Designated contracting states

Kind code of ref document: A1

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

AX Request for extension of the european patent

Extension state: AL LT LV MK

AKX Designation fees paid

Designated state(s): CH DE GB IT LI

17Q First examination report despatched

Effective date: 20070928

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): CH DE GB IT LI

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

REF Corresponds to:

Ref document number: 50311059

Country of ref document: DE

Date of ref document: 20090226

Kind code of ref document: P

REG Reference to a national code

Ref country code: CH

Ref legal event code: NV

Representative=s name: SIEMENS SCHWEIZ AG

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: 20091008

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

Ref country code: GB

Payment date: 20101018

Year of fee payment: 8

Ref country code: IT

Payment date: 20101027

Year of fee payment: 8

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

Ref country code: CH

Payment date: 20110106

Year of fee payment: 8

Ref country code: DE

Payment date: 20101220

Year of fee payment: 8

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

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: 20111031

Ref country code: DE

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

Effective date: 20120501

Ref country code: CH

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

Effective date: 20111031

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 50311059

Country of ref document: DE

Effective date: 20120501

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

Effective date: 20121029

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

Ref country code: GB

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

Effective date: 20121029

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 NON-PAYMENT OF DUE FEES

Effective date: 20121029