EP1529580A1 - Moule de fonderie - Google Patents

Moule de fonderie Download PDF

Info

Publication number
EP1529580A1
EP1529580A1 EP03024967A EP03024967A EP1529580A1 EP 1529580 A1 EP1529580 A1 EP 1529580A1 EP 03024967 A EP03024967 A EP 03024967A EP 03024967 A EP03024967 A EP 03024967A EP 1529580 A1 EP1529580 A1 EP 1529580A1
Authority
EP
European Patent Office
Prior art keywords
wall
projection
turbine
mold
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.)
Granted
Application number
EP03024967A
Other languages
German (de)
English (en)
Other versions
EP1529580B1 (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

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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.
  • a casting mold is produced from a wax model of the component, which at least in part represents the negative of the component to be produced, in that the wax model is coated with ceramic.
  • the object is achieved by a mold according to claim 1, which is used for the production of the casting.
  • FIG. 1 shows a component 1 which, for example, at least partially has a cavity 31 and can be produced with the casting mold according to the invention. Therefore, the component 1 has a wall 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. 7) or steam turbine 300, 303 (FIG. 9). This is, for example, a turbine blade 120, 130, 354, 357 (FIG. 7) or a combustor liner 155 (FIG. 8) made of, for example, an iron-, nickel- or cobalt-based superalloy.
  • 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 casting mold 16 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.
  • 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.
  • 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 is made by pouring a ceramic Through hole 13 in the wax model of the component 1 or by inserting correspondingly shaped pins, For example, ceramic pins, in the walls 25, 28 of the Mold 16 has been made. Likewise, in the wax model of the component by means of sliders or pins corresponding to which are shaped part 7 or 10 of the hole that Through holes 13 are generated.
  • the projection 19 in the gap 26 prevents the Pour a padding with material 22, so that after Removing the mold 16 with its inner wall 25 and its outer wall 28 and the projection 19 at least partially a through hole 13 results.
  • 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 a further embodiment of a casting 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.
  • the passage opening 13 of the component 1 to be produced is still somewhat closed. This is useful, for example, if subsequently at least one coating is applied to the outer surface 11 of the component 1. Since the passage opening 13 is still closed, the passage opening 13 is also not contaminated or narrowed by the material of the coating. Only with a final processing step, the material of the thin compared to the thickness of the wall 4 coating and the little material 22, which still closes the passage opening 13, quickly and easily removed.
  • 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 exemplary embodiment of a casting mold 16 designed according to the invention.
  • 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.
  • FIG. 5 shows a further exemplary embodiment of a casting mold 16 designed according to the invention.
  • a second projection 19 ' is also 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 plan view of an outer wall 28 of a casting 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 series 125 by a turbine disk 133 are mounted on the rotor 103.
  • On the rotor 103 is coupled to a generator or a Work machine (not shown).
  • the gas turbine 100 During operation of the gas turbine 100 is from the compressor 105 sucked through the intake housing 104 air 135 and compacted. The at the turbine end of the compressor 105th provided compressed air is the burners 107th guided and mixed there with a fuel. The mixture is then to form the working medium 113 in the Combustion chamber 110 burned. From there it flows Working fluid 113 along the hot gas passage 111 past the Vanes 130 and the blades 120. To the Blades 120 relaxes the working fluid 113th momentum transferring, so that the blades 120 the rotor 103 drive and this the coupled to him Working machine.
  • 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 that are produced with the mold 16 of the invention (FIG. 2) in the cast and / or directionally solidified turbine blade 120, 130.
  • the vane 130 has an inner housing 138 of the Turbine 108 facing Leitschaufelfuß (not here shown) and a Leitschaufelfuß opposite Guide vane head on.
  • the vane head is the rotor 103 facing and on a mounting ring 140 of the stator 143rd established.
  • 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 in particular for a detection of Losses of the heat shield elements 155 designed. These are between the combustion chamber wall 153 and the heat shield elements 155, a number of temperature sensors 158 are positioned.
  • FIG. 9 shows by way of example a steam turbine 300, 303 with a turbine shaft 309 extending along a rotation axis 306.
  • 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, the turbine shaft 309 having a bearing region 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 turbine shafts 309a and 309b which are fixed in the area of the bearing 318 connected to each other.
  • Each sub-turbine shaft 309a, 309b has one as a central bore 372a along the axis of rotation 306 trained cooling line 372 on.
  • the cooling line 372 is connected to the steam outlet region 351 via a radial Bore 375a having inflow line 375 connected.
  • the coolant line 372 In the Medium pressure turbine section 303 is 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 section 300 into the central bore 372a can flow.
  • a trained discharge line 372 passes the steam through the storage area 321 into the Medium-pressure turbine part 303 and there to the mantle surface 330 of the turbine shaft 309 in the steam inflow region 333.
  • the steam flowing through the cooling line has a significantly lower Temperature than that in the Dampfeinström Scheme 333rd incoming superheated steam, making an effective Cooling of the first blade rows 342 of the medium-pressure turbine section 303 and the mantle surface 330 in the area this blade rows 342 is ensured.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
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 true EP1529580A1 (fr) 2005-05-11
EP1529580B1 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)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2011586A1 (fr) * 2007-06-27 2009-01-07 United Technologies Corporation Noyaux de moulage par coulée et procédés
EP1760402A3 (fr) * 2005-08-30 2009-11-11 United Technologies Corporation Méthode de moulage de trous de refroidissement
CH700320A1 (de) * 2009-01-30 2010-07-30 Alstom Technology Ltd Verfahren zum herstellen eines bauteils einer gasturbine.
WO2012000636A1 (fr) * 2010-06-30 2012-01-05 Voith Patent Gmbh Stator et procédé de production d'un stator
WO2015195110A1 (fr) * 2014-06-18 2015-12-23 Siemens Energy, 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
EP2841710B1 (fr) 2012-04-24 2018-10-31 United Technologies Corporation C ur de moteur à turbine à gaz créant une partie de profil aérodynamique extérieure
EP1876325B2 (fr) † 2006-07-05 2023-01-25 Raytheon Technologies Corporation Système de référence externe et de positionnement des trous de refroidissement par film utilisant des trous de localisation d'un noyau
CN121607574A (zh) * 2026-01-29 2026-03-06 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

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US20110088379A1 (en) * 2009-10-15 2011-04-21 General Electric Company Exhaust gas diffuser
US9249687B2 (en) 2010-10-27 2016-02-02 General Electric Company Turbine exhaust diffusion system and method
US9957813B2 (en) * 2013-02-19 2018-05-01 United Technologies Corporation Gas turbine engine airfoil platform cooling passage and core
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

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US4565490A (en) * 1981-06-17 1986-01-21 Rice Ivan G Integrated gas/steam nozzle
EP0227579A2 (fr) * 1985-12-23 1987-07-01 United Technologies Corporation Passage de refroidissement avec chambre de tourbillonnement
DE2754231C1 (de) * 1976-12-07 1994-01-20 Rolls Royce Plc Verfahren zur Herstellung hohler Gußkörper, insbesondere Hohlschaufeln für Gasturbinenstrahltriebwerke
EP0585183A1 (fr) * 1992-08-10 1994-03-02 Howmet Corporation Coulée à cire perdue utilisant un noyau avec moyens de contrôle de l'épaisseur de paroi incorporés
US5623985A (en) * 1996-03-13 1997-04-29 Pcc Airfoils, Inc. Apparatus and method for molding an article
EP0559251B1 (fr) * 1992-02-18 1998-12-02 General Motors Corporation Procédé et moule pour la production des structure coulées, à paroi mince avec une résistance à chaud élevée et produit obtenue
DE19821770C1 (de) * 1998-05-14 1999-04-15 Siemens Ag Verfahren und Vorrichtung zur Herstellung eines metallischen Hohlkörpers
US5950705A (en) * 1996-12-03 1999-09-14 General Electric Company Method for casting and controlling wall thickness
US6340047B1 (en) * 1999-03-22 2002-01-22 General Electric Company Core tied cast airfoil
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

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US3646185A (en) * 1967-03-13 1972-02-29 Irving C Jennings Method of casting a diffuser element
US5465780A (en) * 1993-11-23 1995-11-14 Alliedsignal Inc. Laser machining of ceramic cores
US5609779A (en) * 1996-05-15 1997-03-11 General Electric Company Laser drilling of non-circular apertures
DE19939179B4 (de) * 1999-08-20 2007-08-02 Alstom Kühlbare Schaufel für eine Gasturbine
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

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DE2754231C1 (de) * 1976-12-07 1994-01-20 Rolls Royce Plc Verfahren zur Herstellung hohler Gußkörper, insbesondere Hohlschaufeln für Gasturbinenstrahltriebwerke
US4565490A (en) * 1981-06-17 1986-01-21 Rice Ivan G Integrated gas/steam nozzle
EP0227579A2 (fr) * 1985-12-23 1987-07-01 United Technologies Corporation Passage de refroidissement avec chambre de tourbillonnement
EP0559251B1 (fr) * 1992-02-18 1998-12-02 General Motors Corporation Procédé et moule pour la production des structure coulées, à paroi mince avec une résistance à chaud élevée et produit obtenue
EP0585183A1 (fr) * 1992-08-10 1994-03-02 Howmet Corporation Coulée à cire perdue utilisant un noyau avec moyens de contrôle de l'épaisseur de paroi incorporés
US5623985A (en) * 1996-03-13 1997-04-29 Pcc Airfoils, Inc. Apparatus and method for molding an article
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
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

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1760402A3 (fr) * 2005-08-30 2009-11-11 United Technologies Corporation Méthode de moulage de trous de refroidissement
EP1876325B2 (fr) † 2006-07-05 2023-01-25 Raytheon Technologies Corporation Système de référence externe et de positionnement des trous de refroidissement par film utilisant des trous de localisation d'un noyau
EP2011586A1 (fr) * 2007-06-27 2009-01-07 United Technologies Corporation Noyaux de moulage par coulée et procédés
CH700320A1 (de) * 2009-01-30 2010-07-30 Alstom Technology Ltd Verfahren zum herstellen eines bauteils einer gasturbine.
WO2010086402A3 (fr) * 2009-01-30 2010-10-21 Alstom Technology Ltd. Procédé de production d'un élément de turbine à gaz
WO2012000636A1 (fr) * 2010-06-30 2012-01-05 Voith Patent Gmbh Stator et procédé de production d'un stator
EP2841710B1 (fr) 2012-04-24 2018-10-31 United Technologies Corporation C ur de moteur à turbine à gaz créant une partie de profil aérodynamique extérieure
WO2015195110A1 (fr) * 2014-06-18 2015-12-23 Siemens Energy, 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
US10022790B2 (en) 2014-06-18 2018-07-17 Siemens Aktiengesellschaft Turbine airfoil cooling system with leading edge impingement cooling system turbine blade investment casting using film hole protrusions for integral wall thickness control
CN121607574A (zh) * 2026-01-29 2026-03-06 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

Also Published As

Publication number Publication date
US7237595B2 (en) 2007-07-03
EP1529580B1 (fr) 2009-01-07
US20060032604A1 (en) 2006-02-16
DE50311059D1 (de) 2009-02-26

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