EP1857198A1 - Procédés et matériaux pour fixer les noyaux de moulage - Google Patents

Procédés et matériaux pour fixer les noyaux de moulage Download PDF

Info

Publication number
EP1857198A1
EP1857198A1 EP07251140A EP07251140A EP1857198A1 EP 1857198 A1 EP1857198 A1 EP 1857198A1 EP 07251140 A EP07251140 A EP 07251140A EP 07251140 A EP07251140 A EP 07251140A EP 1857198 A1 EP1857198 A1 EP 1857198A1
Authority
EP
European Patent Office
Prior art keywords
casting
core
cores
casting core
bringing
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
EP07251140A
Other languages
German (de)
English (en)
Other versions
EP1857198B1 (fr
Inventor
P. Brennan Reilly
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.)
Raytheon Technologies Corp
Original Assignee
United Technologies 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 United Technologies Corp filed Critical United Technologies Corp
Publication of EP1857198A1 publication Critical patent/EP1857198A1/fr
Application granted granted Critical
Publication of EP1857198B1 publication Critical patent/EP1857198B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • 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
    • B22C9/103—Multipart cores

Definitions

  • the invention relates to investment casting. More particularly, the invention relates to investment casting core assemblies.
  • Investment casting is commonly used in the aerospace industry. Various examples involve the casting of gas turbine engine parts. Exemplary parts include various blades, vanes, seals, and combustor panels. Many such parts are cast with cooling passageways. The passageways may be formed by sacrificial casting cores.
  • Exemplary cores include ceramic cores, refractory metal cores (RMCs), and combinations thereof.
  • the ceramic cores may form feed passageways whereas the RMCs may form cooling passageways extending from the feed passageways through walls of the associated part. It is understood that ceramic cores may be used to form cooling passageways and metal cores may be used to form feed passageways.
  • Ceramic cores may be made by molding a "green" core and then firing to harden.
  • Refractory metal cores may be made by casting or from sheetstock (e.g., by stamping or cutting/forming) or by other suitable methods.
  • the cores may be assembled to each other and secured, for example, with a ceramic adhesive.
  • An exemplary ceramic adhesive is alumina-based.
  • the adhesive may comprise alumina powder and a binder such as colloidal silica.
  • the core(s) may be overmolded with a sacrificial material (e.g., a wax) to form a pattern in a shape at least partially corresponding to that of the part to be cast.
  • a sacrificial material e.g., a wax
  • a shell may be formed over the pattern (e.g., a ceramic shell formed in a multi-stage stuccoing process).
  • the sacrificial material may be removed (e.g., by a steam dewaxing) leaving the core within a mold chamber formed by the shell.
  • the shell may be fired to harden.
  • Molten metal may be poured into the shell and allowed to solidify.
  • the casting shell and core(s) are destructively removed.
  • Exemplary shell removal is principally mechanical.
  • Exemplary core removal is principally chemical.
  • the cores may be removed by chemical leaching.
  • Exemplary leaching involves use of an alkaline solution in an autoclave. Exemplary leaching techniques are disclosed in US Patents 4,141,781 , 6,241,000 , and 6,739,380 .
  • one aspect of the invention involves a method for attaching a first casting core to a second casting core.
  • a first portion of the first casting core is brought into engagement or close proximity with a second portion of the second casting core.
  • the first and second portions are dipped in a ceramic slurry to form a coating around the first and second portions.
  • the coating is hardened to form a joint between the first and second portions.
  • the resulting composite core may be easier to manufacture than a similarly shaped non-composite core.
  • the metallic casting core may comprise a refractory metal-based substrate (e.g., optionally coated).
  • the method may be used to form a turbine blade core assembly or a turbine vane core assembly.
  • the slurry may be heated to harden.
  • the metallic casting core and ceramic casting core may be vibrated during the introducing.
  • the bringing may be performed with the ceramic casting cores in a green state or in a fired state.
  • the slurry may comprise zircon and aqueous colloidal silica.
  • FIG. 1 shows an exemplary method 20 for forming an investment casting mold.
  • One or more metallic core elements are formed 22 (e.g., of refractory metals such as molybdenum and niobium by stamping or otherwise cutting from sheet metal or of alloys or intermetallics containing one or more refractory metals) and coated 24.
  • Suitable coating materials include silica, alumina, zirconia, chromia, mullite and hafnia.
  • the coefficient of thermal expansion (CTE) of the refractory metal and the coating are similar.
  • Coatings may be applied by any appropriate line-of sight or non-line-of sight technique (e.g., chemical or physical vapor deposition (CVD, PVD) methods, plasma spray methods, electrophoresis, and sol gel methods). Individual layers may typically be 0.1 to 1 mil ( ⁇ 0.0025 to 0.025 mm) thick. Layers of Pt, other noble metals, Cr, Si, W, and/or Al, or other non-metallic materials may be applied to the metallic core elements for oxidation protection in combination with a ceramic coating for protection from molten metal erosion and dissolution.
  • CVD chemical or physical vapor deposition
  • PVD physical vapor deposition
  • One or more ceramic cores may also be formed 26 (e.g., of or containing silica in a molding and firing process).
  • One or more of the coated metallic core elements (hereafter refractory metal cores (RMCs)) are assembled 28 to one or more of the ceramic cores.
  • RMCs refractory metal cores
  • the assembly may include use of a ceramic slurry discussed below.
  • the core assembly is then overmolded 30 with an easily sacrificed material such as a natural or synthetic wax (e.g., via placing the assembly in a mold and molding the wax around it). There may be multiple such assemblies involved in a given mold.
  • the overmolded core assembly (or group of assemblies) forms a casting pattern with an exterior shape largely corresponding to the exterior shape of the part to be cast.
  • the pattern may then be assembled 32 to a shelling fixture (e.g., via wax welding between end plates of the fixture).
  • the pattern may then be shelled 34 (e.g., via one or more stages of slurry dipping, slurry spraying, or the like).
  • the drying provides the shell with at least sufficient strength or other physical integrity properties to permit subsequent processing.
  • the shell containing the invested core assembly may be disassembled 38 fully or partially from the shelling fixture and then transferred 40 to a dewaxer (e.g., a steam autoclave).
  • a dewaxer e.g., a steam autoclave
  • a steam dewax process 42 removes a major portion of the wax leaving the core assembly secured within the shell.
  • the shell and core assembly will largely form the ultimate mold.
  • the dewax process typically leaves a wax or byproduct hydrocarbon residue on the shell interior and core assembly.
  • the shell is transferred 44 to a furnace (e.g., containing air or other oxidizing atmosphere) in which it is heated 46 to strengthen the shell and remove any remaining wax residue (e.g., by vaporization) and/or converting hydrocarbon residue to carbon.
  • Oxygen in the atmosphere reacts with the carbon to form carbon dioxide. Removal of the carbon is advantageous to reduce or eliminate the formation of detrimental carbides in the metal casting. Removing carbon offers the additional advantage of reducing the potential for clogging the vacuum pumps used in subsequent stages of operation.
  • the mold may be removed from the atmospheric furnace, allowed to cool, and inspected 48.
  • the mold may be seeded 50, if necessary(e.g., by locating a metallic seed in the mold to establish the ultimate crystal structure of a directionally solidified (DS) casting or a single-crystal (SX) casting). Nevertheless the present teachings may be applied to other DS and SX casting techniques (e.g., wherein the shell geometry defines a grain selector) or to casting of other microstructures.
  • the mold may be transferred 52 to a casting furnace (e.g., placed atop a chill plate in the furnace).
  • the casting furnace may be pumped down to vacuum 54 or charged with a non-oxidizing atmosphere (e.g., inert gas) to prevent oxidation of the casting alloy.
  • a non-oxidizing atmosphere e.g., inert gas
  • the casting furnace is heated 56 to preheat the mold. This preheating serves two purposes: to further harden and strengthen the shell; and to preheat the shell for the introduction of molten alloy to prevent thermal shock of the shell and premature solidification of the alloy.
  • the molten alloy is poured 58 into the mold and the mold is allowed to cool to solidify 60 the alloy (e.g., during or after withdrawal from the furnace hot zone).
  • the vacuum may be broken 62 and the chilled mold removed 64 from the casting furnace.
  • the shell may be removed in a deshelling process 66 (e.g., mechanical breaking of the shell).
  • the core assembly is removed in a decoring process 68 to leave a cast article (e.g., a metallic precursor of the ultimate part).
  • the cast article may be machined 70, chemically and/or thermally treated 72 and coated 74 to form the ultimate part. Some or all of any machining or chemical or thermal treatment may be performed before the decoring.
  • FIGS. 2-4 show an exemplary composite core in various stages of manufacture.
  • FIG. 5 is a flowchart of the assembly/manufacture steps.
  • FIG. 2 shows a pair of individually-molded ceramic cores 120 and 122.
  • the exemplary cores have respective main body portions or trunks 124 and 126 and terminal portions 128 and 130. Near respective ends 132 and 134 of the terminal portions, the cores may include mating features 136 and 138. Exemplary mating features are shown as a protuberant projection 136 and complementary compartment 138. Alternative mating features include dovetail and other back-locking features, shiplap features, halflap features, and simple butt features. Although illustrated at terminal portions, the mating features may be otherwise formed (e.g., one or more pairs of mating features at intermediate locations along a core body).
  • FIG. 3 shows the cores assembled/mated 180 to each other and held by a fixture 140 with their mating features engaged to each other.
  • Exemplary fixtures 140 may include clamps, robotic actuators, and the like.
  • the fixture 140 may hold the assembled cores during the application of slurry.
  • Exemplary slurry application includes one or more dippings 182 of the terminal portions in a slurry tank to apply a slurry coating 150. If multiple dippings are used, they may be of the same slurry or different slurries from different tanks to produce a desired layering of the coating 150 (e.g., for maximized strength of joint).
  • the terminal portions may be slightly thinned or recessed relative to the adjacent trunk portions so that the build-up of slurry does not excessively increase core thickness or provide discontinuities therein.
  • the fixture 140 may hold the engaged portions of the cores in contact or close proximity (e.g., with a gap sufficiently sized to allow a bonding infiltration of the slurry between the two cores).
  • the coating may be hardened.
  • An'exemplary hardening involves drying 184 without further firing. This may be particularly useful with pre-fired ceramic components which are held together with wax pads.
  • an additional ceramic core may be pre-assembled to one of the cores 120 or 122 and positioned with a wax pad. Room temperature drying of the slurry would preserve the pad.
  • Alternative non-firing drying might involve heating at temperatures of up to 95°C.
  • the hardening may, alternatively, include a firing (e.g., at 1200°C or greater) which may also harden the cores 120 and 122 (e.g., if assembled in a green state or an only partially fired state).
  • the result of the hardening is to produce a joint 154 of sufficient strength to allow further handling and processing steps as described relative to FIG. 1.
  • these may include assembly of the resulting composite ceramic core 160 to one or more other cores such as a refractory metal core 162 (FIG. 4) (e.g., via insertion 186 in a slot cut in the composite core or pre-molded therein).
  • Exemplary slurries may be identical or similar to shell coating slurries. Sequences may be altered relative to application sequences for shell coating slurries to provide desired joint strength and joint surface smoothness. For example, shell coating slurry application sequences typically proceed from fine to coarse. Initial fine slurry is applied to a pattern for smoothness and subsequent coarse slurry for strength. However, it may be desired that the last layer of slurry in the coating 150 be fine for smoothness because the cores generally form internal features whereas the shells generally form external features.
  • Exemplary slurries comprise a combination of zircon and aqueous colloidal silica along with appropriate surfactants and other agents (e.g., for promoting bubble rupture).
  • Variations include use of the slurry coating in combination with a ceramic adhesive in the joint.
  • the adhesive may be introduced during core assembly.
  • Exemplary ceramic adhesives are available from Cotronics Corporation of Brooklyn, New York, under the trademark RESBOND. Use of ceramic adhesive may be particularly appropriate with pre-fired ceramic cores. The ceramic adhesive increases bond strength and may further avoid the need for a subsequent high temperature firing.
  • FIG. 6 shows the assembly of a ceramic core 200 with a refractory metal core 202.
  • a portion 204 of the refractory metal core is positioned within a slot 206 of a ceramic core and retained at least partially by a ceramic adhesive 208.
  • a slurry coating 210 may surround the junction of these two cores to form a joint. The slurry 210 may be applied as described above.
  • a portion of one or both of the cores may be masked during slurry application (e.g., spraying, painting, or dipping) or may be cleaned of slurry after such application.
  • slurry application e.g., spraying, painting, or dipping
  • the overdipping of the RMC-ceramic core joint isolates the unfired ceramic adhesive (if any) from contact with the casting alloy to avoid adverse chemical interaction.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Molds, Cores, And Manufacturing Methods Thereof (AREA)
  • Mold Materials And Core Materials (AREA)
EP07251140A 2006-03-21 2007-03-19 Procédés pour fixer les noyaux de moulage Active EP1857198B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US11/385,382 US20070221359A1 (en) 2006-03-21 2006-03-21 Methods and materials for attaching casting cores

Publications (2)

Publication Number Publication Date
EP1857198A1 true EP1857198A1 (fr) 2007-11-21
EP1857198B1 EP1857198B1 (fr) 2011-09-28

Family

ID=38229583

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07251140A Active EP1857198B1 (fr) 2006-03-21 2007-03-19 Procédés pour fixer les noyaux de moulage

Country Status (5)

Country Link
US (1) US20070221359A1 (fr)
EP (1) EP1857198B1 (fr)
JP (1) JP2007253237A (fr)
CN (1) CN101041175A (fr)
SG (1) SG136062A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2018178762A1 (fr) * 2017-03-29 2018-10-04 Nemak, S.A.B. De C.V. Noyau de coulée et procédé de production s'y rapportant

Families Citing this family (34)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7967555B2 (en) * 2006-12-14 2011-06-28 United Technologies Corporation Process to cast seal slots in turbine vane shrouds
US10468863B1 (en) 2008-04-03 2019-11-05 Arlington Industries, Inc. Duplex electrical connector with one-piece connector body
US7882886B1 (en) * 2008-04-03 2011-02-08 Arlington Industries, Inc. Coring system and method for manufacturing a one-piece die cast electrical connector body
FR2950825B1 (fr) * 2009-10-01 2011-12-09 Snecma Procede ameliore de fabrication d'un ensemble annulaire aubage de turbomachine a la cire perdue, moule metallique et modele en cire pour la mise en oeuvre d'un tel procede
US20110182726A1 (en) * 2010-01-25 2011-07-28 United Technologies Corporation As-cast shroud slots with pre-swirled leakage
US20110204205A1 (en) * 2010-02-25 2011-08-25 Ahmed Kamel Casting core for turbine engine components and method of making the same
US9403208B2 (en) 2010-12-30 2016-08-02 United Technologies Corporation Method and casting core for forming a landing for welding a baffle inserted in an airfoil
US8302668B1 (en) 2011-06-08 2012-11-06 United Technologies Corporation Hybrid core assembly for a casting process
US8291963B1 (en) 2011-08-03 2012-10-23 United Technologies Corporation Hybrid core assembly
CN102366815B (zh) * 2011-10-11 2016-02-03 华文蔚 一种铝合金低压铸造金属型用涂料
CN102366814B (zh) * 2011-10-11 2016-01-20 华文蔚 一种铝合金低压铸造金属型用涂料的制备方法
KR101960715B1 (ko) * 2012-08-02 2019-03-22 한화파워시스템 주식회사 임펠러 또는 터빈 휠의 제조 방법
US9511388B2 (en) * 2012-12-21 2016-12-06 United Technologies Corporation Method and system for holding a combustor panel during coating process
SG10201707985SA (en) * 2013-04-03 2017-10-30 United Technologies Corp Variable thickness trailing edge cavity and method of making
CN105873694B (zh) * 2013-08-23 2018-05-15 西门子能源公司 带有高分解度区域的涡轮机部件铸造芯
WO2015060989A1 (fr) 2013-10-24 2015-04-30 United Technologies Corporation Noyaux de moulage à noyau perdu pour former des passages de refroidissement
WO2015073202A1 (fr) * 2013-11-18 2015-05-21 United Technologies Corporation Noyaux de coulée enduits et procédés de fabrication associés
CN104647586B (zh) * 2013-11-19 2017-09-22 中国科学院金属研究所 一种复杂结构单晶空心叶片用复合陶瓷型芯的制备方法
PL3086893T3 (pl) 2013-12-23 2020-01-31 United Technologies Corporation Rama konstrukcyjna z traconym rdzeniem
EP3096900B1 (fr) * 2014-01-23 2020-04-15 United Technologies Corporation Procédé pour fabriquer un moule de façon additive
JP6347400B2 (ja) * 2014-02-13 2018-06-27 日立金属株式会社 セラミック焼結体の製造方法
CN104028699B (zh) * 2014-04-28 2016-03-16 沈阳明禾石英制品有限责任公司 一种导叶内环分体组合式空心陶瓷型芯的制备方法
US10343218B2 (en) * 2016-02-29 2019-07-09 General Electric Company Casting with a second metal component formed around a first metal component using hot isostactic pressing
US20200047243A1 (en) * 2016-11-01 2020-02-13 Shiloh Industries, Inc. Composite part with external part cast around internal insert and method for producing the same
FR3065661B1 (fr) * 2017-04-28 2019-06-14 Safran Aircraft Engines Noyau pour la fabrication par moulage a la cire perdue d'une aube de turbomachine
US10391549B2 (en) * 2017-06-28 2019-08-27 General Electric Company Additively manufactured casting core-shell hybrid mold and ceramic shell
US20190022757A1 (en) * 2017-07-19 2019-01-24 United Technologies Corporation Linkage of composite core features
CN108607971A (zh) * 2018-07-25 2018-10-02 昆山众异特机械工业有限公司 用于制备新能源汽车的电机壳体的砂芯、模具及压铸设备
KR102075309B1 (ko) * 2019-08-16 2020-02-07 전범서 일체형 콘트롤밸브 하우징용 일체화 코어 및 일체화 코어의 제조방법
US11642720B2 (en) * 2019-10-16 2023-05-09 Raytheon Technologies Corporation Integral core bumpers
CN111136243B (zh) * 2020-01-13 2021-06-18 中北大学 陶瓷/金属复合层的铸造方法
US11813665B2 (en) * 2020-09-14 2023-11-14 General Electric Company Methods for casting a component having a readily removable casting core
US11440146B1 (en) * 2021-04-22 2022-09-13 Raytheon Technologies Corporation Mini-core surface bonding
CN114406201B (zh) * 2022-01-26 2023-11-14 阜新力达钢铁铸造有限公司 导轨无孔立柱的铸造方法及系统

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4141781A (en) 1977-10-06 1979-02-27 General Electric Company Method for rapid removal of cores made of βAl2 O3 from directionally solidified eutectic and superalloy and superalloy materials
GB2211122A (en) 1987-10-22 1989-06-28 Agustin Arana Erana Joining blow core parts together,by a further blowing operation
WO2000078480A1 (fr) 1999-06-24 2000-12-28 Howmet Research Corporation Ame de profil moule a plusieurs elements
US6241000B1 (en) 1995-06-07 2001-06-05 Howmet Research Corporation Method for removing cores from castings
EP1306147A1 (fr) 2001-10-24 2003-05-02 United Technologies Corporation Noyau destiné au moulage de précision
US6739380B2 (en) 2002-04-11 2004-05-25 Rolls-Royce Corporation Method and apparatus for removing ceramic material from cast components
EP1543896A2 (fr) 2003-12-19 2005-06-22 United Technologies Corporation Noyaux pour la coulée de précision

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4774990A (en) * 1986-08-04 1988-10-04 Mazda Motor Corporation High pressure casting method and a casting core
FR2785836B1 (fr) * 1998-11-12 2000-12-15 Snecma Procede de fabrication de noyaux ceramiques minces pour fonderie

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4141781A (en) 1977-10-06 1979-02-27 General Electric Company Method for rapid removal of cores made of βAl2 O3 from directionally solidified eutectic and superalloy and superalloy materials
GB2211122A (en) 1987-10-22 1989-06-28 Agustin Arana Erana Joining blow core parts together,by a further blowing operation
US6241000B1 (en) 1995-06-07 2001-06-05 Howmet Research Corporation Method for removing cores from castings
WO2000078480A1 (fr) 1999-06-24 2000-12-28 Howmet Research Corporation Ame de profil moule a plusieurs elements
EP1306147A1 (fr) 2001-10-24 2003-05-02 United Technologies Corporation Noyau destiné au moulage de précision
US6739380B2 (en) 2002-04-11 2004-05-25 Rolls-Royce Corporation Method and apparatus for removing ceramic material from cast components
EP1543896A2 (fr) 2003-12-19 2005-06-22 United Technologies Corporation Noyaux pour la coulée de précision

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2018178762A1 (fr) * 2017-03-29 2018-10-04 Nemak, S.A.B. De C.V. Noyau de coulée et procédé de production s'y rapportant
KR20190128718A (ko) * 2017-03-29 2019-11-18 네마크 에스.에이.비.드 씨. 브이. 주조 코어 및 주조 코어 제조 방법
JP2020512937A (ja) * 2017-03-29 2020-04-30 ネマク, ソシエダ アノニマ ブルサーティリ デ カピタル バリアブレNemak, S.A.B. de C.V. 鋳造用中子およびその製造方法
US10843255B2 (en) 2017-03-29 2020-11-24 Nemak, S.A.B. De C.V. Foundry core

Also Published As

Publication number Publication date
JP2007253237A (ja) 2007-10-04
SG136062A1 (en) 2007-10-29
US20070221359A1 (en) 2007-09-27
CN101041175A (zh) 2007-09-26
EP1857198B1 (fr) 2011-09-28

Similar Documents

Publication Publication Date Title
EP1857198B1 (fr) Procédés pour fixer les noyaux de moulage
EP1600230B1 (fr) Appareil et Procédé d'élaboration d'un moule de coulée de précision
US7861766B2 (en) Method for firing a ceramic and refractory metal casting core
US8100165B2 (en) Investment casting cores and methods
US7757745B2 (en) Contoured metallic casting core
US9476307B2 (en) Castings, casting cores, and methods
US7753104B2 (en) Investment casting cores and methods
US8251123B2 (en) Casting core assembly methods
US7779892B2 (en) Investment casting cores and methods
US20100129217A1 (en) Castings, Casting Cores, and Methods
US7207374B2 (en) Non-oxidizable coating
EP1785205B1 (fr) Procédé et Appareil pour l'assemblage de noyaux céramique et métallique en coulée de précision
US20110315336A1 (en) Contoured Metallic Casting Core

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: A1

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

AX Request for extension of the european patent

Extension state: AL BA HR MK YU

17P Request for examination filed

Effective date: 20080521

AKX Designation fees paid

Designated state(s): CH DE GB LI

RTI1 Title (correction)

Free format text: METHODS FOR ATTACHING CASTING CORES

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 LI

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 602007017477

Country of ref document: DE

Owner name: UNITED TECHNOLOGIES CORP. (N.D.GES.D. STAATES , US

Free format text: FORMER OWNER: UNITED TECHNOLOGIES CORPORATION, HARTFORD, CONN., US

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602007017477

Country of ref document: DE

Effective date: 20111201

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: 20120629

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602007017477

Country of ref document: DE

Effective date: 20120629

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: 20120331

Ref country code: CH

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

Effective date: 20120331

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 602007017477

Country of ref document: DE

Representative=s name: SCHMITT-NILSON SCHRAUD WAIBEL WOHLFROM PATENTA, DE

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 602007017477

Country of ref document: DE

Representative=s name: SCHMITT-NILSON SCHRAUD WAIBEL WOHLFROM PATENTA, DE

Ref country code: DE

Ref legal event code: R081

Ref document number: 602007017477

Country of ref document: DE

Owner name: UNITED TECHNOLOGIES CORP. (N.D.GES.D. STAATES , US

Free format text: FORMER OWNER: UNITED TECHNOLOGIES CORPORATION, HARTFORD, CONN., US

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 602007017477

Country of ref document: DE

Owner name: RAYTHEON TECHNOLOGIES CORPORATION (N.D.GES.D.S, US

Free format text: FORMER OWNER: UNITED TECHNOLOGIES CORP. (N.D.GES.D. STAATES DELAWARE), FARMINGTON, CONN., US

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

Ref country code: GB

Payment date: 20230221

Year of fee payment: 17

Ref country code: DE

Payment date: 20230221

Year of fee payment: 17

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20230519