EP2399693A2 - Noyau de coulée métallique profilé - Google Patents
Noyau de coulée métallique profilé Download PDFInfo
- Publication number
- EP2399693A2 EP2399693A2 EP11250408A EP11250408A EP2399693A2 EP 2399693 A2 EP2399693 A2 EP 2399693A2 EP 11250408 A EP11250408 A EP 11250408A EP 11250408 A EP11250408 A EP 11250408A EP 2399693 A2 EP2399693 A2 EP 2399693A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- core
- leading portion
- forming
- cutting
- casting core
- 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
Links
- 238000005266 casting Methods 0.000 title claims description 20
- 238000000034 method Methods 0.000 claims abstract description 36
- 239000000919 ceramic Substances 0.000 claims abstract description 19
- 238000005495 investment casting Methods 0.000 claims abstract description 15
- 238000004519 manufacturing process Methods 0.000 claims abstract description 10
- 238000005520 cutting process Methods 0.000 claims description 10
- 239000000463 material Substances 0.000 claims description 10
- 238000003754 machining Methods 0.000 claims description 9
- 229910045601 alloy Inorganic materials 0.000 claims description 7
- 239000000956 alloy Substances 0.000 claims description 7
- 238000000576 coating method Methods 0.000 claims description 5
- 238000000465 moulding Methods 0.000 claims description 5
- 239000011248 coating agent Substances 0.000 claims description 4
- 238000003698 laser cutting Methods 0.000 claims description 3
- 239000007788 liquid Substances 0.000 claims description 3
- 238000001816 cooling Methods 0.000 description 11
- 239000011230 binding agent Substances 0.000 description 5
- 239000007789 gas Substances 0.000 description 5
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 4
- 229910052799 carbon Inorganic materials 0.000 description 4
- 239000003870 refractory metal Substances 0.000 description 4
- 239000002002 slurry Substances 0.000 description 4
- 229910000601 superalloy Inorganic materials 0.000 description 4
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 description 2
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 2
- MCMNRKCIXSYSNV-UHFFFAOYSA-N Zirconium dioxide Chemical compound O=[Zr]=O MCMNRKCIXSYSNV-UHFFFAOYSA-N 0.000 description 2
- 239000000853 adhesive Substances 0.000 description 2
- 230000001070 adhesive effect Effects 0.000 description 2
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 description 2
- 230000000712 assembly Effects 0.000 description 2
- 238000000429 assembly Methods 0.000 description 2
- 230000008901 benefit Effects 0.000 description 2
- 229910010293 ceramic material Inorganic materials 0.000 description 2
- 239000013078 crystal Substances 0.000 description 2
- 125000001183 hydrocarbyl group Chemical group 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000003647 oxidation Effects 0.000 description 2
- 238000007254 oxidation reaction Methods 0.000 description 2
- 230000001590 oxidative effect Effects 0.000 description 2
- 238000005240 physical vapour deposition Methods 0.000 description 2
- 239000000843 powder Substances 0.000 description 2
- 238000007711 solidification Methods 0.000 description 2
- 230000008023 solidification Effects 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- 230000007704 transition Effects 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 241000218642 Abies Species 0.000 description 1
- 241000588731 Hafnia Species 0.000 description 1
- 229910000760 Hardened steel Inorganic materials 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000006227 byproduct Substances 0.000 description 1
- 229910002092 carbon dioxide Inorganic materials 0.000 description 1
- 239000001569 carbon dioxide Substances 0.000 description 1
- 238000005524 ceramic coating Methods 0.000 description 1
- 238000005229 chemical vapour deposition Methods 0.000 description 1
- 238000000354 decomposition reaction Methods 0.000 description 1
- 230000001627 detrimental effect Effects 0.000 description 1
- QDOXWKRWXJOMAK-UHFFFAOYSA-N dichromium trioxide Chemical compound O=[Cr]O[Cr]=O QDOXWKRWXJOMAK-UHFFFAOYSA-N 0.000 description 1
- KZHJGOXRZJKJNY-UHFFFAOYSA-N dioxosilane;oxo(oxoalumanyloxy)alumane Chemical compound O=[Si]=O.O=[Si]=O.O=[Al]O[Al]=O.O=[Al]O[Al]=O.O=[Al]O[Al]=O KZHJGOXRZJKJNY-UHFFFAOYSA-N 0.000 description 1
- 238000007598 dipping method Methods 0.000 description 1
- 238000004090 dissolution Methods 0.000 description 1
- 238000005553 drilling Methods 0.000 description 1
- 238000001035 drying Methods 0.000 description 1
- 238000001962 electrophoresis Methods 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 238000000227 grinding Methods 0.000 description 1
- CJNBYAVZURUTKZ-UHFFFAOYSA-N hafnium(IV) oxide Inorganic materials O=[Hf]=O CJNBYAVZURUTKZ-UHFFFAOYSA-N 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 239000011261 inert gas Substances 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 150000001247 metal acetylides Chemical class 0.000 description 1
- 238000005058 metal casting Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 229910052863 mullite Inorganic materials 0.000 description 1
- 229910000510 noble metal Inorganic materials 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 239000002243 precursor Substances 0.000 description 1
- 230000002028 premature Effects 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 239000011253 protective coating Substances 0.000 description 1
- 238000004080 punching Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 239000000377 silicon dioxide Substances 0.000 description 1
- 238000003980 solgel method Methods 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 238000007669 thermal treatment Methods 0.000 description 1
- 238000009834 vaporization Methods 0.000 description 1
- 230000008016 vaporization Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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
-
- 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
-
- 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
Definitions
- the disclosure relates to investment casting. More particularly, it relates to the investment casting of superalloy turbine engine components.
- Investment casting is a commonly used technique for forming metallic components having complex geometries, especially hollow components, and is used in the fabrication of superalloy gas turbine engine components.
- the disclosure is described in respect to the production of particular superalloy castings, however it is understood that the disclosure is not so limited.
- Gas turbine engines are widely used in aircraft propulsion, electric power generation, and ship propulsion. In gas turbine engine applications, efficiency is a prime objective. Improved gas turbine engine efficiency can be obtained by operating at higher temperatures, however current operating temperatures in the turbine section exceed the melting points of the superalloy materials used in turbine components. Consequently, it is a general practice to provide air cooling. Cooling is provided by flowing relatively cool air from the compressor section of the engine through passages in the turbine components to be cooled. Such cooling comes with an associated cost in engine efficiency. Consequently, there is a strong desire to provide enhanced specific cooling, maximizing the amount of cooling benefit obtained from a given amount of cooling air. This may be obtained by the use of fine, precisely located, cooling passageway sections.
- the cooling passageway sections may be cast over casting cores.
- Ceramic casting cores may be formed by molding a mixture of ceramic powder and binder material by injecting the mixture into hardened steel dies. After removal from the dies, the green cores are thermally post-processed to remove the binder and fired to sinter the ceramic powder together.
- the trend toward finer cooling features has taxed core manufacturing techniques. The fine features may be difficult to manufacture and/or, once manufactured, may prove fragile.
- US-A-6,637,500 , US-A-6,929,054 and US-A-2007/261814 (the disclosures of which are incorporated by reference herein as if set forth at length) disclose use of ceramic and refractory metal core combinations.
- FIG. 1 shows a trailing edge portion of a turbine airfoil 20 as cast within a shell 22.
- the shell contains a core assembly.
- the exemplary core assembly includes a ceramic feed core having spanwise legs 30, 32, and 34 for casting associated passageway legs.
- the leg 34 casts a trailing spanwise passageway 36.
- the core assembly also includes metallic cores, of which cores 40, 42, and 44 are shown.
- the exemplary metallic cores are formed of refractory metal sheet stock.
- the core 40 forms a pressure side outlet circuit
- the core 42 forms a suction side outlet circuit
- the core 44 forms a trailing edge outlet slot 50.
- the outlet slot 50 is fed from the passageway 36.
- a leading portion of the core 44 is secured within a mating slot of the trailing leg 34 of the ceramic core.
- the present invention provides a method for manufacturing an investment casting core from a metallic blank.
- the blank has a thickness between parallel first and second faces less than a width and length transverse thereto.
- the blank is locally thinned from at least one of the first and second faces.
- the blank is through-cut across the thickness.
- the blank is inserted into the leading portion into a slot in a pre-formed ceramic core.
- through-cutting may comprise at least one of laser cutting, liquid jet cutting, and EDM.
- the thinning may comprise at least one of EDM, ECM, MDP, and mechanical machining.
- the investment casting core may be at least partially overmolded by a pattern-forming material for forming a pattern.
- the pattern may be shelled.
- the pattern-forming material may be removed from the shelled pattern for forming a shell.
- Molten alloy may be introduced to the shell.
- the shell may be removed.
- the method may be used to form a gas turbine engine component.
- An exemplary component is an airfoil wherein the core forms trailing edge outlet passageways.
- Another aspect of the present invention provides an investment casting core having a metallic core element and a ceramic core.
- the metallic core element has a tapered leading portion, an intermediate portion downstream of the tapered leading portion, and a trailing portion downstream of the intermediate portion and thicker than the intermediate portion.
- the ceramic casting core has a slot receiving the leading portion.
- FIG. 2 shows an alternative refractory metal core (RMC) 60 which has a leading/upstream edge/end 62 and a trailing/downstream edge/end 64.
- the exploded view of FIG. 3 shows an inboard end 66 and an outboard end 68.
- an upstream-most portion 70 extending aft from the leading edge/end 62 is configured to be received within and mate with a trailing slot 72 of a trailing leg 74 of a ceramic feedcore 76.
- the RMC 60 has an intermediate portion 80 which casts the majority of the ultimate trailing edge discharge slot.
- the RMC pressure side/surface 82 and suction side/surface 84 are separated by an essentially constant RMC thickness T 1 ( FIG. 2A ). Downstream of the portion 80, the exemplary RMC thickens. A relatively thick portion 86 having an essentially constant thickness shown as T 3 extends to the trailing end/edge 64. Of this portion 86, a smaller upstream portion 88 casts pressure side discharge openings in the airfoil.
- FIG. 3 (a partially schematic/simplified view of a pattern) shows the portion 80 having holes 100 for casting posts within the slot.
- FIG. 3 further shows the portion 88 as having streamwise elongate tapering holes 102 which are interspersed with intact portions 104.
- the intact portions 104 cast pressure side openings from the trailing edge discharge slot; whereas the holes 102 cast walls therebetween.
- the feedcore slot 72 and RMC portion 70 both have an upstream-ward taper.
- the exemplary thickness T 2 of the RMC at the leading edge is less than T 1 (e.g., 30-60%).
- the exemplary RMC taper is essentially constant at an angle of ⁇ 1 over a streamwise length L 1 .
- the exemplary taper is provided by relieving/beveling only one of the two faces 82 and 84 (the face 84 in the exemplary embodiment with a bevel facet/surface 110).
- the exemplary relief provides the taper angle ⁇ 1 .
- Exemplary ⁇ 1 are 0.1-3.0°, more narrowly 1.0-2.5°.
- Exemplary taper length L 1 is coincident with or slightly less than a depth D 1 of the slot.
- the exemplary slot has an opening 120 having a height H 1 which may be greater than T 1 and has a base 122 with a height H 2 which is greater than T 2 .
- a portion of the slot between respective slot walls 124 and 126 and the RMC may be filled with an adhesive or slurry 130.
- the exemplary streamwise cross-section of the RMC is shown as generally arcuate with concavity along the pressure side and convexity along the suction side so as to correspond to a median of the airfoil cross-section.
- Exemplary L 1 is 0.040-0.100 inch (1-2.5mm), more narrowly 0.050-0.075 inch (1.3mm-1.9mm).
- Exemplary T 1 is 0.012 inch (0.3mm), more broadly 0.005-0.020 inch (0.13-0.5mm) or 0.010-0.015 inch (0.25-0.38mm).
- Exemplary T 2 is 0.005 inch (0.13mm), more broadly 0.002-0.015 inch (0.05-0.38mm) or 0.003-0.007 inch (0.08-0.18mm) or 25-75% of T 1 , more narrowly, 40-60%.
- Exemplary T 3 is 0.035 inch (0.9mm), more broadly 0.020-0.050 inch (0.5-1.3mm) or 200-500% of T 1 , more narrowly 250-400%.
- Exemplary feedcore thickness at either side of the slot base 122 may be at least 0.018 inch (0.46mm), more narrowly 0.018-0.040 inch (0.46-1.0mm) or 0.08-0.025 inch (0.46-0.64mm).
- the RMC 84 may be machined from a strip having a thickness equal to T 3 , a greater width, and a yet greater length.
- gross thickness features may be machined 202 to provide the thickness T 1 of the intermediate portion and provide the bevel/taper.
- the exemplary machining is from the pressure side face 82 to define the intermediate portion and from the suction side face 84 to provide the taper of the leading portion.
- the step 202 may easily be further divided.
- Exemplary machining may be mechanical machining or may be an abrasive grinding, electrodischarge machining (EDM), electrochemical machining (ECM), or a molecular decomposition process (MDP).
- FIG. 4 further shows: the airfoil 160 having a leading edge 162 and a tip 164; the platform 170 at the inboard end of the airfoil; and the firtree attachment root 172 depending from the underside of the platform.
- the root has the inlet ports 174 to the trunks of the cooling passageway network (cast over the ceramic feedcore trunks).
- FIG. 5 shows the outlet 154 as including a spanwise array of segments/portions/openings 180 along the airfoil pressure side between associated pairs of the dividing walls 152.
- the openings 180 are cast by the intact portions 104 of the RMC portion 88 of FIG. 2 .
- a curving transition 89 ( FIG. 2 ) between the RMC portions 80 and 86/88 casts a curving transition 182 ( FIG. 5 ) between a main portion 184 of the slot and the openings 180.
- Exemplary cutting may be via a punching/stamping operation or, alternatively, mechanical drilling, laser cutting, liquid jet cutting, and/or EDM.
- the RMC is bent 208 (e.g., via stamping). This bending may also form a spanwise variation (e.g., to accommodate a varying relationship in the position of the feedcore relative to the discharge slot) such as creating a net spanwise twist.
- An exemplary stamping is performed via one or more pressing stages in custom presses having opposing die faces contoured to mate with the RMC.
- the RMC may be coated 210 with a protective coating. Alternatively a coating could be applied pre-assembly.
- Suitable coating materials include silica, alumina, zirconia, chromia, mullite and hafnia.
- CTE coefficient of thermal expansion
- 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 (2.5 to 25 ⁇ m) thick.
- Layers of Pt, other noble metals, Cr, Si, W, and/or A1, 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.
- the ceramic core may be (e.g., silica-, zircon-, or alumina-based) molded 212.
- the as-molded ceramic material may include a binder.
- the binder may function to maintain integrity of the molded ceramic material in an unfired green state.
- Exemplary binders are wax-based.
- the preliminary core assembly may be debindered/fired 214 to harden the ceramic (e.g., by heating in an inert atmosphere or vacuum).
- the slot 72 may have been formed as part of the molding 212 or may be cut in the ceramic (e.g., in the green state or in the fired state).
- the RMC may be inserted 216 into the ceramic core to assemble and an adhesive or slurry introduced 218.
- FIG. 6 shows an exemplary method 220 for investment casting using the core assembly.
- Other methods are possible, including a variety of prior art methods and yet-developed methods.
- the fired core assembly is then overmolded 230 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 232 to a shelling fixture (e.g., via wax welding between end plates of the fixture).
- the pattern may then be shelled 234 (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 238 fully or partially from the shelling fixture and then transferred 240 to a dewaxer (e.g., a steam autoclave).
- a dewaxer e.g., a steam autoclave
- a steam dewax process 242 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 244 to a furnace (e.g., containing air or other oxidizing atmosphere) in which it is heated 246 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 248.
- the mold may be seeded 250 by placing 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 252 to a casting furnace (e.g., placed atop a chill plate in the furnace).
- the casting furnace may be pumped down to vacuum 254 or charged with a non-oxidizing atmosphere (e.g., inert gas) to prevent oxidation of the casting alloy.
- the casting furnace is heated 256 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 and premature solidification of the alloy.
- the molten alloy is poured 258 into the mold and the mold is allowed to cool to solidify 260 the alloy (e.g., after withdrawal from the furnace hot zone).
- the vacuum may be broken 262 and the chilled mold removed 264 from the casting furnace.
- the shell may be removed in a deshelling process 266 (e.g., mechanical breaking of the shell).
- the core assembly is removed in a decoring process 268 to leave a cast article (e.g., a metallic precursor of the ultimate part).
- the cast article may be machined 270, chemically and/or thermally treated 272 and coated 274 to form the ultimate part. Some or all of any machining or chemical or thermal treatment may be performed before the decoring.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Molds, Cores, And Manufacturing Methods Thereof (AREA)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/823,165 US20110315336A1 (en) | 2010-06-25 | 2010-06-25 | Contoured Metallic Casting Core |
Publications (3)
Publication Number | Publication Date |
---|---|
EP2399693A2 true EP2399693A2 (fr) | 2011-12-28 |
EP2399693A3 EP2399693A3 (fr) | 2012-07-25 |
EP2399693B1 EP2399693B1 (fr) | 2019-05-01 |
Family
ID=44501655
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP11250408.9A Active EP2399693B1 (fr) | 2010-06-25 | 2011-03-31 | Noyau de coulée métallique profilé |
Country Status (2)
Country | Link |
---|---|
US (1) | US20110315336A1 (fr) |
EP (1) | EP2399693B1 (fr) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2013163020A1 (fr) | 2012-04-24 | 2013-10-31 | United Technologies Corporation | Cœur de moteur à turbine à gaz créant une partie de profil aérodynamique extérieure |
EP2961547A4 (fr) * | 2013-03-01 | 2016-11-23 | United Technologies Corp | Procédé de production d'un composant de moteur à turbine à gaz et noyau utilisé pour produire ce composant |
EP3060363A4 (fr) * | 2013-10-24 | 2017-07-26 | United Technologies Corporation | Noyaux de moulage à noyau perdu pour former des passages de refroidissement |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20140102656A1 (en) | 2012-10-12 | 2014-04-17 | United Technologies Corporation | Casting Cores and Manufacture Methods |
US10370980B2 (en) | 2013-12-23 | 2019-08-06 | United Technologies Corporation | Lost core structural frame |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6637500B2 (en) | 2001-10-24 | 2003-10-28 | United Technologies Corporation | Cores for use in precision investment casting |
US6929054B2 (en) | 2003-12-19 | 2005-08-16 | United Technologies Corporation | Investment casting cores |
US20070261814A1 (en) | 2006-05-12 | 2007-11-15 | United Technologies Corporation | Contoured metallic casting core |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5423372A (en) * | 1993-12-27 | 1995-06-13 | Ford Motor Company | Joining sand cores for making castings |
AU677903B2 (en) * | 1994-06-01 | 1997-05-08 | Toyota Jidosha Kabushiki Kaisha | Casting method with improved resin core removing step and apparatus for performing the method |
FR2812572B1 (fr) * | 2000-07-21 | 2003-03-07 | Montupet Sa | Equipement de moulage de pieces de fonderies avec des moyens perfectionnes de positionnement de noyaux de sable, et procede de positionnement associe |
US7108045B2 (en) * | 2004-09-09 | 2006-09-19 | United Technologies Corporation | Composite core for use in precision investment casting |
US8100165B2 (en) * | 2008-11-17 | 2012-01-24 | United Technologies Corporation | Investment casting cores and methods |
US8171978B2 (en) * | 2008-11-21 | 2012-05-08 | United Technologies Corporation | Castings, casting cores, and methods |
-
2010
- 2010-06-25 US US12/823,165 patent/US20110315336A1/en not_active Abandoned
-
2011
- 2011-03-31 EP EP11250408.9A patent/EP2399693B1/fr active Active
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6637500B2 (en) | 2001-10-24 | 2003-10-28 | United Technologies Corporation | Cores for use in precision investment casting |
US6929054B2 (en) | 2003-12-19 | 2005-08-16 | United Technologies Corporation | Investment casting cores |
US20070261814A1 (en) | 2006-05-12 | 2007-11-15 | United Technologies Corporation | Contoured metallic casting core |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2013163020A1 (fr) | 2012-04-24 | 2013-10-31 | United Technologies Corporation | Cœur de moteur à turbine à gaz créant une partie de profil aérodynamique extérieure |
EP2841710A4 (fr) * | 2012-04-24 | 2016-03-09 | United Technologies Corp | C ur de moteur à turbine à gaz créant une partie de profil aérodynamique extérieure |
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 |
EP2961547A4 (fr) * | 2013-03-01 | 2016-11-23 | United Technologies Corp | Procédé de production d'un composant de moteur à turbine à gaz et noyau utilisé pour produire ce composant |
EP3060363A4 (fr) * | 2013-10-24 | 2017-07-26 | United Technologies Corporation | Noyaux de moulage à noyau perdu pour former des passages de refroidissement |
US10005123B2 (en) | 2013-10-24 | 2018-06-26 | United Technologies Corporation | Lost core molding cores for forming cooling passages |
US10821500B2 (en) | 2013-10-24 | 2020-11-03 | Raytheon Technologies Corporation | Lost core molding cores for forming cooling passages |
Also Published As
Publication number | Publication date |
---|---|
US20110315336A1 (en) | 2011-12-29 |
EP2399693B1 (fr) | 2019-05-01 |
EP2399693A3 (fr) | 2012-07-25 |
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EP2399693B1 (fr) | Noyau de coulée métallique profilé |
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