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Publication numberUS3662816 A
Publication typeGrant
Publication dateMay 16, 1972
Filing dateApr 30, 1970
Priority dateOct 1, 1968
Publication numberUS 3662816 A, US 3662816A, US-A-3662816, US3662816 A, US3662816A
InventorsBishop Thomas H, Young Kenneth K Jr
Original AssigneeTrw Inc
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Means for preventing core shift in casting articles
US 3662816 A
Shell-type casting molds for producing hollow cast articles, the mold being built up by forming a low melting pattern about a ceramic core, inserting thin metal pins through the pattern and into engagement with the core, forming a shell mold about the resulting pattern so that the ends of the pins are anchored in the resulting shell mold, removing the meltable pattern, and casting the molten metal into the cavity thus produced whereby the molten metal dissolves the pins and no holes appear in the finished article.
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nited States Patent Bishop et a].

[ 3,662,816 [451 May 16, 1972 [s41 MEANS FOR PREVENTING CORE SHIFT IN CASTING ARTICLES [72] Inventors: Thomas H. Bishop, Alliance; Kenneth K.

Young, Jr., Paris, both of Ohio [73] Assignee: TRW Inc., Cleveland, Ohio [22] Filed: Apr. 30, 1970 [2]] Appl. No.: 43,624

Related US. Application Data [62] Division of Ser. No. 764,208, Oct. 1, 1968, Pat. No.

[52] US. Cl ..l64/366, 164/399 [51] Int. Cl. ..B22c 9/10, B22c 21/14 [58] Field of Search 164/30, 3], 32, 34, 35, 36,

[56] References Cited UNITED STATES PATENTS 2,096,679 10/1937 Gibson ..l64/399 3,401,738 9/1968 Parille FOREIGN PATENTS OR APPLICATIONS 470,283 l/I929 Germany 164/398 Primary Examiner-J. Spencer Overholser Assistant Examiner-John E. Roethel Attorney-Hill, Sherman, Meroni, Gross & Simpson 57 ABSTRACT Shell-type casting molds for producing hollow cast articles, the mold being built up by forming a low melting pattern about a ceramic core, inserting thin metal pins through the pattern and into engagement with the core, forming a shell mold about the resulting pattern so that the ends of the pins are anchored in the resulting shell mold, removing the meltable pattern, and casting the molten metal into the cavity thus produced whereby the molten metal dissolves the pins and no holes appear in the finished article.

1 Claim, 6 Drawing Figures MEANS FOR PREVENTING CORE SHIFT IN CASTING RTICLES CROSS REFERENCE TO RELATED APPLICATION BACKGROUND OF THE INVENTION 1. Field of the Invention This invention is in the field of precision investment casting molds and, more specifically relates to a means for preventing core movement or shifting of a core in a shell mold, such means including a plurality of thin wire pins which are anchored in the shell mold and extend into engagement with the surface of the core, thereby spacing the core properly from the wall of the casting cavity.

2. Description of the Prior Art Modern investment casting procedures are frequently used to produce castings which have complex hollow interiors. Some of the best examples of such cast articles are turbine blades and vanes containing a hollow interior for the purpose of providing cooling to the blade or vane during use. In order to provide the hollow interior in the cast article, of course, it is necessary to use a core, usually ceramic in composition. A problem arises when there is even a slight movement or shift of the core in the mold which may occur during removal of the pattern material,.during preheating of the mold prior to pouring the metal therein, or during pouring of the metal into the mold.

A prior practice which has attempted to solve this problem involved drilling holes in the wax pattern until the core was reached. Then, when the shell mold was formed about the pattern, the holes would be filled with the ceramic material of the shell mold making composition. After removal of the wax, the portions ofthe ceramic material which had found their way into the holes formed posts which remained to hold the core in place. However, when the metal was cast around these ceramic posts, holes were left in the casting wall. These holes then had to be plugged with metal or otherwise removed.

Another method which has been tried involves the use of chaplets consisting of two discs of metal connected by a cylinder. The pattern material such as wax was injected around the chaplet, with one head of the chaplet contacting the core and the other head pressing against the mold wall. The chaplet was held in place by the pressure exerted against the two heads. The disadvantage of this method is that a relatively large mass of metal in the chaplet prevents fusion with the poured metal.

SUMMARY OF THE INVENTION The present invention provides a mold structure for producing hollow castings. The mold is built up by first forming a low melting pattern about a ceramic core, then inserting metal wires through the resulting pattern into engagement with the ceramic core while leaving exposed end portions on the wires.

A ceramic shell mold is then formed about the combination of core, pattern and wires, thereby anchoring the exposed end portions of the wires in the completed shell mold. When the pattern material is melted out, the metal wires remain anchored in the shell mold and provide lateral support for the core. Next, the molten metal is cast into the casting cavity provided by the removal of the pattern, thereby causing the portions of the wires which extended through the casting cavity to be fused within the molten metal and disappear, so that no imperfections remain in the body of the finished casting.

BRIEF DESCRIPTION OF THE DRAWING FIG. 1 is a view in elevation of a pattern having a core therein;

FIG. 2 is a cross-sectional view taken substantially along the line II-II of FIG. 1;

FIG. 3 is a view similar to FIG. 2 but illustrating the manner in which the wire pins are positioned through the pattern and against the core;

FIG. 4 is a view similar to FIG. 3 but illustrating the complete assembly resulting after the shell mold has been formed around the core and pattern;

FIG. 5 is a view similar to FIG. 4 but illustrating the elements of the assembly after the pattern material has been removed; and

FIG. 6 is a view similar to FIG. 5 but showing the mold assembly after casting and solidification of the metal, but prior to the removal of the core.

DESCRIPTION OF THE PREFERRED EMBODIMENTS In FIG. 1, reference numeral 10 indicates generally a relatively low melting pattern composed of wax, polystyrene or similar low melting pattern making material. The particular pattern shown in FIG. 1 is to be used for the manufacture of a turbine blade, the blade having an arcuate vane section 11, an upper shroud 12 and a relatively massive root portion 13. A gate forming portion 14 is also included on the pattern to provide the cavity through which molten metal may be introduced into the finished mold. While FIG. 1 is concerned, for purposes of simplicity, with a single pattern it should be recognized that the present invention can be used and usually will be used with clusters of patterns.

The pattern material has an internal core 15 composed of a ceramic material such as fused silica. Typically, the material of the pattern is injected about the ceramic core 15 in a conventional pattern making mold. The core 15 may be provided with upper and lower extensions 15a and 15b which serve to anchor the top and bottom of the core when the ceramic mold is formed about the core.

As illustrated in FIG. 3, a plurality of wire pins 16 is then positioned at selected locations along the length and breadth of the pattern, each of the pins 16 having an end portion 17 which passes through the pattern material and engages the surface of the ceramic core 15. In order to expedite insertion of the pin 16 through the pattern material, it is preferable to preheat the pin 16 slightly above the melting temperature of the wax or other pattern material so that only a minimum diameter hole is provided by the insertion of the pin 16 through the pattern material. In order to facilitate removal of the pin, it is desirable that the diameter of the pin 16 be kept very small, on the order of less than 0.050 inches, although this value can be increased for larger sizes of castings.

As also illustrated in FIG. 3, the opposed end portions 18 of the pin 16 extend beyond the pattern material by a matter of an eighth or a quarter inch or so to serve as anchoring means in the completed shell mold.

In order to avoid contamination of the melt with the metal of the pins 18 when they are fused therein, it is preferable that the pins be composed of the same metal as will be used for forming the ultimate casting.

As seen in FIG. 4, a shell mold 19 is then built up around the combination of the core 15, the pattern 10 and the pin 16.

There are a number of ways in which to build up a ceramic shell mold about a low melting pattern. Usually, the pattern assembly is dipped in a series of ceramic slurries, with intermediate drying, to a form a mold which, after firing, provides a relatively gas permeable ceramic structure of one-eighth to one-quarter inch or so in thickness.

A particularly preferred method of building up the ceramic shell mold involves dipping the pattern in an aqueous ceramic slurry having a' temperature about the same as that of the pattern material to form a refractory layer of a few mils in thickness. A typical slurry may contain ceramic material such as zirconium oxide, a binder such as colloidal silica and a thickener and low temperature binder such as methyl cellulose. The initial layer while still wet is then dusted with small particles (40 to 200 mesh) of a refractory glass composition such as that known as Vycor which is a finely divided, high (nun-n:

silicon oxide glass containing about 96 percent silica and a small amount of boric acid, together with traces of aluminum, sodium, iron and arsenic. The pattern with the dusted wet refractory layer on it is then suspended on a conveyor and moved to a drying oven having a controlled humidity and temperature, thereby drying the coated pattern adiabatically.

The steps of dipping, dusting and adiabatic drying are then repeated using air at progressively lower humidities for succeeding coats. For example, the first two coats can be dried with air having a relative humidity of 45 to 55 percent. The third and fourth coats can then be dried with a relative humidity of 35 to 45 percent, the fifth and sixth coats with a relative humidity of 25 to 30 percent, and the final coat with a relative humidity of to 25 percent.

The first layer is preferably applied to a thickness of 0.005 to 0.020 inches, and the fine refractory particles are dusted onto the wet layer with sufficient force to embed the particles therein. It is preferred that the dusting procedure used provide a dense uniform cloud of fine particles that strike the wet coating with substantial impact force. The force should not be so great, however, as to break or knock off the wet prime layer from the pattern. This process is repeated until a plurality of integrated layers is obtained, the thickness of the layers being about 0.005 to 0.020 inches.

After the mold is built up on the pattern material, the pattern can be removed by heat, and then the green mold is ready for firing. Generally, firing temperatures on the order of l,500 to 1,900 F. are used. The resulting shell molds are hard, smooth and relatively permeable.

The condition of the assembly after melt out of the pattern and firing of the mold is illustrated in FIG 5. It will be seen that the core 15 remains laterally supported within the casting cavity by virtue of the pins 16 which have become anchored in the ceramic shell mold.

FIG. 6 illustrates the assembly after the molten metal has been poured into the casting cavity 20 to provide a casting 21.

The molten metal which is usually superheated by a matter of several hundred degrees above its liquidus temperature before pouring, causes the portions of the pins 16 which had previously extended into the casting cavity to become fused therein while the end portions 18 of the pins remain anchored in the walls of the shell mold 19.

After solidification of the metal, the shell mold 1 9 is broken oh and the silica core 15 is removed as by dissolution in strong alkali solutions. The presence of the wires maintains the same distance between the core surface and the mold wall surface during wax removal, mold preheating, and during pouring of the metal into the mold. This prevents core movement and the resulting undersize wall thickness.

The process of the present invention was used to cast turbine blades from a nickel base superalloy. The pins employed were about 0.020 inches in diameter and extended for about one-eighth to one-quarter inch beyond the surface of the pattern. Consistently good results were obtained with respect to preventing core movement during the mold making and casting process as evidenced by the fact that the method was used on a 200 piece production run and resulted in a better than percent yield of good parts, whereas the same number of blades produced without the supporting wires yielded only about 10 percent good parts.

It should be evident that various modifications can be made to the described embodiments without departing from the scope of the present invention.

We claim as our invention:

1. A mold structure comprising a solid ceramic core, a one piece ceramic shell mold surrounding said core, and a plurality of thin metallic pins of uniform diameter anchored medially in the shell mold as a result of firing of a ceramic mold-making composition in the manufacture of such shell mold, the free ends of said pins extending into firm abutting engagement with said core to provide lateral support thereof.

Patent Citations
Cited PatentFiling datePublication dateApplicantTitle
US2096679 *Oct 28, 1935Oct 19, 1937Fanner Mfg CoChaplet
US3401738 *Feb 10, 1966Sep 17, 1968United Aircraft CorpCore location in precision casting
DE470283C *Jan 10, 1929Louis RettbergMit federnden Schenkeln versehene Kernstuetze
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US4283835 *Apr 2, 1980Aug 18, 1981United Technologies CorporationCambered core positioning for injection molding
US4487246 *Apr 12, 1982Dec 11, 1984Howmet Turbine Components CorporationSystem for locating cores in casting molds
US4596281 *Sep 2, 1982Jun 24, 1986Trw Inc.Mold core and method of forming internal passages in an airfoil
US4811778 *Apr 4, 1988Mar 14, 1989Rolls-Royce PlcMethod of manufacturing a metal article by the lost wax casting process
US4940074 *Jun 30, 1986Jul 10, 1990United Technologies CorporationCore pinning machine
US5505250 *Aug 19, 1994Apr 9, 1996Rolls-Royce PlcInvestment casting
US5545003 *Feb 25, 1994Aug 13, 1996Allison Engine Company, IncSingle-cast, high-temperature thin wall gas turbine component
US5641014 *Jun 7, 1995Jun 24, 1997Allison Engine CompanyMethod and apparatus for producing cast structures
US5810552 *Jun 7, 1995Sep 22, 1998Allison Engine Company, Inc.Single-cast, high-temperature, thin wall structures having a high thermal conductivity member connecting the walls and methods of making the same
US5924483 *Jul 18, 1997Jul 20, 1999Allison Engine Company, Inc.Single-cast, high-temperature thin wall structures having a high conductivity member connecting the walls and methods of making the same
US6071363 *Jun 3, 1996Jun 6, 2000Allison Engine Company, Inc.Single-cast, high-temperature, thin wall structures and methods of making the same
US6244327 *Dec 8, 1998Jun 12, 2001Allison Engine Company, Inc.Method of making single-cast, high-temperature thin wall structures having a high thermal conductivity member connecting the walls
US6255000Jun 7, 1995Jul 3, 2001Allison Engine Company, Inc.Single-cast, high-temperature, thin wall structures
US6464462Aug 8, 2001Oct 15, 2002General Electric CompanyGas turbine bucket wall thickness control
US6530416 *Mar 5, 1999Mar 11, 2003Siemens AktiengesellschaftMethod and device for producing a metallic hollow body
US7325587 *Aug 30, 2005Feb 5, 2008United Technologies CorporationMethod for casting cooling holes
US7913743Jun 12, 2008Mar 29, 2011Pcc Airfoils, Inc.Method of forming a pattern
CN101992268BNov 20, 2010Sep 5, 2012沈阳工业大学Preparation process of high-temperature alloy multigang hollow turbine blade
EP0072088A2 *May 24, 1982Feb 16, 1983ROLLS-ROYCE plcFoundry machinery
EP0251982A2 *Jun 25, 1987Jan 7, 1988United Technologies CorporationCore pinning machine
EP0559251A1 *Feb 4, 1993Sep 8, 1993General Motors CorporationSingle-cast, high-temperature thin wall structures and methods of making the same
EP0750956A2 *Feb 4, 1993Jan 2, 1997General Motors CorporationSingle-cast, high-temperature thin wall structures and methods of making the same
EP1053804A1 *May 20, 1999Nov 22, 2000Asea Brown Boveri AGChaplet
WO1994013415A1 *Dec 16, 1993Jun 23, 1994Gyoergy GalMethod of preparing a casting mould for precision casting
U.S. Classification164/366, 164/399
International ClassificationB22C9/04, B22C9/10, B22C21/14, B22C21/00
Cooperative ClassificationB22C9/10, B22C9/04, B22C21/14
European ClassificationB22C21/14, B22C9/04, B22C9/10