US3401738A - Core location in precision casting - Google Patents
Core location in precision casting Download PDFInfo
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- US3401738A US3401738A US526432A US52643266A US3401738A US 3401738 A US3401738 A US 3401738A US 526432 A US526432 A US 526432A US 52643266 A US52643266 A US 52643266A US 3401738 A US3401738 A US 3401738A
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- 238000005495 investment casting Methods 0.000 title description 6
- 238000005266 casting Methods 0.000 description 12
- 239000000463 material Substances 0.000 description 8
- 229910045601 alloy Inorganic materials 0.000 description 5
- 239000000956 alloy Substances 0.000 description 5
- 239000000945 filler Substances 0.000 description 4
- 238000010438 heat treatment Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 238000007711 solidification Methods 0.000 description 3
- 230000008023 solidification Effects 0.000 description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 3
- 238000001816 cooling Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 229910001092 metal group alloy Inorganic materials 0.000 description 2
- 239000002002 slurry Substances 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000007598 dipping method Methods 0.000 description 1
- 238000001035 drying Methods 0.000 description 1
- 229910002804 graphite Inorganic materials 0.000 description 1
- 239000010439 graphite Substances 0.000 description 1
- 238000002386 leaching Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
- B22D27/00—Treating the metal in the mould while it is molten or ductile ; Pressure or vacuum casting
- B22D27/04—Influencing the temperature of the metal, e.g. by heating or cooling the mould
- B22D27/045—Directionally solidified castings
-
- 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
Definitions
- This invention relates to a mold for investment casting of hollow articles and more particularly to elongated articles having one or more passages extending longitudinally therethrough from end-to-end of the article.
- a turbine blade or vane it is desirable for certain purposes to have the grains running in a direction longitudinally of the -portion of the blade over which the gas flow is directed.
- This ' may be accornplished by casting the article in a heated mold, one end of which is in engagement with a chill plate with the mold cavity opening directly into the plate.
- One feature of the invention is the support of the core adjacent to the chill plate such that the grain structure of the part is not afiected and such that the passages formed by the core will be precisely located within the article.
- Such cast articles when produced in this manner have a growth portion formed adjacent to the chill plate that is subsequently removed in forming the finished article ready for use.
- a feature of the invention is the location of the core supporting structure within this growth zone and outside of the finished article with the support so arranged as not to afiect the desired grain growth.
- FIG. 1 is a sectional view through a mold and the surrounding heating structure for casting a turbine blade.
- FIG. 2 is a fragmentary sectional view along the line 2-2 of FIG. 1.
- FIG. 3 is a transverse section along the line 3-3 of FIG. 2.
- FIG. 4 is a View similar to FIG. 3 showing a modification.
- FIG. 5 is a fragmertary sectional view of a modified mold for use in casting a turbine vane.
- FIG. 6 is a sectional view along the line 6-6 of FIG 5.
- FIG. 7 is a transverse sectional view along the line 7-7 of FIG. 6.
- the mold 10 is shown as made up of a plurality of individual mold elements 1011, 10b and 10c which in the particular arrangement shown are used for producing turbine blades.
- the mold is formed by the investment casting process and to accomplish this a pattern is provided in the usual way around which the 3,40l,738 Patented Sept. 17, 1968 "ice mold material is formed as by successively dipping and drying the pattern with coatings of suitable slurries in a well-known manner for making shell molds.
- the mold In forming the mold there is a pouring spout 12 which communicates with a top filler 14 for each of the blade patterns. Below the filler 14 is the airfoil section 16 of the blade and at the bottom of the airtoil section is the root portion 18. Communicating and over substantially the same dimension as the root portion is a growth portion 20, described in detail later.
- the wax pattern used in forming the mold supports a core element 22 for each of the blades. As best shown in FIG. 2, the core element includes a plurality of parallel small diameter rods 24, FIG. 2, interconnected by a top crossbar 26 and a bottom crossbar 28.
- the top bar is embedded in the mold material in the portion of the mold above the filler 14 and the bottom crossbar 28 is supported by inwardly extending mold projections 30 which support opposite ends of the crossbar and which, as shown in FIG. 1, are spaced from opposite side walls of the growth zone 20.
- the bars 24 may be of any desired cross section but in the arrangement shown they are relatvely fiat with curved opposite edges, as best shown in FIG. 3.
- the latter is mounted on a chill plate 32 to which the growth portion of the mold cavity is directly open.
- the chill plate 32 is preferably water cooled for the rapid removal of heat from the material when the desired metallic alloy has been poured into the mold.
- the mold is surrounded by :a cylindrical graphite susceptor 34 and the latter is surrounded by a plurality of heating coils 36 in aXially spaced relation to the susceptor. By selectively energizng these coils the entire mold may be heated to the desired temperature before any alloy is poured therein and the rate of cooling of the mold may be adjusted by suitable de-energizing of the coils.
- T o obtain the desired directional grain growth within the mold
- the entire mold is heated by the coils to a temperature of above that of the melting of the alloy and the chill plate is kept at a temperature of preferably below that of the boilng point of water by the circulation of water therethrough.
- the alloy begins to solidify upwardly from the chill plate and because of the directional solidification a grain growth is obtained such that from :a point above the top edge of the growth zone, represented by the dotted line 38, the growth is in parallel grains vertically located within the mold.
- a cap -40 may be placed on top of the mold after the alloy has been poured in order to retain heat at this end of the mold during the solidification process.
- the growth zone is removed by cutting the casting along the line 38 and the tip of the blade is cut off, for example, along the 'line 42 thereby removing the crossbars 26 and 28 and leaving a turbine blade element having passages extending longitudinally therethrough.
- the core materal will have been removed in 'any desired way, as 'by leaching.
- the core may be of different configurations dependent upon the shape of the passage desired.
- the airfoil section 16' of the blade has a hollow therein formed by a single core element 22' with grooves 23 on opposite side walls thereof to form a ridged inner wall surface on the blade, as will be apparent.
- the mold is used to produce a turbine vane having an airfoil portion 44, an inner shroud 46 and an outer shroud 48.
- the dotted line 50 represents material removed from the cast article to produce the finished shroud 46 and a similar dotted line 52 represents the portion of the cast article removed to form the outer shroud 48.
- the growth zone between the chill plate 54 and the finished portion of the cast article is that portion of the casting below the dotted line 56 which represents the approximate upper edge of the so-called growth zone.
- a wax pattern is arranged so that when it is successively and repeatedly dip ped in 'a slurry of mold material and dred, it will ⁇ be producing a top filler 58 communicating with the space 60 within the mold which is above and substantially coextensive with the inner shroud 464 Below the airfoil section 44 is the outer shroud 48 and the growth zone 62 is coexistence laterally therewith.
- the pattern supports a core 641, the upper end of which extends beyond the pattern itself and is therefore embedded in a portion 66 of the mold located vertically above the portion 60.
- the lower portion of the core is supported 'by a transverse core plug 68 which extends laterally from the core and is embedded in the mold material forming a portion of the boundary of the growth zone.
- the plug 68 which may extend laterally in both directions if desired for more secure support serves to support the lower end of the core with which it is integral in precise position within the airfoil portion of the mold after the pattern material has been melted out.
- the mold having .been completed and the pattern material having been melted out, the mold is positioned on a chill plate 70 in the same manner that the mold is placed on the chill plate of FIG. 1. After this is completed the heating structure for the mold is placed therearound, as in FIG. 1, and the casting procedure is carried out in the same manner.
- the growth zone which has been referred to above, is described in greater detail in the copending application of Sink, Ser. No. 472,530, filed July 16, 1965, having the same assignee as the present application.
- a heating a-rrangement and chill plate by which the mold is heated and by which the cooling of the mold is controlled is described in the application of Barrow et al., Ser. No. 472,644, filed July 16, 1965, and also having the same assignee as the present application.
- a mold for the production of cast hollow articles including, a shell having a main cavity corresponding substantially in shape to the article to be cast, and a core positioned within the cavity corresponding substantially in shape to the opening within the cast article, a filling space in the mold at one end of, and forming a Continuation of the main cavity, the end of the core extending beyond the filling space and being positioned in and supported by the mold, a cavity extension at the other end of the main cavity, and supporting elements extending laterally froni the mold into contact with the adjacent end portion of the core, the latter end portion being located within said cavity extension, the end of the cavity extension being open to be positioned on a chill plate, and the cavity extension providing a growth zone in the casting 'which is outside the dimensions of the finished article.
- a mold for the production of cast hollow articles which are directionally solidified by casting in a heated mold with one end of the casting against a chill plate, said mold including a shell having a main cavity corresponding in shape to the article, a filling cavity forming an extension at one end of the main cavity, and a growth zone cavity extension at the opposite end of the main cavity, the growth zone cavity extension having an open end for contact with the chill plate, and a core positioned within the cavities and extending from the filling cavity through the main cavity and into the growth zone to dene a space within the cast article, said core extending into and being supported by the portion of the mold defining the filling cavity, the other end of the core terminating within the growth zone cavity extension (short of the open end to be out of contact with the chill plate), said mold in this growth zone extension having inwardly extending elements to engage and support the end of the core to locate it within the growth zone.
- a mold as in claim 3 in which the temperature of the mold and the chill plate is so controlled as to produce directional grain growth from the growth zone to the filling cavity, and the core supporting elements are so positioned and 'have such a lateral dimension as not to afiect detrimentally the directional grain growth within the casting.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Molds, Cores, And Manufacturing Methods Thereof (AREA)
Description
Sept. 17, 1968 D. R. PARILL CORE LOCATION IN FRECISION CASTING 2 Sheets-Sheet 1 Filed Feb. lO, 1966 &401338 Sept. 17, '1968 D. R. PARILLE CORE LOCATION IN PRECISION CASTING 2 Sheets-Sheet 2 Filed Feb. 10. 1966 F/G. a
United States Patent O" 3,401,738 CORE LOCATION IN PRECISION CASTING Donald R. Parille, Wapping, Conn., assignor to United Aircraft Corporation, East Hartford, Conn., a corporation of Delaware Filed Feb. 10, 1966, Ser. No. 526,432 6 Claims. (Cl. 164-353) ABSTRACT OF THE DISCLOSURE An improved mold for investment casting hollow articles, wherein the core is supported, at the end adjacent to the chill plate, by lateral projections located in a growth zone separate from the finished article and where the core support is out of contact with the chill plate.
This invention relates to a mold for investment casting of hollow articles and more particularly to elongated articles having one or more passages extending longitudinally therethrough from end-to-end of the article.
One feature of the invention is an arrangement for supporting the core which forms the passages in the finished article in such a :manner within the mold that the cast article will have the desired gran structure within the portion of the cast article that becomes the finished part.
Cast parts -are being produced which use, for example, turbine vanes and blades in which by directional solidification the grains within the finished part extend in a particular direction. In a turbine blade or vane it is desirable for certain purposes to have the grains running in a direction longitudinally of the -portion of the blade over which the gas flow is directed. This 'may be accornplished by casting the article in a heated mold, one end of which is in engagement with a chill plate with the mold cavity opening directly into the plate. One feature of the invention is the support of the core adjacent to the chill plate such that the grain structure of the part is not afiected and such that the passages formed by the core will be precisely located within the article.
Such cast articles when produced in this manner have a growth portion formed adjacent to the chill plate that is subsequently removed in forming the finished article ready for use. A feature of the invention is the location of the core supporting structure within this growth zone and outside of the finished article with the support so arranged as not to afiect the desired grain growth.
Other features and advantages will be apparent from the specification and claims, and from the accompanying drawings which illustrate an embodiment of the invention.
FIG. 1 is a sectional view through a mold and the surrounding heating structure for casting a turbine blade.
FIG. 2 is a fragmentary sectional view along the line 2-2 of FIG. 1.
FIG. 3 is a transverse section along the line 3-3 of FIG. 2.
FIG. 4 is a View similar to FIG. 3 showing a modification.
FIG. 5 is a fragmertary sectional view of a modified mold for use in casting a turbine vane.
FIG. 6 is a sectional view along the line 6-6 of FIG 5.
FIG. 7 is a transverse sectional view along the line 7-7 of FIG. 6.
Referring first to FIG. 1, the mold 10 is shown as made up of a plurality of individual mold elements 1011, 10b and 10c which in the particular arrangement shown are used for producing turbine blades. The mold is formed by the investment casting process and to accomplish this a pattern is provided in the usual way around which the 3,40l,738 Patented Sept. 17, 1968 "ice mold material is formed as by successively dipping and drying the pattern with coatings of suitable slurries in a well-known manner for making shell molds.
In forming the mold there is a pouring spout 12 which communicates with a top filler 14 for each of the blade patterns. Below the filler 14 is the airfoil section 16 of the blade and at the bottom of the airtoil section is the root portion 18. Communicating and over substantially the same dimension as the root portion is a growth portion 20, described in detail later. The wax pattern used in forming the mold supports a core element 22 for each of the blades. As best shown in FIG. 2, the core element includes a plurality of parallel small diameter rods 24, FIG. 2, interconnected by a top crossbar 26 and a bottom crossbar 28. The top bar is embedded in the mold material in the portion of the mold above the filler 14 and the bottom crossbar 28 is supported by inwardly extending mold projections 30 which support opposite ends of the crossbar and which, as shown in FIG. 1, are spaced from opposite side walls of the growth zone 20. The bars 24 may be of any desired cross section but in the arrangement shown they are relatvely fiat with curved opposite edges, as best shown in FIG. 3.
After the -mold has been completed and the wax pattern has been melted out to produce a mold, as shown in FIG. 1, the latter is mounted on a chill plate 32 to which the growth portion of the mold cavity is directly open. The chill plate 32 is preferably water cooled for the rapid removal of heat from the material when the desired metallic alloy has been poured into the mold. The mold is surrounded by :a cylindrical graphite susceptor 34 and the latter is surrounded by a plurality of heating coils 36 in aXially spaced relation to the susceptor. By selectively energizng these coils the entire mold may be heated to the desired temperature before any alloy is poured therein and the rate of cooling of the mold may be adjusted by suitable de-energizing of the coils.
T o obtain the desired directional grain growth within the mold, the entire mold is heated by the coils to a temperature of above that of the melting of the alloy and the chill plate is kept at a temperature of preferably below that of the boilng point of water by the circulation of water therethrough. When a metallic alloy is poured into the mold cavity the alloy begins to solidify upwardly from the chill plate and because of the directional solidification a grain growth is obtained such that from :a point above the top edge of the growth zone, represented by the dotted line 38, the growth is in parallel grains vertically located within the mold. By selectively and successively de-energizing the coils beginning with the lowermost coil, the rate and thereby the directional growth of the grains is controlled to obtain the desired grain structure. A cap -40 may be placed on top of the mold after the alloy has been poured in order to retain heat at this end of the mold during the solidification process.
After the alloy is cooled within the mold the growth zone is removed by cutting the casting along the line 38 and the tip of the blade is cut off, for example, along the 'line 42 thereby removing the crossbars 26 and 28 and leaving a turbine blade element having passages extending longitudinally therethrough. Obviously, the core materal will have been removed in 'any desired way, as 'by leaching.
The core may be of different configurations dependent upon the shape of the passage desired. For example, as shown in FIG. 4, the airfoil section 16' of the blade has a hollow therein formed by a single core element 22' with grooves 23 on opposite side walls thereof to form a ridged inner wall surface on the blade, as will be apparent.
In the arrangement shown in FIGS. 5, 6 and 7, the mold is used to produce a turbine vane having an airfoil portion 44, an inner shroud 46 and an outer shroud 48. The dotted line 50 represents material removed from the cast article to produce the finished shroud 46 and a similar dotted line 52 represents the portion of the cast article removed to form the outer shroud 48. The growth zone between the chill plate 54 and the finished portion of the cast article is that portion of the casting below the dotted line 56 which represents the approximate upper edge of the so-called growth zone.
In this arrangement, a wax pattern is arranged so that when it is successively and repeatedly dip ped in 'a slurry of mold material and dred, it will `be producing a top filler 58 communicating with the space 60 within the mold which is above and substantially coextensive with the inner shroud 464 Below the airfoil section 44 is the outer shroud 48 and the growth zone 62 is coexistence laterally therewith. The pattern supports a core 641, the upper end of which extends beyond the pattern itself and is therefore embedded in a portion 66 of the mold located vertically above the portion 60. The lower portion of the core is supported 'by a transverse core plug 68 which extends laterally from the core and is embedded in the mold material forming a portion of the boundary of the growth zone. The plug 68 which may extend laterally in both directions if desired for more secure support serves to support the lower end of the core with which it is integral in precise position within the airfoil portion of the mold after the pattern material has been melted out. By locating the plug 68 below the upper limits of the growth zone, it will be clear that the lateral opening forming in the casting by the plug 68 is removed during the machining process that completes the vane.
In this arrangement, as in FIGS. 1, 2 and 3, the mold having .been completed and the pattern material having been melted out, the mold is positioned on a chill plate 70 in the same manner that the mold is placed on the chill plate of FIG. 1. After this is completed the heating structure for the mold is placed therearound, as in FIG. 1, and the casting procedure is carried out in the same manner.
The growth zone, which has been referred to above, is described in greater detail in the copending application of Sink, Ser. No. 472,530, filed July 16, 1965, having the same assignee as the present application. A heating a-rrangement and chill plate by which the mold is heated and by which the cooling of the mold is controlled is described in the application of Barrow et al., Ser. No. 472,644, filed July 16, 1965, and also having the same assignee as the present application.
It is to be understood that the invention is not limited to the specific embodiment herein illustrated and described but may be used in other ways without departure from its spirit as defined by the following claims.
The embodirnents of the invention in which an exclusive property or privilege is claimed are defined as follows:
1. A mold for the production of cast hollow articles including, a shell having a main cavity corresponding substantially in shape to the article to be cast, and a core positioned within the cavity corresponding substantially in shape to the opening within the cast article, a filling space in the mold at one end of, and forming a Continuation of the main cavity, the end of the core extending beyond the filling space and being positioned in and supported by the mold, a cavity extension at the other end of the main cavity, and supporting elements extending laterally froni the mold into contact with the adjacent end portion of the core, the latter end portion being located within said cavity extension, the end of the cavity extension being open to be positioned on a chill plate, and the cavity extension providing a growth zone in the casting 'which is outside the dimensions of the finished article.
2. A mold as in claim 1 in which the supporting elements are located in the growth zone.
3. A mold for the production of cast hollow articles which are directionally solidified by casting in a heated mold with one end of the casting against a chill plate, said mold including a shell having a main cavity corresponding in shape to the article, a filling cavity forming an extension at one end of the main cavity, and a growth zone cavity extension at the opposite end of the main cavity, the growth zone cavity extension having an open end for contact with the chill plate, and a core positioned within the cavities and extending from the filling cavity through the main cavity and into the growth zone to dene a space within the cast article, said core extending into and being supported by the portion of the mold defining the filling cavity, the other end of the core terminating within the growth zone cavity extension (short of the open end to be out of contact with the chill plate), said mold in this growth zone extension having inwardly extending elements to engage and support the end of the core to locate it within the growth zone.
4. A mold as in claim 3 in which the elements are located externally of the part of the cast article that is used as a finished part.
5. A mold as in claim 3 in which the lateral dimension of the extensions is such as not to interfere with the desired grain growth in the cast article.
6. A mold as in claim 3 in which the temperature of the mold and the chill plate is so controlled as to produce directional grain growth from the growth zone to the filling cavity, and the core supporting elements are so positioned and 'have such a lateral dimension as not to afiect detrimentally the directional grain growth within the casting.
References Cited UNITED STATES PATENTS 239,609 4/1881 Hartman 164-399 404,187 5/1889 Fisher 164-399 1,952,500 3/1934 Huetteman 164-368 2,651,823 9/ 1953 Hohlfelder 164 398 2,985,930 5/1961 Hohlfelder 164-398 3,233,294 2/1966 Carpousis et al 164-353X J. SPENCER OVERHOLSER, P'ma'yExam'ner.
E. MAR, Assistant Exam'ner.
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US526432A US3401738A (en) | 1966-02-10 | 1966-02-10 | Core location in precision casting |
Applications Claiming Priority (1)
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US526432A US3401738A (en) | 1966-02-10 | 1966-02-10 | Core location in precision casting |
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US3401738A true US3401738A (en) | 1968-09-17 |
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US526432A Expired - Lifetime US3401738A (en) | 1966-02-10 | 1966-02-10 | Core location in precision casting |
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Cited By (23)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3596703A (en) * | 1968-10-01 | 1971-08-03 | Trw Inc | Method of preventing core shift in casting articles |
US3620289A (en) * | 1968-08-05 | 1971-11-16 | United Aircraft Corp | Method for casting directionally solified articles |
US3659645A (en) * | 1965-08-09 | 1972-05-02 | Trw Inc | Means for supporting core in open ended shell mold |
US3662816A (en) * | 1968-10-01 | 1972-05-16 | Trw Inc | Means for preventing core shift in casting articles |
US3668389A (en) * | 1969-09-19 | 1972-06-06 | United Aircraft Corp | Photosensitive device comprising photoconductive and photovoltaic layers |
US3794100A (en) * | 1970-06-18 | 1974-02-26 | Cryomagnetics Corp | Method of making a billet suitable for manufacturing into a superconductor |
US3795978A (en) * | 1971-09-24 | 1974-03-12 | J Raymond | Method of fabricating a composite superconductor |
US3809147A (en) * | 1970-06-18 | 1974-05-07 | J Raymond | Method for making products suitable for use in forming composite superconductors |
US3818578A (en) * | 1970-06-18 | 1974-06-25 | Cyromagnetics Corp | Method of casting and working a billet having a plurality of openings therein |
US3957104A (en) * | 1974-02-27 | 1976-05-18 | The United States Of America As Represented By The Administrator Of The United States National Aeronautics And Space Administration | Method of making an apertured casting |
US4093017A (en) * | 1975-12-29 | 1978-06-06 | Sherwood Refractories, Inc. | Cores for investment casting process |
US4180119A (en) * | 1978-09-18 | 1979-12-25 | Howmet Turbine Components Corporation | Mold for directionally solidified single crystal castings and method for preparing same |
FR2524830A1 (en) * | 1982-04-12 | 1983-10-14 | Howmet Turbine Components | PROCESS FOR POSITIONING CORES IN MOLDS |
US4474224A (en) * | 1981-08-12 | 1984-10-02 | Rolls-Royce Limited | Foundry machinery |
US4596281A (en) * | 1982-09-02 | 1986-06-24 | Trw Inc. | Mold core and method of forming internal passages in an airfoil |
US4811778A (en) * | 1987-06-03 | 1989-03-14 | Rolls-Royce Plc | Method of manufacturing a metal article by the lost wax casting process |
US4913217A (en) * | 1989-01-23 | 1990-04-03 | Farley, Inc. | Locators for expendable core in die casting die |
US5505250A (en) * | 1993-08-23 | 1996-04-09 | Rolls-Royce Plc | Investment casting |
US5718278A (en) * | 1995-12-13 | 1998-02-17 | Baum; Robert | Method for producing hollow ring having inner round radius design |
US6467526B1 (en) | 2000-10-23 | 2002-10-22 | I.B. Goodman Manufacturing Co., Inc. | Method of making a jewelry ring in a vertical mold |
US20100200189A1 (en) * | 2009-02-12 | 2010-08-12 | General Electric Company | Method of fabricating turbine airfoils and tip structures therefor |
US20160158834A1 (en) * | 2013-07-31 | 2016-06-09 | United Technologies Corporation | Castings and Manufacture Methods |
US20190099803A1 (en) * | 2016-03-01 | 2019-04-04 | Safran Aircraft Engines | Core for casting a blade of a turbomachine |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US239609A (en) * | 1881-04-05 | hartman | ||
US404187A (en) * | 1889-05-28 | Chaplet for sand cores | ||
US1952500A (en) * | 1931-07-14 | 1934-03-27 | Hammer Bray Company | Mold for casting gas burners |
US2651823A (en) * | 1951-01-09 | 1953-09-15 | F Hohlfelder Company | Chaplet |
US2985930A (en) * | 1959-02-04 | 1961-05-30 | F Hohlfelder Company | Chaplets |
US3233294A (en) * | 1962-02-07 | 1966-02-08 | U S Magnet & Alloy Corp | Method and apparatus for casting vertically stacked magnet bodies |
-
1966
- 1966-02-10 US US526432A patent/US3401738A/en not_active Expired - Lifetime
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US239609A (en) * | 1881-04-05 | hartman | ||
US404187A (en) * | 1889-05-28 | Chaplet for sand cores | ||
US1952500A (en) * | 1931-07-14 | 1934-03-27 | Hammer Bray Company | Mold for casting gas burners |
US2651823A (en) * | 1951-01-09 | 1953-09-15 | F Hohlfelder Company | Chaplet |
US2985930A (en) * | 1959-02-04 | 1961-05-30 | F Hohlfelder Company | Chaplets |
US3233294A (en) * | 1962-02-07 | 1966-02-08 | U S Magnet & Alloy Corp | Method and apparatus for casting vertically stacked magnet bodies |
Cited By (30)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3659645A (en) * | 1965-08-09 | 1972-05-02 | Trw Inc | Means for supporting core in open ended shell mold |
US3620289A (en) * | 1968-08-05 | 1971-11-16 | United Aircraft Corp | Method for casting directionally solified articles |
US3662816A (en) * | 1968-10-01 | 1972-05-16 | Trw Inc | Means for preventing core shift in casting articles |
US3596703A (en) * | 1968-10-01 | 1971-08-03 | Trw Inc | Method of preventing core shift in casting articles |
US3668389A (en) * | 1969-09-19 | 1972-06-06 | United Aircraft Corp | Photosensitive device comprising photoconductive and photovoltaic layers |
US3818578A (en) * | 1970-06-18 | 1974-06-25 | Cyromagnetics Corp | Method of casting and working a billet having a plurality of openings therein |
US3794100A (en) * | 1970-06-18 | 1974-02-26 | Cryomagnetics Corp | Method of making a billet suitable for manufacturing into a superconductor |
US3809147A (en) * | 1970-06-18 | 1974-05-07 | J Raymond | Method for making products suitable for use in forming composite superconductors |
US3795978A (en) * | 1971-09-24 | 1974-03-12 | J Raymond | Method of fabricating a composite superconductor |
US3957104A (en) * | 1974-02-27 | 1976-05-18 | The United States Of America As Represented By The Administrator Of The United States National Aeronautics And Space Administration | Method of making an apertured casting |
US4093017A (en) * | 1975-12-29 | 1978-06-06 | Sherwood Refractories, Inc. | Cores for investment casting process |
US4180119A (en) * | 1978-09-18 | 1979-12-25 | Howmet Turbine Components Corporation | Mold for directionally solidified single crystal castings and method for preparing same |
US4474224A (en) * | 1981-08-12 | 1984-10-02 | Rolls-Royce Limited | Foundry machinery |
US4487246A (en) * | 1982-04-12 | 1984-12-11 | Howmet Turbine Components Corporation | System for locating cores in casting molds |
FR2524830A1 (en) * | 1982-04-12 | 1983-10-14 | Howmet Turbine Components | PROCESS FOR POSITIONING CORES IN MOLDS |
US4596281A (en) * | 1982-09-02 | 1986-06-24 | Trw Inc. | Mold core and method of forming internal passages in an airfoil |
US4811778A (en) * | 1987-06-03 | 1989-03-14 | Rolls-Royce Plc | Method of manufacturing a metal article by the lost wax casting process |
US4913217A (en) * | 1989-01-23 | 1990-04-03 | Farley, Inc. | Locators for expendable core in die casting die |
US5505250A (en) * | 1993-08-23 | 1996-04-09 | Rolls-Royce Plc | Investment casting |
US6032719A (en) * | 1995-12-13 | 2000-03-07 | Baum; Robert | Method for producing hollow jewelry ring |
US5916271A (en) * | 1995-12-13 | 1999-06-29 | Baum; Robert | Hollow jewelry ring having inner round design |
US5979537A (en) * | 1995-12-13 | 1999-11-09 | Baum; Robert | Wax replica and soluble core insert used for producing hollow jewelry ring |
US5718278A (en) * | 1995-12-13 | 1998-02-17 | Baum; Robert | Method for producing hollow ring having inner round radius design |
US6123141A (en) * | 1995-12-13 | 2000-09-26 | Baum; Robert | Method of forming a wax replica |
US6467526B1 (en) | 2000-10-23 | 2002-10-22 | I.B. Goodman Manufacturing Co., Inc. | Method of making a jewelry ring in a vertical mold |
US20100200189A1 (en) * | 2009-02-12 | 2010-08-12 | General Electric Company | Method of fabricating turbine airfoils and tip structures therefor |
US20160158834A1 (en) * | 2013-07-31 | 2016-06-09 | United Technologies Corporation | Castings and Manufacture Methods |
US9802248B2 (en) * | 2013-07-31 | 2017-10-31 | United Technologies Corporation | Castings and manufacture methods |
US20190099803A1 (en) * | 2016-03-01 | 2019-04-04 | Safran Aircraft Engines | Core for casting a blade of a turbomachine |
US10618106B2 (en) * | 2016-03-01 | 2020-04-14 | Safran Aircraft Engines | Core for casting a blade of a turbomachine |
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