US2679669A - Method of making hollow castings - Google Patents
Method of making hollow castings Download PDFInfo
- Publication number
- US2679669A US2679669A US116869A US11686949A US2679669A US 2679669 A US2679669 A US 2679669A US 116869 A US116869 A US 116869A US 11686949 A US11686949 A US 11686949A US 2679669 A US2679669 A US 2679669A
- Authority
- US
- United States
- Prior art keywords
- molybdenum
- casting
- bucket
- turbine
- passages
- 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.)
- Expired - Lifetime
Links
Images
Classifications
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/49336—Blade making
- Y10T29/49339—Hollow blade
- Y10T29/49341—Hollow blade with cooling passage
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/4981—Utilizing transitory attached element or associated separate material
Definitions
- the present invention relates to a method for making hollow castings.
- the present invention relates to a method for making turbine buckets, compressor blades, and the like, which have spaced air passages therethrough to provide cooling means for the bucket during the operation of the turbine engine.
- a turbine In turbo-jet engines, a turbine .operated by burning gases drives a blower furnishing air to the burners. Such turbines operate at very high temperatures, and it is, therefore, very desirable to provide suitable means for cooling the turbine buckets.
- An object of the present invention is to provide a method for manufacturing hollow castings having one or more void passages therein at predetermined positions.
- Another object of the invention is to provide a method of manufacturing turbine buckets having air passages through their vane portions.
- a further object of the invention is to provide a method for manufacturing passaged turbine buckets which controls depth, thickness,andtaper of the passage.
- a further object of the present invention is to provide turbine buckets, compressor vanes, and the like, having a high degree of resistance to thermal shock, a high resistance to corrosion, and having passages therethrough permitting the circulation of a cooling fluid.
- the present invention comprises a method for producing hollow castings having voids extending in predetermined relationship through the casting by forming a body of molybdenum, which may be molybdenum Wire, strip molybdenum or molybdenum tubes, into the configuration desired in the voids of the final casting, casting the body metal about the prearranged molybdenum body, and finally heating the resulting structure in an oxidizing atmosphere at a temperature suflficient to form molybdenum trioxide from the molybdenum.
- molybdenum is heated in air at a temperature of about 1,500 E, the trioxide of molybdenum is formed.
- molybdenum may be taken into solution in the body metal during casting
- means are provided within the scope of the invention for preventing such solution, these means comprising coating the molybdenum wire with a particular type of ceramic composition which protects the body metal during the period when the molybdenum trioxide is being volatilized and prevents such solution.
- molybdenum trioxide is a powerful oxidizing agent
- wire of a very small diameter may be provided within the body structure of the turbine bucket, so that upon volatilization, very fine diameter air passages result.
- the position of the ducts may be located precisely within the article.
- the ducts produced in the cast article may have any configuration and need not be continuous. For example, it may be desirable in some cases to provide tapered air passages which terminate inside the body structure itself. This type of structure is also easily produced by the practice of the present invention.
- the first step of the procedure consists in providing molybdenum wire, or strips, and forming the same into the configuration of the void passages which are to be produced in the finished turbine bucket. It is generally preferable to coat the molybdenum Wire with a ceramic composition to prevent the molybdenum from migrating into the body metal during theoxidization proce- Per cent Alumina 20 Silica 60 Calcium oxide 15 Boric oxide This glass composition and other similar glass compositions have the property of high resistance to thermal shock, and also have a coefiicient of thermal expansion which is close to that of molybdenum itself. In addition, the compositions show good adherence to molybdenum.
- the molybdenum wires in the network desired for the voids of the final bucket preferably are held in place by having their ends encased in a refractory ceramic block.
- This block serves not only to hold the molybdenum strands in correct alignment, but also may serve as a bottom closure for the subsequent molding steps.
- a pattern of a low-melting substance is produced about the molybdenum wire strands in the shape of the bucket which is to be cast around the strands.
- This low-melting substance is preferably wax, although substances such as mercury, lead, and other lowmelting metals or alloys may be used as well.
- the assembly is invested in an investment mold which is preferably a ceramic mold of the type commonly used in precision casting. There, the wax pattern is melted out and a suitable body metal is cast about the molybdenum network.
- the only qualification of a body metal limiting its use in the present invention is that it be able to withstand the temperatures in the vicinity of 1,500 F.
- Suitable alloys for casting turbine buckets are well known in the art as, for example, .Stellites, Vitallium alloys which are stainless alloys of cobalt, chromium and molybdenum and various cobalt base alloys containing chromium, tungsten, and carbon may also be used.
- the mold is removed.
- a corrosion-resistant coating to protect the same during the subsequent oxidization step.
- Three eminently suitable materials for coating purposes in this connection are silicon, aluminum and zirconium. These coatings have the ability to form strongly adhering, corrosion-resistant about the bucket body.
- the assembly comprising the cast turbine bucket body containing the molybdenum wire is subjected to an oxidization operation for a time and at a temperature suificient to form molybdenum trioxide from the molybdenum wire and to volatilize the molybdenum trioxide.
- a temperature suificient to form molybdenum trioxide from the molybdenum wire and to volatilize the molybdenum trioxide Normally, temperatures of 1,500 F. and above, will be employed during this step. The upper limit for this oxidizing temperature is fixed by the temperature at which deterioration of the properties of the body metal begins to occur.
- oxygen or water vapor may be added to an air atmosphere during this treatment.
- any ceramic material which was added as a protection to the body metal may be removed from the void passages formed in the body by simply shaking the article until the ceramic material drops out.
- the bucket at this stage will have air passages therethrough corresponding to the positions of the original molybdenum wire.
- the cast bucket can then be. conveniently machined or brought down to finished dimensions, if necessary.
- the above procedure may be modified by substituting hollow molybdenum tubes for the molybdenum wire. Since molybdenum has a rather low coefficient of expansion, there is a possibility that the molybdenum tubes will buckle during casting. To overcome this, and provide internal support against the pressure of the liquid metal durin pouring, the tubes may be filled with a loosely compacted ceramic material of the type indicated above, which may be completely forced out of the passages after the casting procedure.
- Figure 1 is a view in perspective of the molybdenum wire network as originally formed
- Figure 2 is a perspective view of the assembly after the wax pattern has been formed thereon;
- Figure 3 is a cross-sectional plan vieu of a ceramic mold assembly containing the molybdenum wire network
- Figure 4 is a perspective view, with parts broken away, to show the internal void passages of a cast turbine bucket.
- Figure 5 is a cross-sectional view taken substantially along the line VV of Figure 4.
- the first step of the procedure is to form a network of individual molybdenum wires H] in the alignment desired for the 5 air ducts to be formed in the turbine bucket.
- the ends ofthe individual wires it! are anchored in a refractory ceramic block II in their proper alignment.
- the individual molybdenum wires H) are preferably slightly longer than the actual length of the air ducts to be formed so that the wire ends can be anchored in the mold.
- the next step is to cast a low-melting pattern about the network of molybdenum wires l0, and such a pattern is illustrated in Figure 2. It will be seen that this pattern comprises a vane portion l2 and a base or root portion l3.
- the assembly shown in Figure 2 is invested in a ceramic investment mold [4.
- the wax or other low-melting material is melted out, leaving the individual wires Ill supported within the ceramic mold [4 by the refractory ceramic block H which can also serve as a bottom closure for the mold it. If the ends of the wires project beyond the pattern they will be anchored in the mold.
- a suitable body metal is next cast around the molybdenum network. After the casting has set, the entire casting is submitted to an oxidation treatment described previously where the molybdenum is removed from the body metal by sublimation. Prior to the oxidation procedure, the ceramic block H is trimmed from the assembly. The oxidation step thus leaves a bucket body I5 on a base I6 and having air passages ll extending through the base portion l6 and into the leading and trailing edges of the vane portion of the turbine bucket.
- compressed air may be forced through the passages [7, thus cooling the interior of the bucket body as well as the leading and trailing edges.
- the method of manufacturing castings having void passages therethrough in predetermined configuration which comprises forming a molybdenum core coated with a ceramic material into a network having the configuration required in the void passages, casting a heat-resistant body metal about the coated core, heating the assembly with the molybdenum core exposed in an oxidizing atmosphere to a temperature sufficient to oxidize the molybdenum into molybdenum trioxide and to volatilize the molybdenum trioxide formed, and subsequently removing said ceramic material from the body metal.
- the method of making castings having void passages therethrough in a predetermined configuration which comprises forming molybdenum wire having a coating comprising vitrified calcium sages, casting a heat-resistant body metal about the molybdenum network, heating the assembly and exposing said wire to an oxidizing atmosphere of a temperature sufiicient to oxidize the molybdenum into molybdenum trioxide and to volatilize the molybdenum trioxide formed, and subsequently removing said vitrified silicates from the body metal.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
June 1, 1954 R. A. KEMPE METHOD OF MAKING HOLLOW CASTINGS Filed Sept. 21, 1949 fZZVEZ-ZLUI" fioberefi. K 8122 03 MW 111L155 Patented June 1, 1954 METHOD OF MAKING HOLLOW CASTINGS Robert A. Kempe, Cleveland, Ohio, assignor to Thompson Products, Inc., Cleveland, Ohio, a
corporation of Ohio Application September 21, 1949, Serial No. 116,869
2 Claims. 1
The present invention relates to a method for making hollow castings.
More particularly, the present invention relates to a method for making turbine buckets, compressor blades, and the like, which have spaced air passages therethrough to provide cooling means for the bucket during the operation of the turbine engine.
In turbo-jet engines, a turbine .operated by burning gases drives a blower furnishing air to the burners. Such turbines operate at very high temperatures, and it is, therefore, very desirable to provide suitable means for cooling the turbine buckets.
An object of the present invention is to provide a method for manufacturing hollow castings having one or more void passages therein at predetermined positions.
Another object of the invention is to provide a method of manufacturing turbine buckets having air passages through their vane portions.
A further object of the invention is to provide a method for manufacturing passaged turbine buckets which controls depth, thickness,andtaper of the passage.
A further object of the present invention is to provide turbine buckets, compressor vanes, and the like, having a high degree of resistance to thermal shock, a high resistance to corrosion, and having passages therethrough permitting the circulation of a cooling fluid.
In essence, the present invention comprises a method for producing hollow castings having voids extending in predetermined relationship through the casting by forming a body of molybdenum, which may be molybdenum Wire, strip molybdenum or molybdenum tubes, into the configuration desired in the voids of the final casting, casting the body metal about the prearranged molybdenum body, and finally heating the resulting structure in an oxidizing atmosphere at a temperature suflficient to form molybdenum trioxide from the molybdenum. When molybdenum is heated in air at a temperature of about 1,500 E, the trioxide of molybdenum is formed. This trioxide sublimes so that the oxide is volatilized almost immediately upon formation, resulting in the disintegration of the molybdenum. It is this characteristic of molybdenum that I employ to remove the molybdenum from the body metal, thus leaving voids in the structure corresponding to the position of the original molybdenum network.
Since, under certain conditions, molybdenum may be taken into solution in the body metal during casting, means are provided within the scope of the invention for preventing such solution, these means comprising coating the molybdenum wire with a particular type of ceramic composition which protects the body metal during the period when the molybdenum trioxide is being volatilized and prevents such solution.
In addition, since molybdenum trioxide is a powerful oxidizing agent, I have provided means for protecting the outer surfaces of the body metal during the time when the molybdenum trioxide is being volatilized from the body metal.
The advantages of the presently proposed process are many fold. For one, extremely fine ducts may be formed in the turbine bucket. Since molybdenum is quite malleable, molybdenum.-
wire of a very small diameter may be provided within the body structure of the turbine bucket, so that upon volatilization, very fine diameter air passages result.
In addition, another important advantage of the present procedure is that the position of the ducts may be located precisely within the article. By providing cooling ducts parallel to and quite close to the leading edge of a turbine bucket, the tendency of the bucket to overheat along its leading edge is substantially reduced.
Another advantage of the method herein proposed lies in the fact that the ducts produced in the cast article may have any configuration and need not be continuous. For example, it may be desirable in some cases to provide tapered air passages which terminate inside the body structure itself. This type of structure is also easily produced by the practice of the present invention.
The complete process for the production of a turbine bucket using the principles of the present invention will be presently described, but it will be appreciated by those skilled in the art that the invention is in no way restricted to the production of such turbine buckets or other parts for gas turbine engines, but will find general applicability in casting procedures wherein it is desired to produce hollow castings having one or more void passages therein of predetermined length and position.
The first step of the procedure consists in providing molybdenum wire, or strips, and forming the same into the configuration of the void passages which are to be produced in the finished turbine bucket. It is generally preferable to coat the molybdenum Wire with a ceramic composition to prevent the molybdenum from migrating into the body metal during theoxidization proce- Per cent Alumina 20 Silica 60 Calcium oxide 15 Boric oxide This glass composition and other similar glass compositions have the property of high resistance to thermal shock, and also have a coefiicient of thermal expansion which is close to that of molybdenum itself. In addition, the compositions show good adherence to molybdenum.
The molybdenum wires in the network desired for the voids of the final bucket preferably are held in place by having their ends encased in a refractory ceramic block. This block serves not only to hold the molybdenum strands in correct alignment, but also may serve as a bottom closure for the subsequent molding steps.
After arranging the molybdenum wire in the proper configuration, a pattern of a low-melting substance is produced about the molybdenum wire strands in the shape of the bucket which is to be cast around the strands. This low-melting substance is preferably wax, although substances such as mercury, lead, and other lowmelting metals or alloys may be used as well. After the low-melting pattern has been set, the assembly is invested in an investment mold which is preferably a ceramic mold of the type commonly used in precision casting. There, the wax pattern is melted out and a suitable body metal is cast about the molybdenum network. The only qualification of a body metal limiting its use in the present invention is that it be able to withstand the temperatures in the vicinity of 1,500 F. wihout substantial corrosion or without substantial loss of hot strength. Suitable alloys for casting turbine buckets are well known in the art as, for example, .Stellites, Vitallium alloys which are stainless alloys of cobalt, chromium and molybdenum and various cobalt base alloys containing chromium, tungsten, and carbon may also be used.
After the bucket has been cast about the molybdenum network, the mold is removed. At this stage, it is often desirable to provide the outer surface of the turbine bucket body with a corrosion-resistant coating to protect the same during the subsequent oxidization step. Three eminently suitable materials for coating purposes in this connection are silicon, aluminum and zirconium. These coatings have the ability to form strongly adhering, corrosion-resistant about the bucket body.
After the casting procedure, the assembly comprising the cast turbine bucket body containing the molybdenum wire is subjected to an oxidization operation for a time and at a temperature suificient to form molybdenum trioxide from the molybdenum wire and to volatilize the molybdenum trioxide. Normally, temperatures of 1,500 F. and above, will be employed during this step. The upper limit for this oxidizing temperature is fixed by the temperature at which deterioration of the properties of the body metal begins to occur. To make the atmosphere more strong- 4 1y oxidizing, oxygen or water vapor may be added to an air atmosphere during this treatment.
After the molybdenum has been completely removed by volatilization, any ceramic material which was added as a protection to the body metal may be removed from the void passages formed in the body by simply shaking the article until the ceramic material drops out.
The bucket at this stage will have air passages therethrough corresponding to the positions of the original molybdenum wire. The cast bucket can then be. conveniently machined or brought down to finished dimensions, if necessary.
Where it is desired to make relatively large hollow passages within a cast article, the above procedure may be modified by substituting hollow molybdenum tubes for the molybdenum wire. Since molybdenum has a rather low coefficient of expansion, there is a possibility that the molybdenum tubes will buckle during casting. To overcome this, and provide internal support against the pressure of the liquid metal durin pouring, the tubes may be filled with a loosely compacted ceramic material of the type indicated above, which may be completely forced out of the passages after the casting procedure.
The procedure described above is illustrated in the drawing, in which:
Figure 1 is a view in perspective of the molybdenum wire network as originally formed;
Figure 2 is a perspective view of the assembly after the wax pattern has been formed thereon;
Figure 3 is a cross-sectional plan vieu of a ceramic mold assembly containing the molybdenum wire network;
Figure 4 is a perspective view, with parts broken away, to show the internal void passages of a cast turbine bucket; and
Figure 5 is a cross-sectional view taken substantially along the line VV of Figure 4.
As shown on the drawing:
As shown in Figure 1, the first step of the procedure is to form a network of individual molybdenum wires H] in the alignment desired for the 5 air ducts to be formed in the turbine bucket.
The ends ofthe individual wires it! are anchored in a refractory ceramic block II in their proper alignment. The individual molybdenum wires H) are preferably slightly longer than the actual length of the air ducts to be formed so that the wire ends can be anchored in the mold.
The next step is to cast a low-melting pattern about the network of molybdenum wires l0, and such a pattern is illustrated in Figure 2. It will be seen that this pattern comprises a vane portion l2 and a base or root portion l3. Next, the assembly shown in Figure 2 is invested in a ceramic investment mold [4. Here, the wax or other low-melting material is melted out, leaving the individual wires Ill supported within the ceramic mold [4 by the refractory ceramic block H which can also serve as a bottom closure for the mold it. If the ends of the wires project beyond the pattern they will be anchored in the mold.
A suitable body metal is next cast around the molybdenum network. After the casting has set, the entire casting is submitted to an oxidation treatment described previously where the molybdenum is removed from the body metal by sublimation. Prior to the oxidation procedure, the ceramic block H is trimmed from the assembly. The oxidation step thus leaves a bucket body I5 on a base I6 and having air passages ll extending through the base portion l6 and into the leading and trailing edges of the vane portion of the turbine bucket. Thus, when the turbine bucket is mounted in the turbine assembly, compressed air may be forced through the passages [7, thus cooling the interior of the bucket body as well as the leading and trailing edges.
From the foregoing, it will be apparent that I have herein provided a method for producing hollow castings, and more particularly, a method for providing air passages within the body structure of a turbine bucket. The procedure given above is adaptable to a large variety of precision casting methods where it is desired to provide a casting with void passages of definite configuration, size and shape.
It will be understood that modifications and variations may be effected without departing from the scope of the novel concept of the present invention.
I claim as my invention:
1. The method of manufacturing castings having void passages therethrough in predetermined configuration which comprises forming a molybdenum core coated with a ceramic material into a network having the configuration required in the void passages, casting a heat-resistant body metal about the coated core, heating the assembly with the molybdenum core exposed in an oxidizing atmosphere to a temperature sufficient to oxidize the molybdenum into molybdenum trioxide and to volatilize the molybdenum trioxide formed, and subsequently removing said ceramic material from the body metal.
2. The method of making castings having void passages therethrough in a predetermined configuration which comprises forming molybdenum wire having a coating comprising vitrified calcium sages, casting a heat-resistant body metal about the molybdenum network, heating the assembly and exposing said wire to an oxidizing atmosphere of a temperature sufiicient to oxidize the molybdenum into molybdenum trioxide and to volatilize the molybdenum trioxide formed, and subsequently removing said vitrified silicates from the body metal.
References Cited in the file of this patent UNITED STATES PATENTS Number Name Date 1,416,412 Pack May 16, 1922 1,465,472 Hansen Aug. 21, 1923 1,544,930 Pack July 7, 1925 1,710,534 Field Apr. 23, 1929 1,988,861 Thorausch et a1. Jan. 22, 1935 2,074,007 Wissler Mar. 16, 1937 2,085,324 Linclner June 29, 1937 2,204,123 Collins June 11, 1940 2,362,507 Steinbock et al. Nov. 14, 1944 2,362,875 Zahn Nov. 14, 1944 2,368,295 Goran Jan. 30, 1945 2,368,296 Goran Jan. 30, 1945 2,373,405 Lowit Apr. 10, 1945 2,388,299 Thielemann Nov. 6, 1945 2,499,977 Scott Mar, 7, 1950 2,510,735 Badger June 6, 1950 FOREIGN PATENTS Number Country Date 588,113 Great Britain May 14, 1947 608,766 Great Britain Sept. 21, 1948 238,186 Switzerland Nov. 1, 1945 245,674 Germany Apr. 15, 1912 OTHER REFERENCES Metal Progress, May 1948, vol. 53, page 684.
Claims (1)
1. THE METHOD OF MANUFACTURING CASTINGS HAVING VOID PASSAGES THERETHROUGH IN PREDETERMINED CONFIGURATION WHICH COMPRISES FORMING A MOLYBDENUM CORE COATED WITH A CERAMIC MATERIAL INTO A NETWORK HAVING THE CONFIGURATION REQUIRED IN THE VOID PASSAGES, CASTING A HEAT-RESISTANT BODY METAL ABOUT THE COATED CORE, HEATING THE ASSEMBLY WITH THE MOLYBDENUM CORE EXPOSED IN AN OXIDIZING ATMOSPHERE TO A TEMPERATURE SUFFICIENT
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US116869A US2679669A (en) | 1949-09-21 | 1949-09-21 | Method of making hollow castings |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US116869A US2679669A (en) | 1949-09-21 | 1949-09-21 | Method of making hollow castings |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US2679669A true US2679669A (en) | 1954-06-01 |
Family
ID=22369730
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US116869A Expired - Lifetime US2679669A (en) | 1949-09-21 | 1949-09-21 | Method of making hollow castings |
Country Status (1)
| Country | Link |
|---|---|
| US (1) | US2679669A (en) |
Cited By (33)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2802372A (en) * | 1955-08-19 | 1957-08-13 | James A Hatch | Cast worm wheel and method and apparatus for manufacturing the same |
| US2844855A (en) * | 1953-11-05 | 1958-07-29 | Bristol Aero Engines Ltd | Method of producing castings with one or more internal passages |
| US2866618A (en) * | 1953-02-13 | 1958-12-30 | Thomas W Jackson | Reverse flow air cooled turbine blade |
| US2872715A (en) * | 1954-10-22 | 1959-02-10 | Morris Bean And Company | Method of casting metal around sheet metal inserts |
| US2895191A (en) * | 1955-07-11 | 1959-07-21 | Hills Mccanna Co | Method of and apparatus for precision coring in the casting of metallic articles |
| US2981989A (en) * | 1955-08-19 | 1961-05-02 | James A Hatch | Method and apparatus for manufacturing a cast worm wheel |
| US2989801A (en) * | 1958-02-12 | 1961-06-27 | Lear Inc | Electrical contact assembly and process of manufacture |
| US3017159A (en) * | 1956-11-23 | 1962-01-16 | Curtiss Wright Corp | Hollow blade construction |
| US3028661A (en) * | 1956-09-03 | 1962-04-10 | Int Nickel Co | Manufacture of turbine or compressor blades |
| US3029485A (en) * | 1959-01-14 | 1962-04-17 | Gen Motors Corp | Method of making hollow castings |
| US3109745A (en) * | 1960-06-01 | 1963-11-05 | Union Carbide Corp | Cerium monosulfide articles, method of making same, and composition thereform |
| US3142875A (en) * | 1961-04-06 | 1964-08-04 | Howe Sound Co | Metal casting cores |
| US3273210A (en) * | 1963-11-07 | 1966-09-20 | Taccone Corp | Machine for removing molds from flasks |
| US3314875A (en) * | 1962-07-24 | 1967-04-18 | Gen Electric | Electrode holder |
| US3452804A (en) * | 1965-12-02 | 1969-07-01 | Edward J Mellen | Method of making a permeable shell mold |
| US3707750A (en) * | 1968-11-14 | 1973-01-02 | Mtu Muenchen Gmbh | Method for manufacturing a turbine blade |
| 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 |
| FR2426511A1 (en) * | 1978-05-24 | 1979-12-21 | Trw Inc | PROCESS FOR FORMING A CASTING MOLD WITH INTERNAL CORE |
| US4418124A (en) * | 1980-10-06 | 1983-11-29 | General Electric Company | Plasma spray-cast components |
| US4418455A (en) * | 1981-05-04 | 1983-12-06 | Electric Power Research Institute, Inc. | Method of manufacturing a fluid cooled blade or vane |
| US4422229A (en) * | 1979-02-24 | 1983-12-27 | Rolls-Royce Limited | Method of making an airfoil member for a gas turbine engine |
| US4440834A (en) * | 1980-05-28 | 1984-04-03 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation, S.N.E.C.M.A. | Process for the manufacture of turbine blades cooled by means of a porous body and product obtained by the process |
| US4631092A (en) * | 1984-10-18 | 1986-12-23 | The Garrett Corporation | Method for heat treating cast titanium articles to improve their mechanical properties |
| US4726104A (en) * | 1986-11-20 | 1988-02-23 | United Technologies Corporation | Methods for weld repairing hollow, air cooled turbine blades and vanes |
| US20050002786A1 (en) * | 2003-05-27 | 2005-01-06 | Snecma Moteurs | Hollow fan blade for turbine engine and method of manufacturing such a blade |
| US20070056709A1 (en) * | 2005-09-13 | 2007-03-15 | United Technologies Corporation | Method for casting core removal |
| US20090028707A1 (en) * | 2007-07-26 | 2009-01-29 | United Technologies Corporation | Apparatus and method for repairing airfoil tips |
| US20090114797A1 (en) * | 2003-10-15 | 2009-05-07 | Beals James T | Refractory metal core coatings |
| US20150040570A1 (en) * | 2013-03-03 | 2015-02-12 | Rolls-Royce North American Technologies, Inc. | Gas turbine engine component having foam core and composite skin with cooling slot |
| US20150167493A1 (en) * | 2013-12-18 | 2015-06-18 | General Electric Company | Turbine bucket and method for cooling a turbine bucket of a gas turbine engine |
| US20160061043A1 (en) * | 2014-09-03 | 2016-03-03 | General Electric Company | Turbine bucket |
| US20170051613A1 (en) * | 2015-08-17 | 2017-02-23 | United Technologies Corporation | Cupped contour for gas turbine engine blade assembly |
| US20170246678A1 (en) * | 2016-02-29 | 2017-08-31 | General Electric Company | Casting with first metal components and second metal components |
Citations (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE245674C (en) * | ||||
| US1416412A (en) * | 1921-02-25 | 1922-05-16 | Doehler Die Casting Co | Die-casting process |
| US1465472A (en) * | 1922-04-06 | 1923-08-21 | Thomas C Hansen | Method of making crowns and forms therefor |
| US1544930A (en) * | 1922-12-01 | 1925-07-07 | Doehler Die Casting Co | Method of casting |
| US1710534A (en) * | 1926-09-02 | 1929-04-23 | Wheeling Mold & Foundry Compan | Process for casting hollow bodies |
| US1988861A (en) * | 1929-02-23 | 1935-01-22 | Ig Farbenindustrie Ag | Production of metallic plates suitable for use as accumulator electrodes |
| US2074007A (en) * | 1934-08-03 | 1937-03-16 | Union Carbide & Carbon Corp | Method of making articles of cobaltchromium-tungsten alloys |
| US2085324A (en) * | 1934-09-05 | 1937-06-29 | American Smelting Refining | Metal mold |
| US2204123A (en) * | 1938-01-05 | 1940-06-11 | Columbus Dental Mfg Co | Pattern for castings |
| US2362507A (en) * | 1942-10-27 | 1944-11-14 | Steinbock | Method and means for producing commercial castings |
| US2362875A (en) * | 1943-06-03 | 1944-11-14 | Austenal Lab Inc | Casting procedure |
| US2368295A (en) * | 1942-09-14 | 1945-01-30 | Allis Louis Co | Method of making cast squirrel cage rotors |
| US2368296A (en) * | 1943-10-29 | 1945-01-30 | Allis Louis Co | Rotor construction |
| US2373405A (en) * | 1941-02-14 | 1945-04-10 | Callite Tungsten Corp | Process of making seamless hollow bodies of refractory metals |
| CH238186A (en) * | 1943-07-22 | 1945-06-30 | Schweizerische Lokomotiv | Process for the production of cavities in the interior of castings. |
| US2388299A (en) * | 1943-09-27 | 1945-11-06 | Gen Electric | Method of fabricating molds |
| GB588113A (en) * | 1944-12-27 | 1947-05-14 | Peglers Ltd | Improvements in, or relating to, die-casting of non-ferrous metals |
| GB608766A (en) * | 1944-12-01 | 1948-09-21 | Bbc Brown Boveri & Cie | Improvements in turbine blades |
| US2499977A (en) * | 1943-11-03 | 1950-03-07 | Gen Electric | Method of forming grid-like structures |
| US2510735A (en) * | 1946-04-10 | 1950-06-06 | United Aircraft Corp | Turbine element |
-
1949
- 1949-09-21 US US116869A patent/US2679669A/en not_active Expired - Lifetime
Patent Citations (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE245674C (en) * | ||||
| US1416412A (en) * | 1921-02-25 | 1922-05-16 | Doehler Die Casting Co | Die-casting process |
| US1465472A (en) * | 1922-04-06 | 1923-08-21 | Thomas C Hansen | Method of making crowns and forms therefor |
| US1544930A (en) * | 1922-12-01 | 1925-07-07 | Doehler Die Casting Co | Method of casting |
| US1710534A (en) * | 1926-09-02 | 1929-04-23 | Wheeling Mold & Foundry Compan | Process for casting hollow bodies |
| US1988861A (en) * | 1929-02-23 | 1935-01-22 | Ig Farbenindustrie Ag | Production of metallic plates suitable for use as accumulator electrodes |
| US2074007A (en) * | 1934-08-03 | 1937-03-16 | Union Carbide & Carbon Corp | Method of making articles of cobaltchromium-tungsten alloys |
| US2085324A (en) * | 1934-09-05 | 1937-06-29 | American Smelting Refining | Metal mold |
| US2204123A (en) * | 1938-01-05 | 1940-06-11 | Columbus Dental Mfg Co | Pattern for castings |
| US2373405A (en) * | 1941-02-14 | 1945-04-10 | Callite Tungsten Corp | Process of making seamless hollow bodies of refractory metals |
| US2368295A (en) * | 1942-09-14 | 1945-01-30 | Allis Louis Co | Method of making cast squirrel cage rotors |
| US2362507A (en) * | 1942-10-27 | 1944-11-14 | Steinbock | Method and means for producing commercial castings |
| US2362875A (en) * | 1943-06-03 | 1944-11-14 | Austenal Lab Inc | Casting procedure |
| CH238186A (en) * | 1943-07-22 | 1945-06-30 | Schweizerische Lokomotiv | Process for the production of cavities in the interior of castings. |
| US2388299A (en) * | 1943-09-27 | 1945-11-06 | Gen Electric | Method of fabricating molds |
| US2368296A (en) * | 1943-10-29 | 1945-01-30 | Allis Louis Co | Rotor construction |
| US2499977A (en) * | 1943-11-03 | 1950-03-07 | Gen Electric | Method of forming grid-like structures |
| GB608766A (en) * | 1944-12-01 | 1948-09-21 | Bbc Brown Boveri & Cie | Improvements in turbine blades |
| GB588113A (en) * | 1944-12-27 | 1947-05-14 | Peglers Ltd | Improvements in, or relating to, die-casting of non-ferrous metals |
| US2510735A (en) * | 1946-04-10 | 1950-06-06 | United Aircraft Corp | Turbine element |
Cited By (42)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2866618A (en) * | 1953-02-13 | 1958-12-30 | Thomas W Jackson | Reverse flow air cooled turbine blade |
| US2844855A (en) * | 1953-11-05 | 1958-07-29 | Bristol Aero Engines Ltd | Method of producing castings with one or more internal passages |
| US2872715A (en) * | 1954-10-22 | 1959-02-10 | Morris Bean And Company | Method of casting metal around sheet metal inserts |
| US2895191A (en) * | 1955-07-11 | 1959-07-21 | Hills Mccanna Co | Method of and apparatus for precision coring in the casting of metallic articles |
| US2802372A (en) * | 1955-08-19 | 1957-08-13 | James A Hatch | Cast worm wheel and method and apparatus for manufacturing the same |
| US2981989A (en) * | 1955-08-19 | 1961-05-02 | James A Hatch | Method and apparatus for manufacturing a cast worm wheel |
| US3028661A (en) * | 1956-09-03 | 1962-04-10 | Int Nickel Co | Manufacture of turbine or compressor blades |
| US3017159A (en) * | 1956-11-23 | 1962-01-16 | Curtiss Wright Corp | Hollow blade construction |
| US2989801A (en) * | 1958-02-12 | 1961-06-27 | Lear Inc | Electrical contact assembly and process of manufacture |
| US3029485A (en) * | 1959-01-14 | 1962-04-17 | Gen Motors Corp | Method of making hollow castings |
| US3109745A (en) * | 1960-06-01 | 1963-11-05 | Union Carbide Corp | Cerium monosulfide articles, method of making same, and composition thereform |
| US3142875A (en) * | 1961-04-06 | 1964-08-04 | Howe Sound Co | Metal casting cores |
| US3314875A (en) * | 1962-07-24 | 1967-04-18 | Gen Electric | Electrode holder |
| US3273210A (en) * | 1963-11-07 | 1966-09-20 | Taccone Corp | Machine for removing molds from flasks |
| US3452804A (en) * | 1965-12-02 | 1969-07-01 | Edward J Mellen | Method of making a permeable shell mold |
| US3707750A (en) * | 1968-11-14 | 1973-01-02 | Mtu Muenchen Gmbh | Method for manufacturing a turbine blade |
| 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 |
| FR2426511A1 (en) * | 1978-05-24 | 1979-12-21 | Trw Inc | PROCESS FOR FORMING A CASTING MOLD WITH INTERNAL CORE |
| US4422229A (en) * | 1979-02-24 | 1983-12-27 | Rolls-Royce Limited | Method of making an airfoil member for a gas turbine engine |
| US4440834A (en) * | 1980-05-28 | 1984-04-03 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation, S.N.E.C.M.A. | Process for the manufacture of turbine blades cooled by means of a porous body and product obtained by the process |
| US4418124A (en) * | 1980-10-06 | 1983-11-29 | General Electric Company | Plasma spray-cast components |
| US4418455A (en) * | 1981-05-04 | 1983-12-06 | Electric Power Research Institute, Inc. | Method of manufacturing a fluid cooled blade or vane |
| US4631092A (en) * | 1984-10-18 | 1986-12-23 | The Garrett Corporation | Method for heat treating cast titanium articles to improve their mechanical properties |
| US4726104A (en) * | 1986-11-20 | 1988-02-23 | United Technologies Corporation | Methods for weld repairing hollow, air cooled turbine blades and vanes |
| US20050002786A1 (en) * | 2003-05-27 | 2005-01-06 | Snecma Moteurs | Hollow fan blade for turbine engine and method of manufacturing such a blade |
| US7575039B2 (en) * | 2003-10-15 | 2009-08-18 | United Technologies Corporation | Refractory metal core coatings |
| US20090114797A1 (en) * | 2003-10-15 | 2009-05-07 | Beals James T | Refractory metal core coatings |
| US7240718B2 (en) * | 2005-09-13 | 2007-07-10 | United Technologies Corporation | Method for casting core removal |
| US20070056709A1 (en) * | 2005-09-13 | 2007-03-15 | United Technologies Corporation | Method for casting core removal |
| US20090028707A1 (en) * | 2007-07-26 | 2009-01-29 | United Technologies Corporation | Apparatus and method for repairing airfoil tips |
| US9759090B2 (en) * | 2013-03-03 | 2017-09-12 | Rolls-Royce North American Technologies, Inc. | Gas turbine engine component having foam core and composite skin with cooling slot |
| US20150040570A1 (en) * | 2013-03-03 | 2015-02-12 | Rolls-Royce North American Technologies, Inc. | Gas turbine engine component having foam core and composite skin with cooling slot |
| US20150167493A1 (en) * | 2013-12-18 | 2015-06-18 | General Electric Company | Turbine bucket and method for cooling a turbine bucket of a gas turbine engine |
| CN104727856A (en) * | 2013-12-18 | 2015-06-24 | 通用电气公司 | Turbine bucket and method for cooling a turbine bucket of a gas turbine engine |
| JP2015117700A (en) * | 2013-12-18 | 2015-06-25 | ゼネラル・エレクトリック・カンパニイ | Turbine bucket and method for cooling turbine bucket of gas turbine engine |
| US9528380B2 (en) * | 2013-12-18 | 2016-12-27 | General Electric Company | Turbine bucket and method for cooling a turbine bucket of a gas turbine engine |
| CN104727856B (en) * | 2013-12-18 | 2018-01-26 | 通用电气公司 | The method of turbine vane and turbine vane for cooling combustion turbine engine |
| US20160061043A1 (en) * | 2014-09-03 | 2016-03-03 | General Electric Company | Turbine bucket |
| US9835087B2 (en) * | 2014-09-03 | 2017-12-05 | General Electric Company | Turbine bucket |
| US20170051613A1 (en) * | 2015-08-17 | 2017-02-23 | United Technologies Corporation | Cupped contour for gas turbine engine blade assembly |
| US10344597B2 (en) * | 2015-08-17 | 2019-07-09 | United Technologies Corporation | Cupped contour for gas turbine engine blade assembly |
| US20170246678A1 (en) * | 2016-02-29 | 2017-08-31 | General Electric Company | Casting with first metal components and second metal components |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US2679669A (en) | Method of making hollow castings | |
| US3824113A (en) | Method of coating preformed ceramic cores | |
| US7152659B2 (en) | Component casting | |
| RU2240203C2 (en) | Casting core for investment pattern casting (variants), casting core - shell mold assembly, casting mold and casting produced with use of such core | |
| US3957104A (en) | Method of making an apertured casting | |
| EP1764170B1 (en) | Method for core removal in lost wax casting | |
| US3643728A (en) | Process of casting nickel base alloys using water-soluble calcia cores | |
| CA1064220A (en) | Investment casting mold and process | |
| US4287932A (en) | Process for the precision molding of castings | |
| IT8319396A1 (en) | Process for the heat treatment of NICRALY alloys for use as materials for ceramic furnaces and heat treatment furnaces | |
| US3957715A (en) | Casting of high melting point metals and cores therefor | |
| US11014151B2 (en) | Method of making airfoils | |
| US20050230078A1 (en) | Methods for manufacturing investment casting shells | |
| US4190450A (en) | Ceramic cores for manufacturing hollow metal castings | |
| JP2005177863A (en) | Investment casting cores | |
| US3286312A (en) | Refractory coated casting mold | |
| JPH06583A (en) | Core for casting of titanium and its alloy | |
| US6494250B1 (en) | Impregnated alumina-based core and method | |
| US3441078A (en) | Method and apparatus for improving grain structures and soundness of castings | |
| JPH05202438A (en) | Pinning wire article | |
| JPH0335839A (en) | Molding material | |
| RU2572118C1 (en) | Method of producing of combined shell moulds as per consumable patterns to produce castings out of heat-resistant alloys with directed and single-crystal structures | |
| US3132388A (en) | Method of removing the pattern from a thin shell investment mold | |
| US6802358B2 (en) | Method for production of an oxidation inhibiting titanium casting mould | |
| GB2202772A (en) | Improvements in or relating to supporting cores during investment casting |