Patent Application
20110132563
This invention relates to the field of investment casting.
Investment casting is one of the oldest known metal-forming processes, dating back thousands of years to when it was first used to produce detailed artwork from metals such as copper, bronze and gold. Industrial investment castings became more common in the 1940's when World War II increased the demand for precisely dimensioned parts formed of specialized metal alloys. Today, investment casting is commonly used in the aerospace and power industries to produce gas turbine components such as blades or vanes having complex airfoil shapes and internal cooling passage geometries.
The production of an investment cast gas turbine blade or vane involves producing a ceramic casting mold having an outer ceramic shell with an inside surface corresponding to the airfoil shape, and one or more ceramic cores positioned within the outer ceramic shell, corresponding to interior cooling passages to be formed within the airfoil. Molten alloy is introduced into the ceramic casting mold and is then allowed to cool and to harden. The outer ceramic shell and ceramic core(s) are then removed by mechanical or chemical means to reveal the cast blade or vane having the external airfoil shape and hollow interior cooling passages in the shape of the ceramic core(s).
A ceramic core for injection casting is manufactured by first precision machining the desired core shape into mating core mold halves formed of high strength hardened machine steel, then joining the mold halves to define an injection volume corresponding to the desired core shape, and vacuum injecting a ceramic molding material into the injection volume. The molding material is a mixture of ceramic powder and binder material. Once the ceramic molding material has hardened to a green state, the mold halves are separated to release the green state ceramic core. The fragile green state core is then thermally processed to remove the binder and to sinter the ceramic powder together to create a material that can withstand the temperature requirements necessary to survive the casting of the molten alloy. The complete ceramic casting vessel is formed by positioning the ceramic core within the two joined halves of another precision machined hardened steel mold (referred to as the wax pattern mold or wax pattern tool) which defines an injection volume that corresponds to the desired airfoil shape of the blade, and then vacuum injecting melted wax into the wax mold around the ceramic core. Once the wax has hardened, the wax mold halves are separated and removed to reveal the ceramic core encased inside a wax pattern, with the wax pattern now corresponding to the airfoil shape. The outer surface of the wax pattern is then coated with a ceramic mold material, such as by a dipping process, to form the ceramic shell around the core/wax pattern. Upon sintering of the shell and consequential removal of the wax, the completed ceramic casting mold is available to receive molten alloy in the investment casting process, as described above.
The known investment casting process is expensive and time consuming, with the development of a new blade or vane design typically taking many months and hundreds of thousands of dollars to complete. Furthermore, design choices are restricted by process limitations in the production of ceramic cores because of their fragility and an inability to achieve acceptable yield rates for cores having fine features or large sizes. The metals forming industry has recognized these limitations and has developed at least some incremental improvements, such as the improved process for casting airfoil trailing edge cooling channels described in U.S. Pat. No. 7,438,527. As the market demands ever higher efficiency and power output from gas turbine engines, the limitations of existing investment casting processes become ever more problematic.
While incremental improvements have been presented in the field of investment casting technology, the present inventors have recognized that the industry is faced with fundamental limitations that will significantly inhibit component designs for planned advances in many fields, for example in the next generation of gas turbine engines. Gas turbine firing temperatures continue to be increased in order to improve the efficiency of combustion, and gas turbine hot gas path component sizes continue to increase as power levels are raised, so there is now a need to design an internally cooled 4th stage gas turbine blade in excess of a meter in length. No such blade has heretofore been produced, nor is it believed that such a blade can be produced effectively with today's existing technology. In prior art turbines, there was no need for internal cooling of the 4th stage due to the high temperature capability of available superalloys. Due to increased firing temperatures, the next generation 4th stage turbine blades will exceed the operating limits of these known alloys and will require active internal cooling passages to protect the integrity of the component. However, due to the complex cooling design and projected size of these new blades, the ceramic cores that would be necessary for investment casting of such cooling passages are beyond the commercially practical capabilities of existing investment casting processes. Similar limitations may be experienced in other industries as desired designs exceed casting capabilities.
As a result, the present inventors have developed and are disclosing herein an entirely new regiment for investment casting. This new regiment not only extends and refines existing capabilities, but it also provides new and previously unavailable design practicalities for the component designer. As a result, the processes disclosed herein enable the timely and cost efficient production of cast metal alloy components having feature geometries that may be larger or smaller than currently available geometries, may be more complex or shapes that could never before have been cast, and may have feature aspect ratios that were previously unattainable but that are now needed for the very long and thin cooling passages in a 4th stage internally cooled gas turbine blade.
The present invention moves casting technology beyond foreseeable needs, and it removes the casting process from being a design limitation, thereby allowing designers again to extend designs to the limits of the material properties of the cast alloys and the externally applied thermal barrier coatings.
The investment casting regiment described herein incorporates new and improved processes at multiple steps in the investment casting process. Specific aspects of the new regiment are described below in greater detail and claimed herein; however, the following summary is provided to familiarize the reader with the overall process so that the benefit of the individual steps and synergies there between may be appreciated.
An exemplary investment casting process according to a regiment described herein may start with the manufacturing of a ceramic core for an investment casting mold by using a master mold which is machined from a soft metal, i.e. a relatively soft, easily machined, and inexpensive material (when compared to the currently used high strength machine steel) such as aluminum or mild steel. Two master mold halves are formed, one corresponding to each of two opposed sides of a desired ceramic core shape. Into each master mold a flexible mold material is cast to form two cooperating flexible mold halves, which when joined together define an interior volume corresponding to the desired ceramic core shape. Ceramic mold material is then cast into the flexible mold and allowed to cure to a green state.
The cost and time to produce the master molds is minimized by the use of materials that are easily machined. However, advanced design features for the next generation of gas turbine engines may not translate well using standard machining processes in such materials. Accordingly, at least a portion of the master mold halves may be designed to receive a precision formed insert. The insert may be formed by any known process, such as a Tomo process as described in U.S. Pat. Nos. 7,141,812 and 7,410,606 and 7,411,204, all assigned to Mikro Systems, Inc. of Charlottesville, Va., and incorporated by reference herein. The Tomo process uses a metallic foil stack lamination mold to produce a flexible derived mold, which in turn is then used to cast a component part. The component design is first embodied in a digital model and is then digitally sliced, and a metal foil is formed corresponding to each slice using photolithography or other precision material removal process. The inherent precision of the two-dimensional material removal process in combination with the designer's ability to control the thickness of the various slices in the third dimension provides a degree of three-dimensional manufacturing tolerance precision that was not previously available using standard mold machining processes. The foils are stacked together to form a lamination mold for receiving suitable flexible molding material. The term “flexible” is used herein to refer to a material such as a room temperature vulcanizing (RTV) silicon rubber or other material which can be used to form a “flexible mold” which is not rigid like prior art metal molds, but that allows the mold to be bent and stretched to a degree in order to facilitate the removal of the mold from a structure cast therein. Furthermore, the terms “flexible mold” and “flexible tool” may be used herein to include a self-standing flexible structure as well as a flexible liner or insert contained within a rigid coffin mold. A component is then cast directly into the flexible mold. The flexibility of the mold material enables the casting of component features having protruding undercuts and reverse cross-section tapers due to the ability of the flexible mold material to deform around the feature as the cast part is pulled out of the mold.
In this manner, portions of the ceramic core which have a relatively low level of detail, such as long smooth channel sections, may be translated into the master mold using inexpensive standard machining processes, while other portions of the ceramic core having a relatively high level of detail, such as micro-sized surface turbulators or complex passage shapes, may be translated into the master mold using a precision mold insert. Furthermore, for cooling channel designs requiring the use of multiple cores, the mold inserts may be used to define precision cooperating joining geometries in each of the multiple cores so that when the multiple cores are jointly positioned within a wax mold, the joining geometries of the respective cores will mechanically interlock such that the multiple cores function as a single core during subsequent injection processes.
The invention is explained in detail in the following description in view of the drawings that show:
Prior art investment casting processes require the use of high cost, difficult to machine, hard, tool steel material for the master tool because multiple ceramic cores are cast directly from a single master tool using a high pressure injection process. The high cost results in part because the tool is a highly engineered, multi-piece system due to the need to be able to remove the rigid tool from the cast core in multiple pull planes. The hard tool steel is required because the ceramic material will abrade the tool during the high pressure injection process. In contrast, the present invention uses the master tool only for low pressure or vacuum assisted casting of flexible (e.g. rubber) mold material, as described in the above-cited U.S. Pat. Nos. 7,141,812 and 7,410,606 and 7,411,204. Thus, low strength, relatively soft, easy to machine materials may be used for the master tool, for example, a series 7000 aluminum alloy in one embodiment. This results in a significant time and cost savings when compared to prior art processes.
Another technology which can be exploited in the present invention is described in pending International Patent Application PCT/US2009/58220 also assigned to Mikro Systems, Inc. of Charlottesville, Va., and incorporated by reference herein. That application describes a ceramic molding composition that mimics existing ceramic core molding materials in its fully sintered condition, but that provides significantly improved green body strength when compared to the existing materials. Incorporating such an improved molding composition into the present casting regiment facilitates the production of core geometries that would not previously have survived handling in their green state without an unacceptably high failure rate. Improved green state strength is particularly important during the removal of a ceramic core from a flexible mold when the shape of a core feature is such that the mold must be deformed around the cast material in order to remove the core from the mold. The ceramic material cast into the flexible mold should have adequate green body strength to allow such cast features to be removed from the mold even when they contain protruding undercuts or non-parallel pull plane features requiring some bending of the flexible mold during removal of the green body ceramic core.
A ceramic casting material described in International Patent Application PCT/US2009/58220 exhibits a lower viscosity as a slurry than prior art ceramic core casting materials, thereby allowing the step of
In one embodiment, the epoxy content of the ceramic casting material could range from 28 weight % in a silica based slurry to as low as 3 weight %. The silicone resin may be a commercially available material such as sold under the names Momentive SR355 or Dow 255. This content could range from 3 weight % to as high as 30 weight %. The mix may use 200 mesh silica or even more coarse grains. Solvent content generally goes up as other resins decrease to allow for a castable slurry. The solvent is used to dissolve the silicon resin and blend with the epoxy without a lot of temperature. The Modulus of Rupture (MOR) of the sintered material is on the norm for fired silica, typically 1500-1800 psi with 10% cristobalite on a 3 point test rig. The sintered material MOR is tightly correlated to the cristobalite content, with more cristobalite yielding weaker room temperature strength. The green state MOR depends on the temperature used to cure the epoxy, as it is a high temperature thermo cure system. The curing temperature may be selected to allow for some thermo-forming, i.e. reheating the green state material to above a reversion temperature of the epoxy to soften the material, then bending it from its as-cast shape to a different shape desired for subsequent use. The reheated material may be placed into a setting die within a vacuum bag such that the part is drawn into conformance with the setting die upon drawing a vacuum in the bag. Alignment features may be cast into the core shape for precise alignment with the setting die. Advantageously, a green body MOR of at least 4,000 psi will permit the core to be removed from a flexible mold and handled with a significantly reduced chance of damage, and to provide adequate strength for it to undergo standard machining operations for adding or reshaping features either before or after reshaping in a setting die. Following such thermo-forming or in the absence of it, additional curing may be used to add strength. In one embodiment the Modulus of Rupture achieved was:
MOR cured at 110° C. for 3 hours=4000 psi
MOR cured as above and then at 120° C. for 1 hour=8000 psi.
A 10% as-fired cristobalite content may be targeted. This may be altered by the mineralizers present and the firing schedule. The 10% initial cristobalite content may be used to create a crystalline seed structure throughout the part to assure that most of the rest of the silica converts to cristobalite in a timely fashion when the core is heated prior to pouring molten metal into the ceramic mold. It also keeps the silica from continuing to sinter into itself as it heats up again.
Another parameter of concern in the investment casting business is porosity. Prior art ceramic casting material typically has about 35% porosity. The material described above typically runs around 28% porosity. The danger of a low porosity is that the cast metal cannot crush the ceramic core as it shrinks and cools, thereby creating metal crystalline damage that is referred to in the art as “hot tear”. The material described above has never caused such a problem in any casting trial.
The above described regiment for producing investment casting ceramic cores compares favorably with known prior art processes, as summarized in the following Table 1.
Once the ceramic core is produced, it is incorporated into a ceramic casting vessel and a metal part is cast therein using known processes.
The above-described regiment enables a new business model for the casting industry. The prior art business model utilizes very expensive, long lead time, rugged tooling to produce multiple ceramic casting vessels (and subsequently cast metal parts) from a single master tool with rapid injection and curing times. In contrast, the new regiment disclosed herein utilizes a less expensive, more rapidly produced, less rugged master tool and an intermediate flexible mold derived from the master tool to produce the ceramic core with much slower injection and curing times. Thus, the new casting regiment can be advantageously applied for rapid prototyping and development testing applications because it enables the creation of a first-of-a-kind ceramic core (and subsequently produced cast metal part) much faster and cheaper than with the prior art methods. Furthermore, the new regiment may be applied effectively in high volume production applications because multiple identical flexible molds may be cast from a single master tool, thereby allowing multiple identical ceramic cores to be produced in parallel to match or exceed the production capability of the prior art methods, in spite of the longer casting time required per core due to low pressure injection and potentially longer curing times. The time and cost savings of the present regiment include not only the reduced cost and effort of producing the master tool, but also the elimination of certain post-casting steps that are necessary in the prior art, such as drilling trailing edge cooling holes, since such features may be cast directly into the metal part using a ceramic core formed in accordance with the present invention due to the degree of precision achievable with the precision inserts and the ability to remove the flexible mold in multiple pull planes. The present invention not only produces high precision parts via a flexible mold, but it also enables part-to-part precision to a degree that was unattainable with prior art flex mold processes. Finally, the present regiment provides these cost and production advantages while at the same time enabling the casting of design features that heretofore have not been within the capability of the prior art techniques. thereby for the first time allowing component designers to produce the hardware features that are necessary to achieve next generation gas turbine design goals. For example, the prevent invention facilitates the production of a ceramic core having an overall outer envelope dimension aspect ratio of 20:1 or higher, and/or having an overall length of 30 inches or more. Thus, the present invention permits the commercial production of next generation actively cooled 4th stage turbine blades which is impossible with prior art techniques. It is also now possible to incorporate such large hollow regions in large cast components in order to reduce weight even if cooling is not a requirement.
While various embodiments of the present invention have been shown and described herein, it will be obvious that such embodiments are provided by way of example only. Numerous variations, changes and substitutions may be made without departing from the invention herein.
This application claims benefit of the 8 Dec. 2009 filing date of U.S. provisional application No. 61/267,519 (attorney docket number 2009P22785US), incorporated by reference in its entirety herein.
| Number | Date | Country | |
|---|---|---|---|
| 61267519 | Dec 2009 | US |
