Patent Application
20180178278
The present invention relates to positioning method for multi piece ceramic cores in investment casting of turbine components to create internal cooling passages in castings.
In conventional casting of nickel or cobalt based superalloy turbine blades, quartz cores are frequently used to produce radial cooling air holes or passages in the castings. Quartz cores are extensively used since quartz is relatively cheap, easily formable into thin cores with bends, and is easy to remove from casting by conventional chemical leaching processes. Furthermore, quartz compared with common core ceramics is considerably stronger and can be formed into more complex shapes without breaking down during the casting. Slender passages as small as 0.003 inch in diameter are now produced in castings through use of quartz tubes, which is used in combination with conventional ceramics to form the core.
Due to these benefits, quartz cores are ideally suited for the manufacture of equiaxed grain turbine blade castings having cast-in holes, where typically range of pouring temperature is from 2550 to 2800 degrees F. Generally at temperatures below 2800 degrees F., unreinforced quartz cores do not distort because of their own weight and also are not deflected by flow of molten metal into the mold.
But occasionally in small blade designs using quartz cores are difficult while injection of them in wax die has very high risk because of failure of cores due to brittle structure of quartz. Another limitation in the casting of turbine blades with quartz tubes is that the cores are often required to be formed through bending as non linear passage due to the design of the cooling passages in the blade airfoil. Moreover, when the blade has some elements that are close together the design and positioning of cores are very difficult. The cores generally are extended from tip of blade through the root, so that which the cores are extended out from the root and diverged to more than one side, positioning of cores are very considerable because geometry of diverged cores make it difficult to design of wax injection die.
For positioning the cores in described conditions, the conventional methods such as pins or locators cannot easily be used. Different types of pins and locators are used for solid or tubular cores that have large diameters. These methods cannot be easily applied for cores with small diameters which have bends, especially when they are close together because of several air cooling passages. Other techniques such as wax support used for positioning ceramic solid cores in hollow blades or vanes cannot be used for tubular cores is because of their geometry and small diameter.
So an improved method is needed for positioning cores in investment casting process where the multiple cores have the intricate design. An objective of the present invention is to provide a method for positioned cores to meet this need.
To this end, this invention provides a method for positioning cores for use in casting a melt wherein the positioned cores are embedded in two distinct fugitive wax segments. In the present invention, an apparatus includes a first mold, a second mold, ceramic cores, and means for injecting fugitive and final wax.
The first mold has a cavity formed therein for fugitive material or another soluble material such as soluble wax. Each of grooves of cavity has a depth equal to the radius of certain tubular cores. When the ceramic cores, which create the cooling passages, are inserted into the first mold cavity and fugitive wax is injected, the features that position the cores are formed about the cores. The features with the cores are then removed from the first mold and placed in the second mold. The second mold has a cavity that is complementary in shape to the casting design of blade or vane. The features properly locate the ceramic cores within the second mold cavity to ensure that the position of cores in final blade is correct. Wax is then injected into the second mold cavity. The wax adheres to the features and surrounds the cores. The wax-covered ceramic cores and fugitive wax are then removed from the second mold.
Fugitive segments adhering the final wax are then solved in water. Wax Pattern containing only tubular cores is now prepared for investment casting. A ceramic shell is formed about the wax until required thickness, and the wax is melted, leaving a cavity is comprises positioned cores therein. Molten super-alloy is then cast into the cavity to form a blade. After metal is cooled, conventional leaching processes are used to remove ceramic cores from the casting to create tubular cooling channels.
The present invention includes a method for positioning cores in wax pattern to use in casting a nickel or cobalt base super-alloy gas turbine blade or vane. Employing a two-step molding process to inject wax around ceramic cores, intricate cooling channels are created during casting.
The invention can be practiced for complicated ceramic shapes with different assemblies to cast different metals and alloys.
Each of these cavities comprises two parts in each of bottom and top half of first mold. A plurality of grooves 15 is formed in each of mold cavities 13 and 14 whereas the depth of each groove is equal to half of outer diameter of certain core. Indeed each core is placed in a certain groove in the own cavity.
Large cavity 13 has portions 13a and 13c in bottom half 11,
Small cavity 14 has portions 14a and 14c in bottom half 11,
Although
The first mold includes a duct 17 for supplying injected wax to two cavities. In addition the duct divides into two branches for each cavity. Fugitive wax segments are injected into the first mold and two features are formed, as shown in
Features and their cores are placed in bottom half 31 and top half 32 of second mold as shown in
Second mold cavity is designed to receive small and large features 21, 22 and also the positioned cores. Large feature 21 is placed in cavity 33a in bottom half of second mold and small feature 22 is placed in 33b in top half. The end of cores of each feature are extended and fixed between portions of 33e and 33f of the second mold. In each of portions 33e and 33f, nine grooves similar to 16 in first mold, are formed. Each groove has a depth that is equal to the radius of certain core. When the mold is closed, the bottom and top half complete a close space for fixing each of cores.
After the locating features and cores in their places, the wax is injected into cavity between 33c and 33d from duct 35 of second mold. In particular expandable pattern wax, plastic or other material is introduced into the spaces between cores and about the features (21 and 22) to form a pattern that embeds the gathered cores (1-9). The parameters of the injection are very important because the quartz tubes are very brittle especially when they have bends.
So it is suggested that the high temperature and low pressure injection can protect the cores.
Although the cores can be hold and protected by fugitive segments, the direction of duct 35 for injection in second mold should be parallel to cores for preventing break and even displacement of cores. Also for decreasing the mechanical pressure to the cores, the friction between cores and semi liquid wax should be decreased by using higher amount of releasing agent spray on the cores before injection.
After the molten wax has solidified, the complex 41 comprising wax pattern 42, features 21, 22 and their cores 1-9 are removed from the second mold as shown in
For removing fugitive features, the complex 41 dipped in water at 20-30° C. for 10 hours. For accelerating solution of fugitive material, it is be possible using diluted nitric acid especially when the shape of fugitive material is complicated. However, nitric acid may be better than water due to better and faster removal.
Following the solution of fugitive material, the ends of bent and straight forms of the quartz cores extract from root and tip of blade, respectively.
Because the thermal expansion of the core and shell are usually different, it is necessary to provide axial slip to allow small movement and thermal expansion of the quartz core relative to shell during the firing of shell and also casting process. For achieving this target a little wax is added to the straight end of cores that plays an important role for assure the health of cores. This avoids cracking or distortion from different thermal expansion coefficients of quartz and the ceramic shell material which comprises silica, zircon, alumina or other conventional shell materials and ceramic binder.
But for locking the location of cores it is better that region B of core is fully fixed without any freedom in shell because the high amount slip of this end may cause large lateral movement.
The final pattern with slipping core strategies then is invested in ceramic shell pursuant to the well known lost wax by repeated dipping in ceramic slurry, draining excess slurry and stuccoing with coarse grain ceramic stucco until a shell mold is built up on the pattern tree to a desired thickness.
After the end of coating, ceramic shells are dewaxed in autoclave under in conditions of suitable temperature and pressure.
The shell then is fired at elevated temperatures to acquire sufficient strength for casting. Molten superalloy then is poured into the shell that has cavity of blade and cores that positioned into the shell.
The molten superalloy can be solidified in the shell about the cores. The shell is removed from the solidified casting using a mechanical knock-out operation. The cores are selectively removed from the solidified casting by chemical leaching or other conventional core removal methods.
The spaces previously occupied by the core elements 1-9 comprise complex is cooling air passages in the casted blade, while the superalloy in the spaces forms internal walls of the separating the cooling passages.
The present invention makes possible the casting of such components as blades and vanes for gas turbine engine in superalloy materials using investment shell molding to produce equiaxed grained components and having accurately defined, radially extending air cooling passages which may extend through one or more end of the blades or vane.
The present invention also makes possible the casting of such components as blades or vanes having cooling passages containing bends which, as described earlier in the specification were believed to be impossible or very difficult without positioning features in small castings.
The core assemblies including several elements is formed in novel manner by two fugitive segments when the cores are extended two ends of one side of blade or vane which the embedding of several thin walled quartz tubular cores alone in patterns especially in small casting design is very complicated and may be impossible.
These core assemblies (features) is quite complex, time consuming and costly as a result of use of the multiple cores in soluble wax. In addition, these features procedure can result in dimensional accuracy and repeatedly of the core assemblies and thus airfoil castings produced using such core assemblies.
While the invention has been described here above in terms of specific modifications thereof, it is not intended to be limited and changes can made therein is without departing from the scope of the invention as set forth in following claims.
