Source: http://www.patentgenius.com/patent/5868194.html
Timestamp: 2018-02-17 23:46:04
Document Index: 531543750

Matched Legal Cases: ['art 14', 'art 16', 'art 18', 'art 20', 'art 22', 'art 20', 'art 214', 'art 216', 'art 218', 'art 220', 'art 222', 'art 220', 'art 232', 'art 234']

Method of investment casting and a method of making an investment casting mould - Patent # 5868194 - PatentGenius
Method of investment casting and a method of making an investment casting mould
5868194 Method of investment casting and a method of making an investment casting mould
Inventor: Horwood
Application: 08/787,857
Inventors: Horwood; Dominic J. (Derby, GB2)
U.S. Class: 164/122.2; 164/456; 164/516
Field Of Search: 164/4.1; 164/456; 164/122.1; 164/122.2; 164/516
U.S Patent Documents: 5234047
Foreign Patent Documents: 0 655 667; 41 24 961; 4 15761; 0 427 0467; 1 394 872; 1 486 326; 2 067 546; 2 150 875
Abstract: A method of making an investment casting mould comprises producing a CAD definition of a turbine blade, and determining the distribution of isosurfaces of constant temperature around the CAD definition of the at least one article if the external surface of the CAD definition of the at least one article was at a high temperature (Thigh). One of the isosurfaces of constant temperature is selected to define the external shape and the thickness of an investment casting mould. A pattern of the turbine blade is produced from the CAD definition of the turbine blade. The investment casting mould is made with an internal shape defined by the pattern of the turbine blade and an external shape and thickness distribution defined by the selected isosurface of constant temperature. The pattern is then removed from the investment casting mould.
(b) determining the distribution of isosurfaces of a constant physical property around the CAD definition of the at least one article if the external surface of the CAD definition of the at least one article was held at a predetermined physicalproperty value,
(c) selecting one isosurface of the constant physical property value to define the external shape and the thickness of an investment casting mould,
(e) making the investment casting mould with an internal shape defined by the pattern of the at least one article to be produced and an external shape and thickness distribution defined by the selected isosurface of constant physical propertyvalue,
2. A method as claimed in claim 1 wherein the physical property is temperature.
3. A method as claimed in claim 2 wherein step (b) comprises performing heat transfer analysis by analyzing the transfer of heat between the external surface of the CAD definition of the at least one article and a nominal boundary surface spacedfrom and enclosing the CAD definition of the at least one article.
8. A method as claimed in claim 1 wherein step (e) comprises producing the investment casting mould by making a mould to define the external shape of the investment casting mould and injecting a ceramic slurry into a space defined between thepattern and the mould.
14. A method of making an investment casting mould comprising the steps of:
(e) making the investment casting mould with an internal shape defined by the pattern of the at least one article to be produced and an external shape and thickness distribution defined by the selected isosurface of constant temperature,
15. A method as claimed in claim 14 wherein the physical property is temperature.
16. A method as claimed in claim 15 wherein step (b) comprises performing heat transfer analysis by analysing the transfer of heat between the external surface of the CAD definition of the at least one article and a nominal boundary surfacespaced from and enclosing the CAD definition of the at least one article.
24. A method of investment casting compromising the steps of:
(d) determining the distribution of isosurfaces of a constant physical property around the CAD definition of the at least one article if the external surface of the CAD definition of the at least one article was held at a predetermined physicalproperty value,
(e) selecting one isosurface of the constant physical property value to define the external shape and the thickness of an investment casting mould,
(f) supplying the CAD definition of the at least one article, the CAD definition of the casting furnace and the definition of the investment casting mould to the process model of the solidification of molten metal within an investment castingmould within the casting furnace,
(g) using the process model to determine whether the solidification of molten metal within the definition of the investment casting mould in the CAD definition of the casting furnace will produce at least one cast article substantially withoutdefects.
(h) making a pattern of the at least one article to be produced from the CAD definition of the at least one article.
(i) making the investment casting mould with an internal shape defined by the pattern of the at least one article to be produced and an external shape and thickness distribution defined by the selected isosurface of constant physical propertyvalue,
25. A method as claimed in claim 24 wherein the physical property is temperature.
26. A method as claimed in claim 25 wherein step (d) comprises performing heat transfer analysis by analysing the transfer of heat between the external surface of the CAD definition of the at least one article and a nominal boundary surfacespaced form and enclosing the CAD definition of the at least one article.
31. A method as claimed in claim 24 wherein step (i) comprises producing the investment casting mould by making a mould to define the external shape of the investment casting mould and injecting a ceramic slurry into a space defined between thepattern and the mould.
The present invention relates to a method of investment casting, and to a method of making an investment casting mould. The invention is particularly relevant to the casting of articles by directional solidification, and more particularly to thecasting of single crystal articles.
In the investment casting process, or lost wax casting process as it is sometimes called, a wax pattern of an article, or component, is produced. The wax pattern is produced by injecting wax into an accurately formed die. The wax pattern is areplica of the article to be produced. Usually a number of wax patterns are assembled together on a wax gating tree to form a cluster or wax mould assembly. The wax mould assembly is immersed in a liquid ceramic slurry which quickly gels afterdraining. Strengthening refractory granules are sprinkled over the ceramic slurry covered wax mould assembly and the refractory granules bond to the slurry coating to produce a ceramic layer on the wax mould assembly. This process is repeated severaltimes to produce many ceramic layers which have a total thickness of about 1/4 inch (6 mm) to 1/2 inch (12 mm) on the wax mould assembly. The wax is then melted out leaving a ceramic shell mould having an internal cavity identical in shape to that ofthe original wax mould assembly. This ceramic shell mould is called an investment casting mould. The mould is fired at a high temperature between 950.degree. C. and 1100.degree. C. to remove all traces of residual wax, and cure the ceramic shellmould. The ceramic shell mould is then transferred to a casting furnace, which may be operated at either vacuum conditions or at atmospheric conditions. A charge of molten metal is poured into the ceramic shell mould and the mould is allowed to cool toroom temperature, after which the ceramic shell mould is removed leaving the cast article or articles. The ceramic shell mould may be cooled by applying a temperature gradient across the ceramic shell mould to directionally solidify the metal in orderto produce columnar grains, or single crystals in the finished article or articles.
It is also known to produce resin patterns using stereolithography, rather than making wax patterns in a die. The advantage of using stereolithography is that it enables the patterns to be produced quickly for development purposes. The resinpatterns are produced by directing a beam of focused radiation into a bath of liquid resin which is locally cured and solidified by the radiation. The beam of radiation is moved under computerised control to produce a resin pattern of the article to beproduced. The resin pattern is then coated with ceramic slurry as discussed above to produce the ceramic shell mould. However, for production purposes resin patterns are not smooth enough for production quality articles and stereolithographicproduction of resin patterns is slow and expensive compared to the production of wax patterns by wax injection into a die.
The immersing, or dipping, of the wax mould assembly in the ceramic slurry is a relatively uncontrolled process. The build up of ceramic material is governed by the adhesion of the ceramic material onto the wax mould assembly. Random featuressuch as drips and runs are common. In particular, the ceramic shell is thicker on concave external surfaces than on convex external surfaces of the wax mould assembly. In general the article features are blurred, sharp edges are blunted, fillet radiiare enlarged, surfaces are smoothed and bridges may form between completely separate areas of the wax mould assembly. The thickness and external shape of the ceramic shell mould control the heat transfer out of the molten metal during the castingprocess.
It is necessary to have a mathematical description of the external surface of the ceramic shell mould. This description may be derived by running a mathematical model that simulates the build-up of ceramic on the article, for use in processmodels of the investment casting process to produce defect free cast articles.
There is currently no mathematical model of the external surface of the ceramic shell mould which simulates variation in the ceramic shell thickness with variations in the curvature of the external surface of the article. Furthermore there iscurrently no mathematical model of the external surface of the ceramic shell mould which simulates bridging between completely separate areas of the ceramic shell mould.
The present invention seeks to provide a mathematical model that may be used to generate a mathematical description of the external surface of an investment casting mould which more closely resembles real life than currently availablemathematical models.
Preferably step (b) comprises performing a heat transfer analysis by analysing the transfer of heat between the external surface of the CAD definition of the at least one article and a nominal boundary surface spaced from and enclosing the CADdefinition of the at least one article.
Alternatively step (e) comprises producing the investment casting mould by making a mould to define the external shape of the investment casting mould and injecting a ceramic slurry into a space between the pattern and the mould. The mould maybe made by stereolithography from a resin.
(d) determining the distribution of isosurfaces of a constant physical property around the CAD definition of the at least one article if the external surface of the CAD definition of the at least one article was at a predetermined physicalproperty value,
(g) using the process model to determine whether the solidification of molten metal within the definition of the investment casting mould in the CAD definition of the casting furnace will produce at least one cast article substantially withoutdefects,
Preferably step (d) comprises performing a heat transfer analysis by analysing the transfer of heat between the external surface of the CAD definition of the at least one article and a nominal boundary surface spaced from and enclosing the CADdefinition of the at least one article.
Alternatively step (i) comprises producing the investment casting mould by making a mould to define the external shape of the investment casting mould and injecting a ceramic slurry into a space between the pattern and the mould. The mould maybe made by stereolithography from a resin.
A wax mould assembly 10, shown in FIG. 1, comprises a plurality of wax patterns 12 suitable for making turbine vanes or turbine blades for a gas turbine engine. Each of the wax patterns 12 has a first part 14, which defines the shape of the rootof the resulting cast turbine blade, a second part 16, which defines the shape of the platform of the cast turbine blade and a third part 18, which define the shape of the aerofoil portion of the cast turbine blade. The turbine blades to be cast in thisexample are single crystal turbine blades and therefore an associated wax selector part 20 and wax starter part 22 are connected to each wax pattern 12. The wax selector part 20 is a wax helix, although other suitable wax selectors may be used.
The wax patterns 12 and associated wax selectors 20 and wax starters 22 are arranged together on a wax gating tree 24 to form the wax mould assembly 10. The wax gating tree 24 comprises a wax runner which includes a central downpole 26 and aplurality of feeders 28. The wax patterns 12 are arranged generally parallel to the central downpole 26 and the feeders extend generally radially from the central downpole 26 to the wax patterns 12. There are also filters 30 in the feeders 28.
As discussed previously the wax mould assembly 10, including the wax patterns 12 is immersed in liquid ceramic slurry and has refractory granules sprinkled on the gelling liquid ceramic slurry to produce a layer of ceramic. The process ofimmersing in liquid ceramic slurry and sprinkling with refractory granules is repeated until the thickness of ceramic is sufficient for the particular application. Thereafter the ceramic shell mould is dried and heated to remove the wax and then firedto purify and cure the ceramic shell mould.
The finished ceramic shell mould 70 for casting a single crystal turbine blade made from the wax mould assembly is shown in FIG. 2. The ceramic shell mould comprised a plurality of article portions 72 each of which has an article chamber 74 todefine the turbine blade. Each of the article portions also has an associated selector portion 76, which has a selector passage 78, and an associated starter portion 80 which has a starter chamber 82. The ceramic shell mould 70 also comprises a runnerportion 84 to convey molten metal to the article portions 72 via the starter and selector portions 80 and 76. The runner portion 84 includes a single central portion 86 which has a main passage 88 and radial portions portions 80. The ceramic shellmould has a recess 94 which is arranged to fit on a chill plate during the single crystal casting process.
It may be seen from FIG. 3 that the portion of the ceramic shell mould 70 corresponding to the aerofoil portion of the turbine blade has a variation in the thickness of the ceramic shell mould 70. More specifically the ceramic shell mould 70 isthicker on the concave shaped surface than on the convex shaped surface.
When molten metal is poured into the ceramic shell mould 70, the molten metal flows through the main passage 88, the ceramic filters and the radial passages 92 to the starter chambers 82. The molten metal then flows upwardly through the starterchambers 82 and the selector passages 78 into the article chambers 74. In the single crystal casting process the open ends of the starter chambers 82 of the ceramic shell mould 70 are placed onto a chill plates located in the recess 94 of the ceramicshell mould 70. The chill plate causes solidification of the molten metal to occur, and the chill plate and ceramic shell mould 70 are withdrawn slowly from the casting furnace to produce directional solidification of the molten metal within the starterchambers 82 of the ceramic shell mould 70. The selector passages 78 select a single crystal from a plurality of directionally solidifying crystals in the starter chambers 82 of the ceramic shell mould 70.
In one embodiment of the present invention, as shown with reference to FIG. 4, a three demensional CAD (computer aided design) definition of an article to be produced, for example a turbine blade, is produced. The CAD definition of the turbineblade is used as an input to a mathematical model which is used to determine the external shape and the thickness of the ceramic shell mould used for investment casting of the turbine blade.
More specifically, as shown in FIGS. 5A-5D, 6A-6E, 7A-7F, we perform a thermal heat transfer analysis using finite element technology. We simulate heat conduction from the external surface of the CAD definition of the article to some nominalsurface spaced from and enclosing the CAD definition of the article, where the external surface of the CAD definition of the article is at a predetermined temperature and the nominal surface is at a temperature significantly cooler than the temperatureat the external surface of the CAD definition of the article.
We then say that the external surface of the ceramic shell mould is defined by an isosurface of constant temperature, and thus the external shape of the ceramic shell mould is defined together with the thickness distribution of the ceramic shellmould. Thus as we move along a conduction heat flux vector away from the turbine blade, the ceramic shell mould thickness in that direction varies in proportion to the variation of temperature due to the heat flow. There is no process physics basedlink for this relationship, we have drawn an analogy between thermal conduction and the real ceramic build up behaviour. The concave surface of the turbine blade concentrates conductive heat flux like a lens reducing heat dissipation and causing theisosurfaces of constant temperature to be further apart, whereas the convex surface of the turbine blade causes the conductive heat flux to diverge increasing heat dissipation and causing the isosurfaces to be closer together.
It can be seen that the use of the isosurfaces of constant temperature results in the ceramic shell mould being thicker on the convex surface and thinner on the convex surface thus matching the real build up exhibited during the immersingtechnique. Furthermore it also produces bridging and smoothing out of features. The particlular isosurface of constant temperature is selected to produce the required thickness distribution of ceramic.
In practice as is shown in FIG. 7B, a CAD definition of a cylinder 102 is produced which is larger than, and encloses the CAD definition of the turbine blade 100. The CAD definition of the turbine blade 100 is substracted from the CAD definitionof the cylinder 102 to produce a hollowed cylinder CAD definition 104, the internal surface of which corresponds to the external surface of the CAD definition of the turbine blade. A finite element mesh 106 is automatically generated from the CADdefinition of the hollowed cylinder 104 as shown in FIG. 7C. Tetrahedral linear finite elements are used. The definition completely describes the hollowed cylinder by splitting the hollowed cylinder into a collection of small solid elements.
A high temperature boundary condition is applied to the internal surface 108 of the hollowed cylinder finite element (FE) mesh and a low temperature boundary condition is applied to the external surface 110 of the hollowed cylinder finite element(FE) mesh, as shown in FIG. 7D. These conditions are applied to enable and promote conductive heat flow through the hollowed cylinder in a radially outward direction. A finite element thermal conduction analysis is run until steady heat flow isachieved at which point there are an infinite number of isosurfaces of constant temperature 112 within the domain of the hollowed cylinder, shown more clearly in FIG. 5.
One isosurface of temperature 112 is selected which gives the required thickness distribution of the ceramic mould 114, i.e. normal spatial deviation from the CAD definition of the article 100 to the isosurface of temperature 112 as shown inFIGS. 7E and 7F.
The ceramic shell mould 114 is produced with an internal shape defined by the pattern of the turbine blade 100 and an external shape and thickness defined by the selected isosurface of constant temperature 112. The ceramic shell mould 114 may beproduced with the external shape defined by the selected isosurface of constant temperature 112 by controlling the number of times the pattern is immersed in the ceramic slurry. In this case the dipping process is calibrated to correlate the number ofdips required to build up the ceramic shell mould to a thickness that approximates to the thickness defined by the isosurface of constant temperature. Alternatively the ceramic shell mould may be produced with an external shape defined by the selectedisosurface of constant temperature 112 by a machining a ceramic block to the required external shape.
In FIGS. 5A-5D is shown a perspective view of a turbine blade 100 with isosurfaces of constant temperature 112, and FIG. 6 shows the effect on the thickness and external shape of the ceramic shell mould of selecting isosurfaces of differentconstant temperatures.
In another embodiment of the present invention, as shown in FIGS. 7A-7F, a method of investment casting is shown where a process model of investment casting process is used to ensure production of defect free cast articles. The process model isan advanced finite element thermal computer model that can be used to predict the casting process and solidification behaviour. A three dimensional CAD (computer aided design) definition of a casting furnace to be used for the investment casting processis produced. A three dimensional CAD (computer aided design) definition of an article to be produced, for example a turbine blade, is produced. The CAD definition of the turbine blade is used as an input to a mathematical model which is used todetermine the external shape and the thickness of the ceramic shell mould used for investment casting of the turbine blade. A process model of molten metal solidification, particularly during directional solidification or single crystal formation, isproduced. The three dimensional CAD definition of the casting furnace, the three dimensional CAD definition of the turbine blade and the definition of the external shape and thickness of the ceramic shell mould are used as inputs to the process model ofthe molten metal solidification process.
In order to determine the external shape and thickness of the ceramic shell mould we perform a thermal heat transfer analysis using finite element technology. We simulate heat conduction from the external surface of the CAD definition of thearticle to some nominal surface spaced from and enclosing the CAD definition of the article, where the external surface of the CAD definition of the article is at a predetermined temperature and the nominal surface is at a temperature significantlycooler than the temperature at the external surface of the CAD definition of the article.
We then say that the external surface of the ceramic shell mould is defined by an isosurface of constant temperature, and thus the external shape of the ceramic shell mould is defined together with the thickness distribution of the ceramic shellmould. The concave surface of the turbine blade concentrates conductive heat flux like a lens reducing heat dissipation and causing the isosurfaces of constant temperature to be further apart, whereas the convex surface of the turbine blade causes theconductive heat flux to diverge increasing heat dissipation and causing the isosurfaces to be closer together.
It can be seen that the use of the isosurfaces of constant temperature results in the ceramic shell mould being thicker on the convex surface and thinner on the convex surface thus matching the real build up exhibited during the immersingtechnique. Furthermore it also produces bridging and smoothing out of features. The particular isosurface of constant temperature is selected to produce is required thickness distribution of ceramic.
Again in practice, as discussed above with reference to FIGS. 5A-5D, 6A-6E, 7A-7F, a CAD definition of a cylinder 102 is produced which is larger than, and encloses the CAD definition of the turbine blade 100. The CAD definition of the turbineblade 100 is subtracted from the CAD definition of the cylinder 102 to produce a hollowed cylinder CAD definition 104, the internal surface of which corresponds to the external surface of the CAD definition of the turbine blade 100. A finite elementmesh is automatically generated from the CAD definition of the hollowed cylinder 106. Tetrahedral linear finite elements are used. This definition completely describes the hollowed cylinder 106 by splitting the hollowed cylinder 106 into a collectionof small solid elements.
A high temperature boundary condition is applied to the internal surface 108 of the hollowed cylinder finite element (FE) mesh 106 and a low temperature boundary condition is applied to the external surface 110 of the hollowed cylinder finiteelement (FE) mesh. 106. These conditions are applied to enable and promote conductive heat flow through the hollowed cylinder 106 in a radially outward direction. A finite element thermal conduction analysis is run until steady heat flow is achievedat which point there are an infinite number of isosurfaces of constant temperature 112.
One isosurface of constant temperature 112 is selected which gives a certain thickness distribution of the ceramic mould 114 i.e. normal spatial deviation from the CAD definition of the turbine blade 100 to the isosurface of constant temperature112.
The process model of the molten metal solidification process then uses the CAD definition of the furnace, the CAD definition of the turbine blade and the definition of the external shape and thickness of the ceramic shell mould as inputs and thendetermines if the selected definition of the external shape and thickness of the ceramic shell mould in conjunction with the shape of the turbine blade and the casting furnace will result in cast turbine blade substantially without defects.
If the process model of the molten metal solidification process determines that the cast turbine blade will be free from defects then the CAD definition of the turbine blade is used to produce a pattern of the turbine blade, the wax pattern isdipped in the ceramic slurry the appropriate number of times, corresponding to the selected isosurface of constant temperature to produce the selected definition of the external shape and thickness of the ceramic shell mould. Then the wax pattern isremoved from the ceramic shell mould, and the ceramic shell mould is fired to strengthen the ceramic shell mould. The ceramic shell mould is then placed in the casting furnace, the molten metal is poured into the ceramic shell mould and the molten metalis solidified in the ceramic shell mould to produce the cast turbine blade. The turbine blade is then removed from the ceramic shell mould.
The CAD definition of the turbine blade may be used to produce the dies used in the wax injection process for making the wax patterns. Alternatively the CAD definition may be used to produce stereolithography resin patterns by controlling a beamof radiation which cures the resin.
The ceramic shell mould is produced with an internal shape defined by the pattern of the turbine blade and an external shape and thickness defined by the selected isosurface of constant temperature. The ceramic shell mould may be produced withthe external shape defined by the selected isosurface of constant temperature by controlling the number of times the pattern is immersed in the ceramic slurry. In this case the dipping process is calibrated to correlate the number of dips required tobuild up the ceramic shell mould to a thickness that approximates the thickness defined by the selected isosurface of constant temperature. Alternatively the ceramic shell mould may be produced with an external shape defined by the selected isosurfaceof constant temperature by machining a ceramic block to the required external shape.
If the process model of the molten metal solidification process determines that the cast turbine blade will not be free from defects then during the determination of the external shape and thickness of the ceramic shell mould another isosurfaceof constant temperature is selected corresponding to a ceramic shell mould thickness either one dip thicker or one dip thinner. The process model of the molten metal solidification process is rerun to determine if the newly selected definition of theexternal shape and thickness of the ceramic shell mould in conjunction with the shape of the turbine blade and the casting furnace will result in cast turbine blade substantially without defects.
If a cast turbine blade without defects is produced the wax patterns and ceramic shell mould with the newly selected thickness is produced and the metal is cast in the mould. If a cast turbine blade with defects is produced then a new isosurfaceis selected and the process model is rerun to determine if the newly selected external shape and thickness of the ceramic shell mould will produce cast turbine blades substantially without defects.
The solidification process preferably includes providing a temperature gradient across the turbine blade to produce a directionally solidified, or single crystal, turbine blade. The temperature gradient may be produced by placing the ceramicshell mould on a cooled chill plate, and moving the chill plate so that the ceramic shell mould is gradually removed from the casting furnace.
A resin pattern assembly 210, shown in FIG. 9, comprises a plurality of resin patterns 212 suitable for making turbine vanes or turbine blades for a gas turbine engine. Each of the resin patterns 212 has a first part 214, which defines the shapeof the root of the resulting cast turbine blade, a second part 216, which defines the shape of the platform of the cast turbine blade and a third part 218, which defines the shape of the aerofoil portion of the cast turbine blade. The turbine blades tobe cast in this example are single crystal turbine blades and therefore an associated resin selector part 220 and resin starter part 222 are connected to each resin pattern 212. The resin selector part 220 is a resin helix, although other suitable resinselectors may be used.
The resin patterns 212 and associated resin selectors 220 and resin starters 222 are arranged together on a resin gating tree 224 to form a resin pattern assembly 210. The resin gating tree 224 comprises a resin runner which includes a centraldownpole 226 and a plurality of feeders 228. The resin patterns 212 are arranged generally parallel to the central downpole 226 and the feeders 228 extend generally radially from the central downpole 226 to the resin patterns 212.
A resin mould assembly 230, shown in FIG. 9, comprises a first resin mould part 232 and a second resin mould part 234. The resin mould assembly 230 is arranged around the resin pattern assembly 210 and is spaced from the resin pattern assembly210 to form a chamber 240. A ceramic shell mould 70 similar to that shown in FIG. 2 is produced by injecting a ceramic slurry into the chamber 240 using a binderless, low pressure, low viscosity injection moulding process. The ceramic slurry comprisesa mono sized particulate ceramic system highly dispersed in a relatively volatile dispersant fluid. The dispersant fluid is then sublimated and the injected ceramic is allowed to cure and solidify. A ceramic slurry which is suitable for such aninjection moulding process is commercially available under the name `CPS Quickset` (Trade Mark), and has the property of isotropic shrinkage on sintering, resulting in mechanical properties and dimensional consistency superior to that of conventionalinjection moulding.
When curing of the ceramic is complete, the resin mould assembly 230 is removed together with the inserts leaving a ceramic shell mould surrounding the resin pattern assembly 210. The ceramic shell mould is then dried. The resin patternassembly 210 is then removed from the ceramic shell mould and the ceramic shell mould is fired. The ceramic shell mould is then tested for cracks before it is used for casting.
The resin pattern assembly 210 and the resin mould assembly 230 are produced by controlling a beam of radiation which cures the resin, ie the resin pattern assembly 210 and resin mould assembly 230 are produced by stereolithography. The resinpattern assembly 210 and resin pattern assembly 230 may be integral.
The CAD definition of the turbine blade 100 is used to produce the resin pattern assembly 210 by stereolithography by controlling the beam of radiation which cures the resin, and thus the internal shape 236 of the chamber 240 is defined by theCAD definition of the turbine blade. The external shape 238 and thickness of the chamber 240 is defined by the selected isosurface of constant temperature 112 and the selected isosurface of constant temperature 112 is used to produce the resin mouldassembly 230 by stereolithography by controlling the beam of radiation which cures the resin. The ceramic shell mould 114 thus has an internal shape 236 defined by the pattern of the turbine blade 100 and an external shape and thickness defined by theselected isosurface of constant temperature 112.
The use of stereolithography to produce a resin pattern assembly and resin mould assembly for producing a ceramic shell mould for investment casting has the advantage that it enables a substantial saving in development time and costs compared tothe long development time and high costs involved in producing dies for wax patterns, and enables castings to be made in six days or less compared to about twenty weeks or more for conventional lost wax casting and the ceramic shell mould produced bythis method mimics the ceramic shell mould produced by dipping so that the lessons learnt during the development can be applied to the dipped ceramic shell moulds. The resin pattern moulds are not sufficiently smooth and accurate to be used inproduction but provide sufficient accuracy for development purposes. The ceramic shell mould produced from the resin pattern assembly and resin mould assembly may be used in the method disclosed with reference to FIG. 8 but instead of producing theceramic shell mould by dipping the ceramic shell mould is produced by injecting into a resin pattern and resin mould assembly and the thickness of the ceramic shell mould is varied accordingly to produce satisfactory castings.
The novel and inventive feature of the present invention is the selection of the isosurface of constant temperature to define the external shape and thickness of the ceramic shell mould in order to produce a ceramic shell mould which more closelyresembles those produced by dipping a wax pattern into a ceramic slurry.
Similarly it is also within the scope of this invention to use other physical properties instead of temperature to select the shape and thickness of the ceramic shell mould. For example it may be possible instead of producing a thermal gradientacross the hollow cylinder to produce a pressure gradient across the hollow cylinder and to determine where the isosurfaces of constant stress are, and to select one of the isosurfaces of constant stress to define the outer surface of the ceramic shellmould. It is possible to use any other suitable physical property which is directional and has a flux and to determine isosurfaces of constant physical property values, and select one of the isosurfaces of constant physical property value.
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