Patent Application
20190168292
The present invention relates to a method for determining the position of a core in an injection mould, in particular a wax injection mould. This method is intended for the manufacture of parts for turbo machines, such as turbine blades.
Conventionally, the lost-wax casting technique first consists in making a model made of wax, or any other material, that can be easily removed later, of the part to be produced; this model includes an internal part forming a ceramic core that represents the cavities that may be desired inside the blading. The wax model is then dipped several times into a casting slip made of a suspension of ceramic particles to make a shell mould by so-called stucco and drying operations.
Wax is then removed from the shell mould, which is an operation by which wax or the material constituting the original model is removed from the shell. After this elimination, a ceramic mould, the cavity of which reproduces all the shapes of the blade and which still contains the ceramic core intended to generate the internal cavities of the blade is obtained. The mould then undergoes a high-temperature heat treatment or “curing” that gives it the necessary mechanical properties.
The shell mould is then ready for the production of the metal part by casting. After checking the internal and external integrity of the shell mould, the next step consists in pouring a molten metal, which fills the voids between the inner wall of the shell mould and the core, and then solidifying same. In the field of lost-wax casting, there are currently several solidification techniques, and therefore several casting techniques, depending on the nature of the alloy and the expected properties of the part resulting from the casting. These may be columnar structure directed solidification (DS), monocrystalline structure directed solidification (SX) or equiaxic solidification (EX).
After casting the alloy, the shell is broken by a stripping operation. In another step, the ceramic core that has remained enclosed in the resulting blade is chemically removed. The metal blade obtained is then subjected to finishing operations to obtain the finished part.
Exemplary embodiments of a turbine blade using the lost-wax casting technology are given in the Applicant's patent applications FR2875425 and FR2874186.
To form the wax model of the blade, a tool, or wax injection mould is used, in which the core is placed and then the liquid wax is injected through a channel provided for this purpose.
This core must be placed extremely precisely in the injection mould because any discrepancy in its positioning will result in non-conformities in the thickness of the blade walls. Since the blade metal is exposed to very high temperatures, these defects would result in significantly reduced blade life. It is therefore necessary to guarantee with great precision the position of the core in the mould. For this purpose, the moulds currently in use include means for statically supporting the core, with such means possibly including rods, the ends of which form support points to support the core in the mould.
While this type of core positioning is effective, it can nevertheless raise a number of difficulties. Indeed, the cores are made in a mould, the footprint of which corresponds to that of the core. However, even a minor manufacturing defect in the core manufacturing mould, an insufficiently precise estimate of the shrinkage and repeatability coefficients of the curing step following the casting operation, may lead to differences in wall thickness on the final part, which, although not leading to non-compliance, are not desirable. An obvious solution would obviously be to manufacture a new core injection mould that would comply with the manufacturing tolerances for the core. However, this solution is not desirable since the step of making a core manufacturing mould is very expensive, both from the financial point of view and from the point of view of the time required to make it.
The purpose of the invention is in particular to provide a simple, effective and economical solution to the problems of the prior art described above.
To this end, it proposes a method for determining the position of the cores in an injection mould, including the steps of:
According to the invention, a defect in the geometry of the cores is compensated by a repositioning of a representative core relative to the functional faces of the theoretical model. All cores are then positioned in an injection mould in the same way as the representative core is positioned in a mould. The method is therefore particularly interesting when the geometry defect (or defects) of the cores corresponds to a deviation of one dimension from a nominal value. The collection of k cores is carried out randomly.
The term “functional face” of the core refers to a face of the core intended to form, before assembling the part, a face with the final geometry of the part. Such a functional face is an outer face of the core that enables the shaping of the inner or outer faces of the metal part and has an impact on the aerodynamics and thermal properties of the part in operation. In the case of a turbine blade, a functional face can refer to an outer face of the core forming an inner face of a core wall, such as a front side or back side wall for example. The internal cavity of the blade can be a cavity for cooling the blade.
The term “three-dimensional model” in reference to a core should be interpreted as a set of digital data allowing a three-dimensional digital reconstruction of the core, for example using a geometric mesh.
The term “spatial” refers to a three-dimensional model positioned in space.
The term “relocated” refers to a three-dimensional spatial model that has been positioned or repositioned in space.
According to another characteristic, each three-dimensional model can be obtained from a three-dimensional survey of the outer surface of the core, for example from a contactless measurement that can be performed by optical triangulation. In such a configuration, a central projector illuminates a room with a network of fringes that are observed by two CCD cameras. A polygonal mesh of the outer surface of each of the cores is deduced from this.
In one particular embodiment of the invention, step d) may include the following steps:
In this alternative embodiment, the determination of the representative core is thus carried out by measuring the differences on a functional side after relocation on the support points. It is indeed interesting to measure the differences relative to at least one functional face since it is a face that has a direct impact on a corresponding face of the final part.
Also, step d) may include the following steps for each core RL:
Preferably, the method includes a checking step, between steps e) and f), consisting in verifying that the relocated spatial model V2 of the core Rrep is better positioned than the relocated spatial model V1 of the core Rrep.
If the relocation V2 is worse than the relocation V1, then the relocation V2 should be repeated on a smaller number of functional faces than the number of functional faces previously used.
The checking step includes the following steps:
The difference Ei,j1 and/or the difference Erep,j2 can be determined along the normal to the theoretical three-dimensional spatial model at the point Pj.
The repositioning of the support points in step f) can be done as follows, for each of the support points Tq:
In a practical embodiment of the invention, k is greater than or equal to five and/or l is greater than or equal to six and/or n is greater than or equal to three. In practice, n is a function of the curvature and tolerance of the functional face considered. The lower the curvature, the smaller n. Thus, the minimum number of n is three, which corresponds to the minimum number of points required to position a plane isostatically in space.
In the manufacture of a turbomachine part, the injection mould is a wax injection mould. The core can be a turbine blade core for example.
The invention will be better understood and other details, advantages and characteristics of the invention will appear in the following non-exhaustive illustrative description, with reference to
In a first step a) of the method, k cores noted R1 . . . Ri . . . Rk are selected in a population of cores, all based on the same theoretical three-dimensional core model. The term “population” here refers to a set of cores, the number of which can be determined or undetermined.
In a second step (b) of the method, a three-dimensional measurement of the external surface of each of the cores is obtained from a contactless measurement that can be an optical measurement, for example by optical triangulation as mentioned above. Of course, other methods of measurement could be used without going beyond the scope of the invention. For example, another method may consist in using a more accurate but much slower sensing device or a three-dimensional measuring machine (TDMM). The three-dimensional survey makes it possible to establish a three-dimensional model of each of the cores, i.e. a digital model including a set of coordinates of points on the surface of a core, thus enabling a relative positioning of the points.
In a third step c), the method includes a step of spatially positioning each of the three-dimensional models relative to l support points T1 . . . Tq . . . Tl of the core in the mould in order to obtain a three-dimensional spatial model V1 for each core. This positioning thus consists of a spatial relocation relative to the l support points.
In practice, this relocation can be achieved by minimizing the difference between the theoretical three-dimensional spatial model and the relocated three-dimensional spatial model V1 of each of the cores, at the level of points Tq. Minimizing can be done using the least squares method.
The method then consists, in a fourth step, in selecting the core noted Rrep, the three-dimensional spatial model V1 of which has the smallest deviation from the calculated mean deviations between the actual models and the theoretical three-dimensional spatial model. This step is executed on n points Pj noted P1 . . . Pj . . . Pn belonging to at least one of the functional faces of the theoretical model of the theoretical core. Preferably, the n points are distributed over a maximum number of functional faces. Preferably, the n points are distributed over the selected functional faces and a number of points per face is selected according to the curvature and tolerance applied to the face considered.
This step of selecting the core representative of the k cores is performed by executing the following steps:
In order to be able to determine the desired new position of the representative core Rrep in the mould, a second relocation of the three-dimensional model must then be performed, in a fifth step, by taking into account at least one functional face of the theoretical model of the core in order to obtain a relocated three-dimensional spatial model V2 of the core Rrep.
Unlike the relocation V1 performed for each of the cores, the relocation of the representative core Rrep is performed only on at least one of the functional faces and does not take into account the support points Tq. The aim here is to enable a repositioning of the representative core Rrep in order to minimize the shape differences between the part obtained from the representative core and a theoretical part from the theoretical core, with the constraint of the support points Tq being eliminated.
Before proceeding to the sixth step, i.e. step f), a preliminary step of checking the relocation of the three-dimensional spatial model of the core (V2) Rrep is performed. This checking step includes the following steps:
When Srep2 is greater than Srep1, several situations arise. If the relocation of the three-dimensional model of the core Rrep has been performed on only one functional face, then it is necessary to establish that the three-dimensional spatial model V1 of the core Rrep is preferable since it shows that the relocation of the cores on the functional faces does not make it possible to obtain a better positioning of the core. If the relocation of the three-dimensional model is performed on a plurality of functional faces, i.e. F functional faces, with F≥2, then the relocation of step e) is performed on F−1 functional faces and then it is determined whether the new relocation V2 of the three-dimensional spatial model Rrep is better than the relocation V1 of the core Rrep by comparing Srep2 with Srep1.
In a complementary approach, it would be possible to classify functional faces into at least two groups, with a first group of primary functional faces and a second group of secondary functional faces. The main functional faces are faces for which the manufacturing tolerances are lower than for the secondary functional faces so that the relocation performed in step e) can be performed preferentially on the main functional faces. Thus, if the relocation of step e) has to be performed again, it is preferable to remove the constraint of the relocation relative to a secondary functional face. Eventually, it will be necessary to check that the differences in the secondary functional faces between the theoretical three-dimensional spatial model and the new three-dimensional model V2 do not exceed the permissible manufacturing tolerances.
The sixth step f) consists in repositioning the support points Tq so that the core Rrep can be supported in the position corresponding to the relocated three-dimensional spatial model V2 of the core Rrep.
This repositioning is obtained by performing the following steps:
In practice, to carry out the second sub-step above, the distance between each pair of points Tq and T′q is determined, which gives us l distances. These distances correspond to the positioning corrections to be applied to the ends of the core support rods.
| Number | Date | Country | Kind |
|---|---|---|---|
| 1657663 | Aug 2016 | FR | national |
| Filing Document | Filing Date | Country | Kind |
|---|---|---|---|
| PCT/FR2017/052185 | 8/3/2017 | WO | 00 |
