FOUNDRY MOLD, METHOD FOR MANUFACTURING THE MOLD AND FOUNDRY METHOD

Abstract

A foundry mold includes at least one molding cavity and one pair of feeder arms. The molding cavity extends, along a horizontal axis, from a first end to a second end, and the first pair of feeder arms comprises a first feeder arm, oriented in a substantially vertical direction and connected to the first end of the first molding cavity, and a second feeder arm, substantially parallel to the first feeder arm and connected to the second end of the first molding cavity.

Claims

1. A foundry mold including at least: a first molding cavity extending, along a horizontal axis, from a first end to a second end, a first pair of feeder arms comprising: a first feeder arm, oriented in a substantially vertical direction and connected to the first end of the first molding cavity, and a second feeder arm, substantially parallel to the first feeder arm and connected to the second end of the first molding cavity, wherein any transverse section of the first and second feeder arms of the first pair of feeder arms, perpendicular to a vertical axis, has a greater area than any transverse section of the first molding cavity perpendicular to the horizontal axis.

2. The foundry mold according to claim 1, comprising docking heads connecting the first and second ends of the first molding cavity to the respective feeder arms of the first pair of feeder arms, each docking head having a transverse section, perpendicular to the horizontal axis, with an area greater than any transverse section of the first molding cavity perpendicular to the horizontal axis, but smaller than any transverse section of the first and second feeder arms of the first pair of feeder arms perpendicular to the vertical axis.

3. The foundry mold according to claim 1, wherein the first and second feeder arms of the first pair of feeder arms have transverse sections, perpendicular to the vertical axis, with areas increasing upward along the vertical axis.

4. The foundry mold according to claim 1, comprising a first row of molding cavities, including the first molding cavity, each molding cavity of the first row of molding cavities extending, along a respective horizontal axis from a first end to a respective second end, the first end of each molding cavity of the first row of molding cavities being connected to the first feeder arm of the first pair of feeder arms, and the second end of each molding cavity of the first row of molding cavities being connected to the second feeder arm of the first pair of feeder arms.

5. The foundry mold according to claim 4, comprising at least a second row of molding cavities and a second pair of feeder arms, each molding cavity of the second row of molding cavities extending, along a respective horizontal axis, from a first end to a respective second end, the first end of each molding cavity of the second row of molding cavities being connected to the first feeder arm of the second pair of feeder arms, and the second end of each molding cavity of the second row of molding cavities being connected to the second feeder arm of the second pair of feeder arms.

6. The foundry mold according to claim 1, wherein the upper ends of the feeder arms are connected to a feeder.

7. The foundry mold according to claim 1, wherein the first molding cavity is configured to mold a turbine engine blade extending from a blade tip to a blade root along the horizontal axis.

8. The foundry mold according to claim 1, configured as a shell mold.

9. A manufacturing method for the foundry mold according to claim 8, comprising: dipping a non-permanent pattern in a slurry; dusting the non-permanent pattern, after dipping, with granules of a refractory material to form a layer of granules of refractory material coated with slurry; removal of the non-permanent pattern from a shell formed by the granules of refractory material coated with slurry; and baking the shell.

10. A casting method, comprising: pouring a metal in the liquid state into the foundry mold according to claim 1; cooling and solidification of the metal in the foundry mold; and demolding of the solidified metal.

11. The casting method according to claim 10, comprising: preheating the foundry mold in an oven prior to the pouring, and in which the mold is held in the oven until and during the pouring.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0015] The invention will be better understood and its advantages will appear more clearly upon reading the detailed description that follows, of an embodiment shown by way of a non-limiting example. The description refers to the appended drawings in which:

[0016] FIG. 1A is a first section view of a foundry mold according to one aspect of the invention,

[0017] FIG. 1B is a section view, perpendicular to FIG. 1 in the plane IB-IB,

[0018] FIG. 2A is a side view of a cluster of non-permanent patterns intended to form the mold of FIGS. 1A and 1B,

[0019] FIG. 2B is a front view of the cluster of FIG. 2A,

[0020] FIG. 3A illustrates a dipping step in a manufacturing method of the mold of FIGS. 1A and 1B starting with the cluster of FIGS. 2A and 2B,

[0021] FIG. 3B illustrates a dusting step in the manufacturing method of the mold of FIGS. 1A and 1B starting with the cluster of FIGS. 2A and 2B,

[0022] FIG. 3C illustrates a baking step in the manufacturing method of the mold of FIGS. 1A and 1B starting with the cluster of FIGS. 2A and 2B,

[0023] FIG. 4A illustrates a pre-heating step in a casting method using the mold of FIGS. 1A and 1B,

[0024] FIG. 4B illustrates a pouring step in the casting method using the mold of FIGS. 1A and 1B,

[0025] FIG. 4C illustrates a cooling step in the casting method using the mold of FIGS. 1A and 1B,

[0026] FIG. 4B illustrates a knockout step in the casting method using the mold of FIGS. 1A and 1B, and

[0027] FIG. 5 illustrates in detail the propagation of two solidification fronts starting from the central zone of a molding cavity of the mold of FIGS. 1A and 1B.

DESCRIPTION OF THE EMBODIMENTS

[0028] A foundry mold 1 according to one embodiment of the invention is illustrated in FIGS. 1A and 1B. As can be seen in these figures, the mold 1, which is of the “shell mold” type, can comprise several molding cavities 2. Each of these molding cavities 2 can extend, along a first horizontal axis X, from a first end 2a to a second end 2b, in such a manner that the first horizontal axis X forms it main axis, and be formed to mold a turbine engine blade extending from a blade tip to a blade root along this first horizontal axis X. However, the technical teaching of the present disclosure are also applicable to the casting of other types of parts.

[0029] The mold 1 can also include several pairs of feeder arms, each of which can comprise a first feeder arm 3 and a second feeder arm 4. Each of these feeder arms 3, 4 can be oriented along a respective main axis in the direction of a substantially vertical axis Z. Each pair of feeder arms 3, 4 can be associated with a row off molding cavities 2 vertically offset from one another. Thus, in each row of molding cavities 2, the first end 2a of each molding cavity 2 can be connected to the first feeder arm 3 of the respective pair of feeder arms 3, 4 by a first docking head 5, and the second end 2b of each molding cavity 2 be connected to the second feeder arm 4 of the respective pair of feeder arms 3, 4 by a second docking head 6. The pairs of feeder arms 3, 4 can be laterally offset from one another in the direction of a second horizontal axis Y, substantially perpendicular to the first horizontal axis X. The molding cavities 2 can also be arranged in several rows densely occupying the volume of the mold 1. When the molding cavities 2 are configured to form turbine engine blades, the first and second docking heads 5, 6 can correspond, respectively, to the blade root and to a blade tip bead.

[0030] As illustrated, the mold 1 can have at its top a feeder 7 shaped like a funnel, connected to the tops of the feeder arms 3, 4 of each pair of feeder arms by a network of feeder channels 8.

[0031] To avoid piping defects, it is possible to apply the method of Heuvers' circles, as described for example by R. Wlodawer in Directional Solidification of Steel Castings, Pergamon Press, 1966, in such a manner that the area Ab of any transverse section S.sub.b of the first and second feeder arms 3, 4 of each pair, perpendicular to the vertical axis Z, is greater than the area A.sub.c of any transverse section S.sub.c of the molding cavities 2 of the corresponding row, perpendicular to the first horizontal axis X. In addition, each docking head 5, 6 can have a transverse section St with an area A.sub.t, perpendicular to the horizontal axis X, greater than the area A.sub.c of any transverse section Sc of the corresponding molding cavity 2, perpendicular to the horizontal axis X, but less than the area A.sub.b of any transverse section Sb of the corresponding feeder arm 3, 4 of the first pair of feeder arms perpendicular to the vertical axis Z. Moreover, each feeder arm 3, 4 can have transverse sections Sb with area A.sub.b increasing upward along the vertical axis. As illustrated in FIG. 1A, this can be obtained with a divergence angle α of, for example, between 5 and 15° between opposite edges of the feeder arm 3, 4. Thus, as illustrated in FIG. 5, the solidification of the metal, which can be triggered within each molding cavity 2, where the transverse section is narrowest, will be able to extend until the feeder arms 3, 4 with two opposite and constantly increasing solidification fronts 10, 11, thus avoiding piping defects which can be caused by constrictions in the cavities of the mold.

[0032] Moreover, in order to limit the stresses transmitted by the mold 1 to the metal solidifying in the molding cavities 2 in the locates where they are thinnest, for example at the trailing edges of turbine engine blades, it can be contemplated that the walls of the mold 1 are thinner at these locations than at other locations of the mold 1.

[0033] A first step of the method for manufacturing the mold 1 can be the creation of a non-permanent cluster 21 comprising a plurality of patterns 22, as illustrated in FIGS. 2A and 2B. The portions of the cluster 21 intended to form hollow volumes in the mold 1, such as the patterns 22 intended to form the molding cavities 2, the vertical arms 23 intended to form the feeder arms 3, 4, the cone 24 intended to form the gate 7, and the connection 25 connecting the cone 24 and the feeder arms 3, 4 to form the feeder channels 8, can be formed of a material with a low fusion temperature such as a wax or a modeling resin. When the production of a great number of parts is considered, it is possible in particular to produce these elements by injecting wax or modeling resin into a permanent mold. In the embodiment illustrated, intended for the production of turbine engine blades, the patterns 22 show blades of this type oriented horizontally.

[0034] The non-permanent cluster 21 can also comprise refractory elements to ensure its structural integrity, such as for example descenders (not illustrated). These descenders can be located on the laterals, in order to free the space below the gate 7 to accommodate additional molding cavities 2 there, but it can also be contemplated to have only a single refractory descender located, for example, centrally under the cone 24.

[0035] To produce the mold 1 starting with this non-permanent cluster 21, it is possible to proceed with the dipping of the cluster 21 in a slurry B, as illustrated in FIG. 3A, to then dust it with a refractory sand S, i.e. granules of refractory material, as illustrated in FIG. 3B. The materials use for the slurry B and the refractory sand, as well as the granulometry of the refractory sand S can for example be those disclosed in the French patent application publications FR 2 870 147 A1 and FR 2 870 148 A1. Thus the slurry B can for example contain particles of ceramic materials, particularly in the form of flour, with a mineral colloidal binder and possibly with adjuvants depending on the rheology desired for the slurry, while the refractory sand S can also be ceramic. Among the ceramic materials which can be considered for the slurry B and/or the refractory sand S are alumina, mullite and zircon. The colloidal mineral binder can for example be a water-based colloidal mineral solution, such as for example colloidal silica. The adjuvants can comprise a wetting agent, a thinner and/or a texturing agent. These dipping and dusting steps can be repeated several times, possibly with different slurries B and sands S, until a shell C of sand impregnated with slurry is formed to a desired thickness around the cluster 21. This thickness can be adapted to different locations of the mold, for example by locally limiting some of the dusting.

[0036] The cluster 21, coated with this shell C, can then be heated, for example in an autoclave 200, to a temperature between 160 and 180° C. and at a pressure of 1 MPa to melt and remove from the interior of the shell the low-fusion-temperature material of the cluster 21. Then, in a baking step at a higher temperature, for example between 900 and 1200° C., the slurry B can solidify so as to consolidate the refractory sand S to form the refractory walls of the mold 1, as illustrated in FIG. 3C.

[0037] In a casting method using the mold 1, before proceeding with pouring the metal in the liquid state into this mold 1, it is possible to proceed with a step of preheating this mold 1, as illustrated in FIG. 4A. In this step, after introducing the mold 1 into an oven 100, the mold 1 can be heated in the oven 100, which can reach a first temperature T.sub.1. Then, without removing the mold 1 from the oven 100, while maintaining the oven 100 at the first temperature T.sub.1, it is possible to proceed with the pouring of the metal M in the liquid state into the mold 1, as illustrated in FIG. 4B, so as to fill the hollow volumes of the mold 1, and in particular its molding cavities 2. The metal can be poured into the mold at a second temperature T.sub.2, greater than the first temperature T.sub.1. However, the temperature difference ΔT between the second temperature T2 and the first temperature T.sub.1 can be limited, for example no larger than 170° C., or 100° C., or even 80° C. Thus if the metal is, for example, a nickel-based equiaxial alloy of the Rene 77 type, with a solidus at 1240° C. and a liquidus at 1340° C., the second temperature T.sub.2 can for example be 1450° C., and the first temperature T.sub.1 then be 1350° C., with a difference ΔT no greater than 170° C. Thus, an excessive thermal shock of the melted metal poured into the mold 1, thus reducing the risk of premature and unintentional solidification of the metal in the narrowest passages of the mold 2, a solidification which could cause blockages and local defects in the parts thus produced. The pouring of the liquid metal is carried out rapidly and thus completed in a time t.sub.v, which can for example be approximately 2 seconds, or even a single second.

[0038] In the following step, illustrated in FIG. 4C, the mold 1 can still be maintained in the oven 100 for a first cooling and solidification step of the metal M in the mold 1, in which the cooling rate dT/dt of the oven 100 can be controlled and limited, for example, to approximately 7° C./min at most. This upper limit to the cooling rate also allows limiting the forces exerted on the metal by the difference in thermal contraction between the mold 1 and the cooling metal. Nevertheless, the thermal contraction of the metal M, greater than that of the refractory walls of the mold 1, will cause buckling of the metal in the feeder arms 3, 4 illustrated in dotted lines in FIG. 4C, a buckling which will exert a compression stress on the metal M in the molding cavities 2, so as to balance at least partially the tension stresses caused by the thermal contraction of the metal M in the molding cavities 2. It is thus possible to avoid force concentrations which can perturb the crystallization of the metal and cause weak points in the parts resulting from this casting method.

[0039] In the embodiment illustrated, as the alloy of the Rene 77 type is a polycrystalline equiaxial alloy, the metal will form, during its solidification, a plurality of grains of substantially identical size, typically of the order of 1 mm, but with a more or less random orientation.

[0040] When the oven 100 has cooled sufficiently, until it reaches a third temperature T.sub.3 of between 800° C. and 900° C. for example, it is possible to withdraw the mold 1 from the oven 100 so that it continues to cool naturally after having been placed under an insulating bell surrounded by refractory fabric, until the step of knocking-out the shell illustrated in FIG. 4D, in which the mold is destroyed to remove the solidified metal from it, comprising the turbine engine blades 100 thus formed, on which the subsequent steps of cutting out and finishing can then be carried out.

[0041] Although the present invention has been described by referring to a specific exemplary embodiment, it is clear that different modifications and changes can be carried out on this example without departing from the general scope of the invention as defined by the claims. Consequently, the description and the drawings should be considered in an illustrative, rather than a restrictive sense.