SYSTEM FOR INJECTING AN INJECTION MATERIAL INTO A MOLD FOR MANUFACTURING AN AIRCRAFT ENGINE THRUSTER RADIATOR GRILLE

Abstract

The invention relates to a system (10) for injecting a material into a mold. The mold internally defines filling cavities arranged to form a grid structure created by the intersection of longitudinal cavities (L1-L7) and transverse cavities intended to be filled with an injection material to form, respectively, intersecting spars with rows of transverse blades of a thrust reverser grid of an aircraft engine. The injection system comprises a plurality of injection points for a material opening into an upper zone (Zs) of the mold cavities corresponding to one of the two opposite faces of the grid. The injection points comprise, on the one hand, a first set of points (Pi1-Pi4) arranged in a front portion (Pav) of the mold and, on the other hand, a second set of points (Pi5-Pi8) arranged in a rear portion (Par) of the mold. Figure for the abstract: Fig. 2

Description

Title of the invention: SYSTEM FOR INJECTING AN INJECTION MATERIAL INTO A MOLD FOR PRODUCING AN AIRCRAFT ENGINE THRUST REVERSER GRID Technical field

[0001] The present disclosure relates to a system for injecting a material into a mold for the injection-molding of a thrust reverser grid for an aircraft reactor. Prior art

[0002] An aircraft jet engine thrust reverser grid generally comprises a plurality of spars each extending axially in a longitudinal direction X and the spars are arranged parallel to each other while being spaced from each other in a transverse direction Y. The grid also comprises a plurality of blades extending between the spars in the transverse direction Y, spaced from each other in the longitudinal direction X. The blades define with the spars a plurality of cavities through which a thrust reversing airflow can flow to perform the thrust reversing function of the jet engine. Each blade extends transversely between two consecutive spars to which it is connected by two respective opposite connecting edges.Each blade also extends in a direction Z perpendicular to the longitudinal directions X and transverse directions Y, from a so-called leading edge and to an opposite edge, called the trailing edge, and according to a curvature so as to form an aerodynamic profile of the blade between the two edges.

[0003] Such an inverter grid can be manufactured by injection molding in a mold. However, when producing such a grid by injection, an injection point of the material in the mold represents an area where the microstructure of the injected material has a random orientation, that is to say that the material is not oriented in the desired direction, which gives rise to a zone of structural weakness, called KDF, in the structure of the grid thus injected.

[0004] Furthermore, given the shape to be injected which includes crossings and branches, the material injected into the mold advances on several fronts which can join depending on the crossings and branches of the shape to be injected. The areas of the injected structure where these material fronts join are called bonding lines and are subject to significant structural weaknesses.

[0005] In addition, the thin thickness of the blades, their large number and the extent of the part to injecting can make it difficult to fill the shape by a single injection point.

[0006] In view of the above, it would therefore be interesting to be able to manufacture an aircraft jet engine thrust reverser grid by injection molding, at least partially overcoming the drawbacks set out above. Statement of the invention

[0007] The invention thus relates to a system for injecting a material into a mold for manufacturing by injection a thrust reverser grid of an aircraft reactor, the mold internally defining filling cavities arranged relative to each other so as to form a grid structure formed by the intersecting of longitudinal cavities extending in a longitudinal direction X and transverse cavities extending mainly in a transverse direction Y in the form of rows, the longitudinal and transverse cavities being intended to be filled with an injection material injected by the injection system to respectively form longitudinal spars intersecting with rows of transverse blades of a thrust reverser grid, the transverse blades each comprising a leading edge and a trailing edge which are respectively arranged at two opposite faces of the grid,the mold comprising, along the longitudinal direction of the longitudinal cavities, a so-called front part and a so-called rear part, the injection system comprising a plurality of injection points for an injection material which open into one of the zones of the longitudinal and transverse cavities of the mold corresponding to a face and / or the opposite face of the thrust reverser grid, the plurality of injection points comprising, on the one hand, a first set of injection points arranged in the front part of the mold and, on the other hand, a second set of injection points arranged in the rear part of the mold.

[0008] The arrangement of a plurality of injection points according to such a first set and such a second set which are respectively arranged in line with two distinct parts of the mold (front and rear parts) spaced from each other according to the longitudinal dimension of the latter (longitudinal dimension of the longitudinal cavities) makes it possible to minimize the impact of the structural weaknesses due to the injection points on the structural performance of the thrust reverser grid thus manufactured by injection.

[0009] According to other possible characteristics, taken alone or in combination: - the injection points of the first set of injection points are arranged at intersections between a set of longitudinal cavities and at least one row of transverse cavities of the mold; -the injection points of the second set of injection points are arranged at right of intersection between a set of longitudinal cavities and at least one row of transverse cavities of the mold; -the set of longitudinal cavities comprises longitudinal cavities which are arranged alternately; -the set of longitudinal cavities includes the two longitudinal cavities which frame the other longitudinal cavities; -for a mold having a grid structure with an even number of longitudinal cavities, the set of longitudinal cavities comprises the two longitudinal cavities located at the center of all the longitudinal cavities; -for a mold having a grid structure with an even number of longitudinal cavities, the two longitudinal cavities located at the center of all the longitudinal cavities are not part of the set of longitudinal cavities; - each of the injection points of the plurality of injection points has an injection diameter of between 2 and 8 mm, preferably between 3 and 5 mm; - the injection system includes a third group of injection points; - the injection system further comprises a plurality of ejection points which emerge from an area of ​​the longitudinal and transverse cavities of the mold which is opposite the area where the injection points are arranged, the plurality of ejection points comprising, on the one hand, a first set of ejection points arranged in the front part of the mold at the intersections between the longitudinal cavities and at least one row of transverse cavities of the mold and, on the other hand, a second set of ejection points arranged in the rear part of the mold at the intersections between the longitudinal cavities and at least one row of transverse cavities of the mold;

[0010] - each of the plurality of ejection points has a diameter ejection between 4 and 6mm.

[0011] The invention also relates to a thrust reverser grid manufactured by injection using the injection system briefly described above.

[0012] The invention further relates to a method for injecting a material into a mold for manufacturing by injection a thrust reverser grid of an aircraft reactor, the method using the injection system briefly described above.

[0013] According to a possible characteristic, the injection of the injection material into the mold begins by injecting the injection material through the injection points of the first set of injection points and continues by also injecting the injection material through the injection points of the second set of injection points. Brief description of the drawings

[0014] Other characteristics and advantages of the subject of the present disclosure will emerge from the following description of embodiments, given as non-limiting examples, with reference to the appended figures.

[0015] [Fig. 1] [Fig.l] is a schematic general view of a grid structure formed by the intersecting of longitudinal and transverse cavities of a mold according to one embodiment of the invention;

[0016] [Fig.2] [Fig.2] is a schematic general view of an injection system according to an embodiment of the invention;

[0017] [Fig.3A] [Fig.3A] is a schematic general view showing an arrangement of the injection points on a structure with an even number of longitudinal cavities according to an exemplary embodiment;

[0018] [Fig.3B] [Fig.3B] is a schematic general view showing an arrangement of the injection points on a structure with an even number of longitudinal cavities according to another exemplary embodiment;

[0019] [Fig.4] [Fig.4] is a schematic view of the arrangement of an injection point re relative to a transverse cavity defined between two parts of a mold;

[0020] [Fig.5] [Fig.5] is a schematic view of the arrangement of two points injection at the right of two longitudinal cavity-row of transverse cavities crossings;

[0021] [Fig.6] [Fig.6] is a schematic general view showing the arrangement of points ejection at the right of several longitudinal cavity-row of transverse cavities crossings on the side of the mold which is opposite the side illustrated in figures 1 and 2;

[0022] [Fig.7] [Fig.7] is a schematic general view of an inverter grid of aircraft reactor thrust according to an embodiment of the invention and which was obtained with the injection system of [Fig.2]. Detailed description

[0023] [Fig.l] is a schematic view whose purpose is to show in a top view, in a very simplified manner, the internal zones or cavities defined by the internal structure of a mold used for the manufacture of a thrust reverser grid of an aircraft reactor according to an embodiment of the invention. The configuration illustrated in [Fig.l] is a grid or matrix structure which is imparted by the intersecting of a plurality of lines L1 to L7 (the number is only illustrative) and columns or rows R1-R4, ..., Ri, ..., Rn-1, Rn.

[0024] In the mold, the lines represent longitudinal filling cavities internal to the mold and which correspond, in the thrust reverser grid which will be injection molded, to a plurality of spars which extend in the longitudinal direction X.

[0025] The columns represent rows of trans-filling cavities internal to the mold and which correspond, in the thrust reverser grid, to a plurality of rows of blades which extend in the transverse direction Y. Each blade extends transversely between two consecutive spars in the grid.

[0026] The injection of an injection material into the mold so that it fills the longitudinal and transverse cavities of the aforementioned structure, will make it possible to produce, by injection molding, a thrust reverser grid comprising a plurality of longitudinal spars intersecting with a plurality of rows of transverse blades.

[0027] It will be noted that the shape of the filling cavities, in particular the transverse cavities, is of course not strictly transverse insofar as the blades formed in these cavities are not rectilinear and do not extend solely in a plane comprising the longitudinal direction X and a perpendicular direction Z corresponding to the height of the grid. Indeed, these blades extend in the direction Z but also in both the longitudinal X and transverse Y directions to adopt a curvature having an aerodynamic profile shape with a leading edge located at a first face of the grid and a trailing edge located at a second opposite face of the grid, the position of the trailing edge here being offset longitudinally relative to the position of the leading edge. The two opposite faces of the grid are spaced apart from each other in the direction Z.Therefore, the internal configuration of the mold which makes it possible to define such transverse cavities is more complex than that of [Fig.l] which has been oversimplified for the purposes of the presentation. The internal configuration of two successive transverse cavities Cti, Cti+1 of the mold located between two longitudinal cavities not visible here, following a projection view in a plane defined by the X and Z directions, is illustrated in [Fig.4] which will be described later.

[0028] The internal schematic structure of the mold shown in [Fig.l] has been deliberately separated into two parts Pav and Par which are spaced apart from each other along the longitudinal direction X. One of the parts is called the front part and the other part called the rear part, relative to the position of the corresponding thrust reverser grid in an aircraft engine where the front part corresponds to the part of the grid which is located closest to the inlet of the nacelle of the aircraft engine. These two parts do not necessarily correspond to the two halves of the mold along its length.They are in fact defined in order to make it clear that the injection of injection material into the mold must be carried out at least in two separate places in the mold, distant from each other in the longitudinal direction (in order not to create rebonding lines and areas of structural weakness or significant KDF), and not in a single area of ​​the mold, such as for example the cor area. corresponding to the front part of the mold in the example considered (zone corresponding in the thrust reverser grid to the part located closest to the nacelle entrance).

[0029] [Fig. 2] illustrates very schematically a system for injecting an injection material into the internal cavities of the mold previously described with reference to [Fig. 1]. In [Fig. 2], only the very schematic grid structure of the mold has been illustrated by representing the intersecting of the longitudinal cavities L1-L7 and the rows Rl-Rn of transverse cavities. The mold is thus represented with an upper zone Zs of the longitudinal and transverse cavities which is oriented upwards. This upper zone corresponds to a first face of the thrust reverser grid to be molded where the leading edges of the blades are located. The opposite lower zone Zi of the longitudinal and transverse cavities, corresponding to a second opposite face of the thrust reverser grid where the trailing edges of the blades are located, is not visible in this figure.

[0030] As shown in [Fig. 2] and designated by the general reference number 10, the injection system comprises a plurality of injection points (Pii to Pi8) of an injection material which opens into one of the end faces in the Z direction of the part to be molded. This is the upper end face. It will be noted, however, that in an alternative embodiment not shown, the end face at which the material is injected may be the lower face of the part to be molded. According to another alternative embodiment not shown, the material may be injected at both the upper and lower faces of the part to be molded. In the embodiment of [Fig. 2] the injection points of this plurality of injection points each open at a crossing between a longitudinal cavity and a transverse cavity of the mold.

[0031] However, in an alternative embodiment not shown, the injection points of the plurality of injection points may open at a location other than longitudinal cavity-transverse cavity intersections on the mold.

[0032] As shown in [Fig.2], the plurality of injection points is distributed between the two mold parts Pav and Par so that a first set of injection points is arranged in the front part Pav of the mold and a second set of injection points is arranged in the rear part Par of the mold.

[0033] However, in an alternative embodiment not shown, the plurality of injection points may further comprise a third set of injection points, for example arranged in a central part, between the two front and rear parts of the mold.

[0034] In the embodiment of [Fig.2] the injection points of the first set of injection points are all arranged on the same row of transverse cavities and only on certain longitudinal cavities which form a set of longitudinal cavities, for example on longitudinal cavities arranged alternately with each other. The alternating arrangement is however not systematic and it is therefore conceivable that no injection point is arranged on two consecutive longitudinal cavities or, on the contrary, that two injection points are arranged respectively on two consecutive longitudinal cavities. It should be noted that the end longitudinal cavities, that is to say the two longitudinal cavities which frame the other longitudinal cavities, such as for example L1 and L7 in [Fig.2], each accommodate an injection point.

[0035] In the embodiment of [Fig. 2] the injection points of the second set of injection points are all arranged on the same row of transverse cavities and only on certain longitudinal cavities which are the same longitudinal cavities as those of the first set of injection points, for example on longitudinal cavities arranged alternately with respect to each other. The alternating arrangement is however not systematic and it is therefore conceivable that no injection point is arranged on two consecutive longitudinal cavities or, on the contrary, that two injection points are arranged respectively on two consecutive longitudinal cavities. It should be noted that the end longitudinal cavities, that is to say the two longitudinal cavities which frame the other longitudinal cavities, such as for example L1 and L7 in [Fig. 2], each accommodate an injection point.

[0036] In the example shown in [Fig.2], the number of longitudinal cavities of the mold is odd and the injection points Pii, Pi2, pi3 and Pi4 of the first set are all arranged on longitudinal cavities alternating with each other, for example, on the cavities L1, L3, L5 and L7, and more particularly at the intersection of these cavities with one of the rows of transverse cavities, here R2. The same applies to the injection points Pi5, Pi6, Pi7 and Pi8 of the second set which are arranged at the intersection of the same longitudinal cavities L1, L3, L5 and L7 with another row of transverse cavities, here R9, located in the rear part of the mold. It should be noted that one and / or the other of the first and second sets of injection points may comprise other injection points arranged at intersections between the set of longitudinal cavities defined above and another row of transverse cavities.

[0037] As shown very schematically in [Fig.3A], when the number of longitudinal cavities in the mold is even (in this example, the number is equal to eight but can of course take other values), the injection points Pi (first set), Pi+1 (second set) are arranged alternately on the longitudinal cavities from the two end longitudinal cavities C11 and C18, thus leaving without injection point the two central longitudinal cavities C14 and C15.

[0038] [Fig.3B] illustrates, for its part, another configuration in which the mold comprises an even number of longitudinal cavities (in this example, the number is equal to six but can of course take other values) and the injection points P'i, P'i+1 are arranged alternately on the longitudinal cavities from the two end longitudinal cavities Cl'1 and C1'6, thus resulting in a configuration where the two central longitudinal cavities Cl'3 and Cl'4 each comprise two injection points.

[0039] It will be noted that the injection system 10 comprises a structure for supplying the injection material (e.g. resin) to the injection points which can take different configurations depending on the number and location of the injection points, as well as the internal configuration of the mold. In [Fig. 2], the injection system 10 comprises for example a simple structure formed by an arrangement of vertical conduits or channels for supplying an injection material (one conduit per injection line) 12, 14, 16, 18 for the front part Pav and 20, 22, 24 and 26 for the rear part Par (these conduits can come from a single upstream conduit, not shown, for supplying injection material) each opening onto a given injection point (Pii to Pi8). Each of the conduits 12, 14, 16, 18, 20, 22, 24 and 26 is for example provided with a controllable shutter (nozzle) to manage the opening and closing and the application of pressure to the material.According to a possible example of an injection sequence, the injection material is first injected into the mold through the injection points in the front part of the mold, and then the material is injected, in addition, through the injection points in the rear part of the mold. If the plurality of injection points further comprises a third set of injection points (one in front, one in the central part and one in the rear), each set can be implemented one after the other, starting from the set located at the front for example, to end with the simultaneous injection by all three sets. Other examples of an injection sequence are conceivable and, for example, the material is injected simultaneously by both sets of injection points (or simultaneously by all three sets of injection points in such a configuration).

[0040] Figures 4 and 5 are partial schematic views of the mold which illustrate an example of positioning of the injection points in the mold relative to the longitudinal and transverse cavities.

[0041] More particularly, [Fig. 4] shows, in a view in a plane X, Z, two parts M1 and M2 of the mold which are arranged here one above the other and arranged relative to each other along a joint plane comprising two bearing surfaces 40, 42, here horizontal, and an inclined closing zone 44 connecting the two bearing surfaces together. The two parts M1 and M2 define transverse cavities between them, here two cavities Cti and Cti+1, which are successively arranged along the X axis between two consecutive longitudinal cavities not shown (in [Fig.5] described below the cavity Cti+1 is arranged between the two consecutive longitudinal cavities Li and Li+1). An injection point Pin is shown in this figure and opens in this example onto the upper zone Zs of the mold, close to the leading edge of the blade to be formed (in a variant not shown, the injection point is arranged at the level of the lower opposite zone Zi of the mold, close to the trailing edge of the blade to be formed). In the mode of [Fig.4], this injection point is located above a crossing between the transverse cavity Cti+1 and the longitudinal cavity Li not shown located in the background but which is visible in [Fig.5]. The injection point Pin thus opens into the cavity Cti+1.

[0042] [Fig. 5] shows in partial top view the upper part Ml of the mold with two injection points Pin and Pin+1 located on the same row of transverse cavities Ri illustrated in dotted lines in the background and on two longitudinal cavities arranged alternately. The injection points Pin and Pin+1 are more particularly arranged respectively at the intersections of the longitudinal cavities Li and Li+2 and the row of transverse cavities Ri. The row of transverse cavities Ri comprises a plurality of transverse cavities of which only some are shown: C'ti+1, Cti+1, C”ti+1 and C'”ti+1. Thus, the injection point Pin makes it possible to inject into the mold an injection material which will be distributed in the longitudinal cavity Li and in the transverse cavities C'ti+1 and Cti+1.Similarly, the injection point Pin+1 allows injection material to be injected into the mold, which will be distributed in the longitudinal cavity Li+2 and in the transverse cavities C”ti+1 and C'”ti+1.

[0043] This injection configuration will therefore be applied by following the configuration of the injection system of [Fig.2] with the injection points defined therein (Pii to Pi8) but can of course be applied to injection systems with other configurations of injection points not shown here (e.g.: different number and position of points). The injected material will therefore be distributed in two distinct zones of the mold, distant from each other, which makes it possible to better control and distribute its distribution than if a single injection zone were envisaged (for example on a single row of transverse cavities).

[0044] The injection system 10 further comprises a plurality of ejection points for the injected part which emerge from a zone Zi, here lower, opposite the zone Zs of the injection points of the longitudinal and transverse cavities of the mold. The zone Zi corresponds here to the second opposite face of the thrust reverser grid, that is to say the one where the trailing edges of the blades of the grid will be located. The plurality of ejection points comprises, on the one hand, a first set of ejection points arranged in the front part Pav of the mold at the intersections between the longitudinal cavities and at least one row of transverse cavities of the mold and, on the other hand, a second set of ejection points arranged in the rear part Par of the mold at the intersections between the longitudinal cavities and at least one row of transverse cavities of the mold. This arrangement of the ejection points facilitates the demolding of the part without excessive mechanical stress on the material. According to a variant not shown, an ejection point is provided at each longitudinal cavity-transverse cavity intersection in order to avoid any deformation during ejection.

[0045] In the example illustrated in [Fig. 6] which is a simplified schematic view from below (as opposed to the view in [Fig. 2]) of the grid structure formed by the intersecting cavities of the mold, the first set of ejection points is arranged at the intersections of all the longitudinal cavities L1 to L7 and of a single row of transverse cavities. The second set of ejection points, for its part, is arranged at the intersections of all the longitudinal cavities L1 to L7 and of a single other row of transverse cavities. This arrangement can also be applied with a different number of longitudinal cavities. In [Fig. 4] an ejection point Pej is shown in the lower zone Zi of the mold at the right of an intersection of the cavity Cti+1 with a longitudinal cavity.

[0046] It will be noted that the general configuration of first and second sets of injection points in the two front and rear parts of the mold makes it possible to position the bonding lines in the transverse blades and not in the grid side members, thus considerably reducing the structural weakening of the side members.

[0047] By way of example, each of the injection points of the plurality of injection points has an injection diameter of between 3 and 5 mm, and for example equal to 4 mm.

[0048] For example, each of the plurality of ejection points has an ejection diameter of between 4 and 6 mm.

[0049] The mold also comprises two other end portions located in alignment with the front Pav and rear Par portions of the mold and which are adjacent to the front Pav and rear Par portions respectively. These other end portions of the mold are configured, in a manner known per se, to conform by injection molding, the front and rear flanges of the thrust reverser grid which are used to mount and fix the grid on the nacelle of the aircraft reactor.

[0050] [Fig. 7] is a schematic view showing a thrust reverser grid 40 seen in perspective from above with the grid structure formed by the intersecting of the spars 42 and the transverse blades 44 and the aforementioned front 46 and rear 48 flanges located in the axial extension of the grid.

[0051] Although the present description refers to specific exemplary embodiments, Modifications may be made to these examples without departing from the general scope of the invention as defined by the claims. Furthermore, individual features of the various embodiments illustrated or mentioned may be combined in additional embodiments. Therefore, the description and drawings should be considered in an illustrative rather than restrictive sense.

Claims

Claims

1. System (10) for injecting a material into a mold for manufacturing by injection a thrust reverser grid of an aircraft reactor, the mold internally defining filling cavities arranged relative to each other so as to form a grid structure formed by the intersecting of longitudinal cavities (L1-L7; Li, Li+1, Li+2) extending in a longitudinal direction (X) and transverse cavities (Cti, Cti+1, C'ti+1, C”ti+1, C'”ti+1) extending mainly in a transverse direction (Y) in the form of rows (Rl-Rn), the longitudinal and transverse cavities being intended to be filled with an injection material injected by the injection system to respectively form longitudinal spars intersected with rows of transverse blades of a thrust reverser grid,the transverse blades each comprising a leading edge and a trailing edge which are respectively arranged at two opposite faces of the grid, the mold comprising, in the longitudinal direction of the longitudinal cavities, a so-called front part (Pav) and a so-called rear part (Par), the injection system (10) comprising a plurality of injection points for an injection material which open into one (Zs) of the zones of the longitudinal and transverse cavities of the mold corresponding to one face and / or the other opposite face of the thrust reverser grid, the plurality of injection points comprising, on the one hand, a first set of injection points (Pii-Pi4) arranged in the front part (Pav) of the mold and, on the other hand, a second set of injection points (Pi5-Pi8) arranged in the rear part (Par) of the mold.,

2. Injection system according to claim 1, in which the injection points (Pii-Pi4) of the first set of injection points are arranged at intersections between a set of longitudinal cavities and at least one row of transverse cavities of the mold.

3. Injection system according to claim 1 or 2, in which the injection points (Pi5-Pi8) of the second set of injection points are arranged at intersections between a set of longitudinal cavities and at least one row of transverse cavities of the mold.

4. An injection system according to claim 2 or 3, wherein the set of longitudinal cavities comprises longitudinal cavities which are arranged alternately (C11, C13, C16, C18).

5. Injection system according to one of claims 2 to 4, in which the set of longitudinal cavities comprises the two longitudinal cavities (C11, C18) which frame the other longitudinal cavities.

6. An injection system according to claim 5, wherein, for a mold having a grid structure with an even number of longitudinal cavities, the set of longitudinal cavities comprises the two longitudinal cavities located at the center (C1'3, Cl'4) of all the longitudinal cavities.

7. An injection system according to claim 5, wherein, for a mold having a grid structure with an even number of longitudinal cavities, the two centrally located longitudinal cavities (C14, C5) of all the longitudinal cavities are not part of the set of longitudinal cavities.

8. Injection system according to one of the preceding claims, in which each of the injection points (Pii-Pi8) of the plurality of injection points has an injection diameter of between 2 and 8 mm, preferably between 3 and 5 mm.

9. An injection system according to one of the preceding claims, wherein the injection system comprises a third group of injection points.

10. Injection system according to one of the preceding claims, further comprising a plurality of ejection points (Pej) which emerge from an area of ​​the longitudinal and transverse cavities of the mold which is opposite the area where the injection points are arranged, the plurality of ejection points comprising, on the one hand, a first set of ejection points arranged in the front part (Pav) of the mold at intersections between the longitudinal cavities and at least one row of transverse cavities of the mold and, on the other hand, a second set of ejection points arranged in the rear part (Par) of the mold at intersections between the longitudinal cavities and at least one row of transverse cavities of the mold.

11. The injection system of claim 10, wherein each of the plurality of ejection points has an ejection diameter of between 4 and 6mm.

12. Method for injecting a material into a manufacturing mold by injection of a thrust reverser grid of an aircraft reactor, the method using the injection system according to one of claims 1 to 11.

13. An injection method according to the preceding claim, wherein the injection of the injection material into the mold begins by injecting the injection material through the injection points of the first set of injection points and continues by also injecting the injection material through the injection points of the second set of injection points.

14. Thrust reverser grid of an aircraft reactor manufactured by the injection system according to one of claims 1 to 11.

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