THRUST REVERSAL MODULE OF A THRUST REVERSAL RING FOR AN AIRCRAFT NACELLE THRUST REVERSER

Abstract

The invention relates to a thrust reverser module (30) of a thrust reverser ring for an aircraft nacelle thrust reverser, characterized in that the thrust reverser module (30) comprises: - a first spar (32) which extends in a longitudinal direction (D) and carries blade elements (32a1, 32a2) each extending transversely relative to the longitudinal direction (D), the transverse blade elements (32a1, 32a2) being distributed along the first spar (32), - a second spar (34) which extends parallel and adjacent to the first spar (32), at least a portion of the transverse blade elements (32a1, 32a2) of the first spar (32) being connected to the second spar (34). Figure for abstract: Fig.2

Description

Title of the invention: THRUST REVERSAL MODULE OF A THRUST REVERSAL RING FOR AN AIRCRAFT NACELLE THRUST REVERSER Technical field

[0001] The present disclosure relates to a thrust reverser module of a thrust reverser ring for an aircraft nacelle thrust reverser, a thrust reverser ring comprising such a module and an aircraft nacelle comprising such a thrust reverser ring. Prior art

[0002] It is known to equip aircraft nacelles with thrust reverser grilles in order to be able to generate, when the operating conditions of the aircraft require it, a counterthrust. Conventionally, the thrust reverser grilles form a ring surrounding the nacelle and each grille comprises blades whose orientation deflects the propulsive airflow towards the front of the reactor when the grilles are deployed. These grilles are generally fixed to the structure of the nacelle by a front end and an opposite rear end of each grille. These grilles generally have a rectangular shape having a grating architecture which comprises a plurality of parallel spars, each extending axially in a longitudinal direction, and a plurality of blade elements which extend transversely between the spars.

[0003] Known thrust reverser grilles are manufactured using processes that can lead to disruptive architectures for the airflow passing through these grilles.

[0004] In view of the above, it would therefore be interesting to design a thrust reverser module structure which disturbs the air flow passing through the module as little as possible. Statement of the invention

[0005] The invention thus relates to a thrust reverser module of a thrust reverser ring for an aircraft nacelle thrust reverser, characterized in that the thrust reverser module comprises: - a first spar which extends in a longitudinal direction and carries blading elements each extending transversely relative to the longitudinal direction, the transverse blading elements being distributed along the first spar, - a second spar which extends parallel to the first spar, at least a portion of the transverse blade elements of the first spar being connected to the second spar.

[0006] The architecture of this module is simple in design and thus makes it possible to produce a module by assembling two adjacent spars by means of blade elements carried by a first spar and which are directly fixed to the second spar. This configuration is particularly favorable to the air flow passing through the module during its use in a thrust reverser ring because this air flow will be very little disturbed by passing along the blade elements. On the contrary, the air flow would be more strongly disturbed in an architecture where two adjacent spars are fixed together by means of the distal ends facing the blade elements carried by these two spars. Indeed, the junction between the distal ends of the blade elements facing the two spars proves to be a flow-disturbing element.

[0007] According to other possible characteristics, taken alone or in combination: the transverse blading elements of said at least part of the transverse blading elements of the first spar each comprise a distal end which is configured to be assembled to the second spar (by means of fixing means between the transverse blading elements and the second spar; -the module comprises first fixing means carried by the transverse blade elements and second complementary fixing means carried by the second spar; - the first fixing means and the second complementary fixing means are of the tenon-mortise type; - the blade elements carry at their distal end at least one tenon-forming element and the second spar carries mortise-forming elements in geometric correspondence with the position of the tenon-forming elements which are opposite; -the second spar comprises a first and a second large opposite faces, said at least a part of the transverse blade elements being connected to the first large face which is arranged opposite; - the second large face of the second spar carries transverse blading elements which each extend transversely relative to the longitudinal direction of the second spar, away from a zone of the second spar called the connection zone of the blading element in question and in a direction opposite to the first large face of the second spar; - the transverse blading elements of said at least part of the blading elements of the first spar being each connected to the first large face of the second spar, at right angles to the connection zone of a transverse blading element carried by the second large face; -the first large face of the second spar carries transverse blading elements which each extend transversely relative to the longitudinal direction of the second spar, the transverse blading elements carried by the first large face of the second spar being offset longitudinally relative to the transverse blading elements carried by the second large face of the second spar so that the blading elements carried by the two opposite large faces form a staggered arrangement; -the transverse blading elements of said at least one part of the transverse blading elements of the first spar being each connected to the first large face of the second spar, between two successive connection zones of two successive transverse blading elements carried by the second large face of the second spar so that the transverse blading elements of said at least one part of the transverse blading elements of the first spar and the transverse blading elements carried by the second large face of the second spar form a staggered arrangement; -the first large face of the second spar carries blading elements which each extend transversely relative to the longitudinal direction of the second spar, the blading elements of said at least part of the blading elements of the first spar each being connected to the first large face of the second spar, between two successive blading elements carried by the first large face of the second spar; -the second large face of the second spar carries blading elements which each extend transversely relative to the longitudinal direction of the second spar, the blading elements carried by the second large face being arranged symmetrically relative to the blading elements carried by the first large face, a blading element on one of the two opposite large faces of the second spar being arranged longitudinally opposite a blading element on the other opposite large face of the spar; -the second large face of the second spar carries blading elements which each extend transversely relative to the longitudinal direction of the second spar, the blading elements carried by the second large face being offset longitudinally relative to the blading elements carried by the first large face (staggered arrangement) and each extend transversely away from a zone of the second spar called the blading element connection zone, in a direction opposite to the first large face, the blading elements of said at least part of the blading elements of the first spar each being connected to the first large face of the second spar, between two successive connection zones of two successive blading elements carried by the second large face; -the module further comprises at least one third spar which extends in a longitudinal direction parallel to the first and second spars, the third spar being assembled to the first or second spar by connecting blade elements carried by one of the spars to the other spar; -said at least one third spar carries blade elements each extending transversely relative to the longitudinal direction of the third spar while being distributed along the third spar.

[0008] The invention also relates to a thrust reverser ring for an aircraft nacelle thrust reverser, comprising one or more thrust reverser modules as briefly explained above.

[0009] The invention further relates to an aircraft nacelle comprising such a thrust reverser ring for an aircraft nacelle thrust reverser.

[0010] The invention also relates to a method for producing a thrust reverser module of a thrust reverser ring for an aircraft nacelle thrust reverser, characterized in that the method comprises the following steps: - provision of a first spar which extends in a longitudinal direction and which carries blading elements each extending transversely relative to the longitudinal direction, the transverse blading elements being distributed along the first spar, -supply of a second spar, -positioning of the second spar parallel and adjacent to the first spar, -connection of at least part of the transverse blade elements of the first spar to the second spar.

[0011] The method has the same advantages as those set out above in relation to the module. Generally, the two spars which are independent of each other (separated) at the start of the method are assembled together, i.e. joined together, in order to form a module by connecting at least some of the blade elements of the first spar with the second spar. Furthermore, all or part of the characteristics of the module presented above may also be the subject of one or more additional characteristics of the method. Brief description of the drawings

[0012] 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.

[0013] [Fig.l] [Fig.l] is a schematic general view of an aircraft nacelle comprising a thrust reverser ring according to one embodiment of the invention;

[0014] [Fig.2] [Fig.2] is a partial schematic general view of a module thrust reversal of an aircraft reactor according to a first embodiment of the invention;

[0015] [Fig.3A] [Fig.3A] is a partial schematic perspective view of one end of a blade element of the thrust reverser module of [Fig.2];

[0016] [Fig.3B] [Fig.3B] is a partial schematic view, similar to that of [Fig.3A], of one end of a blade element of the thrust reverser module of [Fig.2] according to an alternative embodiment;

[0017] [Fig.3C] [Fig.3C] is a partial schematic view, similar to that of [Fig.3B], of one end of a thrust reverser module blade element according to another alternative embodiment;

[0018] [Fig.4] [Fig.4] is a partial schematic general view of a thrust reverser module of an aircraft reactor according to an alternative embodiment of the mode of [Fig.2];

[0019] [Fig.5] [Fig.5] is a partial schematic general perspective view of a thrust reverser module of an aircraft reactor according to a second embodiment of the invention;

[0020] [Fig.6] [Fig.6] is a partial schematic general view of a thrust reverser module of an aircraft reactor according to a third embodiment of the invention;

[0021] [Fig.7] [Fig.7] is a partial schematic top view showing a thrust reverser module according to a fourth embodiment of the invention;

[0022] [Fig.8] [Fig.8] is a partial schematic top view showing a thrust reverser module according to a fifth embodiment of the invention;

[0023] [Fig.9] [Fig.9] is a partial schematic view of a mortise and tenon joint between a spar and a blade element. Detailed description

[0024] [Fig. 1] illustrates an aircraft nacelle 20 of known type, comprising, aligned along the longitudinal axis XX', a front cowling 22 and a rear cowling 24 delimiting between them an annular opening O intended to accommodate a thrust reverser ring for an aircraft nacelle thrust reverser. The thrust reverser comprises in particular, in addition to the thrust reverser ring, actuators which, when controlled by one or more actuating units (engine(s)), make it possible to activate the functional elements of the ring and therefore to deflect in a controlled manner the air flow passing through the ring. The aircraft nacelle forms with the engine or turbomachine a propulsion unit of the aircraft.

[0025] To produce a thrust reverser ring according to one embodiment of the invention, a plurality of thrust reverser ring modules of the type that will be described below are used to form thrust reverser ring grids that are then placed on the nacelle. A grid is for example formed from several spars (for example from 2 to 40 spars) assembled together as described below.

[0026] As shown in [Fig. 2] (top view) and generally designated by the reference numeral 30, a thrust reverser module according to a first embodiment generally comprises a first spar 32 and a second spar 34 which is positioned adjacent to and parallel to the first spar.

[0027] The first spar 32 extends in a longitudinal direction D and carries blading elements, only two of which are shown here, 32al, 32a2 (the number of blading elements is generally much greater than two), and which each extend transversely relative to the longitudinal direction D. The transverse blading elements 32al, 32a2 are distributed, generally regularly, over the length of the spar 32 and are integral with it. In practice, the spars and the blading elements can be produced in a single piece by injection manufacturing in an injection mold. More particularly, the first spar 32 and the transverse blading elements 32al, 32a2 are part of a single piece manufactured in a single piece. The second spar 34, for its part, is not made in the same material as the transverse blade elements 32al, 32a2 of the first spar 32.

[0028] As shown in [Fig. 2], the first spar 32 comprises two large opposite faces which extend mainly, in a three-dimensional reference frame X, Y, Z, along two axes X (longitudinal direction) and Z (height or radial direction when the module is installed on the nacelle): a first large face 32a to which the blade elements 32a 1, 32a2 are connected extending along the third axis Y (width) away from this large face and a second large opposite face 32b which, in this mode, does not carry any blade elements. It will be noted that in another mode not shown, the second large opposite face 32b can carry blade elements which extend in a direction opposite to that of the blade elements 32a 1, 32a2.

[0029] The second spar 34 also comprises a first and a second large opposite faces 34a, 34b, the first large face 34a being arranged opposite the first large face 32a and the blade elements 32a1, 32a2 carried by the latter.

[0030] The second large face 34b of the second spar 34 here also carries blading elements 34b 1, 34b2 (two in number in this example; the remark applied to the blading elements of the first spar also applies here) and which each extend transversely relative to the longitudinal direction of the second spar 34, away from a zone zl, z2 of the second spar called the connection zone of the blading element considered. More particularly, the second spar 34 and the transverse blading elements 34b 1, 34b2 are part of a single piece manufactured in one piece.

[0031] In this embodiment, the blading elements 32al, 32a2 of the first spar 32 are arranged at the same axial dimension or position (along the X axis) along the first spar as the axial dimension or position of the blading elements 34b1, 34b2 of the second spar 34 along this spar. In other words, the blading elements 32al, 32a2 are aligned transversely (along the Y direction) with the blading elements 34b1, 34b2.

[0032] As shown in [Fig.2], the blading elements 32al, 32a2 of the first spar 32 are each assembled on the first large face 34a of the second spar 34 by connection to this face 34a, at right angles to the connection zone zl, z2 of a blading element 34b 1, 34b2 carried by the second large face 34b and which extends in a direction opposite to the face 34a. It will be noted that here all the blading elements 32al, 32a2 of the first spar 32 participate in the assembly with the second spar, which makes it possible to ensure a solid and reliable assembly between the two spars. However, according to a variant not shown, only some of the blading elements carried by the first large face 32a can be used for the assembly.

[0033] The assembly between the blading elements (or only part of them) of the first spar 32 and the first large face 34a of the second spar 34 is generally carried out using first and second mechanical fixing means complementary to each other, for example of the tenon-mortise type, which are distributed between the blading elements of the first spar 32 carrying first fixing means and the first large face 34a of the second spar 34 carrying second fixing means complementary to the first means.

[0034] The blade elements 32al, 32a2 of the first spar 32 each comprise a distal end 32al.l, 32a2.1 which is considered to be free when it is not yet assembled with the second spar 34. Each distal end 32al.l, 32a2.1 is configured to be assembled to the first large face 34a of the second spar by means of the first and second mechanical fixing means which are complementary to each other.

[0035] By way of example, the blade elements 32al, 32a2 carry at their distal end 32al.l, 32a2.1 at least one element forming a tenon 32al.2, 32a2.2 (for example in pawn shape) and the first large face 34a of the second spar carries mortise-forming elements 34al, 34a2 (for example taking the form of a cavity), of complementary shapes and which are arranged in geometric correspondence with the position of the tenon-forming elements arranged opposite. [Fig.3A] illustrates in perspective the tenon 32al.2 arranged on the distal end edge 32al.l of the blade element 32a 1.

[0036] Thus, the tenons 32al.2, 32a2.2 of the blading elements 32al, 32a2 are inserted by force into the facing mortises, which makes it possible to assemble / secure the blading elements of the first spar 32 to the second spar 34. According to a variant not shown, the tenons and mortises are reversed between the blading elements and the second spar. With a tenon-mortise type assembly / connection (regardless of the element which carries the tenon), in a complementary manner, the tenon-forming elements can be glued to the mortise-forming elements. Alternatively, in a complementary manner, the tenon-forming elements can be welded to the mortise-forming elements, in particular if the spars are made of metal or thermoplastic matrix composite materials. Alternatively, in a complementary manner, the tenon-forming elements can be deformed to prevent them from coming out of the mortise-forming elements.Alternatively, in a complementary manner, a screw may be placed through the spar and press the blade element against the spar. Alternatively, in a complementary manner, the tenon elements may be split along their length and clip through the mortise elements. Other complementary assembly / fixing means may alternatively be used between the blade elements and the second spar.

[0037] [Fig.3B] illustrates an alternative embodiment showing two tenons 32al.2', 32al.3' arranged on the distal end edge 32al.1' of the blading element 32al'. A different number of tenons or a single element forming a tenon and having an elongated shape following the chord of the blading element can alternatively be envisaged.

[0038] [Fig.3C] illustrates another variant with two tenons of different shapes, for example trapezoidal, or square, or even rectangular, 32al.2”, 32al.3” arranged on the distal end edge 32al.1” of the blade element 32al”. These elements are inserted into complementary shapes (through openings here) 34al” and 34a2” of the spar 34”.

[0039] As shown in [Fig. 2], the blade elements 34b 1, 34b2 may also each carry one or more tenons and mortises may be made on the second large face 32b of the first spar, as on the first large face 34a, in order to be able to assemble the elementary module of [Fig. 2] with other identical modules using the same principle of direct fixing / connection between blade elements and spar. This constitutes, step by step, a grid thrust reverser ring by adding additional spars (the module thus formed is a multi-spar module which can be made up of n spars with n greater than or equal to two and less than or equal to 5, or even n less than or equal to 40; when n is equal to 40 or close to 40, the module thus formed can cover approximately 90° of circumference of the reverser ring) which can be easily adjusted to the desired dimensions (depending on requirements).

[0040] It will be noted that the space between the two adjacent spars 32, 34 defines an aerodynamic inversion channel. This channel here comprises the transverse blade elements 32a 1, 32a2 originating solely from the first spar.

[0041] [Fig. 4] illustrates a thrust reverser module 30' according to an alternative embodiment in which the first large face 34a' of the second spar 34' carries blading elements 34al', 34a2' (two in number in this example; the remark applied to the blading elements of the embodiment of [Fig. 2] also applies here) which each extend transversely relative to the longitudinal direction of the second spar 34 in the direction of the first large face 32a' of the first spar 32. The blading elements 34al', 34a2' carried by the first large face 34a' are offset longitudinally (along the length of the spar 34') relative to the blading elements 34bl', 34b2' carried by the second large face 34b'.

[0042] Thus, the blading elements 34al', 34a2' are inserted between the blading elements carried by the first large face 32a' of the first spar 32' and, in this case, the blading element 34al' is interposed between the two consecutive blading elements 32al, 32a2 (staggered arrangement). It should be noted that this arrangement can be obtained by longitudinally spacing the blading elements of the two spars 32 and 34 of [Fig. 2] in order to add the blading elements 34a1', 34a2'. This makes it possible to maintain the same longitudinal spacing between the consecutive blading elements 32al', 34al, 32a2', 34a2 in the module thus assembled. Again, as in the mode of [Fig.2], the space between the two adjacent spars 32, 34 defines an inversion aerodynamic channel which comprises the transverse blade elements 32al, 32a2 from the first spar and the transverse blade elements from the second spar.This remark also applies to the modes of figures 6, 7 and 8 which will be described later.

[0043] It will be noted that the first spar 32' may, as illustrated in dotted lines, carry on its second large opposite face 32b' blading elements 32b1, 32b2 which extend away from this large face. As for the mode of [Fig.2], the blading elements 34al', 34a2' ([Fig.4]) may be assembled with the large face 32a' of the first spar by means of an identical tenon-mortise type fixing system, including or not one or other of the additional fixing means, or even an alternative fixing system.

[0044] In this arrangement, the spar 32a' thus also carries blade elements which are offset longitudinally (along the length of the spar 32') from one large face to the other, as for the spar 34'. The two spars thus have an identical configuration (staggered arrangement) as illustrated in [Fig. 4], which allows them to be fitted together at will to form a grid from elementary modules assembled with each other.

[0045] [Fig. 5] illustrates a thrust reverser module 40 according to a second embodiment which differs from the embodiment of [Fig. 2] by a longitudinal offset between the blading elements 42al, 42a2, 42a3 carried by the first large face 42a of the first spar 42 and the blading elements 44b1, 44b2, 44b3 carried by the second large face 44b of the second spar 44.

[0046] More particularly, the blading elements 42al, 42a2, 42a3 are each assembled on the first large face 44a of the second spar 44 by connection to this face 44a, between two successive connection zones zl, z2, z3 of two successive blading elements 44b1, 44b2, 44b3 carried by the second large face 44b of the second spar 44. The assembly / connection means are, here, as for the mode of [Fig. 2] of the tenon-mortise type, and more particularly, the blading elements 42al, 42a2, 42a3 each carry, at their distal end opposite the large face 44a of the second spar, respectively a tenon-forming element 42al.2, 42a2.2, 42a3.2 which fits into a mortise-forming element arranged in geometric correspondence on the large face 44a opposite (for example, elements 44al and 44a3 in dotted lines).The complementary assembly / fixing elements or means carried by the first large face 44a of the second spar 44 are offset longitudinally relative to the blade elements 44b1, 44b2, 44b3 carried by the second large face 44b.

[0047] It will be noted that the blading elements 44b1, 44b2, 44b3 carried by the second large face 44b also carry elements forming tenons which allow them to be assembled with the large face of another spar of another module 40. Similarly, the second large face 42b of the first spar carries elements forming mortises in order to be able to be assembled in an identical manner with the blading elements of another module 40.

[0048] Everything that has been said previously about the first mode of [Fig.2] and its variants also applies here and will not be repeated.

[0049] [Fig. 6] illustrates a thrust reverser module 50 according to a third embodiment in which two adjacent parallel spars 52, 54 both carry blading elements but which, unlike the embodiment of [Fig. 5], are directed in opposite directions to each other. The first spar 52 is identical to the spar 42 of [Fig. 5] and the blading elements 52al, 52a2 which it carries on its first large face 52a assemble with the first large face 54a, in a manner identical to that described with reference to the mode of [Fig.5], as illustrated in dotted lines in [Fig.6]. However, the blading elements 54al, 54a2 carried by the first large face 54a which is opposite the blading elements 52a 1, 52a2 of the first spar 52 are oriented opposite the blading elements 44b 1, 44b2, 44b3 of [Fig.5]. The blading elements 54a1, 54a2 may be identical and carry elements forming tenons to assemble with the first large face 52a opposite (see the dotted lines between the large face 52a provided with elements forming mortises and the blading elements 54a1, 54a2) and thus obtain a double assembly or not carry such elements (a single assembly is then produced by means of only the blading elements 52a1, 52a2 of the first spar 52 connected to the second spar 54).

[0050] [Fig. 7] illustrates a thrust reverser module 50' according to an alternative embodiment which differs from the module 50 of [Fig. 6] in that the second large face 54b' of the second spar 54' also carries blading elements 54bl, 54b2, 54b3 which each extend transversely relative to the longitudinal direction of the second spar 54'. These blading elements carried by the second large face 54b' are arranged symmetrically with respect to the blading elements 54al, 54a2, 54a3 carried by the first large face 54a', that is to say that a first blading element carried by one face is arranged opposite a second blading element carried by the opposite face and directed in a direction opposite that of the first blading element (ladder arrangement).

[0051] As for the mode of [Fig.6], the blade elements 54al, 54a2, 54a3 may or may not be assembled with the first large face 52a of the first spar 52' ​​opposite.

[0052] Furthermore, the second large face 52b may also carry blading elements shown in dotted lines and which are arranged symmetrically with respect to the blading elements 54al and 54a2.

[0053] The two spars 52', 54' (with the blading elements shown in dotted lines) thus have an identical symmetrical configuration but in a longitudinally offset manner from one spar to the other as illustrated in [Fig.7], which makes it possible to interpose the blading elements of one spar with those of the opposite spar. This architecture also makes it possible to nest them at will (blading elements-spar) to form a grid from elementary modules assembled with each other.

[0054] [Fig.8] illustrates a thrust reverser module 60 according to a fourth embodiment which comprises four adjacent spars assembled by fitting together two by two.

[0055] This mode is based on several previous modes / variants, namely the mode of the [Fig.6] where the blading elements carried by the first large face of the first spar are assembled with the first large face opposite the second spar, between two consecutive blading elements carried by the first large face opposite the second spar, on the variant of [Fig.4] where the blading elements carried by the two large opposite faces of the second spar are offset longitudinally from one face to the other and, in the mode of [Fig.7] where the blading elements carried by the first large face of the first spar are assembled with the first large face opposite the second spar, in zones situated between two consecutive blading elements carried by the second large opposite face of the second spar.

[0056] More particularly, the module 60 of [Fig.8] comprises two end spars 62, 64 identical to the spar 52 of [Fig.6] and which frame two central spars 66, 68 having a structure of the type of that of the spar 34' of [Fig.4] with the blade elements offset longitudinally from one face to the other.

[0057] Each end spar 62, 64 comprises respective blade elements 62al, 62a2, 62a3 and 64al, 64a2 which are each oriented opposite a first large face 66a, 68b of the adjacent spar 66 and 68 and which are assembled with mortise-forming elements arranged on this face, namely 66c 1, 66c2, 66c3 and 68c 1, 68c2.

[0058] The first large face 66a, 68b of the spar 66, 68 carries respective blading elements 66al, 66a2, 66a3 and 68bl, 68b2 which are assembled with mortise-forming elements arranged on the large face opposite the corresponding end spar 62, 64, namely 62c 1, 62c2, 62c3 and 64c 1, 64c2.

[0059] Furthermore, each central spar 66, 68 carries on its large face arranged opposite the other large face of the other central spar blading elements 66b1, 66b2, 66b3 and 68a1, 68a2, 68a3, 68a4 which are assembled with mortise-forming elements arranged on the large opposite face, namely respectively 68c3, 68c4 and 66c4, 66c5, 66c6.

[0060] It will be noted that each central spar thus comprises one, two or three elements forming mortises between two consecutive blade elements carried by the same large face so as to allow the insertion of tenon-forming elements on each of the two large opposite faces of the spar.

[0061] The mortise-forming elements of each central spar are arranged between the successive connection zones of the successive blade elements.

[0062] [Fig.9] illustrates very schematically a possible example of a tenon-mortise assembly between a blade element A carried by a spar L1, provided with a tenon-forming element Al and a mortise-forming element M made in an adjacent spar L2. The mortise-forming element M is here a through hole and the tenon-forming element Al is inserted into it and its opening end is then deformed, for example by crushing, in order to prevent its axial withdrawal.

[0063] This assembly possibility also applies to the modes and variants described above and which may be affected by such an assembly mode.

[0064] The various modules described above make it possible, from elementary segments comprising, in a minimal configuration with two assembled elementary segments ([Fig.2]), a first spar carrying transverse blade elements and a second spar carrying means for receiving (e.g.: mortises) transverse blade elements of the first spar (the second spar carrying or not transverse blade elements), to constitute inversion modules by assembling these two elementary segments, or even more than two of these segments. With a limited number of patterns of elementary segments (elementary segments having different configurations), it is possible to produce different arrangements of thrust inversion modules, possibly combining several embodiments and / or variants between them.The different embodiments and / or variants differ from each other, in particular by the arrangement of the blade elements on the side members and their orientation.

[0065] A thrust reverser ring according to the invention may comprise only reverser modules according to one or other of the modes and variants described above, alone or combined with each other, or it may comprise such reverser modules according to one or other of the modes and variants described above, alone or combined with each other, as well as conventional thrust reverser grids.

[0066] It will be noted that in any of the modes and variants described above, the ring may be locally interrupted to accommodate specific arrangements. It may thus be interrupted to allow a passage for a pylon or mast used to suspend the engine.

[0067] Generally speaking, the ring which is the subject of the invention therefore does not extend over 360° strictly speaking but it nevertheless has a thrust reversal structure in the general shape of a ring.

[0068] 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. Thrust reverser module (30) of a thrust reverser ring for an aircraft nacelle thrust reverser, characterized in that the thrust reverser module (30) comprises: - a first spar (42) which extends in a longitudinal direction (D) and carries blade elements (42al, 42a2, 42a3) each extending transversely relative to the longitudinal direction (D), the transverse blade elements (42al, 42a2, 42a3) being distributed along the first spar (42), the first spar (42) comprising a first large face (42a) to which the blade elements (42al, 42a2, 42a3) are connected and a second large opposite face (42b), - a second spar (44) which extends parallel to the first spar (42), the second spar (44) comprising a first large face arranged opposite the first large face (42a) of the first spar (42) and the blade elements (42al, 42a2,42a3) carried by the first large face (42a) and a second opposite large face (44b) carrying blading elements (44bl, 44b2, 44b3), the blading elements (42al, 42a2, 42a3) carried by the first large face (42a) of the first spar (42) being offset longitudinally relative to the blading elements (44b 1, 44b2, 44b3) carried by the second large face (44b) of the second spar (44), at least a portion of the transverse blading elements (42al, 42a2, 42a3) of the first spar (42) being connected to the second spar (44).,

2. Thrust reverser module according to claim 1, characterized in that the transverse blade elements (32al, 32a2) of said at least part of the transverse blade elements of the first spar (32) each comprise a distal end which is configured to be assembled to the second spar (34) by means of fixing means between the transverse blade elements (32a 1, 32a2) and the second spar (34).

3. Thrust reversal module according to claim 2, characterized in that it comprises first fixing means carried by the transverse blade elements (32al, 32a2) and second complementary fixing means carried by the second spar (34).

4. Thrust reverser module according to one of claims 1 to 3, ca- characterized in that the first large face (34a') of the second spar (34') carries blading elements (34al', 34a2') which each extend transversely relative to the longitudinal direction of the second spar (34'), the blading elements (32al, 32a2) of said at least one part of the blading elements of the first spar (32') being each connected to the first large face (34a') of the second spar (34'), between two successive blading elements (34al', 34a2') carried by the first large face (34a').

5. Thrust reverser module according to one of the preceding claims, characterized in that it comprises at least one third spar which extends in a longitudinal direction parallel to the first and second spars, the third spar being assembled to the first or second spar by connecting blade elements carried by one of the spars to the other spar.

6. Thrust reverser ring for aircraft nacelle thrust reverser, characterized in that it comprises one or more thrust reverser modules according to one of claims 1 to 5.

7. Method for producing a thrust reverser module (30) of a thrust reverser ring for an aircraft nacelle thrust reverser, characterized in that the method comprises the following steps: - providing a first spar (42) which extends in a longitudinal direction (D) and which carries blade elements (42al, 42a2, 42a3) each extending transversely relative to the longitudinal direction (D), the transverse blade elements (42al, 42a2, 42a3) being distributed along the first spar (42), the first spar (42) comprising a first large face (42a) to which the blade elements (42al, 42a2, 42a3) are connected and a second large opposite face (42b), - providing a second spar (44) which comprises a first large face (42a) to which the blade elements (42al, 42a2, 42a3) are connected and a second large opposite face (42b), face (44a) and a second large opposite face (44b) carrying blading elements (44b 1, 44b2, 44b3),-positioning the second spar (44) parallel and adjacent to the first spar (42), with the first large face (44a) arranged opposite the first large face (42a) of the first spar (42) and the blading elements (42a1, 42a2, 42a3) carried by the first large face (42a), the blading elements (42a1, 42a2, 42a3) carried by the, first large face (42a) of the first spar (42) being offset longitudinally relative to the blading elements (44b 1, 44b2, 44b3) carried by the second large face (44b) of the second spar (44), -connection of at least a portion of the transverse blading elements (42a 1, 42a2, 42a3) of the first spar (42) to the second spar (44).

Images