Thrust reverser ring for an aircraft nacelle thrust reverser and aircraft nacelle

Abstract

The invention relates to a thrust reverser ring of an aircraft jet engine extending along a longitudinal axis. The ring comprises thrust reverser modules each extending in a longitudinal direction (D) parallel to the longitudinal axis, the thrust reverser modules being distributed circumferentially about the axis so as to form a ring. One thrust reverser module (10) is arranged between two adjacent thrust reverser modules and is mechanically independent of the latter, the thrust reverser module (10) comprising: - a spar (12) which extends in the longitudinal direction (D) and includes two opposite ends (12c, 12d) spaced apart from each other in this direction, each end being configured to attach the spar to an aircraft nacelle; and - a plurality of transverse blade members (14a, 14b) which are distributed along the spar, extending away from the spar.

Description

DESCRIPTION TITLE: THRUST REVERSER RING FOR AIRCRAFT NACELLE THRUST REVERSER AND AIRCRAFT NACELLE Technical field

[0001] The present disclosure relates to a thrust reverser ring for an aircraft nacelle thrust reverser 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 vanes 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 vanes which extend transversely between the spars.

[0003] Known thrust reverser grids are manufactured using relatively complex and / or expensive processes.

[0004] In view of the above, it would therefore be interesting to be able to manufacture a thrust reverser ring structure for an aircraft nacelle thrust reverser in a simpler manner than in the prior art. Statement of the invention

[0005] The invention thus relates to a thrust reverser ring for an aircraft nacelle thrust reverser, the ring extending around a longitudinal axis, characterized in that the thrust reverser ring comprises a plurality of thrust reverser modules which each extend along a longitudinal direction parallel to the longitudinal axis of the ring and which are distributed circumferentially around the longitudinal axis, at least one thrust reverser module of the plurality of thrust reverser modules being arranged between two adjacent thrust reverser modules and mechanically independent of the latter, said at least one thrust reverser module comprising: -a single spar extending in the longitudinal direction and having two opposite ends spaced apart from each other in that direction, each of the two opposite ends being configured to attach the spar to an aircraft nacelle, -a plurality of transverse vane elements which are distributed along the spar extending from the spar.

[0006] At least one of the thrust reverser modules comprising a single spar is mechanically independent of the two adjacent modules which frame it, that is to say that it is not mechanically linked or secured to them in a circumferential direction relative to the longitudinal axis of the ring, when considering the modules arranged side by side according to the general shape of the ring. The module or modules concerned are simply arranged next to each other and are mechanically linked only to the aircraft nacelle via their two opposite front and rear ends. Such a thrust reverser module structure simplifies the production of the thrust reverser ring structure of an aircraft nacelle and therefore its manufacturing cost, insofar as the module or modules concerned do not need to be assembled with adjacent modules to form grids which must then each be fixed to the nacelle.Indeed, this or these modules are directly positioned and fixed to the nacelle. A thrust reverser module as defined above therefore does not comprise several spars and a fortiori does not constitute a grid formed by an intersecting of spars and blades connected to each other. It should be noted that each end of the spar is only configured to fix the spar to the nacelle, i.e. the thrust reverser module defined above, and not several spars.

[0007] According to other possible characteristics, taken alone or in combination: -at least one of the two opposite ends of the spar of said at least one thrust reverser module extends in the extension of the spar in its longitudinal direction; -at least one of the two opposite ends of the spar of said at least one thrust reverser module comprises a plate which extends circumferentially relative to the longitudinal axis of the ring; -at least one of the two opposite ends of the spar of said at least one thrust reverser module comprises a plate which extends transversely relative to the longitudinal direction of the spar; -the spar comprising two large opposite faces, said at least one thrust reverser module comprises at least one lateral closing plate of the module which extends parallel to a first of the two large opposite faces of the spar and opposite the transverse blade elements which extend from said first large face of the spar;- said at least one thrust reverser module comprises two lateral closure plates of the module which extend respectively parallel to the two large opposite faces of the spar and which are respectively arranged opposite the transverse blade elements which extend from each of the two large opposite faces of the spar; - the lateral closure plate or plates of the module are also fixed to the large face of the spar which is opposite the plate concerned; - the spar comprising two large opposite faces, the transverse blade elements extend from each of the two large opposite faces of the spar; -the transverse blading elements are distributed on the two large opposite faces of the spar in a symmetrical manner relative to the spar, a blading element on one of the two large opposite faces of the spar being arranged longitudinally opposite a blading element on the other large opposite face of the spar; -the transverse blade elements extend on either side of the spar, being offset longitudinally from one of the two large opposite faces of the spar to the other large opposite face of the spar; -the transverse blade elements extend from only one of the two large opposite faces of the spar.

[0008] The invention also relates to an aircraft nacelle comprising a thrust reverser ring as briefly explained above.

[0009] The invention further relates to a method for producing a thrust reverser ring for an aircraft nacelle thrust reverser, the ring extending along a longitudinal axis. The method comprises the following steps: -providing a plurality of thrust reverser modules each comprising, on the one hand, a single spar which extends in a longitudinal direction and which has two opposite ends spaced apart from each other in this direction and, on the other hand, a plurality of transverse blade elements which are distributed along the spar extending from the spar, -positioning the thrust reverser modules on an aircraft reactor nacelle by distributing them circumferentially around the longitudinal axis of the ring so as to form a thrust reverser ring, the longitudinal directions of the thrust reverser modules being parallel to the longitudinal axis of the ring,-fixing at least one thrust reverser module of the plurality of thrust reverser modules to the nacelle solely via the two opposite ends of the spar of said at least one module so that said at least one thrust reverser module is arranged between two adjacent thrust reverser modules while being mechanically independent of the latter.,

[0010] The method briefly described above thus makes it possible to simply produce a new thrust reverser ring configuration for a thrust reverser of an aircraft nacelle. Said at least one thrust reverser module described above (with its single spar) is in fact directly positioned on the nacelle and fixed to it, without needing to be fixed to the adjacent modules arranged circumferentially on either side of it. The method may also include any of the characteristics defined above in relation to the thrust reverser ring. Brief description of the drawings

[0011] 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.

[0012] [Fig. 1] Figure 1 is a schematic general view of a thrust reverser module of a thrust reverser ring according to one embodiment of the invention;

[0013] [Fig. 2] Figure 2 is a schematic general view of an aircraft nacelle comprising a thrust reverser ring formed by one or more of the modules such as that illustrated in Figure 1 and which is or are uniquely attached to the nacelle;

[0014] [Fig. 3A] Figure 3A is a partial schematic general view of a free end of a thrust reverser module spar according to a first embodiment of the invention;

[0015] [Fig. 3B] Figure 3B is a partial schematic general view from above showing two adjacent thrust reverser modules fixed by each of their free ends identical to that of Figure 3A;

[0016] [Fig. 4A] Figure 4A is a partial schematic general view of a free end of a thrust reverser module spar according to a second embodiment of the invention;

[0017] [Fig. 4B] Figure 4B is a partial schematic general view showing the attachment of the two opposite free ends of the module of Figure 4A;

[0018] [Fig. 5A] Figure 5A is a partial schematic general view of a free end of a thrust reverser module spar according to a third embodiment of the invention;

[0019] [Fig. 5B] Figure 5B is a partial schematic general view showing the attachment of the two opposite free ends of the module of Figure 5A;

[0020] [Fig. 6A] Figure 6A is a general view of a thrust reverser module of a thrust reverser ring according to another embodiment of the invention;

[0021] [Fig. 6B] Figure 6B is a partial schematic top view showing the assembly of blade elements with one of the closure plates of the module of Figure 6A;

[0022] [Fig. 7A] Figure 7A is a partial schematic top view showing a thrust reverser module according to a first embodiment variant;

[0023] [Fig. 7B] Figure 7B is a partial schematic top view showing a thrust reverser module according to a second embodiment variant. Detailed description

[0024] As shown schematically in Figure 1 and designated by the general reference number 10, a thrust reverser module according to one embodiment of the invention generally comprises a single spar 12, and a plurality of blade elements 14a-b arranged transversely relative to a longitudinal direction D of the spar, being distributed along the latter and fixed to the latter.

[0025] The spar 12 more particularly comprises two large opposite faces 12a, 12b (the large face 12a being visible in perspective in FIG. 1) which, in a three-dimensional reference frame X, Y, Z, each extend mainly in a plane defined by the two directions X (longitudinal direction) and Z (height or radial direction). The spar also has a thickness (not shown in the very schematic FIG. 1) which extends in the third direction Y, perpendicular to the planes of the two large opposite faces 12a, 12b when these are flat.

[0026] The spar 12 comprises two opposite ends 12c, 12d spaced apart from each other along the longitudinal direction D (axis X) and which are each configured to fix the spar 12 to an aircraft nacelle such as that illustrated schematically in FIG. 2. Different possible configurations of spar ends will be described later with reference to FIGS. 3A to 5B.

[0027] In the embodiment shown in Figure 1, the transverse blade elements 14a-b are connected to each of the two large opposite faces 12a, 12b of the spar. The thrust reverser module 10 thus comprises a first group of transverse blade elements 14a connected to the first large face 12a and a second group of transverse blade elements 14b connected to the second large opposite face 12b.

[0028] In this embodiment, the two groups of transverse blading elements are connected symmetrically with respect to the spar 12, thus giving the module a general ladder shape in top view. More particularly, a blading element 14a arranged on the large face 12a of the spar is arranged in the longitudinal direction D of the spar opposite a blading element 14b arranged on the other large opposite face 12b of the spar.

[0029] The two opposite ends 12c and 12d of the spar have, for example, the configuration illustrated in FIG. 3A for the end 12c: each end extends longitudinally in the extension of the spar, that is to say that it extends along a plane defined by the directions X and Z, like the two large opposite faces 12a and 12b of the spar. Each end has one or more fixing holes (in FIG. 3A a single fixing hole tl passing through the thickness, in the direction Y, of the end 12c is shown). A fixing plate 12cl is attached to the end 12c in order to fix the latter (and therefore the spar) to a part of the aircraft nacelle forming a support for the spar. In the embodiment shown, the plate 12cl extends in the extension of the end 12c by a portion 12cl.l, then extends transversely relative to the longitudinal direction D of the spar 12, in the form of a return 12cl.2.Figure 3B illustrates in top view (projected in an XY plane) two modules 10 adjacent to each other which are not mechanically connected to each other (mechanical independence in a transverse or circumferential direction) but which are each mechanically connected to a peripheral edge B1 of the nacelle via their free end 12c. As shown, the generally L-shaped fixing plate 12cl is fixed to the end 12c with one or more suitable fixing members (e.g. bolts, rivets, etc.) 01 cooperating with the fixing hole t1 and the corresponding fixing hole t2 of its portion 12cl.l. The fixing plate 12cl is fixed to the edge B1 with one or more suitable fixing members (e.g. bolts, rivets, etc.) 02 cooperating with the fixing hole t2 of its portion 12cl.2.As shown for the right module 10 of figure 3B, a second plate 12cl (this plate may or may not be identical to the plate used for the left module 10) may be provided on the opposite face of the free end 12c to reinforce the fixing of the spar on the edge Bl. The two fixing plates thus frame on either side. the free end 12c of the spar. The same mounting can be provided at the opposite end (not shown) of the spars. In Figure 3B two modules 10 have been shown side by side (arranged circumferentially around a longitudinal axis XX' of the ring and the nacelle illustrated in Figure 2) but, in an alternative embodiment not shown, the module 10 of Figures 1 and 3A can be arranged next to a different thrust reverser module, for example of the conventional type (spar carrying transverse blade elements). Generally speaking, the shape of each plate adapts to the shape of revolution of the part of the nacelle on which each plate is fixed and can thus, for example, adopt a curvature around the Y axis.

[0030] Figures 4A and 4B illustrate another embodiment in which each of the two opposite ends 12c', 12d' of the single spar 12 comprises a plate 12c'l, 12'dl which extends, on the one hand, in the extension of the longitudinal direction of the spar 12 and, on the other hand, by flaring laterally or transversely with respect to this longitudinal direction. It will be noted that, depending on the end of the spar concerned, the plate is arranged against the edge or longitudinal edge of the spar corresponding to the leading edge or the trailing edge of the blade elements, as illustrated in Figure 4B. The plate is, for example, a part mechanically attached to the end of the spar or forming an integral part of the spar which is generally manufactured by injection molding. The 12c'l, 12'dl plate thus extends substantially in an XY plane which is perpendicular to the XZ plane of the two large opposite faces of the spar.The plate may not extend precisely in the XY plane since its general shape may be slightly curved with a convexity which is directed upwards along Z (fig. 4B) so as to match a complementary shape (concavity facing downwards) of a part of the nacelle on which the end 12c', 12d' is intended to be fixed. In general, the shape of each plate adapts to the shape of revolution of the part of the nacelle on which each plate is fixed and may thus, for example, adopt a curvature around the X axis. The plate has a general flattened and flared shape giving the plate, when viewed from above, a substantially trapezoidal or spatula shape. Fixing holes t4 and t5 passing through the thickness of the plate 12d'l (resp. 12c'l) cooperate with appropriate fixing members (e.g. bolts,. rivets...) in order to fix the end 12d' (resp. 12c') (and therefore the spar) to the part of the aircraft nacelle forming a support for the end of the spar. In Figure 4B parts 13, 14 respectively forming supports for the two opposite ends 12c' and 12d' of the spar have been shown (these parts 13, 14 are secured to the nacelle) and thus allow the fixing of each plate 12c'l, 12d'l on the part 13, 14 concerned (and therefore on the relevant peripheral edge of the nacelle) by means of appropriate fixing members cooperating with the holes t4 and t5. When the plates 12c'l, 12d'l are positioned on the nacelle (Figure 2), each plate extends circumferentially relative to the longitudinal axis XX' of the ring and of the nacelle.

[0031] Figures 5A and 5B illustrate another embodiment in which each of the two opposite ends 12c", 12d" of the single spar 12 comprises a plate 12c"l, 12"dl which extends transversely relative to the longitudinal direction of the spar 12 and here in a transverse plane defined by the directions Y and Z. In general, the shape of the plates 12c"l, 12"dl adapts to the shape of revolution of the part of the nacelle on which each plate is fixed and can thus, for example, adopt a curvature around the Y axis in addition to its general T shape in top view (in projection in an XY plane). Fixing holes t6 and t7 passing through the thickness of the plate 12c"l in figure 5A cooperate with appropriate fixing members (e.g. bolts, rivets, etc.) in order to fix the end 12c" (and therefore the spar) to the part of the nacelle forming a support for the end of the spar.In Figure 5B parts 16, 17 respectively forming supports for the two opposite ends 12c" and 12d" of the spar have been shown and thus allow the fixing of each plate 12c"l, 12d"l on the part 16, 17 concerned by means of appropriate fixing members cooperating with the holes t6 and t7. When the plates 12c"l, 12d"l are positioned on the nacelle (Figure 2), each plate extends circumferentially relative to the longitudinal axis XX' of the reactor and the nacelle.

[0032] Figure 2 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 a thrust reverser of aircraft nacelle. The thrust reverser includes, in particular, in addition to the thrust reverser ring, actuators which, when controlled by one or more actuating units (engine(s)), enable the functional elements of the ring to be activated and therefore the airflow passing through the ring to be diverted. The aircraft nacelle, together with the engine or turbomachine, forms a propulsion unit for the aircraft.

[0033] For the production of a thrust reverser ring according to one embodiment of the invention, a plurality of thrust reverser modules are provided and include one or more modules 10 in accordance with what has been previously described. The other thrust reverser modules used to form the ring comprise spars to which transverse blade elements are connected and which can be mechanically linked together as in the prior art, unlike the modules 10 previously described.

[0034] In a minimal thrust reverser ring configuration, the ring comprises a single thrust reverser module 10 and the other modules are for example of the conventional type and assembled together so as to form grids which are then mounted on the nacelle.

[0035] In a different configuration of thrust reverser ring, the latter only comprises thrust reverser modules 10 in accordance with what has been previously described in order to simplify the production of the ring as much as possible. In another configuration, the thrust reverser ring comprises, on the one hand, several thrust reverser modules 10 in accordance with what has been previously described, not necessarily adjacent to each other and, on the other hand, conventional thrust reverser modules or conventional grids. Whatever the configuration chosen, the thrust reverser module(s) 10 are mechanically independent of the adjacent modules (namely the two adjacent modules which frame a thrust reverser module 10).

[0036] Each thrust reverser module 10 is positioned in the annular opening O defined previously, at a radial position, taken relative to the longitudinal axis XX' of the nacelle, which corresponds substantially to that of two respective front and rear peripheral edges 22a and 24a of the two front and rear cowlings. The two front and rear peripheral edges 22a and 24a are separated longitudinally from each other by the opening annular O. Each of the two peripheral edges forms a fixing support for one of the two opposite ends of the spar of each of the thrust reverser modules. In this regard, each edge may be configured in a suitable manner to allow such fixing, in particular one of the fixing methods described above in relation to Figures 3A-5B and may, for example, comprise a fixing part dedicated to this purpose (e.g.: annular rim extending around the circumference of the peripheral edge concerned or annular segments).

[0037] In practice, the or each thrust reverser module 10 is positioned by fixing the two opposite ends of the module to the two respective edges 22a and 24a of the nacelle. In an example of a thrust reverser ring configuration shown in FIG. 2, several modules 10 are present and adjacent to each other. A module 10 is positioned next to an adjacent module 10, previously fixed to the nacelle, without being connected or mechanically linked (voluntarily) to this adjacent module in any way (in particular without being linked laterally or circumferentially to this adjacent module). The same is true with the module arranged on the opposite side. The adjacent modules 10 two by two are freely arranged next to each other, a slight lateral / circumferential mechanical clearance even being provided between these modules.More particularly, when two modules 10 are positioned side by side in the annular opening O, a group of transverse blading elements of one of the two modules is arranged opposite another group of transverse blading elements of the adjacent module and, more particularly, the transverse blading elements opposite the two modules 10 are arranged in the same position relative to the longitudinal direction of the side members of these modules. Although these transverse blading elements opposite are not connected to each other and there is even mechanical clearance between them, the overall impression which emerges from the geometric juxtaposition of these modules is that the transverse blading elements opposite each other are each considered as a half-blading and that two half-bladings opposite thus generally form a single transverse blading.The above also applies to the case where a module 10 is arranged next to a conventional module which can, in turn, be mechanically linked to another conventional module.

[0038] The thrust reverser modules 10 of Figure 2 are thus positioned next to each other in the annular opening O and are distributed circumferentially around the axis XX', so as to form a thrust reverser ring structure where only three modules 10 have been detailed (the other modules 10 have been symbolically represented by dotted lines parallel to each other). It will be noted that the modules 10 present in the thrust reverser ring structure may not be adjacent to each other but be dispersed within the plurality of other thrust reverser modules. For example, each module 10 may be arranged between two thrust reverser grids which are each formed from several conventional thrust reverser modules (a conventional grid is formed from an intersecting of spars and transverse blade elements generally obtained in a single block by injection molding).

[0039] In Figure 6A a thrust reverser module 30 according to another embodiment of the invention is shown. The references assigned to the elements of the module 10 of Figure 1 have been repeated to the extent that the elements concerned are not modified.

[0040] The thrust reverser module 30 comprises at least one plate, here two plates 32, 34, for lateral closure of the module which extend respectively parallel to the two large opposite faces 12a, 12b of the single spar, namely in a plane XZ. The two closure plates 32, 34 are respectively arranged opposite the two large opposite faces 12a, 12b of the spar. Each plate 32, 34 is for example fixed to the transverse blade elements 14a, 14b connected to the spar 12 and which extend from the large face of the spar which is opposite the plate concerned. The two closure plates 32, 34 thus form lateral end flanks for the blade elements.In the embodiment shown, each plate 32 and 34 may also comprise two returns 32a, 32b and 34a, 34b which extend transversely in the direction of the spar 12, respectively from the two opposite ends of the central part 32a, 34a of the plate concerned. As shown in FIG. 6A, each of the returns is fixed to the large face opposite the spar. Thus, each plate provided with its two returns forms a laterally closed structure for the module of FIG. 1 which is composed of the spar and the. transverse blading elements. When several modules 30 are placed on the nacelle to adopt the ring configuration of Figure 2 (it will be noted that only one module 30 can be present in a thrust reverser ring), two adjacent modules 30 are thus closed relative to each other along the circumferential direction given by the thrust reverser ring and without mechanical connection with each other. The same is true between a module 30 and an adjacent module or an adjacent conventional grille. In this way, the cavities which define the passages for the reversing airflow through the thrust reverser ring are now each delimited within the same module: each cavity crossed by the airflow is delimited by the module spar, two consecutive blading elements (along the longitudinal direction of the spar) located on the same large face and the facing closure plate.In the installed configuration of Figure 2 with the modules 10 of Figure 1, each cavity crossed by the air flow is delimited by the two longitudinal members facing two adjacent modules 10 and by the two consecutive half-blades located on the same large face of one of the two modules 10 and by the two consecutive half-blades located opposite and on the same large face of the other module 10. For the same transverse dimension of half-blade, the configuration of Figure 2 with the modules 30 has air passage cavities of smaller section than with the modules 10. However, it is conceivable that the blade elements of the modules 30 have a transverse dimension corresponding substantially to the sum of the transverse dimensions of the two blade elements facing the two adjacent modules 10.As with the modules 10 of Figure 1, in the installed configuration of Figure 2 with the modules 30 of Figure 6A, the modules 30 which are arranged adjacent to each other in the circumferential direction of the thrust reverser ring are mechanically independent of each other in this direction, i.e. they are not mechanically connected to each other (in particular by their closing plates 32, 34) and are even slightly spaced transversely / circumferentially from each other by a small circumferential clearance.

[0041] The side closure plates may be attached to the single spar blade members by various means. For example, a mortise and tenon type mounting may be used in which the distal ends of the blading elements each carry one or more protrusions (e.g.: protrusions 14a 1 for blading elements 14a) which are housed in openings opposite the corresponding closure plate (e.g.: openings 32a 1 of closure plate 32), as shown in Figure 6B. It will be noted that the connection between the blading element and the plate can be achieved by crushing the head of the protrusion or tenon as for crushing the rivet heads. Alternatively, it is for example possible to glue or weld the distal ends of the blading elements to the opposite closure plate. The fixing of the two lateral closure plates can be identical. It will be noted that the returns of the two lateral closure plates can also be fixed to the central spar in the same way as described previously.

[0042] Generally speaking, the side closure plates make it possible to improve the mechanical strength of the blade elements and to channel the air flow over the entire transverse dimension of the blade elements, unlike the embodiments which only use the modules of Figure 1.

[0043] It will be noted that the configuration of the module of Figure 6A can, alternatively, be implemented differently. For example, the blade elements 14a and 14b can be carried respectively by the side plates 32 and 34 and are connected to the large facing face of the spar 12 in the same manner as described above. The spar 12 does not carry any spar (in a variant not shown, the blade elements are distributed between the plates and the spar). Thus, in the final configuration the blade elements 14a and 14b extend respectively between the plates 32, 34 and the large facing faces of the spar.

[0044] In an alternative embodiment not shown, the spar carries blading elements and the module comprises one or two lateral closure plates which, for example, are not fixed to the blading elements of the spar.

[0045] In the embodiment described, all the thrust reverser modules that constitute the thrust reverser ring have the configuration of Figure 6A. However, according to a variant not shown, only one or some of the modules of the ring may have this configuration, the other modules having the configuration of Figure 1 or a conventional configuration, or the other modules comprise one or modules with the configuration of Figure 1 and one or more modules with a conventional configuration. For example, in areas where the airflow is desired to be deflected longitudinally and transversely, the blade elements must deflect the flow longitudinally and the spars must also deflect the flow transversely. For these cases, the module of Figure 6A, which gives more transverse stiffness to the flow deflection module, is more suitable. The spars are then also profiled.

[0046] It will be noted that, in a thrust reverser ring configuration installed on a reactor nacelle, the module 30 of FIG. 6A may not be arranged next to another module 30 but, for example, next to a conventional thrust reverser grid, without being mechanically linked thereto. The use, in a thrust reverser ring, of modules according to the invention, in addition to conventional grids, makes it possible, for example, to arrange several modules circumferentially instead of having to produce a grid of smaller width with a mold different from the mold which is used to produce the conventional grids of the ring. The manufacture of the ring is thus simplified.

[0047] Furthermore, the use, in a thrust reverser ring (with or without conventional grids), of modules according to the invention, makes it possible to orient the deflected jet more easily by modifying the reorientation of each module separately, where this proves more difficult within a conventional grid given the interaction between a given spar and the other spars of the grid.

[0048] In an alternative embodiment shown in Figure 7A, the transverse blade elements are offset longitudinally from a large face 12a' of the spar 12 to the opposite large face 12b' of the spar. In other words, the first group of transverse blade elements 14a' connected to the first large face 12a' of the spar is offset longitudinally relative to the second group of transverse blade elements 14b' connected to the second opposite large face 12b' of the spar (asymmetry). In other words, the transverse blading elements are arranged in a staggered pattern along the spar 12' on either side thereof: a transverse blading element of one of the two groups of transverse blading elements which are connected to a large face is arranged, along the spar, between two transverse blading elements of the other group which are connected to the large opposite face. The module of Figure 7A thus has the general shape of a ladder with offset rungs. It should be noted that side closure plates, similar or identical to those of Figure 6A, can be added to the module of Figure 7A.

[0049] In an alternative embodiment shown in Figure 7B, the transverse blade elements 14" are arranged on only one side of the spar 12" and are therefore connected to only one of the two large opposite faces of the spar, thus giving the module a general comb shape. It will be noted that a lateral closure plate, similar or identical to one of the plates of Figure 6A, can be added to the module of Figure 7B on the side where the transverse blade elements 14" extend.

[0050] 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.

[0051] Generally speaking, the ring which is the subject of the invention does not therefore extend over 360° strictly speaking but it nevertheless has a thrust reversal structure in the general shape of a ring.

[0052] 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 ring for aircraft nacelle thrust reverser, the ring extending around a longitudinal axis (XX'), characterized in that the thrust reverser ring comprises a plurality of thrust reverser modules (10; 30) which each extend in a longitudinal direction (D) parallel to the longitudinal axis (XX') of the ring and which are distributed circumferentially around the longitudinal axis (XX'), at least one thrust reverser module of the plurality of thrust reverser modules being arranged between two adjacent thrust reverser modules and mechanically independent of the latter, said at least one thrust reverser module comprising: -a single spar (12) which extends in the longitudinal direction (D) and which comprises two opposite ends (12c, 12d) spaced apart from each other in this direction, each of the two opposite ends (12c, 12d) being configured to fix the spar (12) to an aircraft nacelle, -a plurality of transverse blade elements (14a, 14b) which are distributed along the spar extending from the spar.

2. Thrust reversal ring according to claim 1, characterized in that at least one (12c; 12c 7 ) of the two opposite ends (12c, 12d; 12c', 12d') of the spar (12) of said at least one thrust reverser module extends in the extension of the spar in its longitudinal direction (D).

3. Thrust reversing ring according to claim 1 or 2, characterized in that at least one (12c 7 ) from the two opposite ends (12c 7, 12d') of the spar of said at least one thrust reverser module comprises a plate (12c'l) which extends circumferentially relative to the longitudinal axis (XX 7 ) of the ring.

4. Thrust reverser ring according to one of claims 1 to 3, characterized in that at least one (12c") of the two opposite ends (12c", 12d") of the spar of said at least one thrust reverser module comprises a plate (12c"l) which extends transversely relative to the longitudinal direction (D) of the spar.

5. Thrust reverser ring according to one of claims 1 to 4, characterized in that the spar (12) comprising two large opposite faces (12a, 12b), said at least one thrust reverser module (30) comprises at least one lateral closing plate (32, 34) of the module which extends parallel to a first (12b) of the two large opposite faces (12a, 12b) of the spar (12) and opposite the transverse blade elements (14b) which extend from said first large face (12b) of the spar.

6. Thrust reversing ring according to one of the preceding claims, characterized in that, the spar (12; 12') comprising two large opposite faces (12a, 12b; 12a', 12b'), the transverse blade elements (14a, 14b; 14a', 14b 7 ) extend from each of the two large opposite faces of the spar.

7. Thrust reversal ring according to the preceding claim, characterized in that the transverse blade elements (14a, 14b) are distributed on the two large opposite faces (12a, 12b) of the spar (12) symmetrically with respect to the spar.

8. Thrust reversing ring according to claim 6, characterized in that the transverse blade elements (14a', 14b 7 ) extend on either side of the spar (12') while being offset longitudinally by one (12a 7 ) of the two large opposite faces of the spar to the large opposite face (12b 7 ) of the spar (12').

9. Thrust reverser ring according to one of claims 1 to 5, characterized in that the transverse blade elements (14") extend from only one of the two large opposite faces of the spar (12").

10. Aircraft nacelle, characterized in that it comprises a thrust reverser ring for a thrust reverser according to one of claims 1 to 9.

11. Method for producing a thrust reverser ring for an aircraft nacelle thrust reverser, the ring extending along a longitudinal axis (XX 7 ), the method comprises the following steps: - providing a plurality of thrust reverser modules (10; 30) each comprising, on the one hand, a single spar (12) which extends in a longitudinal direction (D) and which comprises two opposite ends (12c, 12d) spaced apart from each other in this direction and, on the other hand, a plurality of transverse blade elements (14a, 14b) which are distributed along of the spar (12) extending from the spar, -positioning the thrust reverser modules (10; 30) on an aircraft reactor nacelle by distributing them circumferentially around the longitudinal axis (XX') of the ring so as to form a thrust reverser ring, the longitudinal directions (D) of the thrust reverser modules being parallel to the longitudinal axis of the ring, -fixing at least one thrust reverser module (10; 30) of the plurality of thrust reverser modules on the nacelle solely by means of the two opposite ends (12c, 12d) of the spar (12) of said at least one module so that said at least one thrust reverser module is arranged between two adjacent thrust reverser modules while being mechanically independent of the latter.

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