Thrust reverser module of a thrust reverser ring for an aircraft nacelle thrust reverser
Patent Information
- Application Number
- EP2024710477
- Authority / Receiving Office
- EP · EP
- Patent Type
- Applications
- Current Assignee / Owner
- Priority Date
- 2023-02-28
- Filing Date
- 2024-02-28
- Publication Date
- 2026-01-07
AI Technical Summary
Conventional thrust reversal grids in aircraft nacelles disrupt air flow significantly, leading to inefficiencies in counterthrust operations.
A thrust reversal module design featuring a staggered arrangement of transverse blade elements between two parallel spars, allowing for minimal air flow disturbance and improved mechanical strength through mortise-tenon type fixing mechanisms, enabling flexible access to fixing means and assembly configurations.
The module minimizes air flow disruption and enhances mechanical strength, allowing for efficient counterthrust operations while providing flexibility in assembly and fixing mechanisms.
Smart Images
Figure FR2024050256_06092024_PF_FP
Abstract
Description
DESCRIPTION TITLE: 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 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 vane 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 airflow passing through the module as little as possible. Statement of the invention The invention thus relates to a thrust reverser module for 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 and comprises first and second opposite large faces, at least a portion of the transverse blading elements of the first spar being connected to the first large face of the second spar which is arranged opposite, the second large face of the second spar carrying 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 a portion of the transverse 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 transverse blading elements carried by the second large face of the second spar, so that the transverse blading elements of said at least part of the transverse blading elements of the first spar connected to the second spar and the transverse blading elements carried by the second large face of the second spar form a staggered arrangement relative to the second spar.,
[0005] The architecture of this module is simple in design and thus allows a module to be produced by assembling two adjacent spars by means of blade elements carried by a first spar and which are directly fixed on 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. The air flow would on the contrary be more strongly disturbed in an architecture where two adjacent spars are fixed together by means of the distal ends in with regard to the blading elements carried by these two spars. Indeed, the junction between the distal ends of the blading elements opposite the two spars proves to be a flow-disrupting element. Furthermore, in the aforementioned module, the transverse blading elements of the first spar are connected / assembled on the first large face of the second spar, between the zones of the second spar where the transverse blading elements carried by the second large face of the second spar are connected to the second large face of the second spar. This assembly arrangement offers the possibility of leaving free access to the zones of the second large face of the second spar which are respectively arranged each between two connection zones between, on the one hand, the transverse blading elements of the second large face of the second spar and, on the other hand, the latter.Thus, depending on the circumstances, it is possible to access, from these areas of the second large face of the second spar which are left free, the fastening means cooperating with or used on the second spar (on the side of the first large face) to cooperate with complementary fastening means carried by the blading elements of the first spar. Such access allows, for example, to access at least part of these fastening means, or to ensure the locking of these fastening means or even to reinforce their mechanical connection with the second spar. Such flexibility of use is not possible if the blading elements of the first spar were each connected to the first large face of the second spar, at the connection zone of a transverse blading element carried by the second large face of the second spar.Access to these fastening means on the side of the second large face of the second spar would then be hidden by the blading elements and therefore impossible. This arrangement also offers the possibility of using a wide variety of possible fastening means, which is not possible in the aforementioned case. Furthermore, the assembly of the transverse blading elements carried by the first spar with the first large face of the second spar in areas of the second spar which are free of any connection, on the side of the second large face of the second spar, with transverse blading elements, makes it possible not to weaken the connection areas between these transverse blading elements and the second large face. face of the second spar. The second spar thus has improved mechanical strength.
[0006] According to other possible features, 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 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 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 with respect to the blading elements carried by the first large face, a blading element on one of the two large opposite faces of the second spar being arranged longitudinally opposite a blading element on the other large opposite 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.
[0007] 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.
[0008] The invention further relates to an aircraft nacelle comprising such a thrust reverser ring for an aircraft nacelle thrust reverser.
[0009] 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: -supply of a first spar which extends in one direction longitudinal and which carries blading elements each extending transversely relative to the longitudinal direction, the transverse blading elements being distributed along the first spar, -providing a second spar which comprises a first and a second opposite large face, the second large face of the second spar carrying transverse blading elements which each extend transversely relative to the longitudinal direction of the second spar, away from an area of the second spar, called the connection area of the blading element in question, and in a direction opposite to the first large face of the second spar, -positioning the second spar parallel and adjacent to the first spar, -connection of at least a portion of the transverse blade elements of the first spar to the first large face (of the second spar which is arranged opposite, the transverse blade elements of said at least a portion of the transverse blade 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 transverse blade elements carried by the second large face of the second spar so that the transverse blade elements of said at least a portion of the transverse blade elements of the first spar connected to the second spar and the transverse blade elements carried by the second large face of the second spar form a staggered arrangement relative to the second spar.
[0010] 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, 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
[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 an aircraft nacelle comprising a thrust reverser ring according to one embodiment of the invention;
[0013] [Fig. 2] Figure 2 is a partial schematic general view of a thrust reverser module of an aircraft reactor according to a first embodiment of the invention;
[0014] [Fig. 3A] Figure 3A is a partial schematic perspective view of one end of a blade element of the thrust reverser module of Figure 2;
[0015] [Fig. 3B] Figure 3B is a partial schematic view, similar to that of Figure 3A, of one end of a blade element of the thrust reverser module of Figure 2 according to an alternative embodiment;
[0016] [Fig. 3C] Figure 3C is a partial schematic view, similar to that of Figure 3 B, of one end of a thrust reverser module blade element according to another alternative embodiment;
[0017] [Fig. 4] Figure 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 Figure 2;
[0018] [Fig. 5] Figure 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;
[0019] [Fig. 6] Figure 6 is a partial schematic general view of a thrust reverser module of an aircraft reactor according to a third embodiment of the invention;
[0020] [Fig. 7] Figure 7 is a partial schematic top view showing a thrust reverser module according to a fourth embodiment of the invention;
[0021] [Fig. 8] Figure 8 is a partial schematic top view showing a thrust reverser module according to a fifth embodiment of the invention;
[0022] [Fig. 9] Figure 9 is a partial schematic view of a mortise and tenon joint between a spar and a blade element. Detailed description
[0023] Figure 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 assembly of the aircraft.
[0024] To produce a thrust reverser ring according to one embodiment of the invention, a plurality of thrust reverser ring modules of the type described below are used to form thrust reverser ring grids which 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.
[0025] As shown in Figure 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.
[0026] The first spar 32 extends in a longitudinal direction D and carries blading elements, only two of which are shown here, 32a 1, 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 32a 1, 32a2 are distributed, generally regularly, along the length of the spar 32 and are integral with it. In practice, the spars and the blading elements can be made in a single piece by injection manufacturing in an injection mold. More particularly, the first spar 32 and the transverse blading elements 32a 1, 32a2 are part of a single piece. manufactured in one piece. The second spar 34, for its part, is not made in one piece with the transverse blade elements 32a 1, 32a2 of the first spar 32.
[0027] As shown in Figure 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.
[0028] 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.
[0029] The second large face 34b of the second spar 34 here also carries blading elements 34b1, 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 34bl, 34b2 are part of a single piece manufactured in one piece.
[0030] In this embodiment, the blading elements 32a 1, 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 34bl, 34b2 of the second spar 34 along this spar. In other words, the blading elements 32a 1, 32a2 are aligned transversely (along the Y direction) with the blading elements 34bl, 34b2.
[0031] As shown in Figure 2, the blade elements 32a1, 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 the right of the connection zone zl, z2 of a blading element 34bl, 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.
[0032] 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.
[0033] The blade elements 32al, 32a2 of the first spar 32 each comprise a distal end 32a1.1, 32a2.1 which is considered to be free when it is not yet assembled with the second spar 34. Each distal end 32al.1, 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.
[0034] By way of example, the blade elements 32a 1, 32a2 carry at their distal end 32a 1.1, 32a2.1 at least one tenon-forming element 32a 1.2, 32a2.2 (for example in the form of a pin) and the first large face 34a of the second spar carries mortise-forming elements 34a 1, 34a2 (for example in 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. Figure 3A illustrates in perspective the tenon 32al.2 arranged on the distal end edge 32a 1.1 of the blade element 32a 1.
[0035] Thus, the tenons 32a 1.2, 32a2.2 of the blading elements 32a 1, 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 blade elements and the second spar. With a mortise-and-tenon type joint / connection (regardless of which element 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, particularly 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 protruding from the mortise-forming elements. Alternatively, in a complementary manner, a screw can be placed through the spar and press the blade element against the spar. Alternatively, in a complementary manner, the tenon-forming elements can be split along their length and clip through the mortise-forming elements.Other complementary assembly / fixing means can alternatively be used between the blade elements and the second spar.
[0036] Figure 3B illustrates an alternative embodiment showing two tenons 32a 1.2', 32a 1.3' arranged on the distal end edge 32a 1.1' of the blading element 32a 1'. 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.
[0037] Figure 3C illustrates another variant with two tenons of different shapes, for example trapezoidal, or square, or even rectangular, 32a 1.2", 32a 1.3" arranged on the distal end edge 32a 1.1" of the blade element 32a 1". These elements are inserted into complementary shapes (through openings here) 34a 1" and 34a2" of the spar 34".
[0038] As shown in Figure 2, the blade elements 34b1, 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 Figure 2 with other identical modules using the same principle of direct fixing / connection between blade elements and spar. A thrust reverser ring grid is thus formed step by step by adding additional spars (the module thus formed is a multi-spar module which may be made up of n side members 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 or close to 40, the module thus formed can cover approximately 90° of circumference of the inversion ring) which can be easily adjusted to the desired dimensions (depending on requirements).
[0039] 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 32al, 32a2 originating only from the first spar.
[0040] Figure 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 34a1', 34a2' (two in number in this example; the remark applied to the blading elements of the mode of Figure 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 34a1', 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'.
[0041] 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 34a1' 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 32a1', 34a1, 32a2', 34a2 in the module thus assembled. Again, as in the mode of Figure 2, the space between the two adjacent spars 32, 34 defines an inversion aerodynamic channel which includes the transverse blade elements 32a1, 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.
[0042] 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 32bl, 32b2 which extend away from this large face. As for the mode of figure 2, the blade elements 34a 1', 34a2' (fig. 4) can 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.
[0043] 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 Figure 4, which allows them to be fitted together at will to form a grid from elementary modules assembled with each other.
[0044] Figure 5 illustrates a thrust reverser module 40 according to a second embodiment which differs from the embodiment of Figure 2 by a longitudinal offset between the blading elements 42a 1, 42a2, 42a3 carried by the first large face 42a of the first spar 42 and the blading elements 44b 1, 44b2, 44b3 carried by the second large face 44b of the second spar 44 (staggered arrangement with respect to the second spar when the blading elements 42a 1, 42a2, 42a3 are connected to the second spar; in Figure 5 the blading elements 42a 1, 42a2, 42a3 are in the approach position with respect to the second spar 44 and not yet connected to the latter).
[0045] More particularly, the blading elements 42a1, 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 Z1, Z2, Z3 of two successive blading elements 44bl, 44b2, 44b3 carried by the second large face 44b of the second spar 44. The assembly / connection means may be, here, as for the mode of FIG. 2, 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 42 carrying first fixing means and the first large face 44a of the second spar 44 carrying second fixing means complementary to the first means. More particularly, the blade elements 42a1, 42a2, 42a3 each carry, at their distal end opposite the large face 44a of the second spar, respectively a tenon-forming element 42a 1.2, 42a2.2, 42a3.2 which fits into a mortise-forming element arranged in geometric correspondence on the large face 44a opposite (for example the elements 44a 1 and 44a3 in dotted lines). On the side of the second large face 44b of the second spar, it is thus possible to access the distal end of the tenon-forming elements which are engaged in the corresponding openings opposite (above-mentioned mortise-forming elements and visible in FIG. 5 in alignment with the tenon-forming elements) of the second spar 44 when these openings are through-holes. Depending on the configurations envisaged, the openings may or may not be through-holes, depending on whether or not access is desired to the fixing means from the second large face 44b of the second spar.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 blading elements 44bl, 44b2, 44b3 carried by the second large face 44b.
[0046] It will be noted that the blading elements 44bl, 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. The different modes of figures 3A-3C described above can also be applied here, as well as the mode of figure 9 which will be described later.The arrangement illustrated in Figure 5 shows that, on the side of the second large face 44b of the second spar 44, it is possible to access the area of the second spar left free between the connection areas Z1, Z2, Z3 (of the successive blading elements 44bl, 44b2, 44b3), where the blading elements 42al, 42a2, 42a3 carried by the first large face 42a of the first spar 42 are connected / assembled / fixed to the first large face 44a of the second spar 44 (when the openings shown pass through the thickness of the second spar). It is thus possible to access the mechanical attachment / assembly between the blading elements 42a1, 42a2, 42a3 and the second spar 44 and, for example, to complete and / or reinforce this attachment or this mechanical assembly. The mode of figure 9 which will be described later thus illustrates an example of a fixing means for which the access cleared on the side of the. second large face 44b of the second spar 44 proves useful. This may also prove useful with other attachment means such as those of the modes of Figures 3A-3C.
[0047] Everything that has been said previously about the first mode of Figure 2 and its variants also applies here (except with regard to the particularities of the assembly of the blading elements of the first spar at the connection zones Z1, Z2 of the second spar) and will not be repeated.
[0048] Figure 6 illustrates a thrust reverser module 50 according to a third embodiment in which two adjacent parallel spars 52, 54 both carry blade elements but which, unlike the mode of Figure 5, are directed in opposite directions to each other. The first spar 52 is identical to the spar 42 of FIG. 5 and the blade elements 52a 1, 52a2 that 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 blade elements 54a1, 54a2 carried by the first large face 54a which is opposite the blade elements 52a 1, 52a2 of the first spar 52 are oriented in the opposite direction to the blade elements 44b 1, 44b2, 44b3 of FIG. 5.The blading elements 54a 1, 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 54a 1, 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 52a 1, 52a2 of the first spar 52 connected to the second spar 54).
[0049] Figure 7 illustrates a thrust reverser module 50' according to an alternative embodiment which differs from the module 50 of Figure 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 54a1, 54a2, 54a3 carried by the first large face 54a', that is to say that a first blading element carried by a face is arranged opposite a second element of blading carried by the opposite face and directed in a direction opposite to that of the first blading element (ladder arrangement).
[0050] As for the mode of figure 6, the blade elements 54a1, 54a2, 54a3 may or may not be assembled with the first large face 52a of the first spar 52' opposite.
[0051] 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 54a1 and 54a2.
[0052] The two spars 52', 54' (with the blading elements shown in dotted lines) thus have an identical symmetrical configuration but offset longitudinally from one spar to the other as illustrated in Figure 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.
[0053] Figure 8 illustrates a thrust reverser module 60 according to a fourth embodiment which comprises four adjacent spars assembled by interlocking with each other two by two.
[0054] This mode is based on several previous modes / variants, namely the mode of Figure 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 Figure 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, on the mode of Figure 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 areas located between two consecutive blading elements carried by the second large opposite face of the second spar.
[0055] More particularly, the module 60 of figure 8 comprises two end spars 62, 64 identical to the spar 52 of figure 6 and which frame two central spars 66, 68 having a structure of the type of that of the spar 34' of figure 4 with the blade elements offset longitudinally from one face to the other.
[0056] Each end spar 62, 64 comprises respective blade elements 62a1, 62a2, 62a3 and 64a1, 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 66cl, 66c2, 66c3 and 68cl, 68c2.
[0057] The first large face 66a, 68b of the spar 66, 68 carries respective blading elements 66a1, 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 62cl, 62c2, 62c3 and 64cl, 64c2.
[0058] Furthermore, each central spar 66, 68 carries on its large face arranged opposite the other large face of the other central spar blading elements 66bl, 66b2, 66b3 and 68a1, 68a2, 68a3, 68a4 which are assembled with elements forming mortises arranged on the large opposite face, namely respectively 68c3, 68c4 and 66c4, 66c5, 66c6.
[0059] 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.
[0060] The mortise-forming elements of each central spar are arranged between the successive connection zones of the successive blade elements.
[0061] Figure 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 on the side of a large face of the second spar L2 and its emerging end is then deformed, from the opposite large face of the second spar L2, for example by crushing, in order to prevent its axial withdrawal. In this mode, the clear access to the fixing / assembly means on the side of the opposite large face of the second spar L2 proves useful.
[0062] This assembly possibility also applies to the modes and variants described above which may be affected by such an assembly mode.
[0063] 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 in the arrangement of the blade elements on the side members and their orientation.
[0064] 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.
[0065] 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.
[0066] 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.
[0067] 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 reversing module (30) of a thrust reversing ring for an aircraft nacelle thrust reverser, characterized in that the thrust reversing module (30) comprises: -a first spar (42) which extends in a longitudinal direction (D) and carries blading elements (42a 1, 42a2, 42a3) each extending transversely relative to the longitudinal direction (D), the transverse blading elements (42a 1, 42a2, 42a3) being distributed along the first spar (42), -a second spar (44) which extends parallel to the first spar (42) and comprises first and second opposite large faces (44a, 44b), at least a portion of the transverse blading elements (42a1, 42a2, 42a3) of the first spar (42) being connected to the first large face (44a) of the second spar (44) which is arranged opposite, the second large face (44b) of the second spar (44) carrying transverse blading elements (44b1, 44b2, 44b3) which each extend transversely relative to the longitudinal direction of the second spar (44), away from a zone (Zl, Z2, Z3) of the second spar (44) called the connection zone of the blading element in question, and in a direction opposite the first large face (44a) of the second spar (44), the transverse blade elements (42a 1, 42a2,42a3) of said at least one part of the transverse blading elements of the first spar (42) being each connected to the first large face (44a) of the second spar (44), between two successive connection zones (Zl, Z2, Z3) of two successive transverse blading elements (44b1, 44b2, 44b3) carried by the second large face (44b) of the second spar (44), so that the transverse blading elements (42a1, 42a2, 42a3) of said at least one part of the transverse blading elements of the first spar (42) connected to the second spar and the transverse blading elements (44b1, 44b2, 44b3) carried by the second large face (44b) of the second spar (44) form a staggered arrangement relative to the second spar.,
2. Thrust reverser module according to claim 1, characterized in that the transverse blade elements (32a 1, 32a2) of said at least a portion 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 (32a 1, 32a2) and second complementary fixing means carried by the second spar (34).
4. Thrust reverser module according to one of the preceding claims, characterized in that the first large face (34a') of the second spar (34') carries blading elements (34a 1', 34a2') which each extend transversely relative to the longitudinal direction of the second spar (349, the blading elements (32a 1, 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 (349, between two successive blading elements (34a1', 34a29 carried by the first large face (34a9 ■
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 (42a 1, 42a2, 42a3) each extending transversely relative to the longitudinal direction (D), the transverse blade elements (42a 1, 42a2, 42a3) being distributed along the first spar (42), -providing a second spar (34) which comprises first and second opposite large faces (44a, 44b), the second large face (44b) of the second spar (44) carrying transverse blading elements (44b1, 44b2, 44b3) which each extend transversely relative to the longitudinal direction of the second spar (44), away from a zone (Zl, Z2, Z3) of the second spar (44), called the connection zone of the blading element in question, and in a direction opposite to the first large face (44a) of the second spar (44), -positioning the second spar (44) parallel and adjacent to the first spar (42), -connecting at least a portion of the transverse blading elements (42a1, 42a2, 42a3) of the first spar (42) to the first large face (44a) of the second spar (44) which is arranged opposite, the transverse blading elements (42a 1, 42a2,42a3) of said at least one part of the transverse blading elements of the first spar (42) each being connected to the first large face (44a) of the second spar (44), between two successive connection zones (Z1, Z2, Z3) of two successive transverse blading elements (44b 1, 44b2, 44b3) carried by the second large face (44b) of the second spar (44), so that the transverse blading elements (42a 1, 42a2, 42a3) of said at least one part of the transverse blading elements of the first spar (42) connected to the second spar and the transverse blading elements (44b 1, 44b2, 44b3) carried by the second large face (44b) of the second spar (44) form a staggered arrangement relative to the second spar.,