Thrust reverser ring for 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 a longitudinal axis, the thrust reverser modules being circumferentially distributed around the axis to form the ring. A thrust reverser module (10) is arranged between and mechanically independent of two adjacent thrust reverser modules, said thrust reverser module (10) comprising: a spar (12) extending in a longitudinal direction (D) and comprising two opposite ends (12c, 12d) spaced apart from each other in the longitudinal direction, each end being configured to attach the spar to an aircraft nacelle; and a plurality of transverse blade elements (14a, 14b) distributed along the spar, extending from the spar.

Description

Technical Field

[0001] This disclosure relates to a thrust reverser ring for an aircraft nacelle thrust reverser and an aircraft nacelle including the thrust reverser ring. Background Technology

[0002] It is known in the prior art that aircraft nacelles are equipped with thrust reverser cascades to generate reverse thrust when required by the aircraft during operation. Typically, the thrust reverser cascades form a ring around the nacelle, and each cascade includes blades whose orientation, when deployed, deflects the propulsive airflow toward the front of the jet engine. These cascades are typically secured to the nacelle structure by their leading and opposing trailing ends. Such cascades generally have a rectangular shape resembling a duckboard architecture, comprising: multiple parallel spars, each extending axially in the longitudinal direction; and multiple blades extending laterally between the spars.

[0003] Existing methods for manufacturing thrust reverser blades are relatively complex and / or costly.

[0004] In view of the above, it is advantageous to manufacture the thrust reverser ring structure for aircraft nacelle thrust reversers in a simpler manner than existing technologies. Summary of the Invention

[0005] Therefore, the object of the present invention is to provide a thrust reverser ring for an aircraft nacelle thrust reverser, the ring extending about a longitudinal axis, characterized in that the thrust reverser ring includes a plurality of thrust reverser modules, each of the thrust reverser modules extending along a longitudinal direction parallel to the longitudinal axis of the ring and circumferentially distributed around the longitudinal axis, at least one of the plurality of thrust reverser modules being disposed between two adjacent thrust reverser modules and mechanically independent of the two adjacent thrust reverser modules, the at least one thrust reverser module comprising: - A single wing sparb extending in the longitudinal direction and including two opposing ends spaced apart in the longitudinal direction, each of the two opposing ends being configured to secure the wing sparb to the aircraft nacelle. - Multiple transverse blade elements, which are distributed along the spar and extend from the spar.

[0006] At least one thrust reverser module, comprising a single spar, is mechanically independent of the two adjacent modules clamping it. That is, when considering modules arranged side-by-side along the overall shape of the thrust reverser ring, this module is not mechanically connected or fixed to adjacent modules in the circumferential direction relative to the longitudinal axis of the thrust reverser ring. The corresponding modules are simply arranged adjacent to each other and mechanically connected to the aircraft nacelle only through their opposing fore and aft ends. This thrust reverser module structure simplifies the manufacturing process of the thrust reverser ring structure of the aircraft nacelle, thereby reducing its manufacturing cost, because the corresponding module does not need to be assembled with adjacent modules to form a blade cascade (after which each blade cascade is fixed to the nacelle). In fact, the module can be directly positioned and fixed to the nacelle. Therefore, the thrust reverser module defined above does not include: multiple spars, let alone forming a blade cascade formed by interconnected spars and blades. It should be noted that each end of the spar is configured only to fix the spar (i.e., the aforementioned thrust reverser module) to the nacelle, not to fix multiple spars.

[0007] Based on other possible features (which can be used individually or in combination): - At least one end of the two opposite ends of the spar of the at least one thrust reverser module extends integrally with the spar along the longitudinal direction of the spar. - At least one end of the two opposite ends of the spar of the at least one thrust reverser module includes a plate extending circumferentially relative to the longitudinal axis of the ring; - At least one end of the two opposite ends of the spar of the at least one thrust reverser module includes a plate that extends laterally relative to the longitudinal direction of the spar; - The spar includes two opposing large surfaces, and the at least one thrust reverser module includes at least one side sealing plate of the module, which extends parallel to the first large surface of the two opposing large surfaces of the spar and is located on the opposite side of the lateral blade element extending from the first large surface of the spar. - The at least one thrust reverser module includes two side sealing plates of the module, which extend parallel to two opposite large surfaces of the spar and are respectively disposed on opposite sides of the lateral blade elements extending from the two opposite large surfaces of the spar. - The side sealing plate of the module is also fixed to the large surface of the wing beam opposite to the corresponding side sealing plate; -The wing spars consist of two opposing large surfaces, and the transverse blade elements each extend from the two opposing large surfaces of the wing spars; - The transverse blade elements are symmetrically distributed on two opposing large surfaces of the spar relative to the spar, and the blade elements on one of the two opposing large surfaces of the spar are arranged to face each other longitudinally with the blade elements on the other opposing large surface of the spar. - The transverse blade element extends from either side of the spar and is offset longitudinally from one of the two opposing large faces of the spar to the other opposing large face of the spar. - The transverse blade element extends only from one of the two opposing large faces of the spar.

[0008] Another object of the present invention is to provide an aircraft nacelle comprising a thrust reverser ring as briefly described above.

[0009] A further objective of this invention is to provide a method for manufacturing a thrust reverser ring for an aircraft nacelle thrust reverser, the thrust reverser ring extending along a longitudinal axis. The method includes the following steps: - Provides multiple thrust reverser modules, each of the thrust reverser modules comprising: a single spar extending in a longitudinal direction and including two opposing ends spaced apart from each other in the longitudinal direction; and multiple transverse blade elements distributed along and extending from the spar. - The thrust reverser modules are positioned on the jet engine nacelle of the aircraft by distributing the thrust reverser modules circumferentially around the longitudinal axis of the thrust reverser ring to form a thrust reverser ring, with the longitudinal direction of the thrust reverser modules parallel to the longitudinal axis of the thrust reverser ring. - At least one thrust reverser module is secured to the nacelle by means of two opposite ends of the spar of the at least one thrust reverser module, such that the at least one thrust reverser module is positioned between two adjacent thrust reverser modules and is mechanically independent of them.

[0010] Therefore, the method briefly described above enables the simple manufacture of a novel thrust reverser ring configuration for aircraft nacelle thrust reversers. At least one of the aforementioned thrust reverser modules (with a single sparsor) can indeed be directly positioned and secured to the nacelle, without needing to be secured to adjacent modules circumferentially positioned on either side. The method may also include any of the aforementioned features associated with the thrust reverser ring. Attached Figure Description

[0011] Other features and advantages of the present disclosure will become apparent from the following description of embodiments, which are given in the form of non-limiting examples, with reference to the accompanying drawings.

[0012] Figure 1 This is a schematic overall view of a thrust reverser module of a thrust reverser ring according to an embodiment of the present invention.

[0013] Figure 2 This is a schematic overall view of an aircraft nacelle, which includes a thrust reverser ring formed by one or more modules, said modules being as follows: Figure 1The module shown is fixed only to the nacelle.

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

[0015] Figure 3B This is a partial schematic overall top view showing two adjacent thrust reverser modules, which are connected to... Figure 3A The free ends are the same, and their respective free ends are fixed.

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

[0017] Figure 4B It shows Figure 4A A partial schematic overall view of the module with its two relatively free ends.

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

[0019] Figure 5B It shows Figure 5A A partial schematic overall view of the module with its two relatively free ends.

[0020] Figure 6A This is an overall view of the thrust reverser module of the thrust reverser ring according to another embodiment of the present invention.

[0021] Figure 6B It shows the blade element and Figure 6A A partial schematic top view of the assembly of one of the module's cover plates.

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

[0023] Figure 7B This is a partial schematic top view showing a thrust reverser module according to a second variant of an embodiment. Detailed Implementation

[0024] like Figure 1 As schematically shown and indicated by general reference numeral 10, a thrust reverser module according to an embodiment of the present invention typically includes: a single spar 12 and a plurality of blade elements 14a-b, the plurality of blade elements being arranged laterally relative to the longitudinal direction D of the spar and distributed along the spar and fixed to the spar.

[0025] More specifically, the wing spars 12 include two opposing large surfaces 12a and 12b (large surface 12a is in...). Figure 1 As can be seen in the 3D diagram, in the X, Y, Z three-dimensional coordinate system, each large surface extends primarily within a plane defined by the X direction (longitudinal direction) and the Z direction (height or radial direction). The sparsity also has a thickness (which, in a very simplified...) Figure 1 (not shown in the image), this thickness extends along the third direction Y, and when the two opposing large surfaces 12a and 12b are planes, this thickness is perpendicular to the plane containing these two large surfaces.

[0026] The spar 12 includes two opposing ends 12c and 12d spaced apart from each other along the longitudinal direction D (X-axis), and each end is configured to fix the spar 12 to a position such as... Figure 2 The aircraft nacelle is shown schematically in the diagram. Various possible configurations at the wing spars will be discussed in subsequent references. Figures 3A to 5B Describe it.

[0027] exist Figure 1 In the illustrated embodiment, the lateral blade elements 14a-b are connected to each of the two opposing large surfaces 12a, 12b of the spar. Therefore, the thrust reverser module 10 includes a first set of lateral blade elements 14a connected to the first large surface 12a, and a second set of lateral blade elements 14b connected to the opposing second large surface 12b.

[0028] In this embodiment, the two sets of transverse blade elements are symmetrically connected relative to the spar 12, so the module has a roughly ladder shape when viewed from the top view. More specifically, the blade element 14a disposed on the large surface 12a of the spar is disposed along the longitudinal direction D of the spar, facing the blade element 14b disposed on the other opposite large surface 12b of the spar.

[0029] For example, the two opposite ends 12c and 12d of the wing spars have, as Figure 3A The configuration of end 12c shown: Each end extends longitudinally integrally with the spar, i.e., like the two opposing large faces 12a and 12b of the spar, extending along a plane defined by the X and Z directions. Each end includes one or more fixing holes ( Figure 3A A single fixing hole t1 is shown, extending through the thickness of end 12c in the Y direction. A fixing plate 12c1 is attached to end 12c to secure end 12c (and consequently the spar) to the portion forming the aircraft nacelle supporting the spar. In the illustrated embodiment, plate 12c1 extends integrally with end 12c via portion 12c1.1 and then extends laterally relative to the longitudinal direction D of spar 12 in the form of a folded-back portion 12c1.2. Figure 3BTwo adjacent modules 10 are shown in a top view (projection on a plane XY). These modules are not mechanically connected (mechanically independent in the lateral or circumferential direction), but are each mechanically connected to the outer edge B1 of the nacelle via their free ends 12c. As shown, a generally L-shaped fixing plate 12c1 is fixed to the end 12c by one or more suitable fixing members (e.g., bolts, rivets, etc.) O1, which mate with fixing holes t1 and corresponding fixing holes t2 of portions 12c1.1 of the fixing plate 12c1. The fixing plate 12c1 is fixed to the edge B1 by one or more suitable fixing members (e.g., bolts, rivets, etc.) O2, which mate with fixing holes t2 of portions 12c1.2 of the fixing plate 12c1. Figure 3B As shown in module 10 on the right, a second plate 12c1 (which may be the same as or different from the plate used in module 10 on the left) can be provided on the opposite surface of the free end 12c to reinforce the fixation of the spar on edge B1. Thus, the two fixing plates clamp the free end 12c of the spar on both sides. The opposite ends of the spar (not shown) can also be installed in the same way. Figure 3B The side-by-side arrangement (around) has been shown in the image. Figure 2 The two modules 10 shown (the thrust reverser ring and the nacelle are arranged circumferentially along their longitudinal axis XX') are different, but in a variant embodiment not shown, Figure 1 and Figure 3A Module 10 can be arranged adjacent to different thrust reverser modules, such as conventional type thrust reverser modules (spars with lateral blade elements). Typically, the shape of each plate is adapted to the rotational shape of the nacelle section to which it is attached, and thus, for example, a curvature around the Y-axis can be adopted.

[0030] Figure 4A and Figure 4B Another embodiment is shown, in which the two opposite ends 12c', 12d' of a single spar 12 each include plates 12c'1, 12d'1, which extend integrally with the spar 12 along its longitudinal direction and extend laterally or laterally relative to the longitudinal direction. It should be noted that, depending on the respective end of the spar, the plate is arranged to abut against the edge or longitudinal edge of the spar, which corresponds to the leading or trailing edge of the blade element, such as... Figure 4B As shown. For example, the plate can be a sheet mechanically attached to the end of the spar, or it can be a sheet forming an integral part of a spar typically manufactured by injection molding. Therefore, plates 12c'1 and 12d'1 extend generally within a plane XY, which is perpendicular to the plane XZ containing the two opposing large faces of the spar. The plate may not extend strictly within the plane XY, as its overall shape may be slightly curved, with the convex surface pointing upwards along the Z direction (…). Figure 4BThis is to match the complementary shape (concave downwards) of the portions of the nacelle to which the ends 12c' and 12d' are fixed. Typically, the shape of each plate is adapted to the rotational shape of the portion of the nacelle to which it is fixed, and therefore, may have curvature about the X-axis, for example. The plate is generally flat and flared, giving it a roughly trapezoidal or scraper shape when viewed from above. Fixing holes t4 and t5, penetrating the thickness of plate 12d'1 (and correspondingly 12c'1), engage with suitable fixing components (e.g., bolts, rivets, etc.) to secure the ends 12d' (and correspondingly 12c') (and thus the spars) to the portion of the aircraft nacelle forming the spars end support. Figure 4B The diagram shows components 13 and 14 that support the two opposing ends 12c' and 12d' of the wing spars, respectively (these components 13 and 14 are fixedly connected to the nacelle), and thus, each plate 12c'1, 12d'1 is fixed to the corresponding component 13, 14 (and consequently to the corresponding outer edge of the nacelle) by suitable fixing members that mate with holes t4 and t5. When the plate 12c'1, 12d'1 is positioned on the nacelle ( Figure 2 Each plate extends circumferentially relative to the longitudinal axis XX' of the thrust reverser ring and nacelle.

[0031] Figure 5A and Figure 5B Another embodiment is shown in which the two opposite ends 12c" and 12d" of a single spar 12 each include plates 12c"1 and 12d"1 that extend laterally relative to the longitudinal direction of the spar 12, and in this embodiment, extend in a transverse plane defined by the Y and Z directions. Typically, the shapes of the plates 12c"1 and 12d"1 are adapted to the rotational shape of the portion of the nacelle to which they are attached, and therefore, for example, may have curvature about the Y-axis in addition to the generally T-shape observed from above (in a plane XY projection). Figure 5A The fixing holes t6 and t7, with a thickness of 12c"1, through the middle plate, mate with suitable fixing components (e.g., bolts, rivets, etc.) to secure the end 12c" (and thus the spar) to the nacelle portion forming the spar end support. Figure 5B The diagram shows components 16 and 17 that support the two opposing ends 12c" and 12d" of the wing spars, respectively, and thus, each plate 12c"1, 12d"1 is fixed to the corresponding components 16 and 17 by suitable fixing members that mate with holes t6 and t7. When the plates 12c"1, 12d"1 are positioned on the nacelle ( Figure 2 Each plate extends circumferentially relative to the longitudinal axis XX' of the jet engine and nacelle.

[0032] Figure 2A known type of aircraft nacelle 20 is shown, comprising a front fairing 22 and a rear fairing 24 arranged along a longitudinal axis XX', defining an annular opening O between them for accommodating a thrust reverser ring of the aircraft nacelle's thrust reverser. In addition to the thrust reverser ring, the thrust reverser specifically includes an actuator that, when controlled by one or more drive units (engines), activates functional elements of the thrust reverser ring, thereby deflecting airflow passing through the thrust reverser ring. The aircraft nacelle, together with an engine or turbine, forms the propulsion assembly of the aircraft.

[0033] To manufacture a thrust reverser ring according to an embodiment of the present invention, a plurality of thrust reverser modules are provided, and these modules include one or more modules 10 as described above. Other thrust reverser modules for forming the thrust reverser ring include spars, transverse blade elements connected to the spars, and these modules can be mechanically coupled together as in the prior art, unlike the modules 10 described above.

[0034] In the minimized thrust reverser ring configuration, the thrust reverser ring includes a single thrust reverser module 10, and other modules, for example of conventional type, are assembled together to form a blade array, which is then mounted on the nacelle.

[0035] In another thrust reverser ring configuration, the thrust reverser ring includes the thrust reverser module 10 as described above to simplify the manufacturing process of the thrust reverser ring as much as possible. In yet another configuration, the thrust reverser ring includes, on the one hand, a plurality of thrust reverser modules 10 as described above (these modules are not necessarily adjacent to each other), and on the other hand, conventional thrust reverser modules or conventional blade cascades. Regardless of the configuration chosen, the thrust reverser module 10 is mechanically independent of adjacent modules (i.e., the two adjacent modules that clamp the thrust reverser module 10).

[0036] Each thrust reverser module 10 is positioned within an annular opening O, defined previously at a radial position relative to the longitudinal axis XX' of the nacelle, which corresponds approximately to the longitudinal axes of the two corresponding forward outer edges 22a and aft outer edges 24a of the forward and aft fairings, respectively. The two forward outer edges 22a and aft outer edges 24a are longitudinally separated from each other by the annular opening O. Each outer edge forms a fixed support for one of the two opposing ends of the spar of each thrust reverser module. In this regard, each edge can be suitably configured to achieve the aforementioned fixation (especially as described above). Figures 3A to 5B One of the fixing methods described above), and may include, for example, fixing pieces specifically designed for this purpose (e.g., annular flanges or annular segments extending circumferentially along the respective peripheral edges).

[0037] In practice, the positioning of a single or each thrust reverser module 10 is achieved by fixing the two opposite ends of the module to the two corresponding edges 22a, 24a of the nacelle. Figure 2 In one example of the thrust reverser ring configuration shown, there are multiple modules 10, which are adjacent to each other. Module 10 is positioned next to an adjacent module 10 that is already fixed to the nacelle, but is not (intentionally) connected or mechanically coupled to that adjacent module (especially not laterally or circumferentially coupled to it). The same applies to modules positioned on opposite sides. Adjacent modules 10 are freely arranged adjacent to each other in pairs, even with small lateral / circumferential mechanical clearances between these modules. More specifically, when two modules 10 are positioned side by side within the annular opening O, one set of lateral blade elements of one of the two modules is arranged to face the other set of lateral blade elements of the adjacent module, and more specifically, the lateral blade elements facing both modules 10 are positioned at the same location in the longitudinal direction relative to the spars of these modules. Although these facing lateral blade elements are not connected to each other and even have mechanical clearances between them, the overall effect presented by the geometric juxtaposition of these modules is that each facing lateral blade element is considered as a half-blade, and thus two facing half-blades typically form a single lateral blade. The above situation also applies to the case where module 10 is arranged adjacent to a conventional module, which itself can be mechanically connected to another conventional module.

[0038] therefore, Figure 2 The thrust reverser modules 10 are positioned adjacent to each other within the annular opening O and are circumferentially distributed around the axis XX' to form a thrust reverser ring structure. Only three modules 10 are shown in detail in this structure (other modules 10 are schematically represented by parallel dashed lines). It should be noted that the modules 10 in the thrust reverser ring structure are not necessarily adjacent to each other and can also be distributed among multiple other thrust reverser modules. For example, each module 10 can be located between two thrust reverser blade cascades, each of which is formed from multiple conventional thrust reverser modules (conventional blade cascades are formed by interlacing spars and transverse blade elements and are usually made into a single block by injection molding).

[0039] Figure 6A A thrust reverser module 30 according to another embodiment of the invention is shown. Provided the corresponding components remain unchanged, Figure 1 The reference numerals for each component of module 10 are shown in the attached figures. Figure 6A It is still in use in China.

[0040] The thrust reverser module 30 includes at least one plate, in this embodiment, two side sealing plates 32, 34 of the module, which extend parallel to the two opposing large surfaces 12a, 12b (i.e., within the plane XZ) of a single spar. The two sealing plates 32, 34 are respectively disposed opposite to the two opposing large surfaces 12a, 12b of the spar. For example, each plate 32, 34 is fixed to lateral blade elements 14a, 14b, which are connected to the spar 12 and extend from the large surface of the spar opposite to the corresponding sealing plate. Thus, the two sealing plates 32, 34 form the lateral end sidewalls of the blade elements. In the illustrated embodiment, each plate 32, 34 may also include two folded-back portions 32a, 32b and 34a, 34b, which extend laterally along the direction of the spar 12 from the two opposing ends of the central portions 32a, 34a of the corresponding plate. Figure 6A As shown, each folded-back section is fixed to the large surface facing the sparsity. Therefore, each plate with two folded-back sections forms a structure for... Figure 1 The module is a laterally enclosed structure consisting of spars and transverse blade elements. Multiple modules 30 are placed on the nacelle to form... Figure 2 In the ring configuration (note that only one module 30 can exist in a thrust reverser ring), two adjacent modules 30 are closed relative to each other along the circumferential direction defined by the thrust reverser ring and are not mechanically connected to each other. The relationship between module 30 and adjacent modules or adjacent conventional blade cascades is similar. In this way, the chambers defining the passage of reversed airflow through the thrust reverser ring are now each defined within the same module: each chamber through which airflow passes is defined by the module's spars, two consecutive blade elements located on the same large surface (along the longitudinal direction of the spars), and facing end plates. Figure 1 Module 10 Figure 2 In the installation configuration, each airflow chamber is defined by two spars facing two adjacent modules 10, two consecutive half-blades located on the same large surface of one of the two modules 10, and two facing consecutive half-blades located on the same large surface of the other module 10. With the half-blades having the same lateral dimension, the module 30... Figure 2 The configuration has an airflow passage chamber with a cross-sectional area smaller than that of module 10. However, it can be assumed that the lateral dimension of the blade element of module 30 roughly corresponds to the sum of the lateral dimensions of the two blade elements facing two adjacent modules 10. Figure 1 Similar to module 10, in which Figure 6A Module 30 Figure 2 In the installation configuration, the modules 30 arranged adjacent to each other along the circumferential direction of the thrust reverser ring are mechanically independent of each other in this direction, that is, they are not mechanically connected to each other (especially not connected through their end plates 32, 34), and are even spaced apart from each other by a small circumferential gap in the lateral / circumferential direction.

[0041] Side sealing plates can be attached to individual spar blade elements in various ways. For example, a mortise and tenon joint mounting structure can be used: each blade element has one or more protrusions at its distal end (e.g., protrusion 14a1 of blade element 14a), which are received in openings facing the corresponding sealing plate (e.g., opening 32a1 of sealing plate 32), such as... Figure 6B As shown. It should be noted that the blade element can be secured to the plate by pressing the head of the protrusion or tenon together, similar to pressing a rivet head together. Alternatively, the distal end of the blade element can be glued or welded to the facing end plate. The two side end plates can be secured in the same way. It should also be noted that the folded-back portions of the two side end plates can be secured to the center spar in the same way described above.

[0042] Typically, with only using Figure 1 Unlike other modules, the side sealing plate can improve the mechanical strength of the blade element and guide airflow across the entire lateral dimension of the blade element.

[0043] It should be noted that, Figure 6A The module configuration can also be achieved in other ways. For example, blade elements 14a and 14b can be carried by side plates 32 and 34, respectively, and connected to the large surface facing the spar 12 in the same manner described above. The spar 12 itself does not carry any blade elements (in a variant not shown, the blade elements are distributed between the plate and the spar). Therefore, in the final configuration, blade elements 14a and 14b extend between the plates 32 and 34 and the large surface facing the spar, respectively.

[0044] In a variant of the embodiment not shown, the spar carries the blade element, and the module includes one or two side panels, for example, which are not fixed to the blade element of the spar.

[0045] In the above embodiments, all thrust reverser modules constituting the thrust reverser ring have Figure 6A The configuration. However, according to a variant not shown, in the thrust reverser ring modules, only one or some modules have this configuration, while the other modules have Figure 1 The configuration or traditional configuration, or other modules, include both those with Figure 1 The configuration includes one or more modules, and further includes one or more modules with a conventional configuration. For example, in areas where airflow needs to be deflected both longitudinally and laterally, the blade element must deflect the airflow longitudinally, while the spars must deflect the airflow laterally. In such cases, Figure 6A The module in this section is more suitable because it can provide higher lateral stiffness for the airflow deflection module. At this time, the spar will also have a specific profile.

[0046] It should be noted that in the configuration of the thrust reverser ring installed in the jet engine nacelle, Figure 6A Module 30 may not be arranged adjacent to another module 30, but rather adjacent to, for example, a conventional thrust reverser blade cascade, without being mechanically connected to it. In the thrust reverser ring, in addition to the conventional blade cascade, multiple modules according to the invention can be arranged circumferentially, for example, without using molds different from those used to manufacture the conventional blade cascade of the thrust reverser ring to manufacture a smaller width blade cascade. Therefore, the manufacturing process of the thrust reverser ring is simplified.

[0047] Furthermore, using the modules according to the invention in the thrust reverser ring (whether or not it includes conventional blade cascades) allows for easier adjustment of the direction of the deflected jet by individually adjusting the orientation of each module, whereas in conventional blade cascades, this is much more difficult to achieve due to the interaction between specific spars and other spars.

[0048] exist Figure 7A In a variant of the illustrated embodiment, the lateral blade elements are longitudinally offset from the large face 12a' of the spar 12 to the opposite large face 12b'. In other words, the first set of lateral blade elements 14a' connected to the first large face 12a' of the spar is longitudinally offset (asymmetrical) relative to the second set of lateral blade elements 14b' connected to the opposite large face 12b' of the spar. In other words, the lateral blade elements are staggered along the spar on both sides of the spar 12': one lateral blade element from one of the two sets of lateral blade elements connected to a large face is positioned along the spar between two lateral blade elements from the other set connected to the opposite large face. Therefore, Figure 7A The module as a whole is shaped like a ladder with stepped offsets. It should be noted that it can be... Figure 6A Similar or identical side panels added Figure 7A The module.

[0049] exist Figure 7B In a variant of the illustrated embodiment, the lateral blade element 14" is disposed only on one side of the spar 12" and therefore only connected to one of the two large faces of the spar, making the module as a whole comb-shaped. It should be noted that the lateral blade element 14" can be connected to the spar on the extended side. Figure 6A One of the boards, similar or the same side panel, is added. Figure 7B Middle module.

[0050] It should be noted that in any of the above methods and variations, the thrust reverser ring may be partially interrupted to accommodate specific setups. For example, the thrust reverser ring may be interrupted to allow passage for the mounting brackets or struts used to suspend the engine.

[0051] Generally speaking, the thrust reverser ring involved in this invention does not extend along 360°, but nevertheless it still has a generally annular thrust reverser structure.

[0052] While this specification relates to specific exemplary embodiments, modifications may be made to these examples without departing from the overall scope of the invention as defined by the claims. Furthermore, individual features of the illustrated or mentioned embodiments may be combined in other embodiments. Therefore, this specification and the accompanying drawings should be considered illustrative rather than restrictive.

Claims

1. A thrust reverser ring for an aircraft nacelle thrust reverser, the thrust reverser ring extending about a longitudinal axis (XX'), characterized in that the thrust reverser ring includes a plurality of thrust reverser modules (10; 30), each of the thrust reverser modules extending along a longitudinal direction (D) parallel to the longitudinal axis (XX') of the ring and circumferentially distributed around the longitudinal axis (XX'), at least one of the plurality of thrust reverser modules being disposed between two adjacent thrust reverser modules and mechanically independent of the two adjacent thrust reverser modules, the at least one thrust reverser module comprising: A single wing sparb (12) extends along the longitudinal direction (D) and includes two opposing ends (12c, 12d) spaced apart from each other along the longitudinal direction, each of the two opposing ends (12c, 12d) being configured to secure the wing sparb (12) to the aircraft nacelle. Multiple transverse blade elements (14a, 14b) are distributed along the spar and extend from the spar.

2. The thrust reverser ring according to claim 1, characterized in that, At least one end (12c; 12c') of the two opposing ends (12c, 12d; 12c', 12d') of the at least one thrust reverser module extends integrally with the spar along the longitudinal direction (D) of the spar.

3. The thrust reverser ring according to claim 1 or 2, characterized in that, At least one end (12c') of the two opposing ends (12c', 12d') of the at least one thrust reverser module includes a plate (12c'1) extending circumferentially relative to the longitudinal axis (XX') of the ring.

4. The thrust reverser ring according to any one of claims 1 to 3, characterized in that, At least one end (12c") of the two opposite ends (12c") of the spar of the at least one thrust reverser module includes a plate (12c"1) extending laterally relative to the longitudinal direction (D) of the spar.

5. The thrust reverser ring according to any one of claims 1 to 4, characterized in that, The spar (12) includes two opposing large surfaces (12a, 12b), and the at least one thrust reverser module (30) includes at least one side sealing plate (32, 34) of the module, the side sealing plate extending parallel to the first large surface (12b) of the two opposing large surfaces (12a, 12b) of the spar (12) and located on the opposite side of the transverse blade element (14b) extending from the first large surface (12b) of the spar.

6. The thrust reverser ring according to any one of the preceding claims, characterized in that, The spar (12; 12') includes two opposing large surfaces (12a, 12b; 12a', 12b'), and the transverse blade elements (14a, 14b; 14a', 14b') each extend from the two opposing large surfaces of the spar.

7. The thrust reverser ring according to the preceding claims, characterized in that, The transverse blade elements (14a, 14b) are distributed symmetrically with respect to the spar on two opposing large surfaces (12a, 12b) of the spar (12).

8. The thrust reverser ring according to claim 6, characterized in that, The lateral blade elements (14a', 14b') extend from either side of the spar (12') and are longitudinally offset from one of the two opposing large faces (12a') of the spar to the opposing large face (12b') of the spar (12').

9. The thrust reverser ring according to any one of claims 1 to 5, characterized in that, The lateral blade element (14") extends only from one of the two opposing large surfaces of the spar (12).

10. An aircraft nacelle, characterized in that, The aircraft nacelle includes: a thrust reverser ring for a thrust reverser according to any one of claims 1 to 9.

11. A method for manufacturing a thrust reverser ring for an aircraft nacelle thrust reverser, the ring extending along a longitudinal axis (XX'), the method comprising the steps of: Provides multiple thrust reverser modules (10; 30), each of the thrust reverser modules includes: a single spar (12) extending in a longitudinal direction (D) and including two opposing ends (12c, 12d) spaced apart from each other in the longitudinal direction; and a plurality of transverse blade elements (14a, 14b) distributed along the spar (12) and extending from the spar; The thrust reverser modules (10; 30) are positioned on the jet engine nacelle of an aircraft by circumferentially distributing the thrust reverser modules (10; 30) around the longitudinal axis (XX') of the ring to form the thrust reverser ring, wherein the longitudinal direction (D) of the thrust reverser modules is parallel to the longitudinal axis of the ring. At least one of the plurality of thrust reverser modules is secured to the nacelle only by the two opposite ends (12c, 12d) of the spar (12) of at least one thrust reverser module (10; 30), such that the at least one thrust reverser module is positioned between two adjacent thrust reverser modules and is mechanically independent of the two adjacent thrust reverser modules.

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