Aircraft nacelle equipped with at least one airflow direction structure comprising transverse deflectors partially housed in longitudinal reinforcements

Abstract

Aircraft nacelle equipped with at least one airflow direction structure comprising transverse deflectors partially housed in longitudinal reinforcements. The invention relates to an aircraft nacelle equipped with a thrust reverser device comprising: at least one deflection system configured to deflect, in the activated state, a channeled airflow in the nacelle towards a lateral opening of the nacelle; at least one direction system (74), configured to direct the airflow deflected by the deflection system, comprising an airflow direction structure positioned at the lateral opening which includes at least first and second longitudinal reinforcements (80) as well as transverse deflectors (76), each longitudinal reinforcement (80) having, for each transverse deflector (76), an opening (84) to house a portion of said transverse deflector (76). Figure 9

Description

Title of the invention: Aircraft nacelle equipped with at least one airflow direction structure comprising transverse deflectors partially housed in longitudinal reinforcements

[0001] The present application relates to an aircraft nacelle equipped with at least one airflow direction structure comprising transverse deflectors partly housed in longitudinal reinforcements and to an aircraft comprising at least one such nacelle.

[0002] According to an embodiment visible in figures 1 to 3, an aircraft 10 comprises several propulsion units 12 positioned under each of the wings 14 of the aircraft 10 and connected to them by masts 16. Each propulsion unit 12 comprises a motor 18 positioned inside a nacelle 20. The motor 18 comprises a fan which has an axis of rotation A18.

[0003] For the remainder of the description, a longitudinal direction is parallel to the axis of rotation A18. A longitudinal plane is a plane containing the axis of rotation A18 and a transverse plane is a plane perpendicular to the axis of rotation A18. The notions front / upstream and rear / downstream refer to the direction of flow of an airflow in the nacelle 20, the latter flowing from the front (upstream) to the rear (downstream).

[0004] The nacelle 20 has an approximately tubular shape and, together with the motor 18, defines an annular duct 22 through which a secondary airflow passes. The nacelle 20 comprises an upstream portion 24 and a downstream portion 26 extending to a trailing edge 28.

[0005] The nacelle 20 includes a thrust reversing device 30 positioned at the downstream part 26 and configured to occupy an activated state in which it diverts at least part of the secondary airflow circulating in the annular duct 22 to the outside and upstream of the nacelle 20 and an inactivated state in which it does not divert the secondary airflow circulating in the annular duct 22.

[0006] The thrust reversing device 30 comprises at least one lateral opening 32 (visible in [Fig. 3]) passing through the nacelle 20. In one configuration, the downstream portion 26 of the nacelle 20 is movable between a first position, corresponding to the inactivated state of the thrust reversing device 30, in which the downstream portion 26 is in contact with the upstream portion 24 (as illustrated in [Fig. 2]), and a second position, corresponding to the activated state of the thrust reversing device 30, in which the downstream portion 26 is moved away from the upstream portion 24 so as to generate the lateral opening 32 (as illustrated in [Fig. 3]). In the activated state, the opening 32 extends between the first and second transverse planes.

[0007] To move the downstream part 26, the thrust reversing device 30 includes several longitudinal actuators 34 connecting the upstream and downstream parts 24, 26, distributed over the circumference of the nacelle and configured to move the downstream part 26 forward and backward or vice versa relative to the upstream part 24.

[0008] The thrust reversing device 30 includes a deflection system 36 configured to occupy a retracted position (visible in [Fig.2]), when the thrust reversing device 30 is in the inactivated state, in which the deflection system 36 does not interfere with the secondary airflow, and a deployed position (visible in [Fig.3]), when the thrust reversing device 30 is in the activated state, in which the deflection system 36 interferes with the secondary airflow and directs it towards the lateral opening 32.

[0009] The thrust reversing device 30 also includes a steering system 38 configured to direct the airflow deflected by the deflection system 36 outwards and upstream of the nacelle. In addition, the downstream part 26 includes a cavity 40, open towards the upstream part 24, configured to house the steering system 38 and the longitudinal actuators 34. This cavity 40 is delimited by inner and outer walls 26.1, 26.2 spaced towards the upstream part 24 and connected at the trailing edge 28.

[0010] According to an embodiment shown in [Fig. 4], the orientation system 38 comprises several blade arrays 42, called cascades, positioned at the lateral opening 32. Each cascade has first walls 42.1 positioned in approximately longitudinal planes and second walls 42.2 positioned in approximately transverse planes. The second walls 42.2 have a blade-like shape to deflect the airflow exiting the lateral opening 32 upstream. Each blade array 42 is made in one piece from a carbon fiber-reinforced composite material. Generally, the orientation system 38 comprises several blade arrays 42 distributed around the circumference of the nacelle 20, each blade array 42 extending along the entire length (dimension taken along the longitudinal direction) of the lateral opening 32.Thus, each blade grid 42 comprises an upstream edge positioned at the level of the first transverse plane of the lateral opening 32 and a downstream edge positioned at the level of the second transverse plane of the lateral opening 42.

[0011] According to one embodiment, each blade grid 42 is obtained by a co-firing process requiring a plurality of inserts to form the different cells delimited by the first and second walls 42.1, 42.2.

[0012] This embodiment is not satisfactory because manufacturing such a grid-shaped part, comprising more than eighty cells, in one piece of composite material, is relatively complex to implement.

[0013] The present invention aims to remedy all or part of the drawbacks of the prior art.

[0014] To this end, the invention relates to an aircraft nacelle, comprising an upstream end and a downstream end, configured to channel an airflow flowing in a longitudinal direction from the upstream end to the downstream end, the nacelle comprising at least one thrust reversal device which includes: a. at least one lateral opening, distant from the upstream and downstream ends, passing through the nacelle, b. at least one movable part configured to occupy a first position, corresponding to an inactivated state of the thrust reversing device, in which the movable part closes the lateral opening, and a second position, corresponding to an activated state of the thrust reversing device, in which the movable part at least partially clears the lateral opening, c. at least one deflection system configured to occupy a first position, when the thrust reversing device is in the inactivated state, in which the deflection system does not interfere with the airflow channeled into the nacelle, and a second position, when the thrust reversing device is in the activated state, in which the deflection system interferes with the airflow channeled into the nacelle and directs it towards the side opening, d. at least one guidance system configured to guide the airflow deflected by the deflection system.

[0015] According to the invention, the orientation system comprises an airflow orientation structure, positioned at the level of the side opening, which includes at least first and second longitudinal reinforcements as well as transverse deflectors, each longitudinal reinforcement having, for each transverse deflector, a light to house a part of said transverse deflector.

[0016] Thus, the transverse deflectors are made independently of each other and independently of the longitudinal reinforcements, which simplifies the realization of the airflow orientation structure.

[0017] According to one embodiment, each light has a contour adjusted to the cross-section of the transverse deflector that it houses.

[0018] According to another embodiment, each light has a contour greater than the cross-section of the transverse deflector, the airflow orientation structure comprising, for each light, a spacing between the transverse deflector and the longitudinal reinforcement filled by a filling material configured to ensure a resumption of forces oriented along the longitudinal direction.

[0019] According to another feature, each longitudinal reinforcement has edges inside and outside, the inside edge being closer to the deflection system than the outside edge.

[0020] According to one embodiment, each light opens at one of the inner and outer edges, the airflow orientation structure comprising at least one closure element to close at least one of the lights.

[0021] According to another embodiment, each light is distanced from the inner and outer edges of the longitudinal reinforcement.

[0022] According to another feature, at least one of the longitudinal reinforcements comprises at least first and second parts, the first part extending from a first edge among the inner and outer edges of the longitudinal reinforcement, the second part extending from a second edge, different from the first edge, among the inner and outer edges of the longitudinal reinforcement, the first and second parts being connected to each other.

[0023] According to another feature, each light is positioned straddling the first and second parts.

[0024] According to another feature, the transverse deflectors extend between the first and second ends. In addition, the first and second longitudinal reinforcements are located respectively at the first and second ends of the transverse deflectors.

[0025] The invention also relates to an aircraft comprising at least one propulsion assembly which includes a nacelle according to one of the preceding characteristics.

[0026] Other features and advantages will become apparent from the following description of the invention, given by way of example only, with reference to the accompanying drawings, among which:

[0027] [Fig. 1] is a perspective view of an aircraft and a propulsion assembly,

[0028] [Fig.2] is a schematic cross-section of a propulsion assembly equipped with a thrust reversing device in the inactivated state illustrating a prior art embodiment,

[0029] [Fig.3] is a schematic cross-section of the propulsion assembly visible in [Fig.2], with the thrust reversing device in the activated state,

[0030] [Fig.4] is a perspective view of a blade grid illustrating a method of lization of prior art,

[0031] [Fig.5] is a schematic cross-section of a propulsion assembly equipped with a thrust reversing device in the inactivated state illustrating one embodiment of the invention,

[0032] [Fig.6] is a schematic cross-section of the propulsion assembly visible in [Fig.5], the with the thrust reversing device in the activated state,

[0033] [Fig.7] is a side view of part of a propulsion assembly comprising a thrust reversing device in the activated state illustrating one embodiment of the invention,

[0034] [Fig.8] is a perspective view of an airflow guidance structure illustrating one embodiment of the invention,

[0035] [Fig.9] is a side view of an airflow direction structure illustrating a first embodiment of the invention,

[0036] [Fig. 10] is a side view of an airflow direction structure illustrating a second embodiment of the invention,

[0037] [Fig. 11] is a cross-section of an airflow guidance structure illustrating a first variant of the second embodiment of the invention,

[0038] [Fig. 12] is a cross-section of an airflow guidance structure illustrating a second variant of the second embodiment of the invention,

[0039] [Fig. 13] is a side view of an airflow guidance structure illustrating a third embodiment of the invention,

[0040] [Fig. 14] is a section along line XIV-XIV of [Fig.9],

[0041] [Fig. 15] is a section along line XV-XV of [Fig. 10].

[0042] According to an embodiment shown in Figures 5, 6, and 7, a propulsion assembly 50 comprises a motor 52 positioned inside a nacelle 54. The nacelle 54 has an approximately tubular shape and, together with the motor 52, defines an annular duct 56 through which a secondary airflow passes. The nacelle 54 comprises an upstream portion 54.1 and a downstream portion 54.2, which has a trailing edge 58.

[0043] According to one application, an aircraft comprises at least one such propulsion assembly. Regardless of the embodiment, the nacelle 54 is tubular and extends between upstream and downstream ends. The nacelle 54 is configured to channel an airflow 60 in a longitudinal direction, from the upstream end to the downstream end.

[0044] The nacelle 54 includes at least one thrust reversing device 62 positioned at the downstream part 54.2 and configured to occupy an activated state (visible in Figures 6 and 7) in which it diverts at least part of the airflow 60 circulating in the annular duct 56 to the outside and the upstream end of the nacelle 54 and an inactivated state (visible in [Fig.5]) in which it does not divert the airflow 60 circulating in the annular duct 56.

[0045] The thrust reversing device 62 comprises at least one lateral opening 64, passing through the nacelle 54 and located away from the upstream and downstream ends of the nacelle 54, configured to connect the annular conduit 56 with the exterior of the nacelle 54, in particular its outer surface F54, and at least one movable part 66 configured to occupy a first position, corresponding to the inactivated state of the thrust reversing device 62 (visible in [Fig. 4]) in which the part mobile 66 closes the lateral opening 64 as well as a second position, corresponding to the activated state of the thrust reversal device 62 (visible on the [Fig.5]) in which the mobile part 66 at least partially clears the lateral opening 64.

[0046] According to one embodiment, the nacelle 54 comprises two lateral openings 64 substantially symmetrical with respect to a vertical longitudinal plane passing through the axis of the motorization.

[0047] According to one configuration, the downstream part 54.2 is a movable tubular O-shaped hood, forming the movable part 66, which translates along the longitudinal direction between a closed position (visible on [Fig.5]) in which the downstream part 54.2 is in contact with the upstream part 54.1, when the thrust reversing device 62 is in the inactivated state, and an open position (visible on Figures 6 and 7) in which the downstream part 54.2 is moved away from the upstream part 54.1 so as to generate the lateral opening(s) 64 between the upstream and downstream parts 54.1, 54.2 when the thrust reversing device 62 is in the activated state.

[0048] The downstream part 54.2 comprises an inner wall 68.1 and an outer wall 68.2 connected at the trailing edge 58, the inner and outer walls 68.1, 68.2 delimiting between them a cavity 70 open towards the upstream part 54.1.

[0049] Of course, the invention is not limited to this configuration for the moving part 66.

[0050] The thrust reversing device 62 includes at least one deflection system 72 configured to occupy a retracted position (visible in [Fig.5]), when the thrust reversing device 62 is in the inactivated state, in which the deflection system 72 does not interfere with the airflow 60 channeled by the nacelle 54 and a deployed position (visible in [Fig.6]), when the thrust reversing device 62 is in the activated state, in which the deflection system 72 is deployed in the annular duct 56, interferes with the airflow 60 and directs it in radial directions (perpendicular to the longitudinal direction) towards the lateral opening 64.

[0051] According to one embodiment, for each lateral opening 64, the deflection system 72 comprises at least one panel 72.1 and, for each panel 72.1, at least one hinge 72.2 connecting the panel 72.1 to the nacelle 54 and at least one connecting rod 72.3 connecting the panel 72.1 to the drive unit 52. Of course, the invention is not limited to this embodiment for the deflection system 72. Thus, each panel could be connected to the drive unit 52 by a hinge.

[0052] The thrust reversing device 62 also includes at least one guidance system 74 configured to guide at least a portion of the airflow 60 deflected by the deflection system 72 and exiting through the lateral opening 64. According to one arrangement, the guidance system 74 is positioned at the level of the lateral opening 64.

[0053] According to one arrangement, the orientation system 74 and the cavity 70 are configured to so that in the inactivated state, the orientation system 74 is positioned in the cavity 70.

[0054] According to an embodiment visible in particular in Figures 5 to 13, the orientation system 74 comprises at least one transverse deflector 76, positioned approximately in a transverse plane, which extends between first and second ends 76.1, 76.2. Each transverse deflector 76 has curved inner and outer edges 76.3, 76.4, substantially in the form of an arc of a circle, connecting the first and second ends 76.1, 76.2, the inner edge 76.3 being closer to the deflection system 72 than the outer edge 76.4. According to one configuration, the inner and outer edges 76.3, 76.4 have curvatures adapted to those of the inner and outer walls 68.1, 68.2 of the downstream part 54.2 of the nacelle 54 so that the orientation system 74 can fit into the cavity 70 when the thrust reversing device 62 is in the inactivated state.

[0055] Each transverse deflector 76 is configured to direct, in radial directions and towards the upstream end, the airflow deflected by the deflection system 72 and exiting the lateral opening 64.

[0056] According to one embodiment, each transverse deflector 76 comprises a blade, in the form of a portion of a crown, which has a concave curvature in longitudinal planes (the center of the radius of curvature being offset upstream with respect to the transverse deflector 76).

[0057] According to one configuration, each transverse deflector 76 has a constant width (distance separating the inner and outer edges 76.3, 76.4) and curvature between its first and second ends 76.1, 76.2. Thus, the airflow exiting the nacelle 54 is substantially constant around the perimeter of the nacelle 54. According to another arrangement, the transverse deflectors 76 have different widths which decrease from upstream to downstream.

[0058] The number of transverse deflectors 76 and their shape are determined so as to obtain the same aerodynamic function as the cascades of the prior art, namely a sufficient flow rate to avoid problems of operation of the blower of the motorization 52 and an efficiency in terms of back pressure.

[0059] The orientation system 74 includes at least one support 78, integral with the nacelle 54, to which each transverse deflector 76 is connected. The support 78 and the various transverse deflectors 76 form an airflow orientation structure.

[0060] According to an embodiment shown in Figures 7 and 8, the support 78 comprises at least first and second longitudinal reinforcements 80, 80', parallel to each other and to the longitudinal direction, which cooperate with the various transverse deflectors 76 so as to form an airflow guidance structure. In one arrangement, the first and second longitudinal reinforcements 80, 80' are positioned, for example, above and below the lateral opening 64, the first end 76.1 of each transverse deflector 76 cooperating with the first longitudinal reinforcement 80, the second end 76.2 of each transverse deflector 76 cooperating with the second longitudinal reinforcement 80'. According to another arrangement, the support 78 comprises, in addition to the first and second longitudinal reinforcements 80, 80' located at the ends of the transverse deflectors 76, intermediate longitudinal reinforcements through which the transverse deflectors 76 pass.

[0061] Each longitudinal reinforcement 80, 80' extends between first and second ends 80.1, 80.2 and has inner and outer edges 80.3, 80.4 connecting the first and second ends 80.1, 76.2, the inner edge 80.3 being closer to the deflection system 72 than the outer edge 80.4.

[0062] According to one configuration, the support 78 comprises an upstream cross member 82.1, oriented in a direction parallel to a transverse plane and positioned upstream of the lateral opening 64, to which are connected the first ends 80.1 of the longitudinal reinforcements 80, 80'. The upstream cross member 82.1 has a curvature substantially identical to that of the nacelle 54. The upstream cross member 82.1 is integral with the upstream part 54.1 of the nacelle 54 or integrated into it.

[0063] The support 78 includes a downstream cross member 82.2, oriented in a direction parallel to a transverse plane and positioned downstream of the lateral opening 64, to which are connected the first ends 80.1 of the longitudinal reinforcements 80, 80'. The downstream cross member 82.2 has a curvature substantially identical to that of the nacelle 54.

[0064] According to one configuration, the upstream and downstream cross members 82.1, 82.2 are parallel to each other and connected by the longitudinal reinforcements 80, 80'. Thus the upstream and downstream cross members 82.1, 82.2 as well as the longitudinal reinforcements 80, 80' form a frame delimiting the lateral opening 64.

[0065] Each transverse deflector 76 has a C-shaped cross-section. Each longitudinal reinforcement 80 may comprise only a web or have an I-shaped, C-shaped or other cross-section and comprise a web and two wings at each end of the web, for example.

[0066] According to one embodiment, each transverse deflector 76 is made of carbon fiber reinforced composite material. The support 78 is also made of carbon fiber reinforced composite material. Of course, the invention is not limited to this type of fiber.

[0067] According to one embodiment, the transverse deflectors 76 are made independently of each other and independently of the support 78. Making the transverse deflectors 76 independently of the support 78 simplifies the construction of the airflow orientation structure.

[0068] Each longitudinal reinforcement 80, 80' comprises, for each transverse deflector 76, a slot 84 configured to allow the transverse deflector 76 to pass through the longitudinal reinforcement 80, 80'.

[0069] According to a configuration visible in figures 9 and 14, the light 84 has a contour fitted to the cross section of the transverse deflector 76 so that a small gap, at most equal to about 1mm and substantially constant, remains around the transverse deflector 76 between the longitudinal reinforcement 80, 80' and the transverse deflector 76.

[0070] According to other configurations visible in Figures 10, 13 and 15, the light 84 has a contour independent of the cross-section of the transverse deflector 76. According to these configurations, the light 84 has a contour greater than the cross-section of the transverse deflector 76. According to one arrangement, the contour is a quadrilateral, such as a rectangle for example, in which the contour of the transverse deflector 76 is inscribed.

[0071] According to this configuration, the airflow guidance structure comprises, for each opening 84, a gap between the transverse deflector 76 and the longitudinal reinforcement 80, 80', this gap being filled by a filling material 86 configured to ensure the absorption of compressive forces oriented along the longitudinal direction. By way of example, the filling material 86 is an elastomer having a hardness between 40 and 90 Shore A.

[0072] According to a configuration visible on [Fig. 10], each light 84 is distant from the inner and outer edges 80.3, 80.4 of the longitudinal reinforcement 80, 80'.

[0073] According to another configuration shown in [Fig. 13], each opening 84 is located at one of the inner and outer edges 80.3, 80.4, in particular at the lower edge 80.3. In this configuration, the airflow direction structure includes at least one closing element 88 to close at least one of the openings 84. In one arrangement, the same closing element 88 is configured to close several openings 84. Alternatively, as illustrated in [Fig. 13], the airflow direction structure includes one closing element 88 for each opening 84. In one embodiment, each closing element 88 is in the form of a plate connected to the edge of the longitudinal reinforcement 80, 80' on either side of the opening 84.

[0074] According to one embodiment, each transverse deflector 76 is immobilized in a transverse plane due to friction between the transverse deflector 76 and the longitudinal reinforcements 80, 80' or due to adhesion between the optional filler material 86 and the longitudinal reinforcement 80, 80' or the transverse deflector 76. Alternatively, each transverse deflector 76 is bonded to at least one of the longitudinal reinforcements 80, 80' through which it passes. Other solutions could be considered for immobilizing the transverse deflectors 76 relative to the longitudinal reinforcements 80, 80'.

[0075] When the thrust reversal device is activated, each transverse deflector 76 is essentially subjected to forces oriented along the longitudinal direction. The fact that the transverse deflectors 76 pass through the longitudinal reinforcements 80, 80' ensures better absorption of these longitudinal forces. Given these constraints, since each transverse deflector 76 is virtually unstressed in a transverse plane, it can be connected to the longitudinal reinforcements 80, 80' by a suitable mechanical linkage.

[0076] According to embodiments visible in figures 10 to 12, at least one of the longitudinal reinforcements 80, 80' is made in at least two parts 90, 92 which each extend between the first and second ends 80.1, 80.2 of the longitudinal reinforcement 80, 80'.

[0077] According to an embodiment shown in Figures 10 and 11, each longitudinal reinforcement 80, 80' comprises a first portion 90 extending between first and second edges 90.1, 90.2, the first edge 90.1 corresponding to the inner edge 80.3 of the longitudinal reinforcement 80, 80', and a second portion 92 extending between first and second edges 92.1, 92.2, the first edge 92.1 corresponding to the outer edge 80.4 of the longitudinal reinforcement 80, 80', the second edges 90.2, 92.2 of the first and second portions 90, 92 overlapping and being connected by connecting elements 94. According to this embodiment, shown in particular in [Fig. 11], each of the first and second portions 90, 92 has a T-shaped cross-section, the head of the T being located at the inner edge or external 80.3, 80.4 of the longitudinal reinforcement 80, 80'.

[0078] According to another embodiment visible in [Fig. 12], at least one of the longitudinal reinforcements 80, 80' is made in three parts 90, 92, 96 and has an I-shaped cross-section which includes a web and two wings at each end of the web. This longitudinal reinforcement 80, 80' comprises a first part 90 in T which includes a head located at the inner edge 80.3 of the longitudinal reinforcement 80, 80' and a leg forming part of the web of the longitudinal reinforcement 80, 80' as well as second and third parts 92, 96 in L which each comprise a first wing located at the outer edge 80.4 of the longitudinal reinforcement 80, 80 and a second wing forming part of the web of the longitudinal reinforcement 80, 80', the leg of the first part 90 being positioned between the second wings of the second and third parts 92 and 96 and connected to the latter by connecting elements 94.Of course, the invention is not limited to these embodiments for the longitudinal reinforcements 80, 80'.

[0079] According to the embodiments shown in Figures 10 to 12, at least one of the longitudinal reinforcements 80 comprises at least first and second parts 90, 92, the first part 90 extending from a first edge among the inner edges and outer 80.3, 80.4 of the longitudinal reinforcement 80, 80', the second part 92 extending from a second edge, different from the first edge, between the inner and outer edges 80.3, 80.4 of the longitudinal reinforcement 80, 80', the first and second parts being connected to each other by connecting elements 94.

[0080] When at least one of the longitudinal reinforcements 80, 80' comprises at least first and second parts 90, 92, each slot 84 provided to allow a transverse deflector 76 to pass through the longitudinal reinforcement 80, 80' is positioned straddling the first and second parts 90, 92. This configuration simplifies the placement of the transverse deflectors 76 in the slots 84, the first and second parts 90, 92 being separated during the placement of the transverse deflectors 76.

[0081] Of course, the invention is not limited to these embodiments for the orientation system 74.

[0082] Thus, regardless of the embodiment, the airflow guidance structure is positioned at the lateral opening 64 and traversed by the airflow 60 deflected by the deflection system 72 when the thrust reversing device is in the activated state. This airflow guidance structure comprises at least first and second longitudinal reinforcements 80, 80' and transverse deflectors 76 partially housed in slots 84 provided in the longitudinal reinforcements 80, 80'. According to one arrangement, the transverse deflectors 76 each have first and second ends housed in slots 84 provided in first and second longitudinal reinforcements 80, 80' positioned respectively at the first and second ends of the transverse deflectors 76.According to this configuration, the transverse deflectors 76 do not necessarily pass completely through the longitudinal reinforcements 80, 80' positioned at their ends. The airflow guidance structure may include at least one intermediate longitudinal reinforcement having an opening 84 for each transverse deflector 76 that passes through it.

Claims

Claims

1. Aircraft nacelle (54), comprising an upstream end and a downstream end, configured to channel an air flow (60) flowing in a longitudinal direction from the upstream end to the downstream end, the nacelle comprising at least one thrust reverser device (62) which comprises: a. at least one lateral opening (64), distant from the upstream and downstream ends, passing through the nacelle, b. at least one movable part (66) configured to occupy a first position, corresponding to an inactivated state of the thrust reverser device, in which the movable part (66) closes the lateral opening (64) as well as a second position, corresponding to an activated state of the thrust reverser device (62), in which the movable part (66) at least partially clears the lateral opening (64), c. at least one deflection system (72) configured to occupy a first position, when the thrust reverser device (62) is in the inactivated state, in which the deflection system (72) does not interfere with the airflow (60) channeled into the nacelle (54) as well as a second position, when the thrust reverser device (62) is in the activated state, in which the deflection system (72) interferes with the airflow (60) channeled into the nacelle (54) and directs it toward the lateral opening (64), d. at least one orientation system (74) configured to orient the air flow (60) deflected by the deflection system (72), e. characterized in that the orientation system (74) comprises an air flow orientation structure, positioned at the lateral opening (64), which comprises at least first and second longitudinal reinforcements (80, 80') as well as transverse deflectors (76), each longitudinal reinforcement (80, 80') having, for each transverse deflector (76), a slot (84) for housing a part of said transverse deflector (76).

2. Nacelle according to the preceding claim, characterized in that each transverse deflector (76) has a cross-section and in that each light (84) has a contour adjusted to the cross-section of the transverse deflector (76) which it houses.

3. Nacelle according to claim 1, characterized in that each transverse deflector (76) has a cross section and in that each light (84) has a contour greater than the cross section of the transverse deflector (76), the air flow orientation structure comprising, for each light (84), a spacing between the transverse deflector (76) and the longitudinal reinforcement (80, 80') filled by a filling material (86) configured to ensure a take-up of the forces oriented in the longitudinal direction.

4. Nacelle according to one of the preceding claims, characterized in that each longitudinal reinforcement (80, 80') has inner and outer edges (80.3, 80.4), the inner edge (80.3) being closer to the deflection system (72) than the outer edge (80.4), and in that each light (84) opens at one of the inner and outer edges (80.3, 80.4), the air flow orientation structure comprising at least one closing element (88) for closing at least one of the lights (84).

5. Nacelle according to one of claims 1 to 3, characterized in that each longitudinal reinforcement (80, 80') has inner and outer edges (80.3, 80.4), the inner edge (80.3) being closer to the deflection system (72) than the outer edge (80.4), and in that each light (84) is distant from the inner and outer edges (80.3, 80.4) of the longitudinal reinforcement (80, 80').

6. Nacelle according to the preceding claim, characterized in that at least one of the longitudinal reinforcements (80, 80') comprises at least first and second parts (90, 92), the first part (90) extending from a first edge among the inner and outer edges (80.3, 80.4) of the longitudinal reinforcement (80, 80'), the second part (92) extending from a second edge, different from the first edge, among the inner and outer edges (80.3, 80.4) of the longitudinal reinforcement (80, 80'), the first and second parts being connected to each other.

7. Aircraft nacelle according to the preceding claim, characterized in that each light (84) is positioned astride the first and second parts (90, 92).

8. Aircraft nacelle according to one of the preceding claims, characterized in that the transverse deflectors (76) extend between

9. of the first and second ends and in that the first and second longitudinal reinforcements (80, 80') are located respectively at the first and second ends of the transverse deflectors (76). Aircraft comprising at least one propulsion assembly which comprises a nacelle according to one of the preceding claims.

Images