AIRCRAFT PROPULSION SYSTEM, INCLUDING AN IMPROVED INTEGRATION THRUSTER REVERSER

Abstract

The invention relates to an aircraft propulsion system (1), comprising a turbomachine (2) and a thrust reverser (30), the reverser comprising a fixed structure (31) equipped with a boundary wall (18) for a secondary flow (21B), belonging to an openable cowling having one end mounted on one end of a structural part (17) of the turbomachine. The reverser includes a device (70) for actuating a deployment member (62) of a flow closure member (58), the actuating device connecting the boundary wall (18) to the deployment member by means of a first articulated linkage (74a). According to the invention, the device (70) comprises a support member (64) fixed to the wall (18), and an upstream offset member (72) arranged in the secondary vein and carried by the support member, the offset member (72) placing the first linkage (74a) upstream of the upstream end of the opening cover. Figure for the abbreviation: Fig. 2

Description

Title of the invention: PROPULSION ASSEMBLY FOR AIRCRAFT, INCLUDING AN IMPROVED INTEGRATION THRUSTER REVERSER technical field

[0001] The invention relates to the field of nacelles and thrust reversers for aircraft propulsion systems, and, more particularly, to systems enabling the deployment of the secondary flow sealing membranes of a propulsion system. Prior art

[0002] Thrust reversers are devices that allow the airflow through the propulsion assembly to be diverted forward, in order to shorten landing distances and limit the stress on the brakes on the landers.

[0003] The grid-type reversers currently used in the aeronautical sector generally include deflector grids integrated into a fixed reverser structure, intended to be connected to a turbomachine casing. A movable reverser structure comprises one or more movable reverser hoods, and it is mounted to be movable in translation relative to the fixed structure between a forward direct thrust position and a rearward thrust reverser position. In the forward direct thrust position, the deflector grids are arranged in a cavity within the movable reverser hoods, and they are isolated from the secondary flow of the propulsion system by a radially internal wall of the reverser hoods. Conversely, in the rearward thrust reverser position, the radially internal rearward wall of the reverser hoods defines an opening through which the secondary flow passes to the deflector grids.

[0004] To divert at least part of the secondary flow towards this passage opening in the direction of the grilles, the inverter is generally equipped with shutters, which, when deployed, at least partially block the secondary flow. In a known manner, this forces the air from the secondary flow through the passage opening and into the grilles, which then generate the forward counter-thrust airflow.

[0005] Although satisfactory, the shutter flap solution is also known to be relatively heavy and bulky. Climate change is a major concern for many legislative and regulatory bodies worldwide. Indeed, various restrictions on carbon emissions have been, are being, or will be adopted by various states. In particular, an ambitious standard applies to both new types of aircraft and those already in service requiring Civil aviation must implement technological solutions to comply with current regulations. For several years now, civil aviation has been actively contributing to the fight against climate change.

[0006] Consequently, the Applicant is constantly working to reduce its negative climate impact by using methods and operating virtuous development and manufacturing processes that minimize greenhouse gas emissions to the minimum possible, in order to reduce the environmental footprint of its activity.

[0007] With this in mind, solutions for obturating the secondary vein have been developed using one or more deployable membranes. Such a membrane design is, for example, known from document FR 3 076 864 A1.

[0008] The deployment of a sealing membrane can be more easily achieved using one or more deployment rods, or cables, one radially external end of which is connected to one end of the membrane, and one radially internal end of which is articulated on a radially internal boundary wall of the secondary vein, this wall belonging to an openable cover of the fixed structure of the inverter.

[0009] When the mobile structure moves towards its rearward thrust reversal position, the membrane gradually unfolds into the secondary vein by plunging radially into the inside of it, driven by the connecting rod(s) which also tilt into the vein.

[0010] In the direct jet position, the end of the membrane connected to the connecting rods is generally clamped between a deflection edge of the fixed structure, and an upstream end of the radially internal wall of the movable hood.

[0011] The hinged cowling of the reverser's fixed structure has an upstream end mounted on a downstream end of a structural part of the turbomachine, generally a casing. Depending on the propulsion system design, the boundary between the hinged cowling and the structural part of the turbomachine may vary in the axial direction. If this boundary is located downstream, the radially inner end of the connecting rod must be mounted not on the hinged cowling, which does not extend sufficiently upstream, but on the structural part of the turbomachine. This is because, to ensure the desired kinematics of the deployment rod when the reverser is opened, this rod may require a specific orientation in the direct thrust configuration.It is this desired orientation that therefore determines the implantation point of the radially internal end of the deployment rod, or any similar deployment element. This constraint is observed both for a vein closure element of the deployable membrane type and of the flap type.

[0012] However, during the assembly of the propulsion unit, the need to connect the reversing gear's deployment link to a structural part of the turbomachine complicates the integration of the reversing gear, which already has other attachment points on the turbomachine. This drawback also arises during maintenance operations of the propulsion unit, when these operations require the complete removal and reassembly of the reversing gear. Description of the invention

[0013] To address at least partially the drawback presented above, the invention relates to a propulsion system for an aircraft, comprising a turbomachine and a thrust reverser, the reverser comprising a fixed structure equipped with a boundary wall for a secondary flow of the propulsion system intended to be traversed by a secondary flow, the boundary wall belonging to an openable hood having an upstream end of the hood mounted on a downstream end of a structural part of the turbomachine,

[0014] the reverser also comprising a movable structure including at least one movable reverser cover equipped with a radially internal wall participating in the radially external delimitation of the secondary flow, the movable structure being movable relative to the fixed structure between an advanced direct thrust position, and a recoiled thrust reversal position in which the fixed structure and an upstream end of the recoiled radially internal wall of the movable reverser cover leave between them an opening for the passage of air through the secondary flow, the thrust reverser also comprising at least one secondary flow closure member, designed to divert at least a part of the secondary flow towards the passage opening, as well as at least one deployment member for the closure member, arranged in the secondary flow and having a first end connected to the closure member.

[0015] The inverter also includes an actuation device for the deployment member, the actuation device connecting the boundary wall to a second end of the deployment member, via a first articulated link.

[0016] According to the invention, the actuation device comprises a support member fixed to the boundary wall, and an upstream offset member arranged in the secondary vein and carried by the support member, the offset member integrating at its upstream end the first articulated link, so as to place the latter upstream of the upstream end of the opening hood, when the mobile structure occupies its advanced direct thrust position.

[0017] The invention thus facilitates the integration of the reversing gear when the boundary between the hinged cowling and the structural part of the turbomachine is in a downstream position, that is, when the structural part of the turbomachine extends relatively far axially downstream. Indeed, in this context, the invention advantageously provides for the implementation of the upstream displacement element within the secondary flow. This makes it possible to retain the mounting of the deployment element on the wall of the hinged cowling, via the actuation device, while placing the first articulated link of the deployment element upstream of the upstream end of the hinged cowling.In other words, when the moving structure occupies its forward direct thrust position, the pivot point of the radially internal end of the deployment member is located axially at the level of the turbomachine structural part, without requiring the deployment member to be mounted on this same turbomachine structural part. This advantageously simplifies the assembly operations of the reversing unit within the propulsion assembly, while allowing the deployment member to adopt the orientation required to ensure the correct deployment of the secondary flow shut-off device.

[0018] The invention preferably provides for at least one of the following optional technical features, implemented individually or in combination.

[0019] Preferably, the upstream displacement member has an aerodynamic profile whose chord line forms with the secondary flow, when the mobile structure occupies its forward direct thrust position, an angle of incidence (Ai) of less than or equal to 10°, and preferably less than or equal to 8°. This makes it possible to strongly limit the aerodynamic disturbances in the secondary flow, by limiting the drag produced in this flow.

[0020] Preferably, the upstream offset member has a leading edge convex upstream, and a trailing edge pointed downstream.

[0021] Preferably, the inverter is configured so that during an initial phase of movement of the moving structure from its forward direct thrust position to its rearward thrust reversal position, the actuation device causes a movement of said first articulated link radially inwards and / or axially upstream.

[0022] Thanks to this particular displacement of the deployment member at the beginning of the inverter's opening phase, the membrane-shaped sealing member is pulled upstream and / or inward, resulting in its detachment. The risks of unwanted contact of this membrane with the inverter's moving cover are advantageously reduced, or even eliminated. The same applies to the risks of mechanical interference between the deployment member and the upstream end. of the radially internal wall of the movable hood, both during the initial phase of moving the movable structure towards its rearward thrust reversal position, and during the final phase of moving the movable structure towards its forward direct thrust position.

[0023] Preferably, the upstream offset member is articulated on the support member by means of a second articulated joint arranged downstream of the first articulated joint when the moving structure is in its forward direct thrust position. This joint provides a degree of freedom preferably used to apply the aforementioned displacement of the deployment member, radially inwards and / or axially upstream, during the initial phase of movement of the moving structure.

[0024] Alternatively, the support member could include a leaf spring to provide a similar function, provided that this leaf spring produces a restoring force on the offset member, aimed at forcing the latter radially inwards and / or axially upstream, during the initial phase of movement of the moving structure.

[0025] According to one possibility, the second articulated joint is arranged in the secondary vein. Alternatively, this second articulated joint could be arranged in a so-called "buried" manner, by being located outside the vein.

[0026] Preferably, in the advanced position of direct push of the mobile structure, the deployment member and the upstream offset member together form a salient angle, the actuation device being designed, during said initial phase of movement of the mobile structure, to force the offset member to tilt around the second articulated link, in a first direction of rotation leading to a reduction of the salient angle.

[0027] Preferably, the actuation device comprises first means for activating the offset member, the first means of activating comprising first elastic return means forcing, during said initial phase of movement of the mobile structure, the offset member to tilt around the second articulated joint, in the first direction of rotation, said first elastic return means being arranged:

[0028] - in the support organ, being preferably arranged so as to generate on the offset member a restoring force orthogonal or substantially orthogonal to a longitudinal direction of this offset member when the moving structure occupies its forward position of direct thrust; and / or

[0029] - in the relocation device; and / or

[0030] - within the second articulated link.

[0031] This design also advantageously allows for the tolerance of radial relative displacements between the boundary walls of the flow. These radial displacements can occur depending on the different loading conditions of the inverter components, but also due to the development of play in the inverter resulting from wear of the components over time.

[0032] Furthermore, the forces exerted by the actuation means cause the sealing membrane to be under tension, whether in the direct jet position and / or during the opening / closing of the diverter. This provides greater stability for this membrane when the sealing element is made with such a deployable membrane.

[0033] Preferably, these initial actuation means are therefore of passive design. Alternatively, they could be controlled means, activated only when actuation is desired, for example, during the opening and / or closing of the inverter, or only during certain phases of these inverter operations. As indicated above, however, a passive design is preferred that also allows the desired forces to be generated by direct jet, in order to tension the diaphragm and enhance its stability within the cavity in which it is stored.

[0034] A hybrid design is also conceivable, in which elastic means would generate the desired forces, but in combination with control means to adjust the stiffness of these elastic means as needed. For example, the stiffness could be adjusted during the opening of the inverter, so that the intensity of the generated forces remains sufficiently high to maintain the desired effect. These alternatives are also applicable to the second set of stresses, presented below.

[0035] Indeed, the actuation device also includes second means for activating the deployment member, the second means of activating comprising second elastic return means forcing, during said initial phase of movement of the mobile structure, the deployment member to tilt around the first articulated link, in a second direction of rotation opposite to the first direction, said second elastic return means being preferably arranged within the first articulated link.

[0036] These second elastic means also serve to reduce the aforementioned salient angle, thereby causing the radially external end of the deployment member to plunge downstream and radially inward. Another advantage of these second elastic means is that they allow the membrane to be deployed during maintenance operations, enabling visual inspection of the membrane from the rear of the inverter, by bringing it into the secondary channel despite the absence of an airflow capable of causing its deployment.

[0037] According to one possibility, the first and second elastic return means are identical, arranged in the downstream displacement member. These elastic return means comprise a first end exerting a first force on a first head of a first piston, the first piston rod of which cooperates with the support member, and a second end opposite the first, exerting a second force on a second head of a second piston, the second piston rod of which cooperates with the second end of the deployment member. This solution proves to be particularly compact and therefore reduces aerodynamic disturbances on the secondary flow.

[0038] Preferably, the reverser is configured so that after the initial phase of movement of the mobile structure, the closing member exerts on the offset member, via the deployment member, a force forcing this offset member to tilt around the second articulated link in a second direction of rotation opposite to the first direction, the actuation device including stop means allowing the rotation of the offset member in the second direction to be stopped during the movement of the mobile structure towards the rearward thrust reversal position.

[0039] Preferably, the boundary wall belonging to the openable cover is a radially internal boundary wall of the secondary vein, or a wall of a bifurcation circumferentially delimiting the secondary vein.

[0040] Preferably, the deployment element is a connecting rod. Alternatively, it could, for example, be a cable, or even an association between a cable and a connecting rod.

[0041] As mentioned previously, the sealing element is preferably a deployable sealing membrane. In this case, the invention therefore implements one or more sealing membranes for the secondary flow, resulting in a significant reduction in the overall mass of the reversing unit. The invention is thus the result of technological research aimed at significantly improving aircraft performance and, in this respect, contributes to reducing the environmental impact of these aircraft (decarbonization). However, alternatively, the sealing element could be a shutter. In this case, the reversing unit then preferably incorporates several shutters of conventional design, distributed circumferentially around the longitudinal central axis of the propulsion assembly.

[0042] Finally, it is indicated that a mixed solution is also conceivable, in which the inverter comprises both sealing membranes and sealing flaps, for example arranged alternately in the circumferential direction.

[0043] Preferably, the fixed structure of the inverter comprises at least one deflection grid arranged, in the forward position of the direct thrust of the moving structure, in a cavity of the moving cover, being isolated from the secondary flow by the wall radially internal to the inverter cover. Alternatively, the deflection grille(s) could be integrated into the inverter's moving structure, without departing from the scope of the invention. Similarly, it is noted that the grilles could be replaced, or used in combination, with one or more flexible structures such as deflection membranes, to redirect the airflow upstream.

[0044] Other advantages and features of the invention will become apparent in the detailed, non-limiting description below. Brief description of the drawings

[0045] The detailed description that follows refers to the accompanying drawings in which:

[0046] [Fig-1] is a schematic half-view in longitudinal section of an assembly propulsive, including a thrust reverser, shown in direct thrust configuration;

[0047] [Fig.2] is a schematic half-view in longitudinal section of the inverter equipping the propulsion assembly shown in [Fig.1], in more detail and presented in the form of a preferred embodiment of the invention, with the reverser shown in direct thrust configuration;

[0048] [Fig.2A] is a schematic half-view of the inverter shown in [Fig.2], represented in the configuration adopted during an initial phase of movement of the moving structure towards its rearward thrust reversal position;

[0049] [Fig.2B] is a schematic half-view of the reverser shown in [Fig.2], represented in an intermediate configuration between the direct thrust configuration and the thrust reversal configuration;

[0050] [Fig.3] is a schematic half-view of the inverter shown in [Fig.2], represented in thrust reversal configuration;

[0051] [Fig.4] is a perspective view of the inverter shown in Figures 2 to 3, represented in direct thrust configuration;

[0052] [Fig.5] is a perspective view of the inverter shown in [Fig.4], represented in thrust reversal configuration;

[0053] [Fig.6] is a perspective view of a connecting rod actuation device deployment of sealing membrane, according to another preferred embodiment of the invention;

[0054] [Fig.7] is an exploded perspective view of the connecting rod actuation device shown in the previous figure;

[0055] [Fig.8] is a schematic half-view in longitudinal section similar to that of the [Fig.2], with the reverser including the connecting rod actuation device shown in figures 6 and 7, the reverser being shown in direct thrust configuration;

[0056] [Fig.9] is a partial and schematic half-view of the inverter shown in [Fig.8], represented in the configuration adopted during an initial phase of movement of the mobile structure towards its rearward thrust reversal position;

[0057] [Fig. 10] is a partial and schematic half-view of the reverser shown in [Fig.8], represented in thrust reversing configuration;

[0058] [Fig. 11] is a schematic half-view in longitudinal section similar to that of [Fig.2], with the reverser comprising the connecting rod actuation device being in the form of another preferred embodiment of the invention, the reverser being shown partially, in direct thrust configuration;

[0059] [Fig. 12] is a partial and schematic half-view of the inverter shown in [Fig. 11], represented in the configuration adopted during an initial phase of movement of the moving structure towards its rearward thrust reversal position;

[0060] [Fig. 13] is a partial and schematic half-view of the reverser shown in [Fig.1 1], represented in thrust reversing configuration;

[0061] [Fig. 14] is a schematic half-view in longitudinal section similar to that of [Fig.2], with the reverser comprising the connecting rod actuation device being in the form of another preferred embodiment of the invention, the reverser being shown partially, in direct thrust configuration;

[0062] [Fig. 15] is a partial and schematic half-view of the inverter shown in [Fig.14], represented in the configuration adopted during an initial phase of movement of the moving structure towards its rearward thrust reversal position;

[0063] [Fig. 16] is a partial and schematic half-view of the reverser shown in [Fig.14], in thrust reversing configuration;

[0064] [Fig. 17] is a schematic half-view in longitudinal section similar to that of [Fig.2], with the reverser comprising the connecting rod actuation device being in the form of another preferred embodiment of the invention, the reverser being shown partially, in direct thrust configuration;

[0065] [Fig. 18] is a partial and schematic half-view of the inverter shown in [Fig.17], represented in the configuration adopted during an initial phase of movement of the moving structure towards its rearward thrust reversal position;

[0066] [Fig. 19] is a partial and schematic half-view of the reverser shown in [Fig.17], in thrust reversing configuration;

[0067] [Fig.20] is a front view of a part of the inverter, showing in a schematically the implantation of the connecting rod actuation device in a different position than that of the previous figures, on a bifurcation wall;

[0068] [Fig.21] is a more detailed perspective view of a connecting rod actuation device of the type of those located in the previous figure;

[0069] [Fig.22] is an exploded perspective view of the actuation device shown in the previous figure, according to a preferred embodiment of the invention;

[0070] [Fig.23] is a cross-sectional view of the actuation device shown in Figures 21 and 22;

[0071] [Fig.24] is a more detailed perspective view of a connecting rod actuation device of the type located in the previous figure, according to another preferred embodiment of the invention;

[0072] [Fig.25] is a perspective view similar to that of the previous figure, from another angle of view;

[0073] [Fig.26] is a more detailed perspective view of part of the connecting rod actuation device shown in Figures 24 and 25;

[0074] [Fig.27] is a view similar to that of [Fig.1 1], with the inverter appearing in the form of another preferred embodiment of the invention;

[0075] [Fig.28] is a view similar to that of [Fig.2], with the inverter appearing in the form of yet another preferred embodiment of the invention. Detailed description of implementation methods

[0076] Figure [Fig. 1] shows a propulsion assembly 1 for an aircraft, having a longitudinal central axis Al.

[0077] Hereafter, the terms "upstream" and "downstream" are defined relative to a general SI direction of gas flow through the propulsion assembly 1, along the axis Al when it generates direct thrust. These terms "upstream" and "downstream" could respectively be replaced by the terms "front" and "rear", with the same meaning.

[0078] The propulsion unit 1 comprises a turbomachine 2, a nacelle 3 and a mast (not shown), intended to connect the propulsion unit 1 to a wing (not shown) of the aircraft.

[0079] In this example, the turbomachine 2 is a twin-spool, turbofan engine comprising, from front to rear, a fan 5, a low-pressure compressor 6, a high-pressure compressor 7, a combustion chamber 8, a high-pressure turbine 9, and a low-pressure turbine 10. The compressors 6 and 7, the combustion chamber 8, and the turbines 9 and 10 form a gas generator. The turbofan engine 2 has a fan casing 11 connected to the gas generator by structural arms 12.

[0080] The nacelle 3 comprises a front section forming an air inlet 13, a middle section which includes two blower hoods 14 enveloping the blower housing 11, and a rear section 15.

[0081] During operation, an airflow 20 enters the propulsion assembly 1 through the air inlet 13, passes through the blower 5 and then splits into a primary flow 20A and a secondary flow 20B. The primary flow 20A flows into a primary gas circulation channel 21A passing through the gas generator. The secondary flow 20B flows into a secondary channel 21B surrounding the gas generator. The secondary channel 21B is radially delimited inwards by fixed elements. In this example, these are, firstly, a first section 17 corresponding to a structural part of the turbomachine, preferably a hub of an intermediate casing 42. This also includes an outer shell 40 as well as the aforementioned structural arms 12. The shell 40 therefore also contributes to radially delimiting the secondary channel 21B outwards, being located in the downstream axial extension of the fan casing 11.

[0082] This is followed by a second section 18 extending rearward from the first section 17, so as to form part of the rear section 15 of the nacelle. This second section 18 is an integral part of a fixed structure of a thrust reverser which will be described below. This same section corresponds more precisely to an opening hood of the nacelle, in that it can either be removed or opened, for example by pivoting, in all cases to provide access to an inter-vein engine compartment, in which equipment 19 is housed that must remain accessible for maintenance operations. In particular, this opening hood includes the radially internal boundary wall of the secondary vein 21B, this wall being referred to as wall 18 in the following description. As indicated later with reference to [Fig.20], the openable hood also includes one or more bifurcations, which also help to delimit the secondary vein, but circumferentially in relation to the AL axis.

[0083] Conventionally, the hinged hood incorporating the wall 18 has an upstream end mounted on a downstream end of the turbomachine structural part 17. This part 17 thus preferentially corresponds to the hub of the intermediate casing 42, or to a compressor casing located further downstream, such as the high-pressure compressor casing. The mounting of the two aforementioned ends onto each other is carried out by conventional means at an axial boundary 23 between the two elements 17, 18. These mounting means differ depending on the nature of the hinged hood, whether it is simply removable, or pivotally mounted relative to the fixed structural part 17 of the turbomachine.

[0084] Radially outwards, the secondary duct 21B is delimited by the blower housing 11 and the ferrule 40 of the intermediate housing 42, and, in the configuration of [Fig.1], by one or more movable reversing hoods 33 forming part of the rear section 15 of the nacelle 3, and which will be described later.

[0085] The nacelle 3 therefore comprises a thrust reverser 30 centered on the axis Al and comprising on the one hand a fixed structure 31 integral with the fan housing 11, and on the other hand a structure 29 movable relative to the fixed structure 31. The fixed structure 31 includes for example a front frame 46 which connects it fixedly to the blower housing 11, preferably via a knife flange assembly located downstream of the outer ferrule 11. This front frame 46 contains a profiled aerodynamic part called a deflection edge 46B, which guides the flow in reverse jet.

[0086] Here, the fixed structure 31 also includes a plurality of deflection grids 32 arranged adjacent to each other around the axis Al, in a circumferential direction of the reverser 30 and the propulsion assembly 1, relative to the axis Al. Furthermore, the movable structure 29 comprises the aforementioned movable reverser hoods 33, for example, two hoods 33 each extending over an angular amplitude of approximately 180°. This configuration with two hoods 33 is particularly well suited to a nacelle design in which the hinged hoods / walls 18 are also mounted, the reverser 30 then having a so-called "D-duct" architecture. In this architecture, hoods 18, 33 are connected in such a way as to open / close simultaneously during maintenance operations on the engine.However, other architectures are possible, such as a so-called "C-shaped" architecture, known by the Anglo-Saxon name "C-Duct", or an "O-shaped" architecture, known by the Anglo-Saxon name "O-Duct". In these last two architectures, the aforementioned opening cover(s) are non-pivoting, and simply removable to allow maintenance operations to be carried out in or from the inter-vein compartment, particularly on equipment 19.

[0087] Each movable reversing gear cover 33 comprises a radially external wall 50, forming an external aerodynamic surface of the reversing gear and nacelle, this surface being enveloped by the outside air. Each cover 33 also comprises a radially internal wall 52 contributing to the delimitation of the secondary channel 21B radially outwards. This wall 52 is located in the downstream continuity of the outer shell 40 of the intermediate housing. The two walls 50, 52 define a cavity 54, preferably open axially towards the front, at the upstream end of the reversing gear cover 33.

[0088] Figure 1 shows the reversing gear 30 in a forward direct thrust configuration, known as "direct jet," corresponding to a standard flight configuration. In this configuration, the cowlings 33 of the movable structure 29 are in a closed position, known as the forward thrust or "direct jet" position, in which these reversing gear cowlings 33 bear against the fixed structure 31, in particular against the deflection edge 46B, which is an integral part of the latter. Indeed, in the direct thrust configuration, the upstream end 52a of the radially internal wall 52 of each cowling 33 bears axially against the deflection edge 46B.

[0089] The movable hood 33 is held in the forward direct thrust position by means for locking this hood onto the fixed structure 31 of the reversing unit. These controlled locking means (not shown) are conventional and will therefore not be described further. As an illustrative example, active locks capable of unlocking under load can be implemented to counteract the compressive force on a seal between the movable structure and the deflection edge. This type of lock can, in effect, over-compress the seal so that unlocking can then be initiated.

[0090] The movable structure 29 is thus translationally movable relative to the fixed structure 31 along the axis A1 of the reverser, between the forward direct thrust position shown in [Fig. 1], and a rearward thrust reversal position which will be described later. In the forward direct thrust position of the movable structure 29, the deflection grids 32 are arranged in the cavity 54 of the reverser covers 33, being isolated from the secondary flow 21B by the radially internal wall 52 of these sliding reverser covers 29. This wall 52, forming the external wall of the secondary flow, is also called the internal acoustic panel.

[0091] This direct thrust configuration is also shown in Figures 2 and 4, while the thrust reversal rearward position of the mobile structure 29 is shown in Figures 3 and 5. [Fig.2A] represents a configuration as adopted during an initial phase of movement of the mobile structure towards its thrust reversal rearward position, while [Fig.2B] represents an intermediate configuration, observed after that of Figure 3A, during the opening of the reverser.

[0092] In [Fig. 3], it is shown that the recessed internal acoustic panel 52 of the reversing hoods exposes upstream an opening 56 for the secondary flow 21B towards the deflection grilles 32. The opening 56 is therefore also delimited upstream by the deflection edge 46B, which flares radially outwards towards the rear, to channel an airflow intended to pass through the grilles 32 when the moving system is in this recessed thrust reversal position. In other words, the deflection edge 46B has a shape that gradually moves away from the axis A1 from front to rear, to guide / deflect the air towards the grilles 32 in the thrust reversal configuration. Downstream, the passage opening 56 is delimited in particular by the upstream end 52a of the radially internal wall 52.

[0093] In order to divert at least a portion of the secondary flow 20B towards the passage opening 56 defined axially between the deflection edge 46B and the upstream end 52a of the radially internal wall 52 of each hood 33, the diverter 30 comprises one or more sealing membranes 58. An embodiment thereof will subsequently be described. in which a single membrane 58 is associated with each inverter cover 33, exhibiting an identical or similar angular amplitude, but it remains possible to provide several circumferentially adjacent membranes associated with each cover 33. Similarly, only the interaction between a membrane 58 and its associated cover 33 will be described below, it being understood that this interaction is identical or similar for all covers of the inverter 33. It is noted, however, that in addition to the possibility of providing several membranes 58, one or more more conventional rigid shutters could be provided in association with this / these membranes, for example, alternating in the circumferential direction. A preferred embodiment is also envisaged with only rigid shutters, as will be described with reference to [Fig. 28].

[0094] The membrane 58 can be made of a material known to those skilled in the art for this type of application. For example, it can be an unimpregnated fabric, such as aramid fibers. The membrane 58 can also be made of a composite material with a particularly flexible matrix, such as aliphatic polyurethane, which allows its use under different temperature conditions, notably lower temperatures for an aliphatic polyurethane membrane than for a silicone membrane. The matrix provides low flexural strength, and the behavior of the resulting structure is indeed that of a membrane. One of the major properties of this membrane 58 is its ability to bend in a perfectly reversible manner (elastically or by fiber sliding) with a very small radius of curvature relative to its surface area, and to have a very small thickness, for example, on the order of 0.1 to 3 mm.For information purposes, it is observed that this membrane 58 behaves like a boat sail or a parachute / a flying wing when it is pressurized.

[0095] It is recalled that in a conventional gate inverter, the moving structure slides relative to the fixed structure by means of a rail / slide system that guides the moving structure from front to back during the opening phase of the inverter, and from back to front during the closing phase. A rearward force applied to the moving structure of the inverter therefore causes it to move backward relative to the fixed structure. This force is usually generated by conventional actuators such as cylinders or ball screws.

[0096] With further reference to figures 1 to 5 representing a preferred embodiment of the invention, the membrane 58 has two opposite ends, namely a first end 58a connecting to one or more actuating rods 62, and a second end 58b connected to a rear frame 60 supporting the grids 32. This support is annular or in the form of an annular section connecting the rear end of several adjacent grids.

[0097] Regarding the first end of the membrane 58a, it is therefore connected to one or more deployment struts 62 arranged in the secondary channel 21B. For example, several struts 62 are spaced circumferentially from one another, and each is connected to the first end of the membrane 58a via a specific connection point 63 for each strut. However, in the remainder of this description, only one strut will be described, it being understood that the design of the other struts is identical or similar, as is their interaction with the surrounding elements. It is noted that in the case of a cable provided in place of the strut 62, the first end of the membrane 58a is connected at the first link 74a, which will be described below.

[0098] The connection point 63 thus connects the first end of the membrane 58a to a first end 62a of the deployment rod 62, this first end of the rod 62a corresponding to a radially external end in the advanced position of direct thrust of the moving structure of the inverter.

[0099] Furthermore, an actuation device 70, specific to the invention, connects the radially internal boundary wall 18 of the vein to a second end 62b of the connecting rod, opposite the first end 62a, and thus corresponding to the radially internal end. This device 70, used for actuation of the connecting rod 62, will be described below.

[0100] As can be seen in Figures 1, 2 and 4, when the movable structure 29 occupies its forward direct thrust position, at least a portion of the sealing membrane 58 is arranged radially between the deflection grids 32 and the radially internal wall 52 of the reversing hood 33, in the cavity 54. Preferably, the portion of the membrane 58 that is in this cavity 54 of the reversing hood 33 radially covers the entire length of the grids 32. As a result, when the movable structure 29 adopts its forward direct thrust position, the first end 58a of the membrane 58 is pinched between the upstream end of the wall 18, and the deflection edge 46B, near the connection point 63 which is located in the vein. In order to avoid possible damage to the membrane 58 due to this pinching, the deflection edge 46B may locally have a notch of a shape adapted to receive the upstream end 52a of the wall 52.Thus, the membrane 58 is also pressed into this notch of the deflection edge 46B, by the support of the upstream end of the wall 52.

[0101] Also, as can be seen in [Fig. 2A] and 2B, when the movable structure 29 moves towards its rearward thrust reversing position, the sealing membrane 58 is partially supported against the upstream end 52a of the radially internal wall 52 of the reversing hood, thus corresponding to the acoustic panel. More precisely, during the rearward movement of the mobile structure 29, the membrane 58 slides on this upstream end 52a of the radially internal wall 52.

[0102] In the thrust reversal position of [Fig. 3], the diaphragm 58 is located axially at a distance from the upstream end 52a, but contact could be maintained between the two without departing from the scope of the invention. In this regard, it is noted that the option with contact corresponds to a minimized stroke of the reverser, while the option without contact generally corresponds to a smoother diaphragm shape in reverse jet, and therefore more efficient from an aerodynamic point of view.

[0103] Thus, the part of the membrane 58 which is located radially outwards with respect to its bearing area on the wall 52 closes part of the upstream axial opening of the cavity 54, while the other part located radially inwards closes at least part of the secondary vein 21B, thereby diverting at least part of the secondary flow 20B towards the passage opening 56 in the direction of the grids 32.

[0104] Another possibility, not shown, consists of carrying out the external radial attachment of the membrane 58, on the external radial wall 50 of the sliding cover 33.

[0105] Although not shown, an alternative is to provide that the grids 32 are replaced by, or provided in combination with, other flow deflection devices to generate the counter-thrust. This is, for example, a flexible structure, such as a membrane / textile, used to redirect the flow exiting the passage opening 56 forward.

[0106] As previously stated, the connecting rod actuation device 70 connects the radially internal boundary wall 18 of the vein (also referred to as IFS, from the English "Inner Fixed Structure") to the second end 62b of the connecting rod. The device 70 and the entire reversing assembly are designed so that the connecting rod 62 is moved from a first position projecting radially into the secondary vein when the moving structure 29 is in its forward forward thrust position, to a second position folded downward when the moving structure 29 is in its rearward thrust reversal position, and vice versa. In the first position shown in [Fig.[2], the connecting rod 62 can indeed adopt a radial or substantially radial orientation in the vein 21B, although a slight inclination from this radial direction remains possible, for example up to a value of 10 to 20°, with the first end of connecting rod 62a preferably located upstream relative to the second end of connecting rod 62b. The connecting rod 62 has a substantial length, for example greater than half the radial thickness of the vein 21B at the point where the connecting rod is located, and even more preferably a length greater than two-thirds of this radial thickness.

[0107] The actuation device 70 includes a support member 64 fixed on the wall 18, as well as an upstream displacement member 72, arranged in the secondary vein 21B and carried by the support member 64.

[0108] The support member 64 takes the form of a single fitting, and of several fittings attached one on top of the other, or attached separately to the wall 18, at the level of its acoustic coating portion. Thus, the member 64 comprises a base 65, fixed in this embodiment to a radially internal surface of the wall 18. From this base 65, the support member 64 comprises an upstream portion projecting radially outwards 67, penetrating the acoustic coating of the wall 18. In addition, the support member 64 comprises a downstream portion projecting radially outwards 69, passing through the entire wall 18 and then penetrating the channel 21B.

[0109] The upstream offset member 72 has an aerodynamic profile, for example, of general revolution, with an axis corresponding to its chord line 71. This chord line 71, which connects a leading edge curved upstream of this profile to a trailing edge pointed downstream, is locally parallel or substantially parallel to the direction of the secondary flow 20B. Indeed, to limit the drag induced by the offset member 72, its chord line 71 forms with the secondary flow 20B, when the moving structure occupies its forward direct thrust position, an angle of incidence (Ai) of less than or equal to 10°, and preferably less than or equal to 8°.

[0110] The offset member 72 also has a connecting tab 73 with the upstream projecting portion 67 of the support member 64, this tab 73 projecting radially inwards from the airfoil. The tab 73 is integral with the airfoil, for example by being formed as a single piece with the airfoil.

[0111] The actuating member 72 comprises, at its leading edge, a first end 72a corresponding to the upstream end, at which is located a first articulated joint 74a with the second connecting rod end 62b. This first articulated joint 74a preferably has a pivot / rotation axis with a circumferential, or substantially circumferential, orientation. A second end 72b of the member 72, opposite the first end 72a and thus corresponding to the downstream end at the trailing edge of the profile, incorporates a cutout 75 in this profile. The cutout 75 delimits a space in which the free radial end of the protruding downstream portion 69 is housed with clearance. This cutout 75 opens preferably radially in both directions, and axially downstream.

[0112] Furthermore, the leg 73 is connected to the upstream projecting part 67 of the support member 64 by means of a second articulated joint 74b, preferably with an axis of pivoting / rotation parallel or substantially parallel to that of the The first articulated joint 74a. The second articulated joint 74b is arranged downstream of the first articulated joint 74a when the moving structure occupies its forward direct thrust position, while remaining arranged upstream of the downstream protruding part 69. Radially, the joint 74b is arranged wholly or partly outside the groove 21B, within the thickness of the wall 18, which is perforated for the passage of the support member 64. This second joint 74b could be arranged more radially towards the inside, or, conversely, be located entirely within the secondary groove 21B, for example by providing this second joint within the aerodynamic profile of the offset member 72.

[0113] It is noted that in direct thrust configuration, the connecting rod 62 and the offset member 72 together form a salient angle B1 opening downstream and radially outwards, this angle B1 preferably being between 70 and 110°.

[0114] One of the features of the invention lies in the fact that when the movable structure is in its forward direct thrust position, the offset member 72 allows the first articulated joint 74a to be placed upstream of the upstream end of the opening hood, and therefore upstream of the upstream end of the radially internal boundary wall 18 of the secondary flow 21 B. In other words, the center of the first articulated joint 74a is arranged radially opposite the structural part 17 of the turbomachine, that is, axially upstream of the boundary 23 between the two elements 17 and 18. The axial distance Da between, on the one hand, the upstream end of the wall 18, and on the other hand, the center of the first joint 74a, when the movable structure is in its forward direct thrust position, is preferably sufficient so as not to hinder the opening of the opening hood 120 for maintenance. which will be described below.This means that the distance Da is preferably sufficient to avoid mechanical interference with the fan cowl 14 and the fan casing 11 when the cowl 120 is opened for maintenance. In this respect, the axial distance Da is also preferably provided so that, in a direct thrust configuration, an axial separation remains between, on the one hand, the upstream end of the wall 18, and on the other hand, a downstream end of the first connection 74a. This axial separation can, for example, be on the order of a few centimeters, or even a greater value.

[0115] This upstream offset of the first articulated link 74a allows the connecting rod 62 to be arranged according to a desired orientation, ensuring the correct deployment of the diaphragm 58, without requiring the connecting rod to be mounted on an element external to the reverser, in this case the structural part of the turbomachine 17 at the axial level of which are located this first axial link 74a, as well as the second end of the connecting rod 62b.

[0116] The connecting rod 62 and the offset member 72 together form a three-point mechanical system with, respectively, the membrane connection point 63, the first articulated joint 74a, and the second articulated joint 74b. This three-point mechanical system, which can be likened to a knee-type joint, is such that during the movement of the mobile structure 29 from its forward position of direct thrust to its rearward position of thrust reversal, there is a relative displacement of the connecting rod 62 with respect to the offset member 72 around the first articulated joint 74a. This leads, at least initially, to a decrease in the salient angle Bl, as can be seen in [Fig. 2A]. The mechanical system then tends to fold.

[0117] To facilitate the folding of this three-point mechanical system when the reversing mechanism is opened, first, preferably passive, load means are provided. These include, firstly, first elastic return means 80a, shown schematically only in the relevant figures. During an initial phase of movement of the movable structure 29 towards its rearward thrust reversing position, these first means 80a, for example of the hinge spring type, force the component 72 to pivot around the second articulated joint 74b in a first direction of rotation 81a, corresponding to the counterclockwise direction in the figures.This first direction of rotation is such that it causes the first end 72a of the component 72, as well as the first link 74a, to tilt upstream and radially inwards during an initial phase of movement of the mobile structure 29 from its forward position of direct thrust to its rearward position of thrust reversal. This initial phase is represented in [Fig. 2A], showing the aerodynamic profile of the component 72 plunging upstream and radially inwards, by pivoting about the first link 74a, in the first direction. This leads to a reduction of the salient angle B1.

[0118] This reduction of angle B1 is accentuated by second passive stressing means, which also include second elastic restoring means 80b, shown only schematically in the relevant figures. During the initial phase of the movement of the mobile structure, the second means 80b, for example also of the hinge spring type, force the connecting rod 62 to tilt relative to the offset member 72 around the first articulated joint 74a, in a second direction of rotation 81b opposite to the first direction 81a, and therefore corresponding to the clockwise direction in the figures.

[0119] The first and / or second elastic return means 80a, 80b can be replaced by an elastic rolling bearing, for example, a bearing of this type from the TECHLAM™ brand. As is known, this type of bearing comprises concentric metal rings of increasing diameters, with a clearance between each of them. This clearance is filled by a high-deformation elastomer. As this bearing rotates, the elastomer is sheared, and this shear is distributed between the various layers of elastomer, which allows for a significant angular deformation, for example on the order of 30° to 90°.

[0120] As mentioned previously, in the direct thrust position, the first and second elastic return means 80a, 80b exert a force on the diaphragm 58, via the connecting rods 62, so as to maintain this diaphragm under tension and promote its stability. During the initial opening phase of the inverter, the first elastic return means 80a cause the upper part of the connecting rod 62 to pivot radially inward and downstream, while the second elastic return means 80b cause the lower part of the connecting rod 62 to pivot radially inward and axially upstream. The end of this initial displacement phase is shown in [Fig. 2A]. The salient angle B1 has therefore been reduced, preferably to a value less than 90°.

[0121] After the initial phase of movement of the mobile structure 29, increasing amounts of air from the secondary flow rush into the membrane 58, which then creates a force on the offset member 72, via the connecting rod 62, forcing this offset member to pivot around the second articulated joint 74b, in the second direction of rotation 81b. This force generated by the membrane 58 then becomes greater than that generated by the first elastic restoring means 80a, which leads to the offset member 72 pivoting in the second direction 81b.

[0122] When the opening of the inverter continues, for example to about 40% of the opening stroke, the offset member 72 is stopped in rotation in the second direction 81b, by the stop between the axial bottom of the cutout 75, and the downstream protruding part 69 of the support member 64. This stop, shown schematically on [Fig.2B], is maintained throughout the end of the opening of the inverter, itself shown schematically on [Fig.3].

[0123] Another advantage associated with the presence of the second elastic return means 80b lies in the easy detection, during maintenance, of any connection problem between the first end of the diaphragm 58a and the connecting rod(s) 62. Indeed, this type of detection is usually particularly complicated due to the difficult visual access to this junction. In the proposed design, any connecting rod 62 with a connection defect to the diaphragm 58 will automatically fold back into the channel 21B in its downstream folded position, under the action of the second elastic return means 80b. Since such a folded connecting rod in the channel 21B remains easily identifiable by an operator performing maintenance operations, the aforementioned detection is effectively simplified.These second elastic means 80b are also useful for extracting the membrane 58 from the cavity 54, during maintenance operations in which no airflow can assist such deployment.

[0124] As previously stated, during the opening of the reversing gear, the three-point mechanical system folds back, resulting in a progressive decrease in the salient angle Bl, until it becomes very small, or even zero, at the end of the opening or before the end of the opening, as can be seen in [Fig. 3]. In this configuration, where the connecting rod 62 adopts its second folded-down position downstream, the three points are aligned or substantially aligned with the second articulated joint 74b located between the first articulated joint 74a and the connection point 63. This alignment occurs parallel or substantially parallel to the axial direction of the reversing gear, and locally to the direction of the secondary flow 20B.

[0125] Figures 6 to 10 illustrate another preferred embodiment of the invention. In this embodiment, the second elastic return means 80b retain the same shape as that described in the previous preferred embodiment. However, the first elastic return means 80a adopt a different shape, which will be described later. In this embodiment, another change lies in the shape of the support member 64, the rear portion of which forms the stop 75, with its external radial end. It is against this stop 75 that the second end 72b of the offset member 72 bears during the opening of the reverser, thus limiting rotation in the second direction 81b. At the front, the support member 64 extends into the secondary channel 21B to house the second articulated link 74b, which is also housed in the aerodynamic profile constituting the offset member 72.

[0126] In this mode, the aerodynamic profile is achieved using a main body having several hollows, which are filled by low-density elements 77, in order to lighten the overall mass of the offset element 72.

[0127] Finally, as mentioned previously, the first elastic return means 80a are housed in an opening in the support member 64. Preferably, this consists of a compression spring 94 bearing at one end against the base 67 of the member 64, and bearing at the other end against a slide 96, which is free to move translationally within the member 64. The compression spring 94 is located downstream of the second articulated joint 74b. The slide 96 carries an actuating pin 99 bearing against the offset member 72, in order to apply a return force to the latter, forcing it to pivot in the first direction 81a. When the mobile structure occupies its advanced position of direct thrust, this restoring force is preferentially oriented orthogonally or substantially orthogonally to a longitudinal direction of this offset member 72, corresponding to its chord line 71.The orientation of this restoring force, applied by pin 99, is thus preferentially radial, or substantially radial.

[0128] For this mode, Figures 8 to 10 represent the inverter at different stages during its opening. These stages correspond respectively to the same stages as those in Figures 2, 2A and 3 of the previous preferred embodiment.

[0129] Figures 11 to 13 represent another preferred embodiment of the invention, similar to that of [Fig. 2], the only modification being the shape of the first elastic return means 80a. Indeed, these are integrated into the offset member 72, and they comprise a compressor spring 94 having one end bearing on a stop surface within the offset member 72, and an opposite end bearing on a piston head 102, which slides in a direction identical or substantially identical to that of the chord line 71. The piston head 102 carries a piston rod 100, the free end of which bears on the projecting downstream portion 69 of the support member 64.It is the combination of these elements which, via the restoring force applied by the spring 94, allows the offset member 72 to tilt in the first direction 81a, during the initial phase of the movement of the reversing mobile structure, towards its rearward thrust reversing position.

[0130] For this mode, Figures 11 to 13 represent the inverter at different stages during its opening. These stages correspond respectively to the same stages as those in Figures 2, 2A and 3 of the previous preferred embodiment.

[0131] Note that in this mode, the second articulated link 74b is located outside the secondary vein 21B, but that it could alternatively be located in this same vein.

[0132] Figures 14 to 16 represent another preferred embodiment of the invention, similar to that of Figures 11 to 13, the only modification being in the shape of the first and second elastic return means 80a, 80b. Indeed, these are identical and therefore grouped within the same elastic return means, comprising a compression spring 94. This, arranged in the offset member 72, comprises a first end exerting a first force on a first head 104 of a first piston, a first piston rod 108 of which bears against the part 69 of the support member 64.

[0133] The compression spring 94 includes a second end opposite to the first, exerting a second force on a second head 106 of a second piston, a second piston rod 110 of which cooperates with the second connecting rod end 62b. Preferably, the end of the second piston rod 110 is articulated on the connecting rod end 62b, eccentrically with respect to the axis of the first articulated joint 74a.

[0134] The two piston heads 104, 106 are movable by sliding in an orifice of the displacement member, preferably parallel or substantially parallel to the chord line 71.

[0135] Thanks to this design, during the initial phase of movement of the reversing unit's moving structure, the release of the spring 94 allows the two piston heads 104, 106 to move in opposite directions of the shift member 72. This leads simultaneously to the rotation of the shift member 72 around the second link 74b in the first direction 81a, as well as to the rotation of the connecting rod 62 along the first link 74a, in the second direction 81b.

[0136] For this mode, Figures 14 to 16 represent the inverter at different stages during its opening. These stages correspond respectively to the same stages as those in Figures 11 to 13 of the previous preferred embodiment.

[0137] Figures 17 to 19 represent another preferred embodiment of the invention, which contrasts with the previous embodiments by the shape of the first elastic return means. Indeed, the second articulated link is eliminated, and the junction between the support member 64 and the offset member 72 is replaced by a leaf spring 112. It is therefore this return leaf 112 which fulfills the function of the aforementioned first elastic return means, by forcing the offset member 72 radially inwards and axially upstream, during the initial phase of the opening of the reverser.

[0138] For this mode, Figures 17 to 19 represent the inverter at different stages during its opening. These stages correspond respectively to the same stages as those in Figures 14 to 16 of the previous preferred embodiment.

[0139] Figure 20 shows a portion of the inverter, displaying the movable cover 33 arranged around the hinged cover 120. As mentioned previously, these two covers 33 and 120 can be designed to pivot simultaneously for maintenance purposes. This is therefore a single cover, referred to as a "D" cover. The preferred embodiments described previously include connecting rod actuation devices (not shown) fixed to the radially internal wall 18 of the secondary channel 21B.

[0140] In the preferred embodiments shown in the following figures, the actuation device 70 is no longer fixed to the wall 18 of the hinged cover 120, but to a bifurcation wall 118 of the same cover. For example, two bifurcations are arranged in clockwise positions at six o'clock and noon, crossing the secondary vein 21B to connect the two walls 18 and 52. In other words, conventionally, these bifurcations circumferentially delimit the vein 21B.

[0141] One of these actuation devices 70 has been shown according to a preferred embodiment of the invention in Figures 21 to 23. The design of the inverter is similar to that of the embodiment described with reference to Figures 2 to 5. Indeed, the actuation device 70 comprises the support member 64 fixed to the bifurcation wall 118, this member 64 projecting circumferentially into the channel 21B and carrying the offset member 72, via the second articulated link 74b. Although not shown, the member 72 does indeed allow the first articulated link 74a to be offset axially upstream, beyond the junction between the upstream end of the hinged cover 120, and the downstream end of the structural part of the turbomachine (not shown).

[0142] For the sake of indication, it is noted that the upstream end of the bifurcation walls 118 is for example mounted on beams in the clockwise position at noon attached to the mounting mast, and on beams in the clockwise position at six o'clock connecting the two half-sides of the inverter.

[0143] Here too, the chord line 71 of the airfoil 72 is locally parallel or substantially parallel to the secondary flow 20B, in the direct thrust configuration shown in [Fig. 21]. Instead of extending radially outwards as in previous preferred embodiments, the support member 64 extends circumferentially, also in the form of an airfoil. To accommodate this modification, the cutout 75 is here open circumferentially and radially inwards.

[0144] Otherwise, the operation of the actuation device 70 remains the same as that described previously. In particular, it is provided that the circumferential projecting part 69 of the member 64 is brought to a stop in the radial bottom of the cutout 75 when the moving structure has reached a predetermined level of opening stroke, corresponding for example to 40% of this total stroke between the forward position of direct thrust and the retracted position of thrust reversal.

[0145] In this preferred embodiment of Figures 21 to 23, the first and second elastic return means 80a, 80b correspond for example to those of the preferred embodiment of Figures 2 to 5, being integrated within the articulated links 74a, 74b.

[0146] According to another preferred embodiment shown in Figures 24 to 26, the first and second elastic return means 80a, 80b correspond to those of the preferred embodiment shown in Figures 6 to 10. Indeed, the second elastic return means 80b remain integrated into the first articulated joint 74a, while the first elastic return means 80a comprise a compression spring 94 actuating a slide 96 equipped with an actuating pin 99, exerting a return force on a circumferential tab 122 of the offset member 72. In this In this mode, the restoring force exerted by the spring 94 on the offset member 72, via the pin 99 on the lug 122, is also orthogonal or substantially orthogonal to the longitudinal direction of this member 72, corresponding to its chord line 71. The spring 94 is therefore circumferentially spaced from the offset member 72. In addition, a stop system similar to those described previously is provided, in order to limit the rotation of the offset member 72 in the second direction, during the opening of the reverser.

[0147] The preferred embodiment of [Fig. 27] is characterized by a fixed connection between the support member 64 and the offset member 72. Due to this fixed connection, the offset member 72 is not designed to pivot radially inward and axially upstream during the initial opening phase of the inverter. This embodiment is thus particularly suitable for use with a secondary vein obturator flap. However, as shown in [Fig. 28], the use of obturator flaps 158, instead of membranes 58, can also be considered with an actuation device 70 having a second articulated connection 74a between the two members 64 and 72.

[0148] Various modifications can be made by a person skilled in the art to the invention described above, solely by way of non-limiting examples, the scope of which is defined by the appended claims. For example, the thrust reverser 30 can alternatively have a "C" or "O" configuration. Furthermore, if the preferred embodiments described above relate to a reverser design with fixed deflection grids, these grids can alternatively be integrated into the moving structure of the reverser. Finally, it is noted that the elements of the various embodiments presented above are interchangeable and / or combinable.

Claims

1. Demands Propulsion assembly (1) for aircraft, comprising a turbomachine (2) and a thrust reverser (30), the reverser comprising a fixed structure (31) equipped with a boundary wall (18, 118) of a secondary flow (21B) of the propulsion assembly intended to be traversed by a secondary flow (20B), the boundary wall (18, 118) belonging to an openable cowling (120) having an upstream end of the cowling mounted on a downstream end of a structural part (17) of the turbomachine, the reverser also comprising a movable structure (29) comprising at least one movable reverser cowling (33) equipped with a radially internal wall (52) participating in the radially external boundary of the secondary flow (21B), the movable structure being displaceable relative to the fixed structure between an advanced direct thrust position,and a rearward thrust reverser position in which the fixed structure and an upstream end (52a) of the radially internal rearward wall of the reverser's movable cover expose between them an opening (56) for the passage of air through the secondary flow, the thrust reverser also comprising at least one secondary flow closure member (58), designed to deflect at least a portion of the secondary flow towards the passage opening (56), as well as at least one closure member (62) for deploying the closure member, arranged in the secondary flow (21B) and having a first end (62a) connected to the closure member, the reverser also comprising a device (70) for actuating the deployment member (62), the actuating device connecting the boundary wall (18, 118) to a second end (62b) of the deployment member, via a first articulated linkage (74a),characterized in that the actuation device (70) comprises a support member (64) fixed to the boundary wall (18, 118), and an upstream offset member (72) arranged in the secondary channel and carried by the support member, the offset member (72) integrating at its upstream end the first articulated link (74a), so as to place the latter upstream of the upstream end of the opening cover (120), when the mobile structure (29) occupies its forward direct thrust position.

2. Propulsion assembly according to claim 1, characterized in that the reverser (30) is configured such that during an initial phase of displacement of the mobile structure (29) from its forward direct thrust position to its rearward thrust reversal position, the actuation device (70) causes a displacement of said first articulated link (74a) radially inwards and / or axially upstream.

3. Propulsive assembly according to claim 2, characterized in that the upstream offset member (72) is mounted articulated on the support member (64), by means of a second articulated link (74b) arranged downstream of the first articulated link (74a), when the movable structure (29) occupies its forward direct thrust position.

4. Propulsive assembly according to claim 3, characterized in that the second articulated link (74b) is arranged in the secondary vein (21B).

5. Propulsion assembly according to claim 3 or 4, characterized in that in the forward direct thrust position of the mobile structure, the deployment member (62) and the upstream offset member (72) together form a salient angle (Bl), the actuation device (70) being designed, during said initial phase of movement of the mobile structure (29), to force the offset member (72) to tilt around the second articulated link (74b), in a first direction of rotation (81a) leading to a reduction of the salient angle (Bl).

6. Propulsion assembly according to claim 5 characterized in that the actuation device (70) comprises first means for activating the offset member, the first means of activating comprising first elastic return means (80a) forcing, during said initial phase of displacement of the mobile structure (29), the offset member (72) to tilt around the second articulated link (74b), in the first direction of rotation (81a), said first elastic return means (80a) being arranged: - in the support member (64), preferably arranged so as to generate on the offset member (72) a return force orthogonal or substantially orthogonal to a longitudinal direction of this offset member (72), when the mobile structure occupies its advanced direct thrust position; and / or - in the offset member (72); and / or - within the second articulated link (74b).

7. Propulsion assembly according to any one of the preceding claims, characterized in that the boundary wall belonging to the openable hood (120) is a radially internal boundary wall (18) of the secondary vein (21B), or a wall (118) of a bifurcation circumferentially delimiting the secondary vein (21B).

8. Propulsive assembly according to any one of the preceding claims, characterized in that the deployment member (62) is a connecting rod.

9. Propulsive assembly according to any one of the preceding claims, characterized in that the sealing member (58) is a deployable sealing membrane.

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