AIRCRAFT PROPULSION ASSEMBLY COMPRISING A MOVING GRILLED AND OPTIMIZEDLY MOUNTED THRUSTER REVERSER
Patent Information
- Application Number
- FR2022000995
- Authority / Receiving Office
- FR · FR
- Patent Type
- Patents
- Current Assignee / Owner
- Filing Date
- 2022-02-04
- Publication Date
- 2025-03-07
- Estimated Expiration
- 2042-02-04
Smart Images
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Abstract
Description
Title of the invention: PROPULSION ASSEMBLY FOR AIRCRAFT COMPRISING A THRUST REVERSER WITH MOVABLE GRIDS AND AN ACTUATOR MOUNTED IN A MANNER OPTIMIZED Technical field
[0001] The invention relates to the field of nacelles and thrust reversers for aircraft propulsion systems, and, more particularly, to nacelles equipped with reversers with moving grids. State of the prior art
[0002] Thrust reversers are devices for diverting the airflow passing through the propulsion unit forward, so as to shorten landing distances and limit the stress on the brakes on the landing gear.
[0003] The grid inverters currently used in the aeronautical sector comprise a front frame forming with the grids a fixed part of the inverter, intended to be connected to a turbomachine casing.
[0004] More recent technical developments have made it possible to develop mobile grid inverters, such as those described for example in documents FR2981989A1, FR2999239A1, FR3002785A1 and FR3073572A1.
[0005] Compared to a conventional inverter with fixed grids, the mobility of the grids makes it possible to reduce the length of the nacelle, and, consequently, to reduce its mass as well as the drag it generates.
[0006] In designs with moving grilles, the installation of the actuators and their support means is complicated by the small space available in the area dedicated to the right of the fan casing and the outer shell of the intermediate casing, when such an intermediate casing is provided. In addition, it is necessary to respect certain constraints such as not placing the actuators around the parts of the fan casing which are subject to deformation in the event of accidental situations involving a loss of fan blades (case of an FBO, from the English "Fan Blade Out").
[0007] These constraints, among others, complicate the installation of the actuators and their support means. There is therefore a need to optimize this installation, so as to meet the constraints set out above, while guaranteeing suitable absorption of the actuator forces by appropriate connection points of the engine structure. Statement of the invention
[0008] To meet this need, the subject of the invention is a propulsion unit for an aircraft equipped with a turbomachine and a nacelle comprising a thrust reverser, the turbomachine comprising a fan casing extending around a longitudinal central axis of the propulsion unit, and also comprising a fixed structure equipped with a deflection edge, the reverser also comprising a mobile structure comprising a reverser cowl and a set of deflection grilles, the set of grilles comprising a plurality of deflection grilles as well as a rear structure for supporting the grilles on which is fixed a rear end of the plurality of deflection grilles, and a front structure for supporting the grilles on which is fixed a front end of the plurality of deflection grilles,the reverser also comprising an actuator for moving the mobile structure in translation relative to the fixed structure along the longitudinal central axis of the reverser, between an advanced direct thrust position and a retracted thrust reversal position, the propulsion assembly further comprising an actuator support device.
[0009] According to the invention, the actuator support device comprises a first connection part for its connection to a support structure, a second connection part for its connection to a body of the actuator, as well as a central part running axially upstream from the first connection part towards the second connection part, extending at least partly radially inwards relative to the actuator.
[0010] The invention provides an optimized solution for the installation of the actuator and its support device, by adapting to the small space available in the dedicated area. Indeed, the support device travels upstream under the actuator, from the first connection part on the support structure which is preferably the deflection edge and / or an outer shell of the intermediate casing, which constitute appropriate connection points of the engine structure to transfer the forces coming from the actuator.
[0011] Furthermore, when such an intermediate casing shroud is provided, which constitutes a preferred solution of the invention but remains optional, the proposed solution makes it possible to separate the actuator and its support device from the parts of the fan casing subject to deformation in the event of accidental situations of the FBO type.
[0012] The invention preferably provides at least one of the following optional technical features, taken alone or in combination.
[0013] Preferably, as mentioned above, said support structure is the deflection edge and / or an outer shell of the intermediate casing fixed to the fan casing and extending the latter downstream. Obviously, in the case where the support structure is formed only from the deflection edge, the outer shell of the intermediate casing remains only optional within the design of the propulsion unit, the deflection edge can in fact be directly fixed on the fan casing by extending the latter downstream.
[0014] Preferably, when such an outer intermediate casing ferrule is provided, the actuator support device extends at least partly between this outer intermediate casing ferrule and the actuator.
[0015] Preferably, the actuator support device forms a guide means for the grid assembly.
[0016] Thus, this preferred embodiment of the invention advantageously provides for using the actuator support device to fulfill an additional function, namely that of guiding the assembly of grids during its movement between the forward direct thrust position and the retracted thrust reversal position. Attributing several functions to the actuator support device responds in an even more relevant manner to the problem raised above, in relation to the small space available between the engine structure and the fan cowls.
[0017] Preferably, the central portion of the actuator support device has an axially extending beam shape.
[0018] Preferably, the propulsion assembly comprises at least one support member for the actuator support device, connecting the latter to the fan casing, each support member preferably taking the form of a connecting rod. Nevertheless, the actuator support device may remain cantilevered upstream, without the use of a support member. In this regard, it is noted that the support member may be configured to produce support either during normal operation of the propulsion assembly, including in direct jet and / or in reverse jet, or only in reverse jet, or only during abnormal operation of the propulsion assembly, for example in an FBO (Fan Blade Out) situation, following a loss of fan blade.
[0019] Preferably, the second connecting part is arranged around the fan casing, close to a junction between this fan casing and the outer shell of the intermediate casing.
[0020] According to a first preferred embodiment, the guide means comprises an axial guide track formed on a radially external surface of the central part of the actuator support device, the guide track cooperating with a complementary axial guide track provided on the set of grids.
[0021] Preferably, the complementary axial guide track is formed on a radially internal surface of an inter-grid axial element arranged between two grids of the set of grids, this inter-grid axial element preferably taking the form of an axial sleeve internally housing at least part of the actuator.
[0022] According to a second preferred embodiment, the guide means comprises an axial guide light crossed by a sliding bridge, connecting two adjacent angular sectors of the front structure supporting the grids, these two adjacent angular sectors being arranged on either side of the actuator in a circumferential direction of the propulsion assembly.
[0023] According to a third preferred embodiment, the guide means comprises two axial guide rails, cooperating respectively with two complementary sliding members, respectively secured to two adjacent angular sectors of the front structure supporting the grids, these two adjacent angular sectors being arranged on either side of the actuator in the circumferential direction of the propulsion assembly.
[0024] Preferably, in the second and third preferred embodiments, the propulsion assembly comprises at least one fixed fan cowl support member, carried by the actuator support device and projecting radially outwards relative to the assembly of grids.
[0025] Preferably, the second connecting portion of the actuator support device cooperates with a rear end portion of the actuator body, preferably via a cardan connection.
[0026] Other advantages and characteristics of the invention will appear in the detailed non-limiting description below. Brief description of the drawings
[0027] The following detailed description refers to the attached drawings in which:
[0028] [Fig-1] is a schematic half-view in longitudinal section of an assembly propulsion, comprising a thrust reverser shown in direct thrust configuration;
[0029] [Fig.2] is a schematic half-view in longitudinal section of the propulsion unit shown in [Fig.l], with the reverser shown in the thrust reverser configuration;
[0030] [Fig.3] is an exploded perspective view of part of the nacelle of the assembly propulsive shown in the preceding figures, showing in particular the elements of the thrust reverser;
[0031] [Fig.4] is an axial view of the rear support structures of the grids shown in the previous figure;
[0032] [Fig.5] is a partial perspective view, in more detail, of a part of the inverter shown in the previous figures;
[0033] [Fig.6] is a partial perspective view, in more detail, of a front part of the nacelle shown in the preceding figures, with a single fan cowl shown;
[0034] [Fig.7] is a schematic half-view in longitudinal section of a front part of the propulsion unit shown in [Fig.l], in more detail and according to a first preferred embodiment of the invention, and still with the reverser in direct thrust configuration;
[0035] [Fig.8] is a schematic half-view in longitudinal section of a front part of the propulsion assembly shown in [Fig.7], with the reverser in thrust reverser configuration;
[0036] [Fig.9A] is a side view of the reverser equipping the forward portion shown in Figures 7 and 8, shown in the direct thrust configuration;
[0037] [Fig.9B] is a sectional view taken along line IXB-IXB of [Fig.9A];
[0038] [Fig.9C] is a perspective view of a portion of the inverter shown in the figures 7 to 9B;
[0039] [Fig. 10] is a side view similar to that of [Fig.9A], with the reverser in the rearward thrust reverser configuration;
[0040] [Fig. 11] is a schematic half-view in longitudinal section of a front part of the propulsion unit shown in [Fig.l], in more detail and according to a second preferred embodiment of the invention, and still with the reverser in direct thrust configuration;
[0041] [Fig. 12] is a schematic half-view in longitudinal section of a forward portion of the propulsion assembly shown in [Fig.12], with the reverser in the thrust reverser configuration;
[0042] [Fig. 13A] is a side view of the reverser equipping the forward portion shown in Figures 11 and 12, shown in the direct thrust configuration;
[0043] [Fig. 13B] is a sectional view taken along line XIIIB-XIIIB of [Fig. 13A]
[0044] [Fig. 13C] is a perspective view of a portion of the inverter shown in the Figures 11 to 13B;
[0045] [Fig.14] is a side view similar to that of [Fig.13A], with the reverser in the rearward thrust reverser configuration;
[0046] [Fig.15] is a side view similar to that of [Fig.14], showing only the inverter grid assembly;
[0047] [Fig. 16] is a schematic half-view in longitudinal section of a front part of the propulsion unit shown in [Fig.l], in more detail and according to a third preferred embodiment of the invention, and still with the reverser in direct thrust configuration;
[0048] [Fig. 17] is a schematic half-view in longitudinal section of a front part of the propulsion assembly shown in [Fig.16], with the reverser in thrust reverser configuration;
[0049] [Fig. 18A] is a side view of the reverser equipping the forward portion shown in Figures 16 and 17, shown in the direct thrust configuration;
[0050] [Fig. 18B] is a sectional view taken along line XVIIIB-XVIIIB of [Fig.l8A];
[0051] [Fig. 18C] is a perspective view of a portion of the reverser shown in Figures 16-18B, with the reverser in the direct thrust configuration;
[0052] [Fig.l9A] is a side view similar to that of [Fig.l8A], with the reverser in the rearward thrust reverser configuration;
[0053] [Fig.l9B] is a perspective view similar to that of [Fig.l8C], with the reverser in the thrust reverser retracted configuration; and
[0054] [Fig.20] is a side view similar to that of [Fig.l9A], showing only the inverter grid assembly. Description of the embodiments
[0055] Figures 1 and 2 show an aircraft propulsion unit 1, having a longitudinal central axis A1.
[0056] Subsequently, the terms “upstream” and “downstream” are defined relative to a general direction SI of flow of the gases through the propulsion unit 1, along the axis A1 when the latter generates thrust. These terms “upstream” and “downstream” could respectively be substituted by the terms “front” and “rear”, with the same meaning.
[0057] The propulsion unit 1 comprises a turbomachine 2, a nacelle 3 as well as a mast (not shown), intended to connect the propulsion unit 1 to a wing (not shown) of the aircraft.
[0058] The turbomachine 2 is in this example a double-flow, double-spool turbojet 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 turbojet engine 2 is provided with a fan casing 11 connected to the gas generator by structural arms 12.
[0059] The nacelle 3 comprises a front section forming an air inlet 13, a middle section which comprises two fan cowls 14 surrounding the fan casing 11, and a rear section 15.
[0060] In operation, an air flow 20 enters the propulsion unit 1 through the air inlet 13, passes through the fan 5 and then divides into a primary flow 20A and a secondary flow 20B. The primary flow 20A flows in a primary gas circulation vein 21A passing through the gas generator. The secondary flow 20B flows in a secondary vein 21B surrounding the gas generator. The secondary vein 21B is delimited radially inwards by a fixed internal fairing which envelops the gas generator. In this example, the fixed internal fairing comprises a first section 17 belonging to the middle section 14, and a second section 18 extending rearwards from the first section 17, so as to form a part of the rear section 15.
[0061] This second section 18 is an integral part of a fixed structure of a thrust reverser which will be described below. This same section will subsequently be called the radially internal delimiting wall 18 of the secondary vein 21B.
[0062] Radially outwardly, the secondary vein 21B is delimited by the fan casing 11, and, in the configuration of [Fig.l], by one or more movable reverser cowls 33 forming a part of the rear section 15 of the nacelle 3, which will be described later. More precisely, between the fan casing 11 and the reverser cowls 33, an outer shroud 40' of an intermediate casing 42' is preferably provided here, the latter comprising the aforementioned structural arms 12, the radially outer end of which is fixed to this shroud 40'. This therefore also participates in delimiting the secondary vein 21B radially outwardly, by being located in the downstream axial extension of the fan casing 11.
[0063] The nacelle 3 therefore comprises a thrust reverser 30 centered on the axis A1 and comprising on the one hand a fixed structure 31, and on the other hand a structure 29 movable relative to the fixed structure 31.
[0064] The fixed structure 31 of the reverser comprises a deflection edge 46' fixedly carried downstream by the outer shell 40' of the intermediate casing, and therefore located in the downstream extension of this shell 40'. Moreover, this shell 40' as well as the fan casing 11 can be considered as forming part of the fixed structure 31 of the reverser. Radially inwards, the fixed structure 31 also comprises the radially internal delimiting wall 18 of the secondary vein 21B. Alternatively, the deflection edge 46' could be carried directly by the downstream end of the fan casing 11, so as to extend the latter axially downstream.
[0065] The mobile structure 29 comprises the aforementioned mobile reverser cowls 33, for example two cowls 33 each extending over an angular amplitude of approximately 180°. This configuration with two cowls 33 is particularly well suited in the case of a nacelle design in which the cowls / walls 18 are also mounted articulated, so that the reverser 30 then has a so-called “D-shaped” architecture, known by the English name “D-Duct”. In this architecture, the cowls 18, 33 are connected so as to open / close simultaneously. during engine maintenance operations. However, other architectures are possible, such as a so-called "C-shaped" architecture, known as "C-Duct", or an "O-shaped" architecture, known as "O-Duct".
[0066] Each reverser cowl 33 comprises a radially external wall 50' forming an external nacelle aerodynamic surface, as well as a radially internal wall 52' participating in the delimitation of the secondary vein 21B radially outwards.
[0067] In addition to the aforementioned reverser cowls 33, the mobile structure 29 comprises at least one set 32' of deflection grids 32, these being arranged adjacently in a circumferential direction of the reverser and the propulsion assembly.
[0068] [Fig.l] shows the reverser 30 in a direct thrust configuration. In this configuration, the two movable cowls 33 and the two sets of grids 32' which are respectively associated with them, are in a closed position, or advanced position, called the advanced direct thrust position of the movable structure 29. In this same position, the grids 32 are housed in a space delimited radially inwards by the deflection edge 46', the outer shroud 40' of the intermediate casing, and possibly by the fan casing 11. This space is also delimited radially outwards by the fan cowls 14. In the direct thrust configuration, the movable structure 29 is in axial support towards the front against the deflection edge 46', which thus makes it possible to channel the secondary flow 20B towards the rear of the propulsion unit 1, so as to generate thrust.
[0069] [Fig. 2] shows the same reverser 30 in a thrust reverser configuration. In this configuration, the movable reverser cowls 33 and the entire movable structure 29 are in an open position, or retracted position, in which the cowls 33 are longitudinally spaced from the deflection edge 46' so as to define a radial opening of the secondary flow path 21B. The grids 32 extend through this radial opening. In this thrust reverser configuration, shutters 34 are deployed radially in the secondary flow path 21B via connecting rods 35, so as to direct the secondary flow 20B towards the grids 32. These make it possible to orient the flow thus redirected towards the front of the propulsion unit 1, in order to generate the desired counter-thrust.
[0070] Thus, in [Fig. 2], the grids 32 and the movable cowls 33 of the movable system 29 are shown in a retracted position, corresponding to the retracted thrust reversal position of the movable structure 29. The latter therefore proves to be movable in translation relative to the fixed structure 31 along the axis A1, between the two positions shown in FIGS. 1 and 2.
[0071] [Fig. 3] represents an exploded perspective view of certain elements of the nacelle 3, including a part of the fixed structure 31 of the reverser 30, which has a general ring shape centered on the axis A1, also corresponding to the longitudinal central axis of the reverser. In this preferred embodiment of the invention, the fixed structure 31 is equipped with elements for guiding the grids 32 during their movement between the advanced and retracted positions, these elements comprising axial rails 40. For example, these are two rails 40 secured to an upper part of the ring, and two other rails 40 secured to a lower part of this same ring. Here, the rails 40 are fixed to the fixed structure 31 by their rear end, while their front end is fixed to another casing (not shown in [Fig. 3]).The rails 40 thus provide, at the circumferential ends of the sets of grids 32', a function of guiding the grids 32 during the axial displacement of the latter, but also, in the thrust reversal configuration, a function of taking up aerodynamic forces, mainly radial and tangential.
[0072] [Fig. 3] schematically represents the grids 32, which follow one another in the circumferential direction 43. Here, they are grouped into two lateral sets each comprising a plurality of grids 32, these two sets being called sets of deflection grids 32'. Alternatively, a single continuous set of grids may be provided, for example by linking the two aforementioned lateral sets at a time position at 6 o'clock or at 12 o'clock.
[0073] Thus, each set of grids 32' comprises several deflection grids 32, and extends over an angular sector close to 180°. The two sets 32' are preferably spaced laterally from each other at their ends facing each other two by two, to provide upper and lower spaces respectively dedicated to the passage of the mast 42 and a lower longitudinal beam 44. Each set of grids 32' also comprises a rear grid support structure 45, on which is fixed a rear end of each of the deflection grids 32 of the set 32', as well as a front grid support structure 45', on which is fixed a front end of each of these deflection grids 32 of the set 32'.The rear and front structures 45, 45' are also referred to as "rear and front grille frames", and they each extend circumferentially along their associated lateral assembly 32', along an identical or similar angular sector as can be seen in [Fig. 4]. The rear end of each grille 32 is therefore intended to be fixed to its associated rear structure 45, by conventional fixing means, just as the front end of each grille 32 is intended to be fixed to its associated front structure 45', still using conventional means.
[0074] As indicated previously, this configuration is particularly well suited in the case of a so-called “D” architecture, preferred for the present invention.
[0075] In a known manner, the fixed structure 31 also comprises members (not shown) forming radial and / or tangential and / or axial stops for the grids 32 of the assemblies 32'.
[0076] In [Fig. 3], the elements of the nacelle 3 are completed by the articulated cowls 18, 33, making it possible to give the “D” architecture to the nacelle. In particular, the pivot axis 48 associated with each reverser cowl 33 has been shown, this pivot axis 48 being parallel or substantially parallel to the axis A1, and allowing the cowl 33 to be movable in rotation between an open maintenance position and a closed flight position, shown in [Fig. 3].
[0077] [Fig. 5] shows in more detail a part of one of the two sets of grids 32'. Preferably, the two sets 32' have an identical or similar design, being symmetrical with respect to a vertical and longitudinal plane passing through the axis A1. Consequently, subsequently, the description which will be given will apply indifferently to each of these two sets 32'.
[0078] The assembly of grids 32' comprises inter-grid axial elements 47, 47' arranged between the grids 32, in the circumferential direction 43 of the nacelle and its reverser 30, and also corresponding to the circumferential direction of the propulsion assembly, in relation to the axis AL. These inter-grid axial elements 47, 47' extend over all or part of the axial length of the assembly 32', and are therefore arranged between the grids 32. With their radially outer surface 49, these elements 47, 47' can form axial sliding tracks for the mobile system 29, as will be detailed below. Furthermore, it may be a question of several kinds of elements, among which first elements 47 ensuring the function of mechanical junction between the grids 32, and second elements 47' fulfilling an additional function of mechanical reinforcement for an actuator 52 of the inverter.The reinforcement 47' may take the form of an axial sheath internally housing at least a portion of the actuator 52, the purpose of which is to move the mobile structure 29 between its forward direct thrust position and its retracted thrust reversal position. Other forms of reinforcement elements may nevertheless be envisaged, without departing from the scope of the invention. Furthermore, it is noted that in a known manner, the rear end of the actuators 52 is intended to be fixed to the rear support structure 45, using dedicated fixing members.
[0079] Referring now to [Fig. 6], one of the two fan cowls 14 is shown which here has the particularity of being pivotally mounted between an open maintenance position, and a closed flight position shown in this [Fig. 6]. The pivoting mounting is achieved using hinges 54 spaced axially from each other, and which jointly define a pivot axis 56 of the cowl 14. This axis 56 is parallel to the axis A1, or substantially parallel to the latter. A symmetrical mounting is provided for the second pivoting fan cowl (not shown in [Fig.6]). However, a solution with fixed fan cowls is also covered by the present invention.
[0080] The direct thrust configuration is also shown in Figures 7 and 9A, 9B and 9C, while the rearward thrust reversal position of the mobile structure 29 is also shown in Figures 8 and 10. All of these Figures 7 to 10 represent a first preferred embodiment of the invention.
[0081] In [Fig. 8], it is shown that the rear grid support structure 45, located directly upstream of the reverser cowl (not shown), reveals upstream a passage opening 56' in the secondary flow path 21B, towards the deflection grids 32. The opening 56' is therefore also delimited upstream by the deflection edge 46', which flares radially outwards going towards the rear, to delimit an air flow intended to pass through the plurality of grids 32 when the mobile system 29 is in this rearward thrust reversal position. In other words, the deflection edge 46' gradually moves away from the axis A1 going from the front to the rear, to guide / deflect the air towards the plurality of grids 32 in the thrust reversal configuration.
[0082] Several actuators 52 may be associated with each set of grids 32', but only one of them is visible in Figures 7, 8 and 9C, while two actuators 52 are visible in Figures 9A, 9B and 10.
[0083] One of the particularities of the invention lies in the fact that an actuator support device 58 is associated with each actuator 52. Only one of these actuator support devices will be described below, in association with its actuator 52, it being understood that all these support devices 58 have an identical or similar design.
[0084] The actuator support device 58 comprises at its downstream end a first connection part 60a for its connection to the deflection edge 46', into which this part 60a can also be integrated. According to alternatives not shown, the first connection part 60a could be fixed to the outer ferrule 40', preferably in a downstream part thereof, or at the interface between the outer ferrule 40' and the deflection edge 46'. In all cases, these elements 40' and / or 46' form a support structure for the first connection part 60a of the actuator support device 58.
[0085] The device 58 also comprises at its upstream end a second connection part 60b for its connection to a body 52a of the actuator 52, corresponding for example to the cylinder in the case of a jack. As can be seen in the figures, the second connection part 60b cooperates with a rear end portion of the body 52a of the actuator 52. This second connection part connection 60b is arranged around the fan casing 11, near a flange joining this casing 11 with the outer shell 40' of the intermediate casing. This allows the support device 58 and its associated actuator 52 to remain axially spaced, downstream, from a more central zone of the fan casing 11, subject to deformation in the event of an FBO type event on the fan. In this regard, it is noted that the second connection part 60b cooperates with the rear end portion of the body 52a via a cardan connection 62.
[0086] Furthermore, a central portion 60c of the actuator support device 58, in the form of an axial beam, runs upstream from the first connection portion 60a to the second connection portion 60b. It is moreover the entire actuator support device 58 which is in the general form of an axial beam, extending parallel or substantially parallel to the axis A1.
[0087] In the radial direction relative to the axis A1, the central portion 60c extends at least in part, and preferably in its entirety, between the outer ferrule 40' and the actuator 58. The beam 60c therefore runs along these elements 40', 58, having an axial length greater than that of the ferrule 40' around which it is located.
[0088] This beam 60c could be cantilevered upstream from the first connecting part 60a, but in this first preferred embodiment of the invention, one or more support members in the form of connecting rods 64 are attached to the second connecting part 60b. They preferably cooperate with the downstream flange of the fan casing 11, or with a connecting member secured to this casing and located close to this downstream flange.
[0089] According to another feature of the invention, the actuator support device 58 forms a guide means for the set of grids 32', the rear frame 45 of which is connected to the actuator 52 supported by this same device 58.
[0090] In the first preferred embodiment of the invention, the guide means comprises an axial guide track 66 formed on a radially external surface of the central part 60c of the support device 58. This track 66 cooperates with a complementary axial guide track 66a provided on the set of grids 32' which it guides. More precisely, the complementary track 66a is formed on a radially internal surface of the inter-grid axial element 47' crossed by the actuator 52, and on either side of which are arranged two grids 32 of the set of grids 32'.
[0091] As best seen in Figures 7 and 9A, in the forward forward thrust position of the grid assembly 32', the track 66 of the support device 58 supports all or almost all of the inter-grid axial element 47'. In contrast, in the rearward reverse thrust position shown in [Fig.8], only a rearward end of the track 66 cooperates with a forward end of the rearward complementary track 66a.
[0092] In this first preferred embodiment, the front grid support frame 45' can thus remain continuous along the circumferential direction 43, all along the assembly 32' to which it belongs.
[0093] According to a second preferred embodiment shown in Figures 11 to 15, the guide means comprises an axial guide light 68, which preferably extends over the entire length of the central part 60c of the support device 58, or over substantially all of this part. The light 68 opens circumferentially on either side of the beam 60c, respectively on the sides of the two adjacent angular sectors 45'a of the front frame 45' supporting the grids. These two angular sectors 45'a are those which are located respectively on either side of the actuator 52 in the circumferential direction 43, and they are connected to each other by a sliding bridge 70 housed movably in the light 68, in the axial direction.
[0094] The other characteristics of the second embodiment are identical or similar to those of the first embodiment, and in the figures, the elements which bear the same numerical references correspond to identical or similar elements.
[0095] In this second preferred embodiment, the proposed design has the advantage of arranging one or more fixed members 72 for supporting the fan cowl 14, visible in [Fig. 13B]. Each support member 72 is carried by the actuator support device 58, for example by its central beam 60b, and it passes through a space between one of the front frame angular sectors 45'a and the actuator 52. In this way, it can project radially outwards relative to the set of grids 32', until it forms a fixed radial support for the opposite fan cowl 14. During the movement of the mobile structure 29, the set of grids 32' therefore moves relative to these support members 72, remaining fixed.
[0096] A third preferred embodiment of the invention, similar to the second, is shown in Figures 16 to 20. In this second embodiment, the guide means comprises two axial guide rails 74, each of which preferably extends over the entire length of the central portion 60c of the support device 58, or over substantially all of this portion. The two rails 74 are respectively arranged on two circumferentially opposite flanks of the central portion 60c. In the representation of figures 16 to 18B, 19A and 20, the rails 74 have a hollow / channel each receiving a sliding member of complementary shape 76. In another embodiment shown in figures 18C and 19B, the hollow / channel is no longer on the rails 74, but conversely on the sliding members of complementary shape 76, integral with the circumferential ends of the angular sectors of the front support frame 45'.
[0097] Indeed, whatever their embodiment, the two sliding members 76 are respectively integral with the two adjacent angular sectors 45'a of the front frame 45', namely those arranged on either side of the actuator 52 in the direction circumferential 43.
[0098] In this third preferred embodiment, the adjacent angular sectors 45'a of the front frame 45' are therefore independent of each other, and they connect several grids 32 of the assembly 32' to each other.
[0099] Here too, it is possible to arrange one or more fixed members 72 for supporting the fan cowl 14, visible in [Fig. 18B]. Each support member 72 is carried by the actuator support device 58, for example by its central beam 60b, and it passes through a space between one of the independent angular sectors 45'a, and the actuator 52.
[0100] Various modifications may be made by those skilled in the art to the invention which has just been described, solely by way of non-limiting examples, and the scope of which is defined by the appended claims. For example, the thrust reverser 30 may alternatively have a “C” or “O” architecture. Furthermore, all the embodiments described above are combinable, and their characteristics interchangeable.
Claims
Claims
1. Propulsion assembly (1) for an aircraft equipped with a turbomachine (2) and a nacelle (3) comprising a thrust reverser (30), the turbomachine comprising a fan casing (11) extending around a longitudinal central axis (A1) of the propulsion assembly, and also comprising a fixed structure (31) equipped with a deflection edge (46'), the reverser also comprising a mobile structure (29) comprising a reverser cowl (33) and a set of deflection grilles (32'), the set of grilles (32') comprising a plurality of deflection grilles (32) as well as a rear structure (45) for supporting the grilles on which is fixed a rear end of the plurality of deflection grilles (32), and a front structure (45') for supporting the grilles on which is fixed a front end of the plurality of deflection grilles (32),the reverser (30) also comprising an actuator (52) for moving the movable structure (29) in translation relative to the fixed structure (31) along the longitudinal central axis (A1) of the reverser, between an advanced direct thrust position and a retracted thrust reversal position, the propulsion assembly further comprising an actuator support device, characterized in that the actuator support device (58) comprises a first connection part (60a) for its connection to a support structure (40', 46') arranged downstream of the fan casing, a second connection part (60b) for its connection to a body (52a) of the actuator (52), as well as a central part (60c) running axially upstream from the first connection part (60a) towards the second connection part (60b), extending at least partly radially inwards relative to the actuator (52),and in that the actuator support device (58) forms a guide means (66, 68, 74) for the grid assembly (32').,
2. Propulsion assembly according to claim 1, characterized in that said support structure (40', 46') is the deflection edge (46') and / or an outer shroud (40') of the intermediate casing fixed to the fan casing (11) and extending the latter downstream.
3. Propulsion assembly according to claim 2, characterized in that the actuator support device (58) extends at least partly between the outer shell (40') of the intermediate casing and the actuator (52).
4. Propulsion assembly according to any one of the preceding claims, characterized in that the guide means comprises an axial guide track (66) formed on a radially external surface of the central part (60c) of the actuator support device (58), the guide track (66) cooperating with a complementary axial guide track (66a) provided on the grid assembly (32').
5. Propulsion assembly according to claim 4, characterized in that the complementary axial guide track (66a) is formed on a radially internal surface of an inter-grid axial element (47') arranged between two grids (32) of the set of grids (32'), this inter-grid axial element (47') preferably taking the form of an axial sheath internally housing at least part of the actuator (52).
6. Propulsion assembly according to any one of the preceding claims, characterized in that the guide means comprises an axial guide light (68) crossed by a sliding bridge (70), connecting two adjacent angular sectors (45'a) of the front structure (45') supporting the grids, these two adjacent angular sectors (45'a) being arranged on either side of the actuator (52) in a circumferential direction (43) of the propulsion assembly.
7. Propulsion assembly according to any one of the preceding claims, characterized in that the guide means comprises two axial guide rails (74), cooperating respectively with two complementary sliding members (76), respectively secured to two adjacent angular sectors (45'a) of the front structure (45') supporting the grids, these two adjacent angular sectors (45'a) being arranged on either side of the actuator (52) in the circumferential direction (43) of the propulsion assembly.
8. Propulsion assembly according to any one of the preceding claims, characterized in that it comprises at least one member (64) for supporting the actuator support device (58), connecting the latter to the fan casing (11), each support member (64) preferably taking the form of a connecting rod.
9. Propulsion assembly according to any one of the preceding claims, characterized in that the second connection part (60b) of the actuator support device (58) cooperates with a rear end portion of the body (52a) of the actuator, preferably via a cardan connection (62).