Nacelle for a propulsion assembly with a high bypass ratio comprising a removable and structural front inner structure

Abstract

The invention relates to a nacelle for a propulsion assembly, said nacelle comprising a front internal structure (14) having a frame formed by longitudinal beams (20) and comprising removable, detachable or retractable wall panels (21) arranged to facilitate access to the components of the engine covered by these wall panels (21) for maintenance.

Description

Technical Field

[0001] This invention relates to the field of cabins for ducted propulsion components of aircraft, and more particularly to the internal streamlined structure of such cabins.

[0002] This invention is particularly concerned with the architecture of propulsion components with ultra-high bypass ratios, i.e., the ratio between the secondary flow rate and the mainstream flow rate can be as high as or exceed 15. Background Technology

[0003] Referring to Figure 1, a conventional ducted propulsion assembly includes a gas generator 1 extending about a longitudinal central axis A1. Relative to the direction D1 of the airflow and gas within the propulsion assembly, the propulsion assembly at its front includes: a hub 2 fixed to the gas generator 1; an external fan housing 3 concentric with the hub 2; and a radial arm 4 connecting the hub 2 and the external housing 3 to each other. The hub 2 and the external housing 3 radially define a first portion 5A (referred to as a "secondary duct") of an annular channel 5 between the hub 2 and the external housing 3, the first portion of which is designed to deliver a flow of cool air (referred to as a "secondary flow") to the rear of the propulsion assembly.

[0004] The gas generator 1 is streamlined by a front internal structure 6 and a rear internal structure 8, the front internal structure typically comprising a panel fixed to the inner housing 7 and / or hub 2 with screws, and the rear internal structure known by the term "fixed internal structure". In the flight position, the front internal structure 6 and the rear internal structure 8 radially inwardly define corresponding longitudinal portions of the second part 5B of the annular channel 5.

[0005] The rear internal structure 8 is typically manufactured in the form of two half-parts that are able to open in a “butterfly” shape (i.e., each half-part moves about a corresponding pivot axis that is generally parallel to the longitudinal central axis A1) so that the maintenance operator can access the components of the gas generator 1 that are not covered by it.

[0006] As is customary, the propulsion assembly in Figure 1 first includes a turbine engine (or engine) comprising a gas generator 1, a hub 2, an outer casing 3, radial arms 4, and a front internal structure 6, and secondly includes a nacelle comprising a rear internal structure 8.

[0007] The panels of the front internal structure 6 are typically removed only when the engine is removed, i.e., when the engine is disconnected from the nacelle.

[0008] To increase the bypass ratio of such propulsion components and achieve a bypass ratio close to 15, architectures such as those shown in Figure 2 are currently being developed. Compared to Figure 1, the outer housing 3 extends rearward, the rear internal structure 8 is shortened so that the rear internal structure can open in a butterfly shape and the front end of the rear internal structure does not abut against the outer housing 3, and the front internal structure 6 extends proportionally rearward.

[0009] In this architecture with an ultra-high bypass ratio, the dimensions of the forward internal structure 6 require it to be supported by sufficiently robust abutment elements. This is especially true when high loads are easily transmitted through the forward internal structure 6, particularly when the nacelle includes a thrust reverser with enclosed flaps that deploy in annular channel 5 under the action of a linkage connected to the forward internal structure 6, or to an element fixed to the forward internal structure 6.

[0010] This abutment element (which is typically formed by a component permanently fixed to the engine) can easily obstruct access to the engine when the front internal structure 6 is removed.

[0011] Furthermore, the size of this front internal structure 6 results in the possibility that it may be necessary to remove the front internal structure during routine maintenance operations without removing the engine, and many of the engine's components can be arranged at the rear of the internal housing 7, below the front internal structure 6.

[0012] Due to the typical geometry of the abutment element and the size of this front internal structure 6, the front internal structure is typically fixed to the abutment element with a large number of screws.

[0013] As a result, the time required to disassemble the front internal structure 6 is unacceptable, considering the time that is typically available for certain routine maintenance operations. Summary of the Invention

[0014] One object of the present invention is to obtain a nacelle that is easily accessible to the engine and its equipment for maintenance of the engine and its equipment, particularly but not limited to the propulsion components, wherein the external fan housing extends rearward in a cantilever manner, as shown in FIG2.

[0015] Another object of the present invention is to obtain a cabin with a forward internal structure that realizes structural functions (e.g., to withstand loads generated by the actuation of a thrust reverser).

[0016] More generally, the present invention relates to obtaining a nacelle that enables the mitigation of deficiencies associated with new architectures of propulsion components with ultra-high bypass ratios, wherein the nacelle includes or does not include a thrust reverser having a completely conventional architecture, such as having a fixed or movable grille and / or having a sliding, integral external fairing (O-shaped architecture), having an external fairing with butterfly openings in the form of two half-parts integrated with two corresponding half-parts of a fixed internal structure (D-shaped architecture), or having an external fairing with butterfly openings in the form of two half-parts independent of the fixed internal structure (C-shaped architecture).

[0017] Therefore, the object of the present invention is a cabin for an aircraft ducted propulsion assembly, the cabin comprising an external structure and a rear internal structure extending about a longitudinal central axis, the rear internal structure being movable between two positions:

[0018] - In the flight position, the rear internal structure radially inward defines a first longitudinal portion of an annular passage, the first longitudinal portion of which is designed to guide secondary flow in the propulsion assembly, and the rear internal structure covers a first longitudinal portion of the internal space, the first longitudinal portion of which is designed to receive the engine of the propulsion assembly, and

[0019] - Maintenance position, in which the rear internal structure is configured to expose at least a portion of the first longitudinal portion of the interior space, so that an operator can access the interior space.

[0020] According to the invention, the cabin includes a forward interior structure comprising beams and one or more wall panels, the beams extending longitudinally and spaced apart from each other circumferentially relative to a longitudinal central axis, and the one or more wall panels being arranged in such a manner as follows:

[0021] - Closed configuration, in which the wall panels and beams cooperate to define a second longitudinal portion of the annular passage radially inward, and to cover a corresponding circumferential portion of the second longitudinal portion of the interior space.

[0022] - Maintenance configuration, in which the wall panels leave circumferential space between the beams so that the operator can access the second longitudinal section of the interior space.

[0023] The beams extend longitudinally, which allows for the firm support of one or more wall panels in a closed configuration, while also facilitating access to the engine due to the circumferential space between the beams when one or more wall panels are arranged in a maintenance configuration.

[0024] Furthermore, this arrangement of beams allows one or more wall panels to be held in a closed configuration by reducing the number of fixing members, which reduces the time required to arrange one or more wall panels in a maintenance configuration.

[0025] Therefore, the forward interior structure of the nacelle facilitates access to the engine, and in particular, provides structural functionality compatible with combining thrust reversers with conventional grilles.

[0026] In one embodiment, the front internal structure includes a rear end portion configured to engage with the front end portion of the rear internal structure when the front internal structure is in a closed configuration and the rear internal structure is in a flight position.

[0027] Preferably, the rear end of the front internal structure may be formed by one or more of the beams.

[0028] In one embodiment, the rear end of the front internal structure engages with the front end of the rear internal structure to transfer axial force from the rear internal structure to the front internal structure.

[0029] In one embodiment, the beams of the front internal structure are configured to be connected to the engine frame, preferably via the front ends of these beams.

[0030] For example, in this embodiment, the frame to which the beam is connected may be the rear hub of the engine's fan module.

[0031] In this embodiment, the engine compartment may include support links, each of which is connected at a first end to a middle or rear portion of a corresponding beam in the beam, and each of the support links is configured to be connected at a second end to the frame of the engine.

[0032] In particular, this support linkage makes it possible to manufacture thinner and lighter beams and to best distribute the load borne by the beams.

[0033] According to a first variant embodiment, at least one of the wall panels is pivotally connected to one or more of the beams, thereby enabling the wall panel to move between a closed configuration and a maintenance configuration.

[0034] According to a second variant embodiment, at least one of the wall panels is configured to be pivotally connected to the engine frame, thereby enabling the wall panel to move between a closed configuration and a maintenance configuration.

[0035] These variations can be combined. For example, according to the first variation, one or more wall panels can be connected to one or more beams in the beam, and according to the second variation, one or more other wall panels can be connected to the engine frame.

[0036] In one embodiment, at least one of the wall panels is pivotally connected to a rear interior structure, the rear interior structure including a front portion having a cutout such that when the rear interior structure is in the flight position and the wall panel is in the closed position, the front portion of the rear interior structure forms a first circumferential segment, and the at least one wall panel connected to the rear interior structure forms a second circumferential segment, the first and second circumferential segments each radially defining a corresponding segment of the second longitudinal portion of the annular passage.

[0037] This allows for limiting the number of beams in the forward internal structure and reduces the weight of the cabin.

[0038] In one embodiment, the nacelle includes a thrust reverser with flaps, the external structure being movable between an forward (avancée) position and a retracted position, and the nacelle includes a linkage connected at a first end to a corresponding beam in the forward internal structure and at a second end to a corresponding flap in the flaps, such that the flaps deploy in an annular channel when the external structure moves from the forward position to the retracted position.

[0039] Another object of the present invention is an aircraft ducted propulsion assembly that includes an engine and a cabin as defined above.

[0040] In one embodiment, the engine includes a hub, an outer housing, and one or more radial arms connecting the hub and the outer housing to each other. The outer housing extends longitudinally at a rear portion relative to a front portion of the front interior structure, such that it defines the annular channel on a portion of the second longitudinal portion, radially inward through one or more panels of the front interior structure and radially outward through the outer housing.

[0041] Another object of the present invention is an aircraft that includes such a propulsion assembly.

[0042] Other advantages and features of the invention will become apparent from the following detailed, non-limiting description. Attached Figure Description

[0043] The following detailed description is with reference to the attached diagram, in which:

[0044] [Figure 1] is a partial schematic half-view of a prior art aircraft propulsion assembly that typically enables a bypass ratio between 9 and 11;

[0045] [Figure 2] is a partial schematic half-view of a prior art aircraft propulsion assembly that typically enables a bypass ratio close to 15;

[0046] [ Figure 3 [Illustration 1] is a partial schematic half-view of an aircraft propulsion assembly according to the present invention, the propulsion assembly including a nacelle equipped with a C-shaped thrust reverser;

[0047] [ Figure 4 [This is similar to the invention] Figure 3 A partial schematic perspective view of the aircraft propulsion assembly, the cabin including the forward interior structure and the rear interior structure. The figure shows half of the forward interior structure in the closed configuration and the rear interior structure in the flight position.

[0048] [ Figure 5 ]yes Figure 4 A partial schematic perspective view of the propulsion assembly, showing the half-part of the rear internal structure in a maintenance position and the half-part of the external structure of the cabin in a maintenance position.

[0049] [ Figure 6 [This is based on the first embodiment] Figure 4 A schematic perspective view of the front internal structure frame, which includes longitudinal beams of the first type fixed to the frame;

[0050] [ Figure 7 ]yes Figure 4 A partial schematic perspective view of the front interior structure, showing that the wall panels of the front interior structure are disconnected from the beams of the front interior structure;

[0051] [ Figure 8 [Illustrated perspective view of a frame of the front internal structure according to a second embodiment, the frame including longitudinal beams fixed to the frame and connecting rods for absorbing circumferential forces;]

[0052] [ Figure 9 [Illustration] is a schematic diagram of a beam of the second type used for the front internal structure according to the invention;

[0053] [ Figure 10 [Illustration] is a schematic diagram of a beam of the third type used for the front internal structure according to the invention;

[0054] [ Figure 11 ]yes Figure 4 A schematic perspective view of the wall panels of the front internal structure;

[0055] [ Figure 12 ]yes Figure 11 A schematic diagram of the front positioning component of the wall panel;

[0056] [ Figure 13 [Is based on the first type used for] Figure 11A schematic diagram of the rear positioning components of the wall panel;

[0057] [ Figure 14 [This is based on the second type used for] Figure 11 A schematic diagram of the rear positioning components of the wall panel;

[0058] [ Figure 15 [Illustration] is a partial schematic perspective view of the front internal structure according to the invention, showing stop members of the first type for holding the wall panels and beams of the front internal structure, the wall panels and beams abutting each other radially;

[0059] [ Figure 16 [Illustration] is a partial schematic perspective view of the front internal structure according to the invention, showing a stop member of the second type for holding the wall panel and the beam of the front internal structure, the wall panel and the beam abutting each other radially;

[0060] [ Figure 17 [Illustration 1] is a partial schematic diagram of the cabin according to the present invention, showing a first type of connection mechanism between the front internal structure and the rear internal structure of the cabin;

[0061] [ Figure 18 [Illustration 1] is a partial schematic diagram of the cabin according to the present invention, which shows a second type of connection mechanism between the front internal structure and the rear internal structure of the cabin;

[0062] [ Figure 19 [Illustration] is a partial schematic perspective view of the front internal structure according to the invention, the beam of which includes a chape for a connecting rod for a hinged thrust reverser;

[0063] [ Figure 20 [Illustration 1] is a partial schematic diagram of the front internal structure according to the present invention, which includes a wall panel hinged to the nacelle frame;

[0064] [ Figure 21 [Illustrated perspective view of a cabin according to the present invention, wherein the front interior structure of the cabin is accommodated in an opening created by the rear interior structure of the cabin;]

[0065] [ Figure 22 [Illustrated perspective view of a partial cabin according to the present invention, wherein the front internal structure is hinged to the rear internal structure of the cabin.] Detailed Implementation

[0066] Figure 3 and Figure 4 Two similar examples of the ducted propulsion assembly 10 according to the present invention are shown.

[0067] The propulsion assembly 10 includes, firstly, a nacelle, and secondly, a turbine engine (also referred to as the "engine" in this specification).

[0068] In this example, the engine is a twin-shaft ducted turbojet engine.

[0069] In the following text, the terms “upstream,” “downstream,” “front,” and “rear” are defined relative to the direction D1 of the airflow and gas flow through the propulsion assembly when the propulsion assembly 10 is propelled.

[0070] The engine has a longitudinal central axis A1 around which various components of the engine extend, particularly a fan (not shown) at the front and a gas generator 1 at the rear. In a manner known per se, the gas generator 1 includes, from front to rear, a low-pressure compressor, a high-pressure compressor, a combustion chamber, a high-pressure turbine, and a low-pressure turbine.

[0071] When the engine is running, airflow enters the propulsion assembly 10 through the air intake 11 located at the front of the propulsion assembly 10, passes through the fan (not visible), and then splits into a central main flow and a secondary flow. The main flow flows in the main duct, which is used for the flow of gas through the gas generator 1. The secondary flow, in itself, flows in an annular channel 5 (referred to as the secondary duct), which surrounds the gas generator 1.

[0072] Reference Figure 3 The engine includes a hub 2 and an outer housing 3. The hub is fixed to a gas generator 1, and the outer housing is concentric with the hub 2. The outer housing 3 includes a front portion (not shown) and a rear portion. The front portion surrounds a fan, and the rear portion is connected to the hub 2 via a radial arm 4. The hub 2 and the outer housing 3 radially define a first portion 5A of a secondary conduit 5 between the hub and the outer housing.

[0073] In this example, the outer housing 3 extends rearward in a cantilever manner relative to the hub 2, and the rear end of the outer housing 3 extends longitudinally rearward relative to the hub 2. To improve the structural strength of the outer housing 3 relative to the hub 2, the radial arm 4 has a longitudinal inclination.

[0074] Still refer to Figure 3 The cabin includes an external structure 12, which contains a movable grid-type thrust reverser 13.

[0075] The cabin also includes an internal structure that radially inwardly defines a second portion 5B of the secondary conduit 5, which is first defined by the rear portion of the external collar 3 and then by the external structure 12 of the cabin radially outward.

[0076] The internal structure includes a front internal structure 14 and a rear internal structure 15.

[0077] In this example, the rear internal structure 15 is made into two half-parts symmetrical about a longitudinal mid-plane that passes through the longitudinal central axis A1 and through the strut 16 of the propulsion assembly 10. More precisely, each half-part of the rear internal structure 15 includes a circumferential end pivotally connected to the strut 16, allowing these half-parts to move about a corresponding pivot axis that is substantially parallel to the longitudinal central axis A1.

[0078] The single half of the rear internal structure 15 is in Figure 4 and Figure 5 As shown in, Figure 3 The half-part shown is in the closed or flying position. Figure 4 The half-part shown is in the open or maintenance position.

[0079] Therefore, the rear internal structure 15 typically has a butterfly-shaped opening.

[0080] When each half of the rear internal structure 15 is in the flight position ( Figure 3 When in flight, the rear internal structure 15 radially inward defines the first longitudinal portion or rear longitudinal portion of the second part 5B of the secondary pipe 5. In the flight position, the rear internal structure 15 radially outward defines the first longitudinal portion or rear longitudinal portion of the internal space in which the gas generator 1 extends.

[0081] In maintenance location ( Figure 4 The rear internal structure 15 exposes at least one circumferential portion of the rear longitudinal portion of the interior space, which allows a maintenance operator to access the interior space to repair the engine.

[0082] exist Figure 5 In the example, the external structure 12 of the cabin includes two half-wall panels 17, of which only one half-wall panel 17 is shown in this figure. The half-wall panel 17 forms an external fairing that can be in a closed position independently of the rear internal structure 15. Figure 3 The cabin moves between the position shown in the diagram and the open position (not shown). Therefore, in this example, the cabin has a C-shaped structure well-known in the art.

[0083] Reference Figure 6 and Figure 7 The front internal structure 14 includes beams 20 and wall panels 21 and 22.

[0084] In this embodiment, each of the beams 20 is connected to a portion of the engine frame 9 via its front end, which in this example corresponds to the rear portion of the hub 2, and are regularly spaced apart from each other circumferentially around the longitudinal central axis A1.

[0085] Each of the fixed beams 20 extends longitudinally, that is, in a direction that is approximately parallel to the longitudinal central axis A1.

[0086] Beam 20 thus forms a frame that is fixed to the engine and is designed to support wall panels 21 and 22 as described below.

[0087] Figure 8 The frame shown is Figure 6 The difference in the framework is that... Figure 8 The frame includes links or supports 23, each link or support connecting two adjacent beams 20 via its rear end. In this example, these supports 23 form annular members that absorb circumferential forces.

[0088] In one embodiment, the bracket 23 is connected to the beam 20 by a detachable fastening device (not shown), allowing the bracket to be quickly removed during maintenance operations.

[0089] exist Figures 6 to 8 In the example, beam 20 is cantilevered, so that the beam is connected to the engine frame 9 only through the front end of the beam.

[0090] In another embodiment, one or more beams of the beams 20 forming the frame of the front internal structure 14 can be based on Figure 9 and Figure 10 The principle shown is stabilized by the support link 24.

[0091] exist Figure 9 In the example shown in the figure, the support link 24 of the single beam 20 is connected to the rear portion of the beam 20 at one end of the support link and to the engine frame 9 at the other end of the support link at a non-zero radial distance X1 from point P1, where the beam 20 is attached to the same frame 9.

[0092] exist Figure 10 In the example shown, the support link 24 of the single beam 20 in the figure is also connected to the rear portion of the beam 20 at one end of the support link. Figure 9 Unlike the example in the example, the support link 24 is sized to connect to a portion of the engine at the other end of the support link, which is located at a non-zero longitudinal distance X2 from the attachment point P1.

[0093] The use of this support link 24 and the selection of the corresponding radial distance X1 or longitudinal distance X2 depend particularly on the available space.

[0094] Reference Figure 6 and Figure 7In this example, the wall panel 22 is designed to extend on both sides of the support column 16 of the propulsion assembly 10 and is fixed, for example, to the beam 20 located circumferentially at the support column 16 by screws.

[0095] Based on the principles described below, panel 21 is, in part, removable, detachable, or retractable.

[0096] This is because panel 21 is designed to move between a so-called closed configuration and a so-called maintenance configuration, in which the panel mates with beam 20 (such as in...). Figure 7 The bottom portion of the wall panel 21 is shown, in the so-called maintenance configuration, the wall panel leaves a circumferential space between the beams 20 (such as in...). Figure 7 The top of the wall panel 21 is shown.

[0097] exist Figure 4 and Figure 5 In the middle, the front internal structure 14 is shown in such a configuration that the wall panels of the structure (similar to...) Figure 7 The wall panel 21) is in a closed configuration.

[0098] In the closed configuration, the wall panel 21 cooperates with the beam 20 to define the second longitudinal portion or the front longitudinal portion of the second part 5B of the secondary pipe 5 radially inward.

[0099] The wall panel 21, which is in a closed configuration, simultaneously covers the corresponding circumferential portion of the second longitudinal portion or the front longitudinal portion of the interior space, in which the gas generator 1 extends.

[0100] Figure 11 The wall panel 21 of the front internal structure 14 is shown.

[0101] The panel 21 includes two longitudinally extending sections 26, and each section has a front end 27, an inner lateral end 28, and an outer lateral end 29.

[0102] The wall panel 21 includes a rear end portion 30, at which two sections 26 are connected to each other.

[0103] The inner lateral ends 28 of the two sections 26 face each other to define a longitudinal opening.

[0104] Reference Figure 4 , Figure 7 and Figure 11 This arrangement of the wall panel 21 allows the wall panel to be arranged on the frame formed by the beams 20, such that the longitudinal opening is circumferentially located at one of the beams 20 (referred to as the reference beam), and such that the outer lateral ends 29 of each segment 26 face:

[0105] - The outer lateral end 29 of another adjacent wall panel 21, together with the outer lateral end of the other adjacent wall panel, defines a longitudinal opening, which is circumferentially located at another beam 20 adjacent to the reference beam 20.

[0106] - or a lateral end of one of the fixed wall panels 22, to define a longitudinal opening together with the lateral end of the fixed wall panel, the longitudinal opening being circumferentially located at another beam 20 adjacent to the reference beam 20.

[0107] The front internal structure 14 may include Figure 11 One or more wall panels 21 of the type shown and / or one or more wall panels of another type, the wall panel including, for example, a single segment 26 or three or more segments 26.

[0108] exist Figure 6 In the example, the frame of the front internal structure 14 includes ten beams 20, two of which are designed to be located on either side of the support column 16 of the propulsion assembly 10, and fixed wall panels 22 extend circumferentially from these beams toward the support column 16. Thus, the frame can, for example, accommodate three wall panels with two sections 26 (such as...). Figure 11 The wall panel 21), and a wall panel having three sections 26 (not shown), or receiving four wall panels having two sections 26 (such as... Figure 11 The wall panel 21 in the middle, and the wall panel having a single section 26 (not shown).

[0109] The following description refers to a single wall panel 21 (such as...) Figure 11 (The wall panels in the example), and by analogy applied to any other wall panel, for example, with a different number of segments 26.

[0110] In order to hold the panel 21 on the frame of the front internal structure 14, in this example, one or more front positioning members using the panel 21 are specified.

[0111] Figure 12 A front positioning member 31 is shown, which includes a convex portion and a concave portion. The convex portion includes a pin 32 that is secured to a bracket 33. The concave portion includes a ring 34 that defines a receiving portion configured to receive a portion of the pin 32.

[0112] exist Figure 11 In the example, the convex portions of the two front positioning members 31 are fixed at the front end of each segment 26 in the wall panel 21.

[0113] exist Figure 6In the example, the corresponding concave portion is fixed to beam 20. In this example, each beam 20 carries two rings 34 at its front end, such that when the wall panel 21 is arranged on the frame in a closed configuration, each pin in the pin 32 is received in the receiving portion of the corresponding ring 34.

[0114] In an embodiment not shown, the receiving portion of the concave part of the component 31 is directly manufactured in the beam 20 and / or frame 9 of the engine.

[0115] In this example, the front internal structure 14 also includes a rear positioning member for the wall panel 21.

[0116] Figure 13 A rear positioning member 36 is shown, which includes a screw 37 and a nut 38, designed to hold the wall panel 21 and the beam 20 against each other in a generally longitudinal direction.

[0117] For this purpose, the rear positioning member 36 includes a bracket 39 that is fastened to the rear end 30 of the wall panel 21, and the rear positioning member includes a hole through which a screw 37 can pass. In this example, each beam 20 of the front internal structure 14 includes at least one hole at its rear end, through which a screw 37 can pass. The front internal structure 14 is configured such that when the wall panel 21 is in a closed configuration, the screw 37 can be inserted through the hole created in the bracket 39 and the hole created in the corresponding beam 20, and then assembled with a nut 38, as... Figure 13 As shown.

[0118] exist Figure 11 In the example, preferably, the panel 21 includes at least three rear positioning members 36 of this type, two positioned at the outer lateral ends 29, and the other circumferentially positioned in the middle of the panel 21, i.e., at a distance equidistant from the outer lateral ends 29 of the panel.

[0119] Figure 14 Another example of the rear positioning member 36 is shown, which is related to... Figure 13 The difference in the rear positioning member is that the screw 37 and nut 38 are replaced by a pin 40, which is axially fixed to the bracket 39 and received in the hole of the beam 20. The end of the pin is elastically deformable so that a predetermined force is required to engage the pin 40 in the hole or to pull the pin out of the hole.

[0120] In these examples, the front positioning member 31 and the rear positioning member 36 are used for axial mounting, and when the wall panel 21 is in the closed configuration, pins 32 and 40 and screws 37 extend in a direction generally parallel to the longitudinal central axis A1. In another embodiment, not shown, the front positioning member 31 and the rear positioning member 36, or a portion thereof, are used for radial mounting.

[0121] These front positioning member 31 and rear positioning member 36 improve the positioning retention of the wall panel 21 in a closed configuration, thereby reducing aerodynamic disturbance.

[0122] The front positioning member 31 and the rear positioning member 36 also facilitate and accelerate the installation and removal of the wall panel 21, i.e., the movement of the wall panel between the closed configuration and the maintenance configuration.

[0123] Figure 15 A beam 20 of the front internal structure 14 in the closed configuration is shown. Figure 11 21.

[0124] The beam 20 has radial bars 42 and circumferential bars 43 forming a cross in its cross section. Each end of the circumferential bars 43 has an abutment element 44 that defines an abutment surface that is generally parallel to the radial bars 42. The radially outward ends of the radial bars 42 have ribs 45 that fit flush with the wall panel 21.

[0125] In another embodiment, not shown, the wall panel 21 radially outwards covers the radial rod 42 (which may not have ribs 45) or more generally the beam 20. This allows for aerodynamic disturbance reduction, in particular. Specifically, this embodiment is compatible with nacelles that do not have thrust reversers or have a D- or O-shaped architecture.

[0126] Reference Figure 11 and Figure 15 Each section 26 of the wall panel 21 includes a bracket 50 that carries a seal 51 configured to abut against the contact surfaces of the two beams 20 of the front interior structure 14 when the wall panel 21 is in a closed configuration.

[0127] Figure 15 A stop member 54 is shown, which is configured to improve the retention of the wall panel 21 relative to the beam 20 in a closed configuration.

[0128] The stop member 54 forms a square bracket, a portion of which is connected (e.g., by welding) to one of the brackets 50 of the wall panel 21, and another portion is configured to radially abut against one of the abutment elements 44 of the beam 20 when the wall panel 21 is in a closed configuration.

[0129] Multiple stop members 54 of this type can be installed to retain the wall panel 21.

[0130] exist Figure 15In this example, the portion of the stop member 54 that radially abuts against one of the abutment elements 44 of the beam 40 forms a stop portion that prevents the wall panel 21 from moving relative to the beam 20 in a first radial direction of movement. Furthermore, each segment 26 of the wall panel 21 includes a portion radially located on the other side of the abutment element 44 that prevents or at least restricts the movement of the wall panel 21 relative to the beam 20 in a second radial direction of movement. Therefore, in this example, the wall panel 21 must be mounted on the beam 20 by axial translation, typically from a source similar to... Figure 7 The configuration shown.

[0131] Typically, this stop member 54 tends to limit the deformation of the wall panel 21 under the aerodynamic stresses acting on the wall panel, and, where applicable, prevents the pin 32 of the positioning member 31 from disengaging, which may optionally be equipped with the front internal structure 14.

[0132] This effect can be achieved through alternative or complementary devices, such as using... Figure 16 The stop member 54 is shown.

[0133] Figure 16 The stop member 54 includes: a guide rail 56 fixed to the wall panel 21; and a slider 57 fixed to the beam 20. Alternatively, in another embodiment (not shown), the guide rail 56 may be fixed to the beam 20, and the slider 57 may be fixed to the wall panel 21.

[0134] Typically, the wall panel 21 may include one or more front positioning members 31 (such as... Figure 12 (as shown in the diagram) and / or one or more rear positioning members 36 (such as a front positioning member) and / or a rear positioning member 36. Figure 13 and Figure 14 Those rear positioning members shown) and / or one or more stop members 54 (such as those shown) and / or one or more stop members 54 Figure 15 and Figure 16 (Those stop components shown).

[0135] These different components allow the wall panel 21 to be installed and removed quickly and used in small quantities, while ensuring that the wall panel 21 is satisfactorily retained in a closed configuration.

[0136] exist Figure 11 In the example, each section 26 of the wall panel 21 is equipped with a bucket-shaped or vent-shaped ventilation member 60 that forms an interface designed to seal with a corresponding interface (not shown) of the engine when the wall panel 21 is in a closed configuration.

[0137] also, Figure 11The wall panel 21 includes a square bracket 62, which, when the wall panel 21 is in a closed configuration, is used to absorb circumferential forces that extend around the longitudinal central axis A1.

[0138] Reference Figure 17 In this example, the cabin includes a linkage 65 configured to connect the front interior structure 14 and the rear interior structure 15 when the front interior structure 14 is in a closed configuration and a flight position, respectively.

[0139] Specifically, the front internal structure 14 includes a rear end portion configured to engage with the front end portion of the rear internal structure 15.

[0140] For this purpose, the connecting mechanism 65 first includes a component 66, which is fixed to the rear end of the wall panel 21 (see...). Figure 11 and Figure 17 When the internal structure 14 is in a closed configuration, the component 66 forms a groove 67 that extends circumferentially and opens radially outward. The component 66 also includes an abutment arm 68.

[0141] Furthermore, the connecting mechanism 65 includes a radial arm 70 attached to the front end of the rear internal structure 15. In the flight position, the radial arm 70 engages with a groove 67 in the component 66, enabling the connecting mechanism 65 to transmit axial force from the rear internal structure 15 to the wall panel 21 or more generally to the front internal structure 14.

[0142] The connecting mechanism 65 also includes a seal 71 that is fixed to the rear internal structure 15 and configured to radially abut against the support arm 68 of the component 66 when the rear internal structure 15 is in the flight position.

[0143] Reference Figure 11 In this example, the component 66 of the connecting mechanism 65 extends from one of the outer lateral ends 29 of the wall panel 21 to the other outer lateral end 29 of the wall panel 21.

[0144] The dimensions of the connecting mechanism 65, especially the circumferential dimensions of the component 66, and the number of connecting mechanisms 65 can be adjusted according to stress that easily passes through the rear internal structure 15 to the front internal structure 14.

[0145] exist Figure 18 In the variant shown, beam 20 includes an extension 75 that extends rearward and carries one or more components similar to the aforementioned component 66 to form one or more connecting mechanisms 65 that connect one or more beams of beam 20 in the flight position to the rear internal structure 15 and the front internal structure 14.

[0146] In other words, the rear end of the front internal structure 14 that mates with the front end of the rear internal structure 15 can be formed by one or more beams of the beams 20.

[0147] This variation allows axial forces to be transmitted directly in beam 20 without passing through wall panel 21.

[0148] Reference Figure 3 and Figure 19 In this example, the thrust reverser 13 includes flaps (not shown). In a manner known per se, these flaps are designed to deploy or retract within the secondary conduit 5 under the combined action of the axial translation of the external structure 12 and the link 80.

[0149] In this example, each of the beams 20 of the front internal structure 14 includes a lug 81 to which the end of a corresponding link 80 of the reverser 13 is hinged, and the other end of the link 80 is typically connected to a corresponding flap of the flap of the reverser 13.

[0150] In particular, Figure 19 The embodiments described are compatible with the cabin, which has an O-shaped architecture.

[0151] Figure 20 A variant embodiment is shown in which the wall panel 21 of the front internal structure 14 is hinged to the frame 9 at the front end of the wall panel so that the wall panel can be moved between a closed configuration and a maintenance configuration by rocking.

[0152] In this case, an attachment device (not shown), such as a bolt, may be provided, which is configured to quickly lock the wall panel 21 onto the beam 20 and unlock the wall panel 21 on the beam 20, preferably at its rear end.

[0153] In the various embodiments described above, the front end of the rear internal structure 15 is longitudinally located at the rear relative to the rear end of the engine's outer housing 3. Therefore, when the rear internal structure 15 is moved from the flight position to the maintenance position, the rear internal structure will not collide with the outer housing 3 (see...). Figure 5 ).

[0154] Figure 21 and Figure 22 Another type of architecture is shown for the front internal structure 14 and the rear internal structure 15, which also enables the avoidance of such collisions.

[0155] exist Figure 21In one embodiment, the rear internal structure 15 (only one half of the rear internal structure in the closed or flight position is shown) includes a cutout 85 that defines a first closed circumferential segment on the front longitudinal portion and forms an opening on a second circumferential segment of the front longitudinal portion.

[0156] The beams 20 of the front interior structure 14 are arranged circumferentially within the second circumferential section such that when one or more wall panels 21 of the front interior structure 14 are supported by the beams 20 in a closed configuration, the wall panels 21 close the second circumferential section and together with the portion of the rear interior structure 15 extending on the first circumferential section of the front longitudinal portion, they form a generally annular structure.

[0157] The geometry of the cutout 85 and the corresponding circumferential dimensions of the first and second circumferential sections are selected such that when the rear internal structure 15 is positioned in the maintenance position, the outer housing 3 extends partially within the opening defined by the cutout 85. Therefore, the corresponding circumferential dimensions of the first and second circumferential sections generally depend on the opening angle of each half of the rear internal structure 15.

[0158] Of course, the half-part of the rear internal structure 15 ( Figure 21 (Not shown in the figure) is symmetrical to the half-part of the rear internal structure shown in the figure.

[0159] In this example, one or more wall panels 21 are based on the reference above. Figures 3 to 20 The same principles described in the embodiments are used in conjunction with beam 20 and / or frame 9 and / or rear internal structure 15.

[0160] Figure 22 It shows the relationship with Figure 21 A different variation of the embodiment, the difference being that the front internal structure 14 includes a wall panel 21 hinged to the rear internal structure 15, such that when the rear internal structure is arranged in a maintenance configuration, the wall panel 21 can be adjusted according to... Figure 22 The configuration shown is folded radially inward to avoid collision or interference between the wall panel 21 and the outer shell 3.

[0161] The wall panel 21 connected to the rear internal structure 15 can be sized to cover only a portion of the second circumferential segment, the other portion of which can be covered by one or more other wall panels 21, which are configured according to the above reference. Figures 3 to 21 The same principles described in the embodiments are used in conjunction with beam 20 and / or frame 9 and / or rear internal structure 15.

[0162] The above description is by no means limiting, and the principles of the invention can be implemented and combined in various ways without departing from the scope of the invention. For example, the propulsion assembly 10 may not have a thrust reverser and may include a fixed external structure 12. Alternatively, the propulsion assembly 10 may include a thrust reverser with flaps, for example, in the case of a D-shaped naval architecture, where the flap linkage does not engage with the forward internal structure 14 but with the aft internal structure 15.

Claims

1. A cabin for an aircraft ducted propulsion assembly (10), the cabin comprising an external structure (12) and a rear internal structure (15) extending about a longitudinal central axis (A1), the rear internal structure (15) being movable between two positions: - In the flight position, the rear internal structure radially defines a first longitudinal portion of an annular channel (5), the first longitudinal portion of which is intended to guide secondary flow in the propulsion assembly (10), and the rear internal structure covers a first longitudinal portion of the internal space of the engine intended to receive the propulsion assembly (10), and - Maintenance position, in which the rear internal structure (15) is configured to expose at least a portion of the first longitudinal portion of the internal space, allowing an operator access to the internal space. The cabin is characterized in that it includes a forward internal structure (14) comprising beams (20) and one or more wall panels (21), the beams (20) extending longitudinally and spaced apart from each other circumferentially relative to the longitudinal central axis (A1), and the one or more wall panels (21) being able to be arranged in: - A closed configuration in which one or more wall panels cooperate with the beam (20) to define a second longitudinal portion of the annular passage (5) radially inward, and to cover a corresponding circumferential portion of the second longitudinal portion of the interior space. - Maintenance configuration in which the one or more wall panels leave circumferential space between the beams (20) so that an operator can access the second longitudinal portion of the interior space.

2. The cabin according to claim 1, wherein, The front internal structure (14) includes a rear end portion configured to engage with the front end portion of the rear internal structure (15) when the front internal structure (14) is in the closed configuration and the rear internal structure (15) is in the flight position.

3. The cabin according to claim 2, wherein, The rear end of the front internal structure (14) is formed by one or more of the beams (20).

4. The cabin according to claim 2, wherein, The rear end of the front internal structure (14) engages with the front end of the rear internal structure (15) to transmit axial force from the rear internal structure (15) to the front internal structure (14).

5. The cabin according to claim 1, wherein, The beams (20) of the front internal structure (14) are configured to be connected, preferably, to the frame (9) of the engine via the front ends of these beams (20).

6. The cabin according to claim 5, the cabin including support links (24), each support link (24) being connected at a first end to a middle or rear portion of a corresponding beam in the beam (20), and each support link being configured to be connected at a second end to the frame (9) of the engine.

7. The cabin according to claim 1, wherein, At least one of the one or more wall panels (21) is pivotally connected to one or more of the beams (20), or is configured to pivotally connect to the frame (9) of the engine, thereby enabling the wall panel to move between the closed configuration and the maintenance configuration.

8. The cabin according to claim 1, wherein, At least one of the one or more wall panels (21) is pivotally connected to the rear interior structure (15), the rear interior structure (15) including a front portion having a cutout such that when the rear interior structure (15) is in the flight position and the one or more wall panels (21) is in the closed configuration, the front portion of the rear interior structure (15) forms a first circumferential segment, and the one or more wall panels (21) connected to the rear interior structure (15) form a second circumferential segment, the first circumferential segment and the second circumferential segment each radially inwardly defining a corresponding segment of the second longitudinal portion of the annular channel (5).

9. The cabin according to claim 1, the cabin including a thrust reverser (13) having flaps, the external structure (12) being movable between an advance position and a retracted position, the cabin including a linkage (80) connected at a first end to a corresponding beam in the beam (20) of the front internal structure (14) and at a second end to a corresponding flap in the flaps, such that the flaps deploy in the annular passage (5) when the external structure moves from the advance position to the retracted position.

10. The cabin according to claim 1, wherein, The beam is cantilevered at its front end.

11. An aircraft ducted propulsion assembly (10), the propulsion assembly (10) comprising an engine and a nacelle according to claim 1, the engine comprising a hub (2), an outer housing (3) and one or more radial arms (4) connecting the hub (2) and the outer housing (3) to each other, the outer housing (3) extending longitudinally at its rear relative to the front portion of the front interior structure (14) such that it defines the annular passage (5) on a portion of the second longitudinal portion through the one or more wall panels (21) of the front interior structure (14) radially inward and through the outer housing (3) radially outward.

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