SUPPORTING STRUCTURE FOR MOUNTING ON A GAS GENERATOR

Description

[0001] The present invention relates to the field of aircraft propulsion assembly suspensions, and more particularly to a load-bearing structure configured to be fixed to a gas generator (in English: "engine core") of a turbofan engine, in order to allow its connection to a receiving structure of the aircraft, which can also be called an aircraft structure, through a suspension.

[0002] Typically, a turbofan engine is suspended from a receiving structure on the aircraft, for example a pylon fixed under the wing, via an upstream suspension attached to an intermediate housing integral with the fan housing and a downstream suspension attached to the turbine housing. This avoids an overhang that would subject the engine to bending stresses that could be detrimental to the fit of the compressor and turbine rotors within their respective housings.

[0003] However, such an arrangement has the disadvantage of being very bulky. With increasing thrust and bypass ratios, the diameter of the fans also increases significantly, making this arrangement increasingly cumbersome. Thus, when a turbofan engine with a high bypass ratio is suspended from the aircraft's wing in such an arrangement, the aircraft's ground clearance may be insufficient to accommodate the propulsion system formed by the turbofan and its nacelle, requiring modifications to the nacelle and / or even the landing gear, which can be costly and negatively impact the aircraft's overall performance.

[0004] To overcome this drawback, several solutions have been proposed for suspending a turbofan engine solely by its gas generator, downstream of the fan. In some solutions, a structural casing for the gas generator, incorporating part of the pylon, has been proposed to resist bending forces, thus allowing the turbofan engine to be suspended through this structural casing, despite the fan being cantilevered. International patent application WO 2008 / 000924 A1 proposes other concepts in which the turbofan engine is suspended from a pylon via a structure attached to an intermediate casing of the gas generator.This, however, implies a concentration of stress, particularly bending stress, on the end of the pylon attached to these added structures, thus requiring significant reinforcement with a substantial penalty in terms of added mass. All these solutions share the drawback of added mass, which can be more or less considerable. Other structures have been disclosed in patent applications FR 2 993 535 A1 and US 2012 / 111995 A1. Subject matter and summary of the invention

[0005] A load-bearing structure according to claim 1 is provided. Preferred embodiments are described in the dependent claims.

[0006] This disclosure aims to address these drawbacks by proposing a load-bearing structure designed for mounting on the gas generator of a turbofan engine for aircraft. This structure connects the turbofan to a suspension system without passing through the fan casing, while simultaneously resisting bending moments in the longitudinal direction without significant weight penalty. To this end, this load-bearing structure, which can be formed as a single, monolithic piece, may comprise two longitudinal beams and a transverse connection linking them, which could, for example, include a hoop.Each of the two longitudinal beams may include at least one front mounting interface and one rear mounting interface for mounting the support structure onto the gas generator, and a lateral suspension point for transmitting longitudinal and vertical forces between the support structure and a suspension structure. The rear mounting interface may be adapted to allow at least one longitudinal deflection of the gas generator, and the transverse connection may include a central suspension point with an opening configured to receive a suspension snout oriented in a longitudinal direction for transmitting lateral and vertical forces between the support structure and the suspension structure. A suspension point of the support structure is understood to mean, for example, a fastener adapted to transmit forces between the support structure and the suspension structure.Since each attachment transmits forces to a fairly precise point, it can also be called an attachment point.

[0007] Thanks to these arrangements, the distances between the center of gravity of the turbofan engine and the mounting points of each forward mounting interface, as well as between this center of gravity and the central suspension point, can be minimized, thus reducing bending stresses, which can be effectively absorbed by the two longitudinal beams without significant weight penalty. Furthermore, the longitudinal travel permitted by the rear mounting interfaces, which can include each of the longitudinal guide means, accommodates the thermal expansion of the operating gas generator.These longitudinal guidance means may include a slide adapted to receive a slider mounted on a stud attached to a turbine housing of the gas generator. However, it is also possible to reverse this arrangement, integrating the slider into the rear mounting interface and the slider onto the turbine housing of the gas generator. To accommodate the lateral thermal expansion of the gas generator, the rear mounting interfaces may also be designed to allow lateral movement of the gas generator. To ensure a solid connection of this structure to the gas generator, each front mounting interface may be designed to transmit longitudinal and transverse forces, for example, by combining at least one bolt to transmit tensile forces and a lug to transmit shear forces.

[0008] A second aspect of this disclosure concerns a structural assembly comprising this load-bearing structure and a suspension structure attached to the load-bearing structure by the rear and central suspension points. To ensure the transmission of forces in two longitudinal planes, the suspension structure may include two suspension triangles, each attached to one of the corresponding rear suspension points, while to transmit forces in a transverse plane, the suspension structure may include a suspension stub, received longitudinally in a corresponding receptacle of the central suspension point. The central suspension point may include a ball joint, having a ball joint nut in which the bore is formed to accommodate angular displacements between the load-bearing structure and the suspension structure.To ensure proper load transfer in the transverse plane, the suspension structure may include a suspension pyramid, with the suspension snout located on a vertex of the suspension pyramid.

[0009] Finally, a third aspect of this disclosure concerns an aircraft comprising at least one receiving structure, a turbofan engine, and the structural assembly connecting the turbofan engine to the receiving structure. The turbofan engine can thus be suspended, for example, from a receiving structure attached to the aircraft's wing, although it is also possible to use the structural assembly to connect the turbofan engine to a receiving structure directly attached to the aircraft's fuselage, particularly the rear fuselage. Brief description of the drawings

[0010] The invention will be better understood and its advantages will appear better on reading the detailed description which follows, of embodiments shown as non-limiting examples. The description refers to the appended drawings in which: there figure 1 is a schematic perspective view of an aircraft, the figure 2 is a schematic longitudinal cross-sectional view of a turbofan engine of the aircraft of the figure 1 , there figure 3 is a side view of a structural assembly connecting the turbofan engine of the figure 2 to a receiving structure of the aircraft of the figure 1 , there figure 4 is a front view of the structural assembly of the figure 3 , there Figure 5 is a three-quarter rear perspective view of the structural assembly of the figure 3 , there figure 6 is a detailed view of a front mounting interface of the structural assembly of the figure 3 , there figure 7is a detailed view of a rear mounting interface of the entire figure 3 , there figure 8 is a detailed view of a central suspension point of a variant of the structural assembly of the figure 3 , there figure 9 is a three-quarter rear perspective view of a variant of the set of the figure 3 , there figure 10 is a schematic top view of a deployment mechanism interposed between an opening cowling of the gas generator of the turbofan engine of the figure 2 and a longitudinal beam of the entire figure 3 with the hood open in the closed position, the figure 11 is a schematic top view of the deployment mechanism of the figure 10 with the hood open in the open position, the figure 12 is a schematic rear view of the deployment mechanism of the figure 10 with the hood open in the open position, the figure 13is a schematic rear view of a variant of the deployment mechanism of the figure 10 with the hood open in the open position, the figure 14 is a schematic top view of another variant of the deployment mechanism of the figure 10 with the hood open in the open position, the figure 15 is a detailed view of an upstream sealing gasket of the opening hood of the figure 10 , in the closed position, the figure 16 is a schematic top view of yet another variant of the deployment mechanism of the figure 10 with the hood open in the open position, the figure 17 is a schematic top view of a deployment mechanism with a hood that opens in the closed position, the figure 18 is a schematic top view of the deployment mechanism of the figure 17 with the hood open in the open position, the figure 19 is a schematic cross-section of the deployment mechanism of the figure 17 , there figure 20is a schematic top view of a deployment mechanism with the hood opening in the closed position, the figure 21 is a schematic top view of the deployment mechanism of the figure 20 , with the hood opening in the open position, and the figure 22 is a schematic top view of the deployment mechanism of the figure 20 , with the hood opening in an intermediate position between the open and closed positions. Detailed description of the invention

[0011] There figure 1 illustrates an aircraft 1 comprising a fuselage 3, a wing 4 and a tail assembly 5, and two propulsion units 6 suspended, under the wing 4, from corresponding receiving structures 2. Each receiving structure 2 can be attached to one of the two wings of the wing 4. Although on the figure 1In this figure, which is a side view of aircraft 1, only one wing of this wing 4 is visible, along with its receiving structure 2 and corresponding propulsion assembly 4. Aircraft 1 may be substantially symmetrical about a longitudinal and vertical plane, such that the other wing, with its respective receiving structure and propulsion assembly 6, is located on the hidden side of aircraft 1 and is therefore not visible. Each receiving structure 2 may, as is known per se, include a pylon attached to the wing, for example, by interfaces fixed to at least one wing spar. However, alternatively or in addition to such a pylon, the receiving structure may also consist of a structural wing box.

[0012] Another identical or similar propulsion unit 6 is also suspended from a second wing on the other side of the aircraft, not visible in the figure. Each of these two propulsion units 6 may include a turbofan engine 7. As schematically illustrated in the figure 2 , this turbofan 7 can include a fan 10 and a gas generator 11 formed by a low pressure compressor 12, a high pressure compressor 13, a combustion chamber 14, a high pressure turbine 15 coupled to the high pressure compressor 13 for its actuation, and a low pressure turbine 16 coupled to the fan 10 and the low pressure compressor 12 for their actuation, aligned in a longitudinal direction along the longitudinal axis X which can also be the thrust axis of the turbofan 7. In each of the two propulsion assemblies 6, the fan 10 and the gas generator 11 receive respective fairings 17, 18.

[0013] In the illustrated aircraft 1, the turbofan engines 7 can have a high bypass ratio, greater than, for example, 5:1, 10:1, or even 15:1. The diameter of the fan 10 is therefore particularly large, such that, to maintain sufficient ground clearance, since the illustrated aircraft 1 is a low-wing aircraft, the fan 10 is offset upwards and forwards compared to a conventional arrangement. To achieve this offset, the fan 10 is not suspended from the receiving structure 2 attached to the wing 4, but is held solely by its structural connections to the gas generator 11. Thus, as illustrated in the figure 1 , the structural assembly 20 linking each turbofan 7 to the wing is not attached directly to the fan 10, but only to the gas generator 11, with the fan 10 thus suspended in cantilever relative to this assembly 20.

[0014] An example of the implementation of set 20 is illustrated on the figures 3 to 5Thus, as can be seen in these figures, this structural assembly 20 comprises a load-bearing structure 30 configured to be attached to the gas generator 11 and a suspension structure 40 to connect the load-bearing structure 30 to the receiving structure of the aircraft 1. More specifically, the load-bearing structure 30, which can notably be formed as a single, monolithic piece, comprises two longitudinal beams 31 and a transverse connection 32 rigidly linking them. In the illustrated embodiment, this transverse connection 32 is arched, but other shapes can be considered for this transverse connection 32, such as, for example, a 360° closed ring, either integral with the two longitudinal beams or attached to them, which could further increase the rigidity of the load-bearing structure 30 in the transverse plane.As in the illustrated embodiment, each of the two longitudinal beams 31 has at least one front mounting interface 33 and one rear mounting interface 34, each interface being configured to mount the structure onto the gas generator 11, and a lateral suspension point 35 for connection with the suspension structure 40. These lateral suspension points 35 on the longitudinal beams 31 are complemented, as illustrated, by a central suspension point 36 for connection with the suspension structure 40, located on the transverse connection 32.

[0015] As illustrated, each front mounting interface 33 allows the supporting structure 30 to be mounted on the gas generator 11. By definition, the gas generator of a turbofan engine is traversed by the primary flow stream of the turbofan engine and surrounded by the secondary flow stream of the turbofan engine. Since each front mounting interface 33 is fixed to the gas generator 11, it is located radially in an inter-flow space between the primary and secondary flow streams.Each forward mounting interface 33 can be configured to be fixed to a housing located upstream of the high-pressure compressor 13 of the gas generator 11, and axially downstream of a housing of the blower 10, for example a housing formed by an inter-compressor housing flange located between the low-pressure compressor 12 and the high-pressure compressor 13, and to transmit forces both in the longitudinal direction and in a transverse plane perpendicular to the longitudinal axis X. For this purpose, as illustrated in detail in the . figure 6 Each front mounting interface 33 may include a plate 331 with through holes 332 for receiving bolts to transmit longitudinal tensile forces, and at least one lug 333 for transmitting transverse shear forces. These transverse forces may be either lateral, i.e., parallel to the lateral axis Y, or vertical, i.e., parallel to the vertical axis Z.

[0016] On the other hand, each rear mounting interface 34 can be configured to be connected to a housing closer to the rear end of the gas generator 11, for example a turbine housing, allowing relative longitudinal and transverse movement of the gas generator 11 with respect to this rear mounting interface 34, so as to accommodate the thermal expansion of the gas generator 11 during operation. Thus, as illustrated in the figure 7Each rear mounting interface 34 may include a slide 341 for receiving a slide 342 mounted on a stud 343 attached to the gas generator 11, for example, to a turbine housing of the gas generator 11, allowing movement of the slide 342 in both the longitudinal and lateral directions. In this way, the rear mounting interfaces 34 will normally transmit only vertical forces to compensate for the longitudinal offset between the center of gravity G of the turbofan engine 7 and the front mounting interfaces 33.

[0017] Thus, when the supporting structure 30 is mounted on the gas generator 11, the latter can be fixed between the two longitudinal beams 31, oriented parallel to the longitudinal axis X of the turbofan engine 7, so that they resist the vertical bending moments, and in particular those generated by the cantilever of the fan 10 (including the fan casing also designated as 10 on the figure 3 ), thus relieving the gas generator housings 11 of such stress.

[0018] The lateral suspension points 35 can be located on the rear ends of the longitudinal beams 31, near the rear mounting interfaces 34, and configured to transmit longitudinal and vertical forces. For this purpose, each lateral suspension point 35 can, for example, include a shaft 351 designed to be received, oriented laterally, in a corresponding opening in the suspension structure 40. The central suspension point 36 can be located, as illustrated, at the center of the transverse link 32 spanning the gas generator 11 when the structure is mounted on it. The central suspension point can then directly overhang the longitudinal axis X of the turbofan engine 7 and be configured to transmit vertical and lateral forces in the transverse plane.For this purpose, the central suspension point 36 includes, as illustrated, an orifice 361 configured to receive a suspension snout 362 oriented in a longitudinal direction. In a variant illustrated in detail on the . figure 8 , the central suspension point 36 can also include a ball joint 363 having a ball joint nut in which the orifice 361 is formed, in order to allow angular movement of the suspension snout 362 in the central suspension point 36, and thus avoid the transmission of moments through the central suspension point 36.

[0019] As illustrated on the figures 3 to 5 , the suspension structure 40 may include two suspension triangles 41, each configured to be connected by a lower point 411 ( Figure 5) to one of the lateral suspension points 35 of the structure 30. When the lateral suspension points 35 include, as in the illustrated example, axles 351, the clevises 412 for receiving them can be formed in the lower ends 411 of the suspension triangles 41. Each suspension triangle 41 can be oriented so as to transmit to the receiving structure 2 the vertical and longitudinal forces it receives through the corresponding lateral suspension point 35. In order to limit their mass, each suspension triangle 41 can be formed, as illustrated, by two connecting rods 413 joined at the lower end 411, although it is also possible to use a triangular plate 41' for each suspension triangle, as in the variant illustrated in the figure 9Each connecting rod 413 of each suspension triangle 41 can be configured, as illustrated, to be connected, by its end opposite the lower point 411, to an attachment point 414 on the receiving structure 2, through a joint 415 allowing at least one angular deflection in the plane of the suspension triangle 41, so as to avoid the transmission of bending moments between the receiving structure 2 and each connecting rod 413. These joints 415 can also include ball joints to allow angular deflections in other planes.

[0020] The suspension 40 may also include, as illustrated, a suspension pyramid 42 configured to connect the central suspension point 36 of the structure 30 to the receiving structure 2. For this purpose, this suspension pyramid 42 may include a summit 421, in which the suspension snout 362 is formed, and four connecting rods joining at the summit 421. More specifically, among these four connecting rods, two upper connecting rods 422 may be rigidly fixed to the summit 421, extend towards corresponding attachment points 423 on the receiving structure 2, and be configured to be connected to these attachment points 423 through joints 424 to prevent the transmission of bending moments, in this inclined plane, between each of the attachment points 423 and the corresponding upper connecting rod 422.Two lower connecting rods 425, each connected by joints 426, 427 corresponding to the apex 421 of the suspension pyramid 42 and to the lower point 411 of a respective suspension triangle 41, can complete the suspension pyramid 42 so as to maintain the gap between the apex 421 of the pyramid 42 and the lower points 411 of the suspension triangles 41. The geometry of the suspension structure 40 can thus be maintained even when the supporting structure 30 is detached from it.

[0021] Like each of the suspension triangles 41, the two upper connecting rods 422 could also be replaced by a triangular plate 422', oriented in the inclined plane and connected in a similar way to the apex 421 of the suspension pyramid 42 and to the attachment points 423 on the receiving structure 2, as in the variant illustrated on the figure 9 , in which the elements equivalent to those of the Figure 5receive the same reference figures. The aerodynamic impact of such a plate 422' on the airflow in the secondary flow duct of the turbofan engine can be controlled, for example, by perforating the plate 422', which also reduces its mass. Although in the illustrated variant the triangular plates 41' and 422' each replace the suspension triangles 41 as well as the upper connecting rods 422, it is also possible to replace only the upper connecting rods 422 or one and / or both of the suspension triangles 41 in a mixed suspension structure combining connecting rods and one or two triangular plates. Furthermore, the plate 422', or even one or both of the plates 41', can be used as a support for a surface heat exchanger, for example, an air-to-air or air-to-oil heat exchanger.

[0022] To allow for inspection, maintenance, or even repair of the gas generator 11, its fairing 18 may include opening covers 50. Each opening cover 50 may be located laterally relative to the gas generator 11 and be connected to the corresponding longitudinal beam 31 of the structure 30 by a deployment mechanism 60. Following an example illustrated in the Figures 10 to 12This deployment mechanism 60 may include a pivoting arm 61 extending between a first end 611 connected to the longitudinal beam 31 by a first hinge 612, the pivot axis of which may be vertical, and a second end 613 connected to the opening cover 50 by a second hinge 614, the pivot axis of which may be parallel to that of the first hinge 612. When the pivot axes of the first and second hinges 612 and 614 are parallel, this pivoting arm 61 may be formed, as illustrated, by two parallel connecting rods 615 and 616, offset from each other along these pivot axes, as illustrated in the figure. figure 12 However, it is also possible that the pivoting arm 61 is formed from a single piece, with a certain width along the pivot axes, as in the variant illustrated on the figure 13 .

[0023] To ensure that the opening cover 50 remains in the open and / or closed position, the deployment mechanism 60 may further include a retaining rod 62 extending from a first end 621, connected by a first joint 622 to the pivoting arm 61 between its two ends 611, 613, and a second end 623, connected by a second joint 624 to the opening cover 50. To allow movement of the opening cover 50 between its open and closed positions, the first joint 622 and / or the second joint 624 of the retaining rod 62 may be mounted on slides 625, as illustrated in the figures. Figures 10 to 12 , and / or the retaining rod 62 can be telescopic, as in the variant illustrated on the figure 14 The deployment mechanism 60 may also include a lock (not shown) to lock the retaining rod 62 when the opening hood 50 is in the open position and / or in the closed position.

[0024] Furthermore, the deployment mechanism 60 may also include, in addition to or as an alternative to the retaining rod 62, a hood support 63 that can be releasably fixed between the longitudinal beam 31 and the opening hood 50 in the open position to maintain this open position, and / or at least one latch (not shown) to lock the opening hood 50 in the closed position by holding it, for example, by its upper and / or lower edge, as illustrated in the Figures 12 And 14 .

[0025] To ensure the airtightness of the opening hood 50 in the closed position, and to contain the fire, it may be provided with at least one sealing gasket 53 on its outer perimeter, and in particular on its upstream edge. As illustrated in the figure 15This sealing gasket 53 may include a rib 531 projecting radially inward on the edge of the opening hood 50, and a groove 532 integral with the gas generator 11 and open radially outward to receive the rib 531 when the opening hood 50 reaches the closed position. This arrangement may, however, also be reversed, so that the rib is located on the gas generator 11 and the groove on the opening hood 50. As illustrated, the groove 532 may, in particular, have a V-shaped cross-section.

[0026] In an illustrated variant on the figure 16 , the deployment mechanism 60 may include at least two pivoting arms 61 parallel and offset from each other in the longitudinal direction, connected in a similar way to the longitudinal beam 31 and the opening hood 50, thus forming with them a deformable parallelogram allowing the orientation of the opening hood 50 to be maintained during its opening and closing.

[0027] When opening the hood, it opens 50 degrees from the closed position shown on the... figure 10 With the deployment mechanism 60, at least one pivoting arm 61 can first be rotated, after unlocking the lock 64 and / or the retaining rod 62, to laterally move the opening cover 50 of the gas generator 11 away from the side while moving it downstream, thus reaching the open position illustrated in the figure 11, in order to make the gas generator 11 accessible, for example for inspection, maintenance and / or repair work. The deployment mechanism 60 can then be locked in this open position with the retaining rod lock 62 and / or the hood support 63 can be fixed between the longitudinal beam 31 and the opening hood 50 to prevent accidental closure. These steps can then be reversed to close the opening hood 50, returning it from the open position illustrated in the figure 11 towards the closed position illustrated on the figure 10 .

[0028] Following a second example illustrated on the figures 17 to 19The deployment mechanism 60 may include, instead of one or more pivoting arms, one or more slides 65 fixed to the longitudinal beam 31 and one or more sliders 66 fixed to the opening cover 50 to allow opening and closing of the opening cover 50 by sliding at least one slider 66 within at least one slide 65. In particular, as illustrated in the Figures 17 and 18 The slide 65 can be oriented along the longitudinal direction, thus allowing the opening cover 50 to slide longitudinally between its open and closed positions. As illustrated in the figure 19, the deployment mechanism 60 may in particular include a first slide 65 located on an upper face of the longitudinal beam 31 and a second slide 65 located on an lower face of the longitudinal beam 31, each receiving at least two slides 66 connected to the opening hood 50 and mutually offset in the longitudinal direction.

[0029] To allow the opening hood 50 to be held in the open and / or closed position, the slide 65 may include at least one locking 651 at the end of its travel. Furthermore, to facilitate their sliding, the slides 66 may be fitted with rollers 661 adapted to roll on bearing surfaces 652 within the slide 65, as illustrated in the figure 19 Since the other illustrated elements are equivalent to those in the first example, they receive the same reference figures on the figures 17 to 19 than on the previous figures.

[0030] When opening the hood, it opens 50 degrees from the closed position shown on the... figure 17 With the deployment mechanism 60 following this second example, and after unlocking at least one slide 66, the opening cover 50 can be slid longitudinally downstream towards the open position illustrated on the figure 18 , in order to make the gas generator 11 accessible, for example for inspection, maintenance and / or repair work. The deployment mechanism 60 can then be locked in this open position to prevent accidental closure. These steps can then be reversed to close the opening cover 50, returning it from the open position shown in the diagram. figure 18 towards the closed position illustrated on the figure 17 .

[0031] To provide even better access to the gas generator, it is also possible to combine a pivoting arm and sliding mechanism, as in a deployment mechanism 60, following a third example illustrated on the Figures 20 to 22As illustrated, each slide 66 can then be connected to the opening cover 50 by a pivoting arm 61 extending between a first end 611 connected to the slide 66 by a first hinge 612, whose pivot axis may be vertical, and a second end 613 connected to the opening cover 50 by a second hinge 614, whose pivot axis may be parallel to that of the first hinge 612. To allow the opening cover 50 to be held in the open and / or closed position, the slide 65 may include at least one end-of-stroke lock 651, as in the second example mentioned above, and at least one of the hinges 612, 614 may include a lock (not illustrated) to release the angular travel of at least one pivoting arm 61. The other illustrated elements being equivalent to those of the first two examples, they are assigned the same reference numerals on the diagrams. figures 17 to 19 than on the previous figures.

[0032] When opening the hood, it opens 50 degrees from the closed position shown on the... figure 20 With the deployment mechanism 60 following this third example, one can first proceed to rotate at least one pivoting arm 61, after its unlocking, to laterally move the opening cover 50 of the gas generator 11 apart, thus reaching the intermediate position illustrated on the figure 22 From this intermediate position, and after unlocking at least one slide 66, the opening cover 50 can be slid longitudinally downstream towards the open position illustrated in the figure 21, in order to make the gas generator 11 accessible, for example for inspection, maintenance and / or repair work. The deployment mechanism 60 can then be locked in this open position to prevent accidental closure. These steps can then be reversed to close the opening cover 50, returning it from the open position shown in the diagram. figure 21 towards the closed position illustrated on the figure 20 passing again through the intermediate position illustrated on the figure 22 .

[0033] Although the present invention has been described with reference to specific examples and embodiments, as well as particular variations, it is evident that various modifications and changes can be made to these examples and their variations. For example, although only one opening hood with a deployment mechanism on one side of the gas generator has been described, it is of course conceivable to have such an opening hood, and a corresponding deployment mechanism, on each side of the gas generator. Therefore, the description and drawings should be considered in an illustrative rather than restrictive sense.

Claims

1. A load-bearing structure (30) configured to be mounted on a engine core (11) of a turbofan engine (7) for an aircraft, the load-bearing structure (30) comprising: two longitudinal beams (31) each including: a forward mounting interface (33) and a rear mounting interface (34), for mounting the load-bearing structure (30) on the engine core (11), the rear mounting interface (34) being able to allow at least the longitudinal travel of the engine core (11), and a lateral suspension point (35) for transmitting longitudinal and vertical forces between the load-bearing structure (30) and a suspension structure (40), and a transverse connection (32) connecting the two longitudinal beams (31) the load-bearing-structure being characterized in that the transverse connection (32) comprises a central suspension point (36) with an orifice (361) configured to receive a suspension snout (362) oriented in longitudinal direction for transmitting lateral and vertical forces between the load-bearing structure (30) and the suspension structure (40).

2. The load-bearing structure (30) as claimed in claim 1, wherein the rear mounting interfaces (34) also be able to allow lateral travel of the engine core (11).

3. The load-bearing structure (30) as claimed in any of claims 1 or 2, wherein each rear mounting interface (34) comprises longitudinal guiding means.

4. The load-bearing structure (30) as claimed in claim 3, wherein the longitudinal guiding means of each rear mounting interface comprise a slide (341) able to receive a slider (342) mounted on a pad (343) forming a single part with a turbine casing of the engine core (11).

5. The load-bearing structure (30) as claimed in any of the preceding claims, wherein each forward mounting interface (33) is able to transmit longitudinal and transverse forces.

6. The load-bearing structure (30) as claimed in any of the preceding claims, formed of a single-unit part.

7. The load-bearing structure (30) as claimed in any of the preceding claims, wherein the transverse connection (32) connecting the two longitudinal beams (31) comprises an arch.

8. A structural assembly (20) comprising a load-bearing structure (30) as claimed in any of the preceding claims and a suspension structure (40) attached to the load-bearing structure (30) by the rear and central suspension points (35,36).

9. The structural assembly (20) as claimed in claim 8, wherein the suspension structure (40) comprises two suspension triangles (41), each attached to one of the corresponding lateral suspension points (35).

10. The structural assembly (20) as claimed in any of claims 8 or 9, wherein the suspension structure (40) comprises the suspension snout (362), received in the longitudinal direction in the corresponding orifice (361) of the central suspension point (36), the central suspension point comprising a ball joint (363) including a ball joint yoke wherein the receptacle (361) is formed.

11. The structural assembly (20) as claimed in claim 10, wherein the suspension structure (30) comprises a suspension pyramid (42), the suspension snout being located on an apex (421) of the suspension pyramid (42).

12. An aircraft (1) comprising at least one receiving structure (2), a turbofan engine (7) and the structural assembly (20) as claimed in any of claims 8 to 11 connecting the turbofan engine (7) to the receiving structure (2).