Aircraft propulsion system comprising a load-bearing structure interposed between an engine and a primary mast structure

Abstract

Aircraft propulsion assembly comprising a support structure interposed between an engine and a primary structure of a mast. The invention relates to an aircraft propulsion assembly (30) comprising: an engine (32) which has front and rear parts offset along a longitudinal axis (X), a primary structure (42) of a mast (34), at least one support structure (48) which extends along the longitudinal axis (X), separate from the rear part and connected to the front part of the engine (32), an engine attachment system (46) which comprises: at least one front attachment (46.1) directly connecting the engine (32) and the primary structure (42), at least one rear attachment (46.2), offset towards the rear relative to the front attachment (46.1), connecting the primary structure (42) and the support structure (48). This solution optimizes the transfer of forces between the motor (32) and the primary structure (42) of the mast. Figure 4

Description

Title of the invention: Aircraft propulsion assembly comprising a load-bearing structure interposed between an engine and a primary mast structure

[0001] The present application relates to an aircraft propulsion assembly comprising a supporting structure interposed between an engine and a primary structure of a mast.

[0002] According to a configuration visible in figures 1 to 3, an aircraft 10 comprises several propulsion units 12 which are positioned under the wing 14 of the aircraft 10.

[0003] A propulsion assembly 12 includes a motor 16, a nacelle (not shown in Figures 2 and 3) positioned around the motor 16 and a mast 18 connecting the motor 16 to the rest of the aircraft 10, in particular to the wing 14.

[0004] For the remainder of this description, a longitudinal axis X is parallel to the axis of rotation A16 of the motor 16. A transverse plane is a plane perpendicular to the axis of rotation A16 of the motor 16. A longitudinal plane is a plane passing through the axis of rotation A16 of the motor 16. A horizontal transverse direction Y is a direction perpendicular to the axis of rotation A16 of the motor 16 and horizontal. A vertical transverse direction Z is a direction perpendicular to the axis of rotation A16 of the motor 16 and vertical. A vertical median plane PMV is a vertical plane containing the axis of rotation A16 of the motor 16. A horizontal median plane is a horizontal plane containing the axis of rotation A16 of the motor 16. The terms front and rear refer to the direction of airflow in the motor 16, which flows from front to rear.

[0005] The engine 16 comprises a fan 20 which includes a fan casing 20.1 and a reactor core 22 comprising a front portion 22.1 positioned inside the fan 20, a central portion 22.2, and a rear portion 22.3 incorporating, in particular, a nozzle. Depending on one configuration, the central portion 22.2 has a smaller cross-section than the front and rear portions 22.1, 22.3. The reactor core 22 has an outer casing called the engine casing F22.

[0006] The mast 18 includes a primary structure 24, in the form of a box, which is connected to the sail 14 by a sail attachment system 26 and to the motor 16 by a motor attachment system 28. This primary structure 24 includes a front end 24.1, a middle part 24.2 and a rear end 24.3.

[0007] According to a first embodiment visible in [Fig.2], the engine attachment system 28 comprises a front attachment 28.1 connecting the front end 24.1 of the primary structure 24 and the front and / or central part 22.1, 22.2 of the reactor core 22, a rear attachment 28.2 connecting the rear end 24.3 of the primary structure 24 and the rear part 22.3 of the reactor core 22 and two connecting rods 28.3, positioned symmetrically with respect to the vertical median plane PMV of the engine 16, connecting the primary structure 24 and the front and / or central part 22.1, 22.2 of the reactor core 22.

[0008] According to a second embodiment visible in [Fig.3], the engine attachment system 28 comprises a front attachment 28.1 which connects the front end 24.1 of the primary structure 24 and the fan casing 20.1 of the fan 20, a rear attachment 28.2 which connects the rear end 24.3 of the primary structure 24 and the rear part 22.3 of the reactor core 22 and two connecting rods 28.3, positioned symmetrically with respect to the vertical median plane PMV of the engine 16, which connect the primary structure 24 and the front and / or central part 22.1, 22.2 of the reactor core 22.

[0009] In certain circumstances, these two embodiments do not allow optimal transfer of forces between the motorization 16 and the primary structure 24 of the mast 18.

[0010] The present invention aims to remedy all or part of the drawbacks of the prior art.

[0011] To this end, the invention relates to an aircraft propulsion system comprising: a. an engine which extends from front to back along a longitudinal axis and comprises, at the front, a front part and, at the rear of the front part, a rear part, the front and rear parts each having a circumferential shape, the front part having a larger cross-section than the rear part, b. a primary mast structure, c. a motor attachment system linking the primary structure and the front part of the motorization, the motor attachment system comprising at least one front attachment directly linking the motorization and the primary structure.

[0012] According to the invention, the propulsion assembly comprises at least one load-bearing structure extending along an axis parallel to the longitudinal axis and at least a portion of the circumference of the rear part of the motor, said load-bearing structure being separate from the rear part of the motor and connected to the front part of the motor, the motor attachment system comprising at least one rear attachment, offset towards the rear relative to the front attachment, connecting the primary structure and the load-bearing structure.

[0013] This solution optimizes the transfer of forces between the motorization and the primary structure of the mast, with the forces being taken up at the same level of the motorization.

[0014] According to another feature, the load-bearing structure is openwork.

[0015] According to another characteristic, the load-bearing structure is substantially shaped tubular

[0016] According to another feature, the front attachment and the supporting structure are connected to the motor at approximately the same transverse attachment plane.

[0017] According to another feature, the load-bearing structure is a lattice structure and includes longitudinal reinforcements and / or at least one transverse reinforcement connected together in such a way as to form quadrilateral or triangular meshes.

[0018] According to another feature, the load-bearing structure extends between front and rear ends, the front end being connected to the motorization, the load-bearing structure comprising at least one transverse reinforcement located at the rear end.

[0019] According to another feature, the load-bearing structure includes at least one intermediate transverse reinforcement, located between the front and rear ends.

[0020] According to another feature, the rear attachment comprises: a. a transverse beam attached to the primary structure, b. at least one first two-point shackle, positioned on one side of a vertical median plane, connected to the transverse beam by a first pivot axis and to the load-bearing structure by a second pivot axis, c. at least one second three-point shackle, positioned on a second side of the vertical median plane, connected to the crossbeam by third and fourth pivot axes and to the supporting structure by a fifth pivot axis.

[0021] According to another feature, the motor attachment system includes at least one fail-safe type safety link, connecting the primary structure and the supporting structure or the rear part of the motorization, configured so as not to form a path of forces when the rear attachment is operational and to form a path of forces in the event of damage to the rear attachment.

[0022] According to another feature, the motor attachment system includes at least one connecting rod which has a first end connected to the supporting structure and a second end connected to the motor.

[0023] According to another feature, the engine attachment system comprises several connecting rods positioned symmetrically with respect to a vertical median plane and / or with respect to a horizontal median plane.

[0024] Other features and advantages will become apparent from the following description of the invention, given by way of example only, with reference to the accompanying drawings, among which:

[0025] [Fig-1] is a perspective view of an aircraft,

[0026] [Fig.2] is a schematic side view of a propulsion assembly of an aircraft (without a nacelle) illustrating an early embodiment of the prior art,

[0027] [Fig.3] is a schematic side view of a propulsion assembly of an aircraft (without a nacelle) illustrating a second embodiment of the prior art,

[0028] [Fig.4] is a schematic side view of a propulsion assembly aircraft (without nacelle) illustrating one embodiment of the invention,

[0029] [Fig.5] is a schematic cross-section of a propulsion assembly aircraft illustrating one embodiment of the invention,

[0030] [Fig.6] is a schematic cross-section of a propulsion assembly of an aircraft illustrating another embodiment of the invention,

[0031] [Fig.7] is a rear view of an aircraft propulsion assembly (without nacelle) illustrating one embodiment of the invention,

[0032] [Fig.8] is a rear view of part of an engine mounting system of the assembly propulsion visible on the [Fig.7],

[0033] [Fig.9] is a schematic side view of a propulsion assembly aircraft comprising an openwork supporting structure illustrating a first embodiment of the invention,

[0034] [Fig. 10] is a schematic lateral representation of an aircraft propulsion assembly comprising an openwork supporting structure illustrating a second embodiment of the invention,

[0035] [Fig. 11] is a schematic lateral representation of an aircraft propulsion assembly comprising an openwork supporting structure illustrating a third embodiment of the invention,

[0036] [Fig. 12] is a rear view of a propulsion assembly comprising an openwork supporting structure illustrating one embodiment of the invention,

[0037] [Fig. 13] is a perspective view of a propulsion assembly comprising an openwork supporting structure (without a nacelle) illustrating one embodiment of the invention,

[0038] [Fig. 14] is a perspective view of part of an engine attachment system of the propulsion assembly visible in [Fig. 13].

[0039] According to an embodiment visible in Figures 4 to 14, a propulsion assembly 30 comprises a motor 32 extending from front to back along a longitudinal axis X and having an axis of rotation A32 parallel to the longitudinal axis X, a nacelle 33 (visible in Figures 5 and 6) positioned around the motor 32 and a mast 34 configured to connect the propulsion unit 30, and more specifically the engine 32, to a wing 36 of an aircraft. The latter comprises at least one such propulsion unit 30.

[0040] According to one configuration, the engine 32 includes a fan 38 and a reactor core 40.

[0041] The fan 38 includes a fan casing 38.1. The engine core 40 comprises, from front to rear, a forward section 40.1 positioned inside the fan 38, a central section 40.2, and a rear section 40.3 incorporating, in particular, high- and low-pressure turbines and a nozzle. Depending on one configuration, the central section 40.2 has a smaller cross-section than the forward and rear sections 40.1 and 40.3. The engine core 40 has an outer casing called the engine casing F40.

[0042] The mast 34 includes a primary structure 42, in the form of a box, which is connected to the sail 36 by a sail attachment system 44 and to the motor 32 by a motor attachment system 46. This primary structure 42 includes a front end 42.1, a middle part 42.2 and a rear end 42.3.

[0043] The engine attachment system 46 comprises at least one forward attachment 46.1 directly connecting the primary structure 42 of the mast and the engine 32 (the fan 38 and / or the forward section 40.1 of the reactor core 40). In a preferred embodiment, the forward attachment 46.1 connects the fan casing 38.1 of the fan 38 and the forward end 42.1 of the primary structure 42. This forward attachment 46.1 is configured to withstand thrust forces. In another configuration, the forward attachment 46.1 is identical to that of the prior art.

[0044] According to a particular feature of the invention, the propulsion assembly 30 comprises at least one support structure 48 which extends between front and rear ends 48.1, 48.2 oriented along an axis parallel to the longitudinal axis X, the front end 48.1 being connected to the motor 32. According to a preferred embodiment, the support structure 48, more particularly its front end 48.1, is connected to the blower 38 and more particularly to the blower housing 38.1.

[0045] The supporting structure 48 is a separate structure from the primary structure 42 of the mast and the outer shell F40 of the reactor core 40. The supporting structure 48 is perforated. Perforated means that the supporting structure has an openness ratio (corresponding to the ratio of the sum of the open areas to the total area) of at least 50%. Furthermore, unlike the outer shell F40 of the reactor core 40, it has sufficient rigidity to form a load path between the engine 32 and the primary structure 42.

[0046] The engine mounting system 46 includes at least one rear attachment 46.2, offset rearward relative to the front attachment 46.1, connecting the primary structure 42 and the supporting structure 48. According to one arrangement, the rear attachment 46.2 connects the middle part 42.2 and / or the rear end 42.3 of the primary structure 42 and the rear end 48.2 of the supporting structure 48 or an area located near this rear end 48.2.

[0047] According to one embodiment, the engine attachment system 46 comprises two connecting rods 46.3, positioned symmetrically with respect to a vertical median plane PMV of the engine 32, connecting the primary structure 42 and the forward and / or central part 40.1, 40.2 of the reactor core 40.

[0048] According to one arrangement, the front attachment 46.1 and the connecting rods 46.3 are connected to the motor 32 at anchor points P46.1, P46.3 positioned approximately in the same transverse attachment plane PTA.

[0049] According to one embodiment, the motor attachment system 46 comprises at least one front attachment 46.1 directly connecting the motor 32 and the primary structure 42, said front attachment 46.1 being connected to the motor 32 at the level of a transverse attachment plane PTA, the supporting structure 48 also being connected to the motor 32 approximately at the level of the transverse attachment plane PTA.

[0050] The supporting structure 48 is spaced, over at least part of the circumference of the engine 32 and preferably over the entire circumference, from the reactor core 40 and positioned between the reactor core 40 and the nacelle 33.

[0051] According to a first configuration, the openwork supporting structure 48 is a beam that does not extend around the reactor core 40.

[0052] According to a second configuration, the supporting structure 48 extends over at least part of the circumference of the reactor core 40. The supporting structure 48 is tubular and extends all around the reactor core 40. The supporting structure is distant from the reactor core 40.

[0053] According to a first embodiment visible in [Fig.4], the supporting structure 48 is cylindrical.

[0054] According to a second embodiment visible in [Fig.9], the supporting structure 48 has a barrel shape.

[0055] According to a third embodiment visible in [Fig. 10], the supporting structure 48 has a hyperboloid shape.

[0056] According to a fourth embodiment visible in [Fig. 11], the supporting structure 48 is frustoconical.

[0057] Of course, the invention is not limited to these geometries for the load-bearing structure 48.

[0058] According to a configuration visible on [Fig.5], in at least one transverse plane, the supporting structure 48 is closer to the nacelle 33 than to the reactor core 40.

[0059] According to another configuration visible on [Fig.6], in at least one transverse plane, the supporting structure 48 is closer to the reactor core 40 than to the nacelle 33.

[0060] According to one embodiment, the load-bearing structure 48 is a truss structure and includes several longitudinal reinforcements 50 as well as at least one transverse reinforcement 52. The load-bearing structure 48 may include at least one longitudinal reinforcement extending from its front end 48.1 to its rear end 48.2.

[0061] According to one configuration, each longitudinal reinforcement 50 is straight and has a circular cross-section. Of course, the invention is not limited to this cross-section for the longitudinal reinforcements 50.

[0062] Some long-line reinforcements 50 are directly connected to the motorization 32, each by a linkage system 54 comprising, for example, at least one element from among a pin, a rivet, a bolt or any other linkage element.

[0063] Some longitudinal reinforcements 50 are directly connected to a transverse reinforcement 52, each by a linking system 54' comprising, for example, at least one element from among a pin, a rivet, a bolt or any other linking element.

[0064] According to an embodiment visible for example in figures 9, 10 and 13, the load-bearing truss structure 48 includes a single rear transverse reinforcement 52, located at its rear end 48.2.

[0065] According to another embodiment visible in [Fig. 11], the lattice support structure 48 includes a rear transverse reinforcement 52, located at the rear end 48.2, as well as at least one intermediate transverse reinforcement 52' located between the front and rear ends 48.1, 48.2 of the lattice support structure 48.

[0066] The lattice support structure 48 could include a front transverse reinforcement located at the front end 48.1 of the lattice support structure 48 and directly connected to the motorization.

[0067] According to embodiments shown in Figures 9, 10 and 13, the longitudinal reinforcements 50 are connected to each other at nodes 56 so as to form quadrilateral meshes. According to these embodiments, the longitudinal reinforcements 50 connected to the transverse reinforcement 52 or to the motor 32 form triangular meshes with the latter.

[0068] According to another embodiment visible in [Fig. 11], the longitudinal reinforcements 50, the transverse reinforcements 52, 52' and the motorization 32 are connected together so as to form triangular meshes.

[0069] Of course, the invention is not limited to these geometries for the mesh. Generally, the load-bearing lattice structure 48 comprises longitudinal reinforcements 50 and / or at least one transverse reinforcement 52 connected together in such a way as to form quadrilateral or triangular meshes in order to obtain an openwork structure.

[0070] The longitudinal and transverse reinforcements 50, 52, 52' can be metallic and / or made of composite material.

[0071] According to one embodiment, at least one transverse reinforcement 52, 52' comprises at least one plate positioned in a transverse plane. According to one arrangement, at least one transverse reinforcement 52 comprises two parallel plates, slightly spaced and connected to each other.

[0072] According to one configuration, at least one transverse reinforcement 52, 52' extends continuously around the entire circumference of the reactor core 40 and forms a ring. According to another configuration, at least one transverse reinforcement 52, 52' forms a U-shape with ends oriented towards the primary structure 42 or towards the propulsion unit 32.

[0073] According to an embodiment shown in detail in Figures 7 and 8, the rear attachment 46.2 connecting the supporting structure 48 and the primary structure 42 is configured to resist forces in the horizontal and vertical transverse directions Y, Z, as well as a torque about the axis of rotation A32 of the motor 32. It comprises: a. a transverse beam 58 integral with the primary structure 42, b. at least one first two-point shackle 60, positioned from a first side of the vertical median plane PMV, connected to the transverse beam 58 by a first pivot axis 60.1 and to the load-bearing structure 48 by a second pivot axis 60.2, c. at least one second three-point shackle 62, positioned on a second side of the vertical median plane PMV, connected to the cross beam 58 by third and fourth pivot axes 62.1, 62.2 and to the supporting structure 48 by a fifth pivot axis 62.3.

[0074] The different pivot axes 60.1, 60.2, 62.1, 62.2, 62.3 are substantially parallel to each other and to the longitudinal axis X.

[0075] According to this embodiment, the first two-point shackle 60 is configured to transfer forces along a substantially vertical axis. In addition, the second three-point shackle 62 is configured to transfer forces along the horizontal and vertical transverse directions Y, Z. The first and second shackles 60, 62 allow for the transfer of torsional forces along the longitudinal axis X.

[0076] According to one embodiment, the engine attachment system 46 comprises at least one fail-safe type connection 64, 64', linking the primary structure 42 and the openwork supporting structure 48 or the engine 32, in particular the reactor core 40, configured so as not to form a load path when the rear attachment 46.2 is operational and functions correctly and forms a path of effort in case of damage to the rear attachment 46.2.

[0077] According to an arrangement visible in figures 7 and 8, the fail-safe type safety link 64 connects the cross beam 58 and the load-bearing structure 48, in particular the rear end 48.2 of the load-bearing structure 48.

[0078] According to another arrangement visible in Figures 13 and 14, the fail-safe type safety link 64' connects the primary structure 42 and the reactor core 40, in particular the rear part 40.3 of the reactor core 40.

[0079] According to one embodiment, the fail-safe type link 64, 64' comprises at least one safety axis 64.1 substantially parallel to the longitudinal axis X.

[0080] According to an arrangement visible in [Fig.8], the fail-safe type safety link 64 comprises a single safety axis 64.1 positioned at the level of the vertical median plane PMV.

[0081] According to an arrangement visible in [Fig. 14], the fail-safe type link 64' comprises two safety axes 64.1, 64.1' positioned symmetrically with respect to the vertical median plane PMV.

[0082] According to an embodiment visible in figures 7 and 12, the engine attachment system 46 comprises at least one connecting rod 66 which has a first end 66.1 connected to the supporting structure 48, more particularly to the rear transverse reinforcement 52, and a second end 66.2 connected to the engine 32 and more particularly to the rear part 40.3 of the reactor core 40.

[0083] According to one configuration, the first end 66.1 of the connecting rod 66 is connected to the supporting structure 48 by a joint that includes at least one pivot axis parallel to the longitudinal axis. In addition, the second end 66.2 of the connecting rod 66 is connected to the reactor core 40 by a joint that includes at least one pivot axis parallel to the longitudinal axis X.

[0084] According to one arrangement, the engine attachment system 46 comprises several connecting rods 66 positioned symmetrically with respect to the vertical median plane PMV.

[0085] According to an embodiment visible in [Fig.12], the engine attachment system 46 comprises several connecting rods 66 positioned symmetrically with respect to a horizontal median plane TDC.

[0086] The connecting rod(s) 66 support the reactor core 40 and bear part of the weight of the reactor core 40. It also limits the radial displacements of the reactor core 40.

[0087] Regardless of the embodiment, the load-bearing structure 48, separate from the rear part of the motor 32, ensures a transfer of forces between the motorization 32 and the primary structure 42 of the mast, the forces being taken up at the level of the same part of the motorization 32, namely the blower housing 38.1.

[0088] This configuration optimizes the transfer of forces between the drive unit 32 and the primary structure 42 of the mast. The large perforations in the supporting structure 48 allow easy access to the reactor core 40. Finally, the use of an openwork supporting structure results in a rigid structure with high stiffness in all directions, while maintaining a constant mass.

[0089] Of course, the invention is not limited to engines that include a fan positioned in a fan housing. Thus, it can be applied to any engine that extends from front to back along a longitudinal axis and comprises a front portion and a rear portion connected to the front portion and offset rearward along the longitudinal axis relative to the front portion. The rear portion may be a part of the reactor core of a turbojet or turboprop engine. Depending on the application, the front portion may be a fan housing 38.1 in the case of a shrouded fan. The front portion may also be a support structure on which an unshrouded fan or an unshrouded propeller, or any other structure of an engine 32 positioned forward of the latter, is mounted, and which is configured to form a force path for the thrust forces generated during the operation of the engine 32.The front and rear parts each have a circumferential shape and the front part has a larger cross-section than the rear part of the 32 engine.

Claims

Demands

1. Aircraft propulsion assembly (30) comprising: a. an engine (32) extending from front to rear along a longitudinal axis (X) and comprising, at the front, a front portion and, at the rear of the front portion, a rear portion, the front and rear portions each having a circumferential shape, the front portion having a larger cross-section than the rear portion, b. a primary mast structure (42), c. an engine attachment system (46) connecting the primary structure (42) and the front portion of the engine (32), the engine attachment system (46) comprising at least one front attachment (46.1) directly connecting the engine (32) and the primary structure (42); d.characterized in that the propulsion assembly (30) comprises at least one support structure (48) extending along an axis parallel to the longitudinal axis (X) and at least a portion of the circumference of the rear part of the motorization (32), said support structure being separate from the rear part of the motorization (32) and connected to the front part of the motorization (32) and in that the motor attachment system (46) comprises at least one rear attachment (46.2), offset rearward relative to the front attachment (46.1), connecting the primary structure (42) and the support structure (48).

2. Propulsion assembly (30) according to the preceding claim, characterized in that the supporting structure (48) is openwork.

3. Propulsion assembly (30) according to any one of the preceding claims, characterized in that the supporting structure (48) is substantially tubular in shape.

4. Propulsion assembly (30) according to any one of the preceding claims, characterized in that the front attachment (46.1) and the carrier structure (48) are connected to the motorization (32) at approximately the same transverse attachment plane (PTA).

5. Propulsion assembly (30) according to any one of the preceding claims, characterized in that the supporting structure (48) is a lattice structure and comprises longitudinal reinforcements (50) and / or to less a transverse reinforcement (52) connected together so as to form quadrilateral or triangular meshes.

6. Propulsion assembly (30) according to the preceding claim, characterized in that the support structure (48) extends between front and rear extremities (48.1, 48.2), the front extremity (48.1) being connected to the motorization (32), the support structure (48) comprising at least one transverse reinforcement (52) located at the rear extremity (48.2).

7. Propulsion assembly (30) according to the preceding claim, characterized in that the supporting structure (48) comprises at least one intermediate transverse reinforcement (52') located between the front and rear ends (48.1, 48.2).

8. Propulsion assembly (30) according to any one of the preceding claims, characterized in that the rear attachment (46.2) comprises: a. a cross beam (58) integral with the primary structure (42), b. at least one first two-point shackle (60), positioned on a first side of a vertical median plane (VMP), connected to the cross beam (58) by a first pivot axis (60.1) and to the carrier structure (48) by a second pivot axis (60.2), c. at least one second three-point shackle (62), positioned on a second side of the vertical median plane (VMP), connected to the cross beam (58) by third and fourth pivot axes (62.1, 62.2) and to the carrier structure (48) by a fifth pivot axis (62.3).

9. Propulsion assembly (30) according to any one of the preceding claims, characterized in that the motor attachment system (46) includes at least one fail-safe type linkage (64, 64'), connecting the primary structure (42) and the carrier structure (48) or the rear part of the motorization (32), configured not to form a path of forces when the rear attachment (46.2) is operational and to form a path of forces in the event of damage to the rear attachment (46.2).

10. Propulsion assembly (30) according to any one of the preceding claims, characterized in that the engine attachment system (46) includes at least one connecting rod (66) which has a first end (66.1) connected to the supporting structure (48) and a second end (66.2) connected to the motorization (32).

11. Propulsion assembly (30) according to the preceding claim, characterized in that the engine attachment system (46) comprises several connecting rods (66) positioned symmetrically with respect to a vertical median plane (VMP) and / or with respect to a horizontal median plane (HMP).

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