Aircraft propulsion system comprising a load-bearing structure connecting an engine and a primary structure of a mast and supporting at least one accessory

Abstract

Aircraft propulsion assembly comprising a supporting structure connecting an engine and a primary structure of a mast and supporting at least one accessory. The invention relates to an aircraft propulsion assembly (30) comprising: an engine (32) having front and rear parts offset along a longitudinal axis (X), a primary structure (42) of a mast (34), at least one supporting structure (48) extending along an axis parallel to the longitudinal axis (X), connected to the front part of the engine (32), supporting at least one accessory (66), an engine mounting system (46) comprising: 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 rearward relative to the front attachment (46.1), connecting the primary structure (42) and the supporting structure (48). This solution optimizes mass distribution.The invention also relates to an aircraft comprising at least one such propulsion system. Figure 4.

Description

Title of the invention: Aircraft propulsion assembly comprising a supporting structure connecting an engine and a primary structure of a mast and supporting at least one accessory

[0001] The present application relates to an aircraft propulsion system comprising a support structure which connects an engine and a primary structure of a mast and supports at least one accessory and to an aircraft comprising at least one such propulsion system.

[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 direction 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. 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 which has 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 and / or the middle part 24.2 of the primary structure 24 and the rear part 22.3 of the reactor core 22, as well as two connecting rods 28.3, positioned symmetrically with respect to the vertical median plane 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 connecting 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 connecting the rear end 24.3 and / or the middle part 24.2 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 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.

[0009] Regardless of the embodiment, the motor attachment system 28 includes, for each of the first, second and third attachments 28.1, 28.2, 28.3, at least one anchor point located on the motor 16, some of these anchor points being offset along the longitudinal direction on the motor housing F22.

[0010] As illustrated in Figures 2 and 3, the F22 engine casing supports numerous accessories E which increase the weight of the assembly formed by the reactor core 40 and the accessories E supported by the reactor core 40.

[0011] This configuration is not optimal in terms of mass distribution.

[0012] The present invention aims to remedy all or part of the drawbacks of the prior art.

[0013] 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 nacelle positioned around the engine, c. a primary mast structure, d. at least one accessory, e. a motor attachment system, linking the primary structure and the motorization, which includes at least one front attachment directly linking the front part of the motorization and the primary structure.

[0014] According to the invention, the propulsion assembly comprises at least one supporting structure extending along an axis parallel to the longitudinal axis between the nacelle and the rear part of the engine, the supporting structure being connected to the front part of the engine. In addition, the engine attachment system comprises at least one rear attachment, offset rearward relative to the front attachment, connecting the primary structure and the supporting structure, the accessory being connected to the supporting structure.

[0015] This solution optimizes mass distribution by fixing the accessory on a structure separate from the motor.

[0016] According to another feature, the propulsion assembly includes at least one link ensuring a transfer of mechanical, electrical or fluidic energy between said at least one accessory and the motorization, and comprising first and second sections connected respectively to said at least one accessory and to the motorization as well as at least one connector configured to connect and disconnect the first and second sections.

[0017] According to another feature, the front attachment and the supporting structure are connected to the motor at approximately the same transverse attachment plane.

[0018] According to another feature, the supporting structure is tubular and extends all around the rear part of the motorization.

[0019] According to another feature, the load-bearing structure is a lattice structure which includes longitudinal reinforcements delimiting meshes.

[0020] According to another feature, the load-bearing structure extends between front and rear ends, the front end being connected to the motorization, the truss load-bearing structure comprising at least one transverse reinforcement located at the rear end.

[0021] According to another feature, at least one transverse reinforcement extends over the entire circumference of the rear part of the motorization so as to form a ring.

[0022] 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.

[0023] 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.

[0024] According to a first configuration, the front and rear parts of the engine are respectively a fan housing of a shrouded fan and a reactor core.

[0025] According to a second configuration, the front and rear parts of the engine are respectively a support structure on which a fan or an unfaired propeller is attached and a reactor core.

[0026] The invention also relates to an aircraft comprising at least one propulsion assembly according to one of the preceding characteristics.

[0027] 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:

[0028] [Fig-1] is a perspective view of an aircraft,

[0029] [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,

[0030] [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,

[0031] [Fig.4] is a schematic side view of a propulsion assembly aircraft (without nacelle) illustrating one embodiment of the invention,

[0032] [Fig.5] is a schematic cross-section of a propulsion assembly aircraft illustrating one embodiment of the invention,

[0033] [Fig.6] is a schematic cross-section of a propulsion assembly of an aircraft illustrating another embodiment of the invention,

[0034] [Fig.7] is a schematic side view of a propulsion assembly aircraft (without nacelle) illustrating one embodiment of the invention,

[0035] [Fig.8] is a schematic perspective representation from the rear of the propulsion assembly (without nacelle) visible in [Fig.7],

[0036] [Fig.9] is a front view of a rear attachment illustrating one embodiment of the invention,

[0037] [Fig. 10] is a schematic lateral representation of an aircraft propulsion assembly comprising a lattice support structure illustrating one embodiment of the invention,

[0038] [Fig. 11] is a schematic side view of an aircraft propulsion assembly comprising a lattice support structure illustrating another embodiment of the invention.

[0039] According to an embodiment shown in Figures 3 to 8, 10 and 11, a propulsion assembly 30 comprises a motor 32 having a rotation axis A32, a nacelle 33 (visible in Figures 5 and 6) positioned around the motor 32, and a mast 34 configured to connect the propulsion assembly 30, and more particularly the motor 32, to a wing 36 of an aircraft. The latter comprises at least one such propulsion assembly 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 reactor core 40 comprises, from front to rear, a front 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 front and rear sections 40.1, 40.3. The reactor core 40 has an outer casing called the engine casing F40, visible in particular in [Fig. 4].

[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 one 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 direction, between the nacelle and the reactor core 40, the front end 48.1 being connected to the engine 32. According to a preferred embodiment, the support structure 48, more particularly its front end 48.1, is connected to the fan 38 and more particularly to the fan casing 38.1.

[0045] 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. Depending on one arrangement, the rear attachment 46.2 connects the middle portion 42.2 and / or the rear end 42.3 of the primary structure 42 and the end rear 48.2 of the supporting structure 48 or an area located near this rear end 48.2.

[0046] 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.

[0047] 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.

[0048] 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 a transverse attachment plane PTA. The supporting structure 48 is also connected to the motor 32 approximately at the transverse attachment plane PTA.

[0049] 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.

[0050] According to one embodiment, the load-bearing structure 48 is a beam that does not extend around the reactor core 40.

[0051] According to another embodiment, 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. According to this embodiment, as illustrated in Figures 5 and 6, the supporting structure 48 comprises an inner face F48 oriented towards the reactor core 40 and an outer face F48' oriented towards the nacelle 33.

[0052] According to a first embodiment visible in [Fig.4], the supporting structure 48 is cylindrical.

[0053] According to another embodiment visible in [Fig. 10], the supporting structure 48 has a barrel shape.

[0054] According to another embodiment visible in [Fig. 11], the supporting structure 48 has a hyperboloid shape.

[0055] Of course, the invention is not limited to these geometries for the load-bearing structure 48.

[0056] 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.

[0057] 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.

[0058] According to one embodiment, particularly as shown in Figures 10 and 11, the load-bearing structure 48 is a perforated structure distinct from the primary structure 42 of the mast and the outer casing F40 of the reactor core 40. This perforated structure has an openness ratio (corresponding to the ratio of the sum of the open areas to the total area) of at least 50%. Moreover, unlike the outer casing F40 of the reactor core 40, it has sufficient rigidity to form a load path between the engine 32 and the primary structure 42. In one configuration, the perforated structure is a truss structure comprising several longitudinal reinforcements 50 and at least one transverse reinforcement 52. The truss load-bearing structure 48 may include at least one longitudinal reinforcement extending from its front end 48.1 to its rear end 48.2.

[0059] 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.

[0060] 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 among a pin, a rivet, a bolt or any other linkage element.

[0061] 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 among a pin, a rivet, a bolt or any other linking element.

[0062] According to an embodiment visible for example in figures 10 and 11, the load-bearing truss structure 48 includes a single rear transverse reinforcement 52 located at its rear end 48.2.

[0063] According to another embodiment visible in [Fig.7], 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.

[0064] 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.

[0065] According to embodiments shown in Figures 10 and 11, the longitudinal reinforcements 50 are connected to each other at nodes 56 so as to form quadrilateral or triangular 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.

[0066] According to another embodiment visible in [Fig.7], the longitudinal reinforcements 50, the transverse reinforcements 52, 52' and the motorization 32 are connected together so as to form triangular meshes.

[0067] Of course, the invention is not limited to these geometries for the mesh. Generally, the longitudinal openwork structure 48 in lattice form comprises longitudinal reinforcements 50 and / or at least one transverse reinforcement 52 connected together so as to form quadrilateral or triangular meshes in order to obtain an openwork structure.

[0068] The longitudinal and transverse reinforcements 50, 52, 52' can be metallic and / or made of composite material.

[0069] 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.

[0070] 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 its ends oriented towards the primary structure 42.

[0071] According to an embodiment shown in detail in [Fig. 9], 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 around 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.

[0072] The different pivot axes 60.1, 60.2, 62.1, 62.2, 62.3 are substantially parallel to each other and to the longitudinal direction X.

[0073] 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 absorption of torsional forces along the longitudinal direction X.

[0074] According to one embodiment, the engine attachment system 46 includes at least one fail-safe type connection 64, 64' linking the primary structure 42 and the supporting structure 48 or the engine 32, in particular the reactor core 40, configured not to form a path of forces when the rear attachment 46.2 is operational and functioning correctly and to form a path of forces in case of damage to the rear attachment 46.2.

[0075] According to an arrangement visible in [Fig.9], 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.

[0076] The propulsion assembly 30 includes at least one accessory 66 necessary for the proper operation of the motor 32. The accessory 66 is selected from a non-exhaustive list of accessories including heat exchangers, pumps, sensors, or electrical or hydraulic control devices, ...

[0077] The propulsion assembly 30 comprises, for at least one accessory 66, depending on its nature, at least one link 68 ensuring the transfer of mechanical, electrical, or fluidic energy between the accessory 66 and the motor 32 and / or to an element positioned in the mast 34, the wing 36, or the fuselage of the aircraft. Depending on one configuration, the energy and / or information link 68 comprises first and second sections 68.1, 68.2 connected respectively to the accessory 66 and the motor 32, as well as at least one connector 68.3 configured to connect and disconnect the first and second sections 68.1, 68.2.

[0078] According to a particular feature of the invention, at least one accessory 66 is connected to the supporting structure 48 in the space between the nacelle 33 and the reactor core 40.

[0079] According to an arrangement visible in Figures 5, the accessory 66 is positioned against the inner face F48. According to another arrangement visible in [Fig. 6], the motor equipment 66 is positioned against the outer face F48'.

[0080] According to one embodiment, the propulsion assembly 30 includes several accessories 66 connected to the supporting structure 48 and positioned on the inner face F48 and / or on the outer face F48'.

[0081] According to a configuration visible in figures 5 and 6, at least one accessory 66' inseparable from the reactor core 40 is fixed to the latter.

[0082] According to the invention, a maximum number of accessories 66 are connected to the supporting structure 48 in order to reduce the number of accessories 66' supported by the reactor core 40.

[0083] This solution optimizes mass distribution by reducing the mass of accessories 66 supported by the motor 32.

[0084] Regardless of the embodiment, the supporting structure 48 (whether solid, openwork or lattice) ensures a transfer of loads 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.

[0085] The fact that the supporting structure 48 is a lattice structure allows for an openwork design that facilitates access to the reactor core 40, particularly for maintenance or repair operations. Finally, the use of a lattice structure reduces mass and provides a rigid structure with significant stiffness in all directions.

[0086] 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 in a longitudinal direction and comprises a front portion and a rear portion connected to the front portion and offset rearward in the longitudinal direction relative to the front portion. The rear portion may be 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 onto which is mounted an unshrouded fan or propeller, or any other structure of an engine 32 positioned forward of the latter and 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

1.

2.

3. Demands Aircraft propulsion assembly (30) comprising: a. an engine (32) which extends from front to rear along a longitudinal axis (X) 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 cross-section greater than that of the rear part, b. a nacelle (33) positioned around the motor (32), c. a primary structure (42) of a mast (34), d. at least one accessory (66), e. a motor attachment system (46), connecting the primary structure (42) and the motorization (32), which includes at least one front attachment (46.1) directly connecting the front part of the motorization (32) and the primary structure (42); f. characterized in that the propulsion assembly (30) comprises at least one support structure (48) which extends along an axis parallel to the longitudinal axis (X) between the nacelle (33) and the rear part of the engine (32), the support structure being connected to the front part of the engine (32), in that the engine 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) and in that at least one accessory (66) is connected to the support structure (48). Propulsion assembly (30) according to the preceding claim, characterized in that the propulsion assembly comprises at least one link (68) ensuring a transfer of mechanical, electrical or fluidic energy between said at least one accessory (66) and the motorization (32) and comprising first and second sections (68.1, 68.2) connected respectively to said at least one accessory (66) and to the motorization (32) as well as at least one connector (68.3) configured to connect and disconnect the first and second sections (68.1, 68.2). Propulsion assembly (30) according to any one of the preceding claims, characterized in that the front attachment (46.1) and the load-bearing structure (48) are connected to the motorization (32) at approximately the same transverse attachment plane (PTA).

4. Propulsion assembly (30) according to any one of the preceding claims, characterized in that the supporting structure (48) is tubular and extends all around the rear part of the motorization (32).

5. Propulsion assembly (30) according to any one of the preceding claims, characterized in that the supporting structure (48) is a lattice structure and includes longitudinal reinforcements (50) delimiting 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 lattice 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 at least one transverse reinforcement (52, 52') extends over the entire circumference of the rear part of the motorization (32) so as to form a ring.

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 engine attachment system (46) includes at least one fail-safe type safety link (64, 64'), connecting the primary structure (42) and the load-bearing 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 front and rear parts of the engine (32) are respectively a fan casing (38.1) of a shrouded fan and a reactor core (40).

11. Propulsion assembly according to any one of claims 1 to 9, characterized in that the front and rear parts of the engine (32) are respectively a support structure on which is attached a fan or an unfaired propeller and a reactor core (40).

12. Aircraft comprising at least one propulsion assembly (30) according to any one of the preceding claims.

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