PROPULSION ASSEMBLY FOR AN AIRCRAFT

Abstract

Propulsion assembly (10) for an aircraft, said propulsion assembly (10) comprising: - a turbomachine (14) including a fluidic system (18), - a cowling (16) which includes at least one panel (20) having a longitudinal edge (22) which is fixed by hinges (25), said at least one panel (20) carrying at least one surface heat exchanger (26) which includes a fluidic circuit (26') connected to said fluidic system (18), characterized in that the fluidic circuit (26') (20) is connected to the fluidic system (18) by at least one first push-fit fitting (30, 30') which is carried by the panel (20). Figure for the abbreviation: Figure 3

Description

Title of the invention: PROPULSION ASSEMBLY FOR AN AIRCRAFT Technical field of the invention

[0001] The present invention relates to a propulsion assembly for an aircraft. Technical background

[0002] The state of the art includes in particular document FR-A1-3 094 750.

[0003] Fig. 1 illustrates a propulsion assembly 10 for an aircraft.

[0004] In the present application, a propulsion unit 10 for an aircraft means an assembly comprising a reactor mast 12, a turbomachine 14 and its cowling 16.

[0005] The reactor pylon 12 is a massive component that allows a turbomachine 14 to be attached to an aircraft, and for example to a wing of the aircraft. The reactor pylon 12 therefore comprises elements for attaching it to the aircraft and elements for attaching the turbomachine 14. The reactor pylon 12 has a generally elongated shape and extends along a first axis A.

[0006] In the present application, the turbomachine 14 is located below or beside the engine pylon 12. The turbomachine may be suspended from the engine pylon 12 under the aircraft wing. Alternatively, the turbomachine may be installed at the rear of the aircraft fuselage.

[0007] The turbomachine 14 has a general elongated shape along a second axis B which can be parallel to the first axis A. The first and second axes A, B are located in the same plane P. This plane P can be vertical or inclined with respect to the vertical.

[0008] The terms 12 o'clock (for 12 o'clock) and 6 o'clock (for 6 o'clock) denote positions of parts around the second axis B, by analogy with the face of a clock when viewed from the rear. The 12 o'clock position is located in plane P and at the level of the reactor mast 12, and the 6 o'clock position is located in plane P below the turbomachine 14.

[0009] The turbomachine 14 includes a lubrication system 18 which allows in particular the lubrication of the turbomachine bearings by circulation of lubricating oil.

[0010] The cowling 16 surrounds the turbomachine 14 and extends along the second axis B. The cowling 16 may comprise several pieces and includes two panels 20 of generally semi-circular shape that extend on either side of the aforementioned plane P. These panels 20 include upper longitudinal edges 22 that are fixed to the reactor mast 12 and arranged on either side of the plane P, near the 12 o'clock position, and lower longitudinal edges 24 that are generally fixed to each other and are therefore located at the 6 o'clock position.

[0011] These panels 20 are hinged at their upper edges 22 so that they can be opened The cowling 16 allows access to the turbomachine 14 during ground maintenance operations, for example. This articulation is made possible by hinges 25 that attach the upper edges 22 of the panels 20 to the reactor mast 12. Each panel 20 is articulated around a third axis C, which can be parallel to the second axis B, for example, from a closed position in which its lower edge 24 is at the 6 o'clock position, to an open position in which its lower edge 24 is away from the 6 o'clock position.

[0012] The cowling 16 can carry at least one surface heat exchanger 26. Such a heat exchanger 26 comprises an oil circuit 26' connected to the lubrication system 18, and a heat exchange surface that is exposed to a cooling airflow. Heat exchange between the surface and the oil circuit 26' of the heat exchanger cools the oil from the lubrication system 18 before returning it to the lubrication system 18, as illustrated by the dashed arrows in [Fig. 1].

[0013] At least a portion of the cowling 16 can internally define an annular flow channel for an airflow around the turbomachine 14, such as a flow channel for a secondary or other flow. In this case, the heat exchange surface of the surface heat exchanger 26 is therefore swept by this airflow.

[0014] The heat exchanger 26 carried by the hood 16 is connected to the lubrication system 18 by means of fluidic connection which must allow the opening of the panels 20 and in particular their pivoting, without necessarily requiring the heat exchanger 26 to be disconnected from the lubrication system 18.

[0015] In the current technique, these connection means are flexible hoses 28, as illustrated in [Fig. 2]. Each of these hoses 28 comprises an end 28a attached to a panel 20 and intended to be connected to the heat exchanger 26 supported by this panel 20, and an opposite end 28b attached to the reactor tower 12 and intended to be connected to the lubrication system 18 of the turbomachine 14. Regardless of the position of the panel 20, the oil circuit 26' of the heat exchanger 26 remains connected to the lubrication system 18 thanks to the flexibility of the hoses 28. [Fig. 2] shows two distinct deformation states of the same hose 28 for two different positions of a panel 20.

[0016] This technology has some drawbacks. First, the area around the pipes 28 must remain clear so as not to impede their movement during the opening and closing of the panels 20. Furthermore, the pipes 28 are relatively long to allow for bending without causing stresses that could lead to breakage. This technology is therefore relatively bulky. In addition, these pipes 28 are oversized to ensure sufficient strength and, in particular, have a large diameter due to the presence of a thick protective layer around them. Finally, this technology is relatively expensive and of significant mass.

[0017] Furthermore, climate change is a major concern for many legislative and regulatory bodies worldwide. Indeed, various restrictions on carbon emissions have been, are being, or will be adopted by various states. In particular, an ambitious standard applies to both new types of aircraft and those already in service, requiring the implementation of technological solutions to bring them into compliance with current regulations. Civil aviation has been actively contributing to the fight against climate change for several years now. Technological research efforts have already led to very significant improvements in the environmental performance of aircraft.The Applicant takes into account the factors impacting all phases of design and development to obtain aeronautical components and products that are less energy-intensive, more environmentally friendly, and whose integration and use in civil aviation have moderate environmental consequences, with the aim of improving aircraft energy efficiency. Consequently, the Applicant continuously works to reduce its negative climate impact by employing methods and operating virtuous development and manufacturing processes that minimize greenhouse gas emissions to the minimum possible, thereby reducing the environmental footprint of its activities.This sustained research and development work focuses on new generations of aircraft engines, the weight reduction of aircraft, particularly through the materials used and lighter onboard equipment, the development of the use of electric technologies for propulsion, and, as essential complements to technological progress, aviation biofuels.

[0018] The present invention proposes a simple, effective and economical solution to at least some of the aforementioned problems of the prior art. Summary of the invention

[0019] The invention is the result of technological research aimed at significantly improving aircraft performance and, in this sense, contributes to reducing the environmental impact of aircraft.

[0020] The invention relates to a propulsion system for an aircraft, this propulsion system comprising:

[0021] - a turbomachine extending along a main axis and comprising a system fluidic

[0022] - a cowling that extends along and around said main axis, the cowling comprising at least one panel extending around said main axis, said at least a panel having a first longitudinal edge which is fixed by hinges which define a pivot axis of the panel, from a closed position in which it extends around the turbomachine to an open position in which it is away from the turbomachine, said at least one panel carrying at least one surface heat exchanger which includes a fluidic circuit connected to said fluidic system,

[0023] characterized in that the fluidic circuit of each of the panels is connected to the fluidic system by at least one first push-fit fitting which is carried by the panel, this first push-fit fitting being engaged in or on a second push-fit fitting of the propulsion assembly to ensure fluidic communication between the fittings when the panel is in the closed position, and being disengaged from this second fitting to break this fluidic communication when the panel is in the open position, each of the first and second fittings being equipped with a self-sealing valve.

[0024] The invention thus proposes to connect the fluid circuit of the panel heat exchanger to the turbomachine's fluid system via push-fit fittings. It is understood that in the closed position, the first and second fittings are inserted into each other and ensure fluid communication between the heat exchanger's fluid circuit and the fluid system. In the open position, the first and second fittings are separated from each other, and the heat exchanger's fluid circuit is no longer in fluid communication with the fluid system. Therefore, simply closing the panel allows the fittings to be inserted into each other, and opening the panel allows the fittings to be separated. Each of these fittings is equipped with a self-sealing valve. In this application, a valve is understood to mean an automatic closing system for the fitting.When a fitting is inserted into another fitting, the valve of each fitting is in a position that allows fluid to pass between the fittings. When a fitting is disassembled, the valve of that fitting is in a position that prevents fluid to pass.

[0025] The propulsion assembly according to the invention may comprise one or more of the following features, taken individually or in combination with each other:

[0026] — said at least one first snap-fit ​​fitting is located on one of the edges of the panel, such as its first edge or a second edge opposite the first edge,

[0027] — said fluid circuit is an oil circuit or a coolant circuit dissement, • The turbomachine includes a longitudinal structure located at a second longitudinal edge of the panel, opposite the first edge, when it is in the closed position, at least a portion of the second fittings being supported by this structure, • the propulsion assembly comprises a reactor mast extending along an axis parallel to the main axis of the turbomachine, the turbomachine being fixed to the reactor mast and extending below or beside this reactor mast which is located at the level of said first longitudinal edge of the panel when it is in the closed position, at least part of the second fittings being supported by this reactor mast, • at least part of the second set of connections is supported by another of the panels, • Each of the first fittings is configured to be engaged in or on one of the second fittings in a direction that is tangent to a circumference centered on the main axis of the turbomachine, • The first and second fittings are located in planes perpendicular to the main axis of the turbomachine. • Each panel includes at least two first connections, one of these first connections being connected to a fluid inlet of said circuit, and the other of these first connections being connected to a fluid outlet of said circuit, • The propulsion assembly includes at least two secondary connections, one of these secondary connections being connected to a fluidic inlet of said fluidic system, and the other of these secondary connections being connected to a fluidic outlet of said system, • Each panel includes an internal concave surface on which at least one heat exchanger is located.

[0028] — each of the first and second fittings is equipped with a ball or piston valve, • The propulsion assembly includes devices for locking the panels in the closed position, these devices being actuable from an unlocked position to a locked position, these devices being configured to cause the first fittings to engage with or onto the second fittings when they are moved from their unlocked position to their locked position,

[0029] — these devices are located next to said first fittings,

[0030] — the casing surrounds at least part of the turbomachine,

[0031] — the casing comprises two panels of generally semi-circular shape which extend on either side of the said main axis,

[0032] — each of these panels has an upper and lower longitudinal edge,

[0033] — the upper longitudinal edge of the panel or each panel is fixed by the hinges,

[0034] — the other of the panels carries another heat exchanger or another type fluidic equipment,

[0035] — said first and second fittings cooperate with each other by male interlocking female,

[0036] — the panel or each panel has a general semi-circular shape. Brief description of the figures

[0037] Other features and advantages will become apparent from the following description of a non-limiting embodiment of the invention with reference to the accompanying drawings in which:

[0038] [Fig-1] [Fig.1] is a partial schematic perspective view of an assembly propulsion system for an aircraft,

[0039] [Fig.2] [Fig.2] is a schematic perspective view of fluidic connection means of a heat exchanger to a fluidic system, according to the prior art of the invention, its cover panels being in the open position,

[0040] [Fig.3] [Fig.3] is a schematic perspective and front view of a propulsion assembly according to an embodiment of the invention,

[0041] [Fig.4] [Fig.4] is a very schematic view of the propulsion assembly of [Fig.3], with its cowling panels in the closed position,

[0042] [Fig.5] [Fig.5] is a very schematic view of the propulsion assembly of [Fig.3], with one of its cowling panels in the open position and the other in the closed position,

[0043] [Fig.6] [Fig.6] is a schematic perspective view of a first push-fit connector and a second push-fit connector usable within the framework of the present invention,

[0044] [Fig.7] [Fig.7] is a schematic half-view in axial section of a propulsion assembly according to an alternative embodiment of the invention,

[0045] [Fig.8] [Fig.8] is a schematic perspective view of the fittings of the propulsion assembly of [Fig.7], these fittings being nested one inside the other,

[0046] [Fig.9] [Fig.9] is a schematic perspective view of the fittings of the propulsion assembly of [Fig.7], these fittings being disassembled from one another,

[0047] [Fig. 10] [Fig. 10] is a schematic perspective view of a female fitting of the propulsion assembly of [Fig. 7],

[0048] [Fig. 11] [Fig. 11] is a schematic perspective view of a male fitting of the propulsion assembly of [Fig. 7],

[0049] [Fig. 12] [Fig. 12] is a schematic half-view in axial cross-section of a propulsion assembly according to another embodiment of the invention,

[0050] [Fig. 13] [Fig. 13] is a schematic half-view in cross-section of the propulsion assembly of [Fig. 12], one of its cowling panels being in the open position and the other in the closed position,

[0051] [Fig. 14] [Fig. 14] is a schematic cross-sectional view of the fittings of the assembly propulsive of the [Fig. 12], these fittings being nested one inside the other,

[0052] [Fig. 15] the [Fig. 15] is a schematic cross-sectional view of the fittings of the assembly propulsive of the [Fig. 12], these fittings being disassembled from one another,

[0053] [Fig. 16] [Fig. 16] is a schematic half-view in axial cross-section of a propulsion assembly according to another embodiment of the invention,

[0054] [Fig. 17] [Fig. 17] is a schematic half-view in cross-section of the propulsion assembly of [Fig. 16], one of its cowling panels being in the open position and the other in the closed position,

[0055] [Fig. 18] [Fig. 18] is a schematic cross-sectional view of the fittings of the propulsion assembly of [Fig. 16], these fittings being nested one inside the other,

[0056] [Fig. 19] [Fig. 19] is a schematic cross-sectional view of the fittings of the propulsion assembly of [Fig. 16], these fittings being disassembled from one another,

[0057] [Fig.20] [Fig.20] is a schematic cross-sectional view of the fittings of the propulsion assembly of [Fig.16], these fittings being nested one inside the other,

[0058] [Fig. 21] [Fig. 21] is a schematic cross-sectional view of the fittings of the propulsion assembly of [Fig. 16], these fittings being disassembled from one another, and

[0059] [Fig.22-23] Figures 22 and 23 are schematic cross-sectional views similar to those of Figures 20 and 21 and illustrating another embodiment variant. Detailed description of the invention

[0060] Figures 1 and 2 have already been described above.

[0061] Reference is made to Figures 3 to 6, which illustrate one embodiment of an assembly propulsive 10 according to the invention.

[0062] The propulsion assembly 10 can be located under the wing of the aircraft or at the rear of the fuselage of the aircraft, for example.

[0063] Furthermore, the propulsion assembly 10 can be of any type and for example of the type twin- or triple-flow turbojet, ducted or unducted fan turbomachine, turboprop, open rotor, etc.

[0064] The propulsion assembly 10 is similar to that described above in relation to [Fig. 1] and comprises:

[0065] - a reactor mast 12, although this is optional,

[0066] - a turbomachine 14 which includes a fluidic system 18, in particular its bearings and rotating elements, and

[0067] - a cowling 16 which can surround the turbomachine 14, as in example re presented.

[0068] The reactor mast 12 has an elongated shape along a first axis A.

[0069] The turbomachine 14 has an elongated shape along a second axis B substantially parallel to the first axis A. The turbomachine 14 is preferably located under the mast reactor 12 so that the axes A, B are contained in the same vertical plane P.

[0070] The reactor mast 12 is thus located at 12 o'clock (12 o'clock) by analogy with the face of a clock.

[0071] At 6 a.m. (6 o'clock), the turbomachine 14 includes a longitudinal mast 17 which forms part of the cowling 16 of the turbomachine 14.

[0072] The casing 16 may comprise several pieces and includes at least two panels 20 of generally semi-circular shape in the example shown. These panels 20 extend on either side of the vertical plane P.

[0073] In the example shown, the panels 20 include upper longitudinal edges 22 which are fixed to the turbomachine 14 or the reactor mast 12 by hinges 25. The upper edges 22 of the panels 20 are separated from each other by the reactor mast 12 in the example shown.

[0074] Each of the panels 20 is hinged about a third axis C which can be parallel to the axis B for example, from a closed position in which its lower edge 24 is applied against the structure 17, as is the case of the left panel in [Fig.4], to an open position in which its lower edge 24 is away from the structure 17, as is the case of the panels 20 in [Fig.3] and the left panel in [Fig.5].

[0075] The angular displacement (arrow Fl - [Fig.5]) between the two positions is for example greater than 30° around the axis C.

[0076] Each of the panels 20 comprises a wall 25 of generally curved shape which includes an external convex surface 25a and an internal concave surface 25b. At least one of these surfaces 25a, 25b is intended to be swept by a flow of gas.

[0077] Each of the panels 20 further comprises at least one surface heat exchanger 26.

[0078] In the example shown, the heat exchanger 26 is located on the internal concave surface 25b of the wall 25 and comprises a fluidic circuit 26' intended to be connected to the fluidic system 18, and a heat exchange surface that is exposed to the flow of cooling gas. This position of the heat exchanger 26 is not, however, limiting. Alternatively, the heat exchanger 26 could, for example, be located on an external convex surface of the panel 20.

[0079] Indeed, within the framework of the present invention, the panel 20 can be an internal or external panel of the turbomachine and propulsion assembly, and can be swept by a gas flow passing inside or outside the panel. The heat exchanger 26 is therefore located inside or outside the panel 20, and thus positioned on an internal or external surface of this panel 20.

[0080] The fluidic system 18 is, for example, a lubrication system but could in The alternative could be a cooling system. The fluid circuit 26' is, for example, an oil circuit but could alternatively be a coolant circuit.

[0081] The fluidic circuit 26' includes a fluidic inlet and outlet 26a, 26b which are connected to the fluidic system 18 by fluidic connection means.

[0082] In the context of the present invention, the connection means for a heat exchanger 26 are carried by the panel 20 that supports this heat exchanger. More specifically, the wall 25 of each of the panels 20 carries at least one push-fit fitting 30 for connecting the fluid circuit 26' to the fluid system 18.

[0083] In the example shown, the fittings 30 are located on the lower edges 24 of the panels 20. [Fig. 3] shows that each panel 20 comprises two male-type push-fit fittings 30 which are axially spaced from each other along the axis B. Each of these fittings 30 is intended to cooperate by male-female push-fit with a complementary fitting 30' carried by the mast 17. It is therefore understood that the mast 17 carries four fittings in the example shown, two fittings 30' are located on one side of the structure and intended to cooperate with the fittings 30 of a first panel 20, and two other fittings 30' are located on the other side of the structure and intended to cooperate with the fittings 30 of the second panel 20.

[0084] One of the fittings 30 of each panel 20 is connected to the inlet 26a of the circuit 26' of the heat exchanger 26 of that panel, and the other fitting 30 of that panel 20 is connected to the outlet of the circuit 26'. This connection can be made by rigid pipes 32.

[0085] On each side of the structure 17, one of the fittings 30' is connected to the inlet 18a of the fluidic system 18, and the other fitting 30' is connected to the outlet 18b of this system 18. This connection can be made by rigid pipes 34.

[0086] Fig. 6 shows a non-limiting example of the embodiment of the fittings 30, 30'. The fittings 30, 30' are preferably intended to cooperate with each other by male-female interlocking, the panels 20 being able to carry the male fittings, or conversely female fittings, and the structure 17 being able to carry the female fittings, or conversely male fittings.

[0087] A male fitting, such as that illustrated on the left in [Fig.6], includes a projecting end 30a, for example cylindrical, and an opposite end 30b for connection to one of the pipes 32.

[0088] The end 30a may include an annular groove 30d for housing a sealing gasket such as an O-ring for example

[0089] A female fitting, such as the one illustrated on the right in [Fig. 6], comprises a hollow end 30c, for example cylindrical, and an opposite end 30b for connection to one of the pipes 34. The ends 30a, 30c are intended to engage with each other. Each of these fittings 30, 30' comprises an internal passage extending between the two ends of the fitting and allowing fluid circulation between these ex- tremites.

[0090] As can be seen in figures 4 and 5, the engagement directions of the fittings (arrow F2) are tangent to circumferences centered on axis B.

[0091] The fittings 30, 30' are equipped with self-sealing valves 36, i.e., valves that automatically close the internal passages of the fittings (see [Fig. 6]). Each valve 36 can be moved from a closed position to an open position simply by inserting the fittings into each other. Each valve 36 can also be moved from an open position to a closed position simply by separating the fittings.

[0092] When a panel 20 is in the closed position, its fittings 30 are engaged in the fittings 30' of the structure 17 and this interlocking ensures fluid communication between the fittings and the connection of the circuit 26' to the fluid system 18. The valves 36 of the fittings are in a position where they do not obstruct the fluid passage between the fittings.

[0093] When a panel 20 is in the open position, its fittings 30 are disengaged from the fittings 30' and the valves 36 close the fluid passages of these fittings.

[0094] In the example shown, the propulsion assembly 10 includes devices 40 for locking the panels 20 in the closed position (Figures 4 and 5). The lower edge 24 of each panel 20 or of one of the panels 20 is equipped with a locking device 40 which cooperates with the structure 17 or the lower edge 24 of the other panel 20.

[0095] Figures 7 to 11 illustrate a variant embodiment of a propulsion assembly 10 according to the invention in which the elements already described above in relation to Figures 3 to 6 are designated by the same references.

[0096] One of the differences between this variant and the previous embodiment is that the fittings 30 of the panels 20 are located on their upper edges 22, therefore in the vicinity of the hinges 25 of articulation of these panels 20.

[0097] Another difference related to the first is that the 30' fittings which cooperate with the 30 fittings of the panels 20 are carried by the reactor mast 12.

[0098] One of the fittings 30 of each panel 20 is connected to the inlet 26a of the circuit 26' of the heat exchanger 26 of that panel, and the other fitting 30 of that panel 20 is connected to the outlet 26b of the circuit 26'. This connection can be made by rigid pipes 32.

[0099] On each side of the reactor mast 12, one of the fittings 30' is connected to the inlet 18a of the fluidic system 18, and the other fitting 30' is connected to the outlet 18b of this system 18. This connection can be made by rigid pipes 34.

[0100] Figures 8 to 11 show another non-limiting example of the implementation of the connections 30, 30'. The fittings 30, 30' are preferably intended to cooperate together by male-female interlocking, the panels 20 being able to carry the male fittings, or vice versa female, and the reactor mast 12 being able to carry the female fittings, or vice versa male.

[0101] A male fitting, such as that illustrated in [Fig. 11], comprises a projecting end 30a, for example cylindrical, and an opposite end 30b for connection to one of the pipes 32.

[0102] The projecting end 30a can carry a sealing gasket 31 such as an O-ring.

[0103] A female fitting, such as the one illustrated on the right in [Fig. 10], comprises a hollow end 30c, for example cylindrical, and an opposite end 30b for connection to one of the pipes 34. The ends 30a, 30c are designed to engage with each other. Each of these fittings 30, 30' comprises an internal passage extending between the two ends of the fitting and allowing fluid circulation between these ends.

[0104] The fittings 30, 30' of figures 8 to 11 are in the form of housings.

[0105] As can be seen in Figures 8 and 9, the engagement directions of the fittings (arrow F2 - [Fig.9]) are tangent to circumferences centered on axis B.

[0106] The fittings 30, 30' are equipped with valves 36 as mentioned above.

[0107] Figures 12 to 15 illustrate an alternative embodiment of a propulsion assembly 10 according to the invention in which the elements already described above are designated by the same references.

[0108] As in the embodiment of figures 3 to 6, the fittings 30 of the panels 20 are located on their lower edges 24.

[0109] Figures 14 and 15 show a more concrete example of the realization of the devices 40 for locking the panels 20 together.

[0110] At least one of the panels 20 may include one or more of these devices 40. Each device 40 includes a hook 42 and a lever 44 for actuating this hook 42. One of the panels 20 carries this device 40 and the other panel 20 includes, opposite this device, a finger 46 or similar device intended to cooperate with this hook 42. When the edges 24 of the panels are brought together, the hook 42 engages with the finger 46 and the actuation of the lever 44 causes a pulling force on the hook 42 on the side opposite the finger 46, which causes the panels 20 to clamp against each other and lock them.

[0111] Figures 14 and 15 also show a more concrete example of the realization of the end pieces 30, 30'. The end pieces 30 are straight and the end pieces 30' are bent in this example.

[0112] Furthermore, the fittings 30 are of the male type and their valves 36 are of the ball type. A ball 50 is housed in the fitting 30 and is movable from a position of closure of the fitting, in which it rests on a seat 52 of the fitting 30, until an opening position of the fitting, in which it is away from this seat 52. The ball 50 is forced into the closed position by a spring 54.

[0113] The fittings 30' are of the female type and their valves 36 are of the piston type. A piston 60 is housed in the fitting 30' and is movable from a closed position of the fitting, in which it bears against a seat 62 of the fitting 30', to an open position of the fitting, in which it is away from this seat 62. The piston 60 is forced into the closed position by a spring 64. Furthermore, the piston 60 includes an extension 66 which is designed to bear against the ball 50 of the corresponding fitting 30 and force it into its open position, when the fittings 30, 30' are engaged with each other (arrow F2).

[0114] One or the other of the fittings 30, 30' carries a sealing gasket 31 such as an O-ring.

[0115] Figures 16 to 21 illustrate a variant embodiment of a propulsion assembly 10 according to the invention in which the elements already described above are designated by the same references.

[0116] The fittings 30 of the panels 20 are located here both on their lower edges 24 and their upper edges 22. The upper edges 22 of the panels 20 thus include fittings 30 which are similar to those in Figures 7 to 11 and which cooperate with fittings 30' carried by the reactor mast 12. These fittings 30 are for example connected to an inlet 26a and an outlet 26b of the circuit 26' of one or more heat exchangers 26.

[0117] The lower edge 24 of one of the panels 20 includes fittings 30 which are similar to those in Figures 3 to 6 and which cooperate with fittings 30' carried by the other of the panels 20. The direct connection of the fittings 30, 30' of the panels 20 allows their circuits 26' to be connected together, these circuits 26' being connected to the fluidic system 18 by the fittings 30 located on the upper edges 22 of the panels 20.

[0118] The fittings 30 located on the upper edges 22 of the panels 20 are straight and cooperate with angled fittings 30' of the reactor mast 12, in the example illustrated in figures 18 and 19.

[0119] The joints 30, 30' of the lower edges 24 of the panels 20 are straight in the example illustrated in figures 20 and 21.

[0120] A locking device 40 is located at these edges 24 to cause the fittings 30, 30' to interlock when locked.

[0121] Figures 22 and 23 show another example of the realization of the joints 30, 30' at the lower edges 24 of the panels 20.

[0122] The lower edge 24 of each of the panels 20 is equipped with two fittings 30 or 30' which are arranged next to each other, and for example one above the other.

[0123] A locking device 40 is located at these edges 24 to cause the interlocking of the 30, 30' fittings during locking.

[0124] The present invention has several advantages, including: - the 30, 30' fittings are rigid, which represents a gain in mass and cost compared to the means of connection of the previous technique; - the fittings can be combined or mounted near the hinges 25, - The diameter of the fittings can be reduced compared to that of the connection methods of the previous technique, thus also limiting their size, - There is no movement in the pipes connected to these fittings, which simplifies the integration and assembly of the various parts. - The connection length of the fluidic circuit to the fluidic system is optimized to reduce its size and cost, - Maintenance of the propulsion system is improved by optimizing the dismantling of the fluidic circuit of the heat exchanger on each panel, - quick connection and disconnection of fittings without risk of leakage, - no special tools are needed to close or open the fittings as well as the fluid circuits, etc.

Claims

Claims

1. Propulsion assembly (10) for an aircraft, this propulsion assembly (10) comprising: - a turbomachine (14) extending along a main axis (B) and comprising a fluidic system (18), - a cowling (16) which extends along and around said main axis (B), the cowling (16) comprising at least one panel (20) which extends around said main axis (B), said at least one panel (20) comprising a first longitudinal edge (22) which is fixed by hinges (25) which define an axis (C) of pivoting of the panel, from a closed position in which it extends around the turbomachine (14) to an open position in which it is spaced from the turbomachine (14), said at least one panel (20) carrying at least one surface heat exchanger (26) which comprises a fluidic circuit (26') connected to said fluidic system (18),characterized in that the fluid circuit (26') (20) is connected to the fluid system (18) by at least one first push-fit connector (30, 30') which is carried by the panel (20), this first push-fit connector (30) being engaged in or on a second push-fit connector (30') of the propulsion unit (10) to ensure fluid communication between the connectors (30, 30') when the panel (20) is in the closed position, and being disengaged from this second connector (30') to break this fluid communication when the panel (20) is in the open position, each of the first and second connectors (30, 30') being equipped with a self-sealing valve.,

2. Propulsion assembly (10) according to claim 1, in which the turbomachine (14) comprises a longitudinal structure (17) which is located at a second longitudinal edge (24) of the panel (20), opposite said first edge (22), when it is in the closed position, at least a part of the second connections (30') being carried by this structure (17).

3. A propulsion assembly (10) according to claim 1 or 2, wherein the propulsion assembly (10) comprises a reactor mast (12) extending along an axis (A) parallel to the main axis (B) of the turbomachine (14), the turbomachine (14) being fixed to the reactor mast (12) and extending under or beside this reactor mast which is located at said first longitudinal edge (22) of the panel (20) when it is in the closed position, at least a portion of the second fittings (30') being carried by this mast reactor (12).

4. Propulsion assembly (10) according to one of the preceding claims, in which at least a portion of the second connections (30') is carried by another of the panels (20).

5. Propulsion assembly (10) according to one of the preceding claims, in which each of the first connections (30, 30') is configured to be engaged in or on one of the second connections (30') in a direction (F2) which is tangent to a circumference centered on the main axis (B) of the turbomachine (14).

6. Propulsion assembly (10) according to one of the preceding claims, in which the first and second connections (30, 30') are located in planes perpendicular to the main axis (B) of the turbomachine (14).

7. Propulsion assembly (10) according to one of the preceding claims, in which each of the panels (20) comprises at least two first connectors (30), one of these first connectors (30) being connected to a fluid inlet (26a) of said circuit (26'), and the other of these first connectors (30) being connected to a fluid outlet (26b) of this circuit (26').

8. Propulsion assembly (10) according to claim 7, in which it comprises at least two second connections (30'), one of these second connections (30') being connected to a fluid inlet (18a) of said fluid system (18), and the other of these second connections (30') being connected to a fluid outlet (18b) of this system (18).

9. Propulsion assembly (10) according to one of the preceding claims, in which each of the panels (20) comprises an internal concave surface on which said at least one exchanger (26) is located.

10. Propulsion assembly (10) according to one of the preceding claims, in which it comprises devices (50) for locking the panels (20) in the closed position, these devices (50) being operable from an unlocking position to a locking position, these devices (50) being configured to cause the first fittings (30) to fit into or onto the second fittings (30') when they are brought from their unlocking position to their locking position.

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