Propulsion unit for an aircraft
Patent Information
- Application Number
- EP2023813818
- Authority / Receiving Office
- EP · EP
- Patent Type
- Applications
- Current Assignee / Owner
- Priority Date
- 2022-11-24
- Filing Date
- 2023-11-15
- Publication Date
- 2025-10-01
AI Technical Summary
Current propulsion assembly technologies for aircraft are bulky, expensive, and environmentally impactful due to the use of flexible and oversized fluid connection pipes, which hinder movement and contribute to carbon emissions, necessitating a more efficient and environmentally friendly solution.
A propulsion assembly with a rotating fluidic connection integrated into the articulation hinges of the cowling panels, allowing for fluid communication between the turbomachine's fluidic system and the heat exchanger, which remains connected without separate fluidic pipes, ensuring seamless movement and reducing environmental footprint.
The solution provides a compact, cost-effective, and environmentally friendly propulsion assembly that minimizes carbon emissions by eliminating the need for bulky fluid connection pipes, enhancing energy efficiency and reducing the environmental impact of aircraft operations.
Smart Images
Figure 1.1
Abstract
Description
[0001] DESCRIPTION
[0002] TITLE: PROPULSION UNIT FOR AN AIRCRAFT
[0003] Technical field of the invention
[0004] The present invention relates to a propulsion assembly for an aircraft.
[0005] Technical background
[0006] The state of the art includes in particular document FR-A1 -3 094 750, US-A1- 2020 / 049028 and CN-A1 -104 791 522.
[0007] Figure 1 illustrates a propulsion assembly 10 for an aircraft.
[0008] In the present application, the term propulsion unit 10 for an aircraft means an assembly comprising a reactor mast 12, a turbomachine 14 and its cowling 16.
[0009] The engine pylon 12 is a solid part that allows a turbomachine 14 to be attached to an aircraft, and for example to a wing of the aircraft. The engine pylon 12 therefore comprises elements for attachment to the aircraft and elements for attachment to the turbomachine 14. The engine pylon 12 has a generally elongated shape and extends along a first axis A.
[0010] In the present application, the turbomachine 14 is located under the engine pylon 12 or next to the engine pylon. The turbomachine may be suspended from the engine pylon 12 under the wing of the aircraft. Alternatively, the turbomachine may be installed at the rear of the fuselage of the aircraft.
[0011] The turbomachine 14 has a general shape elongated 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 relative to the vertical.
[0012] The positions of parts around the second axis B are designated by 12h (for 12 hours) and 6h (for 6 hours), by analogy with the dial of a clock when looking at the assembly from the rear. The 12h position is located in the plane P and at the level of the engine pylon 12, and the 6h position is located in the plane P under the turbomachine 14.
[0013] The turbomachine 14 comprises a lubrication system 18 which in particular makes it possible to lubricate bearings of the turbomachine by circulating lubricating oil.
[0014] The cowling 16 surrounds the turbomachine 14 and extends along the second axis B. The cowling 16 may comprise several pieces and comprises two panels 20 of generally semi-circular shape which extend on either side of the aforementioned plane P. These panels 20 comprise upper longitudinal edges 22 which are fixed to the engine pylon 12 and arranged on either side of the plane P, close to the 12 o'clock position, and lower longitudinal edges 24 which are generally fixed to each other and are therefore located at the 6 o'clock position.
[0015] These panels 20 are hinged by their upper edges 22 to be able to open the cowling 16 and intervene in the turbomachine 14 during a ground maintenance operation for example. This articulation is made possible by hinges 25 for fixing the upper edges 22 of the panels 20 to the engine mast 12. Each of the panels 20 is hinged 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.
[0016] The cowling 16 may carry at least one surface heat exchanger 26. An exchanger 26 of this type comprises an oil circuit 26' connected to the lubrication system 18, and an exchange surface which is exposed to a flow of cooling air. An exchange of calories between the surface and the oil circuit 26' of the exchanger makes it possible to cool the oil coming from the lubrication system 18 before returning it to this lubrication system 18, as illustrated by the dotted arrows in FIG. 1.
[0017] At least a portion of the cowling 16 may internally define an annular flow vein for an air flow around the turbomachine 14, such as a flow vein for a secondary flow or other. In this case, the exchange surface of the surface exchanger 26 is therefore swept by this air flow.
[0018] The exchanger 26 carried by the cowling 16 is connected to the lubrication system 18 by fluid connection means which must allow the opening of the panels 20 and in particular their pivoting, without necessarily requiring the exchanger 26 to be disconnected from the lubrication system 18.
[0019] In the current technique, these connection means are flexible and supple pipes 28, as illustrated in FIG. 2. Each of these pipes 28 comprises an end 28a secured to a panel 20 and intended to be connected to the exchanger 26 carried by this panel 20, and an opposite end 28b secured to the reactor mast 12 and intended to be connected to the lubrication system 18 of the turbomachine 14. Whatever the position of the panel 20, the oil circuit 26' of the exchanger 26 remains connected to the lubrication system 18 thanks to the flexibility of the pipes 28. FIG. 2 shows two distinct states of deformation of the same pipe 28 for two different positions of a panel 20.
[0020] This technology has drawbacks. First of all, it is necessary for the environment around the pipes 28 to remain free so as not to hinder the movement of the pipes 28 when opening and closing the panels 20. The pipes 28 also have a relatively long length to allow their bending without causing stresses leading to breakage or permanent deformation. This technology is therefore relatively bulky. Furthermore, these pipes 28 are oversized to be sufficiently strong and in particular have a large diameter due to the presence of a thick protective layer around these pipes 28. Finally, this technology is relatively expensive and of significant mass.
[0021] Furthermore, climate change is a major concern for many legislative and regulatory bodies around the world. 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 aircraft types and those already in operation, requiring the implementation of technological solutions to make them compliant with current regulations. Civil aviation has been mobilizing for several years now to contribute to the fight against climate change. Technological research efforts have already led to significant improvements in the environmental performance of aircraft.The Applicant takes into consideration the impact factors in all phases of design and development to obtain less energy-intensive, more environmentally friendly aeronautical components and products whose integration and use in civil aviation have moderate environmental consequences with the aim of improving the energy efficiency of aircraft. Consequently, the Applicant is constantly working to reduce its negative climate impact by using methods and operating virtuous development and manufacturing processes and minimizing greenhouse gas emissions to the minimum possible to reduce the environmental footprint of its activity.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 on-board equipment, the development of the use of electrical technologies to ensure propulsion, and, as an essential complement to technological progress, aeronautical biofuels.
[0022] The present invention provides a simple, effective and economical solution to at least some of the above-mentioned problems of the prior art.
[0023] Summary of the invention The invention is the result of technological research aimed at significantly improving the performance of aircraft and, in this sense, contributes to reducing the environmental impact of aircraft.
[0024] The invention relates to a propulsion assembly for an aircraft, this propulsion assembly comprising:
[0025] - a reactor mast extending along a first axis,
[0026] - a turbomachine attached to the reactor mast, this turbomachine extending along a second axis, the first and second axes extending in the same plane, the turbomachine comprising a fluidic system,
[0027] - a cowling which extends along and around the second axis, the cowling comprising at least one panel which extends around said second axis, said at least one panel comprising a longitudinal edge which is fixed to the engine pylon by hinges which define a third pivot axis of the panel, from a closed position in which it extends around the turbomachine to an open position in which it is spaced from the turbomachine, said at least one panel carrying at least one surface heat exchanger which comprises a fluid circuit connected to said fluid system, characterized in that the fluid circuit is connected to the fluid system by at least one of said hinges which forms a rotating fluid connection, this hinge comprising a hinge axis mounted inside a hinge body, the axis and the hinge body being movable relative to each other with respect to the third axis,said hinge axis comprising at least one internal fluid passage and an external cylindrical surface onto which at least one orifice opens in fluid communication with this internal passage, said hinge body extending around said external cylindrical surface and comprising an internal passage which is configured to be placed in fluid communication with said orifice when the panel is in the closed position. Advantageously, the internal passage of the hinge body is configured to be fluidically isolated from said orifice when the panel is in the open position.,
[0028] The invention thus proposes to connect the fluid circuit of the panel exchanger to the fluid system of the turbomachine, by means of at least one of the articulation hinges of the panel, this hinge thus forming a rotating fluid connection. A first specific feature of this rotating fluid connection is that it is centered on the third axis, that is to say on the articulation axis of the corresponding panel. There is therefore no particular force undergone by the connection insofar as it follows the movements of the panel during its movements. Another specific feature of the rotating connection is that it is integrated into a hinge and therefore does not require separate elements. The fluid connection between the fluid circuit and the fluid system depends on the position of the panel around its articulation axis. When the panel is closed, the fluid circuit is connected to the fluid system by the rotating connection which is "open".When the panel is open, the fluid circuit is connected to the fluid system by the rotating connection which is advantageously “closed”, thus preventing fluid leaks at the rotating connection.
[0029] The propulsion assembly according to the invention may comprise one or more of the following characteristics, taken in isolation from one another, or in combination with one another:
[0030] - the hinge pin is mounted movably inside the hinge body, the hinge pin being secured to the panel, and the hinge body being secured to the engine mast,
[0031] - a valve is mounted between the fluid system and the rotating fluid connection,
[0032] - the fluid circuit is connected to the fluid system by two rotating connections, a first of these rotating connections being connected to an inlet of said fluid circuit, and a second of these rotating connections being connected to a fluid outlet of said circuit, - the first and second rotating connections are formed by two separate hinges and are at a distance from each other,
[0033] - the first and second rotating connections are formed by the same hinge and are twinned,
[0034] - the hinge axis is connected to the fluid circuit by at least one rigid pipe,
[0035] - the hinge body is connected to the fluid system by at least one rigid pipe,
[0036] -- said plane in which the first and second axes extend is vertical or inclined relative to the vertical;
[0037] -- said fluid circuit is a lubrication circuit or a coolant circuit;
[0038] -- the cowling surrounds at least part of the turbomachine;
[0039] -- the cowling comprises two panels of generally semi-circular shape which extend on either side of said main axis;
[0040] - each of these panels has an upper longitudinal edge and a lower longitudinal edge;
[0041] - the upper longitudinal edge of the or each panel is fixed by the hinges;
[0042] - the other of the panels carries another heat exchanger or another type of fluidic equipment;
[0043] - the turbomachine extends under the reactor mast or next to the reactor mast;
[0044] - the or each panel has a general semi-cylindrical shape.
[0045] Brief description of the figures
[0046] Other characteristics and advantages will emerge from the following description of a non-limiting embodiment of the invention with reference to the appended drawings in which:
[0047] [Fig. 1] Figure 1 is a partial schematic perspective view of a propulsion unit for an aircraft, [Fig. 2] Figure 2 is a schematic perspective view of means for fluidic connection of a heat exchanger to a fluidic system, according to the technique prior to the invention,
[0048] [Fig. 3] Figure 3 is a half schematic view in axial section of a propulsion assembly for an aircraft, and illustrates a first embodiment of the invention,
[0049] [Fig. 4a-4b] Figures 4a and 4b are partial schematic cross-sectional views of the propulsion assembly of Figure 3, and show two distinct positions of a cowling panel of this propulsion assembly, [Fig. 5a-5b] Figures 5a and 5b are respectively a schematic perspective view with partial cutaway of the swivel fluid connection of the propulsion assembly of Figure 3, and a schematic cross-sectional view of this connection, and illustrate this fluid connection in the open state, [Fig. 6a-6b] Figures 6a and 6b are respectively a schematic perspective view with partial cutaway of the swivel fluid connection of the propulsion assembly of Figure 3, and a schematic cross-sectional view of this connection, and illustrate this fluid connection in the closed state, [Fig.7] Figure 7 is a half schematic axial sectional view of a propulsion assembly for an aircraft, and illustrates a second embodiment of the invention, and.
[0050] [Fig. 8] Figure 8 is a half schematic axial sectional view of a propulsion assembly for an aircraft, and illustrates a third embodiment of the invention.
[0051] [Fig. 9a-9b] Figures 9a and 9b are respectively a schematic perspective view with partial cutaway of the swivel fluid connection of the propulsion assembly of Figure 8, and a schematic cross-sectional view of this connection, and illustrate this fluid connection in the open state, and
[0052] [Fig. 10a-10b] Figures 10a and 10b are respectively a schematic perspective view with partial cutaway of the swivel fluid connection of the propulsion assembly of Figure 8, and a schematic cross-sectional view of this connection, and illustrate this fluid connection in the closed state.
[0053] Detailed description of the invention
[0054] Figures 1 and 2 have already been described in the above.
[0055] Figure 3 illustrates a first embodiment of a propulsion assembly 10 according to the invention. This propulsion assembly 10 comprises:
[0056] - a 12 reactor mast,
[0057] - a turbomachine 14 comprising a fluidic system 18, in particular its bearings and rotating elements, and
[0058] - a cowling 16 which can surround the turbomachine 14, as in the example shown.
[0059] The propulsion unit 10 may be located under the wing of the aircraft or at the rear of the fuselage of the aircraft, for example.
[0060] Furthermore, the propulsion unit 10 may be of any type and for example of the double or triple flow turbojet type, turbomachine with ducted or unducted fan, turboprop, open rotor, etc.
[0061] The fluidic system 18 is for example a fluidic system but could alternatively be a cooling system.
[0062] The cowling 16 comprises two panels 20 of generally semi-circular shape which extend on either side of the plane P passing through the respective axes A, B of the reactor mast 12 and the turbomachine 14.
[0063] In the example shown, the panels 20 comprise upper longitudinal edges 22 which are fixed to the reactor mast 12 by hinges 25. These upper edges 22 are located substantially in a 12 o'clock position while being separated from each other by the reactor mast 12.
[0064] In the example shown, there are three hinges 25 arranged one behind the other along the axis C. It can therefore be considered that there is an upstream hinge 25a, an intermediate hinge 25b and a downstream hinge 25c. Preferably, two of these hinges are mounted fixed and the third is mounted floating so as to have perfect alignment.
[0065] Each of the panels 20 is articulated around a third axis C which may be parallel to the axis B for example, from a closed position in which its lower edge (not visible) is substantially at the 6 o'clock position, to an open position in which its lower edge is distant from the 6 o'clock position. One of the panels 20 in its closed position is illustrated in Figure 4a, and this same panel 20 in its open position is illustrated in Figure 4b. The angular movement (arrow F) between the two positions is for example greater than 30° around the axis C (Figures 4a-4b).
[0066] Each of the panels 20 carries at least one surface heat exchanger 26 which comprises a fluid or fluid circuit 26' connected to the fluid system 18, and an exchange surface which is exposed to a flow of cooling gas.
[0067] In the example shown, the exchanger 26 is located on a concave curved surface of the panel 20, which is oriented towards the axis B, and which is therefore an internal surface of the panel. This position is not limiting. Alternatively, the exchanger 26 could for example be on an external convex surface of the panel 20.
[0068] Indeed, in the context of the present invention, the panel 20 may be an internal or external panel of the turbomachine and of the propulsion assembly, and may be swept by a gas flow passing inside or outside the panel (in particular a secondary flow or a flow external to the turbomachine). The exchanger 26 is therefore located inside or outside the panel 20, and therefore positioned on an internal or external surface of this panel 20.
[0069] The fluid circuit 26' is for example a fluid circuit but could alternatively be a coolant circuit.
[0070] The fluid connection means of the fluid circuit 26' of each exchanger 26 to the fluid system 18 comprise at least one rotating fluid connection 30 which is formed by at least one of the hinges 25 and which can therefore be considered as integrated into at least one of these hinges 25.
[0071] In the example shown, the fluid circuit 26' comprises a fluid inlet 26a and a fluid outlet 26b. The fluid system 18 comprises a fluid inlet 18a and a fluid outlet 18b.
[0072] The fluid inlet 26a of the circuit 26' is connected to the fluid outlet 18b of the system 18 by a first rotating connection 30 which is centered on the pivot axis C of the panel 20 which carries the exchanger 26 with this circuit 26'. This rotating connection 30 is integrated into the hinge 25b.
[0073] The fluid outlet 26b of the circuit 26' is connected to the fluid inlet 18b of the system 18 by a second rotating connection 30' which is also centered on the pivot axis C of the panel 20. This rotating connection 30' is integrated into the hinge 25c.
[0074] In the example shown, each of the hinges 25b and 25c therefore forms a rotating connection 30 within the meaning of the invention.
[0075] Each of these hinges 25b, 25c includes a hinge pin 32 mounted inside a hinge body 34, as illustrated in the upper part of Figure 3.
[0076] The hinge axis and body 32, 34 are movable relative to each other with respect to the axis C. In the example shown, the hinge axis 32 is mounted movable inside the hinge body 34, the hinge axis being integral with the panel 20, and the hinge body 34 being integral with the engine mast 12.
[0077] The hinge axis 32 comprises at least one internal fluid passage 36 and an external cylindrical surface 38 onto which at least one orifice 40 opens in fluid communication with this internal passage 36.
[0078] In the example shown, it can be seen that the hinge pin 32 comprises a threaded end crossed by the internal passage 36. This threaded end facilitates the connection of this passage.
[0079] The hinge body 34 extends around the cylindrical surface 38 and has an internal passage 42 which is configured to be placed in fluid communication with the port 40 when the panel 20 is in the closed position (FIGS. 4a and 5a-5b) and to be fluidically isolated from this port 40 when the panel is in the open position (FIGS. 4b and 6a-6b).
[0080] The passage 42 may comprise an outlet at the outer periphery of the hinge body 34, for the purpose of connecting this passage.
[0081] The first rotating connection 30 can be connected by rigid pipes respectively to the inlet 26a and to the outlet 18b. A valve 33 is advantageously interposed between the connection 30 and the outlet 18b, therefore just upstream of the connection 30. This valve 33 can also be centered on the axis C.
[0082] The second rotating connection 30' can be connected by rigid pipes, respectively to the outlet 26b and to the inlet 18a. A valve 33 is advantageously interposed between the connection 30' and the inlet 18a, therefore just downstream of the connection 30'. This valve 33 can also be centered on the axis C. In the drawing, it can be seen that the hinge 25b is located between the valve 33 and the connection 30'.
[0083] In this application, a rigid pipe is understood to mean a pipe that is not deformable or flexible. The pipe may have any shape, for example, straight or bent. The drawings show schematic examples of shapes of this type of pipe.
[0084] The links 30, 30' are therefore at a distance from each other, along the C axis.
[0085] The valve(s) 33 make it possible to isolate the fluid circuit 26' for the purpose, for example, of dismantling the exchanger 26 or the panel 20 during a maintenance operation.
[0086] The variant embodiment of figure 7 differs from the previous embodiment in particular by the fact that the two rotating connections 30, 30' are here joined together and no longer at a distance from each other.
[0087] For this, the two connections 30, 30' have a hinge axis 32 in common and a hinge body 34 in common. The hinge axis 32 comprises two internal fluid passages 36a, 36b and an external cylindrical surface 38 onto which at least two orifices 40, 40' open in fluid communication respectively with these internal passages 36a, 36b.
[0088] A first of the passages 36a extends over approximately half of the hinge pin 36 and opens at a first end of this hinge pin. This first passage 36a is in fluid communication with the orifice 40. The hinge pin 32 comprises a first threaded end crossed by the internal passage 36a.
[0089] A second of the passages 36b extends over approximately the other half of the hinge axis 36 and opens at a second opposite end of this hinge axis. This second passage 36b is in fluid communication with the orifice 40'.
[0090] The hinge pin 32 includes a second threaded end through which the internal passage 36b passes.
[0091] The orifices 40, 40' are axially spaced from each other and are here axially aligned along the axis C.
[0092] The hinge body 34 extends around the cylindrical surface 38 and has two independent internal passages 42, 42' which are configured to be placed in fluid communication respectively with the ports 40, 40' when the panel 20 is in the closed position and to be fluidically isolated from these ports 40, 40' when the panel 20 is in the open position.
[0093] The passages 42, 42' may each comprise an outlet 42a at the external periphery of the hinge body 34, for the purpose of connecting this passage.
[0094] The rotating links 30, 30' are here integrated into the hinge 25b.
[0095] A valve 33 is interposed between the connection 30, and in particular its passage 36a (by means of its threaded end), and the outlet 18b, therefore just upstream of the connection 30. This valve 33 can also be centered on the axis C. Another valve 33 is interposed between the connection 30', and in particular the end of its passage 36b (by means of its threaded end), and the inlet 18a, therefore just downstream of the connection 30'. This valve 33 can also be centered on the axis C.
[0096] The valves 33 can be connected by rigid pipes, respectively to the outlet 18b and to the inlet 18a. The passages 42, 42' are connected by other rigid pipes, to the inlet 26a and to the outlet 26b of the conduit 26'.
[0097] The alternative embodiment of figures 8, 9a-9b and 10a-10b is close to the previous embodiment insofar as the two rotating connections 30, 30' are joined to each other. The two connections 30, 30' have a hinge axis 32 in common and a hinge body 34 in common. The hinge axis 32 comprises two internal fluid passages 36a, 36b and an external cylindrical surface 38 onto which at least two orifices 40, 40' open in fluid communication respectively with these internal passages 36a, 36b.
[0098] A first of the passages 36a extends along the hinge axis 36 and opens at a first end of this hinge axis. This first passage 36a is in fluid communication with the orifice 40.
[0099] A second of the passages 36b also extends along the hinge axis 36 and opens at the same first end of the hinge axis 36. This second passage 36b is in fluid communication with the orifice 40'.
[0100] The orifices 40, 40' are axially spaced from one another and are here axially aligned along the axis C. These orifices 40, 40' have elongated shapes in the circumferential direction in the example shown.
[0101] The hinge body 34 extends around the cylindrical surface 38 and has two independent internal passages 42, 42' which are configured to be placed in fluid communication respectively with the ports 40, 40' when the panel 20 is in the closed position and to be fluidically isolated from these ports 40, 40' when the panel 20 is in the open position.
[0102] The rotating links 30, 30' are here integrated into the hinge 25b.
[0103] The internal passages 42 are configured to be placed in fluid communication with the ports 40, 40' when the panel 20 is in the closed position (Figures 9a-9b) and to be fluidically isolated from these ports 40, 40' when the panel 20 is in the open position (Figures 10a-10b).
[0104] A double valve 33 is interposed between the two passages 42, 42' of the connections 30, 30', on the one hand, and the outlet 18b and the inlet 18a, on the other hand. This valve 33 can also be centered on the axis C.
[0105] Rigid pipes connect valve 33 to the fluid system 18, and connections 30, 30' to the circuit 26'.
Claims
CLAIMS 1. Propulsion assembly (10) for an aircraft, this propulsion assembly (10) comprising: - a reactor mast (12) extending along a first axis (A), - a turbomachine (14) fixed to the reactor mast (12), this turbomachine (14) extending along a second axis (B), the first and second axes (A, B) extending in the same plane (P), the turbomachine (14) comprising a fluidic system (18), - a cowling (16) which extends along and around the second axis (B), the cowling (16) comprising at least one panel (20) which extends around said second axis (B), said at least one panel (20) comprising a longitudinal edge (22) which is fixed to the engine pylon (14) by hinges (25) which define a third 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 fluid circuit (26') connected to said fluid system (18), characterized in that the fluid circuit (26') is connected to the fluid system (18) by at least one of said hinges (25) which forms a rotating fluid connection (30, 30'), this hinge (25) comprising a hinge axis (32) mounted inside a hinge body (34),the axis and the hinge body (32, 34) being movable relative to each other with respect to the third axis (C), said hinge axis (32) comprising at least one internal fluid passage (36, 36a, 36b) and an external cylindrical surface (38) onto which at least one orifice (40, 40') opens in fluid communication with this internal passage (36, 36a, 36b), said hinge body (34) extending around said external cylindrical surface (38) and comprising an internal passage (42, 42') which is configured, to be placed in fluid communication with said orifice (40, 40') when the panel (20) is in the closed position and to be fluidically isolated from this orifice (40, 40') when the panel (20) is in the open position.
2. Propulsion assembly (10) according to claim 1, wherein said internal passage (42, 42') of the hinge body (34) is configured to be fluidically isolated from said orifice (40, 40') when the panel (20) is in the open position.
3. Propulsion assembly (10) according to claim 1 or 2, in which the hinge axis (32) is mounted movably inside the hinge body (34), the hinge axis (32) being integral with the panel (20), and the hinge body (34) being integral with the reactor mast (36).
4. Propulsion assembly (10) according to one of the preceding claims, in which a valve (33) is mounted between the fluidic system (18) and the rotating fluidic connection (30, 30').
5. Propulsion assembly (10) according to one of the preceding claims, in which the fluid circuit (26') is connected to the fluid system (18) by two rotating connections (30, 30'), a first of these rotating connections (30) being connected to an inlet (26a) of said fluid circuit (26), and a second of these rotating connections (30') being connected to a fluid outlet (26b) of said circuit (26').
6. Propulsion assembly (10) according to claim 5, in which the first and second rotating connections (30, 30') are formed by two separate hinges (25) and are at a distance from each other.
7. Propulsion assembly (10) according to claim 5, in which the first and second rotating connections (30, 30') are formed by the same hinge (25) and are twinned.
8. Propulsion assembly (10) according to one of the preceding claims, in which the hinge axis (32) is connected to the fluid circuit (26') by at least one rigid pipe.
9. Propulsion assembly (10) according to one of the preceding claims, in which the hinge body (34) is connected to the fluidic system (18) by at least one rigid conduit.
10. Propulsion assembly (10) according to one of the preceding claims, in which each of these panels (20) comprises an upper longitudinal edge (22) and a lower longitudinal edge (24), the upper longitudinal edge of the or each panel being fixed by the hinges (25).
11. Propulsion assembly (10) according to one of the preceding claims, in which the other of the panels (20) carries another heat exchanger or another type of fluidic equipment.
12. Propulsion assembly (10) according to one of the preceding claims, in which the or each panel (20) has a generally semi-cylindrical shape.