Propulsion unit for an aircraft

Abstract

The invention relates to a propulsion unit (10) for an aircraft, the propulsion unit (10) comprising: an engine pylon (12); a turbine (14) fixed to the engine pylon (12) and including a fluid system (18); a fairing (16) comprising at least one panel (20) pivotably connectable to the engine pylon (12) by means of a hinge (25), said panel (20) supporting at least one surface heat exchanger (26), at least one surface heat exchanger 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), the at least one hinge forming a rotating fluid connection (30, 30 ').

Description

Technical field

[0001] The present invention relates to a propulsion unit for an aircraft. Background art

[0002] The prior art particularly includes the documents FR-A1-3 094 750, US-A1-2020 / 049028 and CN-A1-104791 522.

[0003] Figure 1 A propulsion unit 10 for an aircraft is shown.

[0004] In the present application, the "propulsion unit 10" for an aircraft refers to a component including a pylon 12, a turbine 14 and its nacelle 16.

[0005] The engine pylon 12 is a solid part for attaching the turbine 14 to an aircraft (for example, the wing of an aircraft). Thus, the engine pylon 12 includes elements for attaching to the aircraft and elements for attaching the turbine 14. The engine pylon 12 has a generally elongated shape and extends along a first axis A.

[0006] In the present application, the turbine 14 is located below or close to the engine pylon 12. The turbine can be suspended from the engine pylon 12, and the engine pylon 12 is located below the wing of the aircraft. Alternatively, the turbine can be installed at the rear of the fuselage of the aircraft.

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

[0008] Similar to the dial when observing the component from the rear, the 12h (12 o'clock) position and the 6h (6 o'clock) position are the positions of the components around the second axis B. The 12h position is located in the plane P and at the engine pylon 12, and the 6h position is located below the turbine 14 in the plane P.

[0009] The turbine 14 includes a lubrication system 18, and the lubrication system 18 lubricates the bearings of the turbine particularly by circulating lubricating oil.

[0010] The fairing 16 surrounds the turbine 14 and extends along a second axis B. The fairing 16 may include a plurality of parts and includes two panels 20 of a generally semi-circular shape, the two panels 20 extending on either side of the above-mentioned plane P. These panels 20 include an upper longitudinal edge 22 and a lower longitudinal edge 24, the upper longitudinal edge 22 being attached to the engine pylon 12 and arranged on either side of the plane P and near the 12h position, and the lower longitudinal edge 24 being generally attached to each other and thus located at the 6h position.

[0011] These panels 20 are hinged at their upper edges 22 such that the fairing 16 can be opened to enable access to the turbine 14, for example, during ground maintenance operations. This hinge may be formed by a hinge 25 for attaching the upper edge 22 of the panel 20 to the engine pylon 12. Each of the panels 20 is hinged, for example, about a third axis C from a closed position, in which the lower edge 24 of the panel is located at the 6h position, to an open position, in which the lower edge 24 of the panel is remote from the 6h position, and the third axis C may be parallel to the second axis B.

[0012] The fairing 16 may carry at least one surface heat exchanger 26. This type of exchanger 26 includes an oil circuit 26’ and an exchange surface, the oil circuit 26’ being connected to the lubrication system 18 and the exchange surface being exposed to a cooling air flow. The heat exchange between the surface of the exchanger and the oil circuit 26’ cools the oil before returning the oil from the lubrication system 18 to the lubrication system 18, as Figure 1 shown by the dashed arrow in.

[0013] At least a part of the fairing 16 may define internally an annular duct for the air flow around the turbine 14, such as a flow duct for a secondary flow, etc. In this case, the exchange surface of the surface heat exchanger 26 is swept by this air flow.

[0014] The heat exchanger 26 carried by the fairing 16 is connected to the lubrication system 18 by fluid connection means which must enable the panel 20 to be opened (in particular pivoted) without requiring the heat exchanger 26 to be disconnected from the lubrication system 18.

[0015] In the current state of the art, these connection means are flexible hoses 28, as Figure 2 shown. Each of these hoses 28 includes an end 28a and an opposite end 28b, the end 28a being fixed to the panel 20 and configured to be connected to the exchanger 26 carried by this panel 20, and the opposite end 28b being fixed to the engine pylon 12 and configured to be connected to the lubrication system 18 of the turbine 14. Regardless of the position of the panel 20, due to the flexibility of the hose 28, the oil circuit 26’ of the exchanger 26 remains connected to the lubrication system 18. Figure 2Shows two different deformed states of the same hose 28 for two different positions of the panel 20.

[0016] This technique has its drawbacks. First, the environment around the hose 28 must remain unused so as not to impede the movement of the hose 28 when the panel 20 is opened and closed. The hose 28 is also relatively long so that the hose can be bent without causing stresses that lead to breakage or permanent deformation. Therefore, this technique is relatively bulky. In addition, these hoses 28 are oversized to have sufficient resistance and have a large diameter especially due to the thick protective layer existing around these hoses 28. Finally, this technique is relatively expensive and of high quality.

[0017] Climate change is also a major concern for many legislative and regulatory bodies around the world. States have adopted, are adopting, or will adopt various restrictions on carbon emissions. In particular, advanced standards apply both to new aircraft and to those already in circulation that need to implement technical solutions to comply with current regulations. For many years, civil aviation has been working to help combat climate change. Technical research work has significantly improved the environmental performance of aircraft. The applicant takes into account influencing factors at all stages of design and development to obtain aviation components and products that consume less energy, are more environmentally friendly, and whose integration and use in civil aviation have a moderate impact on the environment, with the aim of improving the energy efficiency of aircraft. Therefore, the applicant constantly strives to reduce the negative impact of greenhouse gas emissions on the climate by adopting methods and using beneficial development and manufacturing methods, and to reduce greenhouse gas emissions to the lowest possible level in order to reduce the environmental footprint of greenhouse gas emission activities. The focus of this ongoing research and development work is on a new generation of aircraft engines, which makes the aircraft lighter (especially through the materials used and lighter on-board equipment), the development of propulsion using electric technology, and aviation biofuels as an important addition to technological progress.

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

[0019] The present invention is the result of technical research aimed at significantly improving the performance of an aircraft and, in this sense, helps to reduce the impact of the aircraft on the environment.

[0020] The present invention relates to a propulsion unit for an aircraft, the propulsion unit comprising:

[0021] - An engine pylon that extends along a first axis,

[0022] - A turbine fixed to the engine pylon that extends along a second axis, the first axis and the second axis extending in the same plane, the turbine comprising a fluid system,

[0023] - A fairing that extends along and around a second axis. The fairing includes at least one panel that extends around the second axis. The at least one panel includes a longitudinal edge that is fixed to the engine pylon by a hinge. The hinge defines a third pivot axis for the panel to move from a closed position to an open position. In the closed position, the panel extends around the turbine. In the open position, the panel moves away from the turbine. The at least one panel carries at least one surface heat exchanger. The at least one surface heat exchanger includes a fluid circuit connected to the fluid system.

[0024] It is characterized in that the fluid circuit is connected to the fluid system by at least one hinge among the hinges that forms a rotary fluid connector. The hinge includes a hinge pin installed within a hinge body. The pin and the hinge body are capable of moving relative to each other around the third axis.

[0025] The hinge pin includes at least one internal fluid passage and an external cylindrical surface. At least one orifice in fluid communication with the internal passage leads to the external cylindrical surface.

[0026] The hinge body extends around the external cylindrical surface and includes an internal passage that is configured to be in fluid communication with the orifice when the panel is in the closed position.

[0027] Advantageously, the internal passage of the hinge body is configured to be fluidly separated from the orifice when the panel is in the open position.

[0028] Thus, the present invention proposes to connect the fluid circuit of the panel exchanger to the fluid system of the turbine by means of at least one of the panel articulation hinges. Thus, the hinge forms a rotary fluid connector. The first specific characteristic of the rotary fluid connector is that the rotary fluid connector is centered on the third axis, that is, on the hinge axis of the corresponding panel. Therefore, there is no particular stress on the connector because the connector follows the movement of the panel when the panel moves. Another specific characteristic of the rotary connector is that the rotary connector is integrated into the hinge, so no separate element is required. The fluid connector between the fluid circuit and the fluid system depends on the position of the panel around its hinge axis. When the panel is closed, the fluid circuit is connected to the fluid system via an "open" rotary connector. When the panel is open, the fluid circuit is connected to the fluid system via a rotary connector that is advantageously "closed", thereby preventing fluid leakage at the rotary connector.

[0029] The propulsion unit according to the present invention may include one or more of the following features employed individually or in combination with each other:

[0030] - The hinge pin is movably mounted inside the hinge body, the hinge pin is fixed to the panel, and the hinge body is fixed to the engine hanger.

[0031] - The valve is installed between the fluid system and the rotating fluid connector.

[0032] - The fluid circuit is connected to the fluid system through two rotating connectors. The first rotating connector of these rotating connectors is connected to the inlet of the fluid circuit, and the second rotating connector of these rotating connectors is connected to the fluid outlet of the circuit.

[0033] - The first rotating connector and the second rotating connector are formed by two separate hinges and are spaced apart from each other by a distance.

[0034] - The first rotating connector and the second rotating connector are formed by the same hinge and are paired.

[0035] - The hinge pin is connected to the fluid circuit through at least one rigid pipeline.

[0036] - The hinge body is connected to the fluid system through at least one rigid pipeline.

[0037] -- The plane is vertical or inclined relative to the vertical, and the first axis and the second axis extend in the plane.

[0038] -- The fluid circuit is a lubrication circuit or a coolant circuit.

[0039] -- The fairing surrounds at least a part of the turbine.

[0040] -- The fairing includes two panels with a generally semi-circular shape, and the two panels extend on both sides of the main axis.

[0041] - Each of these panels includes an upper longitudinal edge and a lower longitudinal edge.

[0042] - The upper longitudinal edge of the panel or each panel is fixed by a hinge.

[0043] - The other panel of the panels carries another heat exchanger or another type of fluid device.

[0044] -- The turbine extends below or near the engine hanger.

[0045] - The panel or each panel has a generally semi-circular shape. Description of the Drawings

[0046] Other features and advantages will become apparent from the following description of non-limiting embodiments of the present invention and with reference to the drawings, in which:

[0047] ​Figure 1 Figure 1 is a partial schematic perspective view of a propulsion unit for an aircraft,

[0048] Figure 2 Figure 2 is a schematic perspective view of a device for fluidly connecting a heat exchanger to a fluid system according to the prior art of the present invention,

[0049] Figure 3 Figure 3 is a schematic axial cross-sectional half view of a propulsion unit for an aircraft and shows a first embodiment of the present invention,

[0050] [Figures 4a to 4b] Figures 4a to 4b are Figure 3 partial schematic cross-sectional views of the propulsion unit and show two different positions of the fairing panel of the propulsion unit,

[0051] Figure 5a - 5b Figure 5a - 5b respectively are Figure 3 schematic perspective views (partially removed) of the rotating fluid connectors of the propulsion unit of

[0052] Figure 6a - 6b Figure 6a - 6b respectively are Figure 3 schematic perspective views (partially removed) of the rotating fluid connectors of the propulsion unit of

[0053] Figure 7 Figure 7 is a schematic axial cross-sectional half view of a propulsion unit for an aircraft and shows a second embodiment of the present invention, and

[0054] Figure 8 Figure 8 is a schematic axial cross-sectional half view of a propulsion unit for an aircraft and shows a third embodiment of the present invention,

[0055] Figure 9a - 9b Figure 9a - 9b respectively are Figure 8 schematic perspective views (partially removed) of the rotating fluid connectors of the propulsion unit of

[0056] Figure 10a - 10b Figure 10a - 10b respectively are Figure 8 ​​​​​​​​​​​​​​​​​Schematic perspective view (partially removed) of the rotary fluid connector of the propulsion unit, and schematic cross-sectional view of the connector, and shows the fluid connector in the closed state. Detailed Description

[0057] As described above Figure 1 and Figure 2 .

[0058] Figure 3 Shows a first embodiment of the propulsion unit 10 according to the present invention. The propulsion unit 10 includes:

[0059] - An engine pylon 12,

[0060] - A turbine 14, in particular the bearings and rotating elements of the turbine 14, the turbine 14 including a fluid system 18, and

[0061] - A fairing 16, as in the example shown, the fairing 16 can surround the turbine 14.

[0062] For example, the propulsion unit 10 can be located below the wing of the aircraft or at the rear of the fuselage of the aircraft.

[0063] The propulsion unit 10 can be of any type, such as a turbojet engine with two or three streams, a turbine with a ducted or unducted fan, a turboprop engine, an open rotor, etc.

[0064] The fluid system 18 is, for example, a fluid system, but alternatively can be a cooling system.

[0065] The fairing 16 includes two panels 20 of generally semi-circular shape, which extend on both sides of the plane P passing through the respective axes A, B of the engine pylon 12 and the turbine 14.

[0066] In the example shown, the panel 20 includes an upper longitudinal edge 22, and the upper longitudinal edge 22 is fixed to the engine pylon 12 by a hinge 25. These upper edges 22 are substantially located at the 12h position, and the upper edges 22 are separated from each other by the engine pylon 12.

[0067] In the example shown, there are three hinges 25 arranged one behind the other along the axis C. Thus, there are an upstream hinge 25a, a middle hinge 25b, and a downstream hinge 25c. Preferably, two of these hinges are fixedly mounted and the third hinge is floatingly mounted to ensure perfect alignment.

[0068] Each panel in panel 20 is hinged about a third axis C from a closed position to an open position. In the closed position, the lower edge (not visible) of the panel is substantially at the 6h position. In the open position, the lower edge of the panel is away from the 6h position. The third axis C can be parallel to axis B, for example. In FIG. 4a, one panel in panel 20 is shown in its closed position, and in FIG. 4b, the same panel 20 is shown in its open position. The angular deflection (arrow F) between the two positions about axis C is greater than 30° (FIGS. 4a to 4b), for example.

[0069] Each panel in panel 20 carries at least one surface heat exchanger 26. At least one surface heat exchanger 26 includes a fluid or liquid circuit 26’ and an exchange surface. The fluid or liquid circuit 26’ is connected to the fluid system 18, and the exchange surface is exposed to a cooling gas flow.

[0070] In the example shown, the exchanger 26 is located on the concave curved surface of panel 20, which is oriented towards axis B and is thus the inner surface of the panel. This location is not exhaustive. Alternatively, the exchanger 26 can be located, for example, on the outer convex surface of panel 20.

[0071] In the context of the present invention, panel 20 can be an inner panel or an outer panel of a turbine and a propulsion unit. Panel 20 can be swept by a gas flow (especially a secondary flow or a flow outside the turbine) passing through the inside or outside of the panel. Thus, the exchanger 26 is located inside or outside panel 20 and is thus on the inner surface or the outer surface of this panel 20.

[0072] The fluid circuit 26’ is, for example, a fluid circuit, but alternatively can be a coolant circuit.

[0073] The fluid connection means of the fluid circuit 26’ of each exchanger 26 connected to the fluid system 18 includes at least one rotary fluid connector 30. At least one rotary fluid connector 30 is formed by at least one of the hinges 25 and can thus be considered integrated with at least one of these hinges 25.

[0074] In the example shown, the fluid circuit 26’ includes a fluid inlet 26a and a fluid outlet 26b. The fluid system 18 includes a fluid inlet 18a and a fluid outlet 18b.

[0075] The fluid inlet 26a of the circuit 26’ is connected to the fluid outlet 18b of the system 18 through a first rotary connector 30. The first rotary connector 30 is centered on the pivot axis C of panel 20, and panel 20 carries the exchanger 26 having this circuit 26’. This rotary connector 30 is integrated into the hinge 25b.

[0076] The fluid outlet 26b of the circuit 26’ is connected to the fluid inlet 18b of the system 18 by a second rotary connector 30’, which is also centered on the pivot axis C of the panel 20. This rotary connector 30’ is integrated into the hinge 25c.

[0077] In the example shown, therefore, each of the hinges 25b and 25c forms a rotary connector 30 within the meaning of the present invention.

[0078] Each of these hinges 25b, 25c includes a hinge pin 32 mounted inside the hinge body 34, as shown in the upper part of Figure 3 .

[0079] The hinge pin 32 and the hinge body 34 are able to move relative to each other about the axis C. In the example shown, the hinge pin 32 is movably mounted inside the hinge body 34, the hinge pin is fixed to the panel 20, and the hinge body 34 is fixed to the engine hanger 12.

[0080] The hinge pin 32 includes at least one internal fluid passage 36 and an external cylindrical surface 38, and at least one orifice 40 in fluid communication with the internal passage 36 leads to the external cylindrical surface 38.

[0081] In the example shown, the hinge pin 32 includes a threaded end, and the internal passage 36 passes through this threaded end. This threaded end makes it easier to connect the passage.

[0082] The hinge body 34 extends around the cylindrical surface 38 and includes an internal passage 42, which is configured to be in fluid communication with the orifice 40 when the panel 20 is in the closed position (Figs. 4a and Figure 5a - 5b ), and to be fluidly separated from the orifice 40 when the panel is in the open position (Figs. 4b and Figure 6a - 6b ).

[0083] The passage 42 may include an opening at the outer periphery of the hinge body 34 for connecting the passage.

[0084] The first rotary connector 30 may be connected to the inlet 26a and the outlet 18b by rigid pipes respectively. Advantageously, a valve 33 is inserted between the connector 30 and the outlet 18b, i.e., just upstream of the connector 30. This valve 33 may also be centered on the axis C.

[0085] The second rotary connector 30’ may be connected to the outlet 26b and the inlet 18a by rigid pipes respectively. Advantageously, a valve 33 is inserted between the connector 30’ and the inlet 18a, i.e., just downstream of the connector 30’. This valve 33 may also be centered on the axis C. This figure shows that the hinge 25b is located between the valve 33 and the connector 30’.

[0086] In the present application, a rigid pipeline refers to a pipeline that is non-deformable or non-flexible. The pipeline can be of any shape, such as straight or angled. These figures show schematic examples of this type of pipeline.

[0087] Therefore, the connectors 30, 30' are separated along the axis C.

[0088] One or more valves 33 separate the fluid circuit 26', so that the exchanger 26 or the panel 20 can be removed for maintenance.

[0089] Figure 7 The alternative embodiment shown is different from the foregoing embodiment in that the two rotary connectors 30, 30' are adjacent to each other instead of being spaced apart from each other by a distance.

[0090] To achieve this, the two connectors 30, 30' have a common hinge pin 32 and a common hinge body 34.

[0091] The hinge pin 32 includes two internal fluid channels 36a, 36b and an external cylindrical surface 38, and at least two orifices 40, 40' that are in fluid communication with these internal channels 36a, 36b lead to the external cylindrical surface 38.

[0092] The first channel in the channel 36a extends approximately halfway along the hinge pin 36 and opens at the first end of the hinge pin. The first channel 36a is in fluid communication with the orifice 40.

[0093] The hinge pin 32 includes a first threaded end, and the internal channel 36a passes through the first threaded end.

[0094] The second channel in the channel 36b extends approximately halfway along the other half of the hinge pin 36 and opens at the second opposite end of the hinge pin. The second channel 36b is in fluid communication with the orifice 40'.

[0095] The hinge pin 32 includes a second threaded end, and the internal channel 36b passes through the second threaded end.

[0096] The orifices 40, 40' are axially separated and axially aligned along the axis C.

[0097] The hinge body 34 extends around the cylindrical surface 38 and includes two independent internal channels 42, 42', and the two independent internal channels 42, 42' are configured to be in fluid communication with the orifices 40, 40' respectively when the panel 20 is in the closed position, and are in fluid isolation from the orifices 40, 40' when the panel 20 is in the open position.

[0098] The channels 42, 42' can each include an opening 42a at the outer periphery of the hinge body 34 for connecting the channel.

[0099] The rotary connectors 30, 30' are integrated into the hinge 25b.

[0100] The valve 33 is inserted between the connector 30 (in particular its channel 36a (via its threaded end)) and the outlet 18b, i.e., just upstream of the connector 30. The valve 33 can also be centered on the axis C.

[0101] Another valve 33 is inserted between the connector 30' (in particular the end of its channel 36b (via its threaded end)) and the inlet 18a, i.e., just downstream of the connector 30'. The valve 33 can also be centered on the axis C.

[0102] The valve 33 can be connected to the outlet 18b and the inlet 18a respectively through rigid pipelines. The channels 42, 42' are connected to the inlet 26a and the outlet 26b of the pipeline 26' through other rigid pipelines.

[0103] Figure 8 , Figure 9a - 9b and Figure 10a - 10b The alternative embodiment shown is similar to the foregoing embodiment in that the two rotary connectors 30, 30' are adjacent to each other. The two connectors 30, 30' have a common hinge pin 32 and a common hinge body 34.

[0104] The hinge pin 32 includes two internal fluid channels 36a, 36b and an external cylindrical surface 38, and at least two orifices 40, 40' respectively in fluid communication with these internal channels 36a, 36b lead to the external cylindrical surface 38.

[0105] The first channel in the channel 36a extends along the hinge pin 36 and opens at the first end of the hinge pin. The first channel 36a is in fluid communication with the orifice 40.

[0106] The second channel in the channel 36b also extends along the hinge pin 36 and opens at the same first end of the hinge pin 36. The second channel 36b is in fluid communication with the orifice 40'.

[0107] The orifices 40, 40' are axially separated and axially aligned along the axis C. In the example shown, these orifices 40, 40' are elongated in the circumferential direction.

[0108] The hinge body 34 extends around the cylindrical surface 38 and includes two independent internal channels 42, 42', and the two independent internal channels 42, 42' are configured to be in fluid communication with the orifices 40, 40' respectively when the panel 20 is in the closed position and to be fluidly separated from the orifices 40, 40' when the panel 20 is in the open position.

[0109] The rotary connectors 30, 30' are integrated into the hinge 25b.

[0110] The internal channel 42 is configured to be in fluid communication with the orifices 40, 40' when the panel 20 is in the closed position ( Figure 9a - 9b ), and to be fluidly separated from these orifices 40, 40' when the panel 20 is in the open position ( Figure 10a - 10b ).

[0111] The double valve 33 is inserted between the two channels 42, 42' of the connectors 30, 30' on the one hand and the outlet 18b and the inlet 18a on the other hand. The valve 33 can also be centered on the axis C.

[0112] Rigid conduits connect the valve 33 to the fluid system 18 and connect the connectors 30, 30' to the circuit 26'.

Claims

1. A propulsion unit (10) for an aircraft, the propulsion unit (10) comprising: - an engine pylon (12) extending along a first axis (A), - a turbine (14) fixed to the engine pylon (12), the turbine (14) extending along a second axis (B), the first axis and the second axis (A, B) extending in the same plane (P), the turbine (14) comprising a fluid system (18), - a fairing (16) extending along the second axis (B) and around the second axis, the fairing (16) comprising at least one panel (20) extending around the second axis (B), the at least one panel (20) comprising a longitudinal edge (22) fixed to the engine pylon (14) by a hinge (25), the hinge defining a third pivot axis (C) for the panel from a closed position to an open position, in the closed position, the panel extends around the turbine (14), in the open position, the panel moves away from the turbine (14), the at least one panel (20) carrying at least one surface heat exchanger (26), the at least one surface heat exchanger comprising a fluid circuit (26’) connected to the fluid system (18), characterized in that the fluid circuit (26’) is connected to the fluid system (18) by at least one hinge forming a rotary fluid connector (30, 30’) in the hinge (25), the hinge (25) comprising a hinge pin (32) mounted within a hinge body (34), the hinge pin and the hinge body (32, 34) being able to move relative to each other about the third axis (C), the hinge pin (32) comprising at least one internal fluid passage (36, 36a, 36b) and an external cylindrical surface (38), at least one orifice (40, 40’) in fluid communication with the internal passage (36, 36a, 36b) leading to the external cylindrical surface, the hinge body (34) extending around the external cylindrical surface (38) and comprising internal passages (42, 42’), the internal passages being configured to be in fluid communication with the orifices (40, 40’) when the panel (20) is in the closed position and to be fluidly separated from the orifices (40, 40’) when the panel (20) is in the open position.

2. The propulsion unit (10) according to claim 1, wherein, The internal passages (42, 42’) of the hinge body (34) are configured to be fluidly separated from the orifices (40, 40’) when the panel (20) is in the open position.

3. The propulsion unit (10) according to claim 1 or 2, wherein, The hinge pin (32) is movably mounted inside the hinge body (34), the hinge pin (32) being fixed to the panel (20), the hinge body (34) being fixed to the engine pylon (36).

4. The propulsion unit (10) according to any one of the preceding claims, wherein, A valve (33) is mounted between the fluid system (18) and the rotary fluid connector (30, 30’).

5. The propulsion unit (10) according to any one of the preceding claims, wherein, The fluid circuit (26’) is connected to the fluid system (18) by two rotary connectors (30, 30’), a first rotary connector among these rotary connectors (30) being connected to the inlet (26a) of the fluid circuit (26), and a second rotary connector among these rotary connectors (30’) being connected to the fluid outlet (26b) of the circuit (26’).

6. The propulsion unit (10) according to claim 5, wherein, The first rotary connector and the second rotary connector (30, 30’) are formed by two separate hinges (25) and are spaced apart from each other by a distance.

7. The propulsion unit (10) according to claim 5, wherein, The first rotary connector and the second rotary connector (30, 30’) are formed by the same hinge (25) and are paired.

8. The propulsion unit (10) according to any one of the preceding claims, wherein, The hinge pin (32) is connected to the fluid circuit (26’) by at least one rigid pipe.

9. The propulsion unit (10) according to any one of the preceding claims, wherein, The hinge body (34) is connected to the fluid system (18) by at least one rigid pipe.

10. The propulsion unit (10) according to any one of the preceding claims, wherein, Each of these panels (20) includes an upper longitudinal edge (22) and a lower longitudinal edge (24), and the upper longitudinal edge of the panel or each panel is fixed by the hinge (25).

11. The propulsion unit (10) according to any one of the preceding claims, wherein, Another panel among the panels (20) carries another heat exchanger or another type of fluid device.

12. The propulsion unit (10) according to any one of the preceding claims, wherein, The panel or each panel (20) has a substantially semi-circular shape.

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