Propulsion unit for an aircraft

Abstract

The invention relates to a propulsion unit (10) for an aircraft, said propulsion unit (10) comprising:-an engine pylon (12),-a turbine (14) fixed to the engine pylon (12) and comprising a fluid system (18),-a fairing (16) comprising at least one panel (20), the invention relates to an engine suspension (10) comprising a fluid system (18) and at least one panel (14) pivotably connected to the engine suspension (14) and carrying at least one surface heat exchanger (26) 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 telescopic link (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 / 318546, US-A1-2020 / 049028 and DE-A1-10 2006 054003.

[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 the engine pylon 12 or close to the engine pylon. 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 in the same plane P. The plane P can be vertical or inclined with respect to the vertical.

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

[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 can include multiple parts and includes two panels 20 of a generally semi-circular shape, the two panels 20 extending on either side of the aforementioned 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 provide 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 in the panel 20 is hinged about a third axis C, for example from a closed position to an open position, in the closed position, the lower edge 24 of the panel is located at the 6h position, and in the open position, the lower edge 24 of the panel is away from the 6h position, and the third axis C may be parallel to the second axis B.

[0012] The fairing 16 can 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 portion of the fairing 16 can define an annular duct for the air flow around the turbine 14 inside, such as a flow duct for the 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 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, one end 28a being fixed to the panel 20 and configured to be connected to the exchanger 26 carried by the 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 be kept free 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. Thus, this technique is relatively bulky. In addition, these hoses 28 are oversized to have sufficient resistance and, in particular, have a large diameter due to the presence of a thick protective layer around these hoses 28 to resist fire and other incursions. 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, demanding 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 efforts have significantly improved the environmental performance of aircraft. The applicant takes into account influencing factors at all stages of design and development in order 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. Thus, 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 activities that emit greenhouse gases. This ongoing research and development work focuses on a new generation of aircraft engines, which makes aircraft lighter (especially through the materials used and lighter on-board equipment), the development of propulsion using electric technologies, and aviation biofuels as an important complement 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 a technical research aimed at significantly improving the performance of aircraft and, in this sense, helps to reduce the impact of aircraft on the environment.

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

[0021] - a turbine that extends along a main axis and includes a fluid system,

[0022] - A fairing that extends along and around the main axis. The fairing includes at least one panel that extends around the main axis. The at least one panel includes a longitudinal edge that is hinged by a hinge. The hinge defines a 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 is separated 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.

[0023] It is characterized in that the fluid circuit is connected to the fluid system by at least one telescopic link. The at least one telescopic link includes at least one tubular rod. The at least one tubular rod can translate along the elongation axis of the link in a tubular body. The telescopic link has a length that varies according to the position of the panel around the pivot axis. The tubular rod includes a first internal channel. At least when the panel is in the closed position, the first internal channel is in fluid communication with a second internal channel of the tubular body.

[0024] Therefore, the present invention proposes to connect the fluid circuit of the exchanger of the panel to the fluid system of the turbine by at least one telescopic link. A first specific characteristic of the telescopic link is that the length of the telescopic link is automatically adapted according to the position of the panel relative to the turbine. The length of the telescopic link can be adjusted by simply sliding the rod or each rod in the body. Therefore, when the panel moves, there is no special stress on the link. Another specific feature of the link is that when the panel is closed, the link ensures the fluid flow between the exchanger and the fluid system.

[0025] The propulsion unit according to the present invention may include one or more of the following features used alone or in combination with each other:

[0026] - The telescopic link is integrated into a cylinder for connecting the panel to the turbine. The cylinder is configured to pivot the panel around the pivot axis;

[0027] - The telescopic link is connected to at least one pump;

[0028] - The telescopic link is integrated into a connecting rod for holding the panel in a predetermined position relative to the turbine. The connecting rod extends between the panel and the turbine;

[0029] - A seal is installed at one end of the body and cooperates with the rod when the rod moves, and / or a seal is installed at one end of the rod and cooperates with the body when the rod moves in the body;

[0030] - The fluid circuit is connected to the fluid system by two telescopic links, with the first telescopic link of these telescopic links connected to the inlet of the fluid circuit and the second telescopic link of these telescopic links connected to the fluid outlet of the circuit;

[0031] - The fluid circuit is connected to the fluid system by a single telescopic link, where the first internal channel and the second internal channel are independent and are respectively connected to the fluid inlet and the fluid outlet of the fluid circuit;

[0032] - Regardless of the position of the panel around the pivot axis, the first internal channel and the second internal channel are in fluid communication;

[0033] - When the panel is in the open position of the panel, the first internal channel and the second internal channel are fluidly separated from each other;

[0034] - The telescopic link includes a mechanical locking device that locks the tubular rod in place relative to the tubular body along the elongation axis; this enables the fairing to remain open for maintenance purposes;

[0035] - At least one valve is installed between the fluid system and the telescopic link;

[0036] - The telescopic link includes a first tubular rod that can translate within a second tubular rod, and the second tubular rod itself can translate within the tubular body along the elongation axis of the link;

[0037] - The assembly further includes an engine pylon, a turbine is attached to the engine pylon, the turbine is located below the engine pylon, and the panel is attached to the engine pylon by the hinge;

[0038] -- The elongation axes of the engine pylon and the turbine extend in the same plane;

[0039] - The fluid circuit is an oil circuit or a coolant circuit;

[0040] -- The fairing surrounds at least a portion of the turbine;

[0041] - The fairing includes two panels of a generally semi-circular shape that extend on either side of the main axis;

[0042] - Each of these panels includes an upper longitudinal edge and a lower longitudinal edge;

[0043] - The upper longitudinal edge of the said or each panel is attached by a hinge;

[0044] -- The other panel among the panels carries another heat exchanger or another type of fluid device;

[0045] -- The said 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 prior - art device for fluid - connecting a heat exchanger to a fluid system according to the present invention,

[0049] Figure 3 Figure 3 is a schematic perspective view of a propulsion unit according to an embodiment of the present invention,

[0050] Figure 4 Figure 4 is a very schematic axial cross - sectional view of a telescopic link for fluid - connecting a surface exchanger to a fluid system;

[0051] Figure 5 Figure 5 is a very schematic axial cross - sectional view of the telescopic link and shows a variant of an embodiment of the present invention, the link being in the retracted position;

[0052] Figure 6 Figure 6 is a schematic axial cross - sectional half - view of another telescopic link and shows a variant of an embodiment of the present invention,

[0053] Figure 7 Figure 7 is Figure 5 a very schematic axial cross - sectional view of the telescopic link of, the link being in the extended position;

[0054] Figure 8 Figure 8 is a very schematic axial cross - sectional view of the telescopic link and shows another variant of the present invention;

[0055] Figure 9 Figure 9 is a very schematic axial cross - sectional view of the telescopic link and shows another variant of an embodiment of the present invention, the link being in the retracted position here;

[0056] Figure 10 Figure 10 is Figure 9 a very schematic axial cross - sectional view of the telescopic link of, the link being in the extended position;​​​​​​​​​​​​​​​​​​​​

[0057] Figure 11 Figure 11 is a very schematic axial sectional view of a telescopic link and shows another variant of an embodiment of the present invention, the link being in the retracted position;

[0058] Figure 12 Figure 12 is Figure 11 a very schematic axial sectional view of a telescopic link in the deployed position;

[0059] Figure 13 Figure 13 is a very schematic axial sectional view of a telescopic link and shows another variant of an embodiment of the present invention, the link being in the retracted position;

[0060] Figure 14 Figure 14 is Figure 13 a very schematic axial sectional view of a telescopic link in the deployed position;

[0061] Figure 15 Figure 15 is Figure 4 a very schematic view of a telescopic link which is also associated with a circuit for supplying pressurized oil to these links such that the telescopic link can perform an additional function as a cylinder, the telescopic link being used here to supply oil to the fluid circuit of an exchanger, and

[0062] Figure 16 Figure 16 is similar to Figure 15 in which the telescopic link is used to move a panel to which the telescopic link is connected. DETAILED DESCRIPTION

[0063] The foregoing has described Figure 1 and Figure 2 .

[0064] Figure 3 Shows an embodiment of a propulsion unit 10 according to the present invention. The propulsion unit 10 comprises:

[0065] - a turbine 14, in particular the bearings and rotating elements of the turbine 14, the turbine 14 comprising a fluid system 18, and

[0066] - a cowling 16, as in the example shown, the cowling 16 can surround the turbine 14.

[0067] For example, the propulsion unit 10 can be located below the wing of an aircraft or at the rear of the fuselage of the aircraft.

[0068] ​​​​​​​​​​​​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.

[0069] The propulsion unit 10 may also include an engine pylon 12.

[0070] The fairing 16 includes two panels 20 of a generally semi-circular shape that extend on either side of a plane P passing through the main axis B of the turbine 14 or through the respective axes A, B of the engine pylon 12 and the turbine 14 when the engine pylon is part of the propulsion unit. The plane P can be vertical or inclined with respect to the vertical.

[0071] The panel 20 includes an upper longitudinal edge 22 attached by a hinge 25. The hinge 25 can be carried by a beam of the turbine 14 or by the engine pylon 12 if the engine pylon 12 forms part of the propulsion unit 10.

[0072] The upper edge 22 is substantially located at the 12h position and the upper edges 22 are separated from each other by a beam or the engine pylon 12.

[0073] The hinges 25 are generally arranged one behind the other along the pivot axis C of the corresponding panel 20.

[0074] Each panel 20 in the panel 20 is hinged from a closed position to an open position (as shown) about this axis C. In the closed position, the lower longitudinal edge 24 of the panel is substantially located at the 6h position. In the open position, the lower edge 24 of the panel is away from the 6h position. The axis C can be parallel to the axis B, for example. The angular deflection (arrow F) between the two positions is greater than 30°, for example, about the axis C.

[0075] Each panel 20 in the panel 20 carries at least one surface heat exchanger 26. The 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.

[0076] In the example shown, the exchanger 26 is located on the concave curved surface of the panel 20 that is oriented towards the axis B and is thus the inner surface of the panel 20. This position is not exhaustive. Alternatively, the exchanger 26 can be located, for example, on the outer convex surface of the panel 20.

[0077] In fact, in the context of the present invention, the panel 20 can be an inner panel or an outer panel of the turbine and the propulsion unit, and the panel 20 can be swept by a gas flow passing through the inside or outside of the panel. Thus, the exchanger 26 is located inside or outside the panel 20 and thus on the inner surface or the outer surface of the panel 20.

[0078] The fluid system 18 is, for example, a lubrication system, but alternatively can be a cooling system. The fluid circuit 26' is, for example, an oil circuit, but alternatively can be a coolant circuit.

[0079] The connecting means for fluidly connecting the fluid circuit 26’ of each exchanger 26 to the fluid system 18 includes at least one telescopic link 30.

[0080] 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.

[0081] The fluid inlet 26a of the circuit 26’ is connected to the fluid outlet 18b of the system 18 by a first telescopic link 30, and the fluid outlet of the circuit 26’ is connected to the fluid inlet 18a of the system by a second telescopic link 30'.

[0082] Each panel 20 can be moved manually. Alternatively, the movement of each panel 20 can be achieved using hydraulic equipment, which includes at least one cylinder 32 for moving the panel 20 between its end positions.

[0083] In this case, the cylinder 32 is connected to a fluid source (such as oil) by a pump (not shown). The pump supplies oil at a predetermined pressure, enabling the cylinder 32 to extend and enabling the panel 20 to move about its pivot axis C.

[0084] To hold each panel 20 in Figure 3 the open position shown, the propulsion unit 10 can include at least one holding link 34. This type of link 34 extends between the turbine 14 and the panel 20 and is located inside the panel. The length of this type of link 34 can be fixed such that the link holds the panel in the open position.

[0085] Thus, it should be understood that in the prior art, each panel 20 can be connected to the turbine 14 by one or more cylinders 32 and by one or more links 34.

[0086] In the context of the present invention, each telescopic link 30, 30’ also extends between the panel 20 and the turbine 14. Each telescopic link 30, 30' can be independent of the cylinder 32 and the link 34. Alternatively, each telescopic link 30, 30’ is integrated into the cylinder 32 or the link 34.

[0087] When the telescopic links 30, 30’ are integrated into the cylinder 32, the cylinder has the dual function of enabling fluid circulation between the fluid system 18 and the exchanger 26 and moving the panel 20 between its end positions.

[0088] When the telescopic links 30, 30' are integrated into the connecting rod 34, the connecting rod has the dual function of providing fluid communication between the fluid system 18 and the exchanger 26 and holding the panel 20 in its open position or one of its open positions.

[0089] Figure 4 The following figures show multiple different embodiments of these telescopic links 30, 30'.

[0090] Figure 4 A first embodiment is shown, in which the fluid circuit 26' of the exchanger 26 is connected to the fluid system 18 of the turbine 14 by two of the above-mentioned telescopic links 30, 30'.

[0091] Each telescopic link 30, 30' includes a tubular rod 40 that can translate axially along the elongation axis C of the link within a tubular body 42. The length of the telescopic link 30, 30' varies according to the position of the rod 40 within the body 42. When the rod 40 is fully retracted into the body 42, the telescopic link is in the retracted position shown in the figure. When the rod 40 is fully extended from the body 42, the telescopic link is in the deployed position (see Figure 7 ).

[0092] The length of each telescopic link 30, 30' automatically adapts to the position of the panel relative to the turbine. When the panel is open, the link deploys, and when the panel is closed, the link retracts.

[0093] The tubular rod 40 includes a first internal passage 44 that is in fluid communication with a second internal passage 46 of the tubular body 42 at least when the panel is in the closed position and the link is in the retracted position, as shown. When the panel is in the open position and the link is in the deployed position, the passages 44, 46 can also be in fluid communication.

[0094] In the example shown, the passage 44 in the rod 40 extends substantially along the inner side of the rod 40 throughout the length of the rod 40. The passage 44 opens at the end of the rod 40 that engages within the body 42, and the passage 44 is in direct fluid communication with the passage 46 of the body 42 regardless of the position of the rod within the body.

[0095] The rod 40 includes a fluid passage port 48 which is located at the end of the rod outside the body 42 and is in fluid communication with the internal passage 44 of the rod. The body 42 includes a fluid passage port 50 which is located at the end of the body 42 opposite to the end from which the rod 40 departs and is in fluid communication with the internal passage 46 of the body. The port 48 of the link 30 is connected to the inlet 26a of the circuit 26', and the outlet 26b of the circuit 26' is connected to the port 48 of the link 30'. The port 50 of the link 30 is connected to the outlet 18b of the system 18, and the inlet 18a of the system 18 is connected to the port 50 of the link 30'. Regardless of the position of the rod 40 in the body 42, the ports 48, 50 are always in fluid communication with the internal passages 44, 46.

[0096] Therefore, it should be understood that regardless of the positions of the telescopic links 30, 30' and the panel 20 relative to the turbine 14, the fluid circuit 26' of the exchanger 26 is always fluidly connected to the fluid system 18 of the turbine 14.

[0097] The valve 52 can be installed upstream and / or downstream of each telescopic link 30, 30' to fluidly isolate each telescopic link 30, 30' from the fluid system 18 and / or the circuit 26' as required.

[0098] The end portions of each telescopic link 30, 30' can be respectively attached to the panel 20 or the exchanger 26 and the turbine 14 by rotating or pivoting the link 54.

[0099] Now referring to Figure 5 and Figure 6 , Figure 5 and Figure 6 show alternative embodiments of the telescopic links 30, 30' with respect to the sealing means between the body 42 and the rod 40. To prevent fluid leakage, the telescopic links 30, 30' are equipped with at least one seal 56, and the at least one seal 56 can be carried by the body 42 and cooperate with the rod 40, as shown in Figure 5 , or the at least one seal 56 can be carried by the rod 40 and cooperate with the body 42, as shown in Figure 6 . In Figure 5 , the end of the body 42 from which the rod 40 departs is equipped with a seal 54. In Figure 6 , the end of the rod 40 engaging in the body 42 is equipped with a seal 54.

[0100] Figure 5 The configuration shown results in pressure balance on both sides, thereby minimizing the applied pressure, which reduces the stress on the structure when the system is pressurized during operation.

[0101] Figure 8A variant embodiment is shown, in which a single telescopic link 30 can be used to fluidly connect the inlet 26a and outlet 26b of the fluid circuit 26' to the fluid system 18. To achieve this, the telescopic link 30 includes two independent internal fluid circuits, as opposed to the single internal circuit in the foregoing embodiment.

[0102] The rod 40 includes two parallel internal channels 44, 45 extending along the length of the rod. The internal channel 44 is similar to the above-mentioned internal channel, and the internal channel 44 opens at the end of the rod 40 joined in the body 42. The internal channel 45 opens on one side of this end. The body 42 includes two independent internal channels 46, 47. The internal channel 46 is located at the bottom of the body 42, and the internal channel 46 is in fluid communication with the channel 44 regardless of the position of the rod 40 in the body 42. The internal channel 47 is located on one side or the periphery of the body 42, and the internal channel 47 is in fluid communication with the channel 45 regardless of the position of the rod 40 in the body 42.

[0103] The rod 40 includes two fluid channel ports 48, 49. The first port 48 is similar to the above-mentioned port and is in fluid communication with the channel 44. The second port 49 is also located at the end of the rod 40 opposite to the end joined in the body 42 and is in fluid communication with the channel 45.

[0104] The body 42 includes two fluid channel ports 50, 51. The first port 50 is similar to the above-mentioned port and is in fluid communication with the channel 46. The second port 51 is located on one side of the body 42 and is in fluid communication with the channel 47.

[0105] A seal 56 is provided at the end of the rod 40 joined in the body 42, and the seal 56 enables the two internal channels 46, 47 to be separated from the body. Another seal 58 is provided at the end of the body 42 from which the rod 40 departs, and the other seal 58 enables the internal channel 47 to be separated from the outside of the telescopic links 30, 30'.

[0106] Figure 9 and Figure 10 Another embodiment of the present invention is shown, in which the internal channels 45, 46 of the rod 40 and the body 42 are in communication with each other when the panel 20 is in the closed position and are not in communication with each other when the panel 20 is in the open position. Therefore, it should be understood that opening the panel 20 will cause the circuit between the exchanger 26 and the fluid system 18 to be cut off, which limits the risk of leakage, for example.

[0107] The rod 40 includes an internal channel 45, and the internal channel 45 extends along the rod and opens on one side of the rod. The body 42 includes an internal channel 47, and the internal channel 47 is located on one side or the periphery of the body. When the rod is in Figure 9In the retracted position shown, the internal passage 47 is in fluid communication with passage 45. The body 42 also includes a lumen 60 at the bottom of the body, the lumen 60 being separated from passage 47 by a seal 54 carried by the end of the rod 40 engaged within the body 42.

[0108] At Figure 9 the position shown, port 51 is in fluid communication with passage 47. At Figure 10 the position shown, port 51 is no longer in fluid communication with passage 47.

[0109] Figure 11 and Figure 12 show another alternative embodiment of the present invention (corresponding to the above situation), wherein the telescopic links 30, 30' are integrated into the retaining connecting rod 32.

[0110] This variant differs from the previous variant essentially in that the telescopic links 30, 30' further include a mechanical locking device 62 for locking the rod 40 in its deployed position or one of its deployed positions. Thus, it should be understood that in addition to the fluid flow between the circuit 26' and the fluid system 18, the telescopic links 30, 30' also have the function of being able to firmly hold the links in their deployed positions and thus hold the panel 20 in its open position.

[0111] The device 62 can move from Figure 11 the unlocked position shown to Figure 12 the locked position shown, in the unlocked position, the rod 40 can slide freely within the body 42, and in the locked position, the rod 40 is blocked in its deployed position. For example, the blocking can be achieved by engaging the finger 64 of the device 62 in an orifice 66 or slot in the rod 40. The activation of the device 62 can be automatic or controlled.

[0112] Figure 13 and Figure 14 show another alternative embodiment of the present invention, wherein the telescopic links 30, 30' include more than two elements, in particular two rods 40, 68 and the body 42. The first tubular rod 40 can move translationally within the second tubular rod 68, and the second tubular rod 68 itself can move translationally within the tubular body 42 along the elongation axis of the links 30, 30'.

[0113] As described above, the internal passages of the rods 40, 68 and the body 42 are in communication with each other when the links 30, 30' are retracted ( Figure 13 ), and can also be in communication with each other when the links are deployed ( Figure 4 ).

[0114] Now referring to Figure 15 and Figure 16 , Figure 15 andFigure 16 The above-described variant embodiments are shown, in which the telescopic links 30, 30' also serve as cylinders.

[0115] The telescopic links 30, 30' are connected to a pressurized oil supply circuit 70 in addition to being connected to the fluid system 18. The circuit 70 includes a pump 72 that is connected to a fluid reservoir 74, which may be the fluid reservoir of the fluid system 18. The circuit 70 can be separated from the telescopic links 30, 30' by a valve 76.

[0116] In Figure 15 , the telescopic links 30, 30' are used to supply oil from the fluid system 18 to the fluid circuit 26' of the exchanger 26. As shown by the arrows, the oil from the system 18 enters the inlet 26a of the circuit 26' through the link 30. The oil leaves the circuit via the outlet 26b and then enters the system 18 through the link 30'.

[0117] In Figure 16 , both telescopic links 30, 30' serve as cylinders. The valve 52 that connects the telescopic links 30, 30' to the fluid system 18 is closed, and the circuit 70 is used to supply pressurized oil to the two telescopic links 30, 30'. The oil supplied to the telescopic link 30 exerts pressure on the rod 40, thereby forcing the rod 40 to extend. Some of the oil in this oil flows through the internal passage of the link 30 and enters the fluid circuit 26' to enter the other telescopic link 30', such that pressure is also exerted on the rod 40, thereby forcing the rod 40 to extend. The rods 40 of the two links 30, 30' extend, and the panel 20 is moved from its closed position to its open position. This system is naturally reversible.

[0118] When the links serve as cylinders, the pressure of the oil flowing in the fluid system 18 and in the circuit 26' is lower in the case of Figure 15 than the pressure of the oil in the circuit 26' in the case of Figure 16 . For example, Figure 15 the oil pressure in is less than or equal to 6 bar. For example, Figure 16 the oil pressure in is greater than or equal to 50 bar.

Claims

1. A propulsion unit (10) for an aircraft, the propulsion unit (10) comprising: - a turbine (14) extending along a main axis (B) and comprising a fluid system (18), - a cowling (16) extending along and around the main axis (B), the cowling (16) comprising at least one panel (20) extending around the main axis (B), the at least one panel (20) comprising a longitudinal edge (22) hinged by a hinge (25), the hinge defining a 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 is separated 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 telescopic link (10), the at least one telescopic link comprising at least one tubular rod (40) capable of translational movement along the elongation axis of the link in a tubular body (42), the telescopic link (30, 30’) having a length varying according to the position of the panel (20) around the pivot axis (C), the tubular rod (42) comprising a first internal channel (44, 45) which is in fluid communication with a second internal channel (46, 47) of the tubular body (42) at least when the panel (20) is in the closed position.

2. The propulsion unit (10) according to claim 1, wherein, The telescopic link (10) is integrated into a cylinder (32) for connecting the panel (20) to the turbine (14), the cylinder (32) being configured to pivot the panel (20) around the pivot axis (C).

3. The propulsion unit (10) according to claim 1, wherein, The telescopic link (10) is integrated into a connecting rod (34) for holding the panel (20) in a predetermined position relative to the turbine (14), the connecting rod (34) extending between the panel (20) and the turbine (14).

4. The propulsion unit (10) according to any one of the preceding claims, wherein, A seal (58) is mounted at one end of the body (42) and cooperates with the rod (42) when the rod moves, and / or a seal (56) is mounted at one end of the rod (40) and cooperates with the body (42) when the rod moves in the body.

5. The propulsion unit (10) according to any one of the preceding claims, wherein, The telescopic link is connected to at least one pump.

6. 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 telescopic links (10), a first telescopic link of these telescopic links being connected to an inlet (26a) of the fluid circuit (26’), a second telescopic link of these telescopic links being connected to a fluid outlet (26b) of the circuit (26’).

7. The propulsion unit (10) according to any one of claims 1 to 5, wherein, The fluid circuit (26') is connected to the fluid system (18) by a single telescopic link (30), wherein the first and second internal channels (44, 45, 46, 47) are independent and are respectively connected to the fluid inlet (26a) and the fluid outlet (26b) of the fluid circuit.

8. The propulsion unit (10) according to any one of the preceding claims, wherein, Regardless of the position of the panel (20) about the pivot axis (C), the first and second internal channels (44, 45, 46, 47) are in fluid communication.

9. The propulsion unit (10) according to any one of claims 1 to 7, wherein, When the panel (20) is in the open position of the panel, the first and second internal channels (44, 45, 46, 47) are fluidly separated from each other.

10. The propulsion unit (10) according to any one of the preceding claims, wherein, The telescopic link (30, 30') includes a mechanical locking device (62) that locks the tubular rod (40) in place relative to the tubular body (42) along the elongation axis.

11. The propulsion unit (10) according to any one of the preceding claims, wherein, The telescopic link (30, 30') includes a first tubular rod (40) that is translatably movable within a second tubular rod (68), which in turn is translatably movable within the tubular body (42) along the elongation axis of the link.

12. The propulsion unit (10) according to any one of the preceding claims, wherein, At least one valve (52) is mounted between the fluid system and the telescopic link.

13. The propulsion unit (10) according to any one of the preceding claims, wherein, The assembly further includes an engine hanger (12) to which the turbine is attached, the turbine being located below the engine hanger, and the panel (20) is attached to the engine hanger by the hinge (25).

14. The propulsion unit (10) according to any one of the preceding claims, wherein, The fluid circuit (26') is an oil circuit or a coolant circuit. The propulsion unit (10) according to any one of the preceding claims, wherein, The fairing (16) includes two panels (20) of generally semi-circular shape that extend on either side of the main axis, each of these panels including an upper longitudinal edge (22) and a lower longitudinal edge (24), and the upper longitudinal edge of the or each panel is attached by the hinge.

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