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 engine (14) fixed to the engine pylon (12) and comprising a fluidic system (18), - a cowling (16) which comprises at least one panel (20) pivotably connected to the engine pylon (14) and carrying at least one surface heat exchanger (26) which comprises a fluidic circuit (26') connected to the fluidic system (18), characterised in that the fluidic circuit (26') is connected to the fluidic system (18) by at least one telescopic link (30, 30').

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 documents FR-A1 -3 094 750, USAI -2020 / 318546, US-A1 -2020 / 049028 and DE-A1 -10 2006 054003.

[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 pylon 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 pylon 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. A heat exchange 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, 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 rupture or permanent deformation. This technology is therefore relatively bulky. Furthermore, these pipes 28 are oversized to be sufficiently resistant and in particular have a large diameter due to the presence of a thick protective layer around these pipes 28 in order to resist fire and other attacks. Finally, this technology is relatively expensive and of significant mass. Furthermore, climate change is a major concern for many legislative and regulatory bodies around the world.Indeed, various states have adopted, are currently adopting, or will adopt various carbon emission restrictions. In particular, an ambitious standard applies to both new aircraft types and those currently in operation, requiring the implementation of technological solutions to comply 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.

[0021] The present invention provides a simple, effective and economical solution to at least some of the above-mentioned problems of the prior art.

[0022] 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.

[0023] The invention relates to a propulsion assembly for an aircraft, this propulsion assembly comprising:

[0024] - a turbomachine extending along a main axis and comprising a fluidic system,

[0025] - a cowling which extends along and around said main axis, the cowling comprising at least one panel which extends around said main axis, said at least one panel comprising a longitudinal edge which is articulated by hinges which define a pivot axis of the panel, from a closed position in which it extends around the turbomachine to an open position in which it is 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 telescopic connection which comprises at least one tubular rod movable in translation in a tubular body along an elongation axis of the connection, the telescopic connection having a length which varies according to the position of the panel around said pivot axis,the tubular rod comprising a first internal passage in fluid communication with a second internal passage of the tubular body at least when the panel is in the closed position.,

[0026] 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 telescopic connection. A first specific feature of this telescopic connection is that its length automatically adapts according to the position of the panel with respect to the turbomachine. A simple sliding of the rod or each rod in the body is enough to adjust the length of the telescopic connection. There is therefore no particular force undergone by the connection when the panel is moved. Another specific feature of the connection is that it ensures fluid circulation between the exchanger and the fluid system when the panel is closed.

[0027] 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:

[0028] - the telescopic connection is integrated into a cylinder connecting the panel to the turbomachine, this cylinder being configured to cause the panel to pivot around said pivot axis;

[0029] - the telescopic link is connected to at least one pump;

[0030] - the telescopic connection is integrated into a connecting rod for holding the panel in a predetermined position relative to the turbomachine, this connecting rod extending between the panel and the turbomachine;

[0031] - a seal is mounted at one end of the body and cooperates with the rod during its movement, and / or a seal is mounted at one end of the rod and cooperates with the body during movement of the rod in the body;

[0032] - the fluid circuit is connected to the fluid system by two telescopic connections, a first of these telescopic connections being connected to an inlet of said fluid circuit, and a second of these telescopic connections being connected to a fluid outlet of said circuit;

[0033] - the fluid circuit is connected to the fluid system by a single telescopic connection in which the first and second internal passages are independent and connected respectively to a fluid inlet and to a fluid outlet of said fluid circuit;

[0034] - the first and second internal passages are in fluid communication regardless of the position of the panel around said pivot axis;

[0035] - the first and second internal passages are fluidically isolated from each other when the panel is in its open position;

[0036] - the telescopic connection comprises a mechanical locking device for locking the tubular rod relative to the tubular body, in a position along said elongation axis; this makes it possible to keep the covers open to carry out a maintenance operation;

[0037] - at least one valve is mounted between the fluid system and the telescopic connection;

[0038] - the telescopic connection comprises a first tubular rod movable in translation in a second tubular rod which is itself movable in translation in the tubular body along the axis of elongation of the connection;

[0039] - the assembly further comprises a reactor mast to which the turbomachine is fixed, the turbomachine being located under the reactor mast and the panels being fixed to the reactor mast by said hinges;

[0040] - the axes of extension of the reactor mast and the turbomachine extend in the same plane;

[0041] - said fluid circuit is an oil circuit or a coolant circuit;

[0042] -- the cowling surrounds at least part of the turbomachine;

[0043] - the cowling comprises two panels of generally semi-circular shape which extend on either side of said main axis;

[0044] - each of these panels has an upper and lower longitudinal edge;

[0045] - the upper longitudinal edge of the or each panel is fixed by the hinges;

[0046] - the other of the panels carries another heat exchanger or another type of fluidic equipment;

[0047] -- the or each panel has a general semi-circular shape.

[0048] Brief description of the figures

[0049] 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: [Fig. 1] Figure 1 is a partial schematic perspective view of a propulsion unit for an aircraft,

[0050] [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,

[0051] [Fig. 3] Figure 3 is a schematic perspective view of a propulsion unit according to one embodiment of the invention,

[0052] [Fig. 4] Figure 4 is a very schematic axial sectional view of telescopic fluid connection links of a surface exchanger to a fluid system;

[0053] [Fig. 5] Figure 5 is a very schematic axial sectional view of a telescopic link and illustrates an alternative embodiment of the invention, the link here being in a retracted position;

[0054] [Fig. 6] Figure 6 is a schematic half-view in axial section of another telescopic connection and illustrates an alternative embodiment of the invention;

[0055] [Fig. 7] Figure 7 is a very schematic axial sectional view of the telescopic link of Figure 5, the link here being in a deployed position;

[0056] [Fig. 8] Figure 8 is a very schematic axial sectional view of a telescopic connection and illustrates another alternative embodiment of the invention;

[0057] [Fig. 9] Figure 9 is a very schematic axial sectional view of a telescopic link and illustrates another alternative embodiment of the invention, the link here being in a retracted position;

[0058] [Fig. 10] Figure 10 is a very schematic axial sectional view of the telescopic link of Figure 9, the link here being in a deployed position;

[0059] [Fig. 11] Figure 11 is a very schematic axial sectional view of a telescopic link and illustrates another alternative embodiment of the invention, the link here being in a retracted position;

[0060] [Fig. 12] Figure 12 is a very schematic axial sectional view of the telescopic link of Figure 11, the link being here in a deployed position; [Fig. 13] Figure 13 is a very schematic axial sectional view of a telescopic link and illustrates another alternative embodiment of the invention, the link being here in a retracted position;

[0061] [Fig. 14] Figure 14 is a very schematic axial sectional view of the telescopic link of Figure 13, the link here being in a deployed position;

[0062] [Fig. 15] Figure 15 is a very schematic view of the telescopic links of Figure 4 further associated with a pressurized oil supply circuit for these links so that they can provide an additional jack function, the telescopic links being used here to supply oil to the fluid circuit of the exchanger, and

[0063] [Fig. 16] Figure 16 is a view similar to that of Figure 15, the telescopic links being here used to move the panel to which they are connected.

[0064] Detailed description of the invention

[0065] Figures 1 and 2 have already been described in the above.

[0066] Figure 3 illustrates an embodiment of a propulsion assembly 10 according to the invention. This propulsion assembly 10 comprises:

[0067] - a turbomachine 14 comprising a fluidic system 18, in particular its bearings and rotating elements, and

[0068] - a cowling 16 which can surround the turbomachine 14, as in the example shown.

[0069] 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.

[0070] 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.

[0071] The propulsion unit 10 may further comprise a reactor mast 12.

[0072] The cowling 16 comprises two panels 20 of generally semi-circular shape which extend on either side of a plane P passing through the main axis B of the turbomachine 14 or even the respective axes A, B of the reactor mast 12 and of the turbomachine 14 when the reactor mast is part of the propulsion assembly. The plane P may be vertical or inclined relative to the vertical.

[0073] The panels 20 comprise upper longitudinal edges 22 which are fixed by hinges 25. The hinges 25 can be carried by a beam of the turbomachine 14 or by the reactor mast 12 in the case where the latter is part of the propulsion assembly 10.

[0074] The upper edges 22 are located substantially in a 12 o'clock position, being separated from each other by the beam or the reactor mast 12.

[0075] The hinges 25 are generally arranged one behind the other along a pivot axis C of the corresponding panel 20.

[0076] Each of the panels 20 is articulated around this axis C which can be parallel to the axis B for example, from a closed position in which its lower longitudinal edge 24 is substantially at the 6 o'clock position, to an open position (illustrated in the drawing) in which its lower edge 24 is distant from the 6 o'clock position. The angular movement (arrow F) between the two positions is for example greater than 30° around the axis C.

[0077] 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.

[0078] 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 20. This position is not limiting. Alternatively, the exchanger 26 could for example be on an external convex surface of the panel 20.

[0079] 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 flow of gas passing inside or outside the panel. 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.

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

[0081] The fluidic connection means of the fluidic circuit 26' of each exchanger 26 to the fluidic system 18 comprise at least one telescopic connection 30.

[0082] 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.

[0083] The fluid inlet 26a of the circuit 26' is connected to the fluid outlet 18b of the system 18 by a first telescopic connection 30, and the fluid outlet of the circuit 26' is connected to the fluid inlet 18a of the system by a second telescopic connection 30'.

[0084] The movement of each panel 20 can be carried out manually. It could alternatively be carried out using a hydraulic device comprising at least one jack 32 for moving the panel 20 between its extreme positions.

[0085] In this case, the cylinder 32 is connected to a source of fluid such as oil by a pump not shown. The pump supplies oil at a predetermined pressure which makes it possible to deploy the cylinder 32 and to move the panel 20 around its pivot axis C.

[0086] To maintain each panel 20 in the open position illustrated in FIG. 3, the propulsion assembly 10 may comprise at least one holding rod 34. A rod 34 of this type extends between the turbomachine 14 and the panel 20, inside the panel, and its length may be fixed so that it ensures the maintenance of the panel in an open position. It is therefore understood that, in the prior art, each panel 20 may be connected to the turbomachine 14 by one or more jacks 32 and by one or more rods 34.

[0087] In the context of the present invention, each telescopic link 30, 30' also extends between the panel 20 and the turbomachine 14. Each telescopic link 30, 30' may be independent of the cylinder 32 and the connecting rod 34. Alternatively, each telescopic link 30, 30' is integrated into a cylinder 32 or into a connecting rod 34.

[0088] When a telescopic connection 30, 30' is integrated into a jack 32, this jack has a dual function of fluid circulation between the fluid system 18 and the exchanger 26, and of movement of the panel 20 between its extreme positions.

[0089] When a telescopic connection 30, 30' is integrated into a connecting rod 34, this connecting rod has a dual function of fluid circulation between the fluid system 18 and the exchanger 26, and of holding the panel 20 in its open position or in one of its open positions.

[0090] Figures 4 and following illustrate several embodiments for these telescopic connections 30, 30'.

[0091] Figure 4 illustrates a first embodiment in which the fluid circuit 26' of the exchanger 26 is connected by the two telescopic links 30, 30' mentioned above to the fluid system 18 of the turbomachine 14.

[0092] Each telescopic link 30, 30' comprises a tubular rod 40 movable in translation in a tubular body 42 along an elongation axis C of the link. The telescopic link 30, 30' has a length which varies depending on the position of the rod 40 in the body 42. When the rod 40 is fully retracted into the body 42, the telescopic link is in a retracted position illustrated in the drawing. When the rod 40 is fully extended from the body 42, the telescopic link is in a deployed position (see figure 7).

[0093] The length of each 30, 30' telescopic link automatically adapts to the position of the panel relative to the turbomachine. The link deploys when the panel opens and the link retracts when the panel closes.

[0094] The tubular rod 40 has a first internal passage 44 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 illustrated in the drawing. The passages 44, 46 may also be in fluid communication when the panel is in the open position and the link is in the extended position.

[0095] In the example shown, the passage 44 of the rod 40 extends inside and along the rod 40 over substantially its entire length. The passage 44 opens at the end of the rod 40 which is engaged in the body 42 and is in direct fluid communication with the passage 46 of the body 42, regardless of the position of the rod in the body.

[0096] The rod 40 comprises a fluid passage port 48 which is located at the end of the rod located outside the body 42, and which is in fluid communication with the internal passage 44 of this rod. The body 42 comprises a fluid passage port 50 which is located at the end of the body 42 located opposite that through which the rod 40 exits, and which is in fluid communication with the internal passage 46 of the body. The port 48 of the connection 30 is connected to the inlet 26a of the circuit 26' and its outlet 26b is connected to the port 48 of the connection 30'. The port 50 of the connection 30 is connected to the outlet 18b of the system 18 and its inlet 18a is connected to the port 50 of the connection 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.

[0097] It is therefore understood that, whatever the position of the telescopic connections 30, 30' and therefore of the panel 20 relative to the turbomachine 14, the fluid circuit 26' of the exchanger 26 is always fluidically connected to the fluid system 18 of the turbomachine 14. A valve 52 can be mounted upstream and / or downstream of each telescopic connection 30, 30', to fluidically isolate it from the fluid system 18 and / or the circuit 26' depending on the requirements.

[0098] The ends of each telescopic link 30, 30' can be fixed respectively to the panel 20 or to the exchanger 26, and to the turbomachine 14, by swiveling or pivoting links 54.

[0099] We now refer to Figures 5 and 6 which illustrate alternative embodiments of a telescopic connection 30, 30' with regard to sealing means between the body 42 and the rod 40. To prevent fluid leakage, the telescopic connection 30, 30' is equipped with at least one seal 56 which can be carried by the body 42 and cooperate with the rod 40, as illustrated in Figure 5, or carried by the rod 40 and cooperate with the body 42, as illustrated in Figure 6. In the case of Figure 5, it is the end of the body 42 through which the rod 40 exits which is equipped with the seal 54. In the case of Figure 6, it is the end of the rod 40 engaged in the body 42 which is equipped with the seal 54.

[0100] The configuration of Figure 5 leads to pressure balance on both sides, thus minimizing the pressurization effort, which reduces the forces on the structure when the system is pressurized in operation.

[0101] Figure 8 illustrates an alternative embodiment in which a single telescopic connection 30 could be used to fluidically connect the inlet and outlet 26a, 26b of the fluidic circuit 26' to the fluidic system 18. For this, the telescopic connection 30 comprises two independent internal fluidic circuits, compared to a single internal circuit in the previous embodiments.

[0102] The rod 40 comprises two parallel internal passages 44, 45 which extend along the rod. The internal passage 44 is similar to that described above and opens at the end of the rod 40 engaged in the body 42. The internal passage 45 opens on one side of this end. The body 42 comprises two independent internal passages 46, 47. The internal passage 46 is located in the bottom of the body 42 and is in fluid communication with the passage 44 regardless of the position of the rod 40 in the body 42. The internal passage 47 is located on one side or at the periphery of the body 42 and is in fluid communication with the passage 45 regardless of the position of the rod 40 in the body 42.

[0103] The rod 40 comprises two fluid passage ports 48, 49, a first port 48 similar to that described above and which is in fluid communication with the passage 44, and a second port 49 which is also located at the end of the rod 40 opposite that engaged in the body 42 and which is in fluid communication with the passage 45.

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

[0105] A seal 56 is provided at the end of the rod 40 engaged in the body 42 and makes it possible to isolate the two internal passages 46, 47 from the body. Another seal 58 is provided at the end of the body 42 through which the rod 40 exits, and makes it possible to isolate the internal passage 47 from the exterior of the telescopic connection 30, 30'.

[0106] Figures 9 and 10 illustrate another alternative embodiment of the invention in which the internal passages 45, 46 of the rod 40 and the body 42 communicate with each other when the panel 20 is in the closed position, and do not communicate with each other when the panel 20 is in the open position. It is therefore understood that the opening of the panel 20 will cause the circuit between the exchanger 26 and the fluid system 18 to be cut, which limits the risk of leakage for example.

[0107] The rod 40 includes an internal passage 45 that extends along the rod and opens onto one side of the rod. The body 42 includes an internal passage 47 that is located on one side or at the periphery of the body and is in fluid communication with the passage 45 when the rod is in the retracted position shown in Figure 9. The body 42 further includes an internal cavity 60 at the bottom of the body, which is isolated from the passage 47 by a seal 54 carried by the end of the rod 40 engaged in the body 42. In the position of Figure 9, the port 51 is in fluid communication with the passage 47. In the position of Figure 10, the port 51 is no longer in fluid communication with the passage 47.

[0108] Figures 11 and 12 illustrate another alternative embodiment of the invention which corresponds to the scenario mentioned above in which the telescopic connection 30, 30' is integrated into a holding rod 32.

[0109] This variant differs from the previous variants essentially in that the telescopic connection 30, 30' further comprises a mechanical locking device 62 for the rod 40 in its deployed position or in one of its deployed positions. It is therefore understood that, in addition to the fluid circulation between the circuit 26' and the fluid system 18, the telescopic connection 30, 30' also has the function of being able to hold the connection fixedly in its deployed position and therefore of being able to hold the panel 20 in its open position.

[0110] The device 62 is movable from an unlocking position illustrated in FIG. 11, in which the rod 40 can slide freely inside the body 42, to a locking position illustrated in FIG. 12 in which the rod 40 is locked in the deployed position. The locking can be achieved for example by engaging a finger 64 of the device 62 in an orifice 66 or a slot in the rod 40. The activation of the device 62 can be automatic or controlled.

[0111] Figures 13 and 14 illustrate another alternative embodiment of the invention in which the telescopic connection 30, 30' comprises more than two elements and in particular two rods 40, 68 and a body 42. A first tubular rod 40 is movable in translation in a second tubular rod 68 which is itself movable in translation in the tubular body 42 along the axis of elongation of the connection 30, 30'.

[0112] As mentioned above, the internal passages of the rods 40, 68 and the body 42 communicate with each other when the link 30, 30' is retracted (figure 13) and can also communicate with each other when the link is deployed (figure 4).

[0113] We now refer to figures 15 and 16 which illustrate the aforementioned variant embodiment in which the telescopic links 30, 30' also have a jack function.

[0114] In addition to being connected to the fluidic system 18, the telescopic links 30, 30' are connected to a pressurized oil supply circuit 70. This circuit 70 comprises a pump 72 which is connected to a fluidic reservoir 74 which may be a fluidic reservoir of the fluidic system 18. The circuit 70 may be isolated from the telescopic links 30, 30' by a valve 76.

[0115] In Figure 15, the telescopic connections 30, 30' are used to supply the fluid circuit 26' of the exchanger 26 with the oil coming from the fluid system 18. As the arrows show, the oil coming from the system 18 passes through the connection 30 to reach the inlet 26a of the circuit 26'. The oil leaves the circuit via the outlet 26b and then passes through the connection 30' to reach the system 18.

[0116] In Figure 16, the telescopic links 30, 30' both operate as cylinders. The valve 52 that connects the telescopic link 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 that thus supplies the telescopic link 30 applies pressure to the rod 40 that forces it to extend. A portion of this oil circulates through the internal passages of the link 30 and into the fluid circuit 26' to reach the other telescopic link 30' to also apply pressure to the rod 40 that forces it to extend. The rods 40 of the two links 30, 30 extend and move the panel 20 from its closed position to its open position. This system is naturally reversible.

[0117] The pressure of the oil circulating in the fluid system 18 and in the circuit 26' in the case of Figure 15 is lower than that of the oil in the circuit 26' in the case of Figure 16 when using the connections as cylinders. The oil pressure in the case of Figure 15 is for example less than or equal to 6 bars. The oil pressure in the case of Figure 16 is for example greater than or equal to 50 bars.

Claims

CLAIMS 1. Propulsion assembly (10) for an aircraft, this propulsion assembly (10) comprising: - a turbomachine (14) extending along a main axis (B) and comprising a fluidic system (18), - a cowling (16) which extends along and around said main axis (B), the cowling (16) comprising at least one panel (20) which extends around said main axis (B), said at least one panel (20) comprising a longitudinal edge (22) which is articulated by hinges (25) which define an axis (C) for pivoting 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 telescopic connection (10) which comprises at least one tubular rod (40) movable in translation in a tubular body (42) along an axis extension of the connection, the telescopic connection (30,30') having a length which varies depending on the position of the panel (20) around said pivot axis (C), the tubular rod (42) comprising a first internal passage (44, 45) in fluid communication with a second internal passage (46, 47) of the tubular body (42) at least when the panel (20) is in the closed position., 2. Propulsion assembly (10) according to claim 1, in which the telescopic connection (10) is integrated into a cylinder (32) for connecting the panel (20) to the turbomachine (14), this cylinder (32) being configured to cause the panel (20) to pivot around said pivot axis (C).

3. Propulsion assembly (10) according to claim 1, in which the telescopic link (10) is integrated into a connecting rod (34) for holding the panel (20) in a predetermined position relative to the turbomachine (14), this connecting rod (34) extending between the panel (20) and the turbomachine (14).

4. Propulsion assembly (10) according to one of the preceding claims, in which a seal (58) is mounted at one end of the body (42) and cooperates with the rod (42) during its movement, and / or a seal (56) is mounted at one end of the rod (40) and cooperates with the body (42) during the movement of the rod in the body.

5. Propulsion assembly (10) according to one of the preceding claims, in which the telescopic link is connected to at least one pump.

6. 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 telescopic links (10), a first of these telescopic links being connected to an inlet (26a) of said fluid circuit (26'), and a second of these telescopic links being connected to a fluid outlet (26b) of said circuit (26').

7. Propulsion assembly (10) according to one of claims 1 to 5, in which the fluid circuit (26') is connected to the fluid system (18) by a single telescopic connection (30) in which the first and second internal passages (44, 45, 46, 47) are independent and connected respectively to a fluid inlet (26a) and to a fluid outlet (26b) of said fluid circuit.

8. Propulsion assembly (10) according to one of the preceding claims, in which the first and second internal passages (44, 45, 46, 47) are in fluid communication regardless of the position of the panel (20) around said pivot axis (C).

9. Propulsion assembly (10) according to one of claims 1 to 7, in which the first and second internal passages (44, 45, 46, 47) are fluidically isolated from each other when the panel (20) is in its open position.

10. Propulsion assembly (10) according to one of the preceding claims, in which the telescopic connection (30, 30') comprises a device of mechanical locking (62) for locking the tubular rod (40) relative to the tubular body (42), in a position along said elongation axis.

11. Propulsion assembly (10) according to one of the preceding claims, in which the telescopic connection (30, 30') comprises a first tubular rod (40) movable in translation in a second tubular rod (68) which is itself movable in translation in the tubular body (42) along the axis of elongation of the connection.

12. Propulsion assembly (10) according to one of the preceding claims, in which at least one valve (52) is mounted between the fluidic system and the telescopic connection.

13. Propulsion assembly (10) according to one of the preceding claims, in which the assembly further comprises a reactor mast (12) to which the turbomachine is fixed, the turbomachine being located under the reactor mast and the panels (20) being fixed to the reactor mast by said hinges (25).

14. Propulsion assembly (10) according to one of the preceding claims, in which said fluid circuit (26') is an oil circuit or a coolant circuit.Propulsion assembly (10) according to one of the preceding claims, in which the cowling (16) comprises two panels (20) of generally semi-circular shape which extend on either side of said main axis, each of these panels has an upper (22) and lower (24) longitudinal edge, the upper longitudinal edge of the or each panel is fixed by the hinges.

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