Coupling system for automatically connecting and disconnecting a stationary part and a movable part, in particular of a turbine engine

Abstract

The invention relates to a coupling system for connecting and disconnecting a stationary part (52) and a movable part (50) of at least one structure (2), comprising a cam (60) that is intended to be positioned on one of the stationary and movable parts and can pivot about a first axis (Y) in a first plane orthogonal to the first axis (Y), and a roller-holding element (62) intended to be positioned on the other of the stationary and movable parts, holding at least first and second rollers (64, 68) and being able to pivot about a second axis (Z) in the first orthogonal plane, the cam (60) and the roller-holding element (62) being suitable for bearing against one another in a connection position between the stationary part and the movable part in which the first and second axes (Y, Z) are coincident.

Description

[0001] DESCRIPTION

[0002] TITLE: Coupling system for automatically connecting and disconnecting a fixed part and a moving part, particularly of a turbomachine

[0003] technical field

[0004] The invention relates to the automatic connection and disconnection between a fixed part and a moving part of a coupling system, in particular between a fixed part and a moving part of a coupling system adapted to move a moving panel of a turbomachine discharge channel.

[0005] In particular, the invention relates to a coupling system for the automatic connection and disconnection between a fixed part and a moving part of at least one structure, in particular of a turbomachine, an aircraft turbomachine comprising such a coupling system and an aircraft comprising such a turbomachine.

[0006] Previous techniques

[0007] A turbomachine typically includes a primary gas flow channel and a secondary gas flow channel.

[0008] Recently, triple-flow turbomachinery has been designed, and in order to further increase the airflow through the turbomachine compressor, an airflow channel, called a discharge channel, is connected downstream of this compressor.

[0009] Typically, the discharge channel is positioned on an opening cover of the turbomachine which is able to pivot around a longitudinal axis of the turbomachine, relative to the fixed main body of the turbomachine, and which is intended for maintenance and inspection inside the turbomachine.

[0010] A movable panel supported by the opening hood can be moved between an open position, allowing air to flow through the discharge channel, and a closed position, blocking the discharge channel. When the movable panel is in the open position, the airflow through the compressor increases and the air pressure downstream of the compressor decreases.

[0011] The movable panel is made movable between the open and closed positions by means of an actuation device, positioned on the inner face of the opening hood, and connected to the fixed main body of the turbomachine to control its operation.

[0012] In order to be able to open the opening hood and carry out maintenance operations, the connection between the fixed part of the turbomachine and the opening hood must be made disconnectable and reconnectable by a coupling system.

[0013] The coupling systems commonly used for connecting are disconnectable connecting rods, pushrods, forks or dog clutches.

[0014] However, disconnectable connecting rods require manual action to disconnect them.

[0015] However, given its location, the mating system is not accessible.

[0016] Furthermore, the coupling system requires force in two opposite directions to function, while pushrods can only transmit force in one direction. Also, the closing mechanism of the opening hood is incompatible with dog clutches.

[0017] Furthermore, following a maintenance event, the position of the first element of the coupling system positioned on the opening hood and intended to cooperate with the second element of the coupling system positioned on the fixed part may be random.

[0018] However, the coupling system which cannot be connected manually must be adapted for automatic connection and disconnection of the first and second elements regardless of their position after maintenance.

[0019] However, the forks do not allow the coupling system to be reconnected in all possible positions. Description of the invention

[0020] The present invention therefore aims to overcome all or part of the aforementioned disadvantages, and in particular to provide a coupling system allowing automatic connection and disconnection between a fixed part and a moving part of a structure in a plurality of positions of the moving part, in particular between a fixed part and an opening hood of a turbomachine capable of moving a movable panel of a discharge channel of the turbomachine.

[0021] The present invention relates to a coupling system for connecting and disconnecting a fixed part and a moving part of at least one structure, comprising a cam intended to be positioned on one of the fixed and moving parts and being able to pivot about a first axis in a first plane orthogonal to the first axis, and a roller-carrying element intended to be positioned on the other of the fixed and moving parts, carrying at least first and second rollers and being able to pivot about a second axis in said first orthogonal plane, the cam and the roller-carrying element being adapted to bear against each other in a connection position between the fixed part and the moving part in which the first and second axes coincide.

[0022] The mechanical coupling system allows the connection between a fixed part and a moving part and the connection and disconnection of these two parts in several positions of the moving part, without the need for manual intervention.

[0023] It also allows a rotational force to be transmitted in both directions of rotation around an axis.

[0024] In one embodiment, the moving part and the fixed part can be supported by a single structure, such as a turbomachine.

[0025] Alternatively, the moving part and the fixed part can be supported, respectively, by two independent structures.

[0026] In one embodiment, the cam may include a convex portion extended on either side by first and second concave portions, the first concave portion, the convex portion and the second concave portion extending in said first orthogonal plane, each of the first and second concave portions being intended to cooperate with one of the first and second rollers, and the convex portion being intended to cooperate with the roller-carrying element between the first and second rollers in said connection position between the fixed part and the moving part.

[0027] In one embodiment, the roller-carrying element can be connected to a first end of a shaft extending along said second axis, a second end of the shaft opposite to the first end being able to be connected to a linear actuator via a connecting rod, the connecting rod and the linear actuator extending in a second plane orthogonal to said second axis and parallel to said first orthogonal plane.

[0028] According to one characteristic, the coupling system may include a control device adapted to control the rotation of the roller-carrying element around said second axis in said first orthogonal plane.

[0029] Advantageously, the cam can be pivotally fixed on a bearing connecting the cam to the rest of the moving part.

[0030] Preferably, the coupling system includes a device for absorbing tolerance backlash between the first and second rollers and the cam, positioned on one of the cam and the roller-carrying element, such as a leaf spring.

[0031] In one embodiment, the coupling system as described above is adapted to move at least one movable panel of a discharge vein of a turbomachine between an open position and a closed position.

[0032] Advantageously, the coupling system as described above can be adapted to move at least one movable panel of a discharge channel from a third flow channel, defining a third airflow of a triple-flow turbomachine, between an open and a closed position. This turbomachine is preferably adapted to allow the passage of the third airflow to an external flow. The present invention also relates to an aircraft turbomachine comprising one or more coupling systems as described above.

[0033] Advantageously, the turbomachine may include at least one discharge channel, at least one movable panel capable of being moved between an open position allowing air to flow through the discharge channel and a closed position, and a coupling system as previously described for moving the movable panel between the open position and the closed position.

[0034] Advantageously, the turbomachine can be a triple-flow turbomachine, the discharge channel being a discharge channel of a third flow channel delimiting a third air stream, preferably the discharge channel being adapted to allow the passage of the third air stream to an external stream, in particular called secondary air stream.

[0035] Advantageously, the turbomachine includes a first nozzle for separating a first flow stream of the internal airflow, called the primary flow stream, from a flow stream of the external airflow, called the secondary flow stream, and a second nozzle for separating the primary flow stream from a second flow stream of the internal flow, called the third flow stream.

[0036] Advantageously, the turbomachine may include at least one compressor, one combustion chamber, at least one turbine, the primary flow duct delimiting a primary airflow which flows from the first separation nozzle through the compressor, the combustion chamber, and the turbine, the secondary flow duct delimiting a secondary airflow which flows from the first separation nozzle radially out of the first separation nozzle, and a third flow duct delimiting a third airflow which flows from the second separation nozzle radially out of the second separation nozzle.

[0037] In one embodiment, the cam of the coupling system is positioned on an opening hood of the turbomachine. Such a multi-position automatic coupling system allows connection and disconnection between a fixed part and a moving part of a turbomachine, such as an opening hood that needs to be opened for maintenance.

[0038] In one embodiment, the cam is positioned on an opening hood of the turbomachine and the roller-carrying element is positioned on a fixed part of the turbomachine relative to which the opening hood is movable, such as a main body or a fixed section.

[0039] Advantageously, the coupling system may be able to move the movable panel between the open position and the closed position by means of an actuation device linking the movable panel and the coupling system.

[0040] In one embodiment, the turbomachine may include at least one compressor, one combustion chamber, at least one turbine, one flow duct of an external flow, and at least one flow duct of an internal flow in which flows a flow from at least one compressor and which is provided with the discharge duct having a connection to said internal flow duct located longitudinally downstream of said compressor.

[0041] According to one feature, the turbomachine may include a nozzle for separating the flow stream of the external flow, called the secondary flow stream, and the flow stream of the internal flow, called the primary flow stream, which extends through the combustion chamber.

[0042] According to one feature, the turbomachine may include at least one internal flow stream, referred to as the third flow stream, and another internal flow stream carrying a flow from the compressor, extending through the combustion chamber, referred to as the primary flow stream, and comprising a nozzle for separating the primary flow stream from the third flow stream, the third flow stream being located at least partially radially between the primary flow stream and the external flow stream, referred to as the secondary flow stream. According to one feature, the internal flow stream may be radially delimited by an external wall and an internal wall, the discharge stream extending radially outwards from an opening formed in the internal wall of the internal flow stream.

[0043] The present invention also relates to an aircraft comprising at least one coupling system as described above and / or at least one turbomachine as described above.

[0044] Brief description of the drawings

[0045] Other objects, features and advantages of the invention will become apparent from the following description, given solely by way of non-limiting example and made with reference to the accompanying drawings in which:

[0046] [Fig 1] is a cross-sectional view of a first lateral side of a turbomachine according to an embodiment of the invention;

[0047] [Fig 2] is a perspective view of the front area of ​​a first lateral side of the turbomachine illustrated in Figure 1, in which the opening hood is closed;

[0048] [Fig 3] is a view analogous to that of figure 2 when the opening hood is open;

[0049] [Fig 4] is a detail view of figure 1 when the movable panel of the discharge vein is in an open position;

[0050] [Fig 5] is a view analogous to that of figure 4 when the movable panel is in the closed position;

[0051] [Fig 6] is a perspective view of a coupling system according to an embodiment of the invention, in an open position of the movable panel, when the opening hood is closed;

[0052] [Fig 7] represents the coupling system of figure 6 in an open position of the movable panel, when the opening cover is partially open; [Fig 8] represents the coupling system of figure 6 in a closed position of the movable panel, when the opening cover is partially open;

[0053] [Fig 9] represents the coupling system of figure 6 in a closed position of the movable panel, the cam and the roller carrier being, respectively, in the closed and open positions of the movable panel, when the opening hood is partially open;

[0054] [Fig 10] represents the coupling system of figure 6 in a closed position of the movable panel, the cam and the roller carrier being, respectively, in the open and closed position of the movable panel, when the opening hood is partially open;

[0055] [Fig 1 1 ] is a detailed view of the coupling system in Figure 6.

[0056] Detailed description

[0057] Figure 1 represents an aircraft triple-flow turbomachine 2 comprising an unfaired propeller 4 which is provided with blades 6 rotating about a longitudinal axis of the turbomachine 2, a non-rotating stage 8 which is provided with a plurality of variable-pitch blades 10 which are non-rotating about the longitudinal axis, a faired intermediate fan 12, a low-pressure compressor 14, a high-pressure compressor 16, a combustion chamber 18, a high-pressure turbine 20, and a low-pressure turbine 22. The intermediate fan 12 has, in particular, the function of increasing the pressure of the air directed towards the combustion chamber 18.

[0058] The turbomachine 2 also includes a low-pressure shaft 24 integral with the propeller 4, the intermediate blower 12, the low-pressure compressor 14 and the low-pressure turbine 22, and a high-pressure shaft 26 integral with the high-pressure compressor 16 and the high-pressure turbine 20.

[0059] In the illustrated example, the turbomachine 2 comprises a main body 48, a fixed section 52 extending circumferentially around the main body 48 and two half-shells, a downstream portion of which extends circumferentially around the fixed section 52. Each of the half-shells is positioned on one of the two lateral sides of the turbomachine 2, each forming an opening hood 50.

[0060] The intermediate blower 12 is positioned between the main body 48 and an upstream portion of the half-shells.

[0061] In addition, the low pressure compressor 14, the high pressure compressor 16, the combustion chamber 18, the high pressure turbine 20, and the low pressure turbine 22 are positioned between the main body 48 and the fixed section 52.

[0062] Each opening hood 50 is capable of pivoting around the longitudinal axis X of the turbomachine 2 to allow maintenance or inspection operations to be carried out.

[0063] The two opening hoods 50 of the turbomachine 2, movable relative to the fixed section 52, are capable of pivoting in opposite directions.

[0064] Figures 2 and 3 illustrate one of the side faces of the turbomachine 2, with Figure 2 showing the opening hood 50 in the closed position and Figure 3 in the open position.

[0065] Turbomachine 2 has a three-flow aircraft engine architecture with three paths for air passing through propeller 4.

[0066] The turbomachine 2 comprises a first separation nozzle 28 separating a first flow path of the internal airflow 30, called the primary flow path, from a flow path of the external airflow 32, called the secondary flow path. The first separation nozzle 28, supported by the opening cowling 50, is located longitudinally between the propeller 4 and the non-rotating stage 8.

[0067] The turbomachine 2 also includes a second separation nozzle 34 for the primary flow stream 30 and a second internal flow stream 36, referred to as the third flow stream. The second separation nozzle 34, supported by the fixed section 52, is located longitudinally downstream of the non-rotating stage 8. The third flow stream 36 is located radially between the portion of the primary flow stream 30 extending downstream from the second separation nozzle 34 and the secondary flow stream 32. The intermediate fan 12 is located longitudinally between the first separation nozzle 28 and the second separation nozzle 34.

[0068] The primary flow channel 30 delimits a primary airflow which flows from the first separation nozzle 28 through the intermediate blower 12, the low pressure compressor 14, the high pressure compressor 16, the combustion chamber 18, the high pressure turbine 20 and the low pressure turbine 22. The primary flow channel 30 is radially delimited by an external wall 30a of the main body 48 and by an internal wall 30b of the fixed section 52.

[0069] The secondary flow vein 32 delimits a secondary air flow which flows from the first separation nozzle 28 radially outside the first separation nozzle 28. The secondary flow vein 32 is not here delimited radially outside.

[0070] The third flow channel 36 delimits a third airflow which flows from the second separation nozzle 34 radially outside the second separation nozzle 34. The third flow channel 36 is delimited radially by an external wall 36a of the fixed section 52, opposite the internal wall 30b, and by an internal wall 36b of the opening hood 50.

[0071] When the opening hood 50 is in the closed position, the outer wall 36a of the fixed section 52 and the inner wall 36b of the opening hood 50 are positioned opposite each other.

[0072] As more visibly illustrated in Figures 4 and 5, a flow channel of an internal flow of the turbomachine 2, and here the third flow channel 36, is provided with a plurality of discharge channels 38, each connected to the flow channel of the internal flow downstream of the intermediate blower 12.

[0073] Each discharge channel 38 is connected on one side to the third flow channel 36, and opens on the other side onto a radially external surface of the turbomachine 2. Each discharge channel 38 extends radially outwards from an opening 54 forming an air outlet, formed in the internal wall 36b of the third flow channel 36, remaining radially outside the first flow channel 30, in particular remaining radially between the primary flow channel 30 and the secondary flow channel 32 and opening into the secondary flow channel 32.

[0074] The discharge veins 38 of the third flow vein (36) is adapted to allow the passage of the third airflow to the external flow, called secondary airflow.

[0075] The openings 54 are spaced from each other along the circumferential direction of the turbomachine 2.

[0076] In the illustrated example, the turbomachine 2 further comprises a plurality of movable panels 40, each arranged opposite one of the openings 54 of the discharge veins 38.

[0077] Alternatively, the turbomachine 2 may include a single discharge channel 38 extending from a single opening 54 and selectively closed by a single movable panel 40.

[0078] Each movable panel 40 is capable of being moved between an open position in which the movable panel 40 allows air to circulate through the discharge channel 38 and a closed position in which the movable panel 40 closes the discharge channel 38. The open position of the movable panel 40 is shown in Figure 4 and the closed position of the movable panel 40 in Figure 5.

[0079] In the illustrated example, the movable panel 40 in the closed position partly forms the internal wall 36b of the third flow vein 36.

[0080] The turbomachine 2, and in particular the opening cowling 50, may include an upstream fairing 42 forming the outer surface of the turbomachine 2 upstream of the discharge channel 38 and a downstream fairing 44 forming the outer surface of the turbomachine 2 downstream of the discharge channel 38. The upstream fairings 42 and downstream fairings 44 together define an outlet of the discharge channel 38. The movable panel 40 in the closed position extends axially from the upstream fairing 42 towards the downstream fairing 44.

[0081] The turbomachine 2 further includes a plurality of actuation devices 56, each intended to actuate one of the movable panels 40. Each actuation device 56 may include one or more actuators such as cylinders, and is capable of positioning the movable panel 40 in the open position or in the closed position.

[0082] Preferably, each actuation device 56 is directly connected to one of the movable panels 40 to drive its movement.

[0083] In addition, the turbomachine 2 includes a coupling system 58, visible in figure 6, allowing the opening hood 50 and the fixed section 52 to be connected and disconnected automatically.

[0084] The coupling system 58 is further adapted to move the movable panels 40 of the discharge veins 38 between an open position and a closed position.

[0085] In order to limit the weight of the turbomachine 2, each of the first and second lateral sides of the turbomachine 2 has a unique coupling system 58 adapted to move the plurality of movable panels 40 on the lateral side on which the coupling system 58 is positioned.

[0086] In Figure 6, the coupling system 58 is shown in an open position of the movable panels 40.

[0087] The coupling system 58 includes a cam 60 capable of pivoting about a first axis Y in a first plane orthogonal to the first axis Y.

[0088] The coupling system 58 further includes a roller carrier element 62 carrying a first roller 64 and a second roller 68. The roller carrier element 62 is able to pivot about a second axis Z in the first orthogonal plane.

[0089] The cam 60 and the roller carrier element 62 are adapted to bear against each other in a connection position between the fixed section 52 and the opening hood 50. As illustrated in the figure, the first and second axes Y, Z are coincident when the coupling system 58 is in the connection position of the cam 60 and the roller carrier element 62. When the opening hood 50 is opened, the cam 60 and the roller carrier element 62 disconnect, the cam 60 moves away from the roller carrier element 62 and the first and second axes Y and Z are no longer coincident.

[0090] The opening trajectory O of the hinged cover 50 is shown in Figure 7, which illustrates the hinged cover 50 partially open. The cam 60 and the roller-carrying element 62 are shown in their respective opening positions of the movable panels 40.

[0091] In the illustrated embodiment, the cam 60 is positioned on the opening hood 50, fixed for rotation on a bearing 70 extending along the first axis Y. The bearing 70 is itself fixed to a frame 72 by fastening means, such as screw and nut assemblies, and the frame 72 is connected to the inner wall 36b of the opening hood 50.

[0092] Although the frame 72 is perforated for its fixing by the screw and nut assemblies, the bearing 70, which is positioned between the frame 72 and the cam 60, makes it possible to re-establish a fire barrier between the front area on the engine side located in the main body 48 and the internal area of ​​the opening hood 50.

[0093] In addition, the roller-carrying element 62 is connected to a first end 74a of a shaft 74 which is positioned so as to extend along the second axis Z.

[0094] The second end 74b of the shaft 74, opposite the first end 74a, is connected to a linear actuator 76 via a connecting rod 78. The connecting rod 78 and the linear actuator 76 extend in a second plane that is orthogonal to the second Z-axis and parallel to the first plane, which is orthogonal to the first Y-axis. The connecting rod 78 transforms the linear motion of the linear actuator 76 into a rotational motion of the shaft 74, and thus of the roller-carrying element 62, around the second Y-axis.

[0095] Advantageously, the shaft 74 and the linear actuator 76 are each held by a bearing, respectively 80 and 82, fixed, preferably by welding, on the external wall 36a of the main body 48 of the turbomachine 2.

[0096] Alternatively, the cam 60 could be positioned on the fixed section 52 and the roller-carrying element 62 on the opening hood 50. In the illustrated example, the cam 60 has a convex portion 60a extended on either side by first and second concave portions 60b and 60c.

[0097] The first concave portion 60b, the convex portion 60a and the second concave portion 60c extend in the first plane orthogonal to the first Y axis. When the cam 60 and the roller-carrying element 62 are in the connection position, the first concave portion 60b cooperates with the first roller 64, the second concave portion 60c cooperates with the second roller 60c, and the convex portion 60a cooperates with the roller-carrying element 62, particularly in the interval formed between the first and second rollers 64, 68.

[0098] When the opening hood 50 is closed, such a geometry of the cam 60 allows contact between the cam 60 and the roller carrier element 62 in the entire angular range of the cam 60 around the first Y axis, and therefore a passage to the connection position regardless of the position of the cam 60 left after maintenance.

[0099] According to one feature, the coupling system 58 may include a control device adapted to control the rotation of the roller carrier element around the second Z axis, in the first orthogonal plane.

[0100] The control device, not shown, is connected to the linear actuator 76 to control its operation and, consequently, the rotational movement of the roller-carrying element 62 for its passage between the opening and closing positions of the movable panels 40.

[0101] Advantageously, the control device is positioned on a part of the turbomachine 2 which is fixed relative to the movable opening hood 50.

[0102] In addition, the coupling system 58 is connected to the actuation devices 56 intended to actuate the opening and closing of the movable panels 40 so that the movement of the movable panels 40 between the open and closed positions is transmitted by the coupling system 58 via the actuation devices 56. Figure 8 shows the cam 60 and the roller-carrying element 62 of the coupling system 58 in a closed position of the movable panels 40, when the opening hood 50 is partially open.

[0103] Figure 9 shows the cam 60 in the closed position of the movable panels 40 and the roller-carrying element 62 in the open position of the movable panels 40,

[0104] In contrast to figure 9, figure 10 represents the cam 60 in the opening position of the movable panels 40 and the roller carrier element 62 in the closing position of the movable panels 40, when the opening hood is partially open.

[0105] Figures 8, 9 and 10 show that, regardless of the position of the cam 60 around the first Y axis, of the roller carrier element 62 around the second Z axis and of the opening hood 50, the cam 60 and the roller carrier element 62 extend in the same plane corresponding to the first orthogonal plane, and the coupling system 58 according to the invention allows their connection.

[0106] Such a mechanical coupling system 58 allows the transmission of a rotational force without human intervention between a fixed part and a moving part, in particular between the cam 60 and the roller carrier element 62, in two opposite directions each corresponding to the opening or closing of the movable panels 40.

[0107] Such a coupling system 58 also allows adaptation to possible misalignments.

[0108] When the hinged cover 50 closes, the cam 60 comes into contact with the roller carrier element 62, and the cam 60 and the roller carrier element 62 then roll against each other to reach a connection position, with the forces exerted by each of these two elements. This configuration allows the cam 60 and the roller carrier element 62 to align during the closing kinematics of the hinged cover 50.

[0109] Thanks to the convex shape of the first and second rollers 64 and 68, the coupling system 58 compensates for deformations and positioning tolerances of the cam 60 and the roller carrier element 62 while maintaining the functionality of the coupling system 58. Figure 11 is a cross-sectional view of the coupling system 58 along the first plane orthogonal to the first Y-axis, with the opening cover 50 in the closed position and the cam 60 and the roller carrier element 62 coupled.

[0110] As illustrated in Figures 10 and 11, the coupling system 58 preferably includes a play absorption device 84, positioned between the cam 60 and the first and second rollers 64, 68 of the roller carrier element 62, in particular play between the first and second rollers.

[0111] The tolerance play absorption device 84, such as a spring blade, is installed in the contact areas between the cam 60 and the roller carrier element 62.

[0112] In order to prevent the first and second rollers 64, 68 from moving and wearing out over time, the spring blade is positioned to apply a preload to them.

[0113] In the illustrated example, the spring blade is positioned on the cam 60. The spring blade extends around the cam 60, in the first plane orthogonal to the first Y axis.

[0114] The spring blade comprises a first face 86 positioned opposite the cam 60 and a second face 88 opposite it. In addition, the spring blade comprises a first end 84a and a second end 84b opposite each other.

[0115] In a disconnected position between the cam 60 and the roller-carrying element 62, the first face 86 of the first end 84a of the spring blade extends opposite the first concave portion 60b of the cam 60 without contact between the latter two, and the first face 86 of the second end 84b of the spring blade extends opposite the second concave portion 60c of the cam 60 without contact between the latter two.

[0116] In the connection position of the cam 60 and the roller carrier element 62, the second face 88 of the first end 84a of the leaf spring bears against the first roller 64, and the second face 88 of the second end 84b of the leaf spring bears against the second roller 68. In the example illustrated in Figure 11, the second face 88 of the first end 84a bears against the first roller 64, and the first face 86 of the first end 84a bears against the first concave portion 60b of the cam 60. The first end 84a of the leaf spring is compressed and abuts the cam 60, so that a force is transmitted between the cam 60 and the roller carrier element 62.

[0117] Furthermore, the second face 88 of the second end 84b comes to rest against the second roller 64 and the second face 88 of the first end 84a is moved away from the second concave portion 60c of the cam 60 so that only a preload is transmitted between the cam 60 and the roller-carrying element 62.

[0118] Alternatively, the tolerance play absorption device 84 can be positioned on the roller carrier element 62.

[0119] This 84 tolerance play absorption device also helps to limit vibrations.

[0120] In the described embodiment, the coupling system 58 is positioned on the turbomachine 2 for connecting and disconnecting the opening cowling 50 from the rest of the turbomachine 2 and for moving the movable panel 40 of the discharge duct 38, but this embodiment is in no way limiting. The coupling system 58 according to the invention can be applied to the connection and disconnection of any other structure, without being limited to the field of aeronautics.

Claims

DEMANDS 1. Coupling system for connecting and disconnecting a fixed part (52) and a moving part (50) of at least one structure (2), comprising a cam (60) intended to be positioned on one of the fixed and moving parts and being able to pivot about a first axis (Y) in a first plane orthogonal to the first axis (Y), and a roller-carrying element (62) intended to be positioned on the other of the fixed and moving parts, carrying at least first and second rollers (64, 68) and being able to pivot about a second axis (Z) in said first orthogonal plane, the cam (60) and the roller-carrying element (62) being adapted to bear against each other in a connection position between the fixed part and the moving part in which the first and second axes (Y, Z) coincide.

2. Coupling system according to claim 1, in which the cam (60) has a convex portion (60a) extended on either side by first and second concave portions (60b, 60c), the first concave portion (60b), the convex portion (60a) and the second concave portion (60c) extending in said first orthogonal plane, each of the first and second concave portions (60b, 60c) being intended to cooperate with one of the first and second rollers (64, 68), and the convex portion (60a) being intended to cooperate with the roller-carrying element (62) between the first and second rollers (64, 68) in said connection position between the fixed part and the moving part.

3. Coupling system according to claim 1 or 2, wherein the roller-carrying element (62) is connected to a first end of a shaft (74) extending along said second axis (Z), a second end of the shaft (74) opposite to the first end being connected to a linear actuator (76) via a connecting rod (78), the connecting rod (78) and the linear actuator (76) extending in a second plane orthogonal to said second axis (Z) and parallel to said first orthogonal plane.

4. Coupling system according to any one of the preceding claims, comprising a control device adapted to control the rotation of the roller carrier element (62) around said second axis (Z) in said first orthogonal plane.

5. Coupling system according to any one of the preceding claims, wherein the cam (60) is pivotally fixed on a bearing (70) connecting the cam (60) to the rest of the moving part.

6. Coupling system according to any one of the preceding claims, comprising a device for absorbing tolerance backlash (84) between the first and second rollers (62) and the cam (60), positioned on one of the cam (60) and the roller-carrying element (62), such as a leaf spring.

7. Coupling system according to any one of the preceding claims for moving between an open position and a closed position at least one movable panel (40) of a discharge channel (38) of a third flow channel (36) delimiting a third airflow of a triple-flow turbomachine (2), preferably adapted to allow the passage of the third airflow to an external flow.

8. Aircraft turbomachine comprising at least one discharge channel (38), at least one movable panel (40) capable of being moved between an open position allowing air to flow through the discharge channel (38) and a closed position, and a coupling system (58) according to any one of claims 1 to 7 for moving the movable panel (40) between the open position and the closed position, preferably the cam (60) being positioned on an opening hood (50) of the turbomachine (2).

9. Turbomachine according to claim 8, wherein the coupling system (58) is able to move the movable panel (40) between the open position and the closed position by means of an actuation device (56) connecting the movable panel (40) and the coupling system (58).

10. Aircraft comprising at least one coupling system (58) according to any one of claims 1 to 7 and / or at least one turbomachine (2) as defined in claim 8 or 9.

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