A turbofan engine having a set of rotating blades for sealing a bypass flow duct

Abstract

The invention relates to a turbofan engine with a nacelle having a sliding element movable between an advanced position and a retracted position to open a window between the duct and the outside, vanes each rotatable between a stowed position and a deployed position, and a handling system (500) moving each vane, a transmission rotating the vanes one after the other, a drive system (510) converting the translation movement of the sliding element into the rotation movement of the first vane and having a ball screw system (511), a planetary gear train (514), and an arm and lever assembly. The use of rotatable vanes and a simplified handling system on the sliding element can allow a lightweight assembly compared to the use of a reverse door of the prior art.

Description

Technical Field

[0001] The present invention relates to a turbofan engine having a set of blades mounted to rotate to block a duct for bypass flow, and the present invention relates to an aircraft having at least one such turbofan engine. Background Technology

[0002] The aircraft has a fuselage with wings fixed to both sides. At least one turbofan engine is mounted under each wing. Each turbofan engine is secured to the underside of the wing by a pylon, which is secured between the wing structure and the turbofan engine structure.

[0003] A turbofan engine has a motor and a nacelle secured around the motor. The turbofan engine also has a bypass duct between the nacelle and the motor, through which bypass flow circulates.

[0004] The engine nacelle has multiple reversible doors, each of which can rotate between a retracted position and an extended position on the engine nacelle structure. In the retracted position, the reversible door is outside the bypass duct. In the extended position, the reversible door is positioned across the bypass duct to redirect the bypass flow to a window that is in the wall of the nacelle and is open between the bypass duct and the outside of the nacelle.

[0005] Therefore, the bypass flow is redirected outward, more specifically, towards the front of the turbine engine, thus generating reverse thrust. Furthermore, each reverse valve uses a linkage that, in its retracted position, crosses the bypass duct, thus partially obstructing it.

[0006] While the reverse door is perfectly satisfactory, it would be desirable to find a different mechanism, especially one that is lighter and does not obstruct the bypass flow in the retracted position. Summary of the Invention

[0007] One object of the present invention is to provide a turbofan engine having a group of blades mounted to rotate to block a bypass duct.

[0008] To this end, a turbofan engine is proposed, having a longitudinal axis and a motor and a nacelle surrounding the motor and having a fan housing, wherein a duct for bypass flow is defined between the nacelle and the motor, and wherein airflow circulates in the flow direction, the nacelle having:

[0009] - A mounting structure that secures the fan to the housing;

[0010] - A motion assembly having a motion fairing and a slider, the motion fairing being fastened to the slider, the slider being translatable in a translational direction on a fixed structure between an advancing position and a retracted position, in the advancing position the slider being positioned such that the motion fairing is close to the fan housing, and in the retracted position the slider being positioned such that the motion fairing is away from the fan housing, thereby defining an open window between the duct and the outside of the nacelle between the two positions;

[0011] - Multiple blades, including a blade referred to as a first blade, each blade having a first end mounted to be rotatable about a first axis of rotation on a slider, wherein the blades are angled about a longitudinal axis from one to the next, wherein each blade is movable between a retracted position and an extended position, in which the blade is outside the pipe and in which the blade is across the pipe in the extended position.

[0012] - A group of actuators that move a slider between a forward position and a retracted position, and vice versa; and

[0013] - A control system that, when the slider moves from the forward position to the retracted position, moves each blade from the retracted position to the extended position, and vice versa. The control system has the following characteristics:

[0014] - For each blade, a main shaft is mounted so as to be able to rotate about a first axis of rotation on a sliding member, and the blade is fastened to the main shaft by its first end;

[0015] - For each pair of adjacent blades, a transmission mechanism that transmits the rotation of one blade in the pair to the other blade in the same pair.

[0016] - A drive system that converts the translational motion of the slider into the rotational motion of the first blade, and has the following characteristics:

[0017] - A ball screw system having a slotted rod and a ball nut, the slotted rod being connected to a sliding member via a pivoting connection, the screw axis being approximately parallel to the translation direction, and the ball nut being fastened to a fixed structure, wherein the ball nut cooperates with the slotted rod to establish a helical connection.

[0018] - A planetary gear system comprising a sun gear, a ring gear, a planet carrier, and multiple planet gears, wherein the sun gear is integrally formed with the end of a slotted rod, the ring gear is fixedly mounted on a sliding member, the planet carrier is mounted to be able to rotate on the sliding member, and the planet gears are mounted to be able to rotate freely on the planet carrier, wherein the planet gears are distributed around the sun gear and mesh with the sun gear, and wherein the ring gear surrounds the planet gears and meshes with them;

[0019] - An arm that is integrated with the planetary carrier and offset relative to the lead screw axis;

[0020] - A second transmission handle, which is integral with the main shaft of the first blade;

[0021] - A cylindrical component, which is mounted to be able to rotate on a sliding component about a second rotation axis that is generally parallel to the direction of translation, wherein the cylindrical component carries a first tilting arm and a second tilting arm;

[0022] - A first handle, wherein a first end of the first handle is hinged to an arm, and a second end of the first handle is hinged to a first tilting arm, wherein the hinge of the first handle on the arm is a rotation in which the axis of rotation is parallel to and offset relative to the axis of rotation of the lead screw, and wherein the hinge of the first handle on the first tilting arm is a rotation in which the axis of rotation is parallel to and offset relative to the second axis of rotation of the cylinder.

[0023] - A second handle, wherein a first end of the second handle is hingedly mounted on a second transmission handle, and a second end of the second handle is hingedly mounted on a second tilting arm, wherein the hinge of the second handle on the second transmission handle is a rotation in which the axis of rotation is parallel to and offset relative to a first axis of rotation, and wherein the hinge of the second handle on the second tilting arm is a rotation in which the axis of rotation is parallel to and offset relative to a second axis of rotation of the cylinder.

[0024] This turbine engine allows for weight reduction by replacing the reverse door and its drive mechanism with lighter pivot blades that have a simplified control system.

[0025] Advantageously, the dimensions of the second drive lever, the second lever, and the second tilting arm are designed such that when the slider is in the forward position and the blade is in the retracted position, the second axis of rotation, the axis of rotation of the hinge between the second lever and the second tilting arm, and the axis of rotation of the hinge between the second lever and the second drive lever are coplanar, and the axis of rotation of the hinge between the second lever and the second tilting arm is located between the other two axes of rotation.

[0026] Advantageously, the dimensions of the arm, the first handle, and the first tilting arm are designed such that when the slider is in the retracted position and the blade is in the extended position, the axis of rotation of the screw axis, the axis of rotation of the hinge between the arm and the first handle, and the axis of rotation of the hinge between the first handle and the first tilting arm are coplanar, and the axis of rotation of the hinge between the arm and the first handle is between the other two axes of rotation.

[0027] Advantageously, for each main shaft of the pair of adjacent blades, the transmission has a first transmission handle integral with the main shaft, and the transmission also has a connecting rod, each end of which is hinged to one of the two first transmission handles.

[0028] Advantageously, the slotted rod is fastened to the sun gear via a universal joint.

[0029] The present invention also proposes an aircraft having at least one turbofan engine according to one of the above-described variations. Attached Figure Description

[0030] The above and other features of the invention will become clearer from the following description of an exemplary embodiment, which is given with reference to the accompanying drawings, in which:

[0031] Figure 1 It is a side view of an aircraft having a turbofan engine according to the present invention;

[0032] Figure 2 This is a perspective view of the turbofan engine according to the invention in the forward and retracted positions;

[0033] Figure 3 This is a perspective view of a turbofan engine according to the invention in its retracted and extended positions;

[0034] Figure 4 This is a schematic diagram of a turbofan engine according to the present invention, viewed in cross-section along a vertical plane;

[0035] Figure 5 This is a cross-sectional view of the operating system according to the present invention; and

[0036] Figure 6 This is a perspective view of the control system according to the present invention. Detailed Implementation

[0037] In the following description, position-related terms are relative to the direction of airflow in the turbine engine, and are therefore considered from the front to the rear of the aircraft.

[0038] Figure 1 An aircraft 10 with a fuselage 12 is shown, with wings 14 mounted on each side of the fuselage to support at least one turbofan engine 100 according to the invention. The turbofan engine 100 is secured to the underside of the wing 14 by means of pylons 16.

[0039] Figure 2 and Figure 3 A turbofan engine 100 is shown, having a nacelle 102 and a motor 20 housed within the nacelle 102. The turbofan engine has a fan housing 202. The motor 20 is indicated by its exhaust portion at the rear.

[0040] In the following description, and by convention, X denotes the longitudinal axis of the turbofan engine 100, which is parallel to the longitudinal axis of the aircraft 10 and oriented positively toward the front of the aircraft 10; Y denotes the transverse axis, which is horizontal when the aircraft is on the ground; and Z denotes the vertical axis; these three directions X, Y and Z are orthogonal to each other.

[0041] Figure 2 and Figure 3 The turbofan engine 100 is shown in two different operating positions. Figure 4 A cross-sectional schematic diagram of a turbofan engine 100 is shown.

[0042] The turbofan engine 100 has a duct 204 between the nacelle 102 and the motor 20, through which a bypass flow 208 from the air intake circulates through the fan 300 and thus flows in a flow direction from front to rear.

[0043] The nacelle 102 has a fixing structure 206 that is fixedly mounted on the fan housing 202. Specifically, in this case, the fixing structure 206 consists of a front frame 210 and an outer panel 212, the front frame 210 being mounted around the fan housing 202, and the outer panel 212 forming an aerodynamic surface. Figure 3 It is shown as transparent in the middle, and Figure 2 and Figure 3 In the middle, a portion of the outer panel 212 was removed.

[0044] Nacelle 102 has a motion assembly 214, which has a motion fairing 216 (in Figure 3 (It is also transparent in the middle), in Figure 2 and Figure 3 In this process, a portion of the moving fairing is removed, and the moving components form the outer wall of the nozzle.

[0045] The nacelle 102 also has a slider 218. In this case, the slider 218 is in the form of a cylinder with openwork walls. The moving cowling 216 is fastened to the slider 218 downstream of the slider 218 relative to the airflow direction in the turbofan engine 100.

[0046] The sliding member 218 is installed so that it can move along a translational direction that is generally parallel to the longitudinal axis X on the fixed structure 206 of the nacelle 102.

[0047] Slider 218 can be in the forward position ( Figure 2 ) to the retracted position ( Figure 3The movement occurs between the outer panel 212 and the fan housing 202, and vice versa. In the forward position, the slider 218 is positioned as far forward as possible relative to the flow direction, so that the motion fairing 216 is close to the outer panel 212 and the fan housing 202, thus forming an aerodynamic surface. In the retracted position, the slider 218 is positioned as far back as possible relative to the flow direction, so that the motion fairing 216 is away from the outer panel 212 and the fan housing 202, thereby defining a window 220 between the outer panel and the fan housing.

[0048] In the forward position, the motion fairing 216 and the outer panel 212 extend to each other to define the outer surface of the nacelle 102, and the motion fairing 216 and the fan housing 202 extend to each other to define the outer surface of the duct 204.

[0049] In the retracted position, the motion cowl 216, fan housing 202, and outer panel 212 are spaced apart from each other, and a window 220 is defined between these three, opening between the duct 204 and the exterior of the nacelle 102. That is, air from the bypass flow 208 passes through the window 220 to terminate outside the turbofan engine 100.

[0050] Guide the translation of the slider 218 by any appropriate means, such as the track between the fixed structure 206 and the slider 218.

[0051] The nacelle 102 also has a group of actuators 221 that cause the slider 218 to translate between the forward position and the retracted position, and vice versa. Each actuator 221 is controlled by a control unit, such as a processor type, which controls the displacement in one direction or another according to the needs of the aircraft 10.

[0052] For example, each actuator 221 can be in the form of a double-acting jack (two working directions), with the cylinder of the double-acting jack fastened to the fixed structure 206, especially in this case, fastened to the front frame 210, and the rod fastened to the slider 218.

[0053] To orient the air leaving window 220, the cascade (layers) can be fastened to the slider 218 facing window 220.

[0054] The fan housing 202 and the outer panel 212 form the upstream boundary of the window 220 relative to the flow direction, and the motion shroud 216 forms the downstream boundary of the window 220 relative to the flow direction.

[0055] exist Figure 3 In the embodiment of the invention shown, the slider 218 has a U-shaped profile 219, which is coaxial with the longitudinal axis X and opens toward the longitudinal axis X.

[0056] The nacelle 102 has multiple blades 250, which are moved by a control system.

[0057] Figure 5 and Figure 6 The control system 500 is shown.

[0058] Each blade 250 is mounted on a slider 218, in this case on a U-shaped profile 219, and rotates about a first axis of rotation 504 that is generally parallel to the direction of translation. Therefore, each blade 250 is capable of rotating in a retracted position. Figure 2 ) and unfolding position ( Figure 3 The blades move between the duct 204 and the window 220 to redirect the bypass flow 208. In the retracted position, the blades 250 are outside the duct 204, and in the extended position, the blades 250 span the duct 204.

[0059] Each blade 250 is mounted so that when the blade 250 is deployed, the first end moves and the second end moves toward the motor 20 to best seal the pipe 204.

[0060] The blade 250 shifts angularly from one direction to the next around the longitudinal axis X.

[0061] The number of blades 250 and the shape of each blade depend on the size of the turbofan engine 100 and the width of each blade 250, such that in the deployed position, the blades 250 block most of the duct 204.

[0062] By rotating the blades 250 toward the inside of the turbine engine 100, the movement from the retracted position to the deployed position is achieved.

[0063] When the slider 218 is in the forward position, it is in the retracted position; when the slider 218 is in the retracted position, it is in the extended position.

[0064] When the slider 218 moves from the forward position to the retracted position, the control system 500 moves each blade 250 from the retracted position to the extended position, and vice versa.

[0065] Therefore, the operation involves starting from the forward / retracted position, commanding the actuator 221 to move the slider 218 from the forward position to the retracted position. During this movement, the control system 500 moves the blade 250 from the retracted position to the deployed position.

[0066] Therefore, the operation involves starting from the retracted / extended position, commanding the actuator to activate it to move the slider 218 from the retracted position to the forward position. During this movement, the control system 500 moves the blade 250 from the extended position to the folded position.

[0067] Compared to reverse doors using existing technology, using blades 250 that are mounted to rotate on the slider 218 allows for a lighter component.

[0068] For each blade 250, the actuation system 500 has a main shaft 502 mounted to be rotatable about a first axis of rotation 504 on a slider 218, with the blade 250 secured to the main shaft at its first end. Rotation about the first axis of rotation 504 allows movement from an deployed position to a retracted position, and vice versa. In this configuration, each main shaft 502 is mounted to be rotatable on the slider 218, particularly on the U-shaped profile 219.

[0069] The control system 500 enables the rotation of multiple adjacent blades 250. For this purpose, each spindle 502 has a first drive lever 506, which is downstream of a blade 250. In this case, the first drive lever 506 is in the form of a chuck. For two first drive levers 506, the control system 500 has a connecting rod 508, each end of which is hinged to one of the two first drive levers 506. In this case, the hinge (pivot) of the lever 508 on the first drive lever 506 is a rotation whose axis of rotation is parallel and offset relative to a first axis of rotation 504. This arrangement allows the other blades 250 to rotate one after another in the same direction simultaneously while one blade 250 rotates.

[0070] The first transmission lever 506 and the connecting rod 508 form a transmission device that, for each pair of adjacent blades 250, transmits the rotation of one blade 250 in the pair to the other blade 250 in the same pair. Thus, by rotating the first blade 250, the associated other blades 250 also move. Therefore, for each spindle 502 of a pair of adjacent blades 250, the transmission device has a first transmission lever 506 integral with the spindle 502, and the transmission device also has a connecting rod 508, each end of which is hinged to one of the two first transmission levers 506.

[0071] To manipulate the first blade 250, the manipulation system 500 has a drive system 510 that converts the translational motion of the slider 218 into the rotational motion of the first blade 250. With the aid of a transmission mechanism, the rotational motion of the first blade 250 drives the other blades 250 to move one after another.

[0072] The drive system 510 has a ball screw system 511 with a slotted rod 512 and a ball nut. The screw axis 513 of the slotted rod is generally parallel to the translational direction. The ball nut is fastened to a fixed structure 206, in this case, specifically to the front frame 210, wherein the ball nut engages with the slotted rod 512 to establish a helical connection. The slotted rod 512 is also integral with the slider 218, and therefore translates with the slider. In other words, the slotted rod 512 is connected to the slider 218 via a pivot connection to translate with the slider 218, while being able to rotate freely relative to the slider 218. Therefore, when the slider 218 translates, the slotted rod 512 rotates due to the interaction between the stationary ball nut and the slotted rod 512.

[0073] In the embodiments of the invention presented herein, the lead screw axis 513 of the slotted rod 512 is aligned with the first rotation axis 504.

[0074] The drive system 510 has a planetary gear train 514, which includes a sun gear 516, a ring gear 518, a planetary carrier 520, and multiple planetary gears 522. The sun gear 516 is integral with the end of the slotted rod 512. The ring gear 518 is fixedly mounted on a slider 218, particularly on a U-shaped profile 219. The planetary carrier 520 is mounted to rotate on the slider 218, particularly on the U-shaped profile 219. The planetary gears 522 are mounted to rotate freely on the planetary carrier 520. The planetary gears 522 are distributed around and mesh with the sun gear 516, and the ring gear 518 surrounds and meshes with the planetary gears 522. The axes of the components constituting the planetary gear train 514 are generally parallel to the direction of translation.

[0075] The drive system 510 also has an arm 524, which is integrated with the planetary gear carrier 520 and offset relative to the lead screw axis 513.

[0076] The main shaft 502 of the first blade 250 has a second drive lever 526 integral with the main shaft 502, in which case the second drive lever is upstream of the blade 250.

[0077] The drive system 510 also has a cylinder 528, which is mounted to be able to rotate on the slider 218, in particular on the U-shaped profile 219, about a second rotation axis 530 that is generally parallel to the direction of translation.

[0078] The cylinder 528 carries the first tilting arm 532 and the second tilting arm 534, wherein in the embodiments of the invention presented herein, each tilting arm 532, 534 is in the form of a clamp.

[0079] The drive system 510 also has a first lever 536 and a second lever 538.

[0080] The first end of the first handle 536 is hingedly mounted on the arm 524, and the second end of the first handle 536 is hingedly mounted on the first tilting arm 532.

[0081] The hinge of the first lever 536 on arm 524 is a rotation whose axis of rotation is parallel to and offset relative to the lead screw axis 513. The hinge of the first lever 536 on the first tilting arm 532 is a rotation whose axis of rotation is parallel to and offset relative to the second axis of rotation 530 of the cylinder 528.

[0082] The first end of the second handle 538 is hingedly mounted on the second transmission handle 526, and the second end of the second handle 538 is hingedly mounted on the second tilting arm 534.

[0083] The hinge of the second handle 538 on the second transmission handle 526 is a rotation whose axis of rotation is parallel to and offset from the first axis of rotation 504. The hinge of the second handle 538 on the second tilting arm 534 is a rotation whose axis of rotation is parallel to and offset from the second axis of rotation 530 of the cylinder 528.

[0084] Therefore, during the translational movement of the slider 218, the slotted rod 512 translates and rotates about the lead screw axis 513. The rotation of the slotted rod 512 drives the set rotation of the planetary gear train 514, thereby driving the set rotation of the planetary gear carrier 520 and the arm 524. The movement of the arm 524 drives the tilting of the cylinder 528 through the action of the first lever 536 on the first tilting arm 532. The tilting of the cylinder 528 drives the movement of the second tilting arm 534, thereby driving the movement of the second transmission arm 526 through the action of the second lever 538. The movement of the second transmission arm 526 drives the rotation of the main shaft 502, thereby driving the rotation of the first blade 250, and subsequently driving the rotation of the other blades 250.

[0085] Therefore, the control system 500 is particularly lightweight and easy to implement.

[0086] To avoid potential misalignment during the movement of the slider 218, the slotted rod 512 is fastened to the sun gear 516 via a universal joint 540.

[0087] The dimensions of the second drive lever 526, the second lever 538, and the second tilting arm 534 are designed such that when the slider 218 is in the forward position and the blade 250 is in the retracted position, the second rotation axis 530, the axis of rotation of the hinge between the second lever 538 and the second tilting arm 534, and the axis of rotation of the hinge between the second lever 538 and the second drive lever 526 are coplanar, and the axis of rotation of the hinge between the second lever 538 and the second tilting arm 534 is located between the other two axes of rotation. This arrangement allows the axes of rotation to be aligned in the forward / retracted positions, thereby reaching the maximum blocking position.

[0088] The dimensions of arm 524, first handle 536, and first tilting arm 532 are designed such that when the slider 218 is in the retracted position and the blade 250 is in the extended position, the rotation axes of the screw axis 513, the hinge between arm 524 and first handle 536, and the hinge between first handle 536 and first tilting arm 532 are coplanar, and the rotation axis of the hinge between arm 524 and first handle 536 lies between the other two rotation axes. This arrangement allows the rotation axes to be aligned in the retracted / extended positions, thereby reaching the maximum blocking position.

[0089] Blade 250, especially the first blade 250, can be removed for maintenance purposes and can therefore be replaced if necessary.

[0090] The housing may be arranged around a portion of the drive system 510, particularly around the planetary gear train 514, arm 524, second transmission lever 526, cylinder 528, first lever 536, and second lever 538. In other words, the drive system 510 may be arranged within the housing. This advantageously allows for the prevention of contamination of the drive system 510 (e.g., due to dust) and allows for the placement of lubrication devices for the drive system 510 within the housing.

[0091] The present invention has been described in more detail for nacelles located under the wings, but the present invention can also be applied to nacelles located at the rear of the fuselage.

Claims

1. A turbofan engine (100) having a longitudinal axis (X) and having a motor (20) and a nacelle (102) surrounding the motor (20) and having a fan housing (202), wherein, A duct (204) for bypass flow (208) is defined between the nacelle (102) and the motor (20), wherein airflow circulates in the flow direction, and the nacelle (102) has: - A fixing structure (206) is fastened to the fan housing (202); - A motion assembly (214) having a motion fairing (216) and a slider (218) fastened to the slider (218), the slider (218) being translatable in a translational direction on the fixed structure (206) between a forward position and a retracted position, wherein in the forward position the slider (218) is positioned such that the motion fairing (216) is close to the fan housing (202), and in the retracted position the slider (218) is positioned such that the motion fairing (216) is away from the fan housing (202), thereby defining an open window (220) between the motion fairing (216) and the fan housing (202) between the duct (204) and the outside of the nacelle (102); - A plurality of blades (250), including a blade (250) referred to as a first blade (250), each blade having a first end mounted to be rotatable on the slider (218) about a first axis of rotation (504), wherein the blade (250) is angled from one to the next about the longitudinal axis (X), wherein each blade (250) is movable between a retracted position and an extended position, wherein in the retracted position the blade (250) is outside the pipe (204), and in the extended position the blade (250) is across the pipe (204); - A group of actuators (221) that move the slider (218) between the forward position and the retracted position, and vice versa; and - An operating system (500) that, when the slider (218) moves from the forward position to the retracted position, causes each blade (250) to move from the retracted position to the deployed position and vice versa, wherein the operating system (500) has: - A spindle (502) for each blade (250) is mounted to be rotatable about the first axis of rotation (504) on the slider (218), and the blade (250) is fastened to the spindle (502) by a first end of the blade; - For each pair of adjacent blades (250), the transmission device transmits the rotation of one blade (250) in the pair to the other blade (250) in the same pair. - A drive system (510) that converts the translational motion of the slider (218) into the rotational motion of the first blade (250), and has the following features: - A ball screw system (511) having a slotted rod (512) and a ball nut, the slotted rod being connected to the slider (218) via a pivot connection, the screw axis (513) of the slotted rod being approximately parallel to the translation direction, and the ball nut being fastened to the fixed structure (206), wherein the ball nut and the slotted rod (512) are fitted together to establish a helical connection; - A planetary gear system (514) having a sun gear (516), a ring gear (518), a planet carrier (520), and a plurality of planet gears (522). The sun gear is integral with the end of the slotted rod (512). The ring gear is fixedly mounted on the slider (218). The planet carrier is mounted to be rotatable on the slider (218). The plurality of planet gears are mounted to be rotatable on the planet carrier (520). The planet gears (522) are distributed around the sun gear (516) and mesh with the sun gear (516). The ring gear (518) surrounds the planet gears (522) and meshes with them. - Arm (524), which is integral with the planet carrier (520) and offset relative to the lead screw axis (513); - A second transmission handle (526), ​​which is integral with the main shaft (502) of the first blade (250); - A cylindrical member (528) is mounted to be able to rotate on the slider (218) about a second rotation axis (530) that is generally parallel to the translation direction, wherein the cylindrical member (528) carries a first tilting arm (532) and a second tilting arm (534); - A first handle (536), wherein a first end of the first handle (536) is hinged to the arm (524), and a second end of the first handle (536) is hinged to the first tilting arm (532), wherein the hinge of the first handle (536) on the arm (524) is a rotation with the axis of rotation parallel to and offset relative to the lead screw axis (513), and wherein the hinge of the first handle (536) on the first tilting arm (532) is a rotation with the axis of rotation parallel to and offset relative to the second axis of rotation (530) of the cylinder (528); - A second handle (538), wherein a first end of the second handle (538) is hingedly mounted on a second transmission handle (526), ​​and a second end of the second handle (538) is hingedly mounted on a second tilting arm (534), wherein the hinge of the second handle (538) on the second transmission handle (526) is a rotation whose axis of rotation is parallel to and offset relative to the first axis of rotation (504), and wherein the hinge of the second handle (538) on the second tilting arm (534) is a rotation whose axis of rotation is parallel to and offset relative to the second axis of rotation (530) of the cylinder (528).

2. The turbofan engine (100) according to claim 1, characterized in that, The dimensions of the second drive lever (526), ​​the second lever (538), and the second tilting arm (534) are designed such that when the slider (218) is in the forward position and the blade (250) is in the retracted position, the second rotation axis (530), the axis of rotation of the hinge between the second lever (538) and the second tilting arm (534), and the axis of rotation of the hinge between the second lever (538) and the second drive lever (526) are coplanar, and the axis of rotation of the hinge between the second lever (538) and the second tilting arm (534) is located between the other two rotation axes.

3. The turbofan engine (100) according to claim 1, characterized in that, The dimensions of the arm (524), the first handle (536), and the first tilting arm (532) are designed such that when the slider (218) is in the retracted position and the blade (250) is in the extended position, the axis of rotation of the lead screw (513), the axis of rotation of the hinge between the arm (524) and the first handle (536), and the axis of rotation of the hinge between the first handle (536) and the first tilting arm (532) are coplanar, and the axis of rotation of the hinge between the arm (524) and the first handle (536) is between the other two axes of rotation.

4. The turbofan engine (100) according to claim 1, characterized in that, For each main shaft (502) of the pair of adjacent blades (250), the transmission device has a first transmission handle (506) and a connecting rod (508), the first transmission handle being integral with the main shaft (502), and each end of the connecting rod being hinged to one of the two first transmission handles (506).

5. The turbofan engine (100) according to claim 1, characterized in that, The slotted rod (512) is fastened to the sun gear (516) via a universal joint (540).

6. An aircraft (10) having at least one turbofan engine (100) according to claim 1.

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