TURBOMACHINE STATOR BLADE CONTROL MECHANISM WITH A REINFORCEMENT ELEMENT

Abstract

The invention relates to a variable-pitch stator blade control mechanism for a turbomachine, comprising a control ring adapted to be rotated and control levers connecting each stator blade to the control ring such that the rotation of the control ring causes the stator blades to pivot. Each control lever is pivotally mounted on the control ring and comprises a body (21) elongated between a first portion (22) and a second portion (23), the body comprising a central portion (24) connecting the first and second portions. According to the invention, each control lever includes a reinforcing element (40) configured to increase the mechanical strength of the control lever. The reinforcing element comprises a wall (41) inclined relative to the wall of the second portion, forming the central portion, and oriented outwards at an angle of inclination. (See Fig. 4 for abbreviations.)

Description

Title of the invention: TURBOMACHINE STATOR BLADE CONTROL MECHANISM WITH A REINFORCEMENT ELEMENT Technical field of the invention

[0001] The present invention relates to the field of turbomachinery comprising variable-pitch stator blades. It relates in particular to a control mechanism for variable-pitch stator blades. Technological background

[0002] Aircraft turbomachinery can be equipped with variable-pitch stator vanes that allow the turbomachinery to adapt to various operating conditions. These stator vanes can be located at different points within the turbomachine and are known, for example, as "OGV" for Outlet Guide Vane or "VSV" for Variable Stator Vanes. These stator vanes are arranged radially across the turbomachine's airflow and allow it to be straightened.

[0003] To this end, the turbomachine is equipped with a control mechanism comprising a control ring driven in rotation about the longitudinal axis of the turbomachine and driving the pivoting of the variable-pitch stator blades via control levers. The control levers are connected to the variable-pitch stator blades and to the control ring.

[0004] In the case of variable-pitch stator blades equipping an air inlet guide wheel, which is located upstream of the low-pressure compressor, the control mechanism includes a fusible part positioned between the control ring and a control means acting on the rotation of the control ring. The fusible part is configured to break under high mechanical stresses applied to the variable-pitch blades in order to prevent damage to the control means. The mechanical stresses affect all parts of the control mechanism and are caused, for example, by pumping (violent backflow of air upstream of the turbomachine) or by impacts / ingests of a foreign body known by the acronym "FOD" for "Foreign Object Debris". Such an example of a control mechanism is described in document FR-A1-2794801.

[0005] However, the fusible part may not break under lesser mechanical stress, and this can lead to damage to other parts of the control mechanism. The parts of the mechanism most affected are generally the control levers, which can break, deform, and / or disengage from the control ring.

[0006] Damage to the control levers can lead to misalignment of the variable-pitch stator blades, resulting in a loss of turbomachinery performance and collisions between adjacent variable-pitch stator blades, which can then lead to blade breakage. The breakage of these stator blades can release fragments known as "DOD" (Domestic Object Debris), which can damage nearby components such as a crankcase arm, moving blades, etc.

[0007] There is therefore a need to resolve all or part of the aforementioned drawbacks. Summary of the invention

[0008] The objective of the present invention is to provide a simple and economical solution to reliably ensure the operation of the variable pitch stator blade control mechanism in the event of high mechanical stresses.

[0009] We achieve this objective in accordance with the invention by means of a variable-pitch stator blade control mechanism for a turbomachine, this control mechanism comprising a control ring adapted to be driven in rotation about a longitudinal axis and control levers connecting each variable-pitch stator blade to the control ring such that the rotation of the control ring causes each variable-pitch stator blade to pivot, each control lever being pivotally mounted on the control ring by means of a connecting member and comprising a body elongated along an elongation direction between a first portion and a second portion, the body comprising a central portion connecting the first portion and the second portion, each control lever comprising at least one reinforcing element configured to increase the mechanical strength of the control lever,the reinforcing element comprising a wall which is inclined at least with respect to the wall of the second portion and which forms the central portion, the inclined wall being oriented outwards at an angle of inclination whose apex is defined in a plane separating the central portion and the second portion.

[0010] Thus, this solution makes it possible to achieve the aforementioned objective. In particular, the reinforcing element makes it possible to obtain mechanically strengthened and more robust control levers in the event of high mechanical stresses applied to the stator blades. In this description, the expression "high mechanical stresses" refers to a pumping phenomenon that exerts an aerodynamic force on the variable-pitch stator blades due to violent backflows of air and / or the ingestion of foreign bodies that cause impacts on the stator blades. The reinforced mechanical resistance of the control levers This will at least limit their flexing under high mechanical stress, their damage, and their disengagement from the control ring. The reliability of the control mechanism is considerably improved, which makes it possible, on the one hand, to ensure the control of the stator blades under all circumstances (the other parts of the control mechanism are not affected), and on the other hand, to maintain the aerodynamic performance of the turbomachine.

[0011] In addition, the stiffening applied to the control levers limits the increase in mass and does not involve significant structural modifications to themselves or even to the surrounding parts.

[0012] The control mechanism also includes one or more of the following features and / or steps, taken alone or in combination: - the control mechanism includes a control means causing the rotation of the control ring via at least one fusible transmission piece connecting the control ring to the control means. - Each control lever is made of titanium, titanium alloy, steel or an organic matrix composite material. - the second portion of each control lever includes an opening receiving at least part of the connecting member. - the angle of inclination is strictly greater than 180°C. - the angle of inclination is less than 230°. - the inclined wall is also inclined relative to the wall of the first section. - the inclined wall has an upstream end delimited by an extreme point which is arranged radially outside a portion of the external surface of the first portion. - the connecting element is permanently fixed at the level of the second portion. - the connecting element is mounted using a ball joint at the level of the second portion. - - the inclined wall is solid. - - the inclined wall has a thickness approximately equal to the thickness of the second portion.

[0013] The invention also relates to a turbomachine comprising variable-pitch stator blades for straightening an airflow circulating in the turbomachine and a stator blade control mechanism having any one of the preceding characteristics.

[0014] According to an advantageous feature of the turbomachine, it comprises at least one stage formed of an annular row of moving blades and an annular row of stator blades, the stator blades being arranged upstream or downstream of the moving blades.

[0015] According to another advantageous feature, the turbomachine comprises, from upstream to downstream along the longitudinal axis, a low-pressure compressor, a high-pressure compressor, a high-pressure turbine and a low-pressure turbine, at least one of the low-pressure compressor, high-pressure compressor, high-pressure turbine, and low-pressure turbine comprising one or more stages. Brief description of the figures

[0016] The invention will be better understood, and other objects, details, features and advantages thereof will become more apparent upon reading the following detailed explanatory description, of embodiments of the invention given by way of purely illustrative and non-limiting examples, with reference to the accompanying schematic drawings in which:

[0017] - Fig. 1 is a perspective view of an example of a turbomachine to which the invention applies;

[0018] - Figure 2 is a partial view of a turbomachine module comprising a control mechanism for a row of stator blades with variable pitch according to the invention;

[0019] - Fig. 3 is a detailed and partial view of an example of a stator blade with a timing mechanism. variable connected to a control ring by means of a control lever according to the invention;

[0020] - Figure 4 illustrates, in perspective, one embodiment of a control lever intended to equip a control mechanism according to the invention;

[0021] - The [Fig.5] is a side view of the control lever according to the [Fig.4];

[0022] - Figure 6 is a schematic representation of the forces and the imposed displacement to an example of a control lever according to the invention; and

[0023] - Figure 7 is a partial perspective view of another embodiment of a control lever according to the invention. Detailed description of the invention

[0024] Figure 1 represents a turbomachine 1 having a longitudinal axis X and intended to be mounted on an aircraft (not shown). The turbomachine 1 may be a turboshaft engine, a turbojet engine, a turboprop engine, or may include fan rotor blades or rotor blades of at least one propeller, whether shrouded or unshrouded.

[0025] In the present invention, and generally, the terms "upstream" and "downstream" are defined with respect to the circulation of gases or airflows in the turbomachine and here along the longitudinal axis X. The terms "axial" and "axially" are defined with respect to the longitudinal axis X. The terms "external," "outer," "inner," "internal," and "radial" are defined with respect to a radial axis Z extending from the axis longitudinal X and with regard to the distance from the longitudinal axis X. The radial axis is perpendicular to the longitudinal axis X.

[0026] The turbomachine 1 which is represented in [Fig.1] comprises, from upstream to downstream, a low pressure compressor 2, a high pressure compressor 3, a combustion chamber 4, a high pressure turbine 5 and a low pressure turbine 6. The low pressure compressor 2 and low pressure turbine 6 each comprise rotors which are connected by a low pressure shaft while the high pressure compressor 3 and high pressure turbine 5 comprise rotors which are connected by a high pressure shaft.

[0027] The turbomachine advantageously, but not limited to, rotor blades or movable blades which rotate around the longitudinal axis X and which can equip the rotors of the low pressure compressors 2, high pressure compressor 3, low pressure turbine 6 and high pressure turbine 5.

[0028] The turbomachine 1 advantageously, but not exclusively, includes stator blades or fixed blades which equip, for example, the stators of the low pressure compressor 2, high pressure compressor 3, low pressure turbine 5 and high pressure turbine 6.

[0029] In this description, the term "stator blade" or "fixed blade" refers to a blade that is not driven in rotation about the longitudinal axis X of the turbomachine. In other words, the stator blade is distinct from and unlike a rotor blade or moving blade of the turbomachine.

[0030] Advantageously, the stator blades and rotor blades are generally arranged in annular rows. The annular rows of stator blades are positioned upstream and / or downstream of the annular rows of rotor blades along the longitudinal axis X. An annular row of stator blades and an annular row of rotor blades, for example, form a stage.

[0031] Stator vanes are known as "rectifiers" or by the English acronym "VSV" for "Variable Stator Vane". These allow the flow passing through them to be straightened.

[0032] In the embodiment shown in [Fig. 1], the turbomachine 1 comprises a fan 7 or a propeller including an annular row of rotor blades 8 located upstream of the low-pressure compressor 2 and an annular row of stator blades 9 located downstream of the rotor blades 8. The stator blades 9 are outlet guide vanes, also known as OGVs. Both the rotor blades 8 and the stator blades 9 are shrouded. The stator blades 9 advantageously extend through a secondary flow generated by the fan 7 and, in this example, radially outward from the low-pressure compressor 2, which is traversed by a primary flow also generated by the fan 7.

[0033] In another embodiment shown in Figures 2 and 3, the turbomachine 1 comprises an annular row of stator blades 10 which is arranged, for example, upstream of the low-pressure compressor 2 and at the inlet of the turbomachine 1 at the level of an inlet guide wheel 11. The stator blades 10 are surrounded, for example, by a housing 12 on which they are pivotally mounted about a mounting axis A. The housing 12 is advantageously centered on the longitudinal axis X.

[0034] Advantageously, at least one annular row of the stator blades 9, 10 equipping the turbomachine has variable pitch. That is to say, the blades 9, 10 can pivot about an axis so as to modify their angle of incidence relative to the airflow circulating through the casing. Adjusting the angle of incidence increases or decreases the flow rate and thus the velocity of the airflow.

[0035] For this purpose and as shown in [Fig.2], the turbomachine 1 includes a control mechanism 13 which is configured to change the timing of the stator blades 9, 10 according to the operating mode of the turbomachine.

[0036] The control mechanism 13 includes, for example, a control ring 14 which is driven in displacement such that its displacement causes the variable-pitch stator vanes 9, 10 to pivot. The displacement of the control ring 14 in this example is advantageously a rotation about the longitudinal axis X as well as a translation about this same longitudinal axis X. The control ring 14 is advantageously arranged around the housing 12 and is preferably centered on the longitudinal axis X.

[0037] The control mechanism 13 includes a control means 15 that causes the control ring 14 to move. Advantageously, the control means 15 is an actuator such as a cylinder. The control means 15 includes a movable part 16 that moves relative to a fixed body 17. The latter is fixed, for example, to the housing 12. The movable part 16 moves in translation along the longitudinal axis X.

[0038] Advantageously, but not limitingly, the control means 15 is connected to a fluidic power supply source (not shown) to supply chambers (not shown) which are formed between the fixed body 17 and the moving member 16.

[0039] The control mechanism 13 includes a transmission part that is connected via a pivot joint to the control means 15 and to the control ring 14. Advantageously, the transmission part is fusible. The term "fusible" means that the part can break following an impact and / or high mechanical stress. The fusible part may include areas with a restricted cross-section to facilitate its breakage.

[0040] According to one embodiment, the control mechanism 13 comprises a connecting rod 18 or a turnbuckle having a first end 18a articulated for example on the control ring 14 and a second end 18b articulated for example on a first arm 19a of a right-angle lever 19 connected to the control means 15. The connecting rod 18 may have an adjustable length, that is to say that the length measured between its first end 18a and its second end 18b may vary.

[0041] The right-angle lever 19 includes a second arm 19b pivotally articulated on the moving member 16 (for example, a cylinder rod). The fusible transmission element can be the right-angle lever 19 or the connecting rod 18. The connecting rod 18 and the right-angle lever 19 allow the movement of the moving member 16 of the actuator to be transmitted to the control ring 14.

[0042] The control mechanism 13 further advantageously includes control levers 20 which connect each variable-pitch stator blade 10 to the control ring 14 such that the rotation of the control ring 14 (via the control means) causes the stator blades to pivot about the pitch axis A. Advantageously, but not exclusively, the stator blades 10 pivot simultaneously under the action of the control means 15.

[0043] With reference to [Fig. 3], each stator blade 10 extends radially between a first end 10a and a second end 10b. The first end 10a is pivotally mounted, for example, on the housing 12, and the second end 10b is pivotally mounted, for example, on a radially internal annular ferrule (not shown). Advantageously, the first end 10a passes through an opening 12a through the wall of the housing 12 on both sides and extends radially outwards from the housing 12. The first end 10a and the second end 10b are advantageously each in the form of a pivot.

[0044] Figures 4 and 5 illustrate an embodiment of a control lever 20. The control lever 20 comprises, for example, a body 21 elongated along an elongation direction DA. Each elongated body 21 extends between a first portion 22 and a second portion 23, which are connected by a central portion 24. The elongated body 21 is generally delimited by a peripheral edge 25. The peripheral edge 25 is connected, for example, to a radially external surface 26 and a radially internal surface 27. The radially internal surface 27 and the radially external surface 26 are here opposed along a radial direction DR. In the installed position, the radial direction DR is parallel to the radial axis Z.

[0045] According to the example shown, the first portion 22 is connected to the first end 10a of a variable-pitch stator blade 10. The first portion 22 advantageously comprises an orifice 28 which passes through its wall on both sides and on the other hand along the radial direction DR. The orifice 28 opens in particular onto the radially external surface 26 of the elongated body 21.

[0046] In this embodiment, the body 21 includes a recess 29 (shown in dashed lines in [Fig. 5]) which opens onto the radially internal surface 27. The orifice 28 also advantageously opens into this recess 29. The latter allows at least a portion of the pivot of the first end 10a to be received. The recess 29 has an overall rectangular cross-section. This allows for a plane-to-plane connection between the recess and the pivot of the first end 10a, which permits improved torque transmission. Of course, other shapes are possible. The orifice 28 advantageously has a circular cross-section with an axis B.

[0047] Advantageously, the first end 10a of the stator blade 10 is fixed to the first portion 22 by means of fasteners. These fasteners may be bolts with, for example, a threaded rod passing through the orifice 28 and the recess 29, and screwing into a threaded bore of the first end 10b. Another type of fastener allowing for quick disassembly and assembly is of course conceivable.

[0048] Advantageously, the first portion 22 comprises a first maximum thickness el measured along the radial direction RD. The first thickness el is, for example, between 8 mm and 20 mm. At the level of the first portion 22, a portion of the radially internal surface 27a is defined in a plane (perpendicular to the radial direction) which is offset, for example, from the plane in which a portion of the radially internal surface 27b of the second portion 23 is defined, and possibly from the plane of the central portion 24. The first thickness el is advantageously measured between the portion of the radially internal surface 27a and a portion of the radially external surface 26a at the level of the first portion 22.

[0049] The first portion 22 may have a predetermined length L1 which may be equal to a length L2 of the second portion 23 or to a length L3 of the central portion 24. Alternatively, the lengths L1, L2, and L3 may be different. For example, the length L1 is between 20 mm and 50 mm.

[0050] Advantageously, but not exclusively, the width of the control lever body 20, measured along the transverse direction DT, decreases from the first portion 22 to the second portion 23.

[0051] The second portion 23 comprises a second thickness e2 which is less than the first thickness e1 of the first portion 22. The second thickness e2 may be between 0.8 mm and 4 mm. The second thickness e2 is advantageously measured between the radially internal surface portion 27b and a radially external surface portion 26b at the level of the second portion 23.

[0052] With reference to [Fig. 5] and advantageously, the length L2 of the second portion 23 can be identical to a length L2A of the second portion of a prior art control lever. The length L2A of the second portion of the prior art control lever can be between 10 mm and 40 mm. Alternatively, the length L2 can be between 0.8*L2A and 1.2*L2A. This allows, for example, the arrangement of the surrounding parts to be maintained.

[0053] The second portion 23 is advantageously connected to the control ring 14. For this purpose, the second portion 23 comprises, for example, an orifice 30 (shown in dashed lines in [Fig. 5]) passing through the wall on both sides in the radial direction DR and opening onto both the radially internal surface 27 and the radially external surface 26. The orifice 30 advantageously has a circular cross-section with axis C and a predetermined diameter. A connecting member 31 (shown in Figures 4 and 7) passes, for example, at least partially through the orifice 30 so as to allow connection with the control ring 14.

[0054] The connecting member 31 is advantageously, but not exclusively, permanently fixed to the second portion 23. The connecting member 31 may be a pin which comprises, for example, a head 32 (for example, of circular cross-section) from which extends a straight cylindrical body 33 (having an axis D parallel to the radial axis or radial direction DR). The head 32 advantageously has a diameter D32 greater than that of the cylindrical body D33. The head 32 may be crimped, for example, at the orifice 30. The cylindrical body 33 extends on the side of the radially internal surface 27. In other words, the pin is stationary relative to the control lever 20.

[0055] The control lever 20 is made, for example, of a metallic material. Advantageously, but not exclusively, the metallic material may be titanium or a titanium alloy, steel, or an organic matrix composite material (with, for example, a three-dimensionally woven fibrous reinforcement). Titanium or titanium alloy exhibits good thermomechanical properties and very good corrosion resistance.

[0056] The control lever 20 is advantageously made from a single piece (from material or monolithic).

[0057] According to an example of an embodiment, the control lever 20 is manufactured from a block of metal material which is machined.

[0058] Preferably, the control lever 20 is produced by an additive manufacturing or selective powder melting process. Additive manufacturing makes it possible to obtain complex and three-dimensional parts by fusing layers of powder with the least possible material loss.

[0059] There are several additive manufacturing techniques, one of which can be selected from the group including selective laser melting, also referred to as the acronym "SLM" for "Selective Laser Melting" in English, electron beam melting, also designated by the acronym "EBM" for "Electron Beam Melting" in English, direct laser additive construction, also designated by the acronym "CLAD" for "Construction Laser Additive Direct" in English, electron beam additive manufacturing, also designated by the acronym "EBAM" for "Electron Beam Additive Manufacturing" in English, laser metal deposition, also designated by the acronym "LMD" for "Laser Metal Deposition" in English, the binder jetting process, also designated by the terms "Binder Jetting" in English, or selective laser sintering, also designated by the acronym "SLS" for "Selective Laser Sintering" in English.

[0060] Preferably, the additive manufacturing technique used is laser powder bed fusion “SLM”, also known by the acronym “LBM” for “Laser Beam Melting "

[0061] Advantageously, but not limitingly, the manufacturing process is carried out by an additive manufacturing installation, not shown.

[0062] Such an additive manufacturing installation comprises, for example, at least one feed hopper containing a powder, here metallic, in particular titanium or a titanium alloy, at least one device for depositing the powder from the feed hopper onto a build platform, and an energy-generating element, such as a laser, for melting layers of powder. In particular, powder is deposited layer by layer on the build platform, and each layer of powder is melted by the energy-generating element, solidified, and then covered by further layers of the material. This operation is repeated multiple times to form the control lever.

[0063] In the context of additive manufacturing, the manufacturing direction of the control lever 20 is oriented in the elongation direction DA, and preferably from the first portion 22 to the second portion 23. In other words, the successive layers of powder are arranged along the elongation direction DA.

[0064] As shown in Figures 4 to 7, the control lever 20 includes at least one reinforcing element 40 which is configured to increase the mechanical strength of the control lever 20.

[0065] In the present example, the reinforcing element 40 is advantageously located between the first portion 22 and the second portion 23. The reinforcing element 40 is preferably located at the central portion 23 of the control lever 20.

[0066] Advantageously, but not limitingly, the reinforcing element 40 comprises an inclined wall 41 forming the central portion 24. In other words, the inclined wall 41 is connected to a wall of the first portion 22 and to a wall of the second portion 23.

[0067] Advantageously, but not limitingly, the inclined wall 41 is solid.

[0068] As can be seen in [Fig.5], the median plane PI (perpendicular to the plane of [Fig.5]) of the wall 41 has an angle of inclination

[320] with respect to a median plane P2 (perpendicular to the plane of [Fig.5]) of the wall of the second portion 23. The wall 41 is advantageously inclined outwards (from the second portion).

[0069] Advantageously, but not exclusively, the inclination angle

[320] is strictly greater than 180°. The inclination angle

[320] is oriented towards the inside of the control lever 20. Preferably, the apex E of the inclination angle

[320] is defined in a plane P3 which separates the central portion 24 and the second portion 23 along the extension direction DA. The inclination angle

[320] is, for example, between 181° and 230°. This configuration makes it possible to condition the path of forces in the event of exceptional mechanical stresses (ingestion, pumping) in such a way that these impose a downward radial force (towards the longitudinal axis of the turbomachine) which will force the control lever to move radially inwards (as opposed to disengaging).

[0070] Preferably, and with reference to [Fig. 5], the external surface portion 26a of the first portion 22 and the external surface portion 26c of the central portion 24 exhibit surface continuity. The internal surface portion 27b of the first portion 22 and the internal surface portion 27c of the central portion 24 advantageously exhibit surface continuity. Advantageously, the external surface portion 26c of the inclined wall (central portion) and the external surface portion 26b of the second portion exhibit surface continuity. Similarly, optionally, the internal surface portion 267 of the inclined wall (central portion) and the internal surface portion 27b of the second portion exhibit surface continuity.

[0071] As can be seen in [Fig.5], the inclined wall 41 is advantageously also inclined relative to the wall of the first portion 22. Advantageously, the median plane PI is inclined relative to the plane P4 (in which the surface portion 26a is defined) of the first portion 22 at an angle of inclination Ô20.

[0072] Advantageously, but not exclusively, the length L3 corresponding to that of the inclined wall 41 can be identical to a length L3A of the central portion 41 of the anterior art. The length L3A of the central portion of the anterior art can be between 10 mm and 40 mm. Alternatively, the length L3 can be between 0.8*L3A and 1.2*L3A. As shown in [Fig. 5], the length L3 is measured between the plane P3 and a plane PO separating the first portion 22 from the central portion 24.

[0073] Advantageously, the central portion or inclined wall has a thickness e3 which is substantially equal (plus or minus 10 mm) to the second thickness e2 of the second portion 23.

[0074] Advantageously, the inclined wall 41 has an end point F, located at the point where it connects to the first portion 22. The end point F is positioned at a predetermined height H above the first portion 22 along the radial direction DR. The predetermined height H is advantageously measured between the plane P4 and a plane P5 which passes through the end point F and is parallel to the plane P4. In other words, the upstream end of the inclined wall 41 is advantageously positioned radially above the first portion 22.

[0075] Figure 6 schematically represents the behavior of a control lever 20 comprising a reinforcing element 40 and subjected to a significant torque due to a pumping phenomenon or the ingestion / impact of a foreign object. In this example of the representation in the plane of Figure 6, the control lever 20 is connected to the control ring 14 via the first portion 22 and is connected to a variable-pitch stator vane 10 via the second portion 23. Since the second portion 23 is blocked at point C' along the X102 direction, the imposed displacement, induced by the torque exerted on the control lever 20, is converted into a displacement along the Y102 direction with a negative component. In other words, the radial displacement of the control lever 20 is limited by a stop. The first portion 22 pivots about the axis B with the torque applied at point A1'.Point C' slides along Y102, and the lengths Al'B' and B'C' would increase, implying that the control lever 20 deforms without disengaging. Conversely, with a control lever according to the prior art, the length of the second portion, the length of the central portion, and the length of the first portion would increase following the application of a significant torque. The prior art control lever 20 would move along a positive radial component at the second portion. This would cause the control ring pin 14 to disengage. In other words, the stiffened central portion limits the radial displacement of the control lever as well as its deformation and damage.

[0076] Figure 7 illustrates another embodiment of a control lever 20. This control lever 20 differs from the previous embodiments and alternative embodiments in that the connecting member 31 is mounted to move relative to the control lever 20. More specifically, the connecting member 31 is mounted, for example, via a ball joint 44 on the second portion 23. To this end, the ball joint 44 is made by means of an outer ring 45 and an inner ring 46. The outer ring 45 is advantageously pressed into the through hole of the second portion 23, while the head 32 of the connecting member is press-fitted into the inner ring 46 of the joint Ball joint 44. The ball joint 44 allows each control lever 20 to move by deforming without significant effort, since the connecting member 31 (here the pin) and the second part 23 of each control lever 20 can move relative to each other. The control means 15, with its current power, can be retained to move the reinforced control levers 20.

[0077] The configuration of the reinforcement element(s) gives each control lever 20 at least an increased longitudinal stiffness which will increase its resistance to longitudinal deformation.

[0078] With control levers 20 whose shape is optimized with a stiffening wall (a reinforcing element), deformations of the control lever and partial or total disengagement of the pin of the control ring 14 are avoided when a high mechanical torque (moment) is applied (for example in the case of pumping and / or ingestion of a foreign body) on the stator blades.

Claims

Demands

1. A control mechanism (13) for variable-pitch stator blades of a turbomachine (1), said control mechanism (13) comprising a control ring (14) adapted to be driven in rotation about a longitudinal axis (X) and control levers (20) connecting each variable-pitch stator blade (10) to the control ring (14) such that the rotation of the control ring (14) causes each variable-pitch stator blade (10) to pivot, each control lever (20) being pivotally mounted on the control ring (14) by means of a connecting member (30) and comprising a body (21) elongated along an elongation direction between a first portion (22) and a second portion (23), the body (21) comprising a central portion (24) connecting the first portion (22) and the second portion (23),characterized in that each control lever (20) comprises at least one reinforcing element (40) configured to increase the mechanical strength of the control lever (20), the reinforcing element (40) comprising a wall (41) which is inclined at least with respect to the wall of the second portion (23) and which forms the central portion (24), the inclined wall (41) being oriented outwards at an angle of inclination (320) whose apex (E) is defined in a plane (P3) separating the central portion (24) and the second portion (23).

2. Control mechanism (13) according to the preceding claim, characterized in that the control mechanism (13) comprises a control means (15) causing the rotation of the control ring (14) via at least one fusible transmission piece connecting the control ring (14) to the control means (15).

3. Control mechanism (13) according to any one of the preceding claims, characterized in that each control lever (20) is made of titanium, titanium alloy, steel or an organic matrix composite material.

4. Control mechanism (13) according to any one of the preceding claims, characterized in that the second portion (23) of each control lever (20) includes an orifice (30) receiving at least part of the linking member (31).

5. Control mechanism (13) according to any one of the preceding claims, characterized in that the angle of inclination ([320) is strictly greater than 180°C.

6. Control mechanism (13) according to any one of the preceding claims, characterized in that the angle of inclination ([320) is less than 230°.

7. Control mechanism (13) according to any one of the preceding claims, characterized in that the inclined wall (41) is also inclined relative to the wall of the first portion (22).

8. Control mechanism (13) according to any one of the preceding claims, characterized in that the inclined wall (41) has an upstream end delimited by an extreme point (F) which is arranged radially outside an external surface portion of the first portion (22).

9. Control mechanism (13) according to any one of claims 1 to 8, characterized in that the linking member (31) is permanently fixed at the level of the second portion (23).

10. Control mechanism (13) according to any one of claims 1 to 8, characterized in that the linking member (31) is mounted following a ball joint (44) at the level of the second portion (23).

11. Turbomachine (1) comprising variable-pitch stator blades (10) for straightening an airflow circulating in the turbomachine and a control mechanism (13) for the stator blades (10) according to any one of the preceding claims.

12. Turbomachine (1) according to claim 11, characterized in that it comprises at least one stage formed of an annular row of moving blades and an annular row of stator blades (10), the stator blades (10) being arranged upstream or downstream of the moving blades.

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