A turbine engine assembly including a variable-pitch stator vane equipped with a heating element

Abstract

The invention relates to an assembly for a turbomachine of an aircraft having a longitudinal axis (X), the assembly comprising: - a variable-pitch stator vane (2) comprising a blade and a pivot (5) extending radially from the blade (4); and - a heating element (26) comprising a first portion (26a) mounted in the blade (4) and a second portion (26b) connected to an electrical connection device (29). According to the invention, the pivot comprises a main bore (33), a drilled hole (34) passing through the wall of the pivot to open into the main bore (33) and onto the outer surface of the pivot (5), and a radial recess (35) provided in the wall of the pivot, which opens onto the outer surface and onto the outlet of the drilled hole (34), the second portion (26b) forming an extension of the first portion (26a) and extending into the main bore (33), into the drilled hole (34) and then into the radial recess (35) towards the electrical connection device.

Description

Technical Field

[0001] This invention relates to the field of aviation, and more particularly to aircraft propulsion. Specifically, the invention aims at a turbine engine assembly comprising variable pitch stator blades equipped with heating elements. Background Technology

[0002] Many turbine engines, such as turbojet and turboprop engines, are equipped with variable-pitch stator blades. These blades are arranged around the longitudinal axis of the turbine engine and are typically positioned upstream or downstream of the rotor blades, depending on the airflow direction within the engine, to guide the airflow at the correct angle at the outlet or towards the rotor blades. The pitch allows the variable-pitch stator blades to adapt to different turbine engine speeds. For this purpose, the variable-pitch stator blades are connected to a pitch-changing system configured to change their pitch or tilt around their pitch axis during flight.

[0003] The stator blades can be fitted into the compressor of a turbine engine. The pitch changing system includes a control ring centered on the longitudinal axis and multiple levers, each lever connected to a pivot of the stator blade and the control ring. Each pivot is mounted in a corresponding housing within the turbine engine housing via a socket.

[0004] Stator blades can freeze, which can impair their operation and thus reduce turbine engine performance. In this case, variable pitch stator blades are equipped with heating elements, a portion of which is integrated into each blade. Each heating element is connected to a power cable that extends from the outer end of the pivot to the outside of the blade and is connected to an electrical connection located on the outside of the stator blade near the pitch-changing system.

[0005] When the pitch is changed, the power supply cable has excess length to follow the rotation of the stator blades, but this excess length may interact with the pitch-changing system. When the stator blades rotate, the electrical connection device can also move. Spacers are intended to prevent this interaction, but this results in a significant increase in overall size within an already limited space. Nevertheless, mechanical stress and deformation of the power supply cable between the heating element in the moving reference frame and the electrical connection device in the fixed reference frame are unavoidable. This negatively impacts the durability and reliability of the heating element.

[0006] On the other hand, due to space constraints, once the stator blades are installed in the turbine engine, reliable electrical assembly of the heating elements and electrical connections becomes difficult. The assembly of the pitch-changing system and the adjustment of the stator blade pitch involve several operations to tighten and / or loosen components that carry the power supply cables, which can affect the mechanical properties of these components, as well as the mechanical properties of the electrical connectors, the fixation between the heating element and the electrical connections, or the fixation of the heating element itself. A portion of the heating element's length is covered by an insulating sheath that is rigid, fragile, and susceptible to repeated or extreme mechanical stresses, which could lead to breakage. The power supply cables for the heating elements typically include an electrical insulator that is more flexible than the heating element itself and provides greater resistance to repeated stresses. The assembly is also complex because the power supply cables must pass through corresponding sockets and receptacles in the turbine engine housing before the pivots can engage in their housings.

[0007] In addition, heat transfer from the power supply cable of the heating element to the outside is limited by its exposure to the outdoors; the lack of cooling for its exposed parts is a limiting factor for the power flowing through the power supply cable and reduces the accommodative power density.

[0008] Document GB-A-2403778 describes a turbine engine comprising a variable-pitch stator blade equipped with a heating element. The heating element comprises a first portion integrated into the blade and a second portion connected to the first portion, the second portion having a considerable length and extending into a channel formed in the blade. The channel is arranged radially below the blade pivot. The second portion of the heating element passes through a connecting box housed in the blade pivot and extends outside the blade to a power source. The layout of this heating element is complex, considering the additional length that must be handled and arranged in various channels and cavities. The second portion of the heating element is also subjected to various mechanical stresses when the stator blade tilts.

[0009] Some or all of the above-mentioned shortcomings need to be addressed. Summary of the Invention

[0010] The purpose of this invention is to provide a simple, robust, and economical solution for reducing or even eliminating mechanical stress on the power supply of the heating device for a variable pitch stator blade to prevent ice formation, while still allowing the variable pitch stator blade to tilt.

[0011] According to the invention, this is achieved by an assembly of a turbine engine having a longitudinal axis, particularly a turbine engine for aircraft, the assembly comprising: - A variable pitch stator blade, the variable pitch stator blade comprising blades and a pivot extending radially from one end of the blade, the pivot comprising a main bore. - A pitch changing system configured to change the pitch of the stator blades about the pitch axis of the stator blades, and - A heating element comprising a first part and a second part, the first part being mounted inside a blade, and the second part extending outside the blade and connected to an electrical connection device. The pivot includes a bore and a radial groove. The bore passes through the wall of the pivot to lead to a main bore on one side and to the outer surface of the pivot on the other side. The radial groove is formed in the wall of the pivot, leading to the outer surface and to the outlet of the bore. A second portion continues the first portion and extends into the main bore, into the bore, and then into the radial groove toward the electrical connection device.

[0012] Therefore, this solution enables the achievement of the aforementioned objectives. The arrangement of a portion of the second part inside and outside the pivot reduces the length of the pivot and its interaction with the pitch-changing system. Mechanical stress is transferred to other more robust components of the electrical connection. Reducing the length of the second part allows for weight reduction and lower manufacturing costs. Overall dimensions are also improved because the second part outside the pivot is positioned as close as possible to the diameter of the pivot by being mounted in a recess. Assembly and disassembly are also simpler because the shorter second part of the heating element does not require repeated bending to mount the stator blades in the turbine housing and connect them to the pitch-changing system. The lifespan and reliability of the heating element are improved, as are those of the electrical connection. The configuration of the drilled holes and master bores is a simple and cost-effective solution. Furthermore, the connection between the stator blade pivot and the pitch-changing system can be simplified while maintaining robustness, thereby improving the reliability of changing the blade pitch.

[0013] Turbine engine components may include one or more of the following features, either individually or in combination: - The electrical connection device includes at least one junction box and at least one wire harness, the wire harness being connected via the junction box to a first part of the heating element and to a power source, the wire harness extending outside the pivot.

[0014] - The pitch changing system includes a control ring and at least one lever, which is fixed to the radially outer end of a pivot by means of at least one fastening member and connected to the control ring, which is configured to rotate about a longitudinal axis and change the pitch of the stator blades.

[0015] - The component includes a support member that is rotatably fixed to the lever and is configured to carry and retain the connecting box.

[0016] - The support member is fixed to the lever by the same fastening member.

[0017] - The lever includes a channel that radially passes through the walls on both sides of the lever at a first end of the lever, and the channel is configured to receive at least a portion of a second part of a heating element.

[0018] - The component includes a cylindrical socket with a hole configured to be passed through by a pivot, and a second portion of the heating element extends radially above the cylindrical socket.

[0019] - The component includes a cylindrical socket with a hole configured to be passed through by a pivot, and a second portion of the heating element extends between the cylindrical socket and the pivot.

[0020] - The assembly includes multiple variable pitch stator blades arranged around a longitudinal axis, each pivotally connected to a control ring, and wherein the connection means includes multiple connection boxes, each connection box electrically connecting a second part of the heating element and at least two wire harnesses, each wire harness being connected via a connector to another wire harness in one of the connection boxes.

[0021] - The main bore extends coaxially with the pitch axis of the stator blade.

[0022] - The main hole extends at an angle to the radial axis.

[0023] - The main hole extends parallel to the pitch axis.

[0024] The present invention relates to a turbine engine, particularly a turbine engine for aircraft, comprising at least one turbine engine module having any of the aforementioned features. Attached Figure Description

[0025] The invention will be better understood by reading the following detailed description of embodiments of the invention given by way of purely exemplary and non-limiting examples, and by referring to the accompanying drawings, in which: - Figure 1 This is a partial perspective view of a variable pitch stator blade of an annular arrangement according to the present invention; - Figure 2 This is a perspective view of the stator blades according to the present invention, which are connected to the pitch changing system and equipped with a de-icing device; - Figure 3 This is an axial sectional view of an example of a variable pitch stator blade according to the present invention equipped with a de-icing device; - Figure 4 This is a cross-sectional view of another embodiment of the stator blades according to the present invention, equipped with a de-icing device; - Figure 5 An example of a connecting element between a variable pitch stator blade and a control element according to the present invention is shown. Detailed Implementation

[0026] Figure 1 Components for a turbine engine 1 having a longitudinal axis X are shown. The turbine engine is configured to be mounted on an aircraft and may be a turboshaft engine, a turbojet engine, a turbofan engine, or even include ducted or ductless movable fan blades or movable blades of at least one propeller.

[0027] The turbine engine assembly 1 includes at least one variable-pitch stator blade 2 connected to a pitch changing system 3. In this example, multiple stator blades 2 are distributed around a longitudinal axis X. The pitch changing system 3 is configured to change the pitch of at least one stator blade 2 according to the operating mode of the turbine engine.

[0028] In this invention, the term "stator blade" or "fixed blade" refers to a blade that is not driven to rotate about the longitudinal axis X of a turbine engine. In other words, the stator blade is distinct from and opposite to the rotor or movable blades of the turbine engine. The stator blades and rotor blades are typically arranged in annular rows, with the annular rows of stator blades positioned upstream and / or downstream of the annular rows of rotor blades along the longitudinal axis X.

[0029] In this invention, the terms "upstream" and "downstream" are generally defined relative to the flow of gas or air in the turbine engine and are defined herein along the longitudinal axis X. The terms "axial" and "axially" are defined relative to the longitudinal axis X. The terms "external," "outer," "inner," "internal," and "radial" are defined relative to the radial axis Z extending from the longitudinal axis X and relative to the distance from the longitudinal axis X. The radial axis is perpendicular to the longitudinal axis X.

[0030] In this example, the variable pitch stator vane 2 is preferably mounted in the compressor (not shown) or compressor assembly of the turbine engine, and is widely known as "VSV," an acronym for "Variable Stator Vane." The stator vane 2 is used to rectify the airflow passing through the stator vane.

[0031] refer to Figure 2 Each stator blade 2 includes a radially extending blade 4. Each blade 4 includes a leading edge 4a and a trailing edge 4b, which pass through a suction-side surface 4e and a pressure-side surface 4i (see [link to relevant documentation]). Figure 1 )connect.

[0032] Each stator blade 2 includes a pivot 5 extending radially from one end 4c of the blade 4. The pivot 5 is mounted to pivot about a pitch axis A. The pitch axis A extends substantially parallel to the radial axis Z. The pitch axis A may be tilted relative to the radial axis Z.

[0033] Blade 4 and pivot 5 are connected by plate 6, which may be optional. Advantageously, pivot 5 is mounted in a corresponding receiving portion 7 within the outer casing 8 of the turbine engine. Advantageously, the outer casing 8 is centered on a longitudinal axis X. The casing may be formed by at least two sectors around the longitudinal axis (cut along the plane XZ and connected together, for example, by longitudinal bolts) or by a single annular piece. Plate 6 has a circular shape and is configured to be received in a recess 9 within the outer casing 8 (in... Figure 3 As can be seen in the image, the inner surface 6a of plate 6 is flush with the inner surface 8a of outer casing 8. However, plate 6 may have another shape that does not impede the rotation of the blades and their arrangement relative to outer casing 8.

[0034] Advantageously, each pivot 5 is connected to a control ring 10 via a lever 11. The lever 11 and the control ring 10 are part of the pitch changing system 3. The control ring 10 is configured to rotate about the longitudinal axis X and change the pitch of the stator blade 2. The rotation of the control ring 10 is controlled, for example, by a control device (not shown) of the pitch changing system 3. Optionally, the control device is an actuator. In this example, there is at least one lever 11 for each stator blade 2 and a single control ring 10 for the assembly of the stator blade 2.

[0035] Each lever 11 extends between a first end 11a and a second end 11b. The first end 11a is fixed to the radially outer end 5a (free end) of the pivot 5. This fixing is achieved by means of at least one fastening member 14. Each fastening member 14 includes, for example, a threaded rod 15 that engages with a thread 16 disposed at the radially outer end 5a. The thread 16 may be supported by a threaded socket 17. The first end 11a of each lever 11 is penetrated, for example, by a first hole 18 that radially passes through both sides of the wall of the lever 11, and the threaded rod 15 passes through this first hole 18. The second end 11b is fixed to a control ring 10.

[0036] The control ring 10 is centered on the longitudinal axis X. The control ring 10 includes, for example, a plurality of radial apertures 19, each configured to engage with a fixing element 20. The second end 11b of each lever 11 is also penetrated by a second aperture 21 that engages with the fixing element 20. The fixing element 20 includes, for example, a cylindrical pin 22 that passes through the second aperture 21 and the corresponding radial aperture 19. Each lever 11 is pivotable about the axis of the cylindrical pin 22.

[0037] Each stator blade 2 is equipped with a de-icing device 25 that allows for de-icing and / or prevents ice formation. In this example, the de-icing device 25 includes at least one heating element 26, preferably an electric heating element 26.

[0038] refer to Figure 3 Each heating element 26 advantageously includes a first portion 26a mounted within a blade 4. The blade 4 may include a radially extending cavity 27 in which the first portion 26a is received. Advantageously, this extends over the entire radial height of the blade 4 to heat the entire blade 4. In one embodiment, the cavity 27 has a coil or paperclip shape, in which the first portion 26a is arranged. Current flowing through the second portion 26b raises the temperature within the blade 4, thereby preventing icing. The lateral thickness of the first portion 26a is, for example, between 0.1 mm and 10 mm. The first portion 26a is in the form of a heating wire.

[0039] Each heating element 26 includes a second portion 26b extending at least partially outside the blade 4. Advantageously, the second portion 26b is an extension of the first portion 26a. Advantageously, but not limited to, the second portion 26b is coated with a conductive material 28 to effectively transfer heat generated in the second portion 26b of the heating element 26 and prevent its temperature from rising. The conductive material 28 is arranged to increase the diameter or cross-section of the heating element 26 from its junction with the first portion 26a to the opposite end 26ba of the second portion 26b. Each second portion 26b is considered a cold portion of the heating element 26, and each first portion 26a is considered a hot portion of the heating element 26.

[0040] For example, the diameter of the second part 26b can be between 0.3 mm and 10 mm, preferably 3 mm. The conductive material 28 can be magnesium oxide. The magnesium oxide is in powder form, which is compacted and applied to form the conductive material and the insulator of the heating element.

[0041] Heating element 26 is connected to electrical connection device 29. Specifically, connection device 29 includes a power source 30, which may be a battery, motor, or alternator (powered by a turbine engine). Connection device 29 includes at least one connection box 31 configured to protect the fixation between the second portion and the power supply harness described below. This fixation can be achieved, for example, by welding. In this example, each second portion 26b is coupled to connection box 31. In other words, there are as many connection boxes 31 as there are stator blades 2. Connection boxes 31 are located outside the stator blades 2. In an alternative arrangement, the second portion 26b of each heating element 26 (particularly its end) retracts into the connection box 31.

[0042] According to one example, each connector 31 is cylindrical, preferably straight, and includes an outer casing made of, for example, a metallic material. The casing protects the fixing between the heating element 26 and the cable or power supply harness. The connector 31 includes a filler material, such as magnesium oxide (in the form of a compacted powder), which fills the interior of the casing and protects portions of the cable, the heating element, and the fixing. The filler material may include resin disposed at the ends of each connector 31.

[0043] Each junction box 31 is connected to at least one wire harness 32a, 32b in which current flows. For this purpose, the wire harness is connected to a power source 30. Preferably, there are two power supply wire harnesses 32a, 32b, each including a first end 32aa that is connected to a second end 26ba of a second portion 26b of a heating element 26 in the same junction box 31. The cross-section of each power supply wire harness 32a, 32b is larger than the cross-section of the heating element 26, particularly larger than the cross-section of the second portion 26b. The wire harnesses are “folded” to a longer radius. In fact, each power supply wire harness 32a and 32b includes a protective sheath that provides rigidity to the wire harness. Each wire harness includes, for example, a conductive element encapsulated within it by a metal layer forming the protective sheath. The metal layer serves as a mechanical reinforcement (preventing overload of the central conductor) and as a shield to prevent discharge (current leakage). For example, the diameter or cross-section of each power supply wire harness 32a, 32b is at least twice the maximum diameter of the heating element.

[0044] exist Figure 1 and Figure 2 In this configuration, each pair of wire harnesses 32a, 32b extends to the outside of the stator blade 2. Each wire harness 32a, 32b is also connected via connector 50 to another wire harness in one of the other connection boxes 31. Specifically, the second end of the first wire harness 32a1 connected to the first connection box 311 is connected to the first connector 501. The second end of the second wire harness 32b1 connected to the second connection box 312 is connected to the same first connector 501. The third wire harness 32a2 connected to the second connection box 312 is connected to the second connector 502, which is connected to the fourth wire harness, which is connected to the third connection box, and so on. The wire harnesses of two adjacent stator blades 2 are connected via connectors. However, adjacent stator blades 2 are not necessarily connected to each other. Typically, the stator blades are connected in series or in a loop. By connecting the stator blades in series (e.g., stator blade i connected to stator blade i+3), ice formation on a large portion of the stator blade grid 2 is prevented in the event of a failure in one of the loops. Each faulty / "non-anti-icing" stator blade 2 will be surrounded by two "anti-icing (heating element working)" stator blades.

[0045] Advantageously, each connector 50 includes a convex portion and a concave portion, the convex and concave portions including complementary coupling means. Alternatively, each connector 50 is a single piece.

[0046] In one embodiment, the component may include a support ring 43 (in) Figure 1 As can be seen in the image, the support ring 43 is configured to support one or more connectors 50 and power supply harnesses 32a, 32b. The support ring 43 may be centered on a longitudinal axis. The support ring is integral but can be sectored.

[0047] Each pivot 5 includes a radially inwardly extending main bore 33. In this example, each main bore 33 includes an axis coaxial with the pitch axis A of the blade. Alternatively, the axis of each main bore 33 may be inclined relative to or parallel to the pitch axis A. The construction of the main bore will depend on, for example, the fixing of several design elements and / or the pitch changing system. Advantageously, but not limited to, the main bore 33 opens to the radially outer end 5a of each pivot 5. The main bore 33 has a circular radial cross-section, which is not limiting. In this example, the main bore 33 also opens to the inner cavity 27 in the blade 4, thereby allowing the heating element 26 to be guided into and out of the blade 4.

[0048] In this example, each threaded socket 17 is configured to screw onto the threaded rod 15 and be pressed against the inner surface 33a of the main bore 33. The threaded rod 15 extends at least partially into the main bore 33 and the threaded socket 17.

[0049] like Figure 2 As shown, each pivot 5 includes a drilled hole 34 through the wall of the pivot 5. Each drilled hole 34, for example, leads to a main bore 33 on one side and to an outer surface 5c of the pivot 5 on the other. Advantageously, but not limited to, each drilled hole 34 has an axis inclined relative to the radial axis or the axis of the main bore 33. For example, the inclination angle relative to the radial axis Z is between 25° and 70°. In this way, a second portion 26b of the heating element 26 extends in a portion of the main bore 33 and then is oriented toward the drilled hole 34. Upon exiting the drilled hole 34, the second portion 26b faces the radially outer end 5a of the pivot 5. The second portion 26b quickly returns to the radial orientation, which minimizes its overall radial size while maintaining an acceptable minimum radius of curvature for the second portion 26b of the heating element 26. This configuration also allows the fastening member 14, which occupies a portion of the main bore 33, to be bypassed. Furthermore, at least a portion of the second portion 26b of the heating element 26 is arranged outside the pivot 5 and not at the center of the pivot 5, making it easier to attach the lever 11 to the radially outer end 5a of the pivot 5.

[0050] Advantageously, each pivot 5 includes a radial groove 35 formed in the wall of the pivot 5. Each radial groove 35 leads to the outer surface 5c of the pivot 5. Each radial groove 35 has a generally U-shaped or C-shaped radial cross-section. Each radial groove 35 leads to the outlet 34b of the bore 34. Advantageously, each radial groove 35 leads to the radially outer end 5a of the pivot 5, and preferably to the edge 36 of the radially outer end. A portion of each second portion 26b is received in and guided within the radial groove 35. The arrangement of the second portion 26b in the radial groove 35 further reduces the overall radial dimension of the pivot 5 and allows the heating element 26 and the connecting box 31 to be electrically connected before the stator blade 2 is mounted on the turbine engine housing 8. The second portion 26b of the heating element 26 bends towards the horizontal plane with a small overhang at the radially outer end 5a of the pivot 5. This facilitates easy fixation of the lever 11 to the pivot 5.

[0051] Pivots 5 can each be mounted in a cylindrical socket 37. To achieve this, each cylindrical socket 37 includes a hole 38 that is coaxial with the pitch axis A in the mounted state. Each pivot 5 passes through a corresponding hole 38. Advantageously, but not limited to, there is a gap between the outer diameter of the pivot and the inner diameter of the socket 37. In the example shown, each cylindrical socket 37 consists of two parts 37a and 37b. Of course, each cylindrical socket 37 can be formed as a single piece. Each part 37a and 37b extends between a first end 39a and a second end 39b. Each part includes collars 40a and 40b extending radially outward from one of the first and second ends. Each cylindrical socket 37 is also mounted in the receiving portion 7 of the housing. In this way, the collar 40a of the first part 37a rests on the outer surface of the wall of the housing 8, while the collar 40b of the second part rests on the outer surface of the plate 6 (opposite to the inner surface). Alternatively, the socket 37 does not have a collar. The height of the first end 39a of the first portion 37a is greater than the height of the outlet of the bore 34. In other words, the outlet of the bore 34 can lead into the interior of the cylindrical socket 37. In this way, the second portion 26b of the heating element 26 extends between the socket 37 and the pivot 5. Alternatively, the first end 38a of the first portion 37a of the cylindrical socket 37 is lower than the height of the outlet 34a of the bore 34, such that the outlet of the bore 34 is open above the collar 40a. In this way, the second portion 26b of the heating element 26 extends radially above the socket 37.

[0052] refer to Figure 3Advantageously, but not limited to, each lever 11 includes a recess 41 that opens to the inner surface 23 of the lever 11. A first hole 18 opens to the recess 41. In other words, the recess 41 is located at a first end 11a of each lever 11. Each recess 41 forms an abutting surface 42 against which the edge 36 of the radially outer end 5a of the pivot 5 abuts. Each radially outer end 5a of the pivot 5 is received in and at least partially surrounded by the recess 41. This allows the pivot to be better centered and held in place on the lever 11.

[0053] Figure 4 Another embodiment of the turbine engine assembly is shown. This embodiment differs from the previous embodiment in that the support member 45 is configured to support and retain the connecting box 31. In this example, each support member 45 is rotatably fixed to one of the levers 11. For this purpose, each support member 45 is fixed to the lever 11 by the same fastening member 14 located at the radially outer end 5a of the pivot 5. Each support member 45 includes, for example, an arm 46, with a first end 46a fixed to the lever 11. At the opposing second end 46b, the arm 46 includes two lateral panels 47 facing each other and spaced apart in the circumferential direction to create a gap. Each connecting box 31 rests on the arm 46 and is positioned between the two lateral panels 47. Advantageously, each connecting box 31 is fixed to the support member 45, for example, by clamping or gluing. The support member 45 holds the connecting box fixed relative to the lever 11. This eliminates relative movement between the connecting box 31 and the heating element 26. This prevents the connection / fixture between the heating element (first and second parts) or the heating element and the connecting box (both of which are fragile) from absorbing any force during operation.

[0054] In this embodiment, the first end 11a of the lever 11 includes an outer surface 24 radially opposite the inner surface 23. The outer surface 24 is defined in a first plane that extends radially above a second plane, in which the outer surfaces of the remaining portion of the lever body 11 are defined. Here, the second end 11b is located away from the support member 45 and extends radially below the support member 45. This configuration makes it easier to attach each lever 11 to the control ring 10.

[0055] Figure 4 The dashed heating element second portion 26b, which is not yet connected to the connecting box 31, and the second portion 26b connected to the connecting box 31 are also shown. When the second portion is connected, it forms a bend and passes over the fastening member 14.

[0056] Figure 5An embodiment of lever 11 is shown. Lever 11 includes a channel 55 configured to receive at least a portion of the second portion 26 of heating element 26. Channel 55 passes through the walls on both sides along a radial axis. In other words, channel 55 leads to both the outer surface 24 and the inner surface 23, which are opposite each other along the radial axis. In this example, the outer surface 24 of lever 11 is defined in the same plane, but may be defined in two different parallel planes. Channel 55 also leads to the outer peripheral lateral surface 51 of lever 11. Advantageously, the outer peripheral lateral surface connects the outer surface 23 and the inner surface 24. Advantageously, channel 55 is formed at the first end 11a of lever 11. Channel 55 has a U-shaped or C-shaped radial cross-section. Optionally, channel 55 is aligned or substantially aligned with a groove 35 (the axis of the groove may be parallel to the axis of channel 55). Positioning channel 55 on lever 11 further reduces the overall size of the power supply device, particularly the overall size of the second portion 26b of heating element 26.

Claims

1. An assembly of a turbine engine having a longitudinal axis (X), the turbine engine being particularly for use in aircraft, the assembly comprising: - Variable pitch stator blade (2), the variable pitch stator blade includes blades (4) and a pivot (5) extending radially from one end (4c) of the blades (4), the pivot (5) including a main bore (33). - Pitch changing system (3), the pitch changing system being configured to change the pitch of the stator blade (2) around the pitch axis (A) of the stator blade, and - Heating element (26), the heating element comprising a first part (26a) and a second part (26b), the first part being installed inside the blade (4), and the second part extending outside the blade (4) and connected to an electrical connection device (29). The pivot (5) is characterized in that it includes a drilled hole (34) and a radial groove (35), the drilled hole passing through the wall of the pivot (5) to lead to the main hole (33) on one side and to the outer surface (5c) of the pivot (5) on the other side, the radial groove being formed in the wall of the pivot (5) to lead to the outer surface (5c) and to the outlet of the drilled hole (34), the second portion (26b) continuing the first portion (26a), and the second portion (26b) extending into the main hole (33), into the drilled hole (34), and then extending toward the electrical connection device into the radial groove (35).

2. The component according to the preceding claim, characterized in that, The electrical connection device (29) includes at least one connection box (31) and at least one wire harness (32a, 32b), the wire harness being connected via the connection box (31) to a first portion (26a) of the heating element (26) and to a power source (30), the wire harness (32a, 32b) extending outside the pivot (5).

3. The component according to any one of the preceding claims, characterized in that, The pitch changing system (3) includes a control ring (10) and at least one lever (11), the lever being fixed to the radially outer end of the pivot (5) by means of at least one fastening member (14) and connected to the control ring (10), the control ring being configured to rotate about the longitudinal axis X and change the pitch of the stator blade (2).

4. The component according to the preceding claim, characterized in that, The component includes a support member (45) that is rotatably fixed to the lever (11) and is configured to carry and retain the connecting box (31).

5. The component according to the preceding claim, characterized in that, The support member (45) is fixed to the lever (11) by the same fastening member (14).

6. The component according to claim 3 or 4, characterized in that, The lever (11) includes a channel (55) that extends radially through the walls on both sides of the lever at a first end (11a) of the lever, and the channel is configured to receive at least a portion of a second portion (26b) of the heating element (26).

7. The component according to the preceding claim, characterized in that, The component includes a cylindrical socket (37) with a hole (38) configured to be passed through by the pivot (5), and a second portion (26b) of the heating element (26) extending radially above the cylindrical socket (37).

8. The component according to claim 6, characterized in that, The component includes a cylindrical socket (37) with a hole (38) configured to be passed through by the pivot (5), and a second portion (26b) of the heating element (26) extends between the cylindrical socket (37) and the pivot (5).

9. The component according to any one of the preceding claims, characterized in that, The assembly includes a plurality of variable pitch stator blades (2) arranged around the longitudinal axis (X), each pivot (5) being connected to a control ring (10), and wherein the connection device (29) includes a plurality of connection boxes (31), each connection box electrically connecting a second portion (26b) of the heating element (26) and at least two wire harnesses, each wire harness being connected via a connector (50) to another wire harness of one of the connection boxes (31).

10. The component according to any one of the preceding claims, characterized in that, The main bore (33) extends coaxially with the pitch axis of the stator blade.

11. The component according to any one of claims 1 to 10, characterized in that, The main hole (33) extends at an angle to the radial axis.

12. The component according to any one of claims 1 to 11, characterized in that, The main hole (33) extends parallel to the pitch axis.

13. A turbine engine (1) comprising the components according to any one of the preceding claims.

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