Electrical connection for an electric machine in an aircraft turbomachine

Abstract

The present disclosure is an aircraft turbomachine (10) comprising: a gas generator (12) having a longitudinal axis (A), a fan (14) located at an upstream end of the gas generator and configured to rotate about said axis, and an electric machine (70) having a substantially annular shape, the electric machine being coaxially mounted downstream of the fan and comprising a rotor (70a) and a stator (70b), the rotor being rotationally coupled to the fan, and the stator being connected to a power electronic circuit (78) by at least one rigid conductive bar (80).

Description

Technical Field

[0001] The present invention relates to an aircraft turbine equipped with an electric machine and a method for maintaining the turbine. Background Art

[0002] The prior art particularly includes the documents FR-A1-2 842 565, FR-A1-2 896 537 and FR-A1-2 922 265, which describe turbines equipped with electric machines.

[0003] The aviation community is now raising many questions about the relevance of using hybrid engines in commercial aviation. The use of electrical energy is now considered not only to satisfy the functions of the aircraft, but also to electrify the functions of the turbine.

[0004] This observation has led to research on solutions for hybrid engine architectures that combine fossil fuel energy and electrical energy to ensure the drive of the propulsion part (the fan of the turbine) and the supply of certain engine and / or aircraft functions.

[0005] These architectures can in particular be of the high bypass ratio and reduction gear type, or of the multiple (2 or 3) body type. In these architectures, the turbine includes a low-pressure body and a high-pressure body, each body including a shaft connecting the rotor of the compressor to the rotor of the turbine.

[0006] It is known to equip an aircraft turbine with an electric machine. We recall that an electric machine is an electromechanical device based on electromagnetism, for example enabling the conversion of electrical energy into work or mechanical energy. This process is reversible and can be used to generate electricity.

[0007] Therefore, depending on the final use of the machine, we use the following terms:

[0008] - A generator, which represents an electric machine that generates electrical energy from mechanical energy,

[0009] - A motor, which is used to generate mechanical energy from electrical energy.

[0010] The electric machine can operate either in motor mode or in generator mode.

[0011] The integration of a high-power electric machine on the low-pressure body of the turbine, especially on the low-pressure body of a high bypass ratio type turbine, is very complex. Multiple installation areas are possible, but the advantages and disadvantages of each installation area are numerous and different (problems such as the mechanical integration of the machine, the temperature resistance of the machine, the accessibility of the machine, etc.).

[0012] One solution to this problem is to integrate the electric machine directly downstream of the fan of the turbine. However, one difficulty is the connection of the machine to the power electronics circuit, which is generally located at a distance from the machine.

[0013] In such an environment, using an electrical harness presents some technical problems. A large-diameter harness has a very large bending radius, which will not conform to this environment. The integration of the harness will require supports to limit the vibration transmission to the surrounding components and the damage to the surrounding components.

[0014] The present invention proposes a solution to at least some of the problems discussed above. Summary of the Invention

[0015] The present invention proposes an aircraft turbine, which comprises:

[0016] - a gas generator having a longitudinal axis,

[0017] - a fan located at the upstream end of the gas generator and configured to rotate about said axis, and

[0018] - an electric machine having a substantially annular shape, coaxially mounted downstream of the fan and comprising a rotor and a stator, the rotor being rotatably coupled to the fan,

[0019] The fan is configured to generate a main air flow, a part of which flows into the main annular duct of the gas generator to form a main flow, and another part of which flows in a secondary annular duct extending between the gas generator and the nacelle housing to form a secondary flow.

[0020] The main duct is defined by a first annular casing and a second annular casing coaxial with the gas generator, and the main duct is traversed by straightening vanes called IGVs for connecting the first casing and the second casing and by the tubular arms of an inlet housing located downstream of the IGVs.

[0021] The gas generator includes a third annular casing of the gas generator, which coaxially surrounds the second casing, and the second casing and the third casing are connected together at the upstream end thereof to form an annular separator nose for separating the main flow and the secondary flow.

[0022] Characterized in that the stator of the electric machine is connected to the power electronics circuit by at least one rigid conductive rod, which rod comprises:

[0023] - a first end portion for connection to the electric machine, which first end portion is located within the first casing,

[0024] - A second end portion for connection to a circuit, the second end portion being located between a second housing and a third housing, and

[0025] - An intermediate portion extending within one of the tubular arms of the inlet housing.

[0026] Thus, the present invention proposes a solution for motor integration. The first advantage is related to the fact that in the integration area of the machine, ideally directly downstream of the fan and thus upstream of one or more compressors, where the prevailing temperature is relatively low and thus optimal for the machine. In particular, if the turbine includes a speed reducer, the rotor of the machine is driven by the fan and thus rotates at a relatively low speed. Additionally, the machine is located as close as possible to the flow duct of the flow, which has a relatively large diameter and can thus generate significant electricity compared to prior art machines.

[0027] Furthermore, the present invention provides a solution to the problem of electrical connection of the machine in this environment. The connection is ensured by one or more rigid rods, each rigid rod extending through the tubular arm of the inlet housing, i.e., as close as possible to the separator nose of the main and secondary flows of the turbine.

[0028] The turbine according to the present invention may include one or more of the following features, which are adopted independently of each other or in combination with each other:

[0029] - The rod has a generally S-shaped or Z-shaped configuration, and the intermediate portion of the rod is inclined at an angle between 90° and 180° with respect to each of the end portions.

[0030] - The rod has a polygonal and constant cross-section and can be twisted.

[0031] - The turbine includes a nacelle housing surrounding the gas generator and vanes called OGVs for connecting the nacelle housing to the third annular housing.

[0032] - The nacelle housing defines a secondary flow duct for the secondary flow surrounding the gas generator.

[0033] - The OGVs are located downstream of the IGV arms and are arranged to generally correspond to the tubular arms of the inlet housing.

[0034] - The second portion extends generally corresponding to one of the OGVs.

[0035] - The gas generator includes an annular flange for attaching the OGVs, the annular flange being located between the second housing and the third housing, and at least one of these flanges includes a notch for passing the rod.

[0036] - The rod is surrounded by an insulating sheath and includes a first end and a second end, the first end being exposed for releasably attaching to an element for electrically connecting to the stator, and the second end being exposed for releasably attaching to a wire harness for electrically connecting to the circuit;

[0037] - The electric machine is located upstream of the separator nose;

[0038] - The stator of the electric machine is connected to a power electronics circuit by a plurality of rigid conductive rods regularly distributed around the axis;

[0039] - The first end portion is arranged to substantially correspond to the IGV and / or the separator nose;

[0040] - The power circuit is located between the second housing and the third housing;

[0041] - The tubular arm of the inlet housing includes a hole at the radially inner end of the tubular arm through which the first end portion passes, and the tubular arm of the inlet housing includes a lumen through which the intermediate portion passes, the lumen being closed at the radially inner end thereof by a sealing wall of the arm;

[0042] - The hole is formed in an annular attachment flange belonging to the inlet housing, the flange being configured to attach the inlet housing to the annular bearing support and / or the stator of the electric machine.

[0043] The present invention also relates to a method for maintaining a turbine as described above, the method comprising the steps of:

[0044] - Dismounting and removing the OGV arranged to correspond to the rod, and

[0045] - Dismounting and removing the rod for maintenance. Description of the Drawings

[0046] In the following description made by way of non-limiting example and with reference to the drawings, the present invention will be better understood and other details, features and advantages of the present invention will become clearer. In the drawings:

[0047] Figure 1 Figure 1 is a schematic view of an axial cross-section of an aircraft turbine with a high bypass ratio and a reduction gear;

[0048] Figure 2 Figure 2 is a partial schematic semi-view of an axial cross-section of an aircraft turbine equipped with an electric machine according to the present invention;

[0049] Figure 3 Figure 3 is similar to Figure 2 ​​​​​​, and shows the electrical connection rod from the stator of the machine to the power electronics circuit,

[0050] Figure 4 Figure 4 is Figure 2 A schematic perspective view of a part of the turbine of, and in particular shows the tubular arm of the inlet housing, which serves as a passage for the electrical connection rod,

[0051] Figure 5 Figure 5 is Figure 2 Another schematic perspective view of a part of the turbine of, and in particular shows the path of the electrical connection rod,

[0052] [Figures 6a - 6d] Figures 6a to 6d are Figure 3 Detailed views of, and show the steps of a method for maintaining the turbine,

[0053] Figure 7 Figure 7 is Figure 2 A schematic perspective view of a part of the turbine of, and shows one of the steps in the method for maintaining the turbine,

[0054] Figure 8 Figure 8 A schematic cross - sectional view of a wire harness, and

[0055] Figure 9 Figure 9 A schematic cross - sectional view of an embodiment of the electrical connection rod. Detailed Description

[0056] First, referring to Figure 1 , Figure 1 A twin - spool and twin - flow aircraft turbine 10 is schematically shown.

[0057] The turbine 10 generally includes a gas generator 12, upstream of which is arranged a fan 14. The fan 14 is surrounded by a casing 16, which is surrounded by a nacelle 18 that surrounds and extends along a major part of the gas generator 12.

[0058] The gas generator 12 herein includes two spools, namely a low - pressure spool 12a or LP and a high - pressure spool 12b or HP. Each spool includes a compressor and a turbine.

[0059] The terms "upstream" and "downstream" are considered along the main direction F of the gas flow in the turbine 10, which direction F is parallel to the longitudinal axis A of the turbine.

[0060] ​​​​​​​​​​The gas generator 12 includes, from upstream to downstream, a low-pressure compressor 20, a high-pressure compressor 22, a combustion chamber 24, a high-pressure turbine 26, and a low-pressure turbine 28.

[0061] The fan 14 includes a row of annular blades 30 driven to rotate by a fan shaft 32, and the fan shaft is connected to the rotor of the low-pressure body 12a through a speed reducer 33. The airflow passing through the fan (arrow F) is divided into a radially inner annular flow and a radially outer annular flow by an annular separator nose 34 upstream of the gas generator 12. The radially inner annular flow is called the main flow 36, which flows in the main annular duct of the gas generator 12. The radially outer annular flow is called the secondary flow 38, which flows in the secondary annular duct between the gas generator 12 and the nacelle 18 and provides most of the thrust for the turbine.

[0062] The inlet housing 40 structurally connects the gas generator 12 to the housing 16 and the nacelle 18. The inlet housing 40 includes a row of radially inner arms 42 and a row of radially outer straightening vanes 44. The radially inner arms extend into the flow duct of the main flow 36, and the radially outer straightening vanes are called Outer Gear Vanes (OGV) and extend into the flow duct of the secondary flow 38.

[0063] The number of the arms 42 is usually limited (less than ten), and the arms are tubular and penetrated by auxiliary components.

[0064] These arms 42 have a structural function because they enable the transfer of forces between the bearing supports and the suspension. These arms also have the function of allowing the auxiliary components to pass through, enabling the auxiliary components to pass through the duct by straightening them, thereby limiting the aerodynamic losses in the duct. These arms do not have a flow straightening function because they do not have camber and the number is insufficient to perform this function.

[0065] The number of the straightening vanes 44 (OGV) is usually greater than ten. The straightening vanes can straighten the flow of the fan due to their specific number and camber. The straightening vanes also have a structural function because they support the housing (fan housing) around the fan.

[0066] The flow duct of the main flow 36 is also penetrated by straightening vanes 52, which are called Inner Gear Vanes (IGV). The IGVs 52 are evenly distributed around the axis A and are located upstream of the inlet housing 40, more precisely upstream of the arms 42. When the flow from the fan enters the main duct, these vanes can straighten the flow from the fan. These vanes do not have a structural role. These vanes have a sufficient number (for example, more than 10) and have a certain camber to straighten the flow of the fan passing through the main duct.

[0067] The flow duct of the main flow 36 is defined by two coaxial annular casings, namely an inner annular casing 37a and an outer annular casing 37b. In particular, the IGV 52 and the arm 42 are connected to these casings 37a, 37b. The flow duct of the secondary flow 38 is defined internally by an annular casing 39 coaxial with the casings 37a, 37b and externally by the nacelle housing 16. The OGV 44 is connected to the casings 37b, 39.

[0068] Each of the casings 37a, 37b, 39 can be formed by a plurality of adjacent walls or covers.

[0069] The rotor of the low-pressure body 12a and the fan shaft 32 are guided upstream by bearings 46, 48 and 50. These bearings 46, 48, 50 are ball or roller type bearings, and each bearing includes an inner ring mounted on the shaft to be guided, an outer ring carried by an annular bearing support, and roller bearings between the rings.

[0070] In a known manner, the speed reducer 33 is of the epicyclic gear train type and includes a sun gear centered on axis A, an annular gear extending around the axis, and planet gears meshing with the sun gear and the annular gear and carried by a planet carrier.

[0071] In the example shown, the annular gear is fixed and fixedly connected to the support 62 of the bearings 46, 48. The planet carrier is rotatable and coupled by the fan shaft 32. The sun gear of the speed reducer is coupled to the main shaft 58 of the low-pressure body through the input shaft 56.

[0072] The input shaft 56 is guided by a bearing 50 carried by a bearing support 60. The fan shaft 32 is guided by the bearings 46, 48.

[0073] The bearing supports 60, 62 extend around axis A and are fixed parts connected to the stator, in particular to the inlet housing 40.

[0074] Figure 2 is Figure 1 An enlarged and more detailed view of a part of, and shows an embodiment of a turbine according to the present invention.

[0075] Figure 2 The elements already referred to in Figure 1 are denoted by the same reference numerals.

[0076] In particular, Figure 2 shows the region Z between the fan disk 32a and the speed reducer 33, in which the electric machine 70 is mounted. In Figure 2Only one support 33a of the ring gear of the speed reducer 33 is visible therein, and this element is connected, for example, to the inlet housing 40 or the bearing support 62.

[0077] Figure 2 The cross-section in the figure in [the figure] passes through one of the IGVs 52 in the IGVs, and this IGV may be complete.

[0078] This cross-section passes through the OGV 44 and through the arm 42, which is tubular to allow the auxiliary parts to pass through as described above. Each arm 42 includes an upstream edge 42a and a downstream edge 42d, and the upstream edge and the downstream edge are respectively the leading edge and the trailing edge of the main flow 36.

[0079] Each arm 42 includes an inner cavity 42c, which is closed radially externally by the wall 44a of the OGV 44. This wall 44a is formed as a single part with the OGV 44 and is attached to the annular flange of the inlet housing 40, which are respectively the upstream annular flange 43a and the downstream annular flange 43b. The cavity 42c is isolated from the auxiliary parts by the wall 42b.

[0080] The inner cavity 42c of each arm 42 is closed radially internally by the annular wall 40a of the inlet housing 40. At the upstream end of this wall 40a, the inlet housing 40 includes a radially internal annular flange 40b for attaching the bearing support 62. At the downstream end of the wall 40a, the inlet housing 40 includes, for example, a radially internal annular attachment flange 40c for attaching an annular groove for recovering the oil ejected by the speed reducer 33 by centrifugation.

[0081] In Figure 1 The visible speed reducer 33 and the bearings 46, 48, 50 are located in the annular lubrication housing E, which is sealed upstream by the bearing support 62 and at least one invisible seal, and downstream by the bearing support 60 and at least one invisible seal. The outer periphery of the housing E is particularly sealed by the wall 40a.

[0082] Figure 2 It is possible to show that the above-mentioned housing 37a is formed by a plurality of continuous walls (such as the wall 40a) and the annular shroud 64, and this annular shroud is located upstream of the wall 40a and is connected to the inner periphery of the IGV 52.

[0083] The housing 37b is formed by a plurality of continuous walls and particularly the annular shroud 66, and this annular shroud is located upstream of the inlet housing 40. This shroud 66 extends around the shroud 64 and is connected to the outer periphery of the IGV 52.

[0084] The housing 39 is formed by a plurality of successive walls (such as wall 44a) and an annular shroud 68 which is located upstream of the wall 44a. The shroud 68 extends around the shroud 66 and the upstream ends of the shrouds 66, 68 are joined together to form the separator nose 34.

[0085] As described above, the electric motor 70 is located in the annular region Z which is bounded upstream herein by the fan 14, in particular by the disc 32 for attaching the fan blades 30 to the fan shaft 32, and downstream by the bearing support 62.

[0086] The electric motor 70 has a substantially annular shape and includes a rotor 70a and a stator 70b. The rotor 70a has a substantially annular shape extending around the axis A and is carried by a support element 72 which itself has a substantially annular shape.

[0087] In the example shown, the support element 72 includes a cylindrical wall 72a which is surrounded by the rotor 70a and attached to the inner periphery of the rotor. The upstream end of the wall 72a is connected on the one hand to a radially inner annular flange 72b for attachment to the fan disc 32a and on the other hand to an outer annular rim 72c.

[0088] The rim 72c includes an inner cylindrical surface 72d which bears on the outer cylindrical surface of the fan 14 to ensure centering of the rotor 70a. The rim 72c also includes an outer annular wiper 72e of a labyrinth seal.

[0089] The stator 70b also has a substantially annular shape and is carried by an annular support element 74.

[0090] The element 74 includes an outer annular surface 74a which defines internally a flow duct for the air flow F between the fan 14 and the separator nose 34. The element 74 is attached to the outer periphery of the stator 70b and includes an upstream end which cooperates, for example via a wear-resistant annular coating, with the aforementioned wiper 72e.

[0091] The downstream end of the element 74 is axially aligned with the shroud 64, the upstream peripheral edge of which is axially engaged in an annular groove 74b of the element 74. The groove 74b is axially directed downstream. The engagement of the upstream edge of the shroud 64 in the groove 74b of the element 74 ensures an overlap and thus avoids steps in the duct which would disturb the flow F.

[0092] The downstream end of the element 74 also includes an annular flange 76 for attachment to the bearing support 62 or the inlet housing 40. The flange 76 has a substantially U-shaped axial cross-section and has an opening directed radially outwards. Thus, the flange 76 defines an annular space X for the electrical connection of the stator 70b, as will be described in particular below with reference toFigure 3 will be described in more detail. In the example shown, the flange 76 is attached by screws to the flange of the bearing support 62 and the flange 40b of the inlet housing.

[0093] The element 74 can be formed by a single part or by two annular and coaxial parts mounted around each other.

[0094] One of the features of this mounting is that the motor 70 (in particular the stator 70b of this motor) is located as close as possible to the main flow F after passing through the fan 14. On the one hand, this enables a motor with a large diameter and thus a higher potential power compared to the techniques proposed so far, and on the other hand, it enables a motor cooled by the flow F. Advantageously, the heat losses of the motor are dissipated by this cooling.

[0095] For this purpose, preferably, the surface 74a swept by the flow F has an aerodynamic profile, as shown. The element 74 ensures heat exchange by heat conduction between the stator 70b and the flow F.

[0096] The stator 70b is connected to the power electronic circuit 78 by electrical connection means, which is located between the two housings 37b, 39 and thus in the gas generator 12.

[0097] Figures 3 to 5 An embodiment of these electrical connection means including a rigid rod 80 is shown.

[0098] Additionally, although one or more wire bundles can be used for the electrical connection of the stator 70b, at least one rigid rod 80 is used which provides many advantages.

[0099] In a preferred embodiment of the invention, the stator 70b is connected to one end of the rod 80 by a first wire bundle 82c, and the opposite end of the rod is connected to the circuit 78 by a second wire bundle 82d. In this case, preferably, the cross-section of the core 82a of each wire bundle 82c, 82d is the same as or close to the cross-section of the body 80a of the rod 80. Preferably, the cross-section of the rod 80, in particular the cross-section of the body 80a of the rod, is constant over the entire length of the rod.

[0100] In Figure 7 the rod 80 that is integrally visible is shaped to extend from the region Z to the circuit 78. The rod can have a generally complex shape such as an L-shape, an S-shape, a Z-shape, etc.

[0101] The rod 80 includes ends (the upstream end 84a and the downstream end 84b respectively), which are exposed, i.e., not covered by the sheath 80b, so as to be able to connect the rod 80 to the wire bundles 82c, 82d ( Figure 4 , Figure 5 and Figure 7 ).

[0102] Each end of the rod 84a, 84b includes a hole 86 for mounting a bolt 88 (screw and nut, or even washer). The bolt 88 is used to attach the ends 84a, 84b of the rod 80 to the corresponding wire harnesses 82c, 82d preferably through lugs 90. The lugs are connected to one end of the wire harness and include a plate which is intended to be applied on the corresponding ends 84a, 84b and is tightened and attached at the ends by the bolt 88( Figure 5 ).

[0103] As in the example shown( Figure 7 ), the rod 80 can be twisted, and then the rod includes one end 84a extending in a plane P1 in the ends of the rod ( Figure 4 the plane P1 in which passes through the axis A of the turbine) and the other end 84b extending in a plane P2 perpendicular to the plane P1 in the ends of the rod (the plane P2 is substantially tangent to the circumference centered on the axis A- Figure 5 and Figure 7 ).

[0104] The present invention proposes a specific path of the rod 80 from the stator 70b to the circuit 78, more specifically between the wire harnesses 82c, 82d. Note that in practice, the stator 70b can be connected to the circuit 78 by a plurality of rods 80. Then, preferably, these rods 80 are evenly distributed around the axis A, and each rod is connected to the stator 70b and the circuit 78 through the wire harnesses 82c, 82d. Therefore, the following description of the rod 80 applies to each electrical connecting rod from the stator of the motor to the power electronic circuit.

[0105] In Figures 3 to 7 the embodiment shown, the rod 80 then extends along the axis A and the OGV44 through one of the tubular arms 42 of the inlet housing 40.

[0106] Therefore, the rod 80 has a substantially Z-shaped or S-shaped shape and includes:

[0107] - A first end portion 80d, which includes an end 84a for connecting to the motor 70, and the first end portion 80d is located within the first housing 37a,

[0108] - A second end portion 80e, which includes an end 84b for connecting to the circuit 78, and the second end portion 80e is located between the second housing 37b and the third housing 39, and

[0109] - An intermediate portion 80c, which extends within one of the tubular arms 42 of the inlet housing 40.

[0110] The first part 80d is substantially straight and extends from the space X to the interior of the cavity 42c substantially parallel to the axis A. The end 84a is located in the above-mentioned space X and is connected to the wire harness 82c by a bolt 88 in this space X. The first part 80d axially passes through the hole 40d in the upstream flange 40b of the inlet housing 40. Figure 3 It is shown that the wall 40a extends radially inside the rod 80 and thus radially inside the hole 40d to ensure the sealing of the cavity 42c from the outer casing E.

[0111] The intermediate part 80c is inclined at an angle α in the range of 120° to 150° with respect to the first part 80d. The part 80c extends radially outwards from upstream to downstream and can follow the inclination of the arm 42 in which it is received.

[0112] The second part 80e is substantially straight and extends substantially parallel to the axis A to the circuit 78. For this purpose, the second part axially passes through the notch 92 in the downstream flange 43b of the inlet housing 40. This is the axial notch 92, which is formed at the outer periphery of the attachment flange 43b of the OGV 44 and is shaped such that the rod 80 can extend through this notch 92 without disturbing the attachment of the arm 44 to the flange 43b. Figure 5 It is also possible to show that the end 84b bends downstream of the flange 43b to be oriented substantially parallel to this flange.

[0113] The intermediate part 80c is inclined at an angle β in the range of 120° to 150° with respect to the second part 80e.

[0114] Figures 6a to 6d and Figure 7 show the steps of a method for maintaining the turbine 10.

[0115] In the order of the steps shown in Figures 6a to 6d, these steps enable the installation of the rod 80. It should be understood that repeating these steps in the reverse order is sufficient for the removal of the rod 80.

[0116] Before the first step shown in Figures 6a and 6b, the OGV 44 intended to be arranged corresponding to the rod 80 is disassembled and removed.

[0117] Then, the rod 80 can be installed by first engaging the part 80d of the rod through the open radial outer end of the cavity of the arm into the cavity 42c of the arm 42.

[0118] Then, the end 84a of the rod 80 must be as close as possible to the wall 40a and the hole 40d (Figures 6a and Figure 7 ).

[0119] Then, the rod 80 is tilted such that the opposite end 84b of the rod is closer to the axis A (Figure 6b). In fact, for the previous step of facilitating the engagement of the rod 80 in the cavity 42c of the arm, the rod must be tilted substantially radially with respect to the axis A.

[0120] The tilting of the rod 80 continues (Figure 6c), and then the rod can be axially displaced upstream such that the end 84a of the rod passes through the hole 40d and is located in the space X described above.

[0121] Then, surrounding elements such as the OGV 44, the shrouds 64 - 68, and the IGV 52 can be installed.

[0122] Figure 8 A cross - section showing the generally circular shape of the wire harness 82 is presented, which includes a conductive core 82a formed by a strand of conductors and an insulating outer sheath 82b. Figure 9 An example of an embodiment of the rod 80 is shown, which includes a conductor 80a that preferably has a polygonal shape and, for example, a rectangular cross - section. The rod 80 also includes an insulating outer sheath 80b.

[0123] The present invention enables the provision of many advantages:

[0124] - Contrary to a wire harness, the rod 80 enables a very short bending radius, which is necessary in the relevant environment; this enables the thickness of the separator nose 34 to be limited to be close to the thickness of the rod 80; furthermore, the "twistable" profile of the rod enables the rod itself to adapt to the following through - regions: the radial position of the arm 42 entering the inlet housing 40 (in the plane P1) and the axial position at the OGV 44 (in the plane P2);

[0125] - The rod 80 is rigid, so there is no risk of vibration due to excessive flexibility, and thus no specific support is required in the arm of the inlet housing 40;

[0126] - The above - mentioned path is compatible with all oil auxiliaries circulating in the arm of the inlet housing 40; furthermore, the walls of the inlet housing 40 (especially the walls 40a and 42b) isolate the rod 80 from these oil auxiliaries, which limits the risk of fire;

[0127] - This path avoids the passage of the rod 80 into the oil housing E; this avoids the addition of seals; and

[0128] - Modularity is associated with the ease of assembly / disassembly of the rod 80 by removing only a few components of the turbine.

[0129] The present invention can be applied to any turbine equipped with an electric motor upstream of a structural housing (such as an inlet housing or other housing).

Claims

1. An aircraft turbine (10), comprising: - A gas generator (12) having a longitudinal axis (A), - A fan (14) located at the upstream end of the gas generator and configured to rotate about the longitudinal axis, and - An electric machine (70) having a substantially annular shape, coaxially mounted downstream of the fan and including a rotor (70a) and a stator (70b), the rotor being rotatably coupled to the fan, The fan is configured to generate a primary air flow (F), a portion of the primary air flow flowing into the main annular duct of the gas generator to form a main flow (36), and another portion of the primary air flow flowing around the gas generator to form a secondary flow (38), The main annular duct is defined by a first annular casing (37a) and a second annular casing (37b) coaxial with the gas generator, the main annular duct being traversed by an arm called IGV (52) for connecting the first annular casing and the second annular casing and by a tubular arm (42) of an inlet housing (40) located downstream of the IGV, The gas generator includes a third annular casing (39) coaxially surrounding the second annular casing, The second annular casing (37b) and the third annular casing (39) are connected together at their upstream ends to form an annular separator nose (34) for separating the main flow (36) and the secondary flow (38), Characterized in that the stator (70b) of the electric machine (70) is connected to a power electronic circuit (78) by at least one rigid conductive rod (80), which rigid conductive rod comprises: - A first end portion (80d) for connection to the electric machine, which first end portion is located within the first annular casing (37a), - A second end portion (80e) for connection to the power electronic circuit, which second end portion is located between the second annular casing (37b) and the third annular casing (39), and - An intermediate portion (80c) extending within one of the tubular arms (42) of the inlet housing (40).

2. The aircraft turbine (10) according to claim 1, wherein, The rigid conductive rod (80) has a substantially S-shaped or Z-shaped configuration, the intermediate portion (80c) of the rigid conductive rod being inclined at an angle (α, β) between 90° and 180° with respect to each of the first end portion (80d) and the second end portion (80e).

3. The aircraft turbine (10) according to claim 1 or 2, wherein, The rigid conductive rod (80) includes a conductor (80a) and is capable of being twisted, the conductor having a polygonal and constant cross-section.

4. The aircraft turbine (10) according to claim 1 or 2, wherein, The aircraft turbine includes a nacelle housing (16) surrounding the gas generator (12) and vanes called OGV (44) for connecting the nacelle housing to the third annular casing (39).

5. The aircraft turbine (10) according to claim 4, wherein, The gas generator (12) includes annular flanges (43a, 43b) for attaching the OGV (44), the annular flanges being located between the second annular housing (37b) and the third annular housing (39), and at least one of these annular flanges includes a notch (92) for passing the rigid conductive rod therethrough.

6. The aircraft turbine (10) according to claim 1 or 2, wherein, The rigid conductive rod (80) is surrounded by an insulating sheath (80b) and includes a first end (84a) and a second end (84b), the first end being exposed for releasably attaching to an element for electrical connection to the stator (70b), and the second end being exposed for releasably attaching to a wire harness (82b) for electrical connection to the power electronics circuit (78).

7. The aircraft turbine (10) according to claim 1 or 2, wherein, The motor (70) is located upstream of the annular separator nose (34).

8. The aircraft turbine (10) according to claim 1 or 2, wherein, The stator (70b) of the motor (70) is connected to the power electronics circuit (78) by a plurality of rigid conductive rods (80) regularly distributed around the longitudinal axis (A).

9. The aircraft turbine (10) according to claim 1 or 2, wherein, The first end portion (80d) is arranged to generally correspond to the IGV (52) and / or the annular separator nose (34).

10. The aircraft turbine (10) according to claim 1 or 2, wherein, The power electronics circuit (78) is located between the second annular housing (37b) and the third annular housing (39).

11. The aircraft turbine (10) according to claim 1 or 2, wherein, The tubular arm (42) of the inlet housing (40) includes a hole (40d) at the radially inner end of the tubular arm through which the first end portion (80d) passes, and the tubular arm of the inlet housing includes a lumen (42c) through which the intermediate portion (80c) passes, the lumen being closed at the radially inner end thereof by a sealing wall (40a) of the tubular arm.

12. The aircraft turbine (10) according to claim 11, wherein, The hole (40d) is formed in an annular attachment flange (40b) belonging to the inlet housing (40), the annular attachment flange being configured to attach the inlet housing to the annular bearing support (62) and / or the stator (70b) of the motor (70).

13. A method for maintaining an aircraft turbine (10) according to any one of claims 1 to 12, wherein, The aircraft turbine includes a nacelle housing (16) surrounding the gas generator (12) and vanes called OGVs (44) for connecting the nacelle housing to the third annular housing (39), and the method includes the following steps: - disassembling and removing the OGV (44) arranged to correspond to the rigid conductive rod (80), and - disassembling and removing the rigid conductive rod for maintenance.

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