Turbine engine module equipped with electric motor

Abstract

The invention relates to a turbine engine module, comprising: a fan shaft (6), a power shaft (15), the power shaft rotating the fan shaft via a reducer (21) arranged in a lubrication chamber (22), a lubrication system (50) for the reducer (21), the lubrication system having a closed main circuit (51) for supplying the lubrication chamber and a closed auxiliary circuit (60) for supplying the lubrication chamber when the main circuit is inoperative, the auxiliary circuit comprising an auxiliary pump (61) driven by an electric motor (63), and an electric motor (65) configured to provide power to the electric motor (63), the electric motor having a rotor connected to the fan shaft for rotation and a stator mounted on a fixed member at least partially supporting the electric motor.

Description

Technical Field

[0001] The present invention relates to the field of turbine engines equipped with a speed reducer and is particularly directed to a turbine engine module and a corresponding turbine engine equipped with an electric motor for supplying an auxiliary pump of a lubrication system of at least one device of the turbine engine. Background Art

[0002] Aircraft turbine engines, such as twin-flow turbine engines, typically include a ducted fan located at the turbine engine inlet, which is driven by a low-pressure shaft. A speed reducer may be inserted between the fan and the low-pressure shaft, allowing the fan to rotate at a lower speed than the low-pressure shaft. This reduced speed also allows the fan to be larger, thus achieving a very high bypass ratio.

[0003] The reducer (also called "reduction gearbox" or RGB) is of the planetary or planetary type. A reducer is generally equipped with a plurality of rotating gears and / or sprockets, the lubrication and cooling of which are in any case important aspects for the correct functioning of the turbine engine and its efficiency. In fact, when the reducer is not adequately lubricated, the friction between the teeth of the gears and / or sprockets or at the bearings causes them to wear prematurely, thus reducing the efficiency of the reducer. These bearings, gears and / or sprockets of the reducer can generate very high thermal power, which must be evacuated in order to avoid damage to the reducer.

[0004] Lubrication systems are known for lubricating certain components of a turbine engine, in particular the speed reducer, as described in documents US-A1-2016 / 258324 and EP-A1-3184780.

[0005] Depending on the turbine engine's architecture, some lubrication systems are designed to deliver high oil flows, potentially reaching thousands of liters per hour (e.g., over 5,000 liters per hour), to lubricate the reducer and bearings. The lubrication system typically includes a main circuit, comprising at least one oil tank and a main pump, which supplies a lubrication housing, where the reducer and bearings are located. The main pump is mechanically driven by the turbine engine's high-pressure shaft via the accessory gearbox. In this case, the main circuit only lubricates and cools the reducer and bearings when the high-pressure shaft is operating—that is, when the turbine engine is started and in flight. The lubrication system also includes an auxiliary circuit with an auxiliary oil tank and auxiliary pump to cover other operating conditions of the turbine engine, such as during startup, shutdown, or when the fan shaft rotates freely due to wind and drives the low-pressure shaft coupled to it. This latter condition is known as "windmilling." A mechanical solution exists in which the auxiliary pump is driven by the reducer and operates in all conditions of windmilling (both clockwise and counterclockwise), requiring sufficient components to accommodate this. This type of mechanical pump is complex to install and bulky. Furthermore, the pump operates continuously, which leads to premature wear and tear, and requires specific technology to enable the pump to rotate in both directions, like a windmill. There is an electric solution in which the auxiliary pump is powered by an external power source (e.g., a battery) that lubricates the casing, which is detrimental to the turbine engine's quality. Summary of the Invention

[0006] In particular, an object of the present invention is in particular to provide a solution that enables autonomous feeding of the auxiliary pump of the lubrication system while avoiding damage to the quality of the turbine engine and facilitating the installation and disassembly of its components.

[0007] According to the invention, this object is achieved by a turbine engine module comprising:

[0008] a fan shaft guided in rotation about the longitudinal axis X by at least one first guide bearing mounted on a first bearing support attached to the fixed structure of the turbine engine,

[0009] - a power shaft which drives the fan shaft in rotation via a speed reducer arranged in the lubricating casing of the turbine engine,

[0010] - a lubrication system for at least a speed reducer, the lubrication system comprising a closed primary circuit for supplying a lubricated housing and a closed auxiliary circuit for supplying the lubricated housing when the primary circuit is inoperative, the auxiliary circuit comprising at least one auxiliary supply pump driven by an electric motor,

[0011] - The module also includes an electric motor configured to power the electric motor of the auxiliary pump and carried at least partially by the first bearing support, the electric motor comprising: a rotor connected to the fan shaft so as to be driven in rotation about an axis of rotation A parallel to the longitudinal axis X; and a stator mounted on a fixed element at least partially supporting the electric motor.

[0012] Thus, this solution makes it possible to achieve the above-mentioned objectives. In particular, due to the connection of the rotor of the electric motor to the fan shaft, the auxiliary pump of the lubrication system is directly supplied so that, in particular when the main pump is inoperative, the lubricant can circulate in the auxiliary circuit for supplying the lubricating casing. The main pump operates only when the high-pressure shaft rotates at a predetermined speed, while the fan shaft is driven in rotation by the wind (turns like a windmill) when the aircraft is on the ground and when the turbine engine is stopped, when the machine is started or ventilated. The electric motor utilizes the rotation of the fan shaft in different situations so that the rotor of the electric motor is also driven in rotation in all operating situations to generate electricity that can be used to drive various devices in the turbine engine. The lubrication system and the electric motor are autonomous. In addition, this configuration is modular, which makes it easy to disassemble and install from upstream of the turbine engine.

[0013] The fan module also includes one or more of the following features, taken alone or in combination:

[0014] The fan module includes a motion output mechanism that connects the motor's rotor to the fan shaft and transfers motion from the fan shaft to the rotor. This configuration allows the motor to be moved away from the gears of the speed reducer to limit oil splashing onto electrical components.

[0015] -The motion output mechanism includes a gear train.

[0016] - The motor comprises a motion output mechanism connecting the rotor to the fan shaft, the motion output mechanism comprising a drive shaft mounted to rotate freely about an axis of rotation A and on which the rotor is mounted, the drive shaft being coupled to a gear for meshing with a toothed ring gear fixed to the fan shaft.

[0017] The drive shaft is guided in rotation by a first rotor bearing comprising a first ring fixed to the drive shaft and a second ring fixed to a fixed element, the first rotor bearing being arranged upstream of the rotor of the electric machine.

[0018] The drive shaft is guided in rotation by a second rotor bearing comprising a first ring fixed to the drive shaft and a second ring fixed to the fixed element, the second rotor bearing being arranged downstream of the rotor of the electric machine.

[0019] The electric motor is arranged upstream of the reducer relative to the longitudinal axis and at least partially in the lubricating housing.

[0020] The electric motor is housed in a housing formed in said first bearing support.

[0021] The fixing element is a base of the electric machine mounted on the first bearing support, or the fixing element is the first bearing support.

[0022] -The drive shaft is integrated with the gear.

[0023] -The stator of the electric motor extends around the rotor of the electric motor.

[0024] - The electric motor and the electric motor are connected to cables that are looped outside the lubricated housing.

[0025] -The reducer is of the planetary gear type, comprising: a sun gear mounted so as to be movable about the axis X and coupled to the power shaft; and a ring gear centered on the longitudinal axis, coupled to the fan shaft, the reducer also comprising a planet carrier, which is fixed and carries a plurality of movable planetary gears meshing with the ring gear and the sun gear.

[0026] - The reducer is of the planetary gear train type, comprising a sun gear mounted so as to be movable about the axis X and coupled to the power shaft, a fixed ring gear and a planet carrier centered on the longitudinal axis, coupled to the fan shaft and carrying a plurality of movable planetary gears meshing with the ring gear and the sun gear.

[0027] - The gears and ring gear are housed in a lubricated housing.

[0028] The fixing element comprises the housing of the electric motor.

[0029] - The auxiliary pump is installed outside the lubrication housing.

[0030] The invention also relates to an aircraft turbine engine comprising a turbine engine module having any of the above-mentioned characteristics.

[0031] The present invention also relates to a method for assembling the above-mentioned turbine engine module, comprising the following steps:

[0032] - Install the toothed ring gear on the fan shaft,

[0033] - assembling the electric machine by mounting the rotor on the drive shaft and the stator on a fixed element at least partially supporting the electric machine,

[0034] - attaching the base of the electric machine to the first bearing support so that the rotor and the stator are arranged in a housing of the first bearing support which is open in the lubrication housing, and

[0035] - Connect the cables to the motor and the auxiliary pump mounted outside the lubrication housing.

[0036] The assembly method includes the following features and / or steps, taken alone or in combination:

[0037] - a fixed element at least partially supporting the motor including a base or a first bearing support of the motor,

[0038] - Mounting of a first guide bearing support for the fan shaft on the fixed structure of the turbine engine.

[0039] - Assemble the electric machine by mounting the stator on the first bearing bracket.

[0040] - Meshing a gear coupled to the drive shaft with the toothed ring gear.

[0041] -Assemble the reducer.

[0042] -Install the reducer in the lubricated housing of the turbine engine.

[0043] - Attach the fan disc to the fan shaft. BRIEF DESCRIPTION OF THE DRAWINGS

[0044] The invention will be better understood and other objects, details, features and advantages thereof will become clearer by reading the following detailed description of embodiments of the invention given as purely illustrative and non-limiting examples with reference to the following drawings:

[0045] [ Figure 1 ] Figure 1 is a schematic axial cross-sectional view of a twin-flow turbine engine with a speed reducer according to the present invention;

[0046] [ Figure 2 ] Figure 2 is a schematic, partially detailed view of a fan module of a twin-flow turbine engine with a speed reducer interposed between the fan shaft and the power shaft of the turbine engine according to the invention;

[0047] [ Figure 3a ] Figure 3a is a schematic diagram of a system for lubricating components and equipment of a turbine engine having a functioning auxiliary pump according to the present invention;

[0048] [ Figure 3b ] Figure 3b is a schematic diagram of a system for lubricating components and equipment of a turbine engine having a non-functional auxiliary pump according to the present invention;

[0049] [ Figure 4 ] Figure 4 is an embodiment of the arrangement of an electric motor according to the invention cooperating with a fan shaft in a turbine engine module;

[0050] [ Figure 5 ] Figure 5 is another embodiment of the arrangement of an electric machine according to the invention cooperating with a fan shaft in a turbine engine module; and

[0051] [ Figure 6 ] Figure 6 An example of a bearing support upstream of a guide bearing of a fan shaft of a turbine engine is shown, which bearing support carries the electric machine according to the invention. DETAILED DESCRIPTION

[0052] Figure 1 The present invention is shown in an axial cross-section through a turbine engine 1 having a longitudinal axis X. The turbine engine shown is a twin-flow, twin-body turbojet engine intended for installation on an aircraft according to the invention. Of course, the present invention is not limited to this type of turbine engine.

[0053] In the present application, the terms "upstream", "downstream", "axial" and "axially" are relative to the flow direction of the gases in the turbine engine and also along the longitudinal axis X (in Figure 1 Furthermore, the terms “radial”, “radially”, “inner” and “outer” are defined relative to a radial axis Z that is perpendicular to the axis X of the turbine engine.

[0054] This twin-flow, twin-body turbojet engine 1 comprises a fan 2 mounted upstream of a gas generator or gas turbine engine 3. The fan 2 comprises a plurality of fan blades 4 extending radially from the periphery of a disk 5 through which a fan shaft 6 extends. The fan 2 is surrounded by a fan casing 7 carried by a nacelle 8 which surrounds the gas generator 3 and extends along a longitudinal axis X.

[0055] The gas generator 3 comprises, from upstream to downstream, a low-pressure (BP) compressor 9, a high-pressure (HP) compressor 10, a combustion chamber 11, a high-pressure turbine 12, and a low-pressure turbine 13. The HP compressor 10 is connected to the HP turbine via an HP shaft 14, forming a first body, referred to as the high-pressure body. The BP compressor is connected to the HP turbine via a BP shaft 15, forming a second body, referred to as the low-pressure body. The BP shaft 15 extends within the HP shaft 14.

[0056] The air flow F entering the turbine engine via the fan 2 is separated by the turbine engine's separator nose 16 into a primary air flow F1, which flows through the gas generator 3 and, in particular, in a main duct 17, and a secondary air flow F2, which flows around the gas generator 3 in a secondary duct 18. The main duct 17 and the secondary duct 18 are coaxial. The secondary air flow F2 is ejected by a secondary nozzle 19 that terminates at the nacelle 8, while the primary air flow F1 is ejected outside the turbine engine via an ejection nozzle 20 located downstream of the gas generator. The primary and secondary air flows merge at the outlet of their respective nozzles.

[0057] Reference Figure 2 The fan shaft 6 is connected to a power shaft, which drives the fan shaft to rotate about the longitudinal axis X via a power transmission mechanism. In this example, the power shaft is the low-pressure shaft 15. The power transmission mechanism enables the speed of the fan 2 to be reduced to a speed lower than that of the low-pressure shaft 15. On the other hand, the power transmission mechanism enables the use of a large-diameter fan to increase the bypass ratio. The bypass ratio of the fan is advantageously greater than 10. Preferably, the bypass ratio is between 15 and 20.

[0058] The power transmission mechanism includes a speed reducer 21, which in this case is a planetary speed reducer. Of course, a planetary gear speed reducer is also possible. The speed reducer is housed in a lubricating housing 22, which is located upstream of the gas generator 3. The lubricating housing 22 enables lubrication of the speed reducer 21 and the rotary guide bearings of the speed reducer and the fan shaft. Specifically, the lubricating housing 22 is located within an annular inner housing 23, which is extended upstream by a streamlined inlet cone 24.

[0059] The inner housing 23 includes a first annular ring 23a that rotates relative to a second annular ring 23b of the inner housing 23 about the longitudinal axis X. The first ring 23a is mounted on the fan disc 5. The second annular ring 23b is structurally connected to the inlet housing 28 of the inter-duct housing 25 via first stator vanes 26 (known by the abbreviation IGV). The first stator vanes 26 extend radially into the primary air flow F1 and extend about the longitudinal axis X. The inlet housing 28 carries the separator nose 15 upstream. The fan disc 5 and the first ring 23a form a rotor assembly. The inlet housing 28, the stator vanes 26, and the second ring 23b form a stator assembly. The second stator vanes 27 (referred to as OGVs) structurally connect the inlet housing 28 to the fan housing 7. The second stator vanes 27 extend radially into the secondary air flow and extend about the longitudinal axis.

[0060] exist Figure 2In the embodiment of the present invention, the gear train of the speed reducer 21 generally includes a sun gear (or inner planetary gear) 30, a plurality of planetary gears 31, a planet carrier 32, and a ring gear (outer planetary gear) 33. In this example of a planetary speed reducer, the sun gear 30 is centered on the longitudinal axis X and is rotationally coupled to the BP shaft 15 along the longitudinal axis X via a sun gear shaft 34. The sun gear shaft includes a first element (not shown) that mates with a complementary second coupling element (not shown) carried by the BP shaft 15. The planetary gears 31 are carried by the planet carrier 32 and are each guided to rotate about the planetary gear axis, which is parallel to the longitudinal axis X. Each planetary gear 31 meshes with the external teeth of the sun gear 30 and the internal teeth of the ring gear 33. The planet carrier 32 is locked against rotation and fixed to the stator housing of the turbine engine. The ring gear 33, centered on the longitudinal axis X, surrounds the sun gear 30 and is rotationally coupled to the fan shaft 6. The sun gear 30 forms the input of the speed reducer, while the ring gear 33 forms the output of the speed reducer.

[0061] In the case of a planetary gear train, planet carrier 32 is rotationally coupled to fan shaft 6, and ring gear 33 is fixed to the turbine engine's stator housing. In other words, ring gear 33 is fixed and does not rotate. Thus, sun gear 30 forms the input of the speed reducer, while planet carrier 32 forms the output of the speed reducer.

[0062] Fan shaft 6 is guided for rotation relative to the stationary structure of the turbine engine via at least one bearing. A first bearing 35 (here with rolling elements) comprises an inner ring 36 mounted on fan shaft 6, an outer ring 37 carried by a first annular bearing support 38, and rolling elements 39 between the inner and outer rings. Rolling elements 39 of first bearing 35 are advantageously balls. First annular bearing support 38 is fixed to the stationary structure of the turbine engine. Bearing 35 is arranged upstream of reducer 21.

[0063] The turbine engine also includes another guide bearing (second bearing) 40 for the rotation of the fan shaft 6 relative to the fixed structure of the turbine engine. This second bearing 40 (here with rolling elements) is arranged upstream of the first guide bearing 35. The guide bearing 40 includes an inner ring 41 mounted on the fan shaft 6 and an outer ring 42 mounted on a second bearing support 43. Rolling members 44 are inserted between the inner ring and the outer ring. These rolling members 44 include rollers. The second bearing support 43 includes a flange 46 to which the first bearing support 38 is attached. Attachment is accomplished by attachment members 45 such as screws and nuts or other members that enable quick installation and disassembly.

[0064] Reference Figure 3a and 3bThe turbine engine includes a lubrication system 50 for certain equipment and components of the turbine engine (such as the above-mentioned reducer 21 and bearings 35, 40) arranged in a lubricating casing. The lubrication system includes a main circuit 51, which supplies at least the above-mentioned lubricating casing 22 in a closed circuit. The main circuit 51 includes at least one main lubricant supply tank 52 and a main lubricant supply pump 53 for allowing lubricant to circulate from the tank toward the lubricating casing 22. The main circuit 51 also includes a heat exchanger 54, which is arranged downstream of the main pump 53 in the direction of lubricant flow in the turbine engine. The main pump 53 is driven by an accessory gearbox or relay 55 (AGB). The main pump 53 is advantageously mounted on the accessory gearbox 55 (i.e., outside the lubricating casing 22).

[0065] like Figure 1 As shown, in a turbine engine, the accessory gearbox 55 is housed in an area known as the "core area." The "core area" is located in the inter-duct housing 25 (i.e., between the primary duct 17 and the secondary duct 18). The accessory gearbox 55 is driven in rotation by the high-pressure shaft 14 via a radial shaft 56. Alternatively (not shown), the accessory gearbox 55 is housed in the nacelle 8 and driven by the radial shaft 56, which then extends into the housing arms connecting the inter-duct housing 25 and the nacelle 8.

[0066] exist Figure 3a 、 Figure 3b In the embodiment of the present invention, the main pump 53 communicates with an electronic control unit 58 dedicated to controlling certain components and / or devices of the turbine engine. This electronic control unit 58 may be an EEC computer (Electronic Engine Controller). The computer is controlled by a full authority electronic system (known as Full Authority Digital Engine Control, abbreviated as FADEC) that manages the correct operation of the turbine engine. The computer 58 is also connected to, for example, devices for monitoring parameters of the high-pressure shaft 14 (such as its speeds N1, N2) and devices for detecting the pressure P of the lubricant in the main circuit 51.

[0067] Lubrication system 50 (refer to Figure 3a and Figure 3b ) also includes an auxiliary lubrication circuit 60, which is also used to supply lubricated housing 22 in a closed loop. Auxiliary circuit 60 includes an auxiliary lubricant supply pump 61 powered by electrical energy. Auxiliary pump 61 is connected to an auxiliary oil tank 62 on one hand and to lubricated housing 22 on the other. Auxiliary pump 61 is arranged upstream of lubricated housing 22 in the direction of lubricant flow in the auxiliary circuit. Advantageously, auxiliary oil tank 62 serves as an oil accumulation area for oil recovery. This auxiliary oil tank is located at the bottom of housing 22 (similar to the dial of a clock, at the six o'clock position).

[0068] Typically, each lubrication housing in a turbine engine also includes a lubricant recovery pump 64 that returns lubricant from a recovery tank (or accumulation area) to the main supply tank. The auxiliary pump 61 is electric and driven by an electric motor 63. Advantageously, the auxiliary pump 61 and electric motor 63 are located outside the lubrication housing 22 to keep the lubrication housing uncluttered and out of the confined, lubricant-soaked environment.

[0069] Once the high-pressure shaft 14 rotates at a predetermined rotational speed N2 and / or a predetermined pressure P is reached in the main circuit 51, the main pump 53 is ignited (or activated) to allow lubricant to flow from the main tank 51 to the lubrication housing 22. This operating mode occurs after the turbine engine is started and during flight. The auxiliary pump 61 is inactive, and the auxiliary circuit 60 is not supplied with lubricant.

[0070] The turbine engine 1 also includes an electric motor 65, comprising a rotor and a stator, to benefit from the additional electrical power, in particular to power the electric motor 63 of the auxiliary pump 61. Advantageously, but not exclusively, the electric motor 65 functions as a motor, i.e., it enables the conversion of mechanical energy into electrical energy. To this end, the electric motor 65 is coupled to the fan shaft 6, which, during its rotation, provides the electric motor with mechanical power, which is converted into electrical power. The fan shaft 6 is driven in rotation by the BP shaft 15 whenever the HP shaft 14 rotates or when wind acts on the blades of the fan blades. In other words, this additional electrical power is available regardless of the turbine engine's operation, i.e., during windmilling (the fan spinning on the ground or at rest), during flight, during landing, and during startup. Consequently, the lubrication system of the reducer in the lubrication housing 22 (where the reducer is located) is autonomous.

[0071] Of course, the electric machine 65 can be operated in generator mode to convert electrical energy into mechanical energy.

[0072] The electric motor 65 is electrically connected to a relay housing 48 configured to enable or disable the supply of electrical power to the electric motor 63 of the auxiliary pump 61. These relays 48 are themselves electrically connected to a computer 58. These relays cooperate with at least one switch (or valve) 49 configured to occupy an open position or a closed position.

[0073] Figure 3aThe turbine engine is shown shut down. In this case, we assume that calculator 58 is not functioning. By default, the relay housing is closed, and switch 49 is in the off position. The rotation of the fan shaft enables motor 65 to generate electricity, which then drives the electric motor 63 of auxiliary pump 61. Furthermore, the main pump is "deactivated," and the oil flow in main circuit 51 is interrupted. This is achieved by valve 59, installed at least between auxiliary pump 61 and housing 22. The valve is also located between the two circuits and the housing. Specifically, valve 59 allows for two inlet openings and one outlet opening. The first inlet opening connects to auxiliary circuit 60, and the second inlet opening connects to main circuit 51. Valve 59 also includes a blocking element, such as a ball, that blocks one of the inlet openings depending on the pressure in the circuits. By activating auxiliary pump 61, oil is pumped into auxiliary tank 62, particularly from the bottom of the tank. The pressure in auxiliary circuit 60 increases until it reaches a pressure that blocks the inlet of main circuit 51, preventing lubricant from flowing through it to housing 22. Lubricant flows through the auxiliary circuit and toward housing 22.

[0074] Reference Figure 3b , the turbine engine is started. In this case, the calculator 58 is functional and can drive the relay box 48. The switch 49 is in the open position. When the calculator 58 receives information indicating that the high-pressure shaft is rotating at a speed at least equal to the predetermined speed N1 or N2 and / or the pressure in the circuit reaches the predetermined pressure P in the main circuit, the calculator 58 deactivates the relay housing 48 (sending a control command to the relay housing 48). The main circuit can then operate. Oil is pumped out from the auxiliary tank (via the main tank and other tanks) and the outlet connected to the main circuit. This oil outlet connected to the main circuit is radially inside the oil outlet connected to the auxiliary circuit. The increased pressure in the main circuit causes the inlet of the auxiliary circuit 60 to be blocked, thereby preventing the lubricant from flowing to the casing 22. The lubricant flows through the main circuit 51 and flows to the casing 22. No current is generated. The motor does not supply power to the auxiliary pump (no current).

[0075] Reference Figure 4 , the motor 65 is carried by the bearing support 38 located upstream of the reducer 21. In other words, the motor 65 is arranged in the lubricating housing 22 so that the motor 65 can be cooled by the lubricant. The maximum temperature in the lubricating housing 22 is about 150°C, which is acceptable for the motor 65. The temperature of the components of the motor 65 (electrical conductors, electrical insulators, magnetic circuit, temperature sensor, exciter) should generally not exceed this value. In addition, the high power generated by the motor is discharged directly into the lubricating fluid. The lubricating housing 22 (in Figure 2The fan shaft 6 (partially shown in dashed lines) is at least partially defined by the first and second bearing supports 38, 43, and a section of the inner housing 23. Depending on the configuration, a portion of the fan shaft 6 may also define a lubricating housing. Advantageously, the lubricant occupying the lubricating housing 22 is a mist of oil. This lubricating housing facilitates the connection between the motor 65 and the fan shaft 6. Furthermore, the motor 65 is positioned upstream of the reducer 21, with space for mounting the motor upstream of the reducer.

[0076] Bearing support 38 includes a generally cylindrical first section 66, to which is fixed an outer ring 37 of guide bearing 35, which guides the rotation of fan shaft 6. Bearing support 38 includes a generally frustoconical second section 67, which is connected on one hand to first section 66 and on the other hand to a fixed structure 68 of the turbine engine. First section 66 extends radially inward from second section 67. First section 66 and second section 67 are integral.

[0077] Reference Figure 4 7, the bearing support 38 includes a housing 69 for accommodating or carrying at least a portion of the motor 65. In particular, the second section 67 includes a bottom 70 (see Figure 6 ) groove 47, with a bottom portion 70 disposed upstream of bearing support 38. Bottom portion 70 is defined in a plane perpendicular or substantially perpendicular to longitudinal axis X. Bottom portion 70 is extended downstream by a substantially cylindrical skirt portion 71 having an axis parallel to the longitudinal axis. Skirt portion 71 defines a through cavity 72 that opens at bottom portion 70 of groove 47 (upstream of second section 67). In other words, bottom portion 70 includes a first opening having an axis parallel to the longitudinal axis, and a free end portion 73 of skirt portion 71 defines a second opening, through which cavity 72 also opens downstream.

[0078] The rotor 74 is (indirectly) connected to the fan shaft 6 so as to rotate relative to a stator 75 mounted on a fixed element about an axis of rotation A parallel to the longitudinal axis X. The connection between the rotor 74 and the fan shaft 6 is achieved by a motion output mechanism 76 that enables motion to be transmitted from the fan shaft 6 to the motor 65. In other words, the motion output mechanism is (kinematically) arranged between the rotor of the motor and the fan shaft. The motor 65 also includes a base (or bracket) 77 that supports at least the rotor 74, the stator 75, or the motion output mechanism 76.

[0079] As in Figure 4As can be seen in the figure, the base 77 comprises a base plate 78 from which extends a generally cylindrical annular wall 79. The annular wall 79 extends axially within the skirt 71 of the bearing support 38 (or the housing 69). On the upstream side of the bearing support 38, the base 77 is attached to the bottom 70 of the housing 69 by means of attachment members. The attachment members are of the type of screws, nuts, or any other type that enables quick removal and / or installation without damaging the motor 65. Advantageously, the stator 75 is arranged on the radially inner surface of the annular wall 79. The bottom 70, the skirt 71, and the base 77 form the housing 69 of the motor 65.

[0080] The motion output mechanism 76 of the motor 65 includes a drive shaft 80 having an axis of rotation A (parallel to the longitudinal axis X and coaxial with the rotor axis), which is driven in rotation by the fan shaft 6. The drive shaft 80 is supported by a central finger 81, which is fixed to the base plate 78 and coaxial with the drive shaft's axis of rotation A. The drive shaft 80 is hollow, with the finger 81 extending into the drive shaft. Guide bearings, referred to as the first rotor bearing 82 and the second rotor bearing 83, enable the drive shaft 80 to be guided relative to the base 77 (more specifically, the finger 81). The drive shaft 80 is mounted so as to be rotationally free about the axis of rotation A.

[0081] The motion output mechanism 76 includes a gear 84 coupled at one end to the drive shaft 80. The gear 84 is coaxial with the axis of rotation A of the drive shaft 80. The gear 84 is arranged downstream of the free end 73 of the skirt 71 of the housing and also downstream of the annular wall 79. The gear 84 is adapted to mesh with a toothed ring gear 85 that is rotationally fixed to the fan shaft 6. It is understood that the motion output mechanism includes a gear train.

[0082] This configuration of the motion output mechanism enhances the modularity of the motor and the motion output, as well as the ease of removal and installation upstream of the turbine engine for possible maintenance operations. The space upstream of the speed reducer enables the integration of the motion output mechanism.

[0083] To this end, the fan shaft 6 includes a protruding element 86 that extends axially from the wall of the fan shaft 6, to which the toothed ring gear 85 is attached. In particular, the toothed ring gear 85 is retracted onto the fan shaft 6, and an axial pin (not shown) enables the toothed ring gear 85 to be held in place. In an alternative configuration (not shown), the toothed ring gear is integral with the fan shaft 6. The toothed ring gear 85 is coaxial with the fan shaft 6 (i.e., the longitudinal axis X).

[0084] In this embodiment, the drive shaft 80 is integral with the gear 84. The rotor 74 is mounted on the drive shaft 80 so that when the fan shaft 6 rotates, the rotor 74 also rotates relative to the stator 75. Here, the stator 75 of the motor 65 extends around the rotor 74 of the motor 65.

[0085] The first rotor bearing 82 is arranged upstream of the rotor 74, and the second rotor bearing 83 is arranged downstream of the rotor 74. Each of the first rotor bearing 82 and the second rotor bearing 83 includes a first ring fixed to the drive shaft 80 and a second ring fixed to the fixed element. Figure 4 In this case, the first ring is outer ring 87, and the second ring is inner ring 88, which is attached to base 77 (specifically finger 81) of motor 65. The first and second bearings of rotors 82 and 83 are rolling bearings. The first and second bearings also have the same diameter. Alternatively, the diameters may be different. The rolling elements of the first and second bearings, respectively, include balls or rollers.

[0086] Figure 5 Another embodiment of a motor 65 is shown. Reference numerals are retained for identical or substantially identical elements and / or elements having the same function. In this exemplary embodiment, a stator 75 is mounted on a bearing support 38, and a rotor 74 is mounted on a drive shaft 80 of the motor. Drive shaft 80 is freely rotatable about an axis of rotation A relative to a base 77 of the motor 65 by means of at least one rotating guide bearing. Axis of rotation A is substantially parallel to the longitudinal axis X. A proximal end 90 of the drive shaft can be rotationally guided by a first rotor bearing 82 in a receiving chamber 92 of the base 77, while a distal end 91 of the drive shaft is coupled to a gear 84.

[0087] In particular, in this embodiment, the drive shaft 80 includes a first section 93 and a second section 94 that are rotationally fixed. The first section 93 carries the proximal end 90, and the second section 94 carries the distal end 91. The first section 93 includes splines 95 on its radially outer surface (toward its free end 97), and the splines 95 engage with corresponding splines formed on the radially inner surface of the second section 94. In this way, the first section 93 and the second section 94 of the drive shaft 80 are rotationally fixed. The receiving chamber 92 is delimited by an annular diaphragm 96, the axis of which is coaxial with the axis of rotation A of the drive shaft 80, and the annular diaphragm is fixed to the base plate 78. The annular diaphragm 96 extends upward from the inner surface of the base plate 78.

[0088] First rotor bearing 82, arranged upstream of rotor 74, includes a first ring (here, inner ring 88) fixed to drive shaft 80 and a second ring (here, outer ring 87) fixed to the wall of annular partition 96. A free end 97 of first section 93 extends within second section 94. Second rotor bearing 83 is arranged axially downstream of rotor 74 and radially between second section 94 of drive shaft 80 and bearing support 38. The first ring (here, inner ring 88) of second rotor bearing 83 is integral with drive shaft 80, while the second ring (here, outer ring 87) is fixed to bearing support 38. Specifically, stator 75 is mounted on an annular skirt 71 of the bearing support housing. The free end of skirt 71 includes an annular neck 98 that carries outer ring 87 of second rotor bearing 83. In this exemplary embodiment, second rotor bearing 83 has a larger diameter than first rotor bearing 82.

[0089] As in Figure 5 As can be seen in FIG, gear 84 is coupled to second section 94 of drive shaft 80. As in the first embodiment, gear 84 meshes with a toothed ring gear 85 attached to (or integral with) a protruding element 86 of fan shaft 6. Gear 84 is axially arranged between inner ring 88 of second rotor bearing 83 and attachment element 99 (in this case, a nut) to retain gear 84 on second section 94 of drive shaft 80.

[0090] Reference Figure 6 The motor 65 includes at least one cable 100 for transmitting power to the auxiliary pump 61. The cable 100 extends outside the lubricating housing 22, which prevents the cable from coming into contact with the oil bath environment. The cable 100 is advantageously connected (directly or indirectly) to the stator 75 and passes through a hole 101 (e.g., Figure 5 ). The hole 101 has an axis B parallel to the longitudinal axis X. On the other hand, the cable 100 is connected to the electric motor 65 .

[0091] The motor 65 is constructed to facilitate its installation and removal. During the installation or assembly of a module of a turbine engine, in particular a fan module, the reducer 21 is first assembled with its various components by sliding it from upstream to downstream, so that the sun gear 30 is coupled to the low-pressure shaft 15. The fan shaft 6 is connected to the fan shaft 6 by means of an attachment member 103 (e.g. Figure 2 Attached to the radial flange 102 of the ring gear 33 (as shown) Figure 2As shown). These attachment members may include screws, nuts, bolts, studs or other suitable elements to facilitate disassembly and / or installation. The bearing 35 (and its inner and outer rings) are mounted on the fan shaft 6. The bearing 40 (and its inner and outer rings) are also mounted on the fan shaft 6 (advantageously after the bearing 35 is installed). Prior to this, the bearing 35 is mounted on the first bearing bracket 38. The first bearing bracket is then attached to the fixed structure of the turbine engine. The bearing 35 is then tightened to the fan shaft 6, for example using a nut. The first bearing bracket 38 and the second bearing bracket 43 are attached together. Similarly, the bearing 40 is mounted on the second bearing bracket 43 before the second bearing bracket 43 is attached to the first bearing bracket 38.

[0092] The motor 65 (and its rotor 74, stator 75, drive shaft 80, bearings 82, 83, etc.) is assembled and then arranged in the housing 69 (formed in the bearing bracket 38). More specifically, the rotor 74 is mounted on the drive shaft 80 on the base 77. The stator 75 is mounted on a fixed element that at least partially supports the motor, or is mounted on the base 77 (specifically the annular wall 79) of the housing of the motor 65 ( Figure 2 and Figure 4 embodiment), or mounted on the wall of the motor housing (specifically the cylindrical skirt 71 of the first bearing bracket 38) ( Figure 5 embodiment).

[0093] Advantageously, before the motor 65 with the gear 84 is inserted into the housing 69, a toothed ring gear 85 is attached to the fan shaft 6. The base 77 is then attached to the first support 38 so that the rotor 74 and the stator 75 are arranged in the housing 69 of the first bearing support 38, which is open in the lubrication housing 22. Thus, when the lubrication housing is engaged in the housing 69, the gear 84 (carried by the drive shaft 80) meshes with the toothed ring gear 85. The base plate 78 of the base 77 is screwed onto the bottom 70 of the housing 69.

[0094] Disassembly is achieved by reversing these steps.

[0095] The cable 100 is connected to the motor 65 and the auxiliary pump 61 .

[0096] The disk 5 is then inserted upstream of the inner shroud to attach it to the fan shaft 6. Finally, the inlet cone 24 is mounted on the inner shroud to close the fan module.

[0097] exist Figure 5Within the scope of the illustrated embodiment, after the fan shaft 6 is installed, at least a portion of the motion output mechanism 76 is installed on the fan shaft 6. In particular, a toothed ring gear 85 is installed on the fan shaft 6 and attached to the fan shaft. As described above, the toothed ring gear 85 can be made integrally with the fan shaft 6. The gear 84 (previously attached to the second section 94 of the drive shaft 80) is arranged to mesh with the toothed ring gear 85. The second rotor bearing 83 (and its inner and outer rings) is also fixed to the second section 94 of the drive shaft 80. The first bearing support 38 and the second bearing support 43 are installed in the turbine engine together with their respective bearings 35, 40. The motor 65 is assembled and arranged in the housing 69 of the motor 65. In particular, the rotor 74 is mounted on the drive shaft 80 on the base 77, and the stator 75 is mounted on the housing of the motor (specifically, on the cylindrical skirt 71 of the first bearing support 38). Next, first section 93 of drive shaft 80, with rotor 74 and first rotor bearing 82 (inner and outer rings) mounted thereon, is inserted into the housing of the bearing bracket from upstream to downstream. During this insertion, the splines of first section 93 of drive shaft 80 slidably engage with the corresponding splines of second section 94 of drive shaft 80. The base plate 78 of bracket 7 is then screwed onto the bottom 70 of the housing.

[0098] according to Figure 5 In this embodiment, when disassembling the motion output mechanism 76, the toothed ring gear 85, gear 84, bearing 83 (and its inner and outer rings), nut 99, and second section 94 of the drive shaft 80 remain permanently attached to the fan shaft 6. By disconnecting the first section 93 from the second section 94 of the fan shaft 6 via the splines, the base plate 78, bearing 82 (and its inner and outer rings), and rotor 74 are simultaneously disassembled. The stator 75 can then also be removed. The bearing brackets 38 and 43 are then disassembled along with the fan shaft 6.

Claims

1. A turbine engine module, comprising: - Lubricate the housing (22), - a first bearing support (38), a fan shaft (6) guided in rotation about a longitudinal axis X by at least one first guide bearing (35) mounted on a first bearing support (38) attached to a fixed structure (68) of the turbine engine, - a power shaft (15) which drives the fan shaft (6) in rotation via a speed reducer (21) arranged in a lubricating housing (22), a lubrication system (50) for at least the reducer (21), comprising a closed primary circuit (51) for supplying the lubricated housing (22) and a closed auxiliary circuit (60) for supplying the lubricated housing when the primary circuit is inactive, the auxiliary circuit (60) comprising at least one auxiliary pump (61) driven by an electric motor (63), an electric motor (65) configured to power the electric motor (63) of the auxiliary pump (61), the electric motor being carried at least partially by the first bearing support (38) and comprising: a rotor (74) connected to the fan shaft (6) so as to be driven in rotation about an axis of rotation A parallel to the longitudinal axis X; a stator (75) mounted on a fixed element (38, 69, 77) at least partially supporting the electric motor (65), and a motion output mechanism (76) configured to connect the rotor of the motor to the fan shaft and to transfer motion from the fan shaft to the rotor (74), Characterized in that the motion output mechanism (76) includes a gear (84) and a drive shaft (80), the drive shaft being mounted to freely rotate about the rotation axis A, the rotor (74) being mounted on the drive shaft, the drive shaft (80) being coupled to the gear (84) for engaging with a toothed ring gear (85) fixed to the fan shaft (6), and the drive shaft being configured so that when the fan shaft is driven to rotate under any free rotation condition to drive the rotor of the motor that powers the auxiliary pump, it is driven to rotate by the fan shaft.

2. The turbine engine module according to claim 1, characterized in that The drive shaft (80) is guided in rotation by a first rotor bearing (82), which comprises a first ring fixed to the drive shaft (80) and a second ring fixed to the fixing element (38, 69, 77), and the first rotor bearing (82) is arranged upstream of the rotor of the electric motor (65).

3. The turbine engine module according to claim 1 or 2, characterized in that: The drive shaft (80) is guided in rotation by a second rotor bearing (83), which includes a first ring fixed to the drive shaft (80) and a second ring fixed to the fixed element (38, 69, 77), and the second rotor bearing (83) is arranged downstream of the rotor (74) of the electric motor (65).

4. The turbine engine module according to claim 1 or 2, characterized in that: The electric motor (65) is arranged upstream of the reducer (21) relative to the longitudinal axis X and is at least partially arranged in the lubricating housing (22).

5. The turbine engine module according to claim 1 or 2, characterized in that: The motor (65) is housed in a housing (69) formed in the first bearing bracket (38).

6. The turbine engine module according to claim 1 or 2, characterized in that: The fixing element (38, 69, 77) is a base (77) of the motor (65) mounted on the first bearing bracket (38), or the fixing element (38, 69, 77) is the first bearing bracket (38).

7. The turbine engine module according to claim 1 or 2, characterized in that: The drive shaft (80) is integral with the gear (84).

8. The turbine engine module according to claim 1 or 2, characterized in that: The stator (75) of the electric motor (65) extends around the rotor (74) of the electric motor (65).

9. The turbine engine module according to claim 1 or 2, characterized in that: The motor (65) and the electric motor (63) are connected to a cable (100), and the cable (100) circulates outside the lubricating housing (22).

10. The turbine engine module according to claim 1 or 2, characterized in that: The motion output mechanism includes a gear train.

11. The turbine engine module according to claim 1 or 2, characterized in that: The auxiliary pump is mounted outside the lubrication housing.

12. The turbine engine module according to claim 5, characterized in that The first bearing support (38) comprises a first, substantially cylindrical portion (66) to which the outer ring (37) of the rotating guide bearing (35) of the fan shaft (6) is fixed, and a second, substantially truncated cylindrical portion (67) connected on the one hand to the first portion (66) and on the other hand to a fixed structure (68) of the turbine engine.

13. The turbine engine module according to claim 1 or 2, characterized in that: The auxiliary pump (61) is connected to the auxiliary oil tank (62) on one hand and to the lubrication housing (22) on the other hand.

14. The turbine engine module according to claim 13, characterized in that The auxiliary pump (61) is arranged upstream of the lubricating housing (22) along the flow direction of the lubricant in the auxiliary circuit (60). The auxiliary oil tank (62) is an oil accumulation area for recovering oil and is located at the bottom of the lubricating housing (22).

15. The turbine engine module according to claim 13, characterized in that The lubrication system (50) includes: a valve (49) configured to occupy an open position or a closed position and located between the main circuit (51) and the auxiliary circuit (60); and the lubrication housing (22), the valve (49) including a first inlet hole connected to the auxiliary circuit (60), a second inlet hole connected to the main circuit (51), a blocking element for blocking one of the first inlet hole and the second inlet hole according to the pressure in the main circuit (51) and the auxiliary circuit (60), and an outlet hole connected to the lubrication housing (22), the auxiliary circuit (60) and the main circuit (51) being connected to the bottom of the auxiliary oil tank (62).

16. The turbine engine module according to claim 1 or 2, characterized in that: The main circuit (51) includes a main pump (53) in communication with an electronic control unit (58) connected to a relay housing (48) configured to allow or disable power to an electric motor (63) of the auxiliary pump (61), the relay cooperating with at least one valve (49).

17. Aircraft turbine engine (1) comprising a turbine engine module according to any one of claims 1 to 16.

18. Method for assembling a turbine engine module according to any one of claims 1 to 16, characterized in that The method comprises the following steps: - Mounting the toothed ring gear (85) on the fan shaft (6), - assembling the electric motor (65) by mounting the rotor (74) on the drive shaft (80) and the stator (75) on the at least partially supporting fixing element (38, 77), - attaching the base of the electric motor (65) to the first bearing support (38) such that the rotor and the stator are arranged in a housing of the first bearing support (38) which is open in the lubrication housing (22), and - Connecting a cable (100) to the motor (65) and an auxiliary pump (61) mounted outside the lubrication housing (22).

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