FR3137131A1 - TURBOMACHINE MODULE EQUIPPED WITH A FLUIDIC CONNECTION - Google Patents

Abstract

Turbomachine module comprising a fan comprising variable pitch blades, a speed reducer, a system for changing the pitch of the blades, arranged upstream of the reducer and comprising a fluidic actuator, a fluid transfer device (94) upstream of the reducer and configured to supply fluid to the actuator, a fluid supply circuit (90) of which part passes through the reducer and is connected to the transfer device, the module comprising at least one fluid connection (100) from the circuit to the device transfer device, with an elongated shape along an elongation axis (Y) and comprising: - a first tip (101) mounted in a first housing (103) of the transfer device, and - a second tip (102) mounted in a second housing (104) of the circuit, and at least one of the ends being able to slide inside the corresponding housing, or opposite the other of the ends. Figure for abstract: Figure 4

Description

TURBOMACHINE MODULE EQUIPPED WITH A FLUIDIC CONNECTION Technical field of the invention

The present invention relates to the field of aircraft turbomachines, and in particular a turbomachine module comprising variable pitch blades, a system for changing the pitch of the blades, a speed reducer, a device for transferring fluid to the system of changing the pitch of the blades, a fluid supply circuit to the fluid transfer device and a fluid connection connecting the circuit to the transfer device. The invention also relates to a turbomachine comprising such a module.

Technology background

Conventionally, a turbomachine includes a gas generator upstream of which a fan is mounted. The gas generator typically comprises from upstream to downstream, with reference to the gas flow, a low pressure compressor, a high pressure compressor, a combustion chamber, a high pressure turbine and a low pressure turbine. The rotors of the low pressure compressor and the low pressure turbine are mechanically connected by a low pressure shaft so as to form a low pressure body. The body of the high pressure compressor and the high pressure turbine are mechanically connected by a high pressure shaft so as to form a high pressure body. The high pressure shaft is tubular and extends around the low pressure shaft, the high pressure shaft and the low pressure shaft being coaxial. The turbomachine also includes several casings which are fixed elements, that is to say stator elements, as opposed to the rotor elements which are movable in rotation. A turbomachine casing essentially comprises two coaxial annular envelopes, respectively internal and external, and profiled arms which extend between the envelopes and connect them together. The envelopes define between them an annular flow vein for a flow of air which flows around the arms. This type of casing can be located between two compressors of the turbomachine, and is then called inter-compressor casing or intermediate casing. This type of casing can also be located downstream of the turbomachine turbines and is then called exhaust casing.

The blower is rotated by a power transmission shaft through a power transmission mechanism. This power transmission shaft can for example be the low-pressure shaft and the transmission mechanism a speed reducer of the epicyclic or planetary type.

The fan is equipped with blades with variable pitch or pitch, allowing the pitch or orientation of the blades of the blades to be adjusted according to the flight parameters so as to optimize the operation of the fan. Each blade can thus be positioned around a alignment axis which is substantially radial to the longitudinal axis of the turbomachine. This configuration makes it possible to optimize the module in which such a blower is integrated.

Currently, the pitch change of the fan blades is carried out using a pitch change system, located upstream of the speed reducer. This system includes an actuator which is connected on the one hand to a fan shaft which is coupled to the speed reducer and on the other hand to a connecting mechanism coupled to the variable pitch blades. The actuator is located in a rotating frame of the turbomachine and is a linear or rotary actuator, that is to say that it generally comprises a mobile body which, by moving, acts on the position of the blades of the variable pitch blades.

The actuator is further a hydraulic actuator which is supplied with fluid via a fluid transfer device, also located upstream of the speed reducer. The fluid transfer device includes a fixed part and a movable part. Its mobile part is mechanically and hydraulically connected to the actuator. The fixed part of the fluid transfer device is hydraulically connected to a fluid supply circuit, the fluid supply source of which is arranged in a fixed reference of the turbomachine, and mechanically to a fixed stator element such as the carrier -satellite of the speed reducer or an intermediate casing arm for example. The fluid transfer device allows the passage from a fixed reference to a rotating reference and is typically arranged upstream of the speed reducer.

The mechanical connections of the fluid transfer device make the system hyperstatic, that is, there are more connections than necessary to hold the fluid transfer device. This can cause constraints, in particular due to vibrations in operation or positioning faults of the connections to the interfaces of the fluid transfer device, which can lead to breakage.

In order to reduce these constraints, it is known that the connections can accommodate different movements, whether in translation or rotation. One possibility is therefore to influence the hydraulic connections by using, for example, flexible pipes. These pipes can be made of polymer, which gives them great flexibility. However, the environmental parameters of the turbomachine in terms of pressure or temperature accelerate the aging of these polymer pipes, their lifespan is therefore limited. An alternative lies in the use of metal pipes. However, bending these metal pipes can be difficult, especially when the pipes have sections with a large diameter. In addition, these metal pipes retain a certain rigidity which can cause assembly difficulties and residual stresses.

Also, an objective of the invention is therefore to propose an improved turbomachine module not having, at least, one of the aforementioned drawbacks.

Another objective of the invention is to propose a turbomachine module whose hyperstatism of the fluid transfer device is limited so as to reduce the forces transmitted and to facilitate the manufacturing and assembly processes.

• une soufflante centrée sur l’axe longitudinal et reliée à un arbre de soufflante, cette soufflante comprenant une pluralité d’aubes de soufflante à calage variable,
• un réducteur de vitesse comprenant un solaire centré sur l’axe longitudinal, une couronne s’étendant autour de cet axe longitudinal et reliée à l’arbre de soufflante, et des satellites qui sont engrenés avec le solaire et la couronne, le réducteur comprenant en outre un porte-satellites qui supporte les satellites et qui est fixé à un stator du module,
• un système de changement de pas des aubes de soufflante, ce système étant agencé axialement en amont du réducteur de vitesse et comportant un actionneur fluidique solidaire en rotation de la soufflante,
• un dispositif de transfert de fluide agencé axialement en amont du réducteur de vitesse et configuré pour alimenter en fluide l’actionneur,
• un circuit d’amenée de fluide solidaire d’un stator du module et comprenant une partie qui traverse axialement le réducteur de vitesse et qui est reliée au dispositif de transfert de fluide,

caractérisé en ce qu’il comprend au moins un raccord fluidique du circuit au dispositif de transfert de fluide, ce raccord fluidique ayant une forme générale allongée le long d’un axe d’allongement et comprenant :

• un premier embout comprenant une extrémité sphérique montée rotulante dans un premier logement du dispositif de transfert de fluide, et
• un second embout comprenant une extrémité sphérique montée rotulante dans un second logement du circuit,

au moins l’un des embouts étant apte à coulisser axialement le long de l’axe d’allongement à l’intérieur du logement correspondant, ou vis-à-vis de l’autre des embouts.A turbomachine module is therefore proposed extending along a longitudinal axis, comprising:

• a fan centered on the longitudinal axis and connected to a fan shaft, this fan comprising a plurality of fan blades with variable pitch,
• a speed reducer comprising a sun centered on the longitudinal axis, a ring extending around this longitudinal axis and connected to the fan shaft, and satellites which are meshed with the sun and the ring, the reducer comprising in in addition to a satellite carrier which supports the satellites and which is fixed to a stator of the module,
• a system for changing the pitch of the fan blades, this system being arranged axially upstream of the speed reducer and comprising a fluidic actuator integral in rotation with the fan,
• a fluid transfer device arranged axially upstream of the speed reducer and configured to supply fluid to the actuator,
• a fluid supply circuit integral with a stator of the module and comprising a part which passes axially through the speed reducer and which is connected to the fluid transfer device,

characterized in that it comprises at least one fluid connection from the circuit to the fluid transfer device, this fluid connection having a generally elongated shape along an axis of elongation and comprising:

• a first end piece comprising a spherical end rotatably mounted in a first housing of the fluid transfer device, and
• a second end piece comprising a spherical end rotatably mounted in a second housing of the circuit,

at least one of the ends being able to slide axially along the axis of elongation inside the corresponding housing, or opposite the other of the ends.

Thus, thanks to the invention, a connection is ensured between two stator elements, and in particular between a fixed part of the fluid transfer device, which also comprises a mobile part, and the fluid supply circuit which, in turn, , is arranged in a fixed reference of the turbomachine module. In addition, the connection according to the invention allows a reduction in the forces transmitted to the fluid transfer device. Indeed, the fluid connection, having at least one of its ends capable of sliding inside a housing of the fluid transfer device or of the fluid supply circuit, or vis-à-vis the other tips, allows accommodation of the connection between the transfer device and the circuit to different movements. In this way, hyperstatism of the fluid transfer device can be limited or even avoided, which reduces the risk of cracks or rupture.

• les embouts sont solidaires axialement l’un de l’autre et un seul des embouts est monté coulissant axialement dans le logement correspondant ;
• le module comprend un système d’anti-rotation du raccord fluidique autour de l’axe d’allongement vis-à-vis du circuit ou du dispositif de transfert de fluide, ce système d’anti-rotation étant par exemple du type à pige ;
• les embouts sont engagés l’un dans l’autre par une liaison glissière ou télescopique ;
• l’un des embouts comprend une partie mâle engagée dans une partie femelle de l’autre des embouts, les parties mâle et femelle comportant un système d’anti-rotation des embouts l’un par rapport à l’autre vis-à-vis de l’axe d’allongement, ce système d’anti-rotation étant par exemple de type à cannelures ;
• les embouts comprennent un canal interne central et/ou des canaux internes périphériques, le ou les canaux débouchant axialement aux deux extrémités axiales du raccord fluidique et étant en communication fluidique avec des passages internes débouchant dans les logements ;
• les embouts portent des joints annulaires s’étendant autour de l’axe d’allongement et coopérant avec des surfaces annulaires des logements ;
• au moins l’un des premier et second logements comprend une cavité sphérique qui est définie par deux demi-coquilles, une première de ces demi-coquilles comportant une bride annulaire de fixation qui s’étend radialement vers l’extérieur par rapport à l’axe d’allongement et qui est intercalée axialement entre une bride annulaire d’une seconde des demi-coquilles et une bride annulaire du circuit ou du dispositif de transfert de fluide ;
• le circuit comprend au moins un conduit qui traverse axialement le porte-satellites du réducteur de vitesse, et en particulier qui traverse axialement un des paliers de guidage des satellites ;
• en aval du réducteur de vitesse, l’au moins un conduit s’étend en direction radiale par rapport à l’axe longitudinal et traverse intérieurement un bras tubulaire du module ;
• l’axe d’allongement est orienté radialement par rapport à l’axe longitudinal.

The module, according to the invention, may include one or more of the characteristics below, taken in isolation from each other or in combination with each other:

• the end pieces are axially secured to each other and only one of the ends is mounted sliding axially in the corresponding housing;
• the module comprises a system for anti-rotation of the fluid connection around the axis of elongation with respect to the circuit or the fluid transfer device, this anti-rotation system being for example of the pin type ;
• the ends are engaged one into the other by a sliding or telescopic connection;
• one of the tips comprises a male part engaged in a female part of the other of the tips, the male and female parts comprising a system for anti-rotation of the tips one relative to the other opposite of the extension axis, this anti-rotation system being for example of the spline type;
• the end pieces comprise a central internal channel and/or peripheral internal channels, the channel(s) opening axially at the two axial ends of the fluid connection and being in fluid communication with internal passages opening into the housings;
• the end pieces carry annular seals extending around the axis of elongation and cooperating with annular surfaces of the housings;
• at least one of the first and second housings comprises a spherical cavity which is defined by two half-shells, a first of these half-shells comprising an annular fixing flange which extends radially outwards relative to the elongation axis and which is interposed axially between an annular flange of a second of the half-shells and an annular flange of the circuit or fluid transfer device;
• the circuit comprises at least one conduit which passes axially through the planet carrier of the speed reducer, and in particular which passes axially through one of the satellite guide bearings;
• downstream of the speed reducer, the at least one conduit extends in the radial direction relative to the longitudinal axis and internally passes through a tubular arm of the module;
• the axis of elongation is oriented radially relative to the longitudinal axis.

The invention also relates to an aircraft turbomachine comprising at least one turbomachine module as described above.

Brief description of the figures

The invention will be better understood with the help of the description which follows, given solely by way of example and made with reference to the appended drawings in which:

There represents a schematic view, in axial and partial section, of an example of a turbomachine with a ducted fan to which the invention applies,

There represents a schematic view, in axial section of the speed reducer according to the invention,

There represents a schematic view, in partial axial section, of an example of a fan module with a blade pitch change system and a fluid transfer device cooperating with the pitch change system,

There represents a schematic view, in axial section, of an embodiment of the fluid connection of the turbomachine module according to the invention, in particular when the connection comprises end pieces secured to each other and one of the ends is able to slide into a corresponding housing,

There represents a schematic view, in axial section, of an anti-rotation system of the fluid connection of the module according to the invention around the axis of elongation with respect to the fluid supply circuit or the device fluid transfer,

There represents a schematic view, in axial section, of another embodiment of the fluid connection of the turbomachine module according to the invention, in particular when the connection comprises end pieces sliding axially relative to each other, and

There represents a schematic view, in axial and partial section, of another embodiment of the fluid connection of the turbomachine module according to the invention, in particular when the connection comprises end pieces sliding axially relative to each other and of which at least one of the ends is mounted in a spherical cavity formed by half-shells.

Detailed description of the invention

In the present invention, and in general, the terms “upstream” and “downstream” are defined in relation to the circulation of gases in the turbomachine.

To facilitate its manufacture and its assembly/assembly/disassembly, a turbomachine is generally modular, that is to say it includes several modules which are manufactured independently of each other and which are then assembled together. The modularity of a turbomachine also facilitates its maintenance. In the present application, we mean by “turbine machine module”, a module which includes in particular a fan and a fan shaft for driving the fan. For convenience, it will be understood in what follows that the use of the term “turbomachine” refers to a turbomachine module.

In what follows, reference is made to Figures 1 to 3. We are first interested in the which represents a turbomachine 1 to which the invention applies. The turbomachine 1 has a longitudinal axis combustion chamber 6, a high pressure turbine 7 and a low pressure turbine 8. The rotors of the low pressure compressor 4 and the low pressure turbine 8 are mechanically connected by a low pressure shaft 9 so as to form a low pressure body. The body of the high pressure compressor 5 and the high pressure turbine 7 are mechanically connected by a high pressure shaft 10 so as to form a high pressure body. The high pressure body is guided in rotation around the longitudinal axis X by a first bearing 11 with bearings upstream and a second bearing 12 with bearings downstream. The first bearing 11 is mounted radially between an inter-compressor or intermediate casing 13 and an upstream end of the high pressure shaft 10. The intermediate casing 13 is arranged axially between the low and high pressure compressors 4, 5. The second bearing 12 is mounted radially between an inter-turbine casing 14 and a downstream end of the high pressure shaft 10. The inter-turbine casing 14 is arranged axially between the low and high pressure turbines 7, 8. The low pressure body is guided in rotation around the longitudinal axis X via a third bearing 15 with bearings and a fourth preferably double bearing 16 with bearings. The latter are mounted radially between an exhaust casing 17 and a downstream end of the low pressure shaft 9. The exhaust casing 17 is located downstream of the low pressure turbine 8. The third bearing 15 is mounted radially between a inlet casing 18 and an upstream end of the low pressure shaft 9. The high pressure shaft 10 is tubular and extends around the low pressure shaft 9, the high pressure shaft and the low pressure shaft being coaxial.

The fan 3 shown is enclosed by a fan casing 19 which carries a nacelle 20. The fan casing 19 is connected to the gas generator 2 by profiled arms 28 which extend radially.

The fan 3 compresses a flow of air which enters the turbomachine by dividing into a primary air flow F1 and a secondary air flow F2 at the level of a separation nozzle 21. The latter is carried by the casing inlet 18 centered on the longitudinal axis of gas 2 and escapes through a primary nozzle 24. The secondary air flow F2 circulates in a secondary stream 25 and escapes through a secondary nozzle 26. The primary stream 23 and the secondary stream 25 are separated by the inter-vein housing 22.

The fan 3 comprises a series of fan blades 30 extending radially around a fan rotor 31. The fan blades 30 have variable pitch, that is to say that each blade of the fan blades can pivot around a pitching axis substantially radial to the longitudinal axis

The fan rotor 31 is crossed by a cylindrical fan shaft 32, centered on the longitudinal axis X. The fan shaft 32 drives the fan rotor 31 in rotation around the longitudinal axis blower 32 is itself driven in rotation by a power transmission shaft of longitudinal axis X via a power transmission mechanism 33. In the present example, the power transmission shaft is the low pressure shaft 9. The fan shaft 32 and the low pressure shaft 9 are coaxial. Alternatively, the power shaft is a power turbine shaft supplied with gas by the gas generator 2.

The power transmission mechanism 33 is a speed reducer 34, as shown in the figure. . The speed reducer 34 makes it possible to reduce the rotational speed of the fan shaft 32 relative to the speed of the low pressure shaft 9. On the other hand, the speed reducer 34 allows the arrangement of a fan with a large diameter so as to increase the dilution rate.

The reduction gear 34 is of the planetary gear train type. The speed reducer 34 is connected to the fan shaft 32. Typically, the speed reducer 34 comprises a solar 36, satellites 37, a planet carrier 38 and an outer ring 39. In the present example, the solar 36 is centered on the longitudinal axis X and is coupled in rotation with the power shaft (here the low pressure shaft 9) along the longitudinal axis of an axis substantially parallel to the longitudinal axis in rotation using a guide bearing 40, mounted on the planet carrier 38. There are as many bearings 40 as there are planets 37.

The outer crown 39 is coupled in rotation with the fan shaft 32, in particular via a crown holder 41. The crown 39 is centered on the longitudinal axis the input of the speed reducer 34 while the outer ring 39 forms the output thereof. The planet carrier 38 supports the satellites 37 and is, however, fixed relative to the crown 39. The planet carrier 38 is in particular fixed to a fixed structure or stator of the module such as the inlet casing 18 or the intermediate casing 13 .

The different elements of the speed reducer 34 described previously, and in particular their teeth, are lubricated by oil conveyed into the speed reducer 34 via a distributor 42. The arrows of the describe in particular the routing of the oil in the reducer 34.

With reference to Figures 1 and 3, the timing of the fan blades 30 is carried out using a pitch change system 50 installed in the fan rotor 31. The pitch change system 50 is arranged in particular upstream of the reducer 34 of speed. The pitch change system 50 comprises a fluidic actuator 52 intended to act on the blades of the fan 30. The pitch change system 50 also comprises a connecting mechanism 51 connected to the fan blades 30 and to the fluidic actuator 52 .

The fluidic actuator 52 is arranged upstream of the speed reducer 34 and comprises an annular body 53 and a movable body 54 which moves relative to the annular body 53. Advantageously, but not limited to, the actuator 52 is a linear actuator ( linear cylinder) with an axis coaxial with the longitudinal axis X. Alternatively, the actuator is of the rotary type (rotary cylinder) along the longitudinal axis fan shaft 32. The movable body 54 moves mainly in translation along the longitudinal axis The annular body 53 is therefore rotating but not translating. Alternatively, the mobile body 54 moves only in translation.

The movable body 54 of the fluidic actuator 52 comprises a cylindrical wall 70, annular, which extends along the longitudinal axis sealing and guide segments. The movable body 54 further comprises an annular wall 71 which extends radially inwards from the cylindrical wall 70. The annular wall 71 comes into sealed contact with an external surface of the tubular portion 62b of the first casing 62. In d In other words, the annular wall 71 also comprises a through hole of longitudinal axis 53. The chambers 72a, 72b are arranged between the annular body 53 and the mobile body 54.

The movable body 54 moves along the longitudinal axis 72a, 72b, and on the other hand, radially around the tubular portion 62b.

Still in Figures 1 and 3, the mobile body 54 moves axially under the action of a control of the fluidic actuator 52, and in particular the pressure of a fluid circulating in each chamber 72a, 72b. For this, the pitch change system 50 comprises power supply means ensuring its control and described later in the description. The fluid received in the chambers 72a, 72b is for example a hydraulic fluid under pressure, coming from a fluid supply circuit 90, so that the mobile body 54 occupies at least two positions. The movement of the movable body 54 along the longitudinal axis

The turbomachine includes a fluid transfer device 94, between a stator and a rotor. This device 94 is arranged axially upstream of the speed reducer 34 and is configured to supply fluid to the fluidic actuator 52. The actuator 52 being located in a rotating mark, the fluid transfer device 94 or fluid transfer bearing allows the transfer of fluid from the fixed mark to the rotating mark of the turbomachine 1. This transfer device 94 is known under the acronym English “OTB” for “ Oil T ransfert Bearing ”. The location, upstream of the reducer 34, of the fluid transfer device 94 is advantageous because it facilitates its disassembly/assembly without intervening on the speed reducer 34.

The fluid transfer device 94 extends inside the fan shaft 32 (which is hollow) so as to reduce the axial and radial bulk. In the example of Figures 1 and 3, the transfer device 94 is arranged inside the actuator 52. The size is advantageously reduced upstream where the actuator 52 is located. The transfer device 94 comprises a stator part 96 and a rotor part 97. One of the stator 96 and rotor 97 parts is engaged in the other, so as to reduce the bulk and form a compact assembly that is easy to assemble and disassemble. The stator part 96 is mounted integrally with a fixed structure of the turbomachine 1.

The turbomachine 1 also comprises a fluid supply circuit 90 making it possible to distribute a lubricating fluid to the various organs and/or equipment which require it such as the fluidic actuator 52 via the fluid transfer device 94 , bearings, etc. The fluid supply circuit 90 comprises a power source 91, a hydraulic pump 92 making it possible to circulate the fluid towards the organs and/or equipment from the power source 91 and a servovalve 93 making it possible to regulate the pressure of the fluid in the actuator 52 following the necessary timing. The servovalve 93 is electrically controlled by an electronic computer 27 of the turbomachine which is known by the acronym “ECU” for “ Electronic Control Unit ”. The power source 91 is arranged in a fixed reference of the turbomachine and generally in the nacelle 20 illustrated on the or in the inter-vein casing 22. The pump 92 and the servovalve 93 are also arranged in the fixed reference of the turbomachine. In other words, the fluid amendment circuit 90 is integral with a stator of the turbomachine, such as the nacelle 20 or the inter-vein casing 22.

The circuit 90 also comprises at least one part 95 which passes axially through the speed reducer 34 and is connected to the servovalve 93. The planetary carrier 38 which is immobile in rotation allows the passage of the circuit 95 through it as well as to the inside the fan shaft 32. Advantageously, the part 95 is a conduit 95a which passes axially through the planet carrier 38, and in particular which passes axially through one of the guide bearings 40 of the satellites 37, as visible on the .

Downstream of the speed reducer 34, at least one conduit 95b of the fluid supply circuit 90 can extend in the radial direction relative to the longitudinal axis X. This conduit can pass internally through a tubular arm 98 of the module.

With reference to Figures 4 to 7, the turbomachine 1 also comprises at least one fluid connection 100 connecting the fluid supply circuit 90 to the fluid transfer device 94. In use, this connection 100 can be located in the delimited area by dotted lines visible on the . This connector 100 has a generally elongated shape along an elongation axis Y. The fluidic connector 100 further comprises a first end piece 101 which comprises a spherical end 102, which is rotatably mounted in a first housing 103 of the transfer device of fluid 94. The fluid connection 100 also includes a second end piece 104 which comprises a spherical end 105 rotatably mounted in a second housing 106 of the circuit 90.

At least one of the end pieces 101, 104 is able to slide axially along the elongation axis Y inside the corresponding housing 103, 106 or opposite the other of the ends 101, 104 This means for example that only the first end piece 101 can slide axially along the elongation axis Y inside the first housing 103 of the fluid transfer device 94 or that only the second end piece 104 can slide axially along the axis of elongation Y inside the second housing 106 of the circuit 90, or while the first and the second end pieces 101, 104 can both slide axially along the axis of elongation Y in their respective housing 103, 106.

Alternatively, not shown, one of the end pieces 101, 104 can slide axially along the elongation axis Y inside the corresponding housing 103, 106 and also slide axially relative to the other of the end pieces 101 , 104.

The first and second end pieces 101, 104 may generally comprise a central internal channel 107, 107' and/or peripheral internal channels 108, 108' used for the passage of the fluid. These peripheral channels 108, 108' are illustrated in particular by Figures 5 and 7. The channel(s) 107, 107', 108, 108' open axially at the two axial ends of the fluid connection 100 and are in fluid communication with internal passages 109 , 110 opening into the corresponding housings 103, 106 of the transfer device 94 and of the circuit 90.

Each end piece 101, 104 can carry annular seals 111, housed in grooves 112 provided on the external surface of each end piece. These seals 111 extend around the axis of elongation Y and can cooperate with internal annular surfaces 113 of the housings 103, 106. These seals 111 make it possible, among other things, to ensure the tightness of the fluid connection 100.

In the particular case of the , the first end piece 101 and the second end piece 104 are axially integral with each other and only one of the ends 101, 104 is mounted sliding axially in the corresponding housing 103, 106. In the present case, only the first end piece 101 is slidably mounted in the first housing 103. Alternatively, not shown, only the second end piece 104 is slidably mounted in the second housing 106.

In reference to the , an anti-rotation system 114 of the fluidic connector 100 advantageously prevents the rotation of the fluidic connector 100 around the elongation axis Y with respect to the circuit 90 or the fluid transfer device 94. This system The anti-rotation can for example be of the pin type 114a. It is understood that this anti-rotation system 114 is housed at least partly in the fluid connection 100 and at the level of the circuit 90 or the fluid transfer device 94. Advantageously, the anti-rotation system 114 comprises a flat 115 at least one of its ends. In the example illustrated by , this flat 115 is located at the end of the anti-rotation system 114 housed at the level of the circuit 90 or the fluid transfer device 94. Alternatively, the flat 115 can be located at the end of the anti-rotation system -rotation 114 housed in the fluid connection 100, or at each of the ends.

Previously, it was mentioned that at least one of the ends 101, 104 is able to slide axially along the axis of elongation Y with respect to the other of the ends 101, 104. This shape of production is illustrated by the example of Figures 5 and 6.

Advantageously, the first and second end pieces 101, 104 are engaged one into the other by a sliding or telescopic connection 130. In this way, the first end piece 101 and the second end piece 104 slide relative to each other axially along the elongation axis Y.

One of the end pieces 101, 104 advantageously comprises a male part 116 engaged in a female part 117 of the other of the ends 101, 104. In the examples of Figures 6 and 7, the male part 116 belongs to the second end piece 104 while the female part 117 belongs to the first end piece 101. The reverse is also possible.

Advantageously, the male part 116 carries annular seals 118 which extend around the axis of elongation Y and which cooperate with internal annular surfaces 119 of the female part. In addition to maintaining sealing, this makes it possible to limit the axial sliding of the male part 116 relative to the female part 117, so that the male part 116 does not disengage from the female part 117.

Advantageously, the male 116 and female 117 parts comprise an anti-rotation system 114' of the end pieces 101, 104 relative to each other with respect to the elongation axis Y. This system the anti-rotation is for example of the spline type 114b, as shown in the . In such a case, the male part 116 comprises an external groove substantially parallel to the elongation axis Y, which cooperates with an internal groove of the female part 117. The anti-rotation system 114', in particular if that -this is of the grooved type, can also ensure sliding limitation. Indeed, the external groove of the male part 116 can be of a dimension, taken in the axis of elongation Y, less than the dimension of the internal groove of the female part 117 so that an axial play is formed between the male part 116 and the female part 117, allowing the two end pieces 101, 104 to slide relative to each other according to this axial play.

With reference to Figures 5 and 7, one of the first and second housings 103, 106 advantageously comprises a spherical cavity which is defined by two half-shells 120, 121. This spherical cavity is further configured to cooperate in an adjusted manner with the spherical end 102 of one of the end pieces 101, 104. A first 120 of these half-shells 120, 121 comprises an annular fixing flange 122 which extends radially outwards relative to the axis of elongation Y. Advantageously, this annular flange 122 for fixing the first half-shell 120 is interposed axially between an annular flange 123 of a second 121 of the half-shells 120, 121 and an annular flange 124 of the circuit 90 or of the device fluid transfer 94. Alternatively, the first half-shell 120 is part of the circuit 90 or the transfer device 94, in which case, the annular flange 122 for fixing the first half-shell 120 is directly fixed to the annular flange 123 of fixing the second half-shell 121.

Advantageously, the elongation axis Y of the fluid connection 100 is oriented radially relative to the longitudinal axis transfer device 94 are also oriented radially with respect to the longitudinal axis

The invention also relates to an aircraft turbomachine comprising at least one turbomachine module as described in the above.

Claims (12)

Turbomachine module (1) extending along a longitudinal axis (X), comprising:

• a fan (3) centered on the longitudinal axis (X) and connected to a fan shaft (32), this fan comprising a plurality of fan blades (30) with variable pitch,
• a speed reducer (34) comprising a solar (36) centered on the longitudinal axis (X), a ring (39) extending around this longitudinal axis and connected to the fan shaft (32), and satellites (37) which are meshed with the solar and the crown, the reduction gear (34) further comprising a satellite carrier (38) which supports the satellites (37) and which is fixed to a stator (18) of the module,
• a system (50) for changing the pitch of the fan blades (30), this system (50) being arranged axially upstream of the speed reducer (34) and comprising a fluidic actuator (52) integral in rotation with the fan (3 ),
• a fluid transfer device (94) arranged axially upstream of the speed reducer (34) and configured to supply fluid to the actuator (52), and
• a fluid supply circuit (90) integral with a stator (20, 22) of the module and comprising a part (95) which axially passes through the speed reducer (34) and which is connected to the fluid transfer device ( 94),

characterized in that it comprises at least one fluid connection (100) of said circuit (90) to the fluid transfer device (94), this fluid connection (100) having a generally elongated shape along an axis of elongation (Y) and comprising:

• a first end piece (101) comprising a spherical end (102) rotatably mounted in a first housing (103) of the fluid transfer device (94), and
• a second end piece (104) comprising a spherical end (105) rotatably mounted in a second housing (106) of the circuit (90),

at least one of said end pieces (101, 102) being able to slide axially along the elongation axis (Y) inside the corresponding housing (103, 104), or opposite the 'other of said tips. Turbomachine module according to claim 1, characterized in that said end pieces (101, 104) are axially integral with one another and only one of the ends is mounted sliding axially in the corresponding housing (103, 106). Turbomachine module according to claim 2, characterized in that it comprises an anti-rotation system (114) of the fluid connection (100) around the axis of elongation (Y) with respect to the circuit ( 90) or the fluid transfer device (94), this anti-rotation system being for example of the pin type (114a). Turbomachine module according to claim 1, characterized in that said end pieces (101, 104) are engaged one into the other by a slide (130) or telescopic connection. Turbomachine module according to claim 4, characterized in that one of the nozzles (101, 104) comprises a male part (116) engaged in a female part (117) of the other of the nozzles, the male and female parts comprising an anti-rotation system (114') of the end pieces relative to each other with respect to the extension axis (Y), this anti-rotation system being for example of the type with grooves (114b). Turbomachine module according to any one of claims 1 to 5, characterized in that the end pieces (101, 104) comprise a central internal channel (107, 107') and/or peripheral internal channels (108, 108'), the channel(s) (107, 107', 108, 108') opening axially at the two axial ends of the fluid connection (100) and being in fluid communication with internal passages (109, 109', 110, 110') opening into said housing (103, 106). Turbomachine module according to any one of claims 1 to 6, characterized in that the end pieces (101, 104) carry annular seals (111) extending around the elongation axis (Y) and cooperating with annular surfaces (113) of the housings (103, 106). Turbomachine module according to any one of claims 1 to 7, characterized in that at least one of the first and second housings (103, 106) comprises a spherical cavity which is defined by two half-shells (120, 121 ), a first (120) of these half-shells (120, 121) comprising an annular fixing flange (122) which extends radially outwards relative to the axis of elongation (Y) and which is interposed axially between an annular flange (123) of a second (121) of the half-shells (120, 121) and an annular flange (124) of the circuit (90) or of the fluid transfer device (94). Turbomachine module according to any one of claims 1 to 8, characterized in that the circuit (90) comprises at least one conduit (95a) which passes axially through the planet carrier (38) of the speed reducer (34), and in particular which passes axially through one of the guide bearings (40) of the satellites (37). Turbomachine module according to claim 9, characterized in that, downstream of the speed reducer (34), said at least one conduit (95b) extends in the radial direction relative to said longitudinal axis (X) and internally passes through an arm tubular (98) of the module. Turbomachine module according to any one of claims 1 to 10, characterized in that the elongation axis (Y) is oriented radially relative to the longitudinal axis (X). Aircraft turbomachine comprising at least one turbomachine module according to any one of claims 1 to 11.