MODULE FOR AN AIRCRAFT TURBOMACHINE

Abstract

Module (30) for an aircraft turbomachine (10), this module (30) comprising: - a first annular element (B) extending about an axis (A) and including a first annular attachment interface (B1), - a second annular element (C) extending about the axis (A) next to the first element (B), - a third annular element (D) extending about the axis (A) next to the second element (C), and - fluid conduits (90) distributed about the axis (A) and the second element (C), at least some of these conduits (90) being telescopic. Figure for the abbreviation: Figure 7

Description

Title of the invention: MODULE FOR AN AIRCRAFT TURBOMACHINE Technical field of the invention

[0001] The present invention relates to a module for an aircraft turbomachine, as well as a turbomachine comprising such a module. Technical background

[0002] The prior art includes in particular document EP-B1-2 721 260.

[0003] An aircraft turbomachine includes a gas generator which conventionally comprises, from upstream to downstream, with reference to the flow of gases in the turbomachine, at least one compressor, an annular combustion chamber and at least one turbine.

[0004] In the case of a twin-spool turbofan engine, with low-pressure and high-pressure components respectively, the gas generator comprises successively a low-pressure compressor, a high-pressure compressor, the combustion chamber, a high-pressure turbine, and a low-pressure turbine. The gas generator defines a first annular flow path of gas, called the primary flow, which passes through the compressors, the combustion chamber, and the turbines.

[0005] The rotor of the high-pressure compressor is connected to the rotor of the high-pressure turbine by a high-pressure shaft. The rotor of the low-pressure compressor is connected to the rotor of the low-pressure turbine by a low-pressure shaft which passes through the high-pressure shaft and drives a shaft of a propulsion propeller generally located upstream of the gas generator.

[0006] When this propeller is enclosed and therefore surrounded by an annular casing, this propeller is called a blower and generates an airflow, called a secondary flow, which flows around the gas generator.

[0007] The propeller shaft and the low-pressure shaft are guided by bearings housed in a lubrication enclosure. This enclosure is surrounded by the first groove and is at least partially delimited by bearing supports. A first rolling bearing located upstream is supported by a first bearing support, and a second rolling bearing located downstream is supported by a second bearing support. These bearing supports have annular flanges that are radially oriented and axially applied to each other and to an annular flange of a stator housing.

[0008] The lubrication chamber is designed to lubricate the bearings and maintain an oily atmosphere around them. The oil is supplied to the chamber via a supply circuit.

[0009] The propeller includes blades that are susceptible to breakage, although this phenomenon is extremely rare. In such a case, a significant imbalance appears on the propeller shaft, generating cyclic loads and vibrations that the upstream bearing transmits to the stator, with a considerable risk of damage.

[0010] To limit the forces transmitted to the stator in the presence of a large imbalance, a shear screw decoupling device is known from document FR-A1-2 831 624. In practice, the second bearing support is fixed to the stator housing by non-shear screws, and the first bearing support is fixed to the second bearing support by shear screws to form a connection that can be broken. These so-called "fuse" screws, whose operation is fully described in the aforementioned document, have a reduced cross-section portion that is likely to break beyond a predetermined mechanical tensile force and thus achieve the decoupling of the bearing supports. In this situation of shear screw failure, the first bearing support is no longer axially restrained. It moves axially upstream and therefore moves axially away from the second bearing support. This is especially true when the bearing supported by the first bearing support is a roller bearing, which does not provide axial restraint to the bearing support when it is separated from the second bearing support.

[0011] This phenomenon is problematic because the housing continues to be supplied with oil by the aforementioned circuit, and the oil that accumulates in the housing is likely to pass through the annular passage formed between the flanges of the bearing supports, which have moved axially apart. The oil then spills into the engine, generating contamination. This oil can reach the first air intake from which air is drawn to supply air to the aircraft equipped with the turbomachine. There is therefore a risk that the aircraft will be supplied with polluted air, or even with unpleasant fumes and odors.

[0012] Furthermore, in a turbomachine module such as a module with fusible screw bearing supports as described above, it may be necessary to provide fluid conduits around the module in order to be able to convey one or more fluids such as oil or compressed air in particular for the pressurization of the lubrication chamber.

[0013] The fluid conduits are generally distributed around the module and extend between axial ends of the module to be connected to a fluid circuit.

[0014] In practice, connecting these conduits is not simple, particularly when these conduits have to be mounted around the module after the latter has been assembled.

[0015] The invention relates to a technical solution aimed at simplifying the assembly of this type of conduit around a module, this module being for example of the type described above even if this application is not limiting. Summary of the invention

[0016] The invention relates to a module for an aircraft turbomachine, this module comprising:

[0017] - a first annular element which extends around an axis and which comprises a first annular fixing interface,

[0018] - a second annular element which extends around the axis next to the first element and which includes a second annular fixing interface capable of cooperating by axial support with the first fixing interface, this second element comprising a third annular fixing interface,

[0019] - a third annular element that extends around the axis next to the second element and which includes a fourth annular fixing interface capable of cooperating by axial support with the third fixing interface, and

[0020] - fluid conduits which are distributed around the axis and the second element, each of these conduits having a generally elongated shape and extending along the axis from the first and second fixing interfaces to the third and fourth fixing interfaces,

[0021] at least some of these conduits being telescopic and comprising at least two sections engaged one inside the other and capable of sliding axially one inside the other so as to adapt a total length of the conduit along the axis, each telescopic conduit comprising a first longitudinal end engaged in or on a complementary element of the first or second fixing interface, and a second opposite longitudinal end engaged in or on another complementary element of the third or fourth fixing interface.

[0022] The module according to the invention is advantageous for facilitating the assembly and connection of fluid conduits. Assembly is facilitated by the fact that the conduits are telescopic; this telescopic assembly of the sections of each conduit allows these sections to slide into one another in order to shorten and lengthen the conduit as needed. Each conduit is, for example, in a shortened position when one of its ends is connected, and is lengthened just before the other end is connected.

[0023] The module according to the invention may comprise one or more of the following features, taken individually or in combination with each other: • at least one of the sections is straight; • at least one of the sections is angled, and includes, for example, two elbows; • each of the sections has its longitudinal ends which are oriented parallel to the axis; • each telescopic conduit includes at each of its first and second ends a support tab or collar having at least one opening for the passage of a fixing element such as a screw; • the sections are engaged one inside the other in a middle portion of the conduit which is connected by a spacer to said second element; • the spacer includes a collar for fixing the middle portion of the conduit and at least one support bracket having at least one opening for the passage of a fixing element such as a screw; • the first annular element is an annular bearing support or part of an annular bearing support, and / or the second annular element is another annular bearing support or part of another or the same annular bearing support; • the third annular element is an annular housing; • the fixing interfaces are annular flanges that extend around the axis;

[0024] — the module includes a first annular bearing support which extends around a axis and which includes a first annular fixing flange;

[0025] — the module includes a second annular bearing support which extends around the axis and which includes a second annular fixing flange, the first and second flanges being suitable for being applied axially against each other and for being fixed together by shear screws;

[0026] — the module comprises an annular housing which extends around the axis, the second bearing support being fixed to the casing;

[0027] — the module includes a lubrication chamber which is at least partly delimited by the first bearing support, this lubrication enclosure contains a first bearing supported by the first bearing support and a second bearing supported by the second bearing support;

[0028] — the module includes an oil supply circuit for the enclosure;

[0029] — the module includes an annular sealing skirt that extends around the first and second flanges, and comprising a first axial end fixed securely to the first bearing support and a second axial end fixed securely to the second bearing support, this skirt being made of a deformable material and capable of providing a seal around the flanges, between the first and second bearing supports, particularly in the event of shear bolt failure. In normal operation, the shear bolts ensure the axial retention of the first bearing support vis-à-vis the second bearing support. Although the skirt provides a Sealing around the flanges is not necessarily required at this stage, as the flanges may be equipped with their own sealing system. If the shear bolts fail, the bearing supports separate and move axially apart. The skirt then provides a seal around the flanges and is deformable to absorb the relative movements between the bearing supports. Therefore, there is no risk of oil leaking into the engine's oil passage, as the oil remains contained by the skirt.

[0030] — the skirt is made of elastically deformable material, and is for example made of elastomer;

[0031] — the first end of the skirt is fixed to an annular rib of the first bearing support, this rib extending radially outwards;

[0032] — the first end of the skirt is oriented radially outwards from so that a free peripheral edge of this end is oriented radially outwards;

[0033] — the first end of the skirt is pressed against an annular face of the rib thanks to an annular plywood;

[0034] — the plywood is fixed to the rib by screws that pass through holes in the rib, from the end of the skirt and the plywood;

[0035] — the second end of the skirt is fixed to the flange of the second bearing support;

[0036] — the second end of the skirt is radially clamped onto the flange by means of a hose clamp that surrounds the flange;

[0037] — the flange of the second bearing support is axially interposed between the flange of the first bearing support and another flange of the casing;

[0038] — the flange of the second bearing support is fixed to the flange of the housing by screws non-fusible;

[0039] — the skirt has a generally domed shape with a concavity oriented radially towards inside, when the fusible screws are not broken;

[0040] — the skirt defines a free annular cavity around at least part of the first bearing support and / or second bearing support;

[0041] — the skirt is loaded with fibres;

[0042] — the fibers are oriented in the axial direction, which allows the skirt to have a bending deformation capacity and tensile hardness.

[0043] The present invention also relates to an aircraft turbomachine, comprising at least one module as described above.

[0044] The present invention further relates to a method for assembling a module as described above, comprising the following steps:

[0045] a) fixing the first, second and third annular elements, via the first, second, third and fourth interfaces,

[0046] b) engagement of a longitudinal end of each telescopic conduit in or on a complementary element of the first or second fixing interface, or alternatively of the third or fourth interface, this telescopic conduit being previously in a shortened position or subsequently brought into a shortened position,

[0047] c) rotational movement of each telescopic conduit around the axis of engagement of its longitudinal end engaged in the member, until the other longitudinal end of this telescopic conduit is axially aligned with the other member, and

[0048] d) extension of each telescopic conduit to engage the other longitudinal end of this telescopic conduit in or on the other component.

[0049] Advantageously, the first longitudinal end of each telescopic conduit is fixed by a fixing element of the screw type for example to the first or second fixing interface, and the second longitudinal end of each telescopic conduit is fixed by a fixing element of the screw type for example to the third or fourth fixing interface.

[0050] The method may further include a step e) of linking the middle portion of each telescopic conduit to the second element by the aforementioned spacer. Brief description of the figures

[0051] Other features and advantages of the invention will become apparent upon reading the detailed description that follows, for an understanding of which reference should be made to the accompanying drawings in which:

[0052] [Fig-1] [Fig.1] is a schematic half-view in axial section of a part of a aircraft turbomachine,

[0053] [Fig.2] [Fig.2] is a partial schematic axial cross-sectional view of a bearing lubrication chamber,

[0054] [Fig.3] [Fig.3] is a larger-scale view of part of [Fig.2] and shows a decoupling device comprising fusible screws which are here unbroken,

[0055] [Fig.4] [Fig.4] is a view similar to that of [Fig.3] and shows the decoupling device with fusible screws here broken,

[0056] [Fig.5] [Fig.5] is a schematic axial cross-sectional view of a sealing skirt,

[0057] [Fig.6] [Fig.6] is a view similar to that of [Fig.5] and shows the skirt sealing in case of breakage of the fusible screws,

[0058] [Fig.7] [Fig.7] is a schematic perspective view of a module according to one embodiment of the invention,

[0059] [Fig.8] [Fig.8] is a schematic view of a telescopic fluid conduit for a module according to the invention,

[0060] [Fig.9] [Fig.9] is a schematic cross-sectional view of a longitudinal end of the conduit of [Fig.8], engaged in a component of a module element,

[0061] [Fig. 10] [Fig. 10] is a schematic perspective view of the end of the conduit and the element of [Fig. 9],

[0062] [Fig. 11] [Fig. 11] is a schematic cross-sectional view of another longitudinal end of the conduit of [Fig. 8], engaged in a component of another element of the module,

[0063] [Fig. 12] [Fig. 12] is a schematic perspective view of the other end of the conduit and the other element of [Fig. 11],

[0064] [Fig. 13] [Fig. 13] is a schematic perspective view of a portion of the conduit and a connecting spacer for this portion,

[0065] [Fig. 14] [Fig. 14] is another schematic perspective view of the portion of the conduit and the spacer of [Fig. 13],

[0066] [Fig. 15] [Fig. 15] is another schematic perspective view of an alternative embodiment of the spacer,

[0067] [Fig. 16] [Fig. 16] is a schematic cross-sectional view of the duct of [Fig. 8],

[0068] [Fig. 17] [Fig. 17] is a larger-scale view of part of [Fig. 13] and shows the telescopic portion of the duct,

[0069] [Fig. 18] [Fig. 18] is a partial schematic view of a module according to the invention and shows a step in an assembly process according to the invention, and

[0070] [Fig. 19] [Fig. 19] is a partial schematic view of the module of [Fig. 18] and shows another step of an assembly process according to the invention. Detailed description of the invention

[0071] Fig. 1 shows a turbomachine 10 for an aircraft, this turbomachine 10 being here a twin-spool turbojet.

[0072] Axis A designates the longitudinal axis of the turbomachine.

[0073] The turbomachine 10 comprises a gas generator 12 which includes, from upstream to downstream with reference to the gas flow along axis A, a low-pressure (LP) compressor 14, a high-pressure (HP) compressor, an annular combustion chamber, a high-pressure (HP) turbine, and a low-pressure (LP) turbine. The turbomachine 10 is partially shown, and only the LP compressor 14 is depicted in the drawing.

[0074] Although not visible in [Fig. 1], the HP compressor rotor is connected to the HP turbine rotor by a high-pressure shaft, and the LP compressor rotor 14 is connected to the LP turbine rotor by a low-pressure shaft which passes through the high-pressure shaft and drives a propulsion propeller, called a blower. 16, located upstream of the gas generator 12 and which is surrounded by an annular casing called the blower casing 18.

[0075] The blower housing 18 is connected to the gas generator 12 by an intermediate housing 20 which includes a central hub 22 and a series of radial arms 24 connecting the hub 22 to the blower housing 18.

[0076] The gas generator 12 defines a main annular flow channel V1 of a first air flow, called primary flow FL. The gas generator 12 is surrounded by a secondary annular flow channel V2 of a second air flow, called secondary flow F2.

[0077] The airflow F entering the blower 16 splits into a portion forming the primary flow FL. The air in this primary flow FL is compressed in the BP 14 and HP compressors, then mixed with fuel and burned in the combustion chamber. The combustion gases of the primary flow are then expanded in the HP and BP turbines and finally flow through an exhaust nozzle.

[0078] The other part of the airflow entering the blower 16 forms the secondary flow F2 and is intended to be mixed with the primary flow Fl downstream of the nozzle.

[0079] Fig. 1 further shows a module 30 of the turbomachine, this module 30 comprising annular bearing supports 32, 34, an annular housing 36, a lubrication chamber 38 and an oil supply circuit 40 for the chamber 38.

[0080] A first annular bearing support 32 extends around the axis A and includes a first annular fixing flange 32a, more clearly visible in [Fig.2].

[0081] A second annular bearing support 34 extends around the axis A and includes a second annular mounting flange 34a. The flanges 32a, 34a extend radially outwards and are suitable for being applied axially against each other and for being fixed together by screws 42 which are fusible and more clearly visible in figures 2 to 4.

[0082] An annular housing 36 extends around axis A, and the second bearing support 34 is fixed to this housing 36 by screws that are not shear-resistant and are not shown in the drawings. The shear-resistant and non-shear-resistant screws 42 may be located on the same circumference centered on axis A. The housing 36 may be the intermediate housing 20 of [Fig. 1] or another housing fixed to or integral with this intermediate housing 20.

[0083] The housing 36 includes a flange 36a onto which the flange 34a is applied and fixed by the aforementioned non-sheathable screws. The flange 34a of the second bearing support 34 is axially interposed between the flange 32a of the first bearing support 32 and the flange 36a of the housing 36, as illustrated in Figures 2 to 4.

[0084] The lubrication enclosure 38 is at least partly delimited by the first bearing support 32 and contains a first bearing 44, or upstream bearing, carried by the first bearing support 32, and a second bearing 46, or downstream bearing, carried by the second bearing support 34.

[0085] In the example shown, the upstream bearing 44 is a roller bearing and the downstream bearing 46 is a ball bearing.

[0086] Furthermore, in the example shown, the first bearing support 32 has a generally annular and elongated shape along the axis A, and comprises an upstream end carrying the rolling bearing 44, and a downstream end connected to the flange 32a. The second bearing support 34 has a generally annular and radial shape, and comprises a radially internal end carrying the downstream bearing 46, and a radially external end connected to the flange 34a.

[0087] The oil supply circuit 40 of the enclosure 38 is more clearly visible in [Fig.2] and includes an oil distributor 48 and at least one oil line 50. The oil distributor 48 is integral with the housing 36 and includes at least one oil inlet 48a and at least one first oil outlet 48b.

[0088] The oil inlet 48a is suitable for connection to an oil reservoir not shown.

[0089] The oil line 50 is integral with the first bearing support 32 and has an end 40a, here downstream, connected to the first oil outlet 48b of the distributor 48 for the purpose of circulating oil from said inlet 48a to said at least one outlet 48b.

[0090] In the example shown, the distributor 48 comprises two oil outlets 48b, 48c, the first oil outlet 48b mentioned above and a second oil outlet 48c. The second oil outlet 48c can be connected to another line or to an oil nozzle 52 as illustrated in the drawing. The nozzle 52 sprays oil onto the downstream bearing 46, while the line 50 connected to the first outlet 48b of the distributor 48 supplies oil to the upstream bearing 44 for lubrication.

[0091] Preferably, the first outlet 48b is oriented axially, in particular towards the first bearing support 32, i.e. here upstream. The second outlet 48c can be oriented radially inwards.

[0092] Figures 2 to 4 further show that the conduit 50 includes a part which extends axially and which passes through an axial orifice 54 of the second bearing support 34. The conduit 50 is radially interposed between the downstream bearing 46 and the flanges 32a, 34a of the bearing supports 32, 34.

[0093] Fig. 3 shows the default and normal operating case in which the flanges 32a of the bearing supports 32 are applied axially to each other and fixed together by the shear screws 42.

[0094] As mentioned above, in the event of imbalance and vibrations, the shear screws 42 are liable to break as illustrated in [Fig. 4]. The flange 32a of the first bearing support 32, and in particular the first bearing support 32 as a whole, is then no longer axially restrained and moves axially away from the second bearing support 32. The first bearing support 32 then moves towards upstream which creates an annular passage 56 between the flanges 32a, 34a of the bearing supports 32, 34.

[0095] The oil supplied by the distributor 48 continues to flow into the enclosure and accumulates there. This oil is then liable to flow by gravity through the passage 56 and can reach the primary vein VI, which is problematic as mentioned above.

[0096] A simple, effective and economical solution is proposed to this problem, which consists of containing the oil inside the enclosure, even when the screws 42 break and the bearing supports 32, 34 move axially apart from each other.

[0097] As illustrated in figures 5 and 6, an annular sealing skirt 80 is thus proposed which extends around the flanges 32a, 34a and which includes a first axial end 80a fixed in a sealed manner to the first bearing support 32 and a second axial end 80b fixed in a sealed manner to the second bearing support 34.

[0098] The skirt 80 is made of a deformable material, preferably elastically deformable such as an elastomer. The skirt 80 is, for example, made of Viton®.

[0099] The skirt 80 is preferably fiber-reinforced. The fibers are preferably oriented in the axial direction so that the skirt 80 has a bending deformation capacity and a tensile strength.

[0100] The skirt 80 is suitable for ensuring a seal around the flanges 32a, 34a, between the first and second bearing supports 32, 34 in particular in the event of breakage of the shear screws 42 ([Fig.6]).

[0101] In the example shown, the skirt 80 has a generally domed shape with a concavity oriented radially inwards when the fusible screws 42 are not broken ([Fig. 5]). The skirt 80 can define a free annular cavity 82 around at least a portion of the bearing support 32 and / or the bearing support 34.

[0102] In the example shown, the first end 80a of the skirt 80 is fixed to an annular rib 84 of the first bearing support 32. This rib 84 extends radially outwards, here at an axial distance from the flange 32a.

[0103] The first end 80a of the skirt 80 can be oriented radially outwards so that a free peripheral edge 80al of this end 80a is oriented radially outwards.

[0104] The first end 80a of the skirt 80 is clamped against an annular face 84a, here downstream, of the rib 84 by means of an annular plywood 86. This plywood 86 can be sectored to facilitate its assembly.

[0105] The plywood 86 is fixed to the rib 84 by screws 87 which pass through holes in the rib 84, the end 80a of the skirt 80 and the plywood 86.

[0106] The plywood 86 may include a cylindrical rim 86a which surrounds the edge 80a of the end 80a or even a free peripheral edge 84al of the rib 84.

[0107] In the example shown, the second end 80b of the skirt 80 is fixed to the flange 34a of the second bearing support 34.

[0108] The second end 80b of the skirt 80 can be radially clamped onto the flange 34a by means of a clamping collar 88 which surrounds the flange 34a.

[0109] In normal operation, the skirt 80 is in the configuration shown in [Fig. 5] and is not functional. It is in standby mode. When the screws 42 break and the bearing support 32 moves axially away from the bearing support 34, the skirt 80 is in the configuration shown in [Fig. 6] and is functional. The skirt 80 then provides a seal between the flanges 32a and 34a, and any oil that might pass through the passage 56 between the flanges 32a and 34a is retained by the skirt 80 and does not escape from the housing 38.

[0110] Reference is now made to Figures 7 and following, which illustrate the present invention. The invention can be applied to a module 30 as described above, but not only that. It can indeed be applied to another type of module.

[0111] In the following description, the elements already described above in relation to figures 1 to 6 are designated by the same references.

[0112] Module 30 comprises at least three annular elements.

[0113] Module 30 comprises a first annular element B which extends around the axis A and which includes a first annular fixing interface Bl. This first annular element B can be formed by a part of the first bearing support 32, as illustrated in the drawings.

[0114] It can also be seen that the first annular fixing interface Bl is formed by an annular flange 32b of this part of the support 32. The flange 32b is an external annular flange which is therefore radially projecting outwards with respect to the axis A.

[0115] The module 30 comprises a second annular element C extending around the axis A next to the first element B and comprising a second annular fastening interface Cl adapted to cooperate by axial support with the first fastening interface BL

[0116] This second annular element C can be formed by another part of the first bearing support 32, as illustrated in the drawings.

[0117] It can also be seen that the second annular fixing interface Cl is formed by an annular flange 32c of this part of the support 32. The support 32 is thus formed in several axial parts in the example shown. The flange 32b is an external annular flange which therefore projects radially outwards with respect to the axis A.

[0118] The second element C has a third annular fixing interface C2. The fixing interfaces Cl, C2 can be located at longitudinal ends of the second element C.

[0119] The module 30 includes a third annular element D which extends around the axis A next to the second element C and which includes a fourth annular fixing interface DI capable of cooperating by axial support with the third fixing interface C2.

[0120] This third annular element D can be formed by the housing 36, as illustrated in the drawings.

[0121] It can also be seen that the third annular fixing interface Cl is formed by the flange 36a of the housing or another flange of the housing.

[0122] Module 30 further comprises fluid conduits 90 which are distributed around axis A and the second element B.

[0123] Each of these conduits 90 has a general elongated shape and extends along the axis A from the first and second fixing interfaces Bl, Cl, to the third and fourth fixing interfaces C2, Dl, and therefore in particular from the flanges 32b, 32c to the flange 36a.

[0124] At least some of these conduits 90, and advantageously all of them, are telescopic.

[0125] The telescopic conduits 90 comprise at least two sections 90a, 90b engaged one inside the other and capable of sliding axially one inside the other so as to adapt a total length of the conduit 90 along the axis A ([Fig.8]).

[0126] Each telescopic conduit 90 has a first longitudinal end 92 engaged in or on a complementary element 94 of the first or second fixing interface Bl, Cl, and in particular of the flanges 32b, 32c (figures 9 and 10).

[0127] In the example shown, the first end 92 is of the male type and is engaged in the organ 94, which is of the female type. The first end 92 may carry an annular sealing gasket, housed, for example, in an external annular groove of the end 92 and adapted to cooperate with an internal annular surface of the organ 94.

[0128] Each telescopic conduit 90 has a second longitudinal end 96 opposite engaged in or on another component 98 complementary to the third or fourth fixing interface C2, Dl, and in particular to the flange 36a (figures 11 and 12).

[0129] In the example shown, the second end 96 is of the male type and is engaged in the organ 98, which is of the female type. The second end 96 may carry an annular sealing gasket, housed, for example, in an external annular groove of the end 96 and adapted to cooperate with an internal annular surface of the organ 98.

[0130] We can see in [Fig.4] that at least four telescopic conduits 90 can be mounted around the second element C. These conduits 90 are not necessarily identical. In particular, they can differ from each other in their shapes. The 90 conduits, for example, are used to convey oil or pressurized air.

[0131] Fig. 8 illustrates an example of a 90° telescopic conduit.

[0132] At least one of the 90b sections of each conduit 90 may be straight.

[0133] At least one of the sections 90a of each conduit 90 is bent, and comprises by example two elbows.

[0134] Each of the sections 90a, 90b preferably has its longitudinal ends oriented parallel to the axis A so as to facilitate assembly.

[0135] Figures 9 to 12 show details of a telescopic duct 90 and in particular of the longitudinal ends of this duct.

[0136] Each telescopic conduit 90 can include at each of its first and second ends a tab 100 or support collar having at least one orifice 102 for the passage of a fixing element of the screw type 104 for example.

[0137] Advantageously, the sections 90a, 90b are engaged in each other in a median portion 106 of the conduit 90 which is connected by a spacer 108 to the second element C and therefore to the bearing support 34 in the aforementioned example (figures 13 to 15).

[0138] As can be seen in Figures 16 and 17 in particular, at least one seal can ensure the sealing of the connection in this middle portion 106, between a male part of one of the sections 90b and a female part of the other of the sections 90a.

[0139] The spacer 108 preferably comprises a collar 110 for securing the middle portion 106 of the conduit 90 and at least one support bracket 112 having at least one opening for the passage of a fastener such as a screw 114 (Figures 13-15). The support bracket 112 can be applied to the aforementioned rib 84 for securing the skirt 80 by means of the screw 114.

[0140] We will now describe a method for assembling module 30 with reference to [Fig. 18] and 19.

[0141] The assembly process first includes a first step of a) fixing the first, second and third annular elements B, C and D, via the first, second, third and fourth interfaces Bl, Cl, C2 and DI.

[0142] The method includes a subsequent step b) of engaging a longitudinal end of each telescopic conduit 90 in or on the complementary member 94, 98 of the first or second fixing interface B1, Cl, or alternatively of the third or fourth interface C2, Dl, as illustrated in [Fig.18],

[0143] This 90 telescopic conduit is first in a shortened position or subsequently brought into a shortened position, as illustrated in [Fig. 17].

[0144] The method then includes a step of c) rotating (see arrow [Fig. 18]) each telescopic conduit 90 around the engagement axis of its longitudinal end engaged in member 94, 98, until the other longitudinal end of this telescopic conduit 90 is aligned axially with the other member 98, 94 complementary to the third or fourth interface C2, Dl, or alternatively to the first or second fixing interface Bl, Cl.

[0145] The method then includes a step of d) extending each telescopic conduit 90 to engage the other longitudinal end of this telescopic conduit 90 in or this other member 98, 94 (figures 16 and 19).

[0146] As described above, the first longitudinal end of each telescopic conduit 90 can be fixed by a fixing element of the screw type 104 for example to the first or second fixing interface B1, Cl. The second longitudinal end of each telescopic conduit 90 can be fixed by a fixing element of the screw type 104 for example to the third or fourth fixing interface C2,D1.

[0147] The process can then include a step of e) linking the middle portion 106 to the second element C, and in particular to the rib 84 of the bearing support 32, by the aforementioned spacer 108 ([Fig. 11]).

Claims

Demands

1. Module (30) for an aircraft turbomachine (10), this module (30) comprising: - a first annular element (B) extending around an axis (A) and comprising a first annular attachment interface (Bl), - a second annular element (C) extending around the axis (A) next to the first element (B) and comprising a second annular attachment interface (Cl) adapted to cooperate by axial support with the first attachment interface (Bl), this second element (C) comprising a third annular attachment interface (C2), - a third annular element (D) extending around the axis (A) next to the second element (C) and comprising a fourth annular attachment interface (Dl) adapted to cooperate by axial support with the third attachment interface (C2), and - fluid conduits (90) distributed around the axis (A) and the second element (C),each of these conduits (90) having a generally elongated shape and extending along the axis (A) from the first and second fixing interfaces (B1, Cl) to the third and fourth fixing interfaces (C2, D1), at least some of these conduits (90) being telescopic and comprising at least two sections (90a, 90b) engaged one inside the other and capable of sliding axially one inside the other so as to adapt a total length of the conduit (90) along the axis (A), each telescopic conduit (90) comprising a first longitudinal end (92) engaged in or on a complementary element (94) of the first or second fixing interface (B1, Cl), and a second opposing longitudinal end (96) engaged in or on another complementary element (98) of the third or fourth fixing interface (C2, D1).

2. Module (30) according to claim 1, wherein at least one of the segments (90a, 90b) is straight.

3. Module (30) according to claim 1 or 2, wherein at least one of the sections (90a, 90b) is bent, and comprises for example two bends.

4. Module (30) according to any one of the preceding claims, wherein each of the segments (90a, 90b) has its longitudinal ends which are oriented parallel to the axis (A).

5. Module (30) according to any one of the preceding claims, wherein each telescopic conduit (90) comprises at each of its first and second ends (92, 96) a tab (100) or support collar having at least one orifice (102) for the passage of a fixing element of the screw type (104) for example.

6. Module (30) according to any one of the preceding claims, wherein the sections (90a, 90b) are engaged in each other in a median portion (106) of the conduit (90) which is connected by a spacer (108) to said second element.

7. Module (30) according to claim 6, wherein the spacer (108) comprises a collar (110) for fixing the middle portion (106) of the conduit (90) and at least one support tab (112) having at least one opening for the passage of a fixing element such as a screw (114) for example

8. Module (30) according to any one of the preceding claims, wherein the first annular element (B) is an annular bearing support (32) or part of an annular bearing support (32), and / or the second annular element (C) is another annular bearing support or part of another or the same annular bearing support.

9. Module (30) according to any one of the preceding claims, wherein the third annular element (D) is an annular housing (36).

10. Module (30) according to any one of the preceding claims, wherein the fastening interfaces (Bl, Cl, C2, Dl) are annular flanges (32b, 32c, 36c) which extend around the axis (A).

11. Turbomachine (10) for an aircraft, comprising at least one module (30) according to any one of the preceding claims.

12. A method for assembling a module (30) according to any one of claims 1 to 10, wherein it comprises the following steps: a) fixing the first, second and third annular elements (B, C, D), via the first, second, third and fourth interfaces (B1, C1, C2, D1), b) engaging a longitudinal end (92) of each telescopic conduit (90) in or on a complementary member (94) of the first or second fixing interface (B1, C1), or alternatively of the third or fourth interface (C2, D1), this telescopic conduit (90) being previously in a shortened position or subsequently brought into a shortened position, c) rotational movement of each telescopic conduit (90) around the engagement axis of its longitudinal end (92) engaged in the member (94), until the other longitudinal end (96) of this telescopic conduit (90) is axially aligned with the other member (98) of the third or fourth interface (C2, D1), or alternatively of the first or second fixing interface (B1, C1), and d) extension of each telescopic conduit (90) to engage the other longitudinal end (96) of this telescopic conduit (90) in or on the other component (98).

13. Method according to claim 12, wherein the first longitudinal end (92) of each telescopic conduit (90) is fixed by a screw-type fixing element (104) for example to the first or second fixing interface (B 1, Cl), and the second longitudinal end (96) of each telescopic conduit (90) is fixed by a screw-type fixing element (104) for example to the third or fourth fixing interface (C2, Dl).

14. Method according to claim 12 or 13, wherein, the module being as defined in claim 6 or 7, it further comprises a step e) of linking the middle portion (106) of each telescopic conduit (90) to the second element (C) by the spacer (108).

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