• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    There is provided a turbomachine assembly comprising: an inter-turbine casing comprising a hub (1) comprising a bearing support, a shell (2) extending around and away from the hub, at least one arm (40); extending radially between the hub (1) and the ferrule (2), at least one servitude (3) for lubricating the bearing support, the servitude (3) comprising a first pipe (30) having: an end portion (31) ) screwed to the hub (1) to put the first pipe (30) in fluid communication with the bearing support, an intermediate portion (32) integral with the end portion, housed inside the arm (40) when the end portion (31) is screwed to the hub (1), a clamping portion (34) integral with the end portion (31) and adapted to be rotated by a clamping tool, characterized in that the clamping portion (34) is located between the screwable end portion (31) and the intermediate portion (32).
    公开号:FR3036437A1
    申请号:FR1554621
    申请日:2015-05-22
    公开日:2016-11-25
    发明作者:Philippe Pierre Vincent Bouiller；Frederic Francois Jean-Yves Patard
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] The invention relates to a set of turbomachine parts intended to be arranged between two turbines, this set of parts being designed to allow the lubrication of a bearing support of the turbomachine. STATE OF THE ART A conventional turbomachine may comprise two turbines movable about a main axis of the turbomachine: a high pressure turbine and a low pressure turbine arranged downstream of the high pressure turbine, rotatable about an axis main. Such a turbomachine also comprises a structure called bearing support, which extends between the two turbines. The bearing support, as its name suggests, serves as a support for one or more movable bearings. The turbomachine comprises a casing extending between the two turbines (conventionally referred to as an "inter-turbine" casing), the casing being arranged around the bearing support with respect to the main axis. FIG. 1 illustrates a known inter-turbine casing, which comprises a hub 1, a plurality of connecting arms B and an outer shell 2. The arms B are arranged at angular positions spaced apart from each other with respect to the axis X (corresponding to the axis of rotation of the turbines). The link arms B are intended to be connected to the outer shell. 2, which extends around and away from the hub 1. Referring to Figure 2, is disposed around each connecting arm B aerodynamic fairing 4. A fairing 4 comprises in particular a hollow aerodynamic arm 40 which surrounds a connecting arm 30 B and two facing walls interconnected by the aerodynamic arm 40. The set of aerofoil fairings 4 are formed to jointly define a space of generally annular gas flow between the hub 1 and the shell, this space being locally interrupted by each aerodynamic arm 40. Gas can thus pass between two adjacent arms 40. The aerodynamic fairings 4 are adapted to redirect gas from the turbine high pressure to the low pressure turbine. However, the bearing support requires an oil supply to be lubricated. The oil supply of the bearing support is typically provided by at least one servitude (not shown in FIGS. 1 and 2) passing radially through the body of the inter-turbine casing. In order not to hinder the flow of a gas between the aerodynamic arms 40, it is known to provide a hollow passage in a connecting arm B and to house a servitude extending radially inside this passage. Thus, the easement can reach the bearing support by radially crossing the body of the inter-turbine casing. In most known turbomachines, the servitude is fixed to the hub 1 via a connection constituting an independent part. The connector has a first end adapted to be fixed to the bearing support, and a second end, opposite the first end, adapted to be attached to the servitude partially housed within a structural arm. The fitting is confined in a space left between the bearing support and the hub of the inter-turbine casing which surrounds it. A goal generally sought by turbomachine designers is to bring the hub of the inter-turbine casing as close as possible to the bearing support in order to increase its gas flow rate for a predetermined space requirement of the casing (in the example of this example). returns to bring the hub 1 of the X axis). However, the connection between the hub and the bearing support has a relatively bulky diameter which limits such a connection. A first solution for circumventing this limitation could theoretically be to house the connection inside the link arm B. However, this solution would require increasing the diameter of the arm B, and therefore that of the aerodynamic arm 40 which 5 around him. The arm 40 would then occupy a more important place in the gas flow space defined between the hub and the outer shell of the inter-turbine housing, which would reduce the maximum gas flow allowed between the two turbines. Another solution for bringing the hub 1 closer to the axis of the turbomachine (and of the bearing support) has been proposed in the document CA 2715600 A1. This solution consists of an easement directly screwed to the hub. No cumbersome interconnection piece is then used. With reference to FIG. 2 of document CA 2715600 A1, this servitude thus comprises a first end portion intended to be screwed to the bearing support, as well as a second end portion, opposite to the first end portion, having a collar and a clamping support of the servitude. The two end portions are joined by an intermediate portion adapted to fit within a hollow structural arm extending between the hub and the outer shell. When the end portion is screwed to the bearing support and the intermediate portion is housed within the hollow structural arm, the clamping support is further away from the bearing support than the outer shroud. However, the flange limits the axial displacement of the servitude once screwed to the bearing support. The presence of this collar requires screwing the servitude to the hub only after mounting the outer shell around the hub. On the other hand, to secure the servitude to the hub, an operator engages a clamping tool with the clamping support and drives the servitude in rotation. This rotation is transmitted to the screwing end of the servitude via the portion. The intermediate portion of the servitude housed inside the arm is then subjected to a substantial torsional force during the screwing of the servitude with the hub. This torsional force imposes to increase the thickness of the tubular wall of the servitude at the level of the intermediate portion. In addition, if it is desired that the easement maintains a constant feed rate, it is necessary not to reduce its internal diameter, but to increase its external diameter and consequently its bulk in the radial arm which houses it. . This increase in the outer diameter of the servitude further forces to increase the dimensions of the structural arm it passes through, with the consequence of reducing the flow of gas in the annular space 15 between the two turbines. PRESENTATION OF THE INVENTION The invention aims to bring together, in a turbine engine, an inter-turbine casing of a bearing support requiring lubrication, without however reducing the flow rate of gas passing through the inter-turbine casing nor reducing the lubricant supply flow rate of the bearing support. The invention also aims to simplify the disassembly and / or the replacement of a crankcase-inter-turbine. In particular, it is desired to be able to disassemble the inter-turbine casing without having to completely dismantle the servitude. The invention also aims to limit the degradation of the connection of the servitude with the bearing support caused by disassembly of the inter-turbine casing. It is therefore proposed a turbomachine assembly comprising: an inter-turbine casing comprising: a hub comprising a bearing support, a ring extending around and away from the hub, at least one arm; extending radially between the hub and the ferrule, - at least one servitude for lubricating the bearing support, the servitude comprising a first pipe having: an end portion screwed to the hub to put the first pipe in fluid communication with the support bearing, o an intermediate portion secured to the end portion, housed inside the arm when the end portion is screwed to the hub, o a clamping portion secured to the end portion and adapted to be driven in rotation by a clamping tool, characterized in that the clamping portion is located between the screwable end portion and the intermediate portion. First, the clamping bracket of the assembly according to the present invention is much closer to the end portion to be screwed onto the bearing support, compared to the arrangement proposed in the prior art. When an operator rotates the clamping support with the aid of a clamping tool to screw the servitude to the bearing support, no significant torsional force is transmitted to the intermediate portion intended to fit in the structural arm. hollow. As a result, it is perfectly possible to reduce the outer diameter of the intermediate portion without the risk of deformation or breaking of the servitude due to tightening too tight. The dimensions of the link arm can therefore be reduced, which increases the flow of gas in the gas flow space defined between the hub and the outer shell of the inter-turbine casing. Moreover, the fact of arranging the clamping support between the intermediate portion which accommodates in the structural arm and the end potion screwed to the bearing support causes the clamping support to be located between the hub and the bearing support. . Furthermore, the clamping support does not require a large radial space requirement. In this way, it is possible, thanks to the invention, to bring the inter-turbine casing closer to the bearing support in a radial direction, compared to the turbomachines whose servitudes are connected to the support by means of an interconnection piece. additional arranged radially between these servitude and the bearing support. The invention may also be supplemented by the following features, taken alone or in any of their technically possible combinations. The assembly may comprise sealing means adapted to put the end portion in leaktight fluid communication with the bearing support, when the end portion is screwed to the hub. The clamping portion may comprise a plurality of clamping faces defining a polygonal section free surface grippable by a clamping tool. It can also be provided that: the ferrule is of annular shape around a main axis, and has at least one radial orifice therethrough, the first channel comprises a second end portion opposite the screw-end end portion; at the hub, the first pipe has a length that is sufficiently short to allow insertion, along the main axis, of the hub and the first pipe screwed to the hub in the shell, until the second end portion is aligned 3036437 7 with the radial orifice, the ferrule extending around the first pipe screwed to the hub. The easement may further comprise a second pipe adapted to be placed in fluid communication with the first pipe, the servitude being of suitable dimensions to pass through the radial orifice of the shell. The first pipe may comprise a second end portion opposite to the end portion screwed to the hub, the servitude having, from the intermediate portion included to the second end portion, an outer diameter less than or equal to minimum internal diameter of the arm. The easement may further comprise a heat insulation adapted to extend around the intermediate portion of the first pipe, the heat insulation having an outer diameter strictly less than or equal to the minimum internal diameter of the arm. The end portion may have an outer guide surface, and the hub comprise a cavity for receiving the screwable end portion, the cavity having a diameter complementary to the outer guide surface.
    [0002] The first pipe may comprise a flanged portion arranged between the screwable end portion and the clamping portion, the flange having a surface adapted to abut against the hub during screwing of the end portion to the hub. According to a second aspect of the invention, there is provided a method of assembling this assembly for a turbomachine, comprising steps of: screwing the end portion to the hub, by rotating the clamping portion to the using a clamping tool, so as to put the first pipe in fluid communication with the bearing support, insertion of the intermediate portion in the arm, attachment of the arm to the shell, wherein the screwing step is implemented before the insertion step and / or before the fixing step.
    [0003] DESCRIPTION OF THE FIGURES Other characteristics, objects and advantages of the invention will emerge from the description which follows, which is purely illustrative and nonlimiting, and which should be read with reference to the appended drawings in which: FIG. 1 , already discussed, is a sectional view of a turbomachine inter-turbine casing. FIG. 2, already discussed, is a three-dimensional view of the inter-turbine casing shown in FIG. 1. FIG. 3 is a partial profile view of a turbomachine assembly according to one embodiment of the invention . FIG. 3a is a view is a partial three-dimensional view of the turbomachine assembly already shown in FIG. 3. FIG. 4 is an enlarged view of a portion of the turbomachine assembly shown in FIG. - Figure 5 illustrates a section of servitude according to one embodiment of the invention. FIG. 6 is an enlarged view of another part of the turbomachine assembly shown in FIG. 3, according to a first embodiment. FIG. 6bis is an enlarged view of another part of the turbomachine assembly shown in FIG. 3, according to a second embodiment of embodiment. - Figures 7 to 12 show parts of the assembly for turbomachines shown in Figure 3, at different stages of its assembly. In all the figures, similar elements bear identical references.
    [0004] DETAILED DESCRIPTION OF THE INVENTION Referring to FIGS. 3 and 3bis, an assembly for a turbomachine comprises an inter-turbine casing extending around an axis X. In what follows, the term the term "centrifugal" means a direction of approach towards the main axis X, and by the term "centripetal" a sense of distance from the main axis X. In the turbomachine, the inter-turbine casing is between two turbines movable in rotation about this axis X. The turbine casing comprises a hub 1 and an outer shell 2, and at least one connecting arm B connecting the hub to the outer shell 2.
    [0005] The hub 1 extends around the main axis X of your turbomachine. The hub has a generally annular body extending from a shaft of the turbomachine centered on this axis X (not shown in the figures). The hub 1 comprises a bearing support. The hub 1 also has a radially outer surface 11 into which at least one access port 10 opens. The orifice 10 gives access to a portion of the bearing support requiring lubrication. The outer shell 2 also has an annular shape of larger internal diameter than the outer diameter of the hub. The outer shell 2 extends around the hub 1 away from it. The outer shell 2 comprises an annular wall having an internal radiating surface 21 with respect to the X axis, and a radially outer surface 22 opposite to the surface 21. The shell comprises an orifice 20, hereinafter referred to as a radial orifice 20, opening into its two opposite surfaces 21 and 22. Although not shown in Figure 3, the connecting arms B connect the hub 1 to the outer shell 2 and are arranged at different angular positions from each other about the axis X. The link arms B extend radially from the radially outer surface 11 of the hub 1 to the radially inner surface 22 of the shell 2.
    [0006] Thus, in the housing, between the hub 1 and the shell 2, a generally annular flow space of shape locally cut by each connecting arm B. The inter-turbine casing also comprises a plurality of 5 aerodynamic fairings 4 called "aerodynamic profiles", which are interposed between the hub 1 and the outer shell 2, and between connecting arms B. Each of these parts 4 extends over a limited angular sector around the X axis The parts 4 are designed so that, when assembled together, they together define an annular shape 10 about the axis X which can be accommodated in the annular space formed between the hub 1 and the shell 2. The plurality of fairings 4 defines a stream of air arranged between the hub 1 and the outer shell 2. The function of the vein is to redirect air from the turbine arranged upstream of the inter-turbine casing, to the turbine downstream of the casing inter -turbine. A given aerodynamic profile 4 typically comprises a radially inner wall 41, a radially outer wall 42, and a hollow aerodynamic arm 40 connecting the two walls 41 and 42, in accordance with FIG. 2 already described in the introduction.
    [0007] The radially inner wall 41 is provided to be disposed facing the hub 1, and the radially outer wall is provided to be disposed facing the shell 2. The aerodynamic arm 40 extends in a substantially radial direction relative to the X axis.
    [0008] The hollow aerodynamic arm 40 of the aerodynamic part 4 defines an internal radial passage with respect to the axis X, when the part 4 is arranged between the hub 1 and the outer shell 2. The internal passage of a connecting arm B is intended to be aligned radially with a radial orifice 20 formed in the outer shell, and with an access port 10 formed in the hub, when the fairing 4 is installed between the hub 1 and the shell 2.
    [0009] The aerodynamic arm 40 is rectilinear. The assembly therefore comprises two different types of arms arranged radially between the hub 1 and the shell 2: firstly the link arms B, having a main function of mechanical support of the hub 1 with respect to the shell 2, and others by your aerodynamic arms 40, which are arranged at different angular positions of the angular positions of the connecting arms B, and whose main function is to participate in the delineation of the fluid flow vein between two turbines. For example, an alternating arrangement of arms B and 40 around the main axis X may be provided. The turbomachine assembly also comprises at least one servitude 3. The main function of the servitude 3 is to supply lubricant to the bearing support of the hub 1, for example oil. The easement 3 comprises a first pipe 30 intended to be connected to the hub 1. The first pipe 30 comprises a generally rectilinear hollow body. The first channel present is of section adapted to be housed inside an aerodynamic arm 40, without however the outer surface of the first pipe 30 does not touch the inner surface of the arm 40, so that it remains a residual space between the pipe 30 and the arm 40 which houses it. The first pipe 30 comprises a first end portion 31, a second end portion 33, and an intermediate portion 32 interconnecting the two end portions 31 and 33. With reference to FIG. 4, the hub 1 comprises a cavity emerging in its radially outer surface 11 through the access orifice 10. The cavity is shaped to receive at least partially the end portion 31 of the first pipe 30.
    [0010] The hub 1 comprises an internal thread 12 giving into the cavity so as to form a nut. The hub 1 further comprises an inner guiding surface 14 giving in the cavity, centered on a radial axis R, for example secant 5 with the main axis X of the turbomachine. The guide surface 14 is cylindrical in revolution (that is to say of circular section). The hub 1 further has a circumferential free edge 16 protruding radially outwardly from the surface 11 relative to the X axis. The edge 16 defines a perimeter of the access port 10. The portion end 31 of the pipe 30 is adapted to be screwed to the hub 1; it has an axial oil outlet orifice. The portion 31 has in particular an external thread 310 forming a screw to cooperate with the internal screw thread 12 forming a nut.
    [0011] When the threads 12 and 310 are engaged with each other, the first channel is in fluid communication with the bearing support of the hub 1. The end portion 31 further has a complementary circumferential guide surface 312. of the inner surface 14.
    [0012] The surfaces 14 and 312 make it possible to prohibit mobility in any other direction than the screwing axis R of the end portion 31 with respect to the hub, when the portion 31 is screwed to the hub by mutual cooperation of the threads 12 and 310. The portion 31 also has a collar 314 of diameter 25 greater than the diameter of the orifice 10 defined by the edge 16. The collar has in particular a surface provided for abutting against the edge 16 when the portion 31 is inserted, according to the radial axis R and in a centrifugal direction, in the cavity, via the orifice 10. The flange 314 therefore limits the insertion stroke and / or screwing 30 of the end portion 31 in the hub 1.
    [0013] The hub 1 has a wall ending in the edge 16 having a shoulder facing the cavity. This shoulder defines at least one housing extending between the end portion 31 of the pipe 30 and the hub 1 when the threads 310 and 12 are engaged one inside the other. Are housed in this housing sealing means 19 for sealing the fluid connection between the end portion 31 of the first pipe 30 and the hub 1. For example, these sealing means 19 comprise one or more metal gaskets having a C shape, particularly suitable for an environment as hot as a bearing support. The pipe 30 further comprises a clamping portion 34 gripped by a clamping tool in order to apply a tightening torque to the servitude. The collar 314 is located between the clamping portion 34 and the guiding surface 312. With reference to FIG. 5, the clamping portion 34 comprises a plurality of clamping sections defining a free surface 316 of polygonal section which is grippable by the clamping tool, such as a spanner. The number of clamping pieces may be 6 and the surface 316 in this case be of hexagonal section. Returning to FIG. 4, the intermediate portion 32 of the first pipe 30 is intended to be housed inside an aerodynamic arm 40. The clamping portion 34 is located between the intermediate portion 32 and the end 31. The clamping portion 34 is more precisely located between the intermediate portion 32 and flange 314. The intermediate portion 32 is for example of tubular shape. The intermediate portion 32 has an outer diameter 30 strictly smaller than the minimum internal diameter of the arm 40 which the toga 3036437 14 so as to allow that the intermediate portion does not touch the inner surface of the arm 40, but is at a distance from this this. The pipe 30 may be dimensioned to ensure a transit function of a fluid under pressure, but for a support function 5 or support mechanical parts as is the case of the arms B. The section of the pipe 30 may be defined according to the optimized design practices of simple pipes and preferentially be according to standardized dimensions. The end portion 33, opposite to the end portion 31, 10 extends the intermediate portion 32. The portion 33 is provided with an axial oil inlet orifice intended to be aligned with the radial orifice 20 formed in the outer shell 2. The portion 33 is provided with a conical bearing surface 330 forming for example a nipple, the axial orifice being formed in the nipple.
    [0014] The portion 33 is also provided with an external thread 332. The portion 33 has an outer diameter less than or equal to the minimum internal diameter of the arm 40. In this way, the first pipe 30 can be engaged, by its portion 33, in the aerodynamic part 4 from its radially inner wall 41, through its aerodynamic arm 40, then out of the room 4 by its other wall 42. The different portions of the pipe 30 are integral with each other. The end portion 31, the clamping portion 34 and the flange can thus constitute a single piece.
    [0015] The intermediate portion 32 may furthermore be another part welded to the clamping portion 34, and the end portion 31 may be another part welded to the intermediate portion 32. The servitude 3 also comprises a heat-insulation 320 adapted to extend around the intermediate portion 32 of the first duct 30. The heat insulation has a generally tubular shape.
    [0016] The thermal insulation has an outer section of suitable dimensions so that the thermal insulation is at a distance from the internal surface of the aerodynamic arm 40, when the thermal insulation is housed inside the aerodynamic arm 40.
    [0017] In this way, when the first pipe 30 is inserted into an arm 40, the thermal insulation 320 does not touch the inner surface of this arm 40. The space left between the pipe 30 and the arm 40 surrounding it makes it possible to avoid mechanical stress or temperature between the arm 40 and the heat insulation 320.
    [0018] The presence of heat insulation 320 is nevertheless optional. In the absence of this heat insulation 320, the pipe 30 is directly opposite the inner surface of the arm 40. It is then expected that the pipe 30 itself has an outer section of dimensions adapted for the pipe 30 to be at a distance. of the inner surface of the aerodynamic arm 40, when the pipe 30 is housed inside the hollow aerodynamic arm. With reference to FIG. 6, the first pipe 30 has a sufficiently short length relative to the internal diameter of the annular shell 2 to allow, during assembly of the various parts of the inter-turbine casing, engagement of the annular shell 2 , along the main axis X, around the pipe 30 already screwed to the hub 1, and until its end portion 33 is aligned with a corresponding radial orifice 20 of the ferrule 2. This length of the first pipe, measured between its two ends 31 and 33, allows in particular a mounting of the outer shell 2 after the hub 1 and the first pipe 30 of the servitude 3 were screwed together. The easement 3 furthermore comprises a second pipe 36 intended to extend the first pipe 30 and to be in fluid communication with it.
    [0019] According to an oil flow direction in the easement, the second pipe 36 is located upstream of the first pipe 30. The easement further comprises means for interconnecting the two pipes 30 and 36.
    [0020] The second duct 36 comprises a concave end portion 361 adapted to receive the tapered seat 330 of the nipple formed at the end 33 of the first duct 30. The connector 361 and the nipple 330 are held in fluid communication with one another. help of connecting means 5.
    [0021] The connection means 5 may have the shape of a connecting ring 5 defining a housing for the end portion 361, the nipple 330 and the thread 332. The connecting ring 5 comprises an internal thread 52 giving in its housing and adapted to cooperate with the external thread 332. The connecting ring 5 further comprises and an inner shoulder 54 of a shape adapted to axially retain the end portion 361 in the housing when the threads 332 and 52 are engaged. one in the other.
    [0022] The second pipe 36 further comprises an end portion 362 opposite the portion 361, connectable to a third pipe or to a lubricant supply device. The portion 362 may for example be identical to the end portion 33 of the first pipe 30.
    [0023] The second pipe 36 has an intermediate portion 363 connecting its two ends 361 and 362, and of diameter adapted to pass through the radial orifice 20 formed in the annular shell 2. The intermediate portion 363 is bent between its two opposite end portions. 361 and 362 at an angle such that, when the first pipe is screwed to the hub 1 and the second pipe 36 is connected to the first pipe 30, the end portion 362 extends parallel to the main axis X, at a radial distance farther from the axis X than the ferrule 2. The servitude 3 is therefore partly radially outside the inter-turbine casing, which is delimited externally by the ferrule 2.
    [0024] The inter-turbine casing further comprises locking means 6 of the servitude 3 relative to the outer shell 2. The locking means 6 comprise an annular retaining ring 60 adapted to surround the connection ring 5, and thus limit the displacement of the ring 5 in a plane normal to the axis R.
    [0025] The retaining ring 60 has a collar 61 of shape adapted to abut against the radially outer surface 22 of the shell 2, when the retaining ring 6 is engaged at least partially in the radial orifice of the outer shell 2. The flange 61 is pierced with at least one through hole aligned with a blind hole 25 formed in the radially outer surface 22 of the ferrule 2 when the retaining ring 60 is engaged at least partially in the radial orifice of the ferrule. outer ferrule, the blind hole 25 forming a nut. The locking means 6 further comprise a screw 62 of diameter adapted to pass through the through hole formed in the flange 61, and be screwed into the blind hole formed in the shell 2, so as to block any displacement of the retaining ring. parallel to the axis R. The diameter of the through hole formed in the collar 61 may be greater than the diameter of the screw 62, so as to allow a slight play of the retaining ring 60 in a plane normal to the axis R when the ring is partially engaged in the radial orifice of the ferrule 2. The connecting ring 5 may have a spherical bearing intended to bear against the inner surface of the retaining ring 60 and thus sealingly seal the annular space between the two rings.
    [0026] Referring to Figure 6a, an annular seal 57 may be provided between the inner surface of the locking ring 60 and the outer surface of the connecting ring 5 housed therein. The connecting ring. 5 may also comprise a clamping portion 58 gripped by a clamping tool protruding from the radially outer surface 22 of the shell 2. The ring can thus be clamped easily by an operator from outside the outer casing. -turbine.
    [0027] Assembly of the Turbomachine Assembly Next, a method of assembling the various turbomachine parts previously described will be described. In a first step, the pipe 30 is fixed to the hub 1. During this first step, the end portion 31 of the first pipe 30 is inserted into the cavity formed in the hub 1, via the port of FIG. 10. An operator engages a clamping tool with the clamping surface 316 of the clamping portion 34, and rotates the conduit 30 in a direction of screwing the external thread 310 into the thread 12. The conduit 30 is then screwed to the hub 1 according to Figure 7. After the screwing (or during screwing), the complementary guide surfaces 14 and 314 are brought into contact one against the other, thus blocking any displacement of the pipe 30 screwed in a plane normal to the screw axis R. The location of the clamping portion 34 between the intermediate portion 32 and the end portion 31 screwed to the hub 1 lifts the diameter constraints imposed on the intermedia portions. according to the state of the art. It is now possible to reduce the diameter of the intermediate portion 31 without weakening the pipe 30 during its screwing by driving the clamping portion 34 in rotation, by means of a clamping tool, and therefore the diameter of the arm 40 which houses it, and consequently the diameter of the aerodynamic arm which togas the arm 40.
    [0028] With reference to FIG. 8, the fixing of the pipe 30 to the hub 1 may also include the positioning of a removable retaining ring 8 to block a displacement of the collar 314 along the axis R, for example by uncontrolled unscrewing of the first pipe 30 of the hub 1.
    [0029] The retaining ring 8 defines an inner housing 80 of diameter sufficiently large to contain the flange 314 and the edge 16 against which the flange 314 abuts. The retaining ring 8 is further adapted to be engaged, by rotation of the ring 8 along the axis R, in at least one notch 15 formed in the hub 1, when the flange 314 and the edge 16 are at its housing 80. The retaining ring 8 has at least one stop 82 projecting into the housing 80, the stop 82 defining a minimum internal diameter of the ring 8.
    [0030] The minimum diameter of the ring remains greater than the external diameter of the first pipe 30 and the thermal insulation 320. The stop is adapted to limit or even prohibit an axial displacement along the axis R of the collar 314, when the ring is engaged in the or your notches 17 of the hub 1.
    [0031] The retaining ring 8 may comprise a retaining ring 84 of dimensions adapted to be partially received in a corresponding groove 18 of the hub 1, so as to facilitate the positioning of the ring at a radial position which allows its engagement in the or the notches 17 of the hub 1. The ring is formed of a metallic material.
    [0032] Referring to Figure 9, the end 33 of the pipe 30, free at this stage of assembly, is passed inside the arm 40 of one of the aerodynamic fairings 4. The aerodynamic fairing 4, intended for s extend over a limited angular sector around the X axis, can be brought closer to the hub 1 in a substantially centrifugal direction (for example the axis R) illustrated by the arrows of FIG. 9, and fixed to the hub 1 by means of appropriate means. To do this, the end portion 33 of the pipe 30 is inserted in the aerodynamic arm 40 by the radially inner surface 41, then leaves the arm 40 by the radially outer wall 42 of the aerodynamic fairing 4. Once the fairing 4 fixed to the hub 1, the intermediate portion 32 passes radially through the arm 40 of this part and the end portion 33 of the first pipe 30 is at a radial position further from the X axis than that of the aerodynamic fairing 4 The foregoing steps are repeated for each aerodynamic fairing 4 to form the annular air stream around the X axis, for each first pipe 30 to be arranged radially about the X axis, and for each each arm of connection to arrange radially around the axis X. Referring to Figure 10, the annular shell 2 is then fixed to the hub 1 via the connecting arms B. To do this, the assembly "hub 1 + fairings a Erodynamic 4 defining the air vein + connecting arm B + first conduits 30 passing through connecting arms B "is aligned relative to the shell 2 so that the axis of the shell and the hub axis 1 merge into the X axis. The link arms B, and the first pipes then extending radially relative to this common axis X. The aforesaid assembly is inserted into the annular shell 2 by moving along the axis X, with respect to the shell 2, until the end portion 33 of each pipe 30 is aligned with a pipe 30. 21 during said displacement, the end portion 33 is at a distance from the radially inner surface 21 of the ferrule, because of the length chosen for the pipe 30.
    [0033] In this position aligned with the port 20, the link arms B are then attached to the shell via appropriate means. With reference to FIG. 11, the locking means 6 are fixed to the outer shell 2. More specifically, the locking ring 60 is partially inserted into the radial orifice via the outside of the shell, in a centrifugal direction, until its collar comes into abutment against the radially outer surface of the shell 2, and so that its opening hole is aligned with the corresponding blind hole formed in the ferrule. The screw is then engaged through the hole of your collar, then into the blind hole of the ferrule 2.
    [0034] With reference to FIG. 12, the second duct 36 is placed in fluid communication with the first duct 30, by means of connection means 5. More specifically, the end portion 361 is inserted into the housing of the ring. 5 and then connected, for example by welding, to the curved intermediate portion 363 of the pipe 36. The connecting ring is then inserted into the locking ring, itself inserted into the radial orifice. The spherical bearing surface projecting from the outer periphery of the connecting ring then presses the inner surface of the locking ring, thus blocking the connecting ring along the axis R, and thus maintaining the portions 332 and 361 in fluid communication. with each other. At the same time, the complementary outer surface 332 and inner surface 52 are brought into contact so as to improve the sealing of the fluidic connection between the nipple 330 of the duct 30 and the concave end portion 30. 361 of the pipe 36. The assembly of the servitude 3 with the inter-turbine casing as shown in Figure 3 is then obtained.
    [0035] The inter-turbine casing is also assembled with the two upstream and downstream turbines, and the servitude 3 is connected to a lubrication source. In the proposed assembly method, the step of screwing the first pipe 30 to the hub 1 comprising the bearing support is implemented before the ferrule 2 is fastened to the hub 1 by means of the link arms. and before the assembly of aerodynamic fairings 4 which forms the air stream between the turbomachines of the turbomachines. This assembly order is advantageous in that it allows a replacement of the outer shell 2 and / or of at least one connecting arm and / or at least one aerodynamic fairing 4, without having to dismantle the servitude in full. Indeed, it is possible, during such a replacement, to leave the first pipe 30 of the servitude 3 in fluid connection with the bearing support.
    [0036] During the operation of the turbomachine, oil from said source is communicated to the bearing support for lubrication, passing successively through the pipe 36, then through the pipe 30, then through the access port 10. formed in hub 1. 25
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Turbomachine assembly comprising: - an inter-turbine casing comprising: o a hub (1) comprising a bearing support, o a shell (2) extending around and away from the hub, o at least one arm (40) s extending radially between the hub (1) and the ferrule (2), - at least one servitude (3) for lubricating the bearing support, the servitude (3) comprising a first pipe (30) having: o a portion of end (31) screwed to the hub (1) to put the first pipe (30) in fluid communication with the bearing support, o an intermediate portion (32) integral with the end portion, housed inside the arm ( 40) when the end portion (31) is screwed to the hub (1), o a clamping portion (34) integral with the end portion (31) and adapted to be rotated by a clamping tool, characterized in that the clamping portion (34) is located between the screwable end portion (31) and the intermediate portion (32).
    [0002]
    2. A turbomachine assembly according to the preceding claim, 25 comprising sealing means (19) adapted to put the end portion (31) in fluid-tight communication with the bearing support, when the end portion is screwed to hub (1).
    [0003]
    3. Turbomachine assembly according to one of the preceding claims, wherein the clamping portion (34) comprises a plurality of clamping sections defining a free polygonal section surface (316) grippable by a clamping tool.
    [0004]
    4. Turbomachine assembly according to one of the preceding claims, wherein: the ferrule (2) is annular in shape around a main axis (X), and has at least one radial through orifice (20); the first pipe (30) comprises a second end portion (33) opposite to the end portion (31) screwable to the hub (1), - the first pipe (30) has a length sufficiently short to allow insertion along the main axis of the hub (1) and the first pipe (30) screwed to the hub (1) in the shell (2), until the second end portion (33) is aligned with the radial orifice (20), the ferrule (2) extending around the first pipe (30) screwed to the hub (1).
    [0005]
    5. Turbomachine assembly according to the preceding claim, wherein the easement (3) further comprises a second pipe (36) adapted to be in fluid communication with the first pipe (30), the servitude (3) being of dimensions adapted to pass through the radial orifice (20) of the ferrule (2).
    [0006]
    6. Turbomachine assembly according to one of the preceding claims, wherein the first pipe (30) comprises a second end portion (33) opposite the end portion (31) screwable to the hub (1), the servitude (3) having, from the intermediate portion (32) included to the second end portion (33), an outer diameter less than or equal to the minimum internal diameter of the arm (40). 3036437 25
    [0007]
    7. Turbomachine assembly according to one of the preceding claims, wherein the easement (3) further comprises a heat insulation (320) adapted to extend around the intermediate portion (32) of the first pipe (30), the heat insulation (30) having an outer diameter strictly less than or equal to the minimum internal diameter of the arm (40).
    [0008]
    8. A turbomachine assembly according to one of the preceding claims, wherein the end portion (31) has an outer guide surface (312), and wherein the hub (1) comprises a cavity for receiving the portion of screwable end (31), the cavity having a diameter complementary to the outer guide surface (312). 15
    [0009]
    9. A turbomachine assembly according to one of the preceding claims, wherein the first pipe (30) comprises a flange portion (314) arranged between the end portion (31) screwable and the clamping portion (34), the flange having a surface adapted to abut against the hub (1) during screwing of the end portion to the hub (1).
    [0010]
    10. A method of assembling a turbomachine assembly according to one of the preceding claims, comprising steps of: - screwing the end portion (31) to the hub (1), by rotational drive of the portion clamping by means of a clamping tool, so as to put the first pipe (30) in fluid communication with the bearing support, and - insertion of the intermediate portion (32) in the arm (40), - attachment of the arm (40) to the shell (2), wherein the screwing step is carried out before the insertion step and / or before the fixing step.
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    同族专利:
    公开号 | 公开日
    FR3036437B1|2017-05-05|
    CN107646066A|2018-01-30|
    CN107646066B|2019-09-20|
    US10557376B2|2020-02-11|
    WO2016189234A1|2016-12-01|
    EP3298243B1|2019-05-01|
    US20180119575A1|2018-05-03|
    EP3298243A1|2018-03-28|
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    法律状态:
    2016-05-25| PLFP| Fee payment|Year of fee payment: 2 |
    2016-11-25| PLSC| Publication of the preliminary search report|Effective date: 20161125 |
    2017-04-27| PLFP| Fee payment|Year of fee payment: 3 |
    2018-02-02| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 |
    2018-04-23| PLFP| Fee payment|Year of fee payment: 4 |
    2019-04-19| PLFP| Fee payment|Year of fee payment: 5 |
    2020-04-22| PLFP| Fee payment|Year of fee payment: 6 |
    2022-02-11| ST| Notification of lapse|Effective date: 20220105 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1554621A|FR3036437B1|2015-05-22|2015-05-22|TURBOMACHINE ASSEMBLY FOR LUBRICATING A BEARING SUPPORT|FR1554621A| FR3036437B1|2015-05-22|2015-05-22|TURBOMACHINE ASSEMBLY FOR LUBRICATING A BEARING SUPPORT|
    US15/575,654| US10557376B2|2015-05-22|2016-05-20|Turbine engine unit for lubricating a bearing holder|
    PCT/FR2016/051197| WO2016189234A1|2015-05-22|2016-05-20|Turbine engine unit for lubricating a bearing holder|
    EP16729314.1A| EP3298243B1|2015-05-22|2016-05-20|Turbine engine unit for lubricating a bearing holder|
    CN201680029601.2A| CN107646066B|2015-05-22|2016-05-20|For lubricating the turbine engine components of bearing spider|
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