• 专利附录
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    • 专利摘要:
    A suspension device (30) for the suspension of a turbomachine (1) to a pylon (131) is concerned, the device comprising: a first member (31) interposed between a first and a second lug (33a, 33b); ) a second member (130), the first member having a bore (39) for passage of an axis (41) passing through the first and second sockets (43,45) respectively mounted in said first and second ears, and a clamping member (47) cooperating with the axis (41). The device further comprises: a third bushing (55) mounted in the second lug (33b) and having radial centering means (551) which cooperate with complementary centering means (411) of a head portion of the axle (41); and a fourth sleeve (57) mounted axially slideably axially biased by the clamping member (47), and comprising radial centering means (571) which cooperate with complementary centering means (431). ) of the first sleeve (43).
    公开号:FR3059645A1
    申请号:FR1661882
    申请日:2016-12-02
    公开日:2018-06-08
    发明作者:Patrick Tesniere Marc；Emmanuelle Besnard Maryline
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    Holder (s): SAFRAN AIRCRAFT ENGINES Simplified joint-stock company.
    Extension request (s)
    Agent (s): ERNEST GUTMANN - YVES PLASSERAUD SAS.
    (54) SUSPENSION DEVICE FOR TURBOMACHINE.
    FR 3 059 645 - A1 _ Is concerned a suspension device (30), for the suspension of a turbomachine (1) to a pylon (131), the device comprising:
    - A first member (31) interposed between a first and a second lugs (33a, 33b) of a second member (130), the first member having a bore (39) for the passage of an axis (41) passing through the first and second sockets (43,45) mounted respectively in said first and second ears, and
    - A clamping member (47) cooperating with the axis (41).
    The device also includes:
    a third bushing (55) mounted in the second ear (33b) and having radial centering means (551) which cooperate with complementary centering means (411) of a head portion of the axis (41),
    - And a fourth bush (57) mounted to slide axially, urged axially by the clamping member (47), and comprising radial centering means (571) which cooperate with complementary centering means (431) of the first bush ( 43).
    1 330b Jb
    I / '' - 41 410b
    i
    Suspension device for a turbomachine
    The present invention relates to a suspension device, for suspending a turbomachine from a pylon or suspending equipment from a turbomachine body.
    This particularly concerns a situation where a turbomachine, such as an aircraft turbojet or turboprop, is to be suspended from an aircraft structure on which is mounted a fastening member such as a pylon. The pylon is a structural assembly permanently mounted on the aircraft, that is to say that it remains fixed to the structure of the aircraft, typically a wing or a fuselage in the case of an aircraft, in particular during removing or installing the turbomachine.
    The turbomachine is then generally suspended from at least one such pylon by means of a "yoke" (a term from Franglais whose imperfect translation is "yoke" or "yoke"), also called "beam" in the present application. , which generally has the shape of a hoop having two ends which each include a yoke. Each of the two yokes is connected to the body of the turbomachine, typically at an intermediate casing of the turbomachine, by means of a connecting rod as for example described in FR2867155A1 or also of a vibration filtration unit also called "Isolator" as for example described in US5762295A. The beam is part of a device for suspending the turbomachine from the pylon, and is intended to be fixed to the pylon, typically by bolting.
    Comparable situations can be found in the case of equipment suspension from a turbomachine body.
    The assembly between a yoke and a part such as a rod end or an insulator is generally carried out in a configuration where the part is brought between the two ears of the yoke, before installing an axis intended to pass through each ear and the part to be fixed to the yoke by tightening the axis using for example a nut. Such devices for mounting an axis on a yoke, in particular for the suspension of a turbomachine or of equipment, have already been proposed for example in FR3003896A1.
    In fact, solutions are already known in the field where the suspension device comprises:
    - A first member interposed between a first and a second ears of a second member, the first and second ears respectively having first and second orifices, the first member having a bore for the passage of an axis (hereinafter referred to as through axis) ) which passes through first and second sockets mounted respectively in said first and second orifices, the first socket being slidably mounted inside the first orifice,
    a clamping member cooperating with an end section of the through axis to exert an axial force on the first bushing in order to clamp and axially block the first member between the first and second bushings,
    - A third socket mounted in said second orifice of the second ear and free from axial stress with respect to the second socket.
    The bushings are wearing parts that protect the holes (such as bores) from the ears of each yoke of the beam. Thus, the axis mounted on a yoke is not directly in contact with the yoke.
    Among the disadvantages of such an assembly we can note:
    - the possibility of reversing certain sockets,
    - difficulties in mounting the axis in the first multi-room member.
    Indeed, in certain configurations, the suspension beam (yoke) is previously mounted on the pylon while the first member is mounted in the workshop on the turbomachine. This may be the case for example of a pylon disposed laterally on the fuselage of an aircraft, with the beam fixed to the pylon by bolting means, part of the positioning and the tightening being effected from the interior of the fuselage with difficult access. As a result, the aircraft manufacturer can choose to have the beam permanently attached to the pylon. To install the turbomachine on the aircraft, it is then necessary that the assembly of the first member to a yoke of the beam is carried out not in the workshop but during the docking of the turbomachine on the beam fixed to the pylon. The first member, which must be inserted between the two ears of a yoke of the beam, is moved by means of hoisting the turbomachine, called GSE (Ground Support Equipment / Airport Support Equipment). The precision of this movement is very relative, the turbomachine being generally lifted by a hoist and may even under certain conditions be subject to gusts of wind.
    However, the axis provided for assembling the first member to the yoke must pass through the bushings as well as a cylindrical passage of the first member with a radial clearance which can be of the order of less than 0.10 mm.
    It is therefore almost impossible to align the axis of the cylindrical passage 15 of the first member with the axes of the bores while respecting such a small radial clearance, in a docking situation of the turbomachine. The placement of the axle in its housing generally requires a forceful insertion to adapt to the misalignment, which most often results in premature wear of the axle, the sockets, and the first member.
    A technical problem to be solved is to integrate the clearances necessary to allow mounting without major difficulty in a docking situation of the turbomachine, without damaging the axis, the sockets, or the first member (which may include a structure sometimes called "Insulator").
    It can also be sought:
    - a solution allowing reliable security of the axle-clevis assembly so as not to climb upside down or forget about sockets,
    - integrated games, necessary for the proper functioning of the assembly and its mechanical strength.
    To provide a useful solution to overcome at least part of the problems, it is proposed that the suspension device presented above as known, and having the aforementioned characteristics, be such:
    - that the third bush comprises radial centering means which cooperate with complementary centering means of a head section of the through axis,
    - And that the device further comprises a fourth sleeve mounted to slide axially, urged axially by the clamping member, and comprising radial centering means which cooperate with means for centering complementary to the first sleeve so as to center the fourth radially socket relative to the first socket.
    Although the first member may for example be the body of a thin pylon, it is intended that the first member may be multi-room and include a tubular part having said bore for passage of the through axis, said tubular part being axially blocked between (by) the first and second sockets.
    Such a first multi-part member may make it possible to facilitate manufacture and / or to use multifunction parts, such as a fixing block which can define or include a structure called an “isolator” intended to filter the vibrations transmitted by the turbojet engine to the aircraft.
    It is also proposed that the first and second sockets each have a shoulder, said shoulders being located on an inner side of the ears, respectively.
    This will favor the axial supports and, in this axial direction, a good distribution of the forces between the parts concerned.
    It is also expected that the tightening member being completely mounted, an axial clearance (I below) is established between said shoulder of the first sleeve and a wall of a housing of the first ear which faces it.
    Thus, the first socket may move axially from the second socket until its shoulder comes into contact with the interior side of the first ear, this axial spacing aimed at facilitating the introduction of said first member between the two sockets, in particular when this first member comprises a said tubular part. Furthermore, such an axial clearance I will facilitate the adjustment of the operating clearances, the fourth bushing being slidably mounted in its housing provided in the first bushing (connection with radial centering, for example conical, mentioned above).
    It is also expected that the second and third sockets can be mounted axially tightened in said second orifice of the second ear, with an axial clearance (Jb below) between them, on either side of this second ear. This is a relevant way of ensuring freedom of axial constraint, with respect to the second socket, of the third socket mounted in the second orifice of the second ear.
    In addition, such an axial clearance will avoid any interference with the radially centered connection between the third bushing and the through axis, each part playing its role at best:
    - second socket: wedging and holding the first member, between it and the first socket,
    - third sleeve: centered passage for the radial centering effect of the through axis.
    Still for an assembly without major difficulty of this crossing axis, without damaging it, nor the sockets, it is favorable that the fourth socket and said axis, which therefore crosses it, have between them a sliding assembly allowing a radial adjustment of the axis.
    This is permitted by the other aforementioned mounting characteristics.
    To limit the (axial) tightening forces involved, and therefore the risk of plasticization of the through axis, while controlling costs where appropriate, it is also proposed:
    - That the tightening member is a nut, and that, on the side of this nut, the through axis has a shoulder so that said through axis has an end section with a diameter less than the diameter of a first section than the 'through axis present between the first and second ears, the nut being screwed onto said end section,
    - And that the fourth sleeve has a bore provided with a shoulder which internally has a cylindrical wall mounted to slide around a cylindrical wall of said end section, said shoulder having an axial clearance (Jd below) with the shoulder of through axis.
    Thus, the fourth socket can transmit to the first socket the axial tightening applied by the nut, once the axis is installed through the parts which it has to pass through, making it possible to axially tighten and block the first member 31 between the first socket and the second socket.
    It is also proposed that the shoulders of the first and second sockets have different diameters between them and that the housings of the first and second ears which receive them are also of different diameters.
    This will promote the fact that the first and second sockets cannot be reversed during their mounting.
    It is also proposed that the first socket has an outer wall in contact with a wall of the first orifice of said first ear of said second member (which can therefore be a suspension hoop).
    This will promote the efficiency and quality of the radial centering between the first and fourth sockets.
    Again to facilitate the passage of the through axis, it is proposed that the present device further comprises a nozzle having a conical end and which is to be temporarily disposed around said end section of the axis to promote the passage of said axis through the bore of the first organ.
    It is further provided that the first and second sockets can each favorably have a radial clearance (I and / or Ja below) greater than or equal to 1 mm relative to the axis which passes through them.
    Thus, the passage and the mounting security of the axis will be facilitated, without detrimental consequence for the axial tightening and blocking between the first member and the ears of the second member. This is very favorable for the engagement of the axis in the bore of the first member and in the conical bushings, thus allowing more play when the engine is docked.
    Also concerned by the present application is a turbomachine, such as a turbojet or an airplane turboprop, equipped with the aforementioned device having all or some of the characteristics successively mentioned.
    It will be noted that, in the present description:
    - "radial (ement)" has the meaning (overall) radial (ement) to the axis (X1) of mounting / dismounting of said "traversing axis". Typically, at least in the case of the suspension of a turbomachine by a pylon, this axis will be transverse to the axis (X) of revolution of the turbomachine, which is the axis along which generally flows from upstream downstream the flow of fluid to be circulated there,
    - "axial (ely)" has the meaning (globally) following or parallel to the aforementioned axis (X1),
    - and "front and rear", as "upstream and downstream" locate two respective locations along this axis X1. The "front" or "upstream" will be closer to the air intake in the turbomachine than the "rear" or "downstream" which will be further along the X axis, further downstream.
    The invention will be better understood if necessary and other details, characteristics and advantages of the invention may appear on reading the following description given by way of nonlimiting example with reference to the accompanying drawings in which:
    - Figure 1 is a schematic front view (axial) of an aeronautical turbomachine part equipped with the suspension device of the invention mounted on a structure of an aircraft, such as a pylon attached to the fuselage of this aircraft,
    FIGS. 2 and 3 show details of the suspension device, corresponding to respectively perspective and front views according to arrow II in FIG. 1,
    - Figure 4 is a schematic view, partially lateral, partially in section of a partial longitudinal half-section of another example of an aeronautical turbomachine mounted on an aircraft, under a wing seen in section, and equipped with the suspension device the invention,
    - Figure 5 is a view identical to that of Figure 4, with an alternative mounting of the suspension device of the invention,
    - Figures 6,7 correspond to section VI-VI of Figure 2 or 3, at two different times of mounting of the through axis, along the transverse axis X1.
    As shown diagrammatically in FIG. 1, the gas generator 5 of a turbojet engine comprises a casing part 36, for example an intermediate casing, on which are fixed two fixing blocks 31 which can each comprise a structure called “insulator” intended for filter the vibrations transmitted by the turbojet engine to the aircraft. The two fixing blocks 31 are intended to be connected to a suspension part 131, also called “yoke” or “beam” in the present application, fixed to a pylon 32 itself fixed to the fuselage structure of the aircraft . In the case of a turbofan, the casing part 36 forms a radially inner wall of a conduit through which the secondary flow passes. The two fixing blocks 31 and the suspension piece 131 are therefore located in a stream of secondary flow, and constitute an aerodynamic disturbance for the flow.
    The suspension device 30 formed by the suspension part 131 and the fixing blocks 31 thus makes it possible to suspend the turbojet engine, at its intermediate casing 36, from the pylon 32 of the aircraft. In this example, the pylon 32 is positioned laterally on the fuselage of the aircraft. In this case, we can say that the turbojet engine is suspended horizontally.
    In such a case, provision may be made for the suspension part 131 to be a front or rear suspension beam of the engine.
    As a whole, the suspension device 30 comprises, as shown diagrammatically in FIGS. 6 and 7:
    a first member 31, multi-piece in this example, axially interposed between first and second ears (or yokes) 33a, 33b of a second member 130, these first and second ears respectively having first and second orifices 37a, 37b,
    an axial bore 39 formed in a tubular part 51 of said first member
    31,
    a threaded pin 41 passing through the bore 39 and first and second sockets 43, 45 mounted respectively in said first and second orifices 37a, 37b,
    - A clamping member 47, such as a nut, cooperating with a front part, also called end section, 410a of the axis 41 passing through, to clamp and axially lock together the first member 31 and the ears 33a, 33b.
    The terminal section 410a is that which is axially opposite to that 410b, called rear portion or head section, provided with centering means, called complementary, 411 provided to cooperate with the radial centering means 551 of the third bushing 55 that the we present below.
    The through axis 41 is mounted horizontally, along the axis X1, transversely to the engine axis or aircraft axis, X.
    The first member 31 can be secured (directly or for example by bolting) to the gas generator 5 of the turbomachine, more specifically to its intermediate casing 36 (FIG. 1).
    The ears (or yokes) 33a, 33b may be integral with the suspension beam131 by which the turbomachine is here suspended from the pylon
    32.
    Thus, the second member 130 can be formed by any one of the two ends of the suspension beam 131.
    This suspension beam 131 can be in the form of an arch.
    In the example, the first member 31 is multi-piece and includes a fixing block 49 (which may be the structure called "insulator" mentioned above), the tubular piece 51 mounted with a radial clearance in the fixing block 49, and two elastomer sleeves 53a, 53b.
    ίο
    The two elastomer sleeves 53a, 53b are mounted along the axis X1 between two shoulders 51a, 51b at the ends of the tubular part 51 and respectively two metal sides 49a, 49b of the fixing block 49.
    It is therefore understood that the first member 31, which can therefore be multi-room, makes it possible to filter the vibrations transmitted by the turbojet engine to the aircraft via the suspension beam 131, which can be directly fixed to the pylon 32 as shown in FIG. 1 without require intermediate vibration filtering device.
    As shown in FIGS. 2 and 3, screws 50 secure the first member 31 to a motor casing, here the intermediate casing 36.
    From the second to the first of the two ears (or yokes) 33b, 33a, the through axis 41 passes through the tubular piece 51 around which the elastomer sleeves 53a, 53b and the metal pad 49 are mounted, axially (axis X1) clamped between the shoulders 51 a, 51 b of the tubular part 51.
    To allow its installation, the tubular part 51 may be in several parts, such as two parts as illustrated.
    To ensure, as mentioned above:
    - the clearances necessary to allow mounting without major difficulty, without damaging the axis 41, the sockets, or the first member,
    - and those useful for the proper functioning of the assembly and its mechanical strength, it is therefore also proposed that:
    a third socket 55 is mounted in said second orifice 37b of the second ear 33b,
    the third bushing 55 comprises radial centering means 551, such as a conical radial surface, which cooperate with complementary centering means 411, such as another conical radial surface, of the head section 410b of the through axis 41,
    - And the suspension device 30 further comprises a fourth bush 57 mounted to slide axially, urged axially by the clamping member 47, and comprising radial centering means 571 which cooperate with complementary centering means 431 of the first bush 43, so as to center the fourth bush radially with respect to the first bush.
    The respective radial centering means 431 and 571 may again include cooperating conical radial surfaces, in mutual contact, it being specified that the conical radial surfaces could be replaced by curved profiles.
    The third socket 55 is free of axial stress with respect to the second socket 45. Suspension device 30 mounted, with its axially tightened parts, one of these sockets 45, 55 does not push axially on the other. For this, the second and third sockets 45, 55 may be mounted axially tightened in the second orifice 37b of the second ear, with an axial clearance Jb between them, on either side of this second ear 33b. This will also limit the risk of interference between the second socket 45 and the radial centering link established between the third socket 55 and the through axis 41, each part playing its role at best.
    The fourth socket 57 will preferably be mounted directly around the through axis 41 and in the first socket 43.
    To secure the supports of the first and second sockets 43,45 axially against the tubular part 51 during tightening of the axis, these sockets may also each have a shoulder, respectively 43a, 45a, these shoulders being situated on an inner side ears, respectively (therefore towards the first member 31 and its tubular part 51).
    To promote the engagement of the transverse axis 41 in the bore 39 of the first member 31 and in the sockets, thus allowing more radial play to be had when the engine is approaching, with such a radial play which may even being of the order of a mm (or even several mm), it is also proposed that, as illustrated, the first and second sockets 43, 45 each have a radial clearance Ja, Je with respect to the axis 41 which passes through them. This radial clearance is preferably greater than or equal to 1 mm.
    The present assembly will therefore allow the presence of a play of the order of mm and even more.
    Furthermore, it is proposed, to facilitate the axial mounting of the through axis 41, that the fourth bush 57 and said axis 41 which passes through it have between them a sliding radial fit (smooth part 412 not threaded).
    Beyond, towards its axial end opposite the cone 411, the through axis 41 will preferably have a shoulder initiating the front end section, 410a which, for its part, is threaded.
    Indeed, to limit the (axial) tightening forces involved, and therefore the risk of plasticization of the through axis 41, while controlling the costs, it is advised that, on the side of the nut 47, the axis through 41 has this end section 410a shouldered, so that, facing this nut, said axis 41 has an end section S2 of diameter smaller than that of a main section S1 that the axis 41 has between the first and second ears 33a, 33b.
    As for the adjustment of the operating clearances, it will be facilitated if the first sleeve 43 is mounted sliding in the first port 37a and if the second sleeve 45 is mounted tightly in the second port 37b.
    An axial clearance Jc will also then be established between the shoulder 43a of the first sleeve 43 and the inner side 331 which faces it of the first ear 33a.
    Again for the crossing of said axis 41, it is proposed that the fourth sleeve 57 has a bore provided with a shoulder 570 passing its section substantially from S1 to S2, the shoulder 413 of axis 41 and that of the fourth sleeve having an axial clearance Jd between them.
    A relatively limited effort to tighten the nut 47 will then be sufficient for the fourth socket 57 to act effectively on the axis 41.
    To also avoid that the first and second sockets 43,45 can be reversed during their assembly, it is advisable:
    that the shoulders 43a, 45a of the first and second sockets have different diameters between them and that the housings 330a, 330b of the first and second ears 33a, 33b which receive them are also of different diameters,
    - And / or that the first socket 43 has axially a thickness e1 (axis
    X1) greater than that e2 of the second socket 45.
    And to further facilitate the assembly, or even the axial disassembly of the through axis 41, it is also proposed, as shown in FIG. 4, that a nozzle 59 having a conical axial end 590 be temporarily placed around the end part 410a of reduced section S2 of the through axis 41.
    Once the axis 41 is mounted through the bores of the device, along the axis X1, the end piece 59 will be removed which has a hollow part which can be engaged, for example, by screwing around the end part 410a.
    The mounting of this through axis 41 can be done as follows:
    - first, tight mounting of the second and fourth sockets 45, 55 in the second orifice 37b of the second ear 33b,
    - sliding mounting of the first socket 43 in the first orifice 37a of the first ear 33a,
    - said vertical docking, that is to say perpendicular to the axis X1, of the parts 49, 51 of said first multi-piece member 31, also with the elastomer sleeves 53a, 53b already mounted, between the first and second sockets 43, 45. This docking is made possible by the axial clearance Jc of operation of the first socket 43, since the latter can deviate axially from the second socket 45 until its shoulder 43a comes into contact with the interior side 331 of the first lug 33a which faces it, the axial spacing between the first and second sockets 43, 45 then being somewhat greater than the axial length of the tubular part 51 to facilitate the introduction of this tubular part between the two sockets,
    - axial mounting of the through axis 41, by successive passage in the sockets 55 then 45, then in the tubular part 51 of the insulator 49, and in the first socket 43,
    - mounting the fourth socket 57 in its housing provided on the first socket 43, and on the through axis 41; at this stage, the fourth sleeve 57 is not completely in position in its housing of the sleeve 43, this is all the less if the through axis 41 is offset by having used the radial clearances Ja and I allowed by the first ones respectively and second sockets 43.45,
    - Axial tightening of the nut 47, which brings the conical radial surfaces 571 and 431 respective of the sockets 57 and 43 into full contact with each other, and centers the transverse axis 41 with the tubular part 51 of the insulator 49.
    During this tightening, the conical part 411 of the through axis 41 is wedged in its conical housing 551 of the third bush 55, refocusing on the axis X1 the through axis 41.
    The suspension device of the invention can find applications in other examples of mounting an aeronautical turbomachine on an aircraft. In particular, in the case of a turbofan engine with a high dilution rate, the radial dimensions of the fan and its casing are relatively large compared to the radial dimensions of the casing of the gas generator. The pylon on which the gas generator suspension device is mounted can extend over a relatively large radial height, so as to come close enough to a part of the gas generator housing on which a relatively compact radially suspension device is installed.
    An example of a turbofan engine with a high dilution rate is shown very diagrammatically in FIGS. 4 and 5. The fan 2 at the front of the turbojet engine rotates around the axis X of the engine in the fan casing 3, to the passage of the secondary flow 4a. Downstream (or further back along the X axis), the gas generator 5 is housed inside a set of casing (s) 9. The gas generator 5 comprises the compression stages 6 downstream (or at the rear) of the fan, the combustion chamber 7 and the turbine stages 8 through which the gases of the primary flow 4b pass. The gas generator 5 comprises, downstream, an exhaust cone 10 around which the burnt gases of the primary flow 4b flow in particular.
    Two methods of attaching such a turbomachine are shown in Figures 4 and 5 and relate to the invention.
    In the first method of attachment (FIG. 4), the engine is suspended or hung under the wing 11 of an aircraft via, at the rear, a rigid structure forming a pylon 13.
    Axially, the pylon 13 extends between the fan casing 3 and a rear spar 15 of the wing 11.
    Towards the rear, the pylon 13 is fixed to the rear spar 15, by conventional fasteners 17 which may include bolts.
    The attachment of the engine is generally ensured by suspensions, generally identified in 19 and comprising:
    a front attachment means 21 between the fan casing 3 and a structure 23 of the aircraft, which can, as here, be a front spar of the wing 11,
    - And a rear attachment means 25 between a rear part of the housing assembly (s) 9 and the pylon 13.
    At least one of the attachment means 21,25 may comprise a suspension device according to the invention.
    If necessary, the other of these attachment means may comprise at least one ball joint device corresponding to what is disclosed in FR 3 003 896 A1 where, however, there is no radial clearance authorized by the bushings for easy assembly of the axle (with cylindrical body which crosses the cylindrical bore of the ball joint). In addition, the assembly of a suspension beam to the motor by means of the ball joint articulation device of FR 3 003 896 A1 is preferably carried out on a motor in the workshop to succeed in retracting the axis without damaging the bushings. where the ball joint, therefore without docking constraint.
    Note that the fan casing can be extended downstream by an intermediate casing located in the axial extension of the fan casing. For the sake of simplification, the fan casing and the intermediate casing are here represented together by the same part 3. The front fastening means 21 then connects the intermediate casing to the structure 23 of the aircraft.
    In the second attachment mode (Figure 5), we find the pylon 13 fixed rearwardly to the rear spar 15, by conventional fasteners
    17.
    In this case, the attachment of the engine is generally ensured by suspensions generally identified at 27 and comprising:
    - a front hooking means 28 here between a front part of the casing assembly (s) 9 and a front part of the pylon 13,
    - And a rear attachment means 29 between a rear part of said housing assembly (s) 9 and the same pylon 13 of the aircraft.
    As in the case of FIG. 4, at least one of the hooking means 28, 29 can comprise a suspension device according to the invention.
    The suspension device according to the invention, generally identified in FIG. 6, can be used in particular in the two above cases (FIGS. 4 and 5) described by way of examples, and can therefore correspond to one at minus attachment means 21,25,28,29.
    In the case where the suspension device 30 corresponds to at least one of the means 25, 28, 29 for suspending the gas generator 5 from the pylon 13, the first member 31 may consist of a part such as an end of the connecting rod or an insulator, mounted on a casing of the gas generator 5 and intended to be interposed between a first and a second lugs 33a, 33b of the second member 130. This second member 130 may consist of a yoke of a beam fixed to the pylon 13 , under the pylon. Such a configuration makes it possible to keep the beam fixed to the pylon during the installation or the removal of the turbomachine, the assembly between the first member 31 and the second member 130 being made possible in a docking situation of the turbomachine during its pose.
    As an alternative, in particular in the case where the pylon 13 (so-called thin pylon) has a relatively reduced thickness, for example less than 250 mm, at least at its interface with the beam, provision may be made to mount the beam on the turbomachine prior to docking of the turbomachine during installation. It can also be provided to secure the beam to the pylon, when the turbomachine is docked on the pylon, by a fixing device comprising an upper yoke integral with the beam and a transverse axis passing through the yoke and the pylon. The first member 31 then consists of a part of the pylon having a bore made in its thickness for the passage of the axis.
    The invention makes it possible to accommodate a misalignment, during docking, between the respective geometric axes of this bore and the orifices of the yoke.
    Furthermore, in the hypothesis, mentioned at the beginning of the text, of the suspension of an item of equipment from a part of a turbomachine, provision may be made for a fastening member to be fixed to the turbomachine to receive the equipment. The attachment member in this case comprises yokes on which the equipment is mounted, for example by means of connecting rods or insulating blocks which are just fixed to the yokes by pins and sockets in accordance with the provisions described in the above. During assembly or disassembly of the equipment, the attachment member remains attached to the turbomachine.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. Suspension device (30), for suspending a turbomachine (1) with a structural member such as a pylon (13, 32) of an aircraft, or suspending equipment from a turbomachine body, the device comprising:
    - a first member (31) interposed between a first and a second ears (33a, 33b) of a second member (130), the first and second ears respectively having first and second orifices (37a, 37b), the first member (31) having a bore (39) for the passage of an axis (41) which passes through first and second sockets (43,45) mounted respectively in said first and second orifices (37a, 37b), the first socket (43) being mounted sliding inside the first orifice (37a),
    - A clamping member (47) cooperating with an end section (410a) of the axis (41) to exert an axial force on the first sleeve (43) in order to clamp and axially block the first member (31) between the first and second sockets (43.45),
    a third bushing (55) mounted in said second orifice (37b) of the second bushing (33b) and free from axial stress with respect to the second bushing (45), characterized in that:
    the third bushing (55) comprises radial centering means (551) which cooperate with complementary centering means (411) of a head portion of said axis (41),
    - And the device further comprises a fourth sleeve (57) mounted to slide axially, urged axially by the clamping member (47), and comprising radial centering means (571) which cooperate with complementary centering means (431) of the first socket (43) so as to center the fourth socket radially with respect to the first socket.
    [2" id="c-fr-0002]
    2. Device according to claim 1, wherein the first member (31) is multi-room and comprises a tubular part (51) having said bore (39) for the passage of the axis (41), said tubular part (51) being axially blocked between the first and second sockets (43,45).
    [3" id="c-fr-0003]
    3. Device according to any one of the preceding claims, wherein the first and second sockets each have a shoulder (43a, 45a), said shoulders being located on an inner side of the ears (33a, 33b), respectively.
    [4" id="c-fr-0004]
    4. Device according to the preceding claim, wherein the clamping member (47) being completely mounted, an axial clearance (I) is established between the shoulder (43a) of the first sleeve and a wall of a housing (330a) of the first ear (33a) facing it.
    [5" id="c-fr-0005]
    5. Device according to any one of the preceding claims, in which:
    - The tightening member is a nut (47), and on the side of the nut (47), said axis (41) has a shoulder (413) so that the end section (410a) of said axis (41) has a diameter (S2) smaller than the diameter of a main section (S1) that the traversing axis has between the first and second ears (33a, 33b), the nut being screwed onto said terminal section,
    - And the fourth bushing (57) has a bore provided with a shoulder (570) which internally has a cylindrical wall mounted to slide around a cylindrical wall of said end section (410a), said shoulder (570) having axial play (Jd) with the shoulder (413) of the axis (41).
    [6" id="c-fr-0006]
    6. Device according to claim 3 alone or in combination with any one of claims 4 or 5, wherein the shoulders (43a, 45a) of the first and second sockets (43, 45) have different diameters between them and the housings ( 330a, 330b) of the first and second ears (33a, 33b) which receive them are also of different diameters between them.
    [7" id="c-fr-0007]
    7. Device according to any one of the preceding claims, in which the second and third sockets (45, 55) are mounted axially clamped in said second orifice (37b) on either side of said second ear (33b), with a axial clearance (Jb) between them.
    5
    [8" id="c-fr-0008]
    8. Device according to claim 5, alone or in combination with any one of claims 6 to 7, wherein the device further comprises a nozzle (59) having a conical end (590) and which is to be temporarily disposed around said end section (S2) of the axis (41) to promote the passage of said axis in particular through the bore (39) of the
    10 first organ (31).
    [9" id="c-fr-0009]
    9. Device according to any one of the preceding claims, wherein the first and second sockets (43, 45) each have a radial clearance (Je, Ja) greater than or equal to 1 mm relative to the axis (41) which crosses.
    15
    [0010]
    10. Turbomachine (1), such as an aircraft turbojet or turboprop, characterized in that it is equipped with the device (30) according to any one of the preceding claims.
    1/4
    2/4
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    引用文献:
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    FR2867155B1|2004-03-08|2007-06-29|Snecma Moteurs|SUSPENSION OF AN ENGINE TO THE STRUCTURE OF AN AIRCRAFT|
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    法律状态:
    2017-11-20| PLFP| Fee payment|Year of fee payment: 2 |
    2018-06-08| PLSC| Publication of the preliminary search report|Effective date: 20180608 |
    2018-11-27| PLFP| Fee payment|Year of fee payment: 3 |
    2019-11-20| PLFP| Fee payment|Year of fee payment: 4 |
    2020-11-20| PLFP| Fee payment|Year of fee payment: 5 |
    2021-11-18| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1661882A|FR3059645B1|2016-12-02|2016-12-02|SUSPENSION DEVICE FOR TURBOMACHINE|
    FR1661882|2016-12-02|FR1661882A| FR3059645B1|2016-12-02|2016-12-02|SUSPENSION DEVICE FOR TURBOMACHINE|
    US15/826,971| US10562640B2|2016-12-02|2017-11-30|Turbine engine suspension device|
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