AIRCRAFT TURBOMACHINE INLET CONE

Abstract

The invention relates to an inlet cone (9) for an aircraft turbomachine fan mounted movably in rotation about an axis of rotation (R), comprising an upstream cone (1) carrying a vertex (S) and a downstream ferrule (2) equipped with balancing weights, the upstream cone (1) and the downstream ferrule (2) together forming the external surface of said inlet cone (9). According to the invention, the inlet cone (9) further comprises a rotation-locking device (3) provided with at least one tab (31) carrying at least one rotation-locking member (33) of said upstream cone (1) adapted to engage against said lower face of a first support platform (11) of said upstream cone (1), said rotation-locking device (3) of said upstream cone (1) being movably mounted between at least: an engaged position in which said at least one rotation-locking member (33) of said upstream cone (1) is engaged against said lower face of said first support platform (11) of said upstream cone (1),a disengaged position in which said at least one rotation-locking member (33) is radially moved away from said support platform (11) of said upstream cone (1), said inlet cone (9) further comprising unlocking means for said locking device (3) mounted movably in translation about an axis parallel to the axis of rotation (R), the transition of said locking device (3) from the engaged position to the disengaged position being effected by the translation of the unlocking means from an initial position to an unlocking position in which said unlocking means are in contact with said at least one locking member (33) so as to radially move it away from said lower face of the first support platform (11). Figure of the abstract: Figure 3,

Description

Title of the invention: AIRCRAFT TURBOMACHINE INTAKE CONE Scope of the invention

[0001] The present invention relates to the field of turbomachinery fans, particularly for aircraft turbojet engines. More specifically, the invention concerns an inlet cone for such a turbomachine. Prior art

[0002] As illustrated in [Fig. 1], a prior art turbomachine includes at its upstream end an air inlet for supplying a blower via an airflow F. This blower comprises a blower disk 104 centered on the axis of rotation R', and blower blades 105 mounted on the blower disk 104.

[0003] The air flow F entering this turbomachine through the air inlet, in a direction corresponding to the main direction of gas flow within the turbomachine, is deflected by an inlet cone towards the fan blades 105, then is separated into a primary flow passing through the compressor supplying the combustion chamber of the turbojet and a secondary flow which flows around the compressor.

[0004] This inlet cone is centered on the axis of rotation R' and is driven in rotation with the blower disk. It can either be made in one piece as illustrated in [Fig. 5] of document EP2028375, or in several adjacent parts as illustrated in [Fig. 1] and [Fig. 2] of document EP2028375. For example, an upstream part 101 extending from the apex of the cone, otherwise called the upstream cone, and a downstream part 102, otherwise called the downstream ferrule, adjacent to the blower blades and conventionally carrying balancing weights.

[0005] In order to keep the upstream and downstream sections fixed, and these two sections on the blower disk or on a connecting piece to the blower disk, the technique currently employed consists of fixing the upstream cone to the downstream ferrule by means of a plurality of screws 106 regularly spaced around the periphery of the cone. These screws, inserted into longitudinal recesses 103, however, present a major aerodynamic drawback because the recesses are exposed and cause local turbulence that disrupts the incoming airflow.

[0006] To counter this drawback, a solution was proposed in document FR 2 908 827. According to this technique, the turbomachine inlet cone is fixed to the downstream shell by means of several screws, these screws being positioned at the level of holes made at the bottom of an annular groove formed near a downstream end. In order not to disturb the aerodynamics of the turbomachine, this groove is then covered by sealing means having an external surface aligned with that of the cone.

[0007] However, such a solution is not optimal because the different parts must be perfectly calibrated, in particular the sealing means and the orifice, so as to fit together without leaving any potential sources of disturbance to the incoming airflow.

[0008] Furthermore, a disadvantage of such a solution is that it requires a relatively large number of parts for its implementation, which generates significant complexity and cost, which is also unsatisfactory.

[0009] Another disadvantage of such a solution is that it proves relatively complex to dismantle because dismantling the upstream cone requires prior dismantling of a plurality of parts, which can cause premature wear of various parts as well as possible loss of parts, which is not satisfactory. Description of the invention

[0010] The invention aims to remedy at least in part the aforementioned drawbacks relating to prior art techniques.

[0011] To this end, the invention relates to an inlet cone for an aircraft turbomachine fan mounted movably in rotation about an axis of rotation R, comprising an upstream cone carrying a vertex and a downstream ferrule equipped with balancing weights, the upstream cone and the downstream ferrule jointly forming the external surface of said inlet cone.

[0012] According to the invention, the inlet cone further comprises a rotation-locking device provided with at least one tab carrying at least one rotation-locking member of said upstream cone adapted to engage against said lower face of a first support platform of said upstream cone, said rotation-locking device of said upstream cone being movably mounted between at least:

[0013] - an engaged position in which said at least one rotation-blocking member of said upstream cone is engaged against said lower face of said first support platform of said upstream cone, - a disengaged position in which said at least one rotation-locking member is radially moved away from said support platform of said upstream cone,

[0014] said inlet cone further comprising unlocking means for said locking device mounted to translate freely along an axis parallel to the axis of rotation, the passage of said locking device from the engaged position to the disengaged position being effected by the translation of the unlocking means from an initial position, to an unlocking position in which said unlocking means are in contact with said at least one locking device so as to move it radially away from said lower face of said first support platform.

[0015] Thus, the invention proposes a new and inventive approach making it possible to resolve at least in part some of the disadvantages of the prior art.

[0016] In particular, the invention makes it possible to keep the upstream cone fixed relative to the downstream ferrule by means positioned inside to provide an external inlet cone surface which has a smooth surface, and to facilitate the dismantling of the various components of this inlet cone when necessary, for example for maintenance or replacement of parts, by the implementation of mechanically simple and therefore inexpensive parts.

[0017] According to one aspect of at least one embodiment of the invention, the means for unlocking said rotation locking device comprise an unlocking ring, having a substantially circular profile centered on the axis of rotation and configured to come into contact with said at least one rotation locking member, in the unlocking position, so as to disengage it from said first support platform.

[0018] As a result, this allows for the implementation of mechanically simple and inexpensive means while also simplifying the dismantling of the inlet cone.

[0019] According to one aspect of at least one embodiment of the invention, said at least one locking member has an end formed opposite a final portion of said unlocking ring, said end and said final portion having a complementary profile such that a transverse support of said end on said final portion during the passage from the initial position to the unlocking position causes a radial movement of said locking member to move it radially away from said first support platform.

[0020] Such a complementary profile between the unlocking ring and the locking member allows for a mechanically simple unlocking by means of simple mechanical means allowing a radial force to be exerted so as to move the locking member away from the first support platform while limiting the risks of incorrect operation or incorrect placement of one of the elements relative to the other, because the profiles are complementary.

[0021] According to one aspect of at least one embodiment of the invention, the unlocking means further comprise a plurality of pushers each provided in an orifice formed in said upstream cone and being mounted movable in translation along an axis parallel to the axis of rotation R so as to guide said unlocking ring in translation, and in that, in the initial position of the unlocking means, said pushers open flush with the external surface of said upstream cone.

[0022] Such an implementation makes it possible to make the cone unlocking means upstream accessible to a user who wishes to perform an operation, without having to dismantle many parts, which therefore represents a saving of time and limits the risks of mechanical breakage during dismantling.

[0023] According to one aspect of at least one embodiment of the invention, the locking means further comprise a slide formed of a first part bearing against said pushers and said unlocking ring and extending in a direction perpendicular to the axis of rotation R, and of a second part extending in a direction parallel to the axis of rotation R and forming a platform for said unlocking ring.

[0024] Such a slide makes it possible to stabilize the translational movement of the unlocking means and thus to avoid a shift in movement between the translation of the pusher and the translation of the unlocking ring, or an undesired translation along another axis.

[0025] According to one aspect of at least one embodiment of the invention, the unlocking means further comprise an end stop capable of limiting the translation of said slide towards said at least one locking member in rotation.

[0026] This end stop makes it possible to limit the translational movement of the unlocking means so as not to damage the locking device or the unlocking means.

[0027] According to one aspect of at least one embodiment of the invention, the unlocking means further comprise a return spring bearing between said end stop and said slide and configured to return said slide to the initial position.

[0028] According to one aspect of at least one embodiment of the invention, the unlocking means further include means for holding said unlocking ring in position against said slide.

[0029] These retaining means make it possible to keep the unlocking ring in position against the slide and thus to limit the risks of damage to the elements of the unlocking means.

[0030] According to one aspect of at least one embodiment of the invention, the inlet cone includes means for locking against rotation the unlocking means.

[0031] This makes it possible to stabilize the translational movement of the unlocking means and thus to avoid a shift of one of the components of the unlocking means.

[0032] The invention also relates to a blower for an aircraft turbomachine mounted movably in rotation around an axis of rotation R, characterized in that it comprises an inlet cone according to one of the aforementioned embodiments.

[0033] According to one aspect of at least one embodiment of the blower, the transition from said engaged position to said disengaged position is effected by the rotation of said cone input relative to said at least one blocking device in the direction of rotation corresponding to the direction of rotation of said blower around the axis of rotation R.

[0034] The invention also relates to an aircraft turbomachine comprising a blower according to one of the aforementioned embodiments.

[0035] According to one aspect of at least one embodiment, the turbomachine is an aircraft turbojet engine. Presentation of the figures

[0036] The invention, as well as its various advantages, will be more easily understood in the light of the following description of an illustrative and non-limiting embodiment thereof, and the accompanying drawings, among which:

[0037] [Fig. 1] already described, is a schematic side view in cross-section illustrating a state-of-the-art inlet cone;

[0038] [Fig.2] is a side view in cross-section schematically illustrating an inlet cone according to one embodiment of the invention, the locking device being in the engaged position, the unlocking means being in the initial position;

[0039] [Fig.3] is a detailed view of the unlocking means, in the unlocking position rusting;

[0040] [Fig.4] is a detailed view of [Fig.3], illustrating the unlocking ring and the rotation locking device;

[0041] [Fig.5] is a rear perspective view of the inlet cone of the [Fig.2];

[0042] [Fig.6] is a front perspective view of a locking device according to the mode of realization illustrated in [Fig.2];

[0043] [Fig.7] is a schematic front view of the operation of the locking device compared to the first support platform;

[0044] [Fig.8] is a side view in cross-section schematically illustrating an inlet cone According to a second embodiment of the invention, the locking device being in the engaged position, the unlocking means being in the initial position, and

[0045] [Fig.9] represents a schematic view of a turbofan engine, in cross-section longitudinal. Description of the implementation methods

[0046] It should be noted that, throughout the description, the terms "upstream" and "downstream" are to be considered in terms of the main direction of gas flow within the turbomachine, and therefore at their arrival on the external surface of the inlet cone by way of the air flow F.

[0047] With reference first to [Fig. 9], an aircraft turbomachine 901 is shown, according to a preferred embodiment of the invention. This is a twin-spool, turbofan engine. However, it could be a tur- a machine of another type, for example a turboprop, without departing from the scope of the invention. The turbojet 901 has a central longitudinal axis 902 around which its various components extend. It comprises, from upstream to downstream along a principal direction 905 of gas flow through this turbojet, a fan 903, a low-pressure compressor 904, a high-pressure compressor 906, a combustion chamber 911, a high-pressure turbine 907 and a low-pressure turbine 908.

[0048] Conventionally, after passing through the blower, the air splits into a central primary flow 912a and a secondary flow 912b that surrounds the primary flow. The primary flow 912a flows into a main gas circulation channel 914a, passing through the compressors 904, 906, the combustion chamber 911, and the turbines 907, 908. The secondary flow 912b flows into a secondary channel 914b, radially delimited outwards by an engine casing, surrounded by a nacelle 909. The compressors 904, 906 and the turbines 907, 908 are formed by alternating moving wheels, called rotor wheels, and fixed wheels, called stator wheels.

[0049] The principle of the invention is based on the implementation of an inlet cone comprising both a device for blocking the rotation of the upstream cone, and means for unlocking this blocking device.

[0050] The rotation-locking device is provided with at least one tab carrying at least one rotation-locking element for the upstream cone and adapted to engage against the lower face of a first support platform for the upstream cone, this locking device thus making it possible to hold the upstream cone and the downstream ferrule fixed relative to each other, this locking device being mounted movably between at least:

[0051] - an engaged position in which at least one rotation-locking member of the upstream cone is engaged against the lower face of a first support platform of the upstream cone, - a disengaged position in which at least one rotation-locking member is radially away from the support platform of the upstream cone.

[0052] As for the means for unlocking the rotational locking device, they are mounted to move in translation along an axis parallel to the axis of rotation R, and are therefore movable in translation between an initial position and an unlocking position in which they are in contact with at least one locking member so as to move it radially away from the first support platform. This translation thus allows the locking device to move from the engaged position to the disengaged position.

[0053] Such an inlet cone can for example be implemented within a fan for an aircraft turbomachine, which can in particular be an aircraft turbojet.

[0054] A first embodiment of the invention is now presented in relation to figures 2 to 7, given by way of simple illustrative and non-limiting example.

[0055] As illustrated in these figures, the inlet cone 9 is adapted for an aircraft turbomachine fan mounted movably to rotate about an axis of rotation R intended to be supplied by means of an airflow F.

[0056] The illustrated blower comprises a blower disk 4 centered on the axis of rotation R, and blower blades 5 attached to the blower disk 4.

[0057] This inlet cone comprises an upstream cone 1 bearing a vertex S and a downstream ferrule 2. This upstream cone 1 and this downstream ferrule 2 together form the external surface of the inlet cone 9.

[0058] It should be noted that the downstream ferrule 2 is equipped with balancing weights that can be placed regularly around its inner perimeter.

[0059] The inlet cone 9 further includes a rotation-locking device 3 for the upstream cone. This rotation-locking device is provided with at least one tab 31 carrying at least one rotation-locking member 33 for said upstream cone 1 adapted to engage against an underside face of a first support platform 11 of the upstream cone 1.

[0060] This device 3 for locking the rotation of the upstream cone 1 allows the upstream cone 1 to be locked in rotation relative to the downstream ferrule 2 and is, for this purpose, mounted movably between at least:

[0061] - an engaged position in which at least one rotation-locking member 33 of the upstream cone 1 is engaged against the lower face of the first support platform 11 of the upstream cone 1, and - a disengaged position in which at least one rotation-locking element 33 is radially moved away from the support platform 11 of the upstream cone 1.

[0062] It should be noted that, in this embodiment, the transition from the engaged position to the disengaged position is achieved by rotating the upstream cone 9 relative to at least one locking member 33 in the same direction of rotation as the direction of rotation of the blower around the axis of rotation R.

[0063] In other words, the direction of rotation for engaging the locking devices against the first support platform corresponds to the direction of rotation opposite to the direction of rotation of the blower, while the direction of rotation for disengaging the locking devices from the first support platform corresponds to the direction of rotation of the blower.

[0064] In the embodiment illustrated here, the locking device 3 is formed of a circular body 30 from which extends a plurality of tabs 31 which are oriented in a direction parallel to the axis of rotation R.

[0065] Preferably, these tabs 31 are distributed regularly on the circular body 30 of the locking device 3 so as to distribute the locking forces exerted uniformly on the tabs and on the circular body.

[0066] For example, it could be provided that the tabs are distributed uniformly over the circular body so that an angle between 30 degrees and 120 degrees, for example 60 degrees, separates two tabs.

[0067] Each of these tabs 31 carries at least one rotation locking member 33 capable of engaging against an underside face of the first support platform 11 of the upstream cone 1.

[0068] In the embodiment more particularly visible in [Fig.7], the rotation-locking members 33 of the upstream cone 1 comprise two teeth 33, each of the tabs therefore carrying a pair of teeth 33 which are able to engage against an inferior face of the first support platform 11 of the upstream cone 1.

[0069] According to other embodiments, tabs with a different number of teeth could be provided.

[0070] It could also be envisaged that at least one locking member has a different shape from a tooth.

[0071] Here, the first support platform 11 of the upstream cone 1 extends over the entire inner perimeter of the upstream cone so that each of the pairs of teeth carried by the tabs can engage, without prior indexing, against an underside of the first support platform 11 of the upstream cone 1.

[0072] In this way, in the engaged position, each of the pairs of teeth 33 forms a ratchet against the lower face of the first support platform 11 forming a ratchet.

[0073] In other words, in the engaged position, the ratchet and ratchet mechanism formed by each pair of teeth bearing against the lower face of the first support platform 11 prevents the rotation of the upstream cone in the direction of disengagement rotation and pushes it in the direction of engagement rotation.

[0074] As illustrated more particularly in [Fig. 5], the locking device 3 further comprises at least one notch 32 formed on the circular body 30, and the downstream ferrule 2 has at least one tab 20 extending radially from its inner surface. This tab 20 is configured to fit into at least one notch 32 so as to fix the locking device 3 of the upstream cone 1 against the downstream ferrule 2.

[0075] In the illustrated embodiment, the locking device 3 comprises a plurality of regularly formed notches in the periphery of the circular body 30, opening onto a downstream face of the locking device 3 and oriented in a direction parallel to the axis of rotation R. Similarly, the downstream ferrule 2 has a plurality of tabs 20 extending radially from its inner surface, each tab being configured to fit into an opposite notch 32. To this end, each tab has an end portion oriented so as to fit into the notch 32.

[0076] Once the end portions are inserted into the notches 32, the rotation-locking device 3 is locked in rotation and translation relative to this downstream ferrule 2. In addition, and as more particularly visible in figures 2 and 5, an axial stop ring 34 helps to maintain the rotation and translation of the locking device relative to the downstream ferrule.

[0077] So that the upstream cone 1 and the downstream ferrule 2 are also directly held relative to each other, and to further limit the mechanical forces exerted on the different elements, the downstream ferrule 2 has a second support platform 22, so that, in the engaged position, the first support platform 11 is clamped between the pairs of teeth 33 and the second support platform 22 of the downstream vein 2.

[0078] In addition, and so that the upstream cone 1 and the downstream ferrule 2 are also directly held relative to each other, and to also facilitate the placement and centering of one of the two parts relative to the other, the first support platform 11 further includes an upper face, opposite the lower face, having a threaded portion 12 configured to screw onto a thread of the second support platform 22 provided opposite it.

[0079] Furthermore, and as can be seen in particular on [Fig.2], the first support platform 11 also has a boss 13 formed in the extension of the threaded portion 12 and configured to bear against a projecting portion 23 formed on the second support platform 22 in the extension of the thread.

[0080] The steps for installing the upstream cone against the downstream vein so as to jointly form the external surface of the inlet cone according to the invention are now presented.

[0081] The installation method first includes a step of positioning the upstream cone opposite the downstream ferrule so as to be centered with respect to the axis of rotation R.

[0082] Next, the upstream cone is brought against the downstream ferrule so that the lower face of the first support platform of the upstream cone is opposite said at least one rotation-blocking member of the upstream cone.

[0083] Then, a rotation of the upstream cone in the direction of engagement is carried out so that the locking device 3 comes into the engaged position, at least one rotation-locking member of the upstream cone then being engaged against the lower face of the first support platform of the upstream cone so as to lock the upstream cone in rotation relative to the downstream ferrule.

[0084] We now present the steps of installing the upstream cone 1 against the downstream vein 2 so as to jointly form the external surface of the inlet cone according to the embodiment described in detail above.

[0085] These installation steps may be preceded by a preliminary assembly step of the rotation locking device 3 so as to lock it against the downstream ferrule 2, in particular by the insertion of the end portions into the notches 32 formed in the circular body 30. Once mounted, the rotation locking device 3 is locked in rotation and in translation relative to this downstream ferrule, the axial stop ring 34 allowing to accompany this retention in rotation and in translation of the locking device relative to the downstream ferrule.

[0086] As regards the installation method, it first comprises a step of positioning the upstream cone 1 opposite the downstream ferrule 2 so as to be centered with respect to the axis of rotation R of the blower. The centering of the cone 1 is achieved via the boss 13 formed in the extension of the threaded portion 12 and configured to bear against the projecting portion 23 of the downstream ferrule.

[0087] Next, the upstream cone 1 is brought against the downstream ferrule so that the threaded portion 12 is in contact with the thread of the second support platform 22.

[0088] In parallel, the lower face of the first support platform 11 of the upstream cone 1 is opposite the pairs of teeth 33.

[0089] Then, a rotation of the upstream cone in the direction of engagement is carried out so that the threaded portion screws onto the thread of the second support platform 22.

[0090] In parallel, the plurality of pairs of teeth 33 also pivots in the direction allowed by the ratchet, here the counterclockwise direction, so that the locking device 3 comes into the engaged position, the teeth 33 then being blocked in rotation in the clockwise direction.

[0091] Conversely, the upstream cone 1 must be able to be disassembled and removed from its location in the blower, for example for maintenance or cleaning operations.

[0092] Accordingly, and according to the invention as illustrated in the various figures, the inlet cone 9 further includes means for unlocking the locking device 3.

[0093] These unlocking means are mounted to move in translation along an axis parallel to the axis of rotation R so that the passage of the locking device 3 from the engaged position to the disengaged position is done by the translation of the unlocking means from an initial position, in which the unlocking means are at a distance from the teeth 33, to an unlocking position in which the unlocking means are in contact with the teeth so as to move them radially away from the first support platform.

[0094] In the illustrated embodiment, these means for unlocking the rotation locking device 3 include first of all a release ring 63, having a substantially circular profile centered on the axis of rotation R. This release ring is configured so that, due to translation, it comes into contact with the pairs of teeth 33, in the release position, so as to disengage these pairs of teeth from the lower face of the first support platform 11.

[0095] This disengagement of the lower face of the first support platform 11 of these locking members is done by a radial separation caused by the translation along the direction of the axis of rotation R of the unlocking ring which causes a translation along a radial direction of the pairs of teeth 33.

[0096] This radial spreading movement is facilitated, in this embodiment, by the fact that each tooth has an end 330 provided opposite a final portion 630 of the unlocking ring, and that the end 330 and the final portion 630 have a complementary profile.

[0097] Indeed, in this way, a transverse support of the end 330 of each tooth 33 on the final portion 630 during the passage from the initial position to the unlocking position causes a radial movement of each of the teeth to move them radially away from the lower face of the first support platform 11.

[0098] In this embodiment, each of the ends 330 has a triangular profile, the side intended to be in contact with the final portion 630 being inclined downstream, the end 330 forming an acute angle. As for the final portion 630, it has a triangular profile, the side intended to be in contact with each of the ends 330 being inclined upstream, the final portion 630 forming an obtuse angle.

[0099] So that the upstream cone unlocking means are accessible to a user wishing to perform an operation (for example, maintenance) without having to disassemble numerous parts, the unlocking means further comprise a plurality of pushers 60, each provided in an orifice 69 formed in the upstream cone. These pushers are also mounted to move in translation along an axis parallel to the axis of rotation R so as to guide the unlocking ring 63 in translation. At least one O-ring 70 is present between each pusher 60 and the orifice 69 formed in the cone, providing protection against external damage and ensuring the reliable operation of the pushers and associated parts.

[0100] In addition, in the initial position of the unlocking means, the pushers 60 open flush with the external surface of the upstream cone 1. In this way, they are easily accessible to a user but do not, however, disrupt the circulation of the airflow arriving on the inlet cone.

[0101] In the illustrated embodiment, the unlocking means comprise three pushbuttons 60 each provided in an orifice 69 formed in the upstream cone.

[0102] Here the three orifices are uniformly distributed on the upstream cone, i.e. an angle of approximately 120 degrees between two orifices.

[0103] The use of several distributed pushers, and more particularly uniformly distributed pushers, makes it possible to distribute the pushing forces on the unlocking ring during a translation of these pushers from the initial position to the unlocking position.

[0104] Furthermore, in this embodiment, the unlocking means also include a slide 62.

[0105] The slide 62, here, similarly to the unlocking ring, has a substantially circular profile centered on the axis of rotation R.

[0106] It is formed of a first part 620 bearing against the pushers 60 and the unlocking ring 63 and extending in a direction perpendicular to the axis of rotation R, and of a second part 621 extending in a direction parallel to the axis of rotation R and forming a platform for the unlocking ring 63.

[0107] In other words, the slide 62 is formed of a first part 620 and a second part 621 forming substantially a right angle between them, the second part 621 forming a platform on which the locking ring 63 is supported, the first part being in contact with the pushers 60.

[0108] According to this embodiment, the unlocking means further include means for holding the unlocking ring 63 in position against the slide 62. These means for holding in position are here formed by a stop 67 extending from the second part 621 in a radial direction and by a spring 68 provided between the locking ring 63 and the stop 67 so as to keep the locking ring in contact with the first part of the slide 62.

[0109] When a user presses one or more of the push buttons 60, these are translated in each of the orifices 69 from the initial position to the unlocked position and carry the slide 62 with them. Consequently, the unlocking ring, carried by the second part 621 of the slide, is moved in translation 69 from the initial position to the unlocked position so as to disengage the teeth 33 from the underside of the first support platform 11

[0110] As illustrated, in this embodiment, the unlocking means further include an end stop 65 suitable for limiting the translation of the slide 62 towards the teeth 33.

[0111] This end stop 65 limits the translational movement of the slide 62 and therefore of the release ring 63, so as not to damage the teeth or the release ring. Indeed, if the release ring has too much travel, it risks applying excessive pressure and could damage the teeth or the tabs.

[0112] According to one embodiment, this end stop is also placed so that the translation of the ring allows it to come into contact with the locking member in the unlocking position.

[0113] Here, and as particularly visible in [Fig. 2], the end stop is positioned on the lower face of the first support platform 11 of the upstream cone 1, upstream of an area of ​​the lower face of the first support platform 11 on which is engaged, the locking mechanism in the engaged position.

[0114] In addition, and so as to return the slide to the initial position, the unlocking means include a return spring 66 bearing against the end stop 65 and the slide 62, and therefore provided between the slide 62 and this end stop 65.

[0115] In this way, when the slide 62 moves from the initial position to the unlocked position, the return spring 66 is compressed between the slide 62 and the end stop 65. As soon as no force is exerted on the slide to hold it in the unlocked position, particularly by the pushbuttons, the return spring 66 exerts a force to return to its decompressed state and repositions the slide in the initial position. Incidentally, the slide 62 causes the pushbuttons 60 to return to their initial position, once no opposing force is exerted on the pushbuttons, for example by a user.

[0116] As illustrated in particular on [Fig.2], the entry cone includes in this embodiment means 61 for locking against rotation means for unlocking.

[0117] Such rotational locking means 61 make it possible, in particular, to stabilize the translational movement of the unlocking means and thus prevent a misalignment of one of the components of the unlocking means. More specifically, they prevent a misalignment of one of the components of the unlocking means relative to another when the unlocking means move from an initial position to an unlocked position or vice versa.

[0118] In this embodiment, the locking means 61 are in the form of a pin formed along a radial direction and exerting a force against the pushers 60. These locking means 61 are positioned so that they exert a force against the pushers in the initial position as well as in the unlocking position.

[0119] According to a second embodiment, illustrated in [Fig.8], the downstream ferrule has a plurality of through holes 20 formed so as to be opposite the tabs 31.

[0120] These through holes can also correspond to the insertion holes of the balancing weights, or balancing screws.

[0121] In this case, disassembly may include, in addition to the unlocking means already described in the first embodiment, a step of inserting a tool 6 into the through hole so as to exert radial pressure on the tab. Such radial pressure allows the teeth 33 to be radially separated from the lower face of the first support platform 11 of the upstream cone 1, and thus facilitates unlocking by the unlocking means.

Claims

Demands

1. Inlet cone (9) for an aircraft turbomachine fan mounted movably to rotate about an axis of rotation (R), comprising an upstream cone (1) having a vertex (S) and a downstream ferrule (2) equipped with balancing weights, the upstream cone (1) and the downstream ferrule (2) together forming the external surface of said inlet cone (9), characterized in that the inlet cone (9) further comprises a rotation-locking device (3) having at least one tab (31) carrying at least one rotation-locking member (33) of said upstream cone (1) adapted to engage against said lower face of a first support platform (11) of said upstream cone (1), said rotation-locking device (3) of said upstream cone (1) being movably mounted between at least: - an engaged position in which said at least one rotation-locking member (33) of said upstream cone (1) is engaged against said lower face of said first support platform (11) of said upstream cone (1), - a disengaged position in which said at least one rotation-locking device (33) is radially moved away from said support platform (11) of said upstream cone (1), said entry cone (9) further comprising unlocking means for said locking device (3) mounted movable in translation along an axis parallel to the axis of rotation (R), the passage of said locking device (3) from the engaged position to the disengaged position being effected by the translation of the unlocking means from an initial position, to an unlocking position in which said unlocking means are in contact with said at least one locking member (33) so as to move it radially away from said lower face first support platform (11).

2. Entry cone (9) according to claim 1, characterized in that the means for unlocking said rotation-locking device (3) comprise an unlocking ring (63), having a substantially circular profile centered on the axis of rotation (R) and configured to come into contact with said at least one rotation-locking member (33), in the unlocked position, so as to disengage it from said first support platform (11).

3. Entry cone (9) according to claim 2, characterized in that said at least one locking member (33) has an end (330) formed opposite a final portion (630) of said unlocking ring, said end (330) and said final portion (630) having a complementary profile such that a transverse support of said end (330) on said final portion (630) during the passage from the initial position to the unlocking position causes a radial movement of said locking member (33) to move it radially away from said first support platform (11).

4. Inlet cone (9) according to any one of claims 2 to 3, characterized in that the unlocking means further comprise a plurality of pushers (60) each provided in an orifice (69) formed in said upstream cone (1) and being mounted movable in translation about an axis parallel to the axis of rotation (R) so as to guide in translation said unlocking ring (63), and in that, in the initial position of the unlocking means, said pushers (60) open flush with the external surface of said upstream cone (1).

5. Entry cone (9) according to claim 4, characterized in that the locking means further comprise a slide (62) formed of a first part (620) bearing against said pushers (60) and said unlocking ring (63) and extending in a direction perpendicular to the axis of rotation (R), and of a second part (621) extending in a direction parallel to the axis of rotation (R) and forming a platform for said unlocking ring (63).

6. Entry cone (9) according to claim 5, characterized in that the unlocking means further comprise an end stop (65) capable of limiting the translation of said slide (62) towards said at least one rotation-locking member (33).

7. Entry cone (9) according to claim 6, characterized in that the unlocking means further comprise a return spring (66) bearing between said end stop (65) and said slide (62) and configured to return said slide to the initial position.

8. Entry cone (9) according to any one of claims 5 to 7, characterized in that the unlocking means further comprise means for holding said unlocking ring (63) in position against said slide (62).

9. Entry cone (9) according to any one of the preceding claims, characterized in that it comprises means (61) for locking against rotation the unlocking means.

10. Aircraft turbomachine blower mounted movably to rotate about an axis of rotation (R), characterized in that it comprises an inlet cone according to any one of claims 1 to 9.

11. Blower according to claim 10, characterized in that the transition from said engaged position to said disengaged position is made by the rotation of said inlet cone (1) relative to said at least one locking member (33) in the direction of rotation corresponding to the direction of rotation of said blower around the axis of rotation (R).

12. Aircraft turbomachine comprising a fan (9) according to any one of claims 10 or 11.

13. Aircraft turbomachine according to claim 12, characterized in that it is a turbojet.

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