SYSTEM FOR LOCKING A PLUG IN AN AIRCRAFT TURBOMACHINE PART, PREFERABLY A TURBOMACHINE SHAFT

Abstract

The invention relates to a locking system (120) of a plug (60) on a part (22) of an aircraft turbomachine, comprising a locking ring (38) equipped with a projecting element (44a), which, in a locking position of the ring, is intended to fit into a first recess (44b) of the part (22), the first recess (44b) opening axially, the plug comprising a retaining finger (62) intended to fit into a second recess (144b) of the part, the second recess taking the form of a second notch (144b) opening circumferentially in the first recess (44b). Furthermore, in the ring's locking position, the protruding element (44a) is designed to circumferentially cover, at least partially, the second recess (144b) housing the cap's retaining finger (62). Figure for the abbreviation: Figure 20

Description

Title of the invention: SYSTEM FOR LOCKING A PLUG IN AN AIRCRAFT TURBOMACHINE PART, PREFERABLY A TURBOMACHINE SHAFT technical field

[0001] The invention relates to the field of locking systems for a plug in a part of an aircraft turbomachine, such as for example a turbojet or a turboprop.

[0002] Preferably, the invention relates to a locking system for such a plug, for example in a compressor shaft or a turbine shaft, but it is not limited to this preferred application. PREVIOUS STATE OF THE ART

[0003] In aircraft turbomachine parts, it is sometimes required to install a plug, for example in a hollow shaft to plug the space inside that shaft

[0004] Once in position and during the operation of the turbomachine, the plug may be subjected to significant loads, in particular pressure loads

[0005] A locking system for the plug is therefore necessary to maintain it in its initial position on the turbomachine part. However, the solutions proposed in the prior art are often complex, using, for example, added components such as circlips. Moreover, this type of added component may prove unsuitable for withstanding the significant loads that may be applied to the plug.

[0006] Moreover, the assembly, and especially the disassembly of deformable parts such as a circlip, is sometimes complicated;

[0007] Finally, the design of prior art solutions may require visual access for mounting the plug locking system. However, this visual access is not always possible within the extremely dense environment of a turbomachine.

[0008] There therefore remains a need to improve the design of prior art plug locking systems. Description of the invention

[0009] To meet the aforementioned need, the invention first relates to a locking system for a plug in an aircraft turbomachine part with axis (X), the part extending circumferentially around the axis (X), the system comprising a locking ring equipped with a protruding element, which, in a locking position of the ring, is intended to fit into a first recess of the The turbomachine component has a first recess opening axially, and the plug includes a retaining finger designed to fit into a second recess in the component. This second recess is shaped like a second notch opening circumferentially within the first recess. Furthermore, when the ring is locked in the turbomachine component, the protruding element of the ring is designed to circumferentially cover, at least partially, the second recess housing the retaining finger of the plug.

[0010] Thanks to the design of the invention, the extraction of the stopper is prevented in a simple way, and the system is capable of withstanding significant pressure forces on the stopper.

[0011] Furthermore, the assembly of the locking system according to the invention can easily be carried out blindly, that is to say without visual access to the area of ​​the turbomachine in which the assembly takes place.

[0012] The invention preferably includes at least one of the following optional features, taken individually or in combination.

[0013] Preferably, the locking ring of the plug forms an anti-rotation ring of a coupling system of the turbomachine part with another turbomachine part, preferably two turbomachine shafts, said anti-rotation ring being intended to limit / prevent the rotation of a clamping nut of the coupling system, and the protruding element of the locking ring is intended to cooperate with the first recess provided on the turbomachine part, so as to form together a first rotating coupling device.

[0014] This preferred embodiment allows the ring to perform several distinct functions, contributing both to the anti-rotation of the coupling nut and to the locking of the plug. This results in a simplification of the design, as well as a gain in terms of mass and cost.

[0015] Preferably, the locking ring comprises two protruding elements which, in a locking position of the locking ring, are respectively inserted into two first recesses in the part, the first recesses opening axially, the plug comprising two retaining fingers respectively configured to insert into the two second recesses of the turbomachine part, each of them opening circumferentially into one of the first recesses. Furthermore, in the locking position of the locking ring on the part, said at least two protruding elements of the locking ring circumferentially cover, at least partially, the two second recesses housing the retaining fingers.

[0016] Obviously, the number of retaining fingers on the cap can be greater than two, for example three, four, etc., preferably regularly spaced from each other in the circumferential direction.

[0017] Preferably, the protruding element is a finger, and the first recess in the turbomachine part is a first notch. Alternatively, the finger could be provided on the turbomachine part to be inserted into a notch in the ring, without departing from the scope of the invention.

[0018] The invention also relates to an assembly for an aircraft turbomachine comprising an aircraft turbomachine part, a plug sealing a hollow in the part preferably at an axial end thereof, and a plug locking system as described above.

[0019] Preferably, the assembly also includes a coupling system for the part with another turbomachine part.

[0020] Preferably, the plug comprises a body with an outside diameter substantially equal to an inside diameter of the hollow of the part to be plugged, and the plug retaining finger projects radially outwards from this plug body.

[0021] Preferably, the second recess, which opens into the first recess, is a second circumferential notch made in one of the two lateral sides of the first recess.

[0022] The invention also relates to an aircraft turbomachine, comprising at least one such assembly. It may, for example, be a turbojet or a turboprop.

[0023] Finally, the invention relates to a method for mounting a plug in a turbomachine part, with a plug locking system as described above, the method comprising the following steps:

[0024] - axial insertion of the plug into a recess in the part, so that the finger of the cap is held in place by inserting it into the first recess of the part;

[0025] - rotation of the cap so as to allow its retaining finger to penetrate the second hollowing out of the room;

[0026] - axial displacement of the locking ring, so as to introduce its element into protrusion in the first recess of the part, until the ring reaches its locking position in which its protruding element circumferentially covers, at least in part, the second recess housing the retaining finger.

[0027] Other advantages and features of the invention will appear in the detailed, non-limiting description below. Brief description of the drawings

[0028] [Fig. 1] is a longitudinal cross-sectional view of a turbojet engine;

[0029] [Fig.2] is a longitudinal half-sectional view of a coupling system of two parts of the turbojet engine shown in the previous figure;

[0030] [Fig.3] is a cross-sectional view of the coupling system shown on the [Fig.2], and corresponding to the section taken along line III-III of [Fig.2];

[0031] [Fig.4] is a partial perspective view of a clamping nut of the coupling system shown in Figures 2 and 3;

[0032] [Fig.5] is a partial perspective view of an anti-rotation ring of the coupling system shown in Figures 2 and 3;

[0033] [Fig.6] is a partial perspective view of an anti-rotation ring, according to an alternative;

[0034] [Fig.7] is a partial perspective view of one end of a shaft of the tur-bomachine, intended to be coupled by the coupling system shown in Figures 2 and 3;

[0035] [Fig.8] is a partial perspective view of the coupling system shown in Figures 2 and 3;

[0036] [Fig.9]

[0037] [Fig. 10]

[0038] [Fig. 12] are longitudinal half-section views of the coupling system shown in [Fig.2], in different successive states during a process of mounting this coupling system;

[0039] [Fig. 11] is a cross-sectional view of the coupling system shown in [Fig. 10], and corresponding to the section taken along line XI-XI of [Fig. 10];

[0040] [Fig. 13]

[0041] [Fig. 14] are cross-sectional views of the coupling system shown in the preceding figures, according to an alternative, and in different successive states during the assembly process of this coupling system;

[0042] [Fig. 15] is a longitudinal half-section view of the coupling system similar to that shown in the previous figures, and presented in the form of an alternative;

[0043] [Fig. 16]

[0044] [Fig. 17]

[0045] [Fig. 18]

[0046] [Fig. 19] are partial cross-sectional views of the coupling system according to still another alternative, in different successive states during the assembly process of this coupling system;

[0047] [Fig.20] is a partial perspective view of a locking system for a plug in a part of the turbojet engine, this locking system being integrated into the coupling system shown in the preceding figures;

[0048] [Fig.21] is an axial view of the stopper shown in the previous figure;

[0049] [Fig.22]

[0050] [Fig.23]

[0051] [Fig.24] are partial perspective views of the blocking system shown on the [Fig.20], in different successive states during an assembly process of this locking system;

[0052] [Fig.25] is a partial cross-sectional view of the locking system, in its state such that shown in [Fig.23];

[0053] [Fig.26] is a partial cross-sectional view of the locking system, in its state such that shown in [Fig.24];

[0054] [Fig.27] is a partial cross-sectional view of the locking system, in its state at the end of the assembly process for this system. DETAILED DESCRIPTION OF THE INVENTION

[0055] With reference first to [Fig. 1], an aircraft turbomachine 1 is shown, according to a preferred embodiment of the invention. This is a twin-spool, turbofan engine. However, it could be a turbomachine of another type, for example a turboprop, without departing from the scope of the invention.

[0056] The turbomachine 1 has an axis X around which its various components extend, this axis being called the longitudinal axis of the turbomachine. It comprises, from upstream to downstream along a main direction 5 of gas flow through this turbomachine, a blower 3, a low-pressure compressor 4, a high-pressure compressor 6, a combustion chamber 11, a high-pressure turbine 7 and a low-pressure turbine 8.

[0057] Conventionally, after passing through the blower, the air splits into a central primary flow 12a and a secondary flow 12b which surrounds the primary flow. The primary flow 12a flows into a main gas circulation channel 14a passing through the compressors 4, 6, the combustion chamber 11 and the turbines 7, 8. The secondary flow 12b, on the other hand, flows into a secondary channel 14b delimited radially outwards by an engine casing, surrounded by a nacelle 9.

[0058] Figures 2 to 8 represent a coupling system 20 for two rotating parts of the turbojet 1, having the same axis of rotation X. This is a first shaft 22 corresponding to a shaft of the low pressure turbine, and a second shaft 24 corresponding to a shaft of the low pressure compressor. These two shafts 22, 24 are hollow, and the upstream end of the first shaft 22 fits into the downstream end of the second shaft 24, so as to be coupled in translation and rotation along the axial direction, via the system 20. The two shafts 22, 24, concentric and centered on the X-axis, together with their coupling system 20, form an assembly 30. Several assemblies of this type can be provided within the turbojet, with coupled parts that can belong indifferently to various modules of the turbojet, including the fan, the compressors, the combustion chamber, or even the turbines.

[0059] Here, preference is given to coupling parts with large diameters, where visual access to the coupling area is limited or even nonexistent. This is particularly the case for the architecture partially shown in [Fig. 2], showing the system 20 in an assembled state, in which the two shafts 22, 24 are coupled.

[0060] The coupling system 20 comprises, firstly, a clamping nut 32 for the two shafts, this nut being centered on the X-axis and provided with a first thread 34a, or nut thread, cooperating with a second thread 34b, or first part thread, formed on an external surface of the first shaft 22. As can be seen in Figures 2 and 8, in the assembled state of the coupling system 20, the downstream end of the nut 32 exerts an axial force on the second shaft 24, and more specifically on an internal shoulder of the latter. This axial force pushes the second shaft 34 downstream against an external shoulder of the first shaft 22, with an axial shim 36 optionally interposed between the two shoulders, as shown by way of example in [Fig. 2]. The axial clamping force of the nut is sufficient to generate the desired coupling between the two shafts 22, 24.

[0061] The system 20 also includes an anti-rotation ring 38 intended to limit / prevent the rotation of the nut 32, relative to the first shaft 22, in the mounted state of the system 20.

[0062] The anti-rotation ring 38 is centered on the X-axis, being at least partially arranged internally within the nut 32, and being capable of being moved axially relative to the latter, into different axial positions. In Figures 2 and 8, the anti-rotation ring 38 is shown in its most downstream position relative to the nut 32, corresponding to a final shaft coupling position. It is held there by a circlip 40 or a similar retaining element, carried by the ring 38 and cooperating with a corresponding groove 42a, formed on the inner surface of the nut 32 upstream of the first thread 34a.

[0063] In the final coupling position of the ring 38, it is thus axially retained relative to the nut 32 by means of the circlip 40, or any other translational retaining system associated with the ring. In this position, a first rotational coupling device and a second rotational coupling device are provided, both in the active coupling configuration.

[0064] The first rotational coupling device consists of first rotational coupling members 44a formed on the downstream end of the ring 38, and by first complementary rotational coupling members 44b, provided on the upstream end of the first shaft 22. Here, these are preferably finger-notch assemblies, the fingers 44a preferably being provided on the ring 38, and the notches 44b on the first shaft 22, although a reverse solution is possible. envisaged. The 44b notches are also referred to as the first 44b notches.

[0065] The number of these finger-notch assemblies is preferably less than four, for example three, or two as in the figures. In this case, the two fingers 44a are preferably diametrically opposed, as are their corresponding notches 44b on the upstream end of the first shaft 22, these notches opening axially upstream.

[0066] The fingers 44a, provided at the downstream end of the ring 38, project axially downstream and radially inwards as shown in Figures 2, 5 and 8, or they project only axially downstream, as shown in the alternative of [Fig.6].

[0067] The second rotating coupling device consists of secondary rotating coupling members 46a formed on the outer surface of the ring 38, and of complementary secondary rotating coupling members 46b, provided on the inner surface of the nut 32. Preferably, these are splines 46a, 46b cooperating with each other, in the form of two concentric annular rows of splines. Each annular row of splines 46a, 46b may be uninterrupted over 360°, or extend only over an angular sector less than 360°, or extend over several angular sectors spaced circumferentially from each other. The number of splines per annular row is high, for example, greater than twenty, thirty, or forty. The number of grooves is preferably the same for each of the two annular rows of grooves, and this number is strictly greater than the number of notches and the number of fingers.

[0068] Each groove extends radially, in the conventional form of a tooth, and more precisely radially outwards for grooves 46a, and radially inwards for grooves 46b.

[0069] One of the distinctive features is that the first grooves 46a are axially spaced from the fingers 44a, towards the upstream side. Indeed, there is preferably no axial overlap zone between these elements 46a, 44a.

[0070] Figures 9 to 12 illustrate the method of mounting the coupling system 20 on the two shafts 22, 24.

[0071] First, the system 20 is placed on the first shaft 22, so that the nut 32 surrounds the upstream end of this shaft. Then, this nut 32 is tightened via the first and second threads 34a, 34b. The purpose of this tightening is to axially press the first shaft 22 against the second shaft 24 by pressing the downstream end of the nut against the second shaft 24. The tightening torque applied to the nut 32 corresponds to a minimum torque to ensure the desired coupling of the two shafts. This step is shown schematically in [Fig. 9]. During this step, the ring 38 is held in an inactive upstream position, referred to as the non-coupling position, where It is held axially relative to the nut 32 via the ring 40 which cooperates with another groove 42b on the internal surface of the nut, arranged upstream of the groove 42a.

[0072] The next step is illustrated in Figures 10 and 11. It consists of rotating the ring 38 about the X-axis relative to the fixed nut 32, and translating it downstream. The rotation of the ring serves to align the fingers 44a with the notches 44b, after which the fingers can be axially inserted into these same notches. This axial displacement of the ring effectively brings the anti-rotation ring 38 into a temporary axial position relative to the nut, thus placing the first rotating coupling device 44a, 44b in its coupling configuration. However, the axial displacement of the ring 38 is normally stopped by the lack of alignment between the splines 46a, 46b, as shown in [Fig. 11] on which it is shown that the first grooves 46a are not aligned with inter-groove spaces on the other row of second grooves 46b, and vice versa.Therefore, in the provisional axial position of the ring 38, the second rotating coupling device 46a, 46b remains in a non-coupling configuration.

[0073] During this step, the rotation and translational force on the ring 38 can be exerted simultaneously, in particular when these actions are carried out blindly in the turbojet mounting area.

[0074] To achieve the desired alignment between splines 46a and 46b, shown in particular in [Fig. 3], nut 32 is tightened again on the second shaft 22. An over-torque is thus applied to the nut, with a measured intensity, until the desired alignment between splines 46a and 46b is obtained. This step of applying an over-torque to nut 32 is shown schematically in [Fig. 12].

[0075] Since the pitch of the splines is smaller than that of the notches, the rotation of the nut to be applied to allow the desired correspondence between these splines, and the resulting overtorque, remain advantageously small.

[0076] Next, the ring 38 is further axially displaced relative to the nut 32, from its provisional axial position to its final axial coupling position, so as to make the splines 46a, 46b cooperate as shown in [Fig. 2]. Here again, it is noted that the rotation of the nut 32 and the application of the translational force on the ring 38 can be exerted simultaneously, particularly when these actions are carried out blindly in the turbojet mounting area.

[0077] At the end of this step, the second rotating coupling device 46a, 46b is in its coupling configuration, due to the cooperation between the splines. Similarly, the first rotating coupling device 44a, 44b remains in its coupling configuration, after its fingers 44a have been further inserted into their respective notches 44b, following the additional axial displacement of the ring 38 relative to the nut 32.

[0078] During this additional movement of the ring 38, the circlip 40 inserts itself into the groove 42a of the ring, thus locking it against translation. This allows the entire system 20 to remain in an assembled state, ensuring the coupling of the two shafts 22, 24 in translation and rotation, without risk of the nut 32 loosening.

[0079] Figures 13 and 14 represent an alternative, the design of which advantageously does not require the application of an over-torque on the nut, for the finalization of the assembly of the coupling system 20.

[0080] This alternative has many technical characteristics in common with the embodiment shown in figures 2 to 12, and moreover, in the figures, the elements which bear the same numerical references correspond to identical or similar elements.

[0081] In the alternative configuration shown in Figures 13 and 14, it is demonstrated that, in the provisional axial position of the ring 38, there is a circumferential clearance 48 between each finger 44a and its corresponding notch 44b. This arrangement allows, through partial or total use of the clearance 48, sufficient angular movement of the ring 38 relative to the fixed nut 32, to enable the splines 46a and 46b to be aligned in the circumferential direction. After this operation, the coupling system 20 assumes a state as shown in [Fig. 14]. In this regard, it is noted that the circumferential direction, with respect to the X-axis, also corresponds to the tangential direction.

[0082] As previously indicated, the desired correspondence between the splines 46a, 46b allows the axial displacement of the anti-rotation ring 38, from its provisional axial position to its final axial coupling position.

[0083] It is noted that a hybrid solution is also possible, in which the matching of the splines 46a, 46b is obtained on the one hand by the rotation of the ring 38 by consuming the aforementioned clearance 48, and on the other hand by the application of a slight over-torque on the nut 32.

[0084] Another alternative is shown in [Fig. 15], which provides elastic return means, such as one or more springs 50 arranged axially between the nut 32 and the anti-rotation ring 38. The spring 50 makes it possible to force the ring 38 axially downstream relative to the nut 32, and is therefore capable of generating the axial forces required for the passage of the ring 38 from its most upstream position to its provisional axial position, and then from this provisional axial position to its final axial coupling position.

[0085] This principle also makes it possible to maintain the ring 38 in its final axial position coupling, so that the means of buttressing by ridge are no longer necessarily required.

[0086] Figures 16 to 19 represent different states of the coupling system 20 according to yet another alternative, in which each finger 44a and its corresponding notch 44b have inclined circumferential stop surfaces, forming an angle with respect to the axial direction. In other words, each of these two surfaces 52a, 52b forms a non-zero angle with the axial direction, parallel to the X-axis.

[0087] The inclined circumferential stop surfaces 52a, 52b are shown in [Fig. 16]. They are parallel or substantially parallel, and are respectively formed by a lateral flank of the finger 44a, and by a lateral flank 68 of the notch 44b. The inclination of the circumferential stop surface 52b of the notch 44b is such that it widens circumferentially in an axial direction upstream. Conversely, the inclination of the circumferential stop surface 52a of the finger 44a is such that it narrows circumferentially in an axial direction downstream.

[0088] The position of [Fig. 16] corresponds to that of [Fig. 9], in which the finger 44a is not yet aligned with its associated notch 44b. When such alignment is achieved following rotation of the ring 38, under the action of the operator or the spring 50, the finger 44a is partially inserted into the notch 44b, as shown schematically in [Fig. 17]. The axial insertion is stopped by the stop between the splines. The circumferential clearance 48 observed between the inclined surfaces of the circumferential stop 52a, 52b can then be eliminated, partially or completely, by rotation of the ring 38, in order to align these same splines (not shown in Figures 16 to 19). This step is shown schematically in [Fig. 18]. Next, when the correspondence between the splines is obtained, the ring 38 is moved axially to its final axial coupling position, under the effect of the spring 50.This position is reached when the circumferential stop surfaces 52a, 52b come into contact with each other as shown in [Fig.19], this contact being preferentially surface-based.

[0089] Due to the inclination of the contact surfaces 52a, 52b, the finger 44a, when abutted against the lateral side of the notch 44b, exerts an inclined force on the shaft 22 with a circumferential component. This component is oriented such that the finger 44a forces the second shaft 22 in a direction of rotation that causes the nut 38 to tighten further on this shaft 22.

[0090] Figure 20 shows the assembly 30 comprising the coupling system 20 of the two shafts 22, 24, but also a locking system 120 for a plug 60 in the first shaft 22. Indeed, the plug 60 is mounted at the upstream end of the first shaft 22, at the level of the first rotating coupling device 44a, 44b, or at proximity to the latter. This plug 60 serves to seal, upstream, the hollow space 66 inside the shaft 22, centered on the X axis. This plug 60 may have to support significant loads, in particular pressure loads, which the locking system 120 must be able to withstand.

[0091] In the realization of [Fig.20], the locking system 120 of the plug and the coupling system 20 of the two shafts are thus combined within the assembly 30, and they share common parts in order to present a compact overall design, lower mass, and reduced cost.

[0092] However, it is noted that the locking system 120 according to the invention could be implemented in another environment of the turbojet, not necessarily in association with a coupling system as described above, and possibly on a part other than a shaft.

[0093] Still with reference to [Fig.20], the locking system 120 includes the anti-rotation ring 38, which therefore fulfills the additional function of locking the plug 60. Consequently, in the rest of the description, this ring 38 will therefore be referred to as the locking ring.

[0094] The locking ring 38 is, as previously mentioned, equipped with protruding elements formed by the fingers 44a. In a locking position of the ring 38, corresponding to its final axial coupling position described previously, the fingers 44a are inserted respectively into first recesses in the shaft 22, corresponding to the first notches 44b. Other shapes could nevertheless be adopted for the protruding elements 44a and the first recesses 44b, without departing from the scope of the invention.

[0095] One of the distinctive features here is that the plug 60 has one or more retaining fingers 62, their number preferably being identical to that of the first notches 44b, as is their arrangement. Thus, two retaining fingers 62 are provided on a plug body 64, diametrically opposed. In this regard, it should be noted that the plug body 64 has an outer diameter substantially equal to an inner diameter of the recess 66 of the shaft 22, with only a very small mounting clearance being preferred. Furthermore, the retaining fingers 62 project radially outwards from this plug body 64.

[0096] Each of the retaining fingers 62 is inserted into a second recess in the shaft 22, this second recess taking the form of a second notch 144b opening circumferentially in one of the first notches 44b. Each second notch 144b can be of a dimension considerably smaller than that of the first notch 44b into which it opens, taking for example the form of a simple notch in the circumferential direction.

[0097] More specifically, each second circumferential notch 144b is made in one of the two lateral sides 68 of the first notch 44b into which it opens. In the preferred embodiment shown in [Fig. 20], each second circumferential notch 144b (only one of the two notches 144b being visible in [Fig. 20]) is formed at the axial bottom of its associated first notch 44b.

[0098] Thus, in the locking position of the ring 38 on the upstream end of the first shaft 22, each finger 44a circumferentially covers, at least partially, one of the second notches 144b housing a retaining finger 62 for the plug. More precisely, each finger 44a circumferentially covers the bottom of one of the second notches 144b housing a retaining finger 62.

[0099] Thanks to this overlap, each finger 44a is thus followed by a second notch 144b in the circumferential direction, without these two elements necessarily being in contact with each other. In the event of circumferential play, this play preferentially remains sufficiently small to prevent the complete extraction of the retaining finger 62 from the second notch 144b.

[0100] Fig. 21 shows an axial view of the plug 60, the assembly method of which will now be described with reference to figures 22 to 27.

[0101] First, as can be seen in figures 22, 23 and 25, an axial insertion step of the plug 60 is carried out in the hollow 66 of the first shaft 22, so that each retaining finger 62 of the plug is inserted axially downstream into its first associated notch 44b of the shaft 22, until it reaches the axial bottom of this notch 44b.

[0102] Next, the stopper 60 is rotated about the X-axis on which it is centered, so that each retaining finger 62 enters its associated second notch 144b. The extent of the rotation can be measured, in correlation with the shallow depth of the second notch 144b. Figures 24 and 26 show the system 120 after this step has been performed.

[0103] Finally, [Fig. 27] illustrates the last step, corresponding to the axial displacement of the locking ring 38 into its locking position. This leads to the insertion of each finger 44a into its associated first notch 44b of the shaft 22, until the finger 44a circumferentially covers, at least partially, the second notch 144b which houses the retaining finger 62.

[0104] Of course, various modifications can be made by a person skilled in the art to the invention just described, solely by way of non-limiting examples, and the scope of which is defined by the appended claims. In particular, the technical characteristics of the different embodiments and their alternatives are interchangeable and combinable.

Claims

Demands

1. A locking system (120) for a plug (60) in an aircraft turbomachine part (22) with axis (X), the part (22) extending circumferentially around the axis (X), characterized in that it comprises a locking ring (38) equipped with a projecting element (44a), which, in a locking position of the locking ring (38), is intended to fit into a first recess (44b) of the turbomachine part (22), the first recess (44b) opening axially, the plug (60) comprising a retaining finger (62) intended to fit into a second recess (144b) of the part (22), the second recess (144b) taking the form of a second notch opening circumferentially in the first recess. (44b), and in that in the locking position of the locking ring (38) in the turbomachine part (22), the protruding element (44a) of the locking ring (38) is intended to circumferentially cover, at least in part,the second recess (144b) housing the retaining finger (62) of the stopper (60).

2. Locking system according to claim 1, characterized in that the locking ring (38) of the plug (60) forms an anti-rotation ring of a coupling system (20) of the turbomachine part (22) with another turbomachine part (24), preferably the part (22) and the other part (24) being two turbomachine shafts, said anti-rotation ring (38) being intended to limit / prevent the rotation of a clamping nut (32) of the coupling system, and in that the protruding element (44a) of the locking ring (38) is intended to cooperate with the first recess (44b) provided on the turbomachine part (22), so as to form together a first rotating coupling device.

3. A locking system according to claim 1 or 2, characterized in that the locking ring (38) comprises two projecting elements (44a), which, in a locking position of the locking ring (38), are respectively inserted into two first recesses (44b) of the part (22), the first recesses (44b) opening axially, the plug (60) comprising two retaining fingers (62) respectively configured to insert into the two second recesses (44b) of the turbomachine part (22), each of them opening circumferentially into one of the first recesses (44b), and in that in the locking position of the locking ring (38) on the part (22), said at least two protruding elements (44a) of the locking ring (38) circumferentially cover, at least in part, the two second recesses (144b) housing the retaining fingers (62).

4. Locking system according to any one of the preceding claims, characterized in that the protruding element (44a) is a finger, and in that the first recess (44b) of the turbomachine part (22) is a first notch.

5. Assembly (30) for aircraft turbomachine comprising an aircraft turbomachine part (22) extending around the axis (X), a plug (60) plugging a hollow (66) in the part (22) preferably at an axial end thereof, and a locking system (120) for the plug (60) according to any one of the preceding claims.

6. Assembly according to claim 5, characterized in that it further comprises a coupling system (20) of the part (22) with another part (24) of turbomachine.

7. Assembly according to claim 5 or 6, characterized in that the stopper (60) comprises a body (64) of an outside diameter substantially equal to an inside diameter of the hollow (66) of the part (22) to be stopped, and in that the retaining finger (62) of the stopper (60) projects radially outwards from this stopper body (64).

8. Assembly according to any one of claims 5 to 7, characterized in that the second recess (144b), which opens in the first recess (44b), is a second circumferential notch made in one of the two lateral sides (68) of the first recess (44b).

9. Aircraft turbomachine (1) comprising at least one assembly (30) according to any one of claims 5 to 8.

10. A method for mounting a plug (60) on a turbomachine part (22), with a locking system (120) for a plug (60) according to any one of claims 1 to 4, the method comprising the following steps: - axial insertion of the plug (60) into a recess (66) in the part (22), such that the retaining finger (62) of the plug (60) is inserted into the first recess (44b) in the part (22); - rotation of the plug (60) so as to insert its retaining finger (62) into the second recess (44b) in the part (22); - axial displacement of the locking ring (38), so as to introduce its protruding element (44a) in the first recess (44b) of the part (22), until the ring reaches its locking position in which its protruding element (44a) circumferentially covers, at least in part, the second recess (144b) housing the retaining finger (62).

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