System for locking plug in aircraft turbine engine component, preferably turbine engine shaft

Abstract

The invention relates to a system (120) for locking a plug (60) on an aircraft turbine engine component (22), comprising a locking ring (38) equipped with a protruding element (44a) intended to be inserted in a first groove (44b) of said component (22) in a locking position of the locking ring (38), said first groove (44b) being open in an axial direction, said first groove (44b) being arranged in a locking position of the locking ring (38). The plug comprises a retaining finger (62) intended to be inserted into a second groove of the component in the form of a second slot (144b) opening circumferentially in the first groove (44b). Furthermore, in the ring locking position, the protruding element (44a) is intended to at least partially cover in the circumferential direction the second groove (144b) accommodating the retaining fingers (62) of the plug (60).

Description

Technical Field

[0001] This invention relates to the field of systems for locking plugs into aircraft turbine engine components (e.g., turbojet engines or turboprop engines).

[0002] Preferably, the present invention relates to a system for locking such plugs, for example in a compressor shaft or turbine shaft, but is not limited to this preferred application. Existing technology

[0003] In aircraft turbine engine components, plugs are sometimes required, such as in hollow shafts, to seal the space inside the shaft.

[0004] Once in place and during turbine engine operation, the plug may be subjected to significant loads, particularly pressure loads.

[0005] Therefore, a plug locking system is needed to hold it in its initial position on the turbine engine component. However, solutions proposed in the prior art often prove to be complex, for example, by employing connectors such as retaining rings. Furthermore, this type of connector may prove unsuitable for bearing the significant loads that may be applied to the plug.

[0006] Furthermore, the assembly, and especially the disassembly, of deformable components (such as retaining rings) can sometimes be complex.

[0007] Finally, the design of existing technology solutions may require visual access to assemble the plug locking system. However, in the extremely dense environment of turbine engines, such visual access is not always possible.

[0008] Therefore, it is necessary to improve the design of the plug locking system in the existing technology. Summary of the Invention

[0009] To meet the aforementioned needs, a first objective of the present invention is to provide a system for locking a plug in an aircraft turbine engine component with an axis (X) extending circumferentially about the axis (X). The system includes a locking ring equipped with a protruding element, which, when in the ring-locked position, is intended to be inserted into a first recess in the turbine engine component, the first recess being axially open. The plug includes a retaining finger intended to be inserted into a second recess in the component, the second recess being in the form of a second notch circumferentially communicating with the first recess. Furthermore, when in the ring-locked position in the turbine engine component, the protruding element of the ring is intended to circumferentially at least partially cover the second recess accommodating the plug retaining finger.

[0010] Thanks to the design of this invention, the removal of the plug is easily prevented, and the system is able to withstand significant pressure loads applied to the plug.

[0011] Furthermore, the assembly of the locking system according to the invention can be easily performed blindly, that is, without the need for a visual path to the turbine engine area where the assembly is being performed.

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

[0013] Preferably, the locking ring of the plug forms an anti-rotation ring for a connection system between a turbine engine component and another turbine engine component (preferably two turbine engine shafts), the anti-rotation ring being designed to limit / prevent rotation of the fastening nut of the connection system, and the protruding element of the locking ring being designed to engage with the first groove provided on the turbine engine component to jointly form a first rotary coupling device.

[0014] This preferred embodiment enables the ring to perform several different functions, both helping to prevent the coupling nut from rotating and to help lock the plug. This simplifies the design and reduces weight and cost.

[0015] Preferably, the locking ring includes two protruding elements that, when the locking ring is in the locked position, are respectively inserted into two first grooves of the component, the first grooves being axially open. The plug includes two retaining fingers, respectively configured to be inserted into two second grooves of the turbine engine component, each second groove being in circumferential communication with one of the first grooves. Furthermore, when the locking ring is in the locked position on the component, the at least two protruding elements of the locking ring circumferentially at least partially cover the two second grooves accommodating the retaining fingers.

[0016] Of course, the number of retaining fingers on the plug can be more than two, such as three or four, and preferably they are evenly spaced from each other in the circumferential direction.

[0017] Preferably, the protruding element is a finger, and the first groove of the turbine engine component is a first slot. Alternatively, the finger may be provided on the turbine engine component to insert into a slot of a ring without departing from the scope of the invention.

[0018] Another object of the present invention is to provide an assembly for an aircraft turbine engine, comprising components of the aircraft turbine engine, a plug preferably sealing the component chamber at its axial end, and a plug locking system as described above.

[0019] Preferably, the component further includes a system for connecting the component to another turbine engine component.

[0020] Preferably, the plug includes a body with an outer diameter substantially equal to the inner diameter of the chamber of the component to be plugged, and retaining fingers of the plug protrude radially outward from the plug body.

[0021] Preferably, the second groove communicating with the first groove is a second circumferential groove formed in one of the two sidewalls of the first groove.

[0022] Another object of the present invention is to provide an aircraft turbine engine comprising at least one such component. For example, it may be a turbojet engine or a turboprop engine.

[0023] Finally, the object of the present invention is to provide a method for assembling plugs in turbine engine components using the plug locking system as described above, the method comprising the following steps:

[0024] • The plug is axially introduced into the cavity of the component, such that the retaining fingers of the plug are inserted into the first groove of the component;

[0025] • Rotate the plug to keep the finger inserted into the second groove of the component;

[0026] • The locking ring is moved axially to introduce its protruding element into the first groove of the component until the ring reaches its locked position, wherein its protruding element circumferentially at least partially covers the second groove that accommodates the retaining finger.

[0027] Other advantages and features of the invention will become apparent in the following non-limiting detailed description. Attached Figure Description

[0028] [ Figure 1 [This is a longitudinal sectional view of a turbojet engine;]

[0029] [ Figure 2 This is a longitudinal half-sectional view of the two-component connection system of the turbojet engine shown in the aforementioned figure;

[0030] [ Figure 3 ] for Figure 2 The cross-sectional view of the connection system shown corresponds to the following Figure 2 Cross section of line III-III;

[0031] [ Figure 4 ] for Figure 2 and 3 A partial perspective view of the fastening nuts of the connection system shown;

[0032] [ Figure 5 ] for Figure 2 and 3 A partial perspective view of the anti-rotation ring of the connection system shown;

[0033] [ Figure 6 [A partial perspective view of an anti-rotation ring according to an alternative embodiment;]

[0034] [ Figure 7This is a partial perspective view of the end of a turbine engine shaft, designed to... Figure 2 and 3 The connection system shown is used for connection;

[0035] [ Figure 8 ] for Figure 2 and 3 A partial perspective view of the connection system shown;

[0036] [ Figure 9 ]、[ Figure 10 ]、[ Figure 12 ] for Figure 2 The longitudinal half-sectional view of the connection system shown in different successive states during the assembly of the connection system;

[0037] [ Figure 11 ] for Figure 10 The cross-sectional view of the connection system shown corresponds to the following Figure 10 Cross section of line XI-XI;

[0038] [ Figure 13 ]、[ Figure 14 [This is a cross-sectional view of the coupling system shown in the foregoing figures in different successive states during the method of assembling the coupling system, according to an alternative embodiment;]

[0039] [ Figure 15 This is a longitudinal half-sectional view of a connection system similar to that shown in the foregoing figures and presented as an alternative embodiment;

[0040] [ Figure 16 ]、[ Figure 17 ]、[ Figure 18 ]、[ Figure 19 [A partial cross-sectional view of the coupling system according to yet another alternative embodiment in different successive states during the assembly of the coupling system method;]

[0041] [ Figure 20 This is a partial perspective view of a plug locking system for a turbojet engine component, which is integrated into the connection system shown in the aforementioned figures;

[0042] [ Figure 21 This is an axial view of the plug shown in the aforementioned figure;

[0043] [ Figure 22 ]、[ Figure 23 ]、[ Figure 24 ] for Figure 20 Partial perspective view of the locking system in different successive states during the assembly of the locking system;

[0044] [ Figure 25 To lock the system in Figure 23 A partial sectional view in the state shown;

[0045] [ Figure 26 To lock the system in Figure 24 A partial sectional view in the state shown;

[0046] [ Figure 27 This is a partial cross-sectional view of the locking system in its state after the system assembly method is completed. Detailed Implementation

[0047] First refer to Figure 1 The image shows an aircraft turbine engine 1 according to a preferred embodiment of the present invention. This is a dual-rotor turbofan engine. However, it could also be another type of turbine engine, such as a turboprop engine, without departing from the scope of the invention.

[0048] The turbine engine 1 has an axis X around which its various components extend; this axis is called the longitudinal axis of the turbine engine. Along the main flow direction 5 of the gas passing through the turbine engine, from upstream to downstream, it includes: a fan 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.

[0049] Typically, after passing through the fan, the air is divided into a central main airflow 12a and a secondary airflow 12b surrounding the main airflow. The main airflow 12a flows into the main gas circulation channel 14a, passing through compressors 4 and 6, combustion chamber 11, and turbines 7 and 8. The secondary airflow 12b flows in the secondary channel 14b, which is radially directed outward from the engine casing and surrounded by nacelle 9.

[0050] Figures 2 to 8 A system 20 is shown for connecting two rotating components (which share the same axis of rotation X) of a turbojet engine 1. Here, a first shaft 22 corresponds to the low-pressure turbine shaft, and a second shaft 24 corresponds to the low-pressure compressor shaft. Both shafts 22 and 24 are hollow shafts, with the upstream end of the first shaft 22 inserted into the downstream end of the second shaft 24 to achieve axial translational and rotational connection via system 20. These two coaxial shafts 22 and 24, centered on the X-axis, together with their connection system 20, constitute assembly 30. Multiple such assemblies can be arranged inside the turbojet engine, and the connected components can belong to any different modules of the turbojet engine, such as a fan, compressor, combustion chamber, or turbine.

[0051] This is particularly suitable for connecting components with large diameters and where the field of view in the connection area is limited or even zero. Figure 2 The architecture shown in part is such a case, in which system 20 is in an assembled state and two shafts 22 and 24 are connected together.

[0052] The coupling system 20 first includes a nut 32 for fastening the two shafts. This nut is centered on the X-axis and has a first thread 34a (or nut thread), which mates with a second thread 34b (or first component thread) applied to the outer surface of the first shaft 22. For example... Figure 2 and Figure 8 As shown, in the assembled state of the connecting system 20, the downstream end of the nut 32 applies an axial force to the second shaft 24, or more precisely, an axial force to its internal shoulder. This axial force pushes the second shaft 24 downstream, causing it to abut against the external shoulder of the first shaft 22. An axial washer 36 may be inserted between the two shoulders, such as... Figure 2 As shown in the example, the axial tightening force of the nut must be sufficient to create the required connection between the two shafts 22 and 24.

[0053] System 20 also includes an anti-rotation ring 38, which restricts / prevents rotation of nut 32 relative to first shaft 22 in the assembled state of system 20.

[0054] The anti-rotation ring 38 is at least partially arranged inside the nut 32 with the X-axis as its center, and can move axially relative to the nut at different axial positions. Figure 2 and Figure 8 In this configuration, the anti-rotation ring 38 is positioned downstream of the nut 32, corresponding to the final connection point of the shaft. It is secured in this position by an open ring 40 or a similar retaining element, which is carried by the ring 38 and engages with a groove 42a on the inner surface of the nut 32 upstream of the first thread 34a, corresponding to its position.

[0055] Therefore, in the final engagement position of ring 38, it is axially secured relative to nut 32 by the open ring 40 or any other translational locking system associated with the ring. In this position, both the first and second rotary coupling devices are effectively engaged.

[0056] The first rotary coupling device comprises a first rotary coupling member 44a machined at the downstream end of the ring 38 and a first complementary rotary coupling member 44b machined at the upstream end of the first shaft 22. Here, a finger-groove assembly is preferred, with the finger 44a preferably disposed on the ring 38 and the groove 44b disposed on the first shaft 22, although the reverse is also possible. The groove 44b is also referred to as the first groove 44b.

[0057] The number of such finger-groove assemblies is preferably less than four, for example, three, or two as shown in the figure. In this case, the two fingers 44a are preferably arranged radially symmetrically, and correspondingly, the grooves 44b on the upstream end of the first shaft 22 are also arranged in the same manner, with these grooves opening axially upstream.

[0058] The finger-like object 44a, located at the downstream end of ring 38, is as follows: Figure 2 , 5 As shown in Figure 8, it protrudes axially downstream and radially inward, or as... Figure 6 As shown in the alternative embodiment, it protrudes only axially downstream.

[0059] The second rotary coupling device consists of a second rotary coupling member 46a machined on the outer surface of the ring 38 and a second complementary rotary coupling member 46b machined on the inner surface of the nut 32. Preferably, the mating splines 46a and 46b are arranged in two concentric annular spline rows. Each row of annular splines 46a and 46b can be 360° continuous, or extend only to a sector angle less than 360°, or consist of multiple circumferentially spaced sector segments. The number of splines in each annular row is relatively large, for example, greater than twenty, thirty, or forty. The number of splines in the two annular rows is preferably the same, and this number is strictly greater than the number of slots and the number of fingers.

[0060] Each spline extends radially and has a conventional toothed structure; specifically, spline 46a extends radially outward and spline 46b extends radially inward.

[0061] One characteristic is that the first spline 46a and the fingers 44a are separated in the axial direction (upstream direction). In fact, there is preferably no axial overlap between these elements 46a and 44a.

[0062] Figures 9 to 12 The method of assembling the coupling system 20 on the two shafts 22 and 24 is described.

[0063] First, the system 20 is installed onto the first shaft 22, with the nut 32 fitted onto the upstream end of the shaft. The nut 32 is then tightened via the first and second threads 34a and 34b. This tightening operation aims to press the first shaft 22 axially against the second shaft 24 by compressing the downstream end of the nut 32. The tightening torque applied to the nut 32 must reach the minimum torque required to ensure a reliable connection between the two shafts. This step is schematically shown in... Figure 9 In this step, ring 38 is held in the upstream non-working position, referred to as the non-connected position, where it is axially fixed relative to nut 32 by open ring 40, which engages with another groove 42b on the inner surface of the nut, upstream of groove 42a.

[0064] The next step is as follows Figure 10 and 11As shown. It involves rotating ring 38 about the X-axis relative to a fixed nut 32 while simultaneously translating it downstream. The rotation of the ring is used to mate fingers 44a with slots 44b, after which the fingers can be axially inserted into these slots. This axial movement of the ring does indeed bring the anti-rotation ring 38 to a temporary axial position relative to the nut, thereby bringing the first rotating coupling devices 44a, 44b into their engaged state. However, the axial movement of ring 38 usually stops due to a mismatch between splines 46a, 46b, as... Figure 11 As shown in the figure, the spline gaps on the first spline 46a and the second spline 46b of the other row are not aligned, and vice versa. Therefore, in the temporary axial position of ring 38, the second rotary coupling devices 46a and 46b are still in a non-connected state.

[0065] In this step, rotational and translational forces on ring 38 can be applied simultaneously, especially during "blind assembly" operations in the turbojet engine assembly area.

[0066] To achieve the required match between splines 46a and 46b (especially) Figure 3 (As shown in the diagram), the nut 32 on the second shaft 22 needs to be tightened again. Therefore, an over-torque, which still needs to be precisely measured, is applied to the nut until the desired match between splines 46a and 46b is achieved. This step, which aims to apply an over-torque to the nut 32, is schematically shown in the diagram. Figure 12 middle.

[0067] Because the pitch of the splines is smaller than that of the slots, the amount of rotation required to achieve the desired fit on the nut, and the resulting over-torque, remains at a low level, which is an advantage.

[0068] Subsequently, the actuator ring 38 moves axially relative to the nut 32 from the temporary axial position to the final axial connection position, so that the splines 46a and 46b are as follows: Figure 2 The meshing is shown. It should also be noted that the rotation of nut 32 and the translational force applied to ring 38 can be performed simultaneously, especially during "blind assembly" operations in the turbojet engine assembly area.

[0069] At the end of this step, the second rotary coupling devices 46a and 46b are in their connected state due to the engagement of the splines. Similarly, after the additional axial movement of the ring 38 relative to the nut 32, the fingers 44a of the first rotary coupling devices 44a and 44b are further inserted into their respective slots 44b, and the first rotary coupling devices 44a and 44b also remain in their connected state.

[0070] During this additional movement of ring 38, the open ring 40 engages in the groove 42a of the ring, thereby ensuring its translational locking. This allows the entire system 20 to remain in the assembled state, ensuring the translational and rotational connection of the two shafts 22 and 24 without the risk of nut 32 loosening.

[0071] Figure 13 and 14 An alternative embodiment is shown, which has the advantage of allowing the assembly of the coupling system 20 to be completed without applying over-torque to the nut.

[0072] This alternative embodiment and Figures 2 to 12 The embodiments shown share many common technical features. Furthermore, elements with the same reference numerals in the figures correspond to the same or similar elements.

[0073] exist Figure 13 and 14 In an alternative embodiment, a circumferential clearance 48 is shown between each finger 44a and its corresponding notch 44b in a temporary axial position of the ring 38. This arrangement allows the ring 38 to achieve sufficient angular clearance relative to the fixed nut 32 by partially or completely eliminating this clearance 48, thereby achieving circumferential mating of the splines 46a, 46b. After this operation, the coupling system 20 achieves the following: Figure 14 The state shown is illustrated here. It should be noted that the circumferential direction relative to the X-axis also corresponds to the tangential direction.

[0074] As previously stated, the desired match between splines 46a and 46b enables the anti-rotation ring 38 to move axially from its temporary axial position to its final axial connection position.

[0075] It should also be noted that a hybrid solution is also feasible, in which the matching of splines 46a and 46b is achieved on the one hand by rotating ring 38 to eliminate the aforementioned gap 48, and on the other hand by applying a slight over-torque to nut 32.

[0076] Another alternative implementation is as follows: Figure 15 As shown, an elastic reset device, such as one or more springs 50, is provided, axially arranged between the nut 32 and the anti-rotation ring 38. The spring 50 is capable of forcing the ring 38 to move axially downstream relative to the nut 32, thus generating the axial force required to move the ring 38 from its upstream position to its temporary axial position, and from this temporary axial position to its final axially connected position.

[0077] This principle also allows ring 38 to remain in its final axially connected position, potentially eliminating the need for additional spring-loaded retaining devices.

[0078] Figures 16 to 19Various states of the coupling system 20 according to yet another alternative embodiment are shown, wherein each finger 44a and its corresponding slot 44b have inclined circumferential stop surfaces that are at an angle relative to the axial direction. In other words, each of the two surfaces 52a, 52b forms a non-zero angle with the axial direction parallel to the X-axis.

[0079] Inclined circumferential stop surfaces 52a, 52b, as Figure 16 As shown. They are parallel or substantially parallel, each consisting of a sidewall of the finger 44a and a sidewall 68 of the slot 44b. The inclination angle of the circumferential stop surface 52b of the slot 44b causes it to gradually widen circumferentially in the axial upstream direction. Conversely, the inclination angle of the circumferential stop surface 52a of the finger 44a causes it to gradually narrow circumferentially in the axial downstream direction.

[0080] Figure 16 The position corresponds to Figure 9 At this position, the finger 44a is not yet matched with its associated slot 44b. After this matching is achieved by rotating the ring 38 under the action of the operator or the spring 50, the finger 44a is partially introduced into the slot 44b, as shown below. Figure 17 As shown schematically. Axial introduction stops due to interference between splines. At this point, the circumferential clearance 48 observed between the inclined circumferential stop surfaces 52a, 52b can be partially or completely eliminated by the rotating ring 38 to match these identical splines. Figures 16 to 19 (Not shown in the image). This step is shown schematically. Figure 18 In the middle. Subsequently, when the splines are matched, under the action of spring 50, ring 38 moves axially to its final axial connection position. When the circumferential stop surfaces 52a and 52b are as Figure 19 This position is reached when they come into contact with each other, and this contact is preferably surface contact.

[0081] Due to the inclination of the contact surfaces 52a and 52b, the finger 44a abutting against the sidewall of the slot 44b applies an inclination force with a circumferential component to the shaft 22. The direction of this component causes the finger 44a to force the second shaft 22 to rotate in the direction of rotation that makes the nut 38 tighten more on the shaft 22.

[0082] Figure 20 The diagram shows component 30, which includes a system 20 for connecting two shafts 22, 24, and a system 120 for locking a plug 60 in the first shaft 22. Specifically, the plug 60 is assembled at or near the upstream end of the first shaft 22, at or near the first rotary couplings 44a, 44b. The plug 60 is used to seal a chamber 66 centered on the X-axis within the upstream shaft 22. The plug 60 may be subjected to significant loads, particularly pressure loads, which the locking system 120 must be able to withstand.

[0083] exist Figure 20 In this embodiment, the plug locking system 120 and the two-shaft coupling system 20 are thus combined within the assembly 30, sharing common components to achieve a compact overall design, lighter weight, and lower cost.

[0084] However, it should be noted that the locking system 120 according to the invention can also be implemented in other environments of turbojet engines, is not necessarily associated with the coupling system as described above, and may be used for components other than the shaft.

[0085] Continue to refer to Figure 20 The locking system 120 includes an anti-rotation ring 38, which here also performs the additional function of locking the plug 60. Therefore, in the following sections of the specification, this ring 38 will be referred to as the locking ring.

[0086] As previously described, the locking ring 38 is equipped with a protruding element consisting of fingers 44a. In the ring locked position 38 (corresponding to its final axial connection position as described above), the fingers 44a are inserted into the first grooves, i.e., the first slots 44b, of the shaft 22. However, the protruding element 44a and the first grooves 44b can be in other forms without departing from the scope of the invention.

[0087] A key feature here is that the plug 60 includes one or more retaining fingers 62, preferably in the same number and arrangement as the first slot 44b. Therefore, two retaining fingers 62 are provided on the plug body 64, arranged opposite each other. Here, the outer diameter of the plug body 64 is substantially equal to the inner diameter of the cavity 66 of the shaft 22, preferably retaining only a very small assembly clearance. Furthermore, the retaining fingers 62 protrude radially outward from the plug body 64.

[0088] Each retaining finger 62 is inserted into a second groove in the shaft 22, which takes the form of a second groove 144b that is circumferentially connected to one of the first grooves 44b. The size of each second groove 144b can be much smaller than the size of the first groove 44b it communicates with, for example, it can be in the form of a simple circumferential groove.

[0089] More specifically, each second circumferential slot 144b is formed in one of the two sidewalls 68 of the first slot 44b that communicates with it. Figure 20 In the preferred embodiment shown, each second circumferential slot 144b ( Figure 20 Only one of the two slots 144b is visible in the middle, both of which are made at the axial bottom of their associated first slot 44b.

[0090] Therefore, when the locking ring 38 is in the locked position at the upstream end of the first shaft 22, each finger 44a at least partially covers a second slot 144b that receives the plug retaining finger 62 in the circumferential direction. More specifically, each finger 44a covers the bottom of a second slot 144b that receives the retaining finger 62 in the circumferential direction.

[0091] Due to this overlap, each finger 44a thus immediately follows the second notch 144b in the circumferential direction, and the two elements do not necessarily contact each other. If a circumferential gap exists, it is preferably kept small enough to prevent the finger 62 from completely dislodging from the second notch 144b.

[0092] Figure 21 An axial view of the plug 60 is shown, and its assembly method will now be referred to. Figures 22 to 27 Describe it.

[0093] First, such as Figure 22 , 23 As shown in Figure 25, the step of axially introducing the plug 60 into the first shaft 22 chamber 66 is performed such that each retaining finger 62 of the plug is axially inserted downstream into the first slot 44b of its associated shaft 22 until it reaches the axial bottom of the slot 44b.

[0094] Subsequently, the plug 60 is rotated about its central X-axis to allow each retaining finger 62 to enter its associated second slot 144b. The magnitude of rotation can be kept small, adapted to the shallow depth of the second slot 144b. After performing this step, the system 120 is in the following state: Figure 24 and 26 As shown.

[0095] at last, Figure 27 The final step is described, corresponding to the movement of the locking ring 38 in its locked position. This causes each finger 44a to insert into its associated first slot 44b on the shaft 22 until the finger 44a at least partially covers the second slot 144b that accommodates and holds the finger 62 in the circumferential direction.

[0096] Of course, those skilled in the art can make various modifications to the invention described above by way of non-limiting example only, the scope of which is defined by the appended claims. In particular, the technical features of the various preferred embodiments and their alternative embodiments are interchangeable and / or combinable.

Claims

1. A system (120) for locking a plug (60) in an aircraft turbine engine component (22) with an axis (X), said component (22) extending circumferentially about said axis (X), characterized in that, The system includes a locking ring (38) equipped with a protruding element (44a) which, when in the locked position, is intended to be inserted into a first groove (44b) of the turbine engine component (22), the first groove (44b) being axially open. The plug (60) includes a retaining finger (62) intended to be inserted into a second groove (144b) of the component (22), the second groove (144b) being a second slot circumferentially open in the first groove (44b). When the locking ring (38) is in the locked position in the turbine engine component (22), the protruding element (44a) of the locking ring (38) is intended to at least partially cover the second groove (144b) circumferentially containing the retaining finger (62) of the plug (60).

2. The locking system according to claim 1, characterized in that, The locking ring (38) of the plug (60) constitutes an anti-rotation ring for the connection system (20) between the turbine engine component (22) and another turbine engine component (24). Preferably, the component (22) and the other component (24) are two engine shafts. The anti-rotation ring (38) is designed to limit / prevent the rotation of the fastening nut (32) of the connection system. The protruding element (44a) of the locking ring (38) is designed to cooperate with the first groove (44b) provided on the turbine engine component (22) to jointly form a first rotary coupling device.

3. The locking system according to claim 1 or 2, characterized in that, The locking ring (38) includes two protruding elements (44a) that, when the locking ring (38) is in the locked position, are respectively inserted into two first grooves (44b) of the component (22), the first grooves (44b) being axially open. The plug (60) includes two retaining fingers (62) that are respectively configured to be inserted into two second grooves (144b) of the turbine engine component (22), each second groove being circumferentially open in one of the first grooves (44b). When the locking ring (38) is in the locked position on the component (22), the at least two protruding elements (44a) of the locking ring (38) at least partially cover the two second grooves (144b) accommodating the retaining fingers (62) in the circumferential direction.

4. The locking system according to any one of the preceding claims, characterized in that, The protruding element (44a) is a finger, and the first groove (44b) of the turbine engine component (22) is a first slot.

5. An aircraft engine assembly (30) comprising an aircraft turbine engine component (22) extending about an axis (X), a plug (60) preferably sealing its chamber (66) at an axial end of said component (22), and a plug (60) locking system (120) according to any of the preceding claims.

6. The component according to claim 5, characterized in that, It also includes a system (20) for connecting the component (22) to another engine component (24).

7. The component according to claim 5 or 6, characterized in that, The plug (60) includes a body (64) with an outer diameter substantially equal to the inner diameter of the chamber (66) of the component (22) to be plugged, and retaining fingers (62) of the plug (60) protruding radially outward from the plug body (64).

8. The component according to any one of claims 5 to 7, characterized in that, The second groove (144b) communicating with the first groove (44b) is a second circumferential groove formed in one of the two sidewalls (68) of the first groove (44b).

9. An aircraft turbine engine (1) comprising at least one component (30) according to any one of claims 5 to 8.

10. A method for assembling a plug (60) on an engine component (22) using a plug (60) locking system (120) according to any one of claims 1 to 4, the method comprising the steps of: o The plug (60) is axially introduced into the chamber (66) of the component (22) such that the retaining finger (62) of the plug (60) is inserted into the first groove (44b) of the component (22); o Rotate the plug (60) to keep the finger (62) in the second groove (144b) of the component (22); The locking ring (38) is moved axially to introduce its protruding element (44a) into the first groove (44b) of the component (22) until the ring reaches its locked position, in which its protruding element (44a) at least partially covers the second groove (144b) that accommodates the retaining finger (62) in the circumferential direction.

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