FR3097200A1 - INPUT CONE FOR AN AIRCRAFT TURBOMACHINE - Google Patents

Abstract

The present invention relates to an inlet cone (20) for an aircraft turbomachine (1), comprising a frustoconical body (22) and a tip (21) of elastically deformable material fixed to an end (211) of smaller diameter. of said body (22), characterized in that it further comprises a base (23) for fixing the point (21) to said body (22), the point (21) being fixed to said base (23) which comprises first fixing means on said end (211) as well as second centering means cooperating with complementary means of said end (211). Figure for the abstract: Figure 3

Description

INLET CONE FOR AN AIRCRAFT TURBOMACHINE

Technical field of the invention

The field of the present invention is that of turbomachines, in particular that of gas turbine engines, for example and not limited to a turbojet or an aircraft turboprop.

The present invention relates more particularly to an air inlet cone for an aircraft turbine engine.

Technical background

It is known from the prior art of turbomachines extending along a longitudinal axis and comprising, from upstream to downstream, in the direction of gas flow, a fan, one or more compressor stages (for example a low-pressure compressor and a high-pressure compressor), a combustion chamber, one or more turbine stages (for example, a high-pressure turbine and a low-pressure turbine), and a gas exhaust nozzle.

Conventionally, such turbomachines further comprise, upstream, an air inlet cone which is mounted on the fan, for example via a generally annular shroud itself connected to a compressor shaft turbomachine low pressure. The connection between the inlet cone and the shell is generally made using bolted assemblies. The downstream end of the shroud is flush with the platforms of the fan blades, being located in the aerodynamic continuity of the latter.

Such an inlet cone comprises an upstream end in the shape of a cone tip centered on an axis of rotation of the inlet cone, also corresponding to the longitudinal axis of the fan and of the entire turbomachine.

This point is known to be a point of the turbomachine favoring ice accretion, given that its centering on the axis of rotation does not allow the application of significant centrifugal forces. As a result, the ice forming on the tip can reach a large size before breaking off, with the risk, when it ends up separating from the tip, of damaging the fan blades it strikes or the engine. of the aircraft that ingests it. The ice pack can also build up unevenly on the tip and thus lead to unwanted vibrations of the turbomachine.

In order to overcome this problem, it was proposed to implement a de-icing system whose purpose is to ensure that the ice accreted on the tip is ejected before reaching a critical size. However, this type of system is expensive in terms of mass and size, and above all particularly difficult to set up due to the rotating nature of the inlet cone equipped with it.

It has also been proposed to remove the tip of the inlet cone to deal with these problems of ice accretion in operation. However, the absence of the tip does not make it possible to deflect and correctly guide part of the flow of air entering the turbomachine in operation, in particular to ensure its cooling and improve the flow of air. Furthermore, a truncated inlet cone (i.e. without the tip) does not completely protect the inlet cone against the formation of ice and the ingestion of ice (or other solid particles ) by the turbomachine in operation.

Finally, it is known in the prior art to make, as shown in Figure 2, an inlet cone 10 with an upstream tip 11 of flexible material and a downstream body 12 of rigid material. The tip 11 is glued to the downstream body 12 along a connecting plane P1, to be in aerodynamic continuity. However, it is more difficult to fix reliably, in particular with optimal centering, the tip made of flexible material on the body made of rigid material. In operation, misalignment can cause distortion between the tip and the body of the cone, creating gaps for ice to enter. This can result in irreversible damage to the inlet cone. Thus, such an attachment solution by simple gluing of the tip to the inlet cone is not entirely satisfactory.

In this context, it is interesting to propose a solution making it possible to overcome the drawbacks of the prior art, in particular by improving the integration of a tip on an air inlet cone by a reliable and compatible solution of the available space and maintenance and repair specifications.

The present invention thus proposes an inlet cone for an aircraft turbomachine, comprising a frustoconical body and a tip made of elastically deformable material fixed to an end of smaller diameter of said body.

The inlet cone further comprises a base for fixing the tip to said body, the tip is fixed to said base which comprises first fixing means on said end as well as second centering means cooperating with complementary means of said end .

According to the invention, the tip is secured to the frustoconical body, in a stable and reliable manner by means of the fixing base. Indeed, this base comprises fastening means making it possible to create a specific and robust mechanical connection between the tip and the frustoconical body. The base also includes centering means making it possible to adjust the alignment when assembling the tip on the inlet cone and thus avoid possible distortions between the tip and the frustoconical body in operation.

In addition, the tip of the inlet cone is made of an elastically deformable material, such as an elastomer, so as to allow the tip to deform during its rotation and also to resist temperature variations. Indeed, in operation, the ice is subjected to substantial centrifugal forces which promote its ejection, and allow it to separate from the inlet cone.

This design of the present invention makes it possible to facilitate the phenomenon of de-accretion of the ice forming on the air inlet cone of the turbomachine in operation, while reinforcing the attachment of the tip to the inlet cone.

The invention therefore has the advantage of being based on a simple design, offering very high reliability, and not very penalizing in terms of cost and size.

The inlet cone for the aircraft turbine engine according to the invention may comprise one or more of the following characteristics, taken separately from each other or in combination with each other:
- the tip is made by overmoulding on the base,
- the base comprises a first threaded central hole which is oriented on the side of said body and which receives a stud or a screw, this stud or this screw passing through a second central hole of said end of the body,
- the stud or screw comprises a free end, located on the side opposite the tip, for screwing a nut configured to bear against a transverse wall of the body located at said end,
- the base comprises a cavity, adjacent to the first orifice and oriented on the side of said body, having a grooved inner surface which is capable of receiving a ring of the stud or of the screw in a complementary manner, this ring being axially movable on the stud or the screw and having a fluted outer surface,
- the second central orifice of said body is shaped to ensure rotational locking of the stud or the screw,
- the base comprises at least one inner or outer radial centering surface cooperating with a complementary radial surface of the end of said body.

According to a first variant of the invention, the base comprises a series of teeth oriented axially and configured to cooperate by engagement and abutment with a first series of first complementary recesses of said body, in order to be locked in rotation with respect to of said body.

According to a second variant of the invention, the inlet cone comprises an additional independent member which is interposed between the base and the body in order to block the base in rotation with respect to the body.

Such independent body may include:
- at least one first projecting element oriented axially and configured to cooperate by engagement and abutment with at least one first complementary recess of the base, and
- At least one second projecting element oriented radially and configured to cooperate by engagement and abutment with at least one second complementary recess of said body.

The invention also relates to an aircraft turbomachine, comprising an inlet cone according to the invention.

Brief description of figures

The invention will be better understood and other details, characteristics and advantages of the invention will appear more clearly on reading the following description given by way of non-limiting example and with reference to the appended drawings in which:

Figure 1 is a schematic half view in axial section of an aircraft turbine engine,

Figure 2 is a schematic front perspective view of an inlet cone, according to the prior art,

Figure 3 is a schematic view in axial section of an inlet cone according to a first embodiment of the invention,

Figure 4 is a schematic side view of a fixing stud or fixing screw used in the inlet cone of Figure 3,

Figure 5 is a schematic half view in perspective and in axial section of a base for fixing the inlet cone illustrated in Figure 3,

Figure 6 is a schematic view in perspective and in axial section of a frustoconical body of the inlet cone shown in Figure 3,

FIG. 7 is a schematic view in axial section of an inlet cone according to a second embodiment of the invention,

Figure 8 is a schematic perspective view of a fixing base of the inlet cone illustrated in Figure 7,

FIG. 9 is a diagrammatic half view in perspective and in axial section of a frustoconical body of the inlet cone illustrated in FIG. 7,

Figure 10 is a schematic perspective view of an anti-rotation ring of the inlet cone shown in Figure 7

Figure 11 is a schematic sectional view along a connecting plane P2 of the inlet cone of Figure 7.

Detailed description of the invention

By convention in the present application, the terms “inner” and “outer”, and “inner” and “outer” are defined radially with respect to a longitudinal axis X of the aircraft engine of the turbomachine. Thus, a cylinder extending along the axis X of the engine has an inner face facing the axis of the engine and an outer surface, opposite its inner surface. By "axial" or "axially" is meant any direction parallel to the X axis and by "transversely" or "transverse" any direction perpendicular to the X axis. Similarly, the terms "upstream" and "downstream" are defined with respect to the direction of air circulation in the turbomachine.

Figure 1 shows a turbomachine 1 double flow. However, this is not limiting and the turbomachine may be of another type, such as a turboprop for example.

The turbomachine 1 extends along a longitudinal axis X and comprises, from upstream to downstream, in the direction of gas flow, a fan 2, one or more compressor stages (for example a low-pressure compressor 3 and a high-pressure compressor pressure 4), a combustion chamber 5, one or more turbine stages (for example a high pressure turbine 6 and a low pressure turbine 7), and an exhaust nozzle 8 of the gases. The fan 2, the low pressure compressor 3 and the low pressure turbine 7 are connected to a low pressure shaft extending along the longitudinal axis. The high pressure compressor 4 and the high pressure turbine 6 are connected to a high pressure shaft formed around the low pressure shaft. The low pressure turbine 7 drives the low pressure shaft in rotation, while the high pressure turbine 6 drives the high pressure shaft in rotation.

The turbomachine 1 further comprises, upstream of the fan 2, an air inlet cone 10 which is mounted on the fan 2 via a shroud (not shown), preferably by fasteners of the type bolts. The shroud is arranged downstream of the inlet cone and this shroud is also connected to the low pressure shaft.

The inlet cone 10 with the shroud are connected to the rotor, in other words to the rotating parts of the turbomachine 1. The inlet cone 10 therefore rotates around the longitudinal axis X.

Figure 2 shows the prior art inlet cone 10, as previously described, in the technical background of the present application.

Figures 3 to 6 illustrate a first embodiment of the inlet cone 20 according to the invention, and Figures 7 to 11 illustrate a second embodiment of the inlet cone 30 according to the invention.

According to the first embodiment, the inlet cone 20 has a shape of revolution extending around an axis which coincides with the longitudinal axis X of the turbomachine.

Referring to Figure 3, the cone 20 comprises a tip 21 disposed upstream and a frustoconical body 22 disposed downstream. In operation, the inlet cone 20 rotates around the longitudinal axis X.

The tip 21 comprises a vertex through which passes the axis of rotation X of the inlet cone 20 which therefore coincides with the longitudinal axis X of the turbomachine. On the side opposite the top, the tip 21 is fixed to an upstream end 211 of smaller diameter of the frustoconical body 22 substantially along a connection plane P1 which is perpendicular to the axis X. The frustoconical body 22, for its part, comprises therefore the upstream end 211 and a downstream end which is configured to be assembled with the shroud on the fan 2 of the turbomachine. The upstream end 211 has a general circular shape, preferably complementary with the tip 21 to be in aerodynamic continuity.

One of the particularities of the invention lies in the fact that the inlet cone 20 further comprises a fixing base 23 integral with the tip 21. The base 23 is fixed on the end opposite the top of the tip. 21, so as to be complementary to the upstream end 211 of the body 22 substantially along another connecting plane P2 which is also perpendicular to the axis X. In FIG. 3, the plane P2 connecting at least in part the base 23 at the upstream end 211 of the body, is offset upstream relative to the plane P1 linking at least in part the tip 21 to the end 211.

In general, the base 23 for fixing the tip 21 is connected to the upstream end 211 of the body 22, on the one hand, by first fixing means, and on the other hand, by second centering means. cooperating with complementary means of the upstream end 211.

Indeed, the base 23 comprises a first central threaded hole 233 which is oriented downstream on the side of the upstream end 211. The first hole 233 is configured to receive a first threaded portion 150 of a stud or a screw 15 unique which is positioned on the axis X of the cone 20.

In the example shown in Figure 4, the stud or screw 15 has the shape of a rod extending axially between the first threaded portion 150 upstream, and a second threaded portion 151 downstream. A central portion 152 is disposed between these first and second portions 150, 151. The threaded 150, 151 and central 152 portions form a one-piece body. Central portion 152 may include a fluted outer surface. In addition, the stud or the screw 15 can comprise an independent locking ring 153 mounted around the central portion 152. The locking ring 153 can comprise a splined inner surface adapted to cooperate by axial sliding with the splines of the outer surface the central portion 152. This ring 153 also comprises an outer surface which is also fluted. In the rest of the application, the stud or the screw 15 will be described with reference to the stud 15 which can be replaced by a screw.

Referring to Figure 5, the base 23 has a shape of revolution extending around a longitudinal axis A. The base 23 comprises an internal portion 230 of substantially cylindrical shape, an external portion 231 of substantially annular shape, and a radial portion 232 of annular shape connecting the two inner 230 and outer 231 portions together circumferentially along a plane P3 substantially perpendicular to the axis A. The inner 230, outer 231 and radial 232 portions are in one piece.

The internal portion 230 comprises, from upstream to downstream, a first end 230a extending axially upstream by a chamfer (or in other words a bevelled point), and a second end 230b extending axially downstream between substantially a first outer peripheral edge 230c connected to the radial wall 232 and a second peripheral edge 230d. The chamfer comprises a vertex through which the axis A passes. The first outer peripheral edge 230c passes through the plane P3 and the second peripheral edge 230d passes through a plane P4 which is substantially perpendicular to the axis A. The inner portion 230 comprises the first central orifice 233 extending around the axis A. The first orifice 233 is preferably threaded and configured to receive the first threaded portion 150 of the stud 15 by screwing, as mentioned above. The first orifice 233 can be partly through and opens on the side of the second peripheral edge 230d, by a central cavity extending around the axis A. The central cavity can be divided into two sub-cavities, for example by a shoulder 234 , so as to form a first cavity 234a disposed upstream and on the side of the first orifice 233, and a second cavity 234b disposed downstream and on the side of the second peripheral edge 230d. The first cavity 234a extends substantially, from upstream to downstream, between the plane P3 and the plane P2. The first cavity 234a is configured to cooperate by complementarity with the ring 153 of the stud 15. The second cavity 234b extends substantially, from upstream to downstream, between the plane P2 and the plane P4. First cavity 234a may include straight splines and second cavity 234b may include a smooth cylindrical surface. The shoulder 234 comprises a radial annular surface 236 located inside the internal portion 230 and passing substantially through the plane P2. The second cavity 234b has an outer diameter greater than that of the first cavity 234a, which itself has an outer diameter greater than that of the first orifice 233. Furthermore, the first cavity 234a may comprise a countersink edge 234c which is disposed on the side of the second cavity 234b. The counterbore edge 234c substantially passes through the plane P2.

The outer portion 231 of the base 23 extends axially, from upstream to downstream, substantially between a third internal peripheral edge 231a connected to the radial wall 232, and a fourth peripheral edge 231b. In FIG. 5, the third peripheral edge 231a passes through the plane P3 and the fourth peripheral edge 231b passes through the plane P4. The outer portion 231 comprises a first series of recesses 235 extending substantially axially, from upstream to downstream, between the plane P2 and the plane P4. The first recesses 235 are circumferentially spaced from each other. For example, the recesses 235, two in number, are substantially of the same size and diametrically opposite with respect to the axis A.

The radial portion 232 includes an annular groove 237 so as to circumferentially space the outer portion 231 from the second end 230b of the inner portion 230. The groove 237 therefore has an outer diameter smaller than that of the outer portion 231, and greater than that of the second end 230b of the inner portion. The groove 237 extends substantially between the plane P3 and the plane P4.

Figure 6 illustrates the body 22 of generally frustoconical shape which extends around a longitudinal axis B. The body 22 comprises a series of teeth 214 and an axial extension 212 which extend axially upstream from a surface upstream 211a of a transverse wall of the upstream end 211. The axial extension 212 is adapted to engage and come into abutment in the second cavity 234b of the base 23. The series of teeth 214 is configured to engage and abut in the first series of recesses 235 of the base 23. The series of teeth 214 and the axial extension 212 can have a similar or different axial length. A radial surface 226 is located radially downstream of the axial extension 212 to cooperate and come into abutment against the radial surface 236 of the base. The axial extension 212 has an outer diameter smaller than the outer diameter of the upstream end 211 of the body 21. The axial extension 212 comprises a second central orifice 220 extending around the axis B and which is through. This second orifice 220 can be tapped and configured to receive by screwing the second threaded portion 151 of the stud 15. The teeth 214 are circumferentially spaced from each other on the upstream surface 211a of the transverse wall of the upstream end 211. For example, the teeth 214, two in number, are substantially of the same size and diametrically opposed with respect to the axis B. The teeth 214 are located on a circumference centered on the axis B which has an external diameter which is, on the one hand, lower than that of the upstream end 211, and on the other hand, higher than that of the axial extension 212. Furthermore, the series of teeth 214 delimits with the axial extension 212, an annular groove 213. This groove 213 therefore has an external diameter which is, on the one hand, smaller than that of the series of teeth 214, and on the other hand, larger than that of the axial extension 212. The groove 213 is configured to receive at least partially by complementarity the second peripheral edge 230d of the internal portion 230 of the base 23.

The present application now describes the attachment of the base 23 integral with the tip 21 to the frustoconical body 22 via the stud 15 and a nut 16 (Figure 3).

Advantageously, the tip 21 is molded onto the base 23. First, a shim (for example 0.5 mm thick) can be placed between the counterbore edge 234c and the locking ring 153 of the stud to prevent locking ring 153 from prematurely engaging counterbore edge 234c. Then, the first portion 150 of the pin 15 is screwed into the first hole 233 of the base 23. The wedge is removed so that the ring 153 can then be moved axially on the portion 152, for example by a suitable instrument, and engaged in the first cavity 234a by making the splines coincide with each other. This makes it possible in particular to block the pin 15 in rotation with respect to the base 23.

Secondly, the axial extension 212 fits into the second cavity 234b of the base 23, then the second portion 151 of the stud 15 is screwed into the second orifice 220 of the axial extension 212. The radial surface 226 of the body 22 bears against the radial surface 236 of the base substantially along the plane P2. Similarly, the series of teeth 214 of the body comes into abutment against an abutment surface of the first series of recesses 235 of the base substantially along the plane P2. The fourth edge 230d comes into abutment at least partly against an abutment surface of the groove 213 of the body 22 substantially along the plane P1. This configuration makes it possible in particular to align and center the base of the tip on the upstream end of the body in an optimal manner.

Finally, the nut 16, for example of the self-locking type, can be screwed onto the second portion 151 of the stud 15 and against a downstream surface 211b of the transverse wall of the upstream end 211 of the body 22. The nut the blocking in rotation of the assembly in operation.

Figures 7 to 11 illustrate the second embodiment. The attachment of the base integral with the tip to the frustoconical body by the stud and the nut described above, applies in the case of this second embodiment.

The inlet cone 30 is distinguished from the cone 20 by a simplified attachment between the base 33 of the tip 31 and the body 32. For this, the radial annular surface 336 of the base 33 is external to be able to come into abutment against the complementary radial surface 326 of the upstream end 311 of the body 32 which is also modified accordingly. In addition, an anti-rotation member 14, for example an anti-rotation ring, is introduced to fit between the base 33 and the upstream end 311.

Referring to Figure 8, the fixing base 33 is distinguished from the base 23 by its second end 330b of the internal portion 330 which extends substantially, from upstream to downstream, between the plane P3 and the plane P2 . Thus, the fourth edge 330d passes substantially through the plane P2, so that the radial surface 336 can be located outside the internal portion 330. Furthermore, the second cavity 334b has the same diameter as the annular groove 337. As a result, the outer portion 331 would therefore comprise the second cavity 334b which extends substantially, from upstream to downstream, between the plane P3 and the plane P4. The groove 337 would open downstream into the second cavity 334b.

Referring to Figure 9, the frustoconical body 32 is distinguished from the body 22 by the absence of a series of teeth and groove on the upstream surface 311a of the transverse wall of the upstream end 311. Furthermore, the axial extension 311 further comprises two recesses 324 which are arranged on either side of the first central orifice 320.

Referring to Figure 10, the anti-rotation ring 14 comprises a substantially annular body and at least two projecting elements. A first projecting element 141 extends in the axial direction at the outer periphery of the annular body. In the example shown, these elements 141 are two in number and diametrically opposed. A second projecting element 142 extends radially inward from the annular body, from its inner periphery. In the example shown, these elements 142 are two in number and diametrically opposed. The second protruding element 142 defines a flat-shaped surface. The lands defined by elements 142 have parallel edges.

The present application now describes the attachment of the base 33 integral with the tip 31 to the frustoconical body 32 by means of the stud 15 and a nut 16.

Referring to Figure 7, once the tip 31 molded on the base 33, the first portion 150 of the pin 15 is screwed into the first hole 333. As described above, a wedge can be used to achieve the fixing of the stud 15 comprising the locking ring 153 in the first orifice 333 of the base 33. The locking ring 153 is then moved axially on the portion 152 of the stud, and engaged in the first cavity 334a by making the grooves coincide with each other .

Then the anti-rotation ring 14 is fixed in the second cavity 334b of the base 31, until at least a part of the second projecting element 142 can bear against the radial surface 336 substantially along a plane P2 . Similarly, the first projecting element 141 of the ring 14 comes into abutment against an abutment surface of the first recess 335 complementary to the base substantially along the plane P2.

Then, the axial extension 312 of the body 32 fits into the second cavity 334b of the base 33, then the second portion 151 of the pin 15 is screwed into the second hole 320 of the axial extension 312 of the body 32. In at least a part of the radial surface 326 of the body bears at least partly on the radial surface 336 of the base substantially along the plane P2. At least another part of the radial surface 336 comes into abutment at least in part against a radial surface of the element 142 of the ring 14 substantially along the plane P2. The element 141 of the ring 14 abuts at least partially against the upstream surface 311a of the transverse wall of the upstream end 311 substantially along the plane P1.

In this configuration, the anti-rotation ring 14 is therefore inserted axially between the base 33 along the plane P2 and the body 32 along the plane P1. Furthermore, the second series of recesses 324 of the body 32 comes into abutment between the second projecting elements 142 of the anti-rotation ring 14 (FIG. 11).

Finally, the nut 16 is screwed onto the second portion 151 of the stud 15 and against the downstream surface 311b of the transverse wall of the upstream end of the body 32, to prevent the entire binding from loosening in operation.

The second embodiment has the advantage of simplifying the design of the frustoconical body and the base (in terms of cost and size), while allowing simple and reliable centering and locking in rotation. Indeed, fewer elements need to be machined on the tapered body and the use of an additional ring, to reinforce the anti-rotation blocking, does not generally impact the size of the inlet cone.

According to the invention, the tip 21, 31 of the cone is made of elastically deformable material. For example, this tip may comprise an elastomeric or silicone material. The frustoconical body 22, 32 of the inlet cone is made of a material which is more rigid compared to the tip. For example, this frustoconical body can be made of a metallic material or a composite. The base 23, 33 can be made of the same material as the frustoconical body, such as a metallic or composite material. The tip according to the invention can be molded onto the base. The anti-rotation ring 14 can be made by additive manufacturing.

The different designs of the air inlet cone according to the invention provide several advantages which are, in particular:
- reinforce the point attachment system on the entry cone,
- facilitate the breaking of the layer of ice forming on the entry cone;
- reduce the impacts suffered by the turbomachine during the detachment of the ice;
- Simplify and declutter the assembly and operation of the inlet cone on the turbomachine;
- adapt easily to current turbomachines.

Overall, this proposed solution is simple, effective and economical to produce and assemble on a turbomachine, while ensuring ice deaccretion and optimal life of the air inlet cone.

Claims (10)

Inlet cone (20, 30) for an aircraft turbine engine (1), comprising a frustoconical body (22, 32) and a tip (21, 31) of elastically deformable material fixed to one end (211, 311) of smallest diameter of said body (22, 32), characterized in that it further comprises a fixing base (23, 33) of the tip (21, 31) to said body (22, 32), the tip (21, 31) being fixed to said base (23, 33) which comprises first fixing means on said end (211, 311) as well as second centering means cooperating with complementary means of said end (211, 311). Cone according to Claim 1, in which the tip (21, 31) is produced by overmoulding on the base (23, 33). Cone according to Claim 1 or 2, in which the base (23, 33) comprises a first central threaded hole (233, 333) which is oriented on the side of the said body (22, 32) and which receives a stud or a screw ( 15), this stud or this screw (15) passing through a second central orifice (220, 320) of said end (211, 311) of the body (22, 32). Cone according to Claim 3, in which the stud or the screw (15) comprises a free end, located on the side opposite the point (21, 31), for screwing on a nut (16) configured to bear on a transverse wall of the body (22, 32) located at said end (211, 311). Cone according to Claim 3 or 4, in which the second central orifice (220, 320) of the said body (22, 32) is shaped to ensure that the pin or the screw (15) is locked in rotation. Cone according to one of the preceding claims, in which the base (23, 33) comprises at least one internal radial surface (236) or external (336) for centering cooperating with a radial surface (226, 326) complementary to the end (211, 311) of said body (22, 32). Cone according to one of the preceding claims, in which the base (23) comprises a series of teeth (214) oriented axially and configured to cooperate by engagement and abutment with a series of first recesses (235) complementary to said body (22) , in order to be locked in rotation with respect to said body. Cone according to one of Claims 1 to 6, in which an additional independent member (14) is interposed between the base (33) and the body (32) in order to block the base (33) in rotation with respect to body screws 32). Cone according to claim 8, wherein said independent member (14) comprises:
- at least one first projecting element (141) oriented axially and configured to cooperate by engagement and abutment with at least one first recess (334) complementary to the base (33), and
- At least one second protruding element (142) oriented radially and configured to cooperate by engagement and abutment with at least one second recess (324) complementary to said body (32). Aircraft turbomachine (1), comprising an inlet cone (20, 30) according to one of the preceding claims.