AIRCRAFT TURBOMACHINE ENTRY CONE

Abstract

The present invention relates to an inlet cone (2) for an aircraft turbomachine (1), said cone (2) comprising: - a conical or frustoconical body (20) having through-holes (202) distributed around the axis (X), and - parts (23) of elastically deformable material located in said through-holes (202), each of the parts (23) of elastically deformable material having at least one peripheral rim (230) for retaining said part (23) in the corresponding through-hole (202), said at least one peripheral rim (230) bearing against an internal surface (20a) of said body (20), wherein the cone (2) further comprises an annular flange (90) attached and fixed inside the body (20), said flange (90) extending radially inside the parts (23) of elastically deformable material to close said holes (202) through-holes in case of loss of said parts (23) during operation. Figure for the abbreviation: Figure 6

Description

Title of the invention: INTAKE CONE FOR AN AIRCRAFT TURBOMACHINE Technical field of the invention

[0001] The field of the present invention is that of turbomachinery, for example aircraft turbomachinery. More particularly, the present invention relates to an inlet cone for such aircraft turbomachinery. Technical background

[0002] It is known from the prior art of turbomachinery extending along a longitudinal axis and comprising, from upstream to downstream, in the direction of gas flow, a blower, one or more compressor stages, a combustion chamber, one or more turbine stages, and a gas exhaust nozzle.

[0003] Typically, such turbomachines also include, upstream, an air inlet cone mounted on the fan, for example, via a generally annular ferrule itself connected to a compressor shaft of the turbomachine. The connection between the inlet cone and the ferrule is generally achieved by means of bolted assemblies. The downstream end of the ferrule is flush with the fan blade platforms, lying in aerodynamic continuity with them.

[0004] Such an inlet cone includes an upstream end in the form of a cone tip centered on an axis of rotation of the inlet cone, also corresponding to the longitudinal axis of the blower and of the entire turbomachine.

[0005] This tip is known to be a point on the turbomachine that promotes ice accretion, since its centering on the axis of rotation does not allow for the application of significant centrifugal forces. Consequently, without specific measures, the ice forming on the tip can reach a considerable size before breaking off, with the risk, when it finally detaches from the tip, of damaging the fan blades it strikes or the engine of the aircraft that ingests it. The ice can also accumulate unevenly on the tip, thus causing undesirable vibrations of the turbomachine.

[0006] To overcome this problem, the Applicant has proposed an inlet cone comprising a body and parts made of elastically deformable material located in through-holes in this body. The parts made of elastically deformable material include at least one peripheral rim for retaining this part in the corresponding through-hole. The peripheral rim bears against an internal surface of the body.

[0007] During operation, the ice layer accreted, particularly at the interface between the elastically deformable material parts and the body, is weakened to facilitate ice detachment. This weakening increases the frequency of ice detachment and thus reduces the size of the ice fragments potentially ingested by the turbomachine components downstream of the inlet cone.

[0008] A drawback of this type of inlet cone could be the formation of opening(s) inside the inlet cone in the event of the loss of one or more elastically deformable material parts during operation. These openings can affect the aerodynamics of the inlet cone by generating, for example, air recirculation within the cone. This could thus impact the thrust and / or operability of the turbomachine. The openings can also affect the mechanical strength of the inlet cone, for example, by causing an accumulation of material (such as ice, debris, or birds, depending on the size of the opening) inside the cone, which would generate an imbalance and probably a change in the center of gravity of the turbomachine.Furthermore, the lack of separation between the inlet cone and the ferrule connected to the compressor shaft could also contribute to material accumulating inside the cone coming into contact with components downstream of the cone (such as the compressor shaft) and potentially damaging these components. Therefore, such an inlet cone design might not be entirely satisfactory in operation.

[0009] In this context, it is interesting to propose a solution to overcome the disadvantages of the prior art, in particular by proposing a new geometry of a safe and efficient entry cone in operation, while promoting the controlled breaking of the ice. Summary of the invention

[0010] The present invention thus proposes an inlet cone for an aircraft turbomachine, this inlet cone being configured to be driven in rotation about an X-axis and comprising: - a conical or frustoconical body comprising through-holes distributed around the X-axis, and - parts made of elastically deformable material located in said through housings, each of the parts made of elastically deformable material having at least one peripheral rim for retaining said part in the corresponding through housing, said at least one peripheral rim being supported on an internal surface of said body.

[0011] According to the invention, the inlet cone further comprises an annular flange attached and fixed inside the body, said flange extending radially inside the parts made of elastically deformable material to close said through housings in case of loss of said parts during operation.

[0012] This new design of the present invention ensures safe and efficient operation of the inlet cone in a turbomachine, while facilitating controlled ice breaking. Indeed, the annular flange attached to the inside of the body, particularly at the level of the elastically deformable material parts, allows the through-holes to be closed, especially in the event of the loss of these parts during operation. This effectively prevents any penetration and accumulation of external materials (such as ice, debris, birds, etc.) into the internal cavity of the cone through the through-hole(s) lacking elastically deformable material parts. By preventing the accumulation of materials, the flange reduces the risk of malfunction and / or damage to the inlet cone (and, more generally, to the turbomachine).

[0013] Furthermore, the flange also allows the peripheral edge of the elastically deformable material parts to be radially pressed against the internal surface of the body. This is also intended to reinforce the retention of the elastically deformable material parts in the through-holes.

[0014] The invention therefore has the advantage of being based on a simple design, offering very high reliability, and little penalizing in terms of costs, size and environmental impact, particularly of the aircraft turbomachine.

[0015] The inlet cone according to the invention may comprise one or more of the following features, taken individually or in combination with each other:

[0016] - the flange comprises a frustoconical portion bearing radially against the parts in elastically deformable material, and an annular portion fixed on the internal surface of the body;

[0017] - the flange further comprises an annular shoulder between the portions frustoconical and annular, this shoulder being axially abutted against a part of the internal surface of the body;

[0018] - the annular portion comprises a first annular row of axial teeth separated from each other by radial notches;

[0019] - the internal surface of the body comprises a second annular row of axial teeth separated from each other by radial notches, the second row of axial teeth extending around the first row of axial teeth;

[0020] - the cone further includes a device for locking the flange vis-à-vis the body, this locking device comprising a first so-called anti-rotation ring having tabs oriented radially inwards and engaged between the first axial teeth of the first row of axial teeth, and tabs oriented radially outwards and engaged between second teeth of the second row of axial teeth;

[0021] - the locking device further comprises a second engaged stop ring in an internal annular groove of the second row of axial teeth and capable of axially retaining the first ring;

[0022] - the flange is screwed into the body and includes an external thread configured for cooperate with an internal thread on the internal surface of the body;

[0023] - the annular portion further comprises a third annular row of teeth radial teeth separated from each other by axial notches, the third row of radial teeth being axially butted against a piece of the internal surface of the body;

[0024] - the first ring and / or the second ring is / are split in the third row of radial teeth is in axial butt against an internal wall of the body the first ring is fixed, for example by radial support, in an annular groove of the body.

[0025] The invention also relates to an aircraft turbomachine, comprising an inlet cone according to one of the features of the invention. Brief description of the figures

[0026] The invention will be better understood and other details, features and advantages of the invention will become more apparent upon reading the following description, given by way of non-limiting example and with reference to the accompanying drawings in which:

[0027] [Fig. 1] is a schematic half-view in axial cross-section of an aircraft turbomachine,

[0028] [Fig.2] is a front perspective view schematically representing a first example of an inlet cone of the turbomachine of [Fig.1],

[0029] [Fig.3] is an axial cross-sectional view partially representing the inlet cone of [Fig.2] comprising a conical body and parts made of elastically deformable material,

[0030] [Fig.4] is a front perspective view schematically representing a second example of an inlet cone of the turbomachine of [Fig.1],

[0031] [Fig.5] is an axial cross-sectional view partially representing the inlet cone of [Fig.4] comprising a frustoconical body and parts made of elastically deformable material,

[0032] [Fig.6] is a half axial cross-sectional view schematically representing the inlet cone of [Fig.4] or [Fig.5] further comprising a first configuration of an annular flange attached and fixed inside the frustoconical body and a locking device for the flange on this body,

[0033] [Fig.7] is another axial cross-sectional and perspective view of the inlet cone of [Fig.6],

[0034] [Fig.8a] is a partial axial and perspective cross-sectional view of the flange screwed onto an annular surface of the frustoconical body of [Fig.6] or [Fig.7],

[0035] [Fig.8b] is a partial perpendicular cross-sectional view of the inlet cone of [Fig.8a],

[0036] [Fig.9a] is a perspective view of a first anti-rotation ring of the locking device of [Fig.6] or [Fig.7],

[0037] [Fig.9b] is a partial axial and perspective cross-sectional view of the first ring of [Fig.9a] mounted in the inlet cone of [Fig.8a] or [Fig.8b],

[0038] [Fig. 10a] is a perspective view of a second stop ring of the locking device of [Fig. 6] or [Fig. 7],

[0039] [Fig. 10b] is a partial axial and perspective cross-sectional view of the second ring of [Fig. 10a] mounted in the inlet cone of [Fig. 9b],

[0040] [Fig.1 1] is a half axial cross-sectional view schematically representing the inlet cone of [Fig.4] or [Fig.5] further comprising a second configuration of the annular flange attached and fixed inside the frustoconical body and of the locking device of the flange on this body.

[0041] Elements having the same functions in the different implementations have the same references in the figures. Detailed description of the invention

[0042] By convention in this application, the terms "inside" and "outside," and "internal" and "external," are defined radially with respect to a longitudinal axis X, in particular of the turbomachine engine. Thus, a cylinder extending along the X-axis has an inner face facing the X-axis and an outer surface opposite its inner surface. "Axial" or "axially" means any direction parallel to the X-axis, and "transversely" or "transverse" means any direction perpendicular to the X-axis. Similarly, the terms "upstream" and "downstream" are defined with respect to the direction of airflow in the turbomachine.

[0043] The present invention applies generally and not limited to an aircraft turbomachine 1, illustrated for example in [Fig. 1]. The turbomachine 1 may be a turbojet, a turboprop or a turboshaft engine.

[0044] Figure 1 shows a turbomachine 1 with a double-flow design. This is not, however, limiting and the turbomachine may be of another type, such as a turboprop.

[0045] The turbomachine 1 can extend along a longitudinal axis X and comprises, from upstream to downstream, in the direction of gas flow, a blower 3, one or more The system comprises several compressor stages (e.g., a low-pressure compressor 4 and a high-pressure compressor 5), a combustion chamber 6, one or more turbine stages 7 (e.g., a high-pressure turbine and a low-pressure turbine), and an exhaust nozzle 8. The blower 3, the low-pressure compressor 4, and the low-pressure turbine are connected to a low-pressure shaft extending along the X-axis. The high-pressure compressor 5 and the high-pressure turbine are connected to a high-pressure shaft wound around the low-pressure shaft. The low-pressure turbine drives the low-pressure shaft, while the high-pressure turbine drives the high-pressure shaft.

[0046] The turbomachine 1 may include, particularly upstream of the fan 3, an air inlet cone 2. This cone 2 may be mounted on the fan 3 by means of an annular ferrule (not shown), preferably by bolt-type fasteners. The ferrule is provided downstream of the cone 2 and this ferrule is also connected to the low-pressure shaft.

[0047] The cone 2 with the ferrule can be connected to the rotor, in other words to the rotating parts of the turbomachine 1.

[0048] The cone 2 is configured to be driven in rotation around an axis which can be substantially coincident with the X axis of the turbomachine 1.

[0049] Figures 2 to 11 illustrate examples of embodiments of the inlet cone 2 according to the invention.

[0050] Cone 2 comprises: - a conical or frustoconical body 20 comprising through-holes 202 distributed around the X-axis, and - parts 23 made of elastically deformable material located in the through housings 202.

[0051] Figures 2 and 3 illustrate a non-limiting example of the body 20 having a conical shape. The body 20 can be a single piece (i.e., made from a single piece of material) which has a pointed apex 201 and an annular end located downstream, called the downstream end 203, and opposite the apex 201. This downstream end 203 corresponds to the largest diameter of the body 20.

[0052] The conical body 20 can extend between the apex 201 and the downstream end 203. This downstream end 203 can be configured to assemble with the fan shell 3 of the turbomachine 1.

[0053] The downstream end 203 upstream may have a general circular shape, preferably complementary to that of the fan shell to be in aerodynamic continuity.

[0054] The conical body 20 may include a conical wall 205 which delimits an internal cavity 209. This internal cavity 209 may be annular with respect to the X axis.

[0055] Figures 4 to 11 illustrate another, non-limiting example of the body 20 having a frustoconical shape. The cone 2 of this example in Figures 4 to 11 may further comprise a point 21 fixed to a smaller diameter end of the body 20. This end may be located upstream, referred to as the upstream end 204.

[0056] The frustoconical body 20 can extend between the upstream end 204 and the downstream end 203. This downstream end 203 can also be configured to assemble with the fan shell 3 of the turbomachine 1.

[0057] The upstream end 204 may have a general circular shape, preferably complementary to the tip 21 to be in aerodynamic continuity.

[0058] The frustoconical body 20 may comprise a frustoconical wall 206 and a radial wall 208 (with respect to the X axis), this radial wall 208 being connected to the frustoconical wall 206 upstream of the body 20, in particular at the upstream end 201. In the example of [Fig. 5], the frustoconical walls 206 and radial wall 208 delimit between themselves the internal cavity 209 of the cone 2. This internal cavity 209 may receive at least partially a cylindrical portion 210 of the tip 21.

[0059] The tip 21 can be positioned upstream of the body 20. The tip 21 can include the vertex 201 through which the X-axis passes. On the side opposite the vertex 201, the tip 21 can be fixed to the upstream end 204, for example substantially along a connecting plane that is perpendicular to the X-axis. For this purpose, the tip 21 can include the cylindrical portion 210. This cylindrical portion 210 can be located on the opposite side of the vertex 201 of the tip 21.

[0060] The cylindrical portion 210 can be mounted in a central orifice 200 of the body 20. For this purpose, the cylindrical portion 210 can have at least one threaded portion complementary to a first tapping (or in other words a first internal thread) of the central orifice 200. Alternatively, the cylindrical portion 210 can simply be fitted into the central orifice 200.

[0061] The tip 21 can be one piece (i.e., made from a single piece of material). In particular, the tip 21 can be formed in one piece with the cylindrical portion 210, as illustrated in [Fig. 5].

[0062] The frustoconical body 20 may include the central passage 200. This central passage 200 is configured for the passage of the cylindrical portion 210 of the tip 21. The central passage 200 may be located on the radial wall 208, in particular at the upstream end 204. This central passage 200 may be aligned substantially with the X-axis. The central passage 200 may have the first threaded hole to facilitate the attachment of the cylindrical portion 210.

[0063] The body 20 (whether conical or frustoconical) can be made of a metallic material, such as aluminium or titanium, or of a composite material.

[0064] The body 20 can extend radially between an internal surface 20a and an external surface 20b opposite this internal surface 20a. The external surface 20b of the frustoconical body 20 can be in aerodynamic continuity (or in other words aligned) with an external surface of the tip 21.

[0065] The body 20 (whether conical or frustoconical) therefore comprises the through-holes 202 which are distributed around the X-axis. The through-holes 202 may be through-openings. These through-holes 202 may thus open into the internal cavity 209 of the cone 2. The through-holes 202 may be located on the frustoconical wall 204 or the conical wall 205. The through-holes 202 may be distributed according to one or more annular rows of through-holes. Each through-hole 202 may have a generally oblong, trapezoidal, and / or rectangular shape.

[0066] The number of through-units 202 can range from three to ten. In the non-limiting example shown in Figures 2 and 4, there are six through-units 202. These through-units 202 are arranged around the X-axis in a single annular row. Alternatively, these through-units 202 can be arranged in two or more annular rows of through-units, one after the other.

[0067] The cone 2 therefore comprises the parts 23 made of elastically deformable material. The parts 23 and the tip 21 connected to the frustoconical body 20 can be made of the same elastic deformable material.

[0068] The elastically deformable material of parts 23 and / or tip 21 may include elastomer, silicone, rubber or polytetrafluoroethylene (PTFE).

[0069] The pieces 23 can number from three to ten. The pieces 23 can be distributed according to one or more annular row(s) of pieces.

[0070] Following the example of Figures 2 and 4, without limitation, there are six parts 23. These parts 23 are arranged around the X-axis in a single annular row. Alternatively, these parts 23 may be arranged in two or more annular rows of parts one after the other.

[0071] Each of the parts 23 includes at least one peripheral rim 230 for retaining that part 23 in the corresponding through housing 202. This peripheral rim 230 bears against the internal surface 20a of the body 22.

[0072] As illustrated in Figures 3 and 5, each of the parts 23 may include a single peripheral rim 230 which extends around the entire perimeter of the part 23.

[0073] Each of the parts 23 can include a pad 236. In the example of the figures, each pad 236 can extend outwards relative to the peripheral rim 230.

[0074] The skid 236 may include an internal surface 236a and an external surface 236b opposite this internal surface 236a. The internal surface 236a and external surface 236b of the skid 236 may be substantially parallel to, respectively, the internal surface 20a and the external surface 20b of the body 22. The external surface 236a may be aligned with the external surface 20b of the body 22 so as to ensure aerodynamic continuity. The external surface 236b of the skid 236 may correspond substantially and generally to an external surface of the part 23 under consideration.

[0075] The skate 236 can occupy the entire volume of the through-housing 202. To achieve this, the skate 236 can have a shape complementary to that of the corresponding through-housing 202. For example, the skate 236 may have a generally oblong, trapezoidal, and / or rectangular shape. Figures 2 to 5 illustrate trapezoidal skates 236.

[0076] One of the features of the invention is that the cone 2 further comprises an annular flange 90 attached and fixed inside the body 20. The flange 90 extends radially inside the parts 23 so as to close the through housings 202 in case of loss of the parts 23 in operation.

[0077] The flange 90 can be attached and fixed to the body 20 whether it is conical (figures 2 and 3) or frustoconical (figures 4 to 11).

[0078] The flange 90 can include a frustoconical portion 900 and an annular portion 902. The frustoconical portion 900 is radially supported against the parts 23. The annular portion 902 is fixed on the internal surface 20a of the body.

[0079] The frustoconical portion 900 can be located on the side of the apex 201, and possibly on the upstream end 204 of the frustoconical body 20. The annular portion 902 can be located on the side of the downstream end 203.

[0080] The frustoconical portion 900 may have a first diameter less than a second diameter of the annular portion 902.

[0081] At least part of the frustoconical portion 900 can be radially supported against the internal surface 236a of the parts 23. At least part of the annular portion 902 can be fixed on the body 20, in particular at the level of the internal surface 20a.

[0082] The flange 90 can be a one-piece annular piece (i.e., made from material) and formed of the frustoconical portions 900 and annular portion 902.

[0083] The flange 90 may further include an annular shoulder 904 between the frustoconical portions 900 and annular portion 902. This annular shoulder 904 is axially abutted against a part of the internal surface 20a of the body 20.

[0084] With reference to figures 6 and 7, the annular shoulder 904 can extend radially outwards relative to the frustoconical portion 900.

[0085] Advantageously, the annular portion 902 may comprise a first annular row of axial teeth 922 separated from each other by radial notches 924. The first row of axial teeth 922 and their radial notches 924 (also called first radial notches 924) can be located on a free end of the annular portion 902 which is opposite the frustoconical portion 900.

[0086] The internal surface 20a of the body may include a second annular row of axial teeth 222 separated from each other by radial notches 224. With reference to Figures 5 and 6, the second row of axial teeth 222 and their radial notches 224 (also called second radial notches 224) may be located on an internal projection 22 of the conical or frustoconical body 20. This internal projection 22 may be annular. The internal projection 22 may include an annular groove 221.

[0087] The second row of axial teeth 222 can extend around the first row of axial teeth 922.

[0088] Each of the second axial teeth 222 of the second row of axial teeth 222 may include an internal annular groove 220.

[0089] The cone 2 may further include a locking device 92 for the flange 90 vis-à-vis the body 20. This locking device 92 may include a first ring 94 called an anti-rotation ring.

[0090] The locking device 92 can be used to fix the flange 90 on the body 20 whether it is conical (figures 2 and 3) or frustoconical (figures 4 to 11).

[0091] The first ring 94 may include first tabs 942 oriented radially inwards and engaged between first axial teeth 922 of the first row of axial teeth 922, and second tabs 944 oriented radially outwards and engaged between second axial teeth 222 of the second row of axial teeth 222.

[0092] With reference to figures 9a and 9b, the first ring 94 may comprise an annular body 940 and the first 942 and second 944 tabs extending outward from the annular body 940.

[0093] On the example of [Fig. 11], the first tabs 942 can be oriented radially inwards and in an upstream direction (namely on the side of the top 201 of the body), and the second tabs 944 can be oriented radially outwards and in a downstream direction (namely on the side of the downstream end 203 of the body).

[0094] The first tabs 942 and / or the second tabs 944 can be from two to ten in number. The first 942 and second 944 tabs can each be distributed around the X axis. In the example of Figures 7 and 9a, the first ring 94 can include, but not limited to, two first tabs 942 which are diametrically opposed to each other and two second tabs 944 which are also diametrically opposed to each other.

[0095] The first ring 94 can be split. This facilitates the assembly of this first ring 94 between the flange 90 and the body 20. For example, the first ring 94 can be assembled by compressing it to place it between the flange 90 and the body 20, and then releasing it so that the first ring 94 can return to its original shape. Compressing the first ring 94 restricts its diameter to position the first tabs 942 in the first radial notches 924 and the second tabs 944 in the second radial notches 224. Releasing the first ring 94 allows it to expand and become firmly fixed between the flange 90 and the body 20.

[0096] Following the example of [Fig. 11], the first ring 94 can be fixed, for example by radial support, in the groove 221 of the body 20 (and in particular of the internal projection 22).

[0097] The first 942 and second 944 tabs, and optionally the annular body 940, of the first ring can be embedded (or otherwise wrapped or covered) in an RTV material (English acronym for "Room Temperature Vulcanization"), such as a silicone rubber or silicone elastomer material.

[0098] The locking device 92 may further include a second ring 96, referred to as a stop ring. This second ring 96 is capable of axially retaining the first ring 94.

[0099] The second ring 96 can be engaged in the internal annular groove 220 of the second row of axial teeth 222 (or in other words in the grooves 220 of the second axial teeth 222).

[0100] The second ring 96 can be split.

[0101] With reference to figures 10a and 10b, the second ring 94 may include an annular body 960. This annular body may include a split portion 962.

[0102] The split portion 962 facilitates the mounting of the second ring 96 between the flange 90 and the body 20. For example, the second ring 96 can be mounted by compressing it to position it between the flange 90 and the body 20, and then releasing it so that the second ring 96 can return to its original shape. As mentioned below with reference to the first ring 94, compressing the second ring 96 also restricts its diameter to position it within the groove 220. Releasing the second ring 96 allows it to expand and become firmly fixed on the inner surface 20a, and optionally in the groove 221 of the body 20.

[0103] The flange 90 can be screwed into the conical or frustoconical body 20. For this purpose, the flange 90 may include an external thread 908 which is configured to cooperate with a second internal thread 207 (or in other words a second tapping) on ​​the internal surface 20a of the body 20.

[0104] In particular, at least a part of the annular portion 902 may include the external thread 908. Advantageously the external thread 908 may be located between the shoulder 904 and the first row of axial teeth 922 (Figures 6 and 7).

[0105] The second internal thread 207 can be located on a part of the internal surface 20a of the body, in particular at the internal projection 22.

[0106] As an alternative to screwing the flange 90 to the body 20, the flange 90 can be fixed to the body 20 by a third annular row of radial teeth 909. These third radial teeth 909 of the third annular row of radial teeth 909 can be axially abutted against a piece of the internal surface 20a of the body 20.

[0107] In particular, the annular portion 902 may include the third annular row of radial teeth 909 separated from each other by axial notches (not visible on [Fig.11]).

[0108] The third radial teeth 909 can be oriented radially outwards.

[0109] With reference to [Fig. 11] and in a non-limiting manner, each of the third teeth 909 can be axially abutted against an internal wall 22a of the body 20, and in particular of the internal projection 22.

[0110] The third annular row of radial teeth 909 can be located upstream of the first annular row of axial teeth 222.

[0111] The present application will now describe, with reference to Figures 2 to 11, the various possible and non-limiting configurations of the inlet cone 2 according to the invention.

[0112] Figures 2 and 3 schematically and partially illustrate a first example of the realization of cone 2 as described above.

[0113] The cone 2 according to the first example includes a body 20 which is conical in shape.

[0114] The cone 2 according to the first example may include the flange 90 screwed into the conical body 20. Alternatively, the flange 90 of the cone 2 of the first example can be fixed on the conical body 20 via the third row of radial teeth 909 in axial butt against the piece of the internal surface 20a of the conical body 20.

[0115] The locking device 92 (comprising the first ring 94 and optionally the second ring 96) can be used to fix the flange 90 onto the conical body 20.

[0116] Figures 4 to 10b schematically illustrate, and possibly partially illustrate, a second embodiment of cone 2 according to the invention. Cone 2 of the second example differs from cone 2 of the first example by the body 20, which is frustoconical in shape as described above.

[0117] With reference to Figures 8a and 8b, the cone 2 according to the second example may include the flange 90 screwed into the frustoconical body 20. For this purpose, the flange 90 may be screwed in, in particular by aligning the first 924 and second 224 radial notches with each other, to facilitate the assembly of the first 942 and second 944 tabs of the first ring 94.

[0118] Once the flange 90 is screwed onto the internal surface 20a, the first tabs 942 of the first ring 94 can be engaged in the first radial notches The corresponding 924 and second tabs 944 can be engaged in the corresponding second radial notches 224, so as to lock the flange 90 screwed onto the internal surface 20a against rotation. This is illustrated in Figures 9a and 9b.

[0119] Finally, the second ring 96, which can be split, is mounted in the groove 220 of the second axial teeth 224, so as to axially lock the first ring 94 against the flange 90.

[0120] Fig. 11 schematically illustrates a third example of an embodiment of cone 2 according to the invention.

[0121] Cone 2 of the third example differs from cone 2 of the second example by the attachment of the flange 90 to the body 20.

[0122] The cone 2 of the third example includes the flange 90 having both the first row of axial teeth 922 and the third row of radial teeth 909. This flange 90 can be mounted by pushing the latter into the body 20, so that the third radial teeth 909 are in axial abutments against the internal surface 20a (in particular against the internal wall 22a). Then, the first ring 94 can be mounted by engaging both the first tabs 942 of the first ring 94 in the corresponding first radial notches 924 and the second tabs 944 in the corresponding second radial notches 224, so as to axially lock the flange 90 vis-à-vis the body 20. To achieve this, the first ring 94 can be split to compress it before being mounted in the first 924 and second 224 radial notches. The first ring 94 can then assume its initial shape by expanding to fit into the groove 221.The first ring 94 can be fixed without play (or very little play) in the groove 221, so that the flange 90 radially presses the parts 23 (in particular the peripheral rim 230) against the internal surface 20a.

Claims

Demands

1. Inlet cone (2) for an aircraft turbomachine (1), said inlet cone (2) being configured to be driven in rotation about an axis (X) and comprising: - a conical or frustoconical body (20) having through-holes (202) distributed around the axis (X), and - parts (23) of elastically deformable material located in said through-holes (202), each of the parts (23) of elastically deformable material having at least one peripheral rim (230) for retaining said part (23) in the corresponding through-hole (202), said at least one peripheral rim (230) bearing on an internal surface (20a) of said body (20), characterized in that the cone (2) further comprises an annular flange (90) attached and fixed inside the body (20),said flange (90) extending radially inside the parts (23) made of elastically deformable material to close said through housings (202) in case of loss of said parts (23) during operation.

2. Inlet cone according to claim 1, characterized in that the flange (90) comprises a frustoconical portion (900) radially supported against the elastically deformable material parts (23), and an annular portion (902) fixed on the internal surface (20a) of the body.

3. Inlet cone according to claim 2, characterized in that the flange (90) further comprises an annular shoulder (904) between the frustoconical (900) and annular (902) portions, this shoulder (904) being axially abutted against a part of the internal surface (20a) of the body (20).

4. Inlet cone according to claim 2 or 3, characterized in that the annular portion (902) comprises a first annular row of axial teeth (922) separated from each other by radial notches (924).

5. Inlet cone according to claim 4, characterized in that the internal surface (20a) of the body comprises a second annular row of axial teeth (222) separated from each other by radial notches (224), the second row of axial teeth (222) extending around the first row of axial teeth (922).

6. Inlet cone according to claim 5, characterized in that it further comprises a locking device (92) for the flange (90) vis-à-vis the body (20), this locking device (92) comprising a first ring (94) called anti-rotation having tabs (942) oriented radially inwards and engaged between first axial teeth (922) of the first row of axial teeth (922), and tabs oriented radially outwards and engaged between second teeth (222) of the second row of axial teeth (222).

7. Entry cone according to claim 6, characterized in that the locking device (92) further comprises a second ring (96) called a stop ring engaged in an internal annular groove (220) of the second row of axial teeth (222) and capable of axially retaining the first ring (94).

8. Inlet cone according to any one of claims 1 to 7, characterized in that the flange (90) is screwed into the body (20) and includes an external thread (908) configured to cooperate with an internal thread (207) of the internal surface (20a) of the body.

9. Inlet cone according to claim 5 or 6, characterized in that the annular portion (902) further comprises a third annular row of radial teeth (909) separated from each other by axial notches (909), the third row of radial teeth (909) being axially abutted against a piece of the internal surface (20a) of the body (20).

10. Inlet cone according to any one of claims 6 to 9, characterized in that the first ring (94) and / or the second ring (96) is / are split.

11. Aircraft turbomachine (1) comprising an inlet cone (2) according to any one of the preceding claims.

Images