Inlet cone for aircraft turbine engine and aircraft turbine engine

Abstract

An inlet cone (20) for an aircraft turbine engine (1) is configured to be driven in rotation about an axis (X). The inlet cone comprises a body (22) in the shape of a frustoconical shape and a tip (21) made of an elastically deformable material fixed to an end (221) of the body having a smaller diameter. The body comprises a through housing (222) distributed about the axis and a component (23) made of an elastically deformable material located in the through housing. Each of the parts (23) made of an elastically deformable material comprises at least one peripheral edge (230) for retaining the part in a corresponding through housing (222). The outer peripheral edge is supported on an inner surface (22a) of the main body.

Description

TECHNICAL FIELD

[0001] The field of the invention is that of turboengines, for example of turboengines for aircraft. More particularly, the invention relates to an air inlet cone for such an aircraft turboengine. BACKGROUND

[0002] The prior art includes documents US-A1-2020 / 010172, WO-A1-2020 / 249888, FR-A1-3097200 and WO-A1-2022200733.

[0003] Turboengines extending along a longitudinal axis and comprising, in the flow orientation of the gas, from upstream to downstream, 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 an exhaust nozzle, are known in the prior art.

[0004] Generally, such a turboengine also comprises, upstream, an air inlet cone which is mounted on the fan, for example by means of a generally annular housing which is itself connected to the low-pressure compressor shaft of the turboengine. The connection between the inlet cone and the housing is generally made using a bolted joint. The downstream end of the housing is flush with the platforms of the fan blades, maintaining aerodynamic continuity with the platforms of the fan blades.

[0005] Such an inlet cone comprises an upstream end in the form of a cone tip centred on a rotation axis of the inlet cone which also corresponds to the longitudinal axis of the fan and of the turboengine assembly.

[0006] It is known that this tip is a point on the turboengine which is conducive to icing, since the tip, centred on the rotation axis, makes it impossible to exert a significant centrifugal force. Thus, if no special measures are taken, the ice formed on the tip can grow to a large size before it falls off, with the risk of damaging the fan blades struck by the ice or of the aircraft engine ingesting the ice when the ice finally detaches from the tip. The ice accretion can also accumulate unevenly on the tip, causing unwanted vibrations in the turboengine.

[0007] To overcome this problem, it has been proposed to install a de-icing system, the aim of which is to ensure that the ice accumulated on the tip is evacuated before reaching a critical size. However, this type of system is expensive in terms of mass and overall size, and is particularly tricky to install due to the rotating nature of the equipped inlet cone.

[0008] Removing the tip of the inlet cone has also been proposed to address issues such as icing during operation. However, without a tip, the airflow entering the turbine engine during operation cannot be properly deflected and guided, and in particular, the cooling and improvement of the airflow cannot be ensured. Furthermore, a truncated inlet cone (i.e., without a tip) cannot fully protect the inlet cone during operation from ice formation and the ingestion of ice (or other solid particles) by the turbine engine.

[0009] Finally, as Figure 1 As shown, the production of an inlet cone 10 is known in the prior art, which has an upstream tip 11 made of a flexible material (or in other words, an elastically deformable material) and a downstream body 12 made of a rigid material. The tip 11 is typically glued to the downstream body 12. During operation, the accumulated ice layer, particularly at the junction where the tip and body intersect, is weakened to facilitate ice separation. However, in the case of turbine engine flight operation, this method of separating the ice layer by weakening it and allowing cracks to propagate along it may proceed more slowly than intended. In fact, the larger the ice layer, the slower and more difficult it is to form cracks within it. On the other hand, since the adhesive force between the ice and the cone is greater than the force required to separate the ice by centrifugal force, it may be insufficient, especially at low temperatures (i.e., between -30°C and 15°C), to directly create cracks between the portion of the cone made of flexible material and the accumulated ice. Therefore, this solution is insufficient to rapidly separate the ice layer formed on the inlet cone into multiple small fragments without damaging the turbine engine components located downstream of the cone.

[0010] Furthermore, it is required that the flexible tip generally does not alter the aerodynamic performance or mechanical strength of the inlet cone (and the turbine engine). Specifically, offsets and / or spaces can be created at the bonding interface between the flexible material portion and the rigid material body. During operation, this can lead to deformation between the flexible material portion and the rigid material body (particularly without aerodynamic continuity), where ice may become brittle or enter the space. This can cause irreversible damage to the inlet cone. Therefore, this solution involving the assembly of the flexible portion and the body made of rigid material is not entirely satisfactory for limiting ice buildup on the inlet cone as much as possible.

[0011] In this context, it is of interest to propose a solution that enables the overcoming of the shortcomings of the prior art, particularly by introducing a new geometry for the air inlet cone, which is more conducive to the controlled breaking of ice during operation. Summary of the Invention

[0012] According to the invention, each of the components made of elastically deformable material comprises at least one peripheral edge for retaining said component in the corresponding housing, said at least one peripheral edge being borne against an internal surface of the body. The body comprises through housings distributed around the axis X and components made of elastically deformable material, which are located in said housings.

[0013] According to the invention, each of the components made of elastically deformable material comprises at least one peripheral edge for retaining said component in the corresponding housing, said at least one peripheral edge being borne against an internal surface of the body.

[0014] This design of the invention makes it possible to reduce the size of the ice accumulations on the inlet cone of the turbine engine during operation, thereby enhancing the phenomenon of removal of ice accumulations.

[0015] To achieve this, the components made of elastically deformable material each comprise a peripheral edge that bears against an internal surface of the body of the cone. This peripheral edge makes it possible for the components made of elastically deformable material to be held firmly and effectively in the body of the cone, in particular in the corresponding through housings in the body. In particular, the components made of elastically deformable material are held centrifugally by the peripheral edge pressing against the internal surface of the body of the cone.

[0016] Furthermore, when the cone is rotating, the components made of elastically deformable material, such as elastomers, can deform and move radially (with respect to the axis X) and these components made of elastically deformable material do not detach from the cone (thanks to the peripheral edge) and continue to function also at external temperature variations, such as, for example, low temperatures of -30°C to 15°C. This contributes to weakening the ice layer that accumulates on the external surface of the cone. This embrittlement increases the frequency of ice breakage, thereby reducing the size of the fragments of ice. The fragmentation and separation of the ice are therefore better controlled, so that the size of the fragments of ice that are separated is calibrated and acceptable for possible projection onto components downstream of the cone, such as fan blades of a turbine engine, without damaging the components.

[0017] Thus, in particular for aircraft turbine engines, the advantage of the invention is to provide very high reliability based on a simple design, with very low losses in terms of cost, space requirement and environmental impact.

[0018] The inlet cone for an aircraft turbine engine according to the invention can comprise one or more of the following features, taken independently of one another or in combination with one another: - each of the parts made of elastically deformable material comprises a single outer peripheral edge extending around the entire periphery of the part in question; - each of the parts made of elastically deformable material comprises a gasket occupying the entire volume of the through housing and comprising an outer surface aligned with the outer surface of the main body; - the gasket is substantially elliptical, trapezoidal and / or rectangular in shape; - the gasket extends over a length comprised between 50% and 90% of the total length of the corresponding part made of elastically deformable material, this length being measured substantially in a direction parallel to the outer surface of the gasket of the part in question; - the thickness of the at least one outer peripheral edge is equal to the difference between the thickness of the gasket and the thickness of the main body, each of these thicknesses being measured in a direction perpendicular to the outer surface of the part in question; - each part that is elastically deformable has a maximum thickness comprised between 2 mm and 3 mm, this thickness being measured in a direction perpendicular to the inner surface of the main body; - the main body also comprises a central orifice for the passage of the cylindrical portion of the tip; - the number of through housings and of said parts made of elastically deformable material is between three and ten, preferably, the number of through housings and of said parts made of elastically deformable material is six; - the through housings and the parts made of elastically deformable material are respectively distributed in one or more annular rows of through housings and of parts made of elastically deformable material; - the tip is a single piece; - the main body is made of metal or composite material; - the at least one outer peripheral edge rests directly against the inner surface of the main body; - the at least one outer peripheral edge rests directly against the inner surface of the main body without any adhesive, in particular without any adhesive between the outer peripheral edge and the inner surface of the main body.

[0019] The application also relates to an aircraft turbine engine comprising an inlet cone according to one of the features of the application. BRIEF DESCRIPTION OF DRAWINGS

[0020] The application will be better understood and other details, characteristics and advantages of the application will become more clearly apparent in the course of the following description, given, by way of non-limiting example, with reference to the appended drawings, in which: Figure 1 is a schematic perspective view showing an inlet cone for an aircraft turbine engine according to the prior art, Figure 2It is a schematic half-view of the axial section of an aircraft turbine engine; Figure 3 This is a schematic illustration of the application according to the invention. Figure 2 A front perspective view of an example of the inlet cone of a turbine engine. Figure 4 yes Figure 3 The axial cross-sectional view of the inlet cone shown is shown. Figure 5 It is shown schematically. Figure 3 or Figure 4 Rear perspective view of the tip of the inlet cone. Figure 6 It is shown schematically. Figure 3 or Figure 4 The main perspective view of the entrance cone component made of elastically deformable material and its tip. Figure 7 It is shown schematically. Figure 3 or Figure 4 A front perspective view of a modified component of the entrance cone made of an elastically deformable material.

[0021] Elements that have the same function in different embodiments have the same reference numerals in the drawings. Detailed Implementation

[0022] In accordance with the conventions of this application, the terms "inner" and "outer," as well as "internal" and "external," are defined radially relative to the longitudinal axis X of the engine, particularly a turbine engine. For example, a cylinder extending along the axis X includes an inner surface facing the axis X and an outer surface opposite to it. "Axial" or "axially" refers to any direction parallel to the axis X, and "lateral" or "transverse" refers to any direction perpendicular to the axis X. Similarly, the terms "upstream" and "downstream" are defined relative to the airflow orientation within the turbine engine.

[0023] Figure 1 As described in the background section of this application, and an example of an inlet cone 10 for an aircraft turbine engine 1 according to the prior art is shown, the inlet cone 10 having an upstream tip 11 made of an elastically deformable material and a downstream body 12 made of a rigid material.

[0024] The invention is applied in a general and non-limiting manner, for example in... Figure 2 The aircraft turbine engine 1 is shown in the figure. Turbine engine 1 can be a turbojet engine, a turboprop engine, or a turboshaft engine.

[0025] Figure 2A twin-flow turbo engine 1 is shown. However, this is not limiting, the turbo engine can be another type of turbo engine, such as a turboprop engine.

[0026] The turbo engine 1 can extend along a longitudinal axis X and comprise, in the direction of the gas flow, from upstream to downstream, a fan 2, one or more compressor stages, for example a low-pressure compressor 3 and a high-pressure compressor 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. The fan 2, the low-pressure compressor 3 and the low-pressure turbine 7 are connected to a low-pressure shaft extending along the axis X. The high-pressure compressor 4 and the high-pressure turbine 6 are connected to a high-pressure shaft arranged 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.

[0027] The turbo engine 1 comprises air inlet cones 10, 20, in particular upstream of the fan 2. The cones can be mounted on the fan 2 by means of a casing (not shown), preferably by bolt-type fasteners. The casing is located downstream of the inlet cones and is also connected to the low-pressure shaft.

[0028] The inlet cones 10, 20 can be connected to the rotor, i.e. to the rotating part of the turbo engine 1. The inlet cones 10, 20 are configured to be driven in rotation around a longitudinal axis, which substantially coincides with the axis X of the turbo engine 1.

[0029] Figures 3 to 7 An example of an inlet cone 20 according to the application is shown.

[0030] With reference to Figure 3 and Figure 4 , the inlet cone 20 comprises a frustoconical body 22 and a tip 21 attached to an end 221 of the body 22 having a smaller diameter.

[0031] The tip 21 is made of an elastically deformable material. The elastically deformable material of the tip 21 can be an elastomer, a silicone, a rubber or a polytetrafluoroethylene (PTFE).

[0032] With reference to Figures 3 to 5 , the tip 21 is located upstream of the body 22. The tip 21 can comprise an apex through which the axis X passes. On the side opposite the apex, the tip 21 is fixed, for example substantially along a connection plane P perpendicular to the axis X, to an end 221 that can be arranged upstream, hereinafter referred to as upstream end 221. To this end, the tip 21 can comprise a cylindrical portion 210. This cylindrical portion 210 can be located on the opposite side of the apex of the tip 21.

[0033] The cylindrical portion 210 can be mounted in a central orifice 220 in the main body 22. To achieve this, the cylindrical portion 210 can have at least one threaded portion complementary to a thread in the central orifice 220. Alternatively, the cylindrical portion 210 can simply fit into the central orifice 220.

[0034] The tip 21 can be made in one piece (i.e. from a single material). In particular, the tip 21 is formed in one piece with the cylindrical portion 210, as Figure 5 illustrated.

[0035] The main body 22 can be made of a metallic material such as aluminium or titanium or a composite material.

[0036] The main body 22 can extend between an upstream end 221 and another end located downstream and opposite the upstream end 221 (hereinafter referred to as downstream end 223). This downstream end 223 can be configured to engage with a casing of the fan 2 of the turbine engine 1.

[0037] The upstream end 221 can have a substantially circular shape, preferably complementary to the tip 21, to ensure aerodynamic continuity.

[0038] The main body 22 can extend radially between an inner surface 22a and an outer surface 22b opposite the inner surface 22a. The outer surface 22b can be aerodynamically continuous (or otherwise aligned) with an outer surface of the tip 21.

[0039] The main body 22 can comprise a frustoconical wall 224 and a radial wall 226 (relative to the axis X) connected to the frustoconical wall 224 upstream of the main body 22, in particular at the upstream end 221. In Figure 3 and Figure 4 In the example illustrated, the frustoconical wall 224 and the radial wall 226 define a hollow portion 228 between the frustoconical wall 224 and the radial wall 226. This hollow portion 228 can at least partially house the cylindrical portion 210 of the tip 21.

[0040] The main body 22 can have a first thickness E 22 , for example measured in a direction perpendicular to the inner surface 22a (or outer surface 22b) of the main body 22. In particular, this first thickness E 22 may correspond to the thickness of the frustoconical wall 224 of the main body 22.

[0041] The body 22 comprises through housings 222 distributed around the axis X. The through housings 222 can be holes. The through housings 222 can be located on the frustoconical wall 224. The number of through housings 222 can be between three and ten. The through housings 222 can be arranged in one annular row or in multiple annular rows of through housings. Each through housing 222 can have a substantially elliptical shape, a trapezoidal shape and / or a rectangular shape.

[0042] In the example, but not exclusively, the through housings 222 are six. These through housings 222 are distributed in a single annular row of through housings around the axis X. Alternatively, these through housings 222 can be divided successively into two annular rows or more annular rows of through housings. Figure 3 Figure 4 In the example, but not exclusively, the through housings 222 are six. These through housings 222 are distributed in a single annular row of through housings around the axis X. Alternatively, these through housings 222 can be divided successively into two annular rows or more annular rows of through housings.

[0043] The body 22 can comprise a central orifice 220 for passage. This central orifice 220 is configured for the passage of the cylindrical portion 210 of the tip 21. The central orifice 220 can be located on the radial wall 226, in particular at the upstream end 221. This central orifice 220 can be substantially aligned at the axis X. The central orifice 220 can be threaded to facilitate the attachment of the cylindrical portion 210. The central orifice 220 can have a diameter of at least about 10 mm.

[0044] The body 22 comprises components 23 made of elastically deformable material. The components 23 and the tip 21 can be made of the same elastically deformable material. These components 23 are located in the through housings 222.

[0045] Each component 23 can have a maximum second thickness E 23 of between 2 mm and 3 mm. 23 This second thickness E 23 is measured in a direction perpendicular to the internal surface 22a of the body 22, or in other words on a plane inclined with respect to the axis X. The second thickness E 22 may be greater than the first thickness E 23 of the body 22.

[0046] Each component 23 can have a first overall length L 23 measured, for example, substantially along a direction parallel to the internal surface 22a of the body 22, or else along a plane inclined with respect to the axis X.

[0047] The components 23 can be between three and ten. The components 23 can be distributed in one annular row or in multiple annular rows of components.

[0048] In the example, but not exclusively, the through housings 222 are six. These through housings 222 are distributed in a single annular row of through housings around the axis X. Alternatively, these through housings 222 can be divided successively into two annular rows or more annular rows of through housings. Figure 3 Figure 4In the example shown, but not limited to these, there are six components 23. These components 23 are distributed in a single annular row of components around the axis X. Alternatively, these components 23 can be divided in two annular rows or more annular rows of components in succession.

[0049] One of the features of the application is that each of the components 23 made of elastically deformable material comprises at least one peripheral edge 230 for retaining the component 23 in the corresponding through housing 222. This peripheral edge 230 rests against the inner surface 22a of the main body 22.

[0050] Advantageously, the peripheral edge 230 can rest directly against the inner surface 22a, preferably without adhesive between the peripheral edge 230 and the inner surface 22a.

[0051] As Figure 4 , Figure 6 and Figure 7 indicate, each of the components 23 can comprise a single peripheral edge 230 extending around the entire periphery of the component 23.

[0052] The peripheral edge 230 can have a third thickness E 230 .

[0053] According to another feature of the application, each of the components 23 can comprise a gasket 236. In the example shown, each gasket 236 can project outwardly from the peripheral edge 230.

[0054] The gasket 236 can comprise an inner surface 236a and an outer surface 236b opposite the inner surface 236a. The inner surface 236a and the outer surface 236b of the gasket 236 can be substantially parallel to the inner surface 22a and the outer surface 22b of the main body 22, respectively. The outer surface 236a can be aligned with the outer surface 22b of the main body 22 to ensure aerodynamic continuity. The outer surface 236b of the gasket 236 can substantially and substantially correspond to the outer surface of the component 23 in question.

[0055] The gasket 236 can occupy the entire volume of the through housing 222. To achieve this, the gasket 236 can have a shape complementary to that of the corresponding through housing 222. For example, the gasket 236 is roughly elliptical, trapezoidal and / or rectangular in shape.

[0056] Figure 3 , Figure 4 and Figure 6 The gasket 236 is shown trapezoidal. Alternatively, the gasket 236 can be elliptical, as Figure 7 indicates.

[0057] The gasket 236 can have a fourth thickness E 236 .

[0058] The gasket 236 can have a second length L 236 measured in a direction parallel to the outer surface 236b (or to the inner surface 22a of the main body 22). This second length L 236 may be comprised between 50% and 90% of the total first length L 23 of the component 23 concerned. In the example shown in Figure 4 , the second length L 236 is about 75% of the first length L 23 .

[0059] The third thickness E 230 of the outer peripheral edge 230 can be equal to the difference between the fourth thickness E 236 of the gasket 236 (or the maximum second thickness E 23 of the component 23 concerned) and the first thickness E 22 of the main body 22. Each of these thicknesses E 22 , E 230 , E 236 may be measured in a direction perpendicular to the outer surface 236b of the component 23 concerned (or, in other words, along a direction perpendicular to the inner surface 22a of the main body 22). For example, the third thickness E 230 of the outer peripheral edge 230 can be comprised between 2 mm and 3 mm.

Claims

1. An inlet cone (20) for an aircraft turbine engine (1), the inlet cone (20) being configured to be driven to rotate about an axis (X), and comprising a frustoconical body (22) and a tip (21) made of an elastically deformable material, the tip being fixed to an end of the body (22) having a smaller diameter. The main body (22) includes a through-shell (222) distributed around the axis (X) and a component (23) made of an elastically deformable material, the component being located within the through-shell (222). Its features are, Each of the components (23) made of an elastically deformable material includes at least one outer peripheral edge (230) for holding the component (23) in a corresponding through housing (222), the at least one outer peripheral edge (230) being supported on the inner surface (22a) of the body (22).

2. The inlet cone according to claim 1, characterized in that, Each of the components (23) made of an elastically deformable material includes a single outer peripheral edge (230) extending around the entire periphery of the component (23) in question.

3. The inlet cone according to claim 1 or 2, characterized in that, Each of the components (23) made of a resiliently deformable material includes a liner (236) that occupies the entire volume of the through housing (222) and includes an outer surface (236b) aligned with the outer surface (22b) of the body (22).

4. The inlet cone according to claim 3, characterized in that, The shape of the pad (236) is generally elliptical, trapezoidal and / or rectangular.

5. The inlet cone according to claim 3 or 4, characterized in that, The gasket (236) is within the total length (L) of the corresponding component (23) made of an elastically deformable material. 23 The length (L) is between 50% and 90%. 236 Extending upwards, the length (L) 23 L 236 The measurement is basically taken in a direction parallel to the outer surface (236a) of the liner (236) of the component (23) under discussion.

6. The inlet cone according to any one of claims 3 to 5, characterized in that, The thickness (E) of the at least one outer peripheral edge (230) 230 ) equals the thickness (E) of the pad (236). 236 The thickness (E) of the main body (22) 22 The difference between these thicknesses (E) 22 E 230 E 236 Each thickness in the part (23) is measured in a direction perpendicular to the outer surface (236b) of the part (23) under discussion.

7. The inlet cone according to any one of the preceding claims, characterized in that, Each component (23) capable of elastic deformation has a maximum thickness (E) between 2 mm and 3 mm. 23 The thickness (E) 23 ) is measured in a direction perpendicular to the inner surface (22a) of the body (22).

8. The inlet cone according to any one of the preceding claims, characterized in that, The body (22) also includes a central aperture (220) for the cylindrical portion (210) of the tip (21) to pass through.

9. The inlet cone according to any one of the preceding claims, characterized in that, The number of the through-shell (222) and the component (23) made of elastically deformable material is three to ten, preferably six.

10. The inlet cone according to any one of the preceding claims, characterized in that, The through-shell (23) and the component (23) made of elastically deformable material are respectively distributed in a ring or multiple rings.

11. The inlet cone according to any one of the preceding claims, characterized in that, The tip (21) is a single piece.

12. The inlet cone according to any one of the preceding claims, characterized in that, The main body (22) is made of metal or composite material.

13. The inlet cone according to any one of the preceding claims, characterized in that, The at least one outer peripheral edge (230) directly abuts against the inner surface (22a) of the body (22).

14. An aircraft turbine engine (1), the aircraft turbine engine comprising an inlet cone (20) according to any one of the preceding claims.

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