Components of a turbine engine

Abstract

The present invention relates to a component (1) of a turbomachine extending along an axis, the component comprising a stator; a low-pressure compressor shaft (4); a low-pressure compressor comprising a rotor, the rotor comprising a drum (2) rotatably coupled to the shaft (4) of the low-pressure compressor; a fan (21) comprising a disk (23) rotatably coupled to the shaft (4) of the low-pressure compressor, characterized in that the drum (2) comprises a radially inner part (3) rotatably coupled to the shaft (4) of the low-pressure compressor and a radially outer part (5) fixed to the radially inner part (3) by means of a removable fixing member (11), a first axial retaining member (30) being capable of axially and removably retaining the disk (23) of the fan (21) relative to the shaft (4) of the low-pressure compressor, and a second axial retaining member (15) being capable of axially and removably retaining the radially inner part (3) of the drum (3) relative to the shaft (4) of the low-pressure compressor.

Description

Field of the Invention

[0001] The present invention relates to a component of a turbo engine (for example, in particular, an aircraft turboprop engine or a turbofan engine). Background Art

[0002] A turbo engine conventionally includes, from upstream to downstream with respect to the direction of gas circulation within the turbo engine, a fan, a low-pressure compressor, a high-pressure compressor, a combustion chamber, a high-pressure turbine, a low-pressure turbine, and an exhaust duct.

[0003] The rotor of the high-pressure turbine and the rotor of the high-pressure compressor are rotationally coupled via a first shaft so as to form a high-pressure body.

[0004] The rotor of the low-pressure turbine and the rotor of the low-pressure compressor are rotationally coupled via a second shaft so as to form a low-pressure body, and the fan can be directly or via, for example, an epicyclic gear assembly connected to the rotor of the low-pressure compressor.

[0005] Document FR 3 066 552 discloses, in the name of the applicant, a component of a turbo engine extending along an axis, the component including a stator; the shaft of the low-pressure compressor; a low-pressure compressor including a rotor having a drum rotationally coupled to the shaft of the low-pressure compressor; and a fan including a disk rotationally coupled to the shaft of the low-pressure compressor.

[0006] The structure presented in this document is relatively compact, but specifically requires disassembling the components of the rotor of the low-pressure compressor to access possible elements located downstream of the drum and positioned around the shaft of the low-pressure compressor. In addition, this structure cannot effectively hold the drum in the case of disassembling the fan disk.

[0007] The present invention aims to simply, reliably, and at low cost overcome these drawbacks. Summary of the Invention

[0008] To this end, the present invention relates to a component of a turbo engine extending along an axis, the component including a stator; a low-pressure compressor shaft; a low-pressure compressor including a rotor having a drum rotationally coupled to the shaft of the low-pressure compressor; a fan including a disk rotationally coupled to the shaft of the low-pressure compressor, characterized in that the drum includes a radially inner portion rotationally coupled to the shaft of the low-pressure compressor and a radially outer portion fixed to the radially inner portion via a removable fixing member, a first axial retaining member being able to axially and removably retain the fan disk with respect to the shaft of the low-pressure compressor, and a second axial retaining member being able to axially and removably retain the radially inner portion of the drum with respect to the shaft of the low-pressure compressor.

[0009] The terms axial, radial, and circumferential are defined with respect to the axis of the turbo engine, the axis of the turbo engine being in particular conflated with the axis of the shaft of the low-pressure compressor.

[0010] This component makes it possible to easily disassemble the fan disk and the inner part of the drum of the low-pressure compressor, in order to allow access from the upstream of the turbomachine to any element located downstream of the drum and of the fan disk during possible maintenance operations, without having to disassemble the outer part of the drum.

[0011] In this regard, it is sufficient to remove the first and second removable axial retaining members in order to allow the disassembly of the fan disk and of the inner part of the drum of the low-pressure compressor.

[0012] During this disassembly, suitable tools can be used to hold the outer part of the drum.

[0013] This structure also allows the fan disk to be disassembled only, while still achieving the retention of the drum in place via the second axial retaining member.

[0014] The drum of the low-pressure compressor can be located downstream of the fan disk.

[0015] The terms upstream and downstream are defined with respect to the direction of circulation of the gas within the turbomachine.

[0016] The removable fixing member between the inner and outer parts of the drum can comprise at least one bolt, for example a number of bolts regularly distributed in the circumference.

[0017] The inner part of the drum can comprise a radial annular part which is fixed to the radial annular part of the outer part of the drum via the removable fixing member.

[0018] The member for rotationally coupling the disk of the fan with respect to the shaft of the low-pressure compressor can comprise a rack.

[0019] The fan disk can comprise a cylindrical zone which comprises a rack meshing with an additional rack of the cylindrical zone of the shaft of the low-pressure compressor.

[0020] The rack can extend axially. The rack can allow the assembly and the axial disassembly of the fan disk with respect to the shaft of the low-pressure compressor.

[0021] The member for rotationally coupling the inner part of the drum with respect to the shaft of the low-pressure compressor can comprise a rack.

[0022] The inner part of the drum can comprise a cylindrical zone which comprises a rack meshing with an additional rack of the cylindrical zone of the shaft of the low-pressure compressor.

[0023] The rack can extend axially. The rack can allow the assembly and the axial assembly of the inner part of the drum with respect to the shaft of the low-pressure compressor.

[0024] The cylindrical zones of the inner part of the drum and of the fan disk which have racks of the shaft of the low-pressure compressor can be at least partially located in the same radial plane.

[0025] This feature makes it possible, in particular, to prevent compressive pressurization of the rack during the setting of the axial retaining member.

[0026] The shaft of the low-pressure compressor may include a radially internal rack that meshes with an additional rack of the fan disk.

[0027] The shaft of the low-pressure compressor may include a radially external rack that meshes with an additional rack of the inner part of the drum.

[0028] The member for rotationally coupling the inner part of the drum relative to the shaft of the low-pressure compressor may include teeth extending in a radial plane. The inner part of the drum may include a radially extending annular region that includes teeth that mesh with additional teeth of a radial annular region of the shaft of the low-pressure compressor.

[0029] The teeth may be straight or curved.

[0030] The teeth may permit assembly and axial disassembly of the inner part of the drum relative to the shaft of the low-pressure compressor.

[0031] Teeth may be formed at the downstream end of the inner part of the drum and at the upstream end of the shaft of the low-pressure compressor.

[0032] Teeth may be formed in a region upstream of the rack, thereby allowing rotational coupling of the shaft of the low-pressure compressor and the fan disk.

[0033] The first axial retaining member may include a first stop that is capable of preventing the fan disk from shifting relative to the shaft of the low-pressure compressor in a first direction; and a first nut that is capable of forming a first removable stop that is designed to prevent the fan disk from shifting relative to the shaft of the low-pressure compressor in a second direction opposite to the first direction.

[0034] The first stop may be formed by a radial shoulder disposed in the shaft of the low-pressure compressor, against which the fan disk is axially supported. The downstream end of the fan disk may be axially supported on the shoulder.

[0035] The first nut may include a portion axially supported on the fan disk and a screwing portion on the shaft of the low-pressure compressor, and vice versa.

[0036] The first axial retaining member may include an anti-rotation member that prevents the nut from rotating in the direction in which it is unscrewed. The anti-rotation member may have the form of a ring that includes a portion that is rotationally coupled to the nut and a portion that is rotationally coupled to a fixed element relative to the nut (for example, rotationally coupled to a fan disk). The ring may be axially retained, for example, via an elastic ring that engages in a groove of the fixed element. The second axial retaining member may include a second stop that is capable of preventing the inner part of the roller from shifting in a first direction relative to the axis of the low-pressure compressor; and a second nut that is capable of forming a second removable stop that is capable of preventing the inner part of the roller from shifting in a second direction relative to the axis of the low-pressure compressor, which is opposite to the first direction.

[0037] The second stop may be formed by a radial shoulder arranged in the shaft of the low-pressure compressor, on which the inner part of the roller bears axially.The downstream end of the inner part of the roller may bear axially on said shoulder.

[0038] The second stop may be formed by the axial bearing of a radial zone comprising the coupling toothing between the inner part of the roller and the shaft of the low-pressure compressor.

[0039] The first nut may comprise a portion which is axially supported on the fan disk and a portion which is screwed on the shaft of the low-pressure compressor, or vice versa.

[0040] The assembly may include a dynamic sealing member located between the stator and the shaft of the low pressure compressor downstream of the inner portion of the drum and the fan disk.

[0041] This sealing member may be capable of delimiting upstream of an oil casing of a turbine engine.

[0042] The structure according to the invention makes it possible to easily access the sealing member from upstream of the turbine engine by removing the inner portion of the drum and the fan disk.

[0043] The fan may include an integral bladed disk structure (blisc). An integral bladed disk structure or integrally bladed rotor (IBR) is an assembly including a disk and blades extending from the disk and formed integrally with the disk.

[0044] In this case, in the event of damage to one of the blades, it is necessary to dismantle and change the assembly of the blisk structure. It is therefore particularly advantageous if dismantling of this assembly can be easily performed.

[0045] The invention also relates to a turbine engine comprising at least one assembly of the aforementioned type.

[0046] The turbine engine may be an aircraft turboprop engine or a turbofan engine.

[0047] The invention also relates to an aircraft comprising at least one turbomachine of the aforementioned type. BRIEF DESCRIPTION OF THE DRAWINGS

[0048] Figure 1 is a half axial cross-sectional view of a part of a component according to a first embodiment of the invention,

[0049] Figure 2 is a half axial cross-sectional view of a part of a component according to a second embodiment of the invention,

[0050] Figure 3 is Figure 2 a partially exploded view of a component of

[0051] Figure 4 is Figure 2 an exploded view of a component of DETAILED DESCRIPTION

[0052] Figure 1 A component of a turbomachine according to a first embodiment of the invention is shown. The turbomachine comprises a low-pressure compressor, which includes a rotor that includes a drum 2 rotatably coupled to the shaft of the low-pressure compressor.

[0053] The drum 2 comprises a radially inner part 3 and a radially outer part 5 rotatably coupled to the shaft 4 of the low-pressure compressor.

[0054] The radially outer part 5 comprises a radially inner zone 6 of annular shape and radially extending, and a frustoconical zone 7 extending from the inner zone 6 by flaring in the downstream direction (i.e., to the right in the figure).

[0055] The inner part 3 comprises a radially outer zone 8 of annular shape and radially extending, a radially inner zone 9 of cylindrical shape, and an intermediate zone 10 here of frustoconical shape connecting the inner and outer zones.

[0056] The radially annular zones 6, 8 are fixed to each other via removable fixing members, for example via bolts 11 regularly distributed on the circumference ( Figure 1 shown diagrammatically by dashed lines in

[0057] The inner cylindrical zone 9 comprises an edge 12 extending radially inwards from the upstream end of the cylindrical zone 9, the edge 12 forming an annular shoulder 13 that can be axially supported on an additional annular shoulder 14 of the shaft of the low-pressure compressor 4.

[0058] Said axial support is maintained via a nut 15 that axially advances on said edge 12, for example on the upstream radial face 16 of said edge 12, and is screwed onto a threaded zone 17 at the upstream end of the shaft 4.

[0059] ​​​​The radially inner surface of the cylindrical section 9 further includes an axial rack 17 that extends downstream from the shoulder and meshes with an additional rack 18 disposed at the radially outer surface of the shaft 4.

[0060] The radially inner surface of the edge 12 and the radially inner surface of the downstream end of the cylindrical section form cylindrical supports 19, 20 that mesh with additional cylindrical supports of the shaft 4, and the supports 19, 20 enable the inner part 3 of the drum 2 to be centered on the shaft 4.

[0061] The assembly 1 further includes a fan 21, and the fan 21 includes blades 22 (integral bladed disk structure) that are integral with a disk 23, and the disk 23 is rotationally coupled to the low-pressure compressor shaft 4.

[0062] The disk 23 includes a frustoconical portion 24 that narrows in the downstream direction and extends downstream through a cylindrical portion 25.

[0063] The upstream end of the cylindrical portion 25 includes an annular reinforcement that opens radially inward and delimits an annular shoulder 26. A groove 27 is formed in the radially inner surface of the cylindrical portion 25, upstream of the shoulder 26.

[0064] In addition, a radially outer shoulder 28 is formed between the frustoconical section 24 and the cylindrical section 25 of the disk 23. A nut 15 is axially inserted between the outer shoulder 28 and the upstream radial face 16 of the edge 12.

[0065] The shoulder 28 is axially supported on the nut 15. Alternatively, the downstream end of the cylindrical portion 25 of the disk 23 is axially supported on a radially inner annular shoulder 29 of the shaft 4.

[0066] This support is maintained by a nut 30 that includes an upstream radial edge 31 supported on the shoulder 26 and a cylindrical portion 32, and the downstream end 33 of the cylindrical portion is threaded and meshes with the threading of the radially inner surface of the shaft 4 located downstream of the shoulder 26.

[0067] The nut 30 is held in place by a ring 34 that is rotationally coupled to the nut 30 (e.g., through a finger and notch system), and the ring 34 is also rotationally coupled to the fan disk 23 (e.g., through a finger and notch system).

[0068] The ring 34 is axially held in place by an elastic ring 35 or snap ring that engages in the groove 27.

[0069] In addition, the nut 30 and the cylindrical portion of the disk 25 include an additional cylindrical support 36 that facilitates centering of the nut 30 and is located downstream of the upstream edge 31.

[0070] The cylindrical portion 25 of the disk 23 includes an additional axial rack 37 formed at the radially outer surface of the cylindrical portion 25 and cooperating with an additional rack 38 disposed at the radially inner surface of the shaft 4.

[0071] The racks 17, 18 and 37, 38 are at least partially located in the same radial plane. Figures 2 to 4 Showing a component according to a second embodiment of the present invention, which is different from the reference Figure 1 The disclosed component in that the inner portion 3 of the drum 2 is rotationally connected to the shaft 4 via teeth 39, 40 formed at the radially annular surfaces at the downstream end of the inner portion 3 of the drum 2 and at the upstream end of the shaft 4, respectively.

[0072] The teeth 39, 40 may extend axially in a straight or curved manner. In this embodiment, the nut 15 includes a cylindrical portion 15a having a thread 15b at its downstream end and screwed onto the tapped portion of the shaft 4. In addition, the nut 15 includes an edge 15c radially extending from the upstream end of the cylindrical portion 15a, and the edge 15c is supported on the radial surface 16 or the radial shoulder of the inner portion 3 of the drum 2.

[0073] This component 1 makes it possible to easily disassemble the fan disk 23 and the inner portion 3 of the drum 2 relative to the shaft 4 of the low-pressure compressor to allow access to any element located downstream of the drum and the fan disk from the upstream of the turbomachine during possible maintenance operations without disassembling the outer portion 5 of the drum 2. These elements are, for example, the dynamic sealing member 41 between the stator of the component and the shaft 4 of the low-pressure compressor, which is located downstream of the inner portion 3 of the drum 2 and the fan disk 23. This sealing member 41 is Figure 3 and 4 shown diagrammatically in. This sealing member 41 may delimit the upstream of the oil casing of the turbomachine.

[0074] In order to be able to achieve access, it is sufficient to remove the nuts 15, 30 and the bolts 11 to allow the fan disk 23 and the inner portion 3 of the drum 2 to be disassembled relative to the shaft 4 by translation along the axis X.

[0075] Thus, the structure according to the present invention makes it possible to easily access the sealing member 41 from the upstream of the turbomachine by removing the inner portion 3 of the drum 2 and the fan disk 23.

[0076] During disassembly, a suitable tool can be used to hold the outer portion 5 of the drum 2.

[0077] This structure also allows only the fan disk 23 to be disassembled while still maintaining the drum 2 in place via the nut 15.

Claims

1. A component (1) of a turbomachine extending along an axis, said component comprising a stator; a shaft (4) of a low-pressure compressor; a low-pressure compressor comprising a rotor including a drum (2) rotatably connected to said shaft (4) of the low-pressure compressor; a fan (21) comprising a disk (23) rotatably connected to said shaft (4) of the low-pressure compressor, characterized in that, The drum (2) includes a radial inner portion (3) rotatably coupled to the shaft (4) of the low-pressure compressor and a radial outer portion (5) fixed to the radial inner portion (3) via a removable fixing member (11). A first axial retaining member (30) is capable of axially and removably retaining the disk (23) of the fan (21) relative to the shaft (4) of the low-pressure compressor, and a second axial retaining member (15) is capable of axially and removably retaining the radial inner portion (3) of the drum (2) relative to the shaft (4) of the low-pressure compressor. Wherein, the first axial retaining member (30) includes a first stop (31, 26) capable of preventing the disk (23) of the fan (21) from shifting in a first direction relative to the shaft (4) of the low-pressure compressor, and a first nut capable of forming a first removable stop, the first removable stop being designed to prevent the disk (23) of the fan (21) from shifting in a second direction opposite to the first direction relative to the shaft (4) of the low-pressure compressor.

2. The component (1) according to claim 1, characterized in that, The member for rotatably coupling the disk (23) of the fan (21) relative to the shaft (4) of the low-pressure compressor includes racks (37, 38).

3. The component (1) according to claim 1 or 2, characterized in that, The member for rotatably coupling the inner portion (3) of the drum (2) relative to the shaft (4) of the low-pressure compressor includes racks (17, 18).

4. The component (1) according to claim 1 or 2, characterized in that, The member for rotatably coupling the inner portion (3) of the drum (2) relative to the shaft (4) of the low-pressure compressor includes teeth (39, 40) extending in a radial plane.

5. The component (1) according to claim 1 or 2, characterized in that, The second axial retaining member (15) includes a second stop (13, 14) capable of preventing the inner portion (3) of the drum (2) from shifting in a first direction relative to the shaft (4) of the low-pressure compressor, and a second nut capable of forming a second removable stop, the second removable stop being capable of preventing the inner portion (3) of the drum (2) from shifting in a second direction opposite to the first direction relative to the shaft (4) of the low-pressure compressor.

6. The component (1) according to claim 1 or 2, characterized in that It includes a dynamic seal member (41) between the stator and the shaft (4) of the low-pressure compressor, and the dynamic seal member is located downstream of the inner portion (3) of the drum (2) and the disk (23) of the fan (21).

7. The component (1) according to claim 1 or 2, characterized in that, The fan (21) includes an integrally bladed disk structure.

8. A turbine, comprising at least one assembly (1) according to any one of claims 1 to 7.

9. An aircraft, comprising at least one turbine according to claim 8.

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