ASSEMBLY FOR A TURBINE ENGINE

Abstract

An assembly for a turbine engine extending along an axis, includes a stator, a low-pressure compressor shaft, a low-pressure compressor comprising a rotor comprising a drum rotatably coupled to the shaft of the low-pressure compressor, and a fan comprising a disk rotatably coupled to the shaft of the low-pressure compressor. The drum has a radially internal part rotatably coupled to the shaft of the low-pressure compressor and a radially external part fixed to the radially internal part by means of detachable fixing means. A first axial retention means is configured to axially and detachably retain the disk of the fan relative to the shaft of the low-pressure compressor. A second axial retention means is configured to axially and detachably retain the radially internal part of the drum relative to the shaft of the low-pressure compressor.

Claims

1. An assembly for a turbine engine extending along an axis, including a stator, a low-pressure compressor shaft, a low-pressure compressor including a rotor comprising a drum coupled in rotation to the shaft of the low-pressure compressor, a fan including a disc coupled in rotation to the shaft of the low-pressure compressor, wherein the drum comprises a radially internal portion coupled in rotation to the shaft of the low-pressure compressor and a radially external portion fixed to the radially internal portion via removable fixing means, first axial retention means being configured to axially and removably retain the fan disc with respect to the shaft of the low-pressure compressor, second axial retention means configured to axially and removably remove the radially internal portion of the drum with respect to the shaft of the low-pressure compressor.

2. The assembly according to claim 1, wherein the means for coupling in rotation the disc of the fan with respect to the shaft of the low-pressure compressor include splines.

3. The assembly according to claim 1, wherein the means for coupling in rotation the internal portion of the drum with respect to the shaft of the low-pressure compressor include splines.

4. The assembly according to claim 1, wherein means for coupling in rotation the internal portion of the drum with respect to the shaft of the low-pressure compressor include teeth extending in a radial plane.

5. The assembly according to claim 1, wherein the first axial retention means include a first stop configured to prevent a displacement of the fan disc with respect to the shaft of the low-pressure compressor in a first direction and a first nut configured to form a second removable stop designed to prevent the displacement of the fan disc with respect to the shaft of the low-pressure compressor, in a second direction, opposite the first direction.

6. The assembly according to claim 1, wherein the second axial retention means include a second stop configured to prevent a displacement of the internal portion of the drum with respect to the shaft of the low-pressure compressor in a first direction and a second nut capable of forming a second removable stop capable of preventing the displacement of the internal portion of the drum with respect to the shaft of the low-pressure compressor, in a second direction, opposite the first direction.

7. The assembly according to claim 1, further comprising dynamic sealing means between the stator and the shaft of the low-pressure compressor, located downstream from the internal portion of the drum and of the fan disc.

8. The assembly according to claim 1, wherein the fan includes a blisc.

9. A turbomachine, comprising at least one assembly according to claim 1.

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

Description

BRIEF DESCRIPTION OF THE FIGURES

[0048] FIG. 1 is an axial cross-section half-view of a portion of an assembly according to a first embodiment of the invention,

[0049] FIG. 2 is an axial cross-section half-view of a portion of an assembly according to a second embodiment of the invention,

[0050] FIG. 3 is a partially exploded view of the assembly of FIG. 2,

[0051] FIG. 4 is an exploded view of the assembly of FIG. 2.

DETAILED DESCRIPTION OF THE INVENTION

[0052] FIG. 1 shows an assembly for a turbine engine according to a first embodiment of the invention. The latter includes a low-pressure compressor comprising a rotor comprising a drum 2 coupled in rotation to a shaft of the low-pressure compressor.

[0053] The drum 2 includes a radially internal portion 3 coupled in rotation to a shaft 4 of the low-pressure compressor and a radially external portion 5.

[0054] The radially external portion 5 includes a radially internal zone 6 of annular shape and extending radially, and a frustoconical zone 7 extending from the internal zone 6 by flaring in the downstream direction, i.e. to the right in the figures.

[0055] The internal portion 3 includes a radially external zone 8 of annular shape extending radially, a radially internal zone 9 of cylindrical shape and a median zone 10 connecting the internal and external zones, here of frustoconical shape.

[0056] The radial annular zones 6, 8 are fixed to one another via removable fixing means, for example via bolts 11 (diagrammatically shown in FIG. 1 by mixed lines) regularly distributed over the circumference.

[0057] The internal cylindrical zone 9 includes an edge 12 extending radially inwards from the upstream end of the cylindrical zone 9, said edge 12 forming an annular shoulder 13 capable of axially bearing on an additional annular shoulder 14 of the shaft of the low-pressure compressor 4.

[0058] Said axial bearing is retained via a nut 15 that is axially thrust on said edge 12, in particular on the upstream radial face 16 of said edge 12 and screwed on a threaded zone 17 of the upstream end of the shaft 4.

[0059] The radially internal surface of the cylindrical zone 9 further includes axial splines 17 extending downstream from the shoulder, engaging with additional splines 18 arranged at the radially external surface of the shaft 4.

[0060] The radially internal surface of the edge 12 and the radially internal surface of the downstream end of the cylindrical zone form cylindrical seats 19, 20 engaging with additional cylindrical seats of the shaft 4, said seats 19, 20 being capable of providing a centring of the internal portion 3 of the drum 2 on said shaft 4.

[0061] The assembly 1 further includes a fan 21 comprising blades 22 integral with a disc 23 (blisc), the disc 23 being coupled in rotation to the low-pressure compressor shaft 4.

[0062] The disc 23 includes a frustoconical portion 24 narrowing in the downstream direction and extended downstream by a cylindrical portion 25.

[0063] The upstream end of the cylindrical portion 25 includes an annular reinforcement opening radially inwards and delimiting an annular shoulder 26. A groove 27 is formed in the radially internal surface of the cylindrical portion 25, upstream from said shoulder 26.

[0064] A radially external shoulder 28 is moreover formed between the frustoconical zone 24 and the cylindrical zone 25 of the disc 23. The nut 15 is axially inserted between said external shoulder 28 and the upstream radial face 16 of the edge 12.

[0065] The shoulder 28 axially bears on the nut 15. Alternatively, the downstream end of the cylindrical portion 25 of the disc 23 axially bears on a radially internal annular shoulder 29 of the shaft 4.

[0066] Such a bearing is retained via a nut 30 including an upstream radial edge 31 bearing on the shoulder 26 and a cylindrical portion 32 the downstream end 33 of which is threaded and engaged with a tapping of the radially internal surface of the shaft 4, located downstream from the shoulder 26.

[0067] The nut 30 is retained in position via a ring 34 coupled in rotation to said nut 30, for example via a finger and notch system, said ring 34 also being coupled in rotation with the fan disc 23, for example via a finger and notch system.

[0068] The ring 34 is axially retained in position via an elastic ring 35 or circlips, engaged in the groove 27.

[0069] The nut 30 and the cylindrical portion of the disc 25 include moreover additional cylindrical seats 36 facilitating the centring of the nut 30, and located downstream from the upstream edge 31.

[0070] The cylindrical portion 25 of the disc 23 includes in addition axial splines 37, formed at the radially external surface of said cylindrical portion 25, cooperating with additional splines 38 arranged at the radially internal surface of the shaft 4.

[0071] The splines 17, 18 and 37, 38 are located on the same radial plane, at least in part. FIGS. 2 to 4 show an assembly according to a second embodiment of the invention, which differs from the one disclosed in reference to FIG. 1 in that the internal portion 3 of the drum 2 is coupled in rotation to the shaft 4 via teeth 39, 40 formed respectively at the radial annular surface of the downstream end of the internal portion 3 of the drum 2 and at the radial annular surface of the upstream end of the shaft 4.

[0072] The teeth 39, 40 can extend axially, either in a straight manner, or in a curved manner. In this embodiment, the nut 15 includes a cylindrical portion 15a the downstream end of which is threaded 15b and is screwed on a tapping of the shaft 4. The nut 15 includes moreover an edge 15c extending radially from the upstream end of the cylindrical portion 15a, said edge 15c bearing on the radial face 16 or on a radial shoulder of the internal portion 3 of the drum 2.

[0073] Such an assembly 1 makes it possible to be capable of easily disassembling the fan disc 23 and the internal portion 3 of the drum 2 with respect to the shaft 4 of the low-pressure compressor, to authorise access from the upstream of the turbine engine, to possible elements located downstream from the drum and of the fan disc, during a possible maintenance operation, without requiring disassembly of the external portion 5 of the drum 2. Such elements are for example dynamic sealing means 41 between a stator of the assembly and the shaft 4 of the low-pressure compressor, located downstream from the internal portion 3 of the drum 2 and of the fan disc 23. Such sealing means 41 are diagrammatically shown in FIGS. 3 and 4. Such sealing means 41 can be capable of delimiting the upstream of an oil enclosure of the turbine engine.

[0074] In order to allow such an access, it is sufficient to remove the nuts 15, 30 and the bolts 11 in such a way as to authorise the disassembly of the fan disc 23 and of the internal portion 3 of the drum 2 with respect to the shaft 4, by translation according to the axis X.

[0075] The structure according to the invention then makes it possible to easily access the sealing means 41 from the upstream of the turbine engine, by removing the internal portion 3 of the drum 2 and of the fan disc 23.

[0076] During such a disassembly, the external portion 5 of the drum 2 can be retained using an adapted tool.

[0077] Such a structure can also allow for the disassembly of the fan disc 23 alone while still providing the retaining in position of the drum 2, via the nut 15.