Sleeve for mounting on a low pressure shaft in a turbomachine

Abstract

The invention relates to a rotating assembly (10) of a turbomachine (1), comprising: - a shaft (8) configured to drive a propeller (2) of the turbomachine (1) about an axis (X) and comprising a first flange (18) extending radially from the shaft (8), the first flange (18) being integral with the shaft (8); - a sleeve (19) fitted onto the shaft (8) and comprising a second flange (20) extending radially from the sleeve (19), the sleeve (19) being attached to the first flange (18) of the shaft (8) by the second flange (20); and - at least one component (11, 15, 17, 27, 28) connected to the shaft (8) by the sleeve (19) so as to be rigidly connected to the shaft (8) to move with the shaft, the component comprising at least one sealing element (15).

Description

Technical Field

[0001] This invention relates to the field of aviation propulsion systems, and particularly to propulsion systems with high bypass ratios. Background Technology

[0002] In a manner known per se, a turbine includes bearings configured to support a movable part relative to a stationary part (or stator) of the turbine or relative to another movable part. Specifically, these bearings may include an inner ring mounted on a movable element (e.g., a shaft) and an outer ring mounted on another component of the turbine. In particular, the inner ring may be mounted on a low-pressure shaft using a threaded nut. Thus, the shaft includes complementary threads so that the nut can be secured and tightened against the inner ring. Sealing elements (e.g., knife-shaped edges) may also be provided on the shaft. In particular, these sealing elements may be integral with the low-pressure shaft.

[0003] However, the installation and machining of these different components require specific machining processes, such as the manufacture of threads or sealing elements. These specific machining processes, in addition to increasing the technical difficulty of machining, also create unique damage areas on the shaft, resulting in weak points and / or stress concentration areas. Depending on the materials chosen for the shaft and the knife-edge type sealing elements, especially at the tip of the knife edge (an area unprotected due to friction), the risk of corrosion may also increase.

[0004] Maintenance is particularly complex when the worn or damaged area contacts the shaft.

[0005] These risks are more pronounced in supercritical and fast-moving low-pressure shafts (e.g., in turbines with ductless fans). Summary of the Invention

[0006] One object of the present invention is to overcome the above-mentioned disadvantages by proposing a low-pressure turbine shaft that is easy to manufacture, has an extended service life, and is easier to maintain.

[0007] Therefore, according to a first aspect of the invention, a rotating assembly according to claim 1 is provided. Embodiments of the rotating assembly are defined in the dependent claims.

[0008] According to the second aspect, a rotating assembly is proposed, the rotating assembly comprising:

[0009] - A shaft, configured to drive a turbine propeller about an axis, and including a first flange extending radially from the shaft, the first flange being integral with the shaft;

[0010] - A sleeve, which is fitted onto a shaft and includes a second flange extending radially from the sleeve, the sleeve being secured to a first flange of the shaft via the second flange; and

[0011] - At least one component, which is connected to the shaft via a sleeve to be movably fixed to the shaft, the component including at least one sealing element.

[0012] Some preferred, but non-limiting, features of the rotating assembly according to the second aspect are as follows, which are employed individually or in combination:

[0013] -The second flange is integral with the sleeve;

[0014] - The rotating assembly also includes a fixing member mounted on the sleeve, at least one component being tightly mounted on the sleeve via the fixing member;

[0015] - The sleeve also includes a shoulder extending at a distance from the second flange, and at least one component is tightly mounted between the fixing member and the shoulder;

[0016] - At least one component is removably mounted on the sleeve, and it also includes at least one of the following elements: a bearing ring; and a spoon-shaped portion connected to the lubrication system.

[0017] - The component includes two sealing elements that define the housing, an inner ring of a bearing housed in the housing, and a spoon-shaped portion that includes a lubricating fluid supply channel and an open orifice located on the housing. The lubricating fluid supply channel connects the orifice to the bearing to supply lubricating fluid to the bearing.

[0018] - The first flange is also connected to an additional component of the turbine, the additional component including at least one sealing element, the sealing element preferably including a sealing blade-shaped edge;

[0019] - The first flange is also connected to additional components of the turbine, including additional flanges extending radially from the stationary member; and / or

[0020] - The fixing member is radially outward relative to the sleeve.

[0021] According to a third aspect, the present invention proposes a turbine comprising a rotating assembly according to the first or second aspect. The turbine may further comprise a ductless propeller driven to rotate by a shaft. In one embodiment, the turbine has a bypass ratio greater than 30.

[0022] According to a fourth aspect, the present invention proposes an aircraft comprising at least one turbine according to a third aspect. Attached Figure Description

[0023] Other features, objects, and advantages of the invention will become apparent from the following description, which is entirely illustrative and non-limiting, and should be read in conjunction with the accompanying drawings, in which:

[0024] Figure 1 An example of a rotating assembly according to an embodiment of the present invention is shown schematically;

[0025] Figure 2 This is a partial schematic diagram of an example turbine that may include a rotating component according to the invention;

[0026] Figure 3 An aircraft is schematically shown, which includes two turbines according to one embodiment of the present invention.

[0027] In all the accompanying drawings, similar elements are labeled with the same reference numerals. Detailed Implementation

[0028] The turbofan engine 1 (especially the turbofan engine of the aircraft 100) typically includes, from upstream to downstream, a fan 2 (or propeller), an annular main flow space, and an annular secondary flow space in the gas flow direction, with the secondary flow space located externally relative to the main flow. Therefore, the mass of air drawn in by the fan 2 is divided into the main flow and the secondary flow; the main flow flows in the main flow path, and the secondary flow is concentric with the main flow and flows in the secondary flow path. The fan 2 (or propeller) can be ducted and housed within a fan 2 casing, or it can be a ductless variant of the unducted single fan (USF) type 2. The fan blades 2 can be fixed or have a variable configuration adjusted by a pitch-changing mechanism according to the flight phase.

[0029] The main flow path passes through the main body, which includes one or more compressor stages (e.g., low-pressure compressor 3 (or turbocharger) and high-pressure compressor 4), a combustion chamber, one or more turbine stages (e.g., high-pressure turbine 5 and low-pressure turbine 6), and exhaust nozzles. Typically, high-pressure turbine 5 drives high-pressure compressor 4 via a first shaft 7 (referred to as the high-pressure shaft), while low-pressure turbine 6 drives low-pressure compressor 3 and fan 2 via a second shaft 8 (referred to as the low-pressure shaft). The low-pressure shaft 8 is typically housed within a section of the high-pressure shaft 7.

[0030] Multiple components 11, 15, 29 of the turbine 1 can be removably mounted on the low-pressure shaft 8 to be driven to rotate about the axis of rotation of the low-pressure shaft 8. These components 11, 15, 29 specifically include one or more bearings 11, sealing elements 15, 16, 30 and / or one or more spoon-shaped portions 29.

[0031] As described above, the bearing 11 is configured to support a movable part relative to a fixed part (or stator) of the turbine 1 or relative to another movable part. The bearing 11 specifically includes an inner ring 12 movably fixed to the low-pressure shaft 8, and an outer ring 13 mounted on another part of the turbine 1, the inner ring 12 and outer ring 13, for example, accommodating rolling elements 14. The inner ring 12 and outer ring 13 are movable relative to each other.

[0032] The sealing element 15 is configured to achieve a seal between two parts, and the sealing element may include, for example, a labyrinth seal having at least two axially adjacent clearance constraint portions. The clearance constraint portions may, for example, include at least two knife-shaped edges and / or a twisted portion wound at least two turns. Therefore, the labyrinth seal may include a support portion and a clearance constraint portion, the support portion being movably fixed to the low-pressure shaft 8, and the clearance constraint portion being configured to mate with a complementary sealing element (e.g., a wear-resistant element) mounted on facing parts. It should be noted that the sealing element 15 may include any other type of seal, such as a segmented radial seal, a brush seal, a carbon seal, etc.

[0033] The spoon-shaped portion 29 may be part of the lubrication system of the rotating assembly 1 and is configured to supply lubricating fluid to the parts.

[0034] To facilitate the manufacture and maintenance of the low-pressure shaft 8 and to extend its service life, all or part of the components 11, 15, 16, and 29 driven to rotate by the low-pressure shaft 8 are connected to the shaft via sleeves 19 fitted onto the low-pressure shaft 8. For this purpose, the low-pressure shaft 8 includes a first flange 18 extending radially from the outer radial surface of the shaft. Furthermore, the sleeve 19 includes a second flange 20 extending radially from the sleeve 19 and configured to mate with the first flange 18, thereby allowing the sleeve 19 to be secured to the low-pressure shaft 8. Thus, the sleeve 19 is kinetically (rotationally and translationally) secured to the low-pressure shaft. Therefore, components 11, 15, 17, and 29 are mounted on or formed within the sleeve 19 and are driven by the low-pressure shaft 8 via the sleeve 19. Specifically, components 11, 15, and 29 are not directly mounted on the low-pressure shaft 8 and preferably do not directly contact the low-pressure shaft 8.

[0035] The first flange 18 is integral with the low-pressure shaft 8 to limit the machining requirements of the shaft. The second flange 20 may be integral with the sleeve 19, or added to and fixed to the sleeve 19. The sleeve 19 and the low-pressure shaft 8 form a rotating assembly 10. The first flange 18 and the second flange 20 extend radially outward relative to the rotation axis X of the low-pressure shaft 8.

[0036] Removably securing components 11, 15, and 29 to sleeve 19 instead of to the low-pressure shaft 8 allows for limited machining of the low-pressure shaft 8, thereby increasing its service life. Since replacing worn or damaged components 11, 15, and / or sleeve 19 is sufficient to replace them, replacing or repairing worn or damaged components 11, 15, and 29 is simpler and cheaper. Secured to sleeve 19 via a flange rather than any other connecting device, it also avoids easy damage to the threads during turbine 1 operation and allows for manufacturing with greater manufacturing and alignment tolerances.

[0037] The rotating assembly 10 also includes a lubrication seal 25, which includes a wall 25a fixedly mounted on the stator of the turbine (e.g., the turbine housing). The bearing 11 is housed within the lubrication seal 25. An inner ring 12 is added to and rotatably fixed to a sleeve 19, and an outer ring 13 is fixedly mounted relative to the wall 25a of the lubrication seal 25.

[0038] The casing 25 is defined on both sides by sealing elements 15, 16, including clearance restraints. Advantageously, the use of clearance restraints (e.g., knife-shaped edges or twisted portions) instead of cylindrical seals improves the sealing of the casing 25, achieving a seal over a greater axial length. Furthermore, potential damage to one clearance restraint is compensated for by the presence of other clearance restraints extending immediately downstream from the sealing elements 15, 16, making the sealing of the casing 25 more robust. However, in the case of the high-bypass turbine 1, the low-pressure shaft 8 rotates at very high speeds (the low-pressure turbine is a fast turbine), thus requiring assurance of the sealing of the casing 25, which houses the bearing 11 mounted on the low-pressure shaft 8.

[0039] The first sealing element 15 in the sealing element includes a first portion 15a and a second portion 15b. The first portion 15a is added to and fixed to the sleeve 19, and is also movably fixed to the sleeve 19. The second portion 15b is fixedly mounted relative to the wall 25a of the housing 25. The second sealing element 16 in the sealing element includes a first portion 16a and a second portion 16b. The first portion 16a is fixedly mounted to the sleeve 19, and is also movably fixed to the sleeve 19. The second portion 16b is fixedly mounted relative to the wall 25a of the housing 25. Figure 1 In an exemplary embodiment, the first portion 16a is added to and fixed to the sleeve 19. As a variation, the first portion 16a may be integral with the sleeve 19.

[0040] The bearing 11 is arranged between the first sealing element 15 and the second sealing element 16.

[0041] The sleeve 19 also includes a shoulder 23 extending at a distance from the second flange 20, on which the first sealing element 15 and the inner ring 12 are tightly mounted between the nut 22 and the shoulder 23. This configuration allows the sealing element 15 and the inner ring 12 to be removed relative to the sleeve 19 while ensuring axial positioning of the sealing element and the inner ring on the sleeve 19. Installation of the components 15, 12 is easier, for example, by machining threads at the free end of the sleeve 19, the threads being configured to engage with the threads of the nut 22 in a complementary shape and pitch, allowing the components 12, 15 to be tightened against the shoulder 23 by simply turning the nut 22.

[0042] Shoulder 23 may be integral with sleeve 19. As a variation, shoulder 23 may be formed by adding and securing a component to sleeve 19 (e.g., a threaded nut screwed onto sleeve 19, or a mechanically fixed or welded flange). Shoulder 23 extends radially from sleeve 19. All or part of components 15, 11, 29 are arranged directly or indirectly abutting against sleeve 19 and are secured in place by nut 22. The nut causes components 15, 11, 29 to continuously abut against shoulder 23. Nut 22 and sleeve 19 may, for example, include complementary threads.

[0043] When the first portion 16a of the second sealing element is added to the sleeve 19 (see, for example, see...) Figure 1 Preferably, the first portion 16a is also tightly mounted on the sleeve 19 between the nut 22 and the shoulder 23. Typically, the first portion 16a can be axially positioned between the inner ring 12 of the bearing 11 and the shoulder 23.

[0044] On the other hand, when the first portion 16a of the second sealing element 16 is integral with the sleeve 19, the shoulder 23 can be arranged between the inner ring 12 and the first portion 16, or between the inner ring 12 and the first sealing element 15. In this case, the inner ring may, for example, include an axial region 12a and a radial region 12b, the axial region supporting the rolling portion of the bearing 11, and the radial region extending from the upstream or downstream edge of the axial region.

[0045] In one embodiment, a shoulder 23 extends at a distance from the second flange 20, and a nut 22 is mounted on the free end of a sleeve 19, the free end of which extends relative to the shoulder 23 and the second flange 20. Therefore, the sleeve 19 includes, from its free end, a nut 22, a first sealing element 15, a bearing 11, a second sealing element 16, and a second flange 20.

[0046] The second flange 20 is arranged adjacent to and abuts against the first flange 18 and is held in position, for example, using a bolt 21. For this purpose, the first flange 18 and the second flange 20 each include at least one orifice, and a retaining member 21 is inserted into these orifices to connect the flanges 18 and 20. The orifice may be a through-hole and a smooth orifice, in which case the retaining member 21 may include a threaded rod and a nut. As a variation, at least one of the orifices may be threaded, in which case the retaining member 21 may include a screw and optionally a nut. Other retaining members for connecting the first flange 18 and the second flange 20 are, of course, conceivable.

[0047] The retaining member 21 extends radially outward relative to the sleeve 19. Therefore, the sleeve 19 is closer to the axis X than the retaining member 21, which helps to ensure the seal of the lubricating housing.

[0048] Components 15, 16, 11, and 29 mounted on or formed in sleeve 19 may include at least the inner ring 12 of bearing 11, a first sealing element 15 and a second sealing element 16, and optionally at least one spoon-shaped portion 29. In the exemplary embodiment shown, bearing 11 is arranged between two sealing elements 15 and 16 that axially define lubrication housing 25. The spoon-shaped portion 29 is also inserted between the first sealing element 15 and bearing 11. The first sealing element 15, spoon-shaped portion 19, bearing 11, and, where appropriate, the second sealing element 16 are tightly and continuously mounted between nut 22 and shoulder 23 of sleeve 19. Therefore, nut 22 and components 11, 15, 16, and 29 are not fixed to or even in direct contact with low-pressure shaft 8.

[0049] Here, the first sealing element 15 includes a tubular support 15c and a shield 15a. The tubular support 15c is mounted on the sleeve 19, and the shield extends upstream from the tubular support 15c and carries the clearance constraint portion. The shield 15a extends radially around the nut 22. Further downstream, the second sealing element 16 also includes a support 16c and a shield 16a. The support 16c is connected to the sleeve 19 between the shoulder 23 and the inner ring 12 of the bearing 11. Figure 1 Alternatively, it may be integrated with the sleeve 19, with the cover 16a extending radially around the sleeve 19 between the support portion 16c and the second flange 20 and bearing the gap constraint portion.

[0050] In one embodiment, the clearance constraint portion of the second sealing element 16 includes a first set of clearance constraint portions and a second set of clearance constraint portions. The first set of clearance constraint portions is mounted on the cover 16a, and the second set of clearance constraint portions is mounted on a portion 16b fixed to the wall 25a of the housing. The two sets of clearance constraint portions are axially spaced apart, such that the first set of clearance constraint portions faces the wear-resistant portion fixed to the portion 16b, while the second set of clearance constraint portions faces the wear-resistant portion fixed to the cover 16a. This configuration allows for improved sealing of the housing 25, and due to the presence of multiple sets of clearance constraint portions and the space separating the multiple sets of clearance constraint portions, the axial length of the sealing element 16 is greater.

[0051] In one embodiment, the sum of the axial length of the first sealing element 15 and the axial length of the second sealing element 16 is at most twice the axial distance between the nut 22 and the shoulder 23, and preferably approximately within 10% of the axial distance between the nut and the shoulder.

[0052] To further improve the sealing of the rotating assembly 10, the assembly 10 also includes a third sealing element 30 with a gap constraint portion (knife-shaped edge or twisted portion). The third sealing element 30 includes a first portion 30a and a second portion 30b. The first portion 30a is added and fixed to the first flange 18 by being movably fixed to the low-pressure shaft 8, and the second portion 30b is fixedly mounted relative to the wall 25a of the housing 25. Where appropriate, when the fixing member 21 includes a bolt, the first portion 30a of the third sealing element 30 can be fixed to the first flange 18 using the fixing member 21, for example, between the first flange 18 and the second flange 20. Preferably, the bolt 21 is radially outward relative to the sleeve 19.

[0053] Furthermore, to improve the sealing of the rotating assembly 10, a third sealing element 30 is located outside the housing 25, which differs from the first sealing element 15 and the second sealing element 16, which axially define the housing 25 and allow the wall 25a to rotate relative to the low-pressure shaft 8. For this purpose, the second portion 30b of the third sealing element 30 can be formed by a cylindrical wall extending axially from the wall 25a of the housing 25 along the direction of the second flange 20, while the first portion 30a is curved and includes a radial portion mounted on the first flange 18, and an axial portion extending along the direction of the housing 25 to face the cylindrical wall 30b.

[0054] In addition, the third sealing element 30 extends radially outward relative to the second sealing element 16.

[0055] Where appropriate, the first flange 18 of the low-pressure shaft 8 can be connected to additional parts 24 of the turbine 1, such as the rotor flange (e.g., Figure 1(As shown). Where appropriate, flange 24 extends radially outward relative to fixing member 21.

[0056] The turbine 1 may also include a lubrication system configured to supply lubricating fluid to components such as bearing 11. For example, the lubrication system includes a nozzle 26 that leads to a housing 25 and is configured to supply a quantity of fluid (typically oil) to the bearing 11. In the example shown in the figures, the housing 25 includes the bearing 11 and is defined upstream and downstream by a sealing element 15 mounted on a sleeve 19. Specifically, the nozzle 26 may be located between the bearing 11 and the upstream sealing element. Therefore, a scoop 29 is mounted on the sleeve 19 to extend between the nozzle 26 and the low-pressure shaft 8. The scoop is configured to deliver the fluid supplied by the nozzle 26 to the rolling portion 14 of the bearing 11. For this purpose, the scoop 29 may include a sheath fitted onto the sleeve 19, in which an orifice 17 is formed and a supply channel 27 connecting the orifice 17 to the inner ring 12. When the scoop 29 is attached to the sleeve 19, the orifice 17 is located near, for example, facing, the nozzle 26. Preferably, a supply channel 27 is formed in the spoon-shaped portion 29 and extends axially from the orifice 17 to one or more pipes 28 formed in the inner ring 12 and leading to the rolling portion 14. Under the action of centrifugal force, the fluid is then sprayed by the pipes 28 onto the rolling portion 14 and diffused into the casing 25.

[0057] In one embodiment, the wall 25a of the lubrication seal 25 comprises two parts, each part including retaining flanges 31a and 31b. The retaining flanges 31a and 31b of the wall 25a are both fixed to the same flange 32 of the turbine stator via bolts 33. For example, the retaining flanges 31a and 31b can be mounted from both sides of the flange 32 of the stator, and the three flanges 31a, 32, and 31b are fixed together by bolts 33. Preferably, each retaining flange 31a and 31b is integral with the corresponding portion of the wall 25a.

[0058] This invention is particularly applicable to the case of a USF-type turbine 1, in which the propeller (or fan 2) is ductless and driven by a low-pressure shaft 8 via a reduction gear 9. Therefore, the propeller has a high bypass ratio, typically greater than 30 (e.g., between 40 and 80). The bypass ratio is understood as the ratio between the flow rate of the secondary flow and the flow rate of the main flow. The low-pressure shaft 8 of this turbine 1 is then supercritical (i.e., exhibits a bending deformation mode within its operating range) and fast-moving. Therefore, the low-pressure shaft of this turbine is subjected to a severe vibration environment. Furthermore, the materials typically used for these low-pressure shafts 8 may be susceptible to corrosion and wear.

[0059] Therefore, by specifically fixing the sealing element 15 to the sleeve 19 instead of the low-pressure shaft 8, the material of the sealing element 15 is different from that of the low-pressure shaft 8, thereby reducing the risk of corrosion, particularly at the head of the clearance constraint. Since it is sufficient to remove the sealing element 15 from the sleeve 19 or, possibly, from the low-pressure shaft 8, the sleeve 19 is further greatly simplified.

Claims

1. A rotating component of a turbine, comprising: - A shaft (8) configured to drive a propeller (2) of the turbine (1) about an axis (X) and including a first flange (18) extending radially from the shaft (8) and integral with the shaft (8); - A sleeve (19) is fitted onto the shaft (8) and includes a second flange (20) extending radially from the sleeve (19), the sleeve (19) being secured to a first flange (18) of the shaft (8) via the second flange (20); - Lubrication enclosure (25), the lubrication enclosure comprising a wall fixedly mounted on the stator of the turbine; - A bearing (11) is housed in the lubrication housing (25), the bearing comprising an inner ring (12) and an outer ring (13), the inner ring being mounted on the sleeve (19) by being rotatably fixed to the sleeve, and the outer ring being fixedly mounted relative to the wall (25a) of the lubrication housing; - A first sealing element (15), the first sealing element comprising a labyrinth seal having at least two axially adjacent clearance constraint portions, the first sealing element (15) comprising a first portion (15a) and a second portion (15b), the first portion of the first sealing element being added and fixed to the sleeve (19) by means of movably fixing to the sleeve (19), the second portion of the first sealing element being fixedly mounted relative to the wall (25a) of the lubrication seal (25); - A second sealing element (16) comprising a labyrinth seal having at least two axially adjacent clearance constraint portions, the second sealing element (16) comprising a first portion (16a) and a second portion (16b), the first portion of the second sealing element being fixedly mounted on the sleeve by being movably fixed to the sleeve, the second portion of the second sealing element being fixedly mounted relative to the wall (25a) of the lubrication housing (25), the bearing (11) being axially arranged between the first sealing element and the second sealing element (16); The sleeve (19) also includes a shoulder (23) that extends axially spaced from the second flange (20), and the first sealing element (15) and the inner ring (12) are tightly axially mounted on the sleeve between the nut (22) and the shoulder (23).

2. The rotating assembly (10) according to claim 1, wherein, The sleeve (19) is made of a material different from that of the shaft (8).

3. The rotating assembly (10) according to claim 1 or 2, wherein, The gap constraint portion of the labyrinth seal of the first sealing element (15) includes at least two knife-shaped edges or a twisted portion that wraps around at least two turns, and / or the gap constraint portion of the labyrinth seal of the second sealing element includes at least two knife-shaped edges or a twisted portion that wraps around at least two turns.

4. The rotating assembly according to claim 1 or 2, the rotating assembly further comprising a third sealing element (30), the third sealing element comprising axially adjacent clearance constraint portions, the third sealing element (30) comprising a first portion (30a) and a second portion (30b), the first portion of the third sealing element being added and fixed to the first flange (18) by being movably fixed to the shaft (8), the second portion of the third sealing element being fixedly mounted relative to the wall (25a) of the lubrication seal (25).

5. The rotating assembly (10) according to claim 4, wherein, The third sealing element (30) is arranged radially outward relative to the second sealing element (16).

6. The rotating assembly (10) according to claim 4, wherein, The third sealing element (30) is arranged on the outside of the lubrication seal (25).

7. The rotating assembly (10) according to claim 1 or 2, wherein, The first sealing element (15) and the inner ring (12) are removably mounted on the sleeve (19).

8. The rotating assembly (10) according to claim 7, wherein, At least one of the second and third sealing elements (16, 30) may also be removably mounted on the sleeve (19).

9. The rotating assembly (10) according to claim 1 or 2, wherein, The first part (16a) of the second sealing element (16) is integral with the sleeve (19).

10. The rotating assembly (10) according to claim 1 or 2, wherein, The second flange (20) is integral with the sleeve (19).

11. The rotating assembly (10) according to claim 1 or 2, wherein, The nut (22) is mounted on the free axial end of the sleeve (19).

12. The rotating assembly (10) according to claim 1 or 2, the rotating assembly further comprising an additional flange (24), the additional flange (24), the second flange (20) and the first flange (18) being connected by the same fixing member (21).

13. The rotating assembly (10) according to claim 12, wherein, The fixing member (21) is a bolt, which is arranged radially outward relative to the sleeve (19).

14. The rotating assembly (10) according to claim 12, wherein, The wall (25a) of the lubrication seal (25) includes a third flange (31a), and the stator of the turbine includes a fourth flange (32), the third flange (31a) being fixed to the fourth flange (32) by an additional bolt (33).

15. The rotating assembly (10) according to claim 14, wherein, The wall (25a) includes two wall sections, the first wall section of which is integral with the third flange (31a), and the second wall section of which is integral with the fifth flange (31b), the fifth flange (31b) being fixed to the fourth flange (32) via the additional bolt (33).

16. The rotating assembly (10) according to claim 15, wherein, The fixing member (21) is a bolt, which is arranged radially outward relative to the sleeve (19), and the additional bolt (33) is arranged radially outward of the fixing member (21).

17. The rotating assembly (10) according to claim 1 or 2, wherein, The gap constraint portion of the labyrinth seal of the second sealing element (16) includes a first set of gap constraint portions mounted on a first portion (16a) of the second sealing element and a second set of gap constraint portions mounted on a second portion (16b) of the second sealing element, wherein the first set of gap constraint portions and the second set of gap constraint portions are axially spaced apart.

18. The rotating assembly (10) according to claim 1 or 2, wherein, The sum of the axial length of the first sealing element (15) and the axial length of the second sealing element (16) is less than or equal to twice the axial distance between the nut (22) and the shoulder (23).

19. The rotating assembly (10) according to claim 1 or 2, wherein, The first sealing element (15) includes a first support (15c) fixed to the sleeve (19) and a first shield extending radially around the nut (22), one of the first support (15c) and the first shield having a gap constraint portion of the labyrinth seal.

20. The rotating assembly (10) according to claim 1 or 2, wherein, The second sealing element (16) includes a second support (16c) fixedly mounted on the sleeve (19) and a second shield extending axially between the bearing (11) and the second flange (20).

21. The rotating assembly (10) according to claim 1 or 2, further comprising: - Nozzle (26), the nozzle leading to the lubrication seal (25), the nozzle being connected to the lubrication system and configured to provide a certain amount of fluid to the bearing (11); as well as - A spoon-shaped portion (29) is connected to the lubrication system and is configured to deliver the fluid to the bearing (11).

22. The rotating assembly (10) according to claim 21, wherein, The spoon-shaped portion (29) has an inlet and an outlet, the inlet being arranged facing the nozzle (26) and the outlet leading to the inner ring (12) of the bearing (11).

23. The rotating assembly (10) according to claim 21, wherein, The spoon-shaped portion (29) includes a sheath fitted onto the sleeve (19), in which an orifice (17) is formed and a supply channel (27) fluidly connecting the inlet to the inner ring (12) of the bearing (11).

24. The rotating assembly (10) according to claim 23, wherein, The supply channel (27) extends axially between the inlet and the outlet of the supply channel (27).

25. The rotating assembly (10) according to claim 11, wherein, The nut (22) is installed on the free axial end of the sleeve (19) by screwing.

26. The rotating assembly (10) according to claim 18, wherein, The sum of the axial length of the first sealing element (15) and the axial length of the second sealing element (16) is equal to less than 10% of the axial distance between the nut (22) and the shoulder (23).

27. A turbine (1) comprising a rotating assembly (10) according to any one of claims 1 to 26 and a ductless propeller (2) driven to rotate by the shaft (8), the turbine (1) having a bypass ratio greater than 30.

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