SEALING RING SECTOR FOR AN AIRCRAFT TURBINE TURBINE

Abstract

Sector (34) of a sealing ring (33) for a turbine of an aircraft turbomachine, the sector (34) extending circumferentially around an axis (X) and comprising a body (35) carrying a block of an abradable material (36), the body (35) being axially delimited by an upstream end (37) and by a downstream end (39), characterized in that the body (35) comprises a blind cavity (41) which is axially delimited by a bottom (42) upstream and an opening (43) which opens at the downstream end (39) of the body (35), the cavity (41) having a radial dimension (Dc) with respect to the axis (X) which increases continuously along the axis (X) from the bottom (42) of the cavity (41) to the opening (43) of the cavity (41). Figure for the abridged version: 2

Description

Title of the invention: SEALING RING SECTOR FOR AN AIRCRAFT TURBOMACHINE TURBINE Technical field of the invention

[0001] The present invention relates to a sealing ring sector for an aircraft turbomachine turbine, as well as to a sealing ring formed by such sectors, but also to a turbine comprising such a sealing ring, and finally to a turbomachine comprising such a turbine. Technical background

[0002] Classically, a turbomachine turbine comprises one or more stages arranged axially one after the other, each stage comprising a bladed distributor (stator) and a bladed moving wheel (rotor).

[0003] A movable wheel comprises a disc carrying an annular row of blades.

[0004] Each blade comprises a blade which has a summit at its free external end, this summit being able to be provided or not with one or more scrapers.

[0005] In order to improve the efficiency of a turbine, it is necessary to maximize the amount of exhaust gas acting on the different blades.

[0006] To achieve this, it is known to implant a sectorized sealing ring (known by the English acronym OSAS for "Outer Stationary Air Seal") around the rotating wheel, this ring being fixed to a turbine housing. The ring comprises, for each sector, an internal block of abradable material (for example, a metallic or ceramic block with a honeycomb structure) which cooperates with the tips of the blades to form a dynamic labyrinth-type sealing joint.

[0007] The turbine casing is exposed to the thermal stresses of the exhaust gases, which are at approximately 1000°C. It is known to control the casing temperature by means of a cooling system, in particular to ensure that it does not exceed a critical temperature (for example, 650°C). Controlling the casing temperature also makes it possible to control its expansion, and consequently the radial clearance between the abradable material blocks of the ring and the blade tips, in order to improve turbine performance.

[0008] Such a cooling system is better known by the English acronyms LPTACC (for "Low Pressure Turbine Active Clearance Control") or HPTACC (for "High Pressure Turbine Active Clearance Control"), depending on whether it is associated with a low pressure turbine or a high pressure turbine.

[0009] Conventionally, such a cooling system draws a flow of cold air from the secondary vein using a scoop, and projects it onto the outer skin of the crankcase via various ramps that surround it.

[0010] Engine manufacturers find that thermal insulation of the crankcase against the thermal stresses of the exhaust gases is essential, in order to minimize the amount of air taken up by the cooling system to cool the crankcase, and thus improve the performance of the turbomachine.

[0011] It is known from document FR2961556A1 to limit heat transfer by conduction from the ring to the housing by indirectly fixing the ring to the housing, the ring being fixed to the adjacent distributors which are themselves fixed to the housing.

[0012] Engine manufacturers note that such a solution can be improved.

[0013] Indeed, the solution proposed in the aforementioned document addresses heat transfer by conduction, but it does not take into account heat transfer by radiation, which also contributes to the heating of the housing. In fact, the ring exposed to the exhaust gases transfers its heat by radiation (or radiative heat exchange) to the parts directly adjacent to it, including the turbine housing.

[0014] The objective of the present invention is therefore to provide a simple, effective and economical solution to the aforementioned problem. Summary of the invention

[0015] The invention thus proposes a sector of a sealing ring for a turbine of an aircraft turbomachine, the sector extending circumferentially around an axis X and comprising a body carrying a block of an abradable material which is intended to cooperate with at least one apex of a blade of a moving wheel, the body being delimited axially by an upstream end which has an upstream mounting member and by a downstream end which has a downstream mounting member which is intended to cooperate with a hook of a turbine housing, characterized in that the body comprises a blind cavity which is delimited axially by a bottom upstream and an opening which opens at the downstream end of the body, the cavity having a radial dimension De vis-à-vis the axis X which increases continuously along the axis X from the bottom of the cavity to the opening of the cavity.

[0016] The introduction of such a cavity in the body of the sector makes it possible overall to improve the thermal insulation of the casing, and thus to minimize the amount of air taken in by the cooling system, and consequently to improve the performance of the turbomachine.

[0017] Indeed, the cavity not only allows a portion of the radiative heat flux (or heat flux by radiation) to be captured and evacuated via the opening, but also limits the conductive heat flux (or heat flux by conduction) which passes through the sector.

[0018] In addition, the sizing of the cavity makes it possible to deflect the captured radiative flux towards the opening, in order to promote its evacuation into the vein.

[0019] The sector according to the invention may comprise one or more of the following features, taken individually or in combination with each other: - the bottom of the cavity is located at the upstream end of the body; - the bottom of the cavity is formed by an upstream wall of the body; - the cavity is radially delimited on one side by an internal surface and, on the other side, by an external surface, the internal and external surfaces being located radially opposite each other and each having a radial dimension Dsi, Dse vis-à-vis the X axis which increases continuously along the X axis from the bottom of the cavity located upstream to the opening of the cavity located downstream; - the internal surface is formed by an internal wall of the body and the external surface is formed by an external wall of the body, the internal and external walls being opposite each other; - the internal and external surfaces are reflective, in order to increase the reflection of the radiative heat flux; - the internal and external surfaces have a reflective surface treatment or a reflective coating; - the cavity is circumferentially delimited by a first face which is disposed at a first circumferential extremity of the body and by a second face which is disposed at a second circumferential extremity of the body, the first and second circumferential extremities of the body being circumferentially opposed to each other; - a first wall forms the first face and radially connects the internal and external surfaces of the body, and a second wall forms the second face and radially connects the internal and external surfaces of the body; - the body includes at its downstream end a notch open axially towards the downstream and which is intended to receive an upstream rim of a distributor arranged axially downstream of the sealing ring, the upstream rim being located radially outside vis-à-vis the cavity; - the upstream mounting element is a rim that protrudes axially upstream from the body, the rim being intended to insert axially into a groove open axially downstream of a rail of the turbine housing; - the downstream mounting element is a housing open radially outwards, the housing being intended to receive the hook of the turbine housing.

[0020] The present invention also relates to a sealing ring for a turbine of an aircraft turbomachine, the ring comprising a plurality of sectors as described above, the sectors being arranged circumferentially end to end around the X axis.

[0021] The present invention further relates to a turbine of an aircraft turbomachine comprising a sealing ring as described above and a wheel radially arranged inside the ring, the wheel comprising a disc carrying an annular row of blades, each blade comprising a blade which has a crest at its free outer end, the blocks in an abradable material of the different sectors of the ring cooperating with the crests of the blades of the wheel.

[0022] The present invention finally relates to an aircraft turbomachine comprising a turbine as described above. Brief description of the figures

[0023] The invention will be better understood and other details, features and advantages of the invention will become more apparent upon reading the following description, given by way of non-limiting example and with reference to the accompanying drawings in which:

[0024] [Fig-1] [Fig.1] is a schematic axial half-sectional view of a turbomachine aircraft;

[0025] [Fig.2] [Fig.2] is a detailed view of [Fig.1] which illustrates in particular a ring sealing of a turbine according to the invention;

[0026] [Fig.3] [Fig.3] is a schematic perspective view of a sector of the sealing ring which is illustrated in [Fig.2]. Detailed description of the invention

[0027] Figure 1 shows a partial turbomachine 1 of aircraft 2. Aircraft 2 is, for example, an airplane.

[0028] By convention in this application, the terms "upstream" and "downstream" are defined with respect to the direction of gas flow in the turbomachine 1, when the turbomachine 1 is operating in "propeller" mode.

[0029] As illustrated in [Fig.1], the turbomachine 1 conventionally comprises, from upstream to downstream, a shrouded blower 3, a low-pressure compressor 4, a high-pressure compressor 5, an annular combustion chamber 6, a high-pressure turbine 7, a low-pressure turbine 8 and an exhaust nozzle 9.

[0030] The high-pressure compressor 5 and the high-pressure turbine 7 are connected to each other by a high-pressure shaft 11 and together form a high-pressure (HP) body. The low pressure compressor 4 and the low pressure turbine 8 are connected to each other by a low pressure shaft 12 and together form a low pressure (LP) body.

[0031] As illustrated in [Fig.1], the airflow generated by the blower 3 is divided, by a fixed structure 13 of the turbomachine 1, into a primary flow which enters a primary channel 14 to supply the low-pressure compressor 4, and into a secondary flow which flows into a secondary channel 15 around the gas generator, to provide most of the thrust.

[0032] As illustrated in [Fig.1], the blower 3 is driven in rotation by a blower shaft 16 which is itself driven in rotation by the low pressure shaft 12 by means of a speed reducer 17.

[0033] The turbomachine 1 extends around a longitudinal axis X which corresponds in particular to the axis of rotation of the blower shaft 16, the high-pressure shaft 11 and the low-pressure shaft 12.

[0034] Figure 2 shows an upstream part of the low-pressure turbine 8 of the turbomachine 1, and more specifically a rotating wheel 18 of a first stage of the low pressure turbine 8 and a distributor 19 of a second stage of the low pressure turbine 8.

[0035] The distributor 19 is bladed and comprises an annular row of rectifier blades 20. The rectifier blades 20 are arranged between outer and inner rings 21 which define a portion of the primary stream 14 into which the exhaust gases from the combustion chamber 6 flow. The distributor 19 is fixed to a housing 22 of the low-pressure turbine 8. More specifically, the outer ring 21 of the distributor 19 includes, in particular, an upstream spoiler 23 bearing radially on a hook 24 of the housing 22. The distributor 19 is preferably sectored, each sector comprising, for example, two or three rectifier blades 20.

[0036] The rotating wheel 18 is also bladed and free to rotate about the X-axis. The rotating wheel 18 comprises a disk carrying an annular row of blades 25. Each of the blades 25 comprises a blade 26 having a vertex 27 at its free outer end. The blade 26 of each of the blades 25 extends along a stacking axis Z which is substantially perpendicular to the X-axis. The blade 26 has an intrados face 28 and an extrados face connected to each other by a leading edge 29 and a trailing edge 30. The exhaust gases flow around the blade 26 from the leading edge 29 to the trailing edge 30, the leading edge 29 thus being positioned upstream of the trailing edge 30 in the direction of exhaust gas flow. The summit 27 of each of the dawns 25 here includes upstream and downstream licks 31, 32.

[0037] The movable wheel 18 is disposed inside a sealing ring 33 which is fixed to the housing 22. The ring 33 is sectorized and thus comprises a plurality of sectors 34 arranged end to end circumferentially around the axis X.

[0038] Each sector 34 of the ring 33 extends circumferentially around the axis X. Each sector 34 comprises a body 35 carrying a block of an abradable material 36 which cooperates with the tips 27 of the blades 25. The body 35 of each sector 34 is axially delimited by an upstream end 37 which has an upstream mounting member 38 and by a downstream end 39 which has a downstream mounting member 40 which cooperates with the hook 24 of the housing 22 of the turbine 8.

[0039] According to the invention, the body 35 of each sector 34 comprises a blind (or non-opening) cavity 41 which is axially delimited by a bottom 42 upstream and an opening 43 which opens at the downstream end 39 of the body 35. The cavity 41 has a radial dimension De vis-à-vis the axis X which increases continuously (or linearly) along the axis X from the bottom 42 of the cavity 41 to the opening 43 of the cavity 41, so as not only to capture part of the radiative heat flux (or heat flux by radiation) and evacuate it via the opening 43 but also to limit the conductive heat flux (or heat flux by conduction).

[0040] The introduction of such a cavity 41 into the body 35 of the sector 34 makes it possible overall to improve the thermal insulation of the casing 22, and thus to minimize the amount of air taken up by the cooling system, and consequently to improve the performance of the turbomachine 1.

[0041] Indeed, the cavity 41 not only allows a portion of the radiative heat flux to be captured and evacuated via the opening 43, but also limits the conductive heat flux which passes through the sector 34.

[0042] In addition, the dimensioning of the cavity 41 makes it possible to deflect the captured radiative flux towards the opening 43, in order to promote its evacuation into the vein 14.

[0043] In the same way as the turbine 7, 8 or the turbomachine 1, each sector 34 of the ring 33 extends around the axis X.

[0044] In the present application, the terms "internal" and "external" are defined with respect to the X-axis.

[0045] The body 35 of a sector 34 can obviously include several cavities 41 arranged circumferentially next to each other or radially one above the other.

[0046] As defined above, according to the invention, each cavity 41 is blind and axially delimited by a bottom 42 upstream and an opening 43 which leads to the downstream end 39 of the body 35. Each cavity 41 has a radial dimension De with respect to the X-axis which increases continuously along the X-axis from the bottom 42 of the cavity 41 to the opening 43 of the cavity 41.

[0047] Advantageously, the bottom 42 of the cavity or cavities 41 is located at the upstream end 37 of the body 35 of the sector 34. Such a positioning of the bottom 42 makes it possible to maximize the axial dimension of the cavity 41, and consequently to improve its ability to thermally insulate the housing 22.

[0048] Advantageously, the bottom 42 of the cavity or cavities 41 is formed by an upstream wall 44 of the body 35. In the same way, such an arrangement of the bottom 42 makes it possible to maximize the axial dimension of the cavity 41.

[0049] Each cavity 41 can be radially delimited by an internal surface 45 and an external surface 46 located radially opposite each other.

[0050] Advantageously, the internal and external surfaces 45, 46 of a cavity 41 each have a radial dimension Dsi, Dse with respect to the X-axis that increases continuously (or linearly) along the X-axis from the bottom 42 of the cavity 41 located upstream to the opening 43 of the cavity 41 located downstream. Such a dimensioning of the surfaces 45, 46 promotes the evacuation of the radiative heat flux in the vein 14.

[0051] The internal surface 45 of a cavity 41 can be formed by an internal wall 47 of the body 35 and the external surface 46 of a cavity 41 can be formed by an external wall 48 of the body 35, the internal and external walls 47, 48 being opposite each other.

[0052] Advantageously, the internal and external surfaces 45, 46 of a cavity 41 are reflective, so as to promote the reflection of the radiative heat flux. For this purpose, the internal and external surfaces 45, 46 may have a reflective surface treatment or a reflective coating.

[0053] The cavity or cavities 41 can be circumferentially delimited by a first face 49 which is disposed at a first circumferential end 50 of the body 35 and by a second face 51 which is disposed at a second circumferential end 52 of the body 35, the first and second circumferential ends 50, 52 of the body 35 being circumferentially opposed to each other.

[0054] Such a positioning of the first and second faces 49, 51 makes it possible to maximize the circumferential dimension of the cavity or cavities 41, and consequently to improve its ability to thermally insulate the housing 22.

[0055] The first face 49 can be formed by a first wall 53 which radially connects the internal and external surfaces 45, 46 (or the internal and external walls 47, 48) of the body 35. The first wall 53 forms a stiffener which makes it possible to reinforce the structure of the sector 34.

[0056] Similarly, the second face 51 can be formed by a second wall 54 which radially connects the internal and external surfaces 45, 46 (or the internal and external walls 47, 48) of the body 35. In the same way as the first wall 53, the second wall 54 forms a stiffener which makes it possible to reinforce the structure of the sector 34.

[0057] The body 35 may include bridges arranged in the cavity 41, so as to reinforce it. Each bridge thus radially connects the inner and outer walls 47, 48 of the body 35.

[0058] The upstream mounting member 38 of a sector 34 can be a rim 55 which projects axially upstream from the body 35, the rim 55 being intended to fit axially into a groove 56 open axially downstream of a rail 57 of the casing 22 of the turbine 8.

[0059] The downstream mounting element 40 of a sector 34 can be a housing 58 open radially outwards, the housing 58 being intended to receive the hook 24 of the housing 22 of the turbine 8.

[0060] The body 35 of each sector 34 (or each sector 34) can be obtained by additive manufacturing.

[0061] Advantageously, sealing means (for example, strips and / or plates) are arranged between the sectors 34 of the ring 33 to minimize inter-sector leakage.

[0062] According to the embodiment illustrated in figures 2 and 3, each sector 34 is in the form of an arc of a circle around the X axis.

[0063] Each sector 34 comprises a single cavity 41 which is by definition inside the body 35.

[0064] The cavity 41 extends axially from the bottom 42 to the opening 43.

[0065] The bottom 42 is disposed at the upstream end 37 of the body 35 and is formed by an upstream wall 44 of the body 35 which is here substantially radial.

[0066] The opening 43 opens at the downstream end 39 of the body 35, and is therefore disposed at the downstream end 39 of the body 35. The opening 43 is located radially between the block in an abradable material 36 and a notch 59 receiving an upstream rim 60 of the distributor 19.

[0067] The cavity 41 extends radially from an internal surface 45 to an external surface 46.

[0068] The internal and external surfaces 45, 46 are radially opposite each other. The internal surface 45 is formed by an internal wall 47 of the body 35 and the external surface 46 is formed by an external wall 48 of the body 35. The internal and external surfaces 45, 46 each have a radial dimension Dsi, Dse with respect to the X axis which increases continuously (or linearly) along the X axis from the bottom 42 of the cavity 41 to the opening 43 of the cavity 4L. The internal and external surfaces 45, 46 are reflective (or shiny), so as to promote the reflection of the radiative heat flux.

[0069] As illustrated in [Fig.2] by the arrows shown in cavity 41, the internal and external surfaces 45, 46 successively deflect the captured radiative flux to the opening 43 of cavity 41, through which it is evacuated into the primary vein 14.

[0070] The internal and external walls 47, 48 of the body 35 are opposite each other. The inner and outer walls 47, 48 of the body 35 are frustoconical. The walls 47, 48 flare radially from upstream to downstream from the upstream wall 44. The inner wall 47 internally supports the block made of an abradable material 36.

[0071] The block made of an abradable material 36 is stepped. The block made of an abradable material 36 thus comprises an upstream step 61 which cooperates with the upstream blades 31 of the blades 25 and a downstream step 62 which cooperates with the downstream blades 32 of the blades 25, to form a dynamic labyrinth-type sealing joint. The block made of an abradable material 36 may be a metallic or ceramic block with a honeycomb structure.

[0072] The cavity 41 extends circumferentially from a first face 49 to a second face 51.

[0073] The first face 49 is disposed at the first circumferential end 50 of the body 35. The first face 49 is formed by a first wall 53 which radially connects the internal and external surfaces 45, 46 (or the internal and external walls 47, 48).

[0074] The second face 51 is disposed at the second circumferential end 52 of the body 35, the second circumferential end 52 being circumferentially opposite to the first circumferential end 50. A second wall 54 forms the second face 51 and radially connects the internal and external surfaces 45, 46 (or the internal and external walls 47, 48).

[0075] The walls 53, 54 form stiffeners which help to reinforce the structure of sector 34.

[0076] The various sectors 34 of the ring 33 are fixed directly to the housing 22 of the turbine 8. The housing 22 is arranged around the ring 33 and radially opposite the ring 33.

[0077] Each sector 34 is fixed to the housing 22 via the upstream mounting member 38 which is carried by the upstream end 37 of the body 35 and the downstream mounting member 40 which is carried by the downstream end 39 of the body 35.

[0078] More specifically, the upstream mounting member 38 is here a rim 55 which projects axially upstream from a radially internal end of the upstream wall 44. The rim 55 is inserted axially into a groove 56 open axially downstream of a rail 57 of the housing 22. The rim 55 is here integral with the body 35, but it could be attached to the body 35.

[0079] The downstream mounting member 40 is here a housing 58 open radially outwards, the housing 58 receiving the hook 24 of the housing 22 of the turbine 8. The housing 58 is formed by two rims 63 projecting radially outwards from the outer wall 48 of the body 35. In the same way as the axial rim 55, the rims 63 are here integral with the body 35, but they could be attached to the body 35.

[0080] As illustrated in [Fig. 2], the body 35 of each sector 34 comprises at its downstream end 39 a notch 59 open axially downstream, the notch 59 receiving an upstream rim 60 of the distributor 19. The upstream rim 60 forms a thermal shield which contributes to the thermal insulation of the housing 22 (and in particular to the thermal insulation of the hook 24). The notch 59 is located radially outside the cavity 41, and more precisely between the opening 43 of the cavity 41 and the downstream mounting member 40.

[0081] As illustrated in [Fig. 2], the sector 34 further comprises a thermal protection plate 64 attached to the upstream wall 44 of the body 35, this thermal protection plate 64 contributing to the thermal insulation of the housing 22 (and in particular to the thermal insulation of the rail 57). This thermal protection plate 64 comprises an axial web 65 from which an inner flange 66 and an outer flange 67 extend radially. The outer flange 67 of the thermal protection plate 64 is attached to the upstream wall 44 of the body 35 such that the web 65 and the inner flange 66 cover, in particular, the axial rim 55 and the rail 57 of the housing 22.

[0082] The embodiment illustrated in the figures is in no way limiting; the sector 34 (or the ring 33) according to the invention could obviously be mounted in another turbine of the turbomachine 1, for example the high-pressure turbine 7 of the turbomachine 1.

Claims

Demands

1. A sealing ring sector (34) for a turbine (7, 8) of an aircraft turbomachine (1) (2), the sector (34) extending circumferentially about an axis (X) and comprising a body (35) carrying a block of an abradable material (36) intended to cooperate with at least one crest (27) of a blade (25) of a wheel (18), the body (35) being axially delimited by an upstream end (37) having an upstream mounting member (38) and by a downstream end (39) having a downstream mounting member (40) intended to cooperate with a hook (24) of a housing (22) of the turbine (7, 8), characterized in that the body (35) comprises a blind cavity (41) axially delimited by an upstream bottom (42) and a opening (43) which leads to the downstream end (39) of the body (35),the cavity (41) having a radial dimension (De) with respect to the axis (X) which increases continuously along the axis (X) from the bottom (42) of the cavity (41) to the opening (43) of the cavity (41).

2. Sector (34) according to claim 1, characterized in that the bottom (42) of the cavity (41) is disposed at the upstream end (37) of the body (35).

3. Sector (34) according to the preceding claim, characterized in that the bottom (42) of the cavity (41) is formed by an upstream wall (44) of the body (35).

4. Sector (34) according to any one of the preceding claims, characterized in that the cavity (41) is radially delimited on the one hand by an internal surface (45) and, on the other hand, by an external surface (46), the internal and external surfaces (45, 46) being located radially opposite each other and each having a radial dimension (Dsi, Dse) with respect to the axis (X) which increases continuously along the axis (X) from the bottom (42) of the cavity (41) located upstream to the opening (43) of the cavity (41) located downstream.

5. Sector (34) according to any one of the preceding claims, characterized in that the cavity (41) is circumferentially delimited by a first face (49) which is disposed at a first circumferential end (50) of the body (35) and by a second face (51) which is disposed at a second circumferential end (52) of the body (35), the first and second circumferential ends (50, 52) of the body (35) being circumferentially opposed to each other.

6. Sector (34) according to claim 5, characterized in that a first wall (53) forms the first face (49) and radially connects the internal and external surfaces (45, 46) of the body (35), and a second wall (54) forms the second face (51) and radially connects the internal and external surfaces (45, 46) of the body (35).

7. Sector (34) according to any one of the preceding claims, characterized in that the body (35) comprises at its downstream end (39) a notch (59) open axially downstream and which is intended to receive an upstream rim (60) of a distributor (19) disposed axially downstream of the sealing ring (33), the upstream rim (60) being located radially outside vis-à-vis the cavity (41).

8. Sector (34) according to any one of the preceding claims, characterized in that the upstream mounting member (38) is a rim (55) which projects axially upstream from the body (35), the rim (55) being intended to fit axially into a groove (56) which is open axially downstream of a rail (57) of the housing (22) of the turbine (7, 8).

9. Sector (34) according to any one of the preceding claims, characterized in that the downstream mounting member (40) is a housing (58) open radially outwards, the housing (58) being intended to receive the hook (24) of the housing (22) of the turbine (7, 8).

10. Sealing ring (33) for a turbine (7, 8) of an aircraft turbomachine (1) (2), the ring (33) comprising a plurality of sectors (34) according to any one of the preceding claims, the sectors (34) being arranged circumferentially end to end around the axis (X).

11. Aircraft (2) turbomachine (1) turbine (7, 8) comprising a sealing ring (33) according to the preceding claim and a wheel (18) arranged radially inside the ring (33), the wheel (18) comprising a disc carrying an annular row of blades (25), each blade (25) comprising a blade (26) which has a crest (27) at its free outer end, the blocks of an abradable material (36) of the different sectors (34) of the ring (33) cooperating with the crests (27) of the blades (25) of the wheel (18).

12. Aircraft turbomachine (1) (2) comprising a turbine (7, 8) according to the preceding claim.

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