Module for an aircraft turbine engine

Abstract

The invention relates to a module (10) for an aircraft turbine engine (10), the module (10) comprising: - a rotor comprising an impeller (20) of a centrifugal compressor (12) and a wheel (22) of a turbine (16), - a rectifier-diffuser (26) mounted at the impeller (20) outlet, - a turbine distributor (28) mounted upstream of the wheel (22), - an annular combustion chamber (14) axially interposed between the rectifier-diffuser (26) and the distributor (28), - an injector (56) of ventilation air surrounded by the combustion chamber (14) in order to ventilate the wheel (22) of the turbine (16), and - an arrangement of metal plates (32) for connecting the rectifier-diffuser (26) to the distributor (28) and to the injector (56), said arrangement of metal plates (32) being formed as a single piece with the injector (56), and the arrangement of metal plates (32) comprising openings (64) for the withdrawal of air (f5) and for supplying the injector (56) with the withdrawn air.

Description

[0001] DESCRIPTION

[0002] TITLE: MODULE FOR AN AIRCRAFT TURBOMACHINE

[0003] Technical field of the invention

[0004] The present invention relates to a module for an aircraft turbomachine, as well as a turbomachine comprising such a module.

[0005] Technical background

[0006] The state of the art includes in particular document FR-A-2 937 371, FR-A1-2 904 038, FR-A1 -2 975 733, FR-A1 -2 904 034, FR-A1 -2 904 036, US-A1-2008 / 141680, US-B1 -11 ,773,773 and US-A1 -2021 / 293180.

[0007] An aircraft turbomachine includes a gas generator which classically comprises, from upstream to downstream, with reference to the flow of gases in the turbomachine, at least one compressor, one annular combustion chamber and at least one turbine.

[0008] In the case of a twin-spool turbofan engine, with low-pressure and high-pressure components respectively, the gas generator comprises, successively, a low-pressure compressor, a high-pressure compressor, the combustion chamber, a high-pressure turbine, and a low-pressure turbine. The gas generator defines a first annular flow path of gas, called the primary flow, which passes through the compressors, the combustion chamber, and the turbines.

[0009] The high-pressure compressor rotor is connected to the high-pressure turbine rotor by a high-pressure shaft. The low-pressure compressor rotor is connected to the low-pressure turbine rotor by a low-pressure shaft that passes through the high-pressure shaft and drives a propeller shaft, typically located upstream of the gas generator.

[0010] When this propeller is enclosed and therefore surrounded by an annular casing, this propeller is called a blower and generates an airflow, called secondary flow, which flows around the gas generator.

[0011] There are axial compressors and centrifugal compressors, and this application relates to a module and a turbomachine incorporating a centrifugal compressor. The distinctive feature of the centrifugal compressor is that its rotor is formed by an impeller with an axially oriented inlet and a radially oriented outward outlet.

[0012] In a module or turbomachine, the impeller is connected to a turbine wheel by a shaft.

[0013] The combustion chamber is axially interposed between the centrifugal compressor and the turbine wheel and is supplied with air by a rectifier-diffuser mounted at the outlet of the wheel, which allows the air to be rectified before being diffused with an axial component.

[0014] During operation, the turbine wheel is subjected to significant thermal stresses and must be ventilated. It is therefore known that compressed air is drawn upstream of the chamber to ventilate the turbine wheel.

[0015] In particular, it is known to provide a ventilation air injector which is surrounded by the chamber and which includes an air outlet oriented axially downstream in order to ventilate the turbine wheel.

[0016] The applicant has already proposed solutions in the aforementioned documents for guiding the air exiting the compressor or the rectifier-diffuser within the annular space between the combustion chamber and the impeller shaft connecting to the turbine wheel, particularly to supply the injector. These solutions utilize a sheet metal arrangement that connects the rectifier-diffuser to the distributor and to the turbine wheel ventilation injector.

[0017] For example, in document FR-A1-2 904 036, Figure 4 shows a plate arrangement designed to guide a portion of the air exiting the rectifier-diffuser so that this air flows radially from the inside to the outside along a downstream radial face of the impeller. This air is then injected downstream of the chamber. The plate arrangement also guides another portion of the air exiting the rectifier-diffuser towards the turbine wheel ventilation injector.

[0018] The invention proposes an improvement to this technology which makes it possible to ensure better ventilation of the turbine wheel.

[0019] Summary of the invention

[0020] The invention relates to a module for an aircraft turbomachine, this module comprising: - a rotor including a centrifugal compressor impeller and a turbine wheel, the impeller and the wheel being connected to each other by a shaft rotating about an axis,

[0021] - a stator comprising a rectifier-diffuser mounted at the output of the turbine wheel and a turbine distributor mounted upstream of the rotating wheel,

[0022] - an annular combustion chamber, also part of the stator and axially interposed between the rectifier-diffuser and the distributor, the combustion chamber comprising two coaxial annular walls, respectively internal and external, which are connected upstream by an annular chamber bottom,

[0023] - a ventilation air injector also forming part of the stator, said injector being surrounded by the combustion chamber and having a downstream end which forms an air outlet oriented axially downstream in order to ventilate the turbine wheel, and

[0024] - an arrangement of laminations (or portions of laminations) connecting the rectifier-diffuser to the distributor and the injector, this arrangement of laminations also forming part of the stator and comprising:

[0025] + a first annular sheet metal or portion of annular sheet metal which is surrounded by said internal wall of the chamber and which defines with this internal wall a first annular duct for the passage of air exiting the rectifier-diffuser, the air being intended to flow from upstream to downstream in this first duct,

[0026] + a second annular sheet metal or portion of annular sheet metal which surrounds said shaft and which, together with this shaft, defines a second annular air passage duct, this second duct being supplied with air by the first duct and the air being intended to flow from downstream to upstream in this second duct, and

[0027] + a third annular plate or portion of an annular plate located downstream (and preferably just downstream) of the impeller and extending radially from the inside out from the second plate or portion of plate to the impeller outlet, this third plate or portion of plate defining, with a downstream radial face of the impeller, a third annular air passage duct which is supplied with air by the second duct, the air being intended to flow radially from the inside out in this third duct, characterized in that the plate arrangement is formed as a single piece with said injector, and the plate arrangement includes openings for drawing air from the third duct and supplying said injector with this drawn air. The air exiting the rectifier-diffuser has been compressed in the centrifugal compressor and is at a relatively high pressure.Part of this air is guided by the lamination arrangement and flows radially from the inside to the outside along the downstream radial face of the impeller. This flow causes the air to be recompressed by a vortex effect between the downstream radial face of the impeller and the lamination arrangement. Compressed air at a pressure higher than that exiting the rectifier-diffuser is therefore found at the impeller outlet. According to the invention, the lamination arrangement is designed to convey this air to the injector. To this end, the lamination arrangement includes openings for drawing in this air and supplying it to the injector. The turbine wheel is thus ventilated with compressed air at a pressure higher than that exiting the rectifier-diffuser, which is particularly advantageous as it significantly improves the efficiency of this ventilation.Although the temperature of the compressed air exiting the rectifier-diffuser may also increase by viscous friction with the impeller when the air flows along its downstream radial face, the compressed air will have time to return to its initial temperature (at the outlet of the rectifier-diffuser) before reaching the injector because of its passage through the arrangement of laminations which is generally at the temperature of the air exiting the rectifier-diffuser.

[0028] The arrangement of sheet metal can be an arrangement of one or more sheet metal(s) or of one or more portion(s) of sheet metal.

[0029] The module according to the invention may comprise one or more of the following features, taken individually or in combination with each other:

[0030] - the sheet metal arrangement includes at least one first opening upstream for the extraction of air from the third duct, and at least one second opening downstream for supplying the injector with this extracted air;

[0031] - said injector comprises two annular walls, respectively internal and external, the downstream ends of which form said air outlet;

[0032] - said at least one first opening is formed by an annular row of orifices which is located at the level of the external periphery of the wheel, and said at least one second opening is formed by another annular row of orifices which open between the walls of the injector; - the arrangement of sheets forms an internal annular cavity which is interposed radially between the shaft and the combustion chamber and which includes an air inlet formed by said at least one first opening, and an air outlet formed by said at least one second opening;

[0033] - the annular walls of the injector extend axially downstream from a sheet or portion of sheet of the sheet arrangement, such as said second sheet or portion of sheet;

[0034] - the annular walls of the injector are cylindrical walls which are coaxial and centered on the axis;

[0035] - the sheet metal arrangement includes an annular flange for fixing to an annular flange, called the first flange, which is integral with said distributor;

[0036] -- said injector is located radially inside the flange;

[0037] -- said injector is surrounded by this flange;

[0038] - the flange includes radially oriented lunules or lights for the fluidic communication of said first conduit with said second conduit;

[0039] -- the flange is devoid of axial air passages;

[0040] -- the second flange comprises an internal periphery in radial support on an external periphery of said injector;

[0041] - the injector is axially aligned with an annular row of orifices of an annular flange, called the second flange, which is integral with the moving wheel;

[0042] - an annular sealing gasket, for example of the labyrinth type, is mounted, preferably radially, between the second flange and the injector, and in particular the internal periphery of the injector;

[0043] - the moving wheel includes a disc carrying blades on its outer periphery, the disc having an upstream annular face ventilated by air from the injector;

[0044] - the second flange delimits with the upstream face of the disc an annular enclosure for ventilating the disc, this enclosure having an air inlet formed by the said orifices of the second flange;

[0045] -- the enclosure includes an air outlet formed by ventilation openings at the base of the wheel blades;

[0046] - an annular sealing gasket, for example of the labyrinth type, is mounted, preferably radially, between the first and second flanges;

[0047] -- the third annular plate or portion of annular plate is located opposite the impeller. The present invention also relates to an aircraft turbomachine, comprising at least one module as described above.

[0048] Brief description of the figures

[0049] Other features and advantages of the invention will become apparent upon reading the detailed description that follows, for an understanding of which reference should be made to the accompanying drawings in which:

[0050] [Fig.1] Figure 1 is a schematic half-view in axial cross-section of a module according to the invention for an aircraft turbomachine,

[0051] [Fig. 2] Figure 2 is a larger-scale view of part of Figure 1.

[0052] [Fig. 3] Figure 3 is another larger-scale view of part of Figure 1, and

[0053] [Fig.4] Figure 4 is another larger-scale view of part of Figure 1.

[0054] Detailed description of the invention

[0055] Figure 1 shows a module 10 for an aircraft turbomachine, this turbomachine being here a twin-spool turbojet although this example is not limiting.

[0056] Axis A designates the longitudinal axis of the turbomachine.

[0057] The turbomachine is partially represented and includes a gas generator which comprises, from upstream to downstream with reference to the flow of gases along axis A, at least one compressor 12, an annular combustion chamber 14 and at least one turbine 16.

[0058] The turbomachine may include a low-pressure compressor (not shown) followed by a high-pressure centrifugal compressor (shown), and the turbine may also include a high-pressure turbine (shown) followed by a low-pressure turbine (not shown).

[0059] The compressor rotor (centrifugal) 12 is connected to the turbine rotor (high pressure) 16 by a shaft (high pressure) 18. The shaft 18 is movable around the axis A.

[0060] The compressor rotor 12 is formed by an impeller 20. The turbine rotor 16 is formed by an impeller 22. The shaft 18 connects the impeller 20 and the impeller 22 and together they form a rotor or rotating body, particularly a high-pressure one. The combustion chamber 14 comprises two coaxial annular walls, respectively inner 14a and outer 14b, which are connected upstream by an annular chamber bottom 14c.

[0061] As is known, the bottom of chamber 14c is equipped with fuel injection systems 24 into the combustion chamber 14.

[0062] Module 10 includes several other stator elements including a rectifier-diffuser 26 and a distributor 28 of the turbine 16.

[0063] The rectifier-diffuser 26 is mounted at the outlet of the wheel 20 and comprises a first annular part forming a rectifier 26a and a second annular part forming a diffuser 26b. The first part is oriented radially and the second part is oriented towards the chamber 14 with an axial component. This type of rectifier-diffuser 26 is known.

[0064] The distributor 28 is a bladed distributor, that is to say, it comprises an annular row of blades 28a. It is axially interposed between the outlet of chamber 14 and wheel 22.

[0065] The wheel 22 also includes an annular row of blades 22a which are mounted on the periphery of a disk 22b. The blades 22a include feet which are mounted axially in recesses on the outer periphery of the disk 22b in a known manner.

[0066] The wheel 22 is surrounded by a sealing ring 30 which, together with platforms 22c of the blades 22a, defines a first portion of the turbine runner. The blades 28a of the distributor 28 extend between two annular ferrules 28b, 28c of the distributor 28, which delimit between themselves a second portion of the turbine runner, located upstream of the aforementioned first portion. The ferrules 28b, 28c can be formed by platforms placed circumferentially end to end.

[0067] The stator further comprises a lamination arrangement 32 which provides the connection between the rectifier-diffuser 26 and the distributor 28, and more particularly between the rectifier-diffuser 26 and a first annular flange 34 integral with the distributor 28. In the example shown, the first flange 34 comprises an outer periphery 34a fixed to the inner periphery of the distributor 28, and an inner periphery 34b fixed to the lamination arrangement 32. Preferably, the inner periphery 34b of the flange 34 comprises an annular flange 35 for fixing to the lamination arrangement 32. A second annular flange 36 is fixed to the wheel 22. The flange 36 comprises an outer periphery 36a bearing axially on the outer periphery of the disk, for the purpose of retaining the blades (by axial bearing of their feet on the flange 36) on the disk 22b, and an internal periphery 36b fixed to the shaft 18.In particular, in the example shown, the internal periphery 36b is axially intercalated between a portion of shaft 18a, located upstream and attached to the wheel 20 and another portion of shaft 18b, located downstream and attached to the disk 22b.

[0068] An annular sealing gasket 38 is preferably mounted between the second flange 36 and the first flange 34. The gasket 38 is preferably labyrinth-shaped and comprises annular grooves 38a carried by or formed on the second flange 36 and adapted to cooperate by friction with an abradable ring 38b carried by the first flange 34. Preferably, the gasket 38 is located radially inside the flange 35 and thus surrounded by this flange 35. As can be seen in Figure 1, the abradable ring 38b is located (directly) radially below the flange 35.

[0069] The inner periphery 34b of the first flange 34 may include an inward radial extension referenced 34b1.

[0070] The arrangement of sheet metal 32 is both axially intercalated between the wheel 20 and the distributor 28, or here the flanges 34, 36, and radially between the shaft 18 and the combustion chamber 14.

[0071] As its name indicates, the arrangement of sheets 32 is formed by sheets or portions of sheets which allow in particular to guide part of the air exiting the rectifier-diffuser 26, and in particular the part of the air which bypasses the chamber 14 radially from the inside.

[0072] Figures 1 and 2 show the air F1 exiting the centrifugal compressor 12 and supplying the rectifier-diffuser 26, as well as the air F2 exiting the rectifier-diffuser. Part of this air F2 bypasses the chamber 14 internally and is designated as f2. The remainder of this air enters the chamber 14 or bypasses the chamber 14 radially externally.

[0073] The arrangement of sheets 32 includes a first annular sheet 32a or portion of annular sheet which is surrounded by the inner wall 14a of the chamber 14 and which defines with this inner wall 14a a first annular conduit 40 for the passage of air f1, this air f1 being intended to flow from upstream to downstream in this first conduit 40. The sheet 32a extends for example from the inner periphery of the rectifier-diffuser 26 to an annular flange 42 for fixing to the flange 35 of the first flange 34.

[0074] In the example shown, the sheet metal 32a essentially comprises two portions: an upstream portion 32a1, which is cylindrical, and a downstream portion 32a2, which is frustoconical and converges downstream. The upstream end of the upstream portion 32a1 is connected to the inner periphery of the rectifier-diffuser 26, and its downstream end is located inside the inner wall 14a of the chamber 14 and is connected to the upstream end of the second portion 32a2. This second portion 32a2 is substantially parallel to the wall 14a of the chamber, and its inner periphery is connected to the flange 42.

[0075] The flange 42 includes axial ports aligned with ports in the flange 35 for the passage of fasteners 44, such as screw-nuts. Unlike prior art solutions, these flanges 42 and 35 do not have axial air passage ports.

[0076] In the example shown, however, the flange 42 includes lunules 46 or radially oriented lights for the passage of air in a radial direction in particular from the downstream end of the first conduit 40 (arrow f2 in figures 1 and 3).

[0077] The arrangement of the plates 32 includes a second annular plate 32b, or portion of annular plate, which surrounds the shaft 18, and in particular the portion of shaft 18a, and which, together with this shaft 18, defines a second annular air passage 48. This second passage 48 is supplied with air by the first passage 40, in particular through the lunules 46, and the air f3 is intended to flow from downstream to upstream in this second passage 48.

[0078] Sheet metal 32b extends upstream from flange 42 of sheet metal 32a.

[0079] In the example shown, the sheet metal 32b essentially comprises two portions: a first downstream portion 32b1, which is frustoconical and converges upstream, and a second upstream portion 32b2, which is cylindrical. The first portion 32b1 has a downstream end connected to the flange 42 and an upstream end connected to the downstream end of the second portion 32b2. This second portion 32b2 is preferably located at a short radial distance from the shaft 18 so that the conduit 48 has the smallest possible diameter.

[0080] The first portion 32b1 can be located axially opposite the second flange 36, in particular a radial wall 36c of the second flange 36 which extends between the shaft 18 and the first flange 34.

[0081] The first portion 32b1 can be located radially inside the second portion 32a2 and can therefore be enclosed by this portion 32a2 as in the example shown. The second portion 32b2 can be located radially inside the first portion 32a1.

[0082] The arrangement of plates 32 includes a third annular plate 32c or portion of annular plate which is located (preferably just) downstream of the wheel 20 and which extends radially from the inside out from the second plate 32b to the exit of the wheel 20.

[0083] This third sheet metal 32c defines with a downstream radial face 20a of the wheel 20 a third annular air passage 50 f4 which is supplied with air by the second conduit 48. The air f4 is intended to flow radially from the inside to the outside in this third conduit 50 and to be recompressed by vortex effect due to its passage near the face 20a of the wheel 20.

[0084] Sheet metal 32c extends, for example, from the upstream end of sheet metal 32b to the inner periphery of the rectifier-diffuser 26. Sheet metal 32a and 32c can be connected to the rectifier-diffuser 26 in the same area as in the example shown.

[0085] In the example shown, the sheet metal 32c essentially comprises two portions: a first downstream portion 32c1, which is frustoconical and flared upstream, and a second upstream portion 32c2, which is radial and extends outwards. The first portion 32c1 has a downstream end or inner periphery connected to the upstream end of the sheet metal 32b, and in particular to its portion 32b2, and an upstream end or outer periphery connected to the radially inner end of the second portion 32c2. This second portion 32c2 is connected to the rectifier-diffuser 26, specifically to the upstream end of the sheet metal 32a.

[0086] Sheet metal 32c can be located radially inside sheet metal 32a, and therefore be surrounded by sheet metal 32a. In particular, portions 32c1, 32c2 can be surrounded by the first portion 32a1 of sheet metal 32a.

[0087] The first portion 32c1 can be located axially opposite portion 32b1. The second portion 32c2 can be located axially opposite portion 32a2 and / or flange 42.

[0088] In the example shown, the arrangement of sheets 32 internally defines an internal annular cavity 54. This cavity 54 is externally bounded by sheet 32a, internally by sheet 32, upstream by sheet 32c, and downstream by portions 32a2 and 32b1 of sheets 32a and 32b. The arrangement of sheets 32 may include annular stiffening ribs 52. In the example shown, this is the case, for instance, with sheet 32 ​​and, in particular, its second portion 32b2. The ribs 52 are located radially within the internal cavity 54 of the arrangement of sheets 32.

[0089] The module 10 further includes an injector 56 which is surrounded by the chamber 14 and which in the example shown has two annular walls, respectively internal 56a and external 56b (figures 1 and 4).

[0090] This injector 56 allows ventilation air to be injected at the level of the turbine wheel 22b and in particular at the level of its disc 22b.

[0091] For this purpose, the downstream ends of walls 56a, 56b form an air outlet oriented axially downstream and towards wheel 22b.

[0092] In the example shown, the flange 36, and in particular its radial wall 36c, is axially interposed between the outlet of the injector 56 and the wheel 22b and includes an annular row of orifices 58 for the passage of air f6 exiting the injector 56. This air f6 therefore passes through the orifices 58 of the flange 36 and enters an annular enclosure 60 for ventilating the disc 22b. This enclosure 60 has an air inlet formed by the orifices 58, and an air outlet which may be formed by vents (not shown) for ventilating the feet of the blades 22a of the wheel 22.

[0093] In the example shown, we can see that the extension 34b1 is radially supported inwards on the injector 56 and in particular on its outer wall 56b.

[0094] It is also noted that an annular sealing gasket 62 is preferably mounted between the second flange 36 and the injector 56, and in particular between the radial wall 36c of the flange and the internal wall 56a of the injector 56. The gasket 38 is preferably labyrinth-shaped and includes annular grooves 62a carried by or formed on the second flange 36 or its wall 36c and adapted to cooperate by friction with an abradable ring 62b carried by the injector 56 or its wall 56a. Preferably, the seal 38 is located radially inside the orifices 58, which are thus preferably interposed radially between the two seals 62, 38. It is therefore understood that the seals 62, 38 ensure the sealing of the interface between the injector and the flanges 34, 36, and in particular the flange 36.

[0095] According to the invention, the sheet metal arrangement 32 is formed as a single piece with the injector 56, as can be seen in the drawings. Furthermore, the sheet metal arrangement 32 includes openings 64 and 66 for drawing air f5 from the third duct 50 and supplying the injector 56 with this drawn air f5. Preferably, the sheet metal arrangement 32 includes at least one first opening 64 upstream for drawing air f5 from the third duct 50, and at least one second opening 66 downstream for supplying the injector 56 with this drawn air f5.

[0096] As in the example shown, the first opening 64 can be formed by an annular row of orifices which is located at the level of the external periphery of the wheel 20, and the second opening 66 is formed by another annular row of orifices which open between the walls 56a, 56b of the injector 56.

[0097] Advantageously, the first opening 64 or its orifices form(s) an air inlet into the internal cavity 54, and the second opening 66 or its orifices form(s) an air outlet from this cavity 54.

[0098] In the example shown, the first opening 64 (or its orifices) is formed in the portion 32c2 of the sheet 32c, closest to the outer periphery of this sheet 32c. The second opening 66 (or its orifices) is formed in the portion 32b1 of the sheet 32b, closest to the inner periphery of this sheet 32b.

[0099] The walls 56a, 56b of the injector 56 can project axially downstream from the arrangement of sheets 32, and in particular from sheet 32b and more particularly its portion 32b1.

[0100] In the example shown, the walls 56a, 56b of the injector 56 are cylindrical walls which are coaxial and centered on the axis A.

[0101] The drawings show that the arrangement of sheet metal 32 can be formed from a single piece, including the flange 42 and the straightener-diffuser 26.

[0102] It is therefore understood that the air circulates in module 10 as follows. Air F1 exits the centrifugal compressor 12 at a given pressure and flows into the rectifier-diffuser 26, which diffuses air F2. Part of this air F1 bypasses chamber 14 internally and flows through duct 40, passing through the lunules 46. Air F2, F3 then flows through duct 48 to duct 50. When air F4 rises along the downstream face 20a of the impeller 20, it is further compressed by vortex effect and has a pressure higher than that at the outlet of the impeller 20. This air F5 passes through opening 64 to be collected, and then this air F6 then passes through opening 66 to supply the injector, which feeds the ventilation chamber 60 of the impeller 22.

[0103] Although the temperature of the air f4 may also increase by viscous friction with the wheel 20, this air will have time to return to a temperature close to or identical to the air F2 or f1 due to the passage of the air f5 through the arrangement of sheets 32 which is globally at the temperature of the air F2, f1.

[0104] Although not shown, fins could be present on the radial face 20a of the wheel in order to accentuate the air recompression phenomenon f4.

[0105] In general, the invention allows the turbine's impeller to be supplied with air at a higher pressure and with an unchanged temperature. This allows the impeller to be cooled with greater pressure and therefore a higher flow rate while maintaining the temperature without compression, thus improving the cooling of the impeller.

Claims

DEMANDS 1. Module (10) for an aircraft turbomachine, this module (10) comprising: - a rotor comprising a centrifugal compressor impeller (20) (12) and a turbine impeller (22) (16), the impeller (20) and the turbine impeller (22) being connected to each other by a shaft (18) that rotates about an axis (A), - a stator comprising a rectifier-diffuser (26) mounted at the output of the wheel (20) and a turbine distributor (28) mounted upstream of the rotating wheel (22), - an annular combustion chamber (14) also forming part of the stator and axially interposed between the rectifier-diffuser (26) and the distributor (28), the combustion chamber (14) comprising two coaxial annular walls, respectively internal (14a) and external (14b), which are connected upstream by an annular chamber bottom (14c), - a ventilation air injector (56) also forming part of the stator, said injector (56) being surrounded by the combustion chamber (14), and having a downstream end which forms an air outlet oriented axially downstream in order to ventilate the rotating wheel (22) of the turbine (16), and - a lamination arrangement (32) connecting the rectifier-diffuser (26) to the distributor (28) and to the injector (56), this lamination arrangement (32) also forming part of the stator and comprising: + a first annular sheet (32a) or portion of annular sheet which is surrounded by said internal wall (14a) of the chamber (14) and which defines with this internal wall (14a) a first annular duct (40) for the passage of air (f1) exiting the rectifier-diffuser (26), the air (f1) being intended to flow from upstream to downstream in this first duct (40), + a second annular plate (32b) or portion of annular plate surrounding said shaft (18) and defining with this shaft (18) a second annular air passage duct (48), this second duct (48) being supplied with air by the first duct (40) and the air (f3) being intended to flow from downstream to upstream in this second duct (48), and + a third annular plate (32c) or portion of annular plate located downstream of the impeller (20) and extending radially from the inside to the outside from the second plate (32b) or portion of plate to the outlet of the impeller (20), this third plate (32c) or portion of plate defining with a downstream radial face (20a) of the impeller (20) a third annular air passage duct (50) which is supplied with air by the second conduit (48), the air (f4) being intended to flow radially from the inside to the outside in this third conduit (50), characterized in that the arrangement of sheets (32) is formed in one piece with said injector (56), and the arrangement of sheets (32) includes openings (64) for the sampling of air (f5) in the third conduit (50) and the supplying of said injector (56) with this sampling air.

2. Module (10) according to claim 1, wherein the arrangement of sheets (32) includes at least a first opening (64) upstream for the sampling of air (f5) in the third conduit (50), and at least a second opening (66) downstream for supplying the injector (56) with this sampled air.

3. Module (10) according to claim 2, wherein said injector (56) comprises two annular walls, respectively internal (56a) and external (56b) of which downstream ends form said air outlet.

4. Module (10) according to claim 3, wherein said at least a first opening (64) is formed by an annular row of orifices which is located at the level of the external periphery of the wheel (20), and said at least a second opening (66) is formed by another annular row of orifices which open between the walls (56a, 56b) of the injector (56).

5. Module (10) according to claim 3 or 4, wherein the arrangement of sheets (32) forms an internal annular cavity (54) which is radially intercalated between the shaft (18) and the combustion chamber (14) and which includes an air inlet formed by said at least a first opening (64), and an air outlet formed by said at least a second opening (66).

6. Module (10) according to any one of claims 3 to 5, wherein the annular walls (56a, 56b) of the injector (56) extend axially downstream from a sheet (32b) or portion of sheet of the arrangement of sheets (32), such as said second sheet (32b) or portion of sheet.

7. Module (30) according to any one of claims 3 to 6, wherein the annular walls (56a, 56b) of the injector (56) are cylindrical walls which are coaxial and centered on the axis (A).

8. Module (10) according to any one of the preceding claims, wherein the arrangement of sheets (32) includes an annular flange (42) for attachment to an annular flange (34), called the first flange, integral with said distributor (28).

9. Module (10) according to claim 8, wherein the flange (42) comprises radially oriented lunules (46) or lights for the fluidic communication of said first conduit (40) with said second conduit (48).

10. Module (10) according to any one of the preceding claims, wherein the injector (56) is axially aligned with an annular row of orifices (58) of an annular flange (36), called the second flange, integral with the movable wheel (22).

11. Module (10) according to claim 10, in which an annular sealing gasket (62), for example of the labyrinth type, is mounted, preferably radially, between the second flange (36) and the injector (56).

12. Module (30) according to any one of the preceding claims, wherein the moving wheel (22) comprises a disc (22b) having blades (22b) on its outer periphery, the disc (22b) having an upstream annular face ventilated by air from the injector (56).

13. Module (10) according to claim 12, depending on claim 11, in which the second flange (36) delimits with the upstream face of the disc (22b) an annular enclosure (60) for ventilating the disc (22b), this enclosure (60) having an air inlet formed by said orifices (58) of the second flange (36).

14. Module (10) according to any one of claims 8 to 13, depending on claim 8 or 9, in which an annular sealing gasket (38), for example of the labyrinth type, is mounted radially between the first and second flanges (34, 36).

15. Turbomachine for an aircraft, comprising at least one module (10) according to one of the preceding claims.

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