Device for pressurizing a turbine downstream casing and corresponding turbine

Abstract

The invention relates to a device (30) for pressurizing a turbine downstream casing (20), said device being supplied by means of a pressurized air flow and comprising: a first shaft section (9a); a second shaft section (9b) coupled to the first shaft section by internal splines (39) and longitudinal external splines (41) and extending inside said first shaft section over a distance. According to the invention, the device comprises at least a first channel (46) formed by the splines and at least one orifice (43) passing through the second shaft section, arranged upstream of the first channel and in fluid communication with the first channel, open inside the second shaft section, so as to make the pressurized air flow circulate from the first channel between the first and second shaft sections towards the downstream casing.

Description

Technical Field

[0001] This invention relates to the field of turbines, and more particularly to a device for pressurizing the downstream casing of a turbine. The invention is also applicable to corresponding turbines. Background Technology

[0002] The prior art includes documents US-A1-2014 / 150449, US-A1-2020 / 088053 and US-B1-6582187.

[0003] Turbines typically include a drive shaft that rotates guided by rotary guide bearings. These bearings are arranged in one or more sealed lubrication housings, each containing a lubricating mist for the bearings. The housings are pressurized to retain the lubricant within. Lubricant leakage outside the housings poses a risk of turbine ignition and imbalance, excessive lubricant consumption, and / or aircraft nacelle contamination.

[0004] The housing is typically defined by a wall at least partially formed by a fixed housing, rotor housing, bearing support, and / or engine shaft section. Sealing devices are located in the area where the fixed and movable parts meet. Therefore, a bearing housing typically includes two sealing devices, one upstream and one downstream of the housing. The housing is pressurized because the sealing devices cannot guarantee an optimal seal. In practice, the sealing devices are configured such that a permanent airflow passes through the sealing devices from the outside of the housing towards the inside, preventing lubricant from leaving the housing through the sealing devices. The pressure around the housing is greater than the pressure inside the housing to maintain the airflow from the outside of the housing towards the inside through the sealing devices. This air typically comes from a pressurized air source, such as a high-pressure or low-pressure compressor.

[0005] In turbines with a very small "core area" (surrounding the combustion chamber), integrated constraints may arise at the passageway of the drive shaft (e.g., the low-pressure turbine shaft) through a smaller "core area" than is typically defined. The size of the "core area" necessitates a small-diameter shaft (less than 100 mm), which does not allow for the transmission of much torque, thus limiting the ability to transmit torsional torque through this small-diameter shaft.

[0006] The pressurization of the downstream casing of the turbine is typically achieved through a pressurized (or ventilated) airflow that is collected at the high-pressure compressor and spends most of its time upstream of the "core region." Perforations formed at certain locations on the drive shaft allow this pressurized airflow to flow into the downstream casing. The presence of these perforations necessitates the provision of local margins at their locations to compensate for stress concentrations that might impede the assembly of these shafts (e.g., the low-pressure shaft traversing the smaller "core region"). Document US-B1-6582187 includes perforations at upstream connections used to allow cooling airflow towards the interior of the compressor or turbine disk. These perforations cannot be formed on small engines. Summary of the Invention

[0007] The purpose of this invention is to provide pressurization of the downstream casing of a turbine without affecting the mass and structure of the downstream casing.

[0008] According to the invention, this objective is achieved by a device for pressurizing the downstream casing of a turbine having a longitudinal axis X, the device being supplied with pressurized airflow collected upstream of the turbine along the longitudinal axis, the device comprising:

[0009] - First shaft segment, the first shaft segment extends along the longitudinal axis X.

[0010] - A second shaft segment, connected to the first shaft segment by a longitudinal internal spline carried by the first shaft segment and a longitudinal external spline carried by the second shaft segment, the second shaft segment extending at least partially within the first shaft segment along a radial distance perpendicular to the longitudinal axis X along a radial axis Z.

[0011] The device includes at least one first channel and at least one orifice. The first channel is formed by an internal spline and an external spline. The orifice passes through a second shaft section on both sides along a radial axis. The orifice is arranged upstream of the first channel and is in fluid communication with the first channel on one hand, and is open inside the second shaft section on the other hand, so that pressurized airflow flows from the first channel between the first shaft section and the second shaft section, and then flows through the orifice toward the downstream casing of the turbine.

[0012] Therefore, this solution enables the achievement of the aforementioned objectives. Specifically, this configuration allows the downstream housing to be pressurized by allowing pressurized airflow from the collection point (located at the level of the high-pressure compressor) to the downstream housing of the turbine (particularly the low-pressure turbine). The position of the orifice upstream of the spline in the second shaft section avoids perforating the second shaft section in the torque transmission region, which would result in a margin in the shaft at the perforation to maintain stress concentration (forces transmitted to the second shaft section are at and downstream of the spline; no force is transmitted to the shaft at the portion upstream of the spline). Furthermore, the channel between the orifice in the shaft and the spline of the shaft is easy to manufacture and does not require significant structural changes to existing turbine components.

[0013] The device also includes one or more of the following features, which may be used individually or in combination:

[0014] - Internal and external splines include the surfaces that contact each other.

[0015] - The first shaft section is the low-pressure compressor shaft.

[0016] - The second shaft section is the low-pressure turbine shaft.

[0017] - The internal and external splines are configured to produce pairs of internal and external splines adjacent to each other along the circumferential direction, and are configured to make the space between the splines empty, which forms a first channel.

[0018] - The first channel occupies an angle range α, which is measured between one lateral side of the internal or external spline and another lateral side of the internal or external spline spaced apart from the aforementioned lateral side, and the angle range is between 35° and 55°.

[0019] - The first channel alternates with a series of splines on surfaces that are in contact with each other along the circumferential direction.

[0020] - The first shaft segment or the second shaft segment includes a series of teeth arranged downstream of the internal spline and the external spline and configured to perform the function of centering the first shaft segment relative to the second shaft segment.

[0021] - At least one second channel is formed by teeth.

[0022] - The teeth are spaced apart from each other in the circumferential direction to create empty inter-tooth spaces that form the second channel.

[0023] - The internal and external splines have similar cross-sectional shapes and dimensions, and the teeth themselves have similar cross-sectional shapes and dimensions.

[0024] - The first and second channels are evenly distributed around the longitudinal axis.

[0025] - The first shaft section includes at least one opening that extends through the walls of the first shaft section on both sides, the opening being located downstream of the second channel and intended to open within the first shaft section.

[0026] - The pressurization device includes a first shaft and a second shaft. The first shaft includes a first shaft section and a second shaft section. The first shaft extends at least partially within the second shaft. The second shaft includes at least one hole that passes through the walls of the second shaft on both sides. The hole is intended to be arranged near the downstream housing so that pressurized airflow exiting the one or more holes flows into the interior of the downstream housing.

[0027] - The first shaft section includes a plurality of orifices evenly distributed around the longitudinal axis.

[0028] - The spline is straight and parallel to the longitudinal axis.

[0029] - The number of internal longitudinal splines is less or more than the number of external longitudinal splines.

[0030] The present invention also relates to an aircraft turbine comprising a propeller, a gas generator for driving the propeller to rotate about a longitudinal axis X, and means for pressurizing a downstream outer casing, the means being as described above.

[0031] In one feature, the downstream casing is positioned downstream of the combustion chamber of the gas generator.

[0032] The present invention also relates to an aircraft comprising a turbine as described above. Attached Figure Description

[0033] The invention will be better understood after reading the following detailed description of embodiments of the invention given as purely illustrative and non-limiting examples, with reference to the accompanying schematic diagrams, and other objects, details, features, and advantages of the invention will become clearer, as illustrated in the accompanying schematic diagrams:

[0034] [ Figure 1 ] Figure 1 An example of a turbine is shown in axial cross-section, the turbine including a straightener for a single propeller and stator blades to which the present invention is applied;

[0035] [ Figure 2 ] Figure 2 An example of a downstream housing is shown in axial cross-section, the downstream housing containing at least one bearing according to the invention;

[0036] [ Figure 3 ] Figure 3 This is a detailed view of a partial axial cross-section of the inner and outer shafts that form part of the pressurizing device according to the present invention;

[0037] [ Figure 4 ] Figure 4 The connecting device according to the invention and the means for centering the shaft are shown in axial cross-section. The connecting devices cooperate with each other to rotate and fix the inner and outer shafts.

[0038] [ Figure 5 ] Figure 5 It is along Figure 4 A partial view of section AA of the inner and outer shafts shown, which are equipped with connecting splines according to the invention;

[0039] [ Figure 6 ] Figure 6 It is along Figure 4 A partial view of section BB of the inner and outer shafts shown, which are equipped with centering gears according to the invention; and

[0040] [ Figure 7 ] Figure 7 An example of a pressurized airflow path toward the downstream housing according to the invention is shown in axial cross-section. Detailed Implementation

[0041] This invention is applicable to turbines 1 with high propulsion efficiency (small high-pressure main body size). Figure 1 The turbine example shown includes a single propeller 2 and a straightener 25 located downstream of propeller 2. Propeller 2 is ductless. The turbine is designed for installation on an aircraft. This turbine is... Figure 2 The turboprop engine shown is described above as a "single ductless fan". Of course, the invention can be applied to other types of turbines, particularly those smaller than conventional turbines (e.g., turbofan dual-flow and twin-body engines).

[0042] In this invention, generally speaking, the terms "upstream," "downstream," "axial," and "axially" are defined relative to the gas circulation in the turbine, here along the longitudinal axis X (even in...). Figure 2 (From left to right). Similarly, the terms "radial," "inner," and "outer" are defined relative to the radial axis Z perpendicular to the longitudinal axis X and relative to the distance from the longitudinal axis X.

[0043] Furthermore, identical or substantially identical elements and / or elements having the same function are represented by the same reference numerals.

[0044] exist Figure 1In this design, turbine 1 includes a gas generator 3, which typically comprises, from upstream to downstream, a low-pressure compressor 4, a high-pressure compressor 5, a combustion chamber 6, a high-pressure turbine 7, and a low-pressure turbine 8. The low-pressure compressor 4 and the low-pressure turbine 8 are mechanically connected via a low-pressure shaft 9 to form a low-pressure main body. The high-pressure compressor 5 and the high-pressure turbine 7 are mechanically connected via a high-pressure shaft 10 to form a high-pressure main body. The low-pressure shaft 9 extends within and is coaxial with the high-pressure shaft 10.

[0045] In another configuration, not shown, the low-pressure or weak-pressure unit includes a low-pressure compressor connected to the intermediate-pressure turbine. A free-powered turbine is mounted downstream of the intermediate-pressure turbine and connected via a power drive shaft to a propeller, as described below, to drive the propeller to rotate.

[0046] The propeller 2 is formed by a ring of movable blades 21 extending from a rotating housing 11 that is rotatable about a longitudinal axis. Figure 2 In the example shown, propeller 2 is mounted upstream of the gas generator (traction device configuration). Alternatively, the propeller is mounted downstream of the gas generator (thruster configuration).

[0047] The straightener 23 includes multiple stator blades 24 (or fixed blades) referred to as outlet guide vanes (OGVs). The stator blades 24 are evenly distributed around the longitudinal axis X. The stator blades 24 may have variable pitch.

[0048] The airflow F entering the turbine is split into a primary airflow and a secondary airflow F2 at the splitter nose 22 carried by the outer casing 14. The primary airflow F1 flows in the main duct 12, which passes through the gas generator 3 (radially between the inner casing 13 and the outer casing 14) via the annular air inlet 15, and exits through the main nozzle 16 located downstream of the gas generator 3. The secondary airflow F2 passes through the propeller blades 21, the straightener blades 25, and flows around the outer casing 14. The propeller 2 is driven by either the power shaft or the low-pressure shaft 9 (the power shaft of the free-powered turbine and the low-pressure shaft of the low-pressure turbine, respectively). The propeller compresses the airflow outside the outer casing 14 and provides most of the thrust. Optionally, a reduction gear 18 is arranged between the propeller 2 and the power shaft, such as... Figure 2 As shown. The reducer 18 can be a planetary gear system or a planetary gear system.

[0049] The low-pressure shaft 9 is driven to rotate about its longitudinal axis by means of rotary guide bearings. These bearings are mounted upstream and downstream of the low-pressure shaft 9 and are housed within lubrication housings. As previously mentioned, these housings must be pressurized to maintain a lubricant mist (in this case, oil) within the housings. Generally, the higher the external pressure of the housing, the easier it is to ensure a seal. The external pressure is ensured by a pressurization circuit or pressurization device 30 supplied with pressurized or ventilated airflow.

[0050] Specifically, at least one downstream bearing 19 ( Figure 2 It is arranged in an annular downstream shell 20 centered on the longitudinal axis X. Figure 2 The annular housing 20, shown in more detail, is arranged downstream of the high-pressure compressor 5. The downstream housing 20 is at least partially defined by a bearing support 27, which includes an upstream radial outer wall 28 attached to a fixed structure of the turbine. The radial outer wall 28 engages with a collar 38 attached to the low-pressure shaft 9 via an upstream sealing device 29. In this example, the bearing support 27 also includes a first upstream branch 31 that carries an upstream base plate 32 at a first end. This upstream base plate 32 is attached to the outer ring 33a of a first downstream bearing 19a. The bearing support 27 also includes a second branch 34 that carries a downstream base plate 35 at a first end. The downstream base plate is attached to the outer ring 36a of a second downstream bearing 19b. The housing 20 is also partially defined by a radial inner wall. A section of the low-pressure shaft 9 forms the radial inner wall portion of the downstream housing 20. The low-pressure shaft 9, particularly the low-pressure compressor shaft described later, carries the inner rings 33b and 36b of the first and second downstream bearings 19a and 19b.

[0051] The sealing device 29 typically includes a labyrinth seal or a segmented radial seal.

[0052] Reference Figure 7 The pressurized airflow FP is collected upstream of the turbine, particularly from the first stage of the high-pressure compressor 5. The pressurization device 30 is configured such that the pressurized airflow can flow from the high-pressure compressor 5 to the downstream housing 20 between a first shaft and a second shaft. For this purpose, the pressurization device 30 includes a first section of a shaft 9a extending along the longitudinal axis X and a second shaft section connected to the first section of shaft 9a by a coupling device described below. Specifically, the pressurization device 30 includes a first shaft extending along the longitudinal axis X and a second shaft extending at least partially outside the first shaft and coaxial with the axis X. The first shaft is thus hollow. The second shaft is also hollow. The second shaft extends radially away from the first shaft so that the pressurized airflow flows between their inner and outer surfaces.

[0053] In this embodiment, the first shaft is the low-pressure shaft 9, and the second shaft is the high-pressure shaft 10.

[0054] Reference Figure 3 and Figure 4 The low-pressure shaft 9 includes a low-pressure compressor shaft 9a and a low-pressure turbine shaft 9b, which are rotatably fixed by a coupling device. A first shaft section is the low-pressure compressor shaft, and a second shaft section is the low-pressure turbine shaft. The coupling device includes an internal longitudinal spline 39 carried on the inner surface 40 of the low-pressure compressor shaft 9a. The internal spline 39 extends radially inward from the inner surface 40. The coupling device also includes a longitudinal external spline 41 carried by the outer surface 42 of the low-pressure turbine shaft 9b. The external spline 41 extends radially outward from the outer surface 42 of the low-pressure turbine shaft 9b. The internal spline 39 and the external spline 41 extend along a longitudinal axis and are distributed around the longitudinal axis X. The internal and external splines are straight. The connection of splines 39 and 41 allows torque to be transmitted from the low-pressure turbine shaft 9b to the low-pressure compressor shaft 9a.

[0055] Reference Figure 3 and Figure 5 The pressurizing device 30 includes at least one first channel 46 formed by an internal spline 39 and an external spline 41. Figure 5 In, it is shown Figure 4 In the cross-sectional view AA of the shaft, splines 39 and 41 are configured to produce pairs of adjacent internal splines 39 and external splines 41 in a circumferential direction around the longitudinal axis, and also to make the space between the splines empty, which forms a first channel 46.

[0056] To achieve this, the splines are generally similar in shape and size, such that all surfaces contact each other when the splines are joined. The splines in this example are generally trapezoidal. Specifically, each spline 39, 41 includes a top 47, which in this case is flat and is defined by two lateral sides 48, 49. In this embodiment, the lateral sides 48, 49 are defined in planes that are inclined relative to each other and relative to the radial axis, respectively. Here, the inclination angle is between 30° and 60°. The sides can be straight, or of course, other shapes, as long as the sides mate and contact each other.

[0057] Multiple first channels 46 are arranged regularly around the longitudinal axis. Figure 5Two of these first channels 46 are shown, spaced apart by an internal spline 39 and an external spline 41. The first channels 46 extend circumferentially. Each first channel 46 occupies an angular range (circumferential length) α, measured between one side of the internal or external spline and another side of the internal or external spline spaced apart from the aforementioned side. The angular range can be between 35° and 55°. These first channels 46 are formed by “removing” the internal and / or external splines. In this case, the number of internal and external splines is different. The number of internal splines may be less or more than the number of external splines. In the example shown, there are more internal splines than external splines. Figure 5 As can be seen, between each first channel 46 are three internal splines 39 connected to two external splines 41. The pressurized airflow FP passes only through the first channels 46; in this case, the faces (top / side sides) of these splines are in (close) contact with each other. These form seals or block the flow of FP through the channels. In other words, the channels 38 are wider than the simple spaces formed by the possible gaps between the adjacent and contacting surfaces of the splines (as is the case in some turbines of the prior art). The pressurized air flows unobstructed and without pressure loss to the upstream housing, which will be pressurized using this configuration.

[0058] exist Figure 3 In the design, the pressurizing device 30 includes at least one orifice 43 that passes through the walls of the low-pressure turbine shaft 9b on both sides. The axis A of the orifice 43 is parallel to the radial axis Z. The orifice includes an inlet and an outlet. The inlet faces the inner surface section 40 of the low-pressure compressor shaft 9b. The orifice 43 is arranged upstream of splines 39, 41. This arrangement avoids perforating the shaft at the connecting device, which in this case is a spline, thus preventing any allowance in the shaft at the perforation and maintaining stress concentration. A plurality of orifices 43 are formed in the wall and are regularly distributed around the axis X. In particular, each orifice 43 opens to both the outer surface 42 and the inner surface 44 of the low-pressure turbine shaft 9b. In other words, the orifice 43 opens inside the low-pressure turbine shaft 9b.

[0059] Each orifice 43 is located near the end 45 of the low-pressure turbine shaft 9b. Specifically, the axis A of each orifice 43 is located at a predetermined distance d from the end 45. The distance between axis A and the end 45 defines an end section 45a to which a nut 54 is screwed. The nut secures the low-pressure turbine shaft 9b and the low-pressure compressor shaft 9a. Compared to a conventional low-pressure turbine shaft, this end section 45a is "added" to the low-pressure turbine shaft 9b. The end section 45a allows for the addition of the orifice 43. An anti-rotation member 55 is provided to counteract rotation of the fastening nut 54. The anti-rotation member is radially mounted inside the nut 54. The anti-rotation member 55 also functions as a sealing plug and prevents oil leakage.

[0060] Each orifice 43 is located upstream of at least one first channel 46 and is in fluid communication with the first channel 46 such that pressurized airflow flows from upstream to the downstream casing 20 of the turbine between concentric shafts 9a, 9b.

[0061] The low-pressure compressor shaft 9a and the low-pressure turbine shaft 9b include centering devices for centering on the longitudinal axis X. These centering devices include teeth 50, which are internal teeth, carried by the low-pressure compressor shaft 9a. These teeth 50 project radially from the inner surface 40 toward the low-pressure turbine shaft 9b. Alternatively, the teeth are arranged on the outer surface of the low-pressure turbine shaft. The teeth 50 are generally similar in shape and size. Like splines, each tooth 50 includes a flat top and flat lateral sides. The top of each tooth 50 is supported against the outer surface of the low-pressure compressor shaft 9a. These teeth 50 are located downstream of the inner spline 33 and the outer spline 34.

[0062] The pressurizing device 30 also includes at least one second channel 51 formed by teeth 50. Similar to splines 39, 41, the teeth 50 are spaced apart to create empty inter-tooth spaces forming the second channel 51. In this way, a pressurized airflow FP flows between two adjacent but spaced-apart teeth 50. The second channel 51 is distributed around a longitudinal axis.

[0063] from Figure 4 It can also be seen that the tooth is axially separated from the internal spline and / or the external spline by a first distance l1, which is greater than the axial dimension l2 of the tooth 50. In the example shown, the distance l1 is less than the axial dimension of the spline.

[0064] exist Figure 7In the high-pressure compressor shaft 9a, the low-pressure compressor shaft 9a includes at least one opening 52 facing the high-pressure compressor 5, which radially penetrates the walls of the low-pressure compressor shaft on both sides. In other words, the opening 52 is axially located downstream of the second channel 51 and opens within the low-pressure compressor shaft 9a. Specifically, the shaft 9a includes a plurality of openings 52 evenly distributed around the axis X. It can also be seen that the high-pressure shaft 10 includes at least one hole 53, which penetrates the walls of the high-pressure shaft on both sides and is located downstream of the high-pressure body, near the low-pressure turbine, and has an axis parallel to the radial axis Z. The hole 53 is located downstream of the high-pressure body and near the low-pressure turbine. Advantageously, the plurality of holes 53 are distributed circumferentially around the high-pressure shaft 10. These holes are axially arranged downstream of the orifice 43.

[0065] In this way, the pressurized airflow FP collected from the high-pressure compressor 5 passes through the opening 52 of the low-pressure compressor shaft 9a and flows between the inner surface of the low-pressure compressor shaft 9a and the outer surface of the low-pressure turbine shaft 9b to the second channel 51 (e.g., Figure 7 (As shown by the dashed line in the image), then flows to the first channel 46 (as shown by the dashed line in the image). Figure 7 (As shown by the dashed line in the diagram), the air then enters the interior of the low-pressure turbine shaft 9b and exits through orifice 53. The pressure difference between the upstream and downstream allows the pressurized airflow to pass through. Different channels, orifices, and openings minimize pressure loss, thereby maintaining the pressure from the pressurized airflow supply.

Claims

1. A pressurizing device (30) for pressurizing the downstream casing (20) of a turbine (1) having a longitudinal axis X, the pressurizing device being supplied by a pressurized airflow (FP) collected upstream of the turbine along the longitudinal axis, the pressurizing device (30) comprising: - First shaft section (9a), the first shaft section extends along the longitudinal axis X. - A second shaft segment (9b), connected to the first shaft segment (9a) by a longitudinal internal spline (39) carried by the first shaft segment (9a) and a longitudinal external spline (41) carried by the second shaft segment (9b), the second shaft segment (9b) extending at least partially within the first shaft segment (9a) along a radial distance perpendicular to the longitudinal axis X, the longitudinal internal spline and the longitudinal external spline each comprising a surface. The pressurizing device is characterized by comprising at least one first channel (46) and at least one orifice (43), the at least one first channel being formed by the longitudinal internal spline (39) and the longitudinal external spline (41), the at least one orifice passing through the second shaft section (9b) on both sides along the radial axis, the orifice (43) being arranged upstream of the first channel (46) and in fluid communication with the first channel (46) on one hand, and open inside the second shaft section (9b) on the other hand, so that the pressurized airflow ( The FP flows from the first channel (46) between the first shaft section (9a) and the second shaft section (9b), and then through the orifice (43) toward the downstream housing (20) of the turbine. The longitudinal internal spline (39) and the longitudinal external spline (41) are configured to form a pair of longitudinal internal splines and longitudinal external splines adjacent to each other in the circumferential direction, wherein the faces of the pair of longitudinal internal splines and longitudinal external splines are in contact with each other; and the space between the splines is made empty, the space between the splines forming the first channel (46).

2. The pressurizing device (30) according to claim 1, characterized in that, The first channel (46) occupies an angle range (α) between one side of the longitudinal internal spline or the longitudinal external spline and another side of the longitudinal internal spline or the longitudinal external spline spaced apart from the aforementioned side, and the angle range is between 35° and 55°.

3. The pressurizing device (30) according to claim 1 or 2, characterized in that, The first shaft segment (9a) or the second shaft segment (9b) includes a series of teeth (50) arranged downstream of the longitudinal inner spline and the longitudinal outer spline, and configured to perform the function of centering the first shaft segment relative to the second shaft segment.

4. The pressurizing device (30) according to claim 3, characterized in that, At least one second channel (51) is formed through the tooth (50).

5. The pressurizing device (30) according to claim 3, characterized in that, The teeth (50) are spaced apart from each other in the circumferential direction to create an empty inter-tooth space that forms the second channel (51).

6. The pressurizing device (30) according to claim 4, characterized in that, The teeth (50) are spaced apart from each other in the circumferential direction to create an empty inter-tooth space that forms the second channel (51).

7. The pressurizing device (30) according to claim 3, characterized in that, The longitudinal internal spline (39) and the longitudinal external spline (41) have similar cross-sectional shapes and sizes, and the teeth (50) each have similar cross-sectional shapes and sizes.

8. The pressurizing device (30) according to claim 4, characterized in that, The first channel (46) and the second channel (51) are evenly distributed around the longitudinal axis.

9. The pressurizing device (30) according to claim 4, characterized in that, The first shaft segment (9a) includes at least one opening (52) that extends through the walls of the first shaft segment on both sides, the opening (52) being located downstream of the second channel (51) and intended to be open within the first shaft segment (9a).

10. The pressurizing device (30) according to claim 1 or 2, characterized in that, The pressurization device includes a first shaft (9) and a second shaft (10), the first shaft including a first shaft section and a second shaft section (9b), the first shaft (9) extending at least partially within the second shaft, the second shaft (10) including at least one hole (53) passing through the wall of the second shaft on both sides, the hole (53) being intended to be arranged near the downstream housing (20) such that the pressurized airflow exiting one or more of the holes enters the interior of the downstream housing (20).

11. An aircraft turbine (1), the aircraft turbine comprising a propeller (2) rotating about a longitudinal axis X, a gas generator (3) for driving the propeller (2) to rotate, and a pressurizing device (30) for pressurizing a downstream outer shell (20), the pressurizing device being a pressurizing device according to any one of claims 1 to 10.

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