Turbine blade for an aircraft turbomachine provided with a channel for injecting a primary flow into an interlipped cavity

Abstract

The invention relates to a wheel blade (60) and a sealing element (59) forming an assembly for a turbine wheel. The wheel blade (60) comprises a blade (61) and a platform (62) connected to the sealing element (59). An internal channel (80) passes through the platform (62) in order to draw fluid circulating in a main duct (21A) delimited by the platform and inject the fluid thus drawn into a lip intercavity (50A, 51A) delimited by the sealing element (59). The invention makes it possible to reduce the formation and intensity of secondary flows while increasing the sealing.

Description

Technical Field

[0001] This invention relates to the field of turbines for aircraft turbines. Background Technology

[0002] A conventional turbine in an aircraft turbine comprises one or more stages, each stage including a stator and a rotor wheel. The stator includes fixed blades connected to the housing via their radially outer ends, and these fixed blades are circumferentially distributed around the longitudinal central axis of the turbine to form a stator ring. The rotor wheel includes a disk and blades connected to the disk via their radially inner ends, and which are circumferentially distributed around the disk. The stator of a stage is configured such that the fluid flow permeating into the stage (typically including gas from the combustion chamber) is accelerated and deflected by the stator blades along the direction of the rotor wheel blades of that stage, thereby driving the rotor wheel blades of that stage to rotate about the longitudinal central axis.

[0003] Typically, each stator and rotor blade of a turbine comprises a blade and two platforms that radially define a circumferential portion of an annular main duct between them, in which the blade extends. Fluid passing through the turbine flows primarily within this main duct.

[0004] During conventional turbine operation, the interaction between the fluid and the stator and rotor impellers generates vortices on the impeller platforms, thus forming a "secondary" flow.

[0005] To illustrate this phenomenon, Figure 1 shows a portion of two blades 1A and 1B of a turbine stator 1, which are circumferentially adjacent to each other. Figure 1 shows more specifically the radial interior of the blade 2 of each of blades 1A and 1B, as well as the platform 3. Each blade 2 of blades 1A and 1B includes a leading edge 4, a trailing edge 5, a lower surface 6, and an upper surface 7. The platform 3 of each blade 1A and 1B defines a circumferential portion of an annular main channel in the radial interior, in which fluid flows in a direction S1 from the leading edge 4 of blade 2 toward the trailing edge 5 of blade 2.

[0006] Given the typical viscosity of the fluid flowing in the main duct of the turbine, the flow of this fluid along the surface of platform 3 has a velocity gradient GV1, such that the velocity of the fluid layer decreases as it gets closer to the surface. Furthermore, the fluid flowing in the main duct is subject to a pressure gradient GP1, which in this example is oriented from the lower surface 6 of blade 2 of blade 1B toward the upper surface 7 of blade 2 of blade 1A. The pressure gradient GP1 is generally sufficient to deflect the fluid layer flowing near the surface of platform 3.

[0007] This results in the emergence of various types of vortices. The first type of vortex, T1, known as a "horseshoe shape," has a shape with two counter-rotating branches distributed on both sides of the blade 2. The second type of vortex, T2, known as a "channel vortex," forms between two adjacent blades 2. The third type of vortex, T3, known as an "angular vortex," travels along the connection line between the blade 2 and the platform 3 of each impeller.

[0008] The secondary flows T1, T2, and T3 that typically occur at the root and tip of blade 2 are not oriented along the main flow direction S1 of the fluid flowing through the main duct, resulting in reduced turbine efficiency and increased kerosene consumption. Summary of the Invention

[0009] One object of the present invention is to limit the formation of such secondary flows or reduce the intensity of such secondary flows.

[0010] More generally, the present invention aims to improve the performance of the turbine of a turbine.

[0011] Therefore, the object of the present invention is a turbine assembly for a turbine according to the features of claim 1.

[0012] The internal channels allow for the extraction of a portion of the fluid flowing along the first surface of the platform, while preventing this portion of the fluid from promoting the formation of secondary flows.

[0013] Therefore, the present invention enables the restriction of the formation of secondary flows and the reduction of the intensity of secondary flows that can still be generated, thereby improving turbine efficiency and reducing turbine kerosene consumption.

[0014] Given the static pressure difference between the region of the main pipe surrounding at least one suction opening and the region surrounding at least one injection opening, fluid flowing in the main pipe and reaching at least one suction opening is indeed drawn into at least one internal channel.

[0015] Given a general structure of a turbine capable of being equipped with such a component, the area surrounding at least one injection opening is located outside the main duct and has a lower static pressure than the area to which at least one intake opening of the main duct leads.

[0016] Therefore, at least one internal channel forms a passive inhalation system that does not require any additional inhalation device, such as one that utilizes mechanical or electrical controls.

[0017] Therefore, the present invention enables the reduction of the formation and / or intensity of secondary flows while avoiding the loss of mixtures, such as losses due to the direct reintroduction of the drawn fluid into the main pipe.

[0018] Furthermore, the injection of fluid thus drawn into the interlip cavity allows for pressurization of the interlip cavity, thereby reducing the pressure difference between the cavity and the upstream cavity extending upstream of the lip outside the main pipe.

[0019] This results in an overall improvement in sealing, particularly reducing the flow rate of fluid that tends to escape from the main pipe along the direction of the upstream cavity.

[0020] Preferably, the sealing element is annular.

[0021] In one embodiment, the upstream portion of the platform is defined by an imaginary line equidistant from the leading and trailing edges of the blade.

[0022] According to a first alternative embodiment, at least one intake opening is positioned upstream of the leading edge of the blade relative to the flow direction of the fluid in the main duct.

[0023] According to a second alternative embodiment, at least one intake opening is positioned downstream of the leading edge of the blade and upstream of the trailing edge of the blade relative to the flow direction of the fluid in the main duct.

[0024] These alternatives can be combined.

[0025] For example, according to a third alternative embodiment, at least one of the intake openings is positioned upstream of the leading edge of the blade relative to the flow direction of the fluid in the main pipe, and at least another of the intake openings is positioned downstream of the leading edge of the blade and upstream of the trailing edge of the blade relative to the flow direction of the fluid in the main pipe.

[0026] In one embodiment, at least one internal channel comprises a plurality of internal channels that are fluidly independent of each other.

[0027] In another embodiment, at least one internal channel includes a plurality of internal channels fluidly connected to each other.

[0028] At least one internal channel may also include a first internal channel and a series of other internal channels that are fluidly connected to each other and fluidly independent of the first internal channel.

[0029] According to another alternative, at least one internal channel may also include a first series of internal channels that are fluidly independent of each other and a second series of internal channels that are fluidly connected to each other and fluidly independent of the first series of internal channels.

[0030] In one embodiment, at least one intake opening is disposed on the lower surface side of the blade.

[0031] In one embodiment, the component includes the wear-resistant portion and a rotor element that carries the lip of the dynamic sealing joint, the interlip cavity extending longitudinally between two lips and radially between the wear-resistant portion and the rotor element carrying the lip.

[0032] In one embodiment, the blade is designed to be fastened to the turbine housing, and a sealing element forms a wear-resistant portion and is carried by the root of the blade, the wear-resistant portion being designed to mate with a lip carried by the turbine rotor.

[0033] Another object of the present invention is a turbine for a turbine engine, the turbine comprising the components described above.

[0034] Another object of the present invention is a turbine including such a turbine.

[0035] According to another aspect, the object of the present invention is a method for manufacturing the components described above.

[0036] Preferably, the method includes the step of additive manufacturing at least one blade of the component.

[0037] Other advantages and features of the invention will become apparent upon reading the following detailed and non-limiting description. Attached Figure Description

[0038] The following detailed description refers to the accompanying drawings, in which:

[0039] [Figure 1] is a partial perspective view of the stator of a conventional turbine for an aircraft turbine as described above, showing the secondary flow generated during turbine operation;

[0040] [ Figure 2 [This is an axial cross-sectional view of the aircraft's propulsion assembly;]

[0041] [ Figure 3 [This is a partial half-view of the axial section of the low-pressure turbine of the turbine.]

[0042] [ Figure 4 [This is a partial half-view of the axial section of the low-pressure turbine of the turbine.]

[0043] [ Figure 5 [Illustrated diagram of the impeller and sealing element according to the invention, including an internal channel configured to extract jet air and inject jet air into a lip cavity defined by the sealing element;]

[0044] [ Figure 6 [A partial perspective view of the impeller according to the invention, showing the suction opening according to the first embodiment;]

[0045] [ Figure 7[A partial perspective view of the impeller according to the invention, showing the suction opening according to the second embodiment;]

[0046] [ Figure 8 [A partial perspective view of the impeller according to the invention, showing the suction opening according to a third embodiment;]

[0047] [ Figure 9 [Illustration 1] is a partial perspective view of the impeller according to the invention, showing the intake opening according to the fourth embodiment. Detailed Implementation

[0048] The accompanying drawings include reference frames L, R, and C that define the longitudinal (or axial) direction, radial direction, and circumferential direction, respectively, which are orthogonal to each other.

[0049] Figure 2 The aircraft propulsion assembly 10 is shown, including a turbine 11 that reduces drag via a nacelle 12. In this example, the turbine 11 is a dual-flow, twin-shaft turbojet engine.

[0050] In the following text, the terms "upstream" and "downstream" are defined relative to the flow direction S1 of the gas through the propulsion assembly 10 when the propulsion assembly 10 is propelled.

[0051] The turbojet engine 11 has a longitudinal central axis A1 around which its various components extend. In this case, the turbojet engine has a fan 13, a low-pressure compressor 14, a high-pressure compressor 15, a combustion chamber 16, a high-pressure turbine 17, and a low-pressure turbine 18 from upstream to downstream. The compressors 14 and 15, the combustion chamber 16, and the turbines 17 and 18 form a gas generator.

[0052] During operation of the turbojet engine 11, airflow 20 enters the propulsion assembly 10 through an air intake upstream of the nacelle 12, passes through the fan 13, and is then split into a central main flow 20A and a bypass flow 20B. Main flow 20A flows in a main duct 21A to allow gas to pass through the gas generator. The bypass flow 20B flows in a bypass duct 21B that surrounds the gas generator and extends radially outward from the nacelle 12.

[0053] In one embodiment, the low-pressure turbine 18 is referred to below. Figure 3 The above, Figure 3 A turbine 18 is shown based on a radial plane including the longitudinal central axis A1.

[0054] The longitudinal central axis A1 corresponds to the rotation axis of the rotor of the turbine 18.

[0055] In this example, the turbine 18 comprises four stages, each stage including a stator 25 and a rotor wheel 26.

[0056] In a manner known per se, the rotor wheels 26 are axially assembled with each other via annular flanges 27 to form the rotor of the turbine 18. As for the stators 25, these stators are connected to the housing 28 to form the stator of the turbine 18.

[0057] Each stator 25 includes a plurality of blades 30 circumferentially distributed around axis A1. Referring to the stator 25 of the last stage of the turbine 18, in... Figure 3 Only one blade 30 of the stator is visible in the image. Each blade 30 includes a blade 31, an inner platform 32, and an outer platform 33. Each blade 30 is connected to the housing 28 by a hook element rigidly connected to its outer platform 33.

[0058] Each rotor wheel 26 includes a disk 35 and a plurality of blades 36 circumferentially distributed around axis A1. Referring to the rotor wheel 26 of the last stage of turbine 18, in... Figure 3 Only one blade 36 of the rotor wheel is visible in the image. Each blade 36 includes a blade 37, an inner platform 38, and an outer platform 39. Each blade 36 is rigidly connected to the disk 35 at the root of its inner platform 38.

[0059] For each blade 30 of the stator 25, platforms 32 and 33 each include a first surface from which blade 31 extends, and the first surface defines a circumferential portion of the main duct 21A through which the main flow 20A passes. Thus, the first surface of the inner platform 32 of each blade 30 defines the main duct 21A radially inward, while the first surface of the outer platform 33 of each blade 30 defines the main duct 21A radially outward.

[0060] Similarly, for each blade 36 of the rotor wheel 26, platforms 38 and 39 each include a first surface from which blade 37 extends and defines a circumferential portion of the main conduit 21A. Thus, the first surface of the inner platform 38 of each blade 36 defines the main conduit 21A radially inward, while the first surface of the outer platform 39 of each blade 36 defines the main conduit 21A radially outward.

[0061] Therefore, in Figure 3 In turbine 18, the main pipe 21A is generally annular.

[0062] In another exemplary embodiment, the low-pressure turbine 18 is referred to below. Figure 4 As stated above.

[0063] Figure 4 It shows the relationship with Figure 3 Part of the same type of turbine 18, which includes stator 25 and rotor wheel 26 belonging to the same stage as stator 25 (in Figure 4 (on the right side) and the lower-level rotor wheel 26 (in) Figure 4Centered on the left side.

[0064] exist Figure 4 In the example, turbine 18 includes a dynamic sealing joint 40 that enables the restriction of gas flow radially downwards from stator 25.

[0065] In a manner known per se, the connector 40 includes two sealing elements, one forming an abrasion-resistant portion 41 and the other forming a lip 42.

[0066] In this example, the wear-resistant part 41 is an annular part that is connected to the inner platform 32 of the blade 30 of the stator 25, such that the wear-resistant part 41 and the blade 30 are constrained to rotate together about the axis A1.

[0067] In this example, the sealing element forming the lip 42 includes a sealing portion 44 that carries the lip and is supported by an annular shield 43 that is constrained to rotate together with the rotor wheel 26 about axis A1.

[0068] The connector 40 forms a cavity 50A between the lips, which extends longitudinally between the lips 42 and is radially defined by the wear-resistant portion 41 on one side and the sealing portion 44 on the other.

[0069] Figure 4 The turbine 18 also includes a dynamic sealing joint 45, which enables the restriction of gas flow in the radial direction above the rotor wheel 26.

[0070] Similar to connector 40, each connector 45 includes two sealing elements, one forming a wear-resistant portion 46 and the other forming a lip 47.

[0071] In this example, the wear-resistant portion 46 of each joint 45 is fixedly connected to the housing 28, while the lip 47 is formed on the outer platform 39 of the blade 36 of the rotor wheel 26, such that the lip 47 and the rotor wheel 26 are constrained to rotate together about the axis A1.

[0072] For each connector 45, the connector 45 forms an interlip cavity 51A that extends longitudinally between the lips 47 of the connector 45 and is radially defined on the one hand by the wear-resistant portion 46 of the connector 45 and on the other hand by a portion of the outer platform 39 of the impeller 36 that is connected to the lip 47.

[0073] Figure 3 The turbine 18 also includes the same type of dynamic sealing joints 40 and 45, which enable the flow of gas to be restricted radially below the stator 25 and radially above the rotor wheel 26, respectively.

[0074] Therefore, these dynamic sealing joints 40 and 45 limit, but do not completely prevent, any flow of gas outside the main pipe 21A, especially taking into account the clearance caused by thermal expansion and the relative movement of the various fixed and movable parts of the turbine 18.

[0075] Therefore, a portion of the mainstream 20A generates bypass flow 20C, such as Figure 3 As illustrated in the diagram.

[0076] This bypass flow passes more precisely through the cavities, which in this example include... Figure 4 The cavities marked in the middle are 50B, 50C, 51B and 51C.

[0077] Cavities 50B, 50C, 51B and 51C extend radially outside the main pipe 21A on both sides of joints 40 and 45, and cavities 50B, 50C, 51B and 51C are fluidly connected to the main pipe 21A through an opening or clearance between rotor wheel 26 and stator 25.

[0078] In this example, cavity 50B is radially defined outward by the internal platform 32 of the stator 25 blades 30 and axially defined downstream by the dynamic sealing joint 40. Cavity 50C is also radially defined outward by the internal platform 32 of the stator 25 blades 30 and axially defined upstream by the dynamic sealing joint 40.

[0079] Based on the relative axial positions of cavities 50B and 50C with respect to connector 40, the cavities are referred to as the "upstream cavity" and the "downstream cavity," respectively.

[0080] In a similar manner, each joint 45 axially defines an upstream cavity 51B and a downstream cavity 51C, each defined radially inward from the outer platform 39 of the blade 36 of the corresponding rotor wheel 26.

[0081] The upstream cavity 50B is fluidly connected to the main pipe 21A through an annular opening that extends axially and / or radially between the downstream end 54A of the inner platform 36 of the rotor wheel 26 located upstream of the stator 25 and the upstream end 55A of the inner platform 32 of the rotor wheel 26 located upstream of the stator 25.

[0082] The downstream cavity 50C is fluidly connected to the main pipe 21A through an annular opening that extends axially and / or radially between the downstream end 55B of the inner platform 32 of the blade 30 of the stator 25 and the upstream end 54B of the inner platform 38 of the blade 36 of the rotor wheel 26 located downstream of the stator 25.

[0083] Cavities 51B and 51C are also fluidly connected to main pipe 21A in a similar manner (see...). Figure 4).

[0084] Figure 5 A portion of the sealing element 59 and the impeller 60 forming the assembly according to the invention is shown schematically.

[0085] The impeller 60 includes blades 61 and platform 62.

[0086] Platform 62 includes a root 62A that extends radially from platform 62 on the side opposite to blade 61.

[0087] The sealing element 59 is connected to the root 62A of the platform 62, for example, by brazing or welding.

[0088] In this non-limiting example, blade 60 corresponds to Figure 3 or Figure 4 One of the stator 25 of the turbine 18 has one of the blades 30, such that the platform 62 of the blade 60 corresponds to the inner platform 32 of the blade 30. In this example, the sealing element 59 includes a wear-resistant portion 41 of the connector 40 extending radially below the stator 25. Figure 5 In the diagram, element 59 schematically shows the wear-resistant part and its support.

[0089] The blade 61 of the whorl 60 includes a leading edge 63, a trailing edge 64, a lower surface (not visible), and an upper surface 66.

[0090] The platform 62 of the blade 60 includes a first surface 71 and a second surface 72 that are radially opposite each other.

[0091] Platform 62 includes upstream end 73 and downstream end 74.

[0092] exist Figure 5 In the simplified diagram, the first surface 71 and the second surface 72 are parallel to each other and parallel to the longitudinal direction L. Of course, each of these surfaces can have a different geometry and be oriented generally according to the direction of inclination relative to the longitudinal direction L and the radial direction R, as shown... Figure 4 The platform 32 is the same as the 30-blade wheel.

[0093] Figure 5 An imaginary line LL1 is shown, equidistant from the leading edge 63 and trailing edge 64 of blade 61.

[0094] exist Figure 5 In the simplified diagram, leading edge 63 and trailing edge 64 are straight lines and parallel to each other. Of course, each of these edges can have a non-linear geometry and be oriented overall according to a direction inclined relative to the radial direction R, as... Figure 4 The leading edge of the blade 31 of the impeller 30 is the same. Therefore, the imaginary line LL1 is not necessarily straight.

[0095] The imaginary line LL1 defines the upstream portion P1 and the downstream portion P2 of platform 62.

[0096] When the impeller 60 is set Figure 3 or Figure 4 When the stator 25 of the turbine 18 is in one of the platforms 62, the first surface 71 of the platform 62 defines the main duct 21A radially inward, and the flow direction S1 of the main duct 20A is guided from the leading edge 63 of the blade 61 toward the trailing edge 64 of the blade 61 and from the upstream portion P1 of the platform 62 toward the downstream portion P2 of the platform 62.

[0097] Under these conditions, the second surface 72 of the upstream portion P1 of platform 62 radially defines the upstream cavity 50B, the second surface 72 of the downstream portion P2 of platform 62 radially defines the downstream cavity 50C, and the sealing element 59 forms a surface 59A that radially defines the interlip cavity 50A.

[0098] Platform 62 includes an internal channel 80 having an intake opening 81 leading to a first surface 71 of the upstream portion P1 of platform 62 and an injection opening 82 leading to a surface 59A formed by sealing element 59. Thus, the internal channel 80 passes through platform 62, root 62A and sealing element 59.

[0099] In this example, the intake opening 81 of the internal channel 80 is more precisely opened upstream of the leading edge 63 of the blade 61.

[0100] As mentioned above, in this example, Figure 5 Element 59 represents the wear-resistant part and its support. Therefore, in this example, surface 59A is formed by the wear-resistant part, and each part of the internal channel 80 is formed by the wear-resistant part on one hand and by the support of the wear-resistant part on the other.

[0101] Alternatively, Figure 5 Element 59 may simply represent a support ring for the wear-resistant portion, in which case surface 59A is formed by the support ring. The wear-resistant portion may include units forming a honeycomb structure such that the injection opening 82 opens onto one or more of these units, which thus form extensions of the internal channel 80 to fluidly connect the internal channel 80 to the interlip cavity 50A. The wear-resistant portion having a honeycomb structure or any other structure may be locally machined to improve or establish this fluid connection between the channel and the interlip cavity 50A.

[0102] The present invention covers any geometry of the internal channel 80, as well as the suction opening 81 and the injection opening 82, provided that the internal channel 80 is capable of drawing a portion of the main stream 20A from the main channel 21A and injecting that portion of the main stream 20A into the lip cavity 50A under the action of the static pressure difference between the main channel 21A and the lip cavity 50A.

[0103] This invention is not in any way limited to the examples shown in the accompanying drawings.

[0104] For example, in an embodiment not shown, platform 62 includes one or more internal channels that are fluid-independent of internal channel 80 or other internal channels that are fluid-connected to internal channel 80.

[0105] Regardless of the number and geometry of the internal channels 80, the internal channels 80 may include one or more intake openings 81 and one or more injection openings 82.

[0106] Figures 6 to 9 Various types of intake openings 81 are shown, in which, in these examples, these intake openings 81 all lead downstream of the first surface 71 of the platform 62, axially close to the leading edge 63 of the blade 61.

[0107] exist Figure 6 In one example, platform 62 includes an internal channel 80 with seventeen intake openings 81 having a circular cross-section, for example, obtained by perforation or additive manufacturing.

[0108] exist Figure 7 In the example, platform 62 includes an internal channel 80 with a single suction opening 81, which is in the form of a groove extending in the circumferential direction C.

[0109] exist Figure 8 In the example, platform 62 includes an internal channel 80 with two intake openings 81 that are in the form of grooves extending in the direction of curvature to extend along the lower surface of blade 61.

[0110] exist Figure 9 In the example, platform 62 includes an internal channel 80 with a single suction opening 81 corresponding to Figure 8 One of the grooves.

[0111] Typically, the geometry of one or more suction openings 81 is chosen to reduce head loss during suction and increase the total pressure of the drawn flow.

[0112] to this end, Figures 6 to 9 One or more suction openings 81 shown lead directly to the main pipe 21A without the need for deflectors, fins or other obstructions, nor do they protrude into the main pipe 21A as in a bucket system.

[0113] When there are multiple suction openings 81, such as Figure 6 As in the example, the opening 81 is preferably circular to reduce the wetting of the surface, thereby reducing friction with the air.

[0114] When the suction opening 81 is formed as follows Figures 7 to 9 When the mouth portion is shown, the opening 81 preferably forms a nozzle, which may optionally extend over the entire available width between adjacent blades 61 (see, for example, [link to previous text]). Figure 7 This nozzle can be formed at an acute angle or have a geometry capable of generating vortices that can increase the total pressure of the fluid at the inlet of the internal channel 80 by using viscosity to draw in air from outside the boundary layer.

[0115] Regarding the geometry of the internal channel 80, the internal channel 80 should have a circular or oval cross-section, with no breaks or obstructions on the surface, in order to reduce the wetted surface and head loss in contact with the flow.

[0116] When the cross-section of the jet opening 82 is smaller than the cross-section of the suction opening 81, the internal channel 80 should have a progressively narrowed cross-section to maintain the lowest possible Mach number and thus reduce head loss.

[0117] These different aspects enable an increase in the flow rate of air drawn in by one or more internal channels 80, thereby reducing the thickness of the boundary layer downstream of one or more intake openings 81. This results in a further reduction in secondary flow and associated losses.

[0118] Furthermore, the increased airflow into the cavity between the lips improves the sealing of the joint that forms the cavity.

[0119] The above-described contents may be implemented for each of the blades 30 of one or more stators 25 of the turbine 18, or only for a portion of those blades 30.

[0120] Furthermore, by analogy, what was just described applies to the blades 36 of the rotor wheel 26 of the turbine 18. Therefore, in one embodiment, one or more blades 36 of one or more rotor wheels 26 of the turbine 18 include... Figure 5 The blades of the whorl 60 are similar to those of the blade 61, and are... Figure 5 The platform 62 of the impeller 60 is similar to an external platform, and the lip connected to the platform 62 enables at least one internal channel 80 to draw a portion of the main stream 20A in the main pipe 21A and spray that portion of the main stream 20A into the corresponding interlip cavity 51A.

[0121] This invention can also be applied to the high-pressure turbine 17 and Figure 2The turbojet engine 11 is implemented in the turbine of different turbines.

Claims

1. An assembly for a turbine (17, 18) of a turbine (11) extending about a longitudinal axis (A1), the assembly comprising at least one blade (60) and a sealing element (59) forming a wear-resistant portion (41) or lip (47) of a dynamic sealing joint (40, 45), the blade (60) comprising a platform (62) and blades (61) extending from the platform (62), the platform (62) forming a first surface (71), the blades (61) extending from the first surface. The first surface is intended to define a main conduit (21A) extending therein from the blade (61) to receive fluid flowing in a direction (S1) from the leading edge (63) of the blade (61) toward the trailing edge (64) of the blade and from the upstream portion (P1) of the platform (62) toward the downstream portion (P2) of the platform, the sealing element (59) being connected to the platform (62) and forming a second surface (59A) intended to define an interlip cavity (50A, 51A), characterized in that, The component includes at least one internal channel (80) passing through the platform (62) and having at least one intake opening (81) and at least one injection opening (82). The at least one intake opening leads to a first surface (71) of an upstream portion (P1) of the platform (62), and the at least one injection opening leads to a second surface (59A). The impeller (60) includes a root (62A) between the platform (62) and the sealing element (59). The internal channel (80) passes through the platform (62), the root (62A), and the sealing element (59). The at least one suction opening (81) is positioned upstream of the leading edge (63) of the blade (61) relative to the flow direction (S1) of the fluid in the main pipe (21A).

2. The component according to claim 1, wherein, The sealing element (59) is annular.

3. The component according to claim 1 or 2, wherein, The upstream portion (P1) of the platform (62) is defined by an imaginary line (LL1) that is equidistant from the leading edge (63) and trailing edge (64) of the blade (61).

4. The component according to claim 1 or 2, wherein, - The at least one suction opening (81) is positioned downstream of the leading edge (63) of the blade (61) and upstream of the trailing edge (64) of the blade (61) relative to the flow direction (S1) of the fluid in the main pipe (21A).

5. The component according to claim 1 or 2, wherein, The at least one internal channel (80) includes a plurality of fluidly independent internal channels and / or a plurality of internal channels fluidly connected to each other.

6. The component according to claim 1 or 2, wherein, The at least one intake opening (81) is provided on the lower surface side of the blade (61).

7. The component according to claim 1 or 2, wherein, The assembly includes the wear-resistant portion (41, 46) and rotor elements (44, 39), the rotor elements carrying the lips (42, 47) of the dynamic sealing joint (40, 45), the interlip cavity (50A, 51A) extending longitudinally between the two lips in the lips (42, 47) and radially between the wear-resistant portion (41, 46) and the rotor elements (44, 39) carrying the lips (42, 47).

8. The component according to claim 1 or 2, wherein, The blade (60) is intended to be fastened to the housing of the turbine (11), and the sealing element (59) forms a wear-resistant portion (41) and is carried by the root of the blade (60), the wear-resistant portion (41) being intended to mate with a lip (47) carried by the rotor of the turbine (11).

9. A turbine (17, 18) for a turbine (11), the turbine comprising components according to any one of claims 1 to 8.

10. A turbine (11), the turbine comprising the turbine (17, 18) according to claim 9.

11. A method for manufacturing a component according to any one of claims 1 to 8, the method comprising the step of additive manufacturing at least one blade (60) of the component.

Images