Movable blades for a wheel of a turbine engine

Abstract

A movable blade (1) for a wheel (2) of an aircraft turbine engine is disclosed, the blade (1) comprising a blade (4) delimited by an outer heel (8), the outer heel comprising a first sealing portion (14), the blade (1) comprising an internal circuit (16) suitable for receiving a first micro gas flow (f1), the circuit (16) comprising a supply cavity (17) opening at the root (9) through at least one inlet opening (18), characterised in that the circuit (16) comprises at least two ducts (19), the at least two ducts being connected to the supply cavity (17) and each leading to the outer surface of the first sealing portion (14) through a discharge opening, so that a gas jet (J) of the first micro gas flow (f1) can be discharged from each discharge opening, each duct (19) being oriented so that a corresponding gas jet (J) can be ejected towards a second micro gas flow (f2) leaking between the heel (8) and a directly adjacent component (22).

Description

Technical Field

[0001] The invention relates to the general field of movable blades of a wheel portion of an aircraft turbine engine. Background Art

[0002] Typically, the axial turbine of a turbine engine comprises a series of axial stages arranged in succession. Each turbine stage comprises an impeller with blades forming a rotor and a turbine stator with blades forming a stator. The wheel portion rotates relative to the corresponding turbine stator. Each turbine stator is attached to an outer casing surrounding the wheel portion.

[0003] The wheel portion comprises an annular disk rotatable about an axis X and a plurality of blades attached to the disk.

[0004] The movable blade comprises an aerodynamic blade extending along a stacking axis Z. The blade of the blade is delimited along the stacking axis Z by an inner root and an outer heel.

[0005] The outer heels of the movable blades 1 of the same wheel part are arranged flanking (or edge-to-edge) one another to define externally a channel through which the main gas flow circulates.

[0006] In order to optimize the efficiency of a turbine (more generally, of a turbine engine), it is necessary to maximize the amount of gas acting on the blades, in other words to minimize the leakage that exists mainly between the heel and the outer casing and between two adjacent heels.

[0007] In order to limit leakage between the heel and the outer casing, it is known to implant at least one (for example two) lip on the heel of each blade, which protrudes towards the outside from the platform of the heel. The lip is intended to cooperate with a block made of wear-resistant material (for example a honeycomb structure) fixed to the outer casing, so as to form a dynamic sealing joint of the labyrinth type. However, such a joint does not guarantee a complete seal between the heel and the block made of wear-resistant material.

[0008] In order to limit the leakage between two adjacent heels, the gap between the two adjacent heels is usually limited. However, it should be noted that the gap between the two heels varies according to the operating speed of the turbine engine, so the sealing may be guaranteed at one operating speed and no longer guaranteed at another operating speed.

[0009] In order to maximize efficiency, engine manufacturers therefore constantly seek to minimize leakage between the heel and the block made of wear-resistant material and between two adjacent heels.

[0010] It is therefore an object of the present invention to provide a simple, effective and economical solution to the above problems.

[0011] The prior art also includes documents US-A1-2018 / 355742 and US-A1-2007 / 134096. Summary of the invention

[0012] The invention therefore proposes a movable blade for a wheel of an aircraft turbine engine, the blade comprising an aerodynamic blade extending along a stacking axis Z, the blade being delimited along the stacking axis Z by an inner root and an outer heel, the heel comprising at least a first protruding lip intended to cooperate with a block made of wear-resistant material, the blade comprising an internal circuit capable of receiving a first microgas flow, the circuit comprising a supply cavity opening at the root through at least one inlet opening, characterised in that the circuit comprises at least two ducts connected to the supply cavity and each leading through a discharge opening to the outer surface of the first lip, so that a gas jet of the first microgas flow is suitable for being discharged from each discharge opening, each duct being oriented so that a corresponding gas jet is suitable for being ejected towards a second microgas flow leaking between the heel and a directly adjacent component.

[0013] Therefore, the gas jet (first micro-stream) hinders the second micro-gas stream, more precisely, the gas jet shears the second micro-gas stream to reduce the flow rate of the second micro-gas stream, thereby reducing leakage between the heel portion and the directly adjacent member.

[0014] This reduction in the flow rate of the second micro gas flow maximizes the efficiency of the turbine engine.

[0015] The directly adjacent component corresponds, for example, to a block made of wear-resistant material or to the heel of a directly adjacent blade.

[0016] The blade according to the invention may include one or more of the following features, taken alone or in combination with each other:

[0017] - The discharge opening is arranged in one of the following alternative ways:

[0018] - two discharge openings are arranged on the outer face of the first lip;

[0019] - two discharge openings are arranged on the sides of the first lip;

[0020] - one of the two discharge openings is arranged on the outer face of the first lip, and the other of the two discharge openings is arranged on the side of the first lip;

[0021] - the circuit comprises a first row of at least three ducts connected to the supply cavity and each opening through a discharge opening to the outer surface of the first lip;

[0022] the circuit comprises a second row of ducts, the second row comprising: at least three ducts connected to the supply cavity and each opening through a discharge opening to the outer surface of the first lip, the discharge openings of the ducts of the first row being offset relative to the discharge openings of the ducts of the second row;

[0023] - at least one of the ducts has a variable cross-section tapering towards the corresponding discharge opening;

[0024] - the supply cavity is suitable for receiving a first micro gas flow escaping from a channel via at least an inlet opening, the channel being suitable for receiving a main gas flow;

[0025] - Each discharge opening is circular;

[0026] - the diameter of the discharge opening of each conduit is between 0.2 mm and 2 mm, preferably between 0.3 mm and 0.6 mm;

[0027] - the heel comprises a second lip which projects away from the first lip;

[0028] - The circuit comprises at least two ducts connected to the supply cavity and each leading to the outer surface of the second lip through a discharge opening, so that a gas jet of the first micro gas flow is suitable for being discharged from each discharge opening, each duct being oriented so that the corresponding gas jet is suitable for being ejected towards the second micro gas flow leaking between the heel and the directly adjacent component.

[0029] The invention further relates to a wheel portion for an aircraft turbine engine, comprising a disk supporting, at its periphery, an annular array of blades as described above.

[0030] The invention also relates to an aircraft turbine engine comprising a blade as described above or a wheel as described above. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] The invention will be better understood and other details, features and advantages of the invention will become more apparent on reading the following description given by way of non-limiting example and with reference to the accompanying drawings, in which:

[0032] [ Figure 1 ] Figure 1 is a front view of a blade according to a first embodiment of the present invention;

[0033] [ Figure 2 ] Figure 2 is a partial front view of a blade according to a second embodiment of the present invention;

[0034] [ Figure 3 ] Figure 3is a schematic partial top view of a paddle showing a first example of an arrangement of discharge openings on the lip;

[0035] [ Figure 4 ] Figure 4 yes Figure 3 A schematic partial front view of the blade shown in ;

[0036] [ Figure 5 ] Figure 5 is a schematic partial front view of a paddle showing a second example of arrangement of the discharge openings on the lip;

[0037] [ Figure 6 ] Figure 6 yes Figure 5 A schematic partial top view of a paddle shown in ;

[0038] [ Figure 7 ] Figure 7 is a schematic partial top view of a paddle showing a third example of an arrangement of discharge openings on the lip;

[0039] [ Figure 8 ] Figure 8 yes Figure 7 A schematic partial front view of the blade shown in ;

[0040] [ Fig. 9 ] Fig. 9 is a schematic partial top view of a paddle showing a first example of an arrangement of a row of discharge openings on the lip;

[0041] [ Fig.10 ] Fig.10 is a schematic partial side view of a paddle showing a second example of an arrangement of a row of discharge openings on the lip;

[0042] [ Fig.11 ] Fig.11 is a schematic partial top view of a paddle showing an example of the arrangement of first and second rows of discharge openings on the lip;

[0043] [ Fig.12 ] Fig.12 is a schematic partial top view of a paddle showing a first alternative embodiment of a conduit;

[0044] [ Fig.12 ] Fig.13 is a schematic partial front elevational view of a paddle showing a second alternative embodiment of the duct;

[0045] [ Fig.14 ] Fig.14 is a schematic partial front view of a paddle showing an example of the orientation of the duct. DETAILED DESCRIPTION

[0046] Figure 1 Shown is a blade 1 of a wheel 2 of an aircraft turbine engine 3, more precisely of a turbine of a turbine engine 3. The blade 1 may be intended to be mounted to a wheel of a compressor of the turbine engine.

[0047] The blade 1 comprises an aerodynamic blade 4 extending along a stacking axis Z. The blade 4 has a pressure side 5 and a suction side connected to each other by a leading edge 6 and a trailing edge 7. A primary gas flow F flows around the blade 4 from the leading edge 6 to the trailing edge 7, so that in the flow direction of the primary gas flow F the leading edge 6 is located upstream of the trailing edge 7.

[0048] In a transverse plane (a plane perpendicular to the stacking axis Z), the blade 4 is shaped along a bisector connecting the leading edge 6 to the trailing edge 7, which bisector divides the blade 1 into a pressure side and a suction side. The pressure and suction sides 5 are curved and are concave and convex respectively.

[0049] In the present application, the terms "pressure side" and "suction side" in connection with different elements of the blade refer to the pressure side and the suction side.

[0050] In the present application, the terms “upstream” and “downstream” are defined relative to the flow direction of the main gas flow F.

[0051] The blade 1 further comprises an outer heel 8 and an inner root 9 which delimit the blade 4 along the stacking axis Z. More precisely, the blade 4 is delimited by an inner platform 10 of the root 9 and an outer platform 11 of the heel 8 .

[0052] The wheel 2 comprises a disk 12 which supports, at its periphery, an annular array of blades 1. More precisely, each root 9 comprises, for example, a bulb configured to engage in a complementary pocket formed in the disk 12. The wheel 2 (respectively, the blade) can rotate about an axis of rotation X coaxial with the longitudinal axis of the turbine engine 3. The wheel 2 can rotate about the axis X from the pressure side to the suction side.

[0053] In the present application, the terms "inner" and "outer" are defined relative to the axis of rotation X of the wheel (or blade).

[0054] The outer platforms 11 of the movable blades 1 of the same wheel part 2 are arranged to flank each other (or edge to edge) to define a channel 13 externally, in which the main gas flow F flows. Similarly, the inner platforms 10 of the movable blades 1 of the same wheel part 2 are arranged to flank each other (or edge to edge) to define a channel 13 internally, in which the main gas flow F flows.

[0055] The heel 8 of the blade 1 comprises at least one protruding lip 14 (first lip) intended to cooperate with a block made of abrasion-resistant material 15. The blade 1 also comprises an internal circuit 16 capable of receiving a first micro gas flow f1, comprising a supply cavity 17 opening at the root 9 through at least one inlet opening 18.

[0056] According to the invention, the circuit 16 comprises at least two ducts 19 connected to the supply cavity 17 and each leading to the outer surface 20 of the lip 14 through a discharge opening 21, so that the gas jet J of the first micro gas flow f1 can be discharged from each discharge opening 21. Each duct 19 is oriented so that the corresponding gas jet J is suitable for spraying towards the second micro gas flow f2 (the second micro gas flow leaks from between the heel 8 and the directly adjacent member 22).

[0057] In the present application, the term "inner" in relation to an element of the blade means that the element is arranged inside the blade. Conversely, the term "outer" in relation to an element of the blade means that the element is arranged outside the blade.

[0058] The first micro gas flow f1 corresponds to the flow escaping from the channel 13 at the inner platform 10 and entering the supply cavity 17 of the circuit 16 via the inlet opening 18. Due to the rotation of the blade 1 about the axis X, the first micro flow f1 once inside the circuit 16 flows from the root 9 to the heel 8.

[0059] The second micro gas flow f2 corresponds to a flow that escapes from the channel 13 at the outer platform 11 and leaks between the heel 8 and the directly adjacent member 22 (e.g., a block made of wear-resistant material 15) or the heel 8 of the directly adjacent blade 23. The second micro flow f2 flows from upstream to downstream, and this flow direction is caused by the pressure difference between upstream and downstream.

[0060] The blade 1 comprises at least one lip 14, and may of course comprise more than one lip, for example two lips (e.g. Figure 2 1 ). One lip 14 projects towards the outside from the outer platform 11. The lip 14 is intended to cooperate with a block made of a wear-resistant material 15 (for example a honeycomb structure), attached to an outer casing 25 surrounding the wheel 2, to form a labyrinth-type joint seal. The lip 14 may be straight and therefore extend along the stacking axis Z. One lip 14 may be inclined at an acute angle relative to the stacking axis Z (advantageously inclined upstream). At least one lip is arranged with a duct, while the other lips may or may not be arranged with a duct.

[0061] The circuit 16 may include two conduits 19 for each lip 14, the discharge openings 21 of the two conduits being arranged on the outer face 26 of the lip 14. In this configuration, the gas jet J from the discharge opening 21 is ejected toward the second micro gas flow f2 (which leaks from between the heel 8 and the block made of the wear-resistant material 15). Therefore, the gas jet J (first micro flow) hinders the second micro gas flow f2 (the jet shears the second micro flow) to reduce the flow rate of the second micro gas flow, thereby reducing the leakage between the heel 8 and the block made of the wear-resistant material 15.

[0062] For each lip 14, the circuit 16 may include two ducts 19, the discharge openings 21 of which are arranged on the sides 27 of the lip 14. The sides 27 include an upstream side 28 (hereinafter referred to as the upstream face), a downstream side 29 (hereinafter referred to as the downstream face), a pressure side side 30 (hereinafter referred to as the pressure side) and a suction side side 31 (hereinafter referred to as the suction side).

[0063] When the discharge opening 21 is arranged on the upstream face 28 (or the downstream face 29), the gas jet J from the discharge opening 21 is ejected toward the second micro gas flow f2 leaking from between the heel 8 and the block made of the wear-resistant material 15. This gas jet J (first micro flow) hinders the second micro gas flow f2 (the jet shears the second micro flow) to reduce the flow rate of the second micro gas flow, thereby reducing the leakage between the heel 8 and the block made of the wear-resistant material 15.

[0064] When the discharge opening 21 is arranged on the pressure side 30 (or the suction side 31), the gas jet J from the discharge opening 21 is ejected toward the second micro gas flow f2 leaking from between the heel 8 and the heel 8 of the directly adjacent blade 23. This gas jet J (first micro flow) hinders the second micro gas flow f2 (the jet shears the second micro flow) to reduce the flow rate of the second micro gas flow, thereby reducing the leakage between the two adjacent heels 8.

[0065] For each lip 14 , the circuit 16 may comprise two ducts 19 , wherein one of the two discharge openings 21 of the two ducts is arranged on the outer face 26 of the lip 14 and the other of the two discharge openings 21 is arranged at a side face 27 of the lip 14 .

[0066] Of course, the circuit 16 may comprise, for each lip 14 , more than two ducts 19 , the discharge openings 21 of which are each arranged on the outer surface 20 of the lip 14 .

[0067] For each lip 14 , the circuit 16 may comprise a first row 32 of at least three ducts 19 connected to the supply cavity 17 and each opening through a discharge opening 21 to the outer surface 20 of the lip 14 .

[0068] In the present application, a row comprises at least three conduits. Within a row, the spacing between two discharge openings may be constant or variable.

[0069] For each lip 14 , the circuit 16 may comprise a second row 33 of at least three ducts 19 connected to the supply cavity 17 and each opening through a discharge opening 21 to the outer surface 20 of the lip 14 .

[0070] The discharge openings 21 of the tubes 19 of the first row 32 may be offset relative to the discharge openings 21 of the tubes 19 of the second row 33 .

[0071] Of course, for each lip, the circuit 16 may comprise more than two rows of at least three ducts (ie more than two rows, each row having at least three ducts). The spacing between two consecutive rows may be constant or variable.

[0072] From the inner end to the corresponding discharge opening 21, the duct 19 extends (or is defined) along an extension axis A. The duct 19 along its extension axis A may have a constant cross section.

[0073] The duct 19 may have a variable cross section along its extension axis A. Advantageously, the duct 19 has a variable cross section tapering towards the discharge opening 21 of the duct to increase the speed of the corresponding gas jet J, thereby intensifying the flow velocity reduction of the second micro gas flow F2.

[0074] By way of example, the cross-section of the conduit 19 (respectively, the discharge opening) may be circular, rectangular, etc.

[0075] Advantageously, when the discharge opening 21 is circular, the diameter of the opening 21 is between 0.2 mm and 2 mm, preferably between 0.3 mm and 0.6 mm.

[0076] Regardless of the shape of the discharge opening 21 , the maximum dimension of the discharge opening 21 is between 0.2 mm and 2 mm.

[0077] The shape of the discharge opening may be different from the shape of the rest of the conduit.

[0078] The duct 19 (or the extension axis A of the duct) may be straight in a longitudinal plane, extending substantially along the stacking axis Z.

[0079] The duct 19 (or its extension axis A) may be inclined in the longitudinal plane at an acute angle α relative to the stacking axis Z. Advantageously, the duct 19 is inclined upstream so that the direction of the gas jet J (first microstream) is opposite to the flow direction of the second microstream f2.

[0080] The ducts of the blade 1 may have the same geometrical characteristics (shape, orientation, etc.) and dimensional characteristics. Conversely, each duct may also have specific geometrical characteristics and dimensional characteristics, depending on the importance of leakage.

[0081] The cavity 17 of the circuit 16 of the blade 1 is supplied (first micro gas flow) by at least one inlet opening 18 arranged at the root 9 of the blade 1. Advantageously, the cavity 17 has large dimensions to minimize pressure losses. A duct 19 is connected to the cavity 17 directly or indirectly.

[0082] According to Figure 1 In the first embodiment shown in FIG. 1 , the blade 1 comprises a single intermediate lip 14. The circuit 16 comprises a cavity 17 extending along the stacking axis Z. The circuit 16 comprises two ducts 19 whose two discharge openings 21 are arranged on the outer face 26 of the lip 14. The two ducts 19 are here directly connected to the cavity 17.

[0083] According to Figure 2 In the second embodiment shown in FIG. 1 , the blade 1 comprises an upstream lip 14 and a downstream lip 14. The circuit 16 comprises two upstream ducts 19, the two discharge openings 21 of which are arranged on the outer face 26 of the upstream lip 14, and two downstream ducts 19, the two discharge openings 21 of which are arranged on the outer face 26 of the downstream lip 14. The ducts 19 are here indirectly connected to the cavity 17, namely through an intermediate channel 34.

[0084] The upstream lip or the downstream lip may be free of a duct (respectively, a discharge opening).

[0085] Figure 3 and Figure 4 A first example of an arrangement of the discharge openings 21 on the lip 14 is shown, in which example two discharge openings 21 are arranged on the outer face 26 of the lip 14 .

[0086] Figure 5 and Figure 6 A second example of an arrangement of the discharge openings 21 on the lip 14 is shown, wherein two discharge openings 21 are arranged on the pressure side 30 of the lip 14 .

[0087] Figure 7 and Figure 8A third example of an arrangement of the discharge openings 21 on the lip 14 is shown, wherein one discharge opening 21 is arranged on the outer face 26 of the lip 14 and one discharge opening 21 is arranged on the pressure side 30 of the lip 14 .

[0088] Fig. 9 A first example of an arrangement of a row 32 of ducts 19 on the lip 14 is shown, wherein the discharge openings 21 of the row 32 of ducts 19 are arranged on the outer face 26 of the lip 14. The discharge openings 21 are arranged along an axis Y, which is tangential to the direction of rotation of the blade 1 about its axis of rotation X. The spacing between two discharge openings 21 is constant.

[0089] Fig.10 A second example of arrangement of a row 32 of ducts 19 on the lip 14 is shown, in which the discharge openings 21 of the row 32 of ducts 19 are arranged on the upstream face 28 of the lip 14. The discharge openings 21 are arranged along an axis Y, which is tangential to the direction of rotation of the blade 1. The spacing between two discharge openings 21 is constant.

[0090] Fig.11 An example of an arrangement of a first row 32 of ducts 19 and a second row 33 of ducts 19 on the lip 14 is shown, wherein the discharge openings 21 of the ducts 19 in the first row 32 are staggered relative to the discharge openings 21 of the ducts 19 in the second row 33. The first row 32 and the second row 33 comprise three and four ducts 19, respectively. The discharge openings 21 of the first row 32 and the discharge openings of the second row 33 are arranged on the outer face 26 of the lip 14. The discharge openings 21 of the first row 32 and the discharge openings of the second row 33 are arranged along the axis Y.

[0091] exist Figures 3 to 11 In the embodiment, each of the ducts 19 (respectively, the discharge opening) has a circular cross section which is constant along its extension axis A.

[0092] Fig.12 A first alternative embodiment of the duct 19 is shown, in which the duct 19 (respectively the discharge opening) has a rectangular cross section along its extension axis A.

[0093] Fig.13 A second alternative embodiment of a duct 19 is shown, in which the duct 19 has a variable cross section along its extension axis A.

[0094] Fig.14 An example of an orientation of the duct 19 is shown in which the duct 19 (or the extension axis A of the duct) is inclined upstream at an acute angle α relative to the stacking axis Z in the longitudinal plane.

[0095] The blade 1 is produced, for example, by a method comprising first obtaining a raw blade by a lost wax casting process and then carrying out various machining operations on the raw blade (for example drilling ducts) to obtain a blade with determined dimensions as depicted in the limiting figures.

[0096] The blade 1 can also be obtained by additive manufacturing (rapid prototyping).

Claims

1. A movable blade (1) for a wheel (2) of an aircraft turbine engine (3), the blade (1) comprising an aerodynamic blade (4) extending along a radial stacking axis (Z), the aerodynamic blade (4) of the blade (1) having a pressure side (5) and a suction side connected to each other by a leading edge (6) and a trailing edge (7), the aerodynamic blade (4) being delimited along the radial stacking axis (Z) by an inner root (9) and an outer heel (8), the outer heel (8) comprising an outer platform (11), the outer heel (8) also comprising at least a first contact sealing lip and a second contact sealing lip, the first contact sealing lip protruding outwards from the outer platform (11) and the second contact sealing lip protruding outwards from the outer platform (11), the second contact sealing lip being remote from the first contact sealing lip, the second contact sealing lip and the first contact sealing lip cooperating with a block made of a wear-resistant material (15), in, The outer platform (11) is defined by an upstream edge, a downstream edge, a pressure edge and a suction edge, the pressure edge being arranged on one side of the pressure side (5) of the aerodynamic blade (4), and the suction edge being arranged on one side of the suction side of the aerodynamic blade (4). The first contact sealing lip and the second contact sealing lip extend circumferentially from the pressure edge of the outer platform (11) to the suction edge, respectively. The first contact sealing lip comprises an upstream surface (28), a downstream surface (29), a pressure side surface (30), a suction side surface (31) and an outer surface (26), wherein the pressure side surface is arranged on one side of the pressure side surface (5) of the aerodynamic blade (4), and the suction side surface is arranged on one side of the suction side surface of the aerodynamic blade (4). The second contact sealing lip comprises an upstream surface (28), a downstream surface (29), a pressure side surface (30) arranged on the pressure side of the aerodynamic blade (4), a suction side surface (31) arranged on the suction side of the aerodynamic blade (4), and an outer surface (26). The blade (1) comprises an internal circuit (16) capable of receiving a first micro gas flow (f1), the circuit (16) comprising a supply cavity (17) opening at the inner root (9) through at least one inlet opening (18), The circuit (16) comprises at least a first conduit and a second conduit, the first conduit and the second conduit being connected to the supply cavity (17), and each of the first conduit and the second conduit leading to the outer surface (20) of the first contact sealing lip through a discharge opening (21), so that the gas jet (J) of the first micro gas flow (f1) is suitable for being discharged from each discharge opening (21), and each of the first conduit and the second conduit is oriented so that the corresponding gas jet (J) is suitable for being sprayed toward the second micro gas flow (f2) leaking between the outer heel (8) and the directly adjacent component (22), the discharge opening (21) of the first conduit is arranged on the outer surface (26) of the first contact sealing lip, and the discharge opening (21) of the second conduit is arranged on the pressure side (30) or the suction side (31) of the first contact sealing lip, The circuit (16) at least further comprises a third conduit and a fourth conduit, wherein the third conduit and the fourth conduit are connected to the supply cavity (17), and each of the third conduit and the fourth conduit leads to the outer surface (20) of the second contact sealing lip through a discharge opening (21), so that the gas jet (J) of the first micro gas flow (f1) is suitable for being discharged from each discharge opening (21), and each of the third conduit and the fourth conduit is oriented so that the corresponding gas jet (J) is suitable for being sprayed toward the second micro gas flow (f2) leaking between the outer heel (8) and the directly adjacent component (22), the discharge opening (21) of the third conduit is arranged on the outer surface (26) of the second contact sealing lip, and the discharge opening (21) of the fourth conduit is arranged on the pressure side (30) or the suction side (31) of the second contact sealing lip.

2. The blade (1) according to claim 1, characterized in that: The ducts each have a variable cross section that tapers toward the corresponding discharge opening (21).

3. The blade (1) according to claim 1 or 2, characterized in that: The supply cavity (17) is suitable for receiving the first micro gas flow (f1) escaping from a channel (13) via at least the inlet opening (18), the channel (13) being suitable for receiving a main gas flow (F).

4. The blade (1) according to claim 1 or 2, characterized in that: Each discharge opening (21) is circular.

5. The blade (1) according to claim 4, characterized in that: The diameter of the discharge opening (21) of each conduit is between 0.2 mm and 2 mm.

6. The blade according to claim 5, characterized in that: The diameter of the discharge opening (21) of each conduit is between 0.3 mm and 0.6 mm.

7. The blade (1) according to claim 1 or 2, characterized in that: The circuit (16) comprises a first row of at least three first ducts connected to the supply cavity (17) and each opening through a discharge opening (21) to the outer face (26) of the first contact sealing lip, The circuit (16) comprises at least three second conduits in a second row, which are connected to the supply cavity (17) and each leads to the pressure side (30) or the suction side (31) of the first contact sealing lip through a discharge opening (21).

8. The blade (1) according to claim 7, characterized in that The circuit (16) comprises at least three third ducts of a third row, which are connected to the supply cavity (17) and each lead through a discharge opening (21) to the outer face (26) of the second contact sealing lip, The circuit (16) comprises at least three fourth conduits in a fourth row, which are connected to the supply cavity (17) and each leads to the pressure side (30) or the suction side (31) of the second contact sealing lip through a discharge opening (21).

9. The blade (1) according to claim 1 or 2, characterized in that: The circuit (16) comprises a first row of at least three first ducts connected to the supply cavity (17) and each opening through a discharge opening (21) to the outer face (26) of the first contact sealing lip, wherein the circuit (16) comprises at least three first ducts of a second row, the at least three first ducts of the second row being connected to the supply cavity (17) and each leading through a discharge opening (21) to the outer face (26) of the first contact sealing lip, The discharge openings (21) of the at least three first conduits in the first row are staggered with the discharge openings (21) of the at least three first conduits in the second row.

10. The blade (1) according to claim 9, characterized in that The circuit (16) comprises at least three third ducts of a third row, which are connected to the supply cavity (17) and each lead through a discharge opening (21) to the outer face (26) of the second contact sealing lip, wherein the circuit (16) comprises at least three third ducts of a fourth row, the at least three third ducts of the fourth row being connected to the supply cavity (17) and each leading through a discharge opening (21) to the outer face (26) of the second contact sealing lip, The discharge openings (21) of the at least three third conduits in the third row are staggered with the discharge openings (21) of the at least three third conduits in the fourth row.

11. The blade (1) according to claim 1 or 2, characterized in that: The circuit (16) comprises a first row of at least three first ducts connected to the supply cavity (17) and each opening through a discharge opening (21) to the outer face (26) of the first contact sealing lip, wherein the circuit (16) comprises at least three first ducts of a second row, the at least three first ducts of the second row being connected to the supply cavity (17) and each leading through a discharge opening (21) to the outer face (26) of the first contact sealing lip, wherein the discharge openings (21) of the at least three first conduits in the first row are staggered with the discharge openings (21) of the at least three first conduits in the second row, wherein the circuit (16) comprises at least three third ducts of a third row, the at least three third ducts of the third row being connected to the supply cavity (17) and each leading through a discharge opening (21) to the outer face (26) of the second contact sealing lip, wherein the circuit (16) comprises at least three third ducts of a fourth row, the at least three third ducts of the fourth row being connected to the supply cavity (17) and each leading through a discharge opening (21) to the outer face (26) of the second contact sealing lip, wherein the discharge openings (21) of the at least three third conduits in the third row are staggered with the discharge openings (21) of the at least three third conduits in the fourth row, wherein the circuit (16) comprises at least three second conduits in a fifth row, the at least three second conduits in the fifth row being connected to the supply cavity (17) and each leading through a discharge opening (21) to the pressure side flank (30) or the suction side flank (31) of the first contact sealing lip, The circuit (16) comprises at least three fourth conduits in a sixth row, which are connected to the supply cavity (17) and each leads to the pressure side (30) or the suction side (31) of the second contact sealing lip through a discharge opening (21).

12. The blade (1) according to claim 1 or 2, characterized in that The pressure side surface (30) of the first contact sealing lip is delimited in radial direction by an outer end and an inner end, The suction side surface (31) of the first contact sealing lip is radially bounded by an outer end and an inner end, wherein, when the discharge opening (21) of the second conduit is arranged at the pressure side surface (30) of the first contact sealing lip, the discharge opening (21) of the second conduit is closer to the outer end of the pressure side surface (30) than to the inner end of the pressure side surface (30), Wherein, when the discharge opening (21) of the second conduit is arranged at the suction side surface (31) of the first contact sealing lip, the discharge opening (21) of the second conduit is closer to the outer end of the suction side surface (31) than to the inner end of the suction side surface (31), The pressure side surface (30) of the second contact sealing lip is radially delimited by an outer end and an inner end, The suction side surface (31) of the second contact sealing lip is radially bounded by an outer end and an inner end, Wherein, when the discharge opening (21) of the fourth conduit is arranged at the pressure side surface (30) of the second contact sealing lip, the discharge opening (21) of the fourth conduit is closer to the outer end of the pressure side surface (30) than to the inner end of the pressure side surface (30), When the discharge opening (21) of the fourth conduit is arranged at the suction side surface (31) of the second contact sealing lip, the discharge opening (21) of the fourth conduit is closer to the outer end of the suction side surface (31) than to the inner end of the suction side surface (31).

13. A wheel part (2) for an aircraft turbine engine (3), comprising a disk (12) supporting at its periphery an annular array of blades (1) according to any one of the preceding claims.

14. Aircraft turbine engine (3) comprising a blade (1) according to any one of claims 1 to 12 or a wheel (2) according to claim 13.

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