Turbine blade for aircraft turbine engine comprising a platform provided with a channel discharging a main flow towards a discharge cavity

Abstract

The invention relates to a turbine blade (60) for a turbine engine, comprising a blade (61) and a platform (62). The platform (62) comprises an inner channel (80) having a suction opening (81) opening into a first surface (71) of an upstream portion (P1) of the platform (62), the first surface (71) defining a primary duct (21A). The inner channel (80) comprises a discharge opening (82) opening into a second surface (72) of a downstream portion (P2) of the platform (62), the second surface (72) defining a discharge cavity (50). The inner channel (80) enables the suction of a portion of the fluid circulating in the primary duct (21A), thereby reducing the intensity of the secondary flow resulting from the friction of the fluid on the first surface (71).

Description

Technical Field

[0001] This invention relates to the field of turbines for aircraft turbine engines.

[0002] More specifically, the present invention relates to nozzles or rotor blades for such turbines. Background Technology

[0003] A conventional aircraft turbine engine comprises one or more stages, each stage including a nozzle and a rotor wheel. The nozzle includes fixed blades connected to the housing at their radially outer ends and circumferentially distributed around the turbine's longitudinal central axis to form a stator ring. The rotor wheel includes a disk and blades connected to the disk at their radially inner ends and circumferentially distributed around the disk. The nozzle of a stage is configured such that the fluid flow entering that stage (typically including gas from the combustion chamber) is accelerated by the stator blades and deflected towards the rotor wheel blades of that stage, thereby driving the rotor wheel to rotate about its longitudinal central axis.

[0004] Typically, each nozzle blade and rotor blade of a turbine includes a blade and two platforms that radially define the circumferential portion of an annular main duct between them, into which the blade extends. Fluid passing through the turbine flows primarily through this main duct.

[0005] When a conventional turbine is in operation, the interaction between the fluid and the nozzle and rotor wheel generates vortices at the blade platform, forming what is known as a "secondary flow".

[0006] To illustrate this phenomenon, Figure 1 shows a portion of two blades 1A and 1B of a turbine nozzle 1, which are circumferentially adjacent to each other. Figure 1 shows more specifically the radially lower portion of the blade 2 and the platform 3 of each of the blades 1A and 1B. Each blade 2 of 1A and 1B includes a leading edge 4, a trailing edge 5, a pressure surface 6, and a suction surface 7. The platform 3 of each blade 1A and 1B defines a circumferential portion of an annular main duct in the radial interior, in which fluid flows in direction S1 from the leading edge 4 to the trailing edge 5 of the blade 2.

[0007] Given the typical viscosity of the fluid flowing in the main bypass duct of the turbine, the fluid flow along the surface of platform 3 has a velocity gradient GV1, such that the closer the fluid layer is to the surface, the slower its velocity. The fluid flowing in the main bypass duct is also subject to a pressure gradient GP1, which in this example is oriented from the pressure surface 6 of blade 2 of blade 1B toward the suction surface 7 of blade 2 of blade 1A. The pressure gradient GP1 is typically sufficient to deflect the fluid layer flowing near the surface of platform 3.

[0008] This results in different types of vortices. The first type, called a "horseshoe vortex" T1, takes the form of two counter-rotating branches distributed on both sides of the blade 2. The second type, called a "channel vortex" T2, forms between two adjacent blades 2. The third type, called an "angular vortex" T3, flows along the connecting line between the blade 2 and the platform 3 of each impeller.

[0009] The secondary flows T1, T2, and T3, which typically occur at the root and tip of blade 2, are not oriented along the main flow direction S1 of the fluid passing through the main duct, thus reducing the efficiency of the turbine engine and increasing its kerosene consumption.

[0010] Similar secondary flows also occur in the turbine rotor wheel. Summary of the Invention

[0011] The present invention aims to provide a blade capable of limiting the formation of such secondary flow or reducing the intensity of such secondary flow.

[0012] Therefore, the present invention relates to a turbine blade for a turbine engine, the turbine blade being designed for mounting about an axis, the turbine blade including blades and at least one platform, the platform including a first surface from which the blade extends, and the first surface being designed to define a main bypass duct into which the blade extends, the main bypass duct receiving fluid flowing in a direction from the leading edge to the trailing edge of the blade and from an upstream portion to a downstream portion of the platform, the platform including a second surface radially opposite the first surface and designed to define an exhaust chamber. According to the invention, the platform includes at least one inner channel having at least one intake opening and at least one exhaust opening, the at least one intake opening opening leading to the first surface of the upstream portion of the platform, and the at least one exhaust opening opening leading to the second surface of the downstream portion of the platform.

[0013] This internal channel allows a portion of the fluid flowing along the first surface of the platform to be drawn in and prevents that portion of the fluid from contributing to the formation of secondary flows.

[0014] Therefore, the present invention restricts the formation of secondary flows and reduces the intensity of secondary flows that may still occur, thereby improving the efficiency of the turbine engine and reducing the kerosene consumption of the turbine engine.

[0015] Considering the static pressure difference between the area of ​​the main duct surrounding at least one intake opening and the area of ​​the discharge chamber surrounding at least one discharge opening, fluid flowing in the main duct and reaching at least one intake opening is actually drawn into at least one inner channel.

[0016] In an operating turbine, the static pressure is actually much lower downstream of the blade than upstream of it, and the static pressure is approximately the same downstream of the blade and in the corresponding exhaust chamber. Therefore, the static pressure in the exhaust chamber at at least one exhaust opening is significantly lower than the static pressure in the main bypass duct at at least one intake opening.

[0017] Therefore, at least one internal channel forms a passive inhalation system that does not require any additional inhalation equipment, such as mechanically or electrically operated equipment.

[0018] Furthermore, discharging the fluid transported by at least one internal channel into the discharge chamber instead of into the main duct avoids or reduces any interference with the main fluid flowing through the main duct.

[0019] Therefore, the present invention enables the reduction of the formation and / or intensity of secondary flows while avoiding mixing losses, such as those caused by the direct reintroduction of the fluid drawn in into the main duct.

[0020] Furthermore, the portion of fluid discharged into the exhaust chamber thus helps drive the turbine rotor, since the exhaust chamber is fluidly connected to the main duct in a manner known per se.

[0021] Specifically, when the impeller is a nozzle of the turbine, the portion of the fluid discharged into the discharge chamber constitutes part of the fluid flow driving the rotor wheel of the same stage, and the discharge chamber located downstream of the nozzle is fluidly connected to the main duct upstream of the rotor wheel of the same stage.

[0022] Preferably, the upstream portion of the platform is defined by an imaginary line that is equidistant from the leading and trailing edges of the blade.

[0023] According to a first alternative embodiment, at least one of the one or more intake openings is positioned upstream of the leading edge of the blade relative to the direction of fluid flow within the main duct.

[0024] According to a second alternative embodiment, at least one of the one or more intake openings is positioned downstream of the leading edge of the blade and upstream of the trailing edge of the blade relative to the direction of fluid flow within the main duct.

[0025] The first alternative embodiment and the second alternative embodiment can be combined.

[0026] 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 fluid flow direction within the main duct, and at least one other intake opening is positioned downstream of the leading edge of the blade and upstream of the trailing edge of the blade relative to the fluid flow direction within the main duct.

[0027] In one embodiment, the platform includes multiple internal channels that are fluidly independent of each other.

[0028] In another embodiment, the platform includes a plurality of internal channels fluidly connected to each other.

[0029] The platform may also include a first inner channel and a series of other inner channels that are fluidly connected to each other and fluidly independent of the first inner channel.

[0030] Alternatively, the platform may 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.

[0031] In one embodiment, the impeller includes one or more blades configured to be oriented in the discharge direction, and a portion of the fluid is discharged from at least one internal channel of the platform through one or more discharge openings.

[0032] In one embodiment, at least one intake opening is arranged on one side of the pressure surface of the blade.

[0033] The present invention also relates to a turbine for a turbine engine.

[0034] In one embodiment, the turbine includes a nozzle that includes at least one blade as defined above.

[0035] In one embodiment, the turbine includes a rotor wheel that includes at least one blade as defined above.

[0036] Needless to say, a turbine may include one or more nozzles and one or more rotor wheels, each of which includes at least one blade as defined above.

[0037] In one embodiment, the turbine includes a rotor, a stator, and a dynamic seal, the rotor and / or stator including at least one blade as defined above, the dynamic seal including a wear member integral with the stator and at least one blade integral with the rotor, the turbine being configured such that the blade defines an exhaust chamber upstream.

[0038] The present invention also relates to a turbine engine including a turbine as defined above.

[0039] According to another aspect, the present invention relates to a method for manufacturing a blade as defined above.

[0040] Preferably, the method includes the step of additive manufacturing the blade.

[0041] Other advantages and features of the present invention will become apparent when reading the following detailed, non-limiting description. Attached Figure Description

[0042] The following detailed description refers to the accompanying drawings, in which:

[0043] [Figure 1] is a schematic partial perspective view of a conventional turbine nozzle for an aircraft turbine engine, which has already been described above, showing the secondary flow that occurs during turbine operation;

[0044] [ Figure 2 [This is a schematic axial cross-sectional view of the aircraft's propulsion unit;]

[0045] [ Figure 3 [This is a schematic partial axial section half-view of the low-pressure turbine of a turbine engine;]

[0046] [ Figure 4 [This is a schematic partial axial section half-view of the low-pressure turbine of a turbine engine;]

[0047] [ Figure 5 [Illustrated diagram of a portion of a wheel blade comprising a platform having an internal channel, according to the present invention;]

[0048] [ Figure 6 [A] schematic partial perspective view of the impeller according to the present invention, showing the suction opening according to the first embodiment;

[0049] [ Figure 7 [A] schematic partial perspective view of the impeller according to the present invention shows the suction opening according to the second embodiment;

[0050] [ Figure 8 [Illustrated partial perspective view of the impeller according to the present invention, showing the suction opening according to the third embodiment;]

[0051] [ Figure 9 [Illustrated partial perspective view of the impeller according to the invention, showing the intake opening according to the fourth embodiment.] Detailed Implementation

[0052] The accompanying drawings include reference frames L, R, and C, which define the longitudinal (or axial), radial, and circumferential directions, respectively, and the reference frames are orthogonal to each other.

[0053] Figure 2 The diagram shows an aircraft propulsion unit 10 including a turbine engine 11 rectified by a nacelle 12. In this example, the turbine engine 11 is a twin-shaft turbofan engine.

[0054] In the following text, the terms "upstream" and "downstream" will be defined relative to the direction S1 of the airflow passing through the propulsion unit when the propulsion unit 10 is propelled.

[0055] The turbofan engine 11 has a longitudinal central axis A1 around which various components of the turbofan engine extend. In this case, the turbofan 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.

[0056] During operation of the turbofan engine 11, airflow 20 enters the propulsion unit 10 through an air inlet upstream of the nacelle 12, passes through the fan 13, and then splits into a central main flow 20A and a secondary flow 20B. Main flow 20A flows in a main gas flow duct 21A that passes through the gas generator. Secondary flow 20B then flows in a secondary duct 21B that surrounds the gas generator and is radially externally defined by the nacelle 12.

[0057] In one exemplary embodiment, the low-pressure turbine 18 is referred to below. Figure 3 The above, Figure 3 The turbine 18 is shown in a radial plane including the longitudinal central axis A1.

[0058] The longitudinal central axis A1 is also the axis of rotation of the rotor of the turbine 18.

[0059] In this example, turbine 18 comprises four stages, each stage including nozzle 25 and rotor wheel 26.

[0060] In a manner known per se, rotor wheels 26 are axially assembled to each other via annular flanges 27 and form the rotor of turbine 18. Nozzle 25 is connected to housing 28 to form the stator of turbine 18.

[0061] Each nozzle 25 includes a plurality of blades 30 circumferentially distributed around axis A1. Referring to the nozzle 25 of the last stage of turbine 18, in... Figure 3 Only one blade 30 of the nozzle of this final stage is shown. 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 via an attachment element integral with the outer platform 33 of the blade.

[0062] 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 final stage rotor wheel is shown. Each blade 36 includes a blade 37, an inner platform 38, and an outer platform 39. Each blade 36 is connected to the disk 35 via a root integral with the inner platform 38 of the blade.

[0063] For each blade 30 of nozzle 25, each of platforms 32 and 33 includes a first surface from which blade 31 extends and defines a circumferential portion of main duct 21A through which the main flow 20A flows. 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.

[0064] Similarly, for each blade 36 of the rotor wheel 26, each of platforms 38 and 39 includes a first surface from which blade 37 extends and defines a circumferential portion of the main duct 21A. Thus, the first surface of the inner platform 38 of each blade 36 defines the main duct 21A radially inward, while the first surface of the outer platform 39 of each blade 36 defines the main duct 21A radially outward.

[0065] Therefore, in Figure 3 In turbine 18, the main bypass duct 21A is generally annular.

[0066] In another exemplary embodiment, the low-pressure turbine 18 is referred to below. Figure 4 As stated above.

[0067] Figure 4 It shows the relationship with Figure 3 A portion of a turbine 18 of the same type, which includes a nozzle 25 and a rotor wheel 26 belonging to the same stage as the nozzle 25. Figure 4 (right side) and lower rotor wheel 26 (in) Figure 4 (Left side of the middle).

[0068] exist Figure 4 In the example, turbine 18 includes a dynamic seal 40, which includes, on one hand, a wear-resistant component 41 integral with the inner platform 32 of the impeller 30 of nozzle 25, and on the other hand, a blade-like portion 42 integral with rotor wheel 26. The seal 40 is used to restrict the flow of gas radially below nozzle 25.

[0069] Figure 4 The turbine 18 also includes dynamic seals 45, each of which includes, on one hand, a wear-resistant component 46 integral with the housing 28, and on the other hand, a blade-like portion 47 integral with the outer platform 39 of the rotor blade 36 of the rotor wheel 26. The seals 45 are used to restrict the flow of gas radially above the rotor wheel 26.

[0070] Figure 3 The turbine 18 also includes dynamic seals 40 and 45 of the same type to restrict gas flow radially below the nozzle 25 and radially above the rotor wheel 26, respectively.

[0071] Therefore, taking into account, in particular, the gaps created by thermal expansion and the relative movement of the various fixed and moving parts of the turbine 18, these dynamic seals 40 and 45 restrict but do not completely prevent the flow of all gas outside the main duct 21A.

[0072] Reference Figure 4 The space radially outside the main duct 21A defines various annular cavities, including cavities 50 and 52, referred to herein as "emission cavities".

[0073] In this example, the discharge chamber 50 is radially externally defined by the second surface of the inner platform 32 of the blade 30 of the nozzle 25, and axially defined upstream by the dynamic seal 40. For each blade 30, in this example, the second surface of the inner platform 32 is radially opposite to the first surface of the inner platform 32. Therefore, the second surface of the inner platform 32 of each blade 30 defines a circumferential portion of the discharge chamber 50.

[0074] The discharge chamber 50 is fluidly connected to the main duct 21A through an annular opening that extends axially and / or radially between the downstream end 54 of the inner platform 32 of the blade 30 of the nozzle 25 and the upstream end 55 of the inner platform 38 of the blade 36 of the rotor wheel 26, which belongs to the same class as the nozzle 25.

[0075] exist Figure 4 In the illustrated embodiment, the discharge chamber 52 is radially inwardly defined by the second surface of the outer platform 39 of the blade 36 of the rotor wheel 26, which belongs to a stage below the stage of the nozzle 25. The discharge chamber 52 is axially defined upstream by a dynamic seal 45, the blade portion 47 of which is integral with the rotor wheel 26. For each blade 36, in this example, the second surface of the outer platform 39 is radially opposite to the first surface of the outer platform 39. Therefore, the second surface of the outer platform 39 of each blade 36 defines a circumferential portion of the discharge chamber 52.

[0076] The discharge chamber 52 is fluidly connected to the main duct 21A through an annular opening that extends axially and / or radially between the downstream end 56 of the outer platform 39 of the blade 36 of the aforementioned rotor wheel 26 and the upstream end 57 of the outer platform 33 of the blade 30 of the nozzle 25.

[0077] exist Figure 3 and Figure 4 In the example shown, turbine 18 includes such discharge chambers 50 or 52 downstream of each dynamic seal 40 or 45.

[0078] Figure 5 A portion of the impeller 60 according to the present invention is shown.

[0079] The impeller 60 includes blades 61 and platform 62.

[0080] In this non-limiting example, the blade 60 corresponds to Figure 3 or Figure 4 In the turbine 18, one of the nozzles 25 is a nozzle of one of the blades 30, such that the platform 62 of the blade 60 corresponds to the inner platform 32 of the blade 30.

[0081] The blade 61 of the impeller 60 includes a leading edge 63, a trailing edge 64, a pressure surface (not shown), and a suction surface 66.

[0082] The platform 62 of the blade 60 includes a first surface 71 and a second surface 72 that are radially opposite each other and define the thickness E1 of the platform 62.

[0083] Platform 62 includes an upstream end 73 and a downstream end 74.

[0084] exist Figure 5 In the simplified schematic diagram shown, the first surface 71 and the second surface 72 are planar and parallel to each other. Needless to say, each of these surfaces may have a non-planar geometry and be oriented along an overall tilt direction relative to the longitudinal direction L and the radial direction R, similar to... Figure 4 The platform 32 of the impeller 30. In this case, more generally, the first surface 71 and the second surface 72 define the thickness E1 of the platform 62 at least at the upstream end 73 and / or the downstream end 74.

[0085] Figure 5 An imaginary line LL1 is shown, equidistant from the leading edge 63 and trailing edge 64 of the blade 61 of the impeller 60.

[0086] exist Figure 5 In the simplified schematic diagram shown, the leading edge 63 and the trailing edge 64 are straight lines and parallel to each other. Needless to say, each of these edges can have a non-linear geometry and be oriented in a general tilt direction relative to the radial direction R, similar to... Figure 4 The leading edge of blade 31 of the impeller 30. Therefore, the imaginary line LL1 is not necessarily straight.

[0087] The hypothetical line LL1 defines the upstream portion P1 and the downstream portion P2 of platform 62.

[0088] When the impeller 60 is installed Figure 3 or Figure 4When one of the nozzles 25 of the turbine 18 is in the turbine, the first surface 71 of the platform 62 defines the main bypass 21A radially inward, and the flow direction S1 of the main flow 20A is from the leading edge 63 of the blade 61 toward the trailing edge 64, and from the upstream portion P1 of the platform 62 toward the downstream portion P2. Under these conditions, the second surface 72 of the platform 62 defines the corresponding exhaust chamber 50 radially outward (see above).

[0089] Platform 62 includes an inner channel 80 having an intake opening 81 and an exhaust opening 82. The intake opening leads to a first surface 71 of an upstream portion P1 of platform 62, and the exhaust opening leads to a second surface 72 of a downstream portion P2 of platform 62.

[0090] In this example, the intake opening 81 of the inner channel 80 more specifically leads upstream of the leading edge 63 of the blade 61.

[0091] The present invention includes any geometry of the inner channel 80, the intake opening 81, and the discharge opening 82, as long as the inner channel 80 allows a portion of the main flow 20A to flow out of the main duct 21A and be discharged into the discharge chamber 50 under the action of the static pressure difference between the main duct 21A and the discharge chamber 50.

[0092] Therefore, the present invention is by no means limited to the examples shown in the accompanying drawings.

[0093] For example, in an embodiment not shown, platform 62 includes one or more additional inner channels that are fluidly independent of or fluidly connected to the inner channel 80.

[0094] Regardless of the number and geometry of the inner channels 80, the inner channels may include one or more intake openings 81 and one or more discharge openings 82.

[0095] Figures 6 to 9 Different types of intake openings 81 are shown. In these examples, all intake openings lead downstream to the first surface 71 of the platform 62 and are axially close to the leading edge 63 of the blade 61.

[0096] exist Figure 6 In the example shown, platform 62 includes an inner channel 80 having seventeen intake openings 81 with a circular cross-section, for example, obtained by drilling or additive manufacturing.

[0097] exist Figure 7 In the example shown, platform 62 includes an inner channel 80 having a single suction opening 81 in the form of a groove extending in the circumferential direction C.

[0098] exist Figure 8In the example shown, platform 62 includes an inner channel 80 having two intake openings 81 in the form of grooves that extend in a bending direction to extend along the pressure surface of blade 61.

[0099] exist Figure 9 In the example shown, platform 62 includes an inner channel 80, which has a... Figure 8 A single suction opening 81 corresponds to one of the grooves in the groove.

[0100] In one embodiment not shown, Figure 5 The impeller 60 includes an impeller configured to be oriented in the discharge direction, through which fluid is discharged from the inner passage 80 via the discharge opening 82.

[0101] The same applies to the blades 36 of the rotor wheel 26 of the turbine 18. Therefore, in one embodiment, each blade of the rotor wheel 26 of the turbine 18 includes, for example, blades 36 of the rotor wheel 26. Figure 5 The blades of the whorl 60 and the blades of the 61, and such as Figure 5 The outer platform of the platform 62 of the impeller 60 is such that at least one inner channel 80 is configured to take a portion of the main stream 20A from the main duct 21A and discharge a portion of the main stream into the corresponding discharge chamber 52.

[0102] In another embodiment, the impeller 30 of at least one nozzle 25 of the turbine 18 includes an inner platform and an outer platform, both of which are similar to Figure 5 Platform 62 of the impeller 60 in the turbine 18. Similarly, the impeller 36 of at least one rotor wheel 26 of the turbine 18 may include an inner platform and an outer platform, both of which are similar to Figure 5 Platform 62 of the impeller 60.

[0103] In another embodiment, one or more nozzles 25 of the turbine 18 and / or one or more rotor wheels 26 may include conventional blades and include at least one such as Figure 5 The alternation of the blades of platform 62 and platform 60 in the middle.

[0104] This invention can also be applied to the high-pressure turbine 17 and... Figure 2 The turbofan engine 11 is implemented in the turbine of a different turbo engine.

Claims

1. A turbine blade (60) for a turbine (18) of a turbine engine (11), the blade being intended to be mounted about an axis (A1), the blade including blades (61) and a platform (62), the blades (61) extending radially from the platform (62) relative to the axis (A1), the platform (62) including a first surface (71), the blades (61) extending from the first surface, and the first surface being intended to define a main bypass duct (21A), the blades (61) extending into the main bypass duct, the main bypass duct receiving along the leading edge of the blades (61). (63) Fluid flowing in the direction (S1) to the trailing edge (64), the platform (62) comprising an upstream portion (P1) and a downstream portion (P2) along the direction (S1), the upstream and downstream portions being defined by an imaginary line (LL1) oriented primarily radially and equidistant from the leading edge (63) and trailing edge (64) of the blade (61), the platform (62) comprising a second surface (72) radially opposite the first surface (71) and intended to define an exhaust chamber (50). in, The platform (62) includes at least one internal channel (80) having at least one intake opening (81) and at least one discharge opening (82). The at least one intake opening opens to the first surface (71) at the upstream portion (P1) of the platform (62), and the at least one discharge opening opens to the second surface (72) at the downstream portion (P2) of the platform (62). The feature is that at least one of the one or more suction openings (81) is positioned upstream of the leading edge (63) of the blade (61) relative to the direction (S1) of fluid flow within the main duct (21A).

2. The blade (60) according to claim 1, wherein, At least one of the one or more suction openings (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 direction (S1) of fluid flow within the main duct (21A).

3. The blade (60) according to claim 1 or 2, wherein, The platform (62) includes multiple internal channels that are fluidly independent of each other and / or multiple internal channels that are fluidly connected to each other.

4. The impeller (60) according to claim 1 or 2, comprising one or more impellers configured to be oriented in the discharge direction, wherein a portion of the fluid is discharged through one or more of the discharge openings (82) into the at least one inner channel (80) of the platform (62).

5. The blade (60) according to claim 1 or 2, wherein, The at least one intake opening (81) is arranged on one side of the pressure surface of the blade (61).

6. A turbine (18) for a turbine engine (11), the turbine comprising a nozzle (25) and / or a rotor wheel (26), the nozzle comprising at least one blade (60) according to any one of claims 1 to 5, the rotor wheel comprising at least one blade (60) according to any one of claims 1 to 5.

7. A turbine (18) for a turbine engine (11), the turbine comprising a rotor, a stator and a dynamic seal (40), the rotor and / or the stator comprising at least one blade (60) according to any one of claims 1 to 5, the dynamic seal (40) comprising a wear member (41) integral with the stator and at least one blade (42) integral with the rotor, the turbine (18) being configured such that the blade (42) defines the exhaust chamber (50) upstream.

8. A turbine engine (11), said turbine engine comprising a turbine (18) according to claim 6 or 7.

9. A method for manufacturing a blade (60) according to any one of claims 1 to 5, comprising the step of additive manufacturing the blade (60).

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