Turbomachine blading comprising a blade and a platform which has an internal flow-intake and flow-ejection canal

Abstract

The present invention relates to blading (25, 26) for a turbomachine (10), comprising: - a blade (31) having an aerodynamic profile; - a platform (32, 33) comprising a flow-path surface (321) intended to delimit a primary flow path (21A) of the turbomachine (10), which path is intended, when the turbomachine (10) is in operation, to receive a flow that splits, upstream of the blade (31), into a suction-face flow (EE) and a pressure-face flow (EI); and - an internal canal (34) which has an intake opening (35) and an ejection opening (36), these each opening onto the flow-path surface (321) of the platform (32, 33), the ejection opening (36) opening downstream of the intake opening (35) and the intake opening (35) opening toward the pressure-face flow (EI).

Description

[0001] Turbomachine blading, comprising a blade and a platform which has an internal flow suction and ejection channel

[0002] FIELD OF THE INVENTION

[0003] The invention relates to the field of aircraft turbomachines, and more particularly to the field of turbomachine blades comprising a blade, a platform and an internal channel for a turbine of a turbomachine.

[0004] STATE OF THE ART

[0005] An aircraft typically includes at least one turbomachine to provide propulsion. The turbomachine may be a turbojet or a turboprop. The turbomachine includes a fan, a compressor, a combustion chamber, a turbine, and a gas exhaust nozzle.

[0006] A turbojet engine can be a dual-flow turbojet engine, in which the air mass drawn in by the fan is divided into a primary flow, which passes through the compressor, the combustion chamber and the turbine, and a secondary flow, which is concentric with the primary flow.

[0007] For example, the turbomachine may include a low-pressure compressor, a high-pressure compressor, a high-pressure turbine, and a low-pressure turbine. The high-pressure turbine rotates the high-pressure compressor via a high-pressure shaft, and the low-pressure turbine rotates the low-pressure compressor via a low-pressure shaft. The low-pressure turbine may also rotate the fan either directly via the low-pressure shaft or via a reduction gear arranged between the low-pressure turbine and the fan, the reduction gear being rotated by the low-pressure shaft.

[0008] The turbomachine extends substantially around a longitudinal axis.

[0009] A conventional aircraft turbomachine turbine comprises one or more stages, each consisting of a nozzle and a moving wheel. The nozzles and the moving wheels are thus arranged alternately along the longitudinal axis of the turbomachine.

[0010] The distributor comprises fixed blades connected by their radially external end to a casing and which are distributed circumferentially around the longitudinal axis of the turbine so as to form a stator ring. The moving wheel comprises a disc and blades connected to the disc by their radially internal end while being circumferentially distributed around the disc. The distributor of a turbine stage is configured so that a flow of fluid entering this stage, typically comprising gases from the combustion chamber, is accelerated and deflected by the stator blades towards the blades of the moving wheel of this stage so as to drive them in rotation around the longitudinal axis. An example of the design of such a turbine is known from document FR 3 034 129.

[0011] In general, a turbine nozzle vane comprises a blade and two platforms which radially delimit between them a circumferential portion of an annular primary flow vein into which the blade extends. The fluid passing through the turbine flows mainly in this primary flow vein.

[0012] During the operation of a conventional turbine, the interaction of the fluid with the distributors and the moving wheels produces vortices at the level of the blade platforms, forming so-called "secondary" flows.

[0013] These secondary flows have the effect of reducing the efficiency of the turbine and increasing the fuel consumption of the turbomachine.

[0014] STATEMENT OF THE INVENTION

[0015] An aim of the invention is to propose a turbomachine blading which makes it possible to limit the formation of these secondary flows and to reduce the intensity of these secondary flows, which makes it possible to improve the aerodynamic efficiency of the blading.

[0016] To this end, the invention relates, according to a first aspect, to a turbomachine blade intended to be mounted around a longitudinal axis, and comprising:

[0017] - a blade which extends radially with respect to the longitudinal axis and which has an aerodynamic profile delimited axially upstream by a leading edge and downstream by a trailing edge, the blade further comprising a lower surface wall and an upper surface wall opposite the lower surface wall, the lower surface wall and the upper surface wall each connecting the leading edge to the trailing edge;

[0018] - a platform comprising a vein surface from which the blade extends, the platform being intended to delimit a primary flow vein of a flow of the turbomachine in operation, the flow dividing upstream of the leading edge of the blade during operation of the turbomachine on the one hand into an extrados flow flowing on the side of the extrados wall of the blade and on the other hand into an intrados flow flowing on the side of the intrados wall of the blade; and

[0019] - an internal channel which has a suction opening and an ejection opening which are each arranged on the side of the intrados wall of the blade and which each open onto the vein surface of the platform, the ejection opening opening downstream of the suction opening and the suction opening opening in the direction of the intrados flow.

[0020] Some preferred but non-limiting features of the blading according to the first aspect are the following, taken individually or in combination: - the suction opening and / or the ejection opening has a circular shape, an oblong shape, a slot shape, a flared shape, or comprises a plurality of orifices;

[0021] - the intrados flow flows generally between a separation point located upstream of the leading edge of the blade and corresponding to a point at which the intrados flow and the extrados flow divide, and an impact point located downstream of the leading edge of the blade and corresponding to a point at which the intrados flow comes into contact with a blade circumferentially adjacent to the blade;

[0022] - the suction opening extends in a main direction and corresponds to one of the following four suction openings:

[0023] - a first suction opening which has an opening which opens onto the vein surface and which extends in a main direction substantially perpendicular to the direction of the intrados flow, the first suction opening opening in the direction of the leading edge or directly upstream of the leading edge of the blade;

[0024] - a second suction opening which has an opening which opens onto the vein surface and which extends in a main direction substantially perpendicular to the direction of the intrados flow, the second suction opening opening downstream of the leading edge of the blade, the second suction opening opening closer to the point of separation than to the point of impact;

[0025] - a third suction opening which has an opening which opens towards the point of impact; or

[0026] - a fourth suction opening which has an opening which opens onto the vein surface and which extends in a main direction substantially parallel to the direction of the intrados flow, the fourth suction opening opening between the leading edge and the trailing edge of the blade in a circumferential direction;

[0027] - the ejection opening extends in a main direction and corresponds to one of the following three ejection openings:

[0028] - a first ejection opening located closer to the leading edge than to the trailing edge of the blade, which opens towards the intrados wall of the blade;

[0029] - a second ejection opening located substantially between the leading edge and the trailing edge of the blade, which opens towards the intrados wall of the blade, the second ejection opening preferably having a main direction substantially parallel to the intrados wall of the blade; or

[0030] - a third ejection opening located closer to the trailing edge than to the leading edge of the blade and which opens towards the trailing edge of the blade;

[0031] - the suction opening corresponds to the first suction opening and the ejection opening corresponds to the third ejection opening; - a section of the internal channel of the ejection opening is smaller than a section of the internal channel of the suction opening;

[0032] - the platform is an internal platform, the vein surface of the internal platform being adapted to delimit radially inwardly the primary flow vein;

[0033] - the blade extends radially around the longitudinal axis and further comprises another blade circumferentially adjacent to the blade, wherein said circumferentially adjacent blade extends radially with respect to the longitudinal axis and has an aerodynamic profile delimited axially upstream by a leading edge and downstream by a trailing edge, the circumferentially adjacent blade further comprises a pressure side wall and an extrados wall opposite the pressure side wall, the pressure side wall and the extrados wall each connecting the leading edge to the trailing edge, wherein the circumferentially adjacent blade is adapted to extend radially from the flow path surface of the platform into the primary flow path so that the extrados wall of the circumferentially adjacent blade is located opposite the pressure side wall of the blade,wherein the intrados flow flows generally between a separation point located upstream of the leading edge of the blade and corresponding to a point at which the intrados flow and the extrados flow divide, and an impact point located downstream of the leading edge of the blade and corresponding to a point at which the intrados flow contacts the extrados wall of the circumferentially adjacent blade;,

[0034] - the blading is a turbine distributor, in particular a low pressure turbine, a turbomachine;

[0035] - the blading is a turbomachine compressor distributor;

[0036] - the blading is a moving turbine wheel, in particular a low-pressure turbine, a turbomachine;

[0037] - the blading is a moving wheel of a turbomachine compressor.

[0038] According to a third aspect, the invention provides a turbomachine turbine comprising at least one blading, in particular a distributor or a moving wheel, according to the second aspect.

[0039] The turbine may be a low pressure turbine. Alternatively, the turbine may be a high pressure turbine.

[0040] According to a fourth aspect, the invention proposes a turbomachine compressor comprising at least one distributor or a moving wheel according to the second aspect.

[0041] The compressor may be a low-pressure compressor. Alternatively, the compressor may be a high-pressure compressor. According to a fifth aspect, the invention provides a turbomachine comprising at least one blade according to the first aspect, in particular a turbomachine comprising a turbine according to the third aspect.

[0042] The turbomachine can be a double-spool turbomachine.

[0043] According to a sixth aspect, the invention proposes an aircraft comprising at least one blade according to the first aspect.

[0044] DESCRIPTION OF FIGURES

[0045] Other characteristics, aims and advantages of the invention will emerge from the following description, which is purely illustrative and non-limiting, and which must be read in conjunction with the appended drawings in which:

[0046] Figure 1 is a partial schematic perspective view of a nozzle of a conventional aircraft turbomachine turbine, illustrating secondary flows that occur during operation of the turbomachine.

[0047] Figure 2 is a schematic axial sectional view of a propulsion assembly for an aircraft.

[0048] Figure 3 is a partial schematic axial sectional view of a low pressure turbine of a turbomachine.

[0049] Figure 4 is a partial schematic illustration of a vane according to one embodiment of the invention, comprising a blade, a platform and an internal channel.

[0050] Figure 5 is a diagram illustrating different configurations of suction openings and ejection openings of a blade according to different embodiments of the invention.

[0051] Figure 6a is a partial schematic perspective view of a blade comprising an internal channel comprising a suction opening according to a first embodiment of the invention.

[0052] Figure 6b is a partial schematic perspective view of a blade comprising an internal channel comprising a suction opening according to a second embodiment of the invention.

[0053] Figure 6c is a partial schematic perspective view of an internal channel of a blade according to one embodiment of the invention.

[0054] DETAILED DESCRIPTION OF THE INVENTION

[0055] In the present application, upstream and downstream are defined relative to a direction S1 of normal flow of the gas through the turbomachine 10 in operation, an air flow flowing in the turbomachine 10 from upstream to downstream. The longitudinal axis X corresponds to an axis of rotation of the turbomachine 10, in particular to an axis of rotation of a turbine 17, 18 of the turbomachine 10. A radial axis is an axis perpendicular to the longitudinal axis X and passing through it. A circumferential axis is an axis perpendicular to the longitudinal axis X and not passing through it. A longitudinal direction L, respectively radial R or circumferential C, corresponds to the direction of the longitudinal axis X, respectively radial or circumferential. The longitudinal directions L, radial R and circumferential C are orthogonal to each other.

[0056] The terms internal and external, respectively, are used in reference to a radial direction R such that the internal part or face of an element is closer to the longitudinal axis X than the external part or face of the same element.

[0057] The turbomachine 10 may be a turbojet or a turboprop. The turbomachine 10 extends around the longitudinal axis X. The turbomachine 10 may comprise a fan 13, at least one compressor 14, 15, a combustion chamber 16, at least one turbine 17, 18, and a gas exhaust nozzle.

[0058] In the non-limiting exemplary embodiment shown in Figure 2, the turbomachine 10 is a twin-spool, twin-flow turbojet engine, shrouded by a nacelle 12. The turbomachine 10 comprises, from upstream to downstream, 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. The high-pressure turbine 17 rotates the high-pressure compressor 15 via a high-pressure shaft, and the low-pressure turbine 18 rotates the low-pressure compressor 14 via a low-pressure shaft. The low-pressure turbine 18 can also rotate the fan 13 either directly via the low-pressure shaft, or via a reduction gear arranged between the low-pressure turbine 18 and the fan 13, the reduction gear being rotated by the low-pressure shaft.The compressors 14 and 15, the combustion chamber 16 and the turbines 17 and 18 form a gas generator. During operation of the turbomachine 10 illustrated in FIG. 2, an air flow enters the turbomachine 10 through an air inlet upstream of the nacelle 12, passes through the fan 13 and then divides into a central primary flow and a secondary flow. The primary flow flows in a primary flow vein 21A and passes through the compressors 14 and 15, the combustion chamber 16 and the turbines 17 and 18, and the secondary flow flows in a secondary flow vein 21B which is concentric with the primary flow vein 21A and is delimited radially outwardly by the nacelle 12.

[0059] In general, a 30 distributor vane 25 of the turbine 17, 18 comprises a blade and two platforms which radially delimit between them a circumferential portion of the annular primary flow vein in which the blade extends. A blade 30 of the movable wheel 26 of the turbine 17, 18 comprises a single platform, which internally delimits the primary flow vein. The fluid passing through the turbine 17, 18 flows mainly in this primary flow vein.

[0060] During operation of a conventional turbine 17, 18, the interaction of the fluid with the distributors 25 and the moving wheels 26 produces vortices at the level of the blade platforms, forming so-called “secondary” flows.

[0061] In particular, Figure 1 illustrates a portion of a blading 25, 26 of a conventional turbomachine, more particularly a portion of two blades 1 of a turbine nozzle 25, these blades 1 being circumferentially adjacent to each other. Figure 1 shows more particularly a radially internal portion of a blade 2 and a platform 3 of each of the blades 1. The blade 2 of each blade 1 comprises a leading edge 4, a trailing edge 5, a pressure side wall 6 and an extrados wall 7. The platform 3 is common to the two blades 1 and is an internal platform which delimits radially inwards a circumferential portion of a primary flow vein in which a fluid flows in a direction S1 going from the leading edge 4 towards the trailing edge 5 of blade 2.

[0062] Given the typical viscosity of the fluid flowing in the primary flow vein, its flow along the surface of the platform 3 has a velocity gradient GV1 such that, in the vicinity of this surface, the velocity of a layer of fluid is lower the closer this layer is to this surface. In other words, due to friction with the platform 3, the flow at the platform 3 has a low velocity, the fluid momentum being low. The fluid flowing in the primary flow vein is also subjected to a pressure gradient GP1 oriented in this example from the intrados wall 6 of the blade 2 of the vane 1 illustrated on the right in FIG. 1 towards the extrados wall 7 of the blade 2 of the adjacent vane 1 illustrated on the left in FIG. 1.The pressure gradient GP1 is generally sufficient to deflect the fluid layers flowing near the surface of the platforms 3, from blade 1 shown on the right in Figure 1 to the adjacent blade 1 shown on the left in Figure 1.

[0063] This results in the appearance of different types of vortices. A first type of vortices T1, called "horseshoe", takes the form of two counter-rotating branches distributed on either side of the blade 2 of the vane 1. A second type of vortices T2, called "passage vortices", develops between two adjacent blades 2 of two adjacent vanes 1. A third type of vortices T3, called "corner vortices", runs along the connection lines between the blade 2 and the platform 3 of the vane 1.

[0064] Such secondary flows T1, T2 and T3, which typically occur at the root and tip of the blades 2, are not oriented in the direction S1 of the main flow of the fluid passing through the primary flow vein and consequently lead to a reduction in the efficiency and an increase in the kerosene consumption of the turbomachine comprising a conventional blading 25, 26. Figure 4 and Figure 5 illustrate non-limiting examples of a blading 25, 26 of a turbomachine 10. The blading 25, 26 of a turbomachine 10 is intended to be mounted around the longitudinal axis X and comprises:

[0065] - a blade 31 which extends radially with respect to the longitudinal axis X and which has an aerodynamic profile delimited axially upstream by a leading edge 51 and downstream by a trailing edge 52, the blade 31 further comprising a lower surface wall 54 and an upper surface wall 53 opposite the lower surface wall 54, the lower surface wall 54 and the upper surface wall 53 each connecting the leading edge 51 to the trailing edge 52; and

[0066] - a platform 32, 33 comprising a flow path surface 321 from which the blade 31 extends, the platform 32, 33 being intended to delimit a flow path of a primary flow 21A of the turbomachine 10 in operation, the flow dividing upstream of the leading edge 51 of the blade 31 during operation of the turbomachine 10 on the one hand into an extrados flow EE flowing on the side of the extrados wall 53 of the blade 31 and on the other hand into an intrados flow El flowing on the side of the intrados wall 54 of the blade 31; and

[0067] - an internal channel 34 which has a suction opening 35 and an ejection opening 36 which are each arranged on the side of the intrados wall 54 of the blade 31 and which each open onto the vein surface 321 of the platform 32, 33, the ejection opening 36 opening downstream of the suction opening 35 and the suction opening 35 opening in the direction of the intrados flow E1.

[0068] The blade 30 provided with such an internal channel 34 makes it possible to suck in a portion of the fluid flowing along the vein surface 321 of the platform 32, 33 and to prevent this portion of the fluid from contributing to the formation of secondary flows. By opening “on” the vein surface 321, it is understood that the suction opening 35 and the ejection opening 36 each form at least one opening made in the vein surface 321. By opening “toward” the intrados flow E1, it is understood that the suction opening 35 comprises an opening opening at least partially at a point of the intrados flow E1.

[0069] Indeed, given the typical viscosity of the fluid flowing in the flow vein of the primary flow 21A, also called primary flow vein 21A, its flow along the vein surface 321 of the platform 32, 33 has a velocity gradient such that, in the vicinity of this vein surface 321, the velocity of a layer of fluid is all the lower the closer this layer is to the vein surface 321. The fluid flowing in the primary flow vein 21A is also subjected to a pressure gradient oriented from the intrados wall 54 of the blade 31 towards an extrados wall 530 of a circumferentially adjacent blade 310 of the blading 25, 26. The pressure gradient tends to deflect the layers of fluid flowing near the vein surface 321 of the platform 32, 33, from the blade 31 towards the circumferentially adjacent blade 310.

[0070] Now, the fluid circulating in the primary flow vein 21A and arriving at the suction opening 35 of the blading 25, 26 described above is sucked into the internal channel 34 taking into account the static pressure differential between the region of the primary flow vein 21A surrounding the suction opening 35, called the suction zone, and the region of the primary flow vein 21A surrounding the ejection opening 36, called the ejection zone. In a turbine 17, 18 in operation, the static pressure is in fact significantly lower downstream of a blade 31 than upstream of the blade 31. Consequently, the static pressure is significantly lower at the ejection zone, which is located downstream of the suction zone, than at the suction zone.

[0071] Thus, this internal channel geometry 34 as described above makes it possible to take a portion of the primary flow from the primary flow vein 21A and eject it at the ejection opening 36 under the effect of the static pressure differential between the suction opening 35 and the ejection opening 36. The suction of the boundary layer thus takes place in the suction zone before and / or during the development of the secondary vortices, which makes it possible to reduce the secondary flows. The sucked flow is accelerated in the internal channel 34, and reinjected into the ejection zone downstream of the suction zone, so as to re-energize the boundary layer in the ejection zone.The blading 25, 26 thus prevents the intrados flow E1 from deviating towards the extrados wall 530 of the circumferentially adjacent blade 310 due to the pressure gradient between the intrados wall 54 of the blade 31 and the extrados wall 530 of the circumferentially adjacent blade 310, at which the pressure is higher than the pressure at the intrados wall 54 of the blade 31. The suction of the boundary layer and the ejection to re-energize the boundary layer are thus improved, which makes it possible to improve the aerodynamic efficiency of the blading 25, 26.

[0072] The blading 25, 26 thus makes it possible to limit the formation of secondary flows and to reduce the intensity of the secondary flows which are likely to occur. Thus, the blading 25, 26 makes it possible to reduce the aerodynamic losses linked to the development of the secondary flows. The blading 25, 26 thus makes it possible to improve the efficiency and reduce the kerosene consumption of the turbomachine 10. In particular, the blading 25, 26 makes it possible to reduce the losses downstream of the blade 31, by reducing the angle and Mach vein distortion generated by the secondary flows.

[0073] The internal channel 34 forms a passive suction system that does not require any additional suction device, for example mechanically or electrically controlled. Indeed, the suction and reintroduction of gases into the primary flow stream 21A operates naturally thanks to the static pressure differential between the suction zone and the ejection zone downstream of the suction zone. The passive suction system thus constitutes a significant advantage compared to a so-called "active" system requiring external intervention, in particular it is simple to manufacture and implement, and robust.

[0074] In addition, the part of the sucked fluid is ejected into the primary flow path 21A, and therefore contributes to driving the turbomachine 10. In particular, when the blading 25, 26 is a nozzle 25 of a turbine 17, 18 of the turbomachine 10, the invention makes it possible to isolate in the nozzle 25 the boundary layer, the source of the appearance of secondary phenomena, in order to then reintroduce it into the primary flow which was depleted thereof. The reintroduction of air occurs substantially in the direction of propagation and before the primary flow reaches the consecutive movable wheel 26 in the primary flow path 21A, and therefore fully participates in the rotation of the movable wheel 26 of the same stage and located directly downstream of the nozzle 25. In other words, the part of the fluid thus ejected into the primary flow path 21A constitutes a part of the flow rate of the fluid driving the consecutive movable wheel 26.The distributor 25 comprising the blade 31, the suction opening 35 and the ejection opening 36, is located upstream of said moving wheel 26. Thus, the flow rate in the primary flow vein 21A is unchanged, and the flow can work normally in order to provide mechanical energy to the moving wheel 26. The gain in the efficiency of the turbine 17, 18 is therefore significant, the primary flow being used in its entirety while being less subject to parasitic vortices which disperse the energy.

[0075] The blade 31 extends in the primary flow vein 21 A of the turbomachine 10 delimited by the vein surface 321 of the platform 32, 33. The intrados wall 54 and the extrados wall 53 of the blade 31 each connect the leading edge 51 and the trailing edge 52 of the blade 31, and are separated by a distance corresponding to a thickness of the blade 31. The leading edge 51 of the blade 31 forms an upstream end of the blade 31 in the primary flow path 21A. The leading edge 51 of the blade 31 is thus configured to extend opposite the flow of gases in the turbomachine 10. The trailing edge 52 of the blade 31 corresponds to the rear part of the aerodynamic profile, where the intrados flow El and the extrados flow EE meet, and forms a downstream end of the blade 31 in the primary flow path 21A.

[0076] The suction opening 35 opens onto the vein surface 321 at the level of the intrados flow El. The ejection opening 36 opens onto the vein surface 321 downstream of the intrados flow El and downstream of the suction opening 35.

[0077] The blade 31 may be a blade 31 of a vane 30 of the vane 25, 26. The vane 25, 26 then comprises a vane 30 which comprises the vane 31 with an aerodynamic profile suitable for being placed in the air flow when the turbomachine 10 is in operation in order to generate lift, and a root configured to be fixed to a rotating or fixed hub of the vane 25, 26 at an internal end of the vane 30. The vane 30 may be a composite vane comprising a structure made of composite material comprising a fiber reinforcement obtained by three-dimensional weaving and a matrix in which the fiber reinforcement is embedded. The fiber reinforcement may be formed from a single-piece fiber preform obtained by three-dimensional or multi-layer weaving with varying thickness. The fibrous reinforcement may then comprise warp and weft strands which may in particular comprise carbon, glass, basalt and / or aramid fibers.The matrix may be a polymer matrix, for example epoxy, bismaleimide or polyimide. The blade 30 may be formed by molding using a vacuum resin injection process of the RTM (for “Resin Transfer Molding) type, or VARRTM (for Vacuum Resin Transfer Molding).

[0078] The blade 31 may be formed from a plurality of blade sections 31 stacked along a blade axis 31 from a radially inner end to a radially outer end of the blade 31.

[0079] The blade 31 further has a chord defined, in a plane normal to the blade axis 31, by a fictitious straight line segment connecting the leading edge 51 and the trailing edge 52 of the blade.

[0080] 31.

[0081] The platform 32, 33 may further comprise a second surface 322 opposite the vein surface 321. The internal channel 34 is formed in the platform 32, 33 between the vein surface 321 and the second surface 322.

[0082] The platform 32, 33 may be an internal platform 32, the vein surface 321 of the internal platform 32 being adapted to delimit radially inwardly the primary flow vein 21A. The second surface 322 of the internal platform 32 is then internal relative to the vein surface 321. Alternatively, the platform 32, 33 may be an external platform 33, the vein surface 321 of the external platform 33 being adapted to delimit radially outwardly the primary flow vein 21A. The second surface 322 of the external platform 32, 33 is then external relative to the vein surface 321. The primary flow vein 21A is substantially annular. For example, a mobile wheel 26 of a compressor 14, 15 or turbine 17, 18 generally comprises an internal platform

[0083] 32, and a distributor 25 of compressor 14, 15 or turbine 17, 18 generally comprises an internal platform 32 and an external platform 33.

[0084] In the schematic and simplified representation of Figure 4, the vein surface 321 and the second surface 322 are planar and parallel to each other. Of course, each of these surfaces 321, 322 may have a non-planar geometry and be generally oriented in an oblique direction relative to the longitudinal L and radial R directions. Furthermore, the leading edge 51 and the trailing edge 52 are rectilinear and parallel to each other. Of course, each of these edges 51, 52 may have a non-rectilinear geometry and be generally oriented in an oblique direction relative to the radial direction R. In particular, a platform 32, 33 may have hollows and bumps on the vein surface 321.

[0085] An imaginary line located equidistant from the leading edge 51 and the trailing edge 52 of the blade 31 delimits an upstream part and a downstream part of the platform 32, 33. The flow flows in the primary flow vein 21A in a flow direction S1 going from the leading edge 51 towards the trailing edge 52 of the blade 31 and from the upstream part towards the downstream part of the platform 32, 33.

[0086] The blading 25, 26 may comprise several blades 30 and / or several platforms 32, 33 as described above. In particular, the blading 25, 26 may comprise the same number of blades 30 and platforms 32, 33, each blade 30 being mounted on a respective platform 32, 33, in particular in the case of blades 30 of a moving wheel 26. Alternatively, several blades 30 may be mounted on the same platform 32, 33, in particular in the case of blades 30 of a distributor 25. For example, the blades 30 may be mounted four by four on respective platforms 32, 33, four blades 30 being mounted on the same platform 32, 33.

[0087] The blade 25, 26 extends radially around the longitudinal axis X and may further comprise a blade 310 circumferentially adjacent to the blade 31. Said circumferentially adjacent blade 310 extends radially with respect to the longitudinal axis X and has an aerodynamic profile delimited axially upstream by a leading edge 510 and downstream by a trailing edge 520. The circumferentially adjacent blade 310 further comprises a pressure side wall 540 and an extrados wall 530 opposite the pressure side wall 540, the pressure side wall 540 and the extrados wall 530 each connecting the leading edge 510 to the trailing edge 520. The circumferentially adjacent blade 310 may be adapted to extend radially from the vein surface 321 of the platform 32, 33 in the primary flow vein 21A so that the extrados wall 530 of the circumferentially adjacent blade 310 is located opposite the intrados wall 54 of the blade 31.

[0088] The circumferentially adjacent blade 310 may be a blade of a circumferentially adjacent vane 300 of the blading 25, 26. The blading 25, 26 then comprises the vane 30 and the circumferentially adjacent vane 300 of the vane 30.

[0089] The circumferentially adjacent blade 300 may be substantially identical to the blade 30. The circumferentially adjacent blade 300 is adjacent to the blade 30. The blade 30 and the circumferentially adjacent blade 300 may be circumferentially distributed side by side in the primary flow path 21A. The intrados flow E1 flows between the intrados wall 54 of the blade 31 and the extrados wall 530 of the circumferentially adjacent blade 310. When the circumferentially adjacent blade 310 of the circumferentially adjacent vane 300 is adapted to extend from the vein surface 321 of the platform 32, 33, the platform 32, 33 is common to the vane 30 and the circumferentially adjacent vane 300. The internal channel 34 is formed in the platform 32, 33 between the blade 31 and the circumferentially adjacent vane 310.The non-limiting example of Figure 5 illustrates such a blading 25, 26 comprising a blade 31 and a circumferentially adjacent blade 310 mounted on a common platform 32, 33. The blade 31 is shown on the right in Figure 5, and the circumferentially adjacent blade 310 is shown on the left in Figure 5.

[0090] Alternatively, the vane 25, 26 may further comprise an adjacent platform substantially identical to the platform 32, 33. The platform 32, 33 and the adjacent platform are fixed relative to each other and together delimit at least a portion of the primary flow vein 21A. The circumferentially adjacent blade 310 is adapted to extend from a vein surface of the adjacent platform into the primary flow vein 21A such that the extrados wall 530 of the circumferentially adjacent blade 310 is located opposite the intrados wall 54 of the blade 31. The internal channel 34 may be formed in the platform 32, 33 or in the circumferentially adjacent platform.

[0091] The position, dimensions and geometry of the suction opening 35 and the ejection opening 36 are chosen according to the characteristics of the flow and the secondary vortices formed at the level of the blades 25, 26, and according to the desired level of re-energization of the boundary layer, and are determined so as to size the flow rate of sucked air, as well as the speed and angle of the ejected air, in order to minimize mixing losses. In particular, the ejection opening 36 can be configured to redirect the gas flow so as to re-energize the boundary layer at the level of the ejection opening 36.The configuration of the suction opening 35 and the ejection opening 36 may result from a compromise between the pressure differential between the suction opening 35 and the ejection opening 36, which is to be increased to increase the flow rate of sucked fluid, and the length of the internal channel 34, which is to be decreased to reduce the aerodynamic losses in the internal channel 34.

[0092] The suction opening 35 and / or the ejection opening 36 may have a circular shape, an oblong shape, a slot shape, a flared shape, or any other shape suitable for sucking and / or ejecting an air flow into the primary flow path 21 A. Alternatively, the suction opening 35 and / or the ejection opening 36 may comprise a plurality of orifices, for example a plurality of circular, oblong, or slot-shaped orifices. For example, the suction opening 35 and / or the ejection opening 36 may have an ovoid, rectangular, triangular, parallelepipedal, conical, prismatic, or any other section that a person skilled in the art might consider.When the suction opening 35 and / or the ejection opening 36 comprises a plurality of orifices, for example circular orifices, the orifices may be arranged in a staggered manner on the vein surface 321 of the platform 32, 33, so as to efficiently collect the air flow contiguous to the vein surface 321. The internal channel 34 connects the circular orifices of the suction opening 35 to the ejection opening 36 and / or connects the suction opening 35 to the circular orifices of the ejection opening 36.

[0093] When the suction opening 35 and / or the ejection opening 36 comprises a plurality of orifices in the form of slots, the internal channel 34 splits into a plurality of passages each opening onto a slot of the suction opening 35 and / or the ejection opening 36.

[0094] The suction opening 35 and / or the ejection opening 36 may comprise an intrusive scoop, a non-intrusive scoop, or one or a plurality of fins.

[0095] The suction opening 35 and / or the ejection opening 36 can be obtained for example by drilling or additive manufacturing.

[0096] Figure 6a, Figure 6b and Figure 6c illustrate different types of suction openings 35 and / or ejection openings 36 according to the invention. In the example of Figure 6a, the internal channel 34 comprises a suction opening 35 having seventeen circular orifices. In the example of Figure 6b, the internal channel 34 comprises a suction opening 35 in the form of a curved slot arranged so as to run along the intrados wall 54 of the blade 31. The ejection opening 36 may be identical to the suction opening 35 of Figure 6a or Figure 6b. In the example of Figure 6c, the internal channel 34 comprises a suction opening 35 in the form of a curved slot, and an ejection opening 36 in the form of a slot.

[0097] The intrados flow El can flow generally between a separation point A located upstream of the leading edge 51 of the blade 31 and corresponding to a point at which the intrados flow El and the extrados flow EE divide, and an impact point B located downstream of the leading edge 51 of the blade 31 and corresponding to a point at which the intrados flow El comes into contact with a blade 310 circumferentially adjacent to the blade 31. The vortices begin to form at the separation point A, and impact the circumferentially adjacent blade 310 at the impact point B. The intrados flow El can be likened to a flow line which extends between the separation point A and the impact point B.

[0098] The separation point A is the point at which the flow circulating in the primary flow vein 21 A and arriving at the blade 31 separates into two, namely the intrados flow El, or intrados vortex, which is adapted to flow towards the trailing edge 52 of the blade 31 on the side of the intrados wall 54 of the blade 31, and the extrados flow EE, or extrados vortex, which is adapted to flow towards the trailing edge 52 of the blade 31 on the side of the extrados wall 53 of the blade 31. The separation point A may be located directly upstream of the leading edge 51, i.e. a distance along the longitudinal axis X between the separation point A upstream of the leading edge 51 and the leading edge 51 of the blade 31 is less than 10% of the chord of the blade 31.

[0099] The point of impact B is the point at which the intrados flow E1 comes into contact with the extrados wall 530 of the circumferentially adjacent blade 310. A distance between the point of impact B and the leading edge 51 of the blade 31 along the longitudinal axis X may be less than, or substantially equal to, a distance between the point of impact B and the trailing edge 52 of the blade 31. For example, the point of impact B may have a position between 30% and 50% of the chord of the blade 31, for example between 35% and 45% of the chord of the blade 31, along the longitudinal axis X. A distance between the point of impact B and the intrados wall 54 of the blade 31 along the circumferential axis may be strictly greater than, or substantially equal to, a distance between the trailing edge 52 of the blade 31 and the intrados wall 54 of the blade 31 along the circumferential axis.The point of impact B is thus located on an opposite side of the intrados wall 54 relative to the chord of the blade 31. The point of impact B may be located substantially on the extrados wall 530 of the circumferentially adjacent blade 310. The point of impact B may correspond substantially to a point on the extrados wall 530 of the circumferentially adjacent blade 310 which is closest to the blade 31 in a circumferential direction C perpendicular to the longitudinal direction L and to the radial direction R.

[0100] The suction opening 35 opens onto the vein surface 321 of the platform 32, 33 on the intrados flow El. In other words, at least a portion of the suction opening 35 is located at the intrados flow El, for example at a point on the flow line of the intrados flow El. For example, at least a portion of the slot, the oblong shape, one or more circular orifices of the suction opening 35, is located on the intrados flow El.

[0101] When the blade 25, 26 comprises a blade 31 and a circumferentially adjacent blade 31, the intrados flow El flows generally between the separation point A and the impact point B located downstream of the leading edge 51 of the blade 31 and corresponding to a point at which the intrados flow El comes into contact with the extrados wall 530 of the circumferentially adjacent blade 310.

[0102] The suction opening 35 and / or the ejection opening 36 may extend in a main direction. The main direction corresponds to a direction in which a dimension of the suction opening 35 and / or the ejection opening 36 is the largest. For example, in the case of an oblong suction opening 35 and / or an ejection opening 36 having a length and a width, the main direction corresponds to the direction of the length of the oblong opening. In the case of a suction opening 35 and / or an ejection opening 36 comprising a plurality of orifices, the main direction corresponds to a direction of the largest dimension over which the orifices extend. In the case of a suction opening 35 and / or an ejection opening 36 in the form of a slot, the main direction corresponds to a direction of the largest dimension of the slot.

[0103] Figure 5 illustrates different possibilities for arranging the suction opening 35 and / or the ejection opening 36. In the following, when an element is described as “substantially parallel” or “substantially perpendicular” to the intrados flow El or to a wall of the blade 31, it is understood that the element may have an inclination of a few degrees, for example an inclination of less than 5°, relative to the parallel or to the perpendicular to the intrados flow El or to the wall of the blade 31. When an element is located “at the level” of another element, it is understood that the element is located at a distance of less than 5% of the chord of the blade 31 from the other element.

[0104] The suction opening 35 can correspond to one of the following four suction openings A1, A2, A3, A4:

[0105] - a first suction opening 35, A1 which has an opening which opens onto the vein surface 321 and which extends in a main direction substantially perpendicular to the direction of the intrados flow E1, the first suction opening 35, A1 opening in the direction of the leading edge 51 or directly upstream of the leading edge 51 of the blade 31;

[0106] - a second suction opening 35, A2 which has an opening which opens onto the vein surface 321 and which extends in a main direction substantially perpendicular to the direction of the intrados flow E1, A2, the second suction opening 35, A2 opening downstream of the leading edge 51 of the blade 31, the second suction opening 35, A2 opening for example closer to the separation point A than to the impact point B;

[0107] - a third suction opening 35, A3 which has an opening which opens towards the point of impact B or directly upstream of the point of impact B; or

[0108] - a fourth suction opening 35, A4 which has an opening which opens onto the vein surface 321 and which extends in a main direction substantially parallel to the direction of the intrados flow E1, the fourth suction opening 35, A4 opening between the leading edge 51 and the trailing edge 52 of the blade 31 in a circumferential direction C.

[0109] The first suction opening 35, A1 makes it possible to capture the boundary layer of the intrados flow El very early, at the beginning or even before the formation of the vortices of the intrados flow El. The first opening 35, A1 is located at the leading edge 51. When the first suction opening 35, A1 opens directly upstream of the leading edge 51, a distance along the longitudinal axis X between the first suction opening 35, A1 upstream of the leading edge 51 and the leading edge 51 is less than 10% of the chord of the blade 31. The first suction opening 35, A1 can open in the direction of the separation point A or directly downstream of the separation point A, that is to say at a distance less than 10% of the chord of the blade 31 from the separation point A, downstream of the latter. The first suction opening 35, A1 opens onto the vein surface 321 in the upstream part of the platform 32, 33.

[0110] The second suction opening 35, A2 makes it possible to capture the vortices of the intrados flow El during formation. The second suction opening 35, A2 is located downstream of the leading edge 51 of the blade 31 and downstream of the separation point A. The second suction opening 35, A2 may open towards the leading edge 51, i.e. closer to the leading edge 51 than to the trailing edge 52, the second suction opening 35, A2 opening onto the vein surface 321 in the upstream part of the platform 32, 33. A distance along the longitudinal axis X between the leading edge 51 of the blade 31 and the second suction opening 35, A2 may be between 1% and 20%, for example between 5% and 10%, of the chord of the blade 31. The second suction opening 35, A2 may open substantially equidistant between the extrados wall 53 of the blade 31 and the wall extrados 530 of the circumferentially adjacent blade 310.

[0111] The third suction opening 35, A3 makes it possible to capture the vortex of the intrados flow E1 before its impact on the extrados wall 530 of the circumferentially adjacent blade 310. The third suction opening 35, A3 is located at the point of impact B or directly upstream of the point of impact B. In other words, the third suction opening 35, A3 opens closer to the leading edge 51 than to the trailing edge 52 of the blade 31 along the longitudinal axis X, or substantially equidistant from the leading edge 51 and the trailing edge 52 of the blade 31 along the longitudinal axis X, for example opens between 30% and 50% of the chord of the blade 31, for example between 35% and 45% of the chord of the blade 31.The third suction opening 35, A3 is further from the intrados wall 54 of the blade 31 than the trailing edge 52 of the blade 31 along the circumferential axis, or has a position along the circumferential axis which corresponds substantially to a position of the trailing edge 52 of the blade 31. The third suction opening 35, A3 may open onto the point of the extrados wall 530 of the circumferentially adjacent blade 310 closest to the blade 31 in the circumferential direction C. When the third suction opening 35, A3 opens onto the point of impact B, the third suction opening 35, A3 opens at the extrados wall 530 of the circumferentially adjacent blade 310.A distance between the third suction opening 35, A3 and the extrados wall 530 of the circumferentially adjacent blade 310 in the longitudinal direction L and / or in the circumferential direction C may be less than 5% of the chord of the blade 31. The main direction of the third suction opening 35, A3 may be substantially parallel to the direction of the intrados flow E1 and / or may be substantially tangent to the extrados wall 530 of the circumferentially adjacent blade 310.

[0112] The fourth suction opening 35, A4 makes it possible to capture the boundary layer which deflects from the intrados wall 54 of the blade 31 towards the extrados wall 530 of the circumferentially adjacent blade 310, and which continues to feed the vortices of the intrados flow El. Indeed, the vortices of the intrados flow El are also fed by the flow along the intrados wall 54 of the blade 31, which is also sucked towards the extrados wall 530 of the circumferentially adjacent blade 310. The fourth suction opening 35, A4 is located between the leading edge 51 and the trailing edge 52 of the blade 31 in the circumferential direction C, for example can open closer to the trailing edge 52 than to the leading edge 51, the fourth suction opening 35, A4 being distant from the intrados wall 54 of the blade 31 by a certain distance along the circumferential axis.The fourth suction opening 35, A4 may open close to the leading edge 51 than to the trailing edge 52 of the blade 31 in the longitudinal direction L, the fourth suction opening 35, A4 opening into the upstream part of the platform 32, 33. The fourth suction opening 35, A4 may open between the separation point A and the impact point B, for example open closer to the separation point A than to the impact point B. The fourth suction opening 35, A4 opens between the blade 31 and the circumferentially adjacent blade 310, for example may open substantially equidistant from the blade 31 and the circumferentially adjacent blade 310. The fourth opening 35, A4 is slightly offset downstream in the representation of FIG. 5, in order to preserve the legibility of the figure.

[0113] The ejection opening 36 can correspond to one of the following three ejection openings E1, E2, E3:

[0114] - a first ejection opening 36, E1 located closer to the leading edge 51 than to the trailing edge 52 of the blade 31, which opens towards the intrados wall 54 of the blade 31;

[0115] - a second ejection opening 36, E2 located substantially between the leading edge 51 and the trailing edge 52 of the blade 31, which opens towards the intrados wall 54 of the blade 31, the second ejection opening 36, E2 preferably having a main direction substantially parallel to the intrados wall 54 of the blade 31; or

[0116] - a third ejection opening 36, E3 located closer to the trailing edge 52 than to the leading edge 51 of the blade 31, and which preferably opens towards the trailing edge 52 of the circumferentially adjacent blade 310. The first ejection opening 36, E1 makes it possible to re-energize the boundary layer at the intrados wall 54 of the blade 31, in a zone of the blading 25, 26 which is located closer to the leading edge 51 than to the trailing edge 52 of the blade 31, therefore before the boundary layer begins to be deflected. The first ejection opening 36, E1 opens onto the vein surface 321 in the upstream part of the platform 32, 33.By opening "towards" the intrados wall 54, it is understood that the first ejection opening 36, E1 is arranged so that a distance along the circumferential axis between the first ejection opening 36, E1 and the intrados wall 54 is less than 50% of a distance along the circumferential axis between the leading edge 51 and the trailing edge 52 of the blade 31. The first ejection opening 36, E1 may be located on the intrados wall 54 of the blade 31. The main direction of the first ejection opening 36, E1 may be substantially perpendicular to the intrados wall 54 of the blade 31.

[0117] The second ejection opening 36, E2 makes it possible to re-energize the boundary layer at the level of the intrados wall 54 of the blade 31, along the blade 31, therefore before the boundary layer comes to feed the vortices in formation. By opening “towards” the intrados wall 54, it is understood that the second ejection opening 36, E2 is located close to the intrados wall 54 so that a distance along the circumferential axis between the second ejection opening 36, E2 and the intrados wall 54 is less than 50% of a distance along the circumferential axis between the leading edge 51 and the trailing edge 52 of the blade 31. The second ejection opening 36, E2 may open onto the vein surface 321 in the upstream part and / or in the downstream part of the platform 32, 33.A main direction of the second ejection opening 36, E2 substantially parallel to the intrados wall 54 makes it possible to best energize the flow at the level of the second ejection opening 36, E2.

[0118] The third ejection opening 36, E3 makes it possible to energize the boundary layer in a zone of the blading 25, 26 which is located near the trailing edge 52 of the blade 31, that is to say closer to the trailing edge 52 than to the leading edge 51 of the blade 31. The third ejection opening 36, E3 opens onto the flow path surface 321 in the downstream part of the platform 32, 33. The third ejection opening 36, E3 may be located directly upstream or directly downstream of the trailing edge 52 of the blade 31 along the longitudinal axis X. The third ejection opening 36, E3 may have a distance along the circumferential axis relative to the trailing edge 52 of the blade 31 corresponding substantially to a distance along the circumferential axis from the leading edge 51 at the trailing edge 52 of the blade 31.The third ejection opening 36, E3 may open substantially equidistant between the intrados wall 54 of the blade 31 and the extrados wall 53 of the circumferentially adjacent blade 310, or may open closer to the extrados wall 530 of the circumferentially adjacent blade 310 than to the intrados wall 54 of the blade 31. The third ejection opening 36, E3 may be substantially parallel to the flow flowing in the primary flow vein 21A, in order to best energize the flow at the third ejection opening 36, E3.

[0119] The combination of the suction opening 35 and the ejection opening 36 is chosen so as to ensure a sufficient pressure gradient between the suction zone and the ejection zone, the total pressure in the suction zone being at least greater than the static pressure in the ejection zone, and so as to minimize the length of the internal channel 34, in order to minimize pressure losses. All combinations of the first, second, third or fourth suction opening 35, A1, A2, A3, A4 with the first, second or third ejection opening 36, E1, E2, E3 are possible.

[0120] In a particular embodiment, the suction opening 35 corresponds to the first suction opening A1 and the ejection opening 36 corresponds to the third ejection opening E3. This particular embodiment makes it possible to establish a significant pressure difference between the first suction opening 35, A1 and the third ejection opening 36, E3, which makes it possible to increase the flow rate of air circulating within the internal channel 34. The ejection opening 36, E3 is located in a low pressure zone, which makes it possible to optimize the effectiveness of the reduction of vortices by the vanes 25, 26, despite the pressure losses due to the significant length of the internal channel 34.

[0121] In other embodiments, the suction opening 35 corresponds to the first suction opening AI and the ejection opening 36 corresponds to the first ejection opening E1, or the suction opening 35 corresponds to the second suction opening A2 and the ejection opening 36 corresponds to the third ejection opening E3, or the suction opening 35 corresponds to the third suction opening A3 and the ejection opening 36 corresponds to the third ejection opening E3, or the suction opening 35 corresponds to the fourth suction opening A4 and the ejection opening 36 corresponds to the second ejection opening E2.

[0122] The internal channel 34 is formed in the platform 32, 33, between the vein surface 321 and the second surface 322 of the platform 32, 33. The internal channel 34 may be a tubular-shaped channel. The internal channel 34 has a shape and dimensions adapted as a function of the flow rate of air drawn in and ejected, that is to say as a function of the flow rate of air circulating in the internal channel 34, so as to give the flow rate of air drawn in by the suction opening 35 an optimized speed and angle at the ejection opening 36. In this respect, the shapes and dimensions of the internal channel 34 are determined according to the specific case, in particular with regard to the predefined location of the blading 25, 26 within the primary flow vein 21A.

[0123] The internal channel 34 may comprise one or more undulations, in other words one or more curvatures, in particular if it is a question of adapting the shape of the internal channel 34 to a particular size within the blade 31 and / or the platform 32, 33. The internal channel 34 has an aerodynamic shape making it possible to reduce aerodynamic losses during the flow of the fluid sucked into the internal channel 34.

[0124] A section of the internal channel 34 of the ejection opening 36 may be smaller than a section of the internal channel 34 of the suction opening 35. A surface area of ​​the ejection opening 36 may be smaller than a surface area of ​​the suction opening 35. The internal channel 34 thus has a flared shape reducing towards the ejection opening 36. Thus, the flow velocity at the ejection opening 36 at the outlet of the internal channel 34 is increased, which makes it possible to optimally re-energize the boundary layer at the ejection opening 36.

[0125] The blading 25, 26 may comprise several internal channels 34 formed in the same platform 32, 33, each internal channel 34 comprising a suction opening 35 and an ejection opening 36 as described above. The several internal channels 34 may be independent or connected together. A blading 25, 26 comprising several internal channels 34 makes it possible to suck the boundary layer at several suction zones, and to re-energize the boundary layer at several ejection zones.

[0126] The internal channel 34 may be hollowed out in the platform 32, 33. The internal channel 34 may be manufactured by casting, or by additive manufacturing, without limitation by metal laser fusion on a powder bed, in particular when the internal channel 34 and / or the platform 32, 33 has a complex geometry. Preferably, the blade 31 and the platforms 32, 33 are manufactured in a single piece.

[0127] The blade 25, 26 of the turbomachine 10 as described above may be a distributor

[0128] 25. The platform 32, 33 of the distributor 25 may be an internal platform 32 and / or an external platform 33 as described above. In particular, the distributor 25 may comprise an internal platform 32 and an external platform 33 as described above, a first internal channel 34 as described above formed in the internal platform 32 and a second internal channel 34 as described above formed in the external platform 33. The distributor 25 is preferably a distributor 25 of a low pressure turbine 18 or a high pressure turbine 17. Alternatively, the distributor 25 may be a distributor 25 of a low pressure compressor 14 or a high pressure compressor 15.

[0129] The blade 25, 26 of the turbomachine 10 as described above may be a moving wheel

[0130] 26. The platform 32, 33 of the movable wheel 26 is an internal platform 32 as described above, the internal channel 34 being formed in the internal platform 32. The movable wheel 26 is preferably a movable wheel 26 of a low-pressure turbine 18 or a high-pressure turbine 17. Alternatively, the movable wheel 26 may be a movable wheel 26 of a low-pressure compressor 14 or a high-pressure compressor 15. A turbine 17, 18 of a turbomachine 10 may comprise at least one blading 25, 26 as described above, for example may comprise one or more distributors 25 and / or one or more movable wheels 26 as described above. Alternatively, a compressor 14, 15 of a turbomachine 10 may comprise at least one blading 25, 26 as described above. Each distributor 25 and / or moving wheel 26 comprises a plurality of blades 30 circumferentially distributed around the axis X.Each distributor 25 and / or mobile wheel 26 may comprise an alternation of conventional blades 31 and platforms 32, 33 and blades 31 and platforms 32, 33 as described above.

[0131] The moving wheels 26 are assembled axially to each other by annular flanges 27 and form the rotor of the turbine 18. The blades 30 of the moving wheel 26 can be connected to the turbine disk 24 by a foot secured to the internal platform 32. The distributors 25 are connected to a turbine casing 28 to form the stator of the turbine 18, for example by at least one attachment element secured to the external platform 33.

[0132] The turbine may be a low pressure turbine 18. Thus, Figure 3 illustrates by way of non-limiting example a low pressure turbine 18 comprising four stages, each stage comprising a distributor 25 and a moving wheel 26. Alternatively, the turbine may be a high pressure turbine 17. The longitudinal axis X corresponds to the axis of rotation of the rotor of the turbine 17, 18.

[0133] A turbomachine 10 may comprise a turbine 17, 18 comprising at least one blade 25, 26 as described above. The turbomachine 10 may be a double-spool turbomachine.

[0134] An aircraft may comprise at least one blade 25, 26 as described above, in particular may comprise at least one turbomachine 10 as described above.

[0135] Other embodiments may be envisaged and a person skilled in the art may readily modify the embodiments or examples set forth above or envisage others while remaining within the scope of the invention.

Claims

DEMANDS 1. Turbomachine blade (25, 26) (10) intended to be mounted around a longitudinal axis (X), and comprising: - a blade (31) which extends radially with respect to the longitudinal axis (X) and which has an aerodynamic profile delimited axially upstream by a leading edge (51) and downstream by a trailing edge (52), the blade (31) further comprising an intrados wall (54) and an extrados wall (53) opposite the intrados wall (54), the intrados wall (54) and the extrados wall (53) each connecting the leading edge (51) to the trailing edge (52); - a platform (32, 33) comprising a flow surface (321) from which the blade (31) extends, the platform (32, 33) being intended to delimit a primary flow channel (21 A) of a flow from the operating turbomachine (10), the flow dividing upstream of the leading edge (51) of the blade (31) during the operation of the turbomachine into, on the one hand, an extrados flow (EE) flowing along the extrados wall (53) of the blade (31) and, on the other hand, an intrados flow (El) flowing along the intrados wall (54) of the blade (31); and - an internal channel (34) which has an aspiration opening (35) and an ejection opening (36) which are each disposed on the side of the intrados wall (54) of the blade (31) and which each open onto the vein surface (321) of the platform (32, 33), the ejection opening (36) opening downstream of the aspiration opening (35) and the aspiration opening (35) opening in the direction of the intrados flow (El).

2. Turbomachine blade (25, 26) according to claim 1, wherein the suction opening (35) and / or the ejection opening (36) has a circular shape, an oblong shape, a slotted shape, a flared shape, or comprises a plurality of orifices.

3. Turbomachine blade (25, 26) of claim 1 or 2, wherein the lower surface flow (El) flows globally between a separation point (A) located upstream of the leading edge (51) of the blade (31) and corresponding to a point at which the lower surface flow (El) and the upper surface flow (EE) divide, and an impact point (B) located downstream of the leading edge (51) of the blade (31) and corresponding to a point at which the lower surface flow (El) comes into contact with a blade (310) circumferentially adjacent to the blade (31), wherein the suction opening (35) extends in a principal direction and corresponds to one of the following four suction openings (A1, A2, A3, A4). - a first aspiration opening (35, A1) which has an opening that leads to the vein surface (321) and which extends in a principal direction substantially perpendicular to the direction of the intrados flow (El), the first suction opening (35, A1) opening towards the leading edge (51) or directly upstream of the leading edge (51) of the blade (31); - a second suction opening (35, A2) which has an opening which opens onto the surface of the vein (321) and which extends along a main direction substantially perpendicular to the direction of the intrados flow (El), the second suction opening (35, A2) opening downstream of the leading edge (51) of the blade (31), the second suction opening (35, A2) opening closer to the separation point (A) than to the impact point (B); - a third suction opening (35, A3) which has an opening that leads towards the point of impact (B); or - a fourth suction opening (35, A4) which has an opening which opens onto the surface of the vein (321) and which extends in a main direction substantially parallel to the direction of the intrados flow (El), the fourth suction opening (35, A4) opening between the leading edge (51) and the trailing edge (52) of the blade (31) in a circumferential direction (C).

4. Turbomachine (10) blade (25, 26) according to any one of claims 1 to 3, wherein the ejection opening (36) extends along a principal direction and corresponds to one of the following three ejection openings (E1, E2, E3): - a first ejection opening (36, E1) located closer to the leading edge (51) than to the trailing edge (52) of the blade (31), which opens towards the intrados wall (54) of the blade (31); - a second ejection opening (36, E2) situated substantially between the leading edge (51) and the trailing edge (52) of the blade (31), which opens towards the lower surface (54) of the blade (31), the second ejection opening (36, E2) preferably having a principal direction substantially parallel to the lower surface (54) of the blade (31); or - a third ejection opening (36, E3) located closer to the trailing edge (52) than to the leading edge (51) of the blade (31) and which opens towards the trailing edge (52) of the blade (31).

5. Turbomachine blade (25, 26) according to claim 3 taken in combination with claim 4, wherein the suction opening (35) corresponds to the first suction opening (35, A1) and the ejection opening (36) corresponds to the third ejection opening (36, E3).

6. Turbomachine blade (25, 26) according to any one of claims 1 to 5, wherein a section of the internal channel (34) of the ejection opening (36) is smaller than a section of the internal channel (34) of the suction opening (35).

7. Turbomachine blade (25, 26) according to any one of claims 1 to 6, wherein the platform (32, 33) is an internal platform (32), the flow surface (321) of the internal platform (32) being adapted to radially delimit inwards the primary flow channel (21A).

8. Turbomachine blade (25, 26) of a turbomachine (10) according to any one of claims 1 to 7, extending radially about the longitudinal axis (X) and further comprising another blade circumferentially adjacent (310) to the blade (31), wherein said circumferentially adjacent blade (310) extends radially with respect to the longitudinal axis (X) and has an aerodynamic profile delimited axially upstream by a leading edge (510) and downstream by a trailing edge (520), the circumferentially adjacent blade (310) further comprising an intrados wall (540) and an extrados wall (530) opposite the intrados wall (54), the intrados wall (54) and the extrados wall (53) each connecting the leading edge (51) to the trailing edge (52), wherein the circumferentially adjacent blade (310) is adapted to extend radially from the vein surface (321) of the platform (32,33) in the primary flow channel (21 A) such that the upper surface (530) of the circumferentially adjacent blade (310) is located opposite the lower surface (54) of the blade (31), in which the lower surface flow (El) flows globally between a separation point (A) located upstream of the leading edge (51) of the blade (31) and corresponding to a point at which the lower surface flow (El) and the upper surface flow (EE) divide, and an impact point (B) located downstream of the leading edge (51) of the blade (31) and corresponding to a point at which the lower surface flow (El) comes into contact with the upper surface (530) of the circumferentially adjacent blade (310).

9. Turbomachine blade (25, 26) according to any one of claims 1 to 8, wherein the blade (25, 26) is a distributor (25) of a turbomachine turbine (17, 18) (10).

10. Turbomachine (10) comprising at least one turbine (17, 18) comprising at least one blade (25, 26) according to any one of claims 1 to 9.

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